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BOMBARDIER BD-100-1A10, Operating Manual

The Bombardier BD-100-1A10 Operating Manual is essential for maximizing the performance of your aircraft. Ensure safe and efficient operation by downloading the free manual from manualshive.com. This comprehensive guide provides detailed instructions for all aspects of the BD-100-1A10, making it a must-have for all owners and pilots.

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FIRE PROTECTION

Volume 2

Flight Crew Operating Manual

Sep 13/2004

09-01-10

CSP 100-6

REV 1

MAIN LANDING GEAR OVERHEAT DETECTION

DESCRIPTION

The Challenger 300 includes two main landing gear bays (MLG), also referred to as main wheel wells. due to the possibility
of brake or tire overheat during takeoff and the fact that the MLG bays are constructed from composite material, an overheat
detection system has been installed as part of the aircraft’s FIREX system.

C

F

O

150

100

2_

003

OVERHEAT
DETECTOR

FIRE DETECTION/EXTINGUISHING

SYSTEM CONTROL UNIT

OVERHEAT

WARNING

OVERHEAT
DETECTION
FAIL

OVERHEAT
DETECTION

TO 

EICAS

LH

RH

MAIN LANDING GEAR BAY

OVERHEAT DETECTION LOOPS

DATA
CONCENTRATOR
UNIT

 1

Summary of Contents for BD-100-1A10

Page 1: ...FLIGHT CREW OPERATING MANUAL VOLUME 2 MODEL BD 100 1A10 CUSTOMER SUPPORT PUBLICATION No 100 6 CSP 100 6 Oct 31 2008 Revision 11...

Page 2: ......

Page 3: ...02 01 Introduction 00 02 01 The Manual 00 02 01 Numbered Changes To The Manual 00 02 01 Pagination 00 02 02 Production Modification Data 00 02 02 Addresses 00 02 02 Abbreviations and Acronyms 00 02 03...

Page 4: ......

Page 5: ...E MANUAL Chapters 1 through 18 of this manual provide the operator of the Challenger 300 with a basic description of the aircraft operating systems from the cockpit controls and indicators to the actu...

Page 6: ...the page are the date of issue or revision date and the chapter title and subject carried in the masthead Blank pages resulting from end of section back up pages color illustrations or illustrations...

Page 7: ...ontrol Valve AOA Angle of Attack ADC Air Data Computer ASEL Altitude Preselect Mode ADDR Address ASYM Asymmetrical ADF Automatic Direction Finder ATC Air Traffic Control ADI Attitude Director Indicato...

Page 8: ...Power Center DIR or DCT Direct DCU Data Concentrator Unit DIS Distance to waypoint Disconnect Delta P Differential Pressure DISC Disconnect DECEL Decelerate DISCH Discharge DECR Decrease DISP Dispatc...

Page 9: ...ew Operating Manual FPM Feet Per Minute FCU Flight Control Unit FPU Flap Power Unit FDR Flight Data Recorder FREQ Frequency FECU Flap Electronic Control Unit FT Feet Foot FF F F Fuel Flow FUSE Fuselag...

Page 10: ...s ICAO International Civil Aviation Organization INT Internal Integral Intersection ICC Integrated Card Cage ISA International Standard Atmosphere ID or IDENT Identification ISO International Standar...

Page 11: ...P Miscompare MAG Magnetic MKR Marker MAINT Maintenance MLG Main Landing Gear MALF Malfunction MLS Microwave Landing System MAN Manual MLW Maximum Landing Weight MAP Ground Map WXR MM Middle Marker MME...

Page 12: ...verboard OB or OUTBD Outboard OVHT Overheat OBS Observer OVLD Overload OEI One Engine Inoperative OVTEMPOver Temperature OEW Operating Empty Weight OXY O2 Oxygen OM Outer Marker OZC Ozone Converter OT...

Page 13: ...nway Visual Range RECIRC Recirculation RVSM Reduced Vertical Separation Minimum RECOG Recognition REV Reverser REF s Reference s RWD Right Wing Down REFL Refuel RWY Runway S S STAT Status SPKR Speaker...

Page 14: ...rtical Speed Volt VMC Minimum Control Speed with the Critical Engine Inoperative VA Design Maneuvering Speed VMU Minimum Unstick Speed VB VC VD Design Speed for Maximum Gust Intensity Design Cruising...

Page 15: ...ocated VGA Minimum Go Around Speed VHF Very High Frequency 30 300 MHz VS VSI Vertical Speed Mode Vertical Speed Indicator W W C Wind Component WOW Weight On Wheels W S Wind Shear WPT s Waypoints W W W...

Page 16: ...Metric multiply CONVERSION TABLE Metric to Standard divide standard factor metric in 2 54 cm in 25 4 mm in2 6 4516 cm2 oz 28 3495 g fl oz 29 574 ml U S gal 3 7854 liters U S gal min 3 7854 liters min...

Page 17: ...23 8 31 35 0 66 2 19 7 2 156 2 69 20 6 246 2 119 48 3 112 0 80 62 2 22 0 30 34 4 68 0 20 6 7 158 0 70 21 1 248 0 120 48 9 110 2 79 61 7 20 2 29 33 9 69 8 21 6 1 159 8 71 21 7 249 8 121 49 4 108 4 78 6...

Page 18: ......

Page 19: ...xhaust System 02 03 05 Air Intake and Exhaust 05 01 05 Air Turbine Starter ATS 18 01 15 Aircraft Dimension Schematic 01 02 02 Aircraft Lighting 16 01 01 Aircraft Symbol 11 01 04 Airflow Paths 18 01 02...

Page 20: ...Servo Motors 04 01 21 Autopilot Takeoff Configuration Warning 04 01 23 Auxiliary Accumulator Servicing 13 01 10 Auxiliary DC Motor Driven Pump 13 01 07 Auxiliary Hydraulic System 13 01 07 Auxiliary Hy...

Page 21: ...1 04 12 CB 6 Right DC Power Center Circuit Breaker Panel Typical 07 01 11 CB 6 Right DC Power Center Circuit Breaker Panel Typical 01 04 12 CDU HF Radio Control 06 01 10 Center Pedestal 01 04 06 Chart...

Page 22: ...l DCP 11 01 35 Display Control Panel DCP 17 01 14 Display Control Panel Com Radio Control 06 01 07 Display Control Panel HF Tuning Control 06 01 10 Display Control Panel Warning Flag 11 01 26 Display...

Page 23: ...06 Engine Fuel Feed 12 01 05 Engine Fuel Shutoff Valve SOV 12 01 06 Engine Fuel System 18 01 04 Engine Idle 18 01 05 Engine Indicating and Crew Alerting System EICAS 03 02 01 Engine Lubrication Schem...

Page 24: ...2 17 Flight Controls Synoptic Page 03 04 05 Flight Crew Oxygen Mask and Storage Cup 08 01 06 Flight Crew Oxygen Mask Cold Weather Storage 08 01 06 Flight Deck Emergency Equipment 08 01 11 Flight Direc...

Page 25: ...ar Extension 15 01 09 Gear Retraction 15 01 09 Gearbox Assembly 05 01 04 General MFD Tuning 06 01 06 Glideslope Flag 11 01 05 Global Positioning System GPS 17 01 34 GPS Control 17 01 34 GPS MAN Mode 1...

Page 26: ...d Air System Controllers IASC 02 04 01 Integrated Avionics Processor System IAPS 03 02 11 Integrated Avionics Processor System Card Cage 03 02 11 Integrated Avionics Processor System Environmental Con...

Page 27: ...em MRS 15 01 10 Mask Containers 08 01 09 Master Disconnect Switch 04 01 23 Master Warning Master Caution Switches 03 02 04 Max Power APR 18 01 07 Message Message Sounds 03 03 06 Messages 03 03 01 META...

Page 28: ...ger Cabin 08 01 11 Passenger Door 01 05 01 Passenger Door Annunciations 01 05 04 Passenger Masks 08 01 10 Passenger Oxygen Control Panel 08 01 19 Passenger Oxygen System 08 01 09 PFD Messages 04 01 25...

Page 29: ...07 Required Navigation Performance RNP 17 01 35 Resolution Advisory 17 01 10 Reverse Thrust Operation 18 01 21 Reversion Control Panel 11 01 36 Reversion Switch Panel 03 02 09 Reversion Switch Panel 1...

Page 30: ...r 11 01 20 Steering and Turning Radii 01 02 07 Steering and Turning Radii Schematic 01 02 07 Steering Control System 15 01 16 Steering Control Unit 15 01 15 Stick Pusher Disconnect Features 10 02 15 S...

Page 31: ...rust Reverse Levers 18 01 07 Thrust Reverser 18 01 19 Thrust Reverser System 18 01 19 Tires and Brakes 15 01 11 To From Indicator 11 01 21 Tops Movement Image 11 02 16 Total Air Temperature Probe 11 0...

Page 32: ...emps Image 11 02 18 Windshield and Side Window Heating 14 01 08 Windshield Ice and Rain Protection 14 01 08 Wing Anti Ice Ducts 14 01 04 Wing Anti Ice System 14 01 03 Wing Anti Ice System Schematic 14...

Page 33: ...r 3 AUTOMATIC FLIGHT CONTROLS Chapter 4 AUXILIARY POWER UNIT Chapter 5 COMMUNICATIONS Chapter 6 ELECTRICAL Chapter 7 OXYGEN AND EMERGENCY EQUIPMENT Chapter 8 FIRE EQUIPMENT Chapter 9 FLIGHT CONTROLS C...

Page 34: ......

Page 35: ...ack Circuit Breaker Panel Typical 01 04 10 CB 4 Right Side Equipment Rack Circuit Breaker Panel Typical 01 04 11 CB 5 Left DC Power Center Circuit Breaker Panel Typical 01 04 12 CB 6 Right DC Power Ce...

Page 36: ......

Page 37: ...ovide hydraulic pow er for braking extending or retracting the landing gear nosewheel steering wing flaps spoilers thrust reversers elevator and rudder The landing gear system is a fully retractable t...

Page 38: ...NSION SCHEMATIC CFO0101002_015 NOTES Measurement at manufacturer empty weight WING AREA WING BASE 522 ft 48 5 m 27 8 ft 8 5 m 27 25 CHORD LINE 10 ft 6 in 3 20 m 63 ft 10 in 19 46 m 3 ft 9 in 1 14 m 23...

Page 39: ...1 CSP 100 6 01 02 03 AIRCRAFT DIMENSION SCHEMATIC Cont CFO0101002_016 2 ft 6 in 0 76 m 4 ft 3 in 1 3 m 61 ft 1 in 18 62 m 68 ft 8 in 20 92 m 20 ft 6 1 m 23 7 ft 7 7 m 16 5 ft 5 0 m 28 6 ft 8 7 m NOTE...

Page 40: ...AIRCRAFT DIMENSION SCHEMATIC Cont CFO0101002_017 6 1 ft 1 9 m 5 1 ft 1 6 m 7 2 ft 2 2 m PASSENGER COMPARTMENT DIMENSIONS LENGTH WIDTH FLOOR LINE WIDTH CENTERLINE HEIGHT VOLUME FLOOR AREA 28 ft 7 in 5...

Page 41: ...AL VHF COMM 3 IF INSTALLED MARKER BEACON RAD ALT ADF 1 ADF 2 VHF COMM 1 TCAS DIRECTIONAL GPS 1 GPS 2 ATC DME 1 TCAS OMNI VHF COMM 2 DME 2 ATC TELECOM Personnel should not stand nearby and in front of...

Page 42: ...RENCES FOR GROUND OPERATION WITH HEAD MOVED 0 3 ft 91 mm OUTBOARD PILOT S EYE POSITION PILOT S EYE POSITION APPROACH VISIBILITY 10 5 ft 3 2 m 19 17 7 7 ft 2 3 m 26 6 ft 8 1 m 8 7 ft 2 6 m MAXIMUM 139...

Page 43: ...URNING RADII SCHEMATIC CFO0101002_006 NOTE MAXIMUM STEERING SYMMETRICAL AND IDLE THRUST NO DIFFERENTIAL BRAKING 65 STEERING ANGLE 3 SLIP DRY RUNWAY SLOW CONTINUOUS TURN MAX A C WEIGHT AFT CG 27 8 ft 8...

Page 44: ...100 6 REV 1 DANGER AREAS CFO0101002_019 WEATHER RADAR 5 ft 1 5 m 15 ft 4 5 m FROM INTAKE 15 ft 4 5 m FROM INTAKE APU EXHAUST 500 F 260 C 19 ft 5 8 m 200 ft 60 9 m FROM TAILPIPE 200 F 93 3 C NOTE EXHA...

Page 45: ...the fuselage and one on each wing at the rear spar for jacking the complete airplane Gear jacking points are also provided for tire wheel brake changes Jacking procedures are located in the Aircraft...

Page 46: ...will be sheared off to provide a physical indication that damage may have been done to the feedback linkage and surrounding area For special hangar operations the torque links may be disconnected to...

Page 47: ...fuselage and on the wing jacking points for mooring the airplane Use chocks on all wheels when mooring the airplane Mooring procedures are located in the Aircraft Maintenance Manual Chapter 10 MOORING...

Page 48: ......

Page 49: ...t recline adjustment height and armrest position CFO0101002_008 HEADREST OXYGEN MASK ARMREST RECLINE ADJUSTMENT CONTROL SEAT BASE VERTICAL ADJUSTMENT CONTROL SHOULDER STRAP RESTRAINT LOCK UNLOCK HANDL...

Page 50: ...ttained when the rear ball is no longer seen as it will be covered by the white ball in front Correct seat placement is obtained height fore aft when All flight controls are unrestricted throughout fu...

Page 51: ...AIRPLANE GENERAL Sep 13 2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100 6 01 04 03 COCKPIT LAYOUT Flight Deck typical...

Page 52: ...L Volume 2 Flight Crew Operating Manual Sep 13 2004 01 04 04 CSP 100 6 REV 1 COCKPIT LAYOUT Cont LEFT SIDE CONSOLE CFO0100002_002 DIM BRT DIM ANNUN DIM BRT PEDESTAL DIM BRT BRT GSHLD L SIDE PFD MFD CO...

Page 53: ...Sep 13 2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100 6 01 04 05 COCKPIT LAYOUT Cont RIGHT SIDE CONSOLE CFO0100002_003 CB PANELS DOME GSHLD R SIDE PFD MFD COCKPIT LIGHTS DIM BRT DIM DIM BRT...

Page 54: ...ERSION PANEL 4 AIR CONDITIONING BLEED PANEL 5 ANTI ICE PANEL 6 ELECTRICAL PANEL 7 PRESSURIZATION PANEL 8 LIGHTING PANEL 9 FLIGHT SPOILERS HANDLE 10 PITCH DISCONNECT HANDLE 11 THRUST LEVERS 12 ENGINE R...

Page 55: ...FUNCTION DISPLAY MFD RIGHT PRIMARY FLIGHT DISPLAY PFD 13 14 15 16 17 18 19 1 2 4 5 6 7 8 9 10 11 12 14 15 16 17 18 19 3 13 AIR OUTLET PILOT AUDIO CONTROL PANEL PILOT COMPASS BARO RUDDER PEDAL ADJUSTM...

