'OVHT' LIGHT WILL ILLUMINATE IF AN OVHT CONDITION EXISTS [>145øF],

• 110ø F 'ON' LT EXTINGUISHED.

  TOILET DRAIN CONNECTION [FORE & AFT]---115VAC ALWAYS

  WASTE WATER MAST DRAIN---115VAC IN FLIGHT

  ---28VAC ON GRD

  ---28VAC ON JACKS WITH EXTERNAL PWR

  ACCESS TO REGISTER BOX STA 259.8 RH SIDE THROUGH NOSE WHEEL WELL ACCESS PANEL

  WIPER LOW SPEED:-130 STROKES/MIN

  WIPER HIGH SPEED:- 160 STROKES/MIN

  MOTOR THERMAL SWITCH ON AT 300 Deg F OR IF FIELD CURRENT > 8 TO 10

  AMPS, AUTORESET.

  Contents

  ---

  ATA CHAPTER 31 [INSTRUMENTS]

  CADC INPUTS:- PITOT,STATIC,TEMPERATURE.

  CADC OUTPUTS:- AIRSPEED [PITOT + STATIC]

  ALTITUDE [STATIC]

  MACH [ALTITUDE + AIRSPEED]

  TRUE AIRSPEED [TEMP + ALT + AIRSPEED]

  ALTITUDE RATE

  PITOT PRESSURE + STATIC PRESSURE = INDICATED AIRSPEED [IAS]

  PITOT PRESSURE + STATIC PRESSURE + STATIC SOURCE ERROR CORRECTION = COMPUTED

  AIRSPEED [CAS]

  CAS + TRANSDUCER NON LINEARILY CORRECTION = CALIBRATED AIRSPEED.

  MACH ALTITUDE + CAS FOR COMPRESSABILITY COMPENSATION = EQUIVALENT AIRSPEED

  [EAS]

  EAS + TAT STATIC PRESSURE + AIR DENSITY COMPENSATION = TRUE AIR SPEED [TAS]

  CADC TAKES INPUT FROM PITOT AND STATIC PRESSURE AND DEVELOPS AIRSPEED, ALTITUDE AND MACH.

  TAT PROBE CONNECTION TO CADC, STATIC AIR TEMPERATURE IS DEVELOPED.

   

  ELECTRIC ALTIMETER :- -1000 TO 50,000ft,WARNING FLAG APPEARS OVER READOUT IF ALTIMETER OR ADC PROBLEM.

  MACH/ASI:- RANGE 60 TO 450 KNOTS, MACH RANGE 0.4 TO 0.999.

  MACH AIRSPEED AURAL WARNING ON WHEN MAX AIRSPEED POINTER COINCIDES WITH AIRSPEED POINTER.

  KNOB IN:- PDCS SETS DESIRED AIRSPEED, PULL TO MANUALLY SET IN APPROX AT 12 O'CLOCK POSITION.

  AIRSPEED CURSOR INOP:- PDCS PROBLEM.

  FAILURE BARS:- MACH BELOW 0.4 OR PROBLEM, A/S < 60 KNOTS OR PROBLEM.

  VMO/MMO CIRCUITARY PROBLEM:- VMO FLAG APPEARS.

   

  FUNCTION SELECTED ON CADC PUSH TEST FOR 35 SECS TEST LT ILLUMINATES

  ALTITUDE FINE1= 10,000+/-20ft [30+/-5secs]

  ALTITUDE RATE 1,2,3+200+/-100 FPM.

  MACH1 = 0.785 +/-0.010 [30+/- 5 SECS].

  CAS1 = 420+/-6 KTS [35 SECS].

  MASTER FAILURE WARNING = VALID.

   

  ALTITUDE ALERT:-

  CADC---> BARO CORRECTED ALTITUDE--->ALT ALERT CONTROLLER--->AURAL ALERTING

  [ELECTRIC ALT] VISUAL ALERTING

  AT 1000 FT FROM SELECTED ALTTITUDE:- 2 SECS TONE AND LT.

  AT 375 FT FROM SELECTED ALTITUDE:- LT OFF.

  FLAPS > 10 UNITS:- NO ALERT [A/C READY FOR LANDING].

  ------------------------------------------------------------------------------

  AIR DATA INSTRUMENTS [PNEUMATIC]:-

  VSI:- 0 TO 6000 FT/MIN,SCREW [LEFT] FOR ZERO ADJUSTMENT.

  MACH/ASI:- 0 TO 160 [LINEAR SCALE 2 KNOTS INCREMENT].160 TO 420 KNOTS [LOG SCALE 10 KNOTS INCREMENTS].

  MACH:- 0.01 INCREMENTS 0.5 TO 1 MACH.

  ALTIMETER:- -1000 FT TO 50,000 FT,BARORANGE 28.1 TO 31.0 IN HG OR 951 TO 1050 mb

  TAT:- -70 TO 50 DEGC IN 5 DEG INCREMENTS.

  RIGHT PROBE:- CADC 1,PDCS.

  LEFT PROBE:- TAT INDICATOR.

  RMI:- PROVIDES MAGNETIC HEADING AND RADIO BEARING INFORMATION. RMI SYNCHROS SENDS INFORMATION TO HSI AND FLIGHT RECORDER AND NAVIGATION SYSTEM.

  SYNCHRONIZING ANNUNCIATOR INDICATES COMPASS CARD IS SYNCHRONIZED WITH FLUX VALVE HEADING OUTPUT.

  OFF FLAG:- DG PROBLEM/COMPASS PROBLEM.

  HSI:- DISPLAYS DATA FROM THE RADIO OR INS SYSTEMS TO INDICATE THE AIRCRAFT POSITION IN HORIZONTAL PLANE.

  ALERT LIGHT:- [OFF IN VOR/ILS MODE] INS WAYPOINT TO APPROACH MODE, A/C REACHES

  TO WAY POINT.

  :- DESIRE TASK PRESET COURSE ARROW.

  :- TO/FROM POINTER.

  :- DIAMOND SHAPE POINTER [DRIFT ANGLE AND TRACK INDICATOR.

  MILES:- MILES TO GO FROM INS OR DME DISTANCE.

  GRD SPEED:- A/C GROUND SPEED FROM INS.

  1/2/3:- WHICH INS OR VHF NAV SYSTEM FEEDING HSI.

  ------------------------------------------------------------------------------

 

GROUND PROXIMITY WARNING SYSTEM [GPWS]

INPUTS TO GP COMPUTER :-

1.GLIDESLOPE DEVIEATION.

2.BAROMETRIC ALT RATE.

3.IAS.

4.RADIO ALTITUDE.

5.DH TRIP POINT.

6.FLAP POSITION.

7.GEAR UP/DOWN.

