McDonnell Douglas DC 10 40 Airplane General

CHAPTER 1

AIRPLANE GENERAL

Page

TABLE OF CONTENTS 01-00-01

INTRODUCTION 01-10-01

DESIGN FEATURES 01-10-01

Aircraft Dimensions 01-10-04

Turning Radius 01-10-05

Compartment Diagram 01-10-06

Miscellaneous External Items 01-10-07/08

COCKPIT 01-20-01

Flight Compartment 01-20-02

Clearview Window 01-20-04

Sun Visor 01-20-05/06

Aft Overhead Panel 01-21-01/02

Forward Overhead Panel 01-21-03/04

Glare shield, Auxiliary & Light Control Panels 01-22-01/02

Center Instrument Panel 01-22-03/04

Captain's Instrument Panel 01-22-05/06

Copilot's Instrument Panel 01-22-07/08

Pedestal (Forward) 01-24-01/02

JLFeb 1/76 01-00-01

Page

COCKPIT (Continued)

Pedestal (Aft) 01-24-03/04

Flight Engineer's Lower Instrument Panel 01-26-01/02

Flight Engineer's Lower Instrument Panel -Fuel and Miscellaneous 01-26-03/04

Flight Engineer's Upper Instrument Panel No. 1 . 01-26-05/06

Flight Engineer's Upper Instrument Panel No. 2 01-26-07/08

Flight Engineer's Upper Instrument Panel No. 3 01-26-09/10

Flight Engineer's Equipment Panel 01-26-11/12

DOORS 01-30-01

Cockpit Door 01-30-03

Lavatory Door 01-30-04

Cabin Door Barrier Straps 01-30-04A/04

Cabin Doors 01-30-05

Cabin Door Interior Controls 01-30-06

Cabin Door Exterior Controls 01-30-06B

Lower Cargo Doors 01-30-07

Annunciator Lights and Cargo Door Warning Test System 01-30-10

LIGHTING 01-40-01

Interior Lighting — Controls and Indicators -- Cockpit Lighting . . 01-40-03

Interior Lighting — Controls and Indicators -- Cabin Lighting . . * 01-40-05

Exterior Lighting 01-40-06

Exterior Lighting — Controls and Indicators . 01-40-07

01-00-02JL

Nov 1/75

Page

SEATS 01-50-01

Captain's and Copilot's Seats 01-50-02

Flight Engineer's Seat 01-50-03

Observer's Seats 01-50-04

Pilot Eye Locator 01-50-05/06

WARNING AND CAUTION SYSTEMS 01-60-01

Aural Warning and Caution System Particulars 01-60-03

Instrument Markings 01-60-05

Pilots' Annunciator Panel and Warning Lights 01-60-06

Flight Engineer's Annunciator Panel 01-60-07

Additional Annunciator Light Information 01-60-08

JLFeb 1/76 01-00-03/04

A I R C R A F T GENERAL

INTRODUCTION

The sweptwing DC-10 Series 40 air-craft is a long range tri-jetdesigned for the transportation ofpassengers and cargo. Three inter-changeable Pratt & Whitney JT9D,high-bypass ratio turbofan enginesare used for propulsion.

DESIGN FEATURES

GENERAL

Fuselage

The wide-bodied fuselage is of semi-monocoque metal construction. Allareas are pressurized except thenose radome, wheelwells, wing centersection, and aft fuselage. The fuse-lage is divided lengthwise into anupper-floor level and a lower-floorlevel. The galley and lavatorycompartments are located on theupper-floor level. The cargo andaccessory compartments are located onthe lower-floor level. Two mainaisles are provided on the upperfloor. Eight passenger entrance/exitdoors are installed.

Cabin windows are double pane con-struction. Either pane is capableof carrying full pressurization.

Wing

The cantilevered wing consists of aprimary box structure with a leadingand trailing edge secondary struc-ture. The box is of two-spar con-struction containing integral,between-spar fuel tanks. This

primary box also carries the mainlanding gear supporting structure,engine pylons, full span leadingedge slats, spoilers, and trailingedge ailerons and flaps. Rupture-resistant fuel tanks and lines areprovided in case of landing gearand/or flap breakaway.

Tail

The tail is of metal construction andincludes an adjustable horizontalstabilizer, right and left two-section elevators, a tail-enginepylon, a fixed vertical stabilizer,and a two-section (four-segment)rudder. The adjustable horizontalstabilizer is pivoted at the trailingedge and uses hydraulic poweredmotors to change the angle-of-incidence.

SYSTEMS

Air Conditioning and Pressurization

The air conditioning and pressuri-zation systems provide heating,cooling, dehumidification, and pres-surization for the cockpit, passengercabin, galley, cabin cargo compart-ments, and avionics compartment.Temperature control is automatic ormanual. Pressurization control hasautomatic, semi-automatic, standby,and manual modes of operation. Theair conditioning system is capable ofmaintaining a comfortable environment,while on the ground, using only theonboard auxiliary power unit.

Automatic Flight

The automatic flight capabilityincludes automatic control (fullor partial) of the aircraft during

JLNov 1/82 01-10-01

takeoff, climb, cruise, descent, andlanding. The system is designed forall-weather operation with a CATIII landing capability. The totalsystem includes a flight director,an autothrottle/speed control system,and an autopilot.

Auxiliary Power Unit

The onboard gas-turbine powered APUis a self-contained source of pneuma-tic and electrical power on theground, and electrical power inflight. The unit may be started orshut down from the cockpit, andnormally is completely automatic inoperation. The unit may be shut downfrom the ground panel.

Communication

The aircraft is equipped with air-to -ground and air-to-air voice cotimuni-cation systems. Cockpit/cabin,ground service interphone, passengeraddress, and voice recorder systemsalso are provided. Cabin attendant,pilot, mechanic, and passenger callsystems are installed in the aircraft.A separate passenger entertainmentsystem also is provided.

Electrical

The electrical system is normallypowered by an ac generator mounted oneach engine. It may also be poweredby an external ac source or by theonboard auxiliary power unit. Por-tions of the system may be poweredby the aircraft battery and/or anair driven generator. DC power isnormally provided through transformer/rectifiers, but may also be providedby a battery. Protective circuitrywith automatic corrective action isstandard equipment.

Emergency Equipment

Emergency equipment is provided forthe flight crew and passengers. Itincludes emergency and first aidoxygen, portable fire extinguishers,emergency lighting, first aid kits,evacuation slides, a crash axe, andflotation gear. Portable megaphones,and crash locator radio (beacon)transmitters also are provided.

Fire Protection

The fire protection system providesdetection, visual/aural warning, andextinguishing capability for eachengine nacelle area and for theauxiliary power unit compartment.Visual overheat indication is alsoprovided for the avionics compartment.Visual smoke and fire detection andextinguishing capabilities are pro-vided for the cargo compartment.

Flight Controls

Primary flight controls consist ofinboard and outboard ailerons; twotwo-section elevators; and a two-section (four segment) rudder.Secondary flight controls consist oflift-augmenting leading edge slats,spoilers (lateral control/speedbrake/ground spoilers), inboard andoutboard flaps, and a dual-ratemovable horizontal stabilizer. Theflight control system is a fullypowered system utilizing power fromthree independent hydraulic systems.

Flight Instruments

The flight instruments and associatedcomponents provide altitude, airspeed,overspeed, attitude, and temperaturedata plus flight data recording.Included are the pitot-static system,the central air data computers, thealtitude, airspeed, and verticalspeed indicators, the gyrosyn compasssystem and the RMI/HSI indicators,and the attitude director indicators.

01-10-02JL

Nov 1/82

Fuel System

Fuel is carried in three integral wingtanks and in the auxiliary tank. Directtank-to-engine feed is normally used.The system also has the capability oftank-to-tank transfer, fuel dumping, andany-tank to any-engine crossfeed. Innormal operation, each engine receivesfuel from its respective main tank. Theauxiliary power unit normally receivesfuel from tank number two. Fueling,defueling, manifold drain, and fuel tankventing are provided. The system per-mits one-man, single-point refuelingand is spillproof and siphonproof.

Hydraulic Power

Three continuously pressurized hydraulicsystems are provided, each powered bytwo engine-driven pumps with intersys-tems motor pump backup. Two electricauxiliary pumps are installed in systemthree. Emergency hydraulic power isavailable from an electric auxiliary pumppowered by an air driven generator.

Ice and Rain Protection

The ice and rain protection systems pro-vide all-weather flight capability. Ther-mal heating is provided for anti-icing theoutboard wing slats, VHF-1 antenna, andfor the nose cowl inlet area of eachengine. Electric heaters provide anti-icing for pitot tubes, static ports, angle-of-attack vane, total air temperatureprobe, and exterior windshields. Elec-tric heaters also are used for defoggingthe windshields and clearview windows.Rain protection is provided for thewindshields by electric wipers and achemical rain repellent system.

Landing Gear

The landing gear, nosewheel steering,brakes, and antiskid systems are basically

conventional. All systems are hydrauli-cally powered. A manual, free-fallalternate gear extension capability isprovided.

Navigation Systems

The navigation equipment includes theVOR/ILS, ADF, DME, radio altitude,and marker beacon systems; the weatherradar, the clock, and (as desired)INS equipment.

