learjet technical manual

7/27/2019 Learjet Technical Manual

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Learjet 35/36 Technical Manua

POWERPLANT 07/03 FOR TRAINING PURPOSES ONLY 2-5

Operational Theory and Engine Power Ratings

The power output of a jet engine, expressed in pounds of

thrust, is determined by the velocity to which it is capable of

accelerating a given mass of air. As a rule, a smaller volume of

air must be accelerated to a higher velocity than that required

to generate the same amount of thrust from a larger volume of

air.

In a turbojet engine, thrust is generated by compressing and

combusting the entire volume of inlet air, and discharging it

from the exhaust nozzle at high velocity. In a turbofan engine, a

portion of the thrust generated by compressing and combust-

ing a smaller volume of air (in the same manner as a turbojet

engine) is used to drive a fan which generates thrust from a

larger volume of air at a lower velocity. This is accomplished by

dividing inlet air drawn into the engine by the fan into primary

(inner) and secondary (outer) paths.

The primary path directs a smaller volume of air through the

engine core where it is compressed, combusted, and acceler-

ated to a higher velocity. In the TFE-731-2-2B, approximately

40% of this “core thrust” is used drive the compressors, fan,

and accessory gearbox, while the remaining 60% is dis-

charged from the inner exhaust nozzle.

The secondary path directs a larger volume of non-combustedair through a concentric bypass duct surrounding the engine

core and discharges it from the outer exhaust nozzle.

Thrust Ratio

Of the 3500 LBS thrust produced by each engine at sea level

and 22°C (72°F), approximately 2019 LBS (58%) is “bypass

thrust” generated by the fan, while 1481 LBS (42%) is gener-

ated by the core. However, because fan efficiency decreases

as altitude increases, the ratio of bypass thrust to core thrust

(thrust ratio) progressively reverses between sea level andapproximately 40,000' MSL.



FOR TRAINING PURPOSES ONLY LEARJET 35/36 CHAPTER 2 07/032-6

Bypass Ratio

The relationship between mass airflow through the bypass duct

and mass airflow through the engine core determines the

engine’s “bypass ratio.”

Of the total 114.0 LBS/SEC mass air flow (Wa) developed by

the fan, approximately 83.0 LBS/SEC is directed through the

bypass duct while approximately 31.0 LBS/SEC is directed

through the core, thereby producing the engine’s 2.73:1 bypass

ratio. Unlike thrust ratio, bypass ratio remains constant regard-

less of factors which influence air density such as altitude,

temperature, and airspeed.

REV. 01/05





LP Compressor Section

The LP compressor section primarily includes a four-stage,

axial-flow compressor and associated shrouds and stator

assemblies.

Each stage of the compressor forms a rotor consisting of an

inner disc with outward extending blades. The four rotors are

coupled together on the forward end of the N1 shaft and rotate

within the shrouds. Each stator assembly is located aft of its

associated rotor and consists of an outer ring with inward

extending vanes.

The shrouds and stator assemblies are fitted together and form

a core housing that establishes the engine’s inner gas path

profile. This core housing is located within an LP case assem-

bly attached to the aft end of the engine support housing.

Each rotor accelerates airflow by the convergent orientation of

its blades, thereby decreasing its pressure. Each stator assem-

bly decelerates airflow by the divergent orientation of its vanes,

thereby increasing its pressure. This process of acceleration

and deceleration effectively increases air pressure through

each stage of compression. Additionally, the diameter of the

rotors and core housing decreases with each stage, resulting in

further compression of core airflow.

The 4th stage stator assembly functions to direct LP compres-sor discharge air (P2.35) to the HP compressor section.

A compressor surge bleed valve, mounted at the 3 o’clock

position of the LP case assembly, functions to release LP com-

pressor discharge pressure (P2.35) under conditions that could

cause compressor stall or surge.

Compression ratio is 1.3:1 per stage, and the maximum LP

spool rotational speed is 20,688 RPM at 100% N1.

REV. 03/09




HP Compressor Section

The HP compressor section primarily includes a single-stage

centrifugal impeller, shroud, diffuser assembly, and deswirl

assembly.

The centrifugal impeller is coupled to the forward end of the N2

shaft and rotates within the shroud. The shroud is housed within

an HP diffuser case attached to the aft end of the LP case

assembly. The diffuser and deswirl assemblies are housed

within a combustion plenum attached to the aft end of the HP

diffuser case.

The impeller accelerates core airflow by centrifugal force

through the radial orientation of its vanes. The shroud contains

the accelerated core air and directs it radially outward to the

diffuser assembly. The diffuser assembly decelerates core

airflow, thereby maximizing HP compressor discharge pressure

(P3) and redirects this air axially to the deswirl assembly. The

deswirl assembly, through the angular orientation of its vanes,

functions to stabilize P3 airflow for delivery to the combustion

section.

Compression ratio is 3.5:1, and the maximum HP spool rota-

tional speed is 29,692 RPM at 100% N2.

Combustion Section

The combustion section primarily includes the combustor, fuelnozzles, and igniters.

The annular, reverse-flow combustor is installed within the

combustion plenum. The combustor consists of an aft “domed”

end from which concentric inner and outer liners (skirts) extend

forward to provide an area for the mixture and ignition of air and

fuel. Corresponding inner and outer transition liners are fitted to

the forward end of each skirt to direct combustion gas flow to

the turbines.

Twelve adapters are positioned around the aft outer skirt for

insertion of the fuel nozzles. Two adapters are positioned at 6

and 7 o’clock on the aft outer skirt for insertion of the spark

igniters.





Oil Pressure System

Engine oil pressure is developed by two pressure elements

integral to a pump assembly that also houses five scavenge

elements. The positive-displacement, gerotor-type pump as-

sembly is mounted on and shaft-driven by the accessory gear

box (AGB). From the tank, oil is drawn through a filter screen to

the inlet port of the pressure elements. Engine oil pressure

developed by these elements is routed through a pressure

regulator that is also integral to the pump assembly. Though

output varies with N2 shaft RPM, nominal pressure element

capacity is approximately 12 GPM at 125 PSI.

1

4

2

3

6

5

1. Oil Tank 4. Filter Bypass Indicator

2. Oil Pump Assembly 5. Supply to Pressure Elements

3. Oil Filter and Cap 6. Return from Scavenge Elements

Pressure Regulator

The pressure regulator functions primarily to maintain operat-

ing pressure between 40 and 45 PSI by diverting excess oil

back to the pressure element inlet. This is accomplished bya spring-loaded piston and pilot valve assembly that is

positioned by oil pressure sensed at the fan reduction gear-

box. With decreasing pressure, less oil is supplied to the

engine. With increasing pressure, more oil is supplied to the

engine.

REV. 03/09



FOR TRAINING PURPOSES ONLYPOWERPLANT 07/03

TFE731 Turbofan Engine

THE AIRPLANE IS POWERED

BY TWO TFE-731-2-2B

LIGHTWEIGHT, MEDIUM-

BYPASS, AXIAL-FLOW,TURBOFAN ENGINES

MANUFACTURED BY

HONEYWELL/GARRETT

AVIATION




Engine Fuel System

P3 AIR

LOW PRESSURE FUEL

HIGH PRESSURE PUMP OUTPUT

METERED FUEL

MECHANICAL LINK

FILTER BYPASS VALVE

P INDICATOR

FUEL FILTER

BOOST PUMP ELEMENT

HIGH PRESSUREPUMP ELEMENT

RELIEFVALVE

INLET FILTER

BYPASSVALVE

TORQUEMOTOR

PRESSUREGULAT

OVERBOARDDRAIN

GOVERNOR

MANUAL MODEADJUSTMENT

FUELINLET

FUEL INLETTEMPERATURE

PORT




Engine Lubrication

NO. 4 & NO. 5BEARING CAVITY

TRANSFER

GEARBOX ASSEMBLY

PLANETARY GEAR ASSY

NO. 1, 2, & 3BEARING

ACCESSORY DRIVE

GEARBOX ASSEMBLY

NO. 6 BEARINGSUMP

VENTBREATHER

PRESSURIZINGVALVE3.5 PSI

ANTI-SIPHONORIFICE

OIL TANK

P INDICATOR

FILTERBYPASSVALVE

FILTER

LUBE ANDSCAVENGEOIL PUMP

CHIP DETECTOR

AIR/OIL COOLER

BYPASS VALVE

TEMPERPRESSURE

OIL COOLER

HIGH PRESSURE OIL

SCAVENGE OIL

VENT LINE

OIL SUPPLY

CHECKVALVE



Learjet 35/36 Technical M


FAN

SPINNER

N1SHAFT

STATORS

SINGLE-STAGE

HP COMPRESSOR

(IMPELLER)

THREE-STAGE

LP TURBINE

COMBUSTOR

INNER EXHAUST

NOZZLE

BYPASS

DUCT

STATORS

FOUR-STAGE

LP COMPRESSOR

* A4 NOZZLE

** A5 NOZZLE

FUEL

NOZZLE

FUEL

DRAIN

SPARK IGNITOR

(6 AND 7 O'CLOCK)

ITT

PROBE

REDUCTION

GEARBOX

FAN

SHAFT

SINGLE-STAGE

HP TURBINE

* **

N2

SHAFT

Engine Air Flow



FOR TRAINING PURPOSES ONLYFIRE PROTECTION 07/03

Lear 35A/36A Engine Fire Extinguishing System

THERMAL DISCHARGEINDICATOR DISC

ENG FIRE

PULL

ARMED ARMED ARM

LEFT FIREEXTINGUISHER

BOTTLE

D

D

D

D

R R

RIGHT FIREEXTINGUISHER

BOTTLE

MANUAL DISCHARGEINDICATOR DISC

D

R

TW0-WAYCHECK VALVES

SHUTOFF VALVE

PRESSURE GAGE

DETONATOR CARTRIDGE

RELIEF VALVE

DISCHARGE

DIFFUSER

DISCHARGE

ORIFICE

LEFT ENGINENACELLE

ELECTRICAL CONNECTION




Motive-Flow Lockout Valves

On airplanes 35-058 and after, and 36-018 and after, a motive-

flow lockout valve prevents the flow of motive-flow fuel to the

motive-flow control valve and jet pumps during engine start.

The lockout valve is spring-loaded closed, and opened by fuel

pressure when the engine accelerates to approximately 45%

N2.

