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provides a signal to generate a “L/R FUEL

FILTER” CAS message (Table 7-4) to indicate

an impending fuel filter bypass situation when-

ever a 6-8 PSID differential is detected. If the

differential pressure exceeds 9-12 PSID, fuel

will bypass the filter and flow unfiltered to the

inlet of the high pressure element of the en-

gine-driven pump.

An amber “L or R FUEL FILTER” CAS mes-

sage will appear if the respective engine or air-

frame fuel filter has an impending bypass

while on the ground. While in flight, the CAS

message will be white.

FUEL CONTROL UNIT (FCU)

The fuel control unit (FCU) is mounted on

the aft side of the engine-driven fuel pump

(Figures 7-15 and 7-16). The primary function

of the FCU is to schedule fuel flow to the fuel

manifold. The normal mode of operation is

computer-on. In the computer-on mode, the

torque motor (Figure 7-16) in the FCU re-

sponds to electrical signals from the fuel com-

puter (DEEC). The backup mode of operation

is manual mode. In manual, the metering valve

(Figure 7-16) in the FCU responds hydrome-

chanically to thrust lever movement.

The FCU includes (Figure 7-16):

• A DC torque motor which schedules fuel

in the computer-on mode in response to

the DEEC. When in manual mode, the

torque motor valve goes full open.

• A metering valve which (1) meters fuel

flow in the manual mode in response to

thrust lever movement and (2) limits

fuel flow in the computer-on mode in re-

sponse to the 105% flyweight governor.

The metering valve is normally full open

during computer-on operation.

• An ultimate overspeed solenoid valve

which is normally open, but is energized

closed by the DEEC at 107% N1 or 109%

N2 to shut off fuel. Operates with com-

puter-on or with MAN selected.

• A manual shutoff valve, operated me-

chanically by thrust lever movement be-

tween CUTOFF and IDLE. Operates

with computer-on or in manual.

• A manual mode solenoid which is nor-

mally energized open by the DEEC dur-

ing computer-on operation.

• Pneumatic circuits to channel and con-

trol P3 bleed-air pressure to pneumat-

ically position the metering valve.

• A mechanical flyweight governor, driven

by N2 to (1) limit engine overspeed to

105% in the computer-on and computer-

off modes and (2) govern engine rpm

relative to thrust lever position in the

manual mode.

FUEL FLOW SENSOR

Each engine has a fuel flowmeter (sensor) lo-

cated between the FCU and the engine fuel

manifolds (Figure 7-16). The flowmeter com-

pensates for fuel temperature changes to de-

termine fuel flow mass and provides this

information to the dual fuel flow converter

(DFFC) located within the tailcone. The dual

channel DFFC sends the fuel flow information

to the DAUs which convert the information to

ARINC 429 bus format, then passes it on to the

symbol generators in the IC-600 integrated

computers. The symbol generator then pro-

vides fuel flow information for display in the

engine instrument section of the EICAS

(Figure 7-5).

Fuel flow information is also sent from the

DAUs to the FMS(s) for fuel burned and fuel

remaining computations and displays.

The DFFC has built-in redundancies should

one output channel fail. The converter oper-

ates on DC power through two circuit break-

ers, labeled L/R FUEL FLOW, located in the

engine group on the left and right circuit

breaker panels respectively.

L E A R J E T 4 5

P I L O T T R A I N I N G M A N U A L

7-22

FOR TRAINING PURPOSES ONLY

FlightSafety

international

Summary of Contents for LEARJET 45

Page 1: ...FlightSafety International 1071 E Aero Park Blvd Tucson AZ 85706 800 203 5627 FlightSafety international LEARJET 45 PILOT TRAINING MANUAL VOLUME 2 ...

Page 2: ...rnational Tucson Learning Center 1071 East Aero Park Blvd Tucson AZ 85706 800 203 5627 Fax 520 918 7111 FlightSafety International Atlanta Learning Center 1010 Toffie Terrace Atlanta GA 30354 800 889 7916 Fax 678 365 2699 Copyright 1997 by FlightSafety International Inc All rights reserved Printed in the United States of America ...

Page 3: ...rization and training purposes only At the time of printing it contained then current information In the event of conflict between data provided herein and that in publications issued by the manufacturer or the FAA that of the manufacturer or the FAA shall take precedence We at FlightSafety want you to have the best training possible We welcome any suggestions you might have for improving this man...

Page 4: ...er 6 AUXILIARY POWER UNIT Chapter 7 POWERPLANT Chapter 8 FIRE PROTECTION Chapter 9 PNEUMATICS Chapter 10 ICE AND RAIN PROTECTION Chapter 11 AIR CONDITIONING Chapter 12 PRESSURIZATION Chapter 13 HYDRAULIC POWER SYSTEMS Chapter 14 LANDING GEAR AND BRAKES Chapter 15 FLIGHT CONTROLS Chapter 16 AVIONICS Chapter 17 MISCELLANEOUS SYSTEMS WALKAROUND APPENDIX ...

Page 5: ...RODUCTION 1 1 GENERAL 1 2 STRUCTURES 1 2 General 1 2 Fuselage 1 2 Wing 1 15 Empennage 1 17 Static Discharge Wicks 1 18 Airplane Antennas 1 19 REVIEW QUESTIONS 1 20 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 6: ...rplane Doors 1 10 1 11 Passenger Crew Entry Door Closed Open 1 11 1 12 Airplane Door Messages and Warnings 1 12 1 13 Door Latch Inspection Ports and Inside Locking Handle 1 13 1 14 Emergency Exit Hatch 1 13 1 15 Windshield and Window Locations 1 14 1 16 Tailcone Access Doors 1 15 1 17 Wing Configuration 1 16 1 18 Learjet 45 Wing 1 17 1 19 Learjet 45 Empennage 1 17 1 20 Airplane Static Discharge Wi...

Page 7: ...he material presented has been prepared for the basic design data and all subsequent changes in airplane appearance or system operation will be covered during academic train ing and in subsequent revisions to this manual No material is meant to supersede or sup plement any of the manufacturer s system or operating manuals LEARJET 45 PILOT TRAINING MANUAL FlightSafety international CHAPTER 1 AIRCRA...

Page 8: ...f danger areas around the Learjet 45 Areas por trayed represent the weather radar transmission cone as well as sections in front of the engine intakes and aft of the engine exhaust cone FUSELAGE General The fuselage is made of conventional metal semimonocoque construction of near circu lar cross section The fuselage is constructed in three major assemblies and then mated into four basic sections F...

Page 9: ...LEARJET 45 PILOT TRAINING MANUAL FlightSafety international 1 3 FOR TRAINING PURPOSES ONLY Figure 1 2 General Dimensions 17 2 9 3 45 8 47 8 3 7 3 7 2 3 5 4 9 9 58 4 14 3 ...

Page 10: ...TRAINING PURPOSES ONLY FlightSafety international Figure 1 3 Turning Radius NOSEWHEEL WINGTIP NOTE TURNING RADIUS EXPRESSED ABOVE IS BASED UPON 60 NOSEWHEEL DEFLECTION 39 ft 4 in 1 199 cm 3 0 f t 1 i n 9 1 7 c m FS 141 85 FS 454 87 FBL 180 72 ...

Page 11: ...THER RADAR 9 FEET 2 7 M ENGINE EXHAUST 750 F 399 C 100 F 38 C 40 FEET 12 M NOTE EXHAUST DANGER AREA SHOWN FOR IDLE RPM VALUES APPROXIMATELY DOUBLE FOR TAKEOFF RPM NOTE NOTE THE ANTENNA SCAN AREA MUST BE FREE OF METALLIC OBJECTS FOR A DISTANCE OF AT LEAST 100 FEET REFUELING OPERATION MUST NOT BE PERFORMED WITHIN 100 FEET OF THE ANTENNA SCAN AREA ...

Page 12: ...nose wheelwell Two removable access panels one on each side of the nose section provide access to the avionic equipment Figures 1 6 and 1 7 The panels are secured with camlock fasteners The nose section avionics bay is cooled in flight by the air outflow from the pressurized section which is exhausted into the nose wheel well LEARJET 45 PILOT TRAINING MANUAL 1 6 FOR TRAINING PURPOSES ONLY FlightSa...

Page 13: ...a full galley in the forward cabin An enclosed aft lavatory features an externally serviced flushing toi let The standard cabin provides seating for eight passengers and an option is available to use the lavatory for a ninth passenger seat The standard lavatory provides 15 cu ft of baggage volume in addition to the 50 cu ft of tailcone baggage The instrument panel typical is displayed in Figure 1 ...

Page 14: ...ROTTLE QUADRANT 2 AIR OUTLETS ANKLE 3 PILOT S CIRCUIT BREAKER PANEL 4 COPILOT S CIRCUIT BREAKER PANEL 5 PUBLICATION STORAGE AREAS 6 AIR OUTLETS WEMAC 7 MAP LIGHTS 8 SUNVISOR 9 DOME LIGHT 10 PILOT S CONTROL COLUMN AND WHEEL 11 COPILOT S CONTROL COLUMN AND WHEEL 12 INSTRUMENT PANEL 13 MAGNETIC COMPASS 14 CREW WARNING PANEL 2 2 1 3 4 5 5 6 6 7 8 9 8 9 7 10 11 12 13 14 ...

Page 15: ...9 5 6 7 7 8 8 9 9 10 11 12 13 14 15 16 17 1 L R DISPLAY UNIT REV PANEL 2 L R AOA INDICATOR OPTIONAL 3 L R DIGITAL CHRONOMETER 4 STANDBY AIRSPEED INDICATOR 5 STANDBY ATTITUDE INDICATOR 6 STANDBY ALTIMETER 7 L R RUDDER PEDAL ADJUSTMENT 8 L R CREW LIGHTS PANEL 9 L R AHRS PANEL 10 ELECTRICAL CONTROL PANEL 11 REVERSION CONTROL PANEL 12 ANTI ICE PANEL 13 AIRPLANE LIGHT CONTROL 14 GEAR HYDRAULIC PANEL 15...

Page 16: ...r door that secure the door halves together The upper entry door has a small vent door lo cated in the center of it When the inside or out side upper door handle is rotated to the open position the vent door cycles open and then closed Through the arrangement in the upper door opening mechanism the vent door opens before the locking pins are retracted and then closes again when the locking pins ar...

Page 17: ...rn ing indications Also the ENTRY DOOR CWP annunciator and the ENTRY DOOR and ENTRY DOOR PIN CAS messages all illuminate if the DOOR circuit breaker on the pilot circuit breaker panel is out Amber caution messages are also displayed on the CAS for additional access doors that are not secure i e tailcone access door the bag gage door and the emergency exit door These same CAS messages are illuminat...

Page 18: ...0 0 80 60 1002 N2 OIL PSI OIL C FF PPH 550 550 75 0 75 0 1700 ELECT VOLTS EMER V AMPS TEMP C 28 5 28 0 28 0 200 300 30 50 HYD ECS MAIN B ACUM OXY C OXY PSI 3000 2000 10 1800 FLT SPLR PIT AIL RUD 0 0 R 3 L 2 Honeywell Honeywell ENTRY DOOR EMERGENCY EXIT EXTERNAL DOORS ENTRY DOOR PIN END R REV UNSAFE R OIL PRESS LOW R ENG PYLON OVHT R FUEL PRESS LOW ENTRY DOOR GEN FAIL R BLEED AIR LEAK R BATT OVHT S...

Page 19: ...ing pins when inserted From inside the aircraft the emergency exit door is opened by pulling the internal latch handle labeled EXIT PULL downwards This extracts the two locking pins located at the top of the hatch The exit door can then be pulled inward The bottom edge of the emer gency exit door sits behind a lip that serves as a non retaining hinge during removal and in stallation of the emergen...

Page 20: ...n type shade installed Fuel Section The fuel section is located aft of the rear pres sure bulkhead This section contains the fuse lage fuel tank Tailcone Section The tailcone section extends aft from the fuel section to the empennage A door is located on either side of the tailcone section Figure 1 16 These doors provide access to the air plane baggage compartment left side and to the tailcone equ...

Page 21: ... with tapering thickness The wing structure is continuous through the fuselage cutout and is provided with four load attach ment points on each side for mating to the fuselage Most of the wing is sealed to form integral fuel tanks on each side Specific wing features are as follows Winglets at the outboard end of each wing reduce the strength of the wingtip vortices thus reducing induced drag Remov...

Page 22: ... I N G M A N U A L 1 16 FOR TRAINING PURPOSES ONLY FlightSafety international SAWTOOTH 3 VORTILONS 4 WING ROOT STALL STRIP 1 TRIANGLES 8 NOTE ILLUSTRATION NOT TO SCALE SAWTOOTH TOP VIEW FLAP AILERON SPOILERON Figure 1 17 Wing Configuration ...

Page 23: ...wler type flaps ailerons and spoilerons The multirole fly by wire spoilers are located on the top surface of the wing and are used on the ground for deceleration inflight as drag devices and as full time spoilerons to supplement or replace normal aileron roll control The main landing gear is attached to and housed within the wings EMPENNAGE The T tail empennage Figure 1 19 is com prised of a dorsa...

Page 24: ...sher system and reduces the need for a yaw damper On aircraft 45 005 thru 45 225 with SB 45 55 6 and aircraft 45 226 subsequent a strap ping is added to the rudder and rudder trim tab These tabs reduce yaw oscillations Dutch roll during flight STATIC DISCHARGE WICKS There are four static discharge wicks on each winglet two on each delta fin three on each elevator and one on the trailing edge of th...

Page 25: ...each delta fin c Most inboard wick on each elevator and d On aft vertical stabilizer fairing AIRPLANE ANTENNAS Figure 1 21 shows the location of the airplane antennas Familiarity with antenna locations is an essential element of an external airplane inspection LEARJET 45 PILOT TRAINING MANUAL FlightSafety international 1 19 FOR TRAINING PURPOSES ONLY Figure 1 21 Airplane Antennas ...

Page 26: ...ircraft D All of the above 3 How many static discharge wicks are at tached to each winglet A 1 B 2 C 3 D 4 4 The Learjet 45 wing has the following specific features A Winglets to reduce the strength of the wingtip vortices thus reducing induced drag B Vortilons and sawtooth cutouts on the leading edge to control span wise flow C Multifunction spoilers which serve both as drag devices and to augmen...

Page 27: ...nerators 2 7 GENERATOR CONTROL UNITS 2 8 ELECTRICAL CONTROL PANEL 2 9 General 2 9 Electrical Indicator Switches 2 10 ELECTRICAL SYSTEM INDICATORS 2 12 DISTRIBUTION SYSTEM COMPONENTS 2 18 Fuses 2 18 Contactors 2 18 Circuit Breakers 2 18 Circuit Breaker Panels 2 18 DISTRIBUTION 2 23 General 2 23 Split Bus System 2 24 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety internatio...

Page 28: ...Busses 2 25 Emergency Battery Bus 2 26 Non Essential Busses 2 26 Distribution Summary 2 26 AC POWER 2 27 ABNORMAL MODES OF OPERATION 2 33 Battery Overheat 2 33 Single Generator Failure 2 34 Dual Generator Failure 2 36 REVIEW QUESTIONS 2 41 LEARJET 45 PILOT TRAINING MANUAL 2 ii FOR TRAINING PURPOSES ONLY FlightSafety international ...

Page 29: ... CWP 2 15 2 13 Electrical System Schematic Display Page EICAS MFD 2 16 2 14 Aft Power Distribution Panels PDP 2 18 2 15 Pilot Circuit Breaker Panel 2 20 2 16 Copilot Circuit Breaker Panel 2 21 2 17 Normal DC Power System Diagram 2 22 2 18 System Power Up on Main Emergency Battery Power On Ground 2 28 2 19 System Power Up with External Power Connected 2 29 2 20 System During Right Engine Battery St...

Page 30: ...2 38 TABLES Table Title Page 2 1 Electrical Limits 2 14 2 2 CAS Message Database and Logic Summary 2 17 2 3 Normal Contactor Operation 2 19 2 4 DC Power Distribution with Double Generator Failure 2 39 2 5 Abnormal Contactor Operation 2 40 LEARJET 45 PILOT TRAINING MANUAL 2 iv FOR TRAINING PURPOSES ONLY FlightSafety international ...

Page 31: ...o assist in engine start and to charge aircraft batteries Additionally an optional APU may be installed to provide for systems operation on the ground and for engine start AC electrical power is provided by two engine driven alternators for the sole purpose of powering the windshield ice and fog protection system The alternators are rated at 200 VAC 200 400 Hz 5KVA AMPS R R E V U N S A F E R O I L...

Page 32: ...s possible to power the DC electrical sys tems from the airplane batteries engine driven generators a ground power unit GPU or an auxiliary power unit APU if installed Figure 2 1 shows the major electrical power system component locations A glossary of abbreviations and acronyms may be found in the appendix tab of this manual LEARJET 45 PILOT TRAINING MANUAL 2 2 FOR TRAINING PURPOSES ONLY FlightSa...

Page 33: ...ower from each battery is used to close the corresponding battery contactor when the main battery switches are selected ON When the battery contactors are closed the main batteries are connected to the respec tive generator bus Figure 2 18 When the airplane is on the ground the bat tery contactors are controlled by voltage sen sors to prevent discharge below 14 volts If a battery is below 14 volts...

Page 34: ...urrent If the emergency battery is se lected to ON and a battery discharge current is sensed by the shunt the white EMER cap tion on the emergency battery switch Figure 2 9 will illuminate indicating emergency bat tery discharge A white EMER BATT annun ciator on the CWP will also illuminate for this condition Figure 2 12 Battery charging from the airplane generators precludes these indi cations un...

Page 35: ...the same switch The bus tie contactor automatically closes when a GPU is connected to the airplane elec trical system The entire DC system is pow ered assuming the avionics master and main battery switches are on and no busses have been deselected via the electrical control panel Figure 2 19 Neither the airplane generators nor the APU will come on line with the GPU selected ON and if they are on w...

Page 36: ...gure 2 9 will also illuminate After depressing the APU GEN switch on the electrical control panel the ON caption will illuminate and the AVAIL caption will extin guish to indicate that the APU contactor has closed connecting the APU generator output to the right generator bus The bus tie contactor automatically closes with the APU generator on line A GPU and APU generator cannot provide airplane e...

Page 37: ... electrical control panel is de pressed Inflight cooling air is routed from a scoop on the engine nacelle to the starter generator Figure 2 8 Cooling while on the ground is provided by a fan mounted on the generator shaft During normal operation both generators op erate independently When both generators are on line the bus tie will normally be open and the left generator will recharge the left ma...

Page 38: ...tart cycle is terminated automatically when starter cut off speed is sensed by a magnetic pickup in the starter This is a back up to the normal cutoff at 50 N2 input to the GCU from the engine computer LINE CONTACTOR CONTROL In the generating mode power is automatically pro vided to the line contactor in order to connect the generator to the generator bus when the out put voltage is at an adequate...

Page 39: ...ult The pilot has a manual over ride option of selecting recycling or dese lecting some of the busses on the DC system During engine start the generator auto start feature reduces engine start switch selections and pilot workload The electrical control panel Figure 2 9 con sists of an illuminated panel with 13 14 when an APU is installed switched S Is All cap tions have white letters on a black ba...

Page 40: ...n until deselected by the crew The bus tie cannot be manually closed when operating on battery power only The CAS also provides a BUS TIE CLSD and BUS TIE MANUAL message Table 2 2 EXT PWR The external power switch is a momentary action switch The green AVAIL caption will illuminate only when a supply of correct voltage and polarity is sensed on a connected GPU When the EXT PWR switch is pressed to...

Page 41: ... both generators have failed L R AV MSTR These switches are alter nate action and allow the crew to connect or disconnect both main avionics and essential avionics busses The main avionics bus con tactors automatically open during engine start on the ground and during starter assisted airstart EMER BATT The bottom half of this al ternate action switch displays OFF when man ually selected to OFF i ...

Page 42: ... C CAS FUEL FLT ECS HYD ELEC SUMRY L F 1000 R 1750 FLAPS 20 6 5 PITCH TRIM LBS FUEL 4500 15 50 0 76 60 984 50 0 80 60 1002 N2 OIL PSI OIL C FF PPH 550 550 75 0 75 0 1750 ELEC VOLTS EMER V AMPS TEMP C 28 5 28 0 28 0 50 65 35 38 HYD ECS MAIN B ACUM CAB ALT OXY QTY 3000 3100 1300 669 FLT SPLR PIT AIL RUD 0 6 5 R 3 L 2 L BATT OVHT L R GENFAIL L BATT OVHT EMER BATT LOW EMER BUS VOLTS R ESS BUS VOLTS L ...

Page 43: ...ential busses Depending on what is powering the air plane electrical system this can be an indi cation of airplane main battery volts GPU volts APU volts or airplane generator volts A L R ESS BUS VOLTS CAS message will be posted if the voltage on the corresponding bus decreases below 22 VDC or increases above 29 5 VDC An indication of EMER V emergency bus voltage is displayed on the SUMRY page im ...

Page 44: ... format on the EICAS MFD ELEC system schematic page Figure 2 9 Additionally the ELEC system schematic dis play shows whether EXT PWR is connected to the airplane and if the APU generator is con nected APU amps are also displayed The display of volts amps and battery tem perature on the EICAS MFD are color coded As limits are exceeded the digital data changes color amber or red When the data is in ...

Page 45: ...ry temperature exceeds 70 degrees Celsius 160 degrees Fahrenheit GEN FAIL red Illuminates if both gener ators are inoperative or off line EMER BATT white Illuminates when the emergency battery is on and is discharging The red annunciators listed above will be ac companied by a red flashing CAS message and flashing Master Warning lights LEARJET 45 PILOT TRAINING MANUAL 2 15 FOR TRAINING PURPOSES ON...

Page 46: ...EMER BUS VOLTS EXT PWR R ESS VOLT BATT TEMPS 0 65 ELECTRICAL SYSTEM PAGE FORMAT NORMAL DISPLAY AMPS GEN R AMPS APU APU APU A 17 0 61 GEN C 30 0 410 AMPS L 75 32 0 L ESS VOLT EMER BUS VOLTS R ESS VOLT BATT TEMPS 310 310 ELECTRICAL SYSTEM PAGE FORMAT EXCEEDANCE DISPLAY AMPS GEN R AMPS A GEN C AMPS L L ESS VOLT EMER BUS VOLTS R ESS VOLT BATT TEMPS ELECTRICAL SYSTEM PAGE FORMAT INVALID DISPLAY Figure ...

Page 47: ...mer volts 22 or 29 5 VDC L R ESS BUS VOLTS ESS volts 22 or 29 5 VDC L R GEN AMPS HIGH Gen amps 300 ground in flight NOTE Inhibited during cross generator start and temporarily suppressed after engine start L R GEN FAIL Left or right generator failed BUS TIE CLSD L and R buses tied auto or manual BUS TIE MANUAL L and R buses tied or untied manually by pilot EXTERNAL POWER Ext power cable connected ...

Page 48: ...mally operated manually CIRCUIT BREAKERS A circuit breaker is designed to open and in terrupt current flow in the event of a mal function Once opened it may be reset as directed by the checklist or at the crew s dis cretion by pushing it back in but if it opens again do not reset An open circuit breaker may be identified by it s white base which can only be seen when it is open Most of the airplan...

Page 49: ...ition shown A Denotes contactor automatically energized closed for the condition shown Switch captions are for illustration purposes only and do not correlate to contactor positions in this table Assumes avionics master switches were turned on prior to second engine start L ISOL R ISOL L ESS AV R ESS AV L ESS R ESS L MAIN AV R MAIN AV L MAIN R MAIN L N ESS R N ESS EXT PWR BUS TIE MAN L GEN OFF ON ...

Page 50: ...OCK 1 20 PITOT 5 WSHLD MOTOR 25 INBD BRAKES MAIN HYD PRESS 2 L PRESS 1 3 CMPTR 2 PWR 1 LEAK DETECT 3 3 INSTR FAN PAX OXY 3 L SQUAT 1 CTRL 2 L BLEED 5 5 PACK ELEV DISC 3 3 SPLR CTRL L FLAP POS 1 L QTY 1 15 L STBY PUMP PWR L STBY PUMP CTRL 3 L WHL MSTR 5 5 AIL AFCS SERVOS 7 5 1 DET DEPLOY 5 L STALL WARN 5 5 PRI PITCH L RUD ADJUST 3 L FUEL FLOW 1 5 EXT ANN 3 L GEN 15 80 BUS BUS CH A 7 5 3 FWSOV STOW ...

Page 51: ...U 4 R CTRL R WARN PANEL DAU 2 AHRS PWR 1 SEC 2 PRI CH A CH B ADC 2 FDR R CLOCK RAD ALT 2 WXR GPWS TCAS INSRUMENTS INDICATIONS AVIONICS COMMUNICATIONS AUDIO 2 COMM 2 ATC 2 HF 2 COMM 3 RAD HOT BUS RMU 2 PWR 3 3 3 5 5 5 5 5 1 10 10 10 3 PRI SEC PWR CTRL NAVIGATION NAV 2 DME 2 ADF 2 FMS 2 OSS 2 FUEL 1 R QTY R STBY PUMP 3 15 CTRL PWR 3 XFLOW VALVE CTRL ENVIR 1 1 5 TEMP CTRL R BLEED R PRESS MAN AUTO ANT...

Page 52: ...CONTACTOR ANTI FLASH CONTACTOR L ESSENTIAL CONTACTOR 40A 40A 20A 40A 40A L NON ESS BUS 80A 130A 150A R NON ESS BUS 80A 130A 150A R HOT BUS L HOT BUS 15A 15A L EMER HOT BUS R EMER HOT BUS START GEN APU MAN BUS TIE L BATT R BATT R GEN L GEN OFF EXT PWR ON AVAIL ON AVAIL R START ON L START ON APU GEN R MAIN OFF R NON ESS OFF L MAIN OFF L NON ESS OFF R AV MSTR OFF L AV MSTR OFF EMER BATT OFF EMER OFF ...

Page 53: ...the switch will extinguish The switch is labeled RADIO CONTROL HOT BUS When this switch is depressed the ON annunciator on the switch will illuminate and main battery power through the right forward hot bus will power the fol lowing normal power source shown in paren thesis Left right audio control unit L R ESS Clearance delivery head L ESS COMM section of the integrated com munication unit 1 L ES...

Page 54: ...d it extinguishes when the bus tie is open MAIN BUSSES The left and right main busses are fed by the respective left and right generator busses through fuses and contactors Figure 2 17 The main busses in turn supply power to the left and right main avionics busses through cir cuit breakers and contactors Both of the main busses are automatically disconnected in the event of a dual generator failur...

Page 55: ... close There are two abnormal conditions that will cause the left isolation contactor to automat ically close If either essential contactor fails opens the left isolation contactor will close Since the right isolation contactor is normally closed either generator bus can then provide generator power through the essential con tactor that is closed to the left and right es sential busses and to esse...

Page 56: ... After reducing the electrical load in ac cordance with AFM procedures one or both non essential busses may be subsequently re connected by depressing the NON ESS switches on the electrical control panel DISTRIBUTION SUMMARY The following series of illustrations show the DC power flow and bus status during a typi cal sequence of events Figure 2 18 illustrates the current flow with only main and em...

Page 57: ...lected closed AC POWER GENERAL As part of the anti ice protection system left and right windshield heaters are powered by two left and right engine driven alternators The alternators are mounted to the front of the engine accessory drive box next to the starter generator and operate from 6 000 to 12 000 rpm Figure 2 7 The alternators supply 200 VAC 200 400 Hz at a maximum of 5 KVA single phase out...

Page 58: ...100A 80A 35A L ESS AVIONIC CONTACTOR 35A L MAIN AV CONTACTOR 35A R MAIN AV CONTACTOR BUS TIE CONTACTOR NORMALLY OPEN ANTI FLASH CONTACTOR L BATTERY CONTACTOR L LINE CONTACTOR 40A 40A 20A 40A R BATTERY CONTACTOR 40A R LINE CONTACTOR L NON ESS BUS 80A 130A 150A R NON ESS BUS 80A 130A 150A R HOT BUS L HOT BUS 15A 15A START GEN GCU APU L EMER HOT BUS R EMER HOT BUS R MAIN CONTACTOR APU CONTACTOR R ESS...

