34-13-00
ALL ú ú 03 Page 4 ú Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 FAULT ISOLATION/MAINT MANUAL
AIR DATA INSTRUMENTS
COMPONENT 102 SHT FIG. QTY ACCESS/AREA REFERENCE
CIRCUIT BREAKER -INDICATOR - STANDBY AIRSPEED, N246 STBY INSTR ALTM VIB, C416 ALTIMETER - STANDBY, N141 ------ 1 1 1 7B26 FLT COMPT P2-1 FLT COMPT P7 FLT COMPT P2-1 34-13-02 34-13-01 * *
* SEE WDM EQUIPMENT LIST
Air Data Instruments - Component Index
Figure 101
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
34-13-00
ALL ú ú 02 Page 101 ú Oct 10/88
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 FAULT ISOLATION/MAINT MANUAL
STANDBY AIRSPEED INDICATOR, N246 STANDBY ALTIMETER, N141
Air Data Standby Instruments - Component Location Figure 102
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
34-13-00
ALL ú ú 02 Page 102 ú Oct 10/89
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
AIR DATA STANDBY INSTRUMENTS - ADJUSTMENT/TEST
______________________________________________
1. General
_______
A. This subject has one task. The task is to do a calibration test and a leak test of the standby altimeter and standby airspeed indicator.
TASK 34-13-00-735-015
2. System Test - Air Data Standby Instruments
__________________________________________
A. References
(1)
24-22-00/201, Manual Control
(2)
34-11-00/201, Pitot-Static System
B. Prepare for Test
S 865-002
(1)
Supply electrical power (Ref 24-22-00/201).
S 865-003
(2)
Make sure this circuit breaker is closed:
(a) P7 Overhead Circuit Breaker Panel
1) 7B26 STBY INSTR ALTM VIB
S 755-021
(3) Feel the standby altimeter casing for vibration.
(a) Make sure the vibrator in the standby altimeter operates.
S 865-005
(4) Set the BARO scale of the standby altimeter to 29.92 inches of mercury (1013 millibars).
C. Instrument Calibration Test
S 865-024
CAUTION: YOU MUST DISCONNECT THE ELEVATOR FEEL COMPUTER FROM THE
_______ PITOT-STATIC SYSTEM. YOU CAN CAUSE DAMAGE TO THE ELEVATOR FEEL COMPUTER.
(1)
Disconnect the pitot and static systems from the elevator feel computer.
S 785-025
(2)
Apply pressures to the pitot-static system for each test point shown in Table 501 (Ref 34-11-00/201).
(a) Add the head correction factor to the standby altimeter indication.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
34-13-00
ALL ú ú 01 Page 501 ú Oct 10/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
(b) Make sure the value on the standby indicator is less than the tolerance shown in Table 501.
~................................................................. | | STATIC | DIFF | PITOT | STANDBY | STANDBY | | TEST | PRESSURE | PRESSURE | PRESSURE | ALTIMETER | AIRSPEED | | POINT | (In. HG) | (In. HG) | (In. HG) | (Feet) | (Knots) | ................................................................... | 1 | 29.921 | 0.695 | 30.616 | 0 |20 | 120 |2 | | 2 | 25.842 | 3.100 | 28.942 | 4,000 |35 | 250 |3 | | 3 | 20.577 | 6.286 | 26.863 | 10,000 |50 | 350 |4 | | 4 | 16.886 | 5.195 | 22.081 | 15,000 |65 | 320 |4 | | 5 | 13.750 | 3.924 | 17.674 | 20,000 |75 | 280 |4 | | 6 | 8.885 | 3.100 | 11.985 | 30,000 |100 | 250 |3 | | 7 | 7.041 | 1.580 | 8.621 | 35,000 |115 | 180 |3 | | 8 | 5.538 | 1.580 | 7.118 | 40,000 |125 | 180 |3 | 2.......…..........…..........…..........….............…..........1
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 導航 NAVIGATION 1(124)