8.SELF TEST.

OUTPUTS FROM GP COMPUTER:-

1.AUDIO WARNING.

2.VISUAL WARNING.

GP INOP LT ON:-

1.SELF TEST ON.

2.PROBLEM [CADC,PDCS,LRRA] WITH COMPUTER.

PULLUP LT:- MODE 1,2,3,4.

BELOW G/S:-MODE 5 WARNING,PUSH TO INHIBIT.

GPWS:-115VAC 400HZ.

PRIORITY MESSAGE MODE

1 WHOOP WHOOP - PULL UP 1 & 2

2 TERRAIN 2

3 TOO LOW - TERRAIN 4

4 TOO LOW - GEAR 4A

5 TOO LOW - FLAPS 4B

6 MINIMUMS 6

7 SINK RATE 1

8 DONT SINK 3

9 GLIDESLOPE 5

MODE 1:- EXCESSIVE DESCENT RATE, PULL UP LIGHT, SINK RATE [AUDIO] EVERY 1.5 SECS, STILL FURTHER DESCENT [EXCESSIVE] PULL UP LT, WHOOP WHOOP PULL UP [AUDIO] EVERY 1.5 SECS. SHOULD BE < 2450 FT TO GET WARNING. NO WARNING < 50 FT.

MODE 2:- EXCESSIVE CLOSURE RATE, PULL UP LTS ON, "TERRAIN TERRAIN" AUDIO, A/C STILL REMAINS, THEN PULLUP LTS ON "WHOOP WHOOP PULL UP" EVERY 1.5 SECS. > 300 FT BARO ALT FROM WHERE PULLUP STOPPED PULL UP LTS OFF, HIGHER SPEED LESS WARNING TIME INTERVAL.

FLAPS DOWN L/G POSITION DOWN < 700 FT NO WARNING ONLY "TERRAIN TERRAIN" FIRST THEN "TERRAIN".

MODE 3:-DESCENT AFTER T/O "DONT SINK" WARNING EVERY 1.5 SECS. AT 100 FT 15 FT LOSS CAUSES WARNING. AT 700 FT LOSS OF > 70 FT CAUSES WARNING.

ON TAKE OFF:- T/O WARNING ARMED, TERRAIN CLEARANCE DISARMED. ON 700 FT DISARMS T/O WARNING ARMS TERRAIN CLEARANCE.

MODE 4A:- WARNING ENABLED IF GEAR UP A/C ASCENDED > 700 FT PROXIMITY TO TERRAIN GEAR UP > 0.35 MACH.

TOO LOW TERRAIN AUDIO EVERY 1.5 SECS GREATER SPEED TILL 1000 FT, THEN NO WARNING.

TOO LOW GEAR AUDIO EVERY 1.5 SECS A/C < 500 FT L/G UP SPEED < 0.35 MACH.

MODE 4B :- PROXIMITY TO TERRAIN GEAR DOWN, FLAPS UP, "TOO LOW FLAPS" AUDIO, FLAPS

NOT IN LDG POSITION, AIRSPEED < 0.28 MACH, SPEED > 0.29 MACH, TOO LOW TERRAIN

EVERY 1.5 SECS TILL 1000 FT WARNING ENABLED IF GEAR DOWN, FLAPS NOT IN LDG

CONFIGURATION PROVIDED A/C HAS FIRST ASCENDED TO 700 FT. IF GEAR IS

RAISED, BOTH "TOO LOW GEAR" AND "TOO LOW FLAPS" AUDIO.

MODE 5:- BELOW GLIDESLOPE HEIGHT < 1000 FT L/G DOWN, GLIDESLOPE DEVIEATION > 1.3 DOTS "GLIDESLOPE" AUDIO EVERY 0.65 SECS INHIBIT BUTTON PRESSED TO SILENCE. TO HEAR AUDIO A/C ASCENDS > 1000 FT. HARD WARNING :- SAME LEVEL AS PULL UP WARNING, SOFT WARNING :- 6db < HARD WARNING.

MODE 6:- DESCENT BELOW MINIMUMS, AT 1000 TO 500 FT "MINIMUMS MINIMUMS" AUDIO ONCE HEARD MDA OR DH INDEX LTS ON.

LRRA PROBLEM:- INOP LT ON, LRRA CANNOT BE TESTED WITH AUTO PILOT ANGAGED.

VERTICAL GYRO:-

ADI,

FLIGHT DIRECTOR,

AUTOPILOT,

WEATHER RADAR.

ADI DISPLAYS INFORMATION FROM ATTITUDE REFERENCE SOURCES, FLIGHT DIRECTOR, VHF NAVIGATION, LRRA, AUTO THROTTLE OR SPEED COMMAND SYSTEM.

TEST :- 10ø PITCH UP,20ø ROLL RIGHT, ATT FLAG.

LRRA ALTITUDE :- 200 FT TO TOUCHDOWN ON RUNWAY SCALE.

RUNWAY FLAG:- APPROACH ALTITUDE AND ILS UNRELIABLE.

DH ILLUMINATES:-A/C ALT < DH SET ON LRRA INDICATOR.

GS FLAG:- VERTICAL DEVIATION DISPLAY UNRELIABLE.

SPEED POINTER:- SPEED FROM SELECTED SPEED.

SPEED FLAG:- UNRELIABLE.

RATE OF TURN POINTER BIASED OUT OF VIEW:- UNRELIABLE.

CMPTR FLAG:-FLIGHT DIRECTOR SYSTEM UNRELIABLE.

VG:- ROLL 180ø,PITCH =/-85ø.

------------------------------------------------------------------------------

PERFORMANCE DATA COMPUTER SYSTEM [PDCS]

STBY:- USED FOR DATA ENTRY AND AUTOMATIC SYSTEM CHECKOUT.

T/O:- T/O DISPLAYS T/O EPR LIMITS FOR TEMPERATURE ENTERED.

CLB:- CLB EPR LIMIT AND SPEEDS FOR THE DESIRED CLIMB PROFILE, BEST ECONOMY, MAX RATE OR CREW SELECTED SPEEDS.

CRZ:- CRUISE EPR LIMIT AND SPEEDS FOR THE DESIRED CRUISE SCHEDULE, BEST ECONOMY, LRC OR CREW SELECTED SPEEDS.

DES:- DESCENT SPEED, TIME, DISTANCE FOR BEST ECONOMY.

HOLD:- HOLDING EPR SPEED AND ENDURANCE.

CON:- MAX CONT THRUST EPR LIMIT FOR EXISTING ALT, TEMP & SPEED.

GA:- GA EPR LIMIT FOR EXISTING ALT, TEMP & SPEED.