Page 59: ...TIE CONTACTOR NORMALLY OPEN ANTI FLASH CONTACTOR L BATTERY CONTACTOR L LINE CONTACTOR 40A 40A 20A 40A R BATTERY CONTACTOR 40A R LINE CONTACTOR L NON ESS BUS 80A 130A 150A R NON ESS BUS 80A 130A 150A R HOT BUS L HOT BUS 15A 15A START GEN GCU APU L EMER HOT BUS R EMER HOT BUS R MAIN CONTACTOR APU CONTACTOR R ESSENTIAL CONTACTOR R NON ESS CONTACTOR L ESSENTIAL CONTACTOR L MAIN CONTACTOR L NON ESS CON...

Page 60: ...NTACTOR L MAIN CONTACTOR L BATTERY CONTACTOR L LINE CONTACTOR 40A 40A 20A 40A R BATTERY CONTACTOR 40A R LINE CONTACTOR L NON ESS BUS L NON ESS CONTACTOR 80A 130A 150A R NON ESS BUS 80A 130A 150A R HOT BUS L HOT BUS 15A 15A START GEN GCU APU L EMER HOT BUS R EMER HOT BUS R MAIN CONTACTOR APU CONTACTOR R ESSENTIAL CONTACTOR R NON ESS CONTACTOR BATTERY POWER GENERATOR POWER GPU POWER CONTACTOR CURREN...

Page 61: ...40A 20A 40A R BATTERY CONTACTOR 40A R LINE CONTACTOR L NON ESS BUS L NON ESS CONTACTOR 80A 130A 150A R NON ESS BUS 80A 130A 150A 15A 15A START GEN GCU APU R MAIN CONTACTOR APU CONTACTOR R ESSENTIAL CONTACTOR R NON ESS CONTACTOR R GEN BUS R HOT BUS L HOT BUS REAR HOT BUS L GEN BUS EMER BATT BUS L ESS BUS L MAIN BUS BATTERY POWER GENERATOR POWER GPU POWER CONTACTOR CURRENT SENSOR LEGEND CIRCUIT BREA...

Page 62: ... L MAIN AV CONTACTOR 35A R MAIN AV CONTACTOR BUS TIE CONTACTOR NORMALLY OPEN L BATTERY CONTACTOR L LINE CONTACTOR 40A 40A 20A 40A R BATTERY CONTACTOR 40A R LINE CONTACTOR L NON ESS BUS 80A 130A 150A R NON ESS BUS 80A 130A 150A R HOT BUS L HOT BUS 15A 15A L EMER HOT BUS R EMER HOT BUS R MAIN CONTACTOR R ESSENTIAL CONTACTOR R NON ESS CONTACTOR L GEN BUS R GEN BUS REAR HOT BUS L ESS AV BUS L ESS BUS ...

Page 63: ...f by the crew The bat tery temperature must be less than 60 C be fore it can again be turned on If the SUMRY or ELEC system schematic is being displayed on the EICAS or MFD dis plays the digital readout of the battery tem perature for the affected battery will change color If the battery temperature exceeds 60 C 140 F the digital battery temperature dis play will change from white to a boxed amber...

Page 64: ...on the left and right NON ESS bus switches an illuminated OFF caption on the GEN switch of the failed generator and an illuminated bar on the BUS TIE switch This is illustrated in Figure 2 23 All other sys tems will continue to operate normally If nec essary the crew should reduce the load further in accordance with AFM procedures and if conditions warrant attempt to reset the failed generator Fol...

Page 65: ...OR 35A R MAIN AV CONTACTOR BUS TIE CONTACTOR NORMALLY OPEN L BATTERY CONTACTOR L LINE CONTACTOR 40A 40A 20A 40A R BATTERY CONTACTOR 40A R LINE CONTACTOR L NON ESS BUS 80A 130A 150A R NON ESS BUS 80A 130A 150A R HOT BUS L HOT BUS 15A 15A L EMER HOT BUS R EMER HOT BUS R MAIN CONTACTOR R ESSENTIAL CONTACTOR R NON ESS CONTACTOR L GEN BUS R GEN BUS REAR HOT BUS L ESS AV BUS L ESS BUS R ESS BUS R ESS AV...

Page 66: ...ery will power the right essential bus and the right essential avionics bus The AFM procedure for L and R GEN FAIL is to turn off the avionics master switches which will also cause the loss of the left and right essential avionics busses Indications on the electrical control panel with a dual generator failure would be OFF cap tions on the left and right MAIN bus switches NON ESS bus switches and ...

Page 67: ...ONTACTOR L BATTERY CONTACTOR L LINE CONTACTOR 40A 40A 20A 40A R BATTERY CONTACTOR 40A R LINE CONTACTOR L NON ESS BUS L NON ESS CONTACTOR 80A 130A 150A R NON ESS BUS 80A 130A 150A R HOT BUS L HOT BUS 15A 15A L EMER HOT BUS R EMER HOT BUS R MAIN CONTACTOR R ESSENTIAL CONTACTOR R NON ESS CONTACTOR BATTERY POWER GENERATOR POWER GPU POWER CONTACTOR CURRENT SENSOR LEGEND CIRCUIT BREAKER DIODE FUSE APU P...

Page 68: ...R 40A 40A 20A 40A R BATTERY CONTACTOR 40A R LINE CONTACTOR L NON ESS BUS L NON ESS CONTACTOR 80A 130A 150A R NON ESS BUS 80A 130A 150A 15A 15A START GEN GCU APU L EMER HOT BUS R EMER HOT BUS R MAIN CONTACTOR APU CONTACTOR R ESSENTIAL CONTACTOR R NON ESS CONTACTOR R GEN BUS R HOT BUS L HOT BUS REAR HOT BUS L GEN BUS EMER BATT BUS R ESS BUS L MAIN BUS L ESS BUS BATTERY POWER GENERATOR POWER GPU POWE...

Page 69: ...G STBY AIRSPEED LIGHTING GEAR CTRL IND PAX OXY MANUAL DEPLOY RMU 1 PWR SEC INBD BRAKES ANTI SKID CKPT EMER INSTR LTS R PRESS EMER LIGHTING ON GROUND R ESS BUS AUDIO 2 RMU 2 PWR SEC R CWP FDR R DISPLAY CTRL IC SG 2 ADC 2 DAU 2 CH B AHRS PWR 1 SEC AHRS PWR 2 PRI R SQUAT SW OTBD BRAKES ANTI SKID BRAKE ACCUM PRESS R STALL WARN SPOILER IND R FLAP POSN CTRL RUD TRIM FORCE SEC PITCH PIT TRIM BIAS R WHEEL...

Page 70: ...tactor automatically energized closed for the condition shown Switch captions are for illustration purposes only and do not correlate to contactor positions in this table Assumption is made that AV Master switches are selected off IAW AFM procedure Single gen failure R Double gen failure R ess contactor fails open In flight right engine start L AV MSTR OFF L AV MSTR OFF R AV MSTR OFF R AV MSTR OFF...

Page 71: ...Control Units provide all of the following functions except A Current limiting control B Voltage regulation C Overspeed protection D Alternator monitoring 5 Which of the following items is not on one of the hot busses A Left and right FWSOVs B Clearance Delivery Head C Left and right fire extinguishers D Cockpit Emergency Instrument Lights 6 The main airplane batteries can be re charged via A The ...

Page 72: ...rplanes equipped with NICAD batteries A On the EICAS or MFD SUMRY page B On the EICAS or MFD ELEC system schematic C On page two of the RMU backup en gine display pages D Both a and b are correct 13 How long will the emergency battery power the emergency battery bus with both generators failed A 1 hour minimum B 1 5 hours minimum C 2 hours minimum D 2 5 hours minimum 14 A single generator failure ...

Page 73: ...or to amber A 275 B Above 300 C Above 400 D 450 19 If the left generator fails inflight what will the left essential VOLTS show on the EICAS SUMRY page A Zero volts will be displayed B It will show emergency battery volt age C It will show voltage of the operating generator D It will show red dashes to indicate the generator has failed 20 What indication s will the crew have of a generator failure...

Page 74: ...ghting Conditions 3 10 EXTERIOR LIGHTING 3 12 Landing Taxi Lights 3 12 Recognition Lights 3 12 Navigation Lights 3 12 Tail Logo Lights Optional 3 12 Anticollision Lights Beacon Strobe 3 12 Wing Inspection Light 3 14 Exterior Convenience Lights Optional 3 15 Abnormal Exterior Lighting Conditions 3 15 REVIEW QUESTIONS 3 16 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety inte...

Page 75: ... Switch 3 8 3 9 Tailcone Compartment Lightswitch 3 9 3 10 Cockpit EMER LIGHT Switch 3 9 3 11 Battery Mode Lighting 3 11 3 12 Emergency Battery Mode Lighting 3 11 3 13 External Airplane Lighting 3 13 3 14 Landing Lights 3 13 3 15 Taxi Light 3 13 3 16 Wing Tip Navigation Light 3 14 3 17 Tail Navigation Light 3 14 3 18 Upper Anticollision Light 3 14 3 19 Lower Anticollision Light 3 14 3 20 Wing Inspe...

Page 76: ...f landing and taxi recognition strobe navigation beacon and a wing inspection light Optional exterior lighting consists of tail logo lights and exterior convenience lights that illuminate the single point refueling and baggage door areas Airplane lighting is divided into interior and exterior lighting Interior lighting is divided into cockpit cabin includes lavatory tailcone baggage and tailcone m...

Page 77: ...2 and the descriptions within this chapter Pilot Left Crew Lights Panel The pilot s L CREW LIGHTS panel Figure 3 3 is 28 VDC powered from the left essen tial bus and protected by a circuit breaker la beled CKPT INSTRS L ESS PWR located within the LIGHTS group of circuit breakers on the left side circuit breaker panel The four pilot LCU channels control Channels 1 2 Pilot side main instru ment pane...

Page 78: ...el if installed FLOOD The entire instrument panel can be illuminated by a fluorescent floodlight located beneath the glareshield Dimming is controlled via this rheostat located on the L CREW LIGHTS panel Power to the floodlight is from LEARJET 45 PILOT TRAINING MANUAL 3 3 FOR TRAINING PURPOSES ONLY FlightSafety international THROTTLE QUADRANT ENGINE FUEL PANEL FLIGHT MGMT SYSTEM APU TRIM HF SELCAL...

Page 79: ...ors S I s Following is a description of each of the rheo stat potentiometer controls located on the copilot s R CREW LIGHTS panel INSTR The copilot s instrument panel group lighting is controlled via the INSTR rheostat as illustrated in Figure 3 2 The display units and the radio management units have their own brightness control however the bezel control backlighting for these units is con trolled...

Page 80: ...s power to the two left bulbs and the copilot s LCU supplies power to the right two bulbs in most of the S Is Exceptions to this are the RAD HOT BUS S I which receives power from the hot bus and the warning S Is MASTER WARN CAUT and engine FIRE PUSH which receive power through the crew warning panel CWP The S I legends illu minate full bright when the NAV lights are OFF and are step dimmed with NA...

Page 81: ...e the tailcone baggage door area and the single point refu eling receptacle areas using rear hot bus power A cabin lighting switch panel is also located on the co pilot s side panel aft of the circuit breaker panel Figure 3 7 These switches can be used to override and disable the switches on the main entryway control panel Control of the NO SMOKING FASTEN SEAT BELT sign is through a switch located...

Page 82: ...htSafety international COCKPIT ENTRY CABIN LIGHT SPOT LIGHT LAV LIGHT SELECT SELECT MENU MUTE MONITOR MODEL 45 CABIN LIGHT SPOT LIGHT DISABLE CABIN MAIN ENTRYWAY CONTROL PANEL MASTER CABIN CONTROL PANEL COCKPIT COPILOT SIDE PANEL PYLON Figure 3 7 Cabin Lighting Controls ...

Page 83: ...6 eye ball type directional lights installed above the seats on each side of the cabin Some seats have only one light while others consist of a two light assembly referred to as table lights Control for the reading lights is by the seat mounted control units Figure 3 7 or by the SPOT light switch on the main entryway con trol panel Power for the reading lights is pro vided by the right non essenti...

Page 84: ... pedestal Figure 3 10 The emergency lighting group consists of 5 exit signs 2 per door 1 on forward face of lavatory partition 4 reading lights 8 floor proximity lights 6 white lens 2 red lens near exits Main door egress light when upper door open Emergency exit egress light external Lavatory light The cockpit EMER LIGHTS switch is lever locked and labeled OFF ARM and ON When the cockpit switch is...

Page 85: ...IGHTING CONDITIONS Single Generator Failure Following a single generator failure the air plane electrical system automatically sheds the non essential busses Normal power to the following cabin lighting will be lost how ever some of the lights can be powered by the emergency lighting system Lavatory Lights Galley Lights Reading Lights To regain full cabin lighting the non essen tial busses may be ...

Page 86: ...ht the left map light and the floodlights will be lost The landing gear indicator lights and the magnetic compass light will continue to op erate however all instrument panel and pedestal switch indicator lights will be inop erable LEARJET 45 PILOT TRAINING MANUAL 3 11 FOR TRAINING PURPOSES ONLY FlightSafety international AUDIO CONTROL PANEL AUDIO CONTROL PANEL RMU 1 RMU 2 4 5 6 CREW WARNING PANEL...

Page 87: ...d landing bulbs When the landing lights are turned on the recognition bulbs illuminate even when the RECOG switch is off The recognition lights receive power from the re spective left and right generator busses and use control power from the respective left and right main busses through the L and R TAXI LDG CTRL circuit breaker When equipped with the pulse light option the RECOG switch is modified...

Page 88: ...ECTION LIGHT RH WHITE POSITION NAV LIGHT WING TIP RH OUTBOARD GREEN POSITION NAV LIGHT WING TIP LH OUTBOARD RED ANTICOLLISION STROBE BEACON LOWER RED WHITE ANTICOLLISION STROBE BEACON UPPER RED WHITE POSITION NAV LIGHT TAIL UPPER WHITE LANDING LIGHT ASSEMBLY UNDERWING FAIRING RECOGNITION LIGHTS OUTBOARD ELEMENTS TAXI LIGHT STRUT Figure 3 13 External Airplane Lighting ...

Page 89: ...nal and the clear flash tube is inhibited until airborne Anytime the BCN position is se lected the red flash tube flashes On aircraft modified by SB 45 33 2 the white flash tube in each light flashes when STROBE is se lected and the red flash tube flashes when the BCN position is selected there is no auto matic control through the squat switch If flight into weather is encountered and the strobe l...

Page 90: ... ered from the hot bus system Selection of the baggage area light is by an ad ditional switch mounted inside the baggage compartment The switch is automatically switched OFF whenever the baggage com partment door is closed The SPPR area light is controlled via the SPPR panel power switch This switch is forced to the OFF position when the door is closed ABNORMAL EXTERIOR LIGHTING CONDITIONS Single ...

Page 91: ...mergency light system installed and the switch is in the ARM position which lights will come on inflight if elec trical power fails A Floor proximity lights B Lavatory lights C Emergency exit lights D All of the above 5 Which of the following lights can be op erated with the aircraft batteries turned OFF A Tailcone equipment bay light B SPPR area floodlight if installed C Baggage area floodlight i...

Page 92: ...hange 4 4 Dimming Function 4 5 CREW WARNING PANEL CWP 4 5 CREW ALERTING SYSTEM CAS 4 5 Operation 4 5 Collector Messages 4 6 CAS Message Inhibit Mode of Operation 4 7 AURAL WARNINGS 4 8 TAKEOFF CONFIGURATION MONITOR 4 8 ABNORMAL CONDITION INDICATIONS 4 10 REVIEW QUESTIONS 4 19 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 93: ...ystem Test Switch 4 4 4 3 CAS Message Display on EICAS 4 6 4 4 Thrust Lever Mute Switch 4 8 TABLES Table Title Page 4 1 Aural Warning and Voice Summary 4 9 4 2 CWP CAS Message Summary 4 11 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 94: ...voice and tone messages It further controls the pilot and co pilot mas ter warning caution annunciators and man ages the fire extinguisher system As illustrated in Figure 4 1 the CWP is center mounted on the main instrument panel and the master warning caution lights are located in the glareshield next to the DU2 and DU3 rever sion switches The CAS displays warning caution and advisory messages as...

Page 95: ...cases there will be an accompanying voice message See Table 4 1 Depressing either flashing master WARN CAUT light causes both master WARN lights to extinguish and the red CAS message to stop flashing Also if the accompanying voice message is mutable it will be cancelled when either master WARN CAUT light is de pressed The applicable CAS message and CWP APU fire or engine fire light remains illumin...

Page 96: ... 160 180 14 1 0 9 120 100 160 400 M GS LOC HDG AP YD SPD GS 180 RA HDG 001 359 CRS ILS1 13 1 NM 25 TGT VOR1 ADF2 RA BARO STD BARO MINIMUMS 4380 20 00 Honeywell Honeywell N1 ITT SAT C CAS FUEL FLT ECS HYD ELEC CAS TAKEOFF INHIBITED SUMRY L F 1000 R 1750 FLAPS 20 6 5 PITCH TRIM LBS FUEL 4500 15 50 0 76 60 984 50 0 80 60 1002 N2 OIL PSI OIL C FF PPH 550 550 75 0 75 0 1750 ELECT VOLTS EMER V AMPS TEMP...

Page 97: ...s held depressed for more than 15 seconds the CWP will play through all tones and voice messages sequentially Depressing either master WARN CAUT switch or the mute switch on the right throttle will mute the voice messages The fire detect lights FIRE PUSH are tested in the LTS position but the detection system is tested separately in the FIRE DET posi tion of the system test switch The system test ...

Page 98: ...WR FAIL CAS message This indicates that one power source has mal functioned but the CWP is still operational Should both power sources subsequently fail an amber LR WARN PWR FAIL and amber WARN AUDIO CAS message will be pre sented indicating that all functions of the CWP including master WARN CAUT all aural alerts and the red FIRE PUSH and en gine extinguisher ARMED light in the en gine fuel contr...

Page 99: ...ch replaces all of the above listed individual CAS messages into a single white L or R ENG SHUTDOWN advisory message when the corresponding thrust lever is placed in cutoff There are two other conditions where two CAS messages are replaced with a single CAS mes sage In the event both inboard and outboard braking systems fail the two individual amber CAS caution messages indicating failure are repl...

Page 100: ...nt a distraction See Table 4 2 for a listing of which CAS mes sages are inhibited for takeoff The takeoff inhibit feature is automatically enabled when all of the following conditions are met Both thrust levers are above the MCR detent The airspeed is above 40 KIAS Both squat switches are in the ground mode Once airborne or following an aborted take off the inhibit mode is automatically disabled b...

Page 101: ...ng is no longer valid Failures of the audio warning system are an nunciated by an amber WARN AUDIO CAS message This indicates a total failure of the audio warning system to include the master warning and master caution chime Should this same message be white it indicates a minor fault was detected and the audio has defaulted to high gain The CWP indicators and CAS messages are still operational in...

Page 102: ... M N C Repeat P M Note 1 N C N C N C Repeat P M Repeat P M Repeat P M 4 16 12 14 4 15 8 7 14 CAUTION AURALS OTHER AURAL TONES Master Caution M C Gear Caution Autopilot Yaw Damper Disconnect Minimums Call Altitude Alert SELCAL Trim in Motion Single Chime Attention 1 M C GEAR Once Once 4 14 Tone Cavalry Charge MINIMUMS MINIMUMS C chord Should mimic standard SELCAL CLACKER Once Once Once P M 16 16 16...

Page 103: ...f it is selected for display on the EICAS or MFD The flight control box logic only applies to ground operations If any of the above conditions are not satisfied and either throttle lever is advanced to MCR or above the takeoff configuration warning voice message will trip This voice message is played on both pilot headsets and the cockpit speaker and will continue to play until the unsafe condi ti...

Page 104: ...LEARJET 45 PILOT TRAINING MANUAL 4 11 FOR TRAINING PURPOSES ONLY FlightSafety international Table 4 2 1 CWP CAS MESSAGE SUMMARY ...

Page 105: ...LEARJET 45 PILOT TRAINING MANUAL 4 12 FOR TRAINING PURPOSES ONLY FlightSafety international Table 4 2 2 CWP CAS MESSAGE SUMMARY CONT ...

Page 106: ...LEARJET 45 PILOT TRAINING MANUAL 4 13 FOR TRAINING PURPOSES ONLY FlightSafety international Table 4 2 3 CWP CAS MESSAGE SUMMARY CONT ...

Page 107: ...G STAB LEAK WING OVHT ICE DET FAIL NO NO Ice detected A I systems OFF supressed on ground 10 ICE DETECTED NO NO Probe heat OFF or pitot heat failed 10 YES YES SAT TAT probe heat failed w right probe heat on 10 YES YES L R or both W S heat ON system failed undertemp 50 F 10 YES YES NAC Switch on low press or Pt2Tt2 probe heat failed 10 YES YES NAC Switch off pressure on 10 YES YES A I on stab under...

Page 108: ...eleased take off config monitor active 14 NO NO Failure of one or more A S circuits transducer or switch off 14 NO NO L and or R inboard normal brakes failed 14 NO NO Copilot s brake LVDT s 1 2 3 or 4 failed use pilot s brake pedals Pilot s brake LVDT s 1 2 3 or 4 failed use copilot s brake pedals 14 EMER PARK BRK NO NO Any gear not down and flaps 25 or both thrust levers MCR and RA 500 14 GEAR NO...

Page 109: ...DU 3 4 OVHT IC BUS FAIL IC 1 2 OVHT LBS KGS CONFIG YES YES 1 or 2 or 1 2 AHRS reverted to basic mode 16 AHRS 1 2 BASIC NO NO Different checklists are loaded into each IC 600 16 CKLST MISMATCH NO NO DAU Reversion Switch on Channel A 16 DAU A REV OXYGEN OFF Oxygen line pressure 50 psi or regulator is turned OFF 17 YES YES 1 2 or 1 2 combination DU overheat 16 NAV HONEYWELL GENERATED MESSAGES OXYGEN ...

Page 110: ...HIGH NO NO DEEC fault 7 YES YES Fuel oil cooler failure fuel too cold 5 7 YES YES Oil filter has an impending bypass ground 7 YES YES Fire sensing element shorted ground 7 YES YES Engine airframe fuel filter impending bypass ground 7 YES YES DEEC has detected minor malfunction ground 7 Metal particles in oil inflight 7 YES YES Engine airframe fuel filter impending by pass inflight 7 YES YES Collec...

Page 111: ...PR IGN MAN APR ON IGN NAC START SYNC APR MCR MCT T O MAN NO NO Sync ON N1 or N2 7 NO NO APR throttle detent selected 7 NO NO MCR throttle detent selected 7 NO NO Main gear is not locked up with SYNC switch on N1 or N2 7 EICAS ENGINE INDICATIONS EI S THRUST REVERSER ENGINE INDICATIONS EI S ON EICAS NO NO MCT throttle detent selected 7 NO NO THRUST REVERSER T O throttle detent selected 7 YES NO Auto...

Page 112: ...ion messages dis played A The crew warning panel CWP B The crew alerting system CAS C The airplane system window on the MFD D The airplane system window on the PFD 5 To eliminate nuisance warning caution lights and tones during preflight the crew should A Enable the takeoff CAS inhibit mode B Enable the landing CAS inhibit mode C Depress either master caution light for 2 seconds or more until the ...

Page 113: ...5 8 FUEL TRANSFER SYSTEM 5 11 Fuel Control Panel 5 11 Crossflow Valve 5 11 Standby Pumps 5 12 Fuselage Transfer Lines 5 12 ENGINE FUEL SUPPLY SYSTEM 5 12 General 5 12 Motive Flow Fuel and Jet Pumps 5 14 Filters 5 14 Main Fuel Shutoff Valves 5 14 Fuel Low Pressure Switches 5 15 RAM AIR VENT SYSTEM 5 16 General 5 16 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety internation...

Page 114: ...VALVES 5 19 FUELING DEFUELING 5 19 General 5 19 Single Point Pressure Refueling SPPR 5 20 Gravity Refueling 5 22 Defueling 5 22 REVIEW QUESTIONS 5 24 LEARJET 45 PILOT TRAINING MANUAL 5 ii FOR TRAINING PURPOSES ONLY FlightSafety international ...

Page 115: ...ontrol Panel 5 11 5 8 Engine Fuel Supply 5 13 5 9 Jet Pump Schematic 5 15 5 10 Ram Air Vent Scoop 5 16 5 11 Fuel Vent System Schematic 5 17 5 12 Fuel Drains 5 18 5 13 Fuel Sump Drain Valve 5 19 5 14 SPPR Adapter Panel 5 20 5 15 Single Point Pressure Refueling SPPR Schematic 5 21 5 16 Defueling System Schematic 5 23 TABLES Table Title Page 5 1 Fuel System CAS Messages 5 9 FOR TRAINING PURPOSES ONLY...

Page 116: ... the collector tank A fifth transfer jet pump is located within each wing in each fuselage tank transfer line outboard of the collector tanks The function 0 2 4 6 8 10 MAIN FUEL LBS X 100 L F 1200 R 1650 LBS FUEL 4480 1630 L FUEL PRESS LOW R FUEL HEATER DEFUEL OPEN FUEL IMBALANCE L FUEL QTY LOW FUEL XFLO R FWSOV CLSD L FWSOV FAULT L FUEL HEATER R ENGFUEL FILTER L FUEL QTY FAULT FUEL XFLO OPEN L ST...

Page 117: ... bladder extends from the wing root to a point just short of the winglets Areas which are not part of the wing fuel cell are the main landing gear wheel well the leading edge forward of spar 1 wing leading edge heat area and the trail ing edge aft of spar 3 in the flap spoiler and aileron areas The usable fuel capacity of both wing tanks is approximately 500 gallons 1 892 liters or approximately 3...

Page 118: ... WING FUSELAGE TANKS ENGINE FUEL SUPPLY SCAVENGE FUEL DRAINS COLLECTOR TANKS VENTS FUSELAGE FUEL CELL 2708 SCAVENGE JET PUMP 8 COLLECTOR TANK 2 STANDBY PUMP 2 TRANSFER JET PUMP 2 MAIN JET PUMP 2 LEFT WING TANK 1678 RIGHT WING TANK 1676 GRAVITY FILL DEFUEL VALVE SPPR FUEL FILTERS NACA RAM AIR INLET PRESSURE SWITCH 2 CROSSFLOW VALVE FLOAT SWITCH 2 Figure 5 1 Fuel System ...

Page 119: ... CAS message is only functional on aircraft 45 195 and subsequent and prior aircraft mod ified by SB 45 28 5 FUSELAGE TANK The fuselage tank is a single bladder type fuel cell located immediately aft of the rear pres sure bulkhead Located within the fuel cell is plumbing for the fuel tank vent system and the single point refueling system The fuselage tank also contains a gravity fuel filler port l...

Page 120: ...w invalid amber dashes One channel of the fuel quantity computer is provided with DC electrical power through the L QTY circuit breaker in the left FUEL group of circuit breakers and the other chan nel through the R QTY circuit breaker in the right FUEL group of circuit breakers LEARJET 45 PILOT TRAINING MANUAL FlightSafety international 5 5 FOR TRAINING PURPOSES ONLY LEFT CHANNEL RIGHT CHANNEL 28...

Page 121: ...ilure may result in a FUEL IMBALANCE amber CAS due to calculation in the fuel quan tity computer FUEL QUANTITY DISPLAY The primary indication of fuel quantity is pro vided on the EICAS display format just below the engine instruments Figure 5 4 The EICAS Engine Instruments and Crew Alerting System is normally displayed on the pilot s inboard display unit DU 2 but can also be selected for display o...

Page 122: ...G LBS ON BOARD N1 ITT SAT C CAS FUEL FLT ECS HYD ELEC SUMRY L F 1200 R 1650 FLAPS 20 6 5 PITCH TRIM LBS FUEL 4480 15 50 0 76 60 984 50 0 80 60 1002 N2 OIL PSI OIL C FF PPH 550 550 75 0 75 0 1630 ELECT VOLTS EMER V AMPS TEMP C 28 5 28 0 27 8 200 300 30 40 HYD ECS MAIN B ACUM OXY C OXY PSI 3000 2000 10 1800 FLT SPLR PIT AIL RUD 0 0 R 3 L 2 Honeywell Honeywell L R FUEL PRESS LOW L R FUEL HEATER DEFUE...

