NOTE: Entry into align mode 5 indicates that an adequate
____ alignment of the INS platform has been achieved. The READY NAV light on the MSU will illuminate when mode 5 is entered.
(5) Check INS/HSI Interface
(a) Position the following switches:
1) On ATLAS ALL EXCEPT AT 701-750, INS switch to normal position (capt 1 - F/O 2). On AT 701-750, INS switches to normal position (Captain's switch to NORM and F/O switch to NORM).
2) VOR-ILS/INS switch to INS (panel P72)
3) Data selector switch to WIND (pilots' control stand)
NOTE: Alignment mode status must be 8 or less prior to
____ this step.
(b)
Press and hold TEST switch on control/display unit. Observe the following indications on appropriate HSI. 1) HEADING and navigation (striped) flags are out of view. 2) Preset heading bug, course pointer and O on azimuth card
are positioned under lubber line. 3) Course deviation bar is positioned one dot to right of center.
(c)
Release test switch.
(6) Check ready nav status.
(a)
Place data selector to DSRTK/STS position.
(b)
Place mode selector to NAV. Observe that READY NAV light goes out, that flight instrument warning flags controlled by INS disappear and that left-most digit of the right display changes from 0 to 1.
F. Restore Airplane to Normal
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(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.
(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)
On ATLAS ALL EXCEPT LH 011-030, 051-070, 082-099; AT 701-750, AZ 221-299, Power 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/ADI Interface Tests
(g)
INS/DME Interface Test
(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)
On airplanes with PMS, when the PMS has waypoint control, the INS CDU's operate as display units only. Proper completion of this test requires that the PMS not be operational during the test.
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(10)
Correct functioning of the equipment cooling system shall be determined prior to this test.
(11)
The Prepare For Test procedure must be completed before the system test can be accomplished. However, the Prepare For Test procedure does not need to be repeated for each test if two or more tests are to be performed in sequence.
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