manualshive.com logo in svg

Beechcraft C-12C, Operator And Technical Reference Manual

The Beechcraft C-12C Operator And Technical Reference Manual is a comprehensive user manual that provides detailed instructions and technical information for operating and maintaining the aircraft. This invaluable manual can be easily downloaded for free from our website, ensuring easy access to essential knowledge for C-12C operators.

Share
Download
background image

TM 1-1520-218-10 

3C-210 

 

A/B 

 

Figure 3C-152.  TVI-920 Transponder/TCAS Mode/Warning Flags and Messages 

Table 3C-110.  TVI-920 Transponder/TCAS Mode/Warning Flags and Messages

 

SLOT NUMBER 

SYMBOL 

INTERPRETATION 

1 

6NM or 12NM 

Selected forward range of traffic display. 

1 & 2 

TCAS OFF 

TCAS set to standby, either manually or automatically. 

3 

TEST 

TCAS set to test mode. 

3 & 4 

No bearing 
message (Red if 
RA; yellow if TA) 

Range and altitude of Resolution Advisories (RA) or Traffic 
Advisories (TA) intruders for which no bearing information is 
available. 

4 ABV 

Traffic displayed in altitudes from + 9900 ft to – 2700 ft, relative 
to own aircraft.  (If no message is displayed, traffic display is 
from + 2700 ft to – 2700 ft relative to own aircraft.) 

4 BLW 

Traffic displayed in altitudes from – 9900 ft to + 2700 ft, relative 
to own aircraft.  (If no message is displayed, traffic display is 
from + 2700 ft to – 2700 ft relative to own aircraft.) 

5 

V/S 

Vertical speed is unreliable, or system is in test mode. 

6 & 7 

ONLY T/A 

TCAS set to or operating in TA only mode.  If TA occurs, 
message and box border change to yellow. 

7 

R/A 

Resolution advisory or vertical speed is unreliable (Red flag). 

7 

TCAS 

TCAS functions have failed (Yellow flag). 

 

 

 

 

 

 

 

Summary of Contents for C-12C

Page 1: ...AL PROCEDURES EMERGENCY PROCEDURES REFERENCES ABBREVIATIONS AND TERMS ALPHABETICAL INDEX OPERATOR S MANUAL FOR ARMY C 12C AIRCRAFT NSN 1510 01 070 3661 ARMY C 12D AIRCRAFT NSN 1510 01 087 9129 ARMY C 12T AIRCRAFT NSN 1510 01 470 0220 Distribution statement A Approved for public release distribution is unlimited This manual supersedes TM 1 1510 218 10 dated 4 September 2001 HEADQUARTERS DEPARTMENT ...

Page 2: ......

Page 3: ...posure to exhaust gases shall be avoided since exhaust gases are an irritant to eyes skin and respiratory system HIGH VOLTAGE High voltage is a potential hazard around AC inverters ignition exciter units and strobe beacons USE OF FIRE EXTINGUISHERS IN CONFINED AREAS Monobromotrifluoromethane CF3Br is very volatile but is not easily detected by its odor Although non toxic it must be considered to b...

Page 4: ... in both bodily injury and equipment damage The battery shall be serviced in accordance with applicable manuals by qualified personnel only Battery electrolyte potassium hydroxide is corrosive Wear rubber gloves apron and face shield when handling batteries If potassium hydroxide is spilled on clothing or other material wash immediately with clean water If spilled on personnel immediately start fl...

Page 5: ...RCRAFT ON GROUND Engines shall be started and operated only by authorized personnel Reference AR 95 1 LCCS contractor personnel are authorized IAW the Contract and Statement of Work Ensure that landing gear control handle is in the DN position ...

Page 6: ... ...

Page 7: ...are Original 0 1 October 2009 TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 943 CONSISTING OF THE FOLLOWING Page Change Page Change No No No No Title 0 9 1 9 19 0 a c 0 9 20 Blank 0 d Blank 0 A 1 0 A 0 A 2 Blank 0 B Blank 0 B 1 B 9 0 i iii 0 B 10 Blank 0 iv Blank 0 Index 1 Index 16 0 1 1 1 3 0 1 4 blank 0 2 1 2 137 0 2 138 Blank 0 3 1 3 88 0 3A 1 3A 47 0 3A 48 Blank 0 3B 1 3B 64 0 3C 1 3C 119 0 3C ...

Page 8: ... ...

Page 9: ...py 2028 DISTRIBUTION STATEMENT A Approved for public release distribution is unlimited TABLE OF CONTENTS Page CHAPTER 1 INTRODUCTION 1 1 CHAPTER 2 AIRCRAFT AND SYSTEMS DESCRIPTION AND OPERATION 2 1 Section I Aircraft 2 1 Section II Emergency Equipment 2 31 Section III Engines And Related Systems 2 31 Section IV Fuel System 2 52 Section V Flight Controls 2 61 Section VI Propellers 2 69 Section VII ...

Page 10: ...m And Minimum 5 13 Section VI Maneuvering Limits 5 14 Section VII Environmental Restrictions 5 14 Section VIII Other Limitations 5 16 Section IX Required Equipment For Various Conditions Of Flight 5 17 CHAPTER 6 WEIGHT BALANCE AND LOADING 6 1 Section I General 6 1 Section II Weight And Balance 6 1 Section III Fuel Oil 6 4 Section IV Personnel 6 6 Section V Mission Equipment 6 11 Section VI Cargo L...

Page 11: ...Section II Operating Procedures And Maneuvers 8A 1 Section III Instrument Flight 8A 20 Section IV Flight Characteristics 8A 20 Section V Adverse Environmental Conditions 8A 23 Section VI Crew Duties 8A 27 CHAPTER 9 EMERGENCY PROCEDURES 9 1 APPENDIX A REFERENCES A 1 APPENDIX B ABBREVIATIONS AND TERMS B 1 INDEX ALPHABETICAL INDEX Index 1 ...

Page 12: ... ...

Page 13: ... the best operating instructions and procedures for the aircraft under most circumstances The observance of limitations performance and weight balance data provided is mandatory The observance of procedures is mandatory except when modification is required because of multiple emergencies adverse weather terrain etc Basic flight principles are not included THIS MANUAL SHALL BE CARRIED IN THE AIRCRA...

Page 14: ...rmation is written to apply to all models and split series effectivities Table 2 1 lists the most significant differences between models including the split series effectivities Aircraft serial numbers are used only where needed for clarification Paragraphs figures tables and charts that apply to specific model s have the corresponding model designator s placed following the paragraph or figure ti...

Page 15: ...10 1 17 NORMAL PROCEDURES This manual contains two Normal Procedures chapters entitled as follows Chapter 8 Normal Procedures C 12C and C 12D1 D2 Aircraft Chapter 8A Normal Procedures C 12T1 T2 Aircraft 1 3 1 4 blank ...

Page 16: ... ...

Page 17: ...as all weather capability Refer to Figure 2 1 Sheets 1 through 3 and Figure 2 2 Distinguishable features of the aircraft are the slender streamlined engine nacelles square tipped wing and tail surfaces a T tail and dual aft body strakes below the empennage The basic mission of the aircraft is to provide a transport service supporting staff in the conduct of command and control functions administra...

Page 18: ...e Antenna 9 ELT Antenna 10 VOR No 1 and No 2 Antennas 2 11 ADF No 1 Sense Antenna 12 Lower Transponder Antenna 13 ADF No 1 and No 2 Loop Antennas 2 14 VHF No 2 and UHF Comm Antenna 15 DME Antenna 16 Marker Beacon Antenna 17 Glideslope Antenna 18 Heat Exchanger Inlet 19 Battery Exhaust Louvers 20 Engine Air Inlet 21 Engine Air Bypass Door 22 Battery Ram Air Inlet 23 GPS Figure 2 1 General Exterior ...

Page 19: ...DF No 1 Sense Antenna 12 Lower Transponder Antenna 13 Radio Altimeter Antennas 14 ADF No 1 and No 2 Loop Antennas 2 15 VHF No 2 and UHF Comm Antenna 16 Marker Beacon Antenna 17 TACAN DME Antenna 18 Glideslope Antenna 19 Heat Exchange Inlet 20 Battery Exhaust Louver 21 Engine Air Inlet 22 Engine Air Bypass Door 23 Battery Ram Air Inlet 24 Condenser Air Inlet Right Air Exhaust Left 25 Battery Ram Ai...

Page 20: ...na 15 ADF No 1 Sense Antenna 16 Lower Transponder Antenna 17 Radio Altimeter Antennas 18 ADF No 1 and No 2 Loop Antennas 2 19 VHF No 2 and UHF Comm Antenna 20 Bottom Mode S Transponder Antenna 21 Marker Beacon Antenna 22 Bottom TCAS Antenna 23 TACAN DME Antenna 24 Glideslope Antenna 25 Heat Exchanger Inlet 26 Battery Exhaust Louvers 27 Engine Air Inlet 28 Engine Air Bypass Door 29 Condenser Air In...

Page 21: ...TM 1 1510 218 10 Figure 2 2 Typical General Interior Arrangement 2 5 ...

Page 22: ...TM 1 1510 218 10 Figure 2 3 Principal Dimensions C Sheet 1 of 2 2 6 ...

Page 23: ...TM 1 1510 218 10 2 7 Figure 2 3 Principal Dimensions D T Sheet 2 of 2 ...

Page 24: ...EEL 19 FEET 6 INCHES RADIUS FOR OUTSIDE GEAR 21 FEET 1 INCH RADIUS FOR WING TIP C 39 FEET 10 INCHES RADIUS FOR WING TIP D T 40 FEET 4 INCHES TURNING RADII ARE PREDICATED ON THE USE OF PARTIAL BRAKING ACTION AND DIFFERENTIAL POWER Figure 2 4 Typical Turning Radius 2 8 ...

Page 25: ...ross Takeoff Weight D2 T a Takeoffs Takeoff should only be performed on a smooth paved runway Takeoffs should not be performed with a tailwind 1 Requirements b Landing Maximum landing weight is 12 500 pounds unless required by an emergency If it is necessary to land with a weight over 12 500 pounds the landing shall be made on a smooth paved runway at a sink rate of 500 feet per minute or less if ...

Page 26: ...ered and the rudder pedals relieved of the steering load when the landing gear is retracted Air oil type shock struts filled with compressed air and hydraulic fluid are incorporated with the landing gear Gear retraction or extension time is approximately 6 seconds a Landing Gear Control Switch Landing gear system operation is controlled by a manually actuated wheel shaped switch placarded LDG GEAR...

Page 27: ...as include the resultant increase in velocity and significant reduction in temperature due to propeller wake EXHAUST DANGER AREA GROUND LEVEL EXHAUST DANGER AREA MAXIMUM POWER PROPELLER DANGER AREA Figure 2 5 Exhaust and Propeller Danger Areas ...

Page 28: ...tor Lights 3 10 Landing Gear Handle Light Test Switch Light Inside Handle 11 PARKING BRAKE Control 12 Landing Gear Handle Down Lock Release 13 Recognition Lights Switch 14 Manual Engine ICE VANE Controls 15 ANNUNCIATOR TEST Switch 16 Stall Warning Landing Gear Warning Test Switch 17 Fire Detection System Test Switch 18 CABIN AIR Control 10 COPILOT AIR Inlet Control 11 OXYGEN Pressure Gauge 12 Pneu...

Page 29: ...nding gear strut activates the left and right engine ambient air shut off valves when the strut is extended h Alternate Landing Gear Extension Handle CAUTION Continued pumping of handle after GEAR DOWN position indicator lights are illuminated could damage the drive mechanism and prevent subsequent retractions Manual landing gear extension is provided through a manually powered system as a backup ...

Page 30: ...anel 15 IFF Antenna Select Panel 16 Transponder Control Panel 17 Alternate Landing Gear Extension Handle 18 YAW DAMP RUDDER BOOST Control Panel 19 AP DME Control Panel 20 AUTOPILOT Mode Selector Panel 21 Landing Gear Alternate Engage Handle 22 ICS 1 Control Panel 23 Aileron Tab Control and Position Indicator 24 ELEVATOR Tab Control and Position Indicator 25 Autopilot Go Around Button PROVISIONS ON...

Page 31: ...l hook and pin locks The landing gear is held in the up position by hydraulic pressure The pressure is controlled by the power pack pressure switch and an accumulator that is pre charged with nitrogen to 800 50 psi Gear doors are opened and closed through a mechanical linkage connected to the landing gear The nose wheel steering mechanism is automatically centered and the rudder pedals relieved of...

Page 32: ... Switch 11 TAXI LIGHT Switch 12 RECOG Recognition Lights Switch 13 HDL LT TEST Switch Light Inside Landing Gear Control Handle 14 GEAR DOWN Indicator Lights 3 15 PARKING BRAKE Control 16 Manual Engine Ice Vane Control 17 ANNUNCIATOR TEST Switch 18 STALL LDG GEAR WARN TEST Switch 19 FIRE PROTECTION TEST Switch 20 CABIN AIR Control 21 COPILOT AIR Inlet Control 22 GYRO SUCTION Gauge 23 Radio Altimete...

Page 33: ...TEST Button 15 DN LOCK REL Landing Gear Handle Down Lock Release 16 LDG GEAR CONTROL Handle 10 LANDING LIGHT Switch 11 TAXI LIGHT Switch 12 RECOG Recognition Lights Switch 13 HDL LT TEST Switch Light Inside Landing Gear Control Handle 14 GEAR DOWN Indicator Lights 3 15 PARKING BRAKE Control 16 Manual Engine Ice Vane Control 17 ANNUNCIATOR TEST Switch 18 STALL LDG GEAR WARN TEST Switch 19 FIRE PROT...

Page 34: ...13 RECOG Light Switch 14 Landing Gear Position Lights 15 PARKING BRAKE Control 16 Landing Gear Handle Down Lock Release 17 HYD FLUID SENSOR TEST Switch 18 Landing Gear WARNING HORN SILENCE Switch 19 Engine Ice Vane Manual Control 20 CABIN TEMP Indicator 21 FLIGHT HOURS Meter 22 ANNUNCIATOR TEST Switch 23 STALL LDG GEAR WARN TEST Switch 24 ENGINE FIRE PROTECTION TEST Switches 25 CABIN AIR Control 2...

Page 35: ...ear switch handle cannot be canceled The gear warning silence switch is a magnetically held switch Once actuated it will stay in the up position until both power levers are advanced above 81 N1 and or airspeed increases above 140 KIAS In either case speeds above or below 140 KIAS the landing gear warning system will be rearmed if both power levers are advanced above 81 N1 With the flaps beyond the...

Page 36: ...nate e g in case of an electrical system failure continue pumping until sufficient resistance is felt to ensure that the gear is down and locked Do not stow the extension lever but leave it in the full up position After a practice alternate extension stow the extension handle reset the LANDING GEAR CONTROL circuit breaker and retract the gear in the normal manner with the landing gear control hand...

Page 37: ...TM 1 1510 218 10 2 21 Figure 2 9 Control Pedestal D2 Sheet 1 of 3 ...

Page 38: ...TM 1 1510 218 10 Figure 2 9 Control Pedestal T1 Sheet 2 of 3 2 22 ...

Page 39: ...TM 1 1510 218 10 2 23 Figure 2 9 Control Pedestal T2 Sheet 3 of 3 ...

Page 40: ...un Visor 7 Oxygen Control Panel 8 Overhead Circuit Breaker and Control Panel 9 Fuel Management Panel 10 Windshield Wipers 11 Magnetic Compass 12 Warning Annunciator Panel 13 Rudder Pedals 14 Caution Annunciator Panel 15 Pedestal Extension 16 Alternate Landing Gear Extension Handle Figure 2 10 Cockpit Typical D T ...

Page 41: ...f the rudder pedals are connected to the master cylinders which actuate the system for the corresponding wheel No emergency brake system is provided Repeated and excessive application of brakes without allowing sufficient time for cooling to accumulate between applications will cause loss of braking efficiency possible failure of brake or wheel structure possible blowout of tires and in extreme ca...

Page 42: ... on either side of the door capture posts mounted on the cargo door In the closed position the door becomes an integral part of the cargo door A button adjacent to the door handle must be pressed before the handle can be rotated to open the door A bellows behind the button is inflated when the aircraft is pressurized to prevent accidental unlatching and or opening of the door A small round window ...

Page 43: ...TM 1 1510 218 10 Figure 2 12 Cabin Door and Cabin Emergency Hatch D T 2 27 ...

Page 44: ...sition Latch handle in place Secure the access door Attach one end of the door support assembly to the cargo door ball stud on the forward side of the door Ensure the support rod detent pin is in place Push out on the cabin doorsill step and allow the cargo door to swing open The gas springs will automatically open the door Attach the free end of the support rod to the ball stud on the forward fus...

Page 45: ...essure vessel Each cabin window has a vertical sliding curtain to regulate light through the window 2 15 SEATS a Pilot and Copilot Seats The pilot s and copilot s seats are separated from the cabin by a removable partition with lockable sliding doors Refer to Figure 2 13 The controls for vertical height adjustment and fore and aft travel are located under each seat The fore and aft adjustment hand...

Page 46: ... 2 Seat Belt Shoulder Harness Buckle 3 Moveable Armrest 4 Seat Height Adjustment Pilot Fore and Aft Adjustment Copilot 5 Seat Fore and Aft Adjustment Pilot Height Adjustment Copilot 6 Expandable Map Pocket Figure 2 13 Pilot s and Copilot s Seats ...

Page 47: ...pressor driven by a single stage reaction turbine The power turbine a two stage reaction turbine counter rotating with the compressor turbine drives the output shaft Both the compressor turbine and the power turbine are located in the approximate center of the engine with their shafts extending in opposite directions Being a reverse flow engine the ram air supply enters the lower portion of the na...

Page 48: ...Truss Assembly 11 Engine Air Intake Screen 12 Ignition Exciter 13 Starter Generator 14 Fuel Boost Pump 15 Air Conditioner Compressor Drive Belt 2 Engine Only 16 Fire Detector 17 Air Conditioner Compressor 2 Engine Only 18 Bleed Air Adapter 19 Bleed Air Line 20 Engine Mount 21 Ignition Exciter Plug 22 Oil Scavenge Tubes 23 Overspeed Governor 24 Prop Device Brush Block Bracket 25 Prop Reverse Linkag...

Page 49: ...t 34 Fireshield 35 Trim Resistor Thermocouple 36 Prop Interconnect Linkage Fore 37 Prop Shaft 38 Tach Generator 39 Chip Detector 40 Oil Pressure Tube 41 Fire Extinguisher Line 42 Ignition Exciter Plug 43 Engine Mount Bolt 44 Linear Actuator 45 Engine Baffle and Seal Assy 46 Fuel Oil Heater 47 Tach Generator Aft 48 Drain Manifold 49 Overhead Breather Tube 50 Engine Truss Mounting Bolt Figure 2 14 E...

Page 50: ...air stream by placing the ice vane switches in the RETRACT position The green annunciator lights will extinguish Retraction should be accomplished at 15 C and above to assure adequate oil cooling The vanes should be either extended or retracted there are no intermediate positions 4 If for any reason the vane does not attain the selected position within 15 seconds a yellow 1 VANE FAIL or 2 VANE FAI...

Page 51: ...TM 1 1510 218 10 Figure 2 15 Overhead Control Panel C D T1 Sheet 1 of 2 2 35 ...

Page 52: ...TM 1 1510 218 10 Figure 2 15 Overhead Control Panel T2 Sheet 2 of 2 2 36 ...

Page 53: ...ition lever controls the cutoff function of its engine mounted fuel control unit From LO IDLE to HIGH IDLE they control the governors of the fuel control units to establish minimum fuel flow levels LO IDLE position sets the fuel flow rate to attain 52 2 C D 56 58 T at sea level minimum N1 and HIGH IDLE position sets the rate to attain 70 minimum N1 The power lever for the corresponding engine can ...

Page 54: ...TM 1 1510 218 10 Figure 2 16 Overhead Circuit Breaker Panel C Sheet 1 of 4 2 38 ...

Page 55: ...TM 1 1510 218 10 Figure 2 16 Overhead Circuit Breaker Panel D1 Sheet 2 of 4 2 39 ...

Page 56: ...TM 1 1510 218 10 2 40 Figure 2 16 Overhead Circuit Breaker Panel D2 Sheet 3 of 4 ...

Page 57: ...TM 1 1510 218 10 Figure 2 16 Overhead Circuit Breaker Panel T1 Sheet 4 of 4 2 41 ...

Page 58: ...ithin the tube forms a pressure barrier that keeps the responder integrity switch contacts closed for fire alarm continuity test functions As the temperature around the sensing cable increases the gases within the tube begin to expand When the pressure from the expanding gases reaches a preset point the contacts of the responder alarm switch close activating the respective fire warning system c Th...

Page 59: ...TM 1 1510 218 10 2 43 Figure 2 17 Instrument Panel C D1 Sheet 1 of 4 ...

Page 60: ...TM 1 1510 218 10 2 44 Figure 2 17 Instrument Panel D2 Sheet 2 of 4 ...

Page 61: ...TM 1 1510 218 10 2 45 Figure 2 17 Instrument Panel T1 Sheet 3 of 4 ...

Page 62: ...TM 1 1510 218 10 Figure 2 17 Instrument Panel T2 Sheet 4 of 4 2 46 ...

Page 63: ...EM a The engine oil tank is integrated with the air inlet casting located forward of the accessory gearbox Oil for propeller operation lubrication of the reduction gearbox and engine bearings is supplied through an external line from the high pressure pump Two scavenge lines return oil to the tank from the propeller reduction gearbox A non congealing external oil cooler keeps the engine oil temper...

Page 64: ...he autoignition system of the corresponding engine The OFF position disarms the system Each switch is protected by a corresponding 5 ampere circuit breaker placarded START CONTR 1 or START CONTR 2 located on the overhead circuit breaker panel Figure 2 16 b Autoignition Lights If an armed auto ignition system changes from a ready condition to an operating condition energizing the two igniter plugs ...

Page 65: ...en the measured ITT is greater than 1200 C When the exceedence ITT value is displayed the actual measured value not the dashes will be displayed up to 1372 C The indicator is equipped with a Built In Test BIT display that will display all active LCD segments for three seconds on power up If the BIT test detects a failed ROM or RAM the BIT indicator will have a blank display If the BIT failure is t...

Page 66: ... are recorded the oldest events shall be discarded The indicator will prefix the digital display with an E when an event is being or has been recorded and not played back The indicator digital display will start flashing whenever indicated torque exceeds 100 The flashing shall cease and digital torque display shall be prefixed with an E when the time torque combination is exceeded and the indicato...

Page 67: ...OTE Pressing the EXCEEDENCE ERASE switch for 0 2 seconds or longer will cause all events to be erased from non volatile memory There is no provision for erasing individual events The Turbine Tachometers are protected by 1 0 ampere circuit breakers placarded TACH N1 1 and 2 located on the pilot s left sub panel d Engine Oil Pressure and Temperature Indicator The indicator displays the measured engi...

Page 68: ... wait a full 10 seconds before starting the engines after turning on the master switch to allow the ETM to complete its startup procedures 2 If the engines are started before the ETM has completed its startup sequence the system will not record any engine starts This will result in inaccurate cycle counts engine start counting and trend analysis NOTE When the ETM system is inoperative pilots are r...

Page 69: ...TM 1 1510 218 10 2 53 Figure 2 18 Fuel System ...

Page 70: ...celle tank to the inlet of the engine driven primary high pressure pump for engine starting and all normal operations Either the engine driven boost pump or stand by fuel pump is capable of supplying sufficient pressure to the engine driven primary high pressure pump and thus maintain normal engine operation c Standby Fuel Pumps A submerged electrically operated standby fuel pump located within ea...

Page 71: ...uxiliary tank is measured by a capacitance type fuel gauging system Two fuel gauges one for the left and one for the right fuel system read fuel quantity in pounds Refer to Section XII for fuel capacities and weights The system is compensated for fuel density changes due to temperature excursions In addition to the fuel gauges yellow 1 or 2 NAC LOW lights on the caution advisory annunciator panel ...

Page 72: ...8 Auxiliary Fuel Transfer Pump Override Switch 1 Engine Figure 2 19 Fuel Management Panel C D T1 Sheet 1 of 2 1 Standby Fuel Pump Switch 1 Engine Override 2 Fuel Quantity Indicator 1 Engine 3 Fuel Quantity Gauging System Control Switch 4 Fuel Quantity Indicator 2 Engine 5 Standby Fuel Pump Override Switch 2 Engine 6 Auxiliary Fuel Transfer Pump Override Switch 2 Engine 7 Crossfeed Valve Switch 8 A...

Page 73: ...ial lubrication from fuel flow When an engine is operating this pump may be severely damaged while cavitating if the firewall valve is closed before the condition lever is moved to the FUEL CUTOFF position The fuel system incorporates a fuel line shutoff valve on each engine firewall The firewall shutoff valves close automatically when the fire extinguisher T handles on the instrument panel are pu...

Page 74: ...rside of the wing adjacent to the nacelle To prevent icing of the vent system one vent is recessed into the wing and the backup vent protrudes out from the wing and contains a heating element The vent line at the nacelle contains an inline flame arrester l Engine Oil to Fuel Heat Exchanger An engine oil to fuel heat exchanger located on each engine accessory case operates continuously and automati...

Page 75: ...TM 1 1510 218 10 2 59 Figure 2 20 Gravity Feed Fuel Flow ...

Page 76: ...TM 1 1510 218 10 2 60 Figure 2 21 Crossfeed Fuel Flow ...

Page 77: ...surized area into the unpressurized area NOTE Transfer of fuel from either of the ferry fuel tanks first will not affect the aircraft center of gravity 1 In preparation for transfer of fuel from the ferry fuel tanks to the nacelle fuel tanks use fuel from both nacelle fuel tanks until each is about half full Open the desired ferry fuel selector valve and open either or both fuel tank selector valv...

Page 78: ...utton switches are located on the outboard grip of each control wheel An ident button pilot s control wheel map button and touch control button copilot s control wheel are located on the inboard grip Both control wheels contain identical DC powered digital clock timers Each control wheel incorporates a bracket to allow mounting a chart holder Figure 2 22 Sheet 4 e Control Wheel Chart Holder T2 An ...

Page 79: ...ch 2 Autopilot Yaw Damp Disconnect 3 Electric Trim Control Switches 4 Pitch Sync and Control Wheel Steering Switch 5 Transponder Indent Switch 6 Map Light Switch 7 8 Day Clock 8 Clock Light Switch Figure 2 22 Control Wheels C D1 Sheet 1 of 4 ...

Page 80: ... 5 Line Advance Switch 6 Map Light Switch 7 8 Day Clock 8 Clock Light Switch COPILOT 1 Microphone Switch 2 Autopilot Yaw Damp Disconnect Switch 3 Electric Trim Control Switches 4 Go Around Switch 5 Touch Control Steering Switch 6 Line Advance Switch 7 Clock Light Switch 8 8 Day Clock 9 Map Light Switch Figure 2 22 Control Wheels D2 Sheet 2 of 4 ...

Page 81: ... Autopilot Yaw Damp Disconnect Switch 3 Electric Trim Control Switches 4 Go Around Switch 5 Touch Control Steering Switch 6 Line Advance Switch 7 Clock 8 Map Light Switch 9 Clock Light Switch Figure 2 22 Control Wheels T1 Sheet 3 of 4 2 65 ...

Page 82: ...2 Autopilot Yaw Damp Disconnect Switch 3 Electric Trim Control Switches 4 Go Around Switch 5 Touch Control Steering Switch 6 Line Advance Switch 7 Clock 8 Map Light Switch 9 Quick Tune Switch Figure 2 22 Control Wheels T2 Sheet 4 of 4 2 66 ...

Page 83: ...e pilot Moving either or both of the BLEED AIR VALVE switches on the overhead control panel to PNEU ENVIRO OFF C D T1 and the ENVIR PNEU BLEED AIR T2 to the off position will disengage the rudder boost system NOTE Condition levers must be in LOW IDLE position to perform rudder boost check 2 The system is controlled by a switch located on the extended pedestal below the rudder trim wheel placarded ...

Page 84: ...ON position to operate the system The dual element thumb switch is moved forward for trimming nose down aft for nose up and when released returns to the center off position Any activation of the trim system through the copilot s trim switch can be cancelled by activation of the pilot s switch Operating the pilot s and copilot s switches in opposing directions simultaneously results in no trim acti...

Page 85: ...ired flap position is obtained return the switch to APPROACH detent In the event that any two adjacent flap sections extend 3 to 5 out of phase with the other a safety mechanism is provided to discontinue power to the flap motor b Wing Flap Position Indicator Flap position in percent of travel from 0 UP to 100 DOWN is shown on an indicator placarded FLAPS below the instrument panel Figure 2 17 The...

Page 86: ...g a power lever Autofeather circuits are protected by one 5 ampere circuit breaker placarded AUTOFEATHER located on the overhead circuit breaker panel Figure 2 16 2 52 PROPELLER GOVERNORS Two governors a constant speed primary governor and an overspeed governor control the propeller RPM The constant speed governor mounted on top of the reduction housing control the propeller through its entire ran...

Page 87: ...the front of the engine when the target mounted on the aft side of the spinner bulkhead passes the magnetic pickup A control box converts this signal pulse rate difference into correction commands which are transmitted to the appropriate governor Speed trim is accomplished by pulse width modulation of an electromagnetic coil in each governor The electromagnetic coil can increase but not decrease t...

Page 88: ...layed back The indicator performs BIT on the LCD display ROM program memory RAM volatile data memory and EEPROM Non volatile data memory and input signal The display BIT shall consist of displaying all active LCD segments for three seconds on power up If the ROM or RAM fails BIT the indicator display will be blank If the input signal fails BIT the indicator will prefix the digital display with F B...

Page 89: ...emoved from each inboard and outboard wing leading edge and both horizontal stabilizers by the flexing of deicer boots which are pneumatically actuated Engine bleed air from the engine compressor is used to supply air pressure to inflate the deicer boots and to supply vacuum through the ejector system for boot hold down during flight A pressure regulator protects the system from over inflation Whe...

Page 90: ...ents by the timer c Alternate Operation The manual prop deice system is provided as a backup to the automatic system A control switch located on the overhead control panel placarded PROP INNER OUTER controls the manual override relays When the switch is in the OUTER position the automatic timer is overridden and power is supplied to the outer heating elements of both propellers simultaneously The ...

Page 91: ...y increased for flight operation through the landing gear safety switch Circuit protection is provided by a 15 ampere circuit breaker placarded STALL WARN on the overhead circuit breaker panel 2 64 STALL WARNING SYSTEM The stall warning system consists of a transducer a lift computer a warning horn and a test switch Angle of attack is sensed by aerodynamic pressure on the lift transducer vane loca...

Page 92: ...rmation the other is electrically heated and is controlled by two toggle switches on the overhead control panel placarded FUEL VENT LEFT ON RIGHT Figure 2 15 They are protected by two 5 ampere circuit breakers placarded FUEL VENT HEAT RIGHT or LEFT located on the overhead circuit breaker panel Each fuel governing line is protected against ice by an electrically heated jacket A 7 5 ampere circuit b...

Page 93: ...arded CABIN PRESS DUMP PRESS TEST is provided to control pressurization The switch is spring loaded to the PRESS position In the DUMP position the safety valve will be opened and the cabin will be depressurized to the aircraft altitude In the PRESS position cabin altitude is controlled by the CABIN CONTROLLER control In the TEST position the landing gear safety switch is bypassed to enable testing...

Page 94: ...sure switch mounted on the back of the overhead control panel completes a circuit to illuminate a red warning annunciator light placarded ALT WARN to warn of operation requiring oxygen 2 Bleed airflow is controlled automatically When the aircraft is on the ground circuitry from the landing gear safety switch prevents ambient air from entering the flow control unit to provide maximum heating 3 The ...

Page 95: ...iluter control lever on the mask regulator in the NORMAL position permits the regulator to automatically schedule a proportional increase in oxygen as the cabin pressure altitude increases When not in use the masks should be stowed with the lever in the 100 position While in use at altitudes below 20 000 feet the lever may at the crew s discretion be placed in the NORMAL position to conserve oxyge...

Page 96: ...lated to the pilot copilot and first aid masks by pulling the AUTO OXYGEN circuit breaker in the ENVIRONMENTAL group on the overhead circuit breaker panel provided the PASSENGER MANUAL O RIDE knob is on the off position b Pilot and Copilot Masks The pilot and copilot masks are diluter demand quick donning masks equipped with a carbon microphone and are stowed on the partition aft and outboard of t...

Page 97: ...TM 1 1510 218 10 Figure 2 24 Oxygen System Servicing Pressure Chart 2 81 ...

Page 98: ... 1 PASSENGER MASK 31 000 0 2 4 2 3 7 3 30 000 0 2 4 4 3 7 3 29 000 0 2 4 7 3 7 3 28 000 0 2 5 0 3 7 3 27 000 0 2 5 3 3 7 3 26 000 0 2 5 6 3 7 3 25 000 0 2 5 9 3 7 24 000 0 2 6 2 3 7 23 000 0 2 6 6 3 7 22 000 0 2 6 9 3 7 21 000 0 2 7 2 3 7 20 000 3 6 7 6 3 7 19 000 3 9 7 9 3 7 18 000 4 2 8 3 3 7 17 000 4 5 8 7 3 7 16 000 4 8 9 1 3 7 15 000 5 1 9 5 3 7 14 000 5 4 10 0 3 7 13 000 5 8 10 4 3 7 12 000 ...

Page 99: ...ided by total crew and passenger LPM usage to obtain total oxygen remaining duration in minutes 31 000 100 8 4 145 5 20 000 100 15 2 80 4 20 000 NORMAL 7 2 169 7 15 000 100 19 0 64 3 15 000 NORMAL 10 2 119 8 10 000 100 23 8 51 3 TWO MAN CREW 10 000 NORMAL 13 8 88 6 31 000 100 12 1 101 0 20 000 100 18 9 64 7 20 000 NORMAL 10 9 112 1 15 000 100 22 7 53 8 15 000 NORMAL 13 9 87 9 10 000 100 27 5 44 4 ...

Page 100: ...000 NORMAL 28 7 42 6 10 000 100 42 3 28 9 TWO MAN CREW PLUS FIVE PASS 10 000 NORMAL 32 3 37 8 31 000 100 30 6 39 9 20 000 100 37 4 32 7 20 000 NORMAL 29 4 41 6 15 000 100 41 2 29 7 15 000 NORMAL 32 4 37 7 10 000 100 46 0 26 6 TWO MAN CREW PLUS SIX PASS 10 000 NORMAL 36 0 33 9 31 000 100 34 3 35 6 20 000 100 41 1 29 7 20 000 NORMAL 33 1 36 9 15 000 100 44 9 27 2 15 000 NORMAL 36 1 33 8 10 000 100 4...

Page 101: ...ntinued CABIN PRESSURE ALTITUDE CREW MASK CONDITION TOTAL FLOW LPM NTPD DURATION IN MINUTES 1 31 000 100 41 7 29 3 20 000 100 48 5 25 2 20 000 NORMAL 40 5 30 2 15 000 100 52 3 23 4 15 000 NORMAL 43 5 28 1 10 000 100 57 1 21 4 TWO MAN CREW PLUS NINE PASS 10 000 NORMAL 47 1 25 9 2 85 ...

Page 102: ...TM 1 1510 218 10 Figure 2 25 Oxygen System C Sheet 1 of 2 2 86 ...

Page 103: ...TM 1 1510 218 10 Figure 2 25 Oxygen System D T Sheet 2 of 2 2 87 ...

Page 104: ...rea fwd part opposite to the aircraft entry door and a storage area that extends from the aft side of the doorway to the back of the pressurized compartment A partition wall with lockable internal sliding doors at the aisle separates the passenger area from the toilet area A mirror is mounted on the right forward partition and a removable low profile electric toilet faces the aisle A garment hang ...

Page 105: ...hen desired the removable waste tank may be removed from the toilet for servicing Section XII contains servicing instructions 2 75 CHEMICAL TOILETS T2 a Description A quick removable side facing toilet with seat belt is located in the aft cabin area Stub partitions and a privacy curtain are provided The chemical toilet contains an inner liner which holds a plastic disposable bag The inner liner an...

Page 106: ...TM 1 1510 218 10 2 90 Figure 2 26 Environmental System ...

Page 107: ...reventing icing of the evaporator The forward evaporator and blower will supply the cockpit forward ceiling outlets and forward floor outlets while the rear evaporator and blower supply the aft ceiling outlets rear floor outlets and toilet compartment Both blower circuit breakers are located in the dc power distribution panel in the lower equipment bay A vane axial blower draws air through the con...

Page 108: ...d Manual Mode Control With the cabin temperature mode selector in the MAN HEAT or MAN COOL position regulation of the cabin temperature is accomplished manually with the MANUAL TEMP switch 1 In the MAN HEAT mode the automatic system is overridden and the system is controlled by opening or closing the two bypass valves with the MANUAL TEMP INCREASE DECREASE switch To increase cabin temperature hold...

Page 109: ...ion diodes to prevent power crossfeed between the generating systems when connection between the generator buses is lost Thus when either generator is lost because of a ground fault the operating generator will supply power for all aircraft dc loads except those receiving power from the inoperative generator s bus that cannot be crossfed When a generator is not operating reverse current and over v...

Page 110: ...TM 1 1510 218 10 Figure 2 27 DC Electrical System Schematic C D1 2 94 ...

Page 111: ...LL WARN LEFT BLEED AIR WARN 1 CHIP DETR LANDING GEAR IND FUEL 1 QTY IND 1 STANDBY PUMP 1 AUXILIARY TRANSFER 1 1 QTY WARN ENGINE 1 OIL TEMP 1 OIL PRESS 2 DUAL FED BUS WARNING ANN PWR FIRE DETR RIGHT BLEED AIR WARN 2 CHIP DETR LANDING GEAR WARN FUEL 2 QTY IND 2 STANDBY PUMP 2 AUXILIARY TRANSFER 1 2 QTY WARN ENGINE 2 OIL TEMP 2 OIL PRESS ELECTRICAL BATT CHARGE 3 DUAL FED BUS WEATHER WSHLD WIPER LEFT ...

Page 112: ...TOFEATHER 2 3 PROP GOV AVIONICS HF POWER 5 DUAL FED BUS FLIGHT ELEC TRIM FLAP MOTOR PILOT TURN SLIP LANDING GEAR RELAY LIGHTS ICE BCN SUBPANEL CONSOLE LIGHTS INST INDIRECT LEFT LANDING LIGHTS RECOG 4 ENVIRONMENTAL TAXI LIGHT 3 TEMP CONTR LEFT BLEED AIR CONTR ELECTRICAL 1 GEN RESET 6 DUAL FED BUS FLIGHT RUDDER BOOST FLAP CONTR COPILOT TURN SLIP LIGHTS EMERG LIGHTS FLT INST NAV OVHD LIGHTS RIGHT LAN...

Page 113: ...E FIRE EXTINGUISHER 1 ENGINE FIRE EXTINGUISHER SPAR THRESHOLD LIGHTS 2 STANDBY FUEL PUMP 1 STANDBY FUEL PUMP SHADIN ETMS DOOR STEP OBSERVATION LIGHTS TRANSPONDER 4 2 FIREWALL SHUTOFF VALVE ELT 4 1 AIRCRAFT WITH AUXILIARY FUEL TANKS ONLY 2 C AIRCRAFT ONLY 3 D AIRCRAFT ONLY IF INSTALLED 5 AIRCRAFT WITH OPTIONAL INTERIOR ONLY 4 2 97 ...

Page 114: ...TM 1 1510 218 10 Figure 2 28 DC Electrical System Schematic D2 T1 Sheet 1 of 2 2 98 ...

Page 115: ...TM 1 1510 218 10 Figure 2 28 DC Electrical System Schematic T2 Sheet 2 of 2 2 99 ...

Page 116: ...N LEFT BLEED AIR WARN 1 CHIP DETR LANDING GEAR FUEL 1 QTY IND 1 STANDBY PUMP 1 AUXILIARY TRANSFER 1 QTY WARN ENGINE 1 OIL TEMP 1 OIL PRESS FURNISHING CIGAR LIGHTER 2 DUAL FED BUS WARNING ANN PWR FIRE DETR RIGHT BLEED AIR WARN 2 CHIP DETR LANDING GEAR WARN FUEL 2 QTY IND 2 STANDBY PUMP 2 AUXILIARY TRANSFER 2 QTY WARN ENGINE 2 OIL TEMP 2 OIL PRESS ELECTRICAL BATTERY CHARGE 3 DUAL FED BUS WEATHER WSH...

Page 117: ...RN SLIP LIGHTS ICE BCN SUBPANEL CONSOLE LIGHTS INST INDIRECT RECOG LANDING LIGHTS ENVIRONMENTAL TEMP CONTR LEFT BLEED AIR CONTR AIR COND CONTR ELECTRICAL 1 GEN RESET TAS PROBE HEAT POWER 6 DUAL FED BUS FLIGHT RUDDER BOOST FLAP CONTR LIGHTS EMERG LIGHTS FLT INST NAV OVHD LIGHTS TAXI LIGHT CABIN LTS SIGNS READING 2 GEN RESET AVIONICS AVIONICS MASTER CONTR COMPASS SWITCHING TRANSPONDER EMERG MODE AVI...