Page 56: ...DRAULIC L MFD L DCP L PFD ATT HDG 1 AIR DATA 1 DISPLAYS INDICATING RECORDING L BLEED VALVES PRESS 1 PACK ENVIRONMENTAL DCU A RDC A CTRL 1 L PWR 1 R PWR 2 ANNUNCIATOR L PITOT TAT VANE CASE CTRL PWR L E...

Page 57: ...S PWR 2 L DC PUMP PTU R SOV R IND LDG GEAR HYDRAULIC DISPLAYS INDICATING RECORDING FDR L PWR 2 R PWR 1 CTRL 2 RDC B DCU B ANNUNCIATOR EMER DOME LIGHTS R ENG R WING BLD LK PWR CTRL R ICE DET CASE VANE...

Page 58: ...SPD ENG RUN CH A SYNC IGN A ENG START A ENGINE L GEN NORM OFF ELEC L ENG SOV GRAVITY X FLOW QTY 1 FUEL FLIGHT CONTROL PAX DOOR ENVIR PAX 2 OXYGEN PWR CTRL L SIDE WINDOW ANTI ICE L FORCE SNSR MSTR DIS...

Page 59: ...GEN NORM OFF NORM OFF ELEC R ENG SOV XFER VALVE QTY 2 FUEL R FORCE SNSR PEDAL ADJ AUTO FLT TRIM MSTR DISC FLIGHT CONTROL LAV SMK DET DRN MAST HTR ENVIRONMENTAL PAX 2 OXYGEN PRESS OFV R FOOT WARM PWR C...

Page 60: ...C B 1 2 1 HF 2 PWR L ATS HYD SOL A PRI STAB MOTOR L LDG L DCPC ESS BUS L SPC BAT BUS R DCPC ESS BUS AVNX ENGINE FIREX FCTL LIGHTS ELECTRICAL EXT BAG AFT BAY CABIN INVRT 5 5 25 5 3 3 3 20 3 100 CFO0106...

Page 61: ...sponder switch activates the transponder IDENT function MICROPHONE SWITCH The microphone switch activates the selected radio transmitter when pulled outboard and the interphone when pushed in board MA...

Page 62: ......

Page 63: ...vent loss of pressur ization in the fuselage COMPONENTS AND OPERATION The passenger door consists of an integral airstair stairway lighting folding handrail actuator assembly two telescopic support st...

Page 64: ...door As the door opens the handrail unfolds parallel to the airstair A nylon stabilizer is mounted between the base of the handrail and the airstair to prevent unwanted movement of the handrail As th...

Page 65: ...gravity When the door is unlocked a red flag indicator shows through a window in the handle To close the passenger door from inside the aircraft push the switch located on the bulkhead forward of the...

Page 66: ...arallel to the primary shaft At each end of the lifting shaft is a lever which connects to the door hinge mechanism Movement of the two levers causes the door to move vertically in re lation to the hi...

Page 67: ...flag attached which states REMOVE BEFORE FLIGHT NOTE The emergency hatch can be opened and removed from inside or outside of the aircraft but must be installed from inside the aircraft COMPONENTS AND...

Page 68: ...nd loop fasteners for the cover EMERGENCY EXIT ANNUNCIATIONS An EMERGENCY EXIT C CAS message is displayed if the proximity sensor detects that the emergency hatch is not completely closed and the lock...

Page 69: ...of a single channel DVD player and two 15 inch flat screen monitors One is installed on the aft side of the left forward wardrobe cabinet and the other is installed on the forward side of the right af...

Page 70: ...counterclockwise to retract the locking pins and open the door inward As the door moves inward the rollers engage into the door tracks allowing the door to be lifted and latched in the overhead positi...

Page 71: ...ity to the various systems and components that require servicing and or inspection REFUEL DEFUEL DOOR OXYGEN FILL AND INDICATOR DOOR GROUND POWER DOOR REFUEL DEFUEL CONTROL PANEL DOOR GROUND AIR SERVI...

Page 72: ...g and allows access to the computer control panel for refueling and defueling LAVATORY WASTE DOOR The lavatory waste door is located on the right side of the aircraft in the aft wing fuselage fairing...

Page 73: ...in front and opens downward The door has a lever type latch mechanism A support strut on the door can be connected to the fair ing bracket to stabilize the door in the open position The strut must be...

Page 74: ...annunciation if a door is not in the correct position under specific conditions For the specific conditions refer to the annunciation description for each door in this section On the ground the CAS di...

Page 75: ...ion when on the ground or in flight CARGO DOOR TO LAND The electronic proximity sensor is indicating that the cargo door is not in the correct position posi tion when the airplane is in flight EMERGEN...

Page 76: ...Instruction Sheet Sep 13 2004 Flight Crew Operating Manual Volume 2 CSP 100 6 1 04 Challenger 300 Flight Crew Operating Manual Volume 2 REVISION 1...

Page 77: ...n 02 02 06 Components And Operation 02 02 06 Single Loops 02 02 06 Dual Sensing Loops 02 02 06 Bleed Air and Anti Ice Ducts 02 02 06 Trim Air System 02 03 01 Description 02 03 01 Air Conditioning Syst...

Page 78: ...an 7850 ft 02 04 06 Climb Mode with Selected Landing Field Elevation Greater Than 7850 ft 02 04 06 Cruise Mode with Selected Landing Field Elevation Greater Than 7850 ft 02 04 06 Takeoff From Airfield...

Page 79: ...al control system ECS provides regulated conditioned air to the flight deck and passenger cabin by using an air conditioning package PACK Aircraft pressurization is accomplished by regulating the over...

Page 80: ......

Page 81: ...t can also be supplied by the APU or an external ground cart Regulating valves and check valves are installed in the aft equipment bay ducting to control bleed air from the left and right engines and...

Page 82: ...urce selection valve operation and air distribution is controlled by two integrated air management sys tem controllers IASC The aircraft IP bleed air system is controlled from the AIR COND BLEED panel...

Page 83: ...re The check valve in the APU duct prevents the reverse flow of manifold air to the APU when the APU is shut down Check valves are not represented on the ECS or A ICE synoptic displays INTERMEDIATE PR...

Page 84: ...controls the opening closing and modulation of the APU bleed valve When the APU bleed valve is open APU bleed air is delivered to the right side of the bleed air manifold When the APU is shut down or...

Page 85: ...All bleed switching is done manually by the aircrew ENGINE START SEQUENCES During engine starts on the ground provided a bleed source has been selected engaging the engine start switch will auto matic...

Page 86: ...SINGLE LOOPS Single loops are used for left and right bleed ducts and trim air ducts DUAL SENSING LOOPS Dual sensing loops are used to monitor the following Bleed air ducts in the engine pylons Bleed...

Page 87: ...ply duct failure The HACKs are located just down stream from the trim air bulkhead AIR CONDITIONING SYSTEM DESCRIPTION The air conditioning system uses hot pressurized bleed air to create a controlled...

Page 88: ...ion loop The air temperature at the PACK discharge can be adjusted by opening or closing the temperature control valve The tem perature control valve modulates the hot air flow which by passes the air...

Page 89: ...TIONING SYSTEM Cont AIR CONDITIONING CONTROLS Controls for the air conditioning system are located at the AIR COND BLEED panel on the center pedestal AIR SOURCE NORM PACK ONLY OFF AIR COND BLEED TRIM...

Page 90: ...the trim air valves and none through the PACK This selection is used when a PACK failure exists A TRIM AIR ONLY S CAS will be displayed RAM AIR INLET Ram air enters the aircraft at the ram air inlet a...

Page 91: ...ovided by two main lines connected to the bulkhead check valve manifold These lines provide air at foot and head level Air distribution from the overhead gaspers is cold air only Air from provided at...

Page 92: ...r Shutoff Valve Check Valve Intermediate Pressure Bleed Aair Ram Air Conditioned Air Cold Air Precooled Air AIR SOURCE NORM PACK ONLY TRIM AIR ONLY OFF 1 1 2 3 4 4 TO OUTFLOW VALVE AVFAN PILOT HEATED...

Page 93: ...ont AIR DISTRIBUTION AND FLOW PATHS CABIN DISTRIBUTION SYSTEM CFO0203002_003 COCKPIT ENTRY WAY COCKPIT DISTRIBUTION DUCT UPPER DISTRIBUTION DUCT LOWER DISTRIBUTION DUCT CABIN LAVATORY CARGO SIDE VIEW...

Page 94: ...2_009 EXHAUST PATH COCKPIT AND CABIN GASPERS SUPPLY COCKPIT CONDITIONED AIR SUPPLY CABIN CONDITIONED AIR SUPPLY COCKPIT SUPPLY DUCT CABIN SUPPLY DUCTS CABIN SUPPLY CABIN SUPPLY DUCTS EXHAUST PATH CABI...

Page 95: ...ks reaches 122 F 50 C in 60 seconds then the fan operates at high speed If the temperature rises above 149 F 65 C during a 60 second time period while the aircraft is above 10 000 ft the fan is turned...

Page 96: ...g Manual May 06 2005 02 03 10 CSP 100 6 REV 2 CABIN and COCKPIT AIR DISTRIBUTION SYSTEM CFO0203002_006 RAM AIR INLET PACK GROUND CONNECT FROM APU RAM AIR EXHAUST TO OUTFLOW VALVE TOP DISTRIBUTION COCK...

Page 97: ...captain s MFD COMPONENTS AND OPERATION INTEGRATED AIR SYSTEM CONTROLLERS IASC Two IASCs control all automatic phases of pressurization Only one controller is active at a time with the other controller...

Page 98: ...m cabin climb rate is 635 sea level fpm slfpm NOTE When step climbs are performed at flight altitudes greater than 25 000 ft and at aircraft climb rates greater than 6000 fpm the cabin climb rate migh...

Page 99: ...takeoff is performed prior to cabin pre pressurization pressure bumps may occur TAKEOFF AND CLIMB Before takeoff cabin altitude may be selected as desired Selected altitude is displayed on the ECS sy...

Page 100: ...43 000 7476 8 6 8000 610 3 4 26 000 3189 8 0 44 000 7669 8 7 9000 716 3 8 27 000 3404 8 2 45 000 7850 8 8 10 000 816 4 1 28 000 3628 8 3 11 000 925 4 4 29 000 3864 8 3 12 000 1036 4 8 30 000 4111 8 3...

Page 101: ...AN and either FMS for a single installation or FMS 1 and FMS 2 for a dual installation Selection of one of the FMS settings will allow the pressurization landing altitude to be set from the applicable...

Page 102: ...CABIN ALTITUDE caution and warning thresholds will reach and remain at landing field pressure altitude 650 ft and 1550 ft respectively with both limited to 14 300 ft If a short climb followed by a lev...

Page 103: ...7850 FT CFO0204002_007 ALTITUDE THROTTLES ADVANCED TAKEOFF ELEVATION 10 000 ft DESCENT RATE 300 fpm 7850 ft CABIN ASCENT RATE 300 fpm LANDING ELEVATION 9000 ft TIME AIRCRAFT CLIM B AIRCRAFT ALTITUDE M...

Page 104: ...crease until the caution threshold reaches 8500 ft and the warning threshold reaches 9400 ft CFO0204002_006 TIME 10 Min T O FIELD ELEVATION CABIN ON DESCENT SCHEDULE TOWARD STORED TAKEOFF FIELD ELEVA...

Page 105: ...RATE APU RPM APU EGT FUEL QTY LBS TOTAL N2 OIL PRESS OIL TEMP FF PPH I T T N1 NU ND STAB AIL TRIM LWD RWD RUD GEAR FLAPS SPOILERS 7300 1000 0 61 0 600 84 7 46 115 7300 300 250 12000 6000 6000 93 0 84...

Page 106: ...sover and up to the trim air check valve L R PYLON BLEED LEAK TO LAND A leak has been detected in the engine pylon or tail cone before shutoff valve AIR COND TEMP FAIL TO LAND The automatic temperatur...

Page 107: ...The crossbleed valve has failed to move to the commanded position AIRCOND FAULT TO LAND A fault has been detected in the air conditioning system or there has been a loss of temperature sensing BLEED...

Page 108: ...ESS ON Emergency depressurization has been selected Emergency depressurization commands the out flow valve open but will attempt to limit the cabin altitude to approximately 15 000 ft MANUAL PRESS ON...

Page 109: ...Avionics Processor System IAPS 03 02 11 Description 03 02 11 Components and Operation 03 02 11 Integrated Avionics Processor System Card Cage 03 02 11 Input Output Concentrator Unit 03 02 11 Integrate...

Page 110: ......

Page 111: ...isual presentation of operating limits Aural alert warning messages Information is provided on four liquid crystal adaptive flight displays AFDs Master warning and caution lights on the glareshield en...

Page 112: ......

Page 113: ...on the Reversion panel to access these displays The FRMT button on the display control panel is used to select the SUMMARY synoptic page for display when PFD REV is selected on the reversion panel The...

Page 114: ...the proper component or display SYSTEMS TEST CONTROL PANEL DESCRIPTION The SYSTEMS TEST control panel is installed in the center pedestal The switch is used to start a pilot initiated test of several...

Page 115: ...NEL B B DCU 1 HS A DCU 8 HS DCU CHANNEL A A DCU 2 HS A DCU 5 HS A DCU 1 HS A DCU 6 B RDC 1 HS B DCU 8 HS B DCU 2 HS B DCU 5 HS RADIO INTERFACE UNIT RIU NO 1 RADIO INTERFACE UNIT RIU NO 2 B DCU 4 LB RI...

Page 116: ...tion message the master caution half of the two switches flash amber A single chime will accompany the master caution lights When the switch is pressed the flashing light in the switches will reset AU...

Page 117: ...generated it appears above the MSGS icon Pressing the CAS switch hides the new message Warning messages can not be paged out of view CKLST Selecting the CKLST switch displays the electronic checklist...

Page 118: ...the N1 analog gage when the thrust reversers are in transition white deployed green or red unsafe A VIB amber icon is displayed below the N1 gage when the vibration exceeds a predetermined value and h...

Page 119: ...sages by order of importance and order of occurrence The order of importance is accomplished by the use of color and aural alerts The four levels of CAS message importance are Warning Caution Advisory...

Page 120: ...ssages most caution messages and all advisory messages are inhibited during the take off and landing phase Selected messages are inhibited for takeoff when airspeed is above 80 kts and the aircraft re...

Page 121: ...magenta invalid or unknown status Each valve has an outline and a flowline REVERSION SWITCH PANEL DESCRIPTION A reversion switch panel located on the pilot s side of the center pedestal above the spo...

Page 122: ...ch is a three position switch 1 All displays use AHRS 1 data NORM The displays use their own side AHRS Pilot 1 copilot 2 2 All displays use AHRS 2 data AIR DATA REVERSION SWITCH The AIR DATA reversion...

Page 123: ...Their are no pilot controlled operations required for the IAPS Their are no pilot controlled reversionary operations for the IAPS COMPONENTS AND OPERATION INTEGRATED AVIONICS PROCESSOR SYSTEM CARD CA...

Page 124: ...eeded during flight and is intended to be a maintenance function COCKPIT VOICE RECORDER DESCRIPTION The cockpit voice recorder CVR is a crash survivable recording device that accommodates mandatory co...

Page 125: ...Chime CONFIGURATION CONFIG RUDDER TRIM 10 Triple Chime CONFIGURATION CONFIG SPOILERS 10 Triple Chime CONFIGURATION CONFIG STAB TRIM 10 Triple Chime CONFIGURATION GEAR 15 Triple Chime GEAR GEAR BAY OVH...