TURB:- TURBULENT AIR PENETRATION SPEED, PITCH ALTITUDE AND N1 FOR FLIGHT LEVEL.

------------------------------------------------------------------------------

FLIGHT RECORDER INPUTS:-

1.FLT RECORDER WARN/CONTROL MODULE

2.TRIP AND DATE ENCODER.

3.AIR DATA COMPUTER.

4.ACCELEROMETER.

5.AIRPLANE COMPASS SYSTEM.

6.AUDIO ACCESSORY UNIT.

ACCELEROMETER DETECTS VERTICAL FORCES :- -3G TO + 6G SUPPLY 26VAC 400 HZ

FLIGHT RECORDER MODULE OFF LT:- AMBER ON :- RECORDER NOT WORKING, LOSS OF POWER, TAPE NOT ADVANCING.

SW IN TEST ON GRD, ENGINES NOT RUNNING, LT ILLUMINATES.

INSTRUMENT COMPARATOR LTS:-

MON PWR:- POWER SUPPLY PROBLEM.

HDG:- CAPT AND F/O COMPASS CARDS FOR HSI DIFFERENT.

PITCH,ROLL:- ADI DISPLAYS DIFFERENT.

HDG,PITCH,ROLL:- LOSS OF EXICTER VOLTAGE FROM COMPARATOR UNIT.

GS,LOC LTS:- COMPARE CAPT,F/O VHF NAV RECIEVERS SIGNALS.

ALT LT:- ALTITUDE SIGNALS FROM #1 AND #2 LRRA RECORDER/TRANSMITTERS ALTITUDE SIGNALS.

Contents

---

ATA CHAPTER 32 [LANDING GEARS]

SELECTOR LEVER SHOULD BE IN OFF FOR MANUAL EXTENSION

STEERING WHEEL 78ø L/R

RUDDER PEDALS 7ø L/R

ON COMPRESSION STROKE SNUBBER VALVE MOVES AWAY FROM UPPER BEARING SO FREEFLOW

ON EXTENSION STROKE SNUBBER VALVE MOVES TOWARDS UPPER BEARING SO RESTRICTED FLOW

MAIN GEAR HYDRAULIC MODLE HAS 2 PRIORITY VALVES [3500 PSI] 2 FLOW RESTRICTORS, 4 FLOW LIMITERS.

TRANSFER CLINDER FUNCTION ;-

1. MOMENTARILY EQUALIZES PRESSURE IN THE MAIN ACTUATOR.

2. DAMPING ACTION ON LANDING IMPACT.

3. PREVENTS PRESSURE FLUCTUATION FROM COACHING THE LOCK ACTUATOR AND POSSIBLE UNLOCKING THE GEAR.

MIL-H-5606,MIL-H-6083 FLUID USED IN LANDING GEARS

CONTROL LEVER POSITION SWITCH S78

LANDING GEAR LEVER LOCK SOLENOID ENERGIZED IN AIR TO ENABLE LEVER MOVEMENT TO UP POSITION.

HYDRAULIC PRESSURE FROM UP LINE IS SENT TO BOTH BRAKE METERING VALVES TO STOP WHEEL ROTATION DURING GEAR RETRACTION.

HYDRAULIC PRESSURE FROM THE DOWN LINE ALSO SUPPLIES THE THRUST REVERSER AND THE NOSE WHEEL STEERING SYSTEM .

SELECTOR VALVE RETURN LINE IS SUPPLY TO SHIMMY DAMPER.

MANUAL RELEASE OF GEAR LANDING GEAR LEVER SHOULD BE IN OFF POSITION

MAIN GEAR CABLE PULL OUT 17.30 INCHES

NOSE GEAR CABLE PULL OUT 8 INCHES

DOWN LOCK VIEWER LOCATED IN THE AISLEWAY OF THE MAIN CABIN AREA [LH SIDE],3RD WINDOW AFT OF EMERGENCY EXIT.

TELEFLEX CABLE [RH MLG] RIGGED WITH A/C ON JACKS,SENDS AIR/GRD SIGNAL TO L/G ACESSORY MODULE,FOR GRD SIGNAL STRUT SHOULD BE COMPRESSED AT LEAST 5".

L/G MODULE M338 LIGHTS ARE ON IN FLIGHT,OFF ON GROUND.

PUSHING BOTH SWITCHES ON M338 SIMULATE AIRPLANE IN AIR CONDITION WITH EXCEPTION OF L/G LEVER LOCK CIRCUIT IN THE AIR-SENSING CIRCUIT.

ENGINE DRUM & BRAKE ASSY LOCATED ON E&E COMPARTMENT CEILING.

ENGINE DRUM & BRAKE ASSY:-

OUTBD:-L/G WARNING HORN SWITCHES[S139,S140]

INBD:- THRUST LEVER ADVANCED SWITCHES[S283,S133]

ON M338:-TO ACTIVATE GRD CRITICAL SYSTEMS ONLY GRD SENSING TEST SWITCH PUSHED, TO ACTIVATE AIR CRITICAL SYSTEMS ONLY THE AIR SENSING SWITCH PUSHED.

RED LT ON WHENEVER:-

1.THE LEVER IS NOT DOWN AND GEAR NOT UP.

2.THE LEVER IS DOWN AND GEAR NOT DOWN AND LOCKED.

3.ENGINE #1 OR ENGINE #2 THROTTLE IS IN IDLE RANGE AND ANY GEAR IS NOT DOWN AND LOCKED.

GREEN LT ON WHENEVER:-

1.THE GEAR IS DOWN AND LOCKED.

LANDING GEAR WARNING HORN SOUNDS WHENEVER:-

1.FLAPS ARE NOT UP AND 10 UNITS OR LESS, ENGINE #1 OR #2 THROTTLES IS IN IDLE RANGE AND GEAR NOT DOWN AND LOCKED [CAN BE RESET WITH L/G WARNING HORN CUTOUT BUTTON]

2.FLAPS 15 UNITS, BOTH ENGINES EPR<1.6 AND GEAR NOT DOWN AND LOCKED, CANNOT BE RESET.

3.FLAPS MORE THAN 25 UNITS AND GEAR NOT DOWN AND LOCKED, CANNOT BE RESET.

NOSEWHEEL STEERING USES "A" SYSTEM PRESSURE.

STEERING ACTUATORS TURNS < 33ø BOTH WORK IN PUSHPULL FASHION, TURNS > 33ø TO 78ø NO PRESSURE TO PULL ACTION ONLY PUSH ACTION ACTUATOR GETS PRESSURE.

TOW PIN INSTALLED IN COVER OF STEERING VALVE TO ENABLE TOWING WITH "A" PRESSURISIED.

78ø L/R STEERING WHEEL TURN CAUSES 95ø NOSEWHEEL TURN.

