757GFSG(06)

AeroEd LLC – Aviation Education Resource

B757 GENERAL FAMILIARIZATION SELF-PACED

This course covers an overview of the Mechanical Systems to include: Description and Operation, Controls and Indications, Component Location, & Servicing.

OBJECTIVES Upon completion of this training, using the study guide provided and appropriate Maintenance Manuals, the student will be able to:

1) Describe the safety precautions to be observed when working on or near the aircraft and its systems. 2) Describe the locations of principle components. 3) Describe the normal functions of each major system, including terminology and nomenclature. 4) Using the proper maintenance manual reference, perform all aircraft system servicing tasks. 5) Interpret reports provided by the crew members.

757 General Familiarization (7-2005) ATA 06 - Page 1 For Self-Paced Training Purposes Only




TABLE OF CONTENTS 757 GENERAL FAMILIARIZATION SELF-PACED

ATA 06 B757 GENERAL FAMILIARIZATION SELF-PACED ........................................................................................................1 OBJECTIVES................................................................................................................................................................1 MANUAL ARRANGEMENT AND NUMBERING SYSTEM ...............................................................................................4

Chapter Numbering ............................................................................................................................................5 Effectivity and Configuration Numbering ............................................................................................................6 Page Numbering .................................................................................................................................................8

LIST OF ABBREVIATIONS...........................................................................................................................................9 REFERENCE PLANES AND LINES.............................................................................................................................. 15

Standard Abbreviations and Definitions ........................................................................................................... 15 Fuselage ........................................................................................................................................................... 15 Wing ................................................................................................................................................................. 15 Vertical Stabilizer ............................................................................................................................................. 16 Horizontal Stabilizer ......................................................................................................................................... 17 Power Plant ...................................................................................................................................................... 18

PRIMARY AIRCRAFT DIMENSIONS ........................................................................................................................... 22 DIMENSIONS ............................................................................................................................................................ 23

Overall Airplane:............................................................................................................................................... 23 Wing: ................................................................................................................................................................ 23 Horizontal Stabilizer: ........................................................................................................................................ 23 Vertical Stabilizer: ............................................................................................................................................ 23 Fuselage: .......................................................................................................................................................... 24 Areas: ............................................................................................................................................................... 24

BODY STATION DIAGRAM........................................................................................................................................ 26 VERTICAL STABILIZER AND RUDDER STATION DIAGRAM....................................................................................... 28 HORIZONTAL STABILIZER AND ELEVATOR STATION DIAGRAM.............................................................................. 29 WING STATION DIAGRAM......................................................................................................................................... 30 ENGINE AND NACELLE STATION DIAGRAM ............................................................................................................. 31 ZONE DIAGRAMS ...................................................................................................................................................... 32

Major Zones...................................................................................................................................................... 32 SERVICE INTERPHONE SYSTEM............................................................................................................................... 34

Component Details ........................................................................................................................................... 34 Audio Amplifier ................................................................................................................................................ 34 Service Interphone Switch................................................................................................................................ 34 Operation.......................................................................................................................................................... 36 Control.............................................................................................................................................................. 36 Cabin Interphone System.................................................................................................................................. 38 Cabin Interphone Handsets............................................................................................................................... 38 Pilots' Call Panel .............................................................................................................................................. 38 Operation.......................................................................................................................................................... 38 Control.............................................................................................................................................................. 40





MANUAL ARRANGEMENT AND NUMBERING SYSTEM

The Maintenance Manual is divided into chapters and groups of chapters. Each group and every chapter has a tab provided for ease of location. The chapterization separates the manual into the primary functions and systems of the airplane. The chapters are further divided into sections and subjects to provide for subsystem and individual unit breakout. Each chapter, section and subject is identified by an assigned number. Each page carries the assigned subject number, page number, page code and the revision date. In addition, the Power Plant chapters are issued in a self-contained set or sets (as applicable, if you have more than one engine type in your model fleet). These pages are further identified by an engine sub-logo, for example PW2000 SERIES ENGINES or RB211-535 SERIES ENGINES, placed to the right of the Maintenance Manual logo at the top of the page. The numbering system is described in detail in the paragraphs that follow.

