Back to home page737-200 AIRCRAFT NOTES PART 4

Home > Pilot Notes

Contents

Illustrated technical information covering Vol 2 Over 800 multi-choice systems questions Study notes and technical information Close up photos of internal and external components A compilation of links to major 737 news stories with a downloadable archive Illustrated history and description of all variants of 737 Detailed tech specs of every series of 737 Databases and reports of all the major 737 accidents & incidents General flightdeck views of each generation of 737's Description & news reports of Advanced Blended Winglets Press reports of orders and deliveries A collection of my favourite photographs that I have taken of or from the 737 Details about 737 production methods A compilation of links to other sites with useful 737 content Get the book of the website A quick concise overview of the pages on this site

spacer

737-200 AIRCRAFT NOTES PART 4.

 

Notes Prepared from B737-200/P&W JT8D MM from 30th October 1995 to 25th April 1996.

By Mr Meljoe Ferreira

Contents

ATA CHAPTER 21 [AIR CONDITIONING/PRESSURIZATION]

ATA CHAPTER 24 [ELECTRICAL POWER]

ATA CHAPTER 26 [FIRE PROTECTION]

ATA CHAPTER 27 [FLIGHT CONTROLS]

ATA CHAPTER 28 [FUEL]

ATA CHAPTER 29 [HYDRAULICS]

ATA CHAPTER 30 [ICE AND RAIN PROTECTION]

ATA CHAPTER 31 [INSTRUMENTS]

ATA CHAPTER 32 [LANDING GEARS]

ATA CHAPTER 33 [LIGHTS]

ATA CHAPTER 35 [OXYGEN SYSTEM]

ATA CHAPTER 36 [PNEUMATICS]

ATA CHAPTER 38 [WATER WASTE]

ATA CHAPTER 49 [AUXILIARY POWER UNIT]

ATA CHAPTER 71 [POWERPLANT]

 

See more details about the book

All of the information, photographs & schematics from this website and much more is now available in a 374 page printed book or in electronic format.

*** Updated 16 Sep 2016 ***

The 737 Tech Site on Facebook The 737 Tech Site on Twitter

 

ATA CHAPTER 21 [AIR CONDITIONING/PRESSURIZATION]

DUCT OVERHEAT LT:-

190øF,250øF WITH PACK TRIP OFF LT.

PACK TRIP OFF LT:-

210øF,365øF,250øF WITH DUCT OVHT LT.

450 Deg F CONTROL THERMOSTAT:-

MODULATES 13TH STAGE VALVE.

PURGE VALVE OPENS:-

A/C ON GRD,

FLAPS NOT UP,

APU BLEED SW OFF,

PACK Sw On.

OPERATING 28VDC.

ACM CAPACITY:-

300cc.

RAM AIR ACTUATOR:-

115VAC

TURBOFAN VALVE:-

28VDC.

RAM AIR ACTUATOR POSITION:-

S1:- A/C ON GRD.

S2:-FLAPS DOWN,A/C IN AIR,DEFLECTOR DOOR CLOSED.

S3:- AFTER S3 CONTROLLER RELEASED,FLAPS UP,230øF SENSOR TAKES OVER.

S4:- INLET MODULATION PANEL AND EXHAUST LOUVERS ALMOST CLOSED.

 

CONTROL CABIN INLINE FAN ON:- [115VAC][RELAY 28VDC]

A/C ON GRD

ONE PACK ON.

 

MAIN DISTRIBUTION MANIFOLD RELIEF VALVE OPENS:-

17" WATER [0.66 PSI ABOVE CABIN PRESSURE] LIMITS TILL 27" WATER[1 PSI ABOVE CABIN PRESSURE].

190øF THERMAL SWITCH:-

DRIVES MIX VALVE FULL CLOSED.

250øF THERMAL SWITCH:-

CLOSES PACK VALVE,

PACK TRIP OFF LT ON.

AIR MIX VALVE:-

115VAC

GASPER FAN:-

115VAC 3 PHASE.

EQUIPMENT BLOWERS:-

115VAC.

AUTOMATIC FLOW CONTROL VALVE CLOSES:-

2.0 TO 2.8 PSI DIFF PRESSURE.

AIRFLOW DETECTOR [BLOWERS]:-

HAS 380øF THERMAL SWITCH.

NORMAL PRESSURE:-

7.8 PSI MAX.

SAFETY RELIEF:-

8.5 PSI MAX.[9.1 PSI VALVE FULLY OPEN].

NEGATIVE RELIEF:-

-0.2 TO -0.3 [-1 PSI FULLY OPEN].

CABIN ALT WARNING:-

HORN HEARD WHEN CAB ALT > 10,000 FT.

FWD OUTFLOW VALVE:-

115VAC,1 PHASE.

AFT OUTFLOW VALVE:-

115VAC,28VDC.

AUTO MODE:-

CABIN PREPRESSURIZED TO 189 FT BELOW RUNWAY ELEVATION [0.1 PSI] FOR T/O AND 300 FT BELOW RUNWAY ELEVATION FOR LANDING.

CHANGE FROM ASCENT TO ISOBARIC SCHEDULE:-

WHEN A/C CABIN PRESSURE IS 0.25 PSI FROM AMBIENT PRESSURE.

AUTO MODE:-

MAX CABIN ASCENT RATE:-

500 FT/MIN.

MAX CABIN DESCENT RATE:-

300 FT/MIN.

AUTO FAIL LT ON:-

1.AC POWER FAILURE > 15 SECS.

2.>1 PSI/MIN RATE OF PRESSURE CHANGE [1800 FT/MIN].

