CHAPTER 1 AIRPLANE GENERAL Page TABLE OF CONTENTS 01-00-01 INTRODUCTION 01-10 ...

68 Pages·2009·6.37 MB·English

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
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Feb 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
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01-00-02 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
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AIRCRAFT GENERAL
INTRODUCTION primary box also carries the main
landing gear supporting structure,
engine pylons, full span leading
The sweptwing DC-10 Series 40 air- edge slats, spoilers, and trailing
craft is a long range tri-jet edge ailerons and flaps. Rupture-
designed for the transportation of resistant fuel tanks and lines are
passengers and cargo. Three inter-
provided in case of landing gear
changeable Pratt & Whitney JT9D, and/or flap breakaway.
high-bypass ratio turbofan engines
are used for propulsion.
Tail
The tail is of metal construction and
DESIGN FEATURES includes an adjustable horizontal
stabilizer, right and left two-
section elevators, a tail-engine
GENERAL
pylon, a fixed vertical stabilizer,
and a two-section (four-segment)
Fuselage rudder. The adjustable horizontal
stabilizer is pivoted at the trailing
The wide-bodied fuselage is of semi-
edge and uses hydraulic powered
monocoque metal construction. All motors to change the angle-of-
areas are pressurized except the
incidence.
nose radome, wheelwells, wing center
section, and aft fuselage. The fuse- SYSTEMS
lage is divided lengthwise into an
upper-floor level and a lower-floor Air Conditioning and Pressurization
level. The galley and lavatory
compartments are located on the The air conditioning and pressuri-
upper-floor level. The cargo and zation systems provide heating,
accessory compartments are located on cooling, dehumidification, and pres-
the lower-floor level. Two main surization for the cockpit, passenger
aisles are provided on the upper cabin, galley, cabin cargo compart-
floor. Eight passenger entrance/exit ments, and avionics compartment.
doors are installed. Temperature control is automatic or
manual. Pressurization control has
Cabin windows are double pane con- automatic, semi-automatic, standby,
struction. Either pane is capable and manual modes of operation. The
of carrying full pressurization. air conditioning system is capable of
maintaining a comfortable environment,
Wing while on the ground, using only the
onboard auxiliary power unit.
The cantilevered wing consists of a
primary box structure with a leading Automatic Flight
and trailing edge secondary struc-
ture. The box is of two-spar con- The automatic flight capability
struction containing integral, includes automatic control (full
between-spar fuel tanks. This or partial) of the aircraft during
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Nov 1/82 01-10-01
takeoff, climb, cruise, descent, and Emergency Equipment
landing. The system is designed for
Emergency equipment is provided for
all-weather operation with a CAT
the flight crew and passengers. It
III landing capability. The total
includes emergency and first aid
system includes a flight director,
oxygen, portable fire extinguishers,
an autothrottle/speed control system,
emergency lighting, first aid kits,
and an autopilot.
evacuation slides, a crash axe, and
flotation gear. Portable megaphones,
and crash locator radio (beacon)
Auxiliary Power Unit transmitters also are provided.
The onboard gas-turbine powered APU Fire Protection
is a self-contained source of pneuma-
The fire protection system provides
tic and electrical power on the
detection, visual/aural warning, and
ground, and electrical power in
extinguishing capability for each
flight. The unit may be started or
engine nacelle area and for the
shut down from the cockpit, and
auxiliary power unit compartment.
normally is completely automatic in
Visual overheat indication is also
operation. The unit may be shut down
provided for the avionics compartment.
from the ground panel.
Visual smoke and fire detection and
extinguishing capabilities are pro-
vided for the cargo compartment.
Communication
Flight Controls
The aircraft is equipped with air-to -
ground and air-to-air voice cotimuni- Primary flight controls consist of
cation systems. Cockpit/cabin, inboard and outboard ailerons; two
ground service interphone, passenger two-section elevators; and a two-
address, and voice recorder systems section (four segment) rudder.
also are provided. Cabin attendant, Secondary flight controls consist of
pilot, mechanic, and passenger call lift-augmenting leading edge slats,
systems are installed in the aircraft. spoilers (lateral control/speed
A separate passenger entertainment brake/ground spoilers), inboard and
system also is provided. outboard flaps, and a dual-rate
movable horizontal stabilizer. The
flight control system is a fully
Electrical powered system utilizing power from
three independent hydraulic systems.
The electrical system is normally
powered by an ac generator mounted on Flight Instruments
each engine. It may also be powered
by an external ac source or by the The flight instruments and associated
onboard auxiliary power unit. Por- components provide altitude, airspeed,
tions of the system may be powered overspeed, attitude, and temperature
by the aircraft battery and/or an data plus flight data recording.
air driven generator. DC power is Included are the pitot-static system,
normally provided through transformer/ the central air data computers, the
rectifiers, but may also be provided altitude, airspeed, and vertical
by a battery. Protective circuitry speed indicators, the gyrosyn compass
with automatic corrective action is system and the RMI/HSI indicators,
standard equipment. and the attitude director indicators.
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01-10-02 Nov 1/82
Fuel System conventional. All systems are hydrauli-
cally powered. A manual, free-fall
Fuel is carried in three integral wing alternate gear extension capability is
tanks and in the auxiliary tank. Direct provided.
tank-to-engine feed is normally used.
