(i)
Press test button on captain's ADI. Verify that ADI displays 10 (| 3) degree pitchup and 20 (| 5) degree roll right indication and that attitude flag comes in view.
(j)
Release test button. Verify that ADI returns to 0-degree pitch and roll and that attitude flag disappears from view.
(k)
Set ATT/COMP STAB switch on the captain's main instrument panel to CAPT 1 - F/O 3 position. Verify that F/O's ADI indicates 0-degree pitch and roll and that attitude flag is out of view.
(l)
Press test button on first officer's ADI. Verify that ADI displays 10 (| 3) degree pitchup and 20 (| 5) degree roll right indication and that attitude flag comes in view.
(m)
Release test button. Verify that ADI returns to 0-degree pitch and roll and that attitude flag disappears from view.
(n)
Return ATT/COMP STAB switch to CAPT 1 - F/O 2 position.
(o)
If the INS is no longer required, restore airplane to normal.
(9) Test Inertial Navigation System/INS-3 Fail Operational Annunciator.
(a)
If required prepare for test as described in par. 2.
(b)
Set the No. 3 MSU to STBY.
EFFECTIVITY AIRPLANES WITH LTN-72 INS
CONFIG 01 A Page 517 Aug 25/87
34-41-00
(c)
Set the No. 3 CDU data selector to DSR TK/STS and verify that the right data display indicates alignment status 80.
(d)
Verify on the fail operational annunciator panel (pilots' center instrument panel) that the INS-3 annunciator shows black.
(e)
Place the No. 3 MSU to the OFF position. Verify that the INS-3 annunciator changes from black to red.
(f)
If the INS is no longer required, restore airplane to normal.
F. Restore Airplane to Normal
(1) Place each INS mode selector switch in OFF position.
CAUTION: FAILURE TO MOVE MODE SELECTOR TO OFF WILL CAUSE INS TO
_______ AUTOMATICALLY SWITCH TO BATTERY POWER AND A WARNING HORN IN NOSE WHEEL WELL TO ACTUATE 30 (| 10) SECONDS AFTER POWER IS REMOVED FROM AIRPLANE.
(2)
Remove electrical power if no longer required. Refer to 24-22-00.
(3)
Remove equipment cooling if no longer required. Refer to 21-58-00.
EFFECTIVITY AIRPLANES WITH LTN-72 INS
CONFIG 01 A Page 518 Aug 25/87
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INERTIAL NAVIGATION SYSTEM - ADJUSTMENT/TEST
____________________________________________
1. Operational Test - Inertial Navigation System
_____________________________________________
A. General
(1)
The inertial navigation system operational test is similar to a preflight procedure used to prepare an inertial navigation system for flight. This test requires no special tools.
(2)
Proper completion of this test specification requires accurate knowledge of airplane test location position expressed in degrees and arc-minutes accurate to 0.1 arc-minute of latitude.
(3)
Proper completion of this test also requires that the following systems or components be operational during the test:
(a)
Central Air Data System (CADS)
(b)
Attitude Director Indicators (ADI)
(c)
Horizontal Situation Indicators (HSI)
B. Equipment and Materials
(1) Cards containing airplane present position and waypoint information.
C. Referenced Procedures
(1)
21-58-00, Equipment Cooling - Adjustment/Test (Operating Test)
(2)
24-22-00, Manual Control - Maintenance Practices (Apply Power)
(3)
33-11-00, Pilots Panel Lights - Adjustment/Test
D. Prepare for Test.
(1)
Set mode selector switch on each mode selector unit (pilots' overhead panel P5) to OFF position.
(2)
Verify setting of mode selector unit remote access switch.
(a)
Remove the two screws securing the access cover to the mode selector unit.
(b)
Verify that the remote access switch is set to the OFF position.
(c)
Replace the access cover.
(3)
Set both CAPT's and F/O's VOR-ILS/INS switches to INS.
(4)
Set ATT/COMP STAB transfer switch on the captain's main instrument panel to CAPT 1 - F/O 2 position.
(5)
Set INS transfer switch on the captain's main instrument panel to CAPT 1 - F/O 2 position.
(6) 中國航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：747飛機維護(hù)手冊AMM CHAPTER 34 - NAVIGATION 第34章導(dǎo)航3(41)