Pneumatics

The pneumatic system distributes andcontrols pneumatic pressure for air con-ditioning, pressurization, anti-icing,heating, ventilation, water pressuriza-tion, and engine starting. Pneumaticpressure is supplied from either anexternal source, the APU, or theengines.

Power Plant

The aircraft is powered by three Pratt &Whitney JT9D dual-rotor, high bypassratio turbofan engines. The enginesincorporate a front fan and booster stagecomprising the low pressure compress-or section, a high pressure compressorwith variable pitch stators, annular com-bustors, and high and low pressureturbines.

Water and Waste Systems

Separate systems are provided for pot-able water and waste service. The pot-able water system includes provisionsfor filling, storage, quantity indication,temperature control, distribution, andoverboard drainage. The waste systemincludes provisions for storage, priming,rinsing, flushing, and drainage.

JLMay 1/76 01-10-03

AIRPLANE DIMENSIONS

NOTEDIMENSIONS ARE APPROXI-MATE, DEPENDING ON GROSSWEIGHT AND STRUT/TIRE IN-FLATION.

50.4m(165 FT 4 IN.)

4.5m(14 FT 9 IN.)

7.4m(24 FT 5 IN.)

0.9m(3 FT)

10.7m(35 FT)

6.0m(19 FT 9 IN.)

21.7m(71 FT 2 IN.)

8.4m(27 FT7 IN.)

55.3 m(181 FT 7 IN.)

8.6 m(28 FT1 IN.) 4.8m

(16 FT)

8.5 m(27 FT 11 IN.)

22.1 m .(72 FT 5 IN.) 52m

(170 FT 6 IN.)

, 17.7m(58 FT 1 IN.)

01-10-04JL

Feb 1/79

TURNING RADIUS (minimum)DC-10-30/40

1EFFECTIVE

TURN ANGLEMAXIMUMSTEERING

ANGLE 68.0° TIRESUPANGLE TURN

CENTER

PAVEMENT WIDTHFOR 180° TURN

NOSE GEAR RADII TRACKMEASURED FROM OUTSIDE FACEOF TIRE.

MINIMUM RADIUS TURNRECOMMENDED FOR NORMAL,ROUTINE OPERATIONS.

TIGHTER TURNS CAN BE MADEO C C A S I O N A L L Y U S I N G ACOMBINATION OF MAXIMUMSTEERING, ASYMETRICAL THRUSTAND L IGHT I N T E R M I T T E N TBRAKING.

MAXIMUM STEERINGSYMMETRICAL THRUST AND NODIFFERENTIAL BRAKINGSLOW CONTINUOUS TURNAFT CENTER OF GRAVITY

MAX GROSS WEIGHT

•MAXIMUM STEERINGASYMETRICAL THRUST ANDL I G H T I N T E R M I T T E N TDIFFERENTIAL BRAKINGSLOW CONTINUOUS TURNAFT CENTER OF GRAVITYMAX GROSS WEIGHT

TYPE OFTURN

EFFECTIVETURN ANGLE

62.9°

66.9°

TIRE SLIPANGLE

5.1°

1.1°

X

42.7 FT

37.2 FT

27.6 FT

Y

72.9 FT

72.9 FT

72.9 FT

W

149.5 FT

141.4 FT

128.5 FT

R1

85.2 FT

83.5 FT

79.8 FT

R2

130.5 FT

125.3 FT

116.1 FT

R3

109.6 FT

107.5 FT

104.7 FT

R4

109.8 FT

105.9 FT

99.5 FT

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MISCELLANEOUS EXTERNAL ITEMS

WINDSHIELDWIPERS

LEFT ANGLE OFATTACK SENSOR

LANDING LIGHTWING SCANLIGHT

PITOT TUBES

OXYGENBLOWOUTDISK

PACK INLET ANDEXIT DOORS

NOSELANDINGLIGHT

RUNWAY TURNOFFLIGHT

WING SCANLIGHT

STATIC PORTS ANGLE OF ATTACKSENSOR

RADOME

RUNWAY TURNOFFLIGHT

CABIN PRESSURERELIEF VALVES

NOSELANDINGLIGHT

LANDINGLIGHT

TATPROBE

JLMay 1/76 01-10-07/08

COCKPIT

The cockpit is arranged in a conventionalmanner, the Captain's seat on the left,the Copilot's seat on the right, andthe Flight Engineer' s station facing out-board behind the Copilot's seat.Seating, communications facilities, andoxygen outlets are provided for a Firstand Second Observer behind the Captain'sstation. Storage facilities for looseequipment are provided at each station inaddition to storage areas in the coatroom.

All controls and indicators in the cockpitare illustrated in this section. Theillustrations are arranged on foldoutpages with an apron so that they may beextended and used as a reference in con-junction with the Controls and Indicatorsillustrations in the other chapters of thisvolume without having to remove theillustration from the book.

JLMay 1/76 01-20-01

FLIGHT COMPARTMENT Captain's Station

CAPTAIN'SINSTRUMENTPANEL

AFT OVERHEAD CIRCUITBREAKER PANEL FORWARD OVERHEAD

CIRCUIT BREAKERPANEL

OVERHEADPANEL

GLARESHIELD

CAPTAIN'SCONSOLE

CAPTAIN'SAUXILIARYPANEL PEDESTAL CENTER

INSTRUMENTPANEL

01-20-02JL

Aug 1/87

FLIGHT COMPARTMENT Copilot's and Flight Engineer's Station

FLIGHT ENGINEER'S OVERHEADCIRCUIT BREAKER PANEL

FLIGHT ENGINEER'SUPPER PANEL NO. 1



COPILOT'SINSTRUMENT PANEL

COPILOT'SAUXILIARY PANEL

COPILOTSCONSOLE

FLIGHT ENGINEER'SCONSOLE

FLIGHT ENGINEER'SLOWER PANEL

FLIGHT ENGINEER'STABLE

FLIGHT ENGINEER'SEQUIPMENT PANEL

JLMay 1/76 01-20-03

CLEARVIEW WINDOW(Left window shown, Right window opposite)

CLEARVIEW WINDOWLOCKLATCH

(Unlocked Position)

(Placard)

Clearview Window CrankPush in to engage, then rotate han-dle to open clearview window.

TRACK BUMPER(Placard)

CLEARVIEW WINDOWOPEN

Clearview Window Locklatch(locked position)

Locks window in closed position.

NOTEOn aircraft with S/B56-9 incor-porated or production equivalent, aninterlock will prevent rotating windowlocklatch to locked position until win-dow is cranked to fully closed posi-tion.

Clearview Window CrankPush in to engage, then rotate han-dle to close clearview window.

Luminous CoatingVisible on inboard carriage rollerlink and end of track when windowis closed and in position for latch-ing.CLEARVIEW WINDOW

CLOSED AND LOCKED

01-20-04JL

Feb 1/82

SUN VISORTRACK

BRACKETADJUSTABLETENSION SCREW

LOCKING PIN HANDLE(Unlocked Position)

LOCKING PIN HANDLE(Locked Position)Spring-loaded to lock position. Turninghandle down releases lock and allowsvisor to be moved to desired location.

SHADE

Visor is moved by turning and holding locking pin han-dle down, grasping the bracket at top of shade andsliding visor to the desired location. Releasing lockingpin locks visor in place.Visor should be moved forward of the forward edge ofclearview window and then raised to the stowed posi-tion before opening the clearview window. This allowsthe clearview window to be opened without damagingthe visor.

NOTEDo not move visor by holding lower edge of shade asdamage may result due to the leverage applied to thebracket and resultant binding in the track. Theadjustable tension screw immediately above theshade should be tightened only to the degreenecessary to hold shade in desired horizontal position.

SUN VISOR(TYPICAL 2 PLACES)

Effective on airplanes with Adjustable Tension Screw type sun visor.

SUN VISOR

TRACKSHADE

Visor is moved by grasping the slide block attop of shade and sliding visor to the desiredlocation.Visor should be moved forward of the forwardedge of clearview window and then raised tothe stowed position before opening the clear-view window. This allows the clearview win-dow to be opened without damaging the visor.

NOTEDo not move visor by holding lower edge ofshade as damage may result due to theleverage applied to the bracket and resultantbinding in the track.

SUN VISOR(TYPICAL 2 PLACES)

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GLARESHIELD, AUXILIARY AND LIGHT CONTROL PANELS

INOPERATIVEON DOMESTICCONFIGURATIONGLARESHIELD

Copilot'sPanel only

CAPTAIN'S LIGHTCONTROL PANEL(Typical for Copilot)

INSTALLED ON SOME AIRPLANESFIRST OFFICER'S AUXILIARY PANEL

(Typical for Captain)

DO NOT LAND AUTOMATICALLY WITH SPARE ENGINE POD placard installedon Domestic configuration airplanes during Spare Engine Transport

JLNov 1/80 01^22-01/02

GLARESHIELD, AUXILIARY AND LIGHT CONTROL PANELS

GLARESHIELD

COPILOT'S PANEL ONLY

CAPTAIN'S LIGHTCONTROL PANEL(Typical For Copliot) INSTALLED ON SOME AIRPLANES

FIRST OFFICER'S AUXILIARY PANEL(Typical For Captain)

EFFECTIVE ON AIRPLANES WITH PMS INSTALLED.

JLJun 1/97 01-22-02A/02!