Page 118: ...METER COPILOT ALT 2 ADF RADAR INPTH 1 RMI 2 AFCS GPAAS POWER COPILOT DCU ARC 210 FMS 2 STORMSCOPE 1 DUAL FED BUS WARNING ANN IND STALL WARN LEFT BLEED AIR WARN 1 CHIP DETR LANDING GEAR FUEL 1 QTY IND 1 STANDBY PUMP 1 AUXILIARY TRANSFER 1 QTY WARN COPILOT HSI MFD ENGINE 1 OIL TEMP 1 OIL PRESS FURNISHING CIGAR LIGHTER 2 DUAL FED BUS WARNING ANN PWR FIRE DETR RIGHT BLEED AIR WARN 2 CHIP DETR LANDING ...

Page 119: ...EAT FUEL 2 FIREWALL VALVE 2 PRESS WARN ENGINE 2 START CONTR 2 ICE VANE CONTR 2 IGNITOR CONTR AUTOFEATHER PROP GOV 5 DUAL FED BUS FLIGHT ELEC TRIM FLAP MOTOR PILOT TURN SLIP LIGHTS ICE BCN SUBPANEL CONSOLE LIGHTS INST INDIRECT RECOG LANDING LIGHTS ENVIRONMENTAL TEMP CONTR LEFT BLEED AIR CONTR AIR COND CONTR ELECTRICAL 1 GEN RESET TAS PROBE HEAT POWER 6 DUAL FED BUS FLIGHT RUDDER BOOST FLAP CONTR LI...

Page 120: ...Electrical System T2 Continued 1 AVIONICS BUS HF RCVR AIR DATA ENCODER AUTOPILOT 1 VHF TRANSPONDER TACAN 1 NAV PAGING GPS 1 ADF TCAS ALTITUDE ALERT 2 RMI 1 DCU FMS 1 1 MODE S 1 AFCS TCAS RMT PILOT AUDIO 2 AVIONICS BUS 2 VHF RADAR MFD INPTH 2 NAV 2 AFCS MLS 2 ADF 2 DCU GPAAS POWER 1 RMI GPAAS FMS 2 COPILOT AUDIO COPILOT ALT UHF RADIO ALTIMETER STORMSCOPE 1 DUAL FED BUS WARNING ANN IND STALL WARN LE...

Page 121: ...OL LEFT FUEL CONTR HEAT SURF DEICE LEFT FUEL VENT HEAT LEFT PITOT HEAT FUEL CROSSFEED 1 FIREWALL VALVE 1 PRESS WARN ENGINE 1 START CONTR 1 ICE VANE CONTR 1 IGNITOR CONTR PROP SYNC 4 DUAL FED BUS WEATHER STALL WARN MANUAL PROP DEICE CONTROL RIGHT FUEL CONTR HEAT BRAKE DEICE RIGHT FUEL VENT HEAT RIGHT PITOT HEAT FUEL 2 FIREWALL VALVE 2 PRESS WARN ENGINE 2 START CONTR 2 ICE VANE CONTR 2 IGNITOR CONTR...

Page 122: ...ry furnishes dc power when the engines are not operating This 24 volt 34 ampere hour battery located in the right wing center section is accessible through a panel on the top of the wing DC power is produced by two engine driven 28 volt 250 ampere starter generators Controls and indicators associated with the dc supply system are located on the overhead control panel and consist of a single BATT O...

Page 123: ...switch is placed in the ON position The light will normally extinguish within 2 to 5 minutes indicating that the battery is approaching a full charge The time interval will increase if the battery has a low state of charge the battery temperature is very low or if the battery has previously been discharged at a very low rate i e battery operation of radios or lights for prolonged periods The cauti...

Page 124: ...rter provides 115 volt and 26 volt 400 Hz ac output The inverters are protected by circuit breakers mounted on the dc power distribution panel mounted beneath the floor Aircraft equipment operating from single phase ac include the following autopilot navigation receivers the tuning portion of the ADF receiver gyro magnetic compass and engine instruments for fuel flow and torquemeters Controls and ...

Page 125: ...the overhead control panel to provide a monitoring capability for both 115 Vac buses AC power load and frequency Hz are continuously displayed Normal output of the inverters will be indicated by 115 Vac and 400 Hz on the meters Figure 2 29 AC Electrical System Schematic Diagram C D1 Sheet 1 of 3 2 109 ...

Page 126: ...TM 1 1510 218 10 Figure 2 29 AC Electrical System Schematic Diagram D2 Sheet 2 of 3 2 110 ...

Page 127: ...TM 1 1510 218 10 Figure 2 29 AC Electrical System Schematic Diagram T Sheet 3 of 3 2 111 ...

Page 128: ... the overhead control panel A switch placarded MASTER PANEL LIGHTS on the overhead control panel provides overall on off control for all engine instrument lights pilot and copilot instrument lights overhead panel lights console and subpanel c Strobe Beacons The strobe beacons are dual intensity units They are protected by a 15 ampere circuit breaker placarded BCN on the overhead circuit breaker pa...

Page 129: ...0 1 Landing Taxi Lights 2 Upper Strobe Beacon 3 Tail Navigation Light 4 Emergency Exit Light 5 Lower Strobe Beacon 6 Wing Navigation Lights 7 Recognition Lights 8 Ice Lights Figure 2 30 Exterior Lighting Typical 2 113 ...

Page 130: ...EL CONSOLE D2 on the overhead circuit breaker panel 3 Radio Panel Instrument Lights D2 T Radio panel instrument lights provide direct adjustable lighting for individual radios and switches A rheostat placarded RADIO PANEL LIGHTS located on the overhead control panel is used to adjust light levels from OFF to BRT bright Turning the control clockwise from OFF turns the lights on and increases their ...

Page 131: ...ected to the emergency battery bus Control is provided by a switch mounted adjacent to the light 2 87 EMERGENCY LIGHTING 2 Interior Lights T2 Dual intensity cold cathode lights are installed on both sides of the overhead trim The circuits are protected by a 10 ampere circuit breaker placarded CABIN LIGHTS located on the overhead circuit breaker panel Control is provided by a switch placarded CABIN...

Page 132: ...zes one static button on each side of the fuselage c Alternate Static System An alternate static airline that terminates just aft of the rear pressure bulkhead provides a source of static air for the pilot s instruments in the event of source failure from the pilot s static air line A control on the pilot s subpanel placarded PILOT S STATIC AIR SOURCE may be actuated to select either NORMAL or ALT...

Page 133: ...TM 1 1510 218 10 Figure 2 31 Pitot and Static System 2 117 ...

Page 134: ...altimeter is located on the upper right side of the instrument panel The altimeter is pneumatically operated and requires no electrical power for operation The altimeter does not have altitude reporting capability A dc powered vibrator operates inside the altimeter whenever power is on It is protected by a 1 ampere circuit breaker placarded COPILOT ALTM located on the overhead circuit breaker pane...

Page 135: ...ides have a master warning light ANVIS yellow and master caution light ANVIS green with a PRESS TO TEST switch located in the right inboard subpanel section The warning annunciator panel is located in the glareshield immediately above the fire extinguisher system controls on the instrument panel The caution advisory panel is located on the subpanel In other respects the annunciator panels are as d...

Page 136: ...ght bleed air warning line has melted or failed indicating possible loss of 2 engine bleed air All 2 FUEL PRESS ANVIS Yellow Fuel pressure failure on right side All 1 CHIP DETR ANVIS Yellow Contamination of 1 engine oil detected All A P TRIM FAIL ANVIS Yellow Trim won t run or running opposite direction commanded All A P DISC ANVIS Yellow Autopilot is disconnected All 2 CHIP DETR ANVIS Yellow Cont...

Page 137: ...l PROP SYNC ON Yellow Synchrophaser turned on with landing gear extended C D 2 VANE FAIL Yellow 2 engine ice vane malfunction Ice vane has not attained proper position All HYD FLUID LOW Yellow Hydraulic fluid level in reservoir is low D2 T1 PASS OXY ON Green Passenger oxygen system is on D 1 VANE EXT Green 1 ice vane extended All 1 IGN ON Green 1 engine ignition start switch on or 1 engine auto ig...

Page 138: ... Green Propeller levers are not in the high RPM low pitch position with the landing gear extended All 2 NAC LOW ANVIS Green 2 engine has 30 minutes fuel remaining at sea level normal cruise power consumption rate All 2 EXTGH DISCH ANVIS Green 2 engine fire extinguisher discharged All 1 VANE FAIL ANVIS Green 1 engine ice van malfunction Ice vane has not attained proper position All DUCT OVERTEMP AN...

Page 139: ...ution light signifies a condition other than hazardous requiring pilot attention A green advisory light indicates a functional situation Refer to Tables 2 11 and 2 12 for a list of causes for illumination of the individual annunciator lights In frontal view both panels present rows of small opaque rectangular indicator lights Word printing on each indicator identifies the monitored function situat...

Page 140: ...nter of the control wheels Figure 2 22 The clocks operate independently of each other receiving dc electrical power through the 5 ampere CABIN LIGHTS circuit breaker located in the overhead circuit breaker panel and a 1 5 ampere fuse located in the instrument lights fuse panel assembly under the aisle forward of the main spar Section XII SERVICING PARKING AND MOORING 2 100 GENERAL CAUTION The foll...

Page 141: ...plicable fuel tank filler cap Make sure latch tab on cap is pointed aft 9 Wash off spilled fuel immediately 10 Handle the fuel hose and nozzle cautiously to avoid damaging the wing skin 5 Disconnect bonding cables from aircraft 2 103 DRAINING MOISTURE FROM FUEL SYSTEM 11 Do not conduct fueling operations within 100 feet of energized airborne radar equipment or within 300 feet of energized ground r...

Page 142: ... Pump Filter Drain 4 Battery Ram Air Vent 13 Refreshment Bar Drain If Installed 5 Battery Drain 14 Oxygen Regulator Vent 6 Boost Pump Drain Both Sides 15 Relief Tube Drain 7 Fuel System Drain Both Sides 16 Surface Deice Ejector Exhaust 8 Leading Edge Tank Drain Both Sides 17 Fuel Sump Drain Both Sides 9 Fuel Vent 18 Heated Fuel Vent Both Sides Figure 2 32 Vent Drain Locations 2 126 ...

Page 143: ... Jet A Gulf Jet A 1 EXXON Co USA EXXON Turbo Fuel B EXXON A EXXON A 1 Mobil Oil Mobil Jet B Mobil Jet A Mobil Jet A 1 Phillips Petroleum Philjet JP 8 Philjet A 50 Shell Oil Aeroshell JP 8 Aeroshell 640 Aeroshell 650 Sinclair Superjet A Superjet A 1 Standard Oil Co Jet A Kerosene Jet A 1 Kerosene Chevron Chevron B Chevron A 50 Chevron A 1 Texaco Texaco Avjet B Avjet A Avjet A 1 Union Oil Union JP 8...

Page 144: ...EL TYPE MAX HOURS PT6A MIL T 5624 MIL T 5624 MIL G 5572 150 Grade JP 8 Grade JP 5 Any AV Gas Maximum operating hours with indicated fuel between engine overhauls TBO 2 105 USE OF FUELS a Fuel Use Limitations There is no special limitation on the use of Army standard fuel but certain limitations are imposed when alternate or emergency fuels are used For the purpose of recording fuel mixtures shall ...

Page 145: ... Hydraulic Landing Gear System D2 T Servicing the hydraulic landing gear system consists of maintaining the correct fluid level and maintaining the correct accumulator precharge The accumulator is located in the reservoir access area and is charged to 800 50 psi using bottled nitrogen A charging gauge is mounted on the accumulator A reservoir located just inboard of the LH nacelle and forward of t...

Page 146: ...er Receptacle 9 Landing Gear Tires 3 Hand Fire Extinguisher 10 Engine Fire Extinguisher 4 Battery 24 Vdc 11 Engine Oil Filler Cap Typical Left and Right 5 Oxygen System Filler Port 12 Wheel Brake Fluid Reservoir 6 Oxygen Cylinder 49 Cu Ft 13 Hydraulic Reservoir 7 Electric Toilet Figure 2 33 Servicing Locations ...

Page 147: ...aircraft empty except for full fuel and oil inflate the strut until the inner cylinder is extended 5 56 to 5 93 inches 8 Remove the tank by pulling the recessed carrying handle on the tank tip b Tank Cleaning 2 108 INFLATING TIRES 1 Dispose of tank contents by holding the tank upside down over a sewer or toilet and pulling the knife valve actuator handle opening the valve and allowing the tank to ...

Page 148: ...ficiently to wet area but without excessive drainage A fine spray is recommended to prevent waste Use diluted hot fluid to remove ice accumulations 3 Remove the cap in the flush hose quick disconnect and connect the hose coupling to the quick disconnect Lock the disconnect lock ring 4 Pull the knife valve actuator to fully open the valve 1 Remove frost or ice accumulations from aircraft surfaces b...

Page 149: ...cing could occur Turn off all external power while connecting the power cable to or removing it from the external power supply receptacle Be certain that the polarity of the external power source is the same as that of the aircraft before it is connected Keep fire and heat away from oxygen equipment Do not smoke while working with or near oxygen equipment and take care not to generate sparks with ...

Page 150: ... abruptly NOTE 7 Tow the aircraft slowly avoiding sudden stops especially over snowy icy rough soggy or muddy terrain To compensate for loss of aircraft cylinder pressure as the oxygen cools to ambient temperature after recharging the cylinder should be charged initially to approximately 10 over prescribed pressure Experience will determine what initial pressure should be used to compensate for th...

Page 151: ... will be dependent upon existing circumstances Allow sufficient slack in ropes chains or cable to compensate for tightening action due to moisture absorption of rope or thermal contraction of cable or chain Do not use slip knots Use bowline knots to secure aircraft to mooring stakes 2 Chock the wheels b Mooring Procedures for High Winds Structural damage can occur from high velocity winds therefor...

Page 152: ... break up the aerodynamic flow of air over the wing thereby reducing the lift being applied against the mooring by the wind The storm appears to pass two times each time with a different wind direction This will necessitate turning the aircraft after the first passing 8 Place control surfaces in locked position and trim tab controls in neutral position Place wing flaps in up position 13 After high...

Page 153: ...TM 1 1510 218 10 Figure 2 34 Mooring 2 137 2 138 blank ...

Page 154: ... ...

Page 155: ...ontrol panel Figure 2 15 Individual system circuit breakers and the associated avionics buses are shown in Figures 2 27 and 2 28 and Tables 2 6 2 7 2 8 and 2 9 With the switch in the ON position the avionics power relay is de energized and power is applied through both the AVIONICS MASTER POWER 1 and 2 circuit breakers to the individual avionics circuit breakers on the overhead circuit breaker pan...

Page 156: ...umentation required to establish and maintain an accurate flight course and position and to make an approach on instruments under Instrument Meteorological Conditions IMC The navigation configuration includes equipment for determining attitude position destination range and bearing heading reference and groundspeed The common avionics in the navigation equipment group consists of the gyromagnetic ...

Page 157: ...tric Knobs 5 ENT Button 6 CLR Button 7 Button 8 Altitude Button 9 MSG Button 10 Left Inner and Outer Concentric Knobs Figure 3 1 KLN 90B Controls Figure 3 2 KLN 90B External Switches Annunciators and Data Loader C D Sheet 1 of 3 Figure 3 2 KLN 90B External Switches and Annunciators T1 Sheet 2 of 3 3 3 ...

Page 158: ...pace are also provided only for the primary area Refer to Figure 3 3 Figure 3 3 Database Area The following is a list of the KLN 90B database contents NOTE Items indicated with an asterisk are included in the primary database coverage area but not in the secondary coverage area The exception is that airports in the primary coverage area include those public and military bases having a runway at le...

Page 159: ...ass high altitude low altitude terminal undefined f Latitude and Longitude g Magnetic variation 3 NDB s a Identifier b Name c Frequency d Latitude and Longitude NOTE Outer compass locators are stored as intersections 4 Intersections low altitude high altitude SID STAR approach and outer markers a Identifier b Latitude and Longitude 5 SID STAR Approach Procedures a All compatible pilot nav SID STAR...

Page 160: ... just barely begins to become snug Do not turn so far counterclockwise that the mechanism starts to bind and can no longer be turned 3 Pull the unit out of the rack by pulling on the sides of the panel DO NOT PULL ON THE KNOBS 4 Remove the old cartridge by pulling it straight out of the back 5 Insert new cartridge into the back of the KLN 90B as indicated by the label on the cartridge When the car...

Page 161: ... The KLN 90B was designed to provide worldwide navigation coverage from North 74o latitude to South 60o latitude Outside this area magnetic variation must be manually entered e Turn On and Self Test 1 Turn on the KLN 90B by pressing the power brightness knob to the IN position It takes a few seconds for the screen to warm up 2 The Turn On page will be displayed for a few seconds During this time t...

Page 162: ...rrected very precisely once a satellite is received 7 Altimeter Setting a With the Army Engine Trend Monitoring AETM system installed and interfaced with the appropriate altimeter the correct barometric altimeter setting is input via the pilot s altimeter It will not be possible to access the BARO field on the Self Test page or the Altitude page If there is no colon after the BARO field it cannot ...

Page 163: ...n the page identifier if there is only one page for a particular page type Whenever a sign is part of a page identifier there will be two or more pages all having the same page number used to present all of the information That is all of the information associated with a particular page number doesn t fit on the page being viewed The lower center segment of the display is used to present four diff...

Page 164: ...select the first character of the waypoint identifier 4 Move the outer knob one step clockwise to move the cursor to the second character position 5 Rotate the inner knob to select the second character 6 Use the outer and inner knobs in this manner until the complete waypoint identifier is displayed Table 3 1 Left Side Types PAGE IDENTIFIER KNOB MARKING PAGE NAME PAGE NUMBERS TRI TRIP Trip Plannin...

Page 165: ...aircraft displayed last To view the rest rotate the left outer knob clockwise Doing so will move the cursor over waypoints two three and four and then will cause the waypoint list to scroll so that the other waypoints in the list may be seen To select the desired waypoint 1 Move the cursor over the appropriate choice 2 Press the ENT button to view the waypoint page for the selected waypoint 3 Pres...

Page 166: ...fly along the active flight plan or direct to a waypoint starting from the initialization waypoint A heading may be entered in the initial heading field while in the take home mode if the one offered is not desired If the take home mode is used the KLN 90B must be initialized to the aircraft s location when it is re installed 8 Use the left knobs to select the NAV 2 page When the KLN 90B reaches t...

Page 167: ...mbers are considered lower than letters The faster the knob is turned the larger the step through the waypoints This variable rate scanning allows quick movement through the list When the knob is turned slowly the waypoints are scanned one at a time A list of the nine waypoints nearest to the present location is located at the beginning of the complete lists for airports VOR s and NDB s It is nece...

Page 168: ... the VOR NDB or airport type waypoint For the airport type waypoint use the right inner knob to select APT 1 for airport name or APT 2 for airport location as appropriate 2 Press the right CRSR button Make sure the right inner button is pushed to the in position 3 Rotate the right outer knob clockwise until the cursor is over the first character in the VOR name NDB name airport name or airport cit...

Page 169: ... on the left side with a flashing cursor over a waypoint identifier The waypoint identifier that appears on the Direct To page is chosen by the KLN 90B according to the following rules 1 If the flight plan 0 page is displayed on the left side and the cursor is over one of the waypoint identifiers in flight plan 0 when the D button is pressed then that waypoint identifier will appear on the direct ...

Page 170: ...to was started while the NAV 1 page was shown on the left side then the left and right pages will revert to the pages that were shown before the direct to was started The selected waypoint is now the active direct to waypoint NOTE In some cases during approach operations the KLN 90B presents a page asking how a waypoint is used when the waypoint identifier is entered character by character When th...

Page 171: ...0 displays the following information a The Active Navigation Leg For direct to operation this consists of the direct to symbol D followed by the active DIRECT TO waypoint identifier For the leg of a flight plan this consists of the FROM waypoint identifier and the active TO waypoint identifier An arrow o precedes the active waypoint identifier KHPN KOSH DIS 683NM GS 193KT ETE 3 34 BRG 303o NAV 1 F...

Page 172: ...m One degree of longitude is 60 nm at the equator and progressively less than 60 nm as one travels away from the equator One degree of longitude is approximately 50 nm at the southern most parts of the U S and is approximately 40 nm at the northern most parts of the U S The MSA altitude information is contained in the database and is updated when the database cartridge is updated Figure 3 12 Minim...

Page 173: ...ange the digits 6 Press altitude to return to the pages previously displayed CAUTION The altitude alerting feature will only be accurate if the barometric altimeter setting is kept updated NOTE Due to the resolution of the altitude input it may be necessary to descend slightly below or climb slightly above the selected altitude before the two tones are activated indicating that the selected altitu...

Page 174: ...age was selected by pressing the altitude button press the altitude button once again to return to the pages previously in view If the NAV 4 page was selected by using the outer and inner knobs insure the cursor function is off and use the outer and inner knobs to select the desired page Approximately 90 seconds before the time to begin the descent the message prompt will flash The message page wi...

Page 175: ...y an aircraft symbol The range scale is displayed in the right corner of the NAV 5 page The range scale indicates the distance from the aircraft s position to the top of the screen Range scale selections from 1 nm to 1000 nm may be made by pressing the appropriate CRSR button and turning the appropriate inner knob When the NAV 5 page is displayed on the left side of the screen and any selected way...

Page 176: ...ner knob The map orientation choices are the same as for the NAV 5 page NOTE The track up graphics presentation can only be displayed if the aircraft is moving at least 2 knots The heading up or North up display may be necessary if there is little or no movement When the desired selections have been made press the right CRSR button to remove the menu Like the NAV 5 page the Super NAV 5 page shows ...

Page 177: ... in the database with regard to altitude when the actual altitude limitations are charted in terms of Mean Sea Level MSL Therefore for flight above or below an area of special use airspace there will be no alert If the actual lower limit is charted in terms of an altitude Above Ground Level AGL it is stored in the KLN 90B as all altitudes below the upper limit If the actual upper limit is charted ...

Page 178: ... States and Canada KORL ORLANDO FL ELV 110FT Z 05 04DT ILS R APT 2 t Airport Pages There are eight airport pages for every airport in the published database The database primary area contains public use and military airports that have a runway at least 1000 feet in length The airport pages contain 1 Airport 1 Page Refer to Figure 3 19 Figure 3 20 APT 2 Page NOTE The APT 1 page has a different form...

Page 179: ...iagram c Runway Lighting Availability Refer to Table 3 6 for displays and explanations Table 3 6 Runway Lighting DISPLAY EXPLANATION L Runway lighting sunset to sunrise LPC Runway lighting is pilot controlled LPT Runway lighting is part time or on request Blank Blank indicates no lighting APT 3 07 13 31 25 d Runway length in feet Figure 3 21 APT 3 Page e Runway Surface Refer to Table 3 7 for runwa...

Page 180: ...quency CL C Class C VFR frequency CLR Clearance delivery CTA Control area VFR frequency CTAF Common traffic advisory frequency CTR Center when center is used for approach departure control DEP Departure control DIR Director approach control radar GRND Ground control MF Mandatory frequency MCOM Multicom PCL Pilot controlled lighting PTAX Pre taxi clearance RAMP Ramp taxi control RDO Radio RDR Radar...

Page 181: ... In a few cases APR DEP CL B CL C TRSA CTA and TMA frequencies are sectorized such that the restriction cannot be displayed on a single page When this occurs TEXT OF FREQUENCY USAGE NOT DISPLAYED is displayed on the APT 4 page There are some airports in the database for which no communications information is available In this case COMM FREQ DATA NOT AVAIL is displayed Table 3 9 Customs Information...

Page 182: ...el Available 80 80 Octane 100 100 Octane 100LL 100 Octane Low Lead 8 Airport 8 Page The APT 8 Page shows the non precision approaches that are available for the selected airport If there are no approaches for this airport in the database this page will display NO APPROACH FOR THIS AIRPORT IN DATABASE Use of approaches will be addressed after flight plans are presented c Oxygen Services If there ar...

Page 183: ...g and distance to the NDB Figure 3 27 Intersection Page 1 The intersection outer marker or outer compass locator name 2 The location of the intersection outer marker or outer compass locator expressed in terms of a radial and distance from a nearby VOR The KLN 90B chooses the closest VOR It takes a few seconds for the VOR ident radial and distance to be calculated and displayed v NDB Page Refer to...

Page 184: ...ts may be defined as a user defined airport VOR NDB or intersection If the waypoint doesn t fit into one of these categories it may be defined as a supplemental waypoint 1 Creating A User Defined Airport Waypoint A user defined airport waypoint must contain an identifier latitude and longitude In addition any combination of airport elevation one runway length and associated runway surface hard or ...

Page 185: ...tude Press the ENT button to approve the waypoint position FARM RWY LEN APT 3 7 Turn the right inner knob one step clockwise to display the APT 2 page as illustrated in Figure 3 30 To enter an airport elevation press the right CRSR button and rotate the right outer knob to position the cursor over the dashes to the right of ELV Use the right inner and outer knobs to enter the elevation Press the E...

Page 186: ... an airport user waypoint Begin by selecting the NDB waypoint type pages The NDB identifier can be one to three characters in length An NDB user waypoint page contains the user identifier at the top of the page and three lines of dashes The top line of dashes may be filled in with the NDB frequency The second line is for latitude and the third line is for longitude Refer to Figure 3 33 1 Use the r...

Page 187: ...4 The active flight plan is always FPL 0 The standard procedure is to create a flight plan in one of the flight plans numbered as 1 through 25 When one of these numbered flight plans is activated it becomes FPL 0 the active flight plan If desired a flight plan may be created directly in the active flight plan This avoids creating the flight plan in a numbered flight plan and then having to activat...

Page 188: ...lowing the creation of a user defined waypoint will appear on the right SWR TYPE WPT 1 EN ROUTE 2 SID STAR VOR SWR D SQUAW VALLEY L 113 20 16o E N 39o 10 82 W120o 16 18 ENR LEG CRSR ENT APT 1 KNEW LAKEFRONT CL C N 30o 02 53 W 90o 01 69 USE INVRT 1 KNEW 2 ENR LEG CRSR ENT Figure 3 38 Waypoint Type Identification Page Figure 3 37 Flight Plan and Waypoint Page 2 Use the same procedure to enter the re...

Page 189: ... the left outer knob one step clockwise to position the cursor over USE INVRT before pressing the ENT button 1 KMKC 2 BUM DEL OSW 4 TUL 6 KRVS CRSR 5 The selected flight plan is now displayed as FPL 0 the active flight plan Any changes made to FPL 0 will not affect how this flight plan is stored as the numbered flight plan ac Adding A Waypoint To A Flight Plan A waypoint may be added to any flight...

Page 190: ...n the CLR button and the ENT button af Storing FPL 0 As A Numbered Flight Plan The active flight plan may be loaded into a numbered flight plan so that it can be recalled for later use 1 Select a numbered flight plan page that does not contain any waypoints If none exist use the procedure for deleting flight plans to clear a flight plan that is no longer required 2 Press the left CRSR button to tu...

Page 191: ...not be given if the change in desired track is less than 5 or the KLN 90B is interfaced with an HSI having a course pointer that is automatically slewed to the correct desired track The desired track displayed on the NAV 3 page also changes to the value of the next leg at the beginning of turn anticipation Turn anticipation becomes inactive when transition to the next leg has been made The KLN 90B...

Page 192: ...he inner knob out it is possible to scan through the waypoints of the active flight plan When the desired waypoint is highlighted press the D button and then the ENT button 3 Press the D button The waypoint page for the selected waypoint will be displayed on the right side Refer to Figure 3 46 4 Press the ENT button to approve the waypoint page The DIRECT TO waypoint identifier in the active fligh...

Page 193: ...re 3 51 NAV 1 D T 1 2 GPT DIS 34NM ETE 11 8 KPIE DIS 477NM ETE 2 39 ENR LEG KNEW GPT DIS 34 2NM GS 180KT ETE 11 BRG 064o DIS DTK 34 063o 76 061o 163 085o 243 092o 477 172o D T 3 ENR LEG 1 KNEW 2 GPT 3 SJI 4 CEW 5 MAI 8 KPIE FPL 0 Figure 3 49 Non Flight Plan Distance Time 1 Page 2 Distance Time 2 Page When FPL 0 is displayed on the left side and the D T 2 page is displayed on the right side the dis...

Page 194: ... b Press the switch and it will change the modes and annunciate the mode selected f Flight Time If RUN WHEN GS 30 knots is selected on the SET 4 page flight time is the amount of time that the aircraft s groundspeed has been above 30 knots Normally this will be the time since takeoff However time spent at groundspeeds less than 30 knots such as intermediate stops without shutting down power is not...

Page 195: ...ctrically driven mechanical indicator the external indicator will be slewed to agree with what was entered on the KLN 90B In some installations where the KLN 90B is interfaced to certain models of EFIS equipment the scale factor will be 7 5 nm full scale 1 Select the NAV 3 MOD 2 or Super NAV 5 page b The course is defined by the active waypoint and the selected magnetic course A course to or from ...

Page 196: ...the external indicator if it was set pictorially correct NAV 1 D CRS 234 GGT DIS 20 0NM GS 154KT ETE 08 BRG 234o 2 If the KLN 90B is interfaced with a compatible EFIS electrically driven mechanical HSI or is not displayed on the external indicator the selected course is chosen by the KLN 90B such that the deviation from the selected course remains the same Figure 3 54 OBS DIRECT TO Course 7 Activa...

Page 197: ...n to the LEG and OBS course modes there are also two approach modes These are approach arm and approach active The status of the approach mode is indicated both on the external switch annunciator and on the status line of the KLN 90B The external annunciator will indicate ARM for the approach arm mode and approach active will be annunciated by ACTV The main difference between these modes from the ...

Page 198: ... automatic and occurs at position C when 1 Select And Load The Approach Into The Flight Plan This can be done at almost any time but must be completed before reaching the final approach fix and should be done as soon as possible position A If the aircraft is greater than 30 nm from the airport the CDI scale factor will remain at the default 5 0 nm full scale deflection 1 The aircraft is 2 nm from ...

Page 199: ...s required to fly a holding pattern position F ao Selecting An Approach Approaches are selected from the APT 8 or ACT 8 page for the destination airport NOTE Approaches can only be entered in FPL 0 the active flight plan If the KLN 90B is turned off for more than 5 minutes the approach is deleted when power is turned back on 1 Turn to the APT or ACT pages and select the destination airport using t...

Page 200: ... by pressing the CLR button At the top of the list of approach waypoints is a header that describes the approach that follows The form of this header is ABBBB CCCC A is the first letter of the type of approach e g V for VOR BBBB will be filled in with the runway that the approach is to Finally CCCC corresponds to the identifier of the airport that the approach is to For example V25R KLAX means the...

Page 201: ...er NAV 5 page and the Super NAV 1 page The suffixes are shown in Table 3 16 Table 3 16 Approach Waypoint Suffixes SUFFIX EXPLANATION f final approach fix i initial approach fix m missed approach point h missed approach holding point Every approach will have an FAF and a MAP Almost all will have an IAF and a missed approach holding point Another item in the flight plan is the line NO WPT SEQ This i...

Page 202: ...ovide the message PRESS ALT TO SET BARO Press the ALT button to bring up the ALT page and verify that the altimeter setting is correct At this time the KLN 90B will change the GDI scale factor to 1 0 nm The external approach mode annunciator will indicate that the approach is in the ARM mode 3 As the initial approach fix is approached the KLN 90B will provide waypoint alerting on the external wayp...

Page 203: ...y one IAF the KLN 90B does not give the option to choose an IAF If there is no active flight plan i e direct to navigation is being used without an active flight plan the KLN 90B will ask to add the airport and the approach to FPL 0 Refer to Figure 3 67 Figure 3 66 GPS Approach Mode Active NOTE V22 KCVN PRESS ENT TO ADD KCVN AND APPR TO FPL 0 APPROVE CRSR ENT Some approach procedures require addin...

Page 204: ... active mode 1 When the aircraft is 2 nm from the FAF the KLN 90B will verify that proper integrity is available If integrity monitoring is available for the approach the KLN 90B will change to the approach active mode This will be annunciated on the external approach status annunciator as well as on the KLN 90B The CDI scale factor will also start to change from 1 0 nm to 0 3 nm 2 Upon reaching t...

Page 205: ...he flight plan 2 When the distance from the present position to the destination airport reaches 30 nm the KLN 90B will arm the approach mode The CDI scale factor will transition to 1 0 nm and the KLN 90B will provide more sensitive integrity monitoring Press the altitude button to update the altimeter setting 3 Change the selected course on the HSI to the final approach course It is possible to ma...

Page 206: ...he missed approach point will become active and the CDI scale factor will remain at 0 3 nm If the auto scale factor was selected on the Super NAV 5 page the scale factor will zoom in on the airport as the aircraft gets closer and closer to the missed approach point Eventually the map scale changes to 1 nm and the runway diagram becomes visible on the map 9 The missed approach instructions may call...

Page 207: ... is named in the same convention as above 1 From the Super NAV 5 page pull out the right inner knob to bring up the waypoint scanning window 2 Turn the right inner knob until the first waypoint of the arc is displayed For approaches this will have an i appended to the waypoint name If the recalculation is to be done from the FPL 0 page turn on the left cursor and move if over the first waypoint of...

Page 208: ...ssary to manually change the active waypoint When the FAF and the missed approach holding point are the same the KLN 90B will automatically change the active waypoint to the FAF when the change from OBS to LEG is made This change needs to be made as soon as possible to ensure the approach active mode becomes the active mode 11 Some DME arcs have defined radials that serve as step down fixes These ...

Page 209: ... start The calculation will usually take a few seconds 6 Once the RAIM calculation is complete the STA 5 page will indicate the results of the test Refer to Figure 3 72 This is done graphically in a bar graph The center of the bar graph represents the ETA Each bar represents 5 minutes of time The RAIM calculation is good for 15 minutes of the ETA Bars that are above the line indicate RAIM is avail...

Page 210: ...oint to the active flight plan az Selecting a STAR The steps required to select a STAR are very similar to those required to select a SID The only difference is the order of the steps to define the STAR and where the STAR is loaded into the flight plan 1 Select the APT 7 or the ACT 7 page for the destination airport Ensure the words SELECT STAR are displayed near the top of the screen 2 Turn the r...

Page 211: ...he identifier and a question mark will appear to the right of the identifier 4 If this is the desired waypoint to delete then press the ENT button If it is not the desired waypoint press the CLR button NOTE Adding waypoints to or deleting waypoints from SID or STAR procedures does not change the way that they are stored in the published database 3 Changing Or Deleting An Entire SID Or STAR Procedu...

Page 212: ...r defined waypoints are listed by category airports A are first VOR s V are second NDB s N are third intersections I are fourth and supplemental S waypoints are last Within each category the waypoints are alphabetized by identifier To the right of the identifier is the type waypoint A V N I or S If the waypoint is used in a flight plan the flight plan number is shown to the right of the waypoint t...

Page 213: ...press the left CRSR button rotate the left outer knob to move the cursor over the RES field Use the left inner and outer knobs to enter the desired fuel quantity Press the left CRSR button to turn off the left cursor function a OTH 5 Page The OTH 5 page displays the following information Refer to Figure 3 75 OTH 5 KLFT LBS FOB 1800 REQD 740 L FOB 1060 RES 500 EXTRA 560 7 The calculated extra fuel ...

Page 214: ...sity altitude and pressure altitude The KLN 90B will also calculate and display real time wing data magnitude and direction The OTH 9 and OTH 10 pages are used to display air data information Figure 3 79 depicts the OTH 9 page display NOTE These air data pages receive inputs from air data sensors and display real time air data information They are independent of the calculator pages that rely on m...

Page 215: ... uploaded to the disks These disks may be used in this specific KLN 90B an unlimited number of times that could be required if switching between the North American and International databases occurs during one update cycle These disks however may not be used to update other KLN 90B s This update protection ensures that Jeppesen Sanderson is properly compensated for their NavData b The aircraft mus...

Page 216: ...ition the flashing part of the cursor over the month 8 Use the left knobs to select the NAV 2 page When the KLN 90B reaches the NAV ready status and is able to navigate the NAV 2 page will display the present position Verify the latitude longitude and distance display of the VOR radial are correct 5 Rotate the left inner knob to select the correct month 6 Turn the left outer knob one step clockwis...

Page 217: ...he KLN 90B is in the OBS mode and the active waypoint is outside the primary coverage area Under both of these conditions the message MAGNETIC VAR INVALID ALL DATA REFERENCED TO TRUE NORTH is displayed on the message page When navigation is within the primary coverage area the SET 2 page does not display magnetic variation However under the above conditions a user entered magnetic variation may be...

Page 218: ...n airport This airport is any airport that is a direct to waypoint or is the to waypoint in the active flight plan The height of the cylinder above the airport is the height selected on the SET 5 page The KLN 90B adds the selected altitude to the elevation stored in the database for the airport The KLN 90B provides an altitude alert light when the aircraft first penetrates the cylinder Figure 3 84...

Page 219: ...tion of the vertical buffer Use the left inner knob to select each number and the left outer knob to position the cursor The buffer may be selected in 100 foot increments After the desired selection has been made press the left CRSR button to turn off the cursor function SET 8 AIRSPACE ALERT ENABLE VERT BUFFER 01000FT Figure 3 88 SET 8 Page 10 The Setup 9 Page There are no aural alarms associated ...

Page 220: ... the cursor function 2 The Trip Planning 1 And 2 Pages The TRI 1 and 2 pages allow trip planning from the aircraft s present position to any selected waypoint Unlike the other trip planning pages in order to use the TRI 1 and 2 pages the KLN 90B must either be receiving GPS signals sufficient to be in the NAV ready status or be in the take home mode The TRI 1 page provides estimates of distance es...

Page 221: ...estination waypoint The estimated amount of fuel required F REQ to fly to the selected waypoint with the specified reserve is now displayed Entering the fuel flow and reserve fuel on the TRI 1 page also inputs this same information on the TRI 3 and 5 pages 10 Press the left CRSR button to turn off the left cursor function 11 Select the TRI 2 page The minimum En route Safe Altitude ESA and a listin...

Page 222: ... receiving GPS signals in order to use these pages 1 Select the TRI 5 page on the left side Figure 3 94 TRI 5 FP 7 750NM KLBB KDAG 217KT 3 27 FF 00600 0 RES 00500 0 F REQ 2569 Figure 3 94 TRI 5 Page 2 Press the left CRSR button to turn on the left cursor function 3 Rotate the left inner knob to select the desired flight plan The first and last waypoints in the selected flight plan are displayed on...

Page 223: ...RS is now displayed 5 Use the left outer knob to move the cursor to the first TEMP position and then enter the outside air temperature in C by using the left inner and outer knobs The first digit of the temperature is either zero if the temperature is above zero or a minus if the temperature is below zero For maximum accuracy the static air temperature should be entered Static air temperature is t...

Page 224: ...is now displayed as illustrated in Figure 3 97 CAL 3 WIND TAS 261KT HDG 343o HDWND 21KT WIND 042o t 53KT Figure 3 98 CAL 3 Page 1 Select the CAL 3 page on the left side 7 Press the left CRSR button to turn off the left cursor function 2 Press the left CRSR button to turn on the cursor function 3 Enter the TAS by using the left inner and outer knobs If the CAL 2 page was previously used to calculat...

Page 225: ...to select the desired values of speed When the desired speed in knots is selected the corresponding speed in miles per hour is displayed 4 Turn the left outer knob to move the cursor to the first FPM position and then enter the desired rate of descent or ascent in feet per minute using the left inner and outer knobs The descent ascent angle is now displayed In addition an angle may be entered and ...

Page 226: ...not be appropriate for the waypoint shown 2 Press the left CRSR button to turn on the left cursor function 2 Press the left CRSR button to turn on the cursor function 3 Rotate the left outer knob to position the cursor over the top time zone abbreviation 3 If desired select another waypoint identifier using the left inner and outer knobs Press the ENT button to view the waypoint page for the waypo...

Page 227: ...aypoint page for the waypoint just entered 6 Press the ENT button again to display the waypoint page for the newly created reference waypoint The waypoint that was used to create the reference waypoint is automatically inserted into the REF field The radial and distance as well as the latitude and longitude are also displayed The left side of the screen shows where the reference waypoint will be i...

Page 228: ...e left side It may be the active flight plan or one of the other 25 numbered flight plans 3 Press the ENT button to compute the Center waypoints Figure 3 107 A Center waypoint will be created at each intersection of the flight plan with a center boundary When computation is complete the CTR 1 page will display how many Center waypoints have been computed Refer to Figure 3 108 USE INVRT 1 KLBB 2 KM...

Page 229: ...aining Center waypoints is modified in any way new Center waypoints may be computed The original Center waypoints are now part of the flight plan and new Center waypoints are computed by treating the original Center waypoints the same as any other waypoints in the flight plan If the interior of a flight plan containing Center waypoints is modified it may be desirable to manually delete obsolete Ce...

Page 230: ...satellites are being acquired and data from them is being obtained STA 1 STATE NAV SV SNR ELE 02 40 11o 11 42 47o 16 36 06o 18B 33 65o The transition stage indicates an adequate number of satellites for navigation has been acquired and is being tracked but no position data can yet be produced Normal navigation is indicated by a NAV NAV A or a NAV D GPS state NAV A indicates that the altitude input...

Page 231: ...gation graphics displays 9 ARM ANNUNCIATOR FAIL This message displays when there is a failure of the KLN 90B ARM annunciator drive circuitry To determine if the approach mode is armed look at the status line of the KLN 90B 10 ARM GPS APPROACH If the approach arm mode has been disarmed the KLN 90B will prompt arming the approach mode when the aircraft is 3 nm from the FAF 11 BAD SATELLITE GEOMETRY ...