Chapter Numbering Chapterization of the maintenance manual has provided a functional breakdown of the entire airplane. The chapter breakdown numbering system uses a three element number (XX-XX-XX). It provides for dividing the material into Chapters, Sections, and Subjects. The three elements of the indicator each contain two digits. For example:



Chapter Numbering (Continued): The chapter number (1st element) and the first number of the section number (2nd element) are assigned by ATA Specification No. 100. Material which is applicable to a system as a whole uses zeros in the 2nd and 3rd elements of the numbers. That is, the chapter number followed by "-00-00". For example: AMM 22-00-00/001 (Auto Flight) is used for general description information which provides an outline breakdown of the sections in the chapter.

Effectivity and Configuration Numbering On each page, there is effectivity data at the lower, inner margin (Fig. 1). When a page applies to all airplanes, the word ALL is in the effectivity block. If the data does not apply to all airplanes, then the effectivity will be one of these types:

1. Physical description - A description of the differences that you can see. When a physical description is used, a reference to the applicable service bulletin and PRR (production change) are provided when that is possible. This is done primarily for the benefit of airline engineering, and maintenance planning groups. For example: AIRPLANES WITH VALVE INSTALLED AWAY FROM THE FILTER (POST-SB 28A-17 OR PRR 54009) AIRPLANES WITH VALVE INSTALLED NEAR THE FILTER (PRE-SB 28A-17)

2. Component dash number - The last digits of the identification number that are on an electrical box.

3. Airplane effectivity numbers - The airline three-letter code, and the numbers or letters that Boeing and each airline agreed on to identify each airplane. If the effectivity is applicable to all subsequent airplanes, the last digits will be 999. For example: 205-999 indicates airplane 205 and all subsequent airplanes. Each paragraph can have an effectivity. Each effectivity is in upper-case letters, on the first line of the paragraph.





Effectivity and Configuration Numbering (Continued): When effectivity differences are extensive and the preceding method becomes cumbersome and distracting from the continuity of subject matter, new page blocks are created. These added page blocks are identified by the addition of a configuration code (CONFIG) immediately above the page number. A previously issued page block is re-issued to incorporate the configuration code as shown in Fig. 1. Configuration codes are issued at page block level only. They are usually used when a change to the airplane results in a major change to the manual. Configuration codes are typically used when there are multiple configurations of page block applicable to a customer's fleet. In some instances, you can have CONFIGs that are provided as place holders. These procedures will be indicated as "NOT USED" in the effectivity block in the lower left corner of the page (Fig. 1). For the effectivity information in the power plant (70 series) chapters of the manual, two situations can exist. The word ALL placed in the effectivity block on a page means that the page pertains to either all airplanes or all engines, whichever the case may be. When the effectivity is limited to a system or component that remains with the airplane during the power plant replacement, the effectivity is expressed in a manner described in the preceding paragraphs. When a manual section, page, step or illustration is limited to an engine type or component, the effectivity is given using the engine model, physical difference, or part number. The word "ALL" in the effectivity block on a page means that the page pertains to all airplanes (if you have only one engine type in your model fleet) or 2) All engines (if you have multiple engine types in your model fleet), whichever the case may be.

Page Numbering Each page block has its own page numbers. The page numbers are in the lower right corner of each page. The page blocks categorize the tasks that they contain. The page blocks are defined by ATA Specification 100:

NOMENCLATURE PAGE BLOCK DESCRIPTION AND OPERATION (D&O) 1 to 99 FAULT ISOLATION (FI) 101 to 199 MAINTENANCE PRACTICES (MP) 201 to 299 SERVICING (SRV) 301 to 399 REMOVAL/INSTALLATION (R/I) 401 to 499 ADJUSTMENT/TEST (A/T) 501 to 599 INSPECTION/CHECK (I/C) 601 to 699 CLEANING/PAINTING (C/P) 701 to 799 APPROVED REPAIRS (AR) 801 to 899

When it is convenient for the user to have different types of tasks in one page block, MAINTENANCE PRACTICES, the 201-to-299 page block, is used.