Jet Pump Operation

When the engines are operating and the motive-flow control

valves or lockout valves are open, motive-flow fuel from each

engine-driven pump is supplied to its associated jet pumps. As

this fuel enters each jet pump through its pressure inlet, pres-

sure is reduced by venturi effect thereby drawing fuel through

its suction inlet.

The pressure of motive-flow fuel supplied to the jet pumps

varies with engine fuel flow, and pressure altitude. With a fuel

flow rate of 1700 PPH at 45,000 feet pressure altitude, motive-

flow pressure is approximately 300 PSI. With a fuel flow rate of

150 PPH at sea level pressure altitude, motive-flow pressure is

approximately 250 PSI.

Similarly, jet pump output pressure varies with input pressure

between approximately 10 PSI at idle thrust (with 250 PSI input

pressure) and 12 PSI at maximum thrust (with 300 PSI input

pressure).

Check valves prevent reverse flow of jet pump output pressure

through the standby pumps when they are inoperative. A

standpipe is fitted to the transfer line from each tip tank jet

pump to prevent siphoning of wing tank fuel to the tip tank

when the associated engine is shutdown.

REV. 03/09



FOR TRAINING PURPOSES ONLYFUEL SYSTEM 07/03

Lear 35A Fuel Venting System

1.0 PSI

PRESSURERELIEF VALVE

1.5 PSIPRESSURE

RELIEF VALVE

VACUUMRELIEF VALVE

LEFTTIP TANK

VENTTUBE

TAILCONEASSEMBLY

HORIZONTALFIN

OVERBOARDVENT TUBE

VENTINTERCONNECT

LINE

VENTSCOOP

FLOATVALVE

FLOATVALVE




1.0 PSI

PRESSURERELIEF VALVE

1.5 PSIPRESSURE

RELIEF VALVE

VACUUM

RELIEF VALVE

LEFTTIP TANK

VENTTUBE

TAILCONEASSEMBLY

HORIZONTALFIN

OVERBOARDVENT TUBE

VENTINTERCONNECT

LINE

VENTSCOOP

FLOATVALVE

FLOATVALVE

Lear 36A Fuel Venting System




Lear 35A Fuel Distribution System (with FUS VALVE switch)

LEFTTIP TANK

FILLERPORT

TAILCONEASSEMBLY

HORIZONTALFIN

MOTIVE-FLOWLINE

JET PUMPOUPUT LINE

TRANSFERJET PUMP

D

TO FCU

STAN

ENG FIREPULL

L

L FUEL

PRESS

JE

L

TO EMPTYLIGHT

FUEL

XFLO

JETTISONTUBE

JETTISONVALVE

INTERCONNECTTUBES

FLAPPER-TYPECHECK VALVES

P

REFUEL/TRANSFERLINES

BYPASS VALVE& DIFF. PRESS.

SWITCH

FUELFILTER

TRANSFERVALVE

FUELSHUTOFF

VALVEMOTIVE-FLOW

CONTROLVALVE

LEFT STANDBYPUMP

P

DURINGXFER

D

CROSSFLOWVALVE

FUEL JTSN

ONL RTO RIGHTJETTISON

VALVE

LEFT WING FUEL

JET PUMP OUTPUT

RIGHT WING FUEL

FUSELAGE FUEL

ENGINE-DRIVEN FUEL PUMP OUTPUT

MOTIVE-FLOW FUEL

STANDBY PUMP OUTPUT

P

D

PRESSURE SWITCH

DRAIN VALVE

LEFTJET PUMP

LEFTWING TANK

D

FUSELAGPUMP

ENGINE-DRIVENFUEL PUMP

75 PSI RELIEF VALVE

D

*

FUSELAGETANK

D

* IF INSTALLED




Lear 36A Fuel Distribution System (with FUS VALVE switch)

LEFTTIP TANK

FILLERPORT

TAILCONEASSEMBLY

HORIZONTALFIN

MOTIVE-FLOWLINE

JET PUMPOUPUT LINE

TRANSFERJET PUMP

D

TO FCU

STAN

ENG FIREPULL

L

L FUEL

PRESS

JE

L

TO EMPTYLIGHT

FUEL

XFLO

JETTISONTUBE

JETTISONVALVE

INTERCONNECTTUBES


P


SWITCH

FUELFILTER

TRANSFERVALVE

FUELSHUTOFF

VALVEMOTIVE-FLOW

CONTROLVALVE

LEFT STANDBYPUMP

REFUEL/TRANSFERLINES

P

DURINGXFER

D

CROSSFLOWVALVE

FUEL JTSN


VALVE

LEFT WING FUEL

JET PUMP OUTPUT

RIGHT WING FUEL

FUSELAGE FUEL


MOTIVE-FLOW FUEL

STANDBY PUMP OUTPUT

P

D

PRESSURE SWITCH

DRAIN VALVE

LEFTJET PUMP

LEFTWING TANK

D

FUSELAGPUMP


75 PSI RELIEF VALVE

D

*

D

* IF INSTALLED




Lear 35A Fuel Distribution System (without FUS VALVE switch)

LEFTTIP TANK

FILLERPORT

TAILCONEASSEMBLY

HORIZONTALFIN

MOTIVE-FLOWLINE

JET PUMPOUPUT LINE

TRANSFERJET PUMP

TO FCU

STAN

ENG FIREPULL

L

L FUEL

PRESS

JE

L

FUEL

XFLO

JETTISONTUBE

JETTISONVALVE

INTERCONNECTTUBES



SWITCH

FUELFILTER

TRANSFERVALVE

FUELSHUTOFF

VALVEMOTIVE-FLOW

CONTROLVALVE

LEFT STANDBYPUMP

REFUEL/TRANSFERLINE

P

D

CROSSFLOWVALVE

FUEL JTSN


VALVE

LEFT WING FUEL

JET PUMP OUTPUT

RIGHT WING FUEL

FUSELAGE FUEL


MOTIVE-FLOW FUEL

STANDBY PUMP OUTPUT

P

D

PRESSURE SWITCH

DRAIN VALVE

LEFTJET PUMP

LEFTWING TANK

D

FUSELAGPUMP


75 PSI RELIEF VALVE

D

*

* IF INSTALLED

FUSELAGETANK

D

DURINGXFER




Lear 35A Fuel Quantity Indicating System

LEFTTIP TANK

P

LEFT WING FUEL

RIGHT WING FUEL

FUSELAGE FUEL

P

P P LWING

FUEL PROBES




ELECTRICAL SYSTEM 07/03 FOR TRAINING PURPOSES ONLY 5-29

BATTERY CHARGING BUS

CABIN CLIMATE

LH RECOG LTAIR COND CONTROL

FREON COMPRESSORCAMERAAUX INVERTERVOLTMETERRECOGNITION LIGHTHYD PUMPFUEL FLOWHOR STAB ACT

LEFT BATTERY BUS

L STALL WARNDOOR ACTUATORENTRY LIGHT

RIGHT BATTERY BUS

R STALL WARN

LEFT GEN BUS

L MAIN POWER BUSL ESS B BUSL ESS A BUS

L LDG LTPRI INV

RIGHT GEN BUS

SEC INVR LDG LT

R ESS A BUSR ESS B BUSR MAIN POWER BUS

LEFT MAIN POWER BUSL IGN START-GENL MAIN BUSPRI INV

RIGHT MAIN POWER BUS

SEC INVR MAIN BUSR IGN START-GEN

LEFT MAIN BUS

L LDG & TAXI LTNAV LTSSTROBE LTS

CABIN LTSFREON CONTROLCABIN BLOWERLH MOD VALVEAUTO CABIN HTNOSE STEERL NAC HTWSHLD HTSQUAT SWAIR DATA SENSORRDNG LTHEAT VALVE INDL DC FEEDERL TURB RPM

RIGHT MAIN BUS

STEREORECOG LTR LDG & TAXI LTBEACON LTSALC SYSSTAB & WING HEATBAT TEMPR NAC HEATFUS LG PUMPFILL & XFERR DC FEEDER BUSRH MOD VALVER TURB RPMCABIN TEMPANTI SKID

LEFT ESS A BUSRAM AIR TEMPAIR BLEEDFUEL COMPTRL FAN RPML ITTWARN LTSSTALL WARN HT

LEFT ESS B BUS

L AIR IGNL FIRE DETL FIRE EXT

L FIREWALL SOVL JET PUMP VALL STBY PUMPL ICE DETECTL PITOT HTPITCHROLLYAWPRI AFCS

AFCS PITCHAFCS ROLLAFCS YAW

OXYGEN VALINSTR LTSFUEL JTSNR FUS VAL

RIGHT ESS A BUS

STALL WARN HTSEC AFCSCAB PRESSWARN LTSSEC PITCH TRIMR FAN RPMR ITTR FIRE DETR FIRE EXTFUEL COMPTR

RIGHT ESS B BUS

SPOILERGEAR

FLAPSTAB & FLAPS PNFUEL QUANTITYOIL TEMPR ICE DETECTR STBY PUMPR JET PUMPR FIREWALL SOVR AIR IGNINSTR LTSR PITOT HTTEST SYSTEMFUEL JTSN

Bus Distribution Table

(35-509 and after, 36-054 and after, and earlier airplanes inc. AMK 85-1)

REV. 03/09




DC Power Indication

DC power indication is provided by a voltmeter and two amme-

ters located on the upper center instrument panel. Additional

indication is provided by annunciators located on the

glareshield panel.

1. DC Voltmeter

The DC voltmeter, labeled DC VOLTS, provides indication of

system voltage. The instrument dial is graduated in 2-volt incre-

ments between 0 and 34 VDC with numerical markings at each

10-volt increment between 0 and 30 VDC. A red line at 32 VDC

denotes the overvoltage warning range. Battery charging bus

power is supplied to the gage through a 5-amp current limiting

fuse.

2. DC Ammeters

Left and right ammeters, labeled AMPS, provide indication of

generator load and battery charging current. Each instrument

dial is graduated in 25-amp increments between 0 and 400-

amps with numerical markings at each 100-amp increment

between 0 and 400-amps. A yellow arc between 320 and 400-

amps denotes the generator overload caution range. A red line

at 400-amps denotes the generator overload warning range.

Note: Indicated load on either generator should not exceed

400-amps during flight or 320-amps during ground operation.