Page 232: ...minutes as a result of updating the database 32 POSITIONS OF OTHER WAYPOINTS HAVE CHANGED Appears when the above message POSITION OF WPT HAS CHANGED would be effective for more than 10 waypoints 33 PRESS ALT TO SET BARO Appears when the approach mode is armed 34 PRESS GPS APR FOR NAV Appears after the NAV flag has displayed due to a RAIM problem while the unit is in the approach mode By pressing t...

Page 233: ... set the indicator to 3 DUP IDENT More than one waypoint of that type has the same identifier 4 ENT LAT LON A reminder to enter the location of a user defined waypoint 5 FPL FULL An attempt has been made to add a waypoint to a flight plan that already contains 30 waypoints 6 IN ACT LIST Appears when a user defined VOR is the active waypoint and attempt is made to change the stored magnetic variati...

Page 234: ...The radar and transponder group provides identification position emergency tracking system and a radar system to locate weather areas The common radar and transponder equipment consists of the stormscope WX 1000E and the transponder set AN APX 100 3 9 STORMSCOPE WX 1000E a Description The Stormscope system consists of three components that detect locate and map areas of vertical electrical dischar...

Page 235: ...r the range remains constant Figure 3 114 120 Weather Mode Press the CLEAR button to erase all weather data from the display and system memory The intensity of a thunderstorm can be identified by the speed with which the discharge points appear The system continually receives and processes new electrical discharge information Monitor this by pressing the clear button often The more intense the sto...

Page 236: ...ress the CLEAR button for properly oriented data following an aircraft heading change Press the MENU button to return to the main menu NOTE The date is set before the time 4 Time Date Mode The TIME DATE mode can be selected only from the main menu The time date mode menu displays four items stopwatch elapsed time time of day and day month and year Refer to Figure 3 115 When first selecting the tim...

Page 237: ...Waypoint Identifier XTK Crosstrack Error Figure 3 117 Heading Options 6 Navaid Option This option creates a weather avoidance and navigational view Refer to Figure 3 118 Using data from the KLN 90B this option provides simultaneous display of both thunderstorm and flight information on the system screen The course line selected waypoints and a course deviation indicator are graphically displayed U...

Page 238: ... enable service personnel to diagnose and correct the problem If continued operation is possible a message to press any key to continue operation will be displayed When the LORAN or GPS receiver fails to acquire a consistent signal and is not certain of its position the message NAV FLAG will appear in place of the CDI Navigational data will not be displayed if the receiver indicates a flag conditi...

Page 239: ...sity operation using both antennas c BOT Selects use of bottom antenna 4 RAD TEST OUT Switch Enables an appropriately equipped transponder to reply test mode interrogations from an AN UPM 92 or similar test set 5 MASTER Control Selects system operating mode a OFF Turns set off b STBY Places set in warmup standby condition Red NO GO light is ON in standby position c NORM Operates set at normal sens...

Page 240: ...lid forward to display the selected MODE 2 code 13 MODE 2 CODE Selectors Selects the desired reply code for mode 2 operations 14 MODE 1 CODE Selectors Selects the desired reply code for mode 1 operations 15 MODE 4 TEST ON OUT Switch a TEST Initiates BIT of Mode 4 operation b ON Enables Mode 4 operation c OUT Disables MODE 4 operation 16 MODE 4 CODE Control Selects dialed in Mode 4 CODE of the day ...

Page 241: ... Observe that the TEST GO indicator light illuminates 5 M 1 Switch Return to ON 12 MODE 4 TEST ON OUT Switch ON 6 Repeat steps 4 and 5 for the M 2 M 3 A and M C mode switches 13 ANT Switch BOT 7 MASTER Control NORM 14 Repeat steps 4 5 and 6 Observe that the TEST GO indicator illuminates 8 MODE 4 Code Control A Set a code in the external computer 9 MODE 4 AUDIO OUT Switch OUT 15 TOP DIV BOT ANT Swi...

Page 242: ...communications set that identification position signals are being generated Set any of the M1 M2 M3 A M C or MODE 4 switches to OUT to inhibit transmission of replies in undesired modes With the IDENT OUT MIC switch set to the MIC position the POS IDENT button must be pressed to transmit identification pulses 2 IDENT OUT MIC Switch Press momentarily to IDENT when directed 5 Shutdown Procedure 1 To...

Page 243: ...nergized and power is applied through both 50 ampere avionics MASTER PWR 1 and 2 circuit breakers to the individual avionics circuit breakers on the overhead circuit breaker panel Refer to Figure 2 16 Sheets 1 and 2 In the off aft position the relay is energized and power is removed from avionics equipment When external power is applied to the aircraft the avionics power relay is normally energize...

Page 244: ...nd allows the pilot to talk to cabin occupants 2 VOL Control Controls audio volume 3 ICS 1 OFF Switches Permits monitoring by pilot of selected audio regardless of position of transmitter selector switch a HF Permits monitoring of HF audio b UHF Permits monitoring of UHF audio c VHF 1 Permits monitoring of VHF 1 audio d VHF 2 Permits monitoring of VHF 2 audio e VOR 1 Permits monitoring of VOR 1 au...

Page 245: ...the ADF or VOR switch must be in the OFF position for the other switch to function a HF Permits reception of audio from the HF transceiver and routes key and microphone signals to the HF transceiver a FILTER V OFF Filters out voice on ADF and VOR audio b UHF Permits reception of audio from the UHF transceiver and routes key and microphone signals to the UHF transceiver b FILTER R OFF Filters out i...

Page 246: ...VOL Control 3 ICS 2 OFF Switches 4 FILTER Switches 5 AUDIO NORM EMER Switch 6 AUDIO SPKR PHONE Switch Figure 3A 2 Copilot s Audio Control Panel d Operation 1 Turn On Procedure The audio control panel is on whenever electrical power is applied to the aircraft and the AVIONICS MASTER switch is ON b Controls and Functions 1 Manual Frequency Selector Switch Hundreds Selects hundreds digit of frequency...

Page 247: ...thod of frequency selection a MANUAL Any one of 7 000 frequencies is manually selected using the five frequency selector switches b PRESET Frequency is selected using the preset channel selector switch for selecting any one of 20 preset channels c GUARD The main receiver and transmitter are automatically tuned to the guard frequency and the guard receiver is disabled 9 SQUELCH OFF ON Switch Turns ...

Page 248: ...te receiver is incorporated to provide monitoring capability for the UHF guard frequency 243 0 MHz UHF audio output is applied to the audio panel where it is routed to the headsets NOTE The PRESET channel selector and manual frequency selectors are inoperative when the mode selector is set to GUARD position The receiver transmitter will be set to the emergency frequency only Existing capabilities ...

Page 249: ...ceiver Operating Procedure a MANUAL Enables the manual selection of any one of 7 000 frequencies is manually selected using the five frequency selector switches 1 Transmitter selector switch No 3 position 2 UHF audio monitor switch ON No 3 position b PRESET Frequency is selected using the preset Channel selector switch for selecting any one of 20 preset channels 3 VOL control Mid position c GUARD ...

Page 250: ... 1 VOL control Counterclockwise OFF a Description The VHF command set is a line of sight radio transceiver which provides transmission and reception of amplitude modulated signals in the very high frequency range of 116 000 to 151 975 MHz for a distance range of approximately 50 miles Two VHF radio sets are installed placarded COMM 1 and COMM 2 Audio signals are applied through the pilot and copil...

Page 251: ...o leveling and response shaping to ensure audio quality Transmitter sidetone comes from detected transmitter signal and is therefore a reliable check of transmission quality Each VHF transceiver is powered through its respective circuit breaker placarded VHF 1 or VHF 2 located on the circuit breaker panel b Operating Controls All operating controls for the transceivers are located on the CTL 22C t...

Page 252: ...illuminates whenever a preset frequency is being displayed in the lower window The TX annunciator illuminates whenever the transceiver is transmitting 11 Preset Frequency Display Displays the pre set inactive frequency and diagnostic messages in the lower window 12 Compare Annunciator An annunciator placarded ACT momentarily illuminates when frequencies are being changed The ACT annunciator flashe...

Page 253: ...elected position of the 8 33 or 25 may or may not be annunciated depending on installation After the desired frequency is set into the preset frequency display it can be transferred to the active frequency display by momentarily setting the XF MEM switch to XF At the same time that the preset frequency is transferred to the active display the previously active frequency is transferred to the prese...

Page 254: ...end of 2 minutes the microprocessor turns it off Most intentional transmissions last much less than 1 minute a 2 minute transmission is most likely the result of a stuck microphone switch This timing feature protects the ACT channel from long term interference When it turns off the transmitter the microprocessor switches the transceiver to receive operation A stuck microphone switch will prevent y...

Page 255: ... the HF radio set while operating the ADF No 2 set causes unreliable ADF signals b Controls and Functions HF Command Set Control Panel Refer to Figure 3A 6 1 Frequency Selectors Operating frequency is selected by turning the frequency selector controls until the desired operating frequency is indicated The controls may be operated in any order 2 MHz Indicators Indicates operating frequency of set ...

Page 256: ...lation up to 55 F 131 F ambient temperature NOTE No warmup is required before operation The system may be operated in the receive mode continuously 1 Mode selector As required 2 Frequency selector Select 3 Squelch control Set turn completely clockwise 4 Tune the system by momentarily pressing the microphone switch A constant tone will be heard while the system is tuning average tuning time is 3 to...

Page 257: ... the tune cycle was initiated This beeping indicates a fault condition To clear the fault initiate a new tune cycle by either turning the mode selector to OFF and back to the operating mode or turning any frequency selector away from and back to the operating frequency The tune tone should be present for approximately 3 to 6 seconds and then disappear If the beeping recurs try the clearing procedu...

Page 258: ...ing in the right side of the aft fuselage In the event the impact switch has been inadvertently actuated the beacon can be reset by actuating the remote mounted switch to the RE ARM aft position TR70 13 or by firmly pressing the RESET switch on the front of the case Access to the ELT is through the door on the bottom of the aft right fuselage b Controls and Functions 1 TR70 17 a ON OFF ARM Switch ...

Page 259: ...tch Selects desired source for magnetic heading information for display on copilot s RMI compass card a 1 Selects compass system No 1 for display b 2 Selects compass system No 2 for display c Controls and Functions Refer to Figure 3A 7 1 Double Needle Pointer Indicates bearing selected by double needle switch 2 Compass Card Indicates aircraft heading at top of dial 3 Heading Index Reference point ...

Page 260: ...SI The warning flag will be in view any time the VLF information is invalid or suspected or when any of the system status annunciators SYS SYN AMB or DR are illuminated If the flag is in view with the Ambiguity AMB annunciator illuminated the flag may be cancelled by pressing the BK key on the CDU 8 COURSE Control Knob Used to select desired VOR course 9 Course Deviation Bar Indicates lateral cour...

Page 261: ...or display on compass card of indicator c Copilot s Horizontal Situation Indicator Refer to Figure 3A 9 1 Heading Marker Positioned by HDG knob to selected heading 2 COMPASS Flag Indicates loss of reliable heading information 3 Lubber Line Indicates heading of aircraft 4 Course Arrow Positioned by COURSE knob to selected VOR radial 5 Compass Card Indicates aircraft magnetic heading supplied by sys...

Page 262: ...eslope Pointer Displays deviation from correct glideslope during ILS approach 3A 17 PILOT S HORIZON REFERENCE INDICATOR a Description The horizon reference indicator is the pilot s basic attitude horizon indicator and the attitude direction instrument for the flight director system Refer to Figure 3A 10 b Controls and Functions 1 Crossed Needles Displays computed steering commands 2 Bank Angle Poi...

Page 263: ...0 GYRO Flag Presence indicates loss of power to or low rotational speed of vertical gyro 11 TEST Push Button When pressed display indicates an additional 10 nose up and 20 right roll and the GYRO flag is visible 12 GS Flag Presence indicates glideslope information is not being presented on indicator 13 Vertical Deviation Indicator Displays glideslope deviation information from VOR No 1 receiver 3A...

Page 264: ...he 5 ampere PILOT TURN SLIP circuit breaker located on the overhead circuit breaker panel 1 2 Minute Turn Marks 2 Turn Rate Indicator 3 Gyro Warning Flag 4 Inclinometer Figure 3A 12 Pilot s Turn and Slip Indicator b Controls and Function 1 Turn Rate Indicator Deflects to indicate rate of turn 2 2 Minute Turn Marks Fixed markers indicate 2 minute turn rate when covered by turn rate indicator 3 GYRO...

Page 265: ...EMS a Description Dual identical compass systems provide accurate directional information for the aircraft at all latitudes of the earth As a heading reference two modes of operation are used directional gyro FREE mode or slaved SLAVE mode In Polar Regions of the earth where magnetic heading references are not reliable the system is operated in the FREE mode In this mode the system furnishes an in...

Page 266: ...1 receiver b VOR 2 Circuits are connected to VOR No 2 receiver 2 Copilot s VOR 1 VOR 2 Switch Controls course select and display circuits of the copilot s HSI a VOR 1 Circuits are connected to VOR No 1 receiver b VOR 2 Circuits are connected to VOR No 2 receiver NOTE If the pilot s and copilot s VOR 1 VOR 2 switches are in the same position the pilot has control of the course select circuits of th...

Page 267: ... VOR 2 switch As required 3 Course deviation indicator Steer aircraft as required to center course deviation bar 4 Marker Beacon Operating Procedure 1 Marker beacon indicator lights Figure 2 17 Observe for beacon indication 2 MKR BCN HI LO sensitivity switch Figure 3A 1 As required 3 MKR BCN VOL control Figure 3A 1 As required 5 Glideslope Operating Procedure 1 Frequency selectors Set desired loca...

Page 268: ...trol Operative only when the mode selector switch is in the LOOP or ADF position Center position removes rotation signals from the loop antenna and the ADF pointer on the RMI s First position left L or right R of center applies slow speed rotation signals to loop antenna and ADF pointer on RMI s for 360 rotation left or right Second position left L or right R of center applies fast speed rotation ...

Page 269: ...r be preset to a value and count down to zero The system is protected by a 1 ampere circuit breaker placarded ADF located on the right subpanel The antenna located on the lower side of the aircraft contains loop and sense antennas preamplifiers and modulators which combine the antenna signals into a single RF signal that is output to the receiver via a triaxial cable Refer to Figure 2 1 b Operatin...

Page 270: ...he 1000 s digit from 9 to 10 and borrows from 10 to 9 The two digits roll over from 17 to 02 and under from 02 to 17 limiting the frequencies to the range or 200 kHz to 1799 kHz b Standby Frequency The standby frequency is displayed in the right portion of the display window when the FRQ message is displayed In this case the standby frequency may be changed with the frequency control knobs as desi...

Page 271: ...r 15 seconds after a number is set in or until the SET RST FLT ET or FRQ button is pressed The preset number will remain unchanged until the SET RST button is pressed When the SET RST button is pressed after a number has been preset the elapsed timer will start counting down When the elapsed timer is counting down pressing the SET RST button again will have no effect unless it is held for approxim...

Page 272: ...frequency controls for VOR 1 c HOLD System will remain tuned to previous channel if the VOR is tuned to a new frequency d VOR 2 Allows channel selection using frequency controls for VOR 2 2 VOL Control Controls volume 1 DME SEL Switch 2 VOL Control Figure 3A 17 DME Control Panel c Controls Indicators and Functions DME Indicator Refer to Figure 3A 18 1 TEST Push Button 2 DME MILES Indicator 3 Contr...

Page 273: ...pilot pitch turn panel located on the pedestal extension The operating status of the autopilot is indicated on the autopilot flight director annunciator located on the instrument panel directly above the pilot s horizon reference indicator Two autopilot control switches are also provided on each control wheel One is placarded PITCH SYNC CWS pitch synchronize and control wheel steering and the othe...

Page 274: ...hen autopilot is driving trim servo in down direction or on some aircraft if autopilot is disengaged when manual down trim is required 10 TRIM UP Indicator Illuminates when autopilot is driving trim servo in up direction or on some aircraft if autopilot is disengaged when manual up trim is required 11 ENG DIS Switch Controls coupling of the automatic pilot a ENG Engages autopilot and illuminates e...

Page 275: ...ndicators and Functions Refer to Figure 3A 21 The autopilot flight director incorporates its own annunciator panel located just above the flight director display on the instrument panel The modes and indications given on the annunciator panel are placarded on the face of the lenses and illuminate when the respective conditions are indicated Dimming of the annunciator panel lights is provided by a ...

Page 276: ...uminate The autopilot will then track the selected radio course with automatic crosswind correction c Navigation Mode With Linear Deviation The system features linearized VOR deviation when a VORTAC is being used A LIN DEV light on the autopilot annunciator will illuminate to indicate operation The lateral deviation bar indicates the distance in nautical miles from the selected radial regardless o...

Page 277: ...attitude and synchronizes the vertical command bar on the pilot s horizon reference indicator to aircraft attitude The ALT or IAS mode will disengage if selected when the PITCH SYNC CWS button is pressed When the autopilot is coupled to the HDG NAV APPR or BACK LOC modes releasing the PITCH SYNC CWS switch will cause the autopilot to couple to the previously selected mode i Altitude Hold Mode Pres...

Page 278: ...ourse in COURSE window 4 NAV selector switch Press Observe that NAV ARM annunciator lamp illuminates 5 NAV CAP annunciator lamp Monitor Illumination indicates capture of new radial k Front Course Approach 1 VOR receiver Tune appropriate frequency 2 COURSE knob Set inbound runway heading in COURSE window 3 HDG knob Set heading marker to desired intercept angle 4 HDG selector switch Press Observe th...

Page 279: ... on the autopilot mode selector panel to the DIS position Section IV RADAR AND TRANSPONDER 3A 28 DESCRIPTION The radar and transponder group provides identification position emergency tracking system and radar system to locate weather areas 3A 29 DIGITAL WEATHER RADAR RDR 2000 SYSTEM a Description The RDR 2000 color weather radar not only displays in flight weather but also permits incorporation o...

Page 280: ... located on the overhead circuit breaker panel b Controls and Functions Refer to Figure 3A 22 1 Brightness BRT Control Knob Controls brightness of the indicator display CW rotation for max brightness 2 Function Switch Knob The function switch knob is utilized to turn the system on off and select LOG TST and SBY positions a LOG Selected VOR frequencies along with bearings and distances are displaye...

Page 281: ...a is displayed on the upper left corner of the indicator 5 TILT Knob Permits manual adjustment of antenna tilt 15 up or down for best indicator presentation The tilt angle is displayed in the right corner of the display 6 GAIN Knob The gain knob adjusts the radar gain from 0 to 20 dB CCW rotation reduces gain The gain knob will only function when in the MAP mode 7 Navigation NAV Button Places indi...

Page 282: ...rning may result in permanent damage to the eyes and other body organs of those persons Never turn the radar on within 5 feet of containers of flammable or explosive material Never operate radar during fueling operations NOTE These procedures should be accomplished prior to flight 1 Accomplish the following procedure completely and exactly 1 Function switch TST 2 TILT UP 7 0 as shown on the indica...

Page 283: ...r left section of the radar display A line representing the course selected by the flight management system is drawn through the corresponding active waypoint Selected course bearing for each NAV system is displayed with NAV data on each side of the screen A waypoint line will also be displayed connecting the waypoints in numerical sequence An R on the left side of the screen indicates all visible...

Page 284: ...e radar screen 5 PAGE Button The PAGE button is used to view consecutive pages within a checklist It is also used along with the or buttons to bypass items without checking them off or return to items previously bypassed 6 Up and Down And Button The buttons are used along with the PAGE button to bypass items in the checklist without checking them off or return to items previously bypassed 7 Input ...

Page 285: ... 15 lines 450 characters If the item is longer than one line long do not use the carriage return to move from one line to the next Use spaces Shift Sp as necessary to move the cursor to the end of the line and to the beginning of the following line The carriage return should be used only at the end of the entire item to make the cursor disappear 3 Error Correction Error correction is accomplished ...

Page 286: ...lag Check not visible Needle indicator Check operation d Encoding Altimeter Emergency Operation 1 Altimeter circuit breaker Pull if encoder fault occurs 3A 33 GROUND PROXIMITY ALTITUDE ADVISORY SYSTEM WARNING The ground proximity altitude advisory system will provide little if any warning for flight into precipitous terrain approaching a sheer wall if there is little gradually rising terrain befor...

Page 287: ...r VOICE OFF switch indicator disables the GPAAS voice advisory and illuminates the VOICE OFF indicator light The VA FAIL annunciator light red will illuminate when the GPAAS fails 2 GPAAS Volume Control A GPAAS volume control placarded VOL located on the instrument panel controls the audio volume of the GPAAS advisory warning messages down to a certain minimum level 3 GPAAS Aural Warning Indicatio...

Page 288: ...t announcement if gear is not down 17 Minimum minimum at decision height 18 Localizer at 1 3 to 1 5 dots either side of center of beam Will be repeated three times at 4 second intervals 19 Glideslope at 1 3 to 1 5 dots above or below center of beam Will be repeated three times at 4 second intervals 20 Altitude altitude at excessive deviation from altitude selected on the altitude alerter 21 Check ...

Page 289: ...isory is repeated once at 100 foot intervals down to 100 feet AGL 5 Aural Glideslope Advisory Mode 5 The aural advisory Glideslope indicates that the aircraft has exceeded 1 3 to 1 5 dots above or below the center of the glideslope beam The glideslope advisory is armed when a valid glideslope signal is detected and the aircraft is below 1000 feet AGL It will be repeated no more than three times at...

Page 290: ......

Page 291: ...7 With the switch in the ON position the avionics power relay is de energized and power is applied through both 50 ampere AVIONICS MASTER POWER 1 and 2 circuit breakers to the individual avionics circuit breakers on the overhead circuit breaker panel Refer to Figure 2 16 Sheet 3 NOTE Should the AVIONICS MASTER POWER switch fail to operate power to the individual avionics circuit breakers can be pr...

Page 292: ...Routes key and mic signals to the 2 VHF transceiver c HF Permits reception of audio from the HF transceiver and routes key and microphone signals to the HF transceiver d UHF Permits reception of audio from the UHF transceiver and routes key and microphone signals to the UHF transceiver e PA Permits cabin paging 3 AUDIO SPKR OFF Switch Determines where selected audio will be heard 4 VOLUME Control ...

Page 293: ...red 4 Transmitting Procedure 1 Transmitter selector switch As required 2 Microphone switch Press listen for sidetone 3 Applicable transceiver volume control Adjust for comfortable audio level d Emergency Operation An audio fail safe system is provided for use in the event of an audio amplifier failure If an audio amplifier fails receiver audio bypasses the amplifier and is applied directly to the ...

Page 294: ...selected 5 Manual Frequency Selector Switch Tens Selects tens digit of frequency 0 through 9 in MHz 6 Preset Channel Selector Selects one of 20 preset channels 7 Manual Frequency Selector Switch Hundreds And Thousands Selects hundreds and thousands digits of frequency 00 25 50 or 75 in MHz 8 Mode Selector Selects method of frequency selection a MANUAL Any one of 7 000 frequencies is manually selec...

Page 295: ...ture effect automatic squelch to help prevent missed radio calls plus audio leveling and response shaping to ensure audio quality Transmitter sidetone comes from detected transmitter signal and is therefore a reliable check of transmission quality Each VHF transceiver is powered through its respective circuit breaker placarded VHF 1 or VHF 2 located on the circuit breaker panel b VHF Transceiver O...

Page 296: ...r The SQ OFF position disables the receiver squelch circuits 10 Annunciators The transceiver control unit contains a MEM memory and a TX transmit annunciator The MEM annunciator illuminates whenever a preset frequency is being displayed in the lower window The TX annunciator illuminates whenever the transceiver is transmitting 11 Preset Frequency Display Displays the pre set inactive frequency and...

Page 297: ...and mode switch to SQ OFF and adjusting the volume level with background noise After a comfortable listening level has been established return the power and mode switch to the ON position All background noise should disappear unless a station or aircraft is transmitting on the active frequency 2 Frequency Selection Frequency selection is made using either the frequency select knobs or the XF MEM s...

Page 298: ... done within 5 seconds after selecting the channel number or the first actuation of the STO button If more than 5 seconds elapse the control will revert to the normal modes of operation and the second store command will be interpreted as the first store command After a frequency has been stored in memory it will remain there until changed by using the STO button Memory is retained even when the un...

Page 299: ...e microphone Power to the system is routed through a 25 ampere circuit breaker placarded HF PWR The receiving portion of the system is protected by a 5 ampere circuit breaker placarded HF RECVR Both circuit breakers are located on the overhead circuit breaker panel Figure 2 16 Sheet 3 The HF system has two methods of frequency selection The first method is called direct tuning frequency agile The ...

Page 300: ...not functional when the FREQ CHAN switch is in the CHAN position The inner knob will provide channel control from 1 through 99 displayed at the right end of the display window 9 STO Button Stores displayed data when programming preset channels 10 OFF VOLUME Switch Applies power to the unit and controls the audio output level 11 SQUELCH Provides variable squelch threshold control 12 CLARIFIER Provi...

Page 301: ...4 Set the desired frequency Refer to frequency tuning 5 Push and release STO button once NOTE T will flash in the display window however a receive only frequency is being set The flashing T should be ignored If another channel is to be set the cursor must be stowed before a new channel can be selected Use the smaller concentric knob to select the channel and repeat the steps for selecting a new fr...

Page 302: ...on III NAVIGATION 3B 11 DESCRIPTION The overall navigation equipment group provides the pilot and copilot with the instrumentation required to establish and maintain an accurate flight course and position and to make an approach on instruments under Instrument Meteorological Conditions IMC The navigation configuration includes equipment for determining attitude position destination range and beari...

Page 303: ...h Dial Displays gyro stabilized magnetic compass information on a dial that rotates with the aircraft throughout 360 The azimuth ring is graduated in 5 increments 3 Lubber Line Fixed heading marks located at the fore upper and aft lower position 4 Heading Bug The notched orange heading bug is positioned on the rotating heading dial by the heading knob to select and display a preselected compass he...

Page 304: ...e aircraft and lubber line markings The symbol shows aircraft position and heading with respect to a radial course and the rotating heading azimuth dial 14 Course Deviation Bar The course deviation bar represents the centerline of the selected VOR or localizer course The miniature aircraft symbol pictorially shows actual aircraft position in relation to this selected course 15 Glideslope Pointer S...

Page 305: ...OURSE Display Provides a digital readout of selected magnetic course 5 Azimuth Marks 6 Course Pointer The yellow course pointer is positioned on the heading dial by the course knob to select a magnetic bearing that coincides with the desired VOR radial or localizer course The course pointer rotates with the heading dial to provide a continuous readout of course error to the computer When either on...

Page 306: ... flag which indicates loss of heading information a VERT flag which covers the glideslope pointer when not receiving glideslope information and a NAV flag which indicates a loss of NAV 2 3B 15 PILOT S ATTITUDE DIRECTOR INDICATOR a Description The pilot s Attitude Director Indicator ADI combines the attitude sphere display with computed steering information to provide the commands required to inter...

Page 307: ...e vertical navigation mode VN illuminates when the aircraft arrives at the designated climb or descent point 14 DH Annunciator Illuminates when aircraft descends below selected decision height as set on the radio altimeter indicator 15 Eyelid Display Surrounds the attitude sphere and provides positive attitude identification by means of a blue eyelid which always shows the relative position of the...

Page 308: ...ctual altitude is displayed The DH display during the test displays all 8 s with the altitude display and then displays the current set altitude for the remainder of the test RA TEST is inhibited as a function of APR CAP 25 Decision Height Display The digital decision height DH display displays decision height range from 0 to 990 feet in 10 foot increments The decision height is set by the DH SET ...

Page 309: ...ng the bottom of the symbolic aircraft at touchdown 8 Expanded Localizer Raw localizer displacement data from the navigation receiver HSI display is amplified approximately 7 1 2 times to permit the expanded localizer pointer to be used as a sensitive reference indicator of the aircraft s position with respect to the center of the localizer It is normally used for assessment only since the pointer...

Page 310: ...tor will illuminate when the aircraft is at or below the selected decision height 2 Decision Height Bug The decision height bug is set to the desired decision height by the DH SET knob 3 Failure Warning Flag The OFF warning flag will be in view whenever the system information is unreliable 4 Altitude Pointer The altitude pointer will point to the existing altitude 5 DH SET Knob The DH SET knob is ...

Page 311: ...system and copilot s RMI 4 GYRO SLAVE FREE Switch Controls system mode of operation a SLAVE Places system in SLAVE mode b FREE Places system in FREE mode 5 INCREASE DECREASE Switch Provides manual fast synchronization for the system a INCREASE Causes gyro heading output to increase b DECREASE Causes gyro heading output to decrease 6 Compass Synchronization Annunciator Two compass slave annunciator...

Page 312: ...equency transfer mode of operation and directly tune the set pull out on the unit s small inner concentric tuning knob until the standby display shows dashes and select the desired frequency To re engage the frequency transfer mode push the small tuning knob back in 7 PUSH TST MODE Knob 1 NAV TAC Refer to Figure 3B 12 A self test is provided to verify range and bearing computation When the NAV TAC...

Page 313: ... and standby frequencies through a power off condition b Controls and Functions 1 Control Display Provides a display of selected frequencies and bearing validity The display contains two frequencies and an X character The upper frequency is the active frequency or the frequency to which the receiver is tuned The lower frequency is the standby frequency The standby frequency is changed by the frequ...

Page 314: ... distance is then indicated in nautical miles on the range groundspeed time to station indicator The distance is measured on a slant from the aircraft to the ground and is commonly referred to as slant range distance Slant range distance should not be confused with actual ground distance The difference between slant range distance and ground distance is smallest at a low altitude and long range Ho...

Page 315: ...own in the VOR ILS mode using the TACAN for DME only b DME Slave Indicator Allows display of nautical miles groundspeed and time to station Refer to Figure 3B 15 1 NM Nautical Miles 2 KT Knot 3 MIN Minutes 4 Photocell Figure 3B 15 DME Slave Indicator 1 NM Displays nautical miles to the station 2 KT Displays aircraft groundspeed 3 MIN Displays time to station 4 Photocell Allows for automatic bright...

Page 316: ...itch is used to select which autopilot flight director computer controls the aircraft flight servos If AP FD 2 is selected the annunciator placarded AP FLT DIR NO 2 located on the copilot s instrument panel directly below the glare shield will illuminate to alert the pilot that the No 2 autopilot flight director computer is controlling the aircraft NOTE The autopilot will disengage when transferri...

Page 317: ...tation sensor detects station passage removing the VOR deviation signal from the command until it is no longer erratic While over the station course changes may be made by selecting a new course on the HSI If the NAV receiver is not valid prior to the capture point the lateral beam sensor will not trip and the system will remain in the HDG mode After capture if the NAV receiver compass data or ver...

Page 318: ...DF 1 and located on the instrument panel both pilot and copilot side will illuminate TACAN navigation information will display on the pilot s HSI and on the DME slave indicator NOTE The NAV TAC receiver must be tuned to a valid TACAN frequency TACAN functions are identical to VOR using TACAN information rather than VOR signals The ARM CAP annunciation is the same as in VOR mode 4 Back Course Mode ...

Page 319: ... command cue will bias out of view if the VG is not valid NOTE If the baro setting on the altimeter is changed a command is generated to fly the aircraft back to the original altitude reference 10 Go Around Mode The go around mode is selected by pressing the remote go around switch When selected all other modes are reset and the remote Go Around GA and Yaw Damp YD ENG annunciators will be illumina...

Page 320: ...l Rate Limit 5 sec Capture Point Function of Beam Beam Rate and Course Error NAV ON COURSE Roll Angle Limit 17 Roll Crosswind 30 of course Correction Limit Error Gain Programming Function of Time and TAS starts at 1200 ft radio altitude GLIDESLOPE CAPTURE GS Receiver and Air Data Computer Beam Capture Function of beam and beam rate Pitch Command Limit 10 Glideslope Damping Vertical Velocity Pitch ...

Page 321: ...slope 2 BANK LIMIT Push Button Selection of the bank limit mode on the autopilot controller provides a lower maximum bank angle while in the Heading Select mode LOW will illuminate on the BANK LIMIT switch The lower bank limit is inhibited and LOW is extinguished during NAV mode captures If heading select is again engaged BANK LIMIT will again be illuminated Pressing BANK LIMIT when illuminated wi...

Page 322: ...n pilot and copilot flight directors 8 Actuation of either pilot s or copilot s electric elevator trim switches while pressing only one switch or pressing pairs of switch elements Any of the following malfunctions will cause the autopilot to automatically disengage 1 Vertical gyro failure 2 Directional gyro failure 3 Autopilot power or circuit failure 4 Torque limiter failure Disengaging under any...

Page 323: ...avigation sensors may be selected separately or blended within the computer It provides for manual operation to selected waypoints or automatic operation providing uninterrupted navigation throughout a complete flight plan The FMS consists of a cockpit mounted Control Display Unit CDU a remote mounted navigation computer and an H field antenna Refer to Figure 3B 18 for an illustration of the CDU T...

Page 324: ... GMT on the effective date the system automatically switches to the revised data If the FMS is in operation at 0000 GMT on the effective date the system automatically switches to the revised data the next time it is turned on If the FMS does not get updated with the latest revision data prior to the effective date the system will continue to function but will provide a message stating D BASE OUT D...

Page 325: ...ssed The message key is used to acknowledge a message annunciator The message annunciator will be extinguished only after the message has been satisfactorily acknowledged 2 Cursor Keys Two cursor keys are provided n and p to position the cursor a bright inverse video rectangle over information in a line or portion of a line on the control display unit in order to approve or change that information...

Page 326: ...osition 14 Data Key The data key placarded DAT is used for viewing the two data menu pages DATA 1 and DATA 2 It is also used for returning from lower level data pages to higher level data pages 15 Navigation Key Pressing the alternate action navigation key placarded NAV allows viewing of the two NAV pages NAV 1 and NAV 2 The NAV 1 page is displayed by pressing the NAV key once the NAV 2 page is di...

Page 327: ...aircraft s DME display should be indicating 34 3 NM SEL CRS 315 The course arrow on the HSI should be indicating 315 HORZ DEV RT 3 The deviation bar on the HSI 3 or CDI should be 3 dots to the right of center or an indication of 3 NM to the right of center VNAV DEV UP 3 The VNAV indicator should be displaying an up 3 dot deflection or an indication of 300 feet below the desired vertical flight pat...

Page 328: ...ght plans SEL FPL The desired flight plan number is entered into this field The flight plan number selected does not have to be displayed on this page 0 The 0 indicates the first flight plan number Flight plan 0 is the active flight plan and is displayed on each flight plan menu page The notes that another operation can be performed by pressing the CLR key while the cursor is over this field When ...

Page 329: ...cted 1 FIRST The first waypoint is displayed at the top of the list of waypoints regardless of the number of waypoints in FPL 0 This line can become a non enterable cursor field and will display WPT when used for manual scrolling of the waypoints 7 A single designates the direct to waypoint if it is part of FPL 0 A single also designates the active waypoint when in OBS method of operation 6 7 When...

Page 330: ...to select either frequencies or TACAN channels The system will remain in the FREQ or CHNL select mode until changed by the pilot RAD DIS Radial and distance from the reference facility to the waypoint LAT LON Position of the waypoint presented as latitude and longitude coordinates using degrees minutes and tenths of minutes RUNWAY OM This cursor field allows selection of runway thresholds and oute...

Page 331: ...e to the active waypoint in hours and minutes This value is based on the present calculated groundspeed assuming that the actual track is equal to the bearing to the waypoint GS Groundspeed in knots TAS The colon when displayed indicates this is an enterable data field only when there is no true airspeed source available A true airspeed may be manually entered so that the system can make a wind ca...

Page 332: ...d and the radial from it Another navaid identifier may be manually inputted and the present position will be referenced to that facility If the navaid is manually changed the system will resume automatic navaid selection for this field in approximately 1 minute 17 Nav 2 Page LEG Varies somewhat depending on whether the method of operation is OBS or AUTO LEG ACT This column header indicates that da...

Page 333: ...tion overflown DIF The difference in position between the systems calculated position and the FIX position in degrees minutes and tenths o minutes UPDATE A cursor field used to update the systems position when the ENTER key is pressed 19 Hold 2 Page The HOLD 2 page is used to update the system position It is also used to make manual altitude heading or groundspeed entries when required by the syst...

Page 334: ...ber of the desired kind of trip planning can be entered in this data field Each of the ADF control heads tied to the frequency management is listed along with its respective active frequency code The frequency code fields are manually enterable a WPT REL TO PRESENT POS Trip planning from the aircraft s present position to another waypoint When the number one VOR NAV receiver is being used as a sen...

Page 335: ...oundspeed and manually input fuel flow UPDATED INPUTS This flashing message appears only if data has not been updated for 15 minutes 5 Position Summary Page The position summary page displays the aircraft s position in latitude and longitude coordinates as determined by each of the sensors POS The aircraft s present position coordinates based on inputs from the pilot selected sensor When BLEND sen...

Page 336: ...data DME 2 REC When valid DME data is received from a second DME station this area displays REC the identifier and paired VHF frequency of the station utilized and the aircraft s distance from the station Under these conditions the system is providing rho rho navigation data When the system is providing rho rho navigation the TACAN bearing data is dashed out 8 GPS Status Page The GPS STATUS page i...

Page 337: ... here n Data 2 Menu Page The data 2 menu page lists the actual data pages that can be selected from its menu Specific data pages are selected by entering the corresponding menu number into the SEL MENU ITEM data field and pressing the ENTER key They may also be selected by placing the cursor over the menu item and pressing the ENTER key 1 Navaid Page This page is used to display the frequency type...

Page 338: ...umber associated with the desired menu item is entered in this field REVIEW D BASE This menu item is selected to display additional data base review pages that are used to review what is presently loaded in the data base The pages accessed via this menu item are the review data base page and the review elements page SELECT D BASE This menu item is selected to display additional data base modificat...

Page 339: ...fy Data Base Page This page is used to select regions of the world from which data will be loaded in the data base It is one of two pages used to configure the data base to the aircraft s specific requirements prior to using the data loader to actually load the data into the data base SEL MENU ITEM The number associated with the desired menu item can be entered in this field The regions of the wor...

Page 340: ...plemental data base memory that have been defined by the user The identifiers are listed in alphabetical order These pages are also used to delete user defined airports from the supplemental data base PREVIOUS PAGE A cursor field used to display the previous page of user defined airports when there is more than one page of these airports NEXT PAGE A cursor field used to display the next page of us...

Page 341: ... either the ADF or the NAV 1 receiver depending on whether ADF or NAV is selected on the RMI e VNAV deviation indicating 3 up 3 Remote annunciators Check ON 4 ENTER key Press to verify satisfactory completion of self test page items 3 Initialization Page CAUTION Position accuracy in initialization is very important since it is possible that the amount of initialization error will be carried by the...

Page 342: ...all of the data on the initialization page and enter the data into memory The first of the flight plan menu pages FPLS will now appear f REF NAME Input the identifier of a navaid or location contained in system memory from which the new waypoint can be referenced g ENTER key Press to enter the identifier b Procedure B 1 DATE Check If incorrect enter the correct Greenwich date in sequence day month...

Page 343: ... loaded into the data base The data base does not need to be reconfigured if there are no configuration changes from the previous loading NOTE The configuration of the main data base can be reviewed at any time after initialization Since so many of the system capabilities depend upon the data base it is important to review which geographic region and which navigational elements within these region...

Page 344: ... occur to data loader Also failing to keep the clear protective cover closed could allow a foreign substance to enter damaging the mechanism or electronics NOTE 6 Establishing Operational Status Refer to Table 3B 4 for Methods of Operation There are a total of 10 000 blocks of data base memory These blocks can be filled with any combinations of geographic regions and navigational elements within t...

Page 345: ...e 1 ON OFF rocker switch Press lower half r Emergency Procedures If the KNS 660 system information is intermittent or lost secure the system and utilize the remaining operational navigation equipment as required 1 FMS NAV CTL switch Press Verify NAV CTL illuminated 2 CDU ON OFF switch Off 3 FMS circuit breaker Pull Section IV RADAR AND TRANSPONDER 3B 27 PILOT S ALTIMETER a Description The altimete...

Page 346: ...re 3 Barometric Pressure and MILLIBARS Counter The barometric pressure and MILLIBARS counter set with the baro knob displays barometric pressure in inches of mercury and millibars 4 Baro Knob The baro knob is used to set the barometric pressure and MILLIBARS counter 5 Altitude Pointer The altitude pointer points to the altitude on the pointer display between 1000 foot levels in 20 foot increments ...

Page 347: ... displayed distance The off screen pointer is replaced by an RMI BUG placed on the outer ring in the direction of the active waypoint and color coded to each navigation system Position of the aircraft is indicated by the green airplane symbol in the center of the screen Indicator brightness is adjustable to accommodate varying ambient light conditions while automatically maintaining equal brightne...

Page 348: ...ever the gain is varied from the preset maximum level the screen will annunciate VAR to remind the pilot to reset the gain for standard intensity levels 5 STBY OFF ON Selector Switch The selector knob permits the pilot to select gyro stabilized control of the weather radar system In the ON position the radar s antenna scan is kept parallel to the horizon and at the same relative tilt angle previou...