LIST OF ABBREVIATIONS A/C: air conditioning A/G: air/ground A/L: auto land A/P: autopilot A/S: airspeed A/T: auto throttle, adjustment/test ABNORM: abnormal AC: alternating current ACARS ARINC: Communications Addressing and Reporting System ACCEL: acceleration, accelerate ACM: air cycle machine ADC: air data computer ADF: automatic direction finder ADI: attitude director indicator ADP: air driven pump, air driven hydraulic pump ADV: advance AFCS: automatic flight control system AGL: above ground level AI: anti-ice AIDS: aircraft integrated data system AIL: aileron ALT: altitude ALTM: altimeter ALTN: alternate ALTNT: alternate AMB: ambient AMM: Airplane Maintenance Manual ANN: announcement ANNUNC: annunciator ANT: antenna AOA: angle of attack APB: auxiliary power breaker APD: approach progress display APL: airplane APPR: approach APPROX: approximately APU: auxiliary power unit ARINC: Aeronautical Radio Incorporated ARINC IO ARINC: I/O error ARNC STP ARINC I/O UART: data strip error ASA: auto land status annunciator ASP: audio selector panel ASYM: asymmetrical

ATC: air traffic control ATC/DABS: air traffic control/discrete address beacon system ATT: attitude ATTND: attendant AUTO: automatic AUX: auxiliary AVM: airborne vibration monitor B/CRS: back course BARO: barometric BAT: battery BFO: beat frequency oscillator BITE: built-in test equipment BK: brake BKGRD: background BPCU: bus power control unit BRKR: breaker BRT: bright BTB: bus tie breaker BTL: bottle C/B: circuit breaker C: center °C: degrees Centigrade CADC: central air data computer CAPT: captain CB: circuit breaker CCA: central control actuator CCW: counterclockwise CDU: control display unit CH: channel CHAN : channel CHG: change CHR: chronograph CHRGR: charger CK: check CKT: circuit CL: close CLB: climb

CLR: clear CLSD: closed CMD: command CMPTR: computer CNX: cancelled



COL: column COMM: communication COMP: compressor COMPT: compartment CON: continuous COND: condition CONFG: configuration CONFIG: configuration CONN: connection CONT: control CP: control panel CPCS: cabin pressure control system CPS: cycles per second CRS: course CRT: cathode ray tube CRZ: cruise CSEU: control system electronics unit CT: current transformer CTN: caution CTR: center CU: control unit CUST: customer CW: clockwise CWS: control wheel steering DA: drift angle DADC: digital air data computer DC: direct current DEC: decrease, decrement DECEL: decelerate DECR: decrease DEG: degree DEPR: depressurize DEPT: departure DEST: destination DET: detector DETNT: detent DEV: deviation DFDR: digital flight data recorder DG: directional gyro DH: decision height DIFF: differential

DIR: direct DISC: disconnect DISCH: discharge DISCONT: discontinued DISENG: disengage DISP: dispatch DIST: distance DK: deck DME: distance measuring equipment DMU: data management unit DN: down DPCT : differential protection current transformer DR: door DSCRT IO: discrete I/O error DSPLY: display DSPY: display EADI: electronic attitude director indicator ECON: economy ECS: environmental control system EDP: engine driven pump, engine hydraulic pump EEC: electronic engine control EFDARS: expanded flight data acquisition and reporting system EFI: electronic flight instruments EFIS: electronic flight instrument system EGT: exhaust gas temperature EHSI: electronic horizontal situation indicator EICAS: engine indicating and crew alerting system ELEC: electrical ELEV: elevation EMER: emergency ENG: engage, engine ENT: entrance, entry ENTMT: entertainment EPC: external power contactor EPR: engine pressure ratio EPRL: engine pressure ratio limit



EQUIP: equipment ERR: error ESS: essential EVAC: evacuation EVBC: engine vane and bleed control EXH: exhaust EXT: external EXTIN: extinguish, extinguished EXTING: extinguishing F/D: flight director F/F: fuel flow F/O: first officer °F: degrees Fahrenheit FAA: Federal Aviation Administration FCC: flight control computer FCEU: flight controls electronic unit FCU: fuel control unit FDR: feeder FIM: Fault Isolation Manual FL: flow FL/CH: flight level change FLD: field FLT: flight FLUOR: fluorescent FMC: flight management computer FMS: flight management system FREQ: frequency FRM: Fault Reporting Manual FSEU: flap/slat electronic unit FT: feet, foot FWD: forward G/S: glide slope, ground slope GA: go-around GB: generator breaker GCB: generator circuit breaker GCR: generator control relay GCU: generator control unit GEN: generator GHR: ground handling relay GND: ground GP: group