12 2



FOR TRAINING PURPOSES ONLYELECTRICAL SYSTEM 07/03

DC Electrical System (35-147 and earlier, and 36-035 and earlier)

L GEN. BUS

L GENRESETSWITCH

VOLTAGEREGULATORCONTROL

RELAY

LEFTGENERATOR

VOLTAGEREGULATOR

FL 4510A

L GENFIELD

275ACURRENTLIMITER

70-AMPOVERLOADSENSORL MAIN

BUSCB

LEFTFEEDER

BUSRELAY

2

L MAIN PWR. BUS

L IGN& STCB

7.5

FL 3510A

FL 1910A

FL 1

LEFT AMPS

BAT 1SWITCH

MAINBATTTERY 1

BAT 1RELAY

ON

OFF

START/GENSWITCH

L GEN

OFF

START

L FUELCONTROL

PANEL

L FUELCOMPUTER

FROMRIGHT MAIN

BUS

L BAT. BUS

BATT. CHG. BUS

L MAIN BUS R MAIN BUS7.5

MAINBUS TIE

CB

DC VOLTS

5A

LEFT GENERATORCONTROL CIRCUIT

LEFTSTARTERRELAYS

POWERRELAY

33 VDCCUTOUTCIRCUIT

EXTERNALPOWER

RECEPTACLE

CONTROLRELAY

5A

FL 1520A

LEFTSTARTER

ON

OFF

AMK 86-5*

*

FL 1750A

FL 250

L ESS. BUS R ESS. BUS7.5

ESSBUS TIE

CB

L ESSBUSCB

40

R ESSBUSCB

40




DC Electrical System (35-148~201, 35-205, and 36-036~040)

L GEN. BUS

L GENRESETSWITCH


RELAY

LEFTGENERATOR

VOLTAGEREGULATOR

FL 4510A

L GENFIELD

275ACURRENTLIMITER


BUSCB

LEFTFEEDER

BUSRELAY

2

L MAIN PWR. BUS

L IGN& STCB

7.5

FL 3510A

FL 1910A

FL 1

LEFT AMPS

BAT 1SWITCH

MAINBATTTERY 1

BAT 1RELAY

ON

OFF

START/GENSWITCH

L GEN

OFF

START

L FUELCONTROL

PANEL

L FUELCOMPUTER

L BAT. BUS

BATT. CHG. BUS


MAINBUS TIE

CB


LEFTSTARTERRELAYS

POWERRELAY

33 VDCCUTOUTCIRCUIT

EXTERNALPOWER

RECEPTACLE

CONTROLRELAY

5A

FL 1520A

LEFTSTARTER

ON

OFF

AMK 86-5*

*

DC VOLTS

5AFL 1750A

FL 250

L ESS. BUS R ESS. BUS7.5

ESSBUS TIE

CB

L ESSBUSCB

40

R ESSBUSCB

40




DC Electrical System (35-202~389 (exc. 205 & 370), and 36-041~047)

L GEN. BUS

L GENRESETSWITCH


RELAY

LEFTGENERATOR

VOLTAGEREGULATOR

FL 4510A

L GENFIELD

275ACURRENTLIMITER


BUSCB

LEFTFEEDER

BUSRELAY

2

L MAIN PWR. BUS

L IGN& STCB

7.5

FL 3510A

FL 1910A

FL 1

LEFT AMPS

BAT 1SWITCH

MAINBATTTERY 1

BAT 1RELAY

ON

OFF

START/GENSWITCH

L GEN

OFF

START

L FUELCONTROL

PANEL

L FUELCOMPUTER

L BAT. BUS

BATT. CHG. BUS


MAINBUS TIE

CB

L ESS. BUS B R ESS. BUS B7.5

ESS BBUS TIE

CB

DC VOLTS

5A


LEFTSTARTERRELAYS

POWERRELAY

33 VDCCUTOUTCIRCUIT

EXTERNALPOWER

RECEPTACLE

CONTROLRELAY

5A

FL 1520A

LEFTSTARTER

ON

OFF

AMK 86-5*

*

FL 5550A

FL 5650A

DC VOLTS

5AFL 1750A

FL 50

L ESS. BUS A R ESS. BUS A 7.5

ESS ABUS TIE

CB

L ESSA BUS

CB

40

R ESSA BUS

CB

40

L ESSB BUS

CB

40

R ESSB BUS

CB

40




DC Electrical System (35-370, 35-390~508, and 36-048~053)

L GEN. BUS

L GENRESETSWITCH


RELAY

LEFTGENERATOR

VOLTAGEREGULATOR

FL 4510A

L GENFIELD

275ACURRENTLIMITER


BUSCB

LEFTFEEDER

BUSRELAY

2

L MAIN PWR. BUS

L IGN

& STCB

7.5

FL 3510A

FL 1910A

FL 1

LEFT AMPS

BAT 1SWITCH

MAINBATTTERY 1

BAT 1RELAY

ON

OFF

START/GENSWITCH

L GEN

OFF

START

L FUELCONTROL

PANEL

L FUELCOMPUTER

L BAT. BUS

BATT. CHG. BUS


MAINBUS TIE

CB


ESS BBUS TIE

CB

DC VOLTS

5A


LEFTSTARTERRELAYS

POWERRELAY

33 VDCCUTOUTCIRCUIT

EXTERNAL

POWERRECEPTACLE

CONTROLRELAY

5A

FL 1520A

LEFTSTARTER

ON

OFF

AMK 86-5*

*

FL 5550A

FL 5650A

DC VOLTS

5AFL 1750A

FL5


ESS ABUS TIE

CB

L ESSA BUS

CB

40

R ESSA BUS

CB

40

L ESSB BUS

CB

40

R ESSB BUS

CB

40

TOCURRENT LIMITER

ANNUNCIATOR

**

L CUR. LIM.FAIL SENSOR

**




DC Electrical System (35-509 and after, and 36-054 and after)

L GEN. BUS

L GENRESETSWITCH


RELAY

LEFTGENERATOR

VOLTAGEREGULATOR

L GENFIELD

275ACURRENTLIMITER


BUSCB

LEFTFEEDER

BUSRELAY

2

L MAIN PWR. BUS

L IGN

& STCB

7.5

FL 3510A

FL 1910A

FL 1

LEFT AMPS

BAT 1SWITCH

MAINBATTTERY 1

BAT 1RELAY

ON

OFF

START/GENSWITCH

L GEN

OFF

START

L FUELCONTROL

PANEL

L FUELCOMPUTER

L BAT. BUS

BATT. CHG. BUS


MAINBUS TIE

CB


ESS BBUS TIE

CB

DC VOLTS

5A


275ACURRENTLIMITER

FL 2

LEFTSTARTERRELAYS

POWERRELAY

33 VDCCUTOUTCIRCUIT

EXTERNAL

POWERRECEPTACLE

CONTROLRELAY

5A

FL 1520A

LEFTSTARTER

ON

OFF

AMK 86-5*

*

FL 5550A

DC VOLTS

5AFL 1750A


ESS ABUS TIE

CB

L ESSA BUS

CB

40

R ESSA BUS

CB

40

L ESSB BUS

CB

40

R ESSB BUS

CB

40

TOCURRENT LIMITER

ANNUNCIATOR

**

L CUR. LIM.FAIL SENSOR

**

R CUR. LIM.FAIL SENSOR

2




AC Electrical System (standard configuration)

PRIINV

60-AMPOVERLOADSENSOR

PRI INVCB

POWERRELAY

26 VACBUSCB

26 VACAUTOTRANS-

FORMER

2

ON OFF

PRISWITCH

60OVERSEN

PORE

AC BUSTIECB

2

* *

R 115 VAC BUS

L ACBUSCB

10

PRIMARY 115VAC POWER

SECONDARY 115 VAC POWER

DC POWER

L 26 VAC BUS 2

PRIMARYINVERTER

INVERTER PARALLELING CONTROL BOX(IPCB)

L GEN. BUS

L 115 VAC BUS 7.5

AC

VOLTS

AC BUSSWITCH

PRI SEC

AC VOLTS

TO WINDSHIELDDEFOG SYSTEM

(35-0671 AND AFTER,AND 36-064 AND AFTER)

*




AC Electrical System (optional configuration)

AC

VOLTS

AC BUSSWITCH

PRI SEC

AC VOLTS

PRIINV


PRI INVCB

POWERRELAY

26 VACBUSCB

26 VACAUTOTRANS-

FORMER

2

ON OFF

PRISWITCH

AUXINV


AUX INVCB

POWERRELAY

2

ON

275-AMPCURRENTLIMITER

275-AMCURRELIMITE

AC BUSTIECB

2

* *

7.5

L AUXBUSCB

10 10R AUXBUSCB

R 115 VAC BUS

L ACBUSCB

10

L 115 VAC BUS

PRIMARY 115VAC POWER

SECONDARY 115 VAC POWER

AUXILIARY 115 VAC POWER

DC POWER

TO WINDSHIELDDEFOG SYSTEM

(35-0671 AND AFTER,AND 36-064 AND AFTER)

*

L 26 VAC BUS 2

AUXILIARYINVERTER

PRIMARYINVERTER

INVERTER PARALLELING CONTROL BOX(IPCB)

L

OFF

AUX INVSWIT

BAT. CHG. BUSL GEN. BUS



FOR TRAINING PURPOSES ONLYHYDRAULIC SYSTEM 07/03

Hydraulic System

MAIN SYSTEM PROVIDES HYDRAULICPRESSURE FOR OPERATION OF THEFOLLOWING ITEMS:

¡ LANDING GEAR

¡ WHEEL BRAKES

¡ FLAPS

¡ SPOILERS

¡ THRUST REVERSERS

ENG FIREPULL

SPOILERSYSTEM

INBOAGEA

SELECT

FLAPSYSTEM

HYDACCUM

ACCUMPRES

GA

AUXHYD

P

SIGHTGLASS

SUPPLYPRESSURE

GAGE

LEFTHYDRAULIC

SUPPLYSHUTOFF

VALVE

20 PSIPRESSURE

RELIEF VALVE

VACUUMRELIEF VALVE

LEFTENGINE-DRIVEN

HYDRAULICPUMP

PUMP SUCTION

AMBIENT

PUMP PRESSURE

RETURN LINE

RESERVOIR PRESSURIZATION AIR

NOSE GEAR DOWN PRESSURE

F FILTER

* IF INSTALLED

NITROGEN GAS



FOR TRAINING PURPOSES ONLYLANDING GEAR & BRAKES 07/03

Landing Gear Installation

TORQUE LINKS

SHOCK STRUT

FORWARDTRUNNIONFITTING

FORWARDTRUNNION

MAIN GEAR

PISTON

BRAKE PRESSURELINES




8-BFOR TRAINING PURPOSES ONLYLANDING GEAR & BRAKES 07/03

Landing Gear Control Circuit

G E A R - D O W N

S A F E T Y S W I T C H

( R I G H T G E A R

O N L Y )

L E F T

S Q U A T

S W I T C H

R I G H T

S Q U A T

S W I T C H

L A N D I N G G E A R

S E L E C T O R V A L V E

L E F T

D O O R - D O W N

S W I T C H

R I G H T

D O O R - D O W N

S W I T C H

O P E N

C L O S E

D O W N

U P

( 3 5 - 2 0 1 A N D E A R L I E R , 3 5 - 2 0 5 ,

A N D 3 6 - 0 4 0 A N D E A R L I E R )

( 3 5 - 2 0 2 A N D A F T E R ( E X C 3 5 - 2 0 5 ) , 3 6 - 0 4 1 A N D

A F T E R ,

A N D E A R L I E R A I R P L A N E S I N C A M K - 7 8 - 1 3 )

R E

S S .

