(b)
Appropriate COURSE knob - Rotate until airplane heading is displayed in COURSE window. Check HSI course arrow is aligned with lubber line.
(4)
Position VHF NAV transfer switch to BOTH ON 1 or BOTH ON 2 as appropriate. Check HSI data source annunciator agrees with selected switch position.
(5)
Return transfer switch to normal.
(6)
On VHF NAV control panel, activate VOR self-test while checking HSI for following:
(a)
After 3 seconds NAV flag goes out of view.
(b)
Course deviation bar remains centered.
(c)
To - From pointer indicates from.
(7)
While continuing VOR self-test, rotate COURSE knob 5 degrees left and 5 degrees right of airplane heading. Check HSI deviation bar deflects 1 dot left and 1 dot right of center.
(8)
Release VOR self-test. Check NAV flag comes into view.
(9)
Tune VHF NAV system to an ILS frequency other than local station. Check HSI GS flag and pointer come into view.
(10)
On VHF NAV control panel, activate ILS UP/LT self-test while, checking HSI for following:
(a)
After 3 seconds NAV and GS flags go out of view.
(b)
Course deviation bar deflect left.
(c)
Glide slope pointer deflects up.
(11)
Release ILS UP/LT self-test. Check NAV and GS flags come into view.
(12)
Return all switches to normal.
(13)
Remove external electrical power if no longer required.
5A5
34-26-21 Page 402 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/84
FLIGHT DIRECTOR (STEERING) COMPUTER - REMOVAL/INSTALLATION
EFFECTIVITY
Airplanes with Collins FD-110 Flight Director System Installed
1. General
A. The flight director steering computers are installed on shelf No. 2 of electronic equipment rack E1.
B. Each computer is held in the rack by a swivel bolt mounted on the equipment shelf.
2. Remove Computer
A. Open applicable Flight Director AC and DC circuit breakers on P6 or P18 circuit breaker panel.
B. Loosen swivel bolt and remove computer.
3. Install Computer
A. Install computer and secure in rack.
4. Test Steering Computer
A. Equipment and Materials
(1) Test Set, Instrument Flight Research Type NAV 401L
B. Prepare to test.
(1)
Provide external electrical power.
(2)
Close following circuit breakers on panels P6 and P18:
(a)
FLT DIR 1 and 2, AC and DC
(b)
VHF NAV 1 and 2, AC and DC
(c)
VERT GYRO 1 and 2
(d)
COMPASS 1 and 2
(e)
INST XFMR 1 and 2
(3)
Open LRRA circuit breakers on panels P6 and P18.
(4)
Position flight instrument transfer switches to normal.
NOTE: The NORMAL position of transfer switches implies captain on 1 and first officer on 2.
(5)
Synchronize captain's and first officer's compass system.
(6)
Position heading and course selectors to airplane heading.
C. Test Computer
(1)
Position flight director mode selector to OFF. Verify ADI command bars are out of view and Cmptr flag shows momