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Title: Boeing 757 OJT Handbook Link: https://rareaviation.com/product/boeing-757-ojt-handbook --- RAW UNFORMATTED TEXT BELOW --- OJT HANDBOOK FOR TRAINING PURPOSES ONLY MAINTENANCE TRAINING PRINCIPAL DIMENSIONS 13-1 Size Comparison w I to 21- PASSENGER COMPARTMENT CONDITIONED AIR DISTRIBUTION NEGATIVE PRESSURE RELIEF ECS CONTROL INDICATION AND WARNING EQUIPMENT COOLING FLIGHT COMPARTMENT CONDITIONED AIR DISTRIBUTION MIX MANIFOLD AND RECIRCULATION SYSTEM FWD CARGO HEAT ENVIRONMENTAL CONTROL SYSTEMS NJ 7 N> TRIM AIR FROM SENSORS NOTE: TOP VIEW OF LETT PACK COOLING PACK ENVIRONMENTAL CONTROL SYSTEM SUPPLY I OVERHEAD PANEL COMPARTMENT TEMPERATURE INOPERATIVE LIGHT (amber) ILLUMINATED - duct temperature overheat or fault in the associated compayagnt temperature control system - associated Compartment Temperatu. Control OFF - trim air OFF COMPARTMENT TEMPERATURE CONTROL AUTO - provides automatic temperature control for associated compartment - rotating the control towards C (cool) or W (warm) sets desired temperature from 65F (1SC) to L5F (30C) OFF - closes the associated compartment trim air valve - associated INOP light illuminates RECIRCULATION FAN SWITCH (alternate action) ON - recirculation fan signaled ON RECIRCULATION FAN INOPERATIVE LIGH> (amber) ILLUMINATED - recirculation fan switch is off or the fan has failed TRIM AIR OFF LIGHT (amber) ILLUMINATED - trim air switch is off TRIM AIR SWITCH (alternate action) ON - trim air regulating valve signaled open AIR CONDITIONING CONTROL PANEL 21-4 OVERHEAD PANEL PACK RESET SWITCH (momentary action) PUSH - resets an overheated pack if the pack has cooled to a temperature below the overheat level PACK INOPERATIVE LIGHT (amber) ILLUMINATED - pack overheat or a fault in the automatic control system PACK OFF LIGHT (amber) ILLUMINATED - pack valve is closed PACK CONTROL SELECTOR OFF - pack valve closed AUTO - pack operation and control is automatic STBY N - (normal) regulates the pack outlet temperature to a constant, moderate temperature C - (cool) sets the pack to full cold operation W - (warm) the pack outlet temperature is controlled by ram air flowing across the pack heat exchangers FOOT HEATER SWITCH LOW or HI - powers an electrically heated floor panel during ground or flight operation SHOULDER HEATER SWITCH LOW or HI - adds heat to the conditioned air flowing to the respective pilot side window area - gives low heat only during ground operation SIDEWALL PANELS AIR CONDITIONING CONTROL PANEL/CREW HEAT 21-5 Recirculation Air Filter 21-6 RECIRCULATION AIR FILTER - REMOVAL/ INSTALLATION THE RECIRC AIR FILTERS ARE LOCATED IN THE AFT END OF THE FORWARD CARGO COMPARTMENT. TWO FILTERS, A PREFILTER AND A HIGH EFFICIENCY FILTER, ARE LOCATED ON EITHER SIDE OF THE MIX MANIFOLD. REMOVAL: 1. REMOVE PARTITION IN AFT END OF FORWARD CARGO COMPARTMENT. 2. FOR THE RIGHT RECIRC AIR FILTER, REMOVE SCREWS FROM FORWARD FACE OF FILTER SUPPORT AND REMOVE TOP RETAINER. 3. FOR LEFT RECIRC FILTER, LOOSEN \ TURN STUDS FROM COVER ASSEMBLY AND REMOVE COVER ASSEMBLY. 4. REMOVE PREFILTER BY PULLING FILTER FIRMLY FORWARD OUT OF SUPPORT. 5. REMOVE HIGH EFFICIENCY FILTER. 6. REINSTALL IN REVERSE ORDER. 