Page 123: ...es of engine and system indications Figure 5 5 If the pilot s inboard display unit DU 2 should fail causing loss of the EICAS display including fuel flow indication fuel quantity indication and fuel system schematic the EICAS display format can be selected on dis play unit DU 3 If it is not possible or de sirable to display the EICAS format on either inboard display unit for some reason the en gin...

Page 124: ...e fuel quantity computer de LEARJET 45 PILOT TRAINING MANUAL FlightSafety international 5 9 FOR TRAINING PURPOSES ONLY CAS MESSAGE W C C C C C A C C A A A A A L R FUEL PRESS LOW A L R FUEL HEATER L R FUEL FILTER DEFUEL OPEN FUEL IMBALANCE L R FUEL QTY LOW FUEL XFLO L R FWSOV CLSD L R FWSOV FAULT L R FUEL HEATER L R FUEL FILTER L R FUEL QTY FAULT FUEL XFLO OPEN L R STBY PUMP ON L R FUEL BAY LOW Low...

Page 125: ...0USED 1000 FUSELAGE 1650 L WING L ENG LBS ON BOARD R WING R ENG USED FUSELAGE L WING L ENG LBS ON BOARD 350 R WING R ENG 700 5360USED 0 FUSELAGE 350 L WING L ENG LBS ON BOARD FUELSYSTEMSCHEMATICNORMALDISPLAY FUELSYSTEMSCHEMATICEXCEEDANCESDISPLAY FUELSYSTEMSCHEMATICINVALIDDISPLAY Figure 5 6 Fuel System Schematic Formats ...

Page 126: ...ng The crossflow valve is normally closed during flight but may be opened should a fuel imbalance occur Fuel can gravity flow be tween wing tanks when the crossflow valve is open or it can be pumped from one wing to the other using either standby pump Selection of the crossflow valve switch XFLOW and the left standby pump switch L STBY Figure 5 8 for example causes the crossflow valve to open and ...

Page 127: ...nt Each standby pump has an associated STBY PUMP PWR and STBY PUMP CTRL circuit breaker located in the FUEL group of circuit breakers on each circuit breaker panel The standby pumps are powered from the re spective L R essential buses The essential buses remain powered by the aircraft batter ies in the event of the loss of both aircraft generators FUSELAGE TRANSFER LINES Two 2 inch transfer lines ...

Page 128: ...NG PURPOSES ONLY FUEL L STBY R STBY XFLOW FUEL USED RESET ON FIRE FIRE FIRE PUSH CLOSED FIRE PUSH L FUEL PRESS LOW L FUEL PRESS LOW L FWSOV CLSD L STBY PUMP ON FUEL XFLO OPEN L STBY PUMP ON FUEL XFLO OPEN ACTIVATES L FUEL PRESSURE LOW ANNUNCIATION Figure 5 8 Engine Fuel Supply ...

Page 129: ...tandby pumps and four scavenge pumps lo cated at various points in each wing tank Figure 5 1 Another jet pump is located in each fuselage to wing tank transfer line for the purpose of pulling fuel from the fuselage tank High pres sure fuel from the corresponding motive flow pump is routed to the jet pumps in each trans fer line The venturi principle draws fuselage fuel forward to the wings when th...

Page 130: ...shutoff valves are powered by the left and right emergency hot busses through the L and R FIRE FWSOV circuit breakers in the ENGINE group on the left and right circuit breaker panels respectively The valves are DC powered and will remain in their last position should DC power fail FUEL LOW PRESSURE SWITCHES The fuel low pressure switch is located in the engine feed line upstream of the engine driv...

Page 131: ... in the top aft part of the fuselage tank An open tube extends from the surge tank to the forward top part of the fuse lage tank to ventilate that part of the tank There is a small drain line which drains the NACA vent scoop to an exit point in the lower fuselage A combination vacuum relief and or pressure relief valve opens at 2 to 3 psi differential is also installed within the fuselage tank to ...

Page 132: ...R TRAINING PURPOSES ONLY FUSELAGE TANK TOP VIEW LEFT WING FUEL TANK RIGHT WING FUEL TANK VENT EXPANSION LINE NACA RAM AIR SCOOP FUSELAGE TANK SIDE VIEW FLOAT VALVE PRESSURE OR VACUMM RELIEF STORAGE LEGEND SURGE TANK FLAME ARRESTOR Figure 5 11 Fuel Vent System Schematic ...

Page 133: ...OW L ENGINE FEED L TRANSFER LINE L EXPANSION LINE L FILTER BEHIND HINGED PANEL R ENGINE FEED R TRANSFER LINE R EXPANSION LINE R FILTER BEHIND HINGED PANEL L INBOARD WING SUMP R INBOARD WING SUMP L OUTBOARD WING SUMP R OUTBOARD WING SUMP FUSELAGE TANK FUEL FILLER DOOR PORT 5 4 Figure 5 12 Fuel Drains ...

Page 134: ...drains located just forward of the main gear wheel well and the outboard wing sump drains are located just outboard of the outboard gear doors The general positions are illustrated in Figure 5 12 The wing sump drains are flush with the bottom of the wing and require a screwdriver to open them FUELING DEFUELING GENERAL The aircraft fuel system and engines are qualified for use with the fuel types s...

Page 135: ...ion The refuel defuel power on off switch is powered through the aircraft s rear hot bus Refueling Shutoff Valve and Pilot Valve The refueling shutoff valve is a poppet type valve that is spring loaded closed Figure 5 15 Fuel pressure fed through the refueling adapter forces the shutoff valve open when re fueling is initiated Fuel flows to the wing tanks through the two transfer lines and also int...

Page 136: ...ING FUEL TANK FUSELAGE FUEL TANK VENT EXPANSION LINE REFUEL DEFUEL D E F U E L PWR ON OFF READY OFF F U E L S Y S P A N E L TOTAL FUEL QTY TO RIGHT ENGINE DEFUELING VALVE PILOT VALVE RIGHT WING STANDBY PUMP NOTE On some aircraft equipped with the optional pylon lights the FUEL SYS switch has three positions Up is labeled ON FLD LT flood light middle ON and down OFF Figure 5 15 Single Point Pressur...

Page 137: ...e shutoff valve to open and refueling to resume GRAVITY REFUELING Refueling the aircraft can also be accom plished via gravity fill through the fuselage filler port located beneath a hinged panel on top of the fuselage Figures 5 2 and 5 13 The wing tanks will fill by gravity from the fuselage tank through the transfer lines the same as if SPPR were used except without the pressure assist from the ...

Page 138: ...E F U E L PWR ON OFF READY OFF F U E L S Y S P A N E L TOTAL FUEL QTY DEFUEL OPEN FUEL XFLO OPEN DEFUEL VALVE NOTE On some aircraft equipped with the optional pylon lights the FUEL SYS switch has three positions Up is labeled ON FLD LT flood light middle ON and down OFF Figure 5 16 Defueling System Schematic ...

Page 139: ...5 A FUEL IMBALANCE caution message will display on the EICAS whenever A The flaps are down and the quantity difference between wing tanks is more than 200 pounds B The flaps are up and the quantity dif ference between wing tanks is more than 350 pounds C Any time the difference is greater than 200 pounds between wing tanks D Both a and b are correct 6 When operating with dual generator fail ure wi...

Page 140: ... fuel imbalance of 350 pounds is indicated B The corresponding wing fuel quan tity is approximately 350 pounds C The wing tank float switch is sub merged D The fuselage fuel tank sensor indi cates a quantity less than 350 pounds 12 Wing fuel can be transfered to the fuse lage tank by turning on both standby pumps A True B False 13 The allow pressure to equal ize between all three fuel tanks A Ram ...

Page 141: ...AL 6 1 AUXILIARY POWER UNIT APU 6 2 General 6 2 Major Sections 6 2 APU Cooling Fans 6 4 APU Systems 6 5 APU Operation 6 7 Maintenance Panel 6 11 Oil Servicing 6 11 REVIEW QUESTIONS 6 12 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 142: ... 3 6 4 APU Exhaust Outlet 6 4 6 5 Left Side APU Cooling Fan 6 4 6 6 Right Side APU Cooling Fan 6 4 6 7 APU Cooling Fan Indicator and Reset Switch 6 5 6 8 APU Controls 6 7 6 9 APU Control Schematic 6 8 6 10 APU Maintenance Panel 6 11 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 143: ...down the APU at takeoff The APU air inlet is located above the left engine pylon and the exhaust is vented through a lou vered port located above the right engine pylon just aft of the ECU exhaust The APU is a fully automatic constant speed gas turbine engine designed to provide both electrical and pneumatic bleed air while on the ground Electrical power is supplied by the auxiliary generator moun...

Page 144: ...nd power unit GPU and a fuel supply from the aircraft main fuel sys tem APU operation is self governing with auto matic start sequence self monitoring and both normal commanded and automatic protective shutdown features An Electronic Control Unit ECU provides monitoring which automati cally maintains the required rpm and operat ing exhaust temperature EGT throughout start acceleration idle and ful...

Page 145: ... Compressor The compressor section consists of a single stage centrifugal impeller and diffuser The compressor develops approximately 45 psi at normal operating speed Combustion Section The combustion section consists of a single annular reverse flow combustion chamber and single ignitor plug 6 3 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ACCESSORY GEARB...

Page 146: ...4 Accessory Gearbox The accessory gearbox driven by the power section reduces the high speed low torque power section rpm to the low speed high torque required to drive the DC starter gen erator The accessories include the lubricating pump assembly fuel control and fuel pump unit and the starter generator APU COOLING FANS Due to potentially high tailcone temperatures when the APU is operating cool...

Page 147: ...chip detector is in stalled into the oil drain plug When the filter becomes contaminated a decrease in oil pres sure results in an automatic shutdown The lower portion of the gearbox is cast to form the oil tank reservoir The APU has no support bearings in the turbine area As a result no oil cooler is required and no external oil service is necessary The maintenance oil filler loca tion is located...

Page 148: ...gnals for automatic fuel and ignition initiation starter relay dropout and ignition termination The ECU controls APU speed at approximately 70 000 rpm When system faults are detected the ECU au tomatically shuts down the APU by closing the fuel solenoid valve Shutdowns due to a mon itored fault illuminate an amber APU FAIL light on the APU control panel and display an amber APU FAIL caution CAS me...

Page 149: ...igure 6 8 is pressed the ECU power supply is activated and initiates an internal test mode The operator must wait at least 10 seconds after pressing the APU MASTER S I before pressing the mo mentary START S I This allows the ECU to complete the power up and test modes Following the BITE test the APU START STOP S I on the cockpit panel is pressed to initiate the start The white START caption is ill...

Page 150: ...ER PRESS OFF R BLEED ON HI FLOW OFF PACK ON APU BLEED PRESSURIZATION CONTROL PANEL APU CONTROL PANEL ELECTRICAL CONTROL PANEL SEE CHAPTER 2 FROM RH ENGINE CHECK VALVE FROM LH ENGINE SEE CHAPTER 11 APU ECU FCU STARTER GENERATOR FUEL IN ACCESSORY GEARBOX COMPRESSOR TURBINE COMBUSTION SECTION IGNITOR EGT THERMOCOUPLE FUEL NOZZLES EXHAUST AIR INTAKE MONOPOLE PACK BI LEVEL PRSOV APU BLEED AIR VALVE ENV...

Page 151: ...is illuminated in the S I Additionally to allow APU bleed air into the cabin and cockpit the PACK S I must be se lected on The conditioning and distribution of APU bleed air is the same as engine bleed air as described in the Air Conditioning chap ter of this manual APU bleed air output is regulated by sensing the APU EGT and inlet air temperature As pneumatic load increases additional fuel flow i...

Page 152: ...U shutdown and an ECU power down A commanded shutdown using the START STOP switch results in an APU shutdown with the ECU remaining pow ered until another start is commanded or the APU MASTER switch is turned off Automatic Shutdown and Start Inhibit The ECU provides automatic shutdown for certain conditions Some fault conditions are detectable prior to a start attempt These con ditions become star...

Page 153: ...imately 18 5 ounces 550 cc below full The Oil Servicing Addendum indicates that action is re quired At the time the LOW annun ciator is illuminated the operator has five 5 hours of operation until oil must be added to the APU gearbox 3 Activation of the momentary OIL TEST switch must only be accom plished when the APU is not running EMERGENCY SHUTDOWN Removes electrical power from the ECU which ca...

Page 154: ...mption rate is ap proximately pounds per hour A 50 B 75 C 100 D 150 5 The AFM limitation field pressure alti tude for APU operation is A 5 000 ft B 8 000 ft C 10 000 ft D 14 000 ft 6 The following switch configuration is re quired to check the APU oil level A Cockpit APU Master Switch must be on only B Right battery and cockpit APU Master Switch must be on C No cockpit switches need to be on D Pow...

Page 155: ...Section 7 4 Exhaust Section 7 5 Accessory Section 7 5 ENGINE INSTRUMENTS 7 6 General 7 6 Engine Displays 7 6 Fan Speed N1 7 7 Turbine Temperature ITT 7 9 Turbine Speed N2 7 10 Oil Indications 7 10 Fuel Flow 7 10 EICAS Engine Indications 7 12 Engine CAS Messages 7 12 Crew Warning Panel CWP 7 14 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 156: ...l Supply 7 20 Engine Fuel Pumps 7 21 Fuel Heater 7 21 Engine Fuel Filter 7 21 Fuel Control Unit FCU 7 22 Fuel Flow Sensor 7 22 Flow Divider 7 24 Fuel Manifolds Nozzles 7 24 ENGINE SUB SYSTEMS 7 24 Ignition 7 24 Starter 7 25 Engine Synchronization 7 27 Automatic Performance Reserve APR 7 28 Engine Vibration Monitor 7 28 Engine Diagnostic System EDS 7 28 LEARJET 45 PILOT TRAINING MANUAL 7 ii FOR TRA...

Page 157: ...7 33 Components 7 33 Electronic Control Unit ECU 7 33 Actuators 7 35 Isolation Valve 7 35 Control Valve 7 35 Latches Hooks 7 35 Indications 7 35 System Operation 7 37 General 7 37 Arming 7 37 Deploy 7 37 Reverse Thrust 7 37 Stow Normal Automatic 7 40 Automatic Throttle Retard 7 40 REVIEW QUESTIONS 7 41 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 158: ...Indicator Display 7 15 7 11 Engine Fuel Control Panel 7 16 7 12 Thrust Levers 7 17 7 13 DEEC on TFE731 20 Engine 7 18 7 14 DEEC Inputs and Outputs 7 19 7 15 Engine Fuel System Components 7 21 7 16 Engine Fuel Control Schematic 7 23 7 17 Engine Start and Ignition Switches 7 25 7 18 EICAS Engine Start Annunciations 7 25 7 19 ENG SYNC Switch 7 27 7 20 EICAS SYNC Annunciation 7 27 7 21 Engine Oil Tank...

Page 159: ...8 Thrust Reverser System Schematic 7 39 7 29 Reverser Thrust Limit Schedule 7 40 TABLES Table Title Page 7 1 Engine Speed Display 7 9 7 2 ITT Display 7 9 7 3 EICAS Engine Annunciations 7 13 7 4 Engine CAS Messages 7 13 7 5 Oil Pressure Display 7 32 7 6 Oil Temperature Display 7 32 LEARJET 45 PILOT TRAINING MANUAL 7 vi FOR TRAINING PURPOSES ONLY FlightSafety international ...

Page 160: ...The op erator will notice no difference in these en gines but the 20AR does have extra temperature margines Hydraulically oper ated target type thrust reversers are a standard feature The TFE731 series engine is manufactured by Honeywell International Inc The engine is a lightweight two spool geared front fan engine Each engine develops 3 500 pounds of thrust static at Sea Level S L up to 88 degre...

Page 161: ...ce decreases as altitude increases Powered by the low pressure turbine the plan etary gear reduction assembly provides power to drive the titanium fan assembly The rpm of the low pressure rotor is designated N1 commonly referred to as fan speed Engine thrust is set using this rpm indication The unheated spinner is bolted to the front of the fan The fixed in place stator directs the majority of the...

Page 162: ... located beneath the engine unit Stall surge protection for the LP compressor is provided by an automatically controlled surge bleed valve This function is controlled by the digital electronic engine control DEEC and prevents engine stall during rapid deceleration or acceleration Air leaving the HP compressor is then forced through a transition duct into a plenum cham ber surrounding the combustor...

Page 163: ...ntrols the mixing of fuel and air contains the combustion of ex panding gases and directs them to the tur bine section Figure 7 2 Two drain valves are located at the lowest part of the combustion plenum and are used to drain fuel from the engine following shut down or an aborted start TURBINE SECTION The expanding combustion gases generating extremely high pressures as they exit the com bustion se...

Page 164: ... the LP turbines are ten thermocouples that extend into the gas path and report the interstage turbine tem perature ITT The combustion gases are then exhausted through the exhaust duct EXHAUST SECTION The resulting thrust created by the combustion air passing through the exhaust section adds to the thrust generated by the inlet fan pass ing through the bypass air duct to produce the total propulsi...

Page 165: ...on the radio management units RMUs and in some cases this is auto matic ENGINE DISPLAYS As illustrated in Figure 7 6 the following is a list of the left and right engine indicators shown in the engine field portion of the EICAS N1 analog fan speed scale with digital readout ITT analog interstage turbine temper ature with digital readout N2 digital readout of turbine speed OIL PSI digital readout o...

Page 166: ...alibration of the engine Each N1 indicator on the EICAS display has both an analog scale arc and pointer together with a four digit readout within a cyan box Figure 7 6 The range of the arc is 0 110 and the range of the digital display is far in ex cess of the engine capability The digital dis play values will change in 0 1 increments The N1 analog scale arc is white with a white pointer The white...

Page 167: ...gure 7 6 EICAS Engine Instrument Display Format N1 ITT SAT C L F 1000 R 1450 FLAPS 20 6 5 PITCH TRIM LBS FUEL 3850 15 50 0 76 60 984 50 0 80 60 1002 N2 OIL PSI OIL C FF PPH 550 550 75 0 75 0 1400 CAS DISPLAY Area 89 6 89 6 LEFT N1 INDICATOR SCALE WHITE HORIZONTAL TICK RED NEEDLE RED WHITE RIGHT N1 INDICATOR SCALE WHITE HORIZONTAL TICK RED NEEDLE RED WHITE LEFT N1 BOX CYAN RED DIGITS WHITE RED RIGH...

Page 168: ...d tick the pointer and the digital display will turn red and a red exceedance arc will appear on the scale from the tick up to 1 014 degrees C An amber caution band will appear prior to the red tick under some conditions See Table 7 2 The engine has different maximum ITT lim its specified for different operating conditions such as start takeoff computer off etc The DEEC will automatically change t...

Page 169: ...of the turbine rotation speed The N2 range is from 0 to 115 percent If N2 exceeds 100 0 the display will change from white to amber and an amber box will appear around the N2 digital display If N2 exceeds 102 5 the display will change from amber to red and a red box will appear around the dig ital display If APR is activated the N2 dis play will not turn amber unless 101 1 is exceeded See Table 7 ...

Page 170: ... converter DFFC located downstream of the FCU fuel control unit and prior to the flow dividers acquires data from two temperature sensing volumetric fuel flow meters and determines fuel mass flow This information is passed through the DAUs to the symbol generators and then to the fuel flow displays on the EICAS 985 880 100 1014 916 985 880 100 1014 941 CONDITION 1 Power set to below T O and APR no...

Page 171: ...his chapter will only discuss the engine and thrust reverser related messages LEARJET 45 PILOT TRAINING MANUAL 7 12 FOR TRAINING PURPOSES ONLY FlightSafety international N1 ITT L F 1000 R 1750 LBS FUEL 4450 50 0 76 60 984 50 0 80 60 1002 N2 OIL PSI OIL C FF PPH 550 550 75 0 104 0 1700 REV IGN NAC IGN NAC S T A R T S T A R T SYNC UNL FIRE FIRE APR ON SYNC MAN MCR MCR MAN LEFT STARTER ENGAGED GREEN ...

Page 172: ... PT2 heat O K L R starter is engaged SYNC is ON N1 or N2 APR throttle detent selected MCR throttle detent selected MCT throttle detent selected IGN NAC START SYNC APR MCR MCT T O Takeoff throttle detent selected Table 7 3 EICAS ENGINE INDICATIONS CAS Message Logic Summary L R FUEL PRESS LOW Low pressure to engine fuel pump inlet 1 psi W Warning C Caution A Advisory Type Msg W C A A A A A A L R ENG...

Page 173: ...S on either DU 2 or DU 3 two pages of engine in dicator displays can be selected on either RMU In some cases this selection will be au tomatic on RMU 1 To manually select the en gine indicator display on a RMU depress the PGE mode select key at the bottom of the RMU This will bring a page menu onto the screen Depress the line select key adjacent to ENGINE PG1 to make the first page of en gine indi...

Page 174: ...ents of each engine s control system are the engine control panel thrust lever the electronic fuel computer DEEC the en gine driven fuel pump and the fuel control unit LEARJET 45 PILOT TRAINING MANUAL FOR TRAINING PURPOSES ONLY FlightSafety international 7 15 FOR TRAINING PURPOSES ONLY Honeywell TUNE SQ DIM 1 2 STO DME TST PGE ID Honeywell TUNE SQ DIM 1 2 STO DME TST PGE ID MORE FUEL HYDM B SPLFLP...

Page 175: ...UST LEVERS Two thrust levers Figure 7 12 are located in a quadrant on the forward section of the cen ter pedestal Thrust reverser levers are pig gyback mounted on the thrust levers The thrust levers operate in a somewhat conven tional manner except the throttle quadrant has detents in the forward range Each thrust lever is connected to a rotary variable differential transformer RVDT In the normal ...

Page 176: ...ed as a green MCR MCT T O or APR on the EICAS just outboard of the N1 dig ital displays Figure 7 8 The IDLE position provides either flight idle or ground idle depending on the signal from the squat switches With the thrust levers at the IDLE position flight idle is approximately 65 N2 at low altitude and increases propor tionately with altitude Ground idle approx imately 52 N2 will be commanded 2...

Page 177: ...r stalls and surges The DEEC ini tiates an automatic start sequence when the thrust lever is positioned to IDLE and the cor responding engine start button is depressed This includes automatic fuel enrichment to 200 degrees Celsius ITT The DEEC receives input signals representing the following engine parameters Figure 7 14 N1 fan speed N2 turbine speed Thrust lever RVDT PT2 inlet pressure TT2 inlet...

Page 178: ...However if electrical power is still available to the DEEC and the computer switch is in MAN it still monitors N1 and N2 and can pro vide engine overspeed protection by energiz ing the ultimate overspeed solenoid closed if N1 reaches 107 or N2 reaches 109 If the L R CMPTR switch is placed to OFF or electrical power to the computer is lost op eration is the same as with the switch in man ual but th...

Page 179: ...ult in reduced engine efficiency Temperature limiting and precise engine speed control is lost except the mechanical governor in the fuel controller should limit N2 to 105 and if MAN is selected on the ENG CMPTR switch the ultimate overspeed protection will still be available depending on the malfunc tion Power adjustments should be made slowly and cautiously and much closer engine mon itoring is ...

Page 180: ...lve will function to by pass the hot oil and limit the fuel temperature If the fuel temper ature exceeds 130 Celsius a white L R FUEL HEATER message will be displayed by the CAS indicating the fuel oil heat exchanger has failed to the hot condition If the fuel is too cold with fuel temperature less than 10 C and the oil temperature is greater than 86 C an amber L R FUEL HEATER caution message will...

Page 181: ...t is energized closed by the DEEC at 107 N1 or 109 N2 to shut off fuel Operates with com puter on or with MAN selected A manual shutoff valve operated me chanically by thrust lever movement be tween CUTOFF and IDLE Operates with computer on or in manual A manual mode solenoid which is nor mally energized open by the DEEC dur ing computer on operation Pneumatic circuits to channel and con trol P3 b...

Page 182: ... FUEL HEATER FUEL OIL COOLER FAILURE TOO COLD IGNITION RELAY LR FUEL FILTER IMPENDING BYPASS FILTER BYPASS ADC L R ENGINE COMPUTER SWITCHES MANUAL SHUTOFF VALVE FUEL FLOW METER FUEL CONTROL UNIT ACC GEAR BOX ENGINE FUEL CONTROL PANEL HYDRAULIC PUMP LEGEND LOW PRESSURE FUEL HIGH PRESSURE FUEL ENGINE BLEED AIR ELECTRICAL MECHANICAL RESTRICTOR HIGH PRESS PUMP LOW PRESS PUMP FUEL L STBY R STBY XFLOW F...

Page 183: ... first is normal engine start when the thrust lever is moved to the idle detent and the START switch is depressed Ignition is commanded on at 6 8 N2 and turned off at approximately 45 N2 The thrust lever must be at IDLE position for automatic activation of ignition during start 2 The second mode is for uncommanded engine deceleration If N1 is below a set point and N2 is not accelerating the igniti...

Page 184: ... right side respectively on the engine fuel control panel on the center pedestal Figure 7 17 The start switch is a momentary action switch with a white ON an nunciator that illuminates when the switch is de pressed indicating the start relay is energized A START annunciator will also appear on the EICAS Figure 7 18 when the starter is engaged For each engine START will ap pear vertically outboard ...

Page 185: ...au tomatic mode the GEN S I must be depressed to turn the generator on The automatic start sequence is generally very reliable and trouble free however the pilot should carefully monitor the N1 and N2 spools ITT and oil pressure during start If both spools do not increase smoothly and rapidly to idle rpm after light off then the start should be aborted The maximum time for the engine to accelerate...

Page 186: ...C annunciates between the N1 indicators If the switch is placed to the N2 position SYNC appears between the N2 digital displays on the EICAS Figure 7 20 In both cases N1 or N2 selected the an nunciator will be green if the landing gear is up and amber if the gear is not locked up Sync must be off for takeoff and landing thus the amber color is to alert the pilot to turn the synchronization system ...

Page 187: ...DEEC command for increased thrust Once APR has been activated in the auto mode the APR arm switch must be cycled to off to return to normal operation If APR is inad vertently activated on the ground i e if the pilot uses differential thrust during taxi cy cling the APR switch off and back to ARM again with the N2 rpm s matched within 15 will reset the system Performance reserve may be selected man...

Page 188: ...required if oil level is one quart low Oil levels should be checked during the exte rior inspection If the oil quantity is not checked within one hour of engine shutdown an inac curate indication may result If preflight oil level checks low start and run the affected en gine until stabilized at idle shut down the en gine and recheck the oil level If there is no oil level indication add enough oil ...

Page 189: ...at portion of the oil that is dispensed to the fan reduction gearbox planetary gears the transfer gearbox and to bearings 4 and 5 is routed through the fuel heater oil cooler FHOC Figure 7 22 This heat exchanger provides for additional oil cooling and for LEARJET 45 PILOT TRAINING MANUAL 7 30 FOR TRAINING PURPOSES ONLY FlightSafety international LEGEND AIR VENT INLET OIL SCAVENGE OIL HIGH PRESSURE...

Page 190: ...vent for the oil system at low altitudes and at high altitudes increases the vent and tank pressure to prevent oil foaming and to ensure proper oil pump operation LEARJET 45 PILOT TRAINING MANUAL 7 31 FOR TRAINING PURPOSES ONLY FlightSafety international L OIL PRESS LOW R OIL PRESS LOW OIL SYSTEM WARNINGS ON CWP ITT L F 1000 R 1750 LBS FUEL 4450 50 0 49 60 984 50 0 80 60 1002 N2 OIL PSI OIL C FF P...

Page 191: ...ressure is below 50 psi Figure 7 23 ENGINE CHIP DETECTOR A magnetic chip detection plug is installed in the scavenge line for detection of metal par ticles in the oil If sufficient metal particles ac cumulate on the chip plug while inflight a white L R ENGINE CHIP advisory CAS message will appear on the EICAS Figure 7 23 An amber L R ENGINE CHIP CAS ap pears if metal particles are detected in the ...

Page 192: ... to a sched ule based upon the airplane s airspeed Figure 7 29 Hydraulic pressure is provided from the main hydraulic system for operation of the thrust re verser unlatch actuators and the primary ac tuators Auxiliary hydraulic system pressure is not provided to the thrust reversers and the thrust reversers do not have a backup accu mulator dedicated to thrust reverser operation An automatic emerg...