B U S

R E

S S .

" B " B U S

G E A R

C B

L A N D I N G G E A R

S E L E C T O R

S W I T C H

U P

D N

O P E N

C L O S E

D O W N

U P

G R O U N D

A I R

G R O U N D

A I R

U P

U P

D O W N

D O O R C O N T R O L

V A L V E

U P

D N

L E F T

G E A R - U P


L E F T

D O W N - A N D - L O C K E D

S W I T C H

R I G H T

G E A R - U P


R I G H T

D O W N - A N D - L O C K E D

S W I T C H

D O W N




Landing Gear System

DOORUPLOCK

ACTUATOR

EMERGENCYAIR BOTTLE

RELIEFVALVE

OVERBOARDVENT

CHARGINGVALVE

EMERGENCY

AIR

T-CHECKVALVE

RESTRICTOR

SHUTTLE VALVE

GEAR EXTENDED,

DOORS OPENING

LANDING

GEAR

TEST

MUTE

LOCKED DNUNSAFE

BRTUP

DN

EMER. GEAR EXT.

PULL GEAR C/B

PUSH LEVER DN

UPLOCKHOOK

NOSE GEAR ASSEMBLY

UPLOCKACTUATOR

RIGHT MAINGEAR ASSEMBLY

RELEASETAB

GEAR-UPSAFETYSWITCH

GEAR-DOWNSAFETY SWITCH

DOOR-DOWNSWITCH

INBOARDDOOR

OUTBOARDDOOR

STRIKER

ROLLER/CAMASSEMBLY

GEARACTUATOR

UPLOCKACTUATOR

DOWN-AND-LOCKEDSWITCH

DOOROPERATING

LINKAGE

NOSE GEARDOORS

UP-AND-LOCKEDSWITCH

INBOARD DOORACTUATORS

ROLLER

LEFT MAINGEAR ASSEMBLY

GEARACTUATOR


UPLOCKHOOK

DOOR-UPSWITCH

UPLOCKACTUATOR

GEAR-UPSAFETYSWITCH

DOOR-DOWNSWITCH

INBOARDDOOR

OUTBOARDDOOR

STRIKER

ROLLER/CAMASSEMBLY

GEARACTUATOR


UPLOCKHOOK

DOOR-UPSWITCH




DOORUPLOCK

ACTUATOR

EMERGENCYAIR BOTTLE

RELIEFVALVE

OVERBOARDVENT

CHARGINGVALVE

EMERGENCY

AIR

T-CHECKVALVE

RESTRICTOR

SHUTTLE VALVE

Landing Gear System

DOORS OPEN,

GEAR

RETRACTING

LANDING

GEAR

TEST

MUTE

LOCKED DNUNSAFE

BRTUP

DN

EMER. GEAR EXT.

PULL GEAR C/B

PUSH LEVER DN

UPLOCKHOOK

NOSE GEAR ASSEMBLY

RELEASETAB

GEARACTUATOR

UPLOCKACTUATOR


DOOROPERATING

LINKAGE

NOSE GEARDOORS

UP-AND-LOCKEDSWITCH

ROLLER

UPLOCKACTUATOR

GEARACTUATOR

UPLOCK

HOOKS


GEAR-UPSAFETYSWITCH


DOOR-UPSWITCHES

DOOR-DOWNSWITCH

INBOARDDOORS

OUTBOARDDOOR

STRIKER

ROLLER/CAMASSEMBLY



UPLOCKACTUATOR

GEARACTUATOR


GEAR-UPSAFETYSWITCH

DOOR-DOWNSWITCH

OUTBOARDDOOR

STRIKER

ROLLER/CAMASSEMBLY





DOORUPLOCK

ACTUATOR

EMERGENCYAIR BOTTLE

RELIEFVALVE

OVERBOARDVENT

CHARGINGVALVE

EMERGENCY

AIR

T-CHECKVALVE

RESTRICTOR

SHUTTLE VALVE

LANDING

GEAR

TEST

MUTE

LOCKED DNUNSAFE

BRTUP

DN

EMER. GEAR EXT.

PULL GEAR C/B

PUSH LEVER DN

UPLOCKHOOK

NOSE GEAR ASSEMBLY

UPLOCKACTUATOR

GEARACTUATOR

UPLOCKHOOK


RELEASETAB

GEAR-UPSAFETYSWITCH


DOOR-UPSWITCH

DOOR-DOWNSWITCH

INBOARDDOOR

OUTBOARDDOOR

STRIKER

ROLLER/CAMASSEMBLY


GEARACTUATOR

UPLOCKACTUATOR


ROLLER

DOOROPERATING

LINKAGE

NOSE GEARDOORS

UP-AND-LOCKEDSWITCH

UPLOCKACTUATOR

GEARACTUATOR

UPLOCKHOOK


GEAR-UPSAFETYSWITCH

DOOR-UPSWITCH

DOOR-DOWNSWITCH

INBOARDDOOR

OUTBOARDDOOR

STRIKER

ROLLER/CAMASSEMBLY



Landing Gear System

GEAR

RETRACTED,

DOORS CLOSING




LANDING

GEAR

TEST

MUTE

LOCKED DNUNSAFE

BRTUP

DN

EMER. GEAR EXT.

PULL GEAR C/B

PUSH LEVER DN

UPLOCKHOOK

NOSE GEAR ASSEMBLY

UPLOCKACTUATOR

GEARACTUATOR

UPLOCKHOOK


RELEASETAB

GEAR-UPSAFETYSWITCH


DOOR-UPSWITCH

DOOR-DOWNSWITCH

INBOARDDOORS

OUTBOARDDOOR

STRIKER

ROLLER/CAMASSEMBLY


GEARACTUATOR

UPLOCKACTUATOR


ROLLER

DOOROPERATING

LINKAGE

NOSE GEARDOORS

UP-AND-LOCKEDSWITCH

UPLOCKACTUATOR

GEARACTUATOR


UPLOCKHOOK


GEAR-UPSAFETYSWITCH

DOOR-UPSWITCH

DOOR-DOWNSWITCH

OUTBOARDDOOR

STRIKER

ROLLER/CAMASSEMBLY


DOORUPLOCK

ACTUATOR

EMERGENCYAIR BOTTLE

RELIEFVALVE

OVERBOARDVENT

CHARGINGVALVE

EMERGENCY

AIR

T-CHECKVALVE

RESTRICTOR

SHUTTLE VALVE

Landing Gear System

GEAR

RETRACTED,

DOORS CLOSED




LANDING

GEAR

TEST

MUTE

LOCKED DNUNSAFE

BRTUP

DN

EMER. GEAR EXT.

PULL GEAR C/B

PUSH LEVER DN

UPLOCKHOOK

NOSE GEAR ASSEMBLY

UPLOCKACTUATOR

GEARACTUATOR

UPLOCKHOOK


RELEASETAB

GEAR-UPSAFETYSWITCH


DOOR-UPSWITCH

DOOR-DOWNSWITCH

INBOARDDOOR

OUTBOARDDOOR

STRIKER

ROLLER/CAMASSEMBLY


GEARACTUATOR

UPLOCKACTUATOR


ROLLER

DOOROPERATING

LINKAGE

NOSE GEARDOORS

UP-AND-LOCKEDSWITCH



UPLOCKACTUATOR

GEARACTUATOR

UPLOCKHOOK

GEAR-UPSAFETYSWITCH

DOOR-UPSWITCH

DOOR-DOWNSWITCH

INBOARDDOOR

OUTBOARDDOOR

STRIKER

ROLLER/CAMASSEMBLY


DOORUPLOCK

ACTUATOR

EMERGENCYAIR BOTTLE

RELIEFVALVE

OVERBOARDVENT

CHARGINGVALVE

EMERGENCY

AIR

T-CHECKVALVE

RESTRICTOR

SHUTTLE VALVE

Landing Gear System

GEAR

RETRACTED,

DOORS OPENING




LANDING

GEAR

TEST

MUTE

LOCKED DNUNSAFE

BRTUP

DN

EMER. GEAR EXT.

PULL GEAR C/B

PUSH LEVER DN

UPLOCKHOOK

NOSE GEAR ASSEMBLY

UPLOCKACTUATOR

GEARACTUATOR

UPLOCK

HOOKS


RELEASETAB

GEAR-UPSAFETYSWITCH


DOOR-UPSWITCHES

DOOR-DOWNSWITCH

INBOARDDOORS

OUTBOARDDOOR

STRIKER

ROLLER/CAMASSEMBLY


GEARACTUATOR

UPLOCKACTUATOR


DOOROPERATING

LINKAGE

NOSE GEARDOORS

UP-AND-LOCKEDSWITCH


ROLLER

UPLOCKACTUATOR

GEARACTUATOR


GEAR-UPSAFETYSWITCH

DOOR-DOWNSWITCH

OUTBOARDDOOR

STRIKER

ROLLER/CAMASSEMBLY


DOORUPLOCK

ACTUATOR

EMERGENCYAIR BOTTLE

RELIEFVALVE

OVERBOARDVENT

CHARGINGVALVE

EMERGENCY

AIR

T-CHECKVALVE

RESTRICTOR

SHUTTLE VALVE

Landing Gear System

DOORS OPEN,

GEAR

EXTENDING




DOORUPLOCK

ACTUATOR

EMERGENCYAIR BOTTLE

RELIEFVALVE

OVERBOARDVENT

CHARGINGVALVE

EMERGENCY

AIR

T-CHECKVALVE

RESTRICTOR

SHUTTLE VALVE

LANDING

GEAR

TEST

MUTE

LOCKED DNUNSAFE

BRTUP

DN

EMER. GEAR EXT.

