(4)
Turn the top and bottom SCC dials to show an indication of E at the index line.
(5)
Make a record of the heading shown on the standby magnetic compass.
(6)
Turn the top and bottom SCC dials to show an indication of W at the index line.
(7)
Make a record of the heading shown on the standby magnetic compass.
(8)
Turn the E-W adjustment screw on the standby magnetic compass until the error in the last two recorded values is at a minimum.
NOTE: Divide the error in each of the two directions as equally as possible.
(9)
Turn the top and bottom SCC dials to show an indication of N at the index line.
(10)
Make a record of the heading shown on the standby magnetic compass.
(11)
Turn the top and bottom SCC dials to show an indication of S at the index line.
(12)
Make a record of the heading shown on the standby magnetic compass.
(13)
Turn the N-S adjustment screw on the standby magnetic compass until the error in the last two recorded values is at a minimum.
NOTE: Divide the error in each of the two directions as equally as possible.
(14)
Continue to adjust the SCC dials for each pair of directions (E-W, N-S). Then turn the E-W and N-S adjustment screws until the errors are at a minimum.
NOTE: Continue to do this procedure until the error in each pair of directions is at a minimum. Start with E-W and turn the E-W adjustment screw. Then do N-S and turn the N-S adjustment screw.
When the errors are at a minimum, do the steps that follow for the 12-point accuracy swing.
(15)
Adjust the SCC dials to indicate these magnetic headings:, 0, 30, 60, 90, 120, 150, 180, 210, 240, 270, 300, and 330 degrees.
(16)
Make a record of the magnetic heading (MH) and standby compass heading (CH).
(17)
Calculate and make a record of the difference for each 30 degree heading in the steer column on the compass correction card as follows:
D = MH - CH
(18)
During these steps, make sure each difference Is less than + 8 degrees. Make sure the difference between the maximum positive and maximum negative value is 10 degrees or less.
(19)
CAA CERTIFICATION: During these steps, make sure each difference is less than + 5 degrees. Make sure the difference between the maximum positive and maximum negative value is 10 degrees or less.
(20)
Put the SCC dials back to the N-N position.
500
34-24-11 Page 204 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 01/95
NOTE: Do this step to keep the magnetic strength-high.
F. Put the airplane back to its usual condition.
(1) Remove the electrical power if it is not necessary
(AMM 24-22-00/201).
500
Aug 01/95 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-24-11 Page 205
MAGNETIC STANDBY COMPASS - REMOVAL/INSTALLATION
1. Remove Magnetic Compass
A. Support compass and remove four brass screws and nuts holding compass to mount. (See figure 401.)
B. Remove compass.
2. Install Magnetic Compass
A. Insert compass in cutout in support. (See figure 401.)
B. Install brass mounting screws and nuts.
CAUTION: DO NOT USE STEEL SCREWS TO ATTACH COMPASS TO MOUNT.
C. Perform compass swing of magnetic standby compass. (Refer to 34-21-0, Compass System Maintenance Practices or 34-24-11, Magnetic Standby Compass Maintenance Practices.))
502
May 01/99 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-24-11 Page 401
H24452
Magnetic Standby Compass Installation 500
34-24-11 Figure 401 Nov 15/72
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
STANDBY ARTIFICIAL HORIZON SYSTEM - DESCRIPTION AND OPERATION
EFFECTIVITY
GJ ALL EXCEPT B-2509, B-2510 and B2524
1. General
A. The standby artificial horizon indicator is fitted to the airplane as a backup system for the attitude reference system. It functions as a completely independent system which provides its own visual indication of airplane attitude in pitch and roll at all times during flight.
B. The system consists of the standby artificial horizon indicator located on the P2 center instrument panel and a standby attitude phase converter located in the lower nose compartment at STA 208, WL 175, RBL 20.
C. The power supply for the system is provided from the STDBY HORIZ circuit breaker, situated on the P18 load control center.
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 导航 NAVIGATION 1(86)