21-7 - range from -1,000 feet up to 14,000 feet CABIN ALTITUDE MANUAL CONTROL - controls cabin outflow valve position with the Altitude Mode Selector in MAN mode ~'' CLIMB - valve opens to increase caL altitude DESCEND - valve closes to reduce cabin altitude RELEASE - spring loaded to neutral position CABIN ALTITUDE AUTO RATE CONTROL - sets limit for cabin altitude rate of climb or descent during auto control - index mark establishes approximately 500 fpm climb and ZOO fpm descent AUTO INOPERATIVE LIGHT (amber) ILLUMINATED - AUTO 1 and AUTO 2 cabin altitude control functions are inoperative or when MAN mode is , selected CABIN ALTITUDE MODE SELECTOR AUTO 1 or 2 - activates associated cabin altitude control for automatic operation - outflow valve positioned automatically MANUAL - bypasses both automatic cabin altitude controls - arms cabin altitude manual control LANDING ALTITUDE SELECTOR ROTATE - sets gear driven numbered drums in the landing altitude indicator CABIN ALTITUDE 21-8 CABIN DIFFERENTIAL PRESSURE INDICATOR CENTER PANEL - indicates differential pressure between cabin and ambient in psi CABIN ALTIMETER - indicates cabin altitude in feet CABIN RATE OF CLIMB INDICATOR - indicates cabin rate of climb or descent in feet per minute (fpm) CABIN ALTITUDE LIGHT (red) ILLUMINATED - cabin altitude exceeds 10,000 feet - extinguishes when cabin altitude descends below 8,500 feet PRESSURIZATION LIMIT PLACARDCABIN ALT LIGHT (red) ILLUMINATED - cabin altitude exceeds 10,000 feet - extinguishes when cabin altitude descends below 8,500 feet CABIN ALTITUDE 21-9 ACTUATOR VALVE AIR/GROUND SIGNAL THRUST LEVER POSITION CABIN PRESSURE I WOE CONTHOL MANUAL AUTO RATE AUTO CABIN ALT CONTROLLER BAROMETRICALLY CORRECTED ALTITUDE DESlEND 003401 AUTO CABIN ALT. CONTROLLER| AUTO INOP [ POPE SELECT 2 CABIN ALTITUDE CONTROL SCHEMATIC 21-10 CARGO HEAT The forward and aft cargo compartments are heated by recirculating compartment air. Cargo compartment heating is completely automatic. There are no xontrols or indicators in the cockpit. ,ach compartment has a recirculation fan that is powered automatically at temperatures below 50F (10C). The fans are shut off at temperatures above 70F (21C). Air recirculating in the forward cargo compartment is heated in an air to air heat exchanger using equipment cooling exhaust air as a heat source. Air recirculating in the aft cargo compartment is heated by an electric heater in the duct downstream of the recirculation fan. The heater is powered anytime the fan is powered. AFT |_ CARGO Lz COMPARTMENT CARGO HEAT SCHEMATICS 21-11 EQUIPMENT COOLING SCHEMATIC 21-12 ,11TDMC1,T __ EQUIPMENT COOLING AIR FAN EQUIPMENT COOLING AIR FILTER EQUIPMENT COOLING FAN CHECK VALVEEquipment Cooling System Components 21-13 21-14 FLIGHT CONTROLS - AUTO FLIGHT INTERFACE SIMPLIFIED CAPTAIN'S PANEL (Pl-Z) A/P DISC RED LIGHT A/P AMBER CAUTION LIGHT CAPT'S AUTOLAND STATUS ANNUNCIATOR CONTROL WHEEL A/P DISENGAGE SWITCH CONTROL STAND (P1O) THRUST LEVERS GO AROUND SWITCHES GLARESHIELD (P55) MODE CONTROL PANEL FIRST OFFICER'S PANEL F/O'S AUTOLAND STATUS ANNUNCIATOR CIRCUIT BREAKER PANEL (P11) AUTOFLIGHT SYSTEM CIRCUIT BREAKERS CONTROL WHEEL A/P DISCONNECT SWITCH NJ X) I N) A/P LATERAL CONTROL SERVOS A/P PITCH CONTROL SERVOS AND ELEVATOR NEUTRAL SHIFT TRANSDUCERS UNDER CABIN FLOOR ROLL AND PITCH FORCE TRANSDUCERS FLIGHT CONTROL COMPUTERS LEFT (E2-1) RIGHT (E2-2) CENTER (E2-3) (PZ-1) A/P ROLLOUT GUIDANCE SERVOS (L,CZR) AUTOPILOT FLIGHT DIRECTOR SYSTEM COMPONENT LOCATIONS INPUTS: OUTPUTS IKJMT out ' IWTRUCTION* QROUNO TtST "St" !.S1. FLIGHT CONTROL COMPUTER (3) FLIGHT MANAGEMENT COMPUTER (2) THRUST MANAGEMENT COMPUTER (1) AZP LATERAL CONTROL SERVOS (3) A/P ROLLOUT GUIDANCE SERVOS (3) AJP