PULL GEAR C/B

PUSH LEVER DN

UPLOCKHOOK

NOSE GEAR ASSEMBLY

UPLOCKACTUATOR


RELEASETAB

GEAR-UPSAFETYSWITCH


DOOR-DOWNSWITCH

INBOARDDOOR

OUTBOARDDOOR

STRIKER

ROLLER/CAMASSEMBLY

GEARACTUATOR

UPLOCKACTUATOR


DOOROPERATING

LINKAGE

NOSE GEARDOORS

UP-AND-LOCKEDSWITCH


ROLLER


GEARACTUATOR


UPLOCKHOOK

DOOR-UPSWITCH

UPLOCKACTUATOR

GEAR-UPSAFETYSWITCH

DOOR-DOWNSWITCH

INBOARDDOOR

OUTBOARDDOOR

STRIKER

ROLLER/CAMASSEMBLY

GEARACTUATOR


UPLOCKHOOK

DOOR-UPSWITCH

Landing Gear System

GEAR

EXTENDED,

DOORS

CLOSING




LANDING

GEAR

TEST

MUTE

LOCKED DNUNSAFE

BRTUP

DN

EMER. GEAR EXT.

PULL GEAR C/B

PUSH LEVER DN

UPLOCKHOOK

NOSE GEAR ASSEMBLY

UPLOCKACTUATOR


RELEASETAB

GEAR-UPSAFETYSWITCH


DOOR-DOWNSWITCH

OUTBOARDDOOR

STRIKER

GEARACTUATOR

UPLOCKACTUATOR


DOOROPERATING

LINKAGE

NOSE GEARDOORS

UP-AND-LOCKEDSWITCH

ROLLER


GEARACTUATOR

UPLOCKACTUATOR

GEAR-UPSAFETYSWITCH

DOOR-DOWNSWITCH

OUTBOARDDOOR

STRIKER

ROLLER/CAMASSEMBLY

GEARACTUATOR

DOOR-UPSWITCH

INBOARDDOORS


UPLOCKHOOK

DOOR-UPSWITCH



ROLLER/CAMASSEMBLY

UPLOCKHOOK

DOORUPLOCK

ACTUATOR

EMERGENCYAIR BOTTLE

RELIEFVALVE

OVERBOARDVENT

CHARGINGVALVE

EMERGENCY

AIR

T-CHECKVALVE

RESTRICTOR

SHUTTLE VALVE

Landing Gear System

GEAR

EXTENDED,

DOORS

CLOSED




Landing Gear System

EMERGENCY

EXTENSION

NOSE GEARUPLOCK

ACTUATOR

DOORUPLOCK

ACTUATOR

LEFT INBOARDMAIN GEAR DOOR

ACTUATOR

RIGHT INBOMAIN GEAR

ACTUATO

LEFT

MAIN GEARACTUATOR

RIGHT

MAIN GEACTUATO

LANDING GEARSELECTOR

VALVE

DOORCONTROL

VALVE

RETURN TORESERVOIR

EMERGENCYAIR BOTTLE

RELIEFVALVE

EMERGENCYBRAKE VALVE

EMERGENCYGEAR VALVE

OVERBOARDVENT

OVERBOARDVENT

TOWHEEL BRAKES

CHARGINGVALVE

EMERGENCY

AIR

T-CHECKVALVE

RESTRICTOR

SHUTTLE VALVEHYDRAULICPRESSURE

HYPR

DOWNSOLENOIDENERGIZED

DOWNSOLENOIDENERGIZED




Wheel Brakes (pilot's brakes applied)

SHUTTLE VALVE

LEFTBRAKE

ASSEMBLIES

OUTBOARD

BRAKEDISCS

HYDRAULICFUSE

PILOT'SPOWER BRAKE

VALVES(OPEN)

INBOARD

LEFTANTI-SKID

VALVE

PARKBRAKE

ANTI-SKIDGEN

LEFTSQUATSWITCHDRIVE

CAP

OUTBOARDSERVO VALVE

INBOARDSERVO VALVE

SHUTOFFVALVE

GROUND

AIR

PARKINGBRAKE VALVE

RIGHTANTI-SKID

VALVE

RIGHTSQUATSWITCH

GRO

A

P

A

R

K

IN

G

B

R

A

K

E

EMERGBRAKELEVER

PARKINGBRAKE

HANDLE(PUSHED IN)

FROMEMERGENCYAIR BOTTLE

COPILOT'SPOWER BRAKE

VALVES(CLOSED)

EMERGENCYBRAKEVALVE

PARKINGBRAKE VALVE

INBOARDSERVO VALVE

SHUTOFFVALVE

MECHANICAL CONNECTION


RETURN LINES

STATIC/TRAPPED FLUID

PNEUMATIC BRAKE LINES

HYDRAULIC BRAKE LINES

ANTI-SKIDCONTROL BOX



FOR TRAINING PURPOSES ONLYFLIGHT CONTROLS 07/03

AUTOPILOT ROLL SERVO

SERVOACTUATOR

SERVO CABLES

CABLE CLAMP

AILERON CABLES

RUDDER CABLES

MOUNTINGPLATE

Ailerons

CONTROL COLUMNSHAKER

TURNBUCKLEACCESS COVER

COPILOT'SCONTROL WHEEL

PILOT'SCONTROL WHEEL

CONTROL COLUMN

AILERON/RUDDERINTERCONNECT

PRESSURESEAL

AS

RIGHT WINGAILERON CABLE

AILERON SECTOR

AI

FUSELAGECABLES




.FORWARD ELEVATORSECTOR

Elevators

AUTOPILOT

PITCH SERVO

AFT ELEVATOR

SECTOR

DOWNASSE

ELEVATO

BELCRAN




Rudder

S

PRIMARY YAW AXISSERVO

SECONDARYAUTO-FLIGHT

SERVO

RUDDER SERVO SECTOR

SERVO SECTOR

RUDDER PEDAL BELLCRANK

RUDDER PEDAL SECTOR

PUSH-PULL TUBES TOTORQUE TUBE ARM

TURNBUCKLE TOCONTROL CABLE

RUDDER PEDALS

RUDDER PEDAL

TORQUETUBE ARM

BRAKELEVER

BRAKE FLUID VALVE




Wing Flaps

FLAP CONTROL VALVE

RESTRICTOR

CHECK VALVE

FLAP

RET

P

PUSH-PULL

TUBESECTOR




Wing Flap System (35-059 and earlier, 36-017 and earlier)

RETURN TORESERVOIR

RESTRICTOR

HYDRAULICPRESSURE

INTERCONNECTCABLES

LEFT FLAPACTUATOR

LEFT FLAPSECTOR

LEFT FLAP

FLAPCONTROL

VALVE

FROM FLAPLEVER/CONTROLCIRCUIT DURING

RETRACTION

RETRACTSOLENOID

(DEENERGIZED)

FROM FLAPLEVER/CONTRCIRCUIT DURI

EXTENSION

EXTENDCIRCUIT

RETRACTCIRCUIT

RIGHT PUSH-P

TUB

LEFT FLAPPUSH-PULL

TUBE

POTENTIOMETER

UP

8°

20°

30°

DN

F

L

A

P

FLAPPOSITIONINDICATOR

SOLENO

FLAPLOAD-LIMITING

VALVE

FLAPS

EXTENDING




Wing Flap System (35-060 and after, 36-018 and after)

FLAPS

EXTENDING

RETURN TORESERVOIR

RESTRICTOR

HYDRAULICPRESSURE

INTERCONNECTCABLES

LEFT FLAPACTUATOR

LEFT FLAPSECTOR

LEFT FLAP

FLAPCONTROL

VALVE

FROM FLAPLEVER/CONTROLCIRCUIT DURING

RETRACTION

RETRACTSOLENOID

(DEENERGIZED)

FROM FLAPLEVER/CONTRCIRCUIT DURI

EXTENSION

EXTENDCIRCUIT

RETRACTCIRCUIT

RIGHT PUSH-P

TUB

LEFT FLAPPUSH-PULL

TUBE

POTENTIOMETER

UP

8°

20°

30°

DN

F

L

A

P

FLAPPOSITIONINDICATOR




Spoiler System

SPOILER

MODE,

EXTENDING

OFFLEFT SPOILER

ACTUATOR

LEFT SPOILERFOLLOW-UP

RIGHT SPOILERFOLLOW-UP

LEFTSERVO VALVE(ENERGIZED)

RIGHT AILERONFOLLOW-UP

INPUT SIGNAL

FLAPSBEYOND 25°INPUT SIGNAL

LEFT AILERONFOLLOW-UP

INPUT SIGNAL


LEFT SPOILERFULLY RETRACTED

INPUT SIGNAL

RIGHT SPOILERFULLY RETRACTED

INPUT SIGNAL

SPOILERONRESET

EXT

RET SPOILER

SPOILERONCB R

R E

RESTRICTORBYPASS VALVE(ENERGIZED)

PUMP PRESSURE

RETURN FLOW



DC POWER

AC POWER

CONTROL CURRENT


R 115 VAC BUS

SPOILERCB

SPOILERCOMPUTER-AMPLIFIER

RELIEF VALVE(CLOSED)

LEFT SPOILER

SPOILER AUG AIL




Spoiler System

SPOILERON

MODE,

RIGHT

SPOILER

EXTENDING

OFFLEFT SPOILER

ACTUATOR

LEFT SPOILERFOLLOW-UP

RIGHT SPOILERFOLLOW-UP

LEFTSERVO VALVE(ENERGIZED)

RIGHT AILERONFOLLOW-UP

INPUT SIGNAL


LEFT AILERONFOLLOW-UP

INPUT SIGNAL


LEFT SPOILERFULLY RETRACTED

INPUT SIGNAL

RIGHT SPOILERFULLY RETRACTED

INPUT SIGNAL

SPOILERONRESET

EXT

RET SPOILER

SPOILERONCB R

R E

RESTRICTORBYPASS VALVE(ENERGIZED)

PUMP PRESSURE

RETURN FLOW



DC POWER

AC POWER

CONTROL CURRENT


R 115 VAC BUS

SPOILERCB

SPOILERCOMPUTER-AMPLIFIER

RELIEF VALVE(CLOSED)

