(4)
Provide electrical power.
(5)
The air data system must have been energized for at least 30 minutes prior to this test.
504
34-17-02 Page 502 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/81
C. Test Altitude Alerting System
(1)
Open the following circuit breakers on panel P18:
(a)
ALT ALERT 26V AC
(b)
AIR DATA COMPUTER 115V AC
(c)
AIR DATA COMPUTER 26V AC
(d)
CAPT AUTO XFORMER 115V AC
(e)
CAPT ALTIMETER 26V AC
(f)
AURAL ALERT UNIT 28V DC
(2)
Check that altitude alert controller and captain's altimeter failure warning flags are in view.
(3)
Set the barometric scale setting on the captain's altimeter to 29.92 inches of mercury (or 1013 millibars).
(4)
Close the circuit breakers opened in step (1). Check that flags on altitude alert controller and captain's altimeter are not in view.
(5)
Open ALT ALERT circuit breaker. Check that altitude alert controller flag appears in view.
(6)
Close ALT ALERT circuit breaker. Check that altitude alert controller flag disappears from view.
(7)
Open CAPT ALTIMETER circuit breaker. Check that altitude alert controller and captain's altimeter flags appear in view.
(8)
Close CAPT ALTIMETER circuit breaker. Check that both flags disappear from view.
(9)
Open AIR DATA COMPUTER 115V AC and 26V AC circuit breakers. Check that altitude alert controller and captain's altimeter flags appear in view.
(10)
Close AIR DATA COMPUTER 115V AC and 26V AC circuit breakers. Check that both flags disappear from view.
(11)
Set altitude alert controller to 5000 feet.
(12)
Using the pitot static test set, gradually apply and release vacuum to approach the selected altitude from above. Check that the following occurs:
(a)
At 1000 .70 feet above, aural alerting unit sounds for 1 to 2 seconds and altitude alert indicators come on.
(b)
At 375 .70 feet above, altitude alert indicators go out.
(c)
At 375 .70 feet below, aural alerting unit sounds for 1 to 2 seconds and altitude alert indicators come on.
(d)
At 1000 .70 feet below, altitude alert indicators go out.
(13)
Using the pitot static test set, gradually apply and release vacuum to approach the selected altitude from below. Check that the following occurs:
(a)
At 1000 .70 feet below, aural alerting unit sounds for 1 to 2 seconds and altitude alert indicators come on.
(b)
At 375 .70 feet below, altitude alert indicators go out.
(c)
At 375 .70 feet above, aural alerting unit sounds for 1 to 2 seconds and altitude alert indicators come on.
(d)
At 1000 .70 feet above, altitude alert indicators go out.
(14)
Repeat steps (12) and (13) with altitude alert controller set at altitudes of 10,000, 20,000, and 35,000 feet respectively.
577
Sep 20/81 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-17-02 Page 503
D. Restore Air Data and Pitot Static System to Normal
(1)
Remove external hoses and static port seals ensuring that no deposit of roughness exists in or about static ports.
(2)
If no longer required, remove electrical power from airplane.
577
34-17-02 Page 504 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Sep 20/81
COMPASS SYSTEMS -DESCRIPTION AND OPERATION
EFFECTIVITY
GJ ALL EXCEPT B-2509 and B-2510
1. General
A. The compass system is designed primarily to furnish the captain and first officer with information concerning the airplane's magnetic heading at all times during flight. Heading information is displayed on the airplane's radio magnetic indicators (RMI's) and the horizontal situation indicators (HSI's). Heading information is also fed to the autopilot, flight recorder, navigation systems, and steering computers.
B. Two compass systems are installed. Each consists of the following components: remote compass transmitter (flux valve), directional gyro, horizontal situation indicator, radio magnetic indicator, servo-amplifier, slaving amplifier, and instrument amplifiers. The servo and slaving amplifiers are contained in the compass racks. A portion of the circuitry in the flight instrument accessory box is also utilized for the flag warning circuits. Location of the components is shown in Fig. 1.
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 通讯描述和操作(93)