CENTER INSTRUMENT PANEL

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PEDESTAL (FORWARD)

NOT INSTALLED ONDOMESTIC CONFIGURATION

T. O. FLAPS 0°-14° PROHIBITED WITH SPARE ENGINEPOD placard installed on Domestic configuration airplanesduring Spare Engine Transport.JL

Feb 1/79 01-24-01/02

PEDESTAL (AFT)

NOT INSTALLED ONDOMESTIC CONFIGURATION

INSTALLED ONSOME AIRCRAFT

JLFeb 1/82 01-24-03/04

PEDESTAL (AFT)

EFFECTIVE ON AIRPLANES WITH PMS INSTALLED.

JLFeb 1/84 01-24-05/06

FLIGHT ENGINEER'S LOWER INSTRUMENT PANEL

JLMay 1/76 01-26-01/02

FLIGHT ENGINEER'S LOWER INSTRUMENT PANELFuel and Miscellaneous

JLAug 1/81 01-26-03/04

FLIGHT ENGINEER'S LOWER INSTRUMENT PANELFuel and Miscellaneous

LOCATED ON EDGEOF TABLE, RIGHT SIDE

Effective for aircraft with decal or dial face identification on fuel quantity gages.

JLNov 1/81 01-26-04A/04B

FLIGHT ENGINEER'S UPPER INSTRUMENT PANEL N0.1

JLAug 1/79 01-26-05/06

FLIGHT ENGINEER'S UPPER INSTRUMENT PANEL NO. 2

INSTALLED ONSOME AIRPLANES



JLJun 1/97 01-26-07/08

FLIGHT ENGINEER'S UPPER INSTRUMENT PANEL NO. 3

UPPER MAIN C. B. PANEL

INOPERATIVEON DOMESTICCONFIGURATION

INSTALLED ONLYON DOMESTICCONFIGURATION


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DOORS

GENERAL

Eight cabin doors, a cockpit door, a doorfor each lavatory, and three lower cargodoors are provided. The cabin doors canbe operated electrically, pneumaticallyor manually. The cockpit and lavatorydoors are operated manually. The lowercargo doors can be operated electricallyor manually.

DESCRIPTION

Cockpit Door

The cockpit door has built-in ventilation,pressure differential relief, and smokeisolation features. The door is manuallyoperated by a standard doorknob. A keyis normally required to open the doorfrom the cabin side; however, if elec-trical power is available and the cockpitis occupied, the door lock may bereleased electromagnetically by a push-button on the overhead panel. The doorcan be opened from inside the cockpit atany time by rotating the doorknob. Acabin viewer is installed in the door toprovide the flight crew with a view of thecabin area.

Lavatory Doors

The lavatory doors are manually operatedfrom inside lavatory, by using a slidingbolt lock. The position of the lock isindicated by a VACANT/OCCUPIED signon cabin side of door. Each door can beunlocked from the cabin side by using anexternal unlocking knob concealed behind

the hinged LAVATORY sign. Lifting thebottom edge of the hinged LAVATORYsign exposes the unlocking knob.

Cabin Doors

Eight cabin doors, four on each side ofaircraft, are used for normal passageand all have emergency opening andescape features.

NOTE

For emergency operation of thecabin doors refer to EmergencyExits in Chapter 7.

Each cabin door is a plug type and opensby moving inward and then sliding upwardinto the ceiling. Each door has interiorand exterior controls for normal openingand closing. The six aft (mid, overwing,and aft) cabin doors have identical interiorcontrols, placarding and operating pro-cedures. The two forward cabin doorsare not identical to the six aft doors andhave different interior controls, placard-ing, and operating procedures.

The interior controls for normal opera-tion of the doors consist of the slide arm-ing lever located on the structure adjacentto the door and two door control switch-lights on the cabin attendants console.The escape slide must be disarmed beforethe switch-lights can be used to open orclose the door. When the escape slide isdisarmed the corresponding cabin doorlight on the Flight Engineer's panel andthe two switch-lights on the adjacent cabinattendan's console will come on.

The exterior controls placarding andoperating procedures are identical for allcabin doors. The exterior controls foreach door are located in a recess in thefuselage forward of the door and consist

JLMay 1/75 01-30-01

of a door control handle, a door controlswitch, and an auxiliary handle. Thedoor control handle is used to arm anddisarm the escape slide. The door con-trol switch is used to open and close thedoor. All cabin doors can be manuallylowered from the outside to the closedposition (by free falling) using the doorcontrol handle and the auxiliary handle.

The left forward cabin door can beopened and closed from the outside withno electrical power on the aircraft. Asocket drive fitting may be operatedmanually or by a drill motor. Thisfeature is normally used by maintenance.

Barrier straps, one for each door, aresecured across open doorways as asafety precaution when a ramp or stair-way is not in place. The straps shouldbe disconnected at both ends from thedoor jamb fittings before closing thedoors. Stowage for the straps is providedin the overhead stowage racks.

Lower Cargo Doors

Three external doors are provided foraccess to the lower cargo compartment.The forward and center doors are locatedin the lower right side of the fuselage;the aft door is located in the lower leftside of the fuselage. Bulk or container-ized cargo can be loaded through the for-ward and center cargo doors; bulk cargoonly can be loaded through the aft door.The doors vary in size but are identificalin operation. They are electricallyoperated but can be operated manuallywhen no electrical power is available.An electrical control panel is installed

in the fuselage forward of each door.Each door has a vent door which ventsfuselage pressure overboard if the cargodoor is not properly locked. Limitswitches control the sequencing of theelectrically operated door mechanismsand also provide a visual warning on theFlight Engineer's panel when the door isnot properly closed and locked. Anemergency call switch on the door pro-vides a visual warning in the flight com-partment if actuated by personnel inad-vertently locked in a cargo compartment.A backup test system also is provided tocheck the integrity of the cargo door elec-trical warning system. The test switchis installed on the Flight Engineer'supper instrument panel.

The doors are hinged at the top and openout and up. The doors are opened,closed, and latched by actuating mech-anisms in the doors. External drivefittings also are provided for actuatingthe operating and latching mechanismsmanually. Viewing ports near thebottom of the doors permit checking theposition of the latching mechansimlockpin.

CONTROLS AND INDICATORS

The controls, indicators, and annuncia-tor lights are on the Overhead Panel,Flight Engineer's Upper Panels No. 2and No. 3 and adjacent to or on eachdoor. Illustrations of the control panelsare in another section of this chapter.Individual controls and indicators alsoare illustrated and described in thissection.

01-30-02JL

Nov 1 /75

DOORS Cockpit Door

CKPT DOOR ButtonWhen pushed the button operatesa solenoid control that unlocks thecockpit door.

(OVERHEAD PANEL)

Cabin ViewerWide angle viewing lens for viewingthe cabin area aft of the cockpitdoor.

KeylockThe aft knob of the door requiresa key to open the door from thepassenger compartment side.The door can be opened at any timefrom the cockpit by rotating theforward knob.

SMOKESCREENQUICKRELEASESNAP

LatchRotary latch is installed for lockingthe door. The latch bolt engages akeeper in the door jamb when thedoor is closed.

Smoke Screen Quick Release PanelThe screen is lowered to the closedposition to cover the louvers when itis desired not to have contami-nated cabin air enter the cockpitand to aid smoke evacuation in thecockpit.

Blowout PanelThe blowout panel is installed to pre-vent the cockpit door from hurtlinginto the cockpit in the event of asudden differential pressure betweencabin and cockpit. Relief is ac-complished when the weak blowoutpanel relief latch releases.

BLOWOUT PANELRELIEF LATCH

LouversLouvers are provided for cockpit/cabin pressure equalization to en-able the cockpit door to be opened.

JLFeb 1/79 01-30-03

DOORS - Lavatory Door

(DOOR INNER SURFACE)UNLOCKING KNOB

SLIDING BOLT LOCK

HINGED BEZEL SIGN(NORMAL POSITION)

VACANT/OCCUPIED SIGNActuated by movement ofsliding bolt lock.

DOOR LOCKED

HINGED BEZELSIGN (OPENPOSITION)

SLIDING BOLT LOCK

UNLOCKING KNOB

Unlocks door from outsidelavatory.

DOOR UNLOCKED

LAVATORY DOOR (TYPICAL)

01-30-04JL

Feb 1/79

DOORS -Cabin Door Barrier Straps

OVERHEAD STOWAGE COMPARTMENTS

DOOR BARRIER STRAPBarrier strap is connectedacross the open doorway tojamb fittings. Disconnect atboth ends from fittings beforeclosing door and stow.

