S 795-009
(2)
Stop for five to six minutes to let the systems become stable.
(a) Read and write the values of the altitude and airspeed on the standby altimeter and standby airspeed indicator.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
34-13-00
ALL ú ú 01 Page 502 ú Jun 10/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
.6 .7 .8 .9 1.0 1.1 1.2
HEAD PRESSURE CORRECTION FACTOR
EXAMPLE: OUTSIDE AIR TEMPERATURE = 40`F VERTICAL SEPARATION = 40 FEET HEAD PRESSURE CORRECTION = +32 FEET TEST ALTITUDE = 35,000 FEET SOURCE AND SENSOR BETWEEN PRESSURE *VERTICAL SEPARATION
NOTE:____ CORRECTION FACTOR MUST BE SUBTRACTED FROM THE ALTITUDE. IF THE PRESSURE SOURCE IS ABOVE THE SENSOR, THE
Head Correction
Figure 501
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
34-13-00
ALL ú ú 01 Page 503 ú Jun 10/88
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
S 795-010
(3) Stop for one more minute and read the altitude and airspeed again.
(a)
Make sure the altitude did not decrease by more than 400 feet
(0.20 in. Hg).
(b)
Make sure the airspeed did not decrease by more than 5.0 knots
(0.16 in. Hg).
S 865-011
CAUTION: THE PITOT LINE PRESSURE MUST BE EQUAL OR MORE THAN THE STATIC
_______ LINE PRESSURE. KEEP THE RATE OF THE PITOT PRESSURE CHANGE LESS THAN 300 KNOTS FOR EACH MINUTE. KEEP THE RATE OF THE STATIC PRESSURE CHANGE LESS THAN 5,000 FEET FOR EACH MINUTE. KEEP THE DIFFERENTIAL PRESSURE BETWEEN 0 AND 9.33 INCHES OF MERCURY. IF YOU DO NOT FOLLOW THE INSTRUCTIONS ABOVE, YOU CAN CAUSE DAMAGE TO THE EQUIPMENT.
(4) Open the pitot and static system cutoff valves.
E. Put the Airplane Back to Its Usual Condition
S 865-017
(1) Put the pitot-static system back to the ambient pressure
(Ref 34-11-00/201).
S 865-027
CAUTION: YOU MUST CONNECT THE ELEVATOR FEEL COMPUTER TO THE PITOT
_______ AND STATIC SYSTEMS. IF YOU DO NOT, THE ELEVATOR FEEL COMPUTER WILL NOT OPERATE PROPERLY.
(2)
Connect the pitot and static systems to the elevator feel computer.
(3)
Remove electrical power if it is not necessary (Ref 24-22-00/201).
S 865-012
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
34-13-00
ALL ú ú 01 Page 504 ú Oct 10/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
STANDBY AIRSPEED INDICATOR - REMOVAL/INSTALLATION
_________________________________________________
1. General
_______
A. This subject contains two tasks. The first task is to remove the standby airspeed indicator. The second task is to install the standby airspeed indicator. The installation task includes a test of the installation of the indicator.
B. The standby airspeed indicator (N246) is installed on the pilot's P2 center instrument panel. The indicator is connected to the auxiliary No. 1 pitot and to the alternate static pitot-static systems.
C. The indicator is held in the instrument panel by an instrument mounting clamp. The instrument mounting clamp is attached to the instrument panel with two mounting screws (see Figure 401). The indicator is held in the mounting clamp by two adjustment screws. To remove the indicator from the instrument panel, it is only necessary to loosen the two adjustment screws.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：747-400 AMM 飞机维护手册 导航 NAVIGATION 1(125)