3.CAB ALT > 13875 FT.

SYBY MODE:- CABIN PREPRESSURIZED TO 200 FT BELOW RUNWAY ELEVATION.

CABIN ALT [AUTO AND STBY MODES]:- > 14,625 FT,OUTFLOW VALVE CLOSES.

MANUAL AC:- 85ø IN 4 SECS [115VAC TX BUS 2].

MANUAL DC:- 85ø IN 8 SECS [28VDC STBY BUS].

 

VALVE POSITION INDICATOR:- 115VAC.

DECR:- 50 FT/MIN.

INCR:- 2000 FT/MIN.

PIP MARK:- 300 FT/MIN.

OUTFLOW VALVE ACTUATOR BRAKE:- 20 TO 29 VDC.

AC ACTUATOR CLUTCH:- NORMALLY ENGAGED, DISENGAGED WITH 28VDC.

DC ACTUATOR CLUTCH:- NORMALLY DISENGAGED, ENGAGED WITH 28VDC.

SWITCH CLOSES CONTACTS WHEN VALVE GATE IS 1/2ø FROM CLOSE.

OUTFLOW VALVE:-1/2ø FROM CLOSE [CLOSING] FWD VALVE CLOSED.


GALLEY POWER:-

115VAC/200VAC 400HZ.

FORWARD GALLEY:-

115VAC GEN BUS 1.

AFT GALLEY:-

115VAC GEN BUS 2.

CARGO COMPT VOLUME FWD:-

370 CU FT.

CARGO COMPT VOLUME AFT:-

505 CU FT.

CLASS D COMPARTMENT.

IN CASE OF CABIN CLIMBING ON DESCENT [THROTTLE BACK]:-

CHECK FOR DUCT LEAKS.

3ø FROM CLOSE [OPENING], FWD OUTFLOW VALVE OPEN.

Contents


ATA CHAPTER 22 [AUTO FLIGHT]

Contents

 


ATA CHAPTER 23 [COMMUNICATIONS]

Contents


ATA CHAPTER 24 [ELECTRICAL POWER]

P5 PANEL:-

P5-2 :-

LE DEVICES.

P5-30:-

THRUST REVERSERS.

P5-14:-

OXYGEN

P5-17:-

TEMPERATURE CONTROL.

P5-19:-

FLIGHT RECORDER.

P5-18:-

STALL WARNING.

P5-3 :-

FLIGHT CONTROLS.

P5-2 :-

FUEL.

P5-10:-

PNEUMATICS.

P5-13:-

AC&DC METERING.

P5-5 :-

CSD & STBY.

P5-4 :-

BUS SWITCHING & GEN AMMS/APU.

P5-9 :-

ANTIICE/WINDOW HEAT.

P5-11:-

ANTIICE.

P5-8 :-

HYDRAULICS.

P5-20:-

DOOR WARNING.

P5-16/P5-6:-

PRESSURIZATION.

115V PHASE TO NEUTRAL.

200V PHASE TO PHASE

AC GENERATOR RATED 40 KVA EACH, APU GENERATOR RATED 40 KVA ON GRD, 45 KVA IN FLT AS BETTER COOLING.

GENERATORS ARE INTERCHANGABLE.

BATTERY:-

22 AMP HR NICAD,24V,20 CELLS.

ENGINE FEEDER LINES:-

6 GAUGE CU THEN 4 GAUGE AL.

APU FEEDER LINES:-

4 GAUGE CU THEN 2 GAUGE AL.

TR UNITS:-

50 AMPERES.

BATTERY CHARGER:-

35 AMPS.

TRANSISTORED INVERTER:-

500VA.

CSD OIL COOLER HAS THERMAL BYPASS FULL OPENS BELOW 150øF [NO OIL THROUGH EXCHANGER].

DIFF PRESSURE BYPASS OPENS AT 50 PSI,AND FULL OPEN AT 90 PSID.

CSD CHARGED 35 PSI.

EXTERNAL FILTER METAL SCREEN, CLEANABLE TYPE, NO BYPASS ONLY INDICATOR [RED].

GOVERNOR ADJUSTMENT ON CSD FOR FREQUENCY ADJUSTMENT [DONE IN SHOP].

RISE [NORMAL]:-

10øC.

IN TEMP:-

55øC.

HIGH OIL TEMP:-

157øC.

CHARGE FILTER [INTEGRAL FILTER] INDICATOR POPS OUT AT 40 TO 55 PSI.

LOW OIL PRESSURE :-

120 TO 160 PSI.

CSD SCHEMATIC:-

FILL PORT--->EXTERNAL FILTER--->COOLER--->CSD--->FILL PORT.

CSD OUTPUT:-

6000 RPM.

CSD CAPACITY:-

1-1/4 US GALLONS.

WET SPLINE CAPACITY:-

1-1/2 US PINTS.

CSD MOUNTED ITEMS:-

CHARGE PRESSURE SENSOR [FOR LOP LT].

DISCONNECT SOLENOID

OIL TEMP OUT [TO OIL COOLER].

OIL TEMP IN [FROM OIL COLLER].

157øC THERMOSWITCH [FOR HOT SWITCH].

 

MANUALLY TRIPPED CSD ALSO TRIPS ENGINE GCR OR FIELD RELAY.

IN SCALE [LOWER]:-

40 TO 160 SCALE.

RISE SCALE [UPPER]:-

0 TO 30 SCALE.

OIL OUT RISES = OIL OUT-OIL IN = AMT OF WORK DONE BY CSD.