DOOR JAMBFITTINGS (2)

STOWAGE CONTAINERFOR BARRIER STRAPS

BARRIER STRAPS(2 STOWED) CABIN DOOR (TYPICAL)

OVERHEAD SIDEWALL STOWAGE COMPARTMENT (TYPICAL)

JLNov 1/78 01-30-04A/04B

DOORS - Cabin

PRESSURE GAGEVIEWING PORT FORDOOR AIR RESERVOIR(Refer to EmergencyExits, Chapter 7)

SLIDE INFLATION CYLINDERLOW PRESSURE SWITCH-LIGHT(Refer to Escape SlidesChapter 7)

MANUAL LIFT BAR(Refer to Emergency Exits,Chapter 7)

SLIDE MODE VERIFICATIONINDICATORS

SLIDE ARMING LEVER

DOOR EMERGENCYCONTROL HANDLE

CABINDOOR CONTROLSWITCH-LIGHT

ATTENDANTSCONSOLE

FORWARD DOORS (2)(View Looking Outboard, Left Side;

Right Side Opposite)PRESSURE GAGEVIEWING PORT FORDOOR AIR RESERVOIR(Refer to EmergencyExits, Chapter 7)

SLIDE INFLATION CYLINDERLOW PRESSURE SWITCH-LIGHT(Refer to Escape Slides,Chapter 7)

MANUAL LIFT BAR(Refer to Emergency Exits,Chapter 7)

SLIDE MODE VERIFICATIONINDICATORS

SLIDE MODE WINDOW

SLIDE ARMING LEVER

DOOR EMERGENCYCONTROL HANDLE

DOOR CONTROLSWITCH-LIGHTS

CABIN ATTENDANTS CONSOLE

AFT DOORS (6)(Mid, overwing and aft)

(View Looking Outboard, Left Side;Right Side Opposite)

JLMay 1/75 01-30-05

DOORS - Cabin Door Interior ControlsTwo Forward Cabin Doors

Slide Arming LeverSLIDEARMED - When moved to SLIDE

ARMED, escape slideis armed and door willbe p n e u m a t i c a l l yp o w e r e d . ARMEDplacard will appear inslide mode verificationindicator.

SLIDEDISARMED - When moved to SLIDE

DISARMED, escapeslide is disarmed anddoor will be electrical-ly powered. ARMEDplacard will disappearfrom view in slidemode verification in-dicator and correspon-ding CABIN DOOR an-nunciation light onF/E's panel and doorcontrol switch-lights atadjacent cabin atten-dant's console willcome on.

NOTEAn interlock mechan-ism locks slide armingmechanism in disarmedposition when door isopen.

Locking Pawl Reset LeverFor operation of lever refer toEmergency Exits in Chapter 7.

GUARD

Door Emergency Control Handle(Red)For Operation of handle refer toEmergency Exits in Chapter 7.

VIEW LOOKING FORWARD(Left Side; Right Side Opposite)

Slide Arming Lever LatchWith Slide Arming Lever in disarmedposition.Sliding latch inboard locks lever indisarmed position. Sliding latch out-board unlocks lever.

SLIDEARMINGLEVER

LOCKPOSITION

UNLOCKPOSITION

VIEW LOOKING DOWNAND INBOARD

Door Control Switch-Lights

To Open — Move slide arming lever toDoor SLIDE DISARMED.

NOTESwitch-lights will come on,indicating correspondingescape slide is disarmedand electrical power isavailable to door.

— Lift plastic cover on uparrow switch-light andpush and hold switch-lightuntil door is opened.

To Close — Lift plastic cover on downDoor arrow switch-light and

push and hold switch-lightuntil door is closed.

— Move slide arming leverto SLIDE ARMED.

NOTESIf switch-light is released while dooris opening or closing, door movementwill stop.If either switch-light sticks indepressed position, door movementcan be stopped by holding oppositeswitch-light in depressed position.

CABIN ATTENDANT CONSOLE(TYPICAL)

Slide Mode Verification Indicator(Two Each Door)Verifies actual condition of escapeslide. ARMED placard visible in-dicates slide is armed. No placardvisible indicates slide not armed.

(Located in forward and aftlower corners of each door)

01-30-06JL

May 1/76

DOORS-Cabin Door Interior ControlsSix Aft (Mid Overwing, and Aft) Cabin Doors

Door Emergency Control Handle(Red)For operation of handle refer toEmergency Exits in Chapter 7.

Slide Mode WindowSLIDEARMED — Indicates escape slide

is armed and door willbe pneumatically po-wered.

SLIDEDISARMED- Indicates escape slide

is disarmed and doorwill be electr ical lypowered.

Slide Arming LeverWhen pushed in (flush), escape slideis armed. SLIDE ARMED placard willappear in window and ARMEDplacard will appear in slide modeverification indicator.When pulled out of recess, escapeslide is disarmed. SLIDE DISARMEDplacard will appear in window andARMED placard will disappear fromview in slide mode verification in-dicator. Corresponding CABIN DOORannunciator light on F/E's panel anddoor control switch-lights at adjacentcabin attendant's console will comeon.

NOTEAn interlock mechanism locks slidearming mechanism in disarmed posi-tion when door is open.

VIEW LOOKING OUTBOARD(TYPICAL)

CABINSIDE WALL

SLIDE ARMINGLEVER IN ARMEDPOSITION

SLIDE ARMINGLEVER INDISARMEDPOSITION

STOWEDPOSITION

SIDE VIEW

Slide Arming Lever LatchWith slide arming lever in disarmedposition, sliding latch outboard lockslever in disarmed position. Slidinglatch inboard unlocks lever.

Door Control Switch-lightsTo Open — Pull slide arming leverDoor out of recess to slide

disarmed position.NOTE

Switch-lights will comeon, indicating correspon-ding escape slide is dis-armed and electricalpower is available todoor.

— Lift plastic cover on uparrow switch-light andpush and hold switch-light until door is open-ed.

To Close — Lift plastic cover onDoor down arrow switch-light

and push and holdswitch-light until door isclosed.

— Stow slide arming leverin slide armed (recessed)position.

NOTESIf switch-light is released while dooris opening or closing, door movementwill stop.If either switch-light sticks indepressed position, door movementcan be stopped by holding oppositeswitch-light in depressed position.

CABIN ATTENDANT CONSOLE(TYPICAL)

Slide Mode VerificationIndicator (Two Each Door)Verifies actual condition of escapeslide. ARMED placard visible in-dicates slide is armed. No placardvisible indicates slide not armed.

(Located at lower forwardand aft corners of each door)

JLMay 1/76 01-30-06A

DOORS-Cabin Door Exterior Controls

Auxiliary HandleHandle is spring-loaded to recessedposition and is used to close door byfree falling. (Normally used bymaintenance.)

Door Control SwitchSwitch is spring-loaded to center-offand is used to open and close doorelectrically.

NOTEIf switch is released while door is op-ening or closing, door movement willstop.

Door Control HandleNOTE

For emergency operation of handlerefer to Emergency Exits in Chapter 7.Pulling handle out of recess infuselage disarms escape slide andprovides access to door controlswitch and auxiliary handle,

NOTEAn interlock mechanism locks slidearming mechanism in disarmedposition when door is open.

NEUTRACPOSITION

(Typical 8 Doors)

Socket Drive Fitting (Left ForwardDoor Only)The socket drive fitting is providedfor opening and closing door if elec-trical power is not available. (Nor-mally used by maintenance.)

Door OperationTo OpenDoor — Pull door control handle

out of recess to disarmescape slide.

— Move door controlswitch to OPEN andhold until door is open-ed.

To CloseDoor — Move door control

switch to CLOSE andhold until door is clos-ed.

— Stow door control han-dle in recess (flush) toarm escape slide.

To FreeFall Door — Rotate door control

handle to FREE FALLand hold.

— Pull auxiliary handle outand down and hold.

— After door descends tofloor level, personnel incabin manually pushdoor outboard to closedposition and hold.

NOTEForward door may re-quire assistance to freefall.

— When door is closed,release auxiliary handle

— Release door controlhandle. Handle returnsto neutral position lock-ing door closed.

— Stow door control han-dle in recess (flush) toarm escape slide.

01-30-06B JLFeb 1/79

LOWER CARGO DOORS—Forward READY TOLOCK LIGHT

CONTROL PANEL

VENT DOORLATCH HANDLE

VENT DOOR

LOCK PINVIEWING

PORT

DOOR AND CARGOCONTROLS INSIDE

FOR MANUAL OPERATIONMAX TORQUE 200 LB-INMAX SPEED 150 RPM

CAUTION:AFTER CLOSINGLOCK LATCHES

CAUTION:BEFORE OPENINGRELEASE LATCHES

DOOR ACTUATORMANUAL DRIVE FITTING

COVERPLATE

DOOR LATCH MANUAL DRIVE FITTING(BEHIND COVER PLATE)

JLFeb 1/80 01-30-07

LOWER CARGO DOORS-Center READY TOLOCK LIGHT

FOR MANUAL OPERATIONMAX TORQUE 200 LB-INMAX SPEED 150 RPM



WING TO FUSELAGEEXTENDED FILLET

CONTROL PANEL

CONTROL PANELACCESS DOOR(IN FILLET)

VENT DOORDOOR ACTUATOR

MANUAL DRIVE FITTING

VENT DOORLATCH HANDLE

ACCESS DOOR(IN FILLET)

LOCK PINVIEWING

PORT

MANUAL OPERATIONWARNING:

DOOR MAY SPRING OPENPRIOR TO MANUALLY UNLATCHING MANUALLY CRANK DOOR ACTUATOR TO THE FULLY CLOSED POSITION00 NOT ATTEMPT TO PRY DOOR OPEN OR OPEN DOOR ELECTRICALLY IF DOOR IS COVERED WITH ICEDO NOT USE POWER TOOLS

0 UNLOCK AND UNLATCH DOORPLACE VENT DOOR HANDLE IN OPEN POSITIONTURN ACTUATOR DRIVE UNTIL LATCHES ARE OPEN

0 LATCH AND LOCK DOORTURN ACTUATOR DRIVE UNTIL VENT DOOR HANDLE CAN BE CLOSED


VENTDOOR

FILLET

01-30-08JL

Feb 1/80

LOWER CARGO DOORS-Aft FOR MANUAL OPERATIONMAX TORQUE 200 LB-INMAX SPEED 150 RPM

CLOSE


OPEN


DOOR ACTUATORMANUAL DRIVE FITTINGREADY TO

LOCK LIGHTVENT DOORLATCH HANDLE

VENT DOOR

LOCKPINVIEWING

PORT

DOOR CONTROLSINSIDE

CONTROL PANEL


COVERPLATE

01-30-09JLFeb 1/80

DOORS-ANNUNCIATOR LIGHTS AND CARGO DOOR WARNING TEST SYSTEM

AVIONIC-COMPT EXT DOOR LightComes on when door handle of theavionic compartment lower door isrotated to the unlatch position.Light remains on until door is fullyclosed and latched.

AVIONIC COMPT WHLWELLDOOR LightComes on when latch pin of theavionic compartment aft door is re-tracted. Light remains on until dooris fully closed and latched.

CABIN DOOR LightsCome on when cabin door(s) arenot closed, fully latched, and theescape slide is not armed.

AIR COND DOORS LightComes on when any one of the threeair conditioning compartmentdoors is unlatched and moved fromthe fully closed position. Light willremain on until all three doors arefully closed and latched. One indi-cating light is provided for the threedoors.

CTR ACCESS COMPT DOORLightComes on when center accessorycompartment door handle is ro-tated to unlatch position. Light willremain on until door is fully closedand latched.


CARGO DOOR Lights(SYS A, SYS B)Come on when cargo door(s) are notclosed and fully locked. An emergencymomentary call switch is installed oneach cargo compartment door for useby personnel inadvertently locked in acargo compartment. When call switchis actuated, corresponding SYS Adoor light comes on.

CARGO DOOR INDICATIONTEST SwitchTEST — (momentary) Turns on

FWD, C T R , and AFTCARGO DOOR SYS A andSYS B lights when cargodoors are fully closed andlocked. System A teststhe integrity of the doorclosed and locked, andemergency call switchescircuitry. System B teststhe integrity of the prox-imity switches and un-locked sensors circuitry.

NORM-CARGO DOOR l igh tsshould be off when cor-responding door is closedand fully locked, and onwhen co r respond ingcargo door is unlockedand open.

NOTECARGO DOOR lights are not dim-able and do not turn on MASTERCAUTION system.


01-30-10

JLFeb 1/79

LIGHTING

GENERAL

The normal aircraft lighting systemscomprise the cockpit, passenger cabinand galley, and exterior systems. Thelatter category includes only thoseexterior lights which are controlled fromthe cockpit. Within each major sub-system the general illumination, supple-mentary, and standby lighting systemsare discussed, if applicable. A descrip-tion of the emergency evacuation lightsmay be found in Chapter 7.

DESCRIPTION

Interior Lighting

Cockpit Lighting - Cockpit illuminationis provided by primary, secondary,thunderstorm, and standby lighting sys-tems. The primary system consists ofintegrally lighted instruments and light-plates with individual control circuits toprovide a continuous control of the illumi-nation from maximum light intensity toOFF. Fluorescent lamps are used in adome light for general illumination ofthe cockpit. For the secondary system,a combination of fluorescent and incandes-cent lamp floodlights are used for themain instrument panels and the FlightEngineer's worktable. Incandescentfloodlights are used for the overheadpanel, the pedestal, and the FlightEngineer's instrument panels. Individualcontrols are used for the floodlights tovary the illumination level from maximumlight intensity to off. A thunderstormswitching circuit is installed to overrideall instrument, floodlight and dome lightcontrols and provide a high intensityillumination. Supplementary map, brief-case, chart holder, worktable, and floor-lights are provided for crew utilization asrequired. A standby lighting system is

provided which automatically turns onselected white floodlights of the secondarylighting system if normal electrical powerfails to supply dc bus three. The standbysystem will provide the following opera-tion: (1) The center instrument panelincandescent floodlights will be energizedonly and will illuminate the standby hori-zon, altimeter, and airspeed indicators.With the incandescent floodlight controlin the full OFF position, the centerinstrument panel will be illuminated witha preset light intensity. With a clockwiserotation of this control the preset illumi-nation level can be increased to maximumlight intensity. With the EMER PWRswitch in the ON position, the incandes-cent floodlights for the Captain and FirstOfficer's instrument panels will be ener-gized with their respective incandescentfloodlight knobs in the full OFF position,and will provide illumination at a presetlight intensity. A clockwise rotation ofthe respective control will allow illumina-tion level to be increased to maximumlight intensity. (2) The left incandescentfloodlights for the overhead panel and theFlight Engineer's upper and lower panelswill be operated at a preset light intensity.In the event of a total loss of electricalpower, the battery switch must be at BATfor the standby lights to operate.

Cabin Lighting - Illumination in the cabinis provided by two general types oflighting. The portion of the cabinbetween the drop ceilings is illuminatedby direct overhead and indirect sidewall(mood) lighting. The areas under thedrop ceilings are illuminated by directceiling floodlights on the cross-aislesand over each main cabin door. Individ-ually controlled reading lights are pro-vided for each seat position. Additionallythere are threshold boarding lights ineach entryway. In the event of cabindepressurization, the overhead lightingin all cabin sections is automaticallyactuated.

JLMay 1/76 01-40-01

Exterior Lighting

The exterior lighting consists of landing,ground operating, anti-collision, scan,high intensity, and position lighting sys-tems. There are four landing lights,one located on each side of the forwardfuselage and two on the nose gear. Twoground flood/runway turnoff lights,located on each side of the fuselage nearthe wing root, may be used to supplementthe nose gear landing lights during taxioperations or for general area illumi-nation. Two anti-collision beacons, onelocated on top and one on the bottom ofthe center fuselage are provided. Scanlights for the wing and number one andthree engine nacelles are located on eachside of the fuselage forward of the wing.Position lighting consists of a non-standard arrangement of lights on eachwing tip. Dual red and dual green lightsare mounted on each tip in the standard

manner, but the white position lights aremounted two on the trailing edge of eachwing tip, rather than on the tail. Thiswingtip arrangement still providesstandard left/right and fore/aft orienta-tion to an external observer. In addi-tion, each wing tip has three sequentiallyflashing high intensity lights which maybe separately controlled from thecockpit.


Controls and indicators are on the Over-head Panel, the Captain's andCopilot's Light Control Panels, FlightEngineer's Lower Panel, and the Pedes-tal. Illustrations of the panels are inanother section of this chapter. Individ-ual controls and indicators also areillustrated and described in anothersection of this chapter.

INTERIOR LIGHTING - Controls and IndicatorsCockpit Lighting STBY COMP Light Switch

Two-posit ion switch controls thestandby compass light.NO SMOKE & SEAT BELTS

Sign SwitchesON — Turns on the respective signs

and sounds a chime in thecabin.

AUTO-The NO SMOKING and FAS-OR TEN SEAT BELT signs willOFF come on and a chime will

sound in the cabin when cabindecompression occurs (Cabinaltitude exceeds 10,000 feet).

AUTO-The RETURN TO CABIN andFASTEN SEAT BELT signs willcome on and a chime willsound in the cabin when theflap handle is out of the UPposition or the landing gearhandle is in the DOWN posi-tion. The NO SMOKING signswill come on and a chime willsound in the cabin when land-ing gear handle is in theDOWN posit ion.

(OVERHEAD PANEL) FGC FLOOD LIGHT KnobRotate to control brilliance of FGC con-trol panel flood lights.

FGC Panel Light Intensity ControlRotate to control brilliance of FGC con-trol panel backlighting.

(GLARESHIELD)

BRIEFCASE Light Knob (2)On /Off switch and intensity control ad-justs brilliance of briefcase area.FLOOR Light Switch (2)

Three-position switch operates cockpitfloor lights as required. Switch posi-tions are self-explanatory.

MAP Light Knob (2)PRESS FOR ON/OFF knob acts as on/off switch and adjusts brilliance by ro-tating.

FLOOD Light Knobs (2)The flood knobs are dual concentricknobs. The large outer knob is an on/off switch and controls the fluorescentlights. The smaller inner knob controlsthe incandescent lights.

PNL & FMA Light Knobs (2)The panel light knobs are dual concen-tric knobs. The larger outer knob con-trols integral panel and instrumentlights. Rotating the knob out of the OFFposition turns on the lights. Further ro-tation varies the intensity of the panellights. The smaller inner knob controlsintensity of FGS mode annunciatorlights.

CAPTAIN'S AND COPILOT'S LIGHT CONTROL PANELS

JLFeb 1/76 01-40-03

INTERIOR LIGHTING - Controls and IndicatorsCockpit Lighting

CTR INST & PED PNL LightKnobsDual knobs permit separate con-trol of center instrument paneland pedestal integral lights.

PED FLOOD Light KnobOn/off switch and intensity controlfor pedestal flood light. Large outerknob adjusts F/E's map light for usewhen F/E is facing forward.

CTR INST FLOOD Light KnobsDual knobs for control of the cen-ter instrument panel flood lights.Large outer knob, with the indexindicator marking, is an on/offswitch and controls the fluores-cent lights. Small inner knob con-trols the incandescent lights.

(PEDESTAL)THNDRSTRM LT Switch

ON — All instrument and controlpanel floodlights, and theflight compartment domelights come on at full inten-sity, overriding all in-dividual controls.