Page 126: ...O LAND 7 ELEVATOR SPLIT 10 ELT ON TO LAND EMER LIGHTS OFF TO LAND 16 EMER LIGHTS ON TO LAND 16 EMERGENCY EXIT TO LAND L R ENG ANTI ICE FAIL TO LAND 18 L R ENG DSPL MISCOMP TO LAND L R ENG FUEL SOV FAI...

Page 127: ...2 L R REVERSER FAIL TO 18 ROLL SPOILERS FAIL 10 EICAS CAUTION MESSAGES All caution messages are preceeded by a single chime Message Inhibits Chapt ref ROLL SPOILERS FAULT ROLL SPOILERS OFF 10 RUDDER L...

Page 128: ...TO LAND FIREX BTL 1 2 FAULT TO LAND FIREX BTL 1 2 LOW TO LAND FLAPS RATE LOW TO LAND L R FUEL EJECTOR FAIL TO LAND FUEL GRAV XFLOW FAIL TO LAND L R FUEL PUMP ON TO LAND FUEL QUANTITY FAULT TO LAND FUE...

Page 129: ...ANCED 12 FUEL GRAV XFLOW OPEN 12 L R FUEL PUMP OFF 12 L R FUEL PUMP ON 12 FUEL XFER OPEN 12 L R GEN OFF 7 GND SPOILERS OFF 10 HYD PUMP NOT AUTO 13 EICAS STATUS MESSAGES Message Inhibits Chapt ref L R...

Page 130: ...E MESSAGE CONFIG RUDDER TRIM VOICE MESSAGE CONFIG SPOILERS VOICE MESSAGE CONFIG STAB TRIM VOICE MESSAGE CPLT BRAKE FAULT TONE ELEC HYD GEN FAIL TONE ELECTRICAL FAULT TONE LEFT R ENG ANTI ICE FAIL TONE...

Page 131: ...ND SPOILERS FAIL TONE GND SPLRS NOT ARMED TONE HYD PRESS LOW TONE LEFT R HYD PRESS LOW TONE HYD PTU FAIL TONE LEFT R HYD SOV FAIL TONE LEFT R HYD TEMP HIGH TONE LEFT RIGHT ENGINE FIRE VOICE MESSAGE LE...

Page 132: ...ONE RUDDER LIMITER FAIL TONE SEC STAB TRIM FAIL TONE SELCAL DATALINK VOICE MESSAGE SELCAL HF 1 2 VOICE MESSAGE SELCAL VHF 1 2 3 VOICE MESSAGE SPOILERS FAIL TONE SPOILERS FAULT TONE STALL VOICE MESSAGE...

Page 133: ...00 AM ECS OXY QTY CAB ALT CAB RATE CAB P LNDG ALT ECS ELECTRICAL HYDRAULIC SUMMARY 1200 6200 1500 9 1 14000 L 45 BLEED PRESS R 60 20 28 5 24 0 35 GEN AMPS GEN AMPS BATT VOLTS BATT TEMP C 0 0 0 30 28 0...

Page 134: ...00 7777 1799 5 118 000 118 000 118 000 118 000 2 0000 190 0 108 00 118 000 STBY ABV TX 2 0000 AM DN UP CAB ALT CAB RATE APU RPM APU EGT FUEL QTY LBS TOTAL N2 OIL PRESS OIL TEMP FF PPH I T T N1 NU ND...

Page 135: ...STBY ABV TX 2 0000 AM DN CAB ALT CAB RATE APU RPM APU EGT FUEL QTY LBS TOTAL N2 OIL PRESS OIL TEMP FF PPH I T T N1 NU ND STAB AIL TRIM LWD RWD RUD GEAR FLAPS 7300 1000 0 61 0 600 84 7 46 115 7300 100...

Page 136: ...5 0 MCT TRIM V T 600 600 93 0 61 0 NI MACH HOLD ITT N2 OIL PRESS OIL TEMP FF PPH 84 7 46 115 7300 84 7 46 115 7300 APU RPM 100 250 APU EGT FUEL QTY LBS TOTAL 12000 6000 6000 S T A R T S T A R T STAB A...

Page 137: ...6 6 GEAR SPOILERS CAB ALT CAB RATE 7300 1000 UP 85 0 MCT 85 0 MCT TRIM 600 600 NI MACH HOLD ITT N2 OIL PRESS OIL TEMP FF PPH 84 7 46 115 7300 84 7 46 115 7300 APU RPM APU EGT FUEL QTY LBS TOTAL 12000...

Page 138: ...7300 APU RPM 100 250 APU EGT FUEL QTY LBS STAB AIL LWD RWD RUD NU ND 6 6 GEAR SPOILERS CAB ALT CAB RATE 7300 1000 FUEL COM1 NAV1 ATC1 TCAS ADF1 HF1 COM3 COM2 118 000 108 00 1200 1799 5 118 000 118 000...

Page 139: ...0 84 7 46 115 7300 APU RPM 250 APU EGT FUEL QTY LBS TOTAL 12000 6000 6000 STAB AIL LWD RWD RUD NU ND 6 6 GEAR CAB ALT CAB RATE 7300 1000 COM1 NAV1 ATC1 TCAS ADF1 HF1 COM3 COM2 118 000 108 00 1799 5 11...

Page 140: ......

Page 141: ...ed Avionics Processing System has failed PFD X TALK FAIL TO LAND Communication between the PFDs has failed REFs menu pages 1 2 and 3 are not synchro nized The EFIS comparator will be inoperative and i...

Page 142: ......

Page 143: ...ector Synchronization 04 01 06 Flight Director Lateral Modes 04 01 07 Flight Director Vertical Modes 04 01 13 Autopilot 04 01 21 Components and Operation 04 01 21 Description 04 01 21 Autopilot Engage...

Page 144: ......

Page 145: ...ommands through the flight director or automatically flying the aircraft through the autopilot The main functions of the AFCS are Dual independent flight directors Two axis pitch and roll autopilot Si...

Page 146: ...e onside displays In all other flight di rector modes only one flight director provides guidance to both left and right flight displays The pilot flying can select the onside flight director using the...

Page 147: ...rated by two gray vertical lines The left section displays lateral modes The center section displays the autopilot yaw damper and active flight director status The right section displays vertical mode...

Page 148: ...d knob Pressing the HDG button engages the heading mode and displays a green HDG annunciation on the PFDs The heading button controls the heading bug and digital display Pressing the push button in th...

Page 149: ...n profile the alti tude preselector is set below existing altitude and the aircraft is within the TOD top of descent window or above the existing altitude for VNAV climb i e VFLC ALT altitude hold but...

Page 150: ...ile in roll lateral GA pitch vertical TO altitude hold vertical speed flight level change and vertical GA modes FD synchronization is deselected when the AP FD button is released and no vertical or la...

Page 151: ...her lateral mode is se lected the flight director automatically defaults to the basic ROLL mode Roll mode generates commands to hold the ex isting heading when the mode is selected unless the roll ang...

Page 152: ...MODE The HDG switch and knob generate commands to capture and maintain a pilot selected heading Selected headings are dis played by a digital heading readout and heading bug on the PFD Heading mode is...

Page 153: ...closure rate Navigation capture clears the heading select mode A localizer capture also clears the half bank mode Dead reckoning operation is executed during the VOR station passage When navigation m...

Page 154: ...h or by pushing the MWS switch on the control wheel GA is deselected if the following occurs Autopilot engagement Another lateral or vertical mode is selected Pressing the SYNC button which selects pi...

Page 155: ...ctors with autopilot disengaged and APPR as the active lateral mode Change the coupled side when APPR mode is active The lateral approach mode generates commands to capture and track the signal from t...

Page 156: ...from the selected LOC source dis played on the PFD Upon back course mode selection the flight director will arm to capture the signal from the selected nav source If the flight director is in nav mode...

Page 157: ...itude by takeoff mode by go around mode by approach capture or any lo calizer capture The Half Bank Mode reduces the maximum commanded bank angle to 15 Half Bank Mode has no effect on roll mode operat...

Page 158: ...selected the FMS may select the pitch hold mode Deselecting VNAV when GP PATH or FCS ALTS are the active modes with flight plan target altitude as the active reference The pitch mode is deselected wh...

Page 159: ...upon the occurrence of any of the following Automatic transition to the track state Turning off the FD while the AP is disengaged Selection of any other active vertical mode Turning the altitude prese...

Page 160: ...r in the vertical capture field capture ALTS in green color in the vertical capture field track When the closest altitude being approached is the FMS altitude altitude select is annunciated on the PFD...

Page 161: ...elected as the active mode Altitude Hold Mode can be deselected as follows Turning Off the Flight Directors while the AP is disengaged Another active vertical mode is selected If VNAV has been selecte...

Page 162: ...above VMO Overspeed Mode is automatically engaged by the FGC unless altitude hold or altitude preselect are active The FGC generates the commands to reduce the airspeed to below VMO MMO While in over...

Page 163: ...s cleared by changing the source of the lateral navigation source to anything other than a valid localizer Glideslope mode generates commands to capture and track glideslope Captures can be performed...

Page 164: ...ive vertical mode Glide path mode generates commands to track a vertical path defined by the FMS Glide path capture disables use of the preselected altitude mode operation Glide path arm is annunciate...

Page 165: ...t directors show the flight guidance commands on the primary flight displays ENGAGEMENT PARAMETERS The autopilot can be engaged using the AP switch on the FGP if the following conditions exist Yaw dam...

Page 166: ...WHEEL PILOT S ROLL DISCONNECT HANDLE ON CONTROL WHEEL FCU FCU 2 TO RDC CH B SPC L DCP L ELEVATOR SURFACE POS L AILERON SURFACE POS RUDDER SURFACE POS R AILERON SURFACE POS R ELEVATOR SURFACE POS PILOT...

Page 167: ...arning sounds for approximately 1 1 2 seconds The autopilot can be manually disengaged by Pressing either master disconnect push button on the control wheels Activating the stab trim switches on the c...

Page 168: ...nized with the actual aircraft vertical and lateral reference when the autopilot is engaged The AP YD DISC switch disconnects the autopilot TOGA switches are provided on both thrust levers Normal and...

Page 169: ...engaged and transferred Right FD selected AP Flashing Red AP disengage warning and transferred to the Right FD Yellow AP engaged and transferred with AP synchronization in process the aileron and elev...

Page 170: ...ield Green Vertical takeoff mode annunciator in vertical capture field 26 V Green VNAV mode FMS NAV is valid and not overspeed mode V is prefixed on the vertical capture annunciator Flashing Yellow VN...

Page 171: ...Illumination of the respec tive red CAS will be accompanied by the takeoff CONFIGURATION voice warning YES AFCS MESSAGES FAIL Monitoring and indication of the autopilot modes may be unreliable AP HOL...

Page 172: ...Illumination of the respec tive red CAS will be accompanied by the takeoff CONFIGURATION voice warning YES AFCS MESSAGES FAIL Monitoring and indication of the autopilot modes may be unreliable AP HOL...

Page 173: ...iption 05 01 06 Components and Operation 05 01 06 APU Fuel Supply 05 01 06 Fuel Control Unit and Fuel Shutoff Solenoid 05 01 06 APU Shutdown Mode 05 01 06 Start and Ignition 05 01 07 Description 05 01...

Page 174: ......

Page 175: ...The APU should not be started above speed limits stated in the Approved Airplane Flight Manual as the APU may reverse windmill An engine control unit ECU controls and monitors all facets of APU operat...

Page 176: ...AUXILIARY POWER UNIT Volume 2 Flight Crew Operating Manual Sep 13 2004 05 01 02 CSP 100 6 REV 1 APU ACCESS PANEL LOCATIONS CFO0501002_007 SIDE ACCESS PANEL BOTTOM ACCESS PANEL...

Page 177: ...AFT BLEED AIR SYSTEM AIRCRAFT SKIN AMBIENT SENSING TEST PORT TORQUE MORTOR CONTROL PRESSURE REGULATOR OIL PUMP BLEED DIFFUSER CFO0501002_005 INLET AIR BLEED AIR ELECTRICAL CIRCUITS ECU FROM TO APU SYS...

Page 178: ...sion of ambient air by a centrifugal compressor The compressed air when mixed with fuel and ignited in the annular reverse flow combustor drives a single stage radial turbine The rotating shaft of the...

Page 179: ...duct is covered by an insulated exhaust muffler EXHAUST GAS TEMPERATURE The APU exhaust gas temperature EGT is displayed as a digital readout on the EICAS LUBRICATION SYSTEM DESCRIPTION The APU has a...

Page 180: ...SOLENOID The APU fuel control unit FCU meters fuel under command of the electronic control unit ECU During the start se quence the fuel shutoff solenoid located between the FCU and the fuel nozzles i...

Page 181: ...st 40 minutes Six consecutive and successful APU starts may be made at 10 minute intervals with a one hour waiting period prior to additional start attempts IGNITION SYSTEM The APU ignition system con...

Page 182: ...fold is no longer available to drive the turbine or cool the combustion system The loss of pneumatic energy is replaced with thermal energy fuel with significant temperature increase The following var...

Page 183: ...and behind the electrical connection assess door DC electrical power provided by the APU generator is controlled from the ELECTRICAL control panel Bleed air services are controlled from the AIR COND B...

Page 184: ...D BLEED CONTROL PANEL The APU bleed selection can be controlled from the AIR COND BLEED panel and the bleed valve position is displayed on the ECS synoptic page AIR SOURCE NORM PACK ONLY OFF AIR COND...

Page 185: ...es located on the ELECTRICAL control panel Shown with optional Hydraulic Motor Generator HMDG system EXT PWR L BATT R BATT OFF AVAIL ON ELECTRICAL OFF OFF OFF ON BUS TIE L GEN APU GEN R GEN R ESS R MA...

Page 186: ...85 0 MCT TRIM V T 600 600 93 0 61 0 NI MACH HOLD ITT N2 OIL PRESS OIL TEMP FF PPH 84 7 46 115 7300 84 7 46 115 7300 APU RPM 100 250 APU EGT FUEL QTY LBS TOTAL 12000 6000 6000 S T A R T S T A R T STAB...

Page 187: ...8 000 2 0000 190 0 108 00 118 000 STBY ABV TX 2 0000 AM DN CAB ALT CAB RATE APU RPM APU EGT FUEL QTY LBS TOTAL N2 OIL PRESS OIL TEMP FF PPH I T T N1 NU ND STAB AIL TRIM LWD RWD RUD GEAR FLAPS 7300 100...

Page 188: ...TEMP FF PPH 84 7 46 115 7300 84 7 46 115 7300 APU RPM 100 250 APU EGT FUEL QTY LBS STAB AIL LWD RWD RUD NU ND 6 6 GEAR SPOILERS CAB ALT CAB RATE 7300 1000 FUEL COM1 NAV1 ATC1 TCAS ADF1 HF1 COM3 COM2 1...

Page 189: ...air has been commanded above 20 000 ft or the APU bleed modulated due to excessive EGT APU FUEL SOV FAIL TO LAND The APU shutoff valve has failed APU OVERSPEED TO LAND The APU has shutdown due to an...

Page 190: ......