PITCH CONTROL SERVOS (3) STABILIZER RIM & ELEVATOR ASYMMETRY MODULE (2) N) to I UJ ao rim>MAINTENANCE CONTROL AND DISPLAY PANEL (E/E BAY SHELF E1-2) EICAS DISPLAY (CENTER P-2) MAINTENANCE CONTROL ANO DISPLAY PANEL SYSTEM - SIMPLIFIED 22-2GROUND NUMBER SWITCH SLEW) NO/SKIP SWITCH INFLIGHT FAULTS MODE SELECT SWITCH KEEP ALIVE LIGHTS YES/ADVANCE SWITCH INSTRUCTION PLATE MESSAGE DISPLAY WINDOW--- POWER ON/OFF SELECT SWITCH TEST SELECT (UP GROUND TEST NUMBER SELECT SWITCH (DOWN SLEW) GROUND TEST MODE SELECT SWITCHD MAINTENCE CONTROL AND DISPLAY PANEL 757 BITE TRAINING MAINTENANCE CONTROL DISPLAY PANEL (MCDP) A. PRELIMINARY NOTES 1. The Maintenance Control Display Panel (MCDP) BITE test is performed at manual power up of the unit. Flight faults can be viewed to check for faults from the last flight. Also previous flight faults can be viewed and ground tests can be performed. 2. To perform the Ground Test, either use a remote MCDP in the flight compartment or another person is required (one in the flight compartment, one at the unit in the main equipment center (MEC). In the flight compartment, controls must be operated, the indicators monitored and (if applicable) the MCDP controls operated. If the remote MCDP control panel is used, the MCDP page on EICAS provides the same readout as the MCDP front panel in the MEC. 3. Prerequisites a. Main AC and DC buses must be powered. b. CBs to be closed: Pl 1-3 MAINT CONT-DISPL 115V AC L BUS Pl 1-3 AIR/GND-SYS 1 28V DC L BUS Pl 1-4 AIR/GND-SYS 2 28V DC R BUS c. Airplane on ground. 22-5 757 BITE TRAINING B. BITE TEST PROCEDURE 1. MCDP - ON a. Press ON/OFF switch and observe test pattern on both lines of display. FAIL, FLT FAULTS and GRD TEST lights come on. b. After 5 seconds, a successful test is indicated by the FAIL and GRD TEST lights extinguishing. The FLT FAULTS light remains on indicating the entering of the flight faults mode. The message "LAST FLT FAULTS?" is displayed. 2. Flight Faults Mode a. View Last Flight Faults by the following procedure: (1) Answer "LAST FLT FAULTS?" by pressing YES/ADV switch. (2) If "NO LAST FLT FAULTS" is displayed, the BITE test passes. There were no flight faults stored from the last fl ight. (3) Otherwise, each of the last flight faults can be displayed sequentially by pressing the YES/ADV switch. (4) The list of flight faults and their corresponding diagnostics can be incremented through by pressing FLT FAULTS. 22-6 757 BITE TRAINING (5) Refer to the Maintenance Manual for interpretation of individual flight faults. (6) The message "ALL LAST FLT FAULT DSPLY" marks the completion of the list. b. View Previous Flight Faults by the following procedure (1) Press NO/SKIP in response to the message "LAST FLT FAULTS?" or "ALL LAST FLIGHT FAULT DISPLY" (2) Press YES/ADV in response to the message "PREV FLT FAULT?" (3) The previous flight faults can be reviewed in the same manner as the last flight faults. (4) If the message is "ALL PREV FLT FAULT DSPLY" or "NO PREV FLT FAULTS", pressing YES/ADV or NO/SKIP returns the message "LAST FLT FAULT?" c. Terminate Flight Faults Mode (1) Press ON/OFF to turn off the MCDP or (2) Press GRD TEST to go to ground test mode. 22-7 757 BITE TRAINING 3. Ground Test Mode a. Press ON/OFF switch if not already ON (1) View valid self test (see para 2) (2) View message "LAST FLT FAULTS?" b. Press GRD TEST switch c. View entry messages (1) The following entry messages automatically sequence: '"SYST ENG IN PROGRESS", "COMP TEST IN PROGRESS","INFC DATA IN PROGRESS", 01 FCC TEST?". (2) If any error messages appear in this initialization test, they can be sequenced by pressing YES/ADV. Refer to the Maintenance Manual to interpret the messages. d. Run ground tests 1) To run 01 FCC TEST, press YES/ADV. Refer to the Maintenance Manual for details in performing the test functions. 