Page 349: ...replacing the magnetic heading when track mode is in operation Power is provided for the unit through a 2 ampere circuit breaker placarded GRPH DSPL located on the overhead circuit breaker panel Figure 2 16 Sheet 3 b Controls and Functions Refer to Figure 3B 21 1 Mode Selector Knob Allows the operator to turn the unit on and select desired mode a OFF Power is removed from the unit when mode select...

Page 350: ...ner by pressing the CANCEL button THE NAVIGATION DATA PRESENTED ON THIS SCREEN IS NOT TO BE USED FOR PRIMARY NAVIGATION CONTENTS OF THE CHECKLISTS ARE THE RESPONSIBILITY OF THE USER INSTALLER 1 Mode selector switch As required 3B 30 POCKET TERMINAL a Description The KA 68 pocket terminal is used to program normal and emergency checklist information into the radar graphics control panel Refer to Fi...

Page 351: ...lected item shown in yellow c Special Functions Certain special functions can be obtained on the pocket terminal by pressing the CONTROL key prior to pressing X C or I CONTROL X erases everything all checklists stored in nonvolatile memory in the KGR 358 After pressing CONTROL X the message ERASE ENTIRE MEMORY YES NO appears on the radar screen If Y E S is entered the radar graphics unit will carr...

Page 352: ...ibility of activating more than one condition at a time a warning priority has been established The highest priority message will be announced first If a higher priority item is received after a message is started voice annunciation of the higher priority message shall be announced after a lower priority message in progress at the end of the message segment It will not stop in the middle of a word...

Page 353: ... followed by the illumination of the VA FAIL light 7 Radio altimeter TEST switch Release c GPAAS Modes of Operation The GPAAS operates in the following modes of operation 1 Aural Two Thousand Advisory Mode 1 The aural advisory Two Thousand indicates that the aircraft is at a radio altitude of 2000 feet AGL This advisory is cancelled when valid information from the radio altimeter is lost during cl...

Page 354: ...um indicates that the aircraft is at the radio altitude selected by the crew with the radio altimeter indicator s decision height knob This advisory is cancelled when valid information from the radio altimeter is lost during climb whenever the aircraft is above 1000 feet AGL or whenever the aircraft is out of the operating altitude range of the radio altimeter 7 Aural Altitude Altitude Advisory Mo...

Page 355: ...stem circuit breakers and the associated avionics buses are shown in Figure 2 28 A three position switch placarded AVIONICS MASTER POWER ON EXT PWR located on the overhead control panel controls a relay which applies power to two 35 ampere circuit breakers placarded AVIONICS MASTER PWR 1 2 located on the overhead circuit breaker panel Figure 2 16 When the AVIONICS MASTER POWER switch is set to the...

Page 356: ...udio g MKR BCN 1 Permits monitoring of 1 and 2 marker beacon audio h MKR BCN 2 Permits monitoring of 2 marker beacon audio i DME TACAN Permits monitoring of DME TACAN audio j ADF 1 Permits monitoring of 1 ADF audio k ADF 2 Permits monitoring of 2 ADF audio 2 Copilot s Transmitter Selector Switch Controls operation of selected system a VHF 1 Routes key and microphone signals to the 1 VHF transceive...

Page 357: ...h Controls both voice and range tone a VOICE Kills range allows voice ADF and VOR b BOTH Allows both voice and range ADF and VOR c RANGE Kills voice allows 1020 Hz range tone ADF and VOR 8 AUDIO EMER NORM Switch Controls routing of received audio signals Located on pilot s audio panel only a EMER Audio signal bypasses amplifier Applies audio signal to headphone only b NORM Routes audio signal thro...

Page 358: ... means of selecting desired reception and transmission sources and also a means of controlling the volume of audio signals received from interphone communication and navigation systems Refer to Figure 3C 2 The user selects between the VHF V UHF or HF transceivers The audio control panel is fed through two 2 ampere circuit breakers placarded AUDIO PILOT and COPILOT located on the overhead circuit b...

Page 359: ...ransmitter selector switch is also set to the INTPH position or the INTPH OFF switch is in the interphone position and the audio speaker switch is in the OFF position b PA Setting the transmitter selector switch to the PA public address position allows the pilot at that station to speak through the four cabin speakers when his microphone is keyed Talking through the PA speakers will override cabin...

Page 360: ...he cabin speakers When set to the OFF position ADF audio is removed from the cabin speakers 8 Pilot and Copilot Public Address Volume Control This knob placarded PA adjusts audio volume to the four cabin speakers 9 Pilot and Copilot Headphone Volume Control This knob placarded PH adjusts audio volume to headphones 10 Pilot and Copilot Cockpit Speaker Volume Control This knob placarded SPKR adjusts...

Page 361: ... UHF COMMUNICATIONS TRANSCEIVER AN ARC 210 V a Description The AN ARC 210 V Communication System provides multimode voice and data communications in either normal or jam resistant modes via Line Of Sight LOS It operates in the 30 400 MHz frequency range VHF UHF and on AM and FM single channel operation b Table 3C 1 lists the frequency coverage and modulation available with the AN ARC 210 V Radio T...

Page 362: ...a second time to commit the preset frequency to memory in the selected location After approximately 5 seconds the control will return to normal operation 4 Frequency Select Knobs Two concentric tuning knobs control the preset or active frequency displays The larger knob changes the three digits to the left of the decimal point in 1 MHz steps The smaller knob changes the three digits to the right o...

Page 363: ...he CTL is in the frequency range of 137 000 to 151 975 MHz the unit behaves the same as a 25 kHz only unit NOTE It is possible that erroneous operation could occur without a fault indication It is the responsibility of the pilot to detect such an occurrence by continually assessing the reasonableness of operation as displayed on the associated transceiver control unit and by the quality of receive...

Page 364: ...F MEM switch to the MEM position The storage location CHAN 1 through CHAN 6 for the recalled frequency is displayed in the active frequency display while the XF MEM switch is held in the MEM position All six stored frequencies can be displayed one at a time in the preset display by repeatedly positioning the XF MEM switch to the MEM position After the desired stored frequency has been recalled to ...

Page 365: ...he transceiver control unit to observe the fault code As long as the temperature remains above the limit the micro processor will not respond to a normal push of the microphone switch If you must transmit however you can override the protection by rapidly keying the microphone switch twice holding it on the second push The shutdown temperature is 160 C 320 F 7 Self test An extensive self test diag...

Page 366: ... LSB to Amplitude Modulation AM modes Mode selection is indicated on the display by the illumination of the respective USB LSB or AM annunciators 4 Frequency Channel Switch A two position push button switch placarded FREQ CHAN located on the upper right portion of the HF control unit controls the method of frequency selection When the switch is in the out position the system is in the direct frequ...

Page 367: ...place the unit into the channel mode press the FREQ CHAN switch This allows access to existing programmed channels Frequencies in the channel mode are stored with channel number emission mode USB LSB or AM and transmit and receive frequency 3 Program Mode When the HF control unit is in the program mode channel numbers emission mode USB LSB or AM and transmit and receive frequency are set up and st...

Page 368: ...lector Switch Set emission mode USB LSB or AM 4 PGM Switch Press check that PGM annunciator in the display is illuminated 5 Tuning Knobs Select channel to be preset operating mode USB LSB or AM and desired receive frequency 6 STO Switch Press and release once 7 Transmit Frequency Set 8 STO Switch Press again If another channel is to be preset use the smaller concentric knob to select the channel a...

Page 369: ...ass rose 360q or HSI ARC which includes course needles a bearing needle heading bug etc 2 MAP A centered 360q MAP or an expanded compass rose segment 80q Both of these modes include the current set of waypoints and course legs from the FMS selected as the Nav Source 3 ADI Provides aircraft attitude pitch and roll lateral deviation and vertical deviation 4 Primary Flight Display PFD ADI and HSI com...

Page 370: ...lay Control Panel Controls and Functions Listed below are the controls found on the Control Panel and their corresponding functions 1 EHSI Brightness Control The brightness control consists of two concentric knobs The inner knob controls the brightness of the EHSI bottom MFD Full counterclockwise rotation of the brightness knob provides the minimum brightness level and full clockwise rotation is i...

Page 371: ...ht center portion of the ADI or PFD display and a Minimum aural annunciation is sounded Once the DH annunciation appears it is removed from the display when the radio altitude climbs at least 25 feet above the decision height If the radio altimeter system fails the decision height annunciator is removed and the radio altitude flag appears 6 Radio Altitude Test The center push button on the DH SET ...

Page 372: ... heading changes If the knob is rotated quickly the heading setting changes numerous degrees per click 17 HDG SYNC Button The center push button on the data selector is a HDG SYNC selection Pressing the PUSH SYNC button will automatically slew the selected heading bug to the lubber line When FMS 1 is the selected navigation source and the PUSH button is pressed the FMS heading bug is displayed on ...

Page 373: ...ion 6 Aircraft Symbol 7 Flight Director Command Bars VBARS 8 GS Pointer 9 Vertical Deviation Scale 10 NAV Source 11 Radio Altitude Readout 12 DH Setting 13 Rising Runway 14 Rate of Turn Scale 15 Rate of Turn Pointer 16 Lateral Deviation Approach Pointer 17 Lateral Deviation Scale 18 Ground 19 FMS Speed Label 20 Speed Deviation Scale 21 Speed Deviation Pointer 22 Marker Beacon Annunciation 23 Pitch...

Page 374: ...ht director annunciations and command bars from the display 2 The pitch scale Figure 3C 7 consists of 2 5q increments between 30q to 40q of pitch Approximately 40q of the pitch scale is visible at any given time 3 The roll scale displays the current roll attitude of the aircraft It rotates about the aircraft symbol such that the aircraft roll is graphically indicated on the roll scale The roll sca...

Page 375: ... standby mode commanded out of view or FD validity flagged d Vertical Guidance The FDS 255 supports glideslope and VNAV Guidance The glideslope scale and pointer are displayed when the navigation source is LOC the localizer is valid and the glideslope is valid The VNAV scale and pointer will be displayed when the navigation course source is FMS the FMS is valid the VNAV is valid and the VNAV is av...

Page 376: ...TM 1 1510 218 10 Figure 3C 7 ADI Pitch Scale 3C 22 ...

Page 377: ...IELD FD ANNUNCIATOR INPUT MFD ANNUNCIATION Lateral Arm NAV Arm while LOC is NOT the NAV source NAV Upper Left White NAV Arm while LOC is the NAV source APR Lateral Arm BC Arm APR Upper Left White VOR APR Arm Lateral Capture BC Capture APR Upper Left Green VOR APR Capture NAV Capture while LOC is NOT the NAV source NAV 3C 23 ...

Page 378: ...ourse or FMS approach mode During localizer or FMS approach deviation the pointer is a trapezoidal runway symbol When the radio altitude reaches 200 feet while in LOC BC or FMS approach mode the runway symbol starts to rise The symbol achieves maximum height when the radio altitude is at a value of zero feet The rising runway correlates to approximately the bottom of the aircraft symbol If the loc...

Page 379: ...s tube to provide assistance in making coordinated maneuvers Aircraft slip skid movement is shown by the movement of the ball l Marker Beacons The inner middle or outer marker beacon annunciation is displayed on the center left of the display when set by the marker beacon receiver The marker beacon annunciator will be removed from the display when the marker beacon signal is no longer available fr...

Page 380: ... EADI except it is configured as an EHSI Flight data information is electronically displayed on both EHSI s Refer to Figure 3C 10 b Power Twenty eight Vdc power is provided to each EHSI through separate 7 ampere circuit breakers placarded EADI 1 2 and EHSI 1 2 located on the overhead circuit breaker panel Figure 2 16 c EHSI Modes The EHSI allows for multiple display formats See Table 3C 6 for the ...

Page 381: ...urse Source Distance Readout 19 Free Format Line ARC 210 Freq 20 Digital HDG Bug Readout 21 Heading Bug 22 Track Indicator 23 Digital Heading Readout 24 DR or RAIM Alert 25 FMS OFST 26 Wind Pointer 27 TO FROM Indicator 28 Miniature Aircraft Figure 3C 10 Electronic Horizontal Situation Indicator Table 3C 6 EHSI Display Modes MODE FORMAT HSI HSI 360 compass HSI ARC Partial 80 compass MAP Map ARC Par...

Page 382: ...ected heading bug is displayed in amber when a cross side source is selected 4 Course Deviation Scale Four white lateral deviation scale dots indicate deviation from course The course deviation scale rotates about the aircraft symbol such that the scale is always perpendicular to the selected primary course The maximum deviation is r 2 5 dots When the selected course or source is invalid the cours...

Page 383: ...gital course readout and course needle change by 1q increments and rotate such that the needle head points to the selected primary course on the compass 12 Wind Direction The MFD displays wind velocity knots and direction degrees on the bottom of the MFD in green below the label WIND If no wind data is available the data will be blank If the wind data is invalid the data will be dashed red 13 Comp...

Page 384: ...he course source distance When the selected heading changes the selected heading readout is displayed If the selected heading does not change for 10 seconds the selected heading readout is removed from the display If the heading bug is off the screen the readout will be constantly displayed 21 Heading Bug The heading bug is magenta and travels around the aircraft symbol on the outside edge of the ...

Page 385: ...icated The indicator is OFF when the angle is between 89q and 91q When FMS is the primary source then the FMS determines the TO FROM indication If the TO FROM indication is invalid or unavailable an active navaid has not been selected or the indicator is OFF the TO FROM flag will be removed from the display 28 Miniature Aircraft The white aircraft symbol is located in the center of the compass ros...

Page 386: ...ations are the same as the HSI ARC mode with the following exceptions 1 Range Arc The range knob concentric with the mode switch selects range on the map format The static dashed range ring and label consist of one cyan arc and cyan text representing half the value of the range setting The arc is half way between the aircraft symbol position and the point of the lubber line Available full scale ra...

Page 387: ...TM 1 1510 218 10 Figure 3C 12 Map ARC Format Figure 3C 13 Map Symbols 3C 33 ...

Page 388: ...INT FMS To To Yes Previous and Active waypoint are connected The FMS flies a DTK FMS Direct To No Desired Track line is drawn to the active waypoint from the computer Direct To position FMS To From Yes Manually entered course line is drawn to the Active waypoint Manual Sequencing Yes A dashed line extends from the active waypoint If the accuracy of the FMS navigation falls below the 95 threshold a...

Page 389: ...er line symbol The point of the lubber line is located directly above the aircraft symbol along the outside of the selected range ring Next to the heading readout is the heading reference indicator T True reference Blanked reference Magnetic reference When the heading is invalid the heading readout is replaced with the heading annunciator The heading annunciator displays HDG in black on a solid re...

Page 390: ...ature aircraft 6 Pitch Scale Measures pitch displacement of miniature aircraft 7 Symbolic Miniature Aircraft Represents aircraft nose and wings Indicates pitch and roll attitude relative to the horizon Adjustable through pitch knob for varying pitch attitudes 3C 17 TURN AND SLIP INDICATORS a Description One turn and slip indicator is installed on the pilot s side of the instrument panel This indic...

Page 391: ...esired altitude reference for the altitude alerting and altitude pre select system The altitude alerter pre selector is powered through a 1 ampere circuit breaker placarded ALT ALERT located on the overhead circuit breaker panel Figure 2 16 b Altitude Alerter Pre Selector Control Indicator and Functions Refer to Figure 3C 16 1 Altitude Display The altitude display indicates the selected altitude 2...

Page 392: ...em receive heading information from compass system number 1 When the switch is set to the NORM position the flight director computer number 1 EHSI number 1 and flight management system receive heading information from compass system number 1 while the flight director computer number 2 and EHSI number 2 receive heading information from compass system number 2 When the switch is set to the ALL SYSTE...

Page 393: ...s and Functions Refer to Figure 3C 17 1 Frequency Display Liquid crystal digital readouts provide a continuous display of both the active frequency or TACAN channel and standby frequency or TACAN channel bottom line placarded SBY when the system is in the frequency mode Display brightness is controlled by a switch placarded VHF NAV ADF located right of the altitude alert on the instrument panel 2 ...

Page 394: ... the knob is turned further to the right Pressing PUSH TST overrides the automatic squelch circuitry Turning the knob clockwise past the automatic squelch threshold while the automatic squelch circuitry is overridden will allow background audio to be heard through the headphones or speaker and demonstrate whether the receiver is working or not and allow setting of audio volume To return the unit t...

Page 395: ...e Pressing the frequency transfer switch with the unit in the standby entry mode causes the frequency displayed in the active digital display to interchange with the frequency shown in the standby digital display b Active Entry Mode While the unit is in the standby entry mode or the channel mode holding the transfer switch pressed for longer than 2 seconds will cause the unit to enter the active e...

Page 396: ...e or program mode 1 Frequency Modes The NAV receiver control unit may be operated in standby entry and active entry a Standby Entry When the unit is operated in the standby entry frequency mode a new frequency is set on the standby digital display using the tuning knobs When the operator is ready the frequency is then transferred to the active display by pressing the frequency transfer switch b Ac...

Page 397: ...de for both bearing and distance functions The NAV TAC control unit Figure 3C 17 tunes the KTU 709 to all 252 TACAN channels and all DME channels TACAN course deviation information may be displayed on the pilot s or copilot s EHSI s When NAV Source Selector is set to radio position the TACAN radio is tuned to a TACAN station and the radio is supplying valid navigational data TACAN or DME distance ...

Page 398: ...entry mode causes the frequency displayed in the active digital display to interchange with the frequency shown in the standby digital display b Active Entry Mode While the unit is in the standby entry mode or the channel mode holding the transfer switch pressed for longer than 2 seconds will cause the unit to enter the active entry mode While in the active entry mode momentarily pressing the tran...

Page 399: ...press the PUSH control knob again c Frequency Channel Selection Modes The ADF receiver control unit may be operated in the frequency mode either standby entry or active entry channel mode or program mode 1 Frequency Modes The ADF receiver control unit may be operated in standby entry or active entry a Standby Entry When the unit is operated in the standby entry frequency mode a new frequency is se...

Page 400: ... overhead control panel Figure 2 15 ON 2 OFF VOL PUSH Knob Turn clockwise out of detent then press to turn off automatic squelch circuit Continue turning knob clockwise until background noise is heard in headphones or speaker ensuring that the receiver is operating then set audio volume to desired level Press knob again to return unit to automatic squelch control 2 ADF Operating Procedure 1 Number...

Page 401: ...lect signal is gain programmed as a function of airspeed When HDG is selected it overrides the NAV BC APR and VOR APR modes In the event of a loss of valid signal from the vertical gyro or compass the command bar on the EADI is biased out of view 2 Navigation Mode NAV The navigation mode represents a family of modes for various navigation systems including VOR localizer TACAN and FMS 1 or FMS 2 a ...

Page 402: ...PR The approach mode is used to make an ILS approach only Pressing the APR button with an ILS frequency tuned arms both the NAV and APR modes to capture the localizer and glideslope respectively No alternate NAV source can be selected Operating LOC mode is the same as described above except if the radio altimeter is invalid in APR mode gain programming is a function of glideslope capture time and ...

Page 403: ...or IAS may be selected as a mode to fly to the selected altitude When outside the altitude bracket trip point the ALTSEL ARM annunciator along with the selected pitch mode is illuminated on the mode selector When reaching the bracket altitude the system automatically switches to the ALTSEL CAP mode and the previously selected pitch mode is cancelled When the altitude is reached the ALTSEL CAP mode...

Page 404: ...pproach mode except that it uses a TACAN in place of a VOR station g Autopilot Controller The autopilot controller provides the means of engaging the autopilot and yaw damper as well as manually controlling the autopilot through the turn knob and pitch wheel Refer to Figure 3C 21 The autopilot system limits are listed in Table 3C 12 1 Pitch Thumbwheel 2 Bank Limit Switch 3 Soft Ride Switch 4 Turn ...

Page 405: ...e Up to 90 Roll Angle Limit 17 LOC CAPTURE LOC or APR or BC Course Knob and NAV Receiver Beam Intercept Up to 90 Roll Angle Limit 25 Roll Rate Limit 5 sec Capture Point Function of Beam Beam Rate and Course Error NAV ON COURSE Roll Angle Limit 17 Roll Crosswind 30 of course Correction Limit error Gain Programming Function of Time and TAS starts at 1200 ft radio altitude GLIDESLOPE CAPTURE LOC or A...

Page 406: ...l any other previously selected vertical mode However for safety movement of the pitch thumbwheel has no effect with the autopilot coupled to a glideslope signal 2 BANK LIMIT Switch Selection of the bank limit mode on the autopilot controller provides a lower maximum bank angle while in the heading select mode LOW will illuminate on the BANK LIMIT switch The lower bank limit is inhibited and LOW i...

Page 407: ... on the control wheel allows the pilot to manually change aircraft attitude altitude vertical speed and or airspeed without disengaging the autopilot After completing the manual maneuver the TCS push button is released and the autopilot will automatically resynchronize to the vertical mode For example with IAS mode selected the pilot may press the TCS push button and manually change airspeed Once ...

Page 408: ...n The CDU operates on the MIL STD 1553B data bus as a Bus Controller BC The CDU that is functioning as bus controller performs all navigation and guidance computations builds all page displays communicates with all external equipment and performs all other computations required to support FMS 800 operation b CDU Operations 1 General Operation Concepts CDU data entry operations are performed with a...

Page 409: ...age FPLN Accesses Flight Plan pages PSN Accesses Pilot Position present position and track pages IDX Accesses index of additional functions not available on top level keys STAT Accesses avionics LRU status pages IFF Function not used STR Accesses Pilot Steering pages INAV Accesses comprehensive data pages for GPS navigation solutions APPLICATION KEYS Deletes data from entry fields or causes data t...

Page 410: ...l either select enable or disable the indicated function or item For single step functions an asterisk to identify the function as enabled will replace the arrow When multiple selections are needed prior to activation of the function a fat arrow to highlight the selection will replace the arrow When all selections are made an asterisk will replace the fat arrow when the function is enabled Symboli...

Page 411: ...ht Plan Edit Pages Table 3C 14 Index and Flight Plan Edit Page Procedures NO DESCRIPTION FUNCTION 1 Press IDX function key to access Index Page 2 Press EDIT function key to access Edit Page 3 Scroll to access Edit 2 Page 4 Scroll to access Index 2 Page ...

Page 412: ...field with no decimal point will accept entries from 0 to 9999 Some entered data is limited by operational considerations e g VNAV angle of 6 0 or 3500 fpm maximum For values which cannot be computed due to insufficient data the CDU will display dashes e g if gross weight cannot be computed by the FMS because total fuel has not been specified Asterisks are displayed if the value is too large for i...

Page 413: ...ypoint is an ICAO identifier and the distance is 999 nm or less the waypoint will be displayed as identifier bearing distance e g EDW 350 45 2 If the waypoint is not a waypoint identifier or the distance is greater than 999 nm the waypoint will be displayed as latitude longitude f Use of Magnetic Variation and Declination Magnetic variation is used in converting most azimuth angles from true to ma...

Page 414: ... ALTN FPLN FULL Attempt to insert more than 60 legs into the alternate flight plan Clear key SP A ANTI JAM MISMATCH Attempt to tune to an anti jam preset that contains a Have Quick net when the V UHF s preset contains a SINCGARS net and vice versa Clear key SP A APPROACH Given for the following conditions 1 For a GPS approach mode 10 seconds after flashing APPROACH annunciation is activated and th...

Page 415: ...mode A B X APPROACH DEFINED Attempt to 1 Enter a VNAV parameter at the MAP or visual runway extension waypoint 2 Delete the V attribute at the MAP of an approach or the RWXND waypoint of a visual approach 3 Attach a Hold to an Initial Approach Fix IAF with a data base holding pattern MAP or Missed Approach Holding Point MAHP with a data base holding pattern 4 Attach a pattern to an IAF with a data...

Page 416: ...point when the MAP is the active waypoint Clear key SP A ATTACH CIR AT A circle pattern without a defined fix has been selected for insertion into the FPLN or alternate flight plan Clear key or valid insert SP N ATTACH CRP AT A closed random pattern without a defined fix has been selected for insertion into the FPLN or alternate flight plan Clear key or valid insert SP N ATTACH FG8 AT A figure 8 p...

Page 417: ... or entering a BARO set on the pilot or copilot vertical steer page A B gps Loss of GPS use as an INAV source five second filter while in approach sealing mode 25 second filter while in oceanic enroute or terminal scaling modes Clear key or re obtaining GPS or selecting an INU only INAV solution A B IFF2 Attempt to set IFF 1 to normal power mode when IFF 2 is active Clear key SP A nav error Downgr...

Page 418: ...n canceled A N X CIR IS ACTIVE Attempt to delete or modify the circle fix delete Mission Flight Patterns MFP attribute or modify the flight plan course or attempt to insert a PPOS hold or insert a waypoint at the active waypoint during pattern execution Clear key SP A CONF LOADXXXXXXX X Request to load the alternate flight plan XXXXXXXX into the CDU from the data cartridge Clear key reselect enter...

Page 419: ...elect ERASE ALTN SP N CONFIRM ERASE FPLN Request to erase flight plan Start 3 page Clear key or reselect ERASE FPLN SP N CONFIRM FPLN RMV Request to remove a Hold FMS approach SID STAR Pattern or Intercept from the flight plan Clear key or reselect FPLN RMV SP N CONFIRM HOLD PPSN Request to hold at present position Clear key reselect HOLD PPSN SP N CONFIRM LOAD ALMNAC Request to load the GPS alman...

Page 420: ...anac data Clear key or reselect SAVE ALMANAC SP N CONFIRM SAVE ALTN Request to save the alternate flight plan to the data cartridge Clear key or reselect SAVE SP N CONFIRM SAVE COMM Request to save COMM data into the data cartridge from the CDU Clear key or reselect SAVE COMM SP N CONFIRM SAVE PTS Request to save markpoint and waypoint lists to the data cartridge Clear key or reselect SAVE MKPT WP...

Page 421: ... execution Clear key SP A CRS CHANGE 90 Attempt to apply course edit greater than 90 degrees from the current inbound course while in automatic or flyover leg sequence mode Clear key SP A crs reversal Generated at 3 nm from a course reversal procedure execution Enabling the holding pattern at the TO or switched to capturing inbound leg of course reversal or sequencing by the FAF or IAF A N X CRS R...

Page 422: ...rt a waypoint between the discontinuity and the associated waypoint or direct to any waypoint AL N DUPLICATE USER WPT Attempt to assign a user waypoint identifier with the function when the same identifier already exists in the User Waypoint List Clear key SP A ELEMENT OMITTED Attempt to initiate Multiple Words of the Dat MWOD LOAD or Frequency Management Training FMT LOAD when the entered list is...

Page 423: ... key or entry of time or return of valid time A N ENTER UTC DATE Attempt to start one of the times without a valid UTC and Date available in system Clear key SP A ENTER WAYPOINT Attempt to enter an alternate flight plan parameter prior to entering the waypoint or attempt to enter a flight plan course when no TO exists Clear key SP A ERF IN PROCESS Attempt to initiate another action on the V UHF wh...

Page 424: ...n a waypoint with a Hold attached or an attempt to insert an offset when a holding fix is the TO waypoint Clear key SP A HOLD IS ACTIVE Attempt to delete the holding fix or modify the flight plan course or insert a PPOS hold or insert a waypoint at the active waypoint during hold execution Clear key SP A INSERT CIR BEFORE A circle pattern with a defined fix has been selected for insertion into the...

Page 425: ...lan Clear key or valid insert SP N INSERT G APR BEFORE A GPS data base approach has been selected for insertion into the flight plan Clear key or valid insert SP N INSRT T APR BEFORE A Tactical approach has been selected for insertion into the flight plan Clear key or valid insert SP N INSRT V APR BEFORE A Visual approach has been selected for insertion into the flight plan Clear key or valid inse...

Page 426: ...ne key for which the entry is allowed SP A INVALID SINCGARS Attempting to perform a SINCGARS time operations when a SINCGARS error condition is present Clear key SP A key alert GPS SA AS keys will expire in 2 hours in the GPS receiver Clear key or entry of new keys passing time test A B load fail Failure passing data to from the data cartridge Clear key or selecting another data loader load reques...

Page 427: ...ration to fit keys available A B NET NOT FOUND Attempt to tune to have a SINCGARS or Have Quick net that is not stored in the CNMS preset list Clear key SP A no appr RAIM Active when the following conditions are true 1 When a transition to GPS approach mode occurs 2 nm from FAF and the approach Predicative RAIM Availability is not available or unable to be computed 2 AIM Available indicates unavai...

Page 428: ...Fix FAF in history or deleted A N X no keys zero Failure to zeroize GPS SA AS keys in all GPS receivers Clear key or subsequent successful clearing of keys A B NO MAG VAR Attempt to enter Magnetic referenced input course bearing or track without Magnetic Variation tables Clear key SP A no raim RAIM is lost in selected GPS receiver and the NO APPR RAIM annunciation is not active or has been removed...

Page 429: ...ntercept The intercept solution for the active waypoint is to the Point of Closest Approach Clear key or non PCA intercept solution becomes available A N RAIM CHECK ACTIVE Attempt to enter RAIM prediction data when automatic approach RAIM point check is in progress Clear key or completion of point check SP A RENUMBER FPLN Attempt to insert a waypoint between non inserted waypoint in the flight pla...

Page 430: ...2 Select a STAR or associated runway and no STAR is currently in the working copy 3 Select a data base GPS approach from the FMS Approach page and no data base GPS approach is currently in the working copy 4 Select a visual approach from the FMS Approach page and no data base GPS approach is currently in the working copy 5 Select an IAF or insert a GPS approach and no data base GPS approach is cur...

Page 431: ... selected Clear key or selecting a SID or RWY SP N SELECT STAR RWY Attempt to access STAR Transitions page without both STAR and RWY selected Clear key or selecting a STAR or RWY SP N SET MASTER OFF Attempt to set late net entry to ON when the ARC 210 has been designated net master Clear key SP A sincgars cue V UHF R T indicates to the FMS that another user is on the cue frequency Clear key A B SI...

Page 432: ...y waypoint or the discontinuity becomes the active waypoint A N X VNAV IS ACTIVE Attempt to toggle between CLIMB and DESCNT when a VNAV is active Clear key SP A V UHF BUSY Attempt to request a V UHF sequence while another sequence is in progress for the same radio Clear key SP A WPT MAX EXCEEDED Attempt to enter a SID or STAR with more than 30 waypoints Clear key SP N wpt passed Active waypoint pa...

Page 433: ...lays only a single annunciation at a time however a marker will appear to indicate when multiple annunciations are present The priority of annunciations is shown in Table 3C 15 The flashes whenever an unacknowledged and lower priority annunciation is generated Annunciations are acknowledged by pressing the CLR key and cycling through the currently active annunciations Additionally the chart indica...

Page 434: ... modes Terminal FMS in Terminal Mode Approach FMS in Transition or Approach Mode RAIM Alert GPS RAIM function detects error RAIM Warn Parallel Track Parallel offset has been applied to the active flight plan CDU MSG Alert Light The MSG Alert column in this table lists which annunciations are accompanied by a message alert No INPUT with a blank screen A bus terminal has taken control of the MIL STD...

Page 435: ...es a RADIO MASTER selection which turns the controlled radio on or off d System Initialization Figure 3C 26 Master Power Page 1 Initialization Overview The FMS 800 system preflight initialization includes confirming or entering the current position time and date for GPS initial acquisition It also verifies the cartridge effectivity date of the data loader cartridge and the erasing or loading of fl...

Page 436: ... and mission data are to be entered manually select ERASE FPLN If a new plan is to be loaded from the cartridge first enter the desired flight plan number or access the Alternate Flight Plan Catalog and select the desired flight plan requires confirmation select twice After loading is complete select FPLN REPLACE This transfers the alternate flight plan data into the active flight plan so that bot...

Page 437: ... page will continuously change as the GPS solution updates even when stationary on the ground When frozen the position can be copied to other pages as desired or used to begin initialization of the GPS receiver 1 When a position is entered manually at line 1 left or right the position is automatically frozen for use To unfreeze select the freeze line and select again 2 The position frozen on the f...

Page 438: ...tion alert threshold nautical miles e External Alert Configuration On the Navigation Configuration 2 page alert thresholds can be entered to configure the FMS alerts to desired limits that the pilot wishes to maintain When the FMS reaches the alert threshold an appropriate annunciation or external alert is provided to advise the pilot When crosstrack deviation is exceeded an XTK ALERT annunciation...

Page 439: ...ollowing the waypoint number and may be viewed by scrolling the Flight Plan page using the n key The crew may delete history waypoints using a entry but may not enter waypoints into history 2 Flight Plan Active Waypoint The waypoint that all flight instruments and CDU guidance display is referred to as the active waypoint Pressing the FPLN key on the CDU accesses the Flight Plan page with the acti...

Page 440: ...light Plan page automatically scrolls as necessary to keep the END indicator in view on the bottom line This permits the pilot to enter a long sequence of points without having to manually scroll the page The FPLN FULL message will appear in the scratchpad if there is an attempt to load a 61st waypoint Figure 3C 32 Flight Plan Active Waypoint c Inserting and Deleting Intermediate Waypoints In most...

Page 441: ...are automatically assigned 6 Scroll to insert additional waypoints if more than three 7 Indicates end of flight plan marker Table 3C 25 Inserting and Deleting Intermediate Flight Plan Waypoint Procedure NO DESCRIPTION FUNCTION 1 Enter next desired waypoint into the scratchpad 2 Insert waypoint moving BRL down in the flight 3 Enter a in scratchpad to delete waypoint 4 Delete waypoint closing up the...

Page 442: ...nd the history waypoints are not renumbered e Modifying Waypoint Locations If a bearing distance e g 050 23 is inserted at a waypoint identifier that waypoint is offset by the bearing and distance and displayed in the scratchpad with the bearing and distance offset applied Refer to Figure 3C 35 and Table 3C 26 If the bearing and distance is applied at any other type of waypoint e g latitude longit...

Page 443: ... The title line displays the number range of the displayed duplicate identifiers i e 1 2 3 4 5 6 etc and the total number of duplicate identifiers for the entered waypoint The scratchpad retains the original waypoint identifier entry until a duplicate waypoint identifier has been selected The information line will display SEARCH IN PROGRESS when a search for duplicates is being conducted If a sear...

Page 444: ...FV ZIMBABWE FW MALAWI FX LESOTHO FY NAMIBIA FZ ZAIRE GA MALI GB FAMBIA GC CANARY ISLANDS GE MELIA GF SIERRA LEONE GG GUINEA BISSAU GL LIBERIA GM MOROCCO GO SENEGAL GQ MAURITANIA GS SAHARA OCCIDENTAL GU REP De GUINEE GV CAPE VERDE HA ETHIOPIA HB BURUNDI HC SOMALIA HE EGYPT HF DJIBOUTI HH ERITREA HK KENYA HL LIBYA HR RWANDA HS SUDAN HT TANZANIA HU UGANDA K USA LA ALBANIA LB BULGARIA LC CYPRUS LD CRO...

Page 445: ...LLES TG GRENADA TI VIRGIN IS U S TJ PUERTO RICO TK ST KITTS NEVIS TL ST LUCIA TN NETHERLANDS ANTILLES ARUBA TQ ANGUILLA ISLAND TR MONTSERRAT IS TT TRINIDAD AND TOBAGO TU VIRGIN IS U K TV ST VINCENT GRENADINES TX BERMUDA U RUSSIA UA KAZAKHSTAN KYRGYZSTAN UB AZERBAIJAN UE RUSSIA UG GEORGIA UH RUSSIA UI RUSSIA UK MOLDOVA UKRAINE UL RUSSIA UM RUSSIA BELARUS UN RUSSIA UO RUSSIA UR RUSSIA KAZAKHSTAN US ...

Page 446: ...th other listed attributes 4 Automatic Leg Advance When waypoints beyond the active waypoint are in the flight plan and the flight plan advance mode is automatic AUTO or FLYOVER mode the FMS 800 computes great circle tracks between those waypoints It also automatically transitions smoothly from one waypoint to the next To sequence past a waypoint the aircraft track angle must be within 90 of the a...

Page 447: ...S will continue to provide guidance to the outbound FROM course from the active waypoint To fly on a desired outbound course perform the following steps 1 Select MAN sequence mode on the Flight Plan page 2 Select via a Direct To or enter the desired active waypoint data 3 Enter the desired course By selecting MAN the new active waypoint is prevented from sequencing when it is inserted into the fli...

Page 448: ...TM 1 1510 218 10 Figure 3C 38 Lateral To To Course Transitions with Automatic Sequencing 3C 94 ...

Page 449: ...TM 1 1510 218 10 3C 95 Figure 3C 39 Lateral Course Edit ...

Page 450: ...ly preceding the active waypoint is the current FROM waypoint The FMS normally provides steering to intercept the course between the FROM and TO waypoints By entering a new FROM waypoint the FMS steers to intercept a new course between the newly entered FROM and original TO waypoints Figure 3C 41 is an example of the effect of modifying the FROM waypoint on guidance to the active waypoint 6 Waypoi...

Page 451: ...etween commanded groundspeed CMD GS groundspeed error 3 Estimated time of arrival and time to go to the active waypoint 4 Toggle between Drift Angle DA and Track Angle Error TKE display 5 Crosstrack deviation 6 Current aircraft track and bearing distance to go to the action deviation 7 Desired track at present position to steer to active waypoint 8 Active waypoint 9 Source for pilot s steering sol...

Page 452: ...ieve the RTA select the Pilot Lateral Steer page The speed command is for the first future flight plan waypoint that has an RTA assigned If the crew desires to be alerted when the actual speed differs from the commanded speed enter the desired threshold on the Navigation Configuration page Refer to Figure 3C 43 and Table 3C 34 When the actual speed differs from the commanded speed by an amount gre...

Page 453: ...ypoint The active waypoint wind will show the current wind conditions and entry is not permitted The wind for history waypoints is the actual wind measured at waypoint passage and entry is not permitted Wind direction is entered in the direction from which the wind is blowing When transferring a flight plan from the alternate to the active flight plan the waypoint wind entered in the alternate fli...

Page 454: ...vides an oceanic flight position reporting and trip log function to simplify crew procedures for these tasks a Data Access and Display To view the Oceanic Mission page press the mission MSN function key on the CDU Select the Oceanic line key to display the Oceanic Reporting page Refer to Figure 3C 45 and Table 3C 36 This page shows the current flight plan waypoints in sequence with each waypoint s...

Page 455: ... approach procedure is prohibited The FMS must sequence through the FAF waypoint for the MAP to become the active waypoint When the DIR TO line select key is pressed the Flight Plan page is accessed with DIR TO displayed on the top line Refer to Figure 3C 46 and Table 3C 37 If the pilot has selected the FMS navigation source on the EHSI the Direct To course may also be activated to the current act...

Page 456: ...rocedure NO DESCRIPTION FUNCTION 1 Press Direct Function Key DIR 2 Indicates the active waypoint 3 Scroll to the desired waypoint DDD 4 The double arrows will disappear when scrolled away from the active waypoint 5 Select the desired waypoint 6 When the Dir To becomes the active waypoint the course indicator displays dir ...

Page 457: ... be pushed one waypoint into the future and the scratchpad waypoint becomes the new active waypoint When the MAP is the active waypoint executing a Direct To the scratchpad waypoint will move the MAP into history not future allowing departure into a missed approach procedure Waypoint insertion between the FAF and the MAP is prohibited even when the FAF is in history Figure 3C 48 Direct To an Impro...

Page 458: ...t 5 When the Direct To becomes the active waypoint the course indicator displays dir To execute a Direct To the non flight plan waypoint that is stored within the FMS like a Markpoint copy the desired waypoint into the scratchpad select DIR and select line select 1L to activate the Direct To the scratchpad waypoint 5 Direct To Vector From Present Position The impromptu point may also be defined as...

Page 459: ...rect To Vector From Present Position Procedure NO DESCRIPTION FUNCTION 1 Press Direct Function Key DIR 2 Indicates the desired vector location Bearing Distance from present position 3 Press line select key DIR TO 4 When the Dir To becomes the active waypoint the course indicator displays dir ...

Page 460: ...ith waypoint switching when a parallel offset is applied NOTE Executing Direct To a waypoint will cancel a parallel course offset if one has been applied 2 Parallel Offset Initiation Termination Or Change Parallel course offsets may be applied changed or deleted any time the active waypoint is not identified as a pattern or an approach waypoint Refer to Figure 3C 52 and Table 3C 42 for an illustra...

Page 461: ... Offset Procedure NO DESCRIPTION FUNCTION 1 Insets a parallel course offset Right or left must be specified as the first character e g RO 4 R5 L7 0 L12 8 2 The current value for parallel course offset or OFFST if none is defined 3 Deletes a parallel course offset if the scratchpad contains 0 0 0 0 or 0 4 Display is returned to OFFST ...

Page 462: ...nsition with Parallel Offsets The parallel offset flight plan may result in severe geometry at waypoints with large course changes To resolve this condition the offset pseudo waypoint is never displaced along the inbound leg track by more than two times the width of the offset Figure 3C 54 shows an offset definition where the along track shift of the pseudo waypoint is less than two times the offs...

Page 463: ...fficient descents with adjustments for actual wind Vertical guidance is not provided during holding pattern DME arc course reversal intercept or pattern execution Also it is not provided for vertical path segments that extend into the previous flight plan leg 2 Assigning an Altitude or Flight Level VNAV guidance requires an altitude or Flight Level FL to be entered at a waypoint in the flight plan...

Page 464: ...nd are automatically referenced by the FMS 800 to the local baroset If a flight level is desired enter FL followed by the three digit flight level This indicates that the altitude is referenced in the FMS 800 to the flight level pressure datum 29 92 in Hg instead of the local barometric pressure The FMS 800 automatically computes the guidance through the transition altitude climbs or transition fl...