SPOILER AUG AIL

LEFT SPOILER




9-IFOR TRAINING PURPOSES ONLYFLIGHT CONTROLS 07/03

Stall Warning System

N U D G E R

W A R

N I N G H O R N

R I G H T

S H A K E R

L E F T F L A P

P O S I T I O N S W I T C H

P I L O T

' S A I R S P E E D /

M A C H I N D I C A T O R

( A L T I T U D E S W I T C H )

C O P I L O T ' S A I R S P E E D /

M A C H I N D I C A T O R

( A L T I T U D E S W I T C H )

L E F T S T A L L

W A R N I N G V A N E

L S T A L L

A N N U N C I A T O R

P I L O T ' S

A N G L E - O F - A T T A C K

I N D I C A T O R

R I G H

T F L A P

P O S I T I O

N S W I T C H

R I G H T S T A L L

W A R N I N G V A N E

R S T A L L

A N N U N C I A T O R

C O P I L O T ' S

A N G L E - O F - A T T A C K

I N D I C A T O R

A U T O P I L O T

C O M P U T E R S

L E F T

S H A K E R

A C C E L E R O M E T E R

( . 5 G L I M I T )

A U T O P I L O T

E L E C T R I C B O X

( N U D G E R C O N T R O L &

M O N I T O R C I R C U I T S )

E L E V A T O R

S E R V O

( N U D G E R & P U S H E R )

R I G H T C H A N N E L

* *

*

* A i r p l a n e s e q u i p p e d w i t h F C - 5 3 0 a u t o p i l o t

L E F T C H A N N E L

G C O M P U T E R

S T A

L L W A R N I N



FOR TRAINING PURPOSES ONLYFLIGHT INSTRUMENTAT ION/AVIONICS 07/03

Pitot-Static System (FC-200)

LEFT AFTINSTRUMENTSTATIC PORT

LEFTPITOT HEAD

D

PILOT'S STATIC PR

PILOT'S

ALTIMETER

PILOT'S

IVSI

COPILOT'S

AIRSPEED

INDICATOR

LEFT FWDINSTRUMENTSTATIC PORT

D

PILOT'S

AIRSPEED

INDICATOR

MACH/OVSPSWITCH

MACH TRIMSWITCH

ALTERNATEINSTRUMENT

STATIC SOURCE

ALTERNATESTATIC SOURCE

VALVE

COPILOT'S STATIC

COPILOT'S PITOT P

PILOT'S PITOT PRE

ALTITUDEPRESSURE

SWITCH

D

STALL WARNALTITUDE SW

AIR DATASENSOR

LEFTSHOULDER

STATIC PORT

RIGHTSHOULDER

STATIC PORT

*

AIRPLANREDUCE

*

SDCMODULE

ALTITUDEALERTER



FOR TRAINING PURPOSES ONLYFLIGHT INSTRUMENTAT ION/AVIONICS 07/03

Pitot-Static System (FC-530)

LEFTPITOT-STATIC

PROBE

D

PILOT'S STATIC PRESSUR

PILOT'S

ALTIMETER

PILOT'S

IVSI

D

PILOT'S

AIRSPEED

INDICATOR

COPILOT'S PITOT PRESS

PILOT'S PITOT PRESSURE

AIR DATAUNIT

.74 MACHSWITCH

L MAIN BUS

STATICSOURCE

CB

7.5

STATICSOURCESWITCH

L R

BOTH

COPILOT'S

AIRSPEED

INDICATOR

COPILOT'S STATIC PRESS



FOR TRAINING PURPOSES ONLYPNEUMATIC SYSTEM 07/03

Pneumatic System (35-086 and earlier (exc. 082), and 36-022 and earlier)

LEFT ENGINE

SHUTOFF ANDPRESS. REG.

VALVE

NACELLEHEATVALVE


VALVE

FLOWCONTROL

VALVE

PNEUMATICSENSELINES

VENTURI

HOT AIRBYPASS VALVE

(H VALVE)

HEATEXCHANGER

DUCT

HEATEXCHANGER

HEATEXCHANGER

OUTLET

RAM AIRFR0M DORSAL

INLETHP BLEED AIR

PORT

TO INLET LIPDIFFUSER

BLEED AIRMANIFOLD

ENG FIREPULL

TOWSHLD, WING,

AND STABANTI-ICE

SYSTEMS

TOCABIN

AIR DIST.SYSTEM

BLEED

AIR L

T

T T

P

T T

P

LP BLEED AIRPORT

BLEED AIRSWITCHES

L ROFF

AIRBLEED

CB

MODULATING VALVECONTROL & WARNING BOX

L ESS. BUS

DC POWERLP BLEED AIR

ELECTRICAL CONNECTIONHP BLEED AIR PRESS. REGULATED BLEED AIR

TEMP. REGULATED BLEED AIR

T

P




Pneumatic System (35-082, 087~112 (exc. 107), and 36-023~031)

LEFT ENGINE


VALVE

NACELLEHEATVALVE


VALVE

FLOWCONTROL

VALVE

PNEUMATICSENSELINES

VENTURI

HOT AIRBYPASS VALVE

(H VALVE)

HEATEXCHANGER

DUCT

HEATEXCHANGER

HEATEXCHANGER

OUTLET

RAM AIRFR0M DORSAL

INLETHP BLEED AIR

PORT


BLEED AIRMANIFOLD

ENG FIREPULL

TOWING AND STAB

ANTI-ICESYSTEM

TOCABIN

AIR DIST.SYSTEM

BLEED

AIR L

T

T T T T

LP BLEED AIRPORT

BLEED AIRSWITCHES

L ROFF

AIRBLEED

CB

MODULATING VALVECONTROL & WARNING BOX

L ESS. BUS

TOWSHLDANTI-ICESYSTEM

P


ELECTRICAL CONNECTIONHP BLEED AIR PRESS. REGULATED BLEED AIR


T

P




Pneumatic System (35-107, 35-113 and after, and 36-032 and after)

LEFT ENGINE


VALVE

NACELLEHEATVALVE


VALVE

FLOWCONTROL

VALVE


ELECTRICAL CONNECTIONHP BLEED AIR

PNEUMATICSENSELINES

VENTURI

HOT AIRBYPASS VALVE

(H VALVE)

HEATEXCHANGER

DUCT

HEATEXCHANGER

HEATEXCHANGER

OUTLET

RAM AIRFR0M DORSAL

INLETHP BLEED AIR

PORT


BLEED AIRMANIFOLD

ENG FIREPULL

TOWING AND STAB

ANTI-ICESYSTEM

TOCABIN

AIR DIST.SYSTEM

BLEED

AIR L

BLEED

AIR R

T

T T T T

LP BLEED AIRPORT

PRESS. REGULATED BLEED AIR


BLEED AIRSWITCHES

L ROFF

EMER. PRESS.VALVE

EMER. PRESS.VALVE


TOCABIN

AIR DIST.SYSTEM

*

*

T

**

*

L MAIN BUS

LH MODVALCB

RH MVALCB

LEFT MOD. VALVECTL. & WARN. BOX

RIGHT MOD. VALVECTL. & WARN. BOX

ON

EMER

EMER.PRESS.

ANEROIDSWITCH

9500'



FOR TRAINING PURPOSES ONLYENVIRONMENTAL SYSTEM 07/03

Air Distribution System

AIRPLANES 35-064~106; 35-108~112, 36-018~031

INTERNALDEFOG OUTLETS

FOOTWARMER

OUTLETS

CREWAIR OUTLETS

LOWER CABIN

DOOR AIR OUTLET

CABIN AIR

DIFFUSERS

TEMP. REGULATED

BLEED AIR(FROM HEAT EXCH.)

CHECKVALVE

BAGGAGECOMPARTMENT

DIFFUSER(35/35A)

INTERNALDEFOG OUTLETS

FOOTWARMER

OUTLETS

CREWAIR OUTLETS

CABIN AIRDIFFUSERS

TEMP. REGULATED

BLEED AIR(FROM HEAT EXCH.)

CHECK

VALVE

BAGGAGE

COMPARTMENTDIFFUSER

(35A)

CHECK

VALVE

EMER.PRESS.

VALVE

DIVAN

DIFFUSER

AIRPLANES 35-107; 35-113~130; 36-032~034

INTERNALDEFOG OUTLET

CABIN AIRDIFFUSERS

TEMP. REG

BLEED(FROM HEA

CHECK

VALVE

AIRPLANES 3




Cabin Temperature Control System (35-086 and earlier (exc. 35-082), and 36-022 and earlier)

DC POWER

ELECTRICAL CONNECTIONPRESS. REGULATED BLEED AIR


FLOWCONTROL

VALVE

PNEUMATICSENSE

LINES

VENTURI

HOT AIRBYPASS VALVE

(H VALVE)

HEATEXCHANGER

DUCT

HEATEXCHANGER

HEATEXCHANGER

OUTLET

RAM AIRFR0M DORSAL

INLET

BLEED AIRMANIFOLD

TOWSHLD, WING,

AND STABANTI-ICESYSTEMS

TO

CABINAIR DIST.SYSTEM

T

T

AIRBLEED

CB

CABIN CO

MAX

NORM

OFFCABIN

AIR

COLD

MAN HOT

FROM LEFTENGINE

FROM RIGHTENGINE

DUCT TEMPSENSOR

DUCT TEMPLIMITER

L ESS. BUS

H

CO

CA

T THERMAL SWITC

AUTO CONTROL




Cabin Temperature Control System (35-082, 35-087~112 (exc. 35-107), and 36-023~031)

DC POWER

ELECTRICAL CONNECTIONPRESS. REGULATED BLEED AIR


PNEUMATIC

SENSELINES

HEATEXCHANGER

DUCT

HEATEXCHANGER

RAM AIRFR0M DORSAL

INLET

TOWSHLD, WING,

AND STABANTI-ICESYSTEMS

TO

CABINAIR DIST.SYSTEM

T

T

AIRBLEED

CB

CABIN CO

MAX

NORM

OFFCABIN

AIR

COLD

MAN HOT

FROM LEFTENGINE

DUCT TEMPSENSOR

DUCT TEMPLIMITER

L ESS. BUS

H

CO

CA

T THERMAL SWITC

AUTO CONTROL

FLOWCONTROL

VALVE

VENTURI

HOT AIRBYPASS VALVE

(H VALVE)

HEATEXCHANGER

DUCT

HEATEXCHANGER

HEATEXCHANGER

OUTLET

RAM AIRFR0M DORSAL

INLET


BLEED AIRMANIFOLD

FROM RIGHTENGINE




Cabin Temperature Control System (35-107, 35-113 and after, and 36-032 and after)

PRE

TEM

FLOWCONTROL

VALVE

PNEUMATICSENSELINES

VENTURI

HOT AIRBYPASS VALVE

(H VALVE)

HEATEXCHANGER

DUCT

HEATEXCHANGER

HEATEXCHANGER

OUTLET

RAM AIRFR0M DORSAL

INLET

BLEED AIRMANIFOLD

TOWING AND STAB

ANTI-ICESYSTEMS

TOCABIN

AIR DIST.SYSTEM

FROM LEFTENGINE

FROM RIGHTENGINE

DUCT TEMPSENSOR

HO

COL

CABIN TEMP.SENSOR

(35-201 AND EARLIER, 35-205,

AND 36-040 AND EARLIER)

(35-202 AND AFTER (EXC 35-205), 36-041 AND AFTER,

AND EARLIER AIRPLANES INC AMK-78-13)

L ESS. BUS

L ESS. "B" BUS

COLD

DUCT TEMPLIMITER

T

T

TEMP. CTL. PRESS. REG.