OVHD PNL LT PNL KnobOn/off switch and intensity controlfor integral panel lights.

OVHD PNL LT FLOOD KnobOn/Off switch and intensity con-trol for overhead panel floodlights.

DOME LT Button (2)On/off push button switch oper-ates dome lights on cockpit ceil-ing. (OVERHEAD PANEL)

BRIEFCASE LT ButtonOn/off push button switch oper-ates briefcase area light.

(FLIGHT ENGINEER'S WORK TABLE)PNL LT KnobOn/off switch and intensity controlfor integral panel and instrumentlights.

TABLE LT KnobOn/Off switch and intensity con-trol for table light.

FLOOD LT KnobOn/off switch and intensity controlfor F/E's flood lights.

CKT BKR LT KnobOn/off switch and intensity controlfor integral lighting of the fwd andaft overhead, F/E's overhead, uppermain, and lower main circuitbreaker panels.

(FLIGHT ENGINEER'SLOWER PANEL)EMER LT

Switch

(FORWARD CABINATTENDANT'S STATION)

For descript ion refer toEmergency Equipment Chapter.

EMER LTTEST Button

EMER LT TESTLight

EMER LTSwitch

Emer LightDISARMED Light

(OVERHEAD PANEL)For description refer toEmergency Equipment Chapter.

EMERGENCYLIGHTS

01-40-04JL

Nov 1/78

INTERIOR LIGHTING - Controls & IndicatorsCabin Lighting

LEFT FORWARD CABIN ATTENDANTPANEL

LEFT MID CABINATTENDANT PANEL

LEFT OVERWING CABINATTENDANT PANEL

LEFT AFT CABIN ATTENDANTPANEL

RIGHT FORWARD CABINATTENDANT PANEL

RIGHT MID CABINATTENDANT PANEL

RIGHT OVERWING CABINATTENDANT PANEL

RIGHT AFT CABIN ATTENDANTPANEL

FORWARD LEFT CABIN ATTENDANT PANEL (TYPICAL)

JLFeb 1/75 01-40-05

EXTERIOR LIGHTING

ANTI-COLLISIONBEACON

GROUND FLOODAND TURNING

NAVIGATION(TYPICAL BOTH WINGS)

WING/NACELLESCAN

NOSE LANDING

LANDING

HIGH INTENSITYRECOGNITION(TYPICAL BOTH WINGS)

TOPRIGHT SIDELEFT SIDEBOTTOMWINGTIPS

01-40-06JL

May 1/76

EXTERIOR LIGHTING - Controls & Indicators

LDG LT Switch (L, R)RET — Light is off and retracted

flush with fuselage.EXT OFF-Unit is extended, light is

off.EXT ON -Unit is extended, light is

on. Requires about 10 sec-onds to extend.

LDG LT Switch (NOSE)TAXI - Lamps are on with less than

full intensity for ground oper-ations.

LAND - Lamps are on at full intensityfor landing.

NOTEThe nose gear landing lightswill come on only when thelanding gear control handleis in the DOWN position.

RUNWAY TURNOFF LT Switch (L,R)The runway turnoff lights may be usedduring all ground operations to sup-plement the available lights.ON — Lights are on. May also be used

for ground servicing.

OVERHEAD PANEL

JLFeb 1/75 01-40-07

EXTERIOR LIGHTING - Controls & Indicators

NAV Light SwitchON - Energizes four position lights in

each wing tip. Two left forwardposition lights emit red lighting,two right forward position lightsemit green lighting, and the afttwo position lights on each wingtip emit white lighting.

BEACON Light SwitchON-Turns on anti-collision lights on

top and bottom of the airplanefuselage.

HI-INT Light SwitchON — Turns on supplemental high in-

tensity recognition lights ineach wing tip. Each wing hasthree lights (two forward andone a f t ) which f lash insequence with anti-collisionlights.

WING Light SwitchON - Turns on the scan lights for the

wing engines and wing surfaces.R ONLY — Turns on only the right scan

light, the left scan remainsoff. Used primarily forground servicing.

OVERHEAD PANEL

01-40-08JL

Nov 1/78

SEATS

GENERAL

The cockpit contains seats for a Captain,| Copilot, Flight Engineer, and a

First and Second Observer. The FlightEngineer's seat is located behind theFirst Officer's station and the Observers'seats are located behind the Captain'sstation. All seats, except the SecondObserver's seat, have electrical and/ormanual adjustments. If the electricalcontrol or power of a seat fails, fullmovement of the seat is possible thrumanual operation. All seats are equippedwith belts and dual shoulder harnesseswith inertia reels. All seats except theSecond Observer's seat are equipped witha crotch belt.

DESCRIPTION

| Seats for the Captain and Copilotare power operated by two electricmotors to provide vertical and horizontaladjustments. The recline, lumbar sup-port, armrest, and thigh support controls

I are manually operated.Copilot's seat has a recline limit switchwhich inhibits outboard movement of theseat whenever the backrest is reclinedmore than one notch from the uprightposition. The seat indicator incorporatestwo numerical index scales; one scalerepresenting the vertical position of theseat and the other the horizontal. By

means of individual exit control switches,the Captain's and Copilot's seat Imay be moved to the full aft and outboardpositions to facilitate exit.

The Pilot Eye Locator consists of opticalpainted white lines on the glareshield.An illustration and the operation of thewhite line optical locator is shown in thissection.

The Flight Engineer's seat also is poweroperated to provide vertical and hori-zontal adjustments. The recline, lumbarsupport, armrest, and swivel controlsare manually operated. The swivel con-trol permits adjustment between forwardand outboard facing positions. Whenfacing forward, the seat can be raisedhigher vertically than when facingoutboard.

On power-operated seats, placing thepower ON/OFF switch to OFF afteradjusting the seat for takeoff or landingprevents seat movement (runaway seat)if an electrical short should occur in theseat wiring.

The First Observer's seat has manualadjustments only. These adjustments pro-vide vertical, forward, aft, lumbar sup-port and swivel movement. The backrestis fixed and cannot be adjusted. TheSecond Observer's seat is a foldingnonadjustable type bolted directly to thefloor structure.

JLMay 1/76 01-50-01

CAPTAIN'S AND COPILOT'S SEATS

Lumbar SupportInf latable pi l low in seatbackcushion with push-button typevalve on lower left edge of seatcushion.Press valve and exert back pres-sure against cushion, forcing airout until desired contour isobtained. Remove finger pres-sure; contour is maintained.Reinflate pillow by depressingand holding valve with no backpressure on seatback cushion.

Armrest Release (2)Flush fingertip control on bottomof armrest releases lock to per-mit adjustment. The inboardarmrest may be swiveled aroundbehind seat back from stowedposition to provide additionalspace for entering or leavingseat.

DUAL SHOULDERHARNESS

STOWED POSITION

SEAT BELTCROTCH STRAPTHIGH SUPPORT

Seat Position IndicatorHorizontal and vertical indexscales indicate seat position.Indicator light on when seatpower switch is in ON position.

CAPTAIN'S SEAT(COPILOT'S OPPOSITE)

Power Control HandlePlacing the four-position handleto FWD, AFT, UP, or DOWN posi-tion will move seat in direction ofhandle movement. When seat isin full outboard and aft position(for exit), placing handle in FWDposition will first move the seatinboard then forward.Handle is spring-loaded to thecenter position.

Power SwitchON/OFF switch controlspower to seat.

Manual Vert ical /HorizontalControl HandlesRaising handles releasesseat position locks for manualadjustment.

Seat ControlsShown upsidedown for clarity.

EXIT Control ButtonWhen pushed the button oper-ates the electric motor to movethe seat aft and outboard for exitfrom cockpit. Seat must bemoved full aft (and the Co-pilot 's seat back must be inthe vertical position) before itcan be moved outboard.

Thigh Support ControlRaising control releases thighsupport for manual adjustment.

RECLINE Control HandleRaising the RECLINE control re-leases seatback lock for manualadjustment from upright to re-cline position.

01-50-02JL

May 1/76

FLIGHT ENGINEER'S SEAT

Armrest Release (2)Flush fingertip control on bottomof armrest releases lock to per-mit adjustment.

STOWEDPOSITION


Lumbar SupportInf latable pillow in seatbackcushion with push-button typevalve on lower left edge of seatcushion.Press valve and exert back pres-sure against cushion, forcing airout until desired contour isobtained. Remove finger pres-sure; contour is maintained.Reinflate pillow by depressingand holding valve with no backpressure on seatback cushion.

SEATBELT

Manual Vertical / HorizontalControl HandlesRaising handles releasesseat position locks for man-ual adjustment.

SWIVEL ControlRaising handle releases lock formanually rotating seat.

Seat ControlsShown upside-down for clarity.

RECLINE Control HandleRaising the RECLINE control re-leases seatback lock for manualadjustment from upright to re-cline position.

Power SwitchON /OFF switch controls power toseat.

Power Control HandlePlacing the four-position handleto FWD, AFT, UP, or DOWN posi-tion will move seat in direction ofhandle movement.Handle is springloaded to thecenter position.

JLFeb 1/75 01-50-03

OBSERVER'S SEATS

Lumbar SupportInflatable pillow in seatback cushion withpush-button type valve on lower left edge ofseat cushion.Press valve and exert back pressure againstcushion, forcing air out until desired contouris obtained. Remove finger pressure; contouris maintained. Reinflate pillow by depressingand holding valve with no back pressure onseatback cushion.