2) To refuse 01 FCC TEST, press NO/SKIP. The second test, "02 TMC TEST?" is then presented. It can be similarly run or refused. 22-8 757 BITE TRAINING 3) Alternately, the UP and DOWN GRD TEST SEL switches can be used to select from the ground tests listed on the MCDP front panel. e. Terminate Ground Test Mode. (1) Press ON/OFF to turn off the MCDP or (2) Press FLT FAULTS to return to fl ight faults mode. C. VERIFY PROCEDURE - Verification is accomplished by repeating the BITE test procedure or by accessing the appropriate Ground Test. D. RESET PROCEDURE - There is no RESET required. E- REFERENCES 1. Maintenance Manual 22-41-00 2. Wiring Diagram Manual 22-41-00 3. Schematics 22-41-00 4. Fault Isolation Manual 22-41-00 22-9 Diagnostic code can be decoded as -follows: DATA SOURCE FCC=1 FMC=2 TMC=3 INTERMITTENT BIT SET 1=YES OR A SENSOR FAULT O=N0 (SSFDS) OCCURED DURING AUTOLAND AFTER APP SELECTED E-103 FCC 0NLY3 X X XXX X DECIMAL CODE ASSIGNMENT (REF 22-41-00 FAULT ISOLATION CHANNEL PROCEDURES) R-2 C-3 FLIGHT FAULT DIAGNOSTIC DISPLAY FORMAT 22-10 FAULT ISOLATION/ MAINTENANCE MANUAL Autopilot (Flight Control) Flight Faults BITE Procedure Figure 103 (Sheet 1) EFFECTIVITY ALL 22-11-00 01.1 Page 103 Sep 15/83 AFDS - FRM/FIM 22-11 22-12 LEFT ANTENNA CENTER ANTENNA RIGHT ANTENNA AFT PILOT CONTROL STAND (PS) L-VHF COMMUNICATIONS CONTROL PANEL R-VHF COMMUNICATIONS CONTROL PANEL CIRCUIT BREAKER PANEL ASSY (P11) VHF COMMUNICATIONS CIRCUIT BREAKERS FORWARD EQUIPMENT CENTER - E4 RACK L-VHF COMMUNICATIONS TRANSCEIVER R-VHF COMMUNICATIONS TRANSCEIVER C-VHF COMMUNICATIONS TRANSCEIVER (E4-3) (E4-3) (E4-4) VHF COMMUNICATIONS SYSTEM - COMPONENT LOCATIONS PILOTS OVERHEAD PANEL IPS) PILOTS CALL PANEL CIRCUIT BREAKER PANEL (P11-2) PASS ADRS CB (28V DC) TAPE REPRO CB (28V DC) LEMD G - GALLEY L - LAVATORY A - ATTENDANT APU/EXT PWR SHIELD (P34) FASTEN SEAT BELT & NO SMOKING RELAYS LEFT H1SC RELAY PANEL (P36) ELECTRONIC RACK E4 PASSENGER ADDRESS AMPLIFIER (E4-3) AUDIO ACCESSORY UNIT (E4-3) TAPE REPRODUCER (E4-4) RT MISC RELAY PANEL (P37) TAPE REPRODUCER CB (115V AC) OXYGEN DEPLOY INDICATION RELAY RT ENGINE START-TO-STOP RELAY LEFT ENGINE START-TO-STOP RELAY PASSENGER ADDRESS SYSTEM - COMPONENT LOCATIONS 6 SERVICE INTERPHONE SERVICE INTERPHONE JACK LOCATIONS 1. LIGHTS/APU/INTERPHONE PANEL E2A-1 BACT14A M21260 NS2126O RS21260 TURNBUCKLES E2B-3 E2A-3 E2B-2 E2A-2 TYPICAL CABLE LENGTHS Elevator Control Cables 27-8 MACH/SPEED TRIM CONTROL COLUMN CUTOFF STABILIZER CONTROL DIAGRAM 27-9 Horizontal Stabilizer Tri Control Cables 27-10 SPOILER CONTROL DIAGRAM 27-11 27-12 SPOILER ACTUATOR REMOVAL/INSTALLATION WARNING: TO PREVENT INJURY TO PERSONNEL, OPEN CSEU CIRCUIT BREAKERS. THIS WILL PREVENT AUTOMATIC SPOILER RETRACTION WHEN SPOILER IS RAISED AND ELECTRICAL POWER IS REMOVED. 1. CONSULT MM 27-61-02 FOR CIRCUIT BREAKERS TO BE PULLED. 2. DEPRESSURIZE HYDRAULIC SYSTEM SUPPLYING ACTUATOR. 3. DISCONNECT ELECTRICAL CONNECTOR. 4. DISCONNECT ACTUATOR ROD END AND BLOCK SPOILER IN THE UP POSITION. WARNING: DO NOT USE MANUAL RELEASE CAM TO RAISE SPOILER ACTUATOR AND PANEL. MANUAL RELEASE SHOULD ONLY BE USED WHEN ACTUATOR LOCK IS TO BE INSTALLED. 