Page 193: ...ING PURPOSES ONLY FlightSafety international HYDRAULIC CONTROL UNIT HCU AFTERBODY THROTTLE RETARD ACTUATOR LOWER DOOR ASSEMBLY PRIMARY ACTUATOR DEPLOY SWITCH LINK RODS UPPER DOOR ASSEMBLY LATCH ASSEMBLY Figure 7 25 Thrust Reverser Doors and Latches ...

Page 194: ...The control valve or hydraulic control unit HCU located on the engine is electrically controlled through solenoids powered by the ECU to route hydraulic pressure to the un latch actuators and to the deploy or stow side of the primary actuators Whenever the con trol valve is positioned to the stow position hydraulic pressure is also sent to the throttle retard actuator Figure 7 28 Latches Hooks Two...

Page 195: ...ploy command ECU power fail The L or R REV FAULT CAS message may be accompanied by a red DEP or UNL EI Normal indications are a white REV display which means that the reverser is armed on the ground the isolation valve is open and hy draulic pressure is available up to the control valve When deploy is commanded the amber UNL annunciators will be on momentarily during deployment When the thrust rev...

Page 196: ...tches will cause the amber UNL annunciator to display on the EICAS until the doors are fully deployed When the doors are fully deployed a deployed switch Figure 7 25 will cause the UNL annunciator to extinguish and a green DEP annunciator to illuminate The thrust reverser doors should fully deploy within 1 second Reverse Thrust When the deployed signal is received by the ECU it energizes a throttl...

Page 197: ...ee page 7 36 THRUST REVERSER CAS MESSAGE DATA BASE THRUST REVERSER ANNUNCIATIONS ON EICAS THRUST REVERSER WARNINGS ON CWP EICAS EI s Logic Summary W Warning C Caution A Advisory Type Msg C A C A W W DEP UNL REV DEP UNL REV TR deployed in flight or on ground w o being unlocked or deploy switch is bad TR unlocked in flight or on ground w o being armed or bad unlock switch HCU powered TR armed in fli...

Page 198: ...S DOOR DOOR ACTUATORS DOOR LATCH HOOK ACTUATORS LATCH HOOK ACTUATORS HCU s CONTROL VALVES ON ENGINE MAIN HYDRAULIC SYSTEM PRESSURE RETURN DEPLOY STOW UNLATCH LEGEND PRESSURE SWITCHES ISOLATION VALVES IN TAILCONE THROTTLE RETARD ACTUATOR THROTTLE RETARD ACTUATOR Figure 7 28 Thrust Reverser System Schematic ...

Page 199: ... cycle and also to correct an abnormal condition inflight autostow Autostow continues until no more than one hook is in the unlocked position An amber UNL will illuminate on the ground if a single unlock switch is indicating unlocked and the thrust reverser is not fully deployed or de ploy has not been commanded i e reverser lever forward of idle deploy position In this case autostow is not comman...

Page 200: ...nue to operate through DAU 2 B Left engine indicators for N1 ITT N2 oil pressure oil temperature and fuel flow will be lost C If the DAU NORM reversion switch is selected to Channel B all engine in struments will be restored D If the IC SG NORM switch is selected to No 2 all engine instruments will be restored 7 When the thrust levers are set to the T O detent the red line is at 941 C on the ITT i...

Page 201: ...The FCU B The fuel flow divider C The motive flow injector pump D The FHOC 16 When operating with a dual generator failure which engine instrument s will be available for display on the RMU A N1 B N2 C Fuel flow D All of the above are available 17 The DEEC functions to provide all of the following except A Overspeed protection B N2 bug rating display C Thrust management D Automatic performance res...

Page 202: ...in ________ of engine shutdown an inac curate indication may result A 10 minutes B 30 minutes C 1 hour D There is no time limit 23 Engine oil is cooled by means of A Finned air oil coolers B Ram air sump vent system C Fuel heater oil cooler assembly D Both a and c 24 Normal oil pressure is A 37 75 psi B 50 64 psi C 65 80 psi D 65 120 psi 25 A an DEP displayed on the EICAS means that the thrust rev...

Page 203: ... Extinguisher Containers 8 4 Exterior Extinguisher Discharge Indicators 8 6 APU FIRE PROTECTION SYSTEM 8 7 General 8 7 Controls and Indications 8 7 System Operation 8 10 FIRE DETECTION SYSTEM TEST 8 10 HAND HELD FIRE EXTINGUISHERS 8 11 REVIEW QUESTIONS 8 12 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 204: ...Extinguishing Agent Containers 8 6 8 6 Fire Extinguisher Discharge Indicators 8 6 8 7 APU Fire Detection Loop 8 7 8 8 APU Fire Extinguisher Container and Pressure Gage 8 8 8 9 APU Control Panel 8 9 8 10 APU Maintenance Control Panel 8 9 8 11 Crew Compartment Fire Extinguishers 8 11 8 12 Cabin Fire Extinguisher 8 11 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety internatio...

Page 205: ...stem includes a horn located in the nose wheel well ENGINE FIRE DETECTION The fire detection system for each engine con sists of heat sensing elements a control unit and a warning light Each engine cowling con tains three heat sensing elements connected to the fire detection control units Each control unit is then connected to respective engine FIRE PUSH switch indicators located on the center ped...

Page 206: ...cate a fire Electrical power for each engine detection system is 28 VDC supplied through the left and right FIRE DET circuit breakers located in the left and right engine circuit breaker groups The engine fire detection systems are powered from the respective left and right es sential busses The fire extinguishers and shut off valves are powered by the left and right hot busses and are functional ...

Page 207: ...ays FIRE red next to the N1 analog RPM tape for the af fected engine Either master WARN light may be depressed to cancel the master WARN lights cancel the voice message and to stop the flashing of the EICAS FIRE annunciator The EICAS FIRE annunciator and the FIRE PUSH button remain illuminated as long as the over LEARJET 45 PILOT TRAINING MANUAL 8 3 FOR TRAINING PURPOSES ONLY FlightSafety internat...

Page 208: ...the fire extinguishing system is from the emergency hot busses and airplane power does not have to be on to perform the engine fire procedure When the FIRE PUSH button is depressed arming of the extinguisher system is evidenced by the illumination of the adjacent Extinguisher 1 and 2 ARMED lights Figure 8 3 The ARMED light switches are guarded with clear plastic covers to prevent inadver tent acti...

Page 209: ...OFF VALVE HYDRAULIC SHUTOFF VALVE TR ISOLATION VALVE RELIEF VALVE RELIEF VALVE TWO WAY CHECK VALVES PRESSURE GAGE PRESSURE GAGE LH CONTAINER RH CONTAINER THERMAL DISCHARGE INDICATOR MANUAL DISCHARGE INDICATOR CLOSED FIRE PUSH ARMED ARMED EXTINGUISHER FIRE 1 2 L ENGINE CLOSED ARMED ARMED EXTINGUISHER FIRE 2 1 R ENGINE LEGEND ENGINE DISCHARGE MANUAL DISCHARGE THERMAL DISCHARGE FIRE PUSH L FWSOV CLSD...

Page 210: ...ief valve on each container is plumbed to a common thermal discharge port on the outside of the fuselage aft of the tailcone access door The thermal relief valves will re lease bottle pressure at approximately 220 F EXTERIOR EXTINGUISHER DISCHARGE INDICATORS Two colored disc type indicators are flush mounted in the right side of the fuselage aft of the tailcone access door Figure 8 6 The red color...

Page 211: ...ishing agent container is located on the forward right hand exterior area of the containment box Figure 8 8 The pres sure gage indicates a discharged partially dis charged or full container CONTROLS AND INDICATIONS APU Cockpit Control Panel The APU cockpit control panel is used to con trol the APU operation and monitor the elec trical load of the starter generator The crew LEARJET 45 PILOT TRAININ...

Page 212: ... event of an overheat or fire Figure 8 10 The ECU commands APU shutdown as a result of the power loss To reapply power to the ECU reset the SHUTDOWN switch In the event of a cockpit or cabin bleed air duct overheat condition the ECS overheat relay and temperature control relays within the APU Maintenance Control Panel open and command the ECU to shut down the APU APU Fire Indications In the event ...

Page 213: ...ING MANUAL 8 9 FOR TRAINING PURPOSES ONLY FlightSafety international I0 0 APU FAIL START RUN ON A P U GEN AMPS MASTER START STOP FIRE PUSH FIRE APU FIRE Figure 8 9 APU Control Panel Figure 8 10 APU Maintenance Control Panel ...

Page 214: ...e panel also sends a signal to the Electronic Control Unit ECU which relays the signal to the cockpit for an APU fire warning The APU shutdown and extinguisher discharge sequence can also be manually initiated by depressing the red FIRE PUSH button located on the APU control panel FIRE DETECTION SYSTEM TEST Rotating the airplane system test knob on the center pedestal to the FIRE DET position and ...

Page 215: ...tinguisher is located within the crew compartment and the second extinguisher is located in the aft area of the passenger com partment As an option two smaller fire ex tinguishers are available as a replacement for the crew compartment extinguisher These are mounted on the front base of the crew seats See Figures 8 11 and 8 12 LEARJET 45 PILOT TRAINING MANUAL 8 11 FOR TRAINING PURPOSES ONLY Flight...

Page 216: ... In the tailcone baggage compartment B At the rear of the cabin C In the tailcone equipment compart ment D This airplane does not have a smoke detector 5 When an overheat fire condition is de tected within an engine nacelle all of the following warnings are activated except A A red FIRE is displayed within the appropriate engine ITT arc on EICAS B A repeating voice message Left or right engine fir...

Page 217: ...9 3 Bleed Switches 9 3 ECS Controller 9 3 ECS Pressure Regulator Shutoff Valves ECS PRSOV 9 4 HP Shutoff Valves HP SOV 9 4 Pylon Overhear Detection 9 9 Bleed Air Duct Overheat Detection 9 9 Tailcone Leak Detection 9 9 Emergency Pressurization 9 11 Servo Air System 9 12 Pneumatic System Indications and Displays 9 12 Pack Control Valve 9 12 REVIEW QUESTIONS 9 14 FOR TRAINING PURPOSES ONLY LEARJET 45...

Page 218: ...matic 9 7 9 4 Tailcone Leak Detection System 9 8 9 5 Emergency Pressurization Distribution 9 10 9 6 Pneumatic System Indications and Displays 9 13 TABLES Table Title Page 9 1 Bleed Air Valve Configuration 9 5 9 2 Bleed Air System CAS Message Database 9 13 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 219: ...rization when demand is high or LP bleed air supply is low The bleed air sup plied by a single engine is capable of provid ing all normal bleed air needs HP bleed air is also used for anti icing of the wings horizontal stabilizer and the engine nacelle inlets A small amount of HP bleed air is also used to pressurize the hydraulic reser voir for CPCS jet pump operation and as a servo air source for...

Page 220: ...automatically by the Cabin Pressurization Controller CPC HIGH PRESSURE HP BLEED AIR SYSTEM High pressure HP bleed air is extracted from each engine through four outlets on the HP compressor transition duct Figure 9 2 Bleed air from the four HP outlets is then routed to a single collector on each engine before being ducted through the engine pylons to the left and right HP SOVs in the tailcone The ...

Page 221: ... channel controls the same valves on the right side The controller channels receive independent inputs from pressure sensors in the HP ducts the Cabin Pressurization Controller Thrust Lever angle BLEED switch position and EMER PRESS switch position The left and right channels of the controller receive 28 VDC from the left and right es sential busses respectively through the L BLEED and R BLEED cir...

Page 222: ...S PRSOVs are closed other than through the L and R BLEED switches The corresponding ECS PRSOV is automatically energized closed by the ECS Controller when an engine FIRE PUSH switch indicator is depressed and both ECS PRSOVs are energized closed when emer gency pressurization is activated HP SHUTOFF VALVES HP SOV The left and right HP SOVs are independently controlled by the left and right channel...

Page 223: ...ed Open Powered Open Powered Open L R BLEED CB Open ECS PRSOV HPSOV EMER PRESS De Powered Open De Powered Closed De Powered Closed FIRE PUSH Depressed CLOSED ECS PRSOV Powered Closed PACK On Dark BI LEVEL PRSOV De Powered Open PACK OFF BI LEVEL PRSOV Powered Closed With Emergency Pressurization activated on both sides subsequent selection of either Bleed S I OFF to reduce temperature is an option ...

Page 224: ...SOV A I PRSOV A I CHECK VALVE A I PRSOV A I CHECK VALVE STAB A I WING A I WING A I ECS CHECK VALVE ECS CHECK VALVE LOW LIMIT TEMP SENSOR EMER PRESS SOV EMER PRESS ISOLATION CHECK VALVES DISTRIBUTION CHECK VALVES 5 EMER PRESS SOV APU CHECK VALVE APU LOAD SOV APU ECU ECS BLEED AIR OVERTEMP SWITCH 700 F 1 ECS BLEED AIR OVERTEMP SWITCH 700 F 1 PACK BI LEVEL PRSOV RAM AIR CHECK VALVE 2 3 3 TEMP CONTROL...

Page 225: ...PRESS SWITCH 130 PSI HP PRESS SWITCH 130 PSI ECS PRSOV ECS PRSOV A I PRSOV A I PRSOV WING A I WING A I ECS CHECK VALVE ECS CHECK VALVE EMER PRESS SOV EMER PRESS SOV APU LOAD SOV FROM APU ECU PACK BI LEVEL PRSOV HIGH PRESSURE LOW PRESSURE APU AIR MIXED AIR COLD AIR LEGEND APU BLEED ON HI FLOW PACK ON OFF OFF OFF EMER PRESS L BLEED R BLEED ON CPCS LEFT CH RIGHT CH 28 VDC 28 VDC L BLEED R BLEED ECS C...

Page 226: ... ECS PRSOV A I PRSOV A I CHECK VALVE A I PRSOV A I CHECK VALVE STAB A I WING A I WING A I ECS CHECK VALVE ECS CHECK VALVE LOW LIMIT TEMP SENSOR EMER PRESS SOV EMER PRESS ISOLATION CHECK VALVES DISTRIBUTION CHECK VALVES 5 EMER PRESS SOV APU CHECK VALVE APU LOAD SOV APU ECU ECS BLEED AIR OVERTEMP SWITCH 700 F 1 ECS BLEED AIR OVERTEMP SWITCH 700 F 2 PACK BI LEVEL PRSOV RAM AIR CHECK VALVE 3 TEMP CONT...

Page 227: ...ents routed near the ducts The elements are the same loop type elements as used for engine fire detection but are designed to trip the detection system at 255 F Left and right sensing elements monitor for bleed air leaks in the ducts from the HP SOVs on each side inboard to the PACK Bi Level PRSOV Figure 9 4 If a leak occurs between either the HP SOV and the ECS check valve down stream of it the c...

Page 228: ...SOV A I CHECK VALVE A I PRSOV A I CHECK VALVE STAB A I WING A I WING A I ECS CHECK VALVE ECS CHECK VALVE LOW LIMIT TEMP SENSOR EMER PRESS SOV EMER PRESS ISOLATION CHECK VALVES DISTRIBUTION CHECK VALVES 5 EMER PRESS SOV APU CHECK VALVE APU LOAD SOV APU ECU ECS BLEED AIR OVERTEMP SWITCH 700 F 1 ECS BLEED AIR OVERTEMP SWITCH 700 F 1 PACK BI LEVEL PRSOV RAM AIR CHECK VALVE 2 3 3 TEMP CONTROL PRSOV 1 L...

Page 229: ...urned off on the left or right side by turning OFF the L or R BLEED switches EMER PRESS Operation The emergency pressurization valves labeled EMER PRESS VALVE in Figure 9 5 are lo cated in the tailcone and are normally closed The valves are energized open when emer gency pressurization is activated At the same time the ECS PRSOVs are energized closed and the HP SOVs are de energized closed These v...

Page 230: ... system receives HP bleed air from ducting located between the engine and the HP SOV The bleed air is regulated to 15 1 psi by the servo air pressure regulating valve and then distributed via tubing to the sys tems that use it Servo air is used to supply actuation power for the cockpit and cabin temperature control valves the low limit temperature control valve on the ECU and to pressurize the hyd...

Page 231: ...0 MANUAL RATE LDG ALT 2200 10 000 CAB TEMP 78 F TEMP CONT CABN CKPT OXY C OXY PSI 10 1800 H C 33 30 W N 3 6 E 12 15 S 21 24 3 2 1 0 1 2 3 1000 20 20 10 10 10 10 150 4500 29 92 IN 5000 160 180 14 1 0 9 120 100 160 400 M GS LOC HDG AP YD SPD GS 180 RA HDG 001 359 CRS ILS1 13 1 NM 25 TGT VOR1 ADF2 RA BARO STD BARO MINIMUMS 4380 20 00 Honeywell Honeywell SYS MFD MENU WX CKLST PLAN MAP TCAS Honeywell H...

Page 232: ...her also increasing total airflow from the en gines The normal position is OFF with no legend in the HI FLOW switch When selected ON illuminates in the S I and a white PACK HI FLOW message is posted on the CAS Activation of HI FLOW requires 28 VDC through the PACK circuit breaker 9 14 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 233: ...llumination of a L or R BLEED AIR LEAK warning CAS message indicates A The respective bleed air detection loop in the tailcone has exceeded 255 F B A bleed air temperature sensor in the pylon has exceeded 250 F C Bleed air in the respective supply duct has exceeded 700 F D PACK turbine discharge has exceeded a temperature of 450 F 6 Wing Stab anti ice is available when both sides are in the emerge...

Page 234: ... pressurization A When the cabin altitude is below 8 000 feet by cycling the L and R BLEED switches OFF and then back ON B When the cabin altitude is below 8 000 feet by selecting the PACK switch to ON C When the cabin altitude is below 8 000 feet by selecting the EMER PRESS switch to OFF D At any altitude by selecting the EMER PRESS switch to OFF 12 Which of the following is true regarding pressu...

Page 235: ...10 3 ANTI ICE SYSTEMS 10 3 Engine Anti Ice System 10 4 Windshield Anti Ice and Defog System 10 6 Wing Stab Anti Ice System 10 9 Pitot Static and Stall Warning Anti Ice Systems 10 13 REVIEW QUESTIONS 10 14 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 236: ... Stab Anti Ice System Schematic 10 10 10 7 Wing Stab Anti Ice System Warnings on CWP and EICAS 10 11 10 8 Pitot Static Probes AOA Transducer Vanes and Total Air Temperature Probe 10 12 TABLES Table Title Page 10 1 Ice and Rain Protection CAS Message Data Base 10 7 10 2 Probes Heat Summary 10 13 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international LEARJET 45 PILOT ...

Page 237: ... turned on be fore icing conditions are encountered To delay equipment turn on until ice build up is visu ally detected on airplane surfaces constitutes an unacceptable hazard to safety of flight Icing conditions exist whenever the SAT is 10 C to 40 C and visible moisture in any form is present such as clouds rain snow sleet ice crystals or fog with visibility of one mile or less LEARJET 45 PILOT ...

Page 238: ...een de tected The ice detector deices itself through integral heating elements until the frequency is restored to a preset point The heaters are then left on for an additional 4 5 seconds to ensure complete deicing of the probe Once the probe has deiced the heating ele ments are de energized If ice subsequently accumulates on the probe the ICE DE TECTED CAS message is again displayed and the deici...

Page 239: ...he external LIGHTS control panel The light beam illuminates an area of the outboard right wing leading edge that has a black spot affixed to it to enhance visual de tection of ice accumulation NOTE Clear ice on the wing leading edge may not be detectable from the cockpit ANTI ICE SYSTEMS Airplane anti icing is accomplished through the use of engine bleed air and electrical heat ing systems to prev...

Page 240: ...ted within each engine nacelle inlet lip and distributes bleed air throughout the inlet lip The dif fuser is connected to the engine bleed air reg ulated pressure duct by the nacelle anti ice duct After circulating around the inlet lip excess bleed air is vented overboard through a hole at the bottom of the nacelle lip Nacelle Heat Switches The two lower switches on the ANTI ICE con trol panel are...

Page 241: ...e corresponding engine inlet pres sure temperature probe Pt2Tt2 is not detected Whenever a NAC annunciator is displayed in amber for the above reasons there is a cor responding amber L or R NAC HT message displayed on the CAS A NAC annunciator will also be amber if the NAC heat switch is off and the pressure switch senses 6 5 psi or more bleed air pressure to that engine nacelle In this case there...

Page 242: ...indshield anti ice defog will be inoperative The windshield is a layered polycarbonate and urethane design with a glass outer layer The underside of the glass is coated with a form of tin oxide that conducts electricity The heat ing element is the tin oxide layer that is heated via AC electricity Each windshield half con tains normal and overtemperature sensors imbedded in the upper forward sectio...

Page 243: ...ary Type Msg W C C C C C C C C C W W A A C C C WING STAB LEAK Leak detected 255 F in wing or stab supply lines STAB OVHT WING OVHT AOA vane heater failed w probe heat ON ICE DET FAIL ICE DETECTED Ice detect system failed L R AOA HT FAIL Ice detected Anti Ice systems OFF ground suppressed L R NAC HT L R NAC HT FAIL ON L R PITOT HT L R WSHLD OVHT L R WSHLD HT FAIL L R WSHLD HT FAULT NAC SW ON low pr...

Page 244: ...cted OFF in this case Although AC electrical power is provided by the engine driven alternators to heat the wind shield heating elements the two channel WSHLD controller is powered by 28 VDC re ceived from the left and right essential buses respectively The left system control is pow ered through the L HEAT WSHLD circuit breaker and the right system is powered through the R HEAT WSHLD circuit brea...

Page 245: ...to push the valves open against spring pressure The servo air to the A I PRSOVs is electrically contolled by the two channel ECS Temperature Controller through a torque motor and shut off solenoid on each side Electrical power to the shut off solenoids is provided when the Wing Stab S I is ON but the circuits also go through the BLEED S Is The shut off solenoids on each A I PRSOV are only ener giz...

Page 246: ...BLEED AIR SENSOR HEAT DETECTION LOOP CHECK VALVES HEAT SENSORS UNDER OVER TEMP SENSOR TEMP SENSOR WING STAB LEAK CAS WING STAB LEAK CWP WING STAB ON L WING STAB HT R WING STAB HT R MAIN BUS L MAIN BUS INTEGRATED ECS TEMP CONTROLLER CAS SEE TABLE 10 1 LEAK DETECTION UNIT 255 F 140 7 F 140 7 F IDLE 70 F IDLE 40 F 225 F 160 F HEAT SENSORS UNDER OVER IDLE 85 F IDLE 49 F 233 F 175 F HEAT SENSORS UNDER ...

Page 247: ...ilizer to the leading edge of the horizontal stabilizer Figure 10 6 A bleed air leak or overtemperature approximately 255 F anywhere along the heat detection el ement causes the red WING STAB LEAK message to be displayed on the CAS and the WING STAB LEAK annunciator on the CWP to illuminate These warnings remain on until the temperature decreases The flight manual 10 11 FOR TRAINING PURPOSES ONLY ...

Page 248: ...onditions The anti ice leak detection elements are tested with the FIRE DET position on the system test knob 10 12 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international Figure 10 8 Pitot Static Probes AOA Transducer Vanes and Total Air Temperature Probe LEFT SIDE RIGHT SIDE ...

Page 249: ...ilure all of the probes elements remain operative But with dual generator failure the main buses are au tomatically shed and only the standby pitot static heat remains powered However if necessary one or both main buses can be re selected on the electrical control panel Turning the L PROBES and R PROBES switches on causes elements in the compo nents listed in Table 10 2 to be energized for anti ic...

Page 250: ...ed electri cally A Nacelle inlet lip heat B Windshield heat C Wing Stab leading edge heat D All of the above 6 A valid Before Starting Engines ground test of the airplane anti ice system is con firmed by A Rain removal system turns on B All anti ice CAS messages are dis played during the test C A WING STAB HT OK message is displayed and red CWP WING OVHT and STAB OVHT annunciators illu minate D An...

Page 251: ...surfaces C Engine nacelle lip D Windshield 11 With EMER PRESS activated what anti icing equipment is available A Nacelle B Wing Stab if one or both BLEED switches are ON C Windshield D All of the above 12 Anti Ice should be turned on A SAT 10 C to 40 C and visible moisture B SAT 10 C or below if runway has slush on it C SAT 10 C or below if runway has standing water D All of the above 10 15 FOR TR...

Page 252: ...rtemp Sensor 11 4 ECU Low Limit Temp Control 11 4 Water Separator 11 4 DUAL ZONE TEMPERATURE CONTROL SYSTEM 11 4 General 11 4 Component Description 11 5 Controls and Operation 11 8 Indications 11 10 DISTRIBUTION SYSTEM 11 11 Cockpit Distribution System 11 11 Cabin Distribution System 11 11 Emergency Pressurization System 11 12 BAGGAGE COMPARTMENT HEATING SYSTEM 11 12 ELECTRIC FOOTWARMER HEAT SYSTE...

Page 253: ...dications 11 9 11 7 Cockpit Cabin Air Distribution System 11 10 11 8 Cockpit Overhead WEMACs 11 11 11 9 Cabin Air Distribution Diffusers 11 11 11 10 Cabin Air Distribution WEMACS 11 11 11 11 Baggage Heater Switch 11 12 11 12 Electric Footwarmer Heat System Component Locator 11 13 11 13 Bleed Air Distribution Overview 11 17 TABLES Table Title Page 11 1 Air Conditioning System CAS Message Database 1...

Page 254: ...and cabin distribu tion systems Temperature control is accomplished by mixing pressurized hot com pressed air and cooled compressed air as pro vided through the onboard environmental control unit ECU Cooling is accomplished by two methods heat transfer within the pre cooler and primary secondary heat exchanger and compression with rapid expansion through the air cycle machine ACM The pressurizatio...

Page 255: ...ows bleed airflow to the ECU and air dis tribution systems to increase This feature as per AFM shall be OFF for takeoff and land ing when using anti ice and above 30 000 The pack bi level valve is powered by the left essential bus and is protected by the PACK cir cuit breaker located on the pilot circuit breaker panel The valve is depowered open and re quires DC electrical power to close During an...

Page 256: ...ing The air exits the secondary heat exchanger outlet and is ducted into the ACM turbine for expansion Bleed air exiting the secondary heat exchanger is ducted to the ACM turbine and the bypass shutoff valve Item 2 in Figure 11 5 ACM tur bine airflow is cooled to near freezing tem peratures through rapid expansion At 40 000 feet the CPCS delivers a signal to open the by pass shutoff valve and allo...

Page 257: ... extracted in the separator is collected in a sump and drawn by bleed air suction from the secondary heat exchanger to the water spray aspirator Figure 11 5 DUAL ZONE TEMPERATURE CONTROL SYSTEM GENERAL The dual zone temperature control system is designed for independent automatic or man ual control of the cockpit and cabin temper atures Control panel temperature selection knobs Figure 11 3 allow e...

Page 258: ...o ON If power fails to the right main bus and the right essential bus temperature control via the Integrated Controller and the temperature con trol valves will be lost The temperature con trol valves fail to the full closed cold posi tion The Integrated Controller uses input signals from the cockpit and cabin temperature sen sor cockpit and cabin duct temperature sen sors and cockpit and cabin te...

Page 259: ...11 6 FOR TRAINING PURPOSES ONLY L E A R J E T 4 5 P I L O T T R A I N I N G M A N U A L FlightSafety international Figure 11 4 Bleed Air Distribution System ...

Page 260: ...11 7 FOR TRAINING PURPOSES ONLY L E A R J E T 4 5 P I L O T T R A I N I N G M A N U A L FlightSafety international Figure 11 5 Environmental Control Unit ECU ...

Page 261: ... the temperature control valves A loss of electrical power to a torque motor shuts off servo air to the valve and spring pres sure closes the valve full cold position CONTROLS AND OPERATION The cockpit and cabin temperature controls are located on the environmental control panel on the copilot s instrument panel Figure 11 6 In the automatic mode the MANUAL TEMP switch indicator S I will be blank T...

Page 262: ...matic mode the corresponding cockpit or cabin over temp limiter should cause the corresponding CKPT or CAB TEMP CONT VALVE to close when the duct temperature reaches 210 F If either duct temp limiter fails to stop the temperature rise in the duct the corresponding CKPT or CAB DUCT OVHT CAS will illuminate when the duct temperature reaches 300 F At this point it will be necessary for the crew to ta...