Armrest Release (2)Flush fingertip control on bottom of armrestreleases lock to permit adjustment.


STOWEDPOSITION

SEATBELT

RETRACTABLE FOOTRESTPress inward at top of sup-port strut for automaticretraction.

FIRST OBSERVER'SSEAT

DUALSHOULDERHARNESS

SEATBELT

SECOND OBSERVER'S SEATShown in the extended position.Normally springloaded in stowedposition.

Seat Controls (S, V, H)Controls release seat for man-ual adjustment to desired po-sition

01-50-04JL

Feb 1/75

PILOT EYE LOCATOR-Optical White Line(Left Side Shown-Right Side Opposite)

VERTICAL SEAT POSITION SIGHTING.Adjust seat vertically so that pilot's line of sight is tangen-tial to top flat surface of glareshield.

FORE AND AFTSEAT POSITION

WHITE LINE OPTICAL LOCATOR(PAINTED ON GLARESHIELD)

FORE AND AFT SEAT POSITION SIGHTINGSight across to the small white line under the oppo-site pilot's glareshield. Adjust fore and aft seat posi-tion until white line appears to touch sloping edge ofglareshield. Readjust seat elevation as required tomaintain line of sight tangential to top flat surface ofglareshield.

TANGENT POINT(GUSSET PADDINGAND WHITE LINE)

JLAug 1/87 01-50-05/06

WARNING AND CAUTION SYSTEMS

GENERAL

The warning and caution systems provideaural, visual, and tactile indications towarn of unsafe operating conditions oraircraft configurations, and systemsmalfunctions. Warnings of fire or over-heating, unsafe landing gear conditions,altitude advisory indications, slatsextended above placarded limit speeds,autopilot disengage, loss of cooling air-flow thru inertial navigation unit, andexcessive cabin altitude are both visualand aural. Stabilizer motion, overspeed,and takeoff configuration warnings areaural only. Stall warning is provided bystick shaker only, with no accompanyingvisual or aural indications.

DESCRIPTION

Central Aural Warning System

Aural warnings (except APU fire) aregenerated in a central control unit whichprovides warning discrimination by meansof varying the pitch, duration, and repeti-tive frequency of the aural signal. Theaural warnings can be tested for all con-ditions except cabin altitude, and altitudeadvisory. Once sounded, the aural warn-ings can be silenced by operating theappropriate silencing switch or returningthe aircraft to the correct configurationfor the condition indicated. Detailedinformation regarding the operation andtesting of each of the central aural warn-ing system functions are covered in thedescription and controls and indicatorssections of each of those chapters dealingwith the applicable systems.

APU Fire Warning Horn

Aural warning for APU fire is providedby an exterior horn, common to bothsystems, located just aft of the left wheelwell. Provisions are made for silencing

the horn and for re-arming the circuitryfor subsequent warnings.

Visual Warning and Caution System

Visual warning and caution indicationsare provided in the engine fire and fuelcontrol handles and by annunciator lights.Where practical, individual lights arelocated adjacent to, or in the controls orindicators for the respective system.Lights pertaining to systems with controlsor indicators in more than one area arelocated on annunciator panels for the For-ward Overhead Panel and Flight Engi-neer's Upper Instrument Panel No. 2.The red MASTER WARN lights comeon to indicate a condition that requiresimmediate attention. The amber MASTERCAUTION lights come on to indicate acondition that requires less than imme-diate attention.

Master warning and master caution lightscome on concurrently with their respec-tive individual warning and caution lightsat the respective crew stations. Addi-tionally, the Captain's and Copilot'sMASTER WARN or MASTER CAUTIONlights will come on whenever certainselected warning or caution lights comeon at the Flight Engineer's station. Push-ing either of the pilots' MASTER WARNor MASTER CAUTION lights will turnthe respective lights off at both sta-tions and reset the system for subsequentindications. The flight engineer'sMASTER WARNING or MASTERCAUTION lights can be reset only fromthe flight engineer's station and do notreset the pilots' lights. The individualwarning or caution lights will remain onuntil the condition has been corrected.During dual land mode, the MASTERWARN and MASTER CAUTION lights areinhibited at 100 feet radio altitude.Certain individual caution lights are

JLMay 1/76 01-60-01

considered advisory and do not cause theMASTER CAUTION lights to come on.

Summary lights and cue lights on the pilots'annunciator panel provide indications ofwarnings or cautions associated with thevarious aircraft systems. The summary lightsare not resettable and will remain on until thecondition is corrected. The cue lights may bereset and, when pushed, will also turn off thepilots' MASTER CAUTION lights. Annun-ciator light brilliance is controlled by PRESSTO BRT/DIM buttons on the Overhead Paneland on the Flight Engineer's panel. The but-tons affect all annunciator lights at the respec-tive crew station except:

• MASTER WARNING lights.

• MASTER CAUTION lights.

• First 8 lights in column 2 and 3 of theFlight Engineer annunciator panel (in-cludes all door lights).

Tactile Warning System

The dual stall warning system actuates a stickshaker to warn of an impending stall. Novisual stall warning is provided.

Ground Proximity Warning System

For detailed description of ground proximitywarning system, refer to Navigation SystemsChapter.


Controls and indicators are on the FlightEngineer's Upper Panel No. 1, Upper Panel No.2, Upper Panel No. 3, the Pilot's InstrumentPanels, Overhead Panel, the Pedestal, and theGlareshield. Illustrations of the panels are inanother section of this chapter. Individualcontrols and indicators are illustrated anddescribed elsewhere in this section.

Vol. III01-60-02

JLSep 15/92

AURAL WARNING AND CAUTION SYSTEM PARTICULARS SHEET 1

WARNINGINDICATED

APU FIRE

CABIN ALTITUDE

ENGINE FIRE

LANDING GEAR(Throttles)

LANDING GEAR(Flaps)

OVERSPEED

STABILIZER INMOTION

STALL WARNING

AUTOPILOTDISENGAGE

AURAL WARNINGCHARACTERISTIC

Extremely loud exteriorhorn.

Intermittent car hornsound (identical to takeoffwarning).

Intermittent, bell-like ring-ing sound.

Continuous car hornsound.

Continuous car hornsound.

Chicken-like cluckingsound (identical to slatsextended and slat handleextend warning).

Continuous deep pitchedair horn sound.

None

Tactile warning by stick shaker. Both columns willvibrate simultaneously.

Warbling horn sound.

VISUAL INDICATION

APU FIRE Light (F/E), APUFIRE Light (summary), MAS-TER WARN Lights.

CABIN ALT Lights.

ENG FIRE Handle, FuelLever, ENGINE FIRE Light,and respective LOOPS A andB Lights.

Red lights for any gear notdown and locked.

None unless unsafe gearcondition exists.

None

(Stabilizer LONG TRIM indi-cator may be crosschecked).

None

Flashing red AP Light forassociated system.

CONDITIONINDICATED

Fire or overheat inAPU compartment.

Cabin altitude hasexceeded allowablelimit.

Fire or overheat inengine nacelle.

Any gear not downand locked and anythrottle retarded toIDLE and air speed isless than 215 knots.

Any gear not downand locked and flapsextended 28.5° ormore.

Airspeed aboveVMO/MMO

Horizontal stabilizer inmotion (no warninguntil continuous move-ment exceeds onedegree).

Airspeed approachingstall condition forflap/slat configuration.

Autopilot disengaged.

DEACTIVATE

HORN Switch on APUGND CONT Panel, orAPU FIRE CONTROLSwitch.

Press CABIN ALTWARN HORN Button.

Press ENGINE FIRELight or pull ENGFIRE Handle.

Gear horn off button,provided flaps are inan approach config.(less than 28.5°).

Extend gear.

Correct overspeedcondition.

Warning silencedwhen stabilizer isstopped.

Correct stall condition.

Press AP Light orAutopilot releasebutton.

TEST

LOOPS TESTSwitch (no au-ral warning intest).

None

LOOPS TESTSwitches.

(1) GEAR LTTEST Button(no auralwarning).(2) GEARHandle whenpulled out (vi-sual and auralwarning).

None

MAX SPDWARN TestSwitch.

Operate longi-tudinal trimcontrols.

STALL TESTSwitch.

None

JLAug 1/81 01-60-03


WARNINGINDICATED

SLATS EXTENDEDWARNING

SLAT HANDLE EX-TEND WARNING (Ef-fective on airplaneswith SB 31-37 incor-porated or productionequivalent.)

TAKEOFF WARNING

ALTITUDE ADVISORY


Chicken-like cluckingsound (identical tooverspeed and slat han-dle extend warning).

Chicken-like cluckingsound (identical to slatsextended and overspeedwarning).

Intermittent car hornsound (identical to cabinaltitude warning).

Dual airhorn sound of 2-second total duration.

None

None

None

VISUAL INDICATION

Slat TAKEOFF Light.

Flap/Slat handle not inUP/RET.

None

PARK BRAKE ON Light.

Steady altitude advisory lighton altimeters. Stays on untilwithin 250 feet of selectedaltitude.

Flashing Altitude Advisorylight on altimeters.

None

Flashing Altitude Advisorylight on altimeters.

CONDITIONINDICATED

Slats extended aboveplacarded slat extendlimit speed.