THE PISTON POSITIONING SYSTEM FUNCTIONS TO ENGAGE OR DISENGAGE RUDDER PEDAL STEERING CAPABILITY.

RUDDER PEDAL STEERING MECHANISM ALSO SUPPLIES STEERING WHEEL FEEL.

A 70 TO 130 PSI SNUBBER COMPENSATOR IS IN THE STEERING METERING VALVE ACTS AS A SHIMMY DAMPER BY PROVIDING PRESSURE TO BOTH SIDES OF THE STEERING ACTUATORS.

PARKING BRAKE SWITCH S100 OPENS PARKING BRAKE SOV.

RETRACT BRAKING PROVIDED BY "A" SYSTEM L/G UPLINE.

BRAKE HAS 5 ROTORS & 6 STATORS.

BRAKE INDICATOR PIN CAN BE 0.6 TO 1.36" LENGTH MINIMUM [1/8"]

WHEEL THERMAL PLUGS :- 350øF.

SAFETY RELIEF VALVE :- 230 PSI.

ANTISKID MODULE M162

ANTISKID VALVES HAVE 1ST STAGE ELECTRICALLY CONTROLLED,2ND STAGE HYDRAULICALLY CONTROLLED.

L/G LEVER UP SWITCHES:- S304 INTERRUPTS PWR TO THE ANTISKID MODULE.

S303 OPENS THE CIRCUIT TO THE ANTISKID INOP LTS ON P2.

PARKING BRAKE VALVE MUST BE OPEN FOR ANTISKID VAlVE TO OPERATE.

BRAKES CAN BE BENDIX, GOODRICH.

ANTISKID "INOP" LT ON WHENEVER :-

1.A VALVE IS OPEN CIRCUITED.

2.A TRANSDUCER IS OPEN CIRCUITED.

3.A FAILURE IN THE CONTROL BOX.

4.THE PARKING BRAKE POSITION IS IN DISAGREEMENT WITH PARKING BRAKE SET SWITCH.

5.POWER FAILURE OR SWITCH OFF.

 

PARKING BRAKE SHOULD NOT BE SET FOLLOWING A HIGH ENERGY STOP TO PREVENT FUSING OF BRAKES, ALLOW 40 TO 60 MTS COOLING TIME. IF PARKING BRAKE SET LONGER THAN 8 HRS, RESET AFTER PRESSURISATION OF SYSTEM.

ANTISKID SW ON-->PARKING BRAKE OFF--->PILOTS "INOP" LT ON--->PARKING BRAKE ON OR OFF--->CONTROL BOX LT ON--->COMPONENT TEST SWITCH TO VALVE/XDCR---->CHECK LT INDICATION [LT ON, CNTRL BOX FAILURE].

ANTISKID HAS PRIORITY OVER AUTOBRAKE FOR SKID AND LOCKED WHEEL PROTECTION.

THREE DECELERATION RATES IN AUTOBRAKE MODE ARE:-

MIN 4 FT/SEC2

MED 7 FT/SEC2,6 FT/SEC2

MAX 10 FT/SEC2

ANTISKID INOP AUTOBRAKES CANNOT BE USED.

AUTOBRAKE HAS 3 MODES:-

ON RAMP:-INITIAL START OF AUTOMATIC BRAKING.

OFF RAMP:-THE TRANSFER OF AUTOMATIC TO MANUAL BRAKING.

DROP OUT:-THE ABRUPT TERMINATION OF AUTOMATIC BRAKING.

AUTOBRAKE MODULE:- M577.

TIRE REMOVAL:-

1.CUTS OR WEATHER CHECKS IN GROOVES,TREAD OR SIDEWALLS WHICH REACH CORD BODY.

2.BLISTERS,BULGES OR OTHER EVIDENCE OF PLY SEPRATION IN TREAD OR SIDEWALL AREA.

3.ANY TIRE WITH A FLAT SPOT THROUGH THE REINFORCING CHORDS AT THE TREADS-UNDER TREAD INTERFACE.

4.OTHER DAMAGE OR COMBINATION OF ITEMS WHICH MIGHT RESULT IN TIRE PROBLEMS. AVERAGE TREAD DEPTH <1/32" ON CENTER GROOVE TIRE MEASURE AT CENTER GROOVE. ON CENTER RIB TIRE, MEASURE AT GROOVES NEAREST CENTER.

TRANSVERSE CUTS:-CUTS DEEPER THAN TREAD GROOVES AND EXTENDING ACROSS A RIB FROM GROOVE TO GROOVE.

CIRCUMFRINTUAL CUTS:-CUTS DEEPER THAN TREAD GROOVE, BUT NOT INTO THE CARCASS PLIES, WITH ENDS NOT MORE THAN «" APART MEASURED TRANSVERSAL AND 2" IN LENGTH MAY CONTINUE IN SERVICE.

DIAGONAL CUTS:-ONE RIB INVOLVED, A CUT LESS THAN GROOVE DEPTH UPTO 12" LENGTH MAY BE LEFT IN SERVICE IF THE ENDS OF CUT IS NOT MORE THAN «" APART, MEASURED TRANSVERSLY.

OPENTREAD SPLICE:-MAY CONTINUE IN SERVICE IF GAP DOES NOT EXTEND COMPLETELY ACROSS RIB. REMOVE FROM SERVICE IF SEPRATION EXISTS.

SKID BURNS,ICE BURNS,FLATS SPOTS:-AN OVAL SHAPED FLAT SPOT CAUSED BY A SKID. MAY BE LEFT IN SERVICE UNLESS THE DEFORMATION EXTENDS TO OR INTO THE CARCASS PLIES OR BALANCE IS AFFECTED.

BLISTER OR BULGE:-SEPARATION OF THE TIRE STRUCTURE IN THE TREAD OR SIDEWALL. REMOVE FROM SERVICE.

CHEVRON CUTTING:-IF DAMAGE EXTENDS ANY SINGLE CUT LIMIT.

GROOVE CRACKING:-A CIRCUMFRINTIAL CRACK AT THE BASE OF A TREAD GROOVE.

RIB UNDERCUTTING:-IF CRACK EXTENDS UNDER A TREAD RIB.

TREAD FLAKING,CHIPPING OR CHUNKING:-IF DAMAGE EXTENDS ACROSS A RIB OR TO THE BASE OF GROOVE. THROWN TREAD, PEELED RIB.

CIRCUMFRINTIAL CRACKS, RADIAL CRACKS, CRACKS IN SIDEWALL OR SHOULDER AREA, IF CRACKS EXPOSE CARCASS PLIES.

OZONE AND WEATHER CHECKING:-SIDEWALL CRACKS CAUSED BY AGE/WEATHER DETERIORATION IF CRACKS EXPOSE CARCASS PLIES.