GPWS: ground proximity warning system GR: gear GRD: ground GS: ground speed GSSR: ground service select relay GSTR: ground service transfer relay GW: gross weight H/L: high/low HDG: heading HF: high frequency HORIZ: horizontal HP: high pressure HSI: horizontal situation indicator HTR: heater HYD: hydraulic IAS: indicated airspeed IDENT: identification IDG: integrated drive generator IGN: ignition ILLUM: illuminate, illuminated ILS: instrument landing system IMP: imperial IN: in, input INBD: inboard INC: incorporated, increase, increment INCR: increase IND: indicator INFC: interface INFLT: inflight INHIB: inhibit INIT: initiation INOP: inoperative INPH: interphone INST: instrument INT: interphone INTLK: interlock INTPH: interphone INTMT: intermittent IP: intermediate pressure IRS: inertial reference system IRU: inertial reference unit



ISLN: isolation ISOL: isolation IVSI: instantaneous vertical speed indicator KG: kilograms KIAS: knots indicated airspeed KTS: knots L: left L/R: left/right L-NAV: lateral navigation LAV: lavatory LB: pound LBS: pounds LCD: liquid crystal display LCR: left-center-right LDG: landing LDG GR: landing gear LE: leading edge LED: light emitting diode LF: left front LGT: light LH: left hand LIM: limit LOC: localizer LN: left nose LR: left rear LRRA: low range radio altimeter LRU: line replaceable unit LSB: lower side band LVR: lever LW: left wing LWR: lower M-SPD: manual speed MAG: magnetic MAINT: maintenance MALF: malfunction MAN: manual MAX: maximum MCDP: maintenance control display panel MCP: mode control panel MCU: modular concept unit MDA: minimum decision altitude

MIC: microphone MIN: minimum MM: Maintenance Manual MOD: module MON: monitor MOT: motion MPU: magnetic pickup MSG: message MSTR: master MSU: mode selector unit MTG: miles to go MU: management unit MUX: multiplexer N/A: not applicable NAC: nacelle NAV: navigation NCD: no computed data NEG: negative NEUT: neutral NLG: nose landing gear NO: number NORM: normal NRM: normal NVMEM RD: non-volatile memory read error NVMEM WR: non-volatile memory write error 02: oxygen OBS: observer OK: okay OPR: operate OPT: option OPRN: operation OUT: output OUTBD: outboard OVHD: overhead OVHT: overheat OVRD: override OXY: oxygen P/RST: press to reset P/S: pitot/static PA: passenger address



PASS: passenger PCA: power control actuator PCT: percentage PDI: pictorial deviation indicator PES: passenger entertainment system PLA: power level angle PLT: pilot PMG: permanent magnet generator PNEU: pneumatic PNL: panel POR: point of regulation POS: position, positive PPOS: present position PRESS: pressure PRG FLOW: program flow error PRIM: primary PROC: procedure PROG MEM ROM: memory error PROJ: projector PROT: protection PS: pitot static PSI: pounds per square inch PSS: passenger service system PSU: passenger service unit PTT: push to talk PTU: power transfer unit PWR: power QAD: quick-attach-detach QTS: quarts QTY: quantity R/T: rate of turn R/W MEM RAM: memory error R: right RA: radio altimeter, radio altitude RAT: ram air turbine RCVR: receiver RDMI: radio distance magnetic indicator REC: recorder RECIRC: re-circulate REF: reference REFRIG: refrigeration

REG: regulator REL: release REP: representative REQ: required RES : reserve RESSTART: power interrupt restart error REV: reverse RF: right front RH: right hand RLSE: release RLY: relay RLY/SW: relay/switch RMI: radio magnetic indicator RMT OUT: high-speed ARINC output error RN: right nose ROT: rotation RPM: revolutions per minute RPTG: reporting RR: right rear RST: reset RTO: rejected takeoff RUD: rudder RW: right wing RWY: runway SAM: stabilizer trim/elevator asymmetry limit module SAT: static air temperature SEC: second SEI: standby engine indicator SEL: select SELCAL: selective calling SERV: service SG: signal generator SLCTD: selected SLCTR: selector SOV: shut off valve SP: speed SPD: speed SPD BK: speed brake SQL: squelch SSB: single side band