Page 191: ...ription 06 01 09 Components and Operation 06 01 09 Receiver Transmitter 06 01 09 HF Coupler 06 01 09 HF Antenna 06 01 09 Display Control Panel HF Tuning Control 06 01 10 MFD HF Control Menu 06 01 10 C...

Page 192: ...ight Compartment Printer Optional 06 01 16 Description 06 01 16 Components and Operation 06 01 16 Flight Data Recorder FDR Optional 06 01 17 Description 06 01 17 Components and Operation 06 01 17 Reco...

Page 193: ...wo maintenance interphone panels AUDIO CONTROL PANELS ACPs An audio control panel ACP is located on both sides of the instrument panel The ACPs allow the pilots to monitor the navigation radios monito...

Page 194: ...tion the oxygen mask microphone is active CONTROL WHEEL TX AND INPH SWITCHES The pilot and copilot s control wheels are equipped with TX INPH momentary switches The TX position allows transmitting on...

Page 195: ...the hand microphones allow the pilots to transmit on the communication radios or interphone HEADSET JACK PLUGS Headset panels are available at the two flight deck positions to connect the headsets to...

Page 196: ...e mounted on the control columns at each of the pilot s stations FLIGHT COMPARTMENT SPEAKERS Two speakers are located overhead in the flight compartment The speaker volume can be adjusted by rotating...

Page 197: ...t when selected on the flight deck audio control panel A headphone and microphone jack are installed at each location Microphone and headset jacks are installed at the following airplane locations Lef...

Page 198: ...lternately select the side 1 radios and the side 2 radios 3 Turn the MENU knob on the DCP to move the selection box on the radio menu to the radio COM NAV ATC TCAS etc frequency or channel that is to...

Page 199: ...submenu on the MFD The following operations are performed on the submenu Change the SQUELCH mode Turn the MENU knob to move the selection box to the SQUELCH control Turn the DATA knob or push the PUS...

Page 200: ...scratch pad and the line select keys Information is entered on the scratchpad then transferred to the appropriate location with the adjacent line select key Messages show if the information entered i...

Page 201: ...ency radio provides long range communication within the frequency range of 2 0 to 29 9999 MHz The HF radio has 280 000 communication channels together with six emergency and 16 programmable preset cha...

Page 202: ...DATA knob or push of the button selects the next squelch level option Select the HF power level Turn the MENU knob to move the selection box to the POWER control Turn the DATA knob or push the PUSH S...

Page 203: ...r HF systems received the message An aural SELCAL alert is sounded to advise the crew of the incoming call The SELCAL message on EICAS is removed when the radio transmit switch is activated for the VH...

Page 204: ...ommunication RADIO INTERFACE UNIT The radio interface unit provides three additional simultaneous voice communication channels when operated in conjunc tion with the SDU HIGH POWER AMPLIFIER The high...

Page 205: ...IC WICKS Static wicks are installed to discharge static electricity thereby reducing radio interference They are installed at the fol lowing locations Winglets wingtips and ailerons Elevators rudder v...

Page 206: ...ROL PANEL The CVR control panel is located on the center pedestal and is used to test the CVR system The CVR control panel contains A green TEST button and green indicator lamp Headset jack ERASE butt...

Page 207: ...nderwater locator device ULD is installed on the front of the recorder The ULD emits a pulsed acoustic signal into the water after ditching of the aircraft The ULD sonar beacon is capable of transmitt...

Page 208: ...telecomputing equipment to UHF antenna and SATCOM links If a data link device is installed on the airplane the cabin communication system has the capability to communicate with the data link device u...

Page 209: ...ing up to 30 days after activation The FDR starts to record when one of the following occurs STROBE BEACON switch is in the BEACON or STROBE position Weight off wheels as sensed by the proximity sensi...

Page 210: ...s failed FDR FAIL TO LAND The flight data recorder has failed FDR FAULT TO LAND The longitudinal lateral or normal accelerations parameters in the flight data recorder are inoper ative It may be possi...

Page 211: ...Pilot Circuit Breaker Panel Typical 07 01 07 CB 2 Copilot Circuit Breaker Panel Typical 07 01 08 CB 3 Left Side Equipment Rack Circuit Breaker Panel Typical 07 01 09 CB 4 Right Side Equipment Rack Ci...

Page 212: ......

Page 213: ...ation A separate battery powers the independent standby instrument system An optional hydraulically driven electrical generator is available to provide electrical power generation in the event all eng...

Page 214: ...INTRODUCTION Cont RIGHT CIRCUIT BREAKER PANEL RIGHT SECONDARY POWER CENTER LEFT CIRCUIT BREAKER PANEL LEFT SECONDARY POWER CENTER RIGHT DC POWER CENTER RIGHT BATTERY LEFT GENERATOR APU GENERATOR EXTER...

Page 215: ...y are fed by the distribution buses of the secondary distri bution centers and distribute electrical power to loads which require pilot access to the associated circuit breaker The electrical system i...

Page 216: ...cation of amps drawn from the GPU is provided With the external power cable connected the following indications are annunciated on the ELECTRICAL synoptic display EXT PWR symbol and line are white whe...

Page 217: ...ment for a limited duration Standby Instrument power is supplied by a dedicated 24 vdc battery The standby instrument is activated by a separate STBY INST switch located on the ELECTRICAL power panel...

Page 218: ...LECTRICAL cockpit control panel CIRCUIT BREAKER PANELS Two circuit breaker panels are located in the cockpit and are fed by the distribution buses of the secondary power centers They distribute power...

Page 219: ...D L DCP L PFD ATT HDG 1 AIR DATA 1 DISPLAYS INDICATING RECORDING L BLEED VALVES PRESS 1 PACK ENVIRONMENTAL DCU A RDC A CTRL 1 L PWR 1 R PWR 2 ANNUNCIATOR L PITOT TAT VANE CASE CTRL PWR L ENG INDICATIN...

Page 220: ...WR 2 L DC PUMP PTU R SOV R IND LDG GEAR HYDRAULIC DISPLAYS INDICATING RECORDING FDR L PWR 2 R PWR 1 CTRL 2 RDC B DCU B ANNUNCIATOR EMER DOME LIGHTS R ENG R WING BLD LK PWR CTRL R ICE DET CASE VANE R S...

Page 221: ...NGINE ELEC L ENG SOV GRAVITY X FLOW QTY 1 FUEL FLIGHT CONTROL PAX DOOR ENVIRONMENT L SIDE WINDOW ANTI ICE L FORCE SNSR MSTR DISC AUTO FLT TRIM ENTRY LIGHTS L CKPT PED CABIN SIGNS WING INSP MAP STOW BC...

Page 222: ...DJ AUTO FLT TRIM MSTR DISC FLIGHT CONTROL CABIN LIGHTS BUS CTRL PWR 1 PWR 2 INDICATING RECORDING 3 3 3 3 3 3 3 3 5 3 3 3 5 50 50 10 3 5 10 NORM 20 HYD GEN APU GEN R GEN R BATT SEC BUS 7 5 3 PWR TEST H...

Page 223: ...BUS L SPC BAT BUS R DCPC ESS BUS AVNX ENGINE FIREX FCTL LIGHTS ELECTRICAL EXT BAG AFT BAY 5 5 25 5 3 3 7 5 25 5 CFO0106002_002 FAN PWR 1 AVNX 35 PWR 2 GROUND SERVICE PWR 1 25 25 ELECT 5 EDC PWR HF 2 P...

Page 224: ...L BATT BUS CBP R ESS BUS CBP R MAIN BUS CBP R BATT BUS CBP CB2 C6 STBY INST R ESS BUS SPC R MAIN BUS SPC R AUX BUS SPC R BATT BUS SPC R BATT BUS DCPC R ESS BUS DCPC R MAIN BUS DCPC R AUX BUS DCPC L SE...

Page 225: ...U APU STRT RIGHT GEN LEFT AUX BUS LEFT MAIN BUS LEFT ESS BUS RIGHT ESS BUS RIGHT MAIN BUS RIGHT AUX BUS LBAT BUS RBAT BUS R BATT OFF R GEN OFF L GEN OFF CAGE STD B R T D I M BARO 240 220 200 180 M 47...

Page 226: ...ght Crew Operating Manual May 06 2005 07 01 14 CSP 100 6 REV 2 CONTROLS AND INDICATIONS EXTERNAL POWER CONTROL PANEL CFO0501002_006 EXTERNAL POWER CONTROL PANEL ON Gnd Service EXT DC AVAIL IN USE APU...

Page 227: ...t Crew Operating Manual Volume 2 REV 1 CSP 100 6 07 01 15 CONTROLS AND INDICATIONS Cont ELECTRICAL SUMMARY PAGE CFO0701002_009 CAS CKLST SKIP FRMT TFC TR WX ENTER A ICE FLT FUEL HYD L R ECS AUTO PLAN...

Page 228: ...Motor Driven Generator HMDG system CFO0701002_010 EXT PWR L BATT R BATT OFF AVAIL ON ELECTRICAL OFF OFF OFF ON BUS TIE L GEN APU GEN R GEN R ESS R MAIN R AUX L ESS L AUX L MAIN STBY INST OFF CFO07010...

Page 229: ...TRIM V T 600 600 93 0 61 0 NI MACH HOLD ITT N2 OIL PRESS OIL TEMP FF PPH 84 7 46 115 7300 84 7 46 115 7300 APU RPM 100 250 APU EGT FUEL QTY LBS TOTAL 12000 6000 6000 S T A R T S T A R T STAB AIL LWD...

Page 230: ...d or the battery has been automatically discon nected for overheat protection ELEC HYD GEN FAIL TO LAND The hydraulic generator has failed to come on line ELECTRICAL FAULT TO LAND An electrical system...

Page 231: ...f the standby instrument battery have failed APU GEN OFF APU GEN switch has been selected OFF L R BATT OFF The affected battery has been selected OFF BUS TIE MAN OPEN The bus tie has been manually sel...

Page 232: ......

Page 233: ...age Cup 08 01 06 Flight Crew Oxygen Mask Cold Weather Storage 08 01 06 Crew Oxygen Mask 08 01 07 Passenger Oxygen System 08 01 09 Description 08 01 09 Components and Operation 08 01 09 Electrical Pneu...

Page 234: ......

Page 235: ...and smoke goggles for aircrew protection Oxygen storage and distribu tion includes a cylinder s to store oxygen supply regulated pressure equipment for cylinder servicing such as refilling and dischar...

Page 236: ...and gives system information to the EICAS OXYGEN SYSTEM BASELINE CONFIGURATION OXYGEN PIPELINE ELECTRICAL SIGNAL LINE ELECTRICAL POWER LINE PNEUMATIC SIGNAL LINE CFO0801002_002 OVERBOARD DISCHARGE IN...

Page 237: ...ERBOARD DISCHARGE INDICATOR FILLER VALVE PRESSURE GAUGE TEST PORT CREW ELECTRICAL ELECTRICAL SUPPLY LP CONF SWITCH PAX E P A V FIRST AID L MAIN TO EICAS PRESSURE TEMPERATURE TRANSDUCER TO THERAPEUTIC...

Page 238: ...pressure for use with passengers therapeutic and crew masks The cylinder and regulator assembly is installed inside a dedicated compartment in the lavatory section right side The cylinder includes sa...

Page 239: ...cated on the right side of the fuselage directly forward of the right engine The oxygen service panel has a filler valve and a pressure gauge Replenishment of the oxygen system is a maintenance functi...

Page 240: ...sk it is impor tant not to stuff the harness into the nosepiece cavity as this could impede donning of the mask Another view is shown for clarity and the instructions are as follows 1 Insert the mask...

Page 241: ...he oxygen supplied to the mask is a mixture of ambient air and pres surized oxygen In this position the operator can turn the flow control knob to adjust the flow 100 When the control knob is in the 1...

Page 242: ...01 08 CSP 100 6 REV 1 OXYGEN SYSTEM Cont MICROPHONE CONTROL When the O2 MASK NORM switch on the associated audio control panel is selected to O2 MASK the microphone in the mask is activated CFO0801002...

Page 243: ...selected to AUTO the passenger oxygen masks automatically deploy if the cabin altitude climbs to 14 500 ft 500 ft Flow continues until cabin altitude drops below 9500 ft 500 ft MANUAL DEPLOYMENT Sett...

Page 244: ...bag incor porates a green chamber which inflates when oxygen flows to the mask When the oxygen masks drop passengers should don masks and pull the mask lanyard to initiate oxygen flow The masks will...

Page 245: ...in the flight compartment contains Halon 1211 Halon 1211 is effective on electrical oil and fuel fires and is suitable for use in cold weather To operate Remove from stowage bracket Hold extinguisher...

Page 246: ...UIPMENT Volume 2 Flight Crew Operating Manual Sep 13 2004 08 01 12 CSP 100 6 REV 1 EMERGENCY EQUIPMENT Cont HALON 1211 DISCHARGE NOZLE DISCHARGE LEVER CLASP NORMAL CHARGE PRESSURE GUAGE LOCKING PIN NY...

Page 247: ...er Useful life of a sealed PBE is 10 years from the date of manufacture NORMAL OPERATION Donning the PBE The PBE is mounted on the bulkhead behind the pilot s seat Some aircraft may have a second port...

Page 248: ...own over the face using the hands to shield the face and glasses from the oronasal mask cone 5 With both hands grasp the adjustment straps at the lower corners of the visor and pull outward sharply to...

Page 249: ...sting Heat is produced by both the chemical air regeneration process and transfer of body heat during the rebreathing cycle Heat build up within the hood is normal and is dependent upon the amount of...

Page 250: ...ath into the hood short circuiting the oxygen generating canister This condition may result in a build up of CO2 within the rebreathing vol ume in the hood Excessive CO2 is normally indicated by breat...

Page 251: ...each passenger seat The life vests are inflated by pulling the red CO2 release tabs An oral inflation tube is also available if the CO2 cartridge does not inflate the vest CFO0801002_007 WAIST STRAP...

Page 252: ...BACK PIECE BEHIND 4 FASTEN RINGS TO CATCH 5 PULL STRAPS TIGHT 6 JERK DOWN ON INFLATION TABS 7 SHOULD IT BECOME NECESSARY LIFE VEST CAN BE ORALLY INFLATED BY BLOWING INTO ORAL INFLATION TUBES CFO08010...

Page 253: ...crew closet or in the aft pyramid cabinet depending on cabin configuration Refer to Air Cruisers Com pany Operator s Guide for further information CONTROLS AND INDICATIONS PASSENGER OXYGEN CONTROL PA...

Page 254: ...oxygen bottle valve is closed or there is a miscompare in the number of bottles installed and the number of bottles selected on the Elec tro Pneumatic Actuating Valve unit This mes sage will normally...

Page 255: ...R Eng Fire Switches 09 01 06 Fire Ext 1 2 Switches 09 01 06 FIREX Bottle Pressures 09 01 07 Auxiliary Power Unit Fire Protection 09 01 08 Description 09 01 08 Components and Operation 09 01 08 Fire Ex...

Page 256: ......

Page 257: ...etection system detects fire in the engines and APU and overheat detection in the main landing gear bays The fire extinguishing system provides extinguishing capability for the engines and APU The det...

Page 258: ...UCTION Cont CFO0901002_007 ENGINE FIRE DETECTION APU FIRE DETECTION MAIN LANDING GEAR MLG OVERHEAT DETECTION FIRE DETECTION AND EXTINGUISHING FIREX CONTROL UNIT ENGINE INDICATION AND CREW ALERTING SYS...

