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A 737-300/400/500MAINTENANCE MANUAL
A/T MODE N1 GA RETARD FMC SPD MCP SPD THR HLD ARM
AUTOFLIGHT STATUS ANNUNCIATOR
Autothrottle System Component Location
Figure 1 (Sheet 3)
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A 737-300/400/500MAINTENANCE MANUAL
ANGLE OF AIRFLOW SENSOR LEFT FLAP(LEFT SIDE OF FUSELAGE)
POSITION SEE J SENSOR
SEE K
POWER LEVER ANGLE SYNCHROS
THRUST (LEFT SIDE OF ENGINES)CONTROL CABLE
MEC FUEL CONTROL BOX
POWER LEVER ANGLE SYNCHRO TRANSMITTERFLAP POSITIONMOUNTING BOLT
TRANSMITTER SYNCHRO
(4 PLACES) XMTR
AIRFLOW
SENSOR
VANE
FUSELAGE
SKIN
INDEX PINS
ELECTRICAL FWD INBD
FWD PLUG
ANGLE OF AIRFLOW SENSOR LEFT FLAP POSITION SENSOR
J K
Autothrottle System Component Location
Figure 1 (Sheet 4)
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A 737-300/400/500MAINTENANCE MANUAL
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A 737-300/400/500MAINTENANCE MANUAL
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G.
H.
I.
J.
A
737-300/400/500MAINTENANCE MANUAL
(4)
AIRPLANES WITH EFIS; The Autoflight Status Annunciators are located on captain's panel (P1) and first officer's panel (P3). The Thrust Mode Annunciator or A/T limit annunciator is located on the center instrument panel (P2).
(5)
The A/T circuit breakers are located on the P18-1 circuit breaker panel.
(6)
The angle of airflow (alpha) sensor is located on the forward left side of the fuselage.
(7)
The A/T computer is located on the E1 rack, shelf 1, in the electronics equipment area.
(8)
The A/T servo actuators are located in the overhead of the electronics equipment area at station 370.
(9)
The Power Lever Angle sensors are located on the left side of each
engine.The Autothrottle engage switch (A/T ARM-OFF) is mounted on the DFCS mode control panel, which is located on the pilot's light shield. Several other controls used with (or indirectly associated with) the Autothrottle system are also grouped together on the panel. These include: IAS/MACH readout, N1 mode select, SPEED mode select, and C/O (IAS/MACH changeover switch). The IAS/MACH speed control is not directly linked with the Autothrottle system but IAS and MACH select signals generated in the DFCS play a part in Autothrottle computations. The C/O (changeover) control is directly associated with the IAS/MACH display.The FMCS provides flight guidance data to the Autothrottle system in the form of optimum airspeed and thrust settings to achieve the most efficient and economical mode of operation for the airplane. Controls for this system are mounted on the CDU, which is located on the forward electronic panel. The CDU is used extensively by the Autothrottle system to display self-test (BITE) information, including test pass/fail results.Various Autothrottle interlocks must be satisfied before the A/T ARM-OFF switch will latch in the engaged position. The Autothrottle system will disengage with the loss of internal valid signal, loss of interfacing system valid, operation of either disengage switch on the forward thrust levers, or operation of the A/T ARM-OFF switch to OFF. A disengage warning light is located on the captain's and first officer's Flight Mode Annunciators (airplanes without EFIS) or on the Autoflight Status Annunciators (airplanes with EFIS).A number of externally generated signals are used for system computation and control (Fig. 2). These signals, together with signal sources, are given in the following list: 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：737-300 400 500 AMM 飞机维护手册 自动飞行 AUTOFLIGHT 2(133)