Page 263: ...e bottom tick mark up to 300 F the top tick mark Each index mark on the scale represents 90 degrees As depicted in Figure 11 6 the analog supply temperature scale is white with white point ers If the duct temperature exceeds 300 F the pointers turn amber Should an invalid tem perature be reported to the Integrated ECS Temp Controller each pointer is replaced with a red X Should an invalid cabin te...

Page 264: ...ilcone area to deliver conditioned bleed air to both sides of the cabin Figure 11 7 Inside the cabin these ducts branch again to route air down to the cabin floor diffusers and up to cabin overhead dif fusers on each side Figure 11 9 Duct split ter mechanisms are located at the duct branch points on both sides of the cabin The splitters are thermal mechanical devices that automat ically divert mor...

Page 265: ...h ON before flight operation of the system is fully automatic and requires no crew regulation or monitoring The system consists of six electrically pow ered blanket heaters an ON OFF switch and control circuitry The blanket heaters are in stalled on all four sides including the door the roof and the floor of the baggage com partment The heaters are self regulating As the temperature of the heaters...

Page 266: ...nsists of three heater blankets a heelplate and as sociated wiring The thermostat is mounted in a bracket located behind the copilot s aft kick panel The circuit breaker is located on the copilot s circuit breaker panel Power is applied through the FOOT WARM circuit breaker to the thermostat If the ther mostat senses temperatures above 60 F 15 6 C the thermostat opens removing electrical power fro...

Page 267: ...that exceeds 450 F in the ECU 5 Which airplane environmental control system requires no pilot monitoring or regulation A Air conditioning system when AUTO is selected B Instrument panel cooling system C Baggage compartment heating sys tem D Air conditioning system when MAN UAL TEMP is selected 6 In the event of inflight dual generator failure the cockpit cabin temperature control system A Must be ...

Page 268: ...chematic page 10 In the event that emergency pressuriza tion activates due to a leak in the cabin A Neither auto or manual temperature control is available B MANUAL TEMP must be selected for cockpit and cabin temperature control C Automatic temperature control will still be operational D Cockpit and cabin temperature control will automatically revert to manual control 11 15 FOR TRAINING PURPOSES O...

Page 269: ... TEMPERATURE SELECTOR 4 9 COCKPIT TEMPERATURE SENSOR EMERGENCY PRESSURIZATION 5 1 EMERGENCY PRESSURIZATION 90V 1 0 DIA POPPET 5 2 EMER PRESS ISOLATION CHECK VALVE 4 DIA INSERT WING TAIL ANTI ICE CONTROL 6 1 PRSOV MODULATING VALVE 2 DIA BTFY 6 2 WING SKIN TEMP SENSOR 6 3 TAIL SKIN TEMP SENSOR 6 4 A I CHECK VALVE 2 DIA INSERT NACELLE A I CONTROL 7 1 A I SOV AUXILIARY POWER UNIT OPTIONAL EQUIPMENT 8 ...

Page 270: ...Selector Knob 12 3 Manual Rate Selector Knob 12 4 CABIN PRESSURE CONTROLLER 12 4 Pressurization Controller Power Source 12 6 Outflow Valves 12 6 Vacuum Jet Pump 12 7 INDICATIONS 12 8 Primary and Secondary Displays 12 8 CAS Messages 12 8 Protection and Warning Features 12 10 SYSTEM OPERATION 12 10 System Test 12 10 Automatic Mode 12 14 Manual Mode 12 16 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT T...

Page 271: ...High Altitude Airport Operation 12 18 REVIEW QUESTIONS 12 21 LEARJET 45 PILOT TRAINING MANUAL 12 ii FOR TRAINING PURPOSES ONLY FlightSafety international ...

Page 272: ...ontroller Flight Abort Mode 12 16 12 9 Controller Descent Mode 12 17 12 10 Controller Takeoff and Landing Above 8 000 feet 12 19 12 11 Controller Takeoff 8 000 feet and Landing 8 000 feet 12 20 12 12 Controller Takeoff 8 000 feet and Landing 8 000 feet 12 20 TABLES Table Title Page 12 1 CPCS CAS Message Logic 12 10 12 2 Protection and Warning Features Normal 12 11 12 3 Protection and Warning Featu...

Page 273: ...the outflow is controlled by two outflow valves lo cated on the forward pressure bulkhead Regulating the outflow of air through the out flow valves is provided by the dual channel cabin pressure control system CPCS lo cated in the cockpit The CPCS regulates the cabin pressurization system automatically based upon a pressurization schedule The crew can also regulate cabin pressure by man ually sele...

Page 274: ...control panel is used to control the pack bilevel pres sure regulating shutoff valve PRSOV When selected on engine bleed air is allowed to enter the environmental control unit ECU Should the pack bilevel PRSOV not open due to a malfunction the only other method to provide a source of engine bleed air for cabin pressurization is via the emergency pressur ization system 12 2 FOR TRAINING PURPOSES ON...

Page 275: ...e limiters on each outflow valve cause the valves to move towards a closed position keeping the cabin from climbing higher Depressing the EMER DEPRESS switch a second time re turns the system to the previous mode auto matic or manual and the ON caption within the switch is extinguished When activated a white advisory CAS message EMER DE PRESS is annunciated LANDING ALTITUDE SELECTOR KNOB The landi...

Page 276: ... microprocessor based electronic unit mounted on the co pilot s lower switch panel Figure 12 2 The CPCS has a redundant cabin pressure control scheme utilizing the two channel controller with independent power sources and sensors for each channel The primary channel left controls only the primary outflow valve and the secondary chan nel right controls only the secondary outflow valve However both ...

Page 277: ... value The air plane has to deviate by 200 feet from the es tablished altitude before the system allows changes in cabin pressure When the airplane descends 1 000 feet the CPC initiates the de scent schedule The rate of climb and descent is non se lectable in the automatic mode The controller 12 5 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international EMER PRESSURE ...

Page 278: ...deployment of the passenger oxy gen system 14 500 feet These output signals are independently generated by the left and right channels of the CPC PRESSURIZATION CONTROLLER POWER SOURCE The two channels of the CPC have indepen dent electrical power sources The left chan nel receives 28 VDC from the Left Main Bus through the L PRESS circuit breaker in the Environmental group on the pilot s circuit b...

Page 279: ...h the CPC would attempt to control the cabin to that altitude during descent but when the air plane descended below that altitude the out flow valves would be forced open by the atmospheric pressure being higher than the cabin pressure The valves open when the at mospheric pressure is 0 5 psid greater than cabin pressure Cabin to atmospheric differential pressure Delta P relief valves are located ...

Page 280: ...arately but is the same format when in the manual mode The delta P display is boxed and changes color from white to amber when the differential pressure is less than 0 5 or greater than 9 5 psid in the automatic mode The delta P dis play changes to red if the value is greater than 9 9 psid The cabin altitude display on the ECS system schematic changes color from white to amber and to red based upo...

Page 281: ...AB CKPT H C OXY QTY 669 LTR OXY QTY 555 LTR OXY QTY LTR CABIN RATE 1000 DELTA P 9 4 CABIN ALT 8750 MANUAL RATE 2200 LDG ALT 10000 CAB TEMP 78 F TEMP CONT CAB CKPT H C CABIN RATE 1000 DELTA P 9 5 CABIN ALT 10000 MANUAL RATE 2200 LDG ALT 10000 CAB TEMP F TEMP CONT CAB CKPT H C CABIN RATE DELTA P CABIN ALT MANUAL RATE LDG ALT EXCEEDANCES DISPLAY TEST OR INVALID DISPLAY NORMAL DISPLAY Figure 12 5 Envi...

Page 282: ...ystem test are annunciated on the CAS as per Table 12 1 and on the CPC LCD Inflight a continuous self test is run on the CPCS con troller and its inputs If the test is successful auto mode will be active and no legend on the LCD CAS is illuminated 12 10 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international CAS Message Logic Summary Type Msg C C C C C A A A W Warnin...

Page 283: ...LTITUDE Initiate emergency descent Mute voice caution message with mute switch Amber CAS message CABIN ALTITUDE illuminates Cabin altitude digital readout on CPC flashes CAB ALT display on EICAS MFD turns from amber to red Master Caution lights flash single chime Emergency cabin pressurization activates Chapter 9 Amber CAS message LR EMER PRESS ON Cabin altitude digital readout on CPC flashes EMER...

Page 284: ...e emergency descent Mute voice caution message with mute switch Cabin altitude digital readout on CPC flashes EICAS MFD CAB ALT display turns from white to red Amber CAS message LR EMER PRESS ON EMER PRESS switch caption ON illuminates Amber CAS message CABIN ALTITUDE Cabin altitude limiters close outflow valves Prerequisites 1 Cabin controller must be in automatic mode 2 Destination LDG ALT set a...

Page 285: ... of the EICAS MFD changes color to amber and is boxed 9 7 PSID Max Delta P limiters open 9 9 PSID Manual Master Caution lights flash Amber CAS message CAB DELTA P Digital Delta P readout on CPC LCD display flashes Delta P readout on ECS page of the EICAS MFD changes color to red and is boxed 0 5 PSID Master Caution lights flash Amber CAS message CAB DELTA P Digital Delta P readout on the CPC LCD d...

Page 286: ...vers are retarded below MCR prior to lift off as in an aborted takeoff the cabin controller enters the takeoff abort mode Figure 12 6 In this mode cabin altitude is rated back to the takeoff field elevation at a rate of 500 fpm for 20 seconds after which the sys tem re enters the ground mode When the airplane becomes airborne the sys tem enters the climb pressurization mode Figure 12 7 For normal ...

Page 287: ...on if the airplane descends 1 000 feet within 10 minutes after takeoff and is 6 000 feet or less above the takeoff field elevation Figure 12 8 When a descent is initiated from cruise alti tude and the airplane has descended 1 000 feet or more below cruising altitude the con troller establishes the cabin altitude on the de scent schedule until landing Figure 12 9 As the aircraft altitude changes du...

Page 288: ...S MAN message will be displayed on the CAS There is no op tion for the crew to choose which channel is active auto or manual Loss of valid input from both ADCs is the only condition that will cause the CPC to au tomatically revert to the manual mode In this case the CPC annunciates a flashing ADC on the LCD an amber CAB PRESS MAN message will be displayed on the CAS and ON will illuminate in the M...

Page 289: ...the last movement of the MANUAL rate knob the display reverts back to actual cabin rate It may be more convenient to use the ECS sys tem schematic display on the EICAS when using the manual controller since it displays actual CABIN RATE and desired MANUAL RATE at the same time During manual mode operation adjustment of the landing altitude knob has no effect on the pressurization system If manual ...

Page 290: ...n schedule of 8 000 feet Figure 12 10 Once the airplane has descended 1 000 feet and the airplane altitude is below 24 500 feet the cabin altitude begins to rise main taining an ascent rate of approximately 600 fpm until the landing field elevation has been reached Once the airplane has landed the squat switches signal the pressurization sys tem to enter the ground mode The second situation that t...

Page 291: ...12 19 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international Figure 12 10 Controller Takeoff and Landing Above 8 000 feet ...

Page 292: ...BIN ALTITUDE SELECTED LANDING ALTITUDE 8 000 FT ASCENT RATE 600 fpm AIRCRAFT ALTITUDE 24 500 FT 1 000 FT DESCENT Figure 12 12 Controller Takeoff 8 000 feet and Landing 8 000 feet AIRCRAFT ALTITUDE DESCENDS 1 000 FT AIRCRAFT CLIM B LIFT OFF THROTTLES ADVANCED ALTITUDE 10 000 FT TAKEOFF FIELD DESCENT RATE 600 fpm 8 000 FT MAXIMUM CABIN ALTITUDE DESCENT RATE 375 fpm 7 000 FT LANDING FIELD ELEVATION F...

Page 293: ...ltitude is climbing due to a significant leak which of following would occur A A white LR CABIN PRESS FAIL message will be displayed on the CAS at a cabin altitude of 8 000 feet B The Master Caution lights will flash and an amber flashing CABIN AL TITUDE message will be displayed on the CAS at an altitude of 8 750 feet C The cabin altitude digital readout on the CPC LCD flashes and the cabin al ti...

Page 294: ...0 feet C 10 000 200 feet D 14 500 250 feet 10 The cabin pressurization system auto matically switches to manual mode when ever A Dual ADC failure occurs B MANUAL PRESS switch has been depressed C Left or right BLEED failure D Cabin pressure controller channel fail ure primary or secondary 11 After experiencing a dual generator fail ure inflight the cabin pressurization sys tem A Reverts to manual ...

Page 295: ...s 13 3 Filter Manifolds 13 6 Accumulators 13 6 Landing Gear Control Valve Module 13 6 HYDRAULIC SYSTEM OPERATION 13 9 Main System 13 9 Auxiliary System 13 9 HYDRAULIC SYSTEM INDICATIONS 13 9 Normal Operation 13 9 Abnormal Operations 13 11 SERVICING 13 11 REVIEW QUESTIONS 13 13 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 296: ...nd MFD 13 7 13 5 Hydraulic System CAS Messages on EICAS 13 8 13 6 Hydraulic System Schematic Displays 13 10 13 7 Hydraulic System Indications on RMU 13 11 13 8 Hydraulic System Ground Service Panel GSP 13 11 TABLES Table Title Page 13 1 Hydraulic System CAS Message Database 13 8 13 2 Hydraulic System Pressure Indications 13 9 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety...

Page 297: ...ine driven pumps supply hydraulic fluid MIL H 5606 pressurized to approxi mately 3 000 psi for operation of the landing gear flaps spoilers spoilerons brakes and thrust reversers A DC motor driven auxiliary hydraulic pump can power all hydraulic subsystems during maintenance by opening the ground servicing valve The auxiliary pump can also provide hydraulic power for brakes prior to engine start S...

Page 298: ...EVEL SENSOR AUX FLUID LOW CAS PASS THROUGH ADD FLUID ADD CAS GSP RESERVOIR FULL FULL GSP INDICATOR OVERFULL OVER GSP INDICATOR 7 6 3 1 2 4 5 EMERGENCY PARKING BRAKE FLAP DRIVE LDG GEAR CONTROL VALVE DOOR CONTROL VALVE LDG GEAR FREE FALL LEVER LANDING GEAR CONTROL VALVE MODULE PRESSURE TRANSDUCER ELECTRICAL MECHANICAL MAIN PRESSURE AUX PRESSURE MAIN RETURN AUX RETURN SUPPLY BLEED AIR ACCUM PRECHARG...

Page 299: ...er caution lights and chime will be displayed 1 2 qt When the sensor detects auxiliary fluid low LOW is also annunciated on the EICAS MFD hydraulic system schematic Figure 13 6 and the hydraulic crossflow valve will close if open isolating the auxil iary system for brake operation only The overfull full and add positions on the fluid level sensor provide signals to indicators on the ground service...

Page 300: ...tailcone forward of the tailcone baggage com partment on the left side It receives 28 VDC power from the left essential bus and is pro tected by two circuit breakers labeled AUX HYD PUMP PWR power and CTRL con trol These circuit breakers are located on the pilot circuit breaker panel in the GEAR HY DRAULICS group Auxiliary pump operation can be manually initiated by depressing the AUX HYD mo menta...

Page 301: ...UID LOW CAS ADD FLUID ADD CAS GSP RESERVOIR FULL FULL GSP INDICATOR OVERFULL OVER GSP INDICATOR 7 6 3 1 2 4 EMERGENCY PARKING BRAKE FLAP DRIVE LDG GEAR CONTROL VALVE DOOR CONTROL VALVE LDG GEAR FREE FALL LEVER PRESSURE TRANSDUCER ELECTRICAL MECHANICAL MAIN PRESSURE AUX PRESSURE MAIN RETURN AUX RETURN SUPPLY BLEED AIR ACCUM PRECHARGE LEGEND SOL EICAS MFD SUMRY HYD INDICATIONS 6 7 4 MAIN HYD PRESS B...

Page 302: ...so contains a pres sure switch that generates an amber AUX HYD PUMP LO caution message if the pump is operating and the pump output pressure to the manifold is less than 1 900 psi ACCUMULATORS Two hydraulic accumulators are installed in the airplane They each contain a permanent precharge that is not serviceable One of the accumulators is a main hydraulic system accumulator Figure 13 1 that is in ...

Page 303: ...TEM EICAS CAS FUEL FLT ECS HYD ELEC SUMRY ELECT VOLTS EMER V AMPS TEMP C 28 5 28 0 28 0 50 65 30 50 HYD ECS MAIN B ACUM CAB ALT OXY QTY 3000 3000 1300 669 FLT SPLR PIT AIL RUD 0 0 R 3 L 2 SUMRY ELEC HYD RTN ECS FLT FUEL M P RNG BRAKE ACCUM 3000 PSI A PUMP AUX RESERVOIR R 3000 L MAIN PSI ENGINE PUMPS Figure 13 4 Hydraulic System Indications on EICAS and MFD ...

Page 304: ...n of auxiliary fluid for the airplane brake system A CAS caution mes sage AUX HYD QTY LO alerts the crew to this condition The hydraulic crossflow valve is 28 VDC pow ered from the left essential bus It is protected LEARJET 45 PILOT TRAINING MANUAL 13 8 FOR TRAINING PURPOSES ONLY FlightSafety international CAS Message Logic Summary Type Msg C C A A C Caution A Advisory BRK ACUM PRESS EMER brk acum...

Page 305: ...re displayed as digital readouts on the SUMRY page of the EICAS MFD and also on the HYD system schematic page MAIN and B ACUM pres sures are displayed in white digits when they are within the normal range Normal pressure with an engine driven pump operating is 2 210 to 3 600 psi If the main hydraulic pressure de creases to below 1 500 psi or increases to above 3 600 psi the digits turn amber and a...

Page 306: ...00 L MAIN PSI ENGINE PUMPS BRAKE ACCUM 850 PSI A PUMP AUX RESERVOIR R 1400 L MAIN PSI ENGINE PUMPS BRAKE ACCUM PSI A PUMP AUX RESERVOIR R L MAIN PSI ENGINE PUMPS NORMAL HYDRAULIC SYSTEM SCHEMATIC PAGE EXCEEDANCES HYDRAULIC SYSTEM SCHEMATIC PAGE TEST INVALID HYDRAULIC SYSTEM SCHEMATIC PAGE LOW Figure 13 6 Hydraulic System Schematic Displays ...

Page 307: ...ontains a two posi tion ground service valve switch that is po sitioned to either GND ground or FLT flight When in GND the valve opens and allows the auxiliary hydraulic pump or the engine driven pumps to power all aircraft sys tems Figure 13 1 Closing the GSP access door automatically repositions the ground ser vice valve to the FLT position The auxiliary hydraulic pump DC motor con tains brushes...

Page 308: ...ing gear B Thrust reversers and flaps C Landing gear gear doors and flaps D Landing gear flaps and thrust re versers 5 The main system digital indication on the EICAS SUMRY page display will be amber if the pressure falls below psi A 1500 B 2200 C 2600 D 3000 6 When does the auxiliary hydraulic pump automatically come on A When the airplane electrical system is powered up B Anytime the airplane is...

Page 309: ...ncy brake accumulator will have to be used for braking D All of the above 10 If the auxiliary hydraulic reservoir be comes excessively low A An AUX HYD QTY LO CAS mes sage is displayed B A LOW annunciation is displayed on the HYD system schematic on the EICAS MFD displays C The HYD XFLOW valve will auto matically close if open D All of the above LEARJET 45 PILOT TRAINING MANUAL 13 13 FOR TRAINING ...

Page 310: ... Gear Operation 14 10 BRAKES 14 17 General 14 17 Brake Operation 14 17 Emergency Brakes 14 22 Parking Brake 14 22 NOSE WHEEL STEERING SYSTEM 14 23 General 14 23 Normal Operation 14 25 Degraded Mode of Operation 14 25 REVIEW QUESTIONS 14 26 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 311: ...ic 14 13 14 13 Landing Gear Emergency Extension Lever 14 14 14 14 Landing Gear Free Fall Extension Schematic 14 15 14 15 Landing Gear Auxiliary Hydraulic Extension Schematic 14 16 14 16 Brake System Schematic 14 18 14 17 Brake Assembly 14 19 14 18 Emergency Parking Brake 14 19 14 19 Anti Skid Switch 14 19 14 20 Brake Accumulator Hydraulic Pressure Display on EICAS 14 20 14 21 Brake Accumulator Hyd...

Page 312: ... TABLES Table Title Page 14 1 Landing Gear and Brakes CAS Message Database 14 4 14 2 Landing Gear WARNING CAUTION Conditions 14 6 LEARJET 45 PILOT TRAINING MANUAL 14 iv FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international FlightSafety international ...

Page 313: ...ncy and parking braking capability is provided by an auxiliary hy draulic pump and a hydraulically charged brake accumulator The Learjet 45 tricycle landing gear is equipped with three air hydraulic type shock struts The nose gear doors and the outboard main gear doors are mechanically linked to the gear and move with them The inboard main gear doors are hydraulically operated and se quenced close...

Page 314: ...unction provides maximum braking without wheel skid With the anti skid function selected wheel speed trans ducers supply electrical signals to the BCUs which control the individual control valves that modulate braking pressure A brake ac cumulator and auxiliary hydraulic pump are installed for parking brake and emergency brake pressure The parking brake is set with a handle located on the center p...

Page 315: ...indicators are illumi nated anytime the inboard gear door on the cor responding main gear is not up and latched or whenever the gear position does not agree with the landing gear switch When the nose and main gear are fully re tracted and both inboard and outboard gear doors for each side are closed all gear posi tion lights are extinguished When the gear is extended and the inboard gear doors are...

Page 316: ...en selected to ON is valid confirmation that the corre sponding main gear is down and locked To avoid erroneous confirmation by a ground ob server insure that the recognition landing light 14 4 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international LEARJET 45 PILOT TRAINING MANUAL FlightSafety international CAS Message Logic Summary Type Msg W W C C C W GEAR Any gea...

Page 317: ...n invalid radio altimeter or if gear limit speeds are exceeded while the gear is in transition or either main gear door is not up and locked The conditions that activate gear caution and the indications are listed in Table 14 2 For gear cautions the master CAUT lights may be extinguished by depressing either mas ter caution light however the amber GEAR CAS message remains in view as long as the co...

Page 318: ... levers are MCR KIAS 170 kts altitude 14 500 the RA is invalid and any gear is NOT down and locked or either main gear door is not up and locked KIAS 210 kts and one or more gear are in transition or either inboard main gear doors is not up and locked Landing Gear Caution consists of the following Illumination of the master CAUT lights and aural master caution tone sounds may be cancelled by depre...

Page 319: ...nsion depends on the air charge in the strut proper strut inflation is an important consideration The shock struts are serviced to a specified pressure with the airplane on jacks When the airplane weight is on the struts the amount of strut extension varies with the airplane load The main gear are normally held in the ex tended position using positive hydraulic pres sure When retracted the main ge...

Page 320: ...Squat switch relay panel SSRP Squat Switch Relay Panel SSRP The squat switch relay panel SSRP is lo cated on the aft pressure bulkhead The SSRP provides air ground signals for numerous equipment items The following is a partial list ing of those items Digital electronic engine computers idle schedule Stall warning system Crew warning panel master CAUT take off landing inhibit Nose wheel steering e...

Page 321: ... the gear strut The uplock hook holds the nose gear up when hydraulic pressure is relieved after gear re traction The nose gear uplock can be released by two methods The nose gear uplock is hydraulically operated for normal extension and is me chanically operated via cabling for free fall ex tension The nose strut incorporates a mechanism to center the nose wheel for retraction At liftoff two cams...

Page 322: ... the UP position energizes the door control valve to the open position This directs hy draulic pressure to release the inboard main gear door latches and opens the inboard doors The three gear advisory lights illuminate as soon as the landing gear control switch is moved to UP When the inboard doors are fully open the gear control valve is energized to the retract posi tion This directs hydraulic ...

Page 323: ...LDG GEAR CONTROL VALVE DOOR CONTROL VALVE FLAP DRIVE FREE FALL VALVE EXTEND RETRACT EXTEND RETRACT HYD XFLOW VALVE SOL SOL LANDING GEAR CONTROL VALVE MODULE MAIN HYD PRESS MAIN RETURN HYD AUX HYD PRESS AUX RETURN HYD ELECTRICAL MECHANICAL LEGEND DOWN DOWN N L R GEAR HYD NOSE STEER ANTI SKID AUX HYD HYD XFLOW VLO 200 VLE 260 UP DN LANDING GEAR FREE FALL LEVER CENTER PEDESTAL Figure 14 11 Landing Ge...

Page 324: ...extend all three landing gear When the gear are down mechanical down locks inside each gear actuator cause the re spective green DOWN lights to illuminate and the nose gear advisory light to extinguish A signal through the main gear downlock switches then energizes the door control valve to the closed position Hydraulic pressure then closes the inboard main gear doors As the in board doors close a...

Page 325: ...AR CONTROL VALVE DOOR CONTROL VALVE FLAP DRIVE FREE FALL VALVE EXTEND RETRACT EXTEND RETRACT HYD XFLOW VALVE LANDING GEAR CONTROL VALVE MODULE MAIN HYD PRESS MAIN RETURN HYD AUX HYD PRESS AUX RETURN HYD ELECTRICAL MECHANICAL LEGEND DN LANDING GEAR FREE FALL LEVER CENTER PEDESTAL DOWN DOWN DOWN N L R ON ON GEAR HYD NOSE STEER ANTI SKID AUX HYD HYD XFLOW VLO 200 VLE 260 UP DN SOL SOL Figure 14 12 La...

Page 326: ...more than 1 minute after the lever is placed down Auxiliary Hydraulic Extension If the main hydraulic system fails inflight procedures call for use of the gear free fall sys tem to lower the gear However should the free fall system fail to fully extend the gear the gear can also be lowered using the auxil iary hydraulic system and the HYD XFLO switch Figure 14 15 If the AUX HYD pump and HYD XFLO a...

Page 327: ...CONTROL VALVE DOOR CONTROL VALVE FLAP DRIVE FREE FALL VALVE EXTEND RETRACT EXTEND RETRACT HYD XFLOW VALVE LANDING GEAR CONTROL VALVE MODULE MAIN HYD PRESS MAIN RETURN HYD AUX HYD PRESS AUX RETURN HYD ELECTRICAL MECHANICAL LEGEND LANDING GEAR FREE FALL LEVER CENTER PEDESTAL DOWN DOWN DOWN N L R ON GEAR HYD NOSE STEER ANTI SKID AUX HYD HYD XFLOW VLO 200 VLE 260 UP DN SOL SOL Figure 14 14 Landing Gea...

Page 328: ...ALVE DOOR CONTROL VALVE FLAP DRIVE FREE FALL VALVE EXTEND RETRACT EXTEND RETRACT HYD XFLOW VALVE LANDING GEAR CONTROL VALVE MODULE MAIN HYD PRESS MAIN RETURN HYD AUX HYD PRESS AUX RETURN HYD ELECTRICAL MECHANICAL LEGEND DN LANDING GEAR FREE FALL LEVER CENTER PEDESTAL DOWN DOWN DOWN N L R ON ON GEAR HYD NOSE STEER ANTI SKID AUX HYD HYD XFLOW VLO 200 VLE 260 UP DN SOL SOL ON Figure 14 15 Landing Gea...

Page 329: ...transitioned to the air mode and the gear control switch is moved to UP a 200 psi braking command is applied for a few seconds to stop wheel rotation Should the main hydraulic system fail the auxiliary hydraulic system provides pressure for normal braking capability with anti skid protection In the event of multiple failures total hydraulic and or electrical emergency braking pressure is available...

Page 330: ...E SHUTOFF VALVES INBOARD BRAKE CONTROL VALVES OUTBOARD BRAKE CONTROL VALVES 2 3 1 4 BRAKE ACCUMULATOR EMERGENCY PARKING BRAKE VALVE WHEEL SPEED TRANSDUCERS 4 BRAKE FUSES 5 PRESSURE TRANSDUCERS 4 ANTI SKID OFF RETURN MAIN HYD SYSTEM PRESS METERED BRAKE PRESS RETURN ELECTRICAL AUX HYD SYSTEM PRESS MECHANICAL CHECK VALVE BRAKE FUSE BRAKE ACCUM TRANSDUCER LEGEND EMER BUS OUTBD BRAKES RT ESS BUS NORM B...

Page 331: ...e ANTI SKID switch located on the GEAR HYD con trol panel Figure 14 19 When the anti skid system is on the S I will be blank when the system has been turned off an OFF legend is displayed on the S I and an amber ANTI SKID FAIL CAS message is posted Anti skid malfunctions may also result in the anti skid CAS message being displayed which may indicate a failure of one or more of the anti skid circui...

