(2)
F/O's Side:
5C8
34-26-0 Page 508 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jan 20/83
(a) Repeat step (1) using F/O's components and VG-2 instead of VG-1
F. Manual Glide Slope (MAN GS) Mode Test
(1)
Captain's Side:
(a)
For captain's instruments, place mode selector in HDG. Apply 2-dot fly-down and fly-right glide slope and localizer signals. Set mode selector to MAN GS position. Check that APD VOR/LOC and GS annunciations are green and that V-bars indicate pitch down and fly-right command.
(b)
Reduce glide slope deviation to zero. Wait 2 minutes. Tilt VG-1 in right roll until V-bars indicate zero roll command. Check that VG tilt is 15 ±3 degrees right roll.
(c)
Level VG-1. Set localizer deviation to zero. Set FLT DIR mode selector to AUTO APP. Apply glide slope signal to give 7-degree pitch up command.
(d)
Place mode selector in MAN GS position. Check that V-bar command reduces to 3 ±1 degrees in 120 ±12 seconds and that APD VOR/LOC and GS annunciations remain green.
(e)
Apply a glide slope signal to give 6 degrees pitch up command. Set marker beacon sensitivity to LOW. Press test switch on front of marker beacon receiver for greater than 3 seconds. Check that V-bar command reduces to 3 ±1 degrees in 7.5 ±2 seconds and that APD VOR/LOC and GS annunciations remain green.
(2)
F/O's Side:
(a) Repeat step (1) for F/O's components.
G. Go-Around Mode Test
(1)
Captain's Side:
(a)
Turn MODE SEL switch to MAN GS. Momentarily press thrust lever GO-AROUND switch. Check that APD GA annunciation is green, that mode selector rotates to GA position, and that V-bars indicated pitchup command.
(b)
Center V-bars by tilting VG-1 in pitch axis, and that tilt table reads 14 ±3 degrees pitchup. Level VG-1.
(c)
Set mode selector in AUTO APP position. Check that GA annunciator goes off and that VOR/LOC and GS annunciations are green. Momentarily press thrust lever GO-AROUND switch. Check that mode switch rotates to GA position that APD GA annunciation is green, and that V-bars indicate pitchup and wings level command.
(d)
Rotate heading marker and pitch command knob on mode selector. Check that V-bar does not respond and APD continues to indicate green GA only.
(e)
Tilt VG-1 20 degrees in right roll. Check that V-bar command indicates fly-left command and that APD GA annunciation remains green.
(f)
Level VG-1. Set heading cursor to angle 10 degrees greater than airplane heading. Switch mode selector rapidly to HDG position. Check that V-bar command indicates fly-right command and that APD GA annunciation remains green.
(2)
F/O's Side:
5C8
Jan 20/83 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-26-0 Page 509
(a) Repeat step (1) using F/O components and VG-2 instead of VG-1.
H. ALTERNATE VHF NAV
(1) Both sides:
(a)
Apply greater than 2-dot fly-left localizer signal and 2-dot fly-up glide slope signal. Set VHF NAV switch to BOTH ON 2. Open the VHF NAV-1 VOR/LOC and G/S circuit breakers. Check that both APD's VOR/LOC and GS annunciations are green and V-bars indicate pitch up and fly left command.
(b)
Close VHF NAV circuit breakers.
(c)
Turn the VHF NAV transfer switch to BOTH ON 1. Open VHF NAV-2 VOR/LOC and G/S circuit breakers. Check for same indication as in (a).
(d)
Close VHF NAV circuit breakers. Return VHF NAV transfer switch to normal.
6. Restore Airplane to Normal
A. Turn all systems off and remove test equipment.
B. Open attitude reference system circuit breakers and install vertical gyros.
C. Close attitude reference system circuit breakers and verify that the system indicates attitude of airplane.
D. Determine if there is further need for electrical power, if not, remove power.
5C8
34-26-0 Page 510 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jan 20/83
ATTITUDE DIRECTOR INDICATOR - REMOVAL/INSTALLATION
1. General
A. Two attitude director indicators (ADI, FDI, or HDI) are installed in the airplane. One is installed on the captain's instrument panel (P1) and one on the first officer's instrument panel (P3).
B. Each indicator is clamp mounted on the panel and is electrically connected to the flight director system thru multipin connectors on the back.
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 通訊描述和操作(126)
