(3)
Position trailing edge flaps to full up position.
(4)
Place A/P ENGAGE A switch to CMD and select HDG SEL mode. Rotate HDG SEL knob to provide 45 degrees preset heading error (either direction). Verify that control wheels rotate and stop between 15 and 19 degrees.
(5)
Lower trailing edge flaps to 1 unit. Verify that control wheels rotate and stop between 23 and 27 degrees.
(6)
Return preset heading error to center. Disengage autopilot.
D. Remove hydraulic power, restore airplane to normal. Remove electrical power if no longer required.
505
Jun 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 22-21-31 Page 505
AUTOTHROTTLE SYSTEM - DESCRIPTION AND OPERATION
EFFECTIVITY
GJ ALL EXCEPT B-2509 and B-2510
1. General
A. Partial provisions are made for an autothrottle system installation. These provisions consist of mountings for two autothrottle clutch assemblies located in the aft ceiling of the electrical and electronics compartment.
5C9
Jun 20/85 22-31-0 Page 1
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
AUTOTHROTTLE SYSTEM - DESCRIPTION AND OPERATION
EFFECTIVITY
WA N235WA thru N241WA GJ B-2509 and B-2510
1. General (Fig 1 and 2)
A. The autothrottle (A/T) system provides automatic speed and thrust control (within engine design parameters) for all phases of flight. The autothrottle is designed to operate primarily with the automatic flight control system (AFCS) and the performance data computer system (PDCS). It also interfaces with several other systems and components.
B. The autothrottle provides individual operation of each engine thrust control system through the autothrottle servomechanisms. The autothrottle outputs are used to achieve and maintain a desired engine pressure ratio (EPR), airspeed, or mach number. In addition to engine thrust control, the A/T computer also provides a computed fast/slow command signal to the ADI's and pitch command signals to the flight director system for controlling speed during climb or descent.
C. The autothrottle system consists of a digital computer, two autothrottle servomechanisms, a longitudinal accelerometer, two engine thrust levers, two engine throttle position transmitters [linear velocity displacement transducers (LVDT)], two A/T annunciator displays on the AFCS flight mode annunciators (FMA), and two A/T warning lights (also located on the FMA). System units and components are shown in Fig. 1, together with those units from other systems which play a vital role in autothrottle system operation.
D. The autothrottle servomechanisms are located on the ceiling (between floor beams) at the aft end of the electronic equipment compartment (Fig. 1). During autothrottle engagement, the autothrottle servomechanism drives the thrust control cables; thus, adjusting the position of the associated thrust lever and also the throttle mechanism on the engine fuel control unit. The pilot can manually override autothrottle thrust lever positioning by applying a small amount of pressure directly to the thrust lever. When this takes place, the autothrottle servomechanism slips and the thrust control cables are driven directly from the thrust lever. Servo operation is controlled from the autothrottle computer.
Oct 20/85 22-31-01 Page 1
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
H79593 H89155 H20245
Autothrottle System Component Location 5B8
22-31-01 Figure 1 (Sheet 1) Feb 20/84
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
553 Auto Throttle System Component Location
Oct 20/85 Figure 1 (Sheet 2) 22-31-01
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Autothrottle System Component Location 580
22-31-01 Figure 1 (Sheet 3) Feb 20/84
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
K82507
Autothrottle Simplified Interface SchematicOct 20/85 Figure 2 22-31-01 Page 5/6BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
E. The autothrottle engage switch (A/T ARM-OFF) is mounted on the AFCS 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, EPR mode select, SPEED mode select, LVL CHG (level change) mode select, C/O (IAS/MACH changeover switch), and PDC ON. The IAS/MACH speed control is not directly linked with the autothrottle system; but IAS and MACH select signals generated in the AFCS play a part in autothrottle computations. The C/O (changeover) control is directly associated with the IAS/MACH display. 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：737 AMM 飛機維護手冊 AUTO FLIGHT 自動飛行 2(80)