Page 465: ...TM 1 1510 218 10 Figure 3C 56 Entry and Display of VNAV Parameters 3C 111 ...

Page 466: ...titude the V attribute will be displayed on the Flight Plan page On MDA approaches no descent angle is defined for the approach so vertical guidance is disabled and the V attribute is not displayed 3 Entry and Display of Climb or Descent Path If only an altitude flight level is entered and no climb or descent path is specified the climb descent path is undefined and no vertical guidance is provide...

Page 467: ... Path Display The DIRECT CLIMB DESCNT vertical rate or angle on the Flight Plan Waypoint page is computed based on the FMS 800 present position and altitude for any waypoint with an altitude assigned not just for the active waypoint Refer to Figure 3C 58 and Table 3C 45 This advisory enables the pilot to plan his climb or descent He is apprised of the actual vertical maneuver required For example ...

Page 468: ...or to VNAV capture the distance to the BOC TOD is displayed This display is dashed after the VNAV path is captured Figure 3C 60 and Table 3C 46 show a typical VNAV profile along with the alerts associated with the VNAV capture and termination Ten seconds prior to the VNAV path capture the CDU page alerts flashes At an altitude 1000 feet below above the waypoint crossing altitude a second alert is ...

Page 469: ... by the pilot The EHSI data includes the HSI course arrow desired track TO FROM pointer and bearing pointer to the FMS 800 outputs These outputs always relate to the flight plan active waypoint or pattern turn point Refer to Figure 3C 61 If the EHSI distance interface is compatible and aircraft switching is installed the distance readout will also show great circle distance to the active waypoint ...

Page 470: ...yellow 3 Flight Director and Autopilot Lateral Bank Steering Using the Flight Director or autopilot the FMS can steer the aircraft directly through all of the possible flight plan maneuvers including holding patterns MFP s SID s STAR s and FMS approaches This interface also enables the FMS to limit the commanded bank angle to the value specified on the Navigation Configuration page The FMS provide...

Page 471: ... FMS course Press the HDG knob on the FDS control panel to activate the FMS heading mode and select the desired heading to intercept the final approach course The FMS roll command will guide the aircraft to acquire and hold the displayed heading and any subsequent desired heading entered by the pilot on the FDS control panel The FMS heading mode will continue to guide to the FDS selected heading a...

Page 472: ...ground station outdated waypoints replaced with current ICAO definition and the on aircraft FMS purged of existing flight plans The updated alternate flight plans can then be used for normal operations 1 Alternate Flight Plan Structure The alternate flight plan operates as a spreadsheet calculator The crew inputs the flight plan routing wind and aircraft performance The FMS 800 calculates the indi...

Page 473: ...TM 1 1510 218 10 Figure 3C 64 Alternate Flight Plan Schedule 3C 119 ...

Page 474: ...elect catalog of available alternate flight plans on data cartridges 14 To access Leg pages 7 To replace active flight plan with alternate flight plan 15 To access Init page 8 Scroll laterally among the Leg pages for each leg 16 Leg number corresponds to the last viewed Leg page pressing this line select key will re access the Leg page Table 3C 48 Alternate Flight Plan Waypoints Page Access Proced...

Page 475: ...l Page Procedure Continued NO DESCRIPTION FUNCTION 1 Return to Alternate Flight Plan page 2 Scroll laterally to access the Fuel Init page 3 Insert initial fuel load 4 Insert zero fuel weight 5 Calculated gross weight 6 Select desired reserve fuel calculation klb 0 0 or min 7 Return to Alternate Flight Plan page 3C 121 ...

Page 476: ...Alternate Climb Init page the FMS calculates a Top Of Climb TOC leg segment that is used for fuel calculations The TOC is displayed on the Alternate Flight Plan Leg A page for the leg that contains the TOC Refer to Figure 3C 67 and Table 3C 50 All leg segments previous to the TOC use the climb leg calculations for fuel burn Following the TOC the fuel burn rates for each leg are used for fuel usage...

Page 477: ... page at the time a new plan is created Waypoints may be inserted and deleted on the Leg A pages or on the Alternate Flight Plan Waypoints page in the same manner as for the active flight plan The zero fuel weight entry is used to calculate the gross weight of the aircraft on the ground with fuel loaded and the gross weight remaining after each leg is flown as indicated on the Alternate Flight Pla...

Page 478: ...fload is entered at a waypoint the arrival and departure fuel and or gross weight will differ by the entered amount Refer to Figure 3C 69 and Table 3C 52 9 Entry and Display of Fuel Weight ONLOAD OFFLOAD If an aerial refueling cargo delivery is planned during the flight plan leg perform the following procedure 7 Entry and Display of Planned Altitude On the Leg C page optional entries of the planne...

Page 479: ...t operate as they do when this page is accessed from the Start 3 page Selecting a line select key on the Alternate Flight Plan Catalog page when accessed from the Alternate Flight Plan page will access the Alternate Flight Plan Load Save page From this page either load the alternate flight plan associated with the line select key pressed or enter a new label for the alternate flight plan and save ...

Page 480: ...d right hand and non standard left hand holding patterns using approved entry flight procedures The FMS supports two types of holding pattern definitions 1 User defined holding patterns attached to fixed waypoints by the user 2 Published holding patterns that are derived from published instrument approach charts A holding pattern may be associated with one fixed waypoint the holding fix When the a...

Page 481: ...pect Further Clearance EFC time 5 Executes the holding pattern at the present position 6 Inserts the holding pattern into the flight plan or removes it 7 Inserts the length of pattern s inbound leg Defaults to 4 nm If computed not entered it remains dashed until the hold pattern is active 8 Enters the duration of the inbound leg in minutes 9 Selects between right and left turns in the pattern Defa...

Page 482: ...he user defined holding pattern definition parameters have been entered the active waypoint or a future fix waypoint may be designated as the holding fix After pressing the FPLN INS line select key on the Hold page the Flight Plan page is accessed with the message ATTACH HOLD AT in the scratchpad Scroll the flight plan to the desired location Press the adjacent line select key to identify the asso...

Page 483: ...TM 1 1510 218 10 3C 129 9 1 Figure 3C 73 Direct Entry Into a Holding Pattern Figure 3C 74 Teardrop Entry Into a Holding Pattern ...

Page 484: ...TM 1 1510 218 10 Figure 3C 75 Parallel Entry Into a Holding Pattern 3C 130 ...

Page 485: ...dicates pattern entry advisory on Hold page 2 Press the FPLN INSR line select key to access Flight Plan page 3 ATTACH HOLD AT is in the scratchpad 4 Scroll to the desired waypoint 5 Pressing line select key will identify the associated waypoint as the holding fix 6 H indicates which flight plan waypoint has been designated as the holding fix ...

Page 486: ...en the holding fix is passed for the first time the holding guidance computations are activated At this time the following changes will take place in the flight plan operation and page displays a The automatic leg advance is suspended b Course edits on the Flight Plan page may no longer be made Inbound holding course edits may be made on the Hold page c All displays reference the inbound course di...

Page 487: ...me entries and displays assist the pilot in executing a holding pattern in accordance with FAA air traffic control procedures This also permits future waypoint ETA s to be more realistically calculated a Entry and Display of Holding Speed Enter a desired holding speed at the IAS line select Refer to Figure 3C 78 and Table 3C 57 When the IAS defaults to blanks the operator must enter a desired hold...

Page 488: ... fix waypoint and resets the holding pattern parameters to default conditions 10 Published Holding Patterns A published GPS approach in the flight plan may include several holding pattern definitions as part of the procedure Published holding patterns are enabled on the Holding Pattern page for the holding fix waypoint To review the holding pattern definition select the right line select key adjac...

Page 489: ...ht plan press the EDIT key on the CDU and then select the SID or STAR line select to access the corresponding SID STAR definition pages Refer to Figure 3C 80 and Table 3C 59 To define a desired SID or STAR enter the airport associated with the desired SID or STAR and select the ORIG or DEST line selects to access the possible procedures for the airport Next select the SID STAR name and desired run...

Page 490: ...y the flight plan with the new procedure The working copy definition of a SID or STAR is accessed from the EDIT menu Refer to Figure 3C 82 and Table 3C 61 When the working copy is defined it can be used to modify the active flight plan procedure with the new definition If a SID is in the flight plan the information line of the SID page displays IN FPLN and asterisks are shown next to the selected ...

Page 491: ...equires crew action to resolve in order to obtain proper flight plan sequencing The waypoint associated with the discontinuity can be either the one preceding following or both A discontinuity is inserted into the flight plan under the following three conditions 1 Following a STAR or preceding a SID when it is inserted in the flight plan DISCONTINUITY 2 When a leg of a SID STAR has a non flyable l...

Page 492: ... of the page also entered on the working copy STAR definition This calls up a listing of available GPS approaches and runways for that airport To select a user defined tactical approach no airport identifier is required select the TACTICAL line key Figure 3C 83 Discontinuity in the Flight Plan Table 3C 62 Discontinuity in the Flight Plan Procedure NO DESCRIPTION FUNCTION 1 Pressing FPLN function k...

Page 493: ...ing procedure with the new definition Using the FMS approach function requires the system to insert a sequence of waypoints into the flight plan All approaches will have a FAF or Runway Extension Point and a MAP GPS approaches may also have a MAHP and an IAF These points are treated by the system as any other waypoint The MSL altitudes may be entered for each point with the exception of the MAP an...

Page 494: ... 5 Fat arrows indicate current selection for insertion 6 Select line key to modify the flight plan with the selected approach procedure This selection will replace the current procedure in the active flight plan Table 3C 64 Active Flight Plan Approach Definition Procedure NO DESCRIPTION FUNCTION 1 Select MAP attribute on the Flight Plan page and Flight Plan Waypoint page to access the current appr...

Page 495: ...udes the descent angle into the MAP will be blanked on the Flight Plan Waypoint page for the MAP and FMS vertical guidance will be disabled for the final approach into the MAP The V attribute for vertical guidance definition will not be displayed on the Flight Plan page for MDA approaches For MDA approach altitudes select the MDA altitude on the autopilot altitude preselector to initiate guidance ...

Page 496: ...re 3C 89 and Table 3C 67 The default visual approach parameters which can be modified are a 5 0 nm final segment and a 3 0 glideslope with a crossing altitude for the runway extension point of 1500 feet AGL Press the FPLN INSR line key to insert the approach into the active flight plan at the desired location in the same manner as for the published GPS approach The Flight Plan page will be display...

Page 497: ...oint distance from runway 5 Enter desired glideslope to runway 6 Indicates elevation of runway from database 7 Insert the approach into the flight plan 8 Press the line select key to insert the approach 9 Runway extension point FAF equivalent 10 Missed Approach Point or Runway Threshold 8 Tactical Approaches Pressing the TACTICAL line select key will access the Tactical Approach page as shown in F...

Page 498: ...ging the FMS Approach Once an FMS Approach of any type is in the flight plan it may be deleted or replaced with a different approach Access the FMS Approach pages via the EDIT key to access a working copy definition of the approach or press the A or F attribute line select on the Flight Plan Waypoint page for the MAP or FAF waypoint to access the current flight plan definition Select the desired a...

Page 499: ...TM 1 1510 218 10 3C 145 Figure 3C 91 Visual Tactical Approach and Sequence Figure 3C 92 Published GPS Approach Scaling and Sequencing ...

Page 500: ...ctly to the DME arc endpoint waypoint without intercepting the arc select Direct To the DME arc endpoint again which will override the DME arc leg intercept b Course Reversal Guidance On selected GPS approaches a published procedure turn may be defined for execution in the approach procedure The FMS performs a course reversal procedure with standard holding pattern entry logic to execute the proce...

Page 501: ... terminate course reversal guidance There are three types of course reversals typically defined within a GPS approach procedure Refer to Figures 3C 94 3C 95 and 3C 96 1 IAF course reversal 2 Collocated IAF FAF course reversal 3 Extended FAF course reversal In the co located IAF FAF and extended FAF type course reversals the course reversal execution is actually performed at the FAF waypoint even t...

Page 502: ...rect to the FAF F attribute waypoint on the Flight Plan page The FMS 800 will display the message FINAL COURSE XXX where XXX is the final approach course as shown in Figure 3C 97 but will execute a course direct to the FAF To intercept the final approach course select the CRS line select with the FINAL COURSE displayed in the scratchpad The FMS will provide lateral guidance to guide the aircraft t...

Page 503: ... another waypoint other than the MAP When disabled by go around the FMS flight mode will switch to TERMINAL mode scaling but lateral guidance will continue to be provided through the MAP waypoint Vertical guidance advisories on the CDU will be terminated when the approach is disabled To re enable the approach select direct to the FAF or any other flight plan waypoint that would place the FAF as a ...

Page 504: ...wo conditions 1 Following a MAP when inserted in the flight plan 2 Following a MAP when a direct to puts the history FAF and MAP waypoints as future waypoints The VERIFY PROC annunciation and CDU alert are displayed when one minute to go before sequencing into the discontinuity If the discontinuity becomes the active waypoint a DISCONTINUITY annunciation is displayed and guidance is provided for w...

Page 505: ...tional 15 Insert pattern width 16 Computed maximum bank limit for pattern width 17 Insert pattern inbound course optional 18 Insert pattern fix optional 3 Circle patterns require all parameters defined above except for pattern length MFP geometry definitions are shown in Figure 3C 99 CRP s are special patterns made up of crew defined points connected together to form an enclosed flight path A CRP ...

Page 506: ...TM 1 1510 218 10 Figure 3C 99 MFP Geometry Definitions 3C 152 ...

Page 507: ...hanged while in the pattern the changes are applied after the aircraft passes the pattern fix transition from TO to FROM except for the pattern length and width which take effect immediately if on the outbound leg When pattern guidance has been activated all course and lateral deviation displays now reference the computed inbound or outbound course of the pattern The 10 second turn alert will be c...

Page 508: ...intercept has not been inserted the computations are performed as if it were a direct to intercept from present position a Direct Intercept When an intercept is the active waypoint the intercept location is regularly updated based on the following information 1 Current own aircraft position and speed 2 Moving target definition The intercept point location is adjusted as required and the inbound co...

Page 509: ...e flight plan sequence Figure 3C 101 Direct Intercept Insertion 4 A calculator function is provided to allow the crew to enter an alternate TAS and see the effect on the intercept This calculator is available for an intercept not inserted into the flight plan and for the next intercept in the flight plan Refer to Figure 3C 104 and Table 3C 72 Table 3C 71 Direct Intercept Insertion Procedure NO DES...

Page 510: ...TM 1 1520 218 10 Figure 3C 102 Direct Intercept Figure 3C 103 Future Intercept Geometry Alternate Intercept Solution 3C 156 ...

Page 511: ... intercept calculator solution 2 The PCA indicates the intercept is not possible 3 The aircraft current true airspeed 4 Time to intercept based on alternate airspeed 5 Insert alternate true airspeed for calculator solution 6 Time to intercept or PCA intercept not possible in this example Figure 3C 105 Markpoint List and Waypoint List Page Access and Usage 3C 157 ...

Page 512: ...same name a prompt will appear to confirm overwriting the old waypoint definition To prevent an overwrite press CLR or confirm to overwrite To use the new user waypoint recall the waypoint by name on the Flight Plan page or any other FMS page that uses ICAO identifier waypoints or copy the waypoint from the User Waypoint List page The User Waypoint List page includes a search utility to help find ...

Page 513: ...Naming Waypoints within the FMS can be given a user defined identifier name by applying a followed by the desired waypoint name Refer to Figure 3C 107 and Table 3C 75 Valid waypoints that can be named by this function are latitude longitude and ident bearing distance waypoints ICAO identifier or existing user defined waypoints can not be renamed with the user waypoint naming function To apply a us...

Page 514: ...fiers in the ICAO database When using the named waypoint with an ICAO duplicate the Select Waypoint page will be accessed to allow selection of the desired waypoint The user named waypoint is identified on the Select Waypoint page with as the country code q From To And Waypoint Data Pages 1 Data Page Overview Independent of the active and alternate flight plans the FMS 800 will compute on demand t...

Page 515: ...TM 1 1520 218 10 10 Figure 3C 108 FROM TO Options for the Data Page Examples Only 3C 161 ...

Page 516: ... while retaining the same FROM waypoint Option 2 Figure 3C 111 To view a direct segment FROM a flight plan waypoint TO a nonflight plan waypoint scroll the flight plan in the LEG mode until the desired FROM waypoint is at the top of the page Then insert the desired TO waypoint on data line 2 in place of the existing TO waypoint Option 3 Figure 3C 112 To view data from present position to any fligh...

Page 517: ...TM 1 1520 218 10 3C 163 Figure 3C 110 Data For Option 1 Figure 3C 111 Data For Option 2 ...

Page 518: ...TM 1 1520 218 10 3C 164 Figure 3C 112 Data For Option 3 Figure 3C 113 Data For Option 4 ...

Page 519: ...TM 1 1520 218 10 3C 165 Figure 3C 114 Data For Option 4 Via Flight Plan Figure 3C 115 Data For Option 5 ...

Page 520: ...110 3C 111 and 3C 112 When PPSN DIRECT is selected the ETE and ETA are calculated for a flight path directly between aircraft present position and the TO waypoint Figures 3C 113 and 3C 115 When PPSN VIA FPLN is selected the ETA and ETE are calculated along the flight plan from present position Figure 3C 114 The ETA and ETE are calculated one of two ways depending on the TO waypoint If the TO waypo...

Page 521: ...ntifier with country code and waypoint type if applicable 3 Waypoint Station declination or magnetic variation 4 Waypoint elevation MSL 5 Waypoint latitude longitude 6 Station frequency and or TACAN channel The wind vector is displayed as either a current wind vector crosswind component or head tail wind component For the headwind tailwind component a n will indicate a tail wind and a p will indic...

Page 522: ...d guidance of the aircraft a GPS Display The GPS INAV page shows the present position output from the GPS receiver It also shows a 95 error figure of merit for the probable system accuracy given the current GPS satellite navigational quality satellite tracking state and geometry as shown in Figure 3C 120 and Table 3C 82 If GPS A H is indicated on the title line the FMS 800 is using airspeed and he...

Page 523: ...ata The FMS 800 provides the crew access to the page displaying the individual channel satellite tracking status for the GPS receiver Selecting the SATS line select key on the GPS INAV page will access this page Refer to Figure 3C 121 and Table 3C 83 NOTE The possible state displays are listed below 1 2 S Search 4 6 T Tracked 3 I Interference 5 D Tracked with data 7 R Recovery The GPS satellite da...

Page 524: ...estored The current state of the GPS RAIM solution is provided on the Primary GPS INAV page as follows 1 NO RAIM when RAIM processing is unavailable 2 RAIM ACT when RAIM processing is actively performing integrity checks 3 RAIM WRN when RAIM has detected an inconsistency The line select key next to RAIM on the RAIM prediction page will enable or disable the RAIM annunciations When OFF is selected ...

Page 525: ...atchpad LS1 retrieves the navigation information for that ID from the data cartridge 9 The airport ID s Navigation Radio Information 1 Navigation Radio Information Overview The FMS 800 provides navigation radio information upon valid entry of an airport identifier The crew may access the Navigation Radio Information page via the NAV function key on the CDU Refer to Figure 3C 123 and Table 3C 85 Se...

Page 526: ... tune the V UHF radios by frequency callsign maritime channel or preset number Frequency tuning is performed directly on the Communications page by entering the desired frequency in the scratchpad and pressing the channel selection line select key Refer to Figure 3C 124 and Table 3C 86 A valid frequency is entered as two to three digits followed by up to four decimals followed by A AM F or FM to d...

Page 527: ... the preset is selected the preset number is displayed in the preset number field on the Communication page along with the associated callsign Refer to Figure 3C 125 and Table 3C 87 To tune the radio to a preset callsign enter the callsign and press the appropriate line select key on the Communication page The FMS 800 will search the preset list for that callsign and tune the radio to that frequen...

Page 528: ...or C coast into the CDU scratchpad and press the CHAN line select key d V UHF Scan Function The FMS 800 ARC 210 provides an ability to continuously scan up to four communications frequencies for incoming signals To enable the ARC 210 scan function access the V UHF control page and toggle the SCAN mode to ON SCAN will replace the callsign field of the communication page and the frequency field will...

Page 529: ... 6 Select frequency and modulation for scan e V UHF Airport Frequency Selection To tune the radio to airport frequencies stored on the data cartridge access the V UHF Airport Frequency page The V UHF Airport Frequency page may be accessed from the Communication page by entering a valid airport identifier and then pressing the line select key 1R Refer to Figure 3C 128 and Table 3C 90 With a valid a...

Page 530: ...displays the guard frequencies and GUARD for the callsign Figure 3C 128 Tuning to Airport Frequencies Table 3C 90 Tuning to Airport Frequencies NO DESCRIPTION FUNCTION 1 Pressing function key COM will access the communication page 2 Enter airport to access airport frequency 3 Indicates page 2 of 3 Scroll vertically to access additional pages 4 Sectorization 5 Communication type 6 Select desired ai...

Page 531: ...is listed below i Loading Multiple Words of the Day An MWOD list can be created manually using the V UHF MWOD Entry pages or loaded from a data cartridge The FMS 800 maintains one MWOD list for V UHF radios consisting of six WOD s To load each WOD element into the MWOD list manually access the MWOD Entry page as shown in Figure 3C 130 and Table 3C 92 To load the MWOD list into the V UHF radio pres...

Page 532: ...FMT Load pages or loaded from the data cartridge Refer to Figure 3C 131 and Table 3C 93 To load each FMT element into the FMT list manually access the FMT Load pages as shown in Figure 3C 131 Finally to load the FMT list into the V UHF radio press the ENTER line select key on any of the V UHF FMT Load pages When an FMT list is successfully loaded into the V UHF radio the radio will acknowledge eac...

Page 533: ...lect GPS TIME to synchronize the radio to GPS UTC Select RECV TIME or SEND TIME to receive or send a time synchronization from another radio Select RESET TIME to reset the internal clock when no other time is available Activate the time synchronization by pressing the ENBLE line select key When performing GPS time synchronization first confirm that the GPS time figure of merit is reasonable by mon...

Page 534: ...radio The designated radio must be operating in an antijam mode when selected Table 3C 96 SINCGARS Page Access Procedure NO DESCRIPTION FUNCTION 1 Enter hopset lockout number or enable fill with a blank scratchpad 2 Enable V UHF as net control station master 3 Access cue cold preset page 4 Access V UHF control page 5 Enter day time for net synchronization 6 Enable late net entry 7 Select ERF fill ...

Page 535: ...ernal QUICK TUNE push button located on the pilot s and copilot s control yokes is dedicated for remote communication radio frequency control The QUICK TUNE push button works in conjunction with the CDU scratchpad to allow the crew to tune the radio displayed on the EHSI To tune the radio to the previously tuned frequency press the QUICK TUNE push button without a valid entry in the CDU scratchpad...

Page 536: ...TM 1 1520 218 10 1 Callsign 2 Active Frequency green 3 Modulation 4 Recall Frequency cyan 5 Free Format Line Figure 3C 135 Electronic Horizontal Situation Indicator Free Format Line 3C 182 ...

Page 537: ...ush Button Example Procedure NO DESCRIPTION FUNCTION 1 Pilot enters a new V UHF frequency in the scratchpad of the CDU 2 Pilot presses the quicktune push button on the flight yoke 3 The CDU scratchpad is cleared 4 The FMS 800 updates the communication page V UHF frequency display 3C 183 ...

Page 538: ...r pages or the start 3 page Points from the ICAO identifier database can be requested from any page where waypoint entry is permitted Refer to Figure 3C 137 and Table 3C 99 Table 3C 99 Data Loader Page Access and Usage Procedure NO DESCRIPTION FUNCTION 1 Pressing function key IDX will access the index page 2 Access the Data Loader pages 3 Saves the fault history of all avionics LRU s to the cartri...

Page 539: ...is cleared when the detailed status page for the failed LRU is accessed Refer to Figure 3C 138 and Table 3C 100 4 Accessing the ICAO Identifier Database ICAO identifiers stored in the data cartridge are accessed by entering the identifier into the scratchpad and pressing a waypoint entry line select key i e a line select key on a CDU page allowing entry of waypoints for example the Flight Plan pag...

Page 540: ...failure is causing nuisance alerts This prohibits the STATUS annunciation from being displayed and the CDU alert or MSG annunciation from being activated for LRU failures All status monitoring results continue to be displayed on the detailed status page The state of this selection is always reset to enable reporting on power up Refer to Figure 3C 139 and Table 3C 101 The definition of each LRU sta...

Page 541: ...control relinquished Bit 13 NVM Status CDU long term memory pilot entered data may be incorrect or unavailable Bit 14 ROM Status CDU memory may be incorrect or unavailable Bus control relinquished Bit 15 RAM Status CDU temporary memory may be incorrect or unavailable Bus control relinquished Bit 16 CPU Status CDU CPU may cease to function or have impaired capability Bus control relinquished BUS MI...

Page 542: ... on power down ADC Status ADC ADC Subsystem Status ADC may be inoperative or have impaired capability V UHF Status Bit 1 Power Supply Ready Fault V UHF radio may be inoperative or have impaired capability Bit 2 High Power Amp HPA Low Voltage Fault V UHF radio may be inoperative or have impaired capability Bit 3 HPA Temperature Fault V UHF radio may be inoperative or have impaired capability Bit 4 ...

Page 543: ...V UHF radio is not responding on the A bus NGO B V UHF radio is not responding on the B bus NGO T V UHF radio is not responding on either 1553 bus w Miscellaneous Functions 1 Miscellaneous Functions The FMS 800 also provides the following functions that are not covered in the previous sections a Timers Three independent stop watch lap counters are available complete with time out annunciations b M...

Page 544: ...regions and airspeed above 10 knots Higher latitudes and low airspeeds may produce unexpected results in system response due to instabilities in the model Prior to accessing the Model Aircraft page enter the initial present position on the Start 1 page Access the Model Aircraft page by pressing the MODEL line select key on the Index 2 page Refer to Figure 3C 141 and Table 3C 104 Toggle the MODE li...

Page 545: ...ssing IDX function key will access the index page 2 Scroll to index 2 page 3 Accesses model aircraft page 4 Inserts the model altitude 5 Inserts the model wind 6 Inserts the model true airspeed 7 Inserts the heading toggles heading mode between flight plan Steering STR and Heading Hold HLD 8 Toggle the line select key for either RUNNING or STOPPED modes 3C 191 ...

Page 546: ...led history file contains start and end dates of the record A new fail history record will begin whenever the crew saves the status data to the cartridge 5 Zeroizing System Data The Lock Zeroize page permits selective blanking of data within CDU nonvolatile memory and the data loader cartridge In addition to selective blanking a single key commands a master zeroize of all data stored in the system...

Page 547: ...sire to zeroize markpoint and user waypoint lists 7 Password entry locks unlocks the system 8 Request zeroization of markpoint and user waypoint lists 9 Request zeroization of flight plan and alternate flight plan 3C 26 PILOT S ALTIMETER BA 141 a Description The pilot s altimeter provides a servoed counter drum pointer display of barometrically corrected pressure altitude Refer to Figure 3C 143 In...

Page 548: ...ltitude Scale The face of the altimeter has a marked scale from 0 to 9 in 20 foot increments 4 Barometric Pressure Counter Drum Indicator Window Inches of Mercury This window indicates barometric pressure as set by manual barometric pressure setting knob 5 Barometric Pressure Counter Drum Indicator Windows Millibars The barometric pressure and millibar counter drum indicator windows display barome...

Page 549: ...lot in judging the bearing of storms and necessary heading changes 1 Mode Selector Control Knob 2 RANGE Selector Control Knob 3 TILT Control Knob 4 BRIGHT GAIN MAX Control Knob 3 With radar graphics interfaced a circle mode may be activated by pressing the page button located on the radar graphics control panel Functional operation in this mode is the same as in the standard display mode and is av...

Page 550: ...adjustment of gain Brightness of the display screen is fully adjustable to compensate for a range of ambient light levels while automatically maintaining equal brightness between the three colors displayed Likewise the gain control can be manually adjusted in both weather and ground mapping modes to provide maximum flexibility in target interpretation Whenever the gain is varied from the preset ma...

Page 551: ...earing for each NAV system is displayed with NAV data on each side of the screen A waypoint line will also be displayed connecting the waypoints in numerical sequence An R on the left side of the screen indicates all visible NAV aids selected by the flight management system will be displayed The level of NAV aids displayed is indicated by one two or three dots on the left side of the R e NAV 1 Sel...

Page 552: ...een checked off the display returns to the index with the next checklist selected An END OF LIST statement follows the last title in an index and the last item in a checklist The pilot may return to the index prior to checking off all items by pressing the IDX button 8 Input Jack Provides a means of connecting the pocket terminal to the unit 9 IDX Button Allows the pilot to return to index c Opera...

Page 553: ...ocket terminal A checklist item may consist of any combination of alphanumeric characters spaces or punctuation up to a length of 15 lines 450 characters If the item is longer than one line long do not use the carriage return to move from one line to the next Use spaces SHIFT SP as necessary to move the cursor to the end of the line and to the beginning of the following line The SHIFT CR should be...

Page 554: ...unted full color digital display system Weather display ground mapping and text functions are provided The inputs are displayed on the screen together with range mode and status alphanumerics to facilitate evaluation of the picture 2 Range Switches The range switches are two alternate action push button switches one placarded and the other placard Ø which are used to select the radar operating ran...

Page 555: ...t Alert Switch The target alert switch is a momentary alternate action push button switch placarded TGT which selects the target alert function TGT mode annunciates significant weather conditions within 7 5 of dead ahead Selecting TGT disables the variable gain rotary control 6 Sector Selection Switch A momentary alternate action push button switch placarded SECT selects either full azimuth scan 1...

Page 556: ...AN display mode In MAP mode radar Sensitivity Time Control STC circuitry is disabled for ground mapping operations In PLAN mode a NAV PLAN format is selected This mode is a north up mode in which the aircraft symbol is positioned with respect to the NAV route and progresses along the displayed route Weather information is not displayed while in PLAN mode 2 Weather Key The weather key placarded WX ...

Page 557: ...multifunction display brightness 11 Data Key This key placarded DAT adds long range navigation information to the MFD MAP or PLAN displays 12 VOR Key This key placarded VOR adds VOR DME symbols to the MFD MAP or PLAN displays 13 Airport Key This key placarded APT adds airport symbols to the MFD MAP or PLAN displays 14 Range Control This control placarded RNG INC DEC selects map range limits of 5 1...

Page 558: ...el The upper half of the switch indicator yellow is placarded VOICE OFF The lower half is an indicator red only and is placarded VA FAIL Pressing the VOICE OFF switch indicator disables the GPAAS voice advisory and illuminates the VOICE OFF indicator light The VA FAIL annunciator light red will illuminate when the GPAAS fails WARNING 2 GPAAS Volume Control A GPAAS volume control placarded VOL loca...

Page 559: ...at 4 second intervals 20 Altitude altitude will be announced at excessive deviation from altitude selected on the altitude alerter 21 Check trim will be announced when trim failure has occurred Will be repeated three times at 4 second intervals 22 Autopilot will be announced when autopilot has disconnected b Normal Operation 1 Turn On Procedure The GPAAS is operable when the following conditions h...

Page 560: ...m indicates that the aircraft is at the radio altitude selected by the crew using the radio altimeter indicator DH knob This advisory is cancelled when valid information from the radio altimeter is lost during climb whenever the aircraft is above 1000 feet AGL or whenever the aircraft is out of the operating altitude range of the radio altimeter 7 Aural Altitude Altitude Advisory Mode 7 The aural ...

Page 561: ...C 920 are illustrated in Figure 3C 150 and detailed in Table 3C 107 Figure 3C 150 TTC 920 Transponder TCAS Control Table 3C 107 TTC 920 Transponder TCAS Control Switch Descriptions SWITCH LEGENDS FUNCTIONS 1 Altitude Enable Switch ALT OFF Enable altitude reporting on transponder 2 Transponder Enable Switch 1 2 Enables 1 or 2 transponder 3 Fail Indicator ATC FAIL Indicates failure in transponder co...

Page 562: ... Table 3C 108 A B Figure 3C 151 TV1 920 Transponder TCAS Display Table 3C 108 TVI 920 Transponder TCAS Display Switch Functions SWITCH LEGENDS FUNCTION 1 Mode push button switch A B Selects above or below for display of traffic 2 Range push button switch R Allow selection of forward direction display range 3C 208 ...

Page 563: ...tical speed is outside of arc preventive resolution exit range if vertical speed is within arc corrective resolution Green Arc Recommended vertical speed to resolve corrective resolution advisory TRAFFIC DISPLAY Aircraft White Own aircraft symbol displayed continuously Range Ring White Two mile radius range about aircraft If no bearing message is displayed only the forward half of ring will be dis...

Page 564: ...r which no bearing information is available 4 ABV Traffic displayed in altitudes from 9900 ft to 2700 ft relative to own aircraft If no message is displayed traffic display is from 2700 ft to 2700 ft relative to own aircraft 4 BLW Traffic displayed in altitudes from 9900 ft to 2700 ft relative to own aircraft If no message is displayed traffic display is from 2700 ft to 2700 ft relative to own air...

Page 565: ...ncreased Climb Climb Now Climb Climb Now Follows Descend advisory when reversal of vertical speed is required due to maneuvering of intruding aircraft Descend Descend Now Descent Descend Now Follows Climb advisory when reversal of vertical speed is required due to maneuvering of the intruding aircraft Threat Situation Resolved Clear of Conflict Intruding aircraft is no longer a threat f Traffic Di...

Page 566: ...rective advisory indicates a necessary change in flight path by displaying a vertical speed range or pitch to be flown to Either advisory serves to ensure that the maximum separation between the aircraft and an intruder is maintained Refer to Table 3C 114 Table 3C 114 Resolution Advisory Inhibits Radio Altitude Resolution Advisory Status Below 1450 FT AGL INCREASE DESCENT RA inhibited Below 1000 F...

Page 567: ...and 2 and also that the 6 nm range is selected NOTE The TA ONLY mode does not identify RA intruders and will not generate corrective or preventive RA displays If an RA threat level aircraft is present the display will show it as a TA target when the TA ONLY mode is selected h Corrective RA Figure 3C 154 shows a corrective RA display advising immediate action to provide maximum aircraft separation ...

Page 568: ...ncrease Descent Increase Descent as appropriate for the advisory 6 A reversal advisory a climb advisory after a descend advisory or a descend advisory after a climb advisory will occur if the TCAS determines that the initial advisory should be reversed An example of when this advisory would occur would be when the intruder causing the initial climb advisory was above you descending into your aircr...

Page 569: ...yed in red would be interpreted the same k Clear of Conflict When the range of an intruder responsible for causing an RA begins to increase its conflict is considered to be resolved If more than one intruder is involved in an RA all conflicts must be resolved before the clear of conflict message will be issued When this occurs Clear of Conflict will be annunciated l Failure Indications 1 Figure 3C...

Page 570: ...TM 1 1520 218 10 A B Figure 3C 156 No Bearing Message Operational Situation A B Figure 3C 157 Failure Indication Display 3C 216 ...

Page 571: ...ome to full voltage and the computer circuits to be reset to initial operating conditions NOTE The average RF output power of the TCAS is below the minimum allowable for human exposure The system may be operated normally on the ground without danger to personnel in the vicinity 1 When executing takeoff and climbout it is suggested the 6 nm or shorter range and ABOVE scan be used This will eliminat...

Page 572: ...for 1 second to verify operation of the light and test mode in the transponder Transponder code digits will display 8888 for 1 second to verify that all digit segments will illuminate o Normal In Flight Operation By selecting TA RA mode the system automatically inhibits RA displays when the aircraft is below 900 feet AGL on approach or 1100 feet AGL on climbout When flying in close proximity to ot...

Page 573: ... RA Flag Displayed Appearance of this flag on the vertical speed indicator indicates failure of the RA functions of the TCAS Follow the same procedure as in 1 above 3 TCAS Flag Displayed Appearance of this flag indicates failure of some part of the TCAS system This includes the associated display systems as well as the units generating the major TCAS functions and signals 1 Verify that ATC FAIL in...

Page 574: ... ...

Page 575: ...TM 1 1520 218 10 CHAPTER 4 MISSION EQUIPMENT 4 1 MISSION EQUIPMENT These aircraft are not equipped with mission equipment 4 1 4 2 blank ...

Page 576: ... ...

Page 577: ... flight and utility system instruments Red markings indicated the limit above or below which continued operation is likely to cause damage or shorten life The Green markings indicate the safe or normal range of operation The Yellow markings indicate that the range of the operation covered by the instrument requires special attention Operation is permissible in the yellow range but should be avoide...

Page 578: ...TM 1 1510 218 10 Figure 5 1 Instrument Markings and Operating Limits C D Sheet 1 of 7 5 2 ...

Page 579: ...TM 1 1510 218 10 5 3 Figure 5 1 Instrument Markings and Operating Limits C D Sheet 2 of 7 ...

Page 580: ...TM 1 1510 218 10 R G R R R R G q q q q Figure 5 1 Instrument Markings and Operating Limits T1 T2 Sheet 3 of 7 5 4 ...

Page 581: ...TM 1 1510 218 10 G R R R R G G Y G R 49 Figure 5 1 Instrument Markings and Operating Limits T1 T2 Sheet 4 of 7 5 5 ...

Page 582: ...TM 1 1510 218 10 Figure 5 1 Instrument Markings and Operating Limits Sheet 5 of 7 5 6 ...

Page 583: ...TM 1 1510 218 10 Figure 5 1 Instrument Markings and Operating Limits Sheet 6 of 7 5 7 ...

Page 584: ...g of the operating and limitation airspeeds KCAS or KIAS This is dependent on the original aircraft type certificate associated with the particular model and or the installation of an approved replacement indicator Figure 5 1 Instrument Markings and Operating Limits C Sheet 7 of 8 Figure 5 1 Instrument Markings and Operating Limits D T Sheet 8 of 8 5 8 ...

Page 585: ...T shall be added to commercial fuel not containing an icing inhibitor during fueling operations regardless of ambient temperatures The additive provides anti icing protection and functions as a biocide to kill microbiological growth in aircraft fuel systems d Limitations with Ferry Fuel Tanks Installed Failure to comply with Paragraph 5 11d 1 could result in the collapse of the tanks If the 1500 f...

Page 586: ...ly the engine driven fuel pump without boost pump fuel pressure is limited to 10 cumulative hours All time in this category shall be entered on DA Form 2408 13 1 for the attention of maintenance personnel Use of aviation gasoline is time limited to 150 hours of operation during any Time Between Overhaul TBO period It may be used in any quantity with primary or alternate fuel NOTE Aviation gasoline...

Page 587: ...e 105 to 135 psig C D 100 to 135 psig T at gas generator speeds N1 greater than 27 000 RPM 72 with oil temperature between 60 C and 71 C Above 21 000 feet the minimum oil pressure is 85 psig Oil pressure between 60 and 85 psig should be tolerated only for the completion of the flight and then only with a power setting not exceeding 49 torque Oil pressure below 60 psig is unsafe and requires that e...

Page 588: ...1 WITHOUT AIR CONDITIONING WITH AIR CONDITIONING 0 to 75 56 62 75 to 80 60 62 80 to 85 65 65 Right engine only after stabilized Section IV LOADING LIMITS 5 19 CENTER OF GRAVITY LIMITATIONS Center of gravity limits and instructions for computation of the center of gravity are contained in Chapter 6 The center of gravity range will remain within limits providing the aircraft loading is accomplished ...

Page 589: ...through 73 22269 c Operations Over 12 500 Pounds Gross Takeoff Weight D2 T WARNING 1 Requirements WARNING Artificial stall warning systems may only provide a 1 to 5 knot stall warning CAUTION Maximum Gross Takeoff Weight charts must be strictly followed during performance planning to ensure climb capability in the event of an engine failure during takeoff a Aircraft shall be equipped with Raisbeck...

Page 590: ...S 5 28 MANEUVERS a The following maneuvers are prohibited 1 Spins 2 Aerobatics of any kind 3 Abrupt maneuvers above 181 KIAS at 12 500 pounds 4 Any maneuver which results in a positive load factor of 3 17 G s or a negative load factor of 1 27 G s with wing flaps up or a positive load factor of 2 0 G s or a negative 1 27 G s with wing flaps down at 12 500 pounds b Recommended turbulent air penetrat...

Page 591: ...t in freezing rain freezing drizzle or mixed icing conditions supercooled liquid water and ice crystals may result in a buildup on protective surfaces exceeding the capability of the ice protection system or may result in ice forming aft of these protected surfaces This ice may not shed using ice protection systems and may seriously degrade the performance and controllability of the aircraft a Dur...

Page 592: ...oach do not operate the propellers in the 1750 to 1850 RPM range 5 40 INTENTIONAL ENGINE CUT SPEED In flight engine cuts below the safe one engine inoperative speed of Vsse 104 KIAS are prohibited 5 41 LANDING ON UNPREPARED RUNWAY CAUTION Operation on unimproved soft or rough surfaces is recommended only for aircraft equipped with high floatation landing gear CAUTION Except in an emergency propell...

Page 593: ...cing additive per MIL I 27686 should be mixed with the fuel at refueling to ensure safe operation In the event that authorized fuels are not available limitations on graph apply 5 43 TIRE LIMITATIONS Maximum tire speeds are High Flotation Gear 139 Knots 160 MPH Standard Gear 155 Knots 180 MPH 5 44 STRUCTURAL LIMITATIONS Maximum sink rate at touchdown 12 500 pounds 600 FPM Refer to Chapter 4 of the...