STA: station STAB: stabilizer STBY: standby STS: system status SURF: surface SW: switch SWITCH IN: switch input error SYNC: synchronous SYS: system SYST: system T/R: thrust reverser T.O. : takeoff TACH: tachometer TAI: thermal anti-ice TAS: true airspeed TAT: total air temperature TCC: turbine case cooling TE: trailing edge TEMP: temperature TFR: transfer THR: thrust THROT: throttle THRSH: threshold THRT: thrust THRU: through TIE: bus tie TLA: thrust lever angle TMC: thrust management computer TMS: thrust management system TMSP: thrust mode select panel TO: takeoff TOL: tolerance TR: transformer rectifier TRP: thrust rating panel TUNE: tuner TURB: turbine TURBL: turbulent, turbulence

UBR: utility bus relay UPR: upper USB: upper side band V/NAV: vertical navigation V/S: vertical speed VERT: vertical VERT: SPD vertical speed VFY: verify VG: vertical gyro VHF: very high frequency VIB: vibration VLD: valid VLV: valve VOL: volume VOLT: voltage VOR VHF: omni range receiver VOX: voice VTR: video tape reproducer W/D: wiring diagram W/W: wheel well WARN: warning WG: wing WHL: wheel WHLS: wheels WPT: waypoint WSHLD: windshield WX: weather WXR: weather X-CH: cross channel X-CHAN: cross channel XDCR: transducer XMISSION: transmission XMIT: transmit XMTR: transmitter XPNDR: transponder Y/D: yaw damper



REFERENCE PLANES AND LINES

The airplane is divided into reference planes (stations), waterlines and buttock lines. These are measured in inches from fixed points of reference. This provides a means of quickly identifying the location of components, the center of gravity and the distribution of the weight.

Standard Abbreviations and Definitions

Fuselage B STA, BS, or STA: Body (Fuselage) Station.

This is a plane perpendicular to the fuselage centerline, It is located 159.00 inches forward of the nose. BBL or BL: Body (Fuselage) Buttock Line.

This is a vertical plane parallel to the fuselage vertical centerline plane, BBL 0.00 located by its distance outboard from the fuselage centerline plane.

BRP: Body (Fuselage) Reference Plane.

This is a plane perpendicular to the BBL plane and passes through the top of the main deck floor beams (BWL 208.10).

BWL or WL: Body (Fuselage) Waterline.

This is a plane perpendicular to the BBL plane. It is located by its distance from a parallel imaginary plane (BWL 0.00). BWL 0.00 is 133.00 inches below the lowest fuselage surface.

LBL: Left Buttock Line RBL: Right Buttock Line

Wing FS: The principal spanwise transverse member of the wing structure.

It is perpendicular to the wing reference plane. ISS: Inboard Slat Stations.

These are planes perpendicular to inboard leading edge slats. They are measured from the intersection of the slat rotation axis and a plane perpendicular to the wing reference plane.

LES: Leading Edge Station.

These are planes perpendicular to the wing reference plane and the leading edge. They are measured from the intersection of the leading edge extension and the wing buttock line 0.00.



Wing Definitions (Continued): MAC: Mean Aerodynamic Chord.

This is the chord of a section of an imaginary airfoil which would have vectors throughout the flight range identical to those of the actual wing.

OSS: Outboard Slat Stations.

These are planes perpendicular to the outboard leading edge slats. They are measured from the intersection of the slat rotation axis and a plane perpendicular to the wing reference plane.

RS: See definition for FS. W STA or WS: Wing Station.

These are planes perpendicular to the wing reference plane and the plane of the outboard rear spar. They are measured from the intersection of the extended leading edge and wing buttock line 0.00.

WBL: Wing Buttock Line.

This is a plane perpendicular to the wing reference plane and parallel to the trace of the fuselage centerline. It is measured from intersection of wing reference plane and body buttock line 0.00.

WRP: Wing Reference Plane.

This is the datum plane of the wing. It is inclined up 5 degrees with respect to the BWL plane and passes through the intersection of the BBL 0.00 and BWL 178.187909.

WTS: Wing Tip Station.

This is a plane perpendicular to the wing reference plane and wing buttock line 0.00. It is measured from the intersection of the leading edge and wing buttock line 0.00.

Vertical Stabilizer ASS: Auxiliary Spar Station.

This is a plane perpendicular to the vertical stabilizer auxiliary spar. It is measured from the Auxiliary Spar Station 0.00, intersection of the auxiliary spar centerline extension and body waterline 228.99 (757 ROOT CHORD).