5. DISCONNECT HYDRAULIC LINES. 6. DISCONNECT ACTUATOR PILLOW BLOCK FROM STRUCTURE AND REMOVE ACTUATOR. 7. MEASURE AND RECORD DISTANCE FROM SHOULDER OF LOCK NUT TO ACTUATOR ROD END. REINSTALLATION: 1. CHECK THAT REPLACEMENT ACTUATOR IS FULLY RETRACTED. 2. LOOSEN LOCKNUT AND TURN ROD END TO OBTAIN MEASUREMENT RECORDED FROM REMOVED ACTUATOR. 3. ALIGN ACTUATOR ATTACH POINTS AND CONNECT PILLOW BLOCK TO STRUCTURE. 4. LOWER SPOILER PANEL AND ATTACH ROD ENDS. 5. CONNECT HYDRAULIC LINES AND ELECTRICAL CONNECTOR. 6. ADJUST ACTUATOR PER MM 27-61-02. 27-13 FLAP/SLAT CONTROL DIAGRAM 27-14 TURNBUCKLES LEADING EDGE SLAT POWER DRIVE UNIT LOOKING FORWARD c-c Flaps/Slats Control Cables 27-15 27-16 PORT ELECTRICAL CONNECTOR PORT A MANUAL OVERRIDE LEVER (SHOWN IN NORMAL NO.2 POSITION) LEADING EDGE SLAT BYPASS VALVE PORT LEADING EDGE SLAT BYPASS VALVE 0 LEADING EDGE SLAT POWER DRIVE UNIT LOCATION LEADING EDGE SLAT LOCKOUT 1. OPEN SNAP PANEL ON LOWER LEFT WING-BODY FAIRING FORWARD OF WING LEADING EDGE. 2. REMOVE ELECTRICAL CONNECTOR FROM SLAT BYPASS VALVE. 3. POSITION MANUAL OVERRIDE LEVEL TO POSITION NO. 1 (BYPASS POSITION). 4. OPEN ALTERNATE SLAT POWER CIRCUIT BREAKERS ON MAIN POW IDISTRIBUTION PANEL. P6D20. , J BYPASS VALVE SEE I 8 POWER INSTALL DRIVE UNIT LOCK TE FLAP PDU (VIEW LOOKING AFT) LE SLAT POU TE FLAP POU TRAILING EDGE FLAP LOCKOUT GAIN ACCESS TO LEFT MAIN WHEEL WELL 2. REMOVE ELECTRICAL CONNECTOR FROM T/E FLAP BYPASS VALVE. 3. POSITION MANUAL OVERRIDE LEVER TO THE NO. I POSITION (BYPASS). 4. INSTALL T/E FLAP PDU LOCK B27008-1. 5. OPEN ALTERNATE FLAP CIRCUIT BREAKER ON MAIN POWER DISTRIBUTION PANEL. P6D23. LVDT AND K7DT THE SPOINER/SPEED BRAKE SYSTEMS WILL BE USED TO DEMONSTRATE THE PROCEDURES INVOLVED IN TESTING AND ADJUSTING LINEAR VARIABLE DISPLACEMENT TRANSFORMERS (LVDT) AND ROTARY VARIABLE DISPLACE- MENT TRANSFORMERS (RVDT). LVDT'S AND RVDTS ARE USED TO PROVIDE POSITION INFORMATION SUCH AS SPOILER LEVER POSITION AND SPOILER PANEL POSITION. TO TROUBLESHOOT THE SPOILER/SPEED BRAKE RVDT AND LVDT REFER TO FAULT ISOLATION MANUAL CHAPTER 27-61-00. TO TEST AND ADJUST SPOILER/SPEED BRAKE RVDT'S AND LVDT'S REFER TO MAINTENANCE MANUAL CHAPTER 27-61-00. IN THE FLAP SYSTEM, RESOLVERS ARE USED FOR FEEDBACK INFORMATION. THE RESOLVERS ARE TESTED AND ADJUSTED USING AN ANGLE POSITION INDICATOR (NORTH AMERICAN MODEL 8810-53128). REFER TO MAINTENANCE MANUAL CHAPTER 27-51-33, PAGE 401. THE MAINTENANCE MANUAL ALSO ILLUSTRATES THE USE OF AN ARINC 429 DATA BUS ANALYZER TO ADJUST THE RESOLVERS. THIS PROCEDURE IS FOUND IN CHAPTER 27-58-01, PAGE 513. 27-18 27-19 SPOILER CONTROL MODULE <6 PLACES) FEEDBACK SPOILER/SPEEDBRAKE CLOSED LOOP CIRCUIT This page intentionally left blank. 27-20 FUEL 1. DEMONSTRATE PROPER METHOD OF FUELING AIRCRAFT USING FUELING CONTROL PANEL. (P28) 2. EXPLAIN USE OF LOAD SELECT PANEL AND TEST SWITCHES. 3. DEMONSTRATE PROPER METHOD OF DEFUELING AIRCRAFT. ALSO TRANSFER FUEL FROM ONE TANK TO ANOTHER. 1. LOCATE FUEL BOOST PUMPS - LET STUDENT REMOVE AND INSTALL PUMP. USE MAINTENANCE MANUAL. LOCATE FILL VALVES - LET STUDENT REMOVE AND INSTALL VALVE. USE MAINTENANCE MANUAL. 