(a)  
AUTOTHROTTLE - AC (C720)

(b)  
AUTOTHROTTLE - DC (C721)

(c)  
SYSTEM A - AUTOPILOT/FLT DIR - AC (C370)

(d)  
SYSTEM A - AUTOPILOT/FLT DIR - DC (C365)

(e)  
SYSTEM A - WARN LIGHT (BTRY) (C728)

(f)  
SYSTEM A - ENGAGE INTERLOCK (C373)

(g)  
AIL FORCE LIMITER (C723)

(h)  
AUTOPILOT/FLT DIRECTOR B - AC (C371)

(i)  
AUTOPILOT/FLT DIRECTOR B - DC (C367)

(j)  
AUTOPILOT/FLT DIRECTOR B - BAT (C374)

(k)  
AUTOPILOT/FLT DIRECTOR B - ENGAGE INTLK B (C716)

(l)  
No. 1 NAV-HSI CRS/HDG (C759), when installed.

(2)  
Remove the AFCS Mode Control Panel from the lightshield. Disconnect wire from pin 7 of connector D301 and tape and stow the wire. (Reference wire diagram 22-31-52).

(3)  
Reinstall the AFCS Mode Control Panel.

(4)  
Close the circuit breakers listed in step (1) above.

(5)  
Verify that the autothrottle will not engage as follows:

(a)  
Set up the PDC for the A/T BITE test. Assure that the A/T disengage lights are on steady. (Refer to the A/T BITE test procedure [Ref. 22-31-01, trouble shooting], if necessary, to establish proper conditions for the A/T BITE test.)

(b)  
On the AFCS Mode control panel, lift the A/T ARM (engage) switch several times and verify that the switch will not hold in the ARM position while the A/T disengage lights remain on steady.

Apr 01/97 22-31-01 Page 201
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

(6)  
Check the AFCS MCP Interface by performing the MCP Interface portion of the AFCS BITE Test. (Test NO. 23 for "A" Channel and test No. 73 for "B" Channel [Ref. 22-11-01, trouble shooting ]).

NOTE:  While the autothrottle is de-activated the autothrottle BITE test cannot be operated.

(7)  
Place INOP placard under the A/T ARM (engage) switch located on the AFCS Mode control panel.

C.  Reactivation Procedure
(1)  
Open all circuit breakers listed in step B.(1).

(2)  
Remove the AFCS Mode control panel from the lightshield.  Connect the previously stowed wire into pin 7 of connector d301. (Reference wire diagram 22-31-52).

(3)  
Reinstall the AFCS Mode control panel.

(4)  
Close the circuit breakers listed in step B.(1).

(5)  
Check the autothrottle system operation by performing the A/T BITE test per 22-31-01, Trouble Shooting.

(6)  
Check the AFCS MCP Interface by performing the MCP Interface portion of the AFCS BITE Test. (Test No. 23 for "A" Channel and test No. 73 for "B" Channel [Ref. 22-11-01, trouble shooting])

(7)  
Check the AFCS A/T Interface by performing the A/T Interface portion of the AFCS BITE test. (Test No. 6 for "A" Channel and test No. 56 for "B" Channel [Ref. 22-11-01, trouble shooting]).

(8)  
Remove the INOP Placard from the A/T ARM (engage) switch.

512 
22-31-01 Page 202  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/83 

AUTOTHROTTLE SYSTEM - ADJUSTMENT/TEST
EFFECTIVITY
SA ZS-SIA and on SD ST-AIB and on WA N235WA thru N241WA GJ B-2509 and B-2510
1.  General
A.  The autothrottle system test assumes that all components are properly installed and wired. It checks operation of the autothrottle system through all signal channels. All systems furnishing signal data and power to the autothrottle system must be in proper working order and operating and the system properly rigged before conducting these tests.
B.  Perform the steps in each paragraph in the order written.
C.  Disregard A/T and A/P-F/D system annunciation status unless applicable to the test in progress.
D.  Ensure that the A/T computer is powered for at least 5 minutes before beginning autothrottle test (par. 4.).
E.  Unless otherwise specified, the A/P systems must be disengaged and the F/D switches on the P7 lightshield panel must be in the ON (toggle up) position.
F.  Momentary hesitation during rotation of electromechanical annunciators on the flight mode annunciator (FMA) panels is normal. Hesitation should not be more than 1 second.
G.  When engaging the autothrottle system, make sure the thrust levers are positioned within approximately 8 degrees of each other. The autothrottle will disengage and the A/T ARM switch will go to OFF whenever the thrust lever positions disagree by more than approximately 10 degrees.
　
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(90)