Vertical Stabilizer (Continued): FIN STA: Fin Station.

This is a plane perpendicular to the centerline of the vertical stabilizer rear spar. It is measured from Fin Station 0.00, intersection of rear spar centerline extension and body waterline 228.99 (757 ROOT CHORD).

FSS: Front Spar Station.

This is a plane perpendicular to the vertical stabilizer front spar. It is measured from the fin front spar station 0.00, intersection waterline 228.99 (757 ROOT CHORD).

LES: Leading Edge Station.

These are planes perpendicular to the vertical stabilizer leading edge. They are measured from the leading Edge Station 0.00, intersection of the leading edge line extension and body waterline 228.99 (757 ROOT CHORD).

LFFS: Lower Front Spar Station.

These are planes perpendicular to the vertical stabilizer lower front spar. They are measured from the Lower Front Spar Station 0.00, intersection of the lower front spar centerline extension and body waterline 228.99 (757 ROOT CHORD).

RUD STA: Rudder Station.

These are planes perpendicular to the rudder hinge centerline. They are measured from Rudder Station 0.00, intersection of rudder hinge centerline and body waterline 228.99 (757 ROOT CHORD).

Horizontal Stabilizer AUX SPAR STA: Auxiliary Spar Station.

These are planes perpendicular to the horizontal stabilizer auxiliary spar. They are measured from Auxiliary Spar Station 0.00, intersection of auxiliary spar extension and stabilizer buttock line 0.00.

ELEV STA: Elevator Station.

These are planes perpendicular to the elevator hinge centerline. They are measured from the intersection of elevator hinge centerline and stabilizer buttock line 0.00.



Horizontal Stabilizer (Continued): FS STA: Front Spar Station.

These are planes perpendicular to the horizontal stabilizer front spar. They are measured from Front Spar Station 0.00, intersection of front spar and trace of body buttock line 0.00 at horizontal stabilizer reference plane.

HSBL: Stabilizer Buttock Line.

This is a plane perpendicular to the horizontal stabilizer reference plane and parallel to the trace of the fuselage centerline. It is measured from stabilizer buttock line 0.00, intersection of horizontal stabilizer reference plane and body buttock line 0.00.

HSRP: Horizontal Stabilizer Reference Plane.

This is the datum plane of the horizontal stabilizer. It is inclined 7° up with respect to the BWL plane and passes through the intersection of the BBL 0.00 and BWL 238.015 planes.

LE STA: Leading Edge Station.

This is a plane perpendicular to the horizontal stabilizer leading edge. It is measured from Stabilizer Leading Edge Station 0.00, intersection of leading edge line extension and stabilizer buttock line 0.00.

RS STA: Rear Spar Station.

This is a plane perpendicular to the horizontal stabilizer rear spar. It is measured from Rear Spar Station 0.00, intersection of rear spar and trace of body buttock line 0.00 at horizontal stabilizer reference plane.

STAB STA: Stabilizer Station. This is a plane perpendicular to the stabilizer rear spar and the horizontal

stabilizer reference plane. Stabilizer station 0.00 is at the intersection of the leading edge extension, body buttock line 0.00 and the horizontal stabilizer reference plane.

Power Plant PPBL: Power Plant Buttock Line.

This is a plane perpendicular to the wing reference plane. It is measured from a parallel plane (PPBL 0.00) that intersects the WBL 255.0 plane at the wing leading edge and angles 1.5 degrees inboard just forward of the wing leading edge.



Power Plant (Continued): PPWL: Power Plant Waterline.

This is a plane perpendicular to the PPBL datum plane and inclined 2.4072 degrees upward from the wing reference plane. The PP WL 100.00 (centerline of engine) is measured 61.70 inches down from the wing leading edge at WBL 255.00.

PPS: or PPSTA Power Plant Station.

This is a plane perpendicular to the engine centerline. The zero position is located 72.30 inches forward of the forward edge of the fan cowl panel.