Page 259: ...OLD VIB VIB ITT IGN IGN N2 OIL PRESS OIL TEMP FF PPH 84 7 46 115 7300 84 7 46 115 7300 APU RPM 300 250 APU EGT FUEL QTY LBS TOTAL 12000 6000 6000 S T A R T S T A R T STAB AIL LWD RWD RUD L R NU ND 6 6...

Page 260: ...ings Both loops must sense the fire or overheat condition un der similar parameters before flight deck fire indications are generated FIRE DETECTION AND EXTINGUISHING CONTROL UNIT The fire detection a...

Page 261: ...GNITION MACH HOLD L STARTER R STARTER OFF OFF FIRE EXT CRANK START START CRANK OFF N2 N1 SYNC EVENT FIRE R ENG FIRE ARMED ARMED AUTO FIRE FIRE L ENG FIRE APU FIRE AUTO APR APU OFF 1 2 3 4 5 6 1 2 3 6...

Page 262: ...s directed into the engine fire zones The selection of the L or R ENG FIRE switch determines which engine the bottles are discharged into the engine nacelle During an engine fire FIRE EXT 1 should alw...

Page 263: ...table provided applies to bottles with 4 3 lb agent Minimum Maximum FIREX Bottle Pressure 4 3 lb nominal weight Gage reading psig Temp C Minimum Maximum 55 251 343 50 277 354 45 288 367 40 302 380 35...

Page 264: ...loops The loops are connected to the fire detection and extinguishing control unit The loops are constructed of an outer metal sheathing and two internal wires that are separated by an insulating mate...

Page 265: ...itch is a momentary switch that applies discharge current to the selected cartridge A pressure switch a pressure gauge and one explosive squib for the APU is installed on the fire bottle The bottle is...

Page 266: ...the possibility of brake or tire overheat during takeoff and the fact that the MLG bays are constructed from composite material an overheat detection system has been installed as part of the aircraft...

Page 267: ...conducts to the second internal wire and a fire indication is generated FIRE DETECTION AND EXTINGUISHING CONTROL UNIT The control unit monitors the electrical resistance of each single loop system Whe...

Page 268: ...will occur Warning W CAS messages illuminate L ENGINE FIRE R ENGINE FIRE APU FIRE MLG BAY OVHT Control unit tests all detection and extinguishing components FIRE SYS IN TEST S CAS illuminates Both mas...

Page 269: ...AND An overheat condition has been detected in the main landing gear bays APU FIRE DET FAIL TO LAND An APU fire detection system has detected a failure that will not allow the detection system to indi...

Page 270: ......

Page 271: ...06 Flap Alerting 10 02 06 Flap Control Lever 10 02 07 Flap Position Indication 10 02 07 Spoiler System 10 02 08 Components and Operation 10 02 09 Spoiler Electronic Control Unit SECU 10 02 09 Flight S...

Page 272: ......

Page 273: ...d spoilers when operated symmetrically flight and ground spoilers DESCRIPTION The primary flight controls are arranged conventionally with rudder pedals and a control wheel and column for both the pil...

Page 274: ...sist the ailerons in roll control In order to reduce roll control forces an aileron balance geared tab is mounted on each aileron The balance tabs have a maximum 15 degrees of travel each side of the...

Page 275: ...t lever is released A microswitch senses the retraction of the roller and sends a signal of the disconnect status and a ROLL DISCONNECT W CAS message will be illuminated RUDDER RUDDER CONTROL SYSTEM T...

Page 276: ...loses pressure the lower rudder PCU is powered by the auxiliary hydraulic system The rudder PCUs also give protection to the rudder control surface against gust loads while the aircraft is on the grou...

Page 277: ...RIM RUDDER TRIM YAW DAMPER RUDDER LIMITER M FGC 1 FGC 2 AFT CABLE QUADRANT AND FEEL MECHANISM ARTIFICIAL FEEL RUDDER PEDALS POWER CONTROL UNIT RUDDER POSITION TO EICAS FLIGHT CONTROL PAGE LEGEND ELECT...

Page 278: ...flight crew to observe YD activity for system checks When the aircraft accelerates above 60 kt IAS the damping function is smoothly disabled until weight is off the wheels at which point it is re ena...

Page 279: ...they rotate in unison A control rod transmits pilot commands to the left and right forward quadrants The left side quadrant assembly includes a cable interface with the stick pusher servo of the stal...

Page 280: ...CONNECT When pulled the PITCH DISC handle isolates a jammed elevator control system Pulling the handle then turning 90 will allow the pilot or copilot to control the non jammed elevator A PITCH DISCON...

Page 281: ...HEMATIC MIC ID MIC ID STICK SHAKER STICK SHAKER STALL PROTECTION SYSTEM STICK PUSHER FLIGHT CONTROL SYNOPTIC PAGE POWER CONTROL UNIT ELEVATORS HORIZONTAL STABILIZER PITCH FEEL UNITS ELEVATOR AUTOPILOT...

Page 282: ......

Page 283: ...controlled and hydraulically actuated Horizontal stabilizer aileron and rudder trims are elec trically operated The multifunction spoilers and ground spoilers are operated hydraulically but controlled...

Page 284: ...switch causes electrical inputs to the rudder power control units that move the rudder to the position selected by the pilot A CONFIG RUDDER TRIM W CAS will also be illuminated if not properly configu...

Page 285: ...he aircraft has a nose down pitching moment with flap extension and nose up pitching moment with spoiler extension When these control surfaces are deflected the horizontal stabilizer trim moves so as...

Page 286: ...ID MIC ID TRIM ACTUATOR FGCS ROLL COMMANDS ROLL COMMANDS M M TRIM MOTOR CABLE INPUT MECHANICAL INPUT MECHANICAL INPUT ELECTRICAL INPUT LEGEND CONFIG AILERON TRIM CONFIGURATION CONFIGURATION WARNING LE...

Page 287: ...BREAKER LEFT MAIN 28 VDC HIGH POWER BREAKER SECONDARY ENGAGE RELAY PRIMARY ENGAGE RELAY RIGHT ESS 28 VDC LEFT MAIN 28 VDC COPILOT MASTER DISC RELAY PILOT MASTER DISC RELAY BRAKE 3 BRAKE 4 MOTOR COMM L...

Page 288: ...ed by the flap control unit before hydraulic pressure is available to the servo valve The pressure switch monitors system pressure between the arming solenoid valve and servo valve If hydraulic pressu...

Page 289: ...ing the flaps to 0 The lever is attached to dual RVDTs co located with a flap lever detent switch below the flap handle These dual RVDTs transmit the selected position to a flap control unit Moving th...

Page 290: ...system is computer controlled and hydraulically operated two ground spoilers provide ground lift dumping functions The multifunction spoilers provide roll assist proportional lift dumping and ground...

Page 291: ...SECU In normal operation there are nine detented positions between 0 and MAX The 0 position is gated and requires pressing the push button on top of the lever to release The 0 position can be reselect...

Page 292: ...t feature on the pilot s control wheel This action disconnects the pilot s wheel from the cable system permitting continued roll assist by the pilot if the jam is not in the pilot s wheel The ROLL SPO...

Page 293: ...TS SECU1 COMMAND MONITOR SECU2 COMMAND MONITOR OUTBD INBD 4 3 2 1 OUTBD INBD OUTBD INBD 4 3 2 1 OUTBD INBD GSSV1 SOV 3 SOV 1 SOV 2 GSSV2 SOV 3 SOV 1 SOV 2 LEFT MAIN 28 VDC ARINC 429 LEFT MAIN 28 VDC O...

Page 294: ...hrottle lever angle wheel speed weight on wheels and radio altitude MANUAL ARM Arms the ground spoilers regardless of the inputs required to arm in the AUTO position When deployed the ground spoiler p...

Page 295: ...ctronic unit PSEU processes information received from landing gear position WOW position thrust reverser position and fuselage door position and provides instructions to other aircraft systems Proximi...

Page 296: ...he angle of attack trip points The stick shaker activation and ignition activation are simultaneous In the event of an AOA increase rate greater than 1 degree per second the stall protection computer...

Page 297: ...eel master disconnect switch MSW The stick pusher is capable of operating immediately when the MSW switch is released This function is inoperable on JAA approved aircraft Should the SPS incorrectly ac...

Page 298: ...Operating Manual Sep 13 2004 10 02 16 CSP 100 6 REV 1 CONTROLS AND INDICATIONS FLAP CONTROL LEVER EICAS TRIM STATUS DISPLAY CFO1005002_007 FLAPS VFE 210 VFE 210 VFE 175 10 20 30 0 CFO1001002_010 TRIM...

Page 299: ...6 GEAR SPOILERS CAB ALT CAB RATE 7300 1000 UP 85 0 MCT 85 0 MCT TRIM 600 600 NI MACH HOLD ITT N2 OIL PRESS OIL TEMP FF PPH 84 7 46 115 7300 84 7 46 115 7300 APU RPM APU EGT FUEL QTY LBS TOTAL 12000 6...

Page 300: ...ON voice warning Configuration PITCH DISCONNECT Pitch disconnect has occurred on the ground with throttles at or above CLB ROLL DISCONNECT Roll disconnect has occurred on the ground with throttles at...

Page 301: ...played unless the primary stabilizer trim has already failed SPOILERS FAIL The spoilers have failed If the spoilers were deployed they will retract down to a float posi tion The spoilers will not floa...

Page 302: ...O LAND The Stall Protection Computer has automati cally reverted to settings for flaps 30 L R STALL SHAKER FAIL TO LAND The respective stall shaker has failed GND SPOILERS OFF The ground spoilers are...

Page 303: ...01 10 Air Data Flags 11 01 10 Air Data System 11 01 11 Description 11 01 11 Components and Operation 11 01 11 Airspeed Display 11 01 11 Reference Speeds 11 01 11 Low Overspeed Flap Speed Cues 11 01 11...

Page 304: ...tor Warning Flag 11 01 21 Flight Director Command Bars 11 01 21 Multifunction Displays 11 01 22 Description 11 01 22 Components and Operation 11 01 23 MFD Control Panel 11 01 23 MFD Control Panel 11 0...

Page 305: ...s 11 02 02 Chart Main Index 11 02 04 Chart Type Menu 11 02 07 Chart List 11 02 08 Chart NOTAMS Menu Display 11 02 10 Graphical Weather Optional 11 02 12 Graphical Weather GWX 5000 11 02 12 GWX Image L...

Page 306: ......

Page 307: ...ltitude attitude heading navigation and system information Each pilot is presented with this information on a primary flight display PFD and a multifunction display MFD A major interface with the EFIS...

Page 308: ...DME OPTION GPS OPTION HF COM OPTION HF COUPLER OPTION REVERSION SWITCH PANEL DISPLAY CONTROL PANEL CURSOR CONTROL PANEL WEATHER RADAR FLIGHT GUIDANCE PANEL PORTABLE MAINTENANCE ACCESS TERMINAL DBU OP...

Page 309: ...play Airspeed Mach display Altitude display Vertical speed display AFCS mode display Navigation display 00 225 IAS M 54 50 42 38 4 2 1 1 4 ALTS 20 10 20 10 350 16000 350 00 4 3 100 00 00 352 00 80 20...

Page 310: ...ters or the triangle shape used with the V bars flight director HORIZON LINE The horizon line is the midpoint indication of aircraft attitude With zero degrees of pitch and roll the white horizontal l...

Page 311: ...oll pointer and moves laterally with respect to the base of the roll pointer One brick width deflection of the rectangle is equivalent to a displacement of one ball width on a conventional slip skid i...

Page 312: ...ft upset or unusual attitudes When the pitch angle exceeds 30 or 20 degrees or roll exceeds 65 degrees left or right only the following information is displayed on the PFD Altitude Airspeed Attitude V...

Page 313: ...13 2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100 6 11 01 07 PRIMARY FLIGHT DISPLAYS Cont Example of decluttered EADI in excessive pitch 10 20 30 50 65 20 10 30 50 65 90 CFO1101002_019 90 1...

Page 314: ...DH MDA is set through the REFS menu ALTITUDE DISPLAY The altitude display is shown on the right side of the PFD as a moving tape with a fixed digital readout window The fine portion of the tape is ma...

Page 315: ...tion deviation and tracking modes The preselect altitude bug will change color and flash when the altitude acquisition and deviation parameters are exceeded Aural alerts accompany the visual alerts fo...

Page 316: ...lay and scroll through the menu pages on the PFD Rotate the MENU knob to position the cyan cursor box around the selectable value for the RA BARO MINS The PUSH SELECT button on the DCP selects the nex...

Page 317: ...a scale that is marked every 5 kt and numerically marked every 20 kt REFERENCE SPEEDS The takeoff reference speeds are presented on the speed scale as a V1 VR V2 and VT Manually set V speed values sho...

Page 318: ...eive data from ADC 1 only An amber ADC 1 message is displayed on both PFDs When 2 is selected the pilot s and copilot s adaptive flight displays receive data from ADC 2 only An amber ADC 2 message is...

Page 319: ...atic system provides total and static pressures to the integrated standby instrument The pressures are sensed by a standby pitot probe and two flush mounted standby static ports The primary pitot stat...

Page 320: ...r to ADC 2 The ADCs use the total air temperature to calculate the static air temperature SAT and the true airspeed TAS The use and distribution of the pitot and static sources are as follows P1 is th...

Page 321: ...and collision avoidance system TCAS Stall protection system The AHRS consists of two computers two flux detector units and two external compensator units Both Attitude Heading Reference Systems are ac...

Page 322: ...flux detectors COMPASS CONTROL AND SLEW SWITCHES There are two COMPASS HEADING switches and SLEW switches located on either side of the main flight instrument panel There are two modes of operation ma...

Page 323: ...When the alignment is complete the messages are removed and the attitude sphere is displayed The aircraft can be moved at this time If excessive airplane motion is detected during a ground alignment t...

Page 324: ...position of the compass card is the fixed lubber line The lubber line indicates the aircraft heading refer ence SELECTED HEADING REFERENCE The selected heading reference is presented on the heading di...

Page 325: ...RC switch on the DCP the available list will be shown VOR 1 LOC 1 VOR 2 LOC 2 FMS 1 FMS 2 OFF no display COURSE DISPLAY The selected source display is a three digit display preceded by a CRS label The...

Page 326: ...distance display shows the DME slant range distance to the navaid station When the DME H button is selected on the DCP the held DME frequency replaces the AUTO annunciation on the NAV CONTROL menu the...

Page 327: ...Flight Guidance modes are displayed on the top center portion of the PFD with three fields divided by thin vertical grey lines The left field of the line represents the lateral modes The center field...

Page 328: ...118 000 118 000 2 0000 190 0 108 00 118 000 STBY ABV TX 2 0000 AM 25 25 CID DIRECT 3 0 10000A 0 20 18325 12000B 95NM CID 95 NM 77 NM 0 20 IRK OSH 215 NM 0 59 KORD 339 NM 1 20 HDG 340 FMS2 340 UTC C 11...

Page 329: ...blank page New messages will then appear on this blank page All messages can be retrieved by subsequently pressing the CAS button on the MFD control panel CKLST The CKLST switch is used to present or...