PUNCTURE:-IF HOLE IS GREATER THAN 0.125" DIAMETER OR EXTENDS INTO CARCASS PLIES.

ITEM LEAK ALLOWABLE

GEARBOX STARTER DRIVE OVERBOARD DRAIN. 10cc/hr

GEARBOX HYDRAULIC PUMP DRIVE OVERBOARD DRAIN 10cc/hr

No4 BEARING DRAIN TUBE [#4 CARBON SEAL] OIL LEAKAGE FROM DRAIN TUBE AT IDLE POWER IS NORMAL

FUEL PUMP DRIVE OVERBOARD DRAIN 10cc/hr

FUEL PUMP DRAIN 60cc/hr [ENGINE RUNNING OR SHUT DOWN]

FUEL CONTROL DRAIN NONE

P&D VALVE DRAIN NO LEAK FROM PLUGGED P&D VALVE DRAIN SB 3757

COMBUSTION CHAMBER NO LEAK WITH ENGINE RUNNING,

9cc MAX ONE TIME ON SHUTDOWN,

60cc/hr MAX AFTER SHUTDOWN,

ON ENGINES WITH P&W DRAIN AS PER SB.

EXHAUST CASE No6 BEARING SUMP OIL WETNESS NOT RESULTING IN OIL PUDDLING WITHIN 20 mins AFTER ENGINE SHUTDOWN.

M577:-

DS1:-INBD SOLENOID VALVE OPEN CIRCUIT

DS2:-OUTBD SOLENOID VALVE OPEN CIRCUIT

DS3:-AUTOMATIC BRAKE NOT SET [IN AIR INDICATION ONLY]

DS4:-BOTH ANTISKID CHANNELS INOP OR PWR LOSS

IF ONLY ONE ANTISKID CHANNEL FAILS, THE AUTOBRAKE "INOP" LT WILL NOT ILLUMINATE. OPERATING PROCEDURE REQUIRES THE AUTOBRAKE SYSTEM TO BE SHUT OFF WHENEVER ONE ANTISKID IS INOP.

BRAKE PEDAL SWITCHES LOCATED ON THE F/O BRAKE PEDAL ASSY UNDERNEATH THE CONTROL CABIN. THESE SWITCHES CONTROL THE OFF RAMP AND DROP OUT FUNCTION OF THE AUTOBRAKE MODE. TRANSFER FROM MANUAL [OFF RAMP] GRADUALLY BY DEPRESSING PEDALS [>1ø <7.5ø] AND HOLDING THEM, IMMEDIEATLY THEN DEPRESS PEDALS >7.5ø [DROP OUT].

CONDITIONS MET FOR AUTOBRAKE MODULE GENERATING ON RAMP SIGNAL:-

1.AUTOBRAKE SELECTED

2.ANTISKID ON AND OPERATIONAL

3.BOTH BRAKE PEDALS OFF

4.BOTH THROTTLES RETARTED

5.SPEED BRAKE HANDLE "ARMED"

6.AT LEAST ONE WHEEL ON EACH GEAR UPTO SPEED

7.PARKING BRAKE VALVE OPEN

TO OVERRIDE AUTOBRAKE THROUGH MANUAL INPUT:-PRESS BRAKE PEDALS, MOVE SPEED BRAKE HANDLE FROM DEPLOYED TO FWD OF VERTICAL BUT NOT DOWN.

AUTOBRAKE CAN BE TERMINATED BY:-

1.ONE OR BOTH PEDALS DEPRESSED AND THEN RELEASED.

2.ONE OR BOTH THROTTLES ADVANCED [IN THE T/O RANGE].

3.SPEED BRAKE HANDLE MOVED TO THE DOWN POSITION.

4.ONE OR BOTH BRAKE PEDALS FULLY DEFLECTED.

5.TURNING THE AUTOBRAKE SYSTEM OFF.

IN ADDITION

LOSS OF PWR, FAILURE OF ANY AUTOBRAKE COMPONENTS, FAILURE IN THE ANTISKID, OR CLOSING OF THE PARKING BRAKE WILL CAUSE ABRUPT DROP OUT OF AUTOBRAKE.

AUTOBRAKE PRESSURE CONTROL MODULE:- V122.

FUSE STOPS FLOW OVER 160cuin TO "A" BRAKES.

AUTOBRAKE MODULE REQUIRES "B" SYSTEM PRESSURE.

PRESSURE SWITCH BETWEEN METERING VALVE & SHUTTLE VALVE CAUSES AUTOBRAKE

SYSTEM TO DISARM IF METERED PRESSURE >200PSI.

PRESSURE SWITCH DOWNSTREAM OF FUSE WILL DEACTIVATE <200PSI DISARMING

AUTOBRAKE SYSTEM.

AUTOBRAKE SYSTEM ARMED WHEN:-

1.DECELERATION RATE SELECTED P2-2.

2.AUTOBRAKE PWR AVAILABLE.

3.TURN ON SELF CHECK [TOSC] SUCCESSFUL.

TOSC COMPLEATED IN 200 MILLISECONDS, NO DISARM LT.

ON LANDING AUTOBRAKE INITIATES WHEN:-

1.WHEEL SPEED >60 KTS [ONE WHEEL ON EACH MLG].

2.BOTH THROTTLES RETARDED.

3.AVERAGE WHEEL SPEED >70 KTS.

DISARM LT ON IF SELECTOR SWITCH OFF--->SOLENOID PR SW >1000PSI WITH NO AUTOBRAKE INPUT.

AUTOBRAKE CONTROL CB MUST BE RESET WHEN FAULT WAS SOLENOID VALVE PR SWITCH HIGH LOGIC,OTHER LANDING MODES SELECTOR SWITCH TO OFF.

 

AUTOBRAKE SELECTED "INOP" LT ON WHENEVER:-

1.BOTH ANTISKID SWITCHES ARE OFF.

2.BOTH ANTISKID "INOP" LTS ARE ON.

3.L/G LEVER IN UP POSITION.

4.PARKING BRAKE IS SET.

5.AUTOBRAKE MODULE POWER LOSS.

6.HARD PEDAL PRESSURE [OVERRIDE]

7.COMPARATOR MONITORING VOLTAGE INPROPER.

8.EITHER SOLENOID VALVE OPEN CIRCUITED.

9.AUTOBRAKE NOT RESET [AIR].

Contents

---

ATA CHAPTER 33 [LIGHTS]

BACKGROUND LIGHTS:- 115VAC TX BUS1 [FLUORESCENT LAMPS]

28VAC TX BUS 2 [INCANDESCENT LAMPS]

28VDC BATT BUS [EMERGENCY LIGHTS]

CB PANEL LIGHTS:- 28VAC TX BUS 2.