RISE AROUND 10ø TO 15øC.IF RISE IS MORE MEANS CSD IS WORKING HARDER THAN NORMAL.

IF IN TEMP IS HIGH IT MEANS THE CSD COOLER IS CLOGGED.

LOP GOES OFF AT 35 TO 40% N2.

GENERATORS 40 KVA,0.95 LEADING TO 0.75 LAGGING,POWER FACTOR 120/208 VOLTS,400HZ AC.

GENERATOR CONSISTS OF AC EXICTER GENERATOR,A ROTATING RECTIFIER AND MAIN GENERATOR.

AC EXICTER CONSISTS OF 6 POLE STATIONARY DC FIELD AND ROTATING ARMATURE. EXICTER FIELD SUPPLIES DC POWER FROM VOLTAGE REGULATOR, THIS CAUSES 3 PHASE VOLTAGE TO BE DEVELOPED IN THE EXICTER ARMATURE. THE VOLTAGE IS RECTIFIED AND FED INTO THE AC GENERATOR ROTATING FIELD. THIS FIELD GENERATES THE USEFUL AC OUTPUT VOLTAGE IN THE AC STATOR. PERMANENT MAGNETS MOUNTED ON EXICTER FRAME BETWEEN 6 STATOR POLES ELIMINATES FLASHING OF FIELD AS RESIDUAL VOLTAGE PROVIDED

 

GENERATOR TERMINALS:-

T1,T4 PHASE A [RED]

T2,T5 PHASE B [BLUE]

T3,T6 PHASE C [YELLOW]

GROUND DIFFERENTIAL PROTECTION TRANSFORMER MOUNTED ON APU GENERATOR ARE INTERCHANGABLE WITH ENGINE GROUND DIFFERENTIAL PROTECTION TRANSFORMERS.

PRINCIPLES:-

1.THERE IS NO PARALLELING OF AC SOURCE OF POWER.

2.THE SOURCE OF POWER SWITCHED ONTO OR ENTERING THE SYSTEM TAKES PRIORITY AND WILL TRIP OFF, OR DISCONNECT THE EXISTING SOURCE.

3.A SOURCE OF POWER DOES NOT ENTER THE SYSTEM AUTOMATICALLY IT HAS TO BE SWITCHED ON WHEN VOLTAGE AND FREQUENCY IS RIGHT.

 

GENERATOR BREAKERS :-

GBs OF ENGINE [2],APU GB & BTBs [2] ARE INTERCHANGABLE AS MAGNETIC LATCH TYPE.

EPC IS NOT INTERCHANGABLE.

APU CAN BE SWITCHED TO ONLY ONE SIDE IN FLIGHT.

TX RELAY IN P6-4 PANEL, AFT R3,R4.

NORMAL:-

GB OR BTB CLOSED, TX BUS POWERED BY GEN BUS 1.

OFF :-

NO COIL ENERGIZED BOTH GBs & BTBs OPEN, TX BUSES NOT POWERED.

ALT :-ONE SIDE GB OR BTB OPEN, BOTH TX BUSES POWERED BY ALT SIDE.

GEN SW ON CLOSES RESPECTIVE GB

APU SW CLOSES APU GB & BTBs [IN FLT ONLY 1 BTB].

GRD PWR SW CLOSES EPC & BTBs

 

TX BUS OFF LT :-

BUS TX RELAY IN CENTER OFF OR NEUTRAL.

BUS OFF LT :-

RESPECTIVE GB & BTB OPEN.

GEN OFF BUS LT :-

RESPECTIVE GB OPEN.

APU GEN BUS OFF LT :-

APU > 95% RPM, APU GB OPEN.

GRD PWR AVAILABLE LT :-

AC PWR RECEPTACLE PLUGGED IN.

PAX CABIN LTS:-

115VAC GRD SERVICE BUS.

SERVICE COMPARTMENT LTS:-

28VAC.

NON ESSENTIAL LTS [PAX READING]:-

28VAC VIA 115VAC MAIN BUS AND TRANSFORMERS

T38,T52 IN J4 AND J5.

T3,T6,T8,T36,T38 LOCATED ON J4.

T37,T52 LOCATED ON J5.

R6:-GRD SERVICE RELAY P6-3.

R9:-TR3 DISCONNECT RELAY.

R89:-BATTERY CHARGER TX RELAY [OPENS WHEN START RELAY R5 ON].

R39:-APU START INTERLOCK RELAY [RELAXES AT STARTER CUTOUT RPM 35/50% RPM].

R1 [EMERGENCY] CONNECTS BATTERY TO HOT BATTERY BUS. [PROVIDED BAT SW ON].

R2 [NORMAL] CONNECTS TR3 TO BATTERY BUS [PROVIDED BAT SW ON].

BATTERY CHARGER:-SOURCE GRD SERVICE BUS 115VAC.

ALT SOURCE:-115VAC MAIN BUS 2.

HOT BATTTERY BUS:-POWERS THE FIRE EXTINGUISHER BOTTLES, THE ENGINE FUEL SOV, BACK UP FOR GCUs.

BATTERY BUS OPERATED BY BATTERY SWITCH.

LOSS OF TR3 CAUSES HOT BATTERY BUS TO SUPPLY BATTERY BUS.

FIRE IN CONTROL CABIN ABNORMAL OR EMERGENCY PROCEDURES:-BOTH GEN SWs TO OFF, PLACE #1 GEN SW ON, IF OK THEN OTHER SIDE ON, CLOSE BUS TX SWITCH GUARD.