*

** R

RR

T

TOCABIN

AIR DIST.SYSTEM

HP B

PNE

AIR

BLCB

ON

CABAIR

OFF

PRESS. CTL. PRESS. REG.

*

**


EMER. PRESS.VALVE

EMER. PRESS.VALVE




Cabin Pressurization System (35-112 and earlier (exc. 35-107), and 36-031 and earlier)

AFT PRESSUREBULKHEAD

RATE-OF-CHANGE CONTROLLER

ABSOLUTEBELLOWS

RATEPRESSURECHAMBER

METERINGVALVE

RATECONTROL

VALVE

RATEDIAPHRAGMS

CABIN ALTITUDE

CONTROLLER

AUXILIARYVOLUME

CHAMBER

RATE-OF-CHANGESELECTOR

CABIN ALTITUDESELECTOR

MANUALCABIN ALTITUDE

SELECTOR

FILTER

UP DN

CABINALTITUDELIMITER

DIFFERENTIALPRESSURE

RELIEF VALVE

TOCABIN DIFF. PRESS.

INDICATOR

SOLENOIDVALVE(N.C.)

SOLENOIDVALVE(N.O.)

SOLENOVALVE(N.C.

SOLENOIDVALVE(N.O.)

ENGINEBLEED AIR

FILTER

EXHAUSTINTO AFT

EQUIP. BAY

PRESSURIZATION JET PUMPAND VACUUM REGULATOR

FWD. PRESSUREBULKHEAD

ANEROIDCAPSULE

INLETSCREEN

STATICPORT




Cabin Pressurization System (35-107, 35-113 and after, and 36-032 and after)

AFT PRESSUREBULKHEAD

MANUALCABIN ALTITUDE

SELECTOR

UP DN

CABINALTITUDELIMITER

DIFFERENTIALPRESSURE

RELIEF VALVE

TOCABIN DIFF. PRESS.

INDICATOR

SOLENOIDVALVE(N.C.)

SOLENOVALVE(N.C.)

SOLENOIDVALVE(N.O.)

ENGINEBLEED AIR

FILTER

EXHAUSTINTO AFT

EQUIP. BAY

PRESSURIZATION JET PUMPAND VACUUM REGULATOR

FWD. PRESSUREBULKHEAD

ANEROIDCAPSULE

STATICPORT

SOLENOVALVE(N.C.)

PRESSURIZATION CONTROLLER

ABSOLUTEBELLOWS

RATEDIAPHRAGM

RATESPRING

RATECONTROL

VALVE

CABINPRESSURE

SENSE PORT

CABINPRESSURECHAMBER

RATEPRESSURECHAMBER

REFERENCEPRESSURECHAMBER

CABINALTITUDESELECTOR

CABINRATE

SELECTOR

AUXILIARYVOLUMETANK

FOLLOWERSPRING

METERINGVALVE

RATECHAMBERCHECKVALVE

SOLENOIDVALVE(N.O.)

FILTER



FOR TRAINING PURPOSES ONLYOXYGEN SYSTEM 07/03

Nose Oxygen System

LANYARDPIN(SECURED)

MASKSUPPLYHOSE

LATCHACTUATOR

VALVE

LANYARDACTUATOR

VALVE

COMPARTMENTCOVERLATCH

(ENGAGED)

0XYGENSUPPLY

LINE

POPPETVALVE(CLOSED)

LANYARDPIN(PULLED)

COMPARTMENTCOVERLATCH

(RELEASED)

POPPETVALVE(OPEN)

TOMASK

TOMASK

FROMDISTRIBUTION

SYSTEM

LANYARD ACTUATOR VALVE DETAIL

PASSENGER OXYGEN NOT ACTIVATED PASSENGER OXYGEN ACTIVATED

OXYGEN MASK

COMPARTMENTS(4 ON 36A)

PILOT'SOXYGENOUTLET

COPILOT'SOXYGENOUTLET

ANEROIDSWITCH

DC POWER



(35-201 AND EARLIER, 35-205,AND 36-040 AND EARLIER)

(35-202 AND AFTER (EXC 35-205), 36-041 AND AFTER,AND EARLIER AIRPLANES INC AMK-78-13)

L ESS. BUS

L ESS. "B" BUS

OXYGEN PRESSURE> 14,000'CAB. ALT.

< 8,000'CAB. ALT.

OXY VLVCB




Dorsal Oxygen System

OVERBOARDDISCHARGE

INDICATOR

DISCCHARGING

VALVE

OXYGEN MASK

COMPARTMENTS

(4 ON 36A)

PRESSURE

REGULATOR/SHUTOFF

VALVE

38 CU-FT

OXYGEN

CYLINDER

PILOTOXYG

OUTL

COPILOOXYG

OUTL

DC POWER



(35-201 AND EARLIER, 35-205,AND 36-040 AND EARLIER)

(35-202 AND AFTER (EXC 35-205), 36-041 AND AFTER,AND EARLIER AIRPLANES INC AMK-78-13)

L ESS. BUS

L ESS. "B" BUS

OXY VLV

CB

OXYGEN PRESSURE> 14

CAB.

< 8,0

CAB.




Nose and Dorsal Oxygen System

OVERBOARD

DISCHARGE

INDICATORDISC

CHARGING

VALVE

OXYGEN MASK

COMPARTMENTS

(4 ON 36A)

PRESSURE

REGULATOR/SHUTOFFVALVE

38 CU-FT

OXYGEN

CYLINDER

PILOT'SOXYGEN

OUTLET

COPILOT'SOXYGEN

OUTLET

ANER

SWIT

DC POWER



(35-201 AND EARLIER, 35-205,

AND 36-040 AND EARLIER)

(35-202 AND AFTER (EXC 35-205), 36-041 AND AFTER,

AND EARLIER AIRPLANES INC AMK-78-13)

L ESS. BUS

L ESS. "B" BUS

OXY VLV

CB

OXYGEN PRESSURE> 14,000'

CAB. ALT.

< 8,000'CAB. ALT.



FOR TRAINING PURPOSES ONLYICE PROTECTION SYSTEMS 07/03

Windshield Bleed Air Anti-Ice (35-086 and earlier (exc. 35-082), and 36-022 and earlier)

OFF

ON

MAN

CLOSECIRCUIT

2

LOW-LIMITSWITCH

PILWINDS

SQUAT SWITCHRELAY PANEL

GROUND

WSHLD

OV HT

AIR

WSHLD HEATSWITCHES

WINDSHIELD HEATCONTROL RELAY

FROM LEFTENGINE

WINDSHIELDOVERHEAT RELAY

REGULATED BLEED AIR

DC POWER

ENGINE BLEED AIR



L MAIN BUS

WSHLD

HT

WSHLDHEATCB

AUTO

OPENCIRCUIT

M MOTOR




Windshield Bleed Air Anti-Ice (35-082, 35-087~112 (exc. 35-107), and 36-023~031)

OFF

ON

MAN

CLOSECIRCUIT

2

LOW-LIMITSWITCH

PILWINDS


GROUND

WSHLD

OV HT

AIR

WSHLD HEATSWITCHES


FROM LEFTENGINE

REGULATED BLEED AIR

ENGINE BLEED AIR

L MAIN BUS

WSHLDHEATCB

AUTO

OPENCIRCUIT

WSHLD

HT

AMBIENT AIR

DC POWER

SERVO PRESSURE LINE



M MOTOR




Windshield Bleed Air Anti-Ice (35-107, 35-113 and after, 36-032 and after)

CLOSECIRCUIT

LOW-LIMITSWITCH

PIWIND


AIR

WSHLD

OV HT

GROUND

WSHLD HEATSWITCH


FROM LEFTENGINE

REGULATED BLEED AIR

ENGINE BLEED AIR

WSHLDHEATCB

OPENCIRCUIT

WSHLD

HT

AMBIENT AIR

DC POWER

SERVO PRESSURE LINE



ON

HOLD

VALVE FULLYCLOSED

OFF

M MOTOR

L MAIN BUS




Windshield/Radome Alcohol Air Anti-Ice (35-112 and earlier (exc. 35-107), and 36-031 and earlier)

ALC

AI

ALC SYSCB

FILTER

1.1 PSIRELIEF VALVE

FILLERCAP

OVERBOARDVENT TUBE

ALCOHOL TANK(2.2 US GAL.)

LOWPRESSURE

SWITCH

WSHLDRADOME

RADOME

PUMP

EXTERNALBLEED AIRNOZZLES

RADOMERADOMEALCOHOLOUTLET

OFF

WINDSHIELDSHUTOFF

VALVE




Windshield/Radome Alcohol Air Anti-Ice (35-107, 35-113 and after, and 36-032 and after)

FILTER

FILLERCAP

OVERBOARDVENT TUBE

EXTERNALBLEED AIRNOZZLES

RADOMERADOMEALCOHOLOUTLET

LOW LEVELFLOAT SWITCH

2.3 PSI BLEED AIRPRESS. REG. ANDSHUTOFF VALVE

ALCOHOL TANK(1.75 US GAL.)

3-WAYVALVE

2.6 PSIRELIEF VALVE

+4.0 PSI/-1 PSIDRELIEF VALVE

ALC SYSCB

WSHLDRADOME

RAD

OFF

RELAYPANEL

ALC

AI




Wing and Stabilizer Bleed Air Anti-Ice

FROM LEFTENGINE

FROM RIGHTENGINE

WING TEMP

SENSOR

OVERBOARDVENT

OHZ. STAB.