Page 330: ...utton is used to display the Hydraulic synoptic page MFD CONTROL PANEL Optional MENU ADV Turn the MENU ADV knob to position the menu cursor around the desired shortcut menu item or alphanumeric entry...

Page 331: ...haracters and counter clockwise to move backwards through the characters With a chart in view rotate the DATA knob to cycle through the list of linked charts associated with the airport identified by...

Page 332: ...ton should be released to complete the STORE action STORE COMPLETE is displayed when a MEM button is released and the current MFD display parameters have successfully been stored A recall is requested...

Page 333: ...rmation in a single combined three dimensional 3D format on the MFD The 3D presentation depicts the flight plan and predicted vertical trajectory of the aircraft so the pilot can interpret the current...

Page 334: ...y depressing the DCP TFC button When there is not an active RA or TA the range is the last active TCAS range A second momentary press of the TFC button removes the TCAS overlay Continuously pressing T...

Page 335: ...nob the active display value or change the state of the item in the selection box REFS REFERENCE The selected V speed references are displayed on the airspeed display V1 VR V2 VT VGA and VREF are init...

Page 336: ...format is normal Position MFD REV L PFD is shut down L MFD displays compressed PFD format EICAS OPTIONAL The EICAS rotary switch is used to ensure that engine and CAS information are always available...

Page 337: ...ion rotary switch Position 1 All displays present AHRS 1 data Position NORM The displays present onside AHRS pilot 1 copilot 2 Position 2 All displays present AHRS 2 data AIR DATA The air data reversi...

Page 338: ...glideslope pointers and scales are not in view until an ILS frequency is selected If the localizer data becomes invalid a red LOC or GS flag is visible and the pointer and scale are removed from sight...

Page 339: ...he chronograph CHR begins counting upon depression of the CHR switch The first switch actuation starts the CHR from zero 00 00 Pressing the switch again stops the CHR timer Pressing the switch a third...

Page 340: ...S W and has numerals every 30 with bars every 10 The last numeral is not shown for example 24 means 240 Heading of the aircraft is read against the vertical lubber line To operate correctly the compas...

Page 341: ...6 11 01 35 STANDBY COMPASS Cont CFO1101002_031 N 3 B 10 10 C 33 LIGHT UNIT COMPASS DIAL COMPENSATORS BRACKET ADJUSTMENT SCREW B C A A B B CENTER INDEX MARK COMPASS CORRECTION CARD STANDBY COMPASS WIT...

Page 342: ...2 1 1 4 ALTS 20 10 20 10 350 16000 350 00 4 3 100 00 00 352 00 80 20 2 29 92 IN 68 68 7 9 UTC C 11 42 SAT 60 5 C ISA TAS GS 385 280 30 HDG 340 TR WX LX TNU NEBOR 2 4 W 100 30 33 N 340 3 6 E 1 2 1 5 S...

Page 343: ...W 30 33 N 3 6 DBQ ALO TNU NEBOR ANOSA CID IOW IA MXO 200 KCID 100 270 150 CFO1101002_005 FIRE 600 600 93 0 61 0 NI MACH HOLD VIB VIB ITT IGN IGN N2 OIL PRESS OIL TEMP FF PPH 84 7 46 115 7300 84 7 46 1...

Page 344: ...C ENTER TR WX SUMRY A ICE ECS ELEC FLT FUEL HYD L R 01002_009 AUTO PLAN SHLDR SIDE CFO1101002_043 MEM 1 MEM 2 MEM 3 STAT UPR ESC CHART JSTK A ICE SKIP CKLST ECS ELEC FUEL TR WX TFC HYD SUMRY FLT CAS E...

Page 345: ...NEL STANDARD OPTIONAL STANDBY INSTRUMENT TUNE NORM CDU ONLY MFD ONLY COM 1 121 50 LEFT DISPLAYS NORM MFD REV PFD REV ATT HDG NORM 1 2 AIR DATA NORM 1 2 RIGHT DISPLAYS NORM PFD REV MFD REV CFO1101002_0...

Page 346: ...enter of the attitude sphere Most likely cause is an AHRS fault or failure FD Indicates a fault in the flight guidance computer FMS 1 FMS 2 Indicates that data from the active nav source is missing or...

Page 347: ...LAND Communication between the PFDs has failed REFs menu pages 1 2 and 3 are not synchro nized The EFIS comparator will be inoperative and is unable to compare one or more of the following parameters...

Page 348: ......

Page 349: ...s Graphical Weather GWX and Enhanced Map Data features to the existing MFD displays The IFIS is made up of one or two optionally File Server Units FSU two Multifunction Controls and two MFDs The FSU p...

Page 350: ...l in of the menu MFD controls are used to select a chart for display pan around the chart zoom in or out on the chart and also change the orientation of the chart When aircraft position is available a...

Page 351: ...t is selected the orientation is set to default portrait or landscape as determined from the Jeppesen database The first push of the orientation button located below the CHART button on the MFD contro...

Page 352: ...e airport Select one of the shortcuts to display the associated chart The origin destination and alternate airport entries are supplied by the FMS when a flight plan is entered The Other Airport entry...

Page 353: ...tcut controls identify the selected chart and provide a quick means of selecting the indicated chart CHANGE SHORTCUT The change shortcut action allows the pilot to change an existing shortcut or fill...

Page 354: ...CHART button on the MFD control to show the last displayed chart 2 Turn the DATA knob on the MFD control to cycle through the list of linked charts associated with the airport iden tified on the displ...

Page 355: ...shows a list of the chart types available for the selected airport The possible selections are as follows Approach Airport Departure Arrival Airspace Noise SELECT CHART TYPE 1 Turn the MENU ADV knob...

Page 356: ...ts to be updated midway through the effective dates of a database Under these conditions the database will contain additional charts that become effective on a given date A chart in the list is displa...

Page 357: ...ontrol to display the Chart List VIA CHART MAIN INDEX The Chart Main Index should be displayed on the MFD 1 Turn the MENU ADV knob on the MFD control to position the menu cursor around the desired cha...

Page 358: ...FLIGHT INSTRUMENTS Volume 2 Flight Crew Operating Manual Dec 05 2006 11 02 10 CSP 100 6 REV 7 ELECTRONIC CHARTS OPTIONAL Cont CHART NOTAMS MENU DISPLAY Continued REV 7...

Page 359: ...ble either by requesting them using the onboard datalink or as hard copy When more than one NOTAM is available for the selected airport the number of available NOTAMS is displayed next to NOTAM legend...

Page 360: ...X 5000 GRAPHICAL WEATHER GWX 5000 The GWX 5000 function allows the pilot to view graphical weather images one at a time on the MFD New and saved GWX images are requested by the pilot via controls on t...

Page 361: ...X image function allows the pilot to select the GWX display format with the last viewed GWX image displayed on the MFD The display last GWX image function steps are as follows 1 Push the UPR or LWR FR...

Page 362: ...e PUSH SELECT button the MFD control to select the highlighted list item For each GWX image on the list a region abbreviation name of the image date month and time of the image is displayed The date m...

Page 363: ...the last model run which is 12Z today NEXRAD IMAGE A NEXRAD image is in view on the lower or upper display area of the MFD when selected from the GWX image list and the GWX format is active The intens...

Page 364: ...ble ground speed a track arrow is drawn from the center point of the storm cell out in the direction of the true track of the cell A ground speed readout in knots is displayed at the end of the track...

Page 365: ...al outlook definitions used by Universal Weather WX DEPICTION is based on a finite number of reporting stations For finer weather detail refer to other sources such as NEXRAD OR TAF reports The follow...

Page 366: ...d speed is indicated with the use of pennants and barbs on an arrow The pennants represent 50 knots barbs represent 10 knobs and half barbs represent 5 knots The total wind speed is obtained by the su...

Page 367: ...of the MFD when selected from the GWX image list and the GWX format is active the specified altitudes available for turbulence images x 1000 ft are 5 10 18 25 30 34 39 45 and 53 The following table l...

Page 368: ...ing image is in view on the lower or upper display area of the MFD when selected from the GWX image list and the GWX format is active The specified altitudes available for icing images x 1000 ft are 0...

Page 369: ...d from real time weather conditions Weather products are transmitted by the satellite on the intervals listed in the following table The following tables list the colors used on NEXRAD images to repre...

Page 370: ...splayed on the first page in order of most recent to oldest The second page displays the current TAF report available for that airport NATIONAL MET REPORTS The NATIONAL MET REPORTS menu provides selec...

Page 371: ...the cursor around the desired overlay selection under the OVERLAYS menu list a To view the overview legends turn the MENU ADV knob to the OVERLAY LEGENDS selection item b Push the PUSH SELECT button...

Page 372: ...n a submenu page of the MFD The airport IDs are supplied by the FMS and are based on the active flight plan The identifier of the OTHER airport is displayed as dashed to indicate an airport may be ent...

Page 373: ...the order they are received Selecting a SIGMET or AIRMET displays that report on a submenu page of the MFD A maximum of 50 active SIGMET reports and 75 active AIRMET reports can be presented To selec...

Page 374: ...r AIRMET depending on the selection made on the GRAPHICAL WEATHER menu page When there are multiple reports available additional pages are available to display the SIGMETs or AIRMETs When graphical SI...

Page 375: ...to control the various layers of information displayed on the GWX format The GWX Overlays Menu is selected from the Graphical Weather Menu with controls on the MFD Control The GWX Overlays Menu is use...

Page 376: ...INSTRUMENTS Volume 2 Flight Crew Operating Manual Dec 05 2006 11 02 28 CSP 100 6 REV 7 OVERLAYS Cont OVERLAY LEGENDS The OVERLAY LEGENDS page displays all the symbology used in the graphical weather o...

Page 377: ...associated airport When no data is received or the received data is corrupted or cannot be interpreted a gray circle is displayed for the associated airport To reduce display clutter the number of dis...

Page 378: ...AY When AIRPORT ICONS is selected ON from the OVERLAYS menu and the GWX format is selected the airport icons are displayed The AIRPORT ICONS depicts airports and reporting stations that are within the...

Page 379: ...GMET is selected from the OVERLAYS menu and the GWX format is selected the graphical SIGMET images are displayed on the MFD The SIGMET consists of a point line or unfilled polygon that defines the geo...

Page 380: ...BASE FUNCTIONS STATUS PAGE The STAT button on the MFD Control is used to display a menu of lesser used menus They are displayed when a Status Format Window is selected The STAT menu includes the follo...

Page 381: ...data bases A list of the installed databases is displayed and includes the name begin date an end date and status current or not current for enabled databases The Database Effectivity page is selecte...

Page 382: ...to enter information to change the chart region cov erage of the database The Chart Subscription page contains a subscription number data entry field a list of enabled regions and an add regions data...

Page 383: ...ed by Rockwell Collins Inc are entered on this page to load optional software FILE SERVER CONFIGURATION PURCHASED OPTIONS TYPE NO PART NO FUNCTION STATUS 12 MAY06 ENGINEERING SNAPSHOT CPN ECP 046 ENAB...

Page 384: ......

Page 385: ...12 01 06 APU Fuel Shutoff Valve SOV 12 01 07 Refueling Defueling 12 01 07 Description 12 01 07 Components and Operation 12 01 07 Fuel Computer 12 01 07 Pressure Fueling 12 01 07 Grounding Receptacles...

Page 386: ......

Page 387: ...nd right wings and supply fuel to the engines and APU Tanks can be refueled through a single point adapter or manually by overwing refueling The fuel computer controls automatic refueling powered cros...

Page 388: ...s replenished by gravity through flapper check valves installed on the division between the collector and the wing tanks and by a scavenge ejector when the engines are operating The right side backup...

Page 389: ...L TANK SYSTEM Cont COMPONENTS AND OPERATIONS TANK CONSTRUCTION The wing tanks are integral type fuel tanks that use a wet wing design and are sealed with a fuel resistant sealant CFO1201002_007 APU LE...

Page 390: ...k one for the wing tank and one for the surge tank which is located in the outboard area of each wing They are used to drain water and contaminates that collect in the fuel tanks and to complete the r...

Page 391: ...er source for its control or oper ation Proper operation of the primary feed ejector is signaled by a pressure switch located at the ejector outlet APU FUEL FEED The APU fuel feed is established from...

Page 392: ...alance Transfer is achieved by opening the transfer valve and then switching on the standby boost pump Fuel will be pumped from the wing through the transfer valve and the in active standby boost pump...

Page 393: ...The dual channel fuel system computer monitors and controls the refueling process Each channel receives signals from the fuel system and aircraft attitude information from the AHRS The computer uses t...

Page 394: ...ct FUEL AUTO position with the fuel selector switch and the two SOV toggle switches ON Verify SOV indication lamps illuminate OP Select TEST position with the fuel selector switch and the two SOV togg...

Page 395: ...weight off wheels indications and pitch and roll attitude from the AHRS to correct the fuel quantity probe data and display accurate fuel quantity information on the EFIS Failure monitoring and indica...

Page 396: ...ATION DESCRIPTION The FUEL control panel provides control and system indications for the fuel system The panel controls the boost pumps and provides manual control and indications of the gravity and p...

Page 397: ...EL QUANTITY INDICATIONS TOTAL FUEL Green digits indicate total fuel quantity over 600 lb 272 kg and each wing over 300 lb 136 kg LEFT OR RIGHT WING TANKS Amber digits and a FUEL IMBALANCE C CAS messag...

Page 398: ...84 7 46 115 7300 84 7 46 115 7300 APU RPM 100 250 APU EGT FUEL QTY LBS STAB AIL LWD RWD RUD NU ND 6 6 GEAR SPOILERS CAB ALT CAB RATE 7300 1000 FUEL COM1 NAV1 ATC1 TCAS ADF1 HF1 COM3 COM2 118 000 108 0...

Page 399: ...th a total fuel weight between 10 000 lb 4536 kg 600 lb 272 kg with a total fuel weight of less than 4700 lb 2132kg L R FUEL PRESSURE LOW The engine fuel pressure is below 6 psig L R FUEL PUMP FAIL TO...

Page 400: ...compensation FUEL XFER FAIL TO LAND The fuel transfer valve has failed L R ENG FUEL SOV CLOSED Respective engine fuel shutoff valve is closed FUEL BALANCED TO LAND The fuel is balanced within 100 lb w...

Page 401: ...Schematic 13 01 05 Right Hydraulic System Schematic 13 01 06 Auxiliary Hydraulic System 13 01 07 Description 13 01 07 Components and Operation 13 01 07 Auxiliary DC Motor Driven Pump 13 01 07 Auxilia...

Page 402: ...Instruction Sheet Sep 13 2004 Flight Crew Operating Manual Volume 2 CSP 100 6 1 04 Challenger 300 Flight Crew Operating Manual Volume 2 REVISION 1...

Page 403: ...IN DC bus can be powered by the L DC generator or the APU The R DCMP is powered by the L ESS bus The bus can be powered by the right dc generator or the APU if the left DC generator fails If no genera...

Page 404: ...ne accessory gearboxes LEFT HYDRAULIC SYSTEM RIGHT HYDRAULIC SYSTEM AUX HYDRAULIC SYSTEM Multi functional spoilers inboard Multi functional spoilers outboard Lower Rudder PCU Ground spoilers inboard G...

Page 405: ...ositions are OFF AUTO and ON The OFF and ON allow manual operation The AUTO position is the normal position for flight In this position the DCMPs will be off with flaps up and on with flaps set at 10...