Page 594: ...orate of Evaluation and Standardization DES USAAVNC Fort Rucker It is fully coordinated with the Master Minimum Equipment List MMEL and AR 95 1 It is the governing document for flight with inoperative components and items of equipment Changes or modification to the REL are not authorized unless approved by DES and distributed by the Fixed Wing Product Manager s Office FWPMO ...

Page 595: ... title page of the booklet supplied by the aircraft manufacturer entitled WEIGHT AND BALANCE DATA and on the various forms and charts which remain with the aircraft The charts and forms referred to in this chapter may differ in nomenclature and arrangement from time to time but the principle on which they are based will not change 6 5 CHARTS AND FORMS The standard system of weight and balance cont...

Page 596: ...cs Compartment 1 Pilot and Copilot Seats 2 Two Place Couch 3 Passenger Seats 5 4 Lavatory 5 Avionics Shelf 6 120 Gallon Ferry Tanks Denotes Seating Centroids Figure 6 1 Aircraft Compartments and Stations C D T1 Sheet 1 of 2 6 2 ...

Page 597: ...2 Pilot and Copilot Seats 3 Two Place Couch 4 Passenger Seats 5 5 Privacy Curtain 6 Lavatory 7 Avionics Shelves Oxygen Bottle 8 120 Gallon Ferry Tanks Denotes Seating Centroids Figure 6 1 Aircraft Compartments and Stations T2 Sheet 2 of 2 6 3 ...

Page 598: ...ty can be subtracted directly from the weight of passengers baggage and fuel As the fuel load is increased the loading capacity is reduced 6 10 FUEL AND OIL DATA a Fuel Moment Chart This chart Figure 6 2 shows usable fuel moment 1000 for US gallons or pounds of fuel at specific weights of 6 5 lb gal JP 4 and 6 8 lb gal JP 5 8 Fuel moments should be determined by entering the chart with fuel weight...

Page 599: ...TM 1 1520 218 10 Figure 6 2 Fuel Moment Chart 6 5 ...

Page 600: ...er seats and floor panels The tank platforms and ferry tanks are secured with seat rail cargo rings on seat rails The fuel tanks are connected to the provisions already installed in the fuel system 6 12 PERSONNEL LOADING AND UNLOADING a Seat Installation The seats are mounted on full length seat tracks to provide for quick removal and various seating arrangements The armrests adjacent to the aisle...

Page 601: ...TM 1 1520 218 10 Figure 6 3 Baggage Moment 6 7 ...

Page 602: ...TM 1 1520 218 10 Figure 6 4 Personnel Moments 6 8 ...

Page 603: ...TM 1 1520 218 10 Figure 6 5 Cargo Moment C D1 T1 1 of 2 6 9 ...

Page 604: ...TM 1 1520 218 10 Figure 6 5 Cargo Moment T2 2 of 2 6 10 ...

Page 605: ...RAVITY PLANNING The cargo loading shall be planned so that the center of gravity of the loaded aircraft will fall within the operating limits shown on Center of Gravity Limitations graph Figures 6 7 and 6 8 Cargo moment may be determined by using the Cargo Moment chart Figure 6 5 6 18 LOAD PLANNING The basic factors to be considered in any loading situation are as follows a Cargo shall be arranged...

Page 606: ...TM 1 1520 218 10 Figure 6 6 Cargo Loading C D T1 1 of 2 6 12 ...

Page 607: ...TM 1 1520 218 10 6 13 Figure 6 6 Cargo Loading T2 2 of 2 ...

Page 608: ...TM 1 1520 218 10 6 14 Figure 6 7 Center of Gravity Limitations ...

Page 609: ...TM 1 1520 218 10 6 15 Figure 6 8 Center of Gravity Limitations Above 12 500 ...

Page 610: ...TM 1 1520 218 10 6 16 Figure 6 9 Cargo Restraint and Tiedown Method ...

Page 611: ...o may vary 6 23 CARGO UNLOADING Unloading of cargo shall be accomplished through the cabin door C or cargo door D T Section VII CENTER OF GRAVITY 6 24 CENTER OF GRAVITY LIMITATIONS Center of gravity limitations are expressed in ARM inches which refers to a positive measurement from the aircraft s reference datum The forward CG limit at 11 279 pounds or less is 181 0 ARM inches At 12 500 pounds the...

Page 612: ... ...

Page 613: ...low the projected line For instance if the projected line intersects the reference line in the ratio of 30 down 70 up between the guidelines then maintain this same 30 70 relationship between the guidelines all the way to the next item a Conditions At Airport Alpha AAA OAT 85 F 30 C Field Elevation 3800 feet c The Airspeed Calibration Normal System Takeoff Ground Roll graph was used to obtain V1 a...

Page 614: ... Complete the card as follows 1 Field Length Available is 6 000 feet Figure 7 1 TOLD Card Back NOTE If the runway has an approved runway overrun that distance may be added to the runway length for Accelerate Stop calculations 3 Pressure Altitude PA To determine the PA add 1000 feet to field elevation for each 1 00 in Hg that the reported altimeter setting value is below 29 92 in Hg and subtract 10...

Page 615: ...llowable takeoff weight is 12 800 pounds Using Figure 7 22 utilize the chart in the same manner In this case the point on the REFERENCE LINE for Flaps 40 is below the 6000 feet field length line the accelerate stop distance is 5 900 feet and accelerate stop can be accomplished at 13 500 pounds For Flaps 0 the maximum takeoff weight to achieve Accel Stop is 12 800 pounds For Flaps 40 it is 13 500 p...

Page 616: ...eoff configuration Flaps 0 or 40 and the fuel load in order to maintain the aircraft at the maximum allowable weight for all of the conditions 1 For this example the takeoff can be accomplished at an aircraft weight of 12 400 pounds with the flaps 0 or 11 800 pounds with the Flaps at 40 This takeoff is planned with Flaps 0 at 12 400 pounds For this example the aircraft Operating Weight is 8 900 po...

Page 617: ...aircraft takeoff WEIGHT POUNDS line Trace horizontally to the right and read the accelerate go distance Figure 7 3 TOLD Card Front In this example the takeoff weight is planned at 12 400 pounds The accelerate go distance is 11 000 feet 1 thru 5 were determined on the back side of the card and transposed to these blocks Enter the distance 11 000 feet in the appropriate block on the TOLD card 6 Mini...

Page 618: ...ding will be accomplished with the Flaps at 40 or any setting greater than APPROACH but less than 100 then Vref is 1 3 times Vs1 the stall speed for FLAPS 40 Use Figure 7 9 Stall Speeds Power Idle to determine applicable stall speeds Enter the speed in the appropriate block on the TOLD card For this example the landing weight assuming an emergency return to the departure airport is 12 400 pounds a...

Page 619: ...REFERENCE LINE Maintain the same relative position between the guidelines and trace down until intersecting the aircraft weight line From that point trace horizontally to the DISTANCE FEET scale to determine the landing distance Figure 7 4 TOLD Card Example Completed g Performance Planning Cruise Recommended Cruise Power 1700 RPM charts beginning at Figure 7 38 are normally used for cruise perform...

Page 620: ...de then the temperature must be calculated using a standard lapse rate and the temperature at the departure airport In this example the temperature at the departure airport is 30 ºC The pressure altitude is 4000 feet and the ISA temperature at that pressure altitude would be 7 ºC Fuel for the mission 2175 pounds Ί fuel flow per hour 550 pounds 3 95 hours 4 00 Temperature decreases at 2 ºC per thou...

Page 621: ...TM 1 1510 218 10 Figure 7 5 Takeoff Performance Planning Tabulations Flaps 0 7 9 ...

Page 622: ...TM 1 1510 218 10 Figure 7 6 Takeoff Performance Planning Tabulations Flaps 0 7 10 ...

Page 623: ...TM 1 1510 218 10 Figure 7 7 Takeoff Performance Planning Tabulations Flaps 40 7 11 ...

Page 624: ...TM 1 1510 218 10 Figure 7 8 Takeoff Performance Planning Tabulations Flaps 40 7 12 ...

Page 625: ...TM 1 1510 218 10 Figure 7 9 Stall Speeds Power Idle 7 13 ...

Page 626: ...TM 1 1510 218 10 Figure 7 10 Temperature Conversion Correction for Compressibility 7 14 ...

Page 627: ...TM 1 1510 218 10 Figure 7 11 ISA Conversion 7 15 ...

Page 628: ...TM 1 1510 218 10 Figure 7 12 Altimeter Position Error Correction Normal System 7 16 ...

Page 629: ...TM 1 1510 218 10 Figure 7 13 Airspeed Calibration Normal System Ground Roll 7 17 ...

Page 630: ...TM 1 1510 218 10 Figure 7 14 Takeoff Gross Weight Limit Flaps 0 To Achieve 100 FPM One Engine Inoperative Rate of Climb At Liftoff 7 18 ...

Page 631: ...TM 1 1510 218 10 Figure 7 15 Takeoff Gross Weight Limit Flaps 40 To Achieve 100 FPM One Engine Inoperative Rate of Climb At Liftoff 7 19 ...

Page 632: ...TM 1 1510 218 10 Figure 7 16 Minimum Take Off Power at 2000 RPM Ice Vanes Retracted 65 Knots 7 20 ...

Page 633: ...TM 1 1510 218 10 Figure 7 17 Minimum Take Off Power at 2000 RPM Ice Vanes Extended 65 Knots 7 21 ...

Page 634: ...TM 1 1510 218 10 Figure 7 18 Takeoff Distance Flaps 0 7 22 ...

Page 635: ...TM 1 1510 218 10 Figure 7 19 Accelerate Stop Distance Flaps 0 7 23 ...

Page 636: ...TM 1 1510 218 10 Figure 7 20 Accelerate Go Distance Flaps 0 7 24 ...

Page 637: ...TM 1 1510 218 10 Figure 7 21 Takeoff Distance Flaps 40 7 25 ...

Page 638: ...TM 1 1510 218 10 Figure 7 22 Accelerate Stop Distance Flaps 40 7 26 ...

Page 639: ...TM 1 1510 218 10 Figure 7 23 Accelerate Go Distance Flaps 40 7 27 ...

Page 640: ...TM 1 1510 218 10 Figure 7 24 Line Speed Check During Takeoff Ground Run 7 28 ...

Page 641: ...TM 1 1510 218 10 Figure 7 25 Climb Two Engines Flaps 0 7 29 ...

Page 642: ...TM 1 1510 218 10 Figure 7 26 Climb Two Engines Flaps 40 7 30 ...

Page 643: ...TM 1 1510 218 10 Figure 7 27 Climb One Engine Inoperative 7 31 ...

Page 644: ...TM 1 1510 218 10 Figure 7 28 Time Fuel Distance to Cruise Climb 7 32 ...

Page 645: ...TM 1 1510 218 10 Figure 7 29 Service Ceiling One Engine Inoperative 7 33 ...

Page 646: ...TM 1 1510 218 10 Figure 7 30 Landing Distance Without Propeller Reversing Flaps 100 7 34 ...

Page 647: ...TM 1 1510 218 10 Figure 7 31 Landing Distance Without Propeller Reversing Flaps 40 7 35 ...

Page 648: ...TM 1 1510 218 10 Figure 7 32 Landing Distance Without Propeller Reversing Flaps 0 7 36 ...

Page 649: ...TM 1 1510 218 10 Figure 7 33 Landing Distance With Propeller Reversing Flaps 100 7 37 ...

Page 650: ...TM 1 1510 218 10 Figure 7 34 Landing Distance With Propeller Reversing Flaps 40 7 38 ...

Page 651: ...TM 1 1510 218 10 Figure 7 35 Landing Distance With Propeller Reversing Flaps 0 7 39 ...

Page 652: ...TM 1 1510 218 10 Figure 7 36 Stopping Distance Factors 7 40 ...

Page 653: ...TM 1 1510 218 10 Figure 7 37 Cabin Altitude for Various Airplane Altitudes 7 41 ...

Page 654: ...2 230 243 231 2 000 14 19 100 904 239 233 239 234 240 235 4 000 18 23 100 880 236 237 237 238 238 239 6 000 21 27 100 858 234 242 235 243 236 244 8 000 25 31 100 838 232 246 233 248 234 249 10 000 39 35 100 820 230 251 231 252 232 253 12 000 33 39 100 806 227 256 228 257 229 258 14 000 36 43 100 794 225 261 226 262 227 263 16 000 40 47 100 786 223 266 224 268 225 269 18 000 44 51 100 778 220 271 2...

Page 655: ... 4 000 8 13 100 880 235 240 236 241 236 242 6 000 11 17 100 858 232 245 233 246 234 247 8 000 15 21 100 840 230 250 231 251 232 252 10 000 19 25 100 824 228 254 229 255 230 257 12 000 23 29 100 808 225 259 226 261 227 262 14 000 26 33 100 796 223 264 224 266 225 267 16 000 30 37 100 788 221 270 222 271 223 272 18 000 34 41 100 782 218 275 219 276 220 278 20 000 38 45 95 740 211 274 212 276 214 278...

Page 656: ...32 249 233 250 8 000 5 11 100 842 228 253 229 254 230 255 10 000 9 15 100 842 226 257 227 259 228 260 12 000 12 19 100 812 224 262 225 264 226 265 14 000 16 23 100 800 221 268 222 269 223 270 16 000 20 27 100 792 219 273 220 274 221 276 18 000 24 31 97 768 213 275 215 277 216 279 20 000 28 35 90 714 205 272 207 275 208 277 22 000 32 38 84 666 196 270 199 273 200 275 24 000 36 42 78 618 188 367 190...

Page 657: ...846 227 255 228 257 229 258 10 000 2 5 100 818 224 260 225 262 226 263 12 000 2 9 100 812 222 265 223 267 232 268 14 000 6 13 100 802 219 271 221 272 222 274 16 000 10 17 100 792 216 276 218 277 219 279 18 000 14 21 94 744 208 274 210 276 211 278 20 000 18 25 86 688 199 271 201 273 203 276 22 000 22 28 80 642 191 268 193 271 195 274 24 000 26 32 74 596 182 265 185 268 187 272 26 000 30 36 69 552 1...

Page 658: ...000 15 9 100 852 225 258 226 259 227 261 10 000 12 5 100 832 223 263 224 265 225 266 12 000 8 1 100 818 220 269 221 270 222 274 14 000 4 2 100 804 217 273 219 275 220 276 16 000 1 7 95 760 210 273 212 275 213 277 18 000 4 11 89 714 203 272 205 274 206 276 20 000 8 15 84 666 195 270 197 273 199 275 22 000 42 18 77 620 186 267 188 270 190 273 24 000 16 22 71 574 177 262 179 266 182 270 26 000 20 26 ...

Page 659: ...26 256 227 257 228 258 8 000 26 19 100 858 223 261 225 262 226 263 10 000 22 15 100 838 221 266 222 268 223 269 12 000 18 11 98 812 217 270 218 271 220 273 14 000 14 7 93 764 211 569 212 271 213 273 16 000 10 3 88 718 203 269 205 271 206 273 18 000 6 1 83 674 295 267 297 270 199 272 20 000 2 5 78 630 187 265 190 268 192 271 22 000 2 8 73 590 179 263 182 266 184 270 24 000 6 12 67 550 171 259 174 2...

Page 660: ...882 224 259 225 260 226 261 8 000 36 29 100 856 221 263 223 264 224 266 10 000 32 25 95 810 215 264 217 266 218 267 12 000 28 21 91 766 209 264 210 266 212 268 14 000 24 17 86 720 202 263 203 266 205 268 16 000 20 13 81 676 195 262 197 265 198 267 18 000 16 9 76 634 187 261 190 264 192 267 20 000 12 5 72 594 180 259 182 263 185 266 22 000 8 2 67 556 172 256 175 261 177 265 24 000 4 2 63 518 163 25...

Page 661: ...66 220 257 222 258 223 260 8 000 42 36 94 824 215 259 217 261 218 262 10 000 39 32 90 780 210 260 211 262 212 263 12 000 35 28 86 736 203 260 205 262 206 264 14 000 31 24 81 690 196 259 198 261 200 264 16 000 27 20 76 648 189 258 191 261 193 263 18 000 23 16 72 608 181 256 184 260 186 263 20 000 19 12 67 568 173 253 176 258 179 261 22 000 14 9 63 532 165 250 169 256 172 260 24 000 10 5 59 496 156 ...

Page 662: ...TM 1 1510 218 10 Figure 7 46 Recommended Cruise Speeds 1700 RPM 7 50 ...

Page 663: ...TM 1 1510 218 10 Figure 7 47 Recommended Cruise Power 1700 RPM 7 51 ...

Page 664: ...TM 1 1510 218 10 Figure 7 48 Fuel Flow at Recommended Cruise Power 1700 RPM 7 52 ...

Page 665: ...0 14 19 100 944 244 238 245 239 245 240 4 000 17 23 100 920 242 243 242 243 243 244 6 000 21 27 100 896 239 247 240 248 241 249 8 000 25 31 100 876 237 252 238 253 239 254 10 000 29 35 100 858 235 257 TORQUE PER ENGINE 256 258 237 259 12 000 32 39 100 844 233 262 234 263 234 264 14 000 36 43 100 834 230 267 231 268 232 269 16 000 40 47 100 826 228 272 229 273 230 275 18 000 43 51 100 818 225 278 2...

Page 666: ...3 4 000 7 13 100 920 240 246 241 246 241 247 6 000 11 17 100 898 237 250 238 251 239 252 8 000 15 21 100 880 235 255 236 256 237 257 10 000 19 25 100 862 233 260 234 261 235 262 12 000 22 29 100 846 231 265 232 266 233 267 14 000 26 33 100 836 228 270 229 272 230 273 16 000 30 37 100 828 226 276 227 277 228 578 18 000 33 41 97 798 220 278 222 279 223 281 20 000 38 45 90 740 212 276 213 278 215 279...

Page 667: ...37 254 238 255 8 000 5 11 100 880 233 258 234 259 235 260 10 000 8 15 100 862 231 263 232 264 233 265 12 000 12 19 100 850 229 268 230 270 231 271 14 000 16 23 100 840 226 274 227 275 228 276 16 000 19 27 99 826 223 278 224 280 226 281 18 000 24 31 93 770 215 276 216 278 218 280 20 000 28 35 86 714 206 274 208 276 209 278 22 000 32 38 80 666 198 272 200 275 202 277 24 000 36 42 74 620 189 269 191 ...

Page 668: ... 882 232 261 233 262 234 263 10 000 2 5 100 866 229 266 230 268 231 269 12 000 2 9 100 850 227 272 228 273 229 274 14 000 6 13 100 838 225 277 226 278 227 280 16 000 9 17 96 800 218 278 220 280 221 281 18 000 14 21 89 744 210 276 211 278 213 280 20 000 18 25 82 690 201 272 202 275 204 277 22 000 22 28 76 644 192 270 194 273 196 276 24 000 26 32 71 596 183 266 186 270 188 273 26 000 30 36 65 552 17...

Page 669: ...000 16 9 100 888 230 264 231 265 232 266 10 000 12 5 100 868 228 269 229 271 230 272 12 000 8 1 100 854 225 275 226 276 227 277 14 000 4 3 96 810 219 275 220 277 221 278 16 000 0 7 90 760 212 275 213 277 214 278 18 000 4 11 85 714 204 274 206 276 207 278 20 000 8 15 79 668 196 272 198 275 200 277 22 000 12 18 74 622 187 269 190 272 191 175 24 000 16 22 68 576 178 264 181 268 183 272 26 000 20 26 6...

Page 670: ... 000 26 19 100 892 229 267 230 268 231 269 10 000 22 15 98 860 224 270 225 271 227 273 12 000 18 11 93 812 218 270 219 272 220 273 14 000 14 7 88 764 211 270 212 272 214 274 16 000 10 3 84 718 204 270 205 272 207 274 18 000 6 1 79 674 196 268 198 271 200 273 20 000 2 5 74 630 188 267 191 270 193 272 22 000 2 8 69 590 180 264 183 268 185 271 24 000 6 12 64 550 172 260 175 265 178 269 26 000 10 16 5...

Page 671: ... 262 228 263 229 264 8 000 36 29 94 856 222 264 223 265 224 266 10 000 32 25 90 810 216 264 217 266 218 268 12 000 28 21 86 766 209 265 211 267 212 268 14 000 24 17 81 720 202 264 204 266 206 268 16 000 20 13 77 676 195 263 197 266 199 268 18 000 16 9 72 634 188 262 190 265 192 268 20 000 12 5 68 594 180 260 183 264 185 267 22 000 8 2 64 556 172 257 175 262 178 266 24 000 4 2 59 520 163 252 167 25...

Page 672: ...66 220 257 222 259 223 260 8 000 42 36 89 826 216 259 217 261 218 263 10 000 39 32 85 780 210 260 212 262 213 264 12 000 35 28 81 736 203 260 205 263 207 265 14 000 31 24 76 690 196 259 198 262 200 264 16 000 27 20 72 648 189 258 191 261 193 264 18 000 23 16 68 608 181 256 184 260 182 263 20 000 19 12 64 568 173 254 177 258 179 262 22 000 15 9 60 532 165 250 169 256 172 260 24 000 10 5 56 496 156 ...

Page 673: ...TM 1 1510 218 10 Figure 7 57 Recommended Cruise Speeds 1800 RPM 7 61 ...

Page 674: ...TM 1 1510 218 10 Figure 7 58 Recommended Cruise Power 1800 RPM 7 62 ...

Page 675: ...TM 1 1510 218 10 Figure 7 59 Fuel Flow at Recommended Cruise Power 1800 RPM 7 63 ...

Page 676: ...52 239 252 240 2 000 14 19 100 976 249 243 249 244 250 244 4 000 17 23 100 954 247 248 247 248 248 249 6 000 21 27 100 932 244 252 245 253 246 254 8 000 25 31 100 914 242 257 243 258 244 259 10 000 28 35 100 898 240 262 241 263 241 264 12 000 32 39 100 884 237 267 238 268 239 269 14 000 36 43 100 874 235 272 236 274 237 275 16 000 40 47 100 866 233 278 234 279 235 280 18 000 43 51 99 856 230 286 2...

Page 677: ...2 10 000 18 25 100 900 238 265 266 240 267 12 000 22 29 100 886 235 271 272 237 273 14 000 26 33 100 878 233 276 277 235 278 16 000 29 37 100 870 231 282 283 233 284 18 000 33 41 95 826 224 282 284 226 285 20 000 37 45 88 766 215 280 NOTE TO OBTAIN FUEL FLOW PER ENGINE DIVIDE THE TOTAL FUEL FLOW VALUE FOR THE CORRESPONDING ALTITUDE BY TWO IAS 250 248 246 243 241 239 236 234 232 225 217 282 218 284...

Page 678: ...7 100 936 243 258 242 259 242 260 8 000 4 11 100 916 238 268 239 264 240 265 10 000 8 15 100 900 236 269 237 270 238 271 12 000 12 19 100 890 234 274 235 275 236 276 14 000 15 23 100 880 261 280 232 281 233 282 16 000 19 27 98 856 227 283 228 284 229 286 18 000 23 31 91 798 218 281 220 283 221 284 20 000 27 35 85 740 210 279 211 281 213 283 22 000 31 38 79 690 201 276 203 279 205 281 24 000 35 42 ...

Page 679: ...63 8 000 6 1 100 922 237 267 237 268 268 269 10 000 2 5 100 904 234 272 235 273 236 274 12 000 2 9 100 890 232 277 233 279 234 280 14 000 5 13 99 874 229 282 530 284 231 285 16 000 9 17 93 820 221 281 222 283 223 284 18 000 13 21 87 768 213 280 214 282 216 283 20 000 17 25 81 714 204 277 206 280 207 282 22 000 21 28 75 666 196 275 198 278 200 280 24 000 26 32 70 618 186 271 189 275 191 278 26 000 ...

Page 680: ...9 100 926 235 270 236 271 237 272 10 000 12 5 100 908 233 275 234 276 235 277 12 000 8 1 99 882 229 279 230 280 231 282 14 000 5 3 93 830 222 279 223 280 224 282 16 000 1 7 88 778 214 278 216 280 217 281 18 000 3 11 82 730 206 277 208 279 209 281 20 000 8 15 77 682 198 275 200 277 202 280 22 000 12 18 72 238 189 272 192 275 194 278 24 000 16 22 66 592 180 268 183 272 186 275 26 000 20 26 61 550 17...

Page 681: ...8 238 269 8 000 26 19 400 930 233 272 234 274 235 275 10 000 22 18 96 882 227 274 228 275 230 276 12 000 18 11 91 834 220 274 222 275 223 277 14 000 14 7 86 784 213 274 215 276 216 277 16 000 10 3 82 736 206 273 208 275 210 277 18 000 6 1 77 690 199 272 201 274 203 277 20 000 2 5 72 646 191 270 193 273 195 276 22 000 2 8 67 604 182 267 185 271 188 274 24 000 6 12 62 564 174 263 177 268 180 272 26 ...

Page 682: ... 230 265 231 266 232 268 8 000 36 29 92 880 225 267 226 268 227 270 10 000 32 25 88 834 219 268 220 270 221 271 12 000 28 21 84 786 212 268 214 270 215 272 14 000 24 17 80 738 205 267 207 270 208 272 16 000 20 13 75 694 198 367 200 269 201 272 18 000 16 9 71 652 190 265 193 269 195 271 20 000 12 5 66 608 183 263 185 267 188 270 22 000 8 2 62 570 175 261 178 265 180 269 24 000 4 2 58 532 166 257 17...

Page 683: ...90 224 261 225 262 226 264 8 000 43 36 87 848 219 263 220 265 221 266 10 000 39 32 84 502 213 264 214 266 216 268 12 000 35 28 80 756 206 264 208 266 210 268 14 000 31 22 75 710 199 263 201 266 203 268 16 000 27 18 71 666 192 262 194 265 196 268 18 000 23 14 67 624 184 260 187 264 189 267 20 000 19 10 62 584 176 258 179 262 182 266 22 000 15 7 59 546 168 255 172 260 175 264 24 000 11 3 55 510 160 ...

Page 684: ...TM 1 1510 218 10 Figure 7 68 Maximum Cruise Speeds 1900 RPM 7 72 ...

Page 685: ...TM 1 1510 218 10 Figure 7 69 Maximum Cruise Power 1900 PRM 7 73 ...

Page 686: ...TM 1 1510 218 10 Figure 7 70 Fuel Flow at Maximum Cruise Power 1900 RPM 7 74 ...

Page 687: ...TM 1 1510 218 10 Figure 7 71 Maximum Range Power 1700 RPM ISA 30 C 7 75 ...

Page 688: ...TM 1 1510 218 10 Figure 7 72 Maximum Range Power 1700 RPM ISA 20 C 7 76 ...

Page 689: ...TM 1 1510 218 10 Figure 7 73 Maximum Range Power 1700 RPM ISA 10 C 7 77 ...

Page 690: ...TM 1 1510 218 10 Figure 7 74 Maximum Range Power 1700 RPM ISA 7 78 ...

Page 691: ...TM 1 1510 218 10 Figure 7 75 Maximum Range Power 1700 RPM ISA 10 C 7 79 ...

Page 692: ...TM 1 1510 218 10 Figure 7 76 Maximum Range Power 1700 RPM ISA 20 C 7 80 ...

Page 693: ...TM 1 1510 218 10 Figure 7 77 Maximum Range Power 1700 RPM ISA 30 C 7 81 ...

Page 694: ...TM 1 1510 218 10 Figure 7 78 Maximum Range Power 1700 RPM ISA 37 C 7 82 ...

Page 695: ... 000 16 19 100 500 189 185 191 187 192 188 4 000 20 23 100 488 186 188 188 190 190 191 6 000 23 27 100 477 184 191 186 193 188 195 8 000 27 31 100 467 182 194 184 196 186 198 10 000 31 35 100 458 179 197 182 199 184 202 12 000 35 39 100 452 177 200 179 203 181 205 14 000 39 43 100 448 171 203 177 206 179 209 16 000 43 47 96 431 168 202 171 206 174 209 18 000 47 51 90 401 159 198 163 203 167 207 20...

Page 696: ...3 100 489 185 190 187 192 189 194 6 000 13 17 100 478 182 193 184 195 186 197 8 000 17 21 100 467 180 196 182 198 184 200 10 000 21 25 100 460 177 199 180 202 182 204 12 000 25 29 100 454 175 202 177 205 180 207 14 000 29 33 99 445 171 203 174 207 177 210 16 000 33 37 92 416 162 199 166 204 169 208 18 000 37 41 86 387 153 195 158 201 162 205 20 000 41 45 80 360 143 188 149 196 154 202 22 000 45 48...

Page 697: ... 4 000 1 3 100 490 183 191 185 194 187 196 6 000 3 7 100 479 181 195 183 197 185 199 8 000 7 11 100 469 178 198 181 200 183 203 10 000 11 15 100 461 175 201 178 204 180 206 12 000 15 19 100 455 173 204 175 207 178 209 14 000 19 23 95 430 165 201 169 205 172 209 16 000 23 27 86 401 157 197 161 202 164 206 18 000 27 31 82 374 147 191 153 198 157 203 20 000 31 35 76 347 135 182 143 192 148 199 22 000...

Page 698: ... 194 4 000 11 7 100 494 181 193 184 196 186 198 6 000 7 3 100 482 179 196 181 199 184 201 8 000 3 1 100 472 176 200 179 202 181 205 10 000 1 5 462 100 174 202 176 205 179 208 12 000 5 9 97 445 168 203 172 206 174 210 14 000 9 13 91 416 160 199 164 204 167 208 16 000 13 17 85 388 151 194 456 200 160 205 18 000 17 20 79 361 141 187 147 195 152 201 20 000 21 25 73 334 126 173 137 188 143 196 22 000 2...

Page 699: ...11 182 192 185 194 187 196 4 000 21 17 100 497 180 195 182 198 184 200 6 000 17 13 100 485 177 198 180 201 182 203 8 000 13 9 100 474 175 201 177 204 180 207 10 000 9 5 96 449 168 100 172 204 174 207 12 000 5 1 91 422 161 197 165 202 168 206 14 000 1 3 85 396 153 194 188 199 161 204 16 000 7 11 75 347 133 179 141 191 147 198 18 000 12 15 70 322 131 183 138 193 20 000 12 15 70 322 131 183 138 193 2...

Page 700: ... 514 181 194 183 196 185 198 4 000 31 27 100 499 178 196 181 199 183 202 6 000 27 23 97 476 173 197 176 200 189 203 8 000 23 19 93 451 167 196 171 200 173 203 10 000 19 15 88 425 160 194 164 199 167 202 12 000 15 11 84 400 153 191 157 196 161 201 14 000 11 7 79 375 144 186 150 193 154 199 16 000 7 3 74 352 134 179 142 189 147 196 18 000 2 1 70 329 132 183 139 192 20 000 2 5 65 306 119 170 131 186 ...

Page 701: ... 2 000 44 41 94 496 174 190 177 193 179 195 4 000 41 27 92 475 170 191 173 194 176 197 6 000 37 33 89 453 165 191 169 195 171 198 8 000 33 29 86 429 159 190 163 195 166 198 10 000 29 25 82 404 152 187 157 193 160 197 12 000 25 21 77 379 144 183 150 190 154 196 14 000 20 17 73 355 134 176 142 186 147 193 16 000 16 13 69 333 133 180 141 189 18 000 12 9 64 311 121 170 131 185 20 000 7 5 58 287 121 17...

Page 702: ...84 175 187 177 189 2 000 51 48 87 477 168 185 171 188 174 191 4 000 47 44 86 457 164 186 167 190 170 193 6 000 43 40 84 437 159 186 163 191 166 194 8 000 40 36 81 414 153 185 158 190 161 194 10 000 35 32 77 390 146 182 151 188 155 193 12 000 31 28 73 366 137 176 144 185 149 191 14 000 27 24 69 342 124 165 135 180 142 188 16 000 23 20 65 320 125 171 134 184 18 000 18 16 59 295 124 177 20 000 22 000...

Page 703: ...e below the projected line For instance if the projected line intersects the reference line in the ratio of 30 down 70 up between the guidelines then maintain this same 30 70 relationship between the guidelines all the way to the next item a Conditions At Airport Alpha AAA OAT 85 F 30 C Field Elevation 3800 feet c The Airspeed Calibration Normal System Takeoff Ground Roll graph was used to obtain ...

Page 704: ...Complete the card as follows 1 Field Length Available is 6 000 feet Figure 7A 1 TOLD Card Back NOTE If the runway has an approved runway overrun that distance may be added to the runway length for Accelerate Stop calculations 3 Pressure Altitude PA To determine the PA add 1000 feet to field elevation for each 1 00 in Hg that the reported altimeter setting value is below 29 92 in Hg and subtract 10...

Page 705: ...llow accomplishment of an acceleration to V1 and stop The maximum allowable takeoff weight is 12 800 pounds Using Figure 7A 26 utilize the chart in the same manner In this case the point on the REFERENCE LINE for Flaps APPROACH is below the 6000 feet field length line the accelerate stop distance is 5 100 feet and accelerate stop can be accomplished at 14 000 pounds For Flaps UP the maximum takeof...

Page 706: ... completed back side of the TOLD card is now used for determining the takeoff configuration Flaps 0 or 40 and the fuel load in order to maintain the aircraft at the maximum allowable weight for all of the conditions 1 For this example the takeoff can be accomplished at an aircraft weight of 12 600 pounds with the flaps UP or at APPROACH This takeoff is planned with Flaps UP at 12 600 pounds Figure...

Page 707: ... accelerate go distance Figure 7A 3 TOLD Card Front In this example the takeoff weight is planned at 12 600 pounds The accelerate go distance is 8 800 feet 1 thru 5 were determined on the back side of the card and transposed to these blocks Enter the distance 8 800 feet in the appropriate block on the TOLD card 6 Minimum Takeoff Power Use Figure 7A 17 Minimum Takeoff Power at 2000 RPM with Ice Van...

Page 708: ... stall speed for FLAPS APPROACH Use Figure 7A 13 Stall Speeds Power Idle to determine applicable stall speeds Enter the speed in the appropriate block on the TOLD card For this example the landing weight assuming an emergency return to the departure airport is 12 600 pounds A landing with the Flaps DOWN is planned The Vso for a 12 600 pound aircraft is 75 KIAS Therefore Vref is 1 3 times 75 97 5 a...

Page 709: ...til intersecting the correct PRESSURE ALTITUDE FEET line 4000 feet Trace horizontally to the right until intersecting the first REFERENCE LINE Maintain the same relative position between the guidelines and trace down until intersecting the aircraft weight line From that point trace horizontally to the DISTANCE FEET scale to determine the landing distance For this example the landing weight is 12 6...

Page 710: ...ropriate cruise chart will suffice Therefore for this example the total fuel in hours and minutes for entry on the DD Form 175 is 3 24 hours 2 If a weather forecast does not include a temperature at the cruise altitude then the temperature must be calculated using a standard lapse rate and the temperature at the departure airport In this example the temperature at the departure airport is 30 ºC Th...

Page 711: ...TM 1 1510 218 10 7A 9 Figure 7A 5 Airspeed Calibration Normal System Takeoff Ground Roll ...

Page 712: ...TM 1 1510 218 10 7A 10 Figure 7A 6 Airspeed Calibration Normal System ...

Page 713: ...TM 1 1510 218 10 7A 11 Figure 7A 7 Altimeter Correction Normal System ...

Page 714: ...TM 1 1510 218 10 7A 12 Figure 7A 8 Airspeed Calibration Alternate System ...

Page 715: ...TM 1 1510 218 10 7A 13 Figure 7A 9 Altimeter Correction Alternate System ...

Page 716: ...TM 1 1510 218 10 7A 14 Figure 7A 10 Indicated Outside Air Temperature Correction ISA ...

Page 717: ...TM 1 1510 218 10 7A 15 Figure 7A 11 ISA Conversion ...

Page 718: ...TM 1 1510 218 10 7A 16 Figure 7A 12 Fahrenheit to Celsius Temperature Conversion ...

Page 719: ...TM 1 1510 218 10 7A 17 Figure 7A 13 Stall Speeds Power Idle ...

Page 720: ...TM 1 1510 218 10 7A 18 Figure 7A 14 Cabin Altitude for Various Airplane Altitudes ...

Page 721: ...TM 1 1510 218 10 7A 19 Figure 7A 15 Takeoff Weight to Achieve Positive One Engine Inoperative Climb at Lift Off Flaps UP ...

Page 722: ...TM 1 1510 218 10 7A 20 Figure 7A 16 Takeoff Weight to Achieve Positive One Engine Inoperative Climb at Lift Off Flaps APPROACH ...

Page 723: ...TM 1 1510 218 10 7A 21 Figure 7A 17 Minimum Takeoff Power at 2000 RPM With Ice Vanes Retracted 65 Knots ...

Page 724: ...TM 1 1510 218 10 7A 22 Figure 7A 18 Minimum Takeoff Power With Ice Vanes Extended 65 Knots ...

Page 725: ...TM 1 1510 218 10 7A 23 Figure 7A 19 Takeoff Flight Path ...

Page 726: ...TM 1 1510 218 10 7A 24 Figure 7A 20 Wind Component ...

Page 727: ...TM 1 1510 218 10 7A 25 Figure 7A 21 Take Off Distance Flaps UP ...

Page 728: ...TM 1 1510 218 10 7A 26 Figure 7A 22 Accelerate Stop Flaps UP ...

Page 729: ...TM 1 1510 218 10 7A 27 Figure 7A 23 Accelerate Go Flaps UP ...

Page 730: ...TM 1 1510 218 10 7A 28 Figure 7A 24 Net Gradient of Climb Flaps UP ...

Page 731: ...TM 1 1510 218 10 7A 29 Figure 7A 25 Take off Distance Flaps APPROACH ...

Page 732: ...TM 1 1510 218 10 7A 30 Figure 7A 26 Accelerate Stop Flaps APPROACH ...

Page 733: ...TM 1 1510 218 10 7A 31 Figure 7A 27 Accelerate Go Flaps APPROACH ...

Page 734: ...TM 1 1510 218 10 7A 32 Figure 7A 28 Net Gradient of Climb Flaps APPROACH ...

Page 735: ...TM 1 1510 218 10 7A 33 Figure 7A 29 Climb Two Engines Flaps UP ...

Page 736: ...TM 1 1510 218 10 7A 34 Figure 7A 30 Climb Two Engines Flaps APPROACH ...

Page 737: ...TM 1 1510 218 10 7A 35 Figure 7A 31 Climb One Engine Inoperative ...

Page 738: ...TM 1 1510 218 10 7A 36 Figure 7A 32 Service Ceiling One Engine Inoperative ...

Page 739: ...TM 1 1510 218 10 7A 37 Figure 7A 33 Time Fuel and Distance to Climb ...

Page 740: ...41 229 242 230 242 231 2000 14 19 100 906 237 232 238 233 239 234 240 235 4000 18 23 100 882 235 236 236 237 237 238 238 239 6000 22 27 100 858 233 241 234 242 235 243 236 244 8000 25 31 100 834 231 245 232 246 233 248 234 249 10 000 29 35 100 814 228 250 230 251 231 252 231 235 12 000 33 39 100 794 226 255 227 256 228 257 229 258 14 000 36 43 100 780 224 259 225 261 226 262 227 263 16 000 40 47 1...

Page 741: ...238 4000 8 13 100 880 233 239 234 240 235 241 236 242 6000 11 17 100 858 231 244 232 245 233 246 234 247 8000 15 21 100 838 229 248 230 250 231 251 232 252 10 000 19 25 100 818 226 253 228 254 229 255 230 257 12 000 23 29 100 796 224 258 225 259 226 260 227 262 14 000 26 33 100 782 222 263 223 264 224 266 225 267 16 000 30 37 100 772 219 268 221 270 222 271 223 272 18 000 34 41 100 764 216 273 218...

Page 742: ...0 862 229 247 231 248 232 249 232 250 8000 5 11 100 840 227 251 228 253 229 254 230 255 10 000 9 15 100 818 225 256 226 257 227 259 228 260 12 000 12 19 100 800 222 261 223 262 225 264 226 265 14 000 16 23 100 786 220 266 221 268 222 269 223 270 16 000 20 27 100 776 217 271 218 273 220 274 222 276 18 000 24 31 100 768 214 276 216 278 217 279 218 281 20 000 27 35 96 734 208 276 210 279 211 281 213 ...

Page 743: ...3 8000 5 1 100 844 225 254 226 255 228 257 228 258 10 000 1 5 100 822 223 259 224 260 225 262 226 263 12 000 2 9 100 800 220 264 222 266 223 267 224 286 14 000 6 13 100 786 218 269 220 271 221 272 222 274 16 000 10 17 100 776 215 274 216 276 218 277 219 279 18 000 14 21 96 742 208 274 210 276 212 279 213 280 20 000 18 25 92 706 202 274 204 277 206 279 207 281 22 000 21 29 87 672 195 274 197 277 19...

Page 744: ... 100 848 224 257 225 258 226 259 227 261 10 000 12 5 100 826 221 262 222 263 224 265 225 266 12 000 8 1 100 804 219 267 220 269 221 270 222 271 14 000 4 3 100 790 216 272 217 273 219 275 220 276 16 000 0 7 97 756 210 273 212 275 213 277 215 279 18 000 4 11 92 714 203 273 205 275 207 277 208 279 20 000 8 15 88 680 197 273 199 276 201 278 202 281 22 000 12 19 83 648 189 271 192 275 194 278 196 281 2...