DIFFUSER

TUBES

LEFT WINGDIFFUSER

TUBE

102°C/215F°

WING OV HT

SENSOR

WINGOV HT

102°C/215F°

STAB OV HTSENSOR

STAB TEMP

SENSOR

SCUPPER

VENTRIGHT WINGDIFFUSER

TUBE

STABWING

HEAT

SWITCH

STAB &

WING HTCB

ON

OFF

R MAIN BUS

PRESS. REG.SHUTOFF

VALVE

STABOV HT




Engine Bleed Air Ice Protection

LEFT ENGINE


VALVE

L ENG

ICE

PRESSURESWITCH

NACELLEHEATVALVE

NAC HEATSWITCHESL

OFF


VALVE

PRESSURESWITCH

NACELLEHEATVALVE

TOENVIRONMENTAL

SYSTEM

TO

WSHLD, WING,AND STABANTI-ICE

SYSTEMS

REGULATED BLEED AIR

DC POWER

LP BLEED AIR


HP BLEED AIR

L NACHEATCB

L MAIN BUS

R NACHEATCB

Pt2/Tt2SENSOR

OFF

R

LP BLEED AIRPORT

HP BLEED AIRPORT

HP BLEED AIRPORT

INLET LIPDIFFUSER

BLEED AIRMANIFOLD

ON ON



ANNUNCIATORS 07/03 FOR TRAINING PURPOSES ONLY


A-1

Annunciator Panel

L ENG

ICE

FUEL

FILTER

BLEED

AIR R

BLEED

A IR L

PITOT

HT

AUG

AIL

STEER

ON

WSHLD

OV HT

DOORSPOILER

STAB

OV HT

LO OIL

PRESS

R FUEL

PRESS

L FUEL

PRESS

AUX

INV

SEC

INV

LOW

FUEL

CUR

LIM

PRI

INV

ENG FIRE

PULL

PITCH

TRIM

RH ENG

CHIP

LH ENG

CHIP

LOW

HYD

FUEL

XFLO

L LO

OIL

R LO

OIL

ENG FIRE

PULL

DH

T. O.

TRIM

BAT

160

R VG

MON

L VG

MON

BAT

140

ALC

AI

R

STALL

L

STALL

WSHLD

HT

WING

OV HT

R FUEL

COMPTR

L FUEL

COMPTR

CAB

ALT

R

GEN

R ENG

ICE

L

GEN

MACH

TRIM

ENG

SYNC

L35ANNU1.DSF

ARMED ARMED

ARMED ARMED

Overview

Learjet 35/36 advisory lights (annunciators) are designed to

provide an easily interpreted representation of both normal,

abnormal, and emergency system conditions. The majority of

annunciators are collocated on the glareshield annunciatorpanel. For organizational purposes, the annunciators are listed

alphabetically.

Where two or more annunciators exist for a particular system,

fault, or function, e.g, [L FUEL PRESS] and [R FUEL PRESS],

the crew must establish the exact source of the annunciated

condition prior to initiating the actions required by published

procedures. Recovery from any annunciated condition must be

made in strict accordance with published procedures. Refer to

the applicable airplane manufacturer's FAA-approved airplaneflight manual (AFM ), supplements thereof, and/or approved

checklists, for procedural information specific to your airplane.

KEY:

Red

Amber

Green

requires immediate attention, hazardous

condition exists.

requires attention, possible dangerous

condition exists.

safe or normal configuration, routine

action.

REV. 11/03



FOR TRAINING PURPOSES ONLY LEARJET 35/36 ANNUNCIATORS 07/03A-2

Illuminates when the alcohol reservoir, forwindshield and radome anti-ice, is empty.D epending upon airplane serial number,

illuminates if pressure pump fails.

Normal indication that the isolation valves are

open and sufficient hydraulic pressure isavailable for the thrust reversers.

Illuminates when corresponding [EN G FIR E

PU LL ] t-handle is pulled and extinguishingagent is available from the associated bottle.

M alfunction detected in the aileron augmenta-tion system in spoiler and spoileron modes.

a. Loss of DC power to auxiliary inverter.

b. Loss of or insufficient AC power output tothe corresponding 115 VA C bus and/or

c. IP C B equalizing circuit malfunction.

d. M ain battery switches set to "on" and asso-ciated IN VER TER switch set to "O FF".

Provides indication of a N iC ad main batteryoverheat condition when one or both batteries

reach 140°F. Illuminated by the low-limittemperature switches.

Provides indication of a N iC ad main batteryoverheat condition when one or both batteries

reach 160°F. Illuminated by the high-limittemperature switches.

ALC

AI

AUG

AIL

AUX

INV

BAT

140

BAT

160

ARM

ARMED





A-3

A ll serial number ranges:

a. Illumination of either annunciator indicates

failure of a SP R V primary valve.

b. Illumination of both annunciators indicatesfailure of either SP R V secondary valve.

c . Indicates excessive bleed air temperature.

A irplanes 35-112 & earlier (excl. 107) ;

36-031 & earlier:

a. Illuminates when corresponding ducttemperature exceeds approximately 645°F.

b. Extinguishes when corresponding duct

temperature falls below approximately590°F.

c . Illuminates when bleed air pressure ex-ceeds approximately 45 PSI.

d. Extinguishes when bleed air pressure fallsbelow 38 PSI.

A irplanes 35-107, 113 & after, 36-032 & after:

a. Illuminates when corresponding ducttemperature exceeds approximately 645°F,

or when pylon temperature exceeds ap-proximately 250°F.

b. Extinguishes when corresponding duct

temperature falls below approximately

590°F or when pylon temperature fallsbelow 240°F.

Illuminates when cabin altitude exceeds8,750 feet.

M etal particle contamination detected withincorresponding engine's oil pump assembly.

Indicates 275-amp current limiter failure.

CAB

ALT

CUR

LIM

LH ENG

CHIP

RH ENG

CHIP

BLEED

AIR L

BLEED

AIR R

or

R CUR

LIMITER

R CUR

LIMITER

REV. 11/03



FOR TRAINING PURPOSES ONLY LEARJET 35/36 ANNUNCIATORS 07/03A-4

Thrust reverser doors are fully deployed.

Illuminates at or below "decision height".

With electrical power applied to the airplane,

annunciator illuminates when:a. Passenger/crew door latching hooks not

disengaged.

b. Passenger/crew door not closed or prop-

erly secured, microswitch(es) closed due tomalfunction, or locking pin disengaged.

(single or dual battery installations)Illuminates upon:

a. DC generating system failure,

b. Depletion of main batteries,

c . and emergency power availability fromcorresponding source.

a. Nacelle temperatures exceed approxi-

mately 410°F in the areas of the pylonfirewall or accessory gearbox.

b. Nacelle temperatures exceed 890°F in thearea of the turbine section.

Illuminates when bleed air pressure is below 2

PSI.

Illuminates when the system is operating and

the nose gear is down and locked to alert the

crew that engine sync should not be usedduring takeoff or landing.

a. Either or both FUEL C M PTR switches set to

"O FF".

b. Fault detected or power loss in Electronicengine control system (EEC ) .

L ENG

ICE

ENG FIRE

PULL

L FUEL

COM PTR

R FUEL

COM PTR

R ENG

ICE

ENG

SYNC

EMER

PWR

EMER

PWR 1

EMER

PWR 2

or

DOOR

DH

DEPLOY





A-5

Illuminates when pressure differential be-

tween the inlet and outlet ports of either filter

reaches 1.25 PS ID (Dynamic) or .95 to 1.3

PSID (Purolator) indicating filter elementobstruction and the existence of a bypasscondition.

a. Illuminates when output pressure of corre-sponding jet pump is below approximately

.25 PS I.

b. Extinguishes when output pressure of corresponding jet pump is above 1.0 PSI or

the standby pumps are operating.

A irplanes 35-490 & after; 36-051 & after:

Illuminates when crossflow valve is open.

a. C orresponding generator is inoperative oroff-line.

b. C orresponding starter/gen switch is set to"STAR T " or "O FF" with at least one BA Tswitch set to "on".

a. Illuminates when oil pressure of eitherengine falls below approximately 23 PS I.

b. Extinguishes when oil pressure rises above30 PSI.

Fuel level in either wing tank is between 400and 500 LBS.

A irplanes 35-646 & earlier; 36-058 & earlier:

a. Illuminates when hydraulic pressure fallsbelow 1125 (+ /- 25) PSI .

b. Extinguishes when hydraulic pressure risesabove 1250 (+ /- 40) PSI .

A irplanes 35-647 & after; 36-059 & after:

a. Illuminates when hydraulic pressure fallsbelow 1000 (+ /- 25) PSI .

b. Extinguishes when hydraulic pressure rises

above 1125 (+ /- 40) PSI .

LOW FUEL

HYD XFLO

L LO R LO

OIL OIL

L

GEN

R

GEN

LO OIL

PRESS

LOW FUEL

HYD XFLO

L LO R LOOIL OIL

LOW

FUEL

or

LOW FUEL

HYD XFLO

L LO R LO

OIL OIL

FUEL

FILTER

L FUEL

PRESS

R FUEL

PRESS



M ach trim system malfunction detected and

system disengaged.

Indicates a red annunciator on the glareshieldis illuminated.

FC -530 equipped airplanes:

a. M alfunction or failure of primary motor orcontrol circuit detected by pitch trim speedcontroller self-monitoring circuit.

b. High speed operation of primary motor withflaps up.

c. M SW switch pressed.

a. O ne or both PITO T HEA T switch(es) set to"O FF".

b. O ne or both heating element(s) inoperativeor malfunction detected.

a. Loss of DC power to corresponding in-verter.

b. Loss of or insufficient AC power output tothe corresponding 115 VA C bus and/or

c.IP C B equalizing circuit malfunction.

d. M ain battery switches set to "on and asso-ciated IN VER TER switch set to "O FF".

Steady I llumination:

a. SPO ILER switch set to "EXT ".

b. Either spoiler extended beyond 1°.

Flashing:

a. Flaps are extended beyond 13° withSPO ILER switch set to EXT .

Illuminates when temperature of horizontal

1 °

PITOT

HT

PITCH

TRIM

PRI

INV

SEC

INV

SPOILER

STAB

MASTR

WARN

MACH

TRIM

learjet technical manual

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