ALL FLIGHT INSTRUMENTS AND RADIOS HAVE 8 ELECTRONICS BUSES IN P6 PANEL, 4 115VAC, 4 28VDC, ALL POWERED BY AC TX BUSES.

POWER TO STBY AC BUS FROM 115VAC #1 TX BUS PHASE A.

NORMAL:-

STBY DC BUS FROM #1 DC BUS.

ALTERNATE:-

STBY AC BUS FROM STATIC INVERTER.

STBY DC BUS FROM BATTERY BUS.

R36:-ALTERNATE RELAY.

R37:-NORMAL RELAY [RELAXES IF < 100VAC FROM TX BUS #1 IN FLT, ENERGIZES R36 PROVIDED BATTERY SWITCH IS ON]

AUTO POSITION CAUSES AUTO TRANSFER ONLY IN FLIGHT.

 

BATTERY POSITION USED FOR:-

1.TESTING INVERTER ON GRD OR IN FLT

2.OVERIDING THE AIR/GRD SYSTEM IN FLT IF NECESSARY.

3.TURNING ON THE INVERTER ON GRD TO PWR THE FUEL QTY GAGES FOR GRD REFUELLING

 

IN CASE OF LACK OF APU OR EXTERNAL POWER.

HIGH MODE CHARGING [BATTERY CHARGER] PROVIDES RAPID CHANGE FOLLOWED BY PULSING CHARGE > 16 AMPS, CHARGER ACTS AS TR UNIT.

 

BATTERY CHARGER PUT IN LOW MODE:-

1. BATTERY THERMAL SWITCH OPENS AT 115øF.

2. R1 BATTERY RELAY ENERGIZES BECAUSE OF LOSS OF TR3 INPUT.

3. FUELLING POWER SELECT RELAY R10 ENERGIZED.

 

CIRCUIT BREAKER PANEL:-

P18-1:-ADF,DME,MARKER BEACON, WEATHER RADAR.

P18-2:-CAPT INSTRUMENTS, VHF1, HF1.

P18-3:-ANTI-ICE & RAIN, PITOT HEATERS, WINDOW HEAT CONTROL.

P18-4:-OXYGEN SYSTEM, AVATORIES, SHAVER & VACCUM CLEANER OUTLETS.

P6-1 :-COMM, AIR DATA, F/O INST, F/O NAV, #2 ELECT,#1 ELECT.

P6-2 :-AUTOPILOT, ENGINE, FLT CONT, HYDRAULIC, INPH PWR, LDG GEAR, FIRE PROTECTION.

P6-3 :-MICS, FUEL SYSTEM, COCKPIT LTS.

P6-4 :-TEMP CONTROL, AIR CONDITIONING, PRESSURIZATION, AC BUS INDICATION.

P6-11:-GEN BUS 1.

P6-12:-GEN BUS 2.

G7 :-BPP.

G5 :-APU GCU.

G4 :- #2 GCU.

G3 :- #1 GCU.

TO CLOSE GCR--->CLOSE GEN SW TO ON MOMENTARILY.

7 WAYS TO TRIP GCR:-

MANUAL:-

1.GEN SW MOMENTARILY TO OFF.

2.FIRE HANDLE PULLED.

3.CSD DISCONNECT SWITCH ACTIVATED MOMENTARILY.

AUTOMATIC:-

1.OVER VOLTAGE.

2.UNDER VOLTAGE.

3.OVERCURRENT.

4.DIFFERENTIAL CURRENT PROTECTION.

FF:-DIFFERENTIAL FAULT, A DIFFERENCE BETWEEN CURRENT LEAVING THE GENERATOR AND CURRENT ARRIVING AT P6 PANEL CALLED FEEDER FAULT.

FF [FEEDER FAULT]:- BY GCR TRIP FROM CURRENT FAULT, OVERCURRENT OR DIFFERENTIAL

CURRENT FAULT.

HV [HIGH VOLTAGE]:-

>130 +/-3 VOLTS.

LV [LOW VOLTAGE] :-

<100 +/-3 VOLTS, FIRE HANDLE PULLED [7 +/- 2SEC TIME DELAY].

MT [MANUAL TRIP] :-

MANUAL TRIP, GEN SWITCH TO OFF, CSD DISCONNECT.

ERASE BUTTON:-

ERASES FF, HV, LV LTS.

MT LTS ERASED BY MOVING GEN SW TO ON MOMENTARILY.

EXTERNAL POWER RECEPTACLE:-

RED NEON LT [EXTERNAL PWR CONNECTED].

WHITE LT [NOT INUSE].

NOT IN USE LT OFF WHEN GRD PWR SW ON AND EPC CLOSES, GRD SERVICE SW ON & GRD SERVICE RELAY ENERGIZES,REFUELING DOOR OPEN REFUEL PWR CONTROL RELAY ENERGIZES.

POWER TEST MODULE M400 USED TO TEST SYSTEM.

AC VOLTMETER SCALE [UPPER] :- 100 TO 130 VOLTS.

LOWER SCALE :- 0 TO 30 VOLTS.

IF GENERATOR IS TURNING WITH GCR OPEN AND RESIDUAL BUTTON PRESSED. VOLTMETER READS 15 TO 20 VOLTS.

Contents


ATA CHAPTER 25 [EQUIPMENT & FURNISHING]

Contents


ATA CHAPTER 26 [FIRE PROTECTION]

ENGINE AND APU FIRE DETECTION UNIT:- M279.

COMPARTMENT OVHT UNIT:- M237.

P28 APU REMOTE FIRE PANEL.

ENGINE OVHT:- 400øF.