2. DEMONSTRATE USE OF BITE ON FUEL PROCESSOR UNIT. 28-1 FUELING VALVE SWITCH FUEL - valve(s) in associated tank signaled to open OFF - valve(s) closed NOTE: tank may be filled to desired quantity and the fueling valve closed manually with the respective switch RIGHT WING STATION BATTERY POWER SWITCH ON - electrical power supplied from hot battery bus ./ FUELING VALVE OPEN LIGHT Cblue) ILLUMINATED - associated valve is open SET SWITCH PUSH - value set in load select control appears in the associated load select indicator REPEATED PUSH - blanks the load select indicator TEST SWITCHES ' - for maintenance use only FUEL QUANTITY INDICATOR - shows quantity of fuel tank LOAD SELECT CONTROLS ROTATE - selects desired a tank LOAD SELECT INDICATOR in associated fuel load for - shows quantity of fuel associated tank when set blank when power applied NOTE desired in Any power interuption will blank all the Load Select Indicators DEFUEL OPEN to open VALVE valve SWITCH in associated tank signaled DEFUEL VALVE OPEN LIGHT OFF - electrical power supplied from ground handling bus (blue) ILLUMINATED - associated valve is open External fueling 28-2 CROSSFEED VALVE SWITCH (alternate action) ON - (bar in view) valve signaled open CROSSFEED VALVE LIGHT (amber) ILLUMINATED - valve nor in signaled position MAIN TANK FUEL PUMP SWITCH (alternate action) ON - (bar in view) pump signaled on MAIN TANK FUEL PUMP LOW PRESSURE LIGHT (amber) ILLUMINATED - output pressure low - pump of? FUEL CONFIGURATION LIGHT (amber) ILLUMINATED - low fuel quantity - unbalance between main tanks - center tank pumps off with fuel in center tank CENTER TANK FUEL PUMP SWITCH (alternate action) ON - (bar in view) pump signaled on CENTER TANK FUEL PUMP LOW PRESSURE LIGHT (amber) ILLUMINATED - no fuel remaining with pump switch )N - output pressure low - associated N2 below 50Z with pump switch ON NOTE: Center tank fuel pump low PRESS lights are inhibited with pump switch OFF. FUEL CONTROL PANEL 28-3 28- dischargeN) CO I in BOOST DISCHARGE CHECK VALVE PRIMER DISCHARGE CHECK VALVE TO CROSSFEED MANIFOLD TO TANK - PRIMER DISCHARGE & VAPOR RETURN AUTO SUMPING JET PUMP MAIN TANK PUMP (TYPICAL) REMOVAL CHECK VALVE (POPPET TYPE) INDEX PIN ELECTRICAL CONNECTORDRAIN PLUG BONDING CLIP BONDING JUMPER PRESSURE SWITCH MOTOR/IMPELLER UNIT MOUNTING SCREWS (5 PLACES) (ALLEN HEAD) CAP ENO MOUNTING SCREWS (4 PLACES) DO NOT REMOVE THESE SCREWS REMOVAL LUG (RING) HOUSING MOUNTING BOLTS i WASHERS (8 PLACES) DO NOT REMOVE THESE BOLTS WITH FUEL IN TANK SPAR BOOST PUMPS - MAIN TANKS 28-OUTLET PUMP HOUSINGTO CROSSFEED MANIFOLD MOUNTING SCREW & WASHER (5) OVERRIDE PUMP ELECTRICAL CONNECTOR AUTO SUMPING JET PUMP DISCHARGE CHECK VALVE (FLAPPER TYPE) REMOVAL HANDLE PUMP INLET REMOVAL CHECK VALVE (POPPET TYPE) CENTER 28- WET SIDE REAR SPAR FUELING VALVE 757 BITE TRAINING FUEL QTY 28-8 757 BITE TRAINING FUEL QUANTITY INDICATING SYSTEM (FQIS) PROCESSOR UNIT A. PRELIMINARY NOTES 1. EICAS maintenance message "FUEL QTY BITE" indicates LRU fault storage in FQIS BITE. 2. BITE operations are performed from the face of the processor in the E3-4 rack of the Main Equipment Center. 3. Two-digit hexadecimal fault and status code display on the face of the processor. 4. Prerequisites a. Right main bus and battery bus must be powered for unrestricted BITE operation. b. CB's to be closed: Pl 1-3 FUEL QTY - L Pl 1-4 FUEL QTY - R NOTE: 1) The alternate processor power sources are utilized when the fueling station is powered. 2) A "VERIFY" test cannot be performed with the alternate power sources (fueling station door open). 28-9 757 BITE TRAINING B. PRESS TEST PROCEDURE 1. Push PRESS TEST switch. 2. 88 should appear on the code display. 3. If not, place DISPLAY CHAN SEL toggle switch to opposite position and push PRESS TEST again. NOTES: 1) If a display cannot be obtained on ei ther channel, the processor i s unpowered or inoperative. 