3. Flight Director System Trouble Shooting Chart
T53774
563
34-26-0 Page 102 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/79
3. Flight Director System Trouble Shooting Chart (Cont.)
T53781
563
Feb 15/79 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-26-0 Page 103
3. Flight Director System Trouble Shooting Chart (Cont.)
T53786
563
34-26-0 Page 104 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/79
3. Flight Director System Trouble Shooting Chart (Cont.)
T53788
511
Feb 15/79 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-26-0 Page 105
3. Flight Director System Trouble Shooting Chart (Cont.)
T53792
503 34-26-0 Feb 15/79 Page 106
3. Flight Director System Trouble Shooting Chart (Cont.)
T53798
503
Feb 15/79 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-26-0 Page 107
FLIGHT DIRECTOR SYSTEM -ADJUSTMENT/TEST
EFFECTIVITY
Airplanes with Collins FD-110 Flight Director System
1. General
A. The following procedures are provided for testing the flight director systems. For these procedures, the airplane compass, vertical gyro, VOR/ILS, low range radio altimeter (LRRA), air data and marker beacon systems must be operational. The use of test equipment listed in par. 2 is also required. Test preparation procedures are contained in par. 3.
2. Equipment and Materials
A. Signal Generator - Instrument Flight Research Corp. NAV-401L or Collins 972Q-4.
B. Calibrated tilt table (2 required)
C. Radio Altimeter Test Set - Bendix Radio Corp., Model AMT-51A
D. Stop watch
E. Air pressure and vacuum source (Ref 34-11-0, Adjustment/Test)
3. Prepare to Test Flight Director System
A. Remove each vertical gyro and attach to a calibrated tilt table.
CAUTION: BEFORE REMOVING OR INSTALLING A VG, ENSURE POWER IS OFF. IF VG HAS BEEN OPERATING, OPEN VG CB'S ON P6 AND P18 PANELS AND ALLOW APPROXIMATELY 3 MINUTES FOR GYROS TO COAST DOWN. IF UNIT IS REMOVED TOO SOON, GYROSCOPIC PRECESSION COULD RESULT IN DAMAGE TO GYRO.
B. Apply external power and check that the following circuit breakers on P6 and P18 are closed: No. 1 INSTRUMENTS (VERT GYRO -1; INSTR TRANS; COMPASS -1; INSTR XFMR -1; ADI; ADI ALT; RMI ALT; FLT DIR -1 AC, DC, ALT AC); No. 1 AIR DATA (AUTO XFMR; COMPUTER-1 AC, 26 VAC); No. 1 NAVIGATION (VHF NAV -1 VOR/LOC, GS; MARKER BEACON); No. 2 INSTRUMENTS (VERT GYRO -2; COMPASS -2; INST XFMR -2; ADI, ADI ALT; RMI ALT; FLT DIR -2 AC, DC, ALT AC); No. 2 NAVIGATION (VHF NAV -2 VOR/LOC, G/S); and AUTOPILOT (WARN LT BAT; ENGAGE INTLK).
C. Synchronize compass system and allow few minutes for gyros to stabilize.
D. Position NAV transfer switches to RADIO. Check HSI nav system annunciators indicate VOR-ILS and that HSI heading bugs are not stowed.
E. Place VERTICAL GYRO, VHF NAV and COMPASS transfer switches to NORMAL.
F. Set HSI course arrows and heading markers to airplane heading.
NOTE: Both heading markers are controlled by HEADING knob on FLT DIR mode selector panel. Capt's course arrow is controlled by left COURSE knob and F/O's course arrow is controlled by right COURSE Knob.
G. Set STANDBY POWER switch on overhead panel to AUTO.
H. Tune both VOR/ILS systems to localizer frequency selected at signal generator. Apply zero deviation localizer and glide slope signals.
5C8
Feb 20/86 34-26-0 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
I. Set PITCH CMD knobs on FLT DIR mode selector to ZERO.
J. Place LIGHTS TEST-BRT-DIM switch on center instrument panel to BRT.
K. Open RADIO ALTM-1 circuit breaker on P18 circuit breaker panel.
L. Set FLT DIR mode selector to HDG. Check following on each ADI: V-bars in view; CMPTR flag, SPEED flag, and FAST/SLOW pointer out of view.
4. Test Flight Director System
A. Warning Flag and V-bar Tests
(1) Check for CMPTR flag(s) in view and V-bar(s) out of view as tabulated below. Check that each side operates independently of other side.
NOTES: 1. Return circuit breakers to initial conditions after each step.
2. The computer flags shall be out of view unless checked for in view. The V-bars shall be in view unless checked for out of view.
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 導航 NAVIGATION 1(97)