ENGINE FIRE:- 600øF.

CARD FAULTY:- IF TEST SW ON MODULE DOES NOT ILLUMINATE LIGHT.

PULLING FIRE HANDLE:-

BLEED VALVE CLOSES,

HYDRAULIC SOV CLOSES,

LOP LT DISARMED,

FUEL SOV CLOSES,

TR ISOLATION VALVE DISARMED,

GCR IN GCU TRIPS [7 +/- SEC],

GB TRIPS.

APU FIRE DETECTOR:- 400øF.

TAILPIPE FIRE DETECTOR:- 750øF.

EXHAUST DUCT OVHT DETECTOR:- 360øF.

OVHT/INOP TEST:- TEST ENGINES 1 AND 2 OVHT DETECTOR CONTINUITY AND APU FIRE DETECTOR SHORT CIRCUITARY DRISCRIMINATION.

THE FIRE TEST SWITCH POSITIONS TESTS ENGINE 1 AND 2,APU AND WHEEL WELL FIRE DETECTOR CONTINUITY.

APU FIRE HANDLE:- FUEL SOV CLOSES,

INLET DOOR CLOSES,

GCR IN GCU TRIPS [7 +/- 2 SECS],

APU GB TRIPS

ARMS EXTINGUISHER SWITCH.

FIRE BOTTLE THERMAL DISCHARGE:- 266øF.

WHEEL WELL FIRE WARNING:- 400øF.

WING BODY OVHT LTS:- 250øF,AUTORESET.

M237 SW UP :- LT GOES OUT [SHORTS].

SW DOWN:- LT ON [OPEN].

LAVATORY FIRE EXTINGUISHER [FREON 1301 400 GMS]:- 180øF.

Contents


ATA CHAPTER 27 [FLIGHT CONTROLS]

AILERON TRAVEL LIMITS -- 4.01" UP & DOWN FROM NEUTRAL .

AILERON TAB TRAVEL LIMITS --

AILERON UP, TAB 1.25"DOWN.

AILERON NEUTRAL, TAB 0.07"UP.

AILERON DOWN, TAB 1.25"UP.

AILERON HAS FOUR HINGES.

AILERON TRIM WHEEL TRAVEL 3.55 TURNS L/R.

FLIGHT CONTROL MODULE PRESSURE SWITCH ILLUMINATES AMBER LOW PRESSURE LIGHT ON

FLIGHT CONTROL PANEL P5 < 1200 PSI LIGHT ON,>1500 PSI LIGHT OUT.

COMPENSATOR IN MODULE KEEPS RETURN FLUID PRESSURIZED FOR WIND GUST PROTECTION WHEN THE FLIGHT CONTROL SWITCH IS PLACED IN STBY RUDDER POSITION, THE LOW PRESSURE LIGHT IS A VALVE POSITION INDICATION AND NOT A HYDRAULIC PRESSURE INDICATION.

BYPASS VALVE OF PCU WILL CLOSE WHEN HYDRAULIC PRESSURE < 645+/-75 PSI, OPEN > 645+/-75 PSI. WHEN BYPASS VALVE IS CLOSE BOTH SIDES OF ACTUATOR CHAMBERS ARE INTERCONNECTED

EXTRA COMPONENTS ON SYSTEM B PCU ARE --

AUTOPILOT SHUTOFF VALVE

TRANSFER VALVE

SELECTOR VALVE

FILTER ASSEMBLY

ENGAGE MECHANISM

LINER TRANSDUCER

SPOILERS NO 1,4,5,8--GROUND SPOILERS 'A'

NO 2,7 --FLIGHT SPOILERS 'B'

NO 3,6 --FLIGHT SPOILERS 'A'

GROUND SPOILERS DEPLOYED-- 60ø.

FLIGHT SPOILERS DEPLOYED-- 40ø.

SPEED BRAKE LEVER 0 TO 23ø.--- SPOILER DOWN PRESSURE PORTED FROM GROUND SPOILER CONTROL VALVE TO GROUND SPOILER BYPASS VALVE.

SPEED BRAKE LEVER 31ø + -- PORTS UP PRESSURE GROUND SPOILER BYPASS VALVE OPEN WHEN RH MLG ON GROUND.

FLIGHT SPOILER HEX HEAD ADJUSTMENT PROVIDES FOR 9ø CONTROL WHEEL TRAVEL BEFORE SPOILER PICKUP.

NO INPUT TO FLIGHT SPOILER ACTUATORS, DOWN PRESSURE PORTED VIA HOLD-DOWN AND THERMAL CHECK VALVE.

SPOILER TRAVEL LIMITED BY STROKE OF ACTUATOR, NO MECHANICAL STOPS.

FOUR ELECTRICAL SWITCHES ARE CONTROLED BY THE SPEED BRAKE SYSTEM --

-- TAKE OFF WARNING.

-- AUTO SPEED BRAKE ARMING

-- AUTO BRAKE OFF RAMP

-- AUTO BRAKE ARMING

MAXIMUM SPOILER RESPONCE OCCURS WITH THE SPEED BRAKES DOWN.

GROUND SPOILERS HAVE MECHANICAL LOCKS IN ACTUATOR

OUTBOARD LOCKS WHEN PISTON RETRACTED

INBOARD LOCKS WHEN PISTON EXTENDED

"SPEED BRAKE DO NOT ARM" AMBER LIGHTS -- INDICATES PROBLEM IN THE CONTROL SYS.