2) The position of the toggle switch is of no consequence to normal processor operation. C. BITE STEP PROCEDURE 1. Push BIT switch and record displayed fault code. 2. Repeat until Status Code F8 or F9 appear. 3. Push BIT switch to display Status Code 00 (end of bit). 4. Push BIT switch to blank the display. NOTES: 1) Faults are recalled in the same order as stored. 2) This procedure may be repeated as many times as desired. 3) Initiation of any BITE procedure , ("BIT", VERIFY or RESET) requires a blank display. 28-10 757 BITE TRAINING D. RESET PROCEDURE 1. Push the RESET switch with a blank di spl ay. 2. Status code Fl indicates reset in progress. 3. Status code F2 indicates a successful reset. NOTES: 1) Repairing a fault does not cause it to be unfaulted in the processor memory. RESET is necessary. E. VERIFY PROCEDURE 1. Fueling station door must be closed. 2. Push VERIFY switch. 3. Status Code F4 appears for approximately 22 seconds. 4. Status Code F5 or F6 then appears. a. If F5, no faults are stored. b. If F6, faults were stored. Repeat BIT to determine the fault codes. NOTES: a. RESET should always be performed prior to VERIFY. b. Faults are not stored on the ground with the fueling station door closed, except during VERIFY. 28-11 757 BITE TRAINING F. IDENTIFIABLE LRU's 1. All tank units and wiring 2. Processor Unit 3. Compensators and Wiring 4. Load Select Control 5. Densitometers 6. Flight Compartment Indicators NOTES: 1) Most fault codes are tabulated on the face of the processor. 2) The Load Select Indicators in the fueling station are not assigned processor fault codes. 3) Fault code B7 is assigned to airplane dual discrete disagreements, including: (a) Fueling station door switch (b) Air-ground switch (c) Lbs/Kgs discrete G. REFERENCES 1. Maintenance Manual Chap. 28, Sect. 41 2. Schematic 28-41-01, Sh 2 3. Training Manual 528-41-013-XX 528-41-513-XX 4. Fault Isolation Manual 28-41-00 28-12 SYSTEM DESCRIPTION GENERAL The airplane is equipped with three separate and independant hydraulic systems, titled LEFT, CENTER, and RIGHT. The hydraulic systems provide power to the thrust reversers, brakes, autopilot servos, flight controls, flaps/slats, landing gear and nose wheel steering. The left and right systems are each powered by one engine pump and one electric pump. The center hydraulic system is powered by two electric pumps. If required, a Ram Air furbine (RAT) can power the center hydraulic system. The left systems flaps/slats, landing gear, and nose wheel steering can also receive power from the right hydraulic system through a power transfer unit (PTU). LEFT SYSTEM CENTER SYSTEM RIGHT SYSTEM ELECTRIC ELECTRIC ELEVATORS UNIT (PTU) NOSE WHEEL STEERING RIGHT AILERON R THRUST REVERSER RUDDER RATIO ELECTRIC I ELECTRIC YAW DAMPERS * RIGHT J AUTOPILOT SERVOS LANDING GEAR ~TT~ ENGINE ENGINE VALVE L THRUST REVERSER ALTERNATE BRAKES LEFT AUTOPILOT SERVOS SPOILERS CENTER I of AUTOPILOT SERVOS FLAPS AND SLATS NORMAL BRAKES SPOILERS M ELEVATOR FEEL STAB TRIMHYDRAULIC SYSTEM DIAGRAM 29-1 BLEED LEFT HYD'RAULIC SC-HEMATIC 29-2 29-3 WELL (OUTBD) LEFT SYSTEM COMPONENTS RAM AIR TURB TO FLIGHT CONTROLS CENTER HYDRAULIC SCHEMATIC 29-4 bJ kD I tn LEFT AFT MING TO BODY FAIRING CENTER SYSTEM COMPONENTS RESERVE BRAKES G BLEED AIR -E- OVHT RIGHT HYDRAULIC SCHEMATIC 29-6 FWO ACMP PRESS/CD FILTER MODULE AC MP FILTER MODULE EDP PRESS/CO RIGHT WHEEL WELL FAIRING RIGHT AFT ENGINE STRUT RIGHT SYSTEM COMPONENTS LT WHL WELL _________ WALL (FWD) LEFT SYSTEM RESERVOIR (LEFT WHEEL WELL) (PUMP) POWER TRANSFER UNIT (MOTOR) PTU FILTER MODULE PTU CASE DRAIN FILTER MODULE f LT WHL WELL KEEL BEAM PTU CONTROL VALVE .