Page 332: ...matically changes the source of hydraulic fluid flow from the main system to the auxiliary hydraulic system if the auxiliary hydraulic system is turned on With the auxiliary hy draulic pump operating normal braking with anti skid protection is available If the hy draulic crossflow valve is open and the fluid level in the auxiliary hydraulic fluid reser voir is low the hydraulic crossflow valve is ...

Page 333: ...mance will be affected PLT BRK FAULT One or more of the pilot s brake pedal transducers or the associated circuit has failed Use the copilot pedals CPLT BRK FAULT One or more of the copilot s brake pedal transducers or the associated circuit has failed Use the pilot pedals In the unlikely event that multiple hy draulic electrical failures render the normal brake system inoperative the crew will be...

Page 334: ...ING BRAKE The brake accumulator also provides pressure for the parking brake The parking brake is set by pulling the emergency parking brake han dle located on the center pedestal Figure 14 18 aft and rotating it left or right to the locked position This action holds the emergency parking control valve open and hydraulic pressure is maintained to the brakes for air plane parking When the parking b...

Page 335: ...conditions occur Both system DC power sources are avail able to the computer The nose gear is down and locked No system faults or failures are detected Once Armed engagement is possible when WOW signals indicate the aircraft is on the ground and information from the wheel speed transducers is available Engaged is de scribed as the operating mode of the NWS system in which the system has been Armed...

Page 336: ...WHEEL AND TIRE ASSEMBLY NOSE GEAR SHOCK STRUT NOSE WHEEL STEERING WEIGHT ON WHEEL SWITCH NOSE WHEEL STEERING ACTUATOR NOSE WHEEL STEERING GEAR BOX Figure 14 24 Nose Steering Components IDENT SWITCH NOT SHOWN ARMING BUTTON AP PITCH ROLL COMMAND SWITCH CONTROL WHEEL TRIM SWITCH CWTS MIC SWITCH NOT SHOWN CONTROL WHEEL MASTER SWITCH MSW CHECKLIST LINE ADVANCE TOUCH CONTROL STEERING TCS ...

Page 337: ... servo actuator When the landing gear is retracted the NOSE STEER ON leg end will extinguish When the nose gear is down and locked for landing the ON leg end will illuminate in the NOSE STEER switch indicator if power to the nose steer computer has not been interrupted in the in terim The system is armed when the ON leg end is illuminated and when the aircraft is on the ground the nose wheel steer...

Page 338: ... gear green DOWN light will not il luminate or test confirmation of a down and locked position can be confirmed by A Turning the landing lights on B Observing an ON caption on the NOSE STEER switch indicator C Turning the taxi lights on D Turning the recognition lights on 5 After a normal gear extension and a main gear green DOWN light will not illumi nate or test confirmation of a down and locked...

Page 339: ...ntrol switch is moved to the UP position C The HYD XFLOW switch is selected ON D Both a and b are true 10 Whenever an AUX HYD QTY LO cau tion message is displayed on the CAS A Remaining auxiliary hydraulic fluid in the reservoir is reserved for the brake system B Extending the landing gear via the auxiliary hydraulic extension method is inhibited C Normal landing gear extension is not affected if ...

Page 340: ... Have both crew members apply brake pedal pressure at the same time C Turn the HYD XFLOW switch to ON activate the auxiliary hydraulic pump and apply brakes as normal D Use the emergency parking brake lever to apply emergency brake pres sure 15 The emergency brake accumulator is sized to provide at least brake applica tions A Three B Four C Five D Six 16 The nosewheel steering system can be activa...

Page 341: ...NTROLS 15 2 Elevators 15 2 Ailerons 15 6 Rudder 15 8 SECONDARY FLIGHT CONTROLS 15 12 Horizontal Stabilizer 15 12 Trim Systems 15 12 Flaps 15 21 Spoilers 15 24 STALL WARNING SYSTEM 15 31 REVIEW QUESTIONS 15 32 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 342: ...on Pilot s Control Wheel 15 8 15 10 Rudder Control System 15 9 15 11 Rudder Trim Tab 15 10 15 12 Rudder Controls 15 11 15 13 Pitch Trim System 15 13 15 14 Trim Control Panel 15 14 15 15 Trim Flap Spoiler Indications 15 18 15 16 Flight FLT System Schematic 15 19 15 17 Flap System 15 22 15 18 Flap Selector 15 23 15 19 System Test Knob 15 24 15 20 PFD Airspeed Indications 15 25 15 21 Spoiler Spoilero...

Page 343: ...TABLES Table Title Page 15 1 Flight Control System CAS Message Database 15 15 LEARJET 45 PILOT TRAINING MANUAL 15 iv FOR TRAINING PURPOSES ONLY FlightSafety international ...

Page 344: ...l axis The primary flight controls are me chanically operated through dual control columns control wheels and rudder pedals The ailerons incorporate mechanical balance tabs to provide aerodynamic assistance Trim systems pitch roll and yaw are electrically operated and controlled The left aileron and the rudder feature trim tabs The movable hor izontal stabilizer provides trim in the pitch 33 3 0 W...

Page 345: ...ction in stick force at high Mach numbers A controls lock is provided to prevent wind gust damage to the primary flight control sur faces When installed as depicted in Figure 15 1 the lock holds the rudder centered full up left aileron and full down elevator displace ment PRIMARY FLIGHT CONTROLS ELEVATORS General The elevators Figure 15 2 are hinged to the aft edge of the horizontal stabilizer and...

Page 346: ...NNECT SENSOR SWITCH ELEVATOR AFT DISCONNECT ACTUATOR ASSEMBLY ELEVATOR DISCONNECT LINEAR ACTUATOR ELEVATOR FORWARD DISCONNECT ASSEMBLY INDEPENDENT PILOT AND COPILOT CABLE CIRCUITS CABLE CIRCUITS SPLIT THROUGH ROTOR BURST ZONE AUTOPILOT PITCH SERVO UP DOWN SPRING ELEVATORS Figure 15 2 Elevator Control System ...

Page 347: ...button will also disengage the clutch while held but does not disengage the autopilot Figure 15 3 The pitch servo receives electrical power through the AFCS SERVOS circuit breaker located in the FLIGHT group on the pilot s cir cuit breaker panel Elevator Up Down Spring The elevator up down spring assembly is in terconnected between the elevator upper and lower pushrods in the vertical stabilizer F...

Page 348: ...n the copi lot s circuit breaker panel Elevator Disconnect In the event of a jam in either elevator me chanical control circuit the two circuits can be disconnected by pulling the ELEV dis connect T handle located at the forward left edge of the center pedestal Figure 15 5 The airplane can then be controlled with the un jammed elevator When the ELEV T handle is pulled the forward and aft disconnec...

Page 349: ...connected through pulleys and cables to the control wheels Figure 15 6 The ailerons can be mechanically posi tioned with either control wheel or by the autopilot roll servo actuator Aileron Balance Tabs Each aileron contains a balance tab controlled by dual push pull tubes attached to the fixed wing surface Figures 15 6 and 15 7 The function of the balance tab is to reduce pilot effort at the cont...

Page 350: ...t essen tial bus through the TRIM AIL circuit breaker located in the FLIGHT group on the pilot s cir cuit breaker panel Uncommanded aileron trim can be stopped by depressing and holding either Control Wheel Master Switch MSW Additionally the AFM procedure for Roll or Yaw Axis Uncommand Motion calls for pulling the 15 7 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety intern...

Page 351: ...wheel Figure 15 9 to the full aft position mechan ically disengages a clutch within the control wheel hub and trips two roll disconnect switches that signal the spoileron system The copilot s control wheel will remain connected to the aileron control system A ROLL DISC message will be posted on the CAS when roll disconnect is actuated The ROLL DISC CAS message is amber on the ground and white when...

Page 352: ...e rudder Figures 15 10 and 15 11 The rudder can also be positioned by a yaw servo which is used by the yaw damper and rudder boost systems The yaw damper switch is located on the flight guidance control panel FGC On aircraft 45 005 thru 45 225 with SB 45 55 6 and aircraft 45 226 subsequent the rud 15 9 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international RUDDER PE...

Page 353: ...L FlightSafety international Figure 15 11 Rudder Trim Tab PILOT RUDDER ADJUST SWITCH COPILOT RUDDER ADJUST SWITCH YAW DAMPER SWITCH ON FGC see Chapter 16 RUDDER BOOST SWITCH RUDDER TRIM SWITCH Figure 15 12 Rudder Controls TRIM TAB RUDDER 8 STRIP ADDED 6 STRIP ADDED ...

Page 354: ...ormal approach and landing can be made with only light control forces to overcome full rudder trim Yaw Servo The yaw servo is used by the yaw damper and the rudder boost The yaw servo is a two direction torque motor it incorporates an electrical clutch that en gages only when the yaw damper is engaged or when the rudder boost is applying rudder pressure When the clutch is engaged the servo is conn...

Page 355: ...izer is attached to the vertical stabilizer at forward and aft at tachment points The aft attach point is the pivot which consists of a large hinge pin in serted through bearings located in the hori zontal and vertical stabilizer The forward attach point is connected to the horizontal sta bilizer actuator which is attached to the ver tical stabilizer forward spar The position of the horizontal sta...

Page 356: ...H TRIM INDICATIONS EICAS DU2 MFD DU3 RMU ENGINE BACKUP PAGES IC 600 BYPASS TRIM Learjet Learjet N1 ITT SAT C END CAS FUEL FLT ECS HYD ELEC SUMRY L F 1000 R 1750 FLAPS 20 6 5 PITCH TRIM LBS FUEL 4450 15 50 0 76 60 984 50 0 80 60 1002 N2 OIL PSI OIL C FF PPH 550 550 75 0 75 0 1700 ELECT VOLTS EMER V AMPS TEMP C 28 5 28 0 28 0 200 300 30 50 HYD ECS MAIN B ACUM CAB ALT OXY PSI 3000 2000 1 300 1800 FLT...

Page 357: ...rimary Pitch Trim General Normally the pitch trim selector switch on the center pedestal is positioned to PRI This po sition enables the Control Wheel Trim Switches CWTS and causes commands from either of these switches to be processed by the 1 IC 600 The 1 IC 600 sends trim com mands to the primary motor on the stabilizer actuator Figure 15 13 Following is a summary of the different pri mary trim...

Page 358: ...etected not accompanied by FAIL message Autospoilers armed Elevator disconnect has split the elevators inflight ELEVATOR DISC Elevator disconnect has split the elevators on ground Mach trim disabled Mach trim OFF MMO PIT TRIM BIAS Pitch trim bias not at zero Pitch trim selected to OFF IC 600 trim fault detected primary bypass trim available Spoileron in roll disconnect mode pilot control wheel dis...

Page 359: ... 600 a white PRI TRIM FAULT CAS message is displayed and primary trim will re vert to IC 600 bypass trim The same moni toring function by the IC 600 takes place dur ing configuration trim and Mach trim opera tion Primary Bypass Trim Primary trim reverts to bypass as a result of a detected malfunction or 1 IC 600 failure and is not crew selectable When in bypass trim a white PRI TRIM FAULT CAS mess...

Page 360: ...ely to 0 78 MI by 42 000 feet When the MACH TRIM FAIL message is posted the Overspeed cue on the airspeed in dicator will also adjust to indicate the Mach Trim Off MMO if the autopilot is not engaged If the autopilot is engaged the Overspeed cue will remain at 0 81 MI Primary Trim Electrical Power Electrical power for primary pitch trim is provided by the L Essential bus The circuit is protected b...

Page 361: ...Y HYD FUEL ECS RTN FLT Honeywell Honeywell STAB TGT WX 4 315 47 0 3 0 33 N 3 6 50 50 360 KDVT LL01 PBD01 PLAB1 PLAB2 TOC FL300 25 FMS1 KDVT 12 5 NM 12 MIN 300 TAS 15 SAT 245 GSPD 10 10 L 1 L RUDDER R NDN NUP 0 10 6 5 PITCH 45 SPLRS FLAPS EXT RET DN UP 8 20 AILERON 10 10 R 1 T R I M S Honeywell TUNE SQ DIM 1 2 STO DME TST PGE ID Honeywell TUNE SQ DIM 1 2 STO DME TST PGE ID FUEL HYDM B SPLFLP MORE 4...

Page 362: ... 8 T R I M S 10 10 L 1 L RUDDER R NDN NUP 0 10 6 5 PITCH 45 SPLRS FLAPS EXT RET DN UP 8 20 AILERON 10 10 R 1 T R I M S 10 10 L RUDDER R NDN NUP 0 10 PITCH SPLRS FLAPS EXT RET DN UP 8 20 AILERON 10 10 T R I M S FLIGHT CONTROL SYSTEM PAGE NORMAL DISPLAY FLIGHT CONTROL SYSTEM PAGE EXCEEDANCE DISPLAY FLIGHT CONTROL SYSTEM PAGE INVALID DISPLAY DN Figure 15 16 Flight FLT System Schematics ...

Page 363: ...indications are provided on the EICAS and the MFD A dig ital display of pitch trim position PIT TRIM is always in view below the CAS window on the right side of the EICAS Figure 15 15 Pitch PIT aileron AIL and rudder RUD trim are all digitally displayed on the SUMRY page They are arranged in a vertical column labeled FLT on the right side of the SUMRY page Figure 15 15 The SUMRY page is the power ...

Page 364: ... two jackscrew ac tuators per flap section Flap motion is a com bination of aft movement to increase lift and downward tilting to increase drag Uncommanded retraction due to airloads vi bration etc is prevented by the irreversibil ity of each actuator The system used to position the flaps is a mi croprocessor based controller Flap Control Unit The controller receives position com mand information ...

Page 365: ...OTION FUEL QTY CMPTR AUTOPILOT SPOILERONS SPOILER VALID STALL WARN 1 OVERSPEED TAKEOFF CONFIGURATION MONITOR FUEL QTY CMPTR CONFIGURATION TRIM HYD PRESS FLAP HYD RETURN SERVO VALVE FLEXIBLE DRIVE SHAFT LEFT FLAP RIGHT FLAP RVDTS 2 RVDT PRESSURE SWITCH RVDTS 2 JACKSCREW ACTUATOR 4 EXTEND RETRACT FLAP POWER UNIT FLAP LEVER DETENT SWITCH ARMING SOLENOID VALVE FLAP DRIVE MOTOR DN UP 8 20 FLAPS FLAPS 2...

Page 366: ...her channel Figure 15 17 il lustrates some but not all of the airplane systems that flap position information is pro vided to Flap position has a full time digital display on the EICAS below the CAS window Figure 15 15 The digital display on the EICAS will have a white box around it anytime the flaps are not in the selected position and also any time the airplane is on the ground and the flaps are...

Page 367: ...be verified on the FLT system schematic page Another mal function that will cause a FLAPS FAIL mes sage is uncommanded movement of the flaps The crew cannot reset the flap system after ex periencing flap asymmetry or uncommanded movement malfunctions However it may be possible to reset the system after other mal functions using the FLAP RESET position on the system test knob Figure 15 19 Flap Oper...

Page 368: ...ssure bulkhead Figure 15 21 The aileron disconnect lever on the pilot s control wheel is used to disconnect the control wheel from the ailerons and signal the spoileron controller to activate the roll dis connect mode of operation Spoiler Lever The spoiler position lever is located on the throttle quadrant and is linked to two RVDTs rotary variable differential transformers There are three labeled...

Page 369: ...ATA COMPUTERS 2 FLT SCHEMATIC ON EICAS MFD SUMRY MENU ON EICAS MFD WHEELSPEED 4 WEIGHT ON WHEELS 2 THRUST LEVER IDLE CUTOFF DETENT SPOILERON RESET SWITCH FLAP POSITION ENGINE HYD PUMP PRESSURE CONFIGURATION TRIM TAKEOFF CONFIGURATION MONITOR SPOILER CONTROLLER L RUDDER R NDN NUP 0 10 6 5 PITCH 0 SPLRS EXT RET AILERON 10 10 R 1 10 10 L 1 T R I M S DN UP 8 20 FLAPS ELECT VOLTS EMER V AMPS TEMP C 28 ...

Page 370: ...n The spoilers can be extended symmetrically on the ground or inflight by moving the spoiler lever aft of the ARM position Placing the lever to any position aft of ARM while on the ground will cause full extension 60 of the spoilers Spoiler extension on the ground re quires approximately 1 second and inflight ap proximately 5 to 7 seconds When the spoiler lever is placed in any posi tion aft of AR...

Page 371: ...d right the computer mix logic retracts the left spoiler first to give differential necessary for the roll commanded If that is not enough differential for the roll commanded the computer then extends the right spoiler as required Autospoiler Mode of Operation The autospoiler mode is designed for automatic extension of the spoilers in the event of an aborted takeoff and for landings This mode full...

Page 372: ...held depressed the spoiler shutoff valve is depowered closed and the spoilers should blow down to a float po sition of approximately 10 When a malfunction causes the spoileron mon itor to trip an amber SPOILERS FAIL mes sage is posted on the CAS If a spoiler surface deploys uncommanded due to a malfunction or deploys further than commanded the mon itor system should cause the spoiler to retract an...

Page 373: ...10 10 160 180 1 0 9 160 FMS AP 120 100 14 RF 25 COPILOT S PFD L R STALLWARN FAIL L AOA HT FAIL R AOA HT FAIL CAS CAUTION MESSAGE STALL STALL STALL AURAL VOICE MESSAGE 2 4 6 8 1 0 2 4 6 8 1 0 R AOA INDICATOR L AOA INDICATOR PILOT S CONTROL COLUMN SHAKER COPILOT S CONTROL COLUMN SHAKER OPTIONAL STALL WARNING COMPUTER L R AIR DATA CMPTR WEIGHT ON WHEELS AOA VANE FLAPS AIR DATA CMPTR WEIGHT ON WHEELS ...

Page 374: ...tall computer will activate the control col umn shaker motors The non cancellable voice message STALL will repeat until the AOA is decreased The AOA indicators if installed will enter the the red band on the indicator STALL WARNING OPERATION The stall warning system does not have on off switches If the circuit breakers are in the systems are powered when the airplane elec trical system is powered ...

Page 375: ...takes approximately 5 seconds to complete and after a slight pause the same sequence occurs for the right side if the test button is held depressed When the right side is testing a R AOA HT FAIL CAS message will be displayed STALL WARNING ELECTRICAL POWER The left and right stall warning systems are power by the L and R Essential Busses re spectively The circuits are protected by the L STALL WARN ...

Page 376: ...lane C Engage the autopilot D Use rudder to control the airplane in the roll axis 6 If the white PRI TRIM FAULT message appears on the CAS A Primary trim is inoperative and sec ondary should be selected B Primary trim will still function and may be in the bypass mode C Mach trim and Configuration trim may be inoperative D Both b c are correct 7 If the 1 IC 600 fails inflight A Primary trim will be...

Page 377: ... trim switch on the center console D Both a c are correct 14 If the spoiler lever is in the ARM position for landing which of the following are re quired for autospoiler deployment A Thrust levers at idle or cutoff B Either main squat switch showing weight on wheels or ground speed in excess of 60 knots C All four wheel speeds indicated in ex cess of 65 knots D Both a b are required 15 If the flap...

Page 378: ...flaps are up C Anytime the autopilot activates sec ondary trim for more than 2 to 3 sec onds D There is no trim in motion clacker in this airplane 19 If the spoilers are inoperative the maxi mum airplane operating altitude is lim ited to A 15 000 feet B FL 270 C FL 350 D FL 410 15 35 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 379: ...YSTEM 16 10 General 16 10 Audio Control System 16 10 Radio Management Units RMUs 16 14 General 16 14 Cross Side Operation 16 15 RMU Display Color Coding 16 15 COM Tuning Operation 16 15 NAV Tuning Operation 16 16 COM and NAV Memory 16 18 ADF Tuning and Mode Control 16 19 Transponder TCAS 16 19 TCAS Controls 16 21 RMU Backup Pages 16 21 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL Fl...

Page 380: ...ADC Test 16 30 Standby Instruments 16 32 ATTITUDE HEADING REFERENCE SYSTEM AHRS 16 33 General 16 33 Slaved Free Modes 16 33 Initialization 16 35 AHRS Power Source 16 35 AHRS Reversion 16 35 AHRU Cooling Fan 16 36 ELECTRONIC DISPLAY SYSTEM EDS 16 36 General 16 36 Display Units DUs 16 36 Bezel Controllers 16 37 PFD Bezel Controller 16 37 EICAS Bezel Controller 16 39 LEARJET 45 PILOT TRAINING MANUAL ...

Page 381: ...strument and Crew Alerting System EICAS 16 63 CAS Messages 16 63 System Display Pages 16 63 Multi Functional Display MFD 16 64 MFD Map Mode 16 64 MFD Plan Mode 16 67 MFD Display Areas and Annunciations 16 67 MFD Selectable Window Displays 16 71 MFD Bezel Menu 16 71 EDS Self Test 16 74 PFD Test Mode 16 74 EICAS Test Mode 16 74 MFD Test Mode 16 74 FLIGHT GUIDANCE AND CONTROL SYSTEM 16 78 General 16 ...

Page 382: ... Functions 16 91 Data Base 16 92 WEATHER RADAR 16 93 General 16 93 Description and Operation 16 93 TCAS TRAFFIC COLLISION AVOIDANCE SYSTEM 16 98 General 16 98 Controls and Displays 16 98 AVIONICS COOLING 16 105 COCKPIT VOICE RECORDER CVR 16 105 CLOCKS 16 106 REVIEW QUESTIONS 16 107 LEARJET 45 PILOT TRAINING MANUAL 16 iv FOR TRAINING PURPOSES ONLY FlightSafety international ...

Page 383: ...ing on RMU 16 16 16 11 COM and NAV Memory Pages on RMU 16 17 16 12 ADF Tuning on RMU 16 18 16 13 ATC IDENT on RMU 16 20 16 14 ATC TCAS Control Page on RMU 16 21 16 15 Backup Engine System Pages on RMU 16 22 16 16 Backup Navigation Display Page on RMU 16 23 16 17 Invalid Backup Navigation Display on RMU 16 24 16 18 Clearance Delivery Head CDH 16 26 16 19 Pitot Static Probes 16 28 16 20 Pitot Static...

Page 384: ...CAS Display Format 16 53 16 35 Primary Flight Display ADC Test CAT II Display Format 16 55 16 36 EICAS Display Format Display Areas 16 62 16 37 MFD Format MAP Display 16 65 16 38 MFD Format WX on Map Display 16 66 16 39 MFD Format PLAN Display 16 68 16 40 MFD Format PLAN with Checklist 16 69 16 41 MFD MAP Symbols 16 70 16 42 MFD Menu Tree 16 71 16 43 Primary Flight Display Test Format 16 75 16 44 ...

Page 385: ...i Function Chronometer 16 106 TABLES Table Title Page 16 1 Avionic Bus Loads 16 10 16 2 Avionics CAS Messages 16 46 16 3 Flap Position Overspeed Display 16 56 16 4 NAV Color Logic on PFD 16 59 16 5 Automatic Flight Control System CAS Messages 16 80 16 6 Flight Director Mode Annunciations 16 84 16 7 WX Radar Storm Intensity Levels 16 95 16 8 Target Depth Range Characteristics 16 97 16 9 TCAS Displa...

Page 386: ...includes attitude heading reference systems AHRS air data systems ADS VHF Nav Comm radios and DMEs A single ADF is provided and a second may be installed as an option The standard weather radar installation is the Honeywell Primus 660 with the Primus 880 weather radar available as an option Single or dual flight management systems FMS a traffic collision avoidance system TCAS and ground proximity ...

Page 387: ...nstallation Additional redundancy features on the DAUs is that each unit is also dual channel CH A and CH B LEARJET 45 PILOT TRAINING MANUAL 16 2 FOR TRAINING PURPOSES ONLY FlightSafety international THROTTLE QUADRANT ENGINE FUEL PANEL FLIGHT MGMT SYSTEM APU SELCAL HF TRIM WX RADAR PILOT S PRIMARY FLIGHT DISPLAY PFD EICAS AUDIO CONTROL PANEL AUDIO CONTROL PANEL RMU 1 RMU 2 MULTI FUNCTION DISPLAY M...

Page 388: ... controllers DISPLAY GUIDANCE COMPUTER IC 600 OR IC SG GENERAL The IC 600s have circuit cards installed to perform the following Symbol generators Both IC 600s Flight director computers Both IC 600s Primary trim No 1 IC 600 only Configuration trim No 1 IC 600 only Mach trim No 1 IC 600 only Autopilot Yaw damper computer No 2 IC 600 only Secondary trim No 2 IC 600 only Rudder boost No 2 IC 600 only...

Page 389: ...8 5 28 0 28 0 50 65 30 50 HYD ECS MAIN B ACUM CAB ALT OXY QTY 3000 3000 1300 669 FLT SPLR PIT AIL RUD 0 6 5 R 1 L 1 DU 1 DU 2 DU 3 DU 4 RMU 1 RMU 2 33 3 0 W N 3 6 E 1 2 1 5 S 2 1 2 4 3 2 1 0 1 2 3 1000 20 20 10 10 10 10 150 4500 29 92 IN 5000 160 180 14 1 0 9 120 100 160 400M GS LOC HDG AP YD SPD GS 180 RA HDG 001 359 CRS ILS1 13 1 NM 25 TGT VOR1 ADF2 RA BARO STD BARO MINIMUMS 4380 20 00 Honeywell...

Page 390: ...C DU3 MFD 33 3 0 W N 3 6 E 1 2 1 5 S 2 1 2 4 3 2 1 0 1 2 3 1000 20 20 10 10 10 10 150 4500 4300 20 80 29 92 IN 5000 160 180 14 1 0 9 120 100 160 400 M GS LOC HDG AP YD SPD GS 180 RA HDG 001 359 CRS ILS1 13 1 NM 25 TGT VOR1 ADF2 RA BARO STD BARO MINIMUM DU4 PFD REMOTE NAV UNIT REMOTE COM UNIT DISCRETES ATTITUDE HEADING REFERENCE SYSTEM AHRS IC 600 IC SG AIR DATA COMPUTER ADC MAG FLUX GATE DATA ACQU...

Page 391: ...iv ing valid weight on wheels information Failure of an IC 600 or failure of the symbol generator within the IC 600 is indicated by blanking of both on side display units DUs a large red X on one or both DUs or erro neous erratic display of data on either or both failed side DUs An IC SG reversion switch is provided on the REVERSION panel Figure 16 4 which allows selection of either IC SG to drive...

Page 392: ...he radio management units RMUs for backup displays In addition to engine information the DAUs also collect analog data from other airplane sys tems such as fuel hydraulic and accumulator pressure DC electrical power flight control settings cabin pressure indications settings and oxygen temperature pressure Some sys tems input information to only one DAU and some inputs are sent to both DAUs A thre...

Page 393: ...Left and right avionics master switches are lo cated on the electrical control panel beneath DU2 Figure 16 5 When the avionics mas ter switches are selected to ON OFF an nunciators extinguished contactors are energized that connect the L R essential avion ics busses and L R main avionics busses to the respective generator busses The associated es sential contactors and main bus contactors must als...

Page 394: ...alled in place of the Mode C units Two integrated navigation units are also lo cated in the nose avionics bay They each con tain a VOR localizer glideslope and marker beacon receiver module a DME module and an ADF module dual ADF modules are op tional The DME module is a six channel scanning DME that simultaneously tracks four selected DME channels for distance ground speed and time to station Two...

Page 395: ...1 2 STO DME TST PGE ID COM 1 NAV 1 ATC TCAS ADF 1 TCAS DSPY 123 20 131 27 MEMORY 3 1471 1 ATC ON RANGE 40 BELOW 110 25 109 35 MEMORY 1 162 5 ANT NB Honeywell TUNE SQ DIM 1 2 STO DME TST PGE ID COM 1 NAV 1 ATC TCAS ADF 1 TCAS DSPY 123 20 131 27 MEMORY 3 1471 1 ATC ON RANGE 40 BELOW 110 25 109 35 MEMORY 1 162 5 ANT NB Honeywell SQ NAV AUDIO 1 COM NAV AUDIO NAV TX SQ E M R G MODES CLR DLY UNIVERSAL D...