"SPEED BRAKE ARMED" GREEN LIGHT----INDICATES NO PROBLEM SENSED IN THE CONTROL SYS

TEST SWITCHES-- TESTS SPEED BRAKE FAILURE AND MONITORING CIRCUITS.

AUTOMATIC GROUND SPEED BRAKE SYSTEM IS CONTAINED IN M338 MODULE.

THE CONTROL CIRCUIT OPERATION IS A FUNCTION OF

--ANTISKID [WHEELSPEED] [4 SECONDS]

-- AIR/GRD

-- THROTTLE POSITION

-- THRUST REVERSER OPERATION

-- SPEED BRAKE LEVER POSITION

WHEEL SPEED > 60 MPH T/R SELECTED, SPEED BRAKE ACTUATOR CAUSES ALL SPOILER PANELS TO DEPLOY

SYSTEM MALFUNCTION TURNS ON AMBER LIGHT AND TURNS OFF GREEN LIGHT [SPEED BRAKE]

MALFUNCTIONS ARE

-- ELECTRICAL POWER IN DISTRIBUTION SYSTEM DUE TO FAILED WHEEL SPEED RELAY

-- SHORT CIRCUIT IN DISTRIBUTION SYSTEM

-- SPEED BRAKE ACTUATOR NOT IN FULL DOWN POSITION

-- GO AROUND RELAY ENERGIZED

-- BOTH ANTISKID CHANNELS INOP

 

TEST SWITCHES SIMULATE FAILURES CANNOT BE USED FOR TROUBLESHOOTING

TEST SWITCH NO1- SIMULATES IMPROPER ELECTRICAL POWER IN THE DISTRIBUTION SYSTEM

TEST SWITCH NO2- SIMULATES A SHORT CIRCUIT IN THE DISTRIBUTION SYSTEM

TEST SWITCH NO3- SIMULATES AN ADVANCED THROTTLE AND SUPPLIES ELECTRICAL POWER TO THE DISTRIBUTION SYSTEM. THE TEST SWITCHES SHOULD BE USED AFTER SPEED BRAKE IS ARMED [GREEN LIGHT], PRESSING SWITCH CAUSES AMBER LIGHT ON & GREEN LIGHT OFF

GREEN SPEED BRAKE LIGHT ON IF SPEED BRAKE LEVER IN ARMED POSITION AND--

1. NO SPEED BRAKE TEST BUTTONS PUSHED

2. AT LEAST ONE INBD OR OUTBD ANTISKID SYSTEM ON AND OPERATABLE

3. SPEED BRAKE HANDLE ACTUATOR IN SPEED BRAKE DOWN POSITION

4. SPEED BRAKE ELECTRICAL CIRCUITARY READY TO OPERATE

AMBER LIGHT ON IF SPEED BRAKE LEVER PLACED IN ARMED POSITION AND --

1. ANY SPEED BRAKE TEST BUTTON PUSHED OR

2. TOTAL ANTISKID [INBD & OUTBD] INOP OR OFF OR

3. SPEED BRAKE HANDLE ACTUATOR NOT IN CORRECT POSITION TO OPERATE TO 'SPOILERS UP'

OR

4. A DETECTED SPEED BRAKE ELECTRICAL CIRCUIT MALFUNCTION

 

THE LOAD LIMITER SYSTEM AND ASYMETTRIC SYSTEM DO NOT FUNCTION DURING

ALTERNATE OPERATION.

 

'A' PRESSURE--->FLOW LIMITER--->CONTROL VALVE--->BYPASS VALVE--->FLAP POWER

UNIT--->MOVES FLAPS

 

SWITCHES ON FLAP CONTROL UNIT

--LEADING EDGE INDICATION [FLAPS 10 UNITS]

--MACH TRIM

--LANDING WARNING

--TAKEOFF WARNING

--FLAPS DOWN LIMIT

--FLAPS UP LIMIT

FLAP LOAD LIMITER TEST

SWITCH TEST--FLAPS NOT >30ø,TEST LIGHT [GREEN] ON, CONTINUITY CHECK

SYSTEM TEST--FLAPS>30 UNITS, FLAPS GO TO 30 UNITS FROM 40 UNITS, WHEN SWITCH RELEASED, FLAPS GO BACK TO 40 UNITS POSITION.

FLAP POSITION IS INDICATED IN UNITS

INBD AFT FLAP DECLUTCHING FORCE IS 300lbs

FLAP TRANSMITTER--28VAC INDICATION SYSTEM

[LEFT] --FLAP INDICATION

[RIGHT]-- FLAP INDICATION, STALL WARNING

INDICATOR USED IN ASYMMETRY PROTECTION SYSTEM 8ø TO 20ø DEVIATION BETWEEN NEEDLES

ASYMMETRY TEST--FLAPS ANY POSITION BUT 1 UNIT, ONE NEEDLE GOES TO 1 UNIT, FLAP BYPASS VALVE CLOSES [BYPASSES][GREEN LIGHT ON WHEN VALVE CLOSED] OR FLAPS MOVING, MOVE SWITCH TO ON, FLAPS STOP UNTIL SWITCH RELEASED

 

