C. If operation of the INS is no longer required, place each INS mode selector switch in OFF position (Ref 34-41).
D. Remove electrical power if no longer required (Ref 24-22-00).
EFFECTIVITY
AIRPLANES WITH PMS 03 Page 502 Apr 25/83
34-62-05
E. Remove equipment cooling if no longer required (Ref 21-58-00).
EFFECTIVITY
AIRPLANES WITH PMS 02 Page 503 Dec 25/82
34-62-05
PMS SWITCHING UNIT - REMOVAL/INSTALLATION
_________________________________________
1. General
_______
A. The switching unit is installed in the main equipment center on shelf E2-5 and held in place by two hold down hooks and retaining nuts. The switching unit is electrically connected by two connectors in the rear of the unit.
2. Equipment and Materials
_______________________
A. Extractor Assembly
3. Referenced Procedures
_____________________
A. 34-62-00, Performance Management System - Adjustment/Test
B. 20-11-22, Electrical/Electronic Black Box - Removal/Installation
4. Remove PMS Switching Unit
_________________________
A. Open PMS circuit breakers on P7 circuit breaker panel.
(1)
PMS CMPTR
(2)
PMS SU PRIM
(3)
PMS SU ALTN
(4)
AUTO THROT
B. On IB airplanes,
also open PMS circuit breakers on P6 circuit breaker panel.
(1)
PMS EPR-1 REF
(2)
PMS EPR-2 REF
(3)
PMS EPR-3 REF
(4)
PMS EPR-4 REF
C. Remove PMS switching unit (Ref 20-11-22).
5. Install PMS Switching Unit
__________________________
A. Place PMS switching unit on mounting shelf.
B. Install PMS switching unit (Ref 20-11-22).
C. Close circuit breakers opened in step 4.A and 4.B.
D. Test Switching Unit (Ref 34-62-06 PMS Switching Unit - Adjustment/Test).
EFFECTIVITY
AIRPLANES WITH PMS 04 Page 401 Aug 25/83
34-62-06
PMS SWITCHING UNIT - ADJUSTMENT/TEST
____________________________________
1. General
_______
A. This procedure tests the PMS switching unit (SU). The test is designed to verify that a replaced PMS SU has been properly installed and will operate. If the integrity of the total performance management system is in doubt, perform Performance Management System - Adjustment/Test (Ref 34-62-00).
B. Proper completion of this test requires the following systems or components be operational during the test.
CAUTION: ALL THE SAFETY PRECAUTIONS/WARNINGS REQUIRED TO BE OBSERVED
_______ DURING OPERATION OF THE FOLLOWING AIRPLANE SYSTEMS MUST BE ADHERED TO IN ORDER TO PREVENT DAMAGE TO TEST EQUIPMENT, AIRPLANE SYSTEMS AND INJURIES TO PERSONNEL.
(1)
Autopilot/Flight Director Pitch Channel
(2)
Central Air Data Computer System
(3)
Inertial Navigation System
C. All systems and components that are operational during this test should be maintained at their normal operating conditions with the airplane on the ground unless otherwise specified.
2. Referenced Procedures
_____________________
A. 21-58-00, Rack-Mounted Equipment Cooling System
B. 24-22-00, Manual Control (Apply Power)
C. 33-11-00, Pilots Panel Lights
D. 34-12-00, Central Air Data Computer System
E. 34-41-00, Inertial Navigation System
3. Prepare for Test
________________
A. Set the altitude selector on the autopilot flight director mode select panel (A/P-F/D MSP) to zero altitude.
B. Set the AUTOPILOT ENGAGE switch on the A/P-F/D MSP to OFF.
C. Ensure the TURB/SPEED switch on the A/P-F/D MSP is not set to PMS.
D. Provide electrical power (Ref 24-22-00).
E. Check for proper operation of pilot's panel illumination, indicator lamps, and annunciator lights using master test and dim control (Ref 33-11-00).
F. Provide cooling air to electronic equipment (Ref 21-58-00).
CAUTION: ENSURE EQUIPMENT COOLING IS OPERATING BEFORE TURN ON OF
_______ ELECTRONIC SYSTEMS, OR DAMAGE TO EQUIPMENT MAY RESULT. EQUIPMENT COOLING SYSTEM MUST BE SET FOR NORMAL COOLING AS DESCRIBED IN 21-58-00.
G. Provide cooling air to INS equipment (Ref 21-58-00).
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：747飞机维护手册AMM CHAPTER 34 - NAVIGATION 第34章导航4(179)