Page 406: ...Ps and other heat sources within the engine nacelle The left and right hydraulic systems have a fuel hydraulic heat exchanger in each wing tank A thermostatically controlled bypass valve is installed...

Page 407: ...EL TANK HEAT EXCHANGER BYPASS VALVE INBOARD BRAKES UPPER RUDDER INBOARD GROUND SPOILERS INBOARD MULTIFUNCTION FLIGHT SPOILERS LEFT AND RIGHT INBOARD ELEVATORS LEFT THRUST REVERSER ALTN FLAPS VALVE FLA...

Page 408: ...HEAT EXCHANGER BYPASS VALVE ALTN FLAPS VALVE FLAPS BRV PTU MOTOR PTU PUMP C P PRESSURE TRANSDUCER 15 MICRON PRESSURE FILTER RETURN FILTER MANIFOLD PRV FIREWALL SHUTOFF VALVE RETURN QUICK DISCONNECT P...

Page 409: ...The pre charge pressure versus tem perature is set so that when the accumulator is discharged the accumulator will still have sufficient oil for a smooth con tinuous operation of the lower rudder as...

Page 410: ...F AUTO and ON In the OFF and ON po sitions the PTU valve is manually closed or open In the AUTO mode the PTU will only start when the left engine or the left EDP is inoperative or failed the right EDP...

Page 411: ...Operating Manual Volume 2 REV 2 CSP 100 6 13 01 09 HYDRAULIC SERVICING Cont HYDRAULIC SERVICING PANEL CFO1301002_007 A B LEFT SYSTEM RETURN B RIGHT SYSTEM PRESSURE RIGHT SYSTEM RETURN LEFT SYSTEM PRE...

Page 412: ...HYDRAULICS Volume 2 Flight Crew Operating Manual May 06 2005 13 01 10 CSP 100 6 REV 2 HYDRAULIC SERVICING Cont AUXILIARY ACCUMULATOR SERVICING CFO1301002_008 C C D D AUXILLARY ACCUMULATOR SERVICING...

Page 413: ...MICRON PRESSURE FILTER ELEMENT ACCUMULATOR AND ACCUMULATOR CHARGE MANIFOLD DRAIN HOLE AUX DCMP PRESSURE SWITCH C AUX ACCUMULATOR PRESSURE SWITCH B PRESSURE TRANSDUCER INTENSIFIER AUXILIARY FILL QUICK...

Page 414: ...ter pedestal From the hydraulic control panel the electric hydraulic pumps shutoff and selector valves and power transfer unit can be manually operated The Engine Indicating and Crew Alerting System E...

Page 415: ...N2 OIL PRESS OIL TEMP FF PPH 84 7 46 115 7300 84 7 46 115 7300 APU RPM 250 APU EGT FUEL QTY LBS TOTAL 12000 6000 6000 STAB AIL LWD RWD RUD NU ND 6 6 GEAR CAB ALT CAB RATE 7300 1000 COM1 NAV1 ATC1 TCAS...

Page 416: ...ulic shutoff valve did not close when one of the following occurred The respective ENG FIRE switch was pressed The respective HYDRAULIC SOV switch was selected CLOSED The automatic overtemp closure wa...

Page 417: ...Engine Anti Ice 14 01 06 Description 14 01 06 Components and Operation 14 01 06 Nacelle Anti Icing Valves 14 01 06 Engine Nacelle Ducting 14 01 06 T2 Sensor 14 01 06 Engine Spinner 14 01 06 Air Data...

Page 418: ......

Page 419: ...data probes are heated using electrical power Anti icing of the aircraft tail surface is not required Two ice detectors provide indication to the flight crew of icing conditions The anti ice protecti...

Page 420: ...quency of the probe to a non icing value that allows the detection system to reassess if ice is accumulating When the ice is removed the heaters are de energized As ice builds again on the probe the h...

Page 421: ...ludes the powerplant interface to the right intermediate pressure valve IPV and right high pressure valve HPV Left pylon dual loops includes the powerplant interface to the left IPV and left HPV Right...

Page 422: ...sociated with wing anti icing The wing anti icing piccolo ducts uniformly spray hot bleed air onto the inner surfaces of the leading edges The bleed air used to anti ice the leading edges is dissipate...

Page 423: ..._006 T T INSULATED DUCTS PICCOLO DUCTS PICCOLO DUCTS WING CROSS BLEED VALVE WING ANTI ICE INTEGRATED AIR SYSTEM IAS CONTROLLER NO 2 INTEGRATED AIR SYSTEM IAS CONTROLLER NO 1 T T T T T T TEMPERATURE SE...

Page 424: ...e nacelle leading edge The air is then discharged overboard through an exhaust duct located at the bottom of the nacelle inlet T2 SENSOR A T2 sensor is installed in the inlet housing of each engine an...

Page 425: ...a probe heater will signal the DCU to display the appropriate EICAS message COMPONENTS AND OPERATION PITOT STATIC PROBES There are two pitot static masts one on either side of the nose The pitot stati...

Page 426: ...ay but not necessarily be indicated by ice accretion on side windows Temperature controllers one for each windshield and window monitor the electrical resistance of the tem perature sensors that are e...

Page 427: ...destal is used to operate the anti ice systems Anti ice system operation and fault presentation is provided on the ANTI ICE synoptic display The ANTI ICE synoptic display monitors the pneumatically op...

Page 428: ...MRY COM1 NAV1 ATC1 TCAS ADF1 HF1 COM3 COM2 118 000 108 00 7777 1799 5 118 000 118 000 118 000 118 000 2 0000 190 0 108 00 118 000 STBY ABV TX 2 0000 AM DN UP CAB ALT CAB RATE APU RPM APU EGT FUEL QTY...

Page 429: ...are not selected on ICE DETECTOR FAIL TO LAND Both ice detectors have failed L R PITOT HEAT FAIL TO LAND The respective pitot mast or base heater has failed L R PROBE HEAT OFF TO LAND Probe heat is o...

Page 430: ...e has been detected and the engine and wing anti ice systems are selected on ICE DETECTOR FAULT TO LAND One ice detector has failed the other should continue to operate normally L R PROBE HT CTRL FAIL...

Page 431: ...TO LAND One ice detector has failed the other should continue to operate normally L R PROBE HT CTRL FAIL TO LAND The respective probe heat controller has failed The probe heat will fail ON TAT HEAT F...

Page 432: ......

Page 433: ...Safety Pin 15 01 08 Normal Extension and Retraction 15 01 09 Gear Extension 15 01 09 Gear Retraction 15 01 09 Manual Release System MRS 15 01 10 Tires and Brakes 15 01 11 Description 15 01 11 Compone...

Page 434: ......

Page 435: ...ed by the Proximity Sensor System PSS and displayed through a combination of EICAS mes sages and aural alerts Each of the main landing gear is equipped with self adjusting multidisc carbon brakes The...

Page 436: ...A GEAR DISAGREE caution message is posted if any of the following conditions occur Any one gear remains in transit for more than 28 seconds The position of at least one gear does not agree with landi...

Page 437: ...arbon Brake Assemblies Dual Wheels Uplock Mechanism Extension and Retraction actuator Auxiliary Extend Assembly Electrical Harnesses and Hydraulic Dressings MAIN GEAR DOOR The main gear door is mechan...

Page 438: ...CFO1501002_001 MECHANICALLY OPERATED DOOR UPLOCK MECHANISM AIRFRAME MOUNTED BRAKE WEAR INDICATOR TWO PER ASSEMBLY BRAKE ASSEMBLY TRAILING ARM UPLOCK ROLLER ON THE PIVOT OF THE MAIN FITTING AND TRAILI...

Page 439: ...2 REV 1 CSP 100 6 15 01 05 LANDING GEAR Cont MAIN GEAR DOWNLOCK SAFETY PINS A downlock safety pin at the end of the side brace assembly secures each of the main landing gear in position while on the g...

Page 440: ...ch provides steering and castering func tions for the NLG during ground maneuvers With the torque link attached the gear can only be rotated 120 in either direction Attempting to rotate beyond this ca...

Page 441: ...olume 2 REV 1 CSP 100 6 15 01 07 LANDING GEAR Cont CFO1501002_004 MANUAL RELEASE ASSEMBLY DOOR RETRACTION ACTUATOR AFT DOOR NOSE GEAR FORWARD DOOR DOOR UPLOCK UPPER DRAG BRACE LOWER DRAG BRACE DOWNLOC...

Page 442: ...ep 13 2004 15 01 08 CSP 100 6 REV 1 LANDING GEAR Cont NOSE GEAR DOWNLOCK SAFETY PIN A downlock safety pin within the drag brace assembly secures the nose landing gear in position while on ground CFO15...

Page 443: ...cally engaged to secure the landing gear in the extended position GEAR RETRACTION During retraction the nose gear retracts forward and the main gear retracts inward During landing gear retraction no W...

Page 444: ...r actuators The MLG quadrant operates the MLG uplock manual release levers via tension cables Displacement of the uplocks releases the MLGs for gravity extension The manual selector valve when activat...

Page 445: ...and outboard brake control valves Ground mode is established by confirmation of either left or right weight on wheels inputs from the proximity sensors that indicates ground for more than 5 seconds or...

Page 446: ...ttle valves Differential braking is not possible with PARK EMER BRAKE handle and does not provide anti skid protection To prevent hydraulic fluid migration from the right system to the left system set...

Page 447: ...AKE CONTROL UNIT PRESSURE LEFT HYDRAULIC SYSTEM RETURN LEFT HYDRAULIC SYSTEM WHEEL SPEED TRANSDUCER PRESSURE SWITCH BRAKE ACCUMULATOR PRESSURE RIGHT HYDRAULIC SYSTEM RETURN RIGHT HYDRAULIC SYSTEM SHUT...

Page 448: ...ACCUMULATORS The main and park emergency brake accumulators are located on the aft side of the underwing fairing support frame The parking emergency brake accumulator is connected to a gauge and charg...

Page 449: ...The Nosewheel Steering System NWS is armed by selecting the NWS switch on The NWS switch is located on the LANDING GEAR control panel and is illuminated when it is in the OFF position Steering command...

Page 450: ...ROL SYSTEM OFF NWS STEERING ACTUATORS NOSE WHEEL ASSEMBLY LEFT HYDRAULIC SYSTEM STEERING MAINFOLD TO EICAS STEERING CONTROL UNIT WOW NOSE LANDING GEAR DOWN AND LOCKED PSEU RUDDER PEDALS NOSEWHEEL STEE...

Page 451: ...R UP UPLOCK SENSOR DETECTS GEAR UP AND BOTH DOWNLOCK SENSORS DETECT GEAR NOT DOWNLOCKED GEAR UP AND NO GEAR WARNING AND EITHER NO GEAR DISAGREE OR GEAR DISAGREE WITH HANDLE UP GEAR UP AND NO GEAR WARN...

Page 452: ...NS DESCRIPTION Flight deck controls activate normal gear extension and retraction emergency extension nosewheel steering and warning horn mute The EICAS presents indications of landing gear operation...

Page 453: ...TRACTION ACTUATOR SEQUENCING CANISTER RESTRICTOR UP GEAR UP DOWN LOCK UNLOCK LOCK UNLOCK LOCK UNLOCK GEAR DOWN UP DOWN GEAR DOWN UP DOWN RH MLG UPLOCK RH SIDE BRACE ACTUATOR LH MLG UPLOCK LH SIDE BRAC...

Page 454: ...RETRACTION ACTUATOR SEQUENCING CANISTER RESTRICTOR UP GEAR UP DOWN LOCK UNLOCK LOCK UNLOCK LOCK UNLOCK GEAR DOWN UP DOWN GEAR DOWN UP DOWN RH MLG UPLOCK RH SIDE BRACE ACTUATOR LH MLG UPLOCK LH SIDE BR...

Page 455: ...ER LANDING GEAR INDICATION In flight landing gear position indication is provided on the EICAS OFF NWS CFO1501002_025 STAB AIL LWD RWD NU 6 6 TRIM CAB ALT CAB RATE 7300 1000 ND FLAPS 0 GEAR SPOILERS S...

Page 456: ...cates that the landing gear position and the LANDING GEAR switch position do not match after the 28 second delay GEAR SYS FAIL TO This indicates a complete failure of the gear control or the loss of t...

Page 457: ...or more of the pilot s brake pedal sensors LVDTs has failed WOW FAIL TO One or more of the following conditions exist Failures have been detected in two or more Weight On Wheels WOW sensors Any disag...

Page 458: ......

Page 459: ...ight Cockpit Lights Panel 16 01 04 Standby Instrument Lighting 16 01 05 Chart Holder and Map Reading Lights 16 01 06 Flashlights 16 01 06 Emergency Lighting 16 01 07 Description 16 01 07 Components an...

Page 460: ......

Page 461: ...The cockpit lighting provides illumination of all control panels and instruments installed in the flight compartment that are not otherwise illuminated by their own integral lighting system or displa...

Page 462: ...ONE 2 PEDESTAL DIMMER ZONE 2 DIMMER ZONE 1 DIMMER ZONE 3 DIMMER ZONE 4 COCKPIT LIGHTS GSHLD L SIDE DIM BRT DIM BRT PEDESTAL DIM ANNUN PFD MFD BRT DIM BRT COCKPIT LIGHTS GSHLD R SIDE DIM BRT PFD MFD DI...

Page 463: ...lled via this potentiometer PEDESTAL This potentiometer controls the lighting intensity of equipment installed in the pedestal The FMS display intensity is reg ulated by the dim button on the FMS cont...

Page 464: ...m the main entryway control panel is disabled The dome light is powered by the right main bus and is protected by the DOME circuit breaker within the CABIN group on the copilot circuit breaker panel W...

Page 465: ...in bus power to the cockpit lights is lost power to the standby lights is automatically switched to the right essential bus These standby instruments are as follows Standby compass Standby instrument...

Page 466: ...are overhead lights that shine downward onto the crew lap area for map reading lighting Individually controlled reading lights are installed in the overhead panel Light intensity is adjusted by a dim...

Page 467: ...rgency lights will provide illumination of the aircraft s immediate area When the battery switch is ON and the EMER LTS switch is OFF an EMER LIGHTS OFF C message is displayed When the EMER LTS switch...

Page 468: ...elected white or red The red light system will generally be used for ground operations since it minimizes the unfavorable effects on vision of the crew or on personnel outside the aircraft during grou...

Page 469: ...ntrolled by the ENTRY light switch and is powered by the hot bus regardless of the BATT switch position GALLEY LIGHTS Fluorescent lighting is provided for the passenger refreshment area LAVATORY LIGHT...

Page 470: ...LIGHTING Volume 2 Flight Crew Operating Manual Sep 13 2004 16 01 10 CSP 100 6 REV 1 AIRSTAIR LIGHTING CFO1601002_024 STAIR LIGHT A A B B MICROSWITCH...

Page 471: ...itched on by a single click on the push button After 15 minutes in normal operation the output will automatically flash for a period of 10 seconds then it will go back to normal operation for approxim...

Page 472: ...LIGHTING CFO1601002_021 TAXI LANDING LIGHTS WING INSPECTION LIGHT BEACON BEACON LANDING LIGHT LANDING LIGHT BEACON NAV ANTI COLLISION LIGHTS NAV ANTI COLLISION LIGHTS NAV ANTI COLLISION LIGHTS LANDIN...

