CIRCUIT BREAKER_______________ LOCATION
PMS EPR-1 REF P6 PMS EPR-2 REF P6 PMS EPR-3 REF P6 PMS EPR-4 REF P6
L. Ensure that gross weight of airplane is entered into the PMS.
4. Test PMS Limit Indicator________________________
A. Press and hold STS/TEST key on the CDU and verify that the following occurs on the LI:
(1)
The character locations, each with a rectangle of 5 by 7 dot matrix, are uniformly illuminated.
(2)
The first digit of the TAT line is '|'.
B. While holding STS/TEST key on the CDU pressed, rotate the Digital Display dimming control on the lightshield from dim to bright and verify that the LI display varies from dim to bright.
C. Release the CDU STS/TEST key.
5. Restore Airplane to Normal__________________________
A. Open all PMS circuit breakers on P7 circuit breaker panel.
B. On IB airplanes,
also open all PMS circuit breakers on P6 circuit breaker panel.
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).
E. Remove equipment cooling if no longer required (Ref 21-58-00).
EFFECTIVITY
AIRPLANES WITH PMS 03 Page 502 Apr 25/83
34-62-03
PMS COMPUTER UNIT - REMOVAL/INSTALLATION
________________________________________
1. General_______
A. The computer 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 computer 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 Computer Unit________________________
A. Open the following circuit breakers:
CIRCUIT BREAKER_______________ LOCATION
PMS CMPTR P7
PMS ADS P7
CONT POS FLAP OUTBD P6
B. On IB airplanes,
also open the following circuit breakers:
CIRCUIT BREAKER_______________ LOCATION
PMS EPR-1 REF P6
PMS EPR-2 REF P6
PMS EPR-3 REF P6
PMS EPR-4 REF P6
C. Remove PMS computer unit (Ref. 20-11-22).
CAUTION: ON AIRPLANES WITH PMS COMMAND EPR (OR N1) ON PILOT'S EPR
_______ (OR N1) INDICATOR(S), IF THE COMMAND SET KNOB ON THESE INDICATOR(S) IS PUSHED-IN FOR AUTOMATIC COMMAND MODE, WHEN PMS CMPTR CIRCUIT BREAKER IS OPEN, OR WHEN PMS COMPUTER IS REMOVED; THE COMMAND INDEX AND COUNTER ON INDICATOR(S) WILL DRIVE TO FULL SCALE CAUSING WEAR ON INDICATOR SERVO MECHANISM. TO PREVENT UNNECESSARY WEAR ON INDICATOR(S), PULL-OUT INDICATOR SET KNOB TO ENGAGE MANUAL COMMAND MODE.
5. Install PMS Computer Unit_________________________
A. Place PMS computer unit on mounting shelf.
B. Install PMS computer unit (Ref 20-11-22).
C. Close circuit breakers opened in step 4.A. and 4.B.
D. Test Computer Unit (Ref 34-62-04 PMS Computer Unit - Adjustment/Test).
EFFECTIVITY
AIRPLANES WITH PMS 04 Page 401 Apr 25/83
34-62-04
PMS COMPUTER UNIT - ADJUSTMENT/TEST
___________________________________
1. General
_______
A. This procedure tests the PMS computer unit (CU). The test is designed to verify that a replaced PMS CU 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) 中國(guó)航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：747飛機(jī)維護(hù)手冊(cè)AMM CHAPTER 34 - NAVIGATION 第34章導(dǎo)航4(175)