LE FLAPS RETRACT PRESSURE TO ACTUATOR IS DIRECT WHILE RETURN IS VIA CONTROL VALVE

TE FLAPS 1 TO 5 UNITS--FLAPS EXTEND, SLATS EXTEND

TE FLAPS 5 TO 10 UNITS-- FLAPS EXTEND, SLATS FULL EXTEND

FLAPS LE ACTUATOR HAS NO MECHANICAL STOPS

LE SLAT ACTUATOR HAS MECHANICAL LOCK IN RETRACTED POSITION

EACH SLAT HAS 1 ACTUATOR/3 POSITION

EACH FLAP HAS 1 ACTUATOR/2 POSITION

EACH SLAT HAS 2 MAIN TRACKS, SLAT 2,3,4,5 HAVE 2 AUXILARY TRACKS

SLAT 1,6 HAVE 3 AUXILARY TRACKS

AUXILARY TRACKS ARE USED AS STABLIZING DEVICE FOR LE SLAT IN THE EXTEND POSITION, THE DETENT ARM WILL HOLD THE EXTENSION ARM ROLLER AND PRELOAD THE TORSION BAR THIS HELPS TO STABLIZE THE SLAT ASSEMBLY

THE EXTENSION AEM ROLLER DO NOT BOTTOM IN TRACKS

REED SWITCHES GIVES FULL UP INDICATION

PROXIMINY SWITCHES [2] GIVE EXTEND, FULL EXTEND INDICATION

UPSTOP ON MAIN TRACKS FWD END OF SLAT

DOWN STOP ON AFT TRACK OF SLAT EACH END, STRIKER PLATES ON SLATS

UPSTOP CONTACTS DOWN STOPS NEVER CONTACT NORMALLY

M229 MODULE LE FLAP AND SLATB INDICATING MODULE E3-2

STALL WARNING SYSTEM AMBER 'OFF' LIGHT ON STALL WARNING MODULE INDICATES---

1.LOSS OF AC PWR TO RESPECTIVE MODULE

2.LOSS OF DC PWR TO RESPECTIVE MODULE

3.LOSS OF HEATER CURRENT TO RESPECTIVE AIRFLOW SENSOR

STALL WARNING SWITCH--

NORMAL--SYSTEM IS OPERATIONAL WITH OFF LT EXTINGUISHED AND L/G SAFETY SENSOR IN AIR MODE,OR RESPECTIVE ENGINE RUNNING

TEST--[MOMENTARY]--WITH ENGINE NOT RUNNING, OFF LIGHT EXTINGUISHES, INDICATOR SPINS, CONTROL COLUMN SHAKES AND STICK NUDGER OPERATES WITH ENGINE RUNNING, OFF LT REMAINS EXTINGUISHED, INDICATOR SPINS, CONTROL COLUMN SHAKES AND STICK NUDGER OPERATES.

HTR OFF-REMOVES VANE HEATER POWER AND PROVIDES AIR MODE SIGNAL FOR MAINTENANCE CHECKS

STABLIZER MAX TRAVEL LIMIT 17 UNITS

GREEN BAND[T/O RANGE]--2.8 TO 9.0 UNITS

A/P ACTUATOR TRAVEL--2.3 TO 12.5 UNITS

ELECTRIC ACTUATOR--2.8 TO 12.5 UNITS

TAKEOFF--9 UNITS, NORMALLY 5 UNITS

PHASE SEQUENCE RELAY R63--PREVENTS OPERATION OF THE MAIN ELECTRIC SYSTEM IF 3 PHASE POWER TO THE MOTOR IS NOT IN THE PROPER PHASE RELATION

SAFETY RELAY PREVENTS MOTOR DRIVE WHENEVER CONTROL POWER IS REMOVED OR LOST R66.

TRIM CONTROL RELAY R64

MAX ELEVATOR TRAVEL LIMITED BY ACTUATOR STROKE, NO MECHANICAL STOPS. HYDRAULIC DAMPING PROVIDES WINDGUST LOCKS

ELEVATOR TRAVEL UP 14.6" DOWN 10.55"

TAB TRAVEL [ONLY WITH NO HYDRAULICS]

WITH ELEVATOR UP 0.92" DOWN

WITH ELEVATOR NEUTRAL 0.22" UP

WITH ELEVATOR DOWN 1.03" UP

ELEVATOR FEEL FORCES VARY AS PER AIRSPEED AND STABILIZER TRIM

DIFF PRESS >25% DIFFERENTIAL PRESSURE LIGHT ON PROVIDED FLAPS ARE FULL UP

T/O WARNING TEST--PUSH EITHER EPR TEST SWITCH ON THE M528 ENGINE ACCESSORY MODULE WHILE THE CORRESPONDING THROTTLE IS ADVANCED, THE RED LIGHT WILL ILLUMINATE ON THE 528 MODULE

IN CASE OF T/O WARNING HORN ON

TO SILENCE HORN--

1.REDUCE BOTH ENGINE EPRs TO LESS THAN 1.4,OR

2.POSITION SPEED BRAKE LEVER IN DOWN DETENT AND PLACE TRAILING EDGE FLAPS AND STABLIZER IN PROPER T/O RANGE

HORN OFF IN FLIGHT

RUDDER DOES NOT HAVE MANUAL REVERSION CAPABILITY, RUDDER HAS NO MECHANICAL STOPS

BUS ROD CONNECTS CAPT & F/O RUDDER PEDALS

RUDDER TRAVEL 21.82" L/R [26DEG]

TRIM--10.22" FROM NEUTRAL[NEW]

MODULE-->ISOLATION VALVE-->PCU-->

STBY PUMP-->STBY MODULE-->STBY RUDDER PCU

YAW DAMPER CONTROL IS LIMITED TO 2ø L/R OF RUDDER CONTROL POSITION

Contents


ATA CHAPTER 28 [FUEL]

CAPACITY--TANK#1&2---1430 US GALLONS/5413 LTS/4222 KGS EACH

CTR---2300 US GALLONS/8717 LTS/6800 KGS EACH [VARIES PER A/C]

TOTAL--15244 KGS

TOTAL 12 ACCESS PANELS BELOW WING

SURGE TANK CAPACITY---30 US GALLONS

FUELLING VALVES--28VDC,BLUE LT INDICATES FUEL SOLENIED ENERGIZED DO NOT OPEN OVERWING FILLER CAP IF PRESSURS FUELLING HAS CAUSED TANK TO BE FILLED DUE TO LOCATION OF PORT, FUEL WILLSPILL OUT.