Page 473: ...gency lights and passenger messages are shown on the EICAS primary and status pages A brief explanation of each message is provided MESSAGE INHIBITS MEANING AURAL WARNING EMER LIGHTS OFF The cabin eme...

Page 474: ...mergency lights and passenger messages are shown on the EICAS primary and status pages A brief explanation of each message is provided MESSAGE INHIBITS MEANING AURAL WARNING EMER LIGHTS OFF The cabin...

Page 475: ...7 01 08 Components and Operation 17 01 08 TCAS Mode Select 17 01 08 Control Operation 17 01 09 Resolution Advisory 17 01 10 Traffic Advisory 17 01 10 TCAS Voice Related Aural Alerts 17 01 11 PFD TCAS...

Page 476: ...ption 17 01 33 Components and Operation 17 01 34 Dead Reckoning DR 17 01 34 FMS Calculated VSPEEDS 17 01 34 GPS Control 17 01 34 Global Positioning System GPS 17 01 34 Predicted RAIM 17 01 35 Required...

Page 477: ...trols and wiring are designed and installed so that the operation of any of the system components will not adversely affect or will not be adversely affected by the simultaneous operation of any other...

Page 478: ...a HI LO sensitivity control This marker receiver provides audio and visual marker information for cockpit indi cations The ADF receiver operates in the frequency range of 190 to 1799 kHz and the mari...

Page 479: ...elect the CONTROL menu of the radio Turn the MENU knob to move the selection box on the CONTROL menu Turn the DATA knob to change the mode or select an option or push the PUSH SELECT button to step th...

Page 480: ...lect ATC 1 or ATC 2 as the active transponder Set the Flight ID Turn the MENU knob to move the selection box to the Flight ID control Turn the TUNE knobs to set the desired Flight ID characters Select...

Page 481: ...the MFD as the master tuner CDU TUNING The CDU provides tuning control of both the on side and cross side radios Data entry to the CDU is made through the scratchpad and the line select keys Informat...

Page 482: ...nd other factors DME HOLD FUNCTION The DME hold function splits the paired tuning between DME and VHF navigation systems to enable independent opera tion The DME hold function holds the DME transceive...

Page 483: ...Y on either MFD causes the TCAS to go to standby mode At system power up on the ground the system powers up in standby mode TA RA is the normal TCAS mode When TA RA mode is set the TCAS computer gener...

Page 484: ...d of the ATC system has the primary responsibility for avoiding mid air collisions The TCAS II system provides no indication of traffic conflicts with the other aircraft without operative transponders...

Page 485: ...b is turned or the knob is pushed The beacon code entry uses active tuning control operation and any code may be entered between 0000 and 7777 The IDENT switch is located on both control wheels and st...

Page 486: ...sion area The PT symbol is displayed if the tar get does not qualify for a TA but is currently within 6 nm and 1200 feet of the TCAS airplane Other Traffic open cyan color diamond The other traffic OT...

Page 487: ...dequate separation Descend Descend Descend to nominal 1500 fpm Descend Crossing Descend Same as Descend Descend aircraft s flight path will cross the flight path of the intruder Increase Descent Follo...

Page 488: ...is tested White TA ONLY appears when RA is inhibited White TCAS OFF appears when the system is off The failure messages appear on the VSI and MFD They are TCAS RA FAIL TCAS FAIL TCAS RESOLUTION ADVISO...

Page 489: ...P is used to display TR WX on the PFD Graphical terrain data is automatically displayed on the MFD when a terrain hazard is encountered Each time the TAWS computer commands a terrain popup the MFD aut...

Page 490: ...Display switches refer to Chapter 11 1 24 for further description DISPLAY CONTROL PANEL DCP TAWS WARN PANEL CAS CKLST SKIP FRMT TFC ENTER TR WX SUMRY A ICE ECS ELEC FLT FUEL HYD L R CFO1101002_009 AUT...

Page 491: ...AIN CLOSURE RATE TERRAIN TERRAIN PULL UPI MODE 2 EXCESSIVE DESCENT RATE SINKRATE PULL UPI MODE 1 SINK AFTER TAKEOFF DON T SINKI MODE 3 EXCESSIVE DEVIATION BELOW GLIDESLOPE GLIDESLOPE MODE 5 EXCESSIVE...

Page 492: ...nunciates a GND PROX amber CAS alert on the PFD and generates an aural SINKRATE SINKRATE The aural alert will be annunciated once and will be repeated only if condition degrades by more than 20 based...

Page 493: ...sub modes Mode 2A and Mode 2B MODE 2A Mode 2A is activated when flaps are not in the landing position Penetration of the alert area will annunciate a GND PROX amber CAS on the PFD and generate an aur...

Page 494: ...GND PROX on the attitude display of the PFD and enable an aural TERRAIN TERRAIN The aural and the visual alerts are annunciated continuously and will remain until the condition is rectified Penetrati...

Page 495: ...r go around the TAWS stores the altitude value at which the descent began and compares successive altitude data to the stored value Activation of the warning is induced when the minimum terrain clear...

Page 496: ...Mode 4A begins at 30 feet AGL and extends vertically to an altitude of 500 feet AGL During penetration of the alert area above 190 knots the upper boundary increases with airspeed to a maximum of 100...

Page 497: ...O LOW TERRAIN warning The aural and visual remain until the airplane exits the envelope Penetration of the alert area below 159 knots annunciates an amber GND PROX display on the PFD and generates an...

Page 498: ...below minimum terrain clearance will annunciate an amber GND PROX display on the PFD and generate an aural TOO LOW TERRAIN warning CFO1701002_018 200 0 400 600 800 1000 1200 1400 1600 1800 2000 2200 2...

Page 499: ...ane continues to descend and deviates more than 2 dots below the glideslope an aural GLIDESLOPE warning is generated at the same volume level as all other warnings An amber GND PROX is dis played on t...

Page 500: ...function generates annunciation for descent below predetermined altitudes The aural ONE HUNDRED FIFTY and THIRTY indicates the transition through 100 50 and 30 feet AGL The last annun ciated or trans...

Page 501: ...t 30 feet AGL at 40 of bank at 150 feet AGL to 55 of bank at 2450 feet AGL This will generate an aural BANK ANGLE BANK ANGLE The alert is annunciated once and will repeat if the bank angle increases b...

Page 502: ...director display is removed from the display an increasing performance shear WINDSHEAR W flashes for 5 seconds then remains steady An aural tone WINDSHEAR WINDSHEAR warning is activated For a decreasi...

Page 503: ...1 SOLID RED Areas of terrain that satisfy the terrain warning alert criteria 2 SOLID AMBER Areas of terrain that satisfy the terrain caution alert criteria 3 GREEN AMBER RED DOT PATTERN Areas of terr...

Page 504: ...LL UP display is annunciated on the PFD When warnings are activated areas which meet the terrain collision alert criteria are depicted red Terrain automatically comes up in MAP mode on MFD at a 10 nm...

Page 505: ...e runway TCF alerts are based on current airplane location nearest runway center point position and radio altitude along with an internal database that includes all worldwide hard surfaced runways gre...

Page 506: ...0 108 00 118 000 STBY ABV TX 2 0000 AM ECS 25 25 340 UTC C 11 42 SAT 15 5 C ISA TAS GS 250 254 30 MFD CONTROL TR WX LX 24 W 30 33 N 3 6 DBQ ALO TNU NEBOR CID IOW IA 200 KCID 100 270 150 FUEL SUMRY TR...

Page 507: ...e radar menu The radar menu can be displayed on the PFD by pressing the RADAR button on the display control panel Selection of the radar display is accomplished by pressing the TR WX button on the dis...

Page 508: ...sabled GROUND CLUTTER SUPPRESSION GCS MODE This feature is selected those radar returns that appear as ground clutter are suppressed This feature eases the interpretation of rainfall when viewed from...

Page 509: ...a single FMS system is installed it is operated via the CDU installed on the right side of the center pedestal When two FMS systems are installed each CDU controls its on side FMS The FMS can be initi...

Page 510: ...has been achieved but before posting FMS computed VSPEEDS on the PFD the aircrew should verify that the inputs that were entered into the FMS for computation of takeoff or approach performance reflect...

Page 511: ...vigation before each flight Status and integrity of the GPS position solution shows on the MFD LRN STATUS page RAIM is used to assure that the GPS solution meets the required accuracy criteria that fo...

Page 512: ...LEGS DEP ARR PERF MFD MENU MFD ADV MFD DATA PREV NEXT EXEC IDX TUN CLR DEL BRT DIM A B C D E F G H I J K L M N O P Q R S T U V W X Y Z SP 1 2 3 4 5 6 7 8 9 0 COM1 COM2 COM3 HF1 HF2 CAB PA HDPH SPKR I...

Page 513: ...ness warning system has failed TAWS TERR FAIL TO LAND The terrain function of the terrain awareness system has failed TAWS TERR NOT AVAIL TO LAND The TAWS terrain data base has no data for the current...

Page 514: ......

Page 515: ...6 Thrust Calculations 18 01 07 Thrust Mode Annunciation 18 01 07 Max Power APR 18 01 07 Auto APR Function 18 01 07 Normal Rated Takeoff N1 Indications TO 18 01 07 Climb Thrust CLB 18 01 08 Cruise Rang...

Page 516: ...7 Thrust Reverser System 18 01 19 Description 18 01 19 Components and Operation 18 01 19 Thrust Reverser 18 01 19 Reverse Thrust Operation 18 01 21 Isolation Control Unit 18 01 21 Directional Control...

Page 517: ...e pads for mounting the hydraulic pump and generator as well as providing lubrication for the engine FLAT RATED THRUST Outside air temperature and pressure altitude are determining factors in achievin...

Page 518: ...tage of the fan air exits into the bypass duct The remainder is directed into the core of the engine This core airflow passes through a four stage axial compressor and a single stage centrifugal compr...

Page 519: ...vanes and stators are programmed by FADEC and positioned by actuators and mechanical linkage High pressure fuel from the engine fuel metering unit is used to hydraulically move the actuators N2 speed...

Page 520: ...ne fuel and cools engine oil The engine fuel temperature is indicated on the FUEL synoptic page A 10 micron fuel filter is used to remove solid contaminants from the fuel The filter is depicted on the...

Page 521: ...n engine overspeed by commanding the shutoff valve in the fuel metering unit to close in order to return the engine to an on speed condition The in control and standby channels continuously share comm...

Page 522: ...feature of the FADEC will automatically increase the thrust for the operating engine to the emergency thrust power setting of APR power Automatic Power Reserve is available when APR is armed during t...

Page 523: ...ses of operation or a specific armed condition With both engines operating the following thrust mode annunciations are presented APR TO CLB CRZ REV MAX POWER APR When either or both thrust levers are...

Page 524: ...positioning the thrust lever in the quadrant range that exists between the IDLE and CLIMB detents In this range the pilot manually sets the thrust levers to maintain cruise speed or sets thrust for th...

Page 525: ...eed of the master engine The left and right engines will automatically designate themselves as master and slave engines using a cross engine communication link The engine with higher N1 compensation o...

Page 526: ...s them by absorbing heat directly as it passes in and around these components The oil is scavenged by dedicated scavenge pumps and returned to the oil tank Power to drive the oil pump is provided by t...

Page 527: ...when the tank is approximately 1 quart below FULL The NO DISPATCH band is approximately 1 6 quarts below FULL If the oil level is below this band the tank should be serviced prior to dispatch However...

Page 528: ...AGB OIL NOZZLES FUEL FILTER ASSEMBLY PRESSURE ADJUSTING VALVE OIL TEMPERATURE TRANSDUCER OIL PRESSURE TRANSDUCER DUAL SWITCH FORWARD SUMP SUPPLY AFT SUMP SUPPLY SIPHON BREAK LAST CHANCE SCREEN ROTATI...

Page 529: ...he AIR COND BLEED panel on the center pedestal A cross bleed valve is installed between the left and right pneumatic ducts that can be opened automatically or manually by press ing the XBLEED push but...

Page 530: ...m occurs Placing the engine run switch to RUN turns on the aircraft electrical boost pump The START switch signals the FADEC to initiate the start sequence DC electrical power and air from the bleed a...

Page 531: ...the N2 reaches or exceeds 46 2 or the OFF position is selected on the throttle quadrant assembly panel For subsequent starts the starter sprag clutch does not require that the engine rotation be comp...

Page 532: ...le of continuos operation by manual activation by the pilot but is normally only energized during the starting sequence COMPONENTS AND OPERATION ENGINE STARTING When the FADEC in control channel is de...

Page 533: ...lly measured by rotary variable differential transformers RVDTs or sensed by micro switches that are housed within the thrust quadrant The information is provided to the FADEC the flight control compu...

Page 534: ...MAX REV APR TO IDLE MAX R ENGINE REV TO GA CFO1801002_006 AUTOMATIC POWER RESERVE APR IDLE IDLE FORWARD THRUST TOGA SWITCH 2 CLB CLIMB REV IDLE REVERSE THRUST MAX REV MAXIMUM REVERSE THRUST TAKE OFF G...

Page 535: ...erser and is controlled by the FADEC and electrical signals from the airplane The hydraulic system has Isolation control unit Directional control unit Hydraulic and electro hydraulic primary locks Doo...

Page 536: ...T REVERSER SYSTEM Cont CFO1801002_010 THRUST REVERSER STOWED FORWARD THRUST THRUST REVERSER DEPLOYED REVERSE THRUST THRUST REVERSER STOWED FORWARD THRUST THRUST REVERSER DEPLOYED REVERSE THRUST EXHAUS...

Page 537: ...rs are fully stowed the REV icon will disappear and the N1 target and bug will reset to the takeoff setting Also the forward interlock baulk will be removed allowing for forward thrust modulation abov...

Page 538: ...on There is a vibration pickup on each engine to pro vide feedback to the aircrew which engine is producing high vibration levels It is also used by maintenance personnel for ground based fan trim bal...

Page 539: ...ameters are presented on the EICAS display Indications include N1 and N2 in percent values as well as ITT fuel flow oil pressure and temperature ignition system and start status high engine vibration...

Page 540: ...1801002_015 START CRANK OFF CRANK START OFF R ENGINE OFF RUN L ENGINE OFF RUN CFO1801002_003 AIR SOURCE NORM PACK ONLY OFF TRIM AIR ONLY RAM AIR ON XBLEED R BLEED OFF APU ON L BLEED OFF T 600 600 85 0...

Page 541: ...e engine oil pressure is low L R REVERSER UNSAFE Illumination of either the L or R REVERSER UNSAFE CAS or a REV EI indicates an unsafe thrust reverser condition The affected engine should automaticall...

Page 542: ...LAND Engine SYNC and Mach hold are not available L R ENG A ICE FAIL ON TO LAND The respective nacelle anti ice has failed ON L R ENG FUEL TEMP LOW TO LAND The fuel temperature in the respective engin...

Page 543: ...ENGINE OIL CHIP TO LAND Metal debris detected in engine lube system AUTO APR OFF Auto APR has been selected off L R ENGINE SHUTDOWN The respective engine has shutdown with the RUN switch OFF or the r...

Page 544: ...Instruction Sheet Sep 13 2004 Flight Crew Operating Manual Volume 2 CSP 100 6 1 04 Challenger 300 Flight Crew Operating Manual Volume 2 REVISION 1...

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