Page 745: ...58 8000 25 19 100 854 222 260 223 261 224 262 225 263 10 000 22 15 100 832 220 265 221 266 222 268 223 269 12 000 18 11 99 806 216 269 218 271 219 272 220 274 14 000 14 7 95 762 210 269 212 271 213 273 215 274 16 000 10 3 91 722 203 269 205 272 207 274 209 276 18 000 6 1 87 682 197 269 199 272 201 275 202 277 20 000 2 5 84 654 191 270 194 273 195 276 197 279 22 000 2 9 80 624 184 270 187 274 189 2...

Page 746: ... 261 8000 36 29 100 858 221 262 222 264 223 265 224 266 10 000 32 25 97 818 216 264 217 266 219 268 220 269 12 000 28 21 93 764 209 264 211 266 212 268 214 270 14 000 24 17 89 724 203 265 205 267 206 269 208 271 16 000 20 13 85 686 196 265 198 268 200 270 202 272 18 000 16 9 81 650 190 265 192 268 194 271 197 273 20 000 12 5 79 626 185 266 187 270 189 273 191 276 22 000 8 1 77 602 179 267 182 271 ...

Page 747: ...259 223 260 224 262 225 263 8000 42 36 96 838 216 260 218 262 219 263 220 265 10 000 39 32 93 790 210 261 212 263 214 265 215 267 12 000 35 28 88 738 204 261 205 263 207 265 209 267 14 000 31 24 84 700 197 261 200 264 201 266 203 268 16 000 27 20 81 664 191 261 194 265 196 267 198 270 18 000 23 16 76 630 185 261 188 265 190 268 192 271 20 000 19 12 76 606 180 263 183 267 185 270 187 273 22 000 15 ...

Page 748: ...TM 1 1510 218 10 7A 46 Figure 7A 42 Normal Cruise Speeds 1700 RPM ...

Page 749: ...TM 1 1510 218 10 7A 47 Figure 7A 43 Normal Cruise Power 1700 RPM ...

Page 750: ...TM 1 1510 218 10 7A 48 Figure 7A 44 Fuel Flow At Normal Cruise Power 1700 RPM ...

Page 751: ...TM 1 1510 218 10 7A 49 Figure 7A 45 Range Profile Normal Cruise Power 1700 RPM ...

Page 752: ...41 229 242 230 242 231 2000 14 19 100 906 237 232 238 233 239 234 240 235 4000 18 23 100 882 235 236 236 237 237 238 238 239 6000 22 27 100 858 233 241 234 242 235 243 236 244 8000 25 31 100 834 231 245 232 246 233 248 234 249 10 000 29 35 100 814 228 250 230 251 231 252 231 235 12 000 33 39 100 794 226 255 227 256 228 257 229 258 14 000 36 43 100 780 224 259 225 261 226 262 227 263 16 000 40 47 1...

Page 753: ...238 4000 8 13 100 880 233 239 234 240 235 241 236 242 6000 11 17 100 858 231 244 232 245 233 246 234 247 8000 15 21 100 838 229 248 230 250 231 251 232 252 10 000 19 25 100 818 226 253 228 254 229 225 230 257 12 000 23 29 100 796 224 258 225 259 226 260 227 262 14 000 26 33 100 782 222 263 223 264 224 266 225 267 16 000 30 37 100 772 220 268 221 270 222 271 223 272 18 000 34 41 100 764 216 273 218...

Page 754: ...0 862 229 247 231 248 232 249 232 250 8000 5 11 100 840 227 251 228 253 229 254 230 255 10 000 9 15 100 818 225 256 226 257 227 259 228 260 12 000 12 19 100 800 222 261 223 262 225 264 226 265 14 000 16 23 100 786 220 266 221 268 222 269 223 270 16 000 20 27 100 776 217 271 218 273 220 274 221 276 18 000 24 31 100 768 214 276 216 278 217 279 218 281 20 000 27 35 100 762 211 281 213 283 214 285 215...

Page 755: ...00 5 1 100 844 225 254 226 255 228 257 228 258 10 000 1 5 100 822 223 259 224 260 225 262 226 263 12 000 2 9 100 800 220 264 222 266 223 267 224 286 14 000 6 13 100 786 218 269 219 271 221 272 222 274 16 000 10 17 100 776 215 274 216 276 218 277 219 279 18 000 13 21 100 772 212 278 213 281 215 282 217 284 20 000 17 25 96 734 205 279 207 281 209 283 210 285 22 000 21 29 91 698 199 274 200 281 202 2...

Page 756: ... 100 848 224 257 225 258 226 259 227 261 10 000 12 5 100 826 221 262 222 263 224 265 225 266 12 000 8 1 100 804 219 267 220 269 221 270 222 271 14 000 4 3 100 790 216 272 217 273 219 275 220 276 16 000 0 7 100 778 213 277 214 278 216 280 217 282 18 000 3 11 96 740 206 277 209 279 210 281 211 283 20 000 7 15 92 706 200 277 202 280 204 282 205 285 22 000 11 19 87 672 192 276 195 279 197 282 199 285 ...

Page 757: ... 25 19 100 854 222 260 223 261 224 262 225 263 10 000 22 15 100 832 220 265 221 266 222 268 223 269 12 000 18 11 100 810 217 270 218 271 220 273 221 274 14 000 14 7 98 780 212 272 214 274 215 276 217 278 16 000 10 3 94 744 206 273 208 275 210 278 211 279 18 000 6 1 91 708 200 274 202 276 204 279 206 281 20 000 3 5 87 678 194 274 196 277 198 280 200 283 22 000 1 9 83 646 187 274 190 278 192 281 995...

Page 758: ... 261 8000 36 29 100 858 221 262 222 264 223 265 224 266 10 000 32 25 99 830 216 266 219 268 220 270 221 271 12 000 28 21 94 774 210 266 212 268 213 270 215 271 14 000 24 17 91 740 205 267 206 269 208 272 210 273 16 000 20 13 88 706 199 268 201 271 203 273 204 275 18 000 16 9 85 674 193 269 195 272 197 275 199 277 20 000 12 5 83 650 188 271 190 274 193 277 194 288 22 000 8 1 79 620 181 271 184 275 ...

Page 759: ...5 263 8000 43 36 98 846 217 261 219 263 220 265 221 266 10 000 39 32 94 798 211 262 213 264 215 266 216 268 12 000 35 28 89 744 204 262 206 264 208 266 209 268 14 000 31 24 86 712 200 264 201 266 203 269 205 270 16 000 27 20 84 680 194 265 196 268 198 270 200 273 18 000 23 16 81 650 188 266 191 269 193 271 195 275 20 000 19 12 79 628 183 267 186 271 188 274 190 277 22 000 15 8 76 602 177 267 180 2...

Page 760: ...TM 1 1510 218 10 Figure 7A 54 Maximum Cruise Speeds 1700 RPM 7A 58 ...

Page 761: ...TM 1 1510 218 10 Figure 7A 55 Maximum Cruise Power 1700 RPM 7A 59 ...

Page 762: ...TM 1 1510 218 10 Figure 7A 56 Fuel Flow At Maximum Cruise Power 1700 RPM 7A 60 ...

Page 763: ...TM 1 1510 218 10 Figure 7A 57 Range Profile Maximum Cruise Power 1700 RPM 7A 61 ...

Page 764: ... 244 232 244 232 2000 14 19 100 946 243 237 244 238 244 238 244 238 4000 18 23 100 920 241 242 241 243 242 243 243 244 6000 21 27 100 896 238 246 239 247 240 248 241 249 8000 25 31 100 874 236 251 237 252 238 253 239 254 10 000 29 35 100 854 233 255 235 257 236 258 236 259 12 000 32 39 100 834 231 260 232 262 233 263 234 264 14 000 36 43 100 820 229 266 230 267 231 268 232 269 16 000 40 47 100 808...

Page 765: ...000 7 13 100 922 239 245 240 246 241 246 241 247 6000 11 17 100 898 236 249 237 250 238 251 239 252 8000 15 21 100 876 234 254 235 255 236 256 237 257 10 000 19 25 100 856 232 259 233 260 234 261 235 262 12 000 22 29 100 834 229 264 230 265 231 266 232 267 14 000 26 33 100 822 227 269 228 270 230 272 230 273 16 000 30 37 100 810 224 274 226 276 227 277 228 278 18 000 33 41 100 800 222 280 223 281 ...

Page 766: ... 234 252 236 253 237 254 237 255 8000 5 11 100 878 232 257 233 258 234 259 235 260 10 000 8 15 100 856 230 262 231 263 232 264 233 265 12 000 12 19 100 838 227 267 229 268 230 270 231 271 14 000 16 23 100 824 225 272 226 274 227 275 228 276 16 000 19 27 100 812 222 278 224 279 225 281 226 282 18 000 23 31 96 776 216 279 218 281 219 283 221 284 20 000 27 35 92 734 210 279 211 281 213 283 214 285 22...

Page 767: ... 1 100 880 230 260 232 261 233 262 234 263 10 000 2 5 100 858 228 265 229 266 230 267 231 269 12 000 2 9 100 838 226 270 227 272 228 273 229 274 14 000 6 13 100 882 223 275 224 277 226 278 227 280 16 000 9 17 97 792 218 278 219 279 221 281 222 283 18 000 13 21 91 744 210 276 212 279 213 281 215 282 20 000 17 25 87 708 204 277 206 279 207 282 209 284 22 000 21 29 83 672 197 277 199 280 201 283 203 ...

Page 768: ...886 229 263 230 264 231 265 232 266 10 000 12 5 100 862 226 268 228 269 229 270 230 272 12 000 8 1 100 840 224 273 225 275 226 276 227 277 14 000 4 3 97 802 218 275 220 277 221 278 222 280 16 000 0 7 92 756 212 275 213 277 215 279 216 281 18 000 4 11 88 714 205 275 207 277 208 280 210 281 20 000 7 15 84 682 199 275 201 278 203 281 204 283 22 000 11 19 80 648 191 275 194 278 196 281 198 283 24 000 ...

Page 769: ...000 26 19 100 890 227 266 228 267 230 268 230 269 10 000 22 15 99 862 224 270 225 271 227 273 228 274 12 000 18 11 94 806 217 270 219 271 220 273 221 275 14 000 14 7 90 762 211 270 213 273 214 274 215 276 16 000 10 3 86 722 205 271 207 273 208 276 210 277 18 000 6 1 83 682 198 271 200 274 202 276 204 279 20 000 2 5 80 656 193 273 195 276 197 279 199 281 22 000 1 9 77 626 187 273 189 277 191 280 19...

Page 770: ...8000 36 29 96 868 222 264 224 266 225 267 226 268 10 000 32 25 92 818 216 265 218 267 219 269 220 270 12 000 28 21 88 766 209 265 211 267 213 269 214 271 14 000 24 17 84 724 203 265 205 268 207 270 208 272 16 000 20 13 81 686 197 266 199 269 201 271 203 273 18 000 16 9 77 652 191 267 194 270 196 273 197 275 20 000 12 5 75 626 186 269 189 272 191 275 193 278 22 000 8 1 73 602 181 270 184 274 186 27...

Page 771: ...2 226 263 8000 43 36 91 838 217 260 218 262 220 264 221 265 10 000 39 32 88 792 211 262 213 264 214 266 215 267 12 000 35 28 83 738 204 261 206 264 208 266 209 268 14 000 31 24 80 700 198 262 200 265 202 267 203 269 16 000 27 20 77 664 192 262 194 265 196 268 198 270 18 000 23 16 74 630 186 263 189 266 191 269 193 272 20 000 19 12 72 606 181 265 184 269 186 272 188 275 22 000 15 8 70 584 176 266 1...

Page 772: ...TM 1 1510 218 10 Figure 7A 66 Normal Cruise Speeds 1800 RPM 7A 70 ...

Page 773: ...TM 1 1510 218 10 Figure 7A 67 Normal Cruise Power 1800 RPM 7A 71 ...

Page 774: ...TM 1 1510 218 10 Figure 7A 68 Fuel Flow at Normal Cruise Power 1800 RPM 7A 72 ...

Page 775: ...TM 1 1510 218 10 Figure 7A 69 Range Profile Normal Cruise Power 1800 RPM 7A 73 ...

Page 776: ... 244 232 244 232 2000 14 19 100 946 243 237 244 238 244 238 244 238 4000 18 23 100 920 241 242 241 243 242 243 243 244 6000 22 27 100 896 238 246 239 247 240 248 241 249 8000 25 31 100 874 236 251 237 252 238 253 239 254 10 000 29 35 100 854 233 255 235 257 236 258 236 259 12 000 33 39 100 834 231 260 232 262 233 263 234 264 14 000 36 43 100 820 229 265 230 267 231 268 232 269 16 000 40 47 100 808...

Page 777: ...000 8 13 100 922 239 245 240 246 241 246 241 247 6000 11 17 100 898 236 249 237 250 238 251 239 252 8000 15 21 100 876 234 254 235 255 236 256 237 257 10 000 19 25 100 856 232 259 233 260 234 261 235 262 12 000 23 29 100 834 229 264 230 265 231 266 232 267 14 000 26 33 100 822 227 269 228 270 230 272 230 273 16 000 30 37 100 810 224 274 226 276 227 277 228 278 18 000 34 41 100 800 222 280 223 281 ...

Page 778: ... 234 252 236 253 237 254 237 255 8000 5 11 100 878 232 257 233 258 234 259 235 260 10 000 9 15 100 856 230 262 231 263 232 264 233 265 12 000 12 19 100 838 227 267 229 268 230 270 231 271 14 000 16 23 100 824 225 272 226 274 227 275 228 276 16 000 20 27 100 812 222 278 224 279 225 281 226 282 18 000 24 31 100 802 220 283 221 285 223 287 223 288 20 000 27 35 96 764 213 284 215 286 217 288 218 289 2...

Page 779: ...1 100 844 230 260 232 261 233 262 234 263 10 000 1 5 100 822 228 265 229 266 230 267 231 269 12 000 2 9 100 800 226 270 227 272 228 273 229 274 14 000 6 13 100 786 223 275 224 277 226 278 227 280 16 000 10 17 100 776 221 281 222 283 223 284 224 285 18 000 13 21 95 772 213 281 216 283 217 285 218 287 20 000 17 25 91 734 207 282 209 284 211 286 212 288 22 000 21 29 87 698 201 282 203 284 204 287 206...

Page 780: ...886 229 263 230 264 231 265 232 266 10 000 12 5 100 862 226 268 228 269 229 270 230 272 12 000 8 1 100 840 224 273 225 275 226 276 227 277 14 000 5 3 100 824 221 278 223 280 224 282 225 283 16 000 1 7 96 782 215 279 216 281 218 283 219 284 18 000 3 11 91 742 208 279 210 282 212 284 213 286 20 000 7 15 88 708 202 280 204 283 206 285 207 287 22 000 11 19 83 672 195 279 197 282 199 285 201 288 24 000...

Page 781: ... 890 227 266 228 267 230 268 230 269 10 000 22 15 100 868 225 271 226 272 227 273 228 275 12 000 18 11 96 820 219 272 220 274 222 275 223 277 14 000 14 7 93 780 213 274 215 276 216 277 218 279 16 000 10 3 90 744 208 275 210 277 211 279 213 281 18 000 7 1 86 710 202 276 204 279 206 281 207 283 20 000 3 5 83 678 196 277 198 280 200 283 202 285 22 000 1 9 80 648 190 278 192 281 194 284 996 287 24 000...

Page 782: ...8000 36 29 98 878 224 266 225 267 226 269 227 270 10 000 32 25 94 830 218 267 219 269 221 270 222 272 12 000 28 21 89 774 211 267 212 269 214 270 215 272 14 000 24 17 86 740 205 268 207 271 209 273 210 275 16 000 20 13 84 706 200 270 202 273 204 275 205 277 18 000 16 9 81 674 195 272 197 275 199 277 201 279 20 000 13 5 78 650 190 274 182 277 194 280 196 283 22 000 9 1 76 622 184 274 187 278 189 28...

Page 783: ...000 43 36 92 846 218 262 219 264 221 265 222 267 10 000 39 32 89 798 212 263 214 265 215 267 216 268 12 000 35 28 84 746 205 263 207 265 209 267 210 269 14 000 31 24 82 712 200 264 202 267 204 269 205 271 16 000 27 20 79 682 195 266 197 269 199 272 201 274 18 000 23 16 77 650 190 268 192 271 194 274 196 276 20 000 19 12 75 628 185 2670 187 274 190 277 192 280 22 000 15 8 73 602 179 271 182 275 185...

Page 784: ...TM 1 1510 218 10 Figure 7A 78 Maximum Cruise Speeds 1800 RPM 7A 82 ...

Page 785: ...TM 1 1510 218 10 Figure 7A 79 Maximum Cruise Power 1800 RPM 7A 83 ...

Page 786: ...TM 1 1510 218 10 7A 84 Figure 7A 80 Fuel Flow At Maximum Cruise Power 1800 RPM ...

Page 787: ...TM 1 1510 218 10 Figure 7A 81 Range Profile Maximum Cruise Power 1800 RPM 7A 85 ...

Page 788: ... PER ENGINE FUEL FLOW TOTAL IAS TAS TORQUE PER ENGINE FUEL FLOW TOTAL IAS TAS FEET qC qC LB HR KTS KTS LB HR KTS KTS SL 11 15 73 788 210 200 69 768 207 197 2 000 15 19 67 730 201 197 64 710 199 195 4 000 20 23 63 674 194 195 59 654 191 192 6 000 24 27 59 628 187 194 55 604 184 191 8 000 28 31 56 584 181 193 52 560 177 189 10 000 32 35 54 546 175 193 49 520 171 189 12 000 35 39 53 516 171 194 48 48...

Page 789: ... PER ENGINE FUEL FLOW TOTAL IAS TAS TORQUE PER ENGINE FUEL FLOW TOTAL IAS TAS FEET qC qC LB HR KTS KTS LB HR KTS KTS SL 11 15 66 734 205 195 63 736 203 193 2 000 15 19 61 694 197 192 57 672 194 190 4 000 20 23 55 632 188 189 51 612 184 186 6 000 24 27 51 580 180 187 47 556 176 183 8 000 28 31 48 534 173 185 43 510 169 180 10 000 32 35 45 492 167 184 40 466 162 179 12 000 35 39 43 458 162 184 38 43...

Page 790: ...NE FUEL FLOW TOTAL IAS TAS FEET qC qC LB HR KTS KTS LB HR KTS KTS SL 1 5 77 814 214 207 74 796 211 205 2 000 5 9 72 758 206 205 67 734 202 201 4 000 9 13 67 702 197 202 63 678 194 199 6 000 13 17 63 654 191 201 59 632 187 198 8 000 17 21 60 612 185 201 56 588 181 197 10 000 21 25 57 568 178 200 53 544 175 196 12 000 25 29 56 540 174 201 52 514 170 197 14 000 29 33 55 514 170 202 50 486 166 198 16 ...

Page 791: ...NE FUEL FLOW TOTAL IAS TAS FEET qC qC LB HR KTS KTS LB HR KTS KTS SL 1 5 70 776 208 202 67 760 206 200 2 000 5 9 64 716 199 199 61 698 197 196 4 000 9 13 59 660 191 196 56 642 189 194 6 000 13 17 56 612 185 195 52 592 182 192 8 000 17 21 52 568 178 194 49 546 175 191 10 000 21 25 49 522 171 192 45 500 168 188 12 000 25 29 47 490 167 193 43 466 163 188 14 000 29 33 46 460 162 193 41 434 157 187 16 ...

Page 792: ...LB HR KTS KTS SL 9 5 80 830 216 213 76 810 213 210 2 000 5 1 76 782 209 212 72 760 206 209 4 000 1 3 71 728 201 210 67 704 198 207 6 000 3 7 67 678 194 209 63 656 191 205 8 000 7 11 64 634 188 208 60 610 184 204 10 000 11 15 61 590 181 207 57 566 178 203 12 000 15 19 60 562 177 209 55 536 173 204 14 000 19 23 58 534 173 210 53 506 168 205 16 000 23 27 57 514 169 212 52 482 164 206 18 000 27 31 57 ...

Page 793: ...LB HR KTS KTS SL 9 5 73 790 210 207 69 774 207 205 2 000 5 1 68 740 203 206 64 720 200 203 4 000 1 3 62 682 194 203 59 660 190 199 6 000 3 7 59 632 187 201 55 612 184 198 8 000 7 11 55 586 181 200 52 566 177 197 10 000 11 15 52 542 174 199 49 520 171 196 12 000 15 19 51 510 169 200 47 488 166 196 14 000 19 23 49 480 164 200 44 456 160 195 16 000 23 27 47 454 159 200 42 428 155 195 18 000 27 31 45 ...

Page 794: ...KTS SL 19 15 81 840 217 218 78 822 214 215 2 000 15 11 77 790 210 217 73 770 207 214 4 000 11 7 74 748 204 217 70 724 201 214 6 000 7 3 70 696 197 216 65 672 193 211 8 000 3 1 67 656 191 216 63 632 188 212 10 000 1 5 65 614 186 216 60 588 182 212 12 000 5 9 63 582 181 216 58 554 177 212 14 000 9 13 62 554 177 219 57 526 172 213 16 000 12 17 61 532 173 221 55 500 167 214 18 000 16 21 60 514 169 223...

Page 795: ...8 210 211 2 000 15 11 70 750 204 211 66 732 201 208 4 000 11 7 66 704 198 210 63 684 195 207 6 000 7 3 61 650 189 208 58 630 186 204 8 000 3 1 59 608 184 208 55 586 180 204 10 000 1 5 56 564 178 207 51 542 174 203 12 000 5 9 54 530 173 208 50 506 169 203 14 000 9 13 52 498 167 207 47 472 163 202 16 000 12 17 50 470 162 207 45 444 157 202 18 000 16 21 48 448 158 209 43 420 152 202 20 000 20 25 47 4...

Page 796: ...LB HR KTS KTS SL 29 25 77 824 211 215 75 812 210 215 2 000 25 21 75 786 207 218 73 774 206 217 4 000 21 17 74 750 203 220 71 736 202 219 6 000 18 13 72 710 198 221 69 694 196 219 8 000 14 9 70 670 193 222 66 648 190 219 10 000 10 5 67 630 188 223 63 606 184 219 12 000 6 1 66 598 183 225 62 576 181 221 14 000 2 3 64 570 179 226 60 546 176 222 16 000 2 7 63 546 174 228 58 520 171 223 18 000 6 11 62 ...

Page 797: ... 760 205 215 68 744 202 213 4 000 21 17 68 714 215 64 694 196 212 6 000 18 13 65 670 193 215 650 190 212 8 000 14 9 62 626 187 215 58 604 211 10 000 10 5 58 582 180 214 54 558 11 000 POUNDS 29 71 199 61 183 176 209 12 000 6 1 57 552 177 216 53 526 173 211 14 000 2 3 55 520 171 216 50 494 167 211 16 000 2 7 53 490 166 217 48 462 161 210 18 000 6 11 51 466 161 217 46 434 155 210 20 000 10 15 50 444 ...

Page 798: ...KTS KTS LB HR KTS KTS SL 39 35 73 810 205 213 71 798 204 212 2 000 35 31 72 722 201 215 69 758 200 214 4 000 31 27 70 734 197 217 69 726 197 217 6 000 28 23 69 698 193 219 67 688 193 219 8 000 24 19 67 660 188 220 65 650 188 221 10 000 20 15 65 622 183 222 63 610 183 222 12 000 16 11 63 588 179 223 61 578 179 223 14 000 12 7 62 562 174 224 60 550 175 225 16 000 8 3 61 538 170 226 59 526 171 227 18...

Page 799: ...6 204 212 67 776 203 211 2 000 35 31 68 748 200 214 65 736 199 213 4 000 31 27 67 712 196 217 64 700 196 216 6 000 28 23 65 676 193 219 62 658 190 216 8 000 24 19 63 636 188 220 59 614 184 216 10 000 20 15 60 594 182 220 56 572 178 216 12 000 16 11 59 562 178 222 55 538 174 217 14 000 12 7 57 534 173 223 53 510 170 218 16 000 8 3 56 506 169 224 51 482 165 219 18 000 4 1 54 482 164 226 49 454 159 2...

Page 800: ... FEET qC qC LB HR KTS KTS LB HR KTS KTS SL 49 45 75 820 205 217 70 798 202 214 2 000 45 41 70 768 198 215 67 750 196 213 4 000 41 37 68 726 193 216 65 710 192 215 6 000 37 33 66 690 189 218 64 674 188 217 8 000 34 29 64 650 184 219 62 636 183 218 10 000 30 25 62 612 179 19 60 596 178 219 12 000 26 21 61 582 174 221 59 566 174 220 14 000 22 17 60 556 170 223 57 538 169 221 16 000 18 13 60 536 167 2...

Page 801: ...9 45 67 780 200 211 64 766 198 209 2 000 45 41 65 736 195 212 62 724 194 211 4 000 41 37 63 700 191 214 61 688 190 213 6 000 37 33 62 664 187 216 60 652 187 216 8 000 34 29 60 626 183 218 58 614 183 218 10 000 30 25 58 588 178 219 56 574 178 218 12 000 26 21 57 556 174 221 55 544 174 220 14 000 22 17 56 528 170 223 53 516 169 222 16 000 18 13 55 504 166 225 52 490 166 224 18 000 14 9 54 484 163 22...

Page 802: ...ET qC qC LB HR KTS KTS LB HR KTS KTS SL 56 52 77 840 207 222 73 814 204 218 2 000 52 48 74 790 201 221 68 760 197 216 4 000 48 44 70 740 194 220 65 714 191 216 6 000 44 40 66 694 188 220 63 670 185 216 8 000 41 36 65 656 183 221 61 632 180 217 10 000 37 32 63 620 179 222 59 594 176 218 12 000 33 28 63 592 175 225 58 564 172 220 14 000 29 24 62 568 171 227 57 538 167 222 16 000 25 20 62 548 168 230...

Page 803: ...B HR KTS KTS SL 56 52 68 788 200 214 64 766 197 210 2 000 52 48 64 738 194 213 61 720 191 210 4 000 48 44 62 696 189 214 60 682 187 212 6 000 44 40 60 654 184 215 58 644 183 214 8 000 41 36 58 618 179 216 56 606 179 216 10 000 37 32 56 580 175 217 56 568 175 217 12 000 33 28 55 548 171 219 53 536 171 219 14 000 29 24 54 520 166 220 52 510 167 221 16 000 25 20 53 496 162 222 51 486 163 223 18 000 2...

Page 804: ...TM 1 1510 218 10 Figure 7A 90 Range Profile Maximum Range Power 1700 RPM 7A 102 ...

Page 805: ...TM 1 1510 218 10 Figure 7A 91 Range Profile Full Main and Auxiliary Tanks 7A 103 ...

Page 806: ...TM 1 1510 218 10 Figure 7A 92 Endurance Profile Full Main and Auxiliary Tanks 7A 104 ...

Page 807: ...TM 1 1510 218 10 Figure 7A 93 Range Profile Full Main Tanks 7A 105 ...

Page 808: ...TM 1 1510 218 10 Figure 7A 94 Endurance Profile Full Main Tanks 7A 106 ...

Page 809: ... ALT IOAT OAT TORQUE PER ENGINE TOTAL FUEL FLOW 13 000 LB 12 000 LB 11 000 LB 10 000 LB FEET qC qC LB HR IAS TAS IAS TAS IAS TAS IAS TAS SL 12 15 100 517 189 180 191 182 193 183 194 185 2000 16 19 100 505 186 182 189 185 191 187 192 188 4000 20 23 100 492 184 185 186 188 188 190 190 192 6000 24 27 100 479 181 188 184 191 186 193 188 195 8000 27 31 100 467 179 191 182 194 184 196 186 198 10 000 31 ...

Page 810: ...000 LB 11 000 LB 10 000 LB FEET qC qC LB HR IAS TAS IAS TAS IAS TAS IAS TAS SL 2 5 100 520 187 181 189 184 191 185 193 187 2000 6 9 100 505 185 184 187 187 189 189 191 190 4000 10 13 100 492 182 187 185 190 187 192 189 194 6000 13 17 100 480 180 190 182 193 184 195 186 197 8000 17 21 100 468 177 193 180 196 182 198 184 201 10 000 21 25 100 456 174 196 177 199 180 202 182 204 12 000 25 29 100 446 1...

Page 811: ...00 LB 10 000 LB FEET qC qC LB HR IAS TAS IAS TAS IAS TAS IAS TAS SL 8 5 100 522 185 183 188 186 190 187 191 189 2000 4 1 100 508 183 186 185 188 187 191 189 192 4000 0 3 100 494 180 189 183 191 185 194 187 196 6000 3 7 100 481 178 192 181 195 183 197 185 199 8000 7 11 100 468 175 194 178 198 181 200 183 203 10 000 11 15 100 456 172 197 175 201 178 204 180 206 12 000 15 19 100 446 169 200 173 204 1...

Page 812: ...000 LB 10 000 LB FEET qC qC LB HR IAS TAS IAS TAS IAS TAS IAS TAS SL 18 15 100 525 184 185 186 187 188 189 190 191 2000 14 11 100 511 181 188 184 190 186 192 188 194 4000 11 7 100 497 179 190 181 193 184 196 186 198 6000 7 3 100 483 176 193 179 196 181 199 183 201 8000 3 1 100 469 173 196 176 200 179 202 181 205 10 000 1 5 100 457 170 199 174 202 176 206 179 208 12 000 5 9 97 436 165 198 169 203 1...

Page 813: ...13 000 LB 12 000 LB 11 000 LB 10 000 LB FEET qC qC LB HR IAS TAS IAS TAS IAS TAS IAS TAS SL 28 25 100 527 182 187 185 189 187 191 189 193 2000 24 21 100 513 180 189 182 192 185 194 186 196 4000 21 17 100 499 177 192 180 195 182 198 184 200 6000 17 13 100 484 174 195 177 198 180 200 182 203 8000 13 9 100 470 171 197 174 201 177 204 179 207 10 000 9 5 95 441 164 195 168 199 171 203 174 207 12 000 5 ...

Page 814: ...EL FLOW 13 000 LB 12 000 LB 11 000 LB 10 000 LB FEET qC qC LB HR IAS TAS IAS TAS IAS TAS IAS TAS SL 38 35 100 530 181 188 183 191 185 193 187 195 2000 35 31 100 515 178 191 181 194 183 196 185 198 4000 31 27 100 500 176 194 178 197 181 200 183 202 6000 27 23 97 475 170 193 173 197 176 200 178 203 8000 23 19 92 447 163 191 167 196 170 200 173 203 10 000 19 15 88 418 155 188 160 194 164 198 167 202 ...

Page 815: ...UE PER ENGINE TOTAL FUEL FLOW 13 000 LB 12 000 LB 11 000 LB 10 000 LB FEET qC qC LB HR IAS TAS IAS TAS IAS TAS IAS TAS SL 48 45 97 521 176 186 179 189 182 192 184 194 2000 44 41 94 499 172 187 175 190 178 193 180 196 4000 40 37 92 478 167 188 171 192 174 195 177 198 6000 37 33 90 453 162 187 166 192 169 195 172 199 8000 33 29 86 425 154 184 159 190 163 194 166 198 10 000 28 25 82 397 146 180 152 1...

Page 816: ...T TORQUE PER ENGINE TOTAL FUEL FLOW 13 000 LB 12 000 LB 11 000 LB 10 000 LB FEET qC qC LB HR IAS TAS IAS TAS IAS TAS IAS TAS SL 55 52 90 503 170 181 173 185 176 188 178 190 2000 51 48 88 481 165 182 169 186 172 189 174 192 4000 47 44 87 461 161 182 165 187 168 191 171 194 6000 43 40 84 438 155 181 160 187 163 190 167 195 8000 39 36 81 411 147 178 153 185 158 190 161 194 10 000 35 32 77 384 138 172...

Page 817: ...TM 1 1510 218 10 Figure 7A 103 Pressurization Controller Setting for Landing 7A 115 ...

Page 818: ...TM 1 1510 218 10 Figure 7A 104 Holding Time 7A 116 ...

Page 819: ...TM 1 1510 218 10 Figure 7A 105 Time Fuel and Distance to Descend 7A 117 ...

Page 820: ...TM 1 1510 218 10 Figure 7A 106 Climb Balked Landing 7A 118 ...

Page 821: ...TM 1 1510 218 10 Figure 7A 107 Normal Landing Distance Without Propeller Reversing Flaps DOWN 7A 119 ...

Page 822: ...TM 1 1510 218 10 7A 120 Figure 7A 108 Landing Distance Without Propeller Reversing Flaps UP ...

Page 823: ...TM 1 1510 218 10 7A 121 Figure 7A 109 Landing Distance With Propeller Reversing Flaps DOWN ...

Page 824: ...TM 1 1510 218 10 7A 122 Figure 7A 110 Landing Distance With Propeller Reversing Flaps UP ...

Page 825: ...TM 1 1510 218 10 7A 123 7A 124 blank Figure 7A 111 Stopping Distance Factors ...

Page 826: ... ...

Page 827: ...he briefing should include but not be limited to copilot and ground crew responsibilities and the coordination necessary to complete the mission most efficiently A review of visual signals is desirable when ground guides do not have a direct voice communications link with the crew Refer to Section VI for crew and passenger briefings Section II OPERATING PROCEDURES AND MANEUVERS 8 7 OPERATING PROCE...

Page 828: ...formed prior to takeoff b Placarded items such as switch and control positions appear in boldface capital letters 8 12 BEFORE EXTERIOR CHECK 1 Forms publications Check DA Forms 2408 12 13 14 and 18 DD Form 365 4 locally required forms and publications and availability of operator s manual 10 and checklist CL 2 Oxygen system Check that oxygen quantity is sufficient for entire mission passenger manu...

Page 829: ...and skin damage such as buckling splitting distortion or dents c Fuel sump drains Check for leaks d Controls and trim tab Check security and trim tab rig e Static wicks Check security and condition f Wing tip and position lights Check condition and for cracked lens g Recognition light Check condition h Landing taxi light Check condition i Outboard wing fuel vent Check free of obstruction and leaks...

Page 830: ...WING LANDING GEAR ENGINE NACELLE AND PROPELLER AREA 2 NOSE SECTION AREA 3 RIGHT WING LANDING GEAR ENGINE NACELLE AND PROPELLER AREA 4 FUSLAGE RIGHT SIDE AREA 5 EMPENNAGE AND TAIL AREA 6 FUSELAGE LEFT SIDE Figure 8 1 Exterior Inspection ...

Page 831: ... cracks and free of obstructions b Auxiliary tank fuel sump drain Check for leaks O c Hydraulic reservoir vent and pump seal drain D2 Check vent clear of obstructions and that no excessive fluid is present d Deice boot Check for bonding cracks loose patches and general condition e Auxiliary tank fuel and cap Check fuel level visually condition of seal and cap tight and properly installed 5 Fuselag...

Page 832: ...oil level oil cap secure and access door locked Locking tab aft b Engine compartment left side Check for fuel and oil leaks security of oil cap and general condition Lock compartment access door c Left cowl locks Locked d Left exhaust stub Check for cracks and free of obstructions e Propeller blades and spinner Check blade condition security of spinner and free propeller rotation f Engine air inle...

Page 833: ...Check condition d Aft access door Check secure e Oxygen filler door Check secure f Static ports Check clear of obstructions g Emergency locator transmitter ARMED h Emergency locator transmitter antenna Check condition 8 18 EMPENNAGE AREA 5 1 Empennage Check as follows a Vertical stabilizer rudder and trim tab Check for skin damage such as buckling distortion or dents and trim tab rig b Antennas Ch...

Page 834: ...in latch handle position Closed and latched The orange colored indicator must align with orange stripe on carrier rod NOTE The untapered shoulder of the latching pins extend past each attachment lug 4 Emergency exit Check secure and key removed ڎ 5 Crew passenger briefing As required Refer to passenger briefing in Paragraph 8 66 8 21 BEFORE STARTING ENGINES 1 Oxygen system Set PULL ON CREW READY S...

Page 835: ...h SLAVE 13 Subpanel Check and set a Engine FIRE PROTECTION TEST switch OFF b LANDING TAXI and RECOG OFF c LDG GEAR CONTR Recheck DN CAUTION Do not use alternate static source during takeoff and landing except in an emergency Pilot s instruments will show a variation in airspeed and altitude d PILOT S STATIC SOURCE Normal ڎ 14 Fuel pumps crossfeed operation Check as follows a FIRE PULL handles Pull...

Page 836: ...cent to the right engine Normally only one engine is started utilizing the GPU reverting to the Battery Start procedure for the second engine start A crewmember should monitor the outside observer throughout the engine start 1 EXTERIOR LIGHTS switches As required 2 Propeller Clear 3 Engine Start a IGNITION AND ENGINE STARTER switch ON IGN ON light should illuminate and associated FUEL PRESS light ...

Page 837: ...FF after 50 N1 and TGT decreasing 4 Engine and systems instruments Check 5 BATTERY CHARGE light on Check 6 INVERTER switches ON check INVERTER lights OFF 7 Second engine generator switch RESET then ON 8 CONDITION levers As required 9 Red anticollision light Reset NOTE To reset turn OFF approximately 5 seconds then ON When voltage drops below approximately 20 volts the red anticollision light may b...

Page 838: ...8 23 6 GPU disconnect As required Disconnect if second engine start is to be a battery start CAUTION Do not turn on generators with GPU connected 7 GEN switch RESET then ON 8 27 SECOND ENGINE START GPU START 1 Propeller area Clear 2 Engine Start a IGNITION AND ENGINE STARTER switch ON IGN ON light should illuminate and associated FUEL PRESS light should extinguish CAUTION If ignition does not occu...

Page 839: ...anning such surfaces within 50 feet of the antenna reflector may damage receiver crystals 6 Avionics controls As required NOTE The radar system should be tested before each flight on which the system is to be used If no significant weather is in the immediate area of the aircraft the system should be left in the STBY position ڎ 7 Electric elevator trim autopilot flight director operation C D1 When...

Page 840: ... and engage AUTO PILOT TRIM TEST switch when elevator trim wheel starts to rotate b Verify that autopilot disengages and AP TRIM FAIL and MASTER WARNING lights illuminate within 10 seconds ڎ 9 Automatic flight control system D2 When the PC determines that an autopilot check is required check as follows a Altitude alert NOTE Pause a few seconds after each step to allow time for the proper indicatio...

Page 841: ...2 Pitch wheel Check that trim responds to pitch wheel movement UP TRIM and DN TRIM annunciators may illuminate 13 Heading bug Center and engage HDG Check that control follows a turn in each direction 14 Disengage AP by selecting GA Check that AP disengages and FD commands 7 nose up wings level attitude 10 Electric elevator trim D2 Check a Elevator trim switch On b Pilot and copilot trim switches C...

Page 842: ... CAUTION Monitor oil temperature closely during ground operation with propellers in FEATHER due to lack of air flow over oil cooler 1 Parking brake As required 2 Propeller feathering Check by pulling propeller levers aft through detent to FEATHER Check that propeller will feather and advance levers to the HIGH RPM position ڎ 3 AUTOFEATHER AUTO IGNITION Check a Condition levers LOW IDLE b ENG AUTO ...

Page 843: ...c pressure and wing deice boots inflation and after 6 seconds for a second drop in pneumatic pressure ڎ 10 Pneumatic System Check as follows a LEFT BLEED AIR VALVE switch OFF b Pneumatic pressure 12 to 20 psi Check c L BL AIR OFF light on Check d RIGHT BLEED AIR VALVE switch OFF e L R BL AIR OFF L R BL AIR FAIL lights and MASTER WARNING light ON f LEFT BLEED AIR VALVE switch OPEN g L BL AIR OFF an...

Page 844: ...tiate abort procedures if required The PNF should ensure that the AUTOFEATHER advisory lights are illuminated if applicable adjust and maintain power at the exact takeoff power settings and monitor all engine instruments Rotate at the recommended rotation speed V1 Vr and establish the climb attitude no greater than 15q that will attain best climb airspeed V2 10 KIAS during the initial climb Rotati...

Page 845: ...the computed obstacle clearance airspeed Vx Climb at this speed until clear of the obstacle After the obstacle is cleared lower the nose slowly and accelerate to Vy Retract flaps after attaining 105 KIAS NOTE The best angle of climb speed Vx is very close to single engine power off stall speed To provide for a margin of safety in the event of engine failure immediately after takeoff the obstacle c...

Page 846: ...rature be obtained at stabilized cruise airspeed Power is set using RPM and torque as the primary control Maximum allowable torque must not be exceeded and TGT must also be observed as a separate limit NOTE A new engine operated at the torque value presented in the cruise power charts will show a TGT margin below the maximum cruise limit for the torque value presented in the charts With ice vanes ...

Page 847: ...CH 1 HSI NAV SOURCE As required a Ensure the correct navigational source for the approach has been selected O 2 TCAS Set as required 8 40 BEFORE LANDING 1 CABIN SIGNS switch BOTH 2 PROP SYNC switch OFF 3 AUTOFEATHER switch ARM 4 BRAKE DEICE As required 5 PROP levers As required NOTE During approach propellers should be set at least to 1900 RPM to prevent glideslope interference ILS approach provid...

Page 848: ...lade erosion b Crosswind Landing When landing in very strong crosswinds flaps extension should be limited to obtain a faster approach and landing speed Use the crab into the wind method to correct for drift during final approach The crab is changed to a slip aileron into wind and top rudder to correct for drift during flare and touchdown After landing position ailerons as required to correct for c...