The system also has the capability of Navigation Systems
tank-to-tank transfer, fuel dumping, and
any-tank to any-engine crossfeed. In The navigation equipment includes the
normal operation, each engine receives VOR/ILS, ADF, DME, radio altitude,
fuel from its respective main tank. The and marker beacon systems; the weather
auxiliary power unit normally receives radar, the clock, and (as desired)
fuel from tank number two. Fueling, INS equipment.
defueling, manifold drain, and fuel tank
venting are provided. The system per-
mits one-man, single-point refueling
Pneumatics
and is spillproof and siphonproof.
The pneumatic system distributes and
Hydraulic Power
controls pneumatic pressure for air con-
ditioning, pressurization, anti-icing,
Three continuously pressurized hydraulic
heating, ventilation, water pressuriza-
systems are provided, each powered by
tion, and engine starting. Pneumatic
two engine-driven pumps with intersys-
pressure is supplied from either an
tems motor pump backup. Two electric
external source, the APU, or the
auxiliary pumps are installed in system
engines.
three. Emergency hydraulic power is
available from an electric auxiliary pump
powered by an air driven generator. Power Plant
Ice and Rain Protection The aircraft is powered by three Pratt &
Whitney JT9D dual-rotor, high bypass
The ice and rain protection systems pro- ratio turbofan engines. The engines
vide all-weather flight capability. Ther- incorporate a front fan and booster stage
mal heating is provided for anti-icing the comprising the low pressure compress-
outboard wing slats, VHF-1 antenna, and or section, a high pressure compressor
for the nose cowl inlet area of each with variable pitch stators, annular com-
engine. Electric heaters provide anti- bustors, and high and low pressure
icing for pitot tubes, static ports, angle- turbines.
of-attack vane, total air temperature
probe, and exterior windshields. Elec-
Water and Waste Systems
tric heaters also are used for defogging
the windshields and clearview windows.
Rain protection is provided for the Separate systems are provided for pot-
windshields by electric wipers and a able water and waste service. The pot-
chemical rain repellent system. able water system includes provisions
for filling, storage, quantity indication,
Landing Gear temperature control, distribution, and
overboard drainage. The waste system
The landing gear, nosewheel steering, includes provisions for storage, priming,
brakes, and antiskid systems are basically rinsing, flushing, and drainage.
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May 1/76 01-10-03
AIRPLANE DIMENSIONS
50.4m
(165 FT 4 IN.)
4.5m 7.4m
(14 FT 9 IN.) (24 FT 5 IN.)
NOTE
DIMENSIONS ARE APPROXI-
10.7m MATE, DEPENDING ON GROSS
0.9m (35 FT) WEIGHT AND STRUT/TIRE IN-
(3 FT) FLATION.
6.0m
(19 FT 9 IN.)
21.7m
(71 FT 2 IN.)
8.4m
(27 FT
7 IN.)
55.3 m
(181 FT 7 IN.)
, 17.7m
(58 FT 1 IN.)
8.6 m
(28 FT
4.8m
1 IN.)
(16 FT)
8.5 m 22.1 m .
(27 FT 11 IN.) (72 FT 5 IN.) 52m
(170 FT 6 IN.)
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01-10-04
Feb 1/79
TURNING RADIUS (minimum)
DC-10-30/40
EFFECTIVE
1TURN ANGLE
MAXIMUM
STEERING
ANGLE 68.0° TIRE
SUP
TURN
ANGLE
CENTER
PAVEMENT WIDTH
FOR 180° TURN
NOSE GEAR RADII TRACK
MEASURED FROM OUTSIDE FACE
OF TIRE.
MINIMUM RADIUS TURN MAXIMUM STEERING •MAXIMUM STEERING
RECOMMENDED FOR NORMAL,
SYMMETRICAL THRUST AND NO ASYMETRICAL THRUST AND
ROUTINE OPERATIONS.
DIFFERENTIAL BRAKING LIGHT INTERMITTENT
TIGHTER TURNS CAN BE MADE DIFFERENTIAL BRAKING
SLOW CONTINUOUS TURN
OCCASIONALLY USING A
SLOW CONTINUOUS TURN
COMBINATION OF MAXIMUM AFT CENTER OF GRAVITY
STEERING, ASYMETRICAL THRUST AFT CENTER OF GRAVITY
MAX GROSS WEIGHT
AND LIGHT INTERMITTENT
MAX GROSS WEIGHT
BRAKING.
TYPE OF EFFECTIVE TIRE SLIP X Y W R1 R2 R3 R4
TURN TURN ANGLE ANGLE
42.7 FT 72.9 FT 149.5 FT 85.2 FT 130.5 FT 109.6 FT 109.8 FT
62.9° 5.1° 37.2 FT 72.9 FT 141.4 FT 83.5 FT 125.3 FT 107.5 FT 105.9 FT
66.9° 1.1° 27.6 FT 72.9 FT 128.5 FT 79.8 FT 116.1 FT 104.7 FT 99.5 FT
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MISCELLANEOUS EXTERNAL ITEMS
WINDSHIELD
WIPERS WING SCAN
LANDING LIGHT
LIGHT
LEFT ANGLE OF
ATTACK SENSOR
OXYGEN
BLOWOUT NOSE RUNWAY TURNOFF
DISK LANDING LIGHT
LIGHT
PITOT TUBES PACK INLET AND
EXIT DOORS
ANGLE OF ATTACK
STATIC PORTS
WING SCAN SENSOR
LIGHT
RADOME
CABIN PRESSURE
LANDING
RELIEF VALVES
LIGHT
NOSE TAT
PROBE
LANDING
RUNWAY TURNOFF
LIGHT
LIGHT
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