PRIMARY AIRCRAFT DIMENSIONS



DIMENSIONS

Overall Airplane: Length -- 155 feet-3 inches Width -- 124 feet-6 inches Height (vertical stabilizer tip, top of the fairing to the ground) -- 44 feet-6 inches

Wing: Root Chord (calculated, at body centerline) -- 360.85 inches Basic Chord (calculated) -- 286.50 inches Tip Chord (calculated) -- 68.00 inches Planform Taper Ratio Tip Chord/Basic Chord -- 0.237 Tip Chord/Root Chord -- 0.188 Dihedral (wing reference plane in relation to the body reference plane) -- 5 degrees Sweepback (25 percent chord line) -- 25 degrees Aspect Ratio -- 7.95 Mean Aerodynamic Chord (basic wing only) -- 199.70 inches

Horizontal Stabilizer: Span -- 600 inches Taper Ratio -- 0.347 Sweepback (25 percent chord line) -- 30.186 degrees Dihedral (horizontal stabilizer reference plane in relation to body reference plane) -- 7 degrees Aspect Ratio -- 4.496

Vertical Stabilizer: Height -- 293.374 inches Taper Ratio -- 0.346 Sweepback (25 percent chord line) -- 40 degrees Aspect Ratio -- 1.615



Fuselage: Height of body reference plane (top of floor beam WL 208.10) above ground at main gear -- 152.10 inches Height (constant cross section) Above body reference plane -- 98.4 inches Below body reference plane -- 75.10 inches Height to centerline of windows above body reference plane -- 38 inches Length -- 1846 inches

Areas: Wing (basic) -- 1951 square feet Horizontal Stabilizer Surfaces (total, includes the area within fuselage) -- 545 square feet Vertical Stabilizer Surfaces (total) -- 370 square feet





BODY STATION DIAGRAM





VERTICAL STABILIZER AND RUDDER STATION DIAGRAM



HORIZONTAL STABILIZER AND ELEVATOR STATION DIAGRAM



WING STATION DIAGRAM



ENGINE AND NACELLE STATION DIAGRAM



ZONE DIAGRAMS

The 757 airplane is divided into 8 major zones to help you find and identify the airplane components and parts. The major zones then are divided into the sub-zones and the sub-zones into zones. The zones are numbered in the sequence that follows:

1. Wings - inboard to outboard and front to back 2. Horizontal Stabilizer and Elevator - inboard to outboard and front to back 3. Vertical Stabilizer and Rudder - root to tip of vertical stabilizer 4. Fuselage - front to back and away from floor line

Each of the structural components, passenger compartment doors, cargo doors, landing gear doors, rudders, elevators, flaps, ailerons, spoilers, leading edge devices, and equivalent components has a different zone number. A three-digit number identifies the major zones, sub-zones, and zones as follows:

1. Major Zone - the first digit is a number from 1 to 8 followed by two zeroes 2. Sub-zone - the first digit represents the major zone, the second digit is a number from 1 to 6 or 9, and

the third digit is a zero 3. Zone - the first two digits represent the sub-zone number and the third digit shows a component or

group of components that are in the sub-zone

Major Zones 100 Lower Half of Fuselage 200 Upper Half of Fuselage 300 Empennage and Body Section 48 400 Power Plants and Nacelle Struts 500 Left Wing 600 Right Wing 700 Landing Gear and Landing Gear Doors 800 Doors





SERVICE INTERPHONE SYSTEM

The service interphone system provides facilities for interphone communication between servicing stations during ground operations. In addition, communication is extended to the flight compartment and attendant stations. The service interphone system includes phone jacks located at convenient service locations around the airplane. The system also includes amplifiers and mixing circuits that are housed inside the audio accessory unit. It is located on shelf E4 of the main equipment center. The SERV INTPH switch activates the system and is located on the right sidewall panel, P61. The system gets power from the 28-volts DC battery bus, through a circuit breaker on overhead panel P11.

Component Details

Audio Amplifier Two identical audio amplifiers with parallel inputs are located in the audio accessory unit on shelf E4-3 in the main equipment center. The amplifiers are used by both the service interphone and the cabin interphone systems. A placard on the audio accessory unit identifies and locates the two amplifiers. There are two outputs from each amplifier. One output goes to the cabin interphone audio on the audio selector panels. The other output goes to the cabin interphone handsets and service interphone jacks. The amplifiers have internal adjustments preset for normal compression, squelch, and volume.

Service Interphone Switch The SERV INTPH switch is located on right sidewall panel P61. In the ON position, the switch connects the microphone lines from the service interphone jacks to the input of the interphone amplifiers. The OFF position disconnects the microphone lines to isolate the service interphone jacks during flight.