Page 849: ...R LANDING 9 TGT ITT Check TGT ITT must be 660 qC or below for 1 minute prior to shutdown Complete the following procedures after the aircraft has cleared the runway 10 CONDITION levers FUEL CUTOFF 1 CONDITION levers As required 11 PROP levers FEATHER 2 ENG AUTO IGN OFF 3 ICE RAIN switches As required WARNING 4 FLAPS As required Do not turn EXTERIOR LIGHTS off until propeller rotation has stopped 5...

Page 850: ...ns and procedures described in this manual 8 49 INSTRUMENT TAKEOFF Complete the Before Takeoff check Engage the HDG mode on the FD Do not engage autopilot Align the aircraft with the runway centerline ensuring that the nose wheel is straight before stopping aircraft Set HDG marker to runway heading If an altitude selector is installed set the initial climb altitude and arm the ALT SEL on the FD Ho...

Page 851: ...ion of NAV TEST prior to the final approach fix may detect certain malfunctions not indicated by the warning flags Section IV FLIGHT CHARACTERISTICS 8 55 STALLS A pre stall warning in the form of a very light buffeting can be felt when a stall is approached A mechanical warning is also provided by a warning horn The warning horn starts to alarm approximately 5 to 10 knots above stall speed with th...

Page 852: ...ith wing flaps up The Stall Speed Chart Figure 8 2 shows the indicated power off stall speeds with aircraft in various configurations Altitude loss during a full stall will be approximately 800 feet Safety and recoverability are greatly enhanced by placing the CONDITION levers at HIGH IDLE before performing power off stalls c Accelerated Stalls The aircraft gives noticeable stall warning in the fo...

Page 853: ...TM 1 1510 218 10 8 27 Figure 8 2 Stall Speed ...

Page 854: ...latively light in the extreme aft CG condition progressing to moderately high with CG at the forward limit Extending and retracting the landing gear causes only slight changes in control pressure Control pressures resulting from changes in power settings or the repositioning of the wing flaps are not excessive in the landing configuration at the most forward CG The minimum speed at which the aircr...

Page 855: ...isually check wheel rotation to ensure brake assemblies have been deiced The condition levers may be returned to LOW IDLE as soon as the brakes are free of ice e Before Takeoff CAUTION If the possibility of ice accumulation on the horizontal stabilizer or elevator exists takeoff will not be attempted If icing conditions are expected activate all anti ice systems before takeoff allowing sufficient ...

Page 856: ...cessitate hours of maintenance if basic preventive measures are not followed In flight the hazards of dust and sand will be difficult to escape since dust clouds over a desert may be found at altitudes up to 10 000 feet During hot weather operations the principle difficulties encountered are high TGT s during engine starting over heating of brakes and longer takeoff and landing rolls due to the hi...

Page 857: ...ry to counter rapid changes in attitude and accept major indicated altitude variations Penetration should be at an altitude that provides adequate maneuvering margins as a loss or gain of several thousand feet of altitude may be expected The recommended penetration speed in severe turbulence is 170 KIAS Pitch attitude and constant power settings are vital to proper flight technique Establish recom...

Page 858: ...nadvertently encountered turn on the anti icing systems prior to the first sign of ice formation Do not operate deicer boots continuously Allow at least 1 2 inch of ice on the boots before activating the deicer boots to remove the ice Continued flight in severe icing conditions should not be attempted If ice forms on the wing area aft of the deicer boots climb or descend to an altitude where condi...

Page 859: ...ncy Procedures a Personnel to include ID tags a Emergency exits b Professional medical equipment etc b Emergency equipment c Survival c Emergency landing ditching procedures 3 Flight Data a Route 8 68 DEPARTURE BRIEFING The following is a guide that should be used as applicable in accomplishing the required crew briefing prior to takeoff However if the crew has operated together previously thru fl...

Page 860: ...rew has operated together previously thru flight and the pilot is certain that the copilot understands all items of the briefing the pilot may omit the briefing by stating Standard briefing when the briefing is called for during the Descent Arrival check 1 Weather altimeter setting 2 Airfield facilities Review a Field elevation b Runway length c Runway condition 3 Approach procedure Review a Appro...

Page 861: ...ct voice communications link with the crew Refer to Section VI for crew and passenger briefings Section II OPERATING PROCEDURES AND MANEUVERS 8A 7 OPERATING PROCEDURES AND MANEUVERS This section deals with normal procedures and includes all steps necessary for safe and efficient operation of the aircraft from the time a preflight begins until the flight is completed and the aircraft is parked and ...

Page 862: ...in boldface capital letters 8A 12 BEFORE EXTERIOR CHECK 1 Forms publications Check DA Forms 2408 12 13 14 and 18 DD Form 365 4 locally required forms and publications and availability of operator s manual 10 and checklist CL 2 Oxygen system Check Refer to Table 8A 1 Oxygen Duration and Figure 8A 1 CAUTION If high or gusty winds are present and the flight controls are unlocked control surfaces may ...

Page 863: ...W annunciator illuminated NOTE It takes approximately 8 seconds for the annunciator to illuminate and to extinguish after release 3 Release the TEST switch HYD FLUID LOW annunciator extinguished e Fire Detection System Checked 12 Lighting and Heating Systems Check a Turn on LANDING TAXI ICE NAV RECOG STROBES and BEACON lights b Turn on PITOT FUEL VENTS and STALL WARN heats c Check all lights and h...

Page 864: ...vents Check free of obstructions 2 Left main landing gear Check as follows a Tires Check for cuts bruises wear appearance of proper inflation wheel condition and that both tires have the same tread design b Brake assembly Check brake lines for damage or signs of leakage and brake linings for wear Also check the brake deice assembly and bleed air hose for condition and security c Shock strut Check ...

Page 865: ...FT WING LANDING GEAR ENGINE NACELLE AND PROPELLER AREA 2 NOSE SECTION AREA 3 RIGHT WING LANDING GEAR ENGINE NACELLE AND PROPELLER AREA 4 FUSELAGE RIGHT SIDE AREA 5 EMPENNAGE AREA 6 FUSELAGE LEFT SIDE Figure 8A 2 Figure Exterior Check ...

Page 866: ... Wheel well condition Check for signs of leakage broken wires and condition e Doors and linkage Check condition security and alignment f Nose gear turning stop Check condition g Tire Check for cuts bruises wear appearance of proper inflation and wheel condition h Shock strut Check for signs of leakage and 3 inches minimum extension i Torque knee Check condition j Shimmy damper and linkage Check fo...

Page 867: ...cuts bruises wear appearance of proper inflation wheel condition and that both tires have the same tread design c Brake assembly Check lines for damage or signs of leakage and brake linings for wear Also check brake deice assembly and bleed air hose for condition and security d Shock strut Check for signs of leakage and minimum strut extension 5 5 inches and left and right extension is approximate...

Page 868: ...ng against the downstops f Static wicks Check g Position and beacon lights Check condition 8A 19 FUSELAGE LEFT SIDE AREA 6 1 Fuselage left side Check as follows a General condition Check for skin damage such as buckling splitting distortion or dents b Static ports Check clear of obstructions c Emergency light Check d Cabin door Check seal and general condition e Fuselage top side Check general con...

Page 869: ...fter the second engine start to allow performing the current limiters check When making a battery start the right engine should be started first A crewmember should monitor the outside observer throughout the engine start 1 BATT switch ON 2 EXTERIOR LIGHTS As required 3 Propeller Clear 4 Engine Start a IGNITION AND ENGINE START switch ON IGN ON annunciator should illuminate and associated FUEL PRE...

Page 870: ... 1 minute minimum b First engine GEN switch RESET then ON when N1 reaches 12 c CONDITION lever after N1 stabilizes at or above 12 for 5 seconds minimum LOW IDLE CAUTION Monitor ITT TGT to avoid a hot start If there is a rapid rise in ITT TGT be prepared to abort the start before limits are exceeded During starting the maximum allowable ITT TGT is 1000 C for 5 seconds If this limit is exceeded disc...

Page 871: ... the aircraft unless a battery indicating a charge of at least 20 volts is in the aircraft If the battery voltage is less than 20 volts the battery must be recharged or replaced with a battery indicating at least 20 volts before connecting external power Use only an external power source fitted with an AN type plug The BATT switch must be OFF prior to connecting an auxiliary power unit An EXTERNAL...

Page 872: ... ENGINE START switch ON IGN ON light illuminated and the associated FUEL PRESS light extinguished CAUTION If ignition does not occur within 10 seconds after moving condition lever to low idle initiate Engine Clearing procedure Paragraph 8A 25 If for any reason a starting attempt is discontinued the entire starting sequence must be repeated after allowing the engine to come to a complete stop 1 min...

Page 873: ...ire or a flat shock strut During taxi operations particular attention should be given to propeller tip clearance Extreme caution is required when operating on unimproved or irregular surfaces or when high winds exist If operations produce a propeller RPM over 1600 retard propeller levers to the detent to limit RPM to 1600 to help reduce the possibility of ingestion of ground debris 1 Brakes Check ...

Page 874: ...on DC loadmeter When AUTO mode is selected monitor prop ammeter for the appropriate number of seconds and ensure the indicator remains in the normal operating range the entire time b Windshield heat Check Note increases on the loadmeter and cycle through both normal and high settings NOTE If windshield heat is needed prior to takeoff use NORMAL setting for a minimum of 15 minutes prior to selectin...

Page 875: ...ontrol wheel Overpower slowly in both pitch and roll axis AP ENGAGE annunciator stops flashing FD flag on ADI retracts If autopilot or yaw damper disengages during overpower test or if AP ENGAGE or YD ENGAGE annunciator continues to flash the system is considered non operative and should not be used The elevator trim system must not be forced beyond the limits that are indicated on the elevator tr...

Page 876: ...de c CABIN PRESS switch TEST Cabin climb descent gauge indicates a descent d CABIN PRESS switch Release Cabin climb descent gauge indicates a climb then stabilizes at zero climb e Altitude selector Set as required Pressure altitude plus 200 feet 14 CONDITION levers As required 15 Ground Proximity Altitude Advisory System GPAAS Check as follows NOTE The GPAAS voice advisory must produce an operatio...

Page 877: ...5 000 to 31 000 feet 115 KIAS b Climb Maximum Rate Maximum rate of climb performance is obtained by setting propellers at 2000 RPM torque at maximum allowable or maximum climb ITT TGT monitor N1 and maintaining Vy Refer to Chapter 7 for Vy for specific weights c Climb Checklist Complete as follows 1 YAW DAMP As required 2 Cabin pressurization Check Adjust rate control knob so that cabin rate of cl...

Page 878: ...t in clean configuration perform the following 1 Cabin pressurization Set Adjust cabin controller dial as required While descending adjust rate control knob so that cabin rate of descent equals one third aircraft rate of descent 2 CABIN SIGNS switch As required 3 POWER levers IDLE 4 PROP levers HIGH RPM 5 GEAR UP 6 FLAPS UP 7 Airspeed Vmo maximum 8 ICE RAIN switches As required 9 RECOG lights As r...

Page 879: ... required accelerate stop distance pre computed on a current Takeoff and Landing Data TOLD card The nose wheel should be on the runway and rolling straight before the power is advanced After the pilot applies power to within 5 of the takeoff power the instructor s actions are the same as during a normal takeoff Use the following procedure 1 PROP levers HIGH RPM 2 FLAPS As required 3 Trim Set 4 Pow...

Page 880: ...rols As required 4 OVERHEAD FLOOD LIGHT OFF 5 STANDBY PUMPS Off 6 MAP lights OFF 7 Windows As required 8 Emergency exit lock As required 9 Galley power switches OFF 10 Aft cabin light OFF 11 Door light OFF CAUTION If strong winds are anticipated while the aircraft is unattended the propellers shall be secured to prevent windmilling with zero engine oil pressure 12 Walk around inspection Complete 1...

Page 881: ... slower than with flaps up The stall speeds graph shows the indicated power off stall speeds with aircraft in various configurations Refer to Figure 8A 3 Altitude loss during a full stall may be as much as 1000 feet Safety and recoverability are enhanced greatly by placing the CONDITION levers at HIGH IDLE before attempting the power off stall c Accelerated Stalls The aircraft gives noticeable sta...

Page 882: ...forward CG The minimum speed at which the aircraft can be fully trimmed is 92 KIAS gear and flaps down propellers at high RPM Control forces produced by changes in speed power setting flap position and landing gear position are light and can be overcome with one hand on the control wheel Trim tabs permit the pilot to reduce control forces to zero During single engine operation the rudder boost sys...

Page 883: ...TM 1 1510 218 10 8A 23 Figure 8A 3 Figure Stall Speeds Power Idle ...

Page 884: ... solution or brake deice to free frozen tires When heat is applied to release tires the temperature should not exceed 71 C 160 F Refer to Chapter 2 for anti icing deicing and defrosting treatment b Engine Starting When starting engines on ramps covered with ice propeller levers should be in the FEATHER position to prevent the tires from sliding To prevent exceeding torque limits when advancing con...

Page 885: ...devices are not accurate and should not be relied upon Keep a comfortable margin of airspeed above the normal stall airspeed Maintain a minimum of 140 knots during sustained icing conditions to prevent ice accumulation on unprotected surfaces of the wing In the event of windshield icing reduce airspeed to 226 knots or below h Descent Use normal procedures in Section II Brake deicing should be cons...

Page 886: ...nes during dusty sandy conditions activate ice vanes When the engine runup areas are slippery the crew may not be able to safely accomplish the runup procedures without causing the aircraft to begin sliding Under those conditions the pilot on the controls must use his judgment to determine which runup procedures will be accomplished Thunderstorms and areas of severe turbulence should be avoided If...

Page 887: ...do not prevail If flight into icing conditions is unavoidable proper use of aircraft anti icing and deicing systems may minimize the problems encountered Approximately 15 minutes prior to flight into temperature conditions that could produce frost or icing conditions the pilot s and copilot s windshield anti ice switches should be set at NORMAL or HIGH temperature position after preheating as nece...

Page 888: ...order to avoid extended exposure to flight conditions more severe than those for which the aircraft has been certified b Avoid abrupt and excessive maneuvering that may exacerbate control difficulties c Do not engage the autopilot d If the autopilot is engaged hold the control wheel firmly and disengage the autopilot e If an unusual roll response or uncommanded roll control movement is observed re...

Page 889: ...just takeoff power b Monitor engine instruments c Power check at 65 knots d Call out engine malfunctions e Tune identify all nav comm radios f Make all radio calls g Adjust transponder and radar as required h Complete flight log during flight and note altitudes and headings i Note departure time j Retract gear and flaps as directed 4 TOLD Card Review a Takeoff power b V1 Vr c V2 10 KIAS climb to 1...

Page 890: ...nications 4 Backup approach frequencies 5 Copilot s duties Review a Nav comm set up b Monitor altitude and airspeeds c Monitor approach d Call out visual field in sight 6 Landing performance data Review a Approach speed b Runway required 7 Passenger briefing As required 8A 30 ...

Page 891: ...DLE TO RELEASE The hatch is of the non hinged plug type that removes completely from the frame when the latches are released After the latches are released the hatch may be pushed into the aircraft NOTE The urgency of certain emergencies requires immediate action by the pilot The most important single consideration is aircraft control All procedures are subordinate to this requirement Reset MASTER...

Page 892: ...TM 1 1510 218 10 9 2 Figure 9 1 Emergency Exits and Equipment ...

Page 893: ... feel when holding rudder pressure to keep the aircraft from yawing the rudder being pressed indicates the good engine and engine instruments and after confirming the failed engine retard the propeller lever to feather the propeller Refer to Chapter 7 for single engine cruise information If one engine malfunctions during flight perform the following procedure 1 Autopilot yaw damp Disengage 2 POWER...

Page 894: ...Oil pressure Check 3 AUTOFEATHER switch OFF e IGNITION AND ENGINE START switch OFF at 50 N1 4 GEN switch OFF 5 PROP SYNC switch OFF 9 GEN switch RESET then ON 6 ICE VANE failed engine EXTEND 10 Engine cleanup Perform if engine restart is unsuccessful 9 10 ENGINE RESTART DURING FLIGHT USING STARTER N1 GREATER THAN ZERO 11 CABIN AIR TEMP MODE switch As required CAUTION 12 Electrical equipment As req...

Page 895: ...ar down indication cannot be determined prepare for a gear up landing also unless the surface of the landing area is hard and smooth the landing should be made with the landing gear up If landing on a rough terrain land in a slightly tail low attitude to keep nacelles from possibly digging in 8 Airspeed 140 KIAS minimum 9 Altitude Below 20 000 feet 10 ENG AUTO IGN switch ARM 11 CONDITION lever LOW...

Page 896: ...TM 1 1510 218 10 9 6 Figure 9 2 Maximum Glide Distance ...

Page 897: ...te readings 6 MANUAL TEMP switch DECREASE hold 3 BLEED AIR VALVE switch OFF 7 LEFT BLEED AIR VALVE switch PNEU ENVIRO OFF NOTE 8 Light still illuminated 30 seconds LEFT BLEED AIR VALVE switch OPEN Brake deice on the affected side and rudder boost will not be available with BLEED AIR VALVE switch off 9 RIGHT BLEED AIR VALVE switch PNEU ENVIRO OFF 4 Cabin pressurization Check 10 Light still illumina...

Page 898: ...re 9 23 SINGLE ENGINE LANDING CHECK 1 CABIN SIGNS switch BOTH Perform the following procedure during final approach to runway 2 BLEED AIR VALVE switches ENVIRO OFF 1 AP YD Disengaged 3 Descend below 14 000 feet as soon as practicable 2 GEAR DOWN lights Check 4 Oxygen As required 3 PROP lever live engine HIGH RPM 9 21 SINGLE ENGINE DESCENT ARRIVAL NOTE NOTE To ensure constant reversing characterist...

Page 899: ...h the propeller lever or by reducing power perform the following procedure 1 POWER lever affected engine IDLE 1 POWER lever IDLE 2 PROP lever FEATHER 2 PROP lever FEATHER 3 CONDITION lever As required 3 CONDITION lever FUEL CUTOFF 4 Engine cleanup As required 4 FIRE PULL handle Pull 9 26 FIRE 5 Fire extinguisher Actuate as required The safety of aircraft occupants is the primary consideration when...

Page 900: ...ent OFF 9 27 FUEL SYSTEM NOTE a Fuel Press Warning Light Illuminated Illumination of the No 1 or No 2 FUEL PRESS warning light usually indicates failure of the respective engine driven boost pump Perform the following With the loss of dc electrical power the aircraft will depressurize All electrical instruments with the exception of the Prop RPM N1 RPM and TGT gauges will be inoperative 1 STANDBY ...

Page 901: ... STANDBY PUMPS OFF 3 CROSSFEED switch As required 4 FUEL CROSSFEED annunciator illuminated Check a DC GEN Light Illuminated Illumination of a 1 or 2 DC GEN caution light indicates failure of a generator or one of its associated circuits generator control unit If one generator system becomes inoperative all nonessential electrical equipment should be used judiciously to avoid overloading the remain...

Page 902: ...rocedure NOTE The avionics power relay is normally hot Pulling the AVIONICS MASTER CONTR circuit breaker will remove power to the relay thus allowing electrical power to the associated buses 1 N1 and TGT indications Check 2 Other engine instruments Monitor f Circuit Breaker Tripped If the circuit breaker is for a nonessential item do not reset in flight If the circuit breaker is for an essential i...

Page 903: ...R switch DN 3 GEAR DOWN lights Check 4 Landing gear alternate engage handle Lift and turn clockwise to the stop IF INDICATOR REMAINS UNSAFE 5 Alternate landing gear extension handle Pump 4 Landing gear emergency extension Perform 6 GEAR DOWN lights illuminated Check NOTE d Landing Gear Emergency Extension D2 T If gear continues to indicate unsafe attempt to verify position visually NOTE b Landing ...

Page 904: ...ended that the fuel load be reduced and the landing made with flaps fully extended on a hard surface runway Landing on soft ground or dirt is not recommended as sod has a tendency to roll up into chunks damaging the underside of the aircraft s structure When fuel load has been reduced prepare for a gear up landing as follows 17 FIRE PULL handles Pull 18 MASTER SWITCH OFF f Landing With Nose Gear U...

Page 905: ... not lock allow the wing to lower slowly to the runway Use the following procedures 7 Seat belts and harnesses Fasten 8 Extension handle Stow 9 LDG GEAR CONTROL DN 10 LANDING GEAR RELAY circuit breaker Pull 11 LANDING GEAR WARN horn circuit breaker Pull 1 Retract the gear and make a gear up landing WARNING Make a normal approach but hold the nose up as long as possible after touchdown then ease th...

Page 906: ...racks that touch the frame as an inner ply crack 9 34 DITCHING If a decision to ditch is made immediately alert all personnel to prepare for ditching Plan the approach into the wind if the wind is high and the seas are heavy If the swells are heavy but the wind is light land parallel to the swells Set up a minimum rate descent power on or off as the situation dictates airspeed 110 to 120 KIAS Do n...

Page 907: ...TM 1 1510 218 10 9 17 Figure 9 3 Emergency Body Positions Figure 9 4 Wing Swell Ditch Heading Evaluation ...

Page 908: ...AKE LIFE RAFT AND FIRST AID KIT PASSENGERS PASSENGERS A SEAT BELTS FASTEN A SEAT BELTS FASTEN B LIFE VEST CHECK DO NOT INFLATE B LIFE VEST CHECK DO NOT INFLATE C ON PILOTS SIGNAL BRACE FOR DITCHING C ON PILOTS SIGNAL BRACE FOR DITCHING D ABANDON AIRCRAFT THROUGH CABIN DOOR TAKE LIFE RAFT AND FIRST AID KIT D ABANDON AIRCRAFT THROUGH CABIN DOOR TAKE LIFE RAFT AND FIRST AID KIT 4 CABIN PRESS switch D...

Page 909: ...ntrol clutch assembly can freeze in flight locking the trim in a cruise position This condition is first noticed when preparing for descent or retrimming at altitude Flight in above freezing temperatures will normally clear the problem before landing however if the elevator control is still frozen during the approach control forces must be overcome manually Descend using power reduction to keep he...

Page 910: ... ...

Page 911: ...viation Regulation General Operating And Flight Rules FM 1 230 Meteorology For Army Aviators FM 1 240 Instrument Flying And Navigation For Army Aviators TC1 218 Aircrew Training Manual ATM TM 1 1510 225 CL Operator s And Crewmember s Checklist Army Model C 12R Aircraft C 12T3 Aircraft C 12F3 Aircraft TM 55 1500 204 25 1 General Aircraft Maintenance Manual TM 55 1500 342 23 Army Aviation Maintenanc...

Page 912: ... ...

Page 913: ...lap speed is the highest speed permissible at which wing flaps may be actuated Vfe Maximum flap extended speed is the highest speed permissible with wing flaps in a prescribed extended position Vle Maximum landing gear extended speed is the maximum speed at which an aircraft can be safely flown with the landing gear extended Vlo Maximum landing gear operating speed is the maximum speed at which th...

Page 914: ...or SL Sea level Wind The wind velocities recorded as variables on the charts of this manual are to be understood as the headwind or tailwind components of the actual winds at 50 feet above runway surface tower winds B 3 POWER TERMINOLOGY Beta Range The region of the POWER lever control which is aft of the IDLE stop and forward of reversing range where blade pitch angle can be changed without chang...

Page 915: ...ompensate for the changes in RPM Constant propeller RPM is thereby maintained at the selected RPM setting Torque meter The torquemeter system determines the shaft output torque Torque values are obtained by tapping into two outlets on the reduction gear case and recording the differential pressure from the outlets Interstage Turbine Temperature ITT The temperature of the gases present between the ...

Page 916: ...gn structural performance or other limitations Maximum Zero Fuel Weight Any weight above the value must be loaded as fuel Moment A measure of the rotational tendency of a weight about a specified line mathematically equal to the product of the weight and the arm Operating Weight Basic empty weight plus crew crew s baggage publications and any other equipment not listed on Chart C that will remain ...

Page 917: ... Capture CDI Course Deviation Indicator CDU Control Display Unit CH CHAN Channel CHG Charge CL CKLST Checklist CLE Clear Entry CLIMB GAD Current Aircraft Climb Performance CLR Clear CMPST Composite COMM Communications COMSEC Communications Secure COND Conditioning COPLT Copilot CR Cursor Return CRS Course CRUISE ALT Cruise Altitude CTAF Common Traffic Advisory Frequency CVR Cockpit Voice Recorder ...

Page 918: ...ight Director FH Frequency Hopping FHDG Free Heading FH M Frequency Hopping Master FL Flight Level FLIP Flight Information Publications FLT Flight FM Frequency Modulation FMS Flight Management System FOB Fuel On Board FPA Flight Path Angle FPL Flight Plan FPM Feet Per Minute FR From Waypoint FREQ Frequency FS Fuselage Station FSB Fasten Seat Belt FSS Flight Service Station FT Foot Feet FT MIN Feet...

Page 919: ...munications Union kHz Kilohertz KIAS Knots Indicated Airspeed L Left LB Pounds LC Local Time LDA Localize Directional Aid LDG Landing LEG DIST Leg Distance LH Left Hand LOC Localizer LONG Longitude LPM Liters Per Minute LSB Lower Sideband LT Light MAG Magnetic MAN Manual MAP Missed Approach Point MAX Maximum Mb Millibars MDA Minimum Descent Altitude MEM Memory MF Mandatory Frequency MFD Multifunct...

Page 920: ... Recall RCV Receiver RDO Radio REC Receiver RECOG Recognition REL Release REM REM Remaining REQ FPM Require Feet Per Minute RES Reserve RMI Radio Magnetic Indicator RNAV Area Navigation RNG Range RPU Receiver Processor Unit RST Reset RT Receiver Transmitter RW Runway S South SAT Static Air Temperature SBS Set Beginning Of Stack SDF Simplified Directional Facility SENS Sensitivity SF Special Functi...

Page 921: ... USB Upper Sideband UT Universal Time Or Greenwich Mean Time UTC Coordinated Universal Time VA Voice Advisory Vac Volts alternating current VAR Magnetic Variation Vdc Volts direct current VERT DEV Vertical Deviation VFR Visual Flight Rules VHF Very High Frequency VIP Video Integrated Processor VNAV Vertical Navigation VNVINACTV VNAV Inactive VOL Volume VOR VHF Omni Range VORTAC Collocated VOR And ...

Page 922: ......

Page 923: ...ditional Alerts T 3C 17 ADF Control Panel F 3A 15 ADF Control Unit F 3B 14 ADF Radio KR 87 3A 24 F 3A 16 ADF RADIO SETS DF 203 3A 23 ADF Radio Sets KDF 806 3B 22 3C 23 ADF Receiver Control Unit KFS 586A F 3C 19 ADI Display Symbology F 3C 6 ADI Excessive Attitude Display F 3C 8 ADI Pitch Scale F 3C 7 Aerial Delivery System 6 15 After Emergency Action 9 4 After Landing 8 44 8A 44 After Takeoff 8 34 ...

Page 924: ...ge F 3 23 Army Aviation Safety Program 1 7 Arrival Briefing 8 69 8A 63 Attribute Designators T 3C 30 Attribute Hierarchy T 3C 31 Audio Control Panel T 3C 6 Audio Control Panel T1 F 3C 2 Audio Control Panel T2 3C 7 F 3C 1 Audio Control Panel 3B 6 F 3B 1 Aural Annunciator Messages T 3C 111 Autoignition System 2 36 Automatic Cancellation of Parallel Course Offsets F 3C 53 Automatic Flight Control Sys...

Page 925: ...ne Inoperative F 7 27 F 7A 31 Climb Two Engines Flaps 0 F 7 25 Climb Two Engines Flaps 40 F 7 26 Climb Two Engines Flaps APPROACH F 7A 30 Climb Two Engines Flaps UP F 7A 29 Climb 8 35 8A 35 Cockpit Typical D T F 2 10 Cold Weather Operations 8 62 8A 56 Communications Description 3 4 Condition Levers 2 28 Control Display Unit Front Panel F 3C 23 Control Lock Installation Typical F 2 23 Control Pedes...

Page 926: ...RDR 2000 System 3A 29 F 3A 22 Dimensions Aircraft 2 3 Direct Entry Into a Holding Pattern F 3C 73 Direct Intercept Insertion F 3C 101 T 3C 71 Direct Intercept F 3C 102 Direct To Page F 3 8 Direct To a Flight Plan Waypoint F 3C 47 T 3C 38 Direct To an Impromptu Waypoint F 3C 48 T 3C 39 Direct To Impromptu Waypoint Inserted as a Future Flight Plan Waypoint F 3C 49 T 3C 40 Direct To Line Select Key F...

Page 927: ...ight 9 8 Engine Shutdown 8 45 8A 45 Engine Starter Generators 2 37 Engine Trend Monitor 2 40 Engine F 2 14 Entering and Deleting Parallel Course Offset Procedure Entering and Deleting Parallel Course Offsets F 3C 52 T 3C 42 Entrance And Exit Provisions 2 12 Entry and Display of VNAV Parameters F 3C 56 T 3C 43 Entry of a New FROM Waypoint F 3C 41 Environmental Controls 2 80 Environmental System F 2...

Page 928: ...al Cruise Power 1800 RPM F 7A 68 Fuel Flow at Recommended Cruise Power 1700 RPM F 7 48 Fuel Flow at Recommended Cruise Power 1800 RPM F 7 59 Fuel Handling Precautions 2 101 Fuel Load 6 9 Fuel Management Panel C D T1 F 2 19 Fuel Moment Chart F 6 2 Fuel Quantity Data T 2 3 Fuel Sample 8 13 8A 13 Fuel Supply System 2 41 Fuel System Anti Icing 2 66 Fuel System Limits 5 11 Fuel System Management 2 42 F...

Page 929: ...Edit Pages F 3C 24 T 3C 14 Indicated Outside Air Temperature Correction ISA F 7A 10 Indicators Airspeed 2 92 Inflating Tires 2 108 Insert Center Waypoints F 3 110 Inserting and Deleting Intermediate Flight Plan Waypoints F 3C 34 T 3C 25 Inserting Flight Plan Waypoints in Sequence Procedure F 3C 33 T 3C 24 Installation Of Protective Covers 2 118 Instrument Approach Information T 3 5 Instrument Appr...

Page 930: ...with Automatic Sequencing F 3C 38 Left Side Types T 3 1 Left Wing Area 1 8 14 8A 14 Level Flight Characteristics 8 60 8A 54 Lighting Emergency 2 87 Lighting Exterior 2 85 Limitations Altitude 5 30 Limitations Autopilot 5 10 Limitations Center Of Gravity 5 19 Limitations Center Of Gravity 6 24 F 6 7 Limitations Engine Operating T 5 1 Limitations Engine 5 14 Limitations Icing Severe 5 34 Limitations...

Page 931: ...um Cruise Power 1900 RPM ISA 30 qC F 7 60 F 7A 95 Maximum Cruise Power 1900 RPM ISA 10 qC F 7 64 Maximum Cruise Power 1900 RPM ISA 20 qC F 7 65 Maximum Cruise Power 1900 RPM ISA 30 qC F 7 66 Maximum Cruise Power 1900 RPM ISA 37 qC F 7 67 Maximum Cruise Speeds 1700 RPM F 7A 54 Maximum Cruise Speeds 1800 RPM F 7A 78 Maximum Cruise Speeds 1900 RPM F 7 68 Maximum Design Maneuvering Speed 5 27 Maximum ...

Page 932: ...e Flight Plan Operation F 3 15 NAV 5 Page F 3 14 NAV Receivers KFS 579A KNR 634 3B 21 NAV TAC Control Unit KFS 579A F 3C 17 Navaid Option F 3 118 Navaid Setup Move F 3 120 Navaid Setup Select F 3 119 Navigation Configuration Page Access and Functions F 3C 30 T 3C 22 Navigation Configuration Page F 3C 43 T 3C 34 Navigation Data Items T 3 19 Navigation Description 3 6 Navigation Radio Information Pa...

Page 933: ...A 97 One Engine Inoperative Maximum Cruise Power 1900 RPM ISA 20 qC F 7 80 One Engine Inoperative Maximum Cruise Power 1900 RPM ISA 30 qC F 7 79 Operating Limits And Restrictions 8 2 8A 2 Operating Parameters T 3C 12 Operating Procedures And Maneuvers 8 7 8A 7 Options Test Mode F 3 116 OTH 3 Page F 3 74 OTH 5 Page F 3 75 OTH 6 Page F 3 76 OTH 7 Page F 3 77 OTH 8 Page F 3 78 OTH 9 Page F 3 79 Overh...

Page 934: ... T2 2 62 Propeller Electrothermal Deicer System C D T1 2 61 Propeller Failure Over 2120 RPM 9 25 Propeller Governors 2 52 Propeller Levers 2 56 Propeller Limitations 5 8 Propeller Reversing 2 57 Propeller Synchrophaser System 2 54 Propeller Tachometers 2 58 Propeller Test Switches 2 53 Published GPS Approach Scaling and Sequencing F 3C 92 Published GPS Approach Access F 3C 88 T 3C 66 Q QUICK TUNE ...

Page 935: ...t T 3C 113 Resolution Advisory Inhibits T 3C 114 Responsibility 6 6 Restraint Devices 6 21 Right Side Types T 3 2 Right Wing Area 3 8 16 8A 16 Rudder System 2 46 Runway Lighting T 3 6 Runway Surface T 3 7 S Satellite Health T 3 18 Scan Preset Page Access and Usage F 3C 127 T 3C 89 Seats 2 15 Second Engine Start Battery Start 8 23 8A 23 Second Engine Start GPU Start 8 27 8A 27 Securing Loads 6 20 S...

Page 936: ...rational Situation F 3C 153 TACAN DME KTU 709 3C 22 TACAN DME 3B 23 Tactical Approach Selection F 3C 90 T 3C 68 Takeoff Distance Flaps 0 F 7 18 Takeoff Distance Flaps 40 F 7 21 Take off Distance Flaps APPROACH F 7A 25 Takeoff Distance Flaps UP F 7A 21 Takeoff Flight Path F 7A 19 Takeoff Gross Weight Limit Flaps 0 To Achieve 100 FPM One Engine inoperative Rate of Climb At Liftoff F 7 14 Takeoff Gro...

Page 937: ...VI 920 Transponder TCAS Display Symbols T 3C 109 Typical General Interior Arrangement F 2 2 Typical Turning Radius F 2 4 U UHF Command Set AN ARC 164 HAVE QUICK 3A 8 UHF Command Set AN ARC 164 3A 7 F 3A 3 3B 7 F 3B 2 UHF MWOD List Selection and Loading F 3C 130 T 3C 92 Unprepared Runway Landing On 5 41 Unpressurized Ventilation 2 79 Use Of Checklist 8 11 8A 11 Use Of Fuels 2 105 Use Of Words Shall...

Page 938: ...ation Page F 3 38 Waypoints With Duplicate Identifier Procedure Waypoints With Duplicate Identifiers F 3C 37 T 3C 28 Weather Radar KWX 58 System T1 3C 27 Weather Radar KWX 58 System 3B 28 Weather Radar And Multifunction Display ED 600 T2 3C 30 Weather Radar Control Indicator T1 F 3C 144 Weather Radar Control Indicator F 3B 20 Weight And Balance Clearance Form F DD Form 365 4 6 8 Weight Balance and...

Page 939: ...retary of the Army GEORGE W CASEY JR General United States Army Chief of Staff Official 0927914 JOYCE E MORROW Administrative Assistant to the Secretary of the Army DISTRIBUTION To be distributed as Electronic Media Only ...

Page 940: ... ...

Page 941: ...orm 2028 1 From Joe Smith 2 Unit home 3 Address 4300 Park 4 City Hometown 5 St MO 6 Zip 77777 7 Date Sent 19 Dec 00 8 Pub Number TM 1 1510 218 10 9 Pub Title Operator s Manual for Army C 12C D T1 T2 Aircraft 10 Pub Date 30 Oct 99 11 Change Number Basic 12 Submitter Rank MSG 13 Submitter FName Joe 14 Submitter MName T 15 Submitter LName Smith 16 Submitter Phone 123 456 7890 17 Problem 1 18 Page 2 1...

Page 942: ......

Page 943: ...ICATIONS EXCEPT RPSTL AND SC SM AND BLANK FORMS PUBLICATION FORM NUMBER TM 9 1005 433 24 DATE 16 Sep 2002 TITLE Organizational Direct Support And General Support Maintenance Manual for Machine Gun 50 Caliber M3P and M3P Machine Gun Electrical Test Set Used On Avenger Air Defense Weapon System ITEM NO PAGE NO PARA GRAPH LINE NO FIGURE NO TABLE NO RECOMMENDED CHANGES AND REASON 1 WP0005 PG 3 2 Test ...

Page 944: ...OL LISTS AND SUPPLY CATALOGS SUPPLY MANUALS PUBLICATION NUMBER DATE TITLE PAGE NO COLM NO LINE NO NATIONAL STOCK NUMBER REFERENCE NO FIGURE NO ITEM NO TOTAL NO OF MAJOR ITEMS SUPPORTED RECOMMENDED ACTION PART III REMARKS Any general remarks or recommendations or suggestions for improvement of publications and blank forms Additional blank sheets may be used if more space is needed TYPED NAME GRADE ...

Page 945: ...ion and Missile Command ATTN AMSAM MMA NP Redstone Arsenal AL 35898 FROM Activity and location Include ZIP Code PART 1 ALL PUBLICATIONS EXCEPT RPSTL AND SC SM AND BLANK FORMS PUBLICATION FORM NUMBER DATE TITLE ITEM NO PAGE NO PARA GRAPH LINE NO FIGURE NO TABLE NO RECOMMENDED CHANGES AND REASON Reference to line numbers within the paragraph or subparagraph TYPED NAME GRADE OR TITLE TELEPHONE EXCHAN...

Page 946: ...ATALOGS SUPPLY MANUALS PUBLICATION NUMBER DATE TITLE PAGE NO COLM NO LINE NO NATIONAL STOCK NUMBER REFERENCE NO FIGURE NO ITEM NO TOTAL NO OF MAJOR ITEMS SUPPORTED RECOMMENDED ACTION PART III REMARKS Any general remarks or recommendations or suggestions for improvement of publications and blank forms Additional blank sheets may be used if more space is needed TYPED NAME GRADE OR TITLE TELEPHONE EX...

Page 947: ... 1000 cu millimeters 06 cu inch 1 cu decimeter 1000 cu centimeters 61 02 cu inches 1 cu meter 1000 cu decimeters 35 31 cu feet APPROXIMATE CONVERSION CHART APPROXIMATE CONVERSION FACTORS To change To Multiply by To change To Multiply by inches centimeters 2 540 ounce inches newton inches 007062 feet meters 305 centimeters inches 394 yards meters 914 meters feet 3 280 miles kilometers 1 609 meters ...

Page 948: ... PIN 0 000 ...

Page 949: ...e it They did not even scan it Why should they get your money Why are not letting you give those free manuals to your friends I am setting this document FREE This document was made by the US Government and is NOT protected by Copyright Feel free to share republish sell and so on I am not asking you for donations fees or handouts If you can please provide a link to liberatedmanuals com so that free...

Reviews:

No comments

Related manuals for C-12C

Prism Designs QUANTUM PRO Owner'S Manual preview
QUANTUM PRO
Brand: Prism Designs Pages: 6
AEROPRAKT 484 Pilot Operating Handbook preview
484
Brand: AEROPRAKT Pages: 53
Curtiss P-40 Tomahawk Manual preview
P-40 Tomahawk
Brand: Curtiss Pages: 21
Swing BrAve 2 Manual preview
BrAve 2
Brand: Swing Pages: 21
ICARO Maverick 3 Manual preview
Maverick 3
Brand: ICARO Pages: 22
Ozone FAZER 4 Pilot'S Manual preview
FAZER 4
Brand: Ozone Pages: 29
Ozone Mantra M4 Pilot'S Manual preview
Mantra M4
Brand: Ozone Pages: 56
Nervures ALPAMAYO II 38 Manual preview
ALPAMAYO II 38
Brand: Nervures Pages: 20
MACFLY POLINI Thor 130 User Manual preview
POLINI Thor 130
Brand: MACFLY Pages: 15
Tiger Aircraft AA-5 TRAVELER Maintenance Manual preview
AA-5 TRAVELER
Brand: Tiger Aircraft Pages: 909
RVE Merak E750 Assembly Instructions Manual preview
Merak E750
Brand: RVE Pages: 56
Pipistrel ALPHA Trainer Operator'S Manual preview
ALPHA Trainer
Brand: Pipistrel Pages: 5
Pipistrel FP03-60E Operator'S Manual preview
FP03-60E
Brand: Pipistrel Pages: 17
Pipistrel VIRUS SW 600 D Pilot Operating Handbook preview
VIRUS SW 600 D
Brand: Pipistrel Pages: 98
Pipistrel 1001 AT 912 LSA Pilot Operating Handbook preview
1001 AT 912 LSA
Brand: Pipistrel Pages: 182
Pipistrel VELIS Electro Pilot Operating Handbook preview
VELIS Electro
Brand: Pipistrel Pages: 244
PowerKites Beamer IV Owner'S Manual preview
Beamer IV
Brand: PowerKites Pages: 52
FreeX MANX L Owner'S Manual preview
MANX L
Brand: FreeX Pages: 55

Brands by name

Popular brands

Load more brands