CAPT SYSTEM ANNUNCIATER:- 28VDC BATT BUS OR DC BUS 1.

FLT CONT:- 7

FUEL:- 3

ELEC:- 9

APU:- 3

OVHT DET:- 3

F/O SYSTEM ANNUNCIATOR:-

ANTIICE:- 11

HYD:- 6

DOORS:- 8

OVHD:- 6

AIR COND:- 11

OVHD:-

EMERGENCY EXIT LTS NOT ARMED,

FLT REC OFF,

NO EQUIP COOLING,

PAX OXY ON,

STALL WARN OFF.

ENTRY SW OFF:- ALL LTS OFF.

ENTRY SW OFF,GPU ON :- ENTRY LTS ON DIM.

ENTRY SW BRIGHT:- FLOURESCENT LAMPS AND THRESHOLD LTS ON.

ENTRY SW DIM:- 2 DIM LTS ON.

ENTRY SW BRIGHT,GPU ON:- BOTH DIM & BRIGHT LTS ON.

PAX SIGNS:- 28VAC BUSES.

2 LAMPS FOR "NO SMOKING SIGNS",3 LAMPS FOR "FASTEN SEAT BELT SIGNS".

SW IN AUTO :-

IF FLAPS ARE LOWERED,SEAT BELT SIGN ON.

IF L/G LOWERED NO SMOKING AND FASTEN SEAT BELTS SIGN ON.

PAX READING LTS:- 28VAC

BALLAST FOR WINDOW LTS BEHIND PSU PANELS.

EXTERNAL BLUE LAVATORY OCCUPIED LT ON WHEN CLOSED.

LAVATORY DOOR OPEN ON GRD,GPU ON:- MIRROR LTS ON.

LAVATORY DOOR OPEN ON GRD:- DOME LTS ON.

LAVATORY DOOR CLOSED ON GRD:- MIRROR LTS ON.

LAVATORY DOOR OPEN IN AIR:- NO LTS.

LAVATORY DOOR CLOSED IN AIR:- MIRROR LTS ON.

ATTENDENT CALL LTS [WITH HIGH TONE]

AMBER LTS:- LAVATORY SWITCHES.

BLUE LTS:- PSU PANEL

PINK LT:- FLIGHT CREW DECK/ATTENDENT.

 

BEAM:- LDG LTS [OUTBD]:- 15ø.

[INBD] :- 11ø.

RUNWAY TURNOFF LTS:- 50ø.

CARGO AND SERVICE COMPT LTS:- 28VAC.

L/G LTS--->PILOTS SW [MASTER], WHEEL WELL SW--->CAN BE TURNED ON, NORMAL IS OFF POSITION.

DUTY CYCLE:-5 MTS ON/5 MTS OFF IF A/C IS STATIONARY.

STEADY:-28VDC LIGHTS [POSITION]

OFF:- ALL LTS OFF.

STEADY/STROBE:- 115VAC TX BUS 1 FLASHING STROBE LTS & POSITION LTS [28 VDC STATIONARY].

POSITION LTS:-

LEFT:- RED.

RIGHT:- GREEN.

TAIL:- WHITE.

STROBE FLASH RATE:- 60+/-3 per min.

ANTICOLLISION LTS:-115VAC 1 FLASH/SECOND.

WING ILLUMINATION LTS:- 49ø FROM A/C CENTER LINE BEAM WIDTH 13ø [28VAC].

EMERGENCY LTS:-EXIT LTS, AISLE LTS, ESCAPE SLIDE LTS, OVERWING EXIT LIGHTS.

ESCAPE SLIDES FWD BATTERY PACK:- FWD LH FWD CARGO.

ESCAPE SLIDES AFT BATTERY PACK:- AFT RH AFT CARGO.

OVERWING LTS LH & RH AFT CARGO [2 PLACES].

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ATA CHAPTER 35 [OXYGEN SYSTEM]

OXYGEN CYLINDERS:-37-1/2,76,114 cu ft

CYLINDERS ARE COMPRESSED TO 1850 PSI AT 70 Deg F [21.1øC]

SAFETY RELIEF VALVE [CYLINDER]:-2800+/-150 PSI. NORMALLY 500 PSI IN DISCHARGE LINE.

THERMAL COMPENSATORS[HEAT SINKS]:- WHITE BAND MARK.

CREW O2 SYSTEM:- BOTTLE-->TDCR-->REGULATOR-->SOV-->DILUTER DEMAND REGS-->MASKS.

RELIEF VALVE ON REGULATOR RELIEVES AT 100 TO 110 PSI TO DISCHARGE IN CYLINDER SHROUD.

CABIN ALTITUDE > 14000 FT OXYGEN AUTOMATICALLY SUPPLIED TO EACH PSU.

ELECTROPNEUMATIC FCU:- CAN BE OPERATED BY

1.CABIN ALT > 14000 FT

2.SW IN ON

PNEUMATIC FCU CAN BE OPERATED BY

1.MANUAL HANDLE

20 PSI CAUSES PSU MASKS TO DROP.

Contents

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ATA CHAPTER 36 [PNEUMATICS]

ENGINE BLEED RELIEF VALVE:- 106 PSI.

APU BLEED RELIEF VALVE:- 80 PSI

APU BLEED TEMP 450øF [MAX],PRESSURE 38 PSI[MIN],APU-->90 lbs per pack/min

AIR VOLUME OUTPUT:-AIR CONDITIONING -->160 lbs/min 2 PACKS.

ENGINE START:- 110 lbs/min [BOTH SIDES].

WING ANTI ICE:-120 lbs/min [BOTH SIDES]

GRD CART:- TEMP 450øF [MAX], PRESSURE 60 PSI [MAX].

450øF THERMOSTAT:- BLEEDS OFF, CONTROL PRESSURE TO CLOSE 13TH STAGE MOD VALVE.

490øF OVERHEAT:-CLOSES BLEED VALVE,OPEN < 20 TO 30øF,HAS TO BE RESET [SWITCH].

HEAT EXCHANGER AND PRECOOLER VALVE MANTAINS 365øF.>365øF VALVE OPENS.

ENGINE BLEED VALVES 115VAC,FIRE HANDLES CLOSES BLEED VALVE.

BEFORE JET START:- ENSURE BATTERY SWITCH ON,PACKS OFF.

FOR PACK USE [NO ENGINES] AC PWR REQUIRED.

AIR CLEANER PURGE VALVE:- OPEN ON GRD, IN FLT [FLAPS DOWN].

TURBOFAN VALVE OPENS:-PURGE VALVE OPENS, APU BLEED SW OFF.