MAIN TANK--11 TANK UNITS,1 COMPENSATOR UNIT.

CTR TANK--2 TANK UNITS,1 COMPENSATOR UNIT.

WHEN SUCTION DEFUELLING ONE TANK, THE OTHER TANK BYPASS VALVE SHOULD BE CLOSED. BOOST PUMPS 3 PHASE,115VAC,400HZ.

WHEN REPLACING CTR TANK BOOST PUMP, CLOSE OPPOSITE SIDE CTR TANK BOOST PUMP VALVE TO PREVENT FUEL FLOW BACK THROUGH REPRIME LINE.

MAIN TANK AFT BOOST PUMP POWERED BY TRANSFER BUS [AS EMERGENCY SOURCE] OTHER PUMPS POWERED BY MAIN BUS.

BOTH LOW PRESSURE LTS ON IN ONE TANK ILLUMINATES MASTER CAUTION LTS.

WHEN REPLACING ENGINE SOV THAT SIDE BYPASS VALVE PLUNGER SHOULD BE PULLED ,IN CASE OF CROSSFEED VALVE BOTH PLUNGERS SHOULD BE PULLED.

SOV [ENGINE/CROSSFEED]---24V/28VDC

FUEL TEMPERATURE GAGE SUPPLY---28VAC THEN RECTIFIED

Contents


ATA CHAPTER 29 [HYDRAULICS]

HYDRAULICS---

SYSTEM'A'.

SYSTEM'B'.

STANDBY SYSTEM.

FLUID SPECIFICATION---BMS 3-11.

FLUSHING SYSTEM REQUIRES 100 US GALLONS.

NORMAL CAPACITY IS 23.6 US GALLONS.

'A' 'B' 'STBY'

RESERVOIR

[US GALLONS] 3.6 1.3 1.9

PUMP [PSI] 3000 3000 2950

[GALLONS/MIN] 22.5 6 3

FILTERS

[PRESSURE] 2 2 1

[RATING][MICRON] 5-15 5-15 5-15

CASE DRAIN 2 2 1

[RATING][MICRON] 10-25 10-25 10-25

RETURN 1 1 1

[RATING][MICRON] 15 10-25

GRD PWR MODULE 5-15

HYDRAULIC SERVICE FILTER 0.4-3

[RATING][MICRON]

VENT FILTER[MICRON] 10

[UNCLEANABLE]

AIR PRESSURE FILTER 200

[MICRON][CLEANABLE]

LOW PR WARNING

[PSI] 1100-1500 1100-1500 1100-1500

LOW PR LTS 2 2 1

OVHT LTS -

220øF[ON] -

235øF[ON]

265øF[OFF]

275øF[OFF]

PR RELIEF VALVE 1 1 1

[PSI] 3500+/-400 3500+/-50 3500+/-50

3100 3400 3400

 

NO EXTERNAL LEAK PROVIDED FROM B NUT

NORMALLY 13TH STAGE AIR USED FROM ENGINE FOR HYDRAULIC PRESSURISATION OF RESERVOIRS

 

NORMAL OPERATIONS

[DESPATCH OPERATIONS]

TUBE CONNECTIONS:-

NO VISIBLE EVIDENCE OF LEAKAGE

[NO VISIBLE EVIDENCE OF LEAKAGE]

STATIC SEALS:-

1 DROP/10MINS

[DETERMINED BY OPERATOR]

DYNAMIC SEALS:-

EDP INLINE VIKERS/ABEX---

30 DROPS/MIN

[60 DROPS/MIN]

YOKE TYPE [VICKERS]---

7 DROPS/MIN

[10 DROPS/MIN'CORRECT AT 1ST OPP]

EMDP TASK/ABEX---

10 DROPS/MIN

[20 DROPS/MIN]

VICKERS---

20 DROPS/MIN

[30 DROPS/MIN,CORRECT AT 1ST OPP]

OTHER DYNAMIC SEALS UNDER STATIC CONDITIONS OF FULL OR PARTIAL PRESSURE---

1 DROP/10 MINS---NO REPAIR REQUIRED,

1 DROP/10 MINS TO 1 DROP/MIN---CORRECT AT INTERMEDIATE CHECK

[1 DROP/ MIN UPTO 30 DROPS/MIN CORRECT AT 1ST OPP]

OTHER DYNAMIC SEALS UNDER DYNAMIC CONDITIONS---

1 DROP/CYCLE

[1 DROP/CYCLE]

Contents


ATA CHAPTER 30 [ICE AND RAIN PROTECTION]

115VAC POWERED ANTIICE VALVE,

NO1&NO2 WINDOWS HEATED TO 110øF,145øF OVHT

NO4&NO5 WINDOWS HEATED TO 90ø TO 110øF

PWR 'ON' LT WILL ILLUMINATE WHEN POWER IS FLOWING THROUGH THE

AUTOTRANSFORMER, AND THE WINDOW IS DRAWING 5 WATTS OF POWER OR MORE.

'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].

    Contents


    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


    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.

    Contents


    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.

    Contents


    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


    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

    .

Footer block

This site has had visitors to date.