5C9 AP/FD BITE Test Group DiagramFeb 20/93 Figure 18 (Sheet 1) 22-11-01 Page 71/72BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
5C9 AP/FD BITE Test Group DiagramFeb 20/93 Figure 18 (Sheet 2) 22-11-01 Page 73/74BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
5C9 AP/FD BITE Test Group DiagramJun 20/83 Figure 18 (Sheet 3) 22-11-01 Page 75/76BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
AUTOPILOT/FLIGHT DIRECTOR SYSTEM - TROUBLE SHOOTING
EFFECTIVITY
WA N235WA thru N259WA SA ZS-SIA and on GJ B-2509 and B-2510
1. General
A. The SP177 AP/FD system contains a sophisticated BITE system which not only determines if the system has failed but also to determine which LRU is at fault.
B. BITE tests are a one man operation conducted from the control cabin. BITE is controlled from the Performance Data Computer (PDC) Control Display Unit (CDU) located on the aisle stand. The Flight Control Computer (FCC) will control the program flow during BITE testing and transmit messages to the CDU by way of the Mode Control Panel (MCP). The operator issues commands and enters results of observations by way of the CDU keyboard.
2. Prepare for Trouble Shooting
A. Verify that electrical power is applied to the airplane main buses and battery switch is
positioned to ON.
B. Close AP/FD system circuit breakers.
C. Close circuit breakers and energize interfacing systems: Attitude reference, Compass, Air Data Computer, PDC, VHF NAV, DME, LRRA and verify normal instrument display on associated flight instruments (Ref Chapter 34).
D. Verify that STAB OUT OF TRIM warning light illuminates when master LIGHTS test and dim switch on P2 panel is held in TEST position.
NOTE: For STAB OUT OF TRIM warning light removal/installation, refer to 33-11-82/201.
E. Tests which require flight control surfaces require hydraulic pressure and activation of applicable flight control surfaces.
WARNING: PRIOR TO APPLYING HYDRAULIC POWER TO FLIGHT CONTROLS, VERIFY THAT PERSONNEL AND EQUIPMENT ARE CLEAR. SUDDEN MOVEMENT OF FLIGHT CONTROL CAN CAUSE INJURY TO PERSONNEL OR DAMAGE TO AIRPLANE AND EQUIPMENT.
F. Prepare for BITE (Fig. 101)
(1)
Place PDC CDU mode switch in STBY position and press RCL, then (-) key, then press PAGE up key until page 5-X appears on CDU display.
NOTE: Airplane on ground (squat) logic is required to enable BITE.
(2)
Check that autopilot warning lights are illuminated red and cannot be extinguished.
(3)
Check that PDC CDU display indicates A/P TESTS, 5-X, SYMPTOM PIREP TEST DESIRED and requests operator response ENG (yes) or ENT (no). See Fig. 101 for desired test. Follow CDU instructions and respond to CDU questions to control test path.
Feb 20/87 22-11-01 Page 101
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
SP 177 AP/FD Bite Sequence Diagram 5C9
22-11-01 Figure 101 (Sheet 1) Jun 20/83
Page 102
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
553 SP 177 AP/FD Bite Sequence Diagram
Sep 20/82 Figure 101 (Sheet 2) 22-11-01
Page 103
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(4)
Selection of SYMPTOM/PIREP (ENG, yes response) allows selection of specific AFCS system; autopilot, flight director, auto throttle or altitude alert. Further selection of autopilot allows selection of specific modes or functions. The selection process determines a specific test group as listed on chart in par. 4.
(5)
A no (ENT) response to SYMPTOM/PIREP steps the display to GROUND FUNCTIONAL TEST DESIRED. A yes response to this test question directs the system to a complete test of all modes, interfaces and LRU's. Refer to system adjustment/test for this overall check. A no response to this test step the system to VERIFICATION which allows selection back to SYMPTOM/PIREP or LRU INTERFACES.
(6)
LRU INTERFACE permits selection to a specific LRU or selection of LAND VERIFY which permits further selection of MINI LAND or FULL LAND for checking the critical circuits used on automatic approaches. A no (ENT) response to LAND VERIFY selects RIGGING which tests elevator and aileron position sensors, neutral shift sensor, and elevator and aileron actuator LVDT's. At completion of test selection, the system is prepared to perform the selected group of tests.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 AUTO FLIGHT 自动飞行 1(78)