Flap/Slat handlemoved from UP/RETabove slat extendlimit speed.

Slats not in T.O. EXTrange. Flaps are inlanding range. Spoilerhandle not fully for-ward. Stabilizer set-ting not in greenband.

Parking brake is notreleased; ground shiftmechanism is inground mode andeither throttle 1 or 2is advanced fortakeoff.

Airplane at capturethreshold relative toselected altitude (750feet or greater).

Deviation occurs fromcapture threshold pri-or to reaching 250feet of selectedaltitude.

Maintain selected alti-tude within ±250feet.

Deviation of morethan ±250 feet afterselected altitudecapture.

DEACTIVATE

Slow to belowplacarded slat extendlimit speed and re-tract slats.

Move flap/slat handleto UP/RET. Slow tobelow placarded slatextend speed beforeextending slats.

Correct controlsetting(s).

Release parkingbrake.

Steady light - Selectnew altitude. FlashingLight - Push altitudeRESET button.

None

None

Configure toany of notedconditions andadvance throt-tle 1 or 2.

None

Selection ofaltitude abovefield elevationand rotation ofBaro SetKnob to 750feet and 250feet of select-ed altitude.


WARNINGINDICATED

DECISION HEIGHT(DH)

INS WARNING (onground)

PASSENGER EMER-GENCY EVACUATION

GROUND PROXIMITYWARNING


Continuous horn sound ofincreasing amplitude.

Loud intermittent exteriorhorn.

High pitched intermittentwarbling sound.

Cabin attendant's chimein cockpit.

Whooping sound and vo-cal command - PULLUP.

Vocal warning -GLIDESLOPE.

VISUAL INDICATION

DH light comes on when de-cision height is reached.

Applicable system INS FLOWOFF Light on. (Pilot Over-head Annunciator Panel)

Flashing red light cockpitoverhead and applicable at-tendant's panels.

Flashing red light cockpitoverhead panel.

Flashing red GPWS Light onglareshield.

Amber BELOW G/S Light onglareshield.

CONDITIONINDICATED

Airplane at 50 feetabove and descend-ing to decision height(DH). Sound stopswhen DH is reached.

(1) Loss of coolingairflow thru INS unit.(2) INS operating onbattery power withAC power removed.

EVACUATION SIGNALcommand switch ON,or in ARM with cabinattendant's EVACswitch on.

EVACUATION SIGNALcommand switch OFFand cabin attendant'sEVAC switch on.

(1) After takeoff, be-tween 50 and 700feet, sink rate greaterthan 100 FPM withgear up or flaps up.(2) During cruise orlanding, gear up be-low 500 feet or flapsup and combinationof radio height andsink rate below 500feet.(3) Excessive sinkrate below 2450 feet.(4) Excessive terrainclosure rate below1800 feet.(5) Excessive devi-ation below theglideslope at radioaltitudes below 1000feet.

DEACTIVATE

DH Light - Press toturn off.

Turn off applicableINS systems.

(1) EVACUATION SIG-NAL command switchOFF and cabin atten-dant's EVAC switchoff. (Pulling hornshutoff button onlysilences individualhorn at applicablestations.)

Cabin attendant'sEVAC switch off.

(1) Increase climbrate.(2) Extend gear.(3) Reduce rate ofdescent.(4) Pull up.(5) Correct deviation.

TEST

SET/TESTknob.

None

None

None

GND PROXIM-ITY TestButton.

JLFeb 1/79 01-60-04A/04B


INSTRUMENT MARKINGS

Four colors are used in the instrument markings. These reflect the latest operating limitations and take theform of arcs and radials. The colors used and their meanings are as follows:

RED Warning, danger, maximum limit, minimum limit

YELLOW Caution, abnormal

WHITE OR GREEN Continuous, normal range

Careful attention should be given to the instrument markings, because of the precautions and limitations theyrepresent.

JLFeb 1/79 01-60-05

ENGINE FIRE LIGHT(GLARESHIELD)

(For description of above lightrefer to Fire Protection Chapter.

MASTER WARN Light (2)

Both lights come on whenevercertain, selected individual warn-ing lights on either Pilot's orFlight Engineer's panels comeon.Pushing either light will turn offthe Captain 's and Copilot'sMASTER WARN lights and resetthe system for subsequent in-dications.

MASTER CAUTION Light (2)

Both lights come on whenevercertain, selected individual cau-tion lights on either Pilots' orFlight Engineer's panels comeon.Pushing either light will turn offthe Captain 's and Copilot 'sMASTER CAUTION lights andreset the system for subsequentindications.

Annunciator Panel

Contains summary lights, cuelights, and caution and advisorylights not located with the con-trols or indicators for the associ-ated systems.

(GLARESHIELD) (GLARESHIELD)

OVERHEAD PANEL

PRESS TO BRT/DIM Switch

When pushed will select the an-nunciator lights bright mode ifdimmed, or the dim mode if onbright. Does not dim the MAS-TER WARN or MASTER CAU-TION lights.

Cue Lights (4)

Light comes on whenever cau-tion light on the Flight Engineer'spanel in the associated systemcomes on. These lights are reset-table. When pushed to reset, willalso turn off the MASTER CAU-TION light.

ANNUN LT TEST Switch

Pushing the switch will turn on alllights on the annunciator paneland selected lights on the over-head and instrument panels.

Summary Lights (6)

Light comes on whenever warn-ing light in the associated systemcomes on. These lights are notresettable.

FLIGHT ENGINEER'S ANNUNCIATOR PANEL

ANNUNCIATOR PANEL

Contains caution and advisory lights not located adjacentto the controls or indicators for the associated system.

MASTER WARNING Light

Comes on whenever any individual warning light comes onexcept for certain warnings associated with flight controland guidance systems and the landing gear.Pushing the light will turn off the light and reset the sys-tem for subsequent indications.

NOTEWhen the F/E's MASTER WARNING light comes on, the pilots'MASTER WARNING lights also come on.

MASTER CAUTION Light

Comes on whenever certain selected caution lights comeon.Pushing the light will turn off the light and reset the sys-tem for subsequent indications.

NOTEWhen the F/E's MASTER CAUTION light comes on, the pilots'MASTER CAUTION lights also come on. When the pilots'MASTER CAUTION lights come on, the F/E's MASTERCAUTION light may not come on depending on the source ofthe individual warning.

(FLIGHT ENGINEER'S PANEL NO. 2)

PRESS TO BRT/DIM Button

When pushed will select the annunci-ator lights bright mode if dimmed, orthe dim mode if on bright.Does not dim the MASTERWARNING, MASTER CAUTION, DCGND SERVICE BUS OFF, orDOORS lights.

AREA TEST ButtonWhen pushed will turn on all annun-ciator lights on the area of the F/E'spanel that has been selected for test.

AREA TEST SELECT SwitchSelect portions of the F/E's panel fortest of annunciator light operation.

ALL TEST SwitchALL TEST — (Momentary) Turns on allannunciator lights on F/E's panel, exceptengine and APU fire detector loops. TheMASTER WARNING and MASTERCAUTION lights on the Glareshield willcome on. The summary and cue lights onthe Overhead Panel will come on.

FLIGHT ENGINEER'S LOWER PANEL

HYD SYS 3 ELEV OFF light installed with SB 29-128.

HYD SYS 3 ELEV OFF light installed with SB 29-128.APU ANTI-ICE ON, 1-3/2-3 PUMP VALVE OPEN

lights not installed on some aircraft.JLJul 15/94 01-60-07

ADDITIONAL ANNUNCIATOR LIGHT INFORMATION

1. Pushing the ANNUN LT TEST Switch — WILL NOT turn on the following lights.

ENG FIRE Handles (3).YAW DAMP TEST Lights group.PA, ATTEND CALLING, MECH CALLING Lights.ENGINE FIRE — Glareshield Light.Flight Guidance Panel Lights.Flight Guidance Mode Annunciation Lights.Marker Beacon Lights.Slat Position Indicating Lights.Thrust Rating Computer Lights.EGT Caution Light (on each EGT Gage).GPWS Lights (Glareshield).BELOW G/S Lights (Glareshield).Radio Altimeter DH Lights.Fuel Lever Lights.

2. All Red Lights will turn on the Red MASTER WARN Lights (2) except the following:

Landing Gear Unsafe (Red Lights).ATS and Autopilots Lights.ENGINE FIRE Lights.GPWS Lights.

3. The following lights will turn on the MASTER CAUTION Lights (3).

FLIGHT ENGINEERHydraulic PRESS LO (6) Hydraulic TEMP HI (6).TANK PUMP PRESS LO (14).APU GEN OFF (1).CSD OIL PRESS LO (3).GEN OFF (3).AC BUS OFF (3).DC BUS OFF (3).USE ENG PNEU SUPPLY (1).RUD STBY PWR OFF (1).HYD SYS 3 ELEV OFF (1).

PILOTSSELECT FLAP LIMIT OVRD (1).SELECT ELEV FEEL MAN (1).UPPER YAW DAMP INOP (1).LOWER YAW DAMP INOP (1).ENG OIL PRESS LO (3).ENG OIL STRAINER CLOG (3).PITOT HEAT INOP (1).

All other amber lights will not turn on the MASTER CAUTION Lights.

01-60-08JL

Jun 1/98

McDonnell Douglas DC 10 40 Airplane General

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