ISOLATION VALVE:-AUTO-->2 BLEED SWITCHES,2 PACK SWITCHES ON, VALVE CLOSED.

APU BLEED VALVE ON:- SW ON, APU >95% RPM.

DUAL BLEED LT ON:- #1ENG BLEED, APU BLEED ON. OR #2ENG BLEED, ISOLATION VALVE, APU BLEED ON.

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ATA CHAPTER 38 [WATER WASTE]

TANK PRESSURE REG:- 25 PSIG

PRESSURE RELIEF VALVE:- 50 PSIG.

HEATER :- 1«qt CAPACITY.

WATER TANK VOLUME :- 34 US GALLONS

CAPACITY:- 30 US GALLONS.

HEATER :- 420 WATTS,3 PROBES,115VAC.

THERMAL SWITCH:-UPTO 125øF.

OVERHEAT SWITCH:-190øF,STOPS PWR TO HEATER ,TURNS ONOVHT LT,HAS TO BE RESET.

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ATA CHAPTER 49 [AUXILIARY POWER UNIT]

AIRESEARCH GTCP 85-129,45 KVA,115V 3 PHASE 400 HZ AC.

WEIGHT 313 lbs, FUEL FLOW MAX LOAD STD DAY:-250 PPH.

RATED SPEED:-6000 RPM AT GENERATOR DRIVE.

EGT:-MAX 649øC.

START 760øC.

OFF LOADED 360øC.

OIL:- MAX 124øC.

TEMPERATURE RISES, AIRFLOW DROPS, BLEED PRESSURE DROPS.

APU LOADED PRESSURE RISES, AIRFLOW DROPS.

SEA LEVEL TO 10,000 FT:- BOTH ELECTRICAL AND PNEUMATIC POWER CAN BE USED.

10,000 TO 17,000 FT:- EITHER ELECTRICAL POWER OR PNEUMATIC POWER CAN BE USED.

17,000 FT TO 35,000 FT:-ONLY ELECTRICAL POWER CAN BE USED.

APU SHROUD HAS 10 LATCHES.

APU FUEL HEATER CONTROL VALVE 42øF TO 56øF.

LOW OIL QTY LT:-1« qt.

LOW OIL PRESSURE LT:-OFF AT 55 PSIG, ON AT 45 PSIG, APU SHUTS DOWN.

HIGH OIL TEMPERATURE:-255øF [124øC],APU SHUTS DOWN.

OVERSPEED:-110% RPM,APU SHUTS DOWN.

APU GEN OFF BUS LT:-95% rpm.

SURGE BLEED VALVE OPENS IN FLIGHT WITH APU BLEED VALVE CLOSED.

APU START, BATT SW ON, MASTER SW TO START AND ON, APU FUEL SOV AND AIR INLET DOOR OPENS, STARTER MOTOR ENERGIZES

AT 10% RPM LOP1 CLOSES AT 4 PSIG, IGNITION SYSTEM ENERGIZES, FUEL SOLENOID OPENS

37% LOP2 OPENS AT 55 PSIG LOP LT OFF

50%:- 50% SW CLOSES, STARTER MOTOR DE-ENERGIZES OR WITHIN 90 SECONDS [OLD SW 35%].

95%:- 95% SW ENERGIZED, APU GEN OFF BUS LT ON, HOUR METER STARTS, APU BLEED SW ARMED, IGNITION OFF,3 WAY SOLENOID VALVE ENERGIZED, LOP AUTOSHUTDOWN  

SYSTEM ARMED, PNEUMATIC SOLENOID VALVE ARMING RELAY ENERGIZED.

APU SHUTDOWN:-

1.MASTER SW TO OFF, CLOSES #1 TANK APU SOV, AIR INLET DOOR AND DE-ENERGIZES FUEL SOLENOID VALVE.

2.PULLING FIRE HANDLE, CLOSES #1 TANK APU SOV, FUEL SOLENOID VALVE AND AIR INLET DOOR.

APU AUTO SHUTDOWN:-

1.OVERSPEED:- 110% RPM [45,000 RPM].

2.LOP:- 45 PSIG.

3.HOT:- 255øF [124øC].

4.APU FIRE DETECTION:- ALSO CLOSES FUEL SOV.

5.TURNING BATTERY SWITCH OFF ON GROUND.

APU OIL TANK 1« US GALLONS CAPACITY.

CENTRIFUGAL SWITCH:-

35%:- STARTER CUT OUT [OLD].

50%:- STARTER CUT OUT [NEW].

95%:- READY TO LOAD.

110%:- OVERSPEED.

THERMOSTAT [650øF] MODULATES BLEED VALVE

IMMERSION THERMOCOUPLE [695øF,NOT USED] CLOSES APU BLEED VALVE.

S1:- RESET SWITCH.

K1:- START-STOP RELAY.

K2:- OVERSPEED SHUTDOWN RELAY.

K3:- OVERSPEED ANTICYCLE RELAY.

K4:- FIRE SHUTDOWN RELAY.

K5:- LOW OIL PRESSURE SHUTDOWN RELAY

K6:- STARTER LOCKOUT RELAY.

K7:- START STOP AUXILIARY RELAY.

M280:- APU CONTROL MODULE.

OVERSPEED LT ON AFTER SHUTDOWN -->K1 DOES NOT ENERGIZE.

Contents

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ATA CHAPTER 71 [POWERPLANT]

6 STAGE LPC DRIVEN BY 3 STAGE LPT.

7 STAGE HPC DRIVEN BY 1 STAGE HPT.

SURGE BLEED VALVE LOCATED ON DIFFUSER FAN DUCT AT :-

8TH STAGE BLEED VALVE AT 6 O'CLOCK POSITION.

13TH STAGE AT 4 O'CLOCK AND 8 O'CLOCK POSITIONS

CAN ANNULAR COMBUSTION CHAMBER.

ENGINE DRY WEIGHT:- 3155 TO 3330 lbs.

LENGTH:- 120".

WEIGHT:- 42.5".

