0.
(f)
Place data selector on control/display unit to TEST. Observe the following indications on appropriate HSI. 1) HEADING and navigation (striped) flags are out of view.
NOTE: Flags are withdrawn when status 80 is attained.
____
2) 11.2 degrees on azimuth card is positioned under lubber line.
EFFECTIVITY
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3) Drift angle bug is positioned at 22.5 degrees on azimuth card. 4) Course pointer is positioned at 59.5 degrees on azimuth card. 5) Course deviation bar is positioned one dot to left of
center. 6) ALERT light illuminates. 7) MILES indicator will read 888 and GND SPEED indicator
will read 512.
(7)
On airplanes with PMS,
check INS/INS Updating Annunciator.
(a)
Position the following switches: 1) INS switch to normal position (Capt 1 - F/O 2) 2) VOR-ILS/INS switch to INS (panel P72)
(b)
Ensure that the CDU AUTO/MAN/RMT switch is in MAN.
(c)
Verify that the MSU mode selector switch is set to ALIGN.
(d)
Verify that the CDU FROM/TO display is 00.
(e)
Set the control display unit WPT switch to any position except 0.
(f)
Place data selector on control/display unit to TEST. Observe that the applicable INS updating annunciator alternately changes black and green.
(8)
Check ready nav status.
(a)
Place data selector to DSR TK/STS position.
(b)
When READY NAV light on MSU comes on, place mode selector to NAV. Observe that READY NAV light goes out. Note and record time.
F. Restore Airplane to Normal
(1) Place mode selector 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 THE NOSE WHEEL WELL TO ACTUATE WHEN POWER IS REMOVED FROM THE 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.
2. System Test - Inertial Navigation System
________________________________________
A. General
(1)
The following procedure accomlishes a system test of the inertial navigation system (INS) and interfacing components. The system test provides a complete system checkout of the inertial navigation system and will normally be performed only at overhaul maintenance periods or when sufficient maintenance is accomplished as to leave the integrity of the total system in doubt.
(2)
The INS system test requires two men, one in the main equipment center and one on the flight deck.
EFFECTIVITY AIRPLANES WITH LTN-72 INS
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(3)
The test procedure allows the testing of the entire inertial navigation system including interface tests or it allows the performance of individual tests including:
(a)
Battery Unit Tests
(b)
Battery Transfer Relay Tests
(c)
Navigation Unit and Control/Display Unit Tests
(d)
INS/Central Air Data System Interface Tests
(e)
INS/HSI Interface Tests
(f)
INS Data Loading and Autofill Tests.
(g)
INS/ADI Interface Tests
(4)
For interfacing systems not mentioned above, refer to the Maintenance Practices sections covering those systems.
(5)
The system installation, inspection and wiring continuity tests shall have been completed, prior to performing these tests.
(6)
Correct functioning of the electrical distribution system shall be determined prior to this test.
(7)
Proper completion of this test specification requires accurate knowledge of airplane test location position expressed in degrees and arc-minutes accurate to .1 arc-minute of latitude.
(8)
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)
(9)
Correct functioning of the equipment cooling system shall be determined prior to this test.
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本文鏈接地址：747飛機維護手冊AMM CHAPTER 34 - NAVIGATION 第34章導航3(35)