(RT WHL WELL POWER TRANSFER UNIT COMPONENTS 29- kD TACHOMETER MODULE RAM AIR TURBINE COMPONENTS 29-10 RAT DEPLOY AND RETRACT WARNING: OPEN HYDRAULIC RAT AUTO (P11D27) AND CONT (P11D26) CIRCUIT BREAKERS AND RAT MAN PWP (P6F1) AND CONT (P6E2) CIRCUIT BREAKERS BEFORE PERFORMING PITOT STATIC SYSTEM TESTING. IF SIMULATED PITOT PRESSURE EQUAL TO 80 KNOTS IS APPLIED, THE RAT WILL DEPLOY. 1. OPEN RIGHT MAIN LANDING GEAR DOOR AND INSTALL LOCK. 2. CLOSE RAT MAN PWP (P6F1), RAT MAN CONT (P6F2), HYDRAULICS RAT CONT (P11D26) AND HYDRAULICS RAT AUTO (P11D27) CIRCUIT BREAKERS. 3. REMOVE GROUND MANUAL SWITCH ACCESS PANEL FROM FAIRING ON RIGHT WHEEL WELL AFT BULKHEAD. 4. DEPLOY RAT BY HOLDING GROUND MANUAL SWITCH IN THE DOWN POSITION. WARNING: CHECK THAT ALL PERSONNEL AND EQUIPMENT ARE CLEAR OF RAT AND DOOR ON DEPLOYMENT AND RETRACTION. RAPID ACTION OF RAT AND DOOR MAY INJURE PERSONNEL OR DAMAGE EQUIPMENT. RETRACT RAT: 1. PRESSURE RIGHT HYDRAULIC SYSTEM. 2. POSITION TURBIN HUB TO ALIGN INDEX MARKS ON HUB AND STRUT. 3. HOLD GROUND MANUAL SWITCH IN THE UP (STOW) POSITION UNTIL THE RAT IS FULLY RETRACTED. 4. CHECK THAT RAT UNLOCK LIGHT ON ENGINE START PANEL (P5) IS EXTINGUISHED AND EICAS MSG IS NOT DISPLAYED. 29-11 This page intentionally left blank. 29-12 30- ANTI-ICED ICE DETECTOR PROBE---- ANTI-ICED TOTAL AIR TEMP PROBE (RIGHT SIDE ONLY) NACELLE TAI VALVE (EACH ENGINE) WING TAI VALVE (EACH SIDE) ANGLE OF ATTACK PROBES (EACH SIDE) PITOT PROBES (2 EACH SIDE) WING AND ENGINE ANTI-ICE CONTROL PANEL (PS) TEST AIR DATA CONTIG LCHPTft- R I/O GNO PROX L STALL R LOG INOP WING DUCT YAW DMPR ANTI ICE LEAK L INOP WINDOU/ FUEL R INOP PROSE HEAT QTY TEST PANEL (P61) AUXILIARY ANNUNCIATOR PANEL (P5) ANTI-ICED AREAS WINDSHIELD WIPER SELECTOR OFF - wipers turned off and sequenced to the stowed position LOW - low speed operation HIGH - high speed operation RAIN REPELLENT SWITCH (momentary action) PUSH - applies measured amount of rain repellent to the associated windshield WING ANTI-ICE SWITCH (alternate action) ON - in flight L and R wing anti-ire valves signaled open ENGINE ANTI-ICE SWITCH (alternate action) ON - engine anti-ice valve signaled open - when Engine Start Selector is in AUTO, selected engine igniter(s) operate continuously ENGINE ANTI-ICE VALVE LIGHT (amber) ILLUMINATED - engine anti-ice valve position disagrees with the switch signaled position ICING LIGHT (amber) ON - ice detection system indicates ice build up on the airplane WING ANTI-ICE VALVE LIGHT (amber) ILLUMINATED - associated wing anti-ice valve position disagrees with the signaled position RAIN REMOVAL/ANTI-ICE 30-2 30- ANTI-ICE/RAIN PROTECTION WINDOW HEAT SWITCH (alternate action) ON - signals window heat controller to apply heat to the associated window WINDOW HEAT INOPERATIVE LIGHT (amber) ILLUMINATED - switch is off - overheat or system fault - system test PROBE HEAT LIGHTS (amber) ILLUMINATED -- neither engine running (ground only) - associated probe is not being heated OVERHEAD PANEL WING ANTI-ICE/WINDOW/PROBE HEAT TEST SWITCH (spring loaded to neutral) WING ANTI-ICE - tests operation of wing anti-ice valves WINDOW/PROBE HEAT - tests window and probe heat systems ACCESSORY PANEL WINDOW/PROBE HEAT 30-4