AFCS MODE CONTROL PANEL - REMOVAL/INSTALLATION
EFFECTIVITY
SA ZS-SIA and on SD ST-AIB and on WA N235WA-N241WA GJ B-2509 and B-2510
1. General
A. The AFCS mode control panel is installed on the glare shield above center instrument panel P2 with screws on the front and bottom of the panel. Three receptacles mate with airplane wiring connectors.
2. Remove Panel
A. Open all autopilot, yaw damper and auto throttle circuit breakers on P6 and P18 load control centers.
B. Open all compass, VOR/ILS, attitude, LRRA, air data computer, area navigation (if applicable) and performance data computer circuit breakers on P6 and P18 load control centers (Ref Chapter 34).
C. Remove 2 screws and light assembly on bottom of control panel.
D. Remove four front panel mounting screws and carefully pull out panel to expose connectors on rear.
E. Disconnect connectors and remove panel.
3. Install Panel
A. Attach connectors to rear of panel and slide into position.
B. Install light assembly and all mounting screws.
C. Close all autopilot, yaw damper and auto throttle circuit breakers on P6 and P18 load control centers.
D. Close all compass, VOR/ILS, attitude, LRRA, air data computer, area navigation (if applicable) and performance data computer circuit breakers on P6 and P18 load control centers.
4. Test Panel
A. General
(1)
An installation test of the AFCS mode control panel is provided by BITE.
(2)
Prepare AFCS for BITE by providing electrical power to autopilot, PDC, attitude reference, compass, VHF NAV, LRRA, air data, auto throttle and flight instruments.
B. Perform Mode Control Panel BITE Test
(1)
Select PDC CDU to autopilot BITE by selecting STBY, pressing RCL, (-) then selecting page 5 (autopilot BITE).
(2)
Select NO (ENT) to SYMPTOM/PIREP and GROUND FUNCT to enter VERIFICATION mode (YES), step system thru LRU component list to obtain MCP INTERFACE test No. (23). Select desired channel to be tested.
(3)
Perform BITE INITIALIZE steps and required actions as requested on CDU and perform BITE.
(4)
Follow instructions to provide system diagnostic routine if a BITE fails. Replace indicated component and recycle system thru BITE until system passes.
(5)
Remove hydraulic and electrical power if no longer required.
Feb 20/85 22-11-341 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
AFCS ANNUNCIATOR - REMOVAL/INSTALLATION
EFFECTIVITY
SA ZS-SIA and on GJ B-2509 and B-2510
1. General
A. An AFCS annunciator is installed on the P1 and P3 panels with screws. Two receptacles on the rear of the annunciator mate with airplane wiring connectors.
2. Remove Annunciator
A. Open all autopilot, auto throttle and performance data computer circuit breakers on P6 and P18 load control centers.
B. Remove screws and carefully pull annunciator to expose connectors on rear.
C. Disconnect connectors and remove annunciator.
3. Install Annunciator
A. Attach connectors to rear of annunciator and slide into position.
B. Install screws.
C. Close all autopilot, auto throttle and performance data computer circuit breakers.
4. Test Annunciator
A. Provide electrical power.
B. Hold annunciator test switch to 1. Observe F/D and A/P - L NAV, VOR LOC, GS, FLARE, V NAV, ALT ACQ, V/S, PDC SPD; A/P STATUS - CWS ROLL, CWS PITCH; A/T - ARM, SPEED, THR HOLD; PDC - CON, HOLD, DES, and GA are annunciated. Observe A/P and A/T amber warning lights illuminate. Release switch.
C. Hold annunciator test switch to 2. Observe F/D and A/P - HDG SEL, VOR LOC, GS, FLARE, SPEED, ALT HOLD, V/S, TO/GA; A/P STATUS - SINGLE CH, A/P OFF; A/T - PDC SPD, EPR (or N1), RETARD; PDC - TURB, CRZ, CLB, and TO are annunciated. Observe A/P and A/T red warning lights illuminate. Release switch.
D. Remove electrical power if no longer required.
Oct 20/89 22-11-351 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
AFCS ACCESSORY BOX - REMOVAL/INSTALLATION
EFFECTIVITY
SA ZS-SIA and on GJ B-2509 and B-2510
1. General
A. The accessory box is retained in the electronic rack with a cam-action lever which hooks over a fork on the shelf.
2. Remove Accessory Box
A. Open all autopilot and yaw damper circuit breakers on P6 and P18 load control centers.
B. Release accessory box by pressing trigger then pulling ejection lever.
C. Remove accessory box.
3. Install Accessory Box
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(37)
