747飞机维护手册AMM CHAPTER 34 - NAVIGATION 第34章导航4(174)

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 A.  One limit indicator is installed in the airplane on the pilot's center panel (P2). The limit indicator has an instrument clamp attached to the rear of the instrument panel behind the panel cutout. The limit indicator slips through the cutout and into the clamp from the front of the panel. The clamp constricts around the indicator, holding it in place, as the clamp adjusting screws on the front of the panel are tightened. The indicator has one electrical cable attached to the rear of the unit through a connector.
 2.  Remove Limit Indicator______________________
 A.  Open PMS LIMIT IND circuit breaker on electronics circuit breaker panel P7.
 B.  Loosen upper right and lower left (clamp adjusting) screws.
 NOTE:____Do not loosen upper left or lower right (mounting) screws. These screws hold the limit indicator clamp in place behind the instrument panel.
 C.  Press on clamp adjusting screws to loosen clamp.
 D.  Pull limit indicator out from instrument panel.
 E.  Remove electrical connector on back of limit indicator.
 3.  Install Limit Indicator_______________________
 A.  Connect electrical connector to rear of limit indicator.
 B.  Insert limit indicator through the cutout and into the clamp at the rear of the instrument panel.
 C.  Tighten upper right and lower left (clamp adjusting) screws.
 D.  Close PMS LIMIT IND circuit breaker on electronics circuit breaker panel P7.
 E.  Test Limit Indicator (Ref 34-62-03 PMS Limit Indicator -Adjustment/Test).

 EFFECTIVITY

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34-62-03
 PMS LIMIT INDICATOR - ADJUSTMENT/TEST
_____________________________________
 1.  General
_______
 A.  This procedure tests the PMS limit indicator (LI). The test is designed to verify that a replaced PMS LI 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).
 CAUTION: ENSURE THAT COOLING AIR IS AVAILABLE TO INS NAVIGATION UNITS
_______ BEFORE OPERATING INS. FAILURE TO PROVIDE ADEQUATE AIR SUPPLY WILL RESULT IN FAILURE OF INS NAVIGATION UNITS.
 EFFECTIVITY

 AIRPLANES WITH PMS    02 Page 501  Aug 25/82

34-62-03
 H.  Ensure that present position latitude and longitude coordinates are entered into each INS (Ref 34-41). Verify that the mode selector switch, on each INS MSU, is set to ALIGN.
 I.  On IB airplanes, ensure that the AUTO/MAN/RMT switch on each INS CDU is set to MAN.
 J.  Ensure the following circuit breakers are closed.
　
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