PARAMETER -9 -15

TAKE OFF EPR [5mts] 2.03 2.13

N1 94.4 97.4

N2 93.1 94.6

MAX CONTINOUS EPR 1.88 1.96

N1 89.2 91.7

N2 90.7 91.9

PP TRIM STOP EPR 1.84 1.97

N1 88.0 92.0

N2 90.2 92.1

MAX CRUISE EPR 1.75 1.83

N1 85.1 87.6

N2 88.8 90.0

DATA PLATE EPR 1.65 1.65

N1 81.9 81.9

N2 87.3 87.3

IDLE EPR [B.O] 1.03 1.04

[N.B] 1.03 1.04

N2 [B.O] 55.2 56.2

[N.B] 57.2 58.7

EGT T/O LIMIT [øC] 580 620

NORMAL 511 543

MAX CONT LIMIT 540 580

NORMAL 474 508

PP TRIM STOP LIMIT - -

NORMAL 466 510

MAX CRUISE EGT LIMIT 510 550

NORMAL 448 483

DATA PLATE EGT NORMAL 426 446

EGT IDLE LIMIT B/O 480 480

LIMIT N/B 420 420

NORMAL B/O 340 360

EPR:- 115VAC TX BUS

TACOMETER:- SELF POWERED

EGT [OLD]:- SELF POWERED [LINEAR SCALE]

EGT [NEW]:- 115VAC STBY BUS [EXPANDED SCALE]

CONTROL VBI:-28VDC BUS 1

AMPLIFIER:- 115VAC BUS 2

FUEL QTY:- 115VAC STBY BUS

OIL QTY:-115VAC TX BUS

OIL TEMP:- 28VAC TX BUS

OIL PRESSURE:-28VAC TX BUS

INSTRUMENT LIGHTING:-28VDC BUS

FUELFLOW MOTOR:- 28VDC BUS

F/F INDICATOR:- 115VAC TX BUS

LINEAR SCALE EGT USES CHROMEL/ALUMEL AND AFTER FIREWALL USES COPPER/CONSTANTAN.

EXPANDED SCALE ONLY USES CHROMEL/ALUMEL.

SCALE 0 TO 850 DEGC,500 TO 700 DEGC EXPANDED.

VIBRATION PICKUPS FRONT 2 O'CLOCK, REAR 6 O'CLOCK.

VIBRATION MONITORING UNIT:- M420 E3-2.

GAGE IN MILS, WHEN TESTED INDICATOR READS 2.3 TO 4.1 MILS.

PRE P&W SB 5425 :- ONE 8TH STAGE, TWO 13 STAGES SURGE BLEED VALVES.

POST P&W SB 5425:- THREE 8TH STAGES, ONE 13TH STAGE SURGE BLEED VALVE, ONE START BLEED CONTROL VALVE.

DURING ACCELERATION, SURGE BLEED VALVES CLOSES,N1 RISES BY 8%,EPR RISES BY 0.06.

DURING DECELERATION, SURGE BLEED VALVES OPENES,N1 DROPS BY 8%,EPR DROPS BY 0.07.

BEARINGS:-

#1 ROLLER LABRYNTH

#2 DUPLEX BALL LABRYNTH

#3 BALL LABRYNTH

#4 DUPLEX BALL LABRYNTH/CARBON AS PER SB

#4« ROLLER LABRYNTH

#5 ROLLER CARBON

#6 ROLLER CARBON

HPC SUPPORTED BY 3,4,5.

LPC SUPPORTED BY 1,2,4-1/2,6.

CHIP DETECTORS ON #4,#4-1/2,#5,#6 SCAVENGE LINES. OIL TANK, GEARBOX, #1 SCAVENGE LINE.

TOTAL 4 SCAVENGE PUMPS,3 NEAR BEARINGS, ONE NEAR GEARBOX

FUEL HEAT DUTY CYCLE :- VALVE [< 0øC] 1 MIN ON/30 MTS OFF.

FUEL HEAT ON, NO RISE IN OIL TEMP:-PUMP PRIMARY STAGE BYPASS VALVE OPEN, FUEL HEATER BLOCKED.

FILTER ICING:-4.4 TO 5.8 DIFF PRESSURE ON,4.0 TO 2.0 DIFF PRESSURE.

HEATER USES 13TH STAGE AIR,28VDC.

FCU SENSES CDP,CIT,N2 RPM, THROTTLE POSITION.

FUEL FLOW METER POWER SUPPLY MODULE M 316 LOCATED ON E3-3 RACK.

P&D VALVE HAS 200 MESH FUEL INLET SCREEN 150 PSI OPEN SECONDARY PORT.

DATA PLATE SPEED COMPARES N2 WITH EPR.

DATA PLATE SPEED TOLERANCE +1.2% AND -0.8% N2,N2 WITHIN TOLERANCE CAN BE TRIMMED,N2 ABOVE TOLERANCE HAS COMPRESSOR DISTRESS,N2 BELOW TOLERANCE HAS TURBINE DISTRESS.

ENGINE TRIMMING DONE AT PART POWER SETTING WITH ENGINE OPERATING UNDER "NO BLEED, NO LOAD" CONDITIONS.

OAT=_____Deg F,BAR PRESS=______inhg,DATA PLATE RPM=_______%N2,DATA PLATE

CORRECTION=_______%N2,ADJUSTED DATA PLATE=______%N2

TOLERANCE +1.2-0.8.

AFTER RUNUP N2 SHOULD READ ADJUSTABLE +/- TOLERANCE IF SO THEN ENGINE CAN BE

TRIMMED,ADJUST AS PER CHART.IDLE RPM=______%N2,P.P.Pt7=_____inHg,PP

EPR=_____,T/O EPR=_____.

POSITION OF SPACER NORMALLY "S".

INSTRUMENTS USED N2 GAGE AND Pt7 GAGE, FINAL ADJUSTMENTS IN DIRECTION, STOW SPACER, CHECK T/O CONDITIONS, IDLE SCREW ADJUSTMENT :- 16 CLICKS=1%N2,1 REV=32 CLICKS, MIL SCREW 10 CLICKS =Pt7 inHg.

CROSS BLEED START REQUIRES :- 80%N2 RPM.

#7 LOW ENERGY IGNITION/HIGH ENERGY IGNITION.

#4 HIGH ENERGY IGNITION.

LOW ENERGY:- 115VAC 1 SPK/2 SECS 4 JOULES.

HIGH ENERGY:- 28VDC 5 SPK/10 SECS 20 JOULES.

16% TO 17% N2 START LEVER ABDVANCED TO IDLE, START VALVE SHOULD CLOSE 35 TO 40% N2.

LOW IGNITION SPARK GAP IS REPLACEABLE ON EXICTER BOX.

ISOLATION VALVE ENERGIZED LT ON:- LOW PRESSURE.

ISOLATION VALVE DEENERGIZED LT ON:- HIGH PRESSURE 28 VDC.

BEFORE MAINTENANCE ON T/R, PULL CBs, DISCONNECT ELECTRICAL PLUG, PLACE T/R GROUND LOCK ASSY.

 

A/C ISOLATION VALVE PRESSURE ISOLATION VALVE LT

GROUND ENERGIZED HIGH OFF

GROUND ENERGIZED LOW ON

AIR DEENERGIZED LOW OFF

AIR DEENERGIZED HIGH ON

AIR DEENERGIZED HIGH OFF

 

ANTI ICE VALVES 115VAC.

Contents

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