Operation The INTERPHONE CABIN SERVICE circuit breaker on overhead panel P11 controls power to the system. The SERV INTPH switch on panel P61 connects the mic lines from the phone jacks to the input of the interphone amplifiers. This switch activates the service interphone system. Then the interphone amplifiers distribute the amplified audio to the audio selector panels in the flight compartment, as well as to the cabin handsets, and to the audio line of the service interphone jacks located at convenient service locations. All microphone inputs from the handsets and from the audio selector panels mixes with that of the service interphone jacks onto a single-party system. The flight crew talks with the service interphone stations by pushing the MIC SELECTOR labeled CAB on the audio selector panels. This switch, along with the SERV INTPH switch on panel P61, connects a flight crew headset to the service interphone system. On the audio selector panel, the CAB switch is a push-on/push-off type and is lighted when on. The same knob also turns a volume control for that particular station. Personnel at the cabin attendant stations use the service interphone system by picking up the attendant handset and talking. Personnel at service locations use the service interphone system by plugging a headset into the phone jack and talking. First, the SERV INTPH switch must be set to ON.

Control To place the system in operation, supply electrical power. On overhead panel P11, make sure the INTERPHONE CABIN SERVICE circuit breaker is closed. On right sidewall panel P61, make sure the SERV INTPH switch is on.





Cabin Interphone System The cabin interphone system provides facilities for interphone communication among cabin attendants, and between the flight compartment crewmembers and attendants. The cabin interphone system microphone circuits can be switched to the input of the passenger address (PA) system to permit announcements.

Cabin Interphone Handsets Each attendant station has a handset. Each handset has the following components: a noise-canceling microphone to decrease the input of airplane noise, a small speaker to listen, buttons to operate the handset, and a magnet-operated hook switch to disconnect the handset from the system when the attendant places the handset back on the hook. In operation, 4 of the handset buttons call specific stations (FWD, MID, AFT, PILOT). The P.A. button connects the handset to the passenger address speakers to make announcements. The RESET button permits the attendant to make more calls without the need to put the handset back on the hook after each call. The button operates the same as when the handset is put on the hook. The ALERT button connects the handset to all stations at the same time. The P.A. PUSH TO TALK switch momentarily connects the microphone to transmit voice during passenger announcements.

Pilot’s Call Panel The pilots' call panel is on overhead panel P5. The cabin interphone system connects to the pilots' call panel through three blue lighted call switches which indicate an attendant call (FWD, MID, AFT), and one blue lighted call switch that indicates an alert call (ALERT). The call switches (FWD, MID, AFT) are used to signal the related attendant station. The ALERT call switch is used to make an alert call.

Operation Cabin interphone calling from one station to another is done by single-digit dialing. Pressing a call switch on a handset activates the system by sending two tones to the audio accessory unit. The tones are processed in the accessory unit and a signal is provided to the called station to turn on the call light. A signal is also sent to the PA system to generate a hi/lo chime for attendant calls or to the aural warning system to generate a hi chime in the flight compartment for pilot calls. The FWD, MID, AFT, and ALERT call switches on the pilots' call panel make it possible for the pilot to make and receive cabin interphone calls. The light in each call switch comes on when there is an incoming call and go off when the pilot pushes the switch. Power failures will automatically connect the microphones of the cabin interphone handsets to the PA system.





Operation (Continued): The controller in the audio accessory unit monitors busy stations, and prevents incoming calls when a called station is busy. The controller also activates the PA hi/lo chime output, and causes the lamp driver to turn on the attendant call light. Attendant to attendant calling can be accomplished except under the following conditions:

1. Calls can not be placed between the two mid attendant stations 2. Any station that has a handset off hook cannot be called 3. No station can call another station that has been called but not answered; however, the station that

placed the call can repeat the call 4. Only one call can be made from a handset without first performing a reset

Any attendant can call the pilot. Multiple calls by attendants to the pilot are possible. After a call, the attendant must put the handset back on the hook (cradle) or push the RESET switch to reset the unit. When the attendant at the called station removes the handset from the hook, a magnetic switch closes and connects the microphone to the system.

Control To place the system in operation, supply electrical power. On overhead panel P11, make sure the INTERPHONE CABIN SERVICE circuit breaker is closed.



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Date post:	20-Jul-2016
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