Page 396: ...d must be se lected ON Assuming power is available to the COM1 and NAV1 units COM and NAV frequencies can still be set using either RMU or the clearance delivery head when EMER is selected on the audio control panel If EMER is selected and electrical power is still available to the audio panel system warning audios will still be available through the cock pit speaker and audio will be routed to th...

Page 397: ...trol the left and right marker beacon receivers respectively The sensitivity is controlled by the rotation of the MUTE con trol If either audio panel MKR sensitivity control is set LO then both MKR receivers are set to LO regardless of the position of the other audio panel controls The pilots can tem porarily mute the on side marker beacon re ceiver audio ident by momentarily depressing the spring...

Page 398: ...s on them The remaining keys are referred to as line select keys The RMUs also contain eight function keys located at the bottom to the left of the tuning knobs The RMU main tuning page Figure 16 8 is di vided into six dedicated windows Each window groups the data associated with a particular func tion The windows COM NAV ATC TCAS ADF and TCAS DSPY each provide for con trol of both frequency and o...

Page 399: ...the active frequency of the COM while the line below it displays a preset frequency Upon pressing the line select key adjacent to the lower pre set frequency a yellow cursor box will move to enclose that frequency This step is not always necessary since the cursor nor mally parks over the preset frequency box Anytime the cursor has been moved to an other spot on the main radio tuning page it will ...

Page 400: ...d on the audio and a MIC STK message will ap pear at the top of the COM window until the mic button is released Ten 10 seconds after the MIC STK annunciation appears the se lected transmitter will automatically turn off A squelch function is associated with COM Depressing the SQ squelch function key at the bottom of the RMU causes the COM radio to open its squelch and allows any noise or sig nal p...

Page 401: ...ME digital station identifier will appear following the DME nomenclature on the top edge of the DME sec tion Also when using DME split tuning an amber H hold appears in front of the DME fre quency This indicates that the distance display DME or TACAN is not paired with the VOR ILS navigation data When the H is dis played on the RMU it will also be displayed following the DME read out on the PFD De...

Page 402: ...ox over the pre vious frequency or vacant position then enter a new frequency using the tuning knob If it is desired to add a new frequency in a par ticular numbered field or location first depress the line select key beside that location This places the cursor box over the frequency field Depressing the button next to the INSERT function label then creates a space for the new frequency at that lo...

Page 403: ...ration is similar to COM NAV operation in that depressing a line select but ton beside the function desired will move the cursor to that location Those airplanes with out TCAS installed will have an ATC legend at the top of the transponder window and those equipped with TCAS will have ATC TCAS labeled above the window Either transponder 1 or 2 can be selected for use and controlled by either RMU A...

Page 404: ...stalled are all of the above plus TA ONLY Selects the TCAS traffic ad visory mode The selectable modes with a Mode S transpon der and TCAS II installed includes all of the above for TCAS I plus TA RA traffic resolution advisory To change the transponder code first highlight the code with the cursor Then using the large outer tuning knob adjust the left two digits use the smaller inner knob to chan...

Page 405: ...e of the large display units If DU 2 is turned off with DU 2 reversion switch the EICAS display does not automatically transfer to DU 3 or 1 RMU Once the engine page has been auto matically selected and the crew then selects another page for display the RMU will auto matically return to Page 1 of the RMU engine display 20 seconds after the last user input to the system Page 1 of the engine display...

Page 406: ...e displayed in white for normal ranges amber for caution ranges and red for the warning range RMU Navigation Page A navigation page Figure 16 16 can also be selected for display on either RMU On the navigation page NAV1 and ADF1 can be tuned directly For all other frequen cies code tuning i e COM1 and ATC1 the op erator must return to the main radio page or LEARJET 45 PILOT TRAINING MANUAL 16 22 F...

Page 407: ...tion NAV 1 bottom right corner Bearing pointers for VOR and ADF Digital VOR and ADF bearing readouts just above CRS TO FROM indication Marker beacons Heading from 2 AHRS lubber line and digital heading readout Lateral deviation VOR and ILS Vertical deviation GS only The navigation displays on both RMUs use AHRS 2 heading information and NAV in formation from NAV1 and ADF1 If the head LEARJET 45 PI...

Page 408: ...s changed VOR and ADF bearing pointer will be dis played on the navigation display when valid frequencies are selected and being received Figure 16 16 The bearing pointer head or tail will extend beyond the compass rose at the ap propriate point when within the 90 arc of the display The VOR pointer is a single line with a circle just aft of the point The ADF pointer is double lines with a diamond ...

Page 409: ... automatically switch to the secondary power source RMU power sources are as follows RMU 1 Primary L ESS BUS Secondary EMER BAT BUS RMU 2 Primary R MAIN AV BUS Secondary R ESS BUS RMU 1 and RMU 2 primary and secondary circuit breakers are located in the COMMU NICATIONS group of circuit breakers on the respective side The RMU 2 primary power is the only power source affected by the avion ics master...

Page 410: ...ow ered Nav section of the integrated navigation unit 1 DME ADF portion not powered The RADIO CTL HOT BUS is only functional when power is not applied to the left essen tial bus When the airplane batteries are on the above equipment receives power from the es sential busses and the RADIO CTL HOT BUS cannot be selected If it was selected before airplane batteries were turned on the ON an nunciator ...

Page 411: ...ransmitter is on Emergency Mode Annunciator Indicates when the CDH has been placed in the emergency mode In the normal mode there is no annunciation In the emer gency mode COM1 and NAV1 are tuned exclusively by the CDH This annuncia tor is not related to the emergency COM frequency of 121 5 nor to the EMER se lection on the audio control panel The CDH has two modes of operation normal and emergenc...

Page 412: ...nd R PROBES switches on the anti ice control panel Each pitot static system Figure 16 20 is in dependent The left side probe provides pitot static source data to the left ADC and the right side probes two provide data to the right ADC and the standby instrument group There are four static sources in the main pitot static system two on each main system pitot static probes The static sources Static ...

Page 413: ...16 22 Should a fault be detected in the displayed data a switch on the reversion panel Figure 16 4 allows se lection of either ADC to provide air data to both IC SGs A complete ADC failure is in LEARJET 45 PILOT TRAINING MANUAL 16 29 FOR TRAINING PURPOSES ONLY FlightSafety international ADC 1 ADC 2 PILOT S HEATED PITOT STATIC PROBE LH COPILOT S HEATED PITOT STATIC PROBES RH 28 VDC 28 VDC 28 VDC pt...

Page 414: ...version ADC source is selected the current flight director vertical modes will drop off but can be re engaged Air data information to the optional FMS s is supplied via the IC 600 units ADC Power Source The left and right No 1 and 2 ADCs receive power from the L and R essential busses re spectively through ADC 1 and ADC 2 circuit breakers Figure 16 22 The circuit breakers are located within the IN...

Page 415: ...FOR TRAINING PURPOSES ONLY FlightSafety international 1 2 ADC NORM REVERSION PANEL IC 600 1 IC SG IC 600 2 IC SG STALL WARNING 1 STALL WARNING 2 SPOILERON CMPTR PILOT PFD COPILOT PFD BARO BARO CAB PRESS CONTROLLER AHRU 1 AHRU 2 DEEC 1 FMS 1 FMS 2 DEEC 2 L ESS BUS R ESS BUS ADC 1 ADC 2 TRANSPONDER 2 TRANSPONDER 1 LDG GEAR CAUT PITOT 1 PITOT 2 STATIC 2 STATIC 1 TOTAL AIR TEMPERATURE TOTAL AIR TEMPER...

Page 416: ...tains a vibrator motor for improved performance The vibrator motor is powered from the emergency battery bus and a red OFF flag appears on the face of the standby altimeter beneath VIB whenever power is lost The standby attitude indicator and it s inter nal lighting are also powered by the emer gency battery bus In the event of dual generator failure the standard emergency bat tery will power the ...

Page 417: ...the attitude and heading displays on the PFDs MFD Figure 16 24 Attitude and or heading information from the AHRS is also used by the flight guidance sys tem FGS flight management system FMS weather radar antenna and the fuel quantity computer AHRS No 2 provides heading in formation through DAU2 for the backup nav igation display on the RMU SLAVED FREE MODES The heading indicators on the PFDs MFD a...

Page 418: ... L ESS BUS FMS 1 R ESS BUS 1 PRI 1 SEC 2 SEC 2 PRI AHRU 1 AHRU 2 IC 600 1 IC SG IC 600 2 IC SG DU1 DU2 DU3 DU4 ADC 1 ADC 2 RMU 1 RMU 2 DAU 2 FREE SLAVE L R AHRS HEADING FREE SLAVE L R AHRS HEADING 1 2 AHRS NORM REVERSION PANEL FLUX VALVE 1 FLUX VALVE 2 FMS 2 Figure 16 24 Attitude Heading Reference System AHRS Schematic ...

Page 419: ... AHRS has a primary and a secondary DC electrical power source Figure 16 24 The No 1 left AHRS receives primary power from the left essential bus and secondary or backup power from the right essential bus The No 2 right AHRS receives primary power from the right essential bus and sec ondary power from the left essential bus Should either essential bus fail in flight power to both AHRS s is uninter...

Page 420: ... displays The EICAS display consists of engine indications CAS messages and airplane system status pages The multi function display MFD is capable of supporting heading data navigation plan map weather radar TCAS information and checklists optional In addition backup dis plays are available on the radio management units RMUs for navigation and critical en gine instruments and data EDS information ...

Page 421: ...and DU3 consist of push buttons that access an array of menus and signal output circuitry to the display controller for rotary knob control PFD Bezel Controller As illustrated in Figure 16 26 the PFD bezel controller is attached to the front of the dis play units at the bottom It performs the fol lowing functions RA BARO This pushbutton allows the minimums knob to be used to set values for either ...

Page 422: ...has BARO displayed and the copilot has RA and the pilot changes the BARO setting the RA display will not change on the copilot PFD When the copilot does change displays from RA to BARO it will synchronize to the last BARO value that was set STD This pushbutton Figure 16 26 is used to select either the standard baro metric correction factor of 29 92 In Hg inches of mercury or 1013 HPA HectoPascals ...

Page 423: ...of any sys tem pushbutton will display a corresponding schematic of that system on the lower portion of the EICAS format Examples of the system schematics are illustrated in the correspond ing chapters for those systems A white box will also be displayed around the menu item that has been selected The default selection when power is applied is the SUMRY menu The SUMRY and system schematic displays...

Page 424: ...tons are momentary action Display Controller Buttons IN HPA Allows the operator to select an al titude display on the PFD that is corrected for either inches of mercury or HectoPascals Power up default is in inches of mercury CUE Allows the pilots to select either a sin gle cue or cross pointer flight director command bar display on the attitude in dicator Power up default is single cue The two fl...

Page 425: ...s on the HSI or ARC displays to a particular navigation source The knobs are labeled BRG left knob and BRG right knob The and symbols correspond to the symbols used on the bearing pointers Figure 16 31 Also the No 1 bearing pointer is cyan in color and the No 2 bearing pointer is dim white When using the HSI or ARC display on the PFD the left bearing source knob BRG is used to select any of the av...

Page 426: ... display unit reversion panel is located above the PFDs on each side of the cockpit Figure 16 30 The panel on the pilot s side is for con trolling the display on DU2 and the panel on the copilot s side is for controlling the display on DU3 The reversion selector knob on these panels plus the push function of the knobs allow the operators to switch the inboard DUs DU2 and DU3 to display either PFD ...

Page 427: ...outboard display units Should DU3 fail no automatic changes to the display configuration will occur Navigation information as desired can be monitored as above on the PFDs RMU Should DU4 fail the copilot s PFD format can be transferred to DU3 replacing the MFD Navigation data can then be selected as above with DU1 failure In all cases with a single display unit failure the MFD display will be lost...

Page 428: ...When annunciated the amber signal s flash for 10 seconds on the PFD s then go steady Airplane flight performance is compared within each IC 600 The following parameters along with their annunciation are monitored Attitude ATT Active when pitch and roll comparators have tripped Pitch PIT Attitude 5 degrees Roll ROL Attitude 6 degrees Heading HDG 6 degrees Altitude ALT 200 feet Airspeed IAS 5 knots ...

Page 429: ...tored against the actual DAU s sensor data The IC 600 that is not displaying EICAS per forms the comparison function for the fol lowing N1 N2 ITT Should exceedances be detected a CHK EICAS message is displayed on the MFD by the CAS Figure 16 38 PRIMARY FLIGHT DISPLAY PFD The PFD is a single display in which all of the required flight and navigation data is dis played for each pilot Information dis...

Page 430: ...or off side IC 600 failure IC 600 1 2 or 1 2 overheat 110 C DU 3 4 or 3 4 overheat 120 C DU 1 2 or 1 2 overheat 120 C L or R PFD is displaying incorrect data DAU engine miscompare logic N1 N2 ITT AHRS 1 or 2 or both reverted to basic mode DAU misc systems miscompare logic EICAS display data may be corrupted DAU reversion switch on Channel A A CKLST MISMATCH Different checklists loaded into each IC...

Page 431: ...E CUE FLIGHT DIRECTOR BAR PARKED ALTITUDE PRESELECT BUG VERTICAL DEVIATION SCALE POINTER AND LABEL SCALE WHITE POINTER LABEL GREEN WHITE YELLOW ALTITUDE TREND VECTOR LOW ALTITUDE AWARENESS BROWN RASTOR LINE WHITE RADIO ALTITUDE ARMED LATERAL FLIGHT DIRECTOR MODE ANNUCATIONS ROLL POINTER AIRSPEED COMMAND SINGLE CUE AIRCRAFT SYMBOL AIRSPEED COMMAND BUG NAV SOURCE ANNUCATION SRN GREEN YELLOW LRN WHIT...

Page 432: ... Figure 16 31 Within the ADI sphere is a pitch tape a roll pointer and sky ground shading A roll scale is also displayed on the top of the ADI sphere The on side AHRS normally provides the infor mation to drive the attitude display The flight director provides the pitch and roll command bars Failure of either the pitch or roll data is indicated by removing the pitch scale mark ings turning the ent...

Page 433: ... M AMBER O CYAN BARO SET BUG HEADING SOURCE ANNUNCIATION AMBER WHITE HEADING COMPARISON MONITOR WARNING FMS MESSAGE FLAG WEATHER RADAR PATCH VOR DME NAVAID BEARING SYMBOL 2 TCAS MODE ANNUNCIATIONS TO FROM TO FR ANNUNCIATION WHITE YELLOW RANGE RING VALUE FLIGHT PLAN LEG WHITE TO WAYPOINT MAGENTA WAYPOINTS WHITE FMS LATERAL DEVIATION WEATHER RADAR VIDEO INVALID WEATHER RADAR TILT ANNUNCIATION FIELD ...

Page 434: ...or mode annunciations com mand bars and couple arrow Low bank limit arc Vertical deviation scale pointer and label Marker beacons Radio altitude digital readout and box Decision height digital readout and label Minimum descent altitude digital readout label and bug Selected airspeed bug digital readout and outline V speed bugs and readouts All failure flags for the above listed items The following...

Page 435: ...ARKED PITCH TAPE ALTITUDE TAPE TAPE RASTER GRAY ALTITUDE ROLLING DIGIT WINDOW ALTITUDE PRESELECT BUG BAROMETRIC CORRECTION IN HPA VERTICAL SPEED POINTER WHITE RED VERTICAL SPEED DIGITAL READOUT WHITE RED VERTICAL SPEED INDICATOR SCALE HEADING BUG OUT OF VIEW ARROW HEADING SCALE CRS DTRK DEVIATION BAR GREEN WHITE YELLOW AIRCRAFT SYMBOL TO FROM TRIANGLE GREEN WHITE YELLOW CRS DTRK POINTER GREEN WHIT...

Page 436: ... is displayed as a magenta rectangular D shape box positioned to the left of the altitude tape with a line extending from the middle edge of the D to the right edge of the altitude tape BARO minimums are set with the RA BARO switch and minimums set knob of the PFD bezel controller For low altitude awareness the same alerts for RA as previously de scribed apply to BARO minimums Marker Beacons Marke...

Page 437: ...ODE FIELD CAPTURED VERTICAL FLIGHT DIRECTOR MODE FIELD ALTITUDE PRESELECT BOX CYAN AMBER DIGITS MAGENTA AMBER 500 FOOT CHEVRON 1000 FOOT CHEVRON VERTICAL SPEED SET DISPLAY TCAS NO FLY ZONE RED TCAS FLY TO ZONE GREEN HEADING SELECT DIGITAL READOUT BEARING 2 ANNUNCIATOR BEARING 1 ANNUNCIATOR WIND DISPLAY COURSE DESIRED TRACK DIGITAL READOUT GREEN WHITE YELLOW MACH SPEED DIGITS WHITE AMBER RED EYEBRO...

Page 438: ...be digitally displayed at the bottom of the tape if Mach is at or above 40MI Figure 16 34 and when the Mach tape is dis played the equivalent IAS will be digi tally displayed at the bottom of the tape Figure 16 33 The IAS tape Figure 16 34 is annotated in 20 knot increments beginning at 40 knots with tick marks in 10 knot incre ments The Mach tape Figure 16 33 is in dexed from 0 to 1 10 Mach with ...

Page 439: ...000 10 10 29 92 IN 340 360 330 1 9 160 GS LOC AP YD GS HDG 001 359 81 M CRS ILS1 2 2 NM 25 TGT VOR1 ADF2 135 2 20 20 10 10 1500 5000 0 ADC TEST CAT2 CAT2 ANNUNCIATION GREEN AMBER ADC TEST ANNUNCIATION V2 GREEN VR CYAN V1 WHITE VSPEED DIGITAL READOUTS 120 1 125 R 320 1000 20 80 Figure 16 35 Primary Flight Display ADC Test CAT II Display Format ...

Page 440: ...nd the Vspeed refer ences will come into view Figure 16 32 V1 and VR are removed from the airspeed tape when the airplane becomes airborne and V2 is automatically removed at V2 40 KIAS With FMS as the default pilot access to the MFD Vspeed bezel menu is not nec essary but can be used if desired to man ually set the Vspeed With FMS installed a white T rotated 90 and labeled RF VREF reference mark c...

Page 441: ... The pointer needle is always in display and will not overwrite the digital display A digital readout is also displayed above the arc display and represents the VS target value set by the VS on the FD This display corresponds to the set bug value for desired VS and has a range of 6000 fpm This display also annunciates TCAS resolution advisory information PFD HSI Heading information is presented as...

Page 442: ...table and displayed when the selected navigation source is VOR LOC ILS The course is in dependently selectable on the pilot and copilot sides using the two course set knobs CRS 1 and CRS 2 on the flight guidance controller panel Desired track information is displayed when the se lected navigation source is FMS and is not pilot selectable with the course set knobs The course select CRS and desired ...

Page 443: ...nciated above the HSI heading indi cator Figure 16 32 Navigation source annunciation The navigation source is displayed below the selected course desired track digital read out The color of the annunciation will be as displayed in Table 16 4 Symbol generator source annunciation This annunciation provides an indica LEARJET 45 PILOT TRAINING MANUAL 16 59 FOR TRAINING PURPOSES ONLY FlightSafety inter...

Page 444: ...ust beneath the cross track mode annunciation SXTK and are Selected heading shown as HDGSEL Heading intercept shown as HDGINT Heading procedure turn shown as PRCHDG FMS generated vertical track alert shown as VTA appears just above the vertical deviation scale and replaces VNV while active FMS Map Mode With FMS selected as the active navigation source a navigation map MAP can be dis played on the ...

Page 445: ... radar control panel range buttons regardless of whether or not WX is selected for display via the display controller pushbutton If WX is turned OFF the range defaults to 100 NM To From indicator When TO is ac tive it will be displayed beneath the half range digital readout When FROM is active the characters FR will be dis played in place of the TO LEARJET 45 PILOT TRAINING MANUAL 16 61 FOR TRAINI...

Page 446: ...REA 15 LINES X 18 CHARACTERS CAS DIVIDER LINES STATIC AIR TEMPERATURE DIGITAL READOUT PITCH TRIM DIGITAL READOUT DIGITS WHITE RED FLAPS DIGITAL READOUT DIGITS WHITE AMBER RED SYSTEM PAGE DIVIDER LINES FUEL QUANTITY DIVIDER LINE MAIN B ACUM CAB ALT OXY QTY 3000 3000 669 EMER V AMPS TEMP C 50 65 30 50 VOLTS 28 5 28 0 28 0 ELECT HYD ECS FLT SPLR PIT AIL RUD 0 8 5 R 1 L 1 1300 CAS FUEL FLT ECS HYD ELE...

Page 447: ...ted to displaying airplane major sub system status Normally the airplane sys tem summary page SUMRY on the menu is in view which provides brief status reports of all of the sub systems Figure 16 36 Menu selectable a system schematic of airplane electrical hydraulic environmental control flight control and fuel systems can be indi vidually selected for more detailed monitor ing by the flightcrew Wh...

Page 448: ...30 as illustrated in Figure 16 37 Heading Source will be the same as se lected for the on side PFD Heading source will be annunciated to the right of the digital heading readout if AHRS or IC SG reversion is selected Drift Bug is presented as an unfilled tri angle bug that rotates around the perime ter of the heading compass The drift bug data is provided by the FMS An amber CHK EICAS message is d...

Page 449: ...45 GSPD 0 50R SRP KPHX BT APT NAV HDG TEST HEADING TEST ANNUNCIATION NDB SYMBOL AND IDENT AIRPORT SYMBOL AND IDENT HEADING BUG OUT OF VIEW ARROW NAVAID VOR DME SYMBOL AND IDENT AIRPORT ON ANNUNCIATOR NAVAID ON ANNUNCIATOR FMS LATERAL DEVIATION Honeywell 1650 R WING R ENG 4050 1720 USED 1000 FUSELAGE 1400 L WING L ENG LBS ON BOARD SUMRY ELEC HYD FLT RTN FUEL ECS M P RNG Figure 16 37 MFD Format MAP ...

Page 450: ...ING SOURCE ANNUNCIATOR DRIFT BUG TRUE AIRSPEED LABEL CYAN DIGITS WHITE STATIC AIR TEMP GROUNDSPD WEATHER RADAR PATCH WEATHER RADAR DISPLAY AREA TICKS MAP RANGE RING AND DIGITAL VALUE DESIGNATOR BEARING AND DISTANCE LRN SOURCE ANNUNCIATOR TO WAYPOINT IDENTIFIER DISTANCE TIME TO GO HEADING BUG WIND DISPLAY AIRPLANE SYMBOL WX MODES AMBER WX TARGET ALERT AMBER CYAN WX MODES AMBER CYAN WX TILT WX Honey...

Page 451: ...tance Common to both navigation displays MAP and PLAN are the following annunciations TO waypoint identifier magenta des ignates the next waypoint on the flight plan Distance is presented in nautical miles as a value from the airplane s present posi tion to the TO waypoint Time To Go TTG provides a display in minutes of the time to fly to the active way point based upon the present groundspeed Tru...

Page 452: ...SAT 245 GSPD 25 N 1000 HDG TEST PLAN CIRCLE FLIGHT PLAN HEADING TEST ANNUNCIATION PLAN AIRCRAFT SYMBOL YELLOW NORTH UP ARROW SYSTEM PAGE DIVIDER LINES DIM WHITE PLAN RANGE Honeywell AMPS GEN R AMPS APU A 28 0 38 R ESS VOLT 0 65 GEN C 28 0 50 AMPS L 35 28 2 L ESS VOLT EMER BUS VOLTS BATT TEMPS SUMRY ELEC HYD FLT FUEL ECS M P RNG RTN Figure 16 39 MFD Format PLAN Display ...

Page 453: ...VT LL01 PBD01 PLAB2 FMS1 LL01 12 5 NM 12 MIN 300 TAS 15 SAT 245 GSPD 25 N 50 230 40 0 DESIGNATOR LINE DASHED CYAN DESGNATOR BOX CYAN RTN RCL PAG M P RNG ENT SKP CHECKLIST Honeywell 1 NORMAL PROCEDURES 2 ABNORMAL PROCEDURES 3 EMERGENCY PROCEDURES MASTER INDEX 1 1 Figure 16 40 MFD Format PLAN with Checklist ...

Page 454: ...igure 16 37 The navaids are derived through the FMS data base and are positioned in relation to the FMS de termined present position A maximum of eight navaids will plot on the MFD 4 VORs and 4 NDBs NAVAIDs may also be included in the flightplan and are in cluded in the total waypoint count max imum of 10 NAVAID displays are selected or deselected with the NAV bezel key on the MFD menu Non Directi...

Page 455: ... the bezel buttons can perform Selection of a submenu Toggling selection of a menu item Selection of a variable parameter for set ting with the bezel knob When a menu item is selected on any of the menus and then the menu is changed the item selected is not affected e g if WX is selected on the main menu and then a submenu is se lected the WX radar display remains in view on the MFD The operator h...

Page 456: ...tion System Menu The system menu Figure 16 42 gives the operator the capability to select a summary of systems indications SUMRY or a system schematic of the listed systems for display at the bottom of the MFD display This is the same menu and display options that are avail able at the bottom of the EICAS display Illustrations of the systems schematics are found in the related chapters of this man...

Page 457: ...tor on the map or to move the designator through the waypoint list and view the flightplan Figure 16 40 shows the designator box and dashed line that connects the box and the airplane symbol The bearing and distance from the airplane to the designator is digitally displayed on the MFD to the right of the TCAS Checklist win dow The power up home position of the des ignator is present position Movem...

Page 458: ...n of the ADI All FD information and FMS map data is removed from display All three marker beacons are displayed Flight test mode RA 100 10 EICAS Test Mode The EICAS test mode illustrated in Figure 16 44 provides for failure mode annunciations for each display on the format The test is initi ated when the TEST button on the appropri ate display controller is pushed and held The test page format rem...

Page 459: ...TUDE RASTOR CYAN ATT FAIL RED FLIGHT DIRECTOR FAIL ANNUNCIATION INVALID VERTICAL DEVIATION RED X INVALID ALTITUDE PRESELECT DIGITS AMBER DASHES INVALID ALTITUDE TAPE RED X INVALID BARO CORRECTION AMBER DASHES INVALID HEADING SELECT AMBER DASHES INVALID VERTICAL SPEED BOX RED LABEL RED INVALID LATERAL DEVIATION RED X INVALID HEADING INVALID DISTANCE AMBER DASH INVALID CRS DTK DIGITAL READOUT AMBER ...

Page 460: ...PPH S T A R T S T A R T FIRE FIRE I N V A L I D S Y S T E M P A G E D I S P A Y A R E A LEARJET 45EICAS TST 1LEARJET 45ABCDEFG 12LEARJET 45HIJKLM 123LEARJET 45NOPQR 1234LEARJET 45STUV 12345LEARJET 45WXY 123456LEARJET 45ZA 12345LEARJET 45BCD 1234LEARJET 45EFGH 123LEARJET 45IJKLM 12LEARJET 45NOPQRS 1LEARJET 45TUVWXYZ LEARJET 45EICAS TST END Figure 16 44 EICAS Display Format Invalid Signals Test Disp...

Page 461: ...I N V A L I D S Y S T E M P A G E D I S P A Y A R E A INVALID HEADING DIGITAL DISPLAY AMBER DASHES INVALID TRUE AIRSPEED AMBER DASHES INVALID STATIC AIR TEMPERATURE AMBER DASHES INVALID GROUNDSPEED AMBER DASHES INVALID HEADING DISPLAY INVALID DISTANCE AMBER DASHES INVALID TIME TO GO AMBER DASHES INVALID WX AMBER INVALID BEZEL MENU DISPLAY Figure 16 45 MFD Format Test Display ...

Page 462: ...e S I legends and green indicators are dimmed through the NAV lights switch The autopilot is single channel with a fail pas sive design The monitor system provides for automatic disconnect in the event of a mal function in the flight director or the autopi lot yaw damper Both attitude heading reference systems AHRS must be functioning for autopilot op eration and both avionics master switches must...

Page 463: ...n At the top center of the PFDs is a field dedi cated to flight director and autopilot annun ciation Figure 16 31 A horizontal arrow appears between the flight director vertical and lateral mode annunciators This arrow points left or right as selected on the FGC XFR switch to indicate which flight director the au topilot will couple to when engaged It also in dicates which flight director has prio...

Page 464: ...r and the rudder boost should still be op erational If a steady YD is displayed nei ther the yaw damper or rudder boost are operational The crew may be able to clear a steady amber AP YD or RB by cycling the IC SG 2 circuit breaker on the copilot s CB panel Mistrim Annunciation When the autopilot is engaged and the roll or pitch servo remain energized for a longer than normal period mistrim the co...

Page 465: ...45 and pitch attitudes between 30 If engaged outside of the normal envelope the AP will return to the maximum limits of 20 to 10 pitch and 30 bank When the AP is engaged with no flight direc tor modes engaged and the roll attitude is within 6 of wings level the autopilot will roll the airplane to a wings level attitude and hold the existing pitch This mode is referred to as the heading hold mode a...

Page 466: ...he AP but allows the airplane to be maneuvered as desired The crew should not apply control wheel pressure when the AP is engaged unless the TCS button is first de pressed and held Applying aileron or eleva tor control wheel pressure without depressing the TCS may result in an AP monitor discon nect While the TCS button is held depressed AP engaged a white TCS annunciator appears at the top of the...

Page 467: ...es If an AP disconnect is due to autopilot mon itor trip the disconnect tone will repeat until acknowledged and the AP will turn red Momentarily depressing at least 2 seconds the MSW acknowledges the monitor discon nect and silences the disconnect tone When reset the red AP will either disappear or turn steady amber An amber AP indicates that the autopilot cannot be reengaged Pulling and re settin...

Page 468: ...C VAPP or FMS FD MODE SELECTED NAV SOURCE SELECTED FD ANNUNCIATION ON PFD APP approach ILS VERTICAL MODES None selected SPD speed IAS to 32 000 MACH above 32 000 VS vertical speed ALT altitude hold FLC flight level change normal or high speed VNV vertical nav FMS GA go around ASEL altitude select N A Any VOR FMS 1 or 2 LOC 1 or 2 LOC 1 or 2 BC VOR FMS 1 or 2 ILS 1 or 2 Any Any Any Any Any Any None...

Page 469: ...tons on the FGC panel have a vertical green bar that illuminates when ever the mode is selected armed or captured FD Cue The flight director symbology is selectable on the display control panels The button labeled CUE will alternately select the single cue or the cross pointer It defaults to single cue at power up The CUE will be the same on both PFDs and the selection is determined by power up de...

Page 470: ...ng mode and displays a green HDG annunciation on the PFDs The FD command bars will command a turn in the di rection the heading bug was moved to achieve the set heading If the heading knob is tuned so as to move the heading bug the long way over 180 to a new heading the FD will command the turn in that direction only when airborne The heading select mode is canceled when any armed lateral mode cap...

Page 471: ...tive nav source Mode opera tion is identical to the VOR mode NAV but with the lateral command gains optimized for operation within 10 miles of the VOR station When selected the VAPP arm annunciator is displayed on the PFD Intercept and capture logic is the same as described for VOR APP LOC or LOC BC Using the FD APP mode for LOC or LOC BC is much the same as described for VOR ex cept the FD annunc...

Page 472: ...s long as VS is not selected When VS mode is engaged rotation of the SPD knob changes the digital vertical speed reference and the vertical speed bug position The integral PUSH IAS M button within the SPD knob is used to toggle the airspeed tape between IAS and Mach SPD Speed Depressing the SPD button engages the speed hold mode IAS or Mach on both FDs The FD will command pitch change as necessary...

Page 473: ...cend to a prese lected altitude and then level off and maintain the preselected altitude The ASEL knob is used to set the altitude preselect function and also provides the altitude reference for the al titude alerter function The preselect altitude is annunciated by a magenta digital display at the top of the altitude tape on the PFD and by a magenta bug located on the left side of the altitude ta...

Page 474: ...of 9 The GA pitch attitude has no significance in relation to airplane performance It is strictly a pitch reference for takeoff or go around When selected GA is annunciated on the PFDs in the vertical mode area and ROL is annunciated in the lateral mode area GA is canceled with ASEL capture or by en gaging any other vertical mode It can also be canceled by depressing the TCS button Maximum Speed M...

Page 475: ...on The best position is used as the basis for the FMS com putations such as course bearing desired track distance estimated time enroute esti mate time of arrival wind speed and direction ground speed etc The FMS interfaces with the IC 600s for a transfer of information to the lateral and ver tical steering commands FMS FUNCTIONS FLP Flight Plan Before using the FMS for navigation an active flight...

Page 476: ...cal di rect to are included Holding Patterns The holding pattern definition page provides a graphic depiction of the holding pattern The pattern is defined with some crew input and when the ACTIVATE line select key is pressed the airplane will proceed from its present position directly to the fix and make the appropriate entry direct parallel or teardrop all automatically calculated and flown by t...

Page 477: ...l A switch is provided on the radar control panel for selecting the different radar modes OFF This position removes electrical power from the system SBY Standby When standby is selected the RTA is powered up but it does not radiate any RF energy nor does the antenna scan The system performs a warm up for approximately 45 seconds when SBY is selected The radar has a forced standby feature FSBY This...

Page 478: ...d the color scheme changes to cyan yellow and magenta Cyan represents the least reflective return yellow is a moderate return and magenta is a strong return LEARJET 45 PILOT TRAINING MANUAL 16 94 FOR TRAINING PURPOSES ONLY FlightSafety international STAB TGT WX 4 3 0 33 N 3 6 50 50 360 KDVT LL01 PBD01 PLAB1 TOC FL300 25 FMS1 KDVT 12 5 NM 12 MIN 300 TAS 15 SAT 245 GSPD 315 47 0 CHK EICAS MAG2 PLAB2...

Page 479: ...n The system is in the variable gain mode with the control knob pulled out and preset fixed gain with it pushed in The VAR legend is displayed when the system is in the variable gain mode Preset gain is the recommended setting for WX mode Gain fixed or variable does not an nunciate on the radar displays Engaging RCT or TGT overrides the variable gain selection and puts the system into the fixed ga...

Page 480: ...gets in the cyan field are displayed as 4th level pre cipitation magenta A RCT replaces the weather operating mode annunciation on the PFDs MFD radar displays when this mode is selected STAB This switch on the radar control panel is used to disable antenna stabilization from AHRS 1 When STAB is selected off the antenna stabi lization is disabled and an amber STAB is annunciated above the radar mod...

Page 481: ...en radar is not se lected for display on the PFDs MFD SECT Sector Scan The SECT pushbutton is used to select either the normal 14 looks per minute 120 scan or the faster update 28 looks per minute 60 scan When sector scan is selected the radar looks 30 from the airplane heading LEARJET 45 PILOT TRAINING MANUAL 16 97 FOR TRAINING PURPOSES ONLY FlightSafety international SELECTED RANGE NM TARGET DEP...

Page 482: ...ommands The pilot should not ma neuver the aircraft based on the traffic display only Pilots are authorized to deviate from their current ATC clearance to the extent nec essary to comply with a TCAS resolution ad visory RA With TCAS II installed the Learjet 45 will also be equipped with a Mode S ATC Transponder TCAS II is capable of generating a TA display of traffic from Mode A transponder equipp...

Page 483: ...al SYS MFD MENU WX CKLST PLAN MAP TCAS Honeywell Honeywell STAB TGT WX 4 315 47 0 3 0 33 N 3 6 50 50 360 KDVT LL01 PBD01 PLAB1 PLAB2 TOC FL300 25 FMS1 KDVT 12 5 NM 12 MIN CHK EICAS 300 TAS 15 SAT 245 GSPD 00 05 20 10 12 TCAS TEST ABV FL RA NO BRG TA NO BRG 6 Figure 16 54 TCAS Display on MFD ...

Page 484: ... WHITE TCAS FAIL AMBER TCAS OFF WHITE TA ONLY WHITE TCAS WHITE TCAS I MODE ANNUNCIATIONS TCAS TEST WHITE TCAS FAIL AMBER TCAS OFF WHITE TA ONLY WHITE RA SYMBOL OT SYMBOL AIRPLANE SYMBOL WHITE 2 NM RANGE RING WHITE TA SYMBOL PA SYMBOL TCAS ZOOM WINDOW DIM WHITE TCAS RANGE SCALE OFF SCALE INTRUDER BEZEL MENU DISPLAY AREA MAP PLAN DISPLAY AREA Figure 16 55 TCAS Annunciations Short Range ...

Page 485: ...12 0510 00 BEZEL MENU DISPLAY AREA MAP PLAN DISPLAY AREA ABOVE BELOW DISPLAY MODE ABV WHITE BLW WHITE ABSOLUTE ALTITUDE ANNUNCIATION WHITE TCAS SCALE HALF RANGE ARC RELATIVE ALTITUDE DISPLAY VERTICAL SENSE ARROW TCAS RANGE DIGITAL READOUT TA NO BEARING DISPLAY AMBER RA NO BEARING DISPLAY RED Figure 16 56 TCAS Annunciations Long Range ...

Page 486: ...ximity traffic are displayed When MANUAL mode is selected the TCAS bezel button on the MFD is alternately depressed to display and remove the TCAS display Range TCAS range is selected on the RMU main radio tuning page The TCAS window pro vides for annunciation and control of range and altitude band selection Placing the cursor over the RANGE field allows the operator to adjust the TCAS range displ...

Page 487: ...eporting altitude the traffic sym bol appears without an altitude tag or trend arrow A maximum of twelve 12 symbols can be dis played at one time including two without bearing Should TCAS direction finding techniques fail to determine the azimuth of an intruder a NO BEARING message is displayed in the top right corner of the TCAS display Figures 16 55 and 16 56 RA Displays The RA displays are inco...

Page 488: ...itor Vertical Speed Monitor Vertical Speed Monitor Vertical Speed Monitor Vertical Speed Descend Descend Descend Climb Crossing Climb Climb Crossing Climb Increase Climb Increase Climb Monitor Vertical Speed Monitor Vertical Speed N A N A N A N A Increase Descent Increase Descent Descend Descend NOW Descend Descend NOW Climb Climb NOW Climb Climb NOW CLIMB DESCEND CROSSOVER CLIMB CROSSOVER DESCEND...

Page 489: ... thermal switch If the tem perature reaches 158 5 F a white NOSE BAY TEMP CAS message will be displayed This message will remain on until the tem perature decreases to below 148 5 F The nose section avionics bay is cooled in flight by the air outflow from the pressurized section and is exhausted into the nose wheel well COCKPIT VOICE RECORDER CVR A Sundstrand solid state cockpit voice recorder is ...

Page 490: ... momentarily To set the clock to GMT or LT both the CTL and the SEL buttons must be pressed simulta neously The CTL button is then pressed to in crement the flashing digit to the desired value Pressing the SEL button enters the selected value and toggles to the next digit to be set The clocks receive 28 VDC power through the 1 amp L and R CLOCK circuit breakers located within the INSTRUMENT INDICA...

Page 491: ...s will be in red C A SPLIT annunciator will appear behind the navigation source annun ciator D There is no indication on the PFD 4 How is the backup navigation display se lected for display on either RMU A Depress the NAV button on the display controller B Depress the NAV MEMORY LSK on the RMU PAGE MENU C Depress the NAVIGATION LSK on the RMU PAGE MENU D It cannot be selected it only comes on auto...

Page 492: ...puter D All of the above 12 Which of the following statements is true regarding AHRS power source A Both systems can be powered from either Ess Bus B Both systems are powered from the Emer Batt Bus C Both systems are powered from the Ess Avionics Busses L R D Each system is powered by the on side L R Main Avionics Busses 13 AHRS failure would be indicated by A ATT Fail and HDG FAIL annuncia tors o...

Page 493: ...eter correction set A With the BARO set knob on DU2 B With the BARO set knob on DU1 C With the BARO set knob of DU4 D BARO correction can not be made on that PFD 20 The PFD navigation source is selected where A On the FGC panel B On the display controller panel C On the FMS NAV menu page D On the bezel controller 21 Which switch on the display controller is used to select LOC as the navigation sou...

Page 494: ...adar cooling fan is in standby C The radar is in forced standby and cannon be turned on while on the ground D The radar display on the MFD is in forced standby but can be selected for display on either PFD 29 Which of the following would discon nect the AP but not the YD A Depressing the AP engage button on the FGC panel B Depressing the arming button on the CWTS and moving the barrel in any direc...

Page 495: ...gen Storage Cylinder 17 1 Overboard Discharge Indicator 17 4 Oxygen System Indications 17 4 Crew Distribution System 17 6 Passenger Distribution System 17 10 Oxygen Duration 17 12 REVIEW QUESTIONS 17 13 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 496: ...ygen Masks 17 7 17 7 Crew Mask Storage Area 17 8 17 8 Audio Control Panel 17 8 17 9 Harness Inflation Tab 17 9 17 10 Crew Oxygen Mask In Place 17 9 17 11 Passenger Oxygen Mask 17 11 17 12 PAX OXYGEN and PRESSURIZATION Control Panel 17 11 TABLES Table Title Page 17 1 Oxygen System CAS Message Data Base 17 6 17 2 Oxygen Quantity Low Invalid CAS Message Data 17 6 17 3 Average Time of Useful Conscious...

Page 497: ...ned for use during an emer gency descent to an altitude that does not re quire oxygen The system is not intended for extended periods of use during flight at alti tudes requiring oxygen or as a substitute for the normal pressurization system Smoking is prohibited on the airplane whenever oxygen is in use by the crew or the passengers OXYGEN STORAGE CYLINDER The oxygen storage cylinder is located i...

Page 498: ...EGULATOR OXYGEN CYLINGER CHARGING VALVE CREW OXYGEN MASK CONNECTION PASSENGER OXYGEN OUTLET STANDARD ON 45 170 AND SUBSEQUENT OPTIONAL ON EARLIER AIRCRAFT PASSENGER OXYGEN MASK CONTAINER LAVATORY AREA PASSENGER OXYGEN MASK CONTAINER CABIN AREA CREW OXYGEN MASK CONNECTION OVERBOARD DISCHARGE INDICATOR OXYGEN CYLINDER SHUTOFF VALVE PAX OXYGEN CONTROL PANEL CPCS Figure 17 1 Oxygen System Diagram ...

Page 499: ...der a low pressure outlet a pressure transducer con nection temperature sensor high pressure re lief and low pressure relief Whenever the oxygen cylinder shutoff valve is open oxygen is only available to both crew masks Oxygen will not be available to pas senger masks unless selected by the crew or automatically if cabin pressure is lost Under normal conditions the shutoff valve should always rema...

Page 500: ... nose Figure 17 4A Also located in this compartment is an electrical remote reading oxygen pressure gage Located aft of the gage is a switch with a red guarded cover that is used to turn on power to the gage This power is supplied by a battery hot bus OVERBOARD DISCHARGE INDICATOR The overboard discharge indicator green blowout disk Figure 17 4B provides the crew with a visual indication that ther...

Page 501: ... in the Supplement section of the Flight Crew Checklist with oxygen quantity expressed in liters System Malfunction Displays On the EICAS and MFD displays as long as the oxygen system operates normally the cylinder quantity reports are displayed in white digits Since the oxygen cylinder is located in an unpressurized area of the airplane the nor mal operating pressure ranges are affected by temper...

Page 502: ...r controls oxygen flow to the mask and provides for normal 100 oxygen and emergency oper ation Figure 17 6 Each mask incorporates a microphone When the masks are donned and the MASK switch is out extended and the INPH switch is out extended the interphone is hot and the on side speaker is on even if the SPKR ON OFF switch is in the OFF de pressed position Both the Puritan Bennett and the Eros mask...

Page 503: ...TRAINING MANUAL FlightSafety international STOWAGE BOX OXYGEN MASK OXYGEN LINE LH SHOWN RH TYPICAL INFLATABLE HARNESS MASK MASK REGULATOR MICROPHONE LINE OXYGEN LINE Figure 17 6 Crew Oxygen Masks Eros Quick Don Mask Puritan Bennett Sweep On 2000 Mask ...

Page 504: ...MERGENCY button knob Figure 17 6 With the oxygen selector lever ex tended down and the PRESS TO TEST but ton knob rotated to the half dot position the mask delivers diluted oxygen from Sea Level to 30 000 feet cabin altitude 100 oxygen above 30 000 feet and automatic pressure breathing above approximately 37 000 feet The Eros regulator can be selected to deliver 100 oxygen at any altitude by depre...

Page 505: ...ith the palm of the hand against the regulator 3 Pull the assembly from its stowage con tainer 4 Place the thumb and middle fingers on the levers located on the levers located on opposite sides of the regulator 5 Depress and hold the red lever firmly to inflate the harness assembly 6 Place the harness assembly over the head Figure 17 10 7 Place the face seal over the nose and mouth 8 Release the r...

Page 506: ...ve This regulator reduces the oxygen flow to the passenger masks when at lower cabin altitudes This ef fectively increases the oxygen duration The AFM Checklist provides oxygen duration charts for modified and unmodified aircraft The checklist also provides tabular oxygen duration for flights above FL410 when one crewmember is wearing an oxygen mask and cabin pressure is normal This data is pro vi...

Page 507: ... PAX OXY AUTO switch is OFF The OFF annunciation in the PAX OXY AUTO switch would extinguish if the passenger oxy gen was manually deployed The passenger mask storage compartment doors are normally held closed with latches When oxygen is admitted to the passenger distribution system the oxygen pressure causes the door actuators plungers to push outward opening each compartment door When the doors ...

Page 508: ...are met See Airplane Flight Manual Section IV or Supplement section of the Crew Checklist for Oxygen Duration Charts Charts are provided for aircraft 45 170 and subsequent and some earlier modified aircraft that have the altitude compensating regulator installed as well as unmodified aircraft The pilot must remember that the crew and pas senger masks are not approved for use above 40 000 feet cabi...

Page 509: ...on control panel will A Open the passenger oxygen control valve B Deploy all of the passenger oxygen masks C Not provide oxygen flow to individ ual passenger masks until the attached mask lanyard is pulled D All of the above are true 4 If the oxygen cylinder shutoff valve was inadvertently left closed the crew would be alerted by A A maintenance technician B An OXYGEN OFF CAS message on the EICAS ...

Page 510: ...fold out pages at the beginning and end of the walkaround section should be unfolded before starting to read The general location photographs do not specify every checklist item However each item is portrayed on the large scale photographs that follow W 1 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 511: ...tandby Pitot Static Probes Covers removed and clear of obstructions Stall Warning Vane Freedom of movement and Static Air Temp Probe Check 1a Left Pitot Static Probe Cover removed and clear of obstructions Stall Warning Vane Freedom of movement and Ice Detect Probe Check LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 512: ...NLY FlightSafety international LEARJET 45 PILOT TRAINING MANUAL 3h AUX HYD Switch Off 3g SUMRY Page B ACUM Pressure 2610 3600 psi 3f AUX HYD Switch ON 3e Fuel Quantities Check 3d EMER BATT Switch EMER 3c L and R BATT Switches On ...

Page 513: ...b EMER BATT Switch OFF 12a Hydraulic Service Panel Check FILTER MAIN or AUX and RESERVOIR ADD or OVER lights not illuminated Access Panel Secure 3m Exterior Lighting Exterior Light Switches ON Check Illumination OFF 3k l AUX HYD Switch ON OFF 3j SUMRY Page B ACUM Pressure 1200 psi or greater 3i EMERGENCY PARKING BRAKE Set ...

Page 514: ...Safety international 5a Radome and Radome Erosion Shoe Condition 4d Ground Wire Disconnected 4c Nose Compartment Doors Wheel and Tire Condition and nose gear uplock forward 4b Gear and Wheel Well Hydraulic leakage condition and cooling vents clear 4a Windshield Condition ...

Page 515: ...nternational 6e Standby Pitot and Static Drains Push up to drain Required if moisture is known or suspected 6d Wing Inspection Light and Lens Condition 6c Nose Compartment Doors Secure 6b Oxygen System Discharge Indicator and Service Door Check and secure 6a Windshield Condition ...

Page 516: ...fety international 7a Emergency Exit Secure 7e Right Generator and Alternator Cooling Scoops Clear 7d Right Engine Inlet and Fan Clear of obstructions and condition 7b Upper Fuselage Antenna and Dorsal Inlets Condition 7c Upper Fuselage Gravity Fueling Door Check and secure ...

Page 517: ...ARJET 45 PILOT TRAINING MANUAL FlightSafety international 7h Toilet Servicing Door Secure 7g Fuel Drains and Access Door Drain if contamination is suspected and secure 7f Lower Fuselage Antennas Landing Light Fairing and Lens Condition ...

Page 518: ...L FlightSafety international 7i Right Main Gear 2 Taxi Light and Doors Condition 3 Wheels Brakes and Tires Condition 7i Right Main Gear 1 Wheel Well Hydraulic fuel leakage and condition 7i Right Main Gear 1 Wheel Well Hydraulic fuel leakage and condition Continued ...

Page 519: ... PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international 8a Right Wing 2 Access Panels Fuel Hydraulic leakage 8a Right Wing 1 Leading Edge Stall Strip Triangles Vortilons and Ice Detect Patch Condition ...

Page 520: ...EARJET 45 PILOT TRAINING MANUAL FlightSafety international 10a Right Aileron Check free motion balance tab linkage and brush seal condition 9b Ground Wire Disconnected 9a Right Winglet Navigation Light Lens and Static Wicks 4 Condition ...

Page 521: ...INING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international 11b Right Engine Oil Check oil level normal 11a Right Brakes and Brake Wear Indicators Condition 10b Right Spoiler and Flap Condition ...

Page 522: ...INING MANUAL FlightSafety international 13b Right Thrust Reverser Condition and completely stowed 13a Right Engine Turbine Exhaust Area Condition clear of obstructions 12b Fuel Quantity Panel Access Door Secure 12a Single point Fueling Access Door Secure ...

Page 523: ...ANUAL FlightSafety international 14a Tailcone Interior Open access Check for fluid leaks main engine fire bottle pressures APU fire bottle pressure security and condition of installed equipment remote circuit beakers set condition of door seal then close access ...

Page 524: ...tic Discharge Wicks 6 on elevators 1 above stinger and 4 on delta fins Condition 15a Vertical Stabilizer Rudder Horizontal Stabilizer Elevator Delta Fins and Logo Lights if installed Condition drain holes clear 14d APU Exhaust Clear of obstructions 14c Right VOR LOC Antenna Condition 14b Engine Fire Extinguisher Discharge Indicators Condition ...

Page 525: ...lightSafety international 16d Baggage Compartment Door Open 1 Baggage Heat Switch On as desired 2 Check condition of door seal then close 16c Battery Vents Clear 16b Left VOR LOC Antenna Condition 16a APU Inlet if installed Clear of obstructions 15d Tailstand Removed ...

Page 526: ...NG MANUAL FlightSafety international 18a Left Engine Oil Check oil level normal 17b Left Thrust Reverser Condition and completely stowed 17a Left Engine Turbine Exhaust Area Condition clear of obstructions 18b Left Brakes and Brake Wear Indicators Condition ...

Page 527: ...R TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international 19b Left Aileron Check free motion balance and trim tab linkage and brush seal condition 19a Left Spoiler and Flap Condition ...

Page 528: ...INING MANUAL FlightSafety international 20b Ground Wire Disconnected 20a Left Winglet Navigation Light Lens and Static Wicks 4 Condition 21a Left Wing Check 1 Leading Edge Stall Strip Triangles Vortilons and Ice Detect Patch Condition Continued next page ...

Page 529: ...ain Gear 1 Wheel Well Hydraulic fuel leakage and condition 22a Fuel Drains and Access Door Drain if contamination is suspected and secure 21a Left Wing Check 2 Access Panels Fuel Hydraulic leakage 21a Left Wing Check 1 Leading Edge Stall Strip Triangles Vortilons and Ice Detect Patch Condition Continued ...

Page 530: ... and Doors Condition 22c Left Engine Inlet and Fan Clear of obstructions and condition 22e Upper Fuselage Fuel Vent Inlet Clear of obstructions and condition 22b Left Main Gear 3 Wheels Brakes and Tires Check Condition 22b Left Main Gear 1 Wheel Well Hydraulic fuel leakage and condition Continued LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 531: ... conversion tables Table Title Page APP 1 Conversion Factors APP 1 APP 2 Fahrenheit and Celsius Temperature Conversion APP 2 Answers to Questions APP 3 Glossary APP 5 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international ...

Page 532: ...APP 1 FOR TRAINING PURPOSES ONLY LEARJET 45 PILOT TRAINING MANUAL FlightSafety international Table APP 1 CONVERSION FACTORS ...

Page 533: ...APP 2 FOR TRAINING PURPOSES ONLY L E A R J E T 4 5 P I L O T T R A I N I N G M A N U A L FlightSafety international Table APP 2 FAHRENHEIT AND CELSIUS TEMPERATURE CONVERSION ...

Page 534: ...D 8 B CHAPTER 5 1 B 2 D 3 D 4 D 5 A 6 D 7 D 8 A 9 C 10 D 11 B 12 B 13 C 14 B CHAPTER 6 1 B 2 A 3 B 4 C 5 C 6 B CHAPTER 7 1 D 2 A 3 C 4 A 5 D 6 B 7 B 8 C 9 B 10 D 11 D 12 C 13 D 14 C 15 D 16 D 17 B 18 D 19 C 20 D 21 B 22 C 23 D 24 C 25 B 26 A CHAPTER 8 1 B 2 A 3 D 4 D 5 C 6 D CHAPTER 9 1 D 2 D 3 C 4 A 5 A 6 A 7 B 8 D 9 D 10 A 11 D 12 D CHAPTER 10 1 C 2 B 3 D 4 A 5 B 6 C 7 A 8 C 9 D 10 D 11 D 12 D C...

Page 535: ...7 D 8 A 9 B 10 D CHAPTER 14 1 A 2 C 3 D 4 B 5 C 6 C 7 A 8 B 9 A 10 D 11 D 12 A 13 C 14 D 15 D 16 B CHAPTER 15 1 B 2 D 3 D 4 C 5 B 6 D 7 B 8 D 9 A 10 A 11 D 12 A 13 D 14 D 15 D 16 C 17 A 18 C 19 C CHAPTER 16 1 A 2 B 3 A 4 C 5 D 6 B 7 A 8 C 9 A 10 D 11 D 12 A 13 D 14 C 15 D 16 D 17 A 18 C 19 B 20 B 21 C 22 D 23 C 24 C 25 C 26 C 27 B 28 A 29 D 30 A CHAPTER 17 1 D 2 C 3 D 4 B 5 D 6 B 7 B ...

Page 536: ... BNK Bank BRG Bearing BSV Brake Shutoff Valve CAP Capture CAS Crew Alerting System CCW Counterclockwise CDH Clearance Delivery Head CDI Course Deviation Indicator CDU Control Display Unit CHK Check COM Communication CPC Cabin Pressure Controller CPCS Cabin Pressurization Control System CRS Course CVR Cockpit Voice Recorder CW Clockwise CWMS Control Wheel Master Switch CWP Crew Warning Panel CWTS C...

Page 537: ... High Speed Profile FLT Flight FMS Flight Management System FMS CDU Flight Management System Control Display Unit FPA Flight Path Angle FPL Flight Plan FPM Feet Per Minute FQF Fuel Quantity Fault CAS MSG FQSC Fuel Quantity Signal Conditioner FR From FSBY Forced Standby WX FWSOV Firewall Shutoff Valves GA Go Around GC Guidance Controller GCU Generator Control Unit GD Gear Down GMAP Groundmapping GP...

Page 538: ...C Master Caution MCR Maximum Recommended Cruise MCR Thrust Lever Position Maximum Cruise EI MCT Thrust Lever Position Maximum Continuous Thrust EI MDA Minimum Descent Altitude MEL Minimum Equipment List MMEL Master Minimum Equipment List MFD Multi Function Display MIC STK Stuck Microphone MIN Minimum MISCMP Miscompare MKR Marker MLS Microwave Landing System MM Middle Marker MPR Manual Power Reserv...

Page 539: ...ross Track Sync Synchronize T O Thrust Lever Position T O Thrust Setting EI TA Traffic Advisory TA RA Traffic Resolution Advisory TACAN Tactical Air Navigation TAS True Air Speed TAT Total Air Temperature TCAS Traffic Alert and Collision Avoidance System TCS Touch Control Steering TEMPS Temperatures TERM Terminal Area TGT Target TOC Top of Climb TOD Top of Descent TR Thrust Reversers TRK Track TST...

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Summary of Contents for LEARJET 45

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FlightSafety LEARJET 45, Pilot Training Manual, Page: 181 / 539

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Summary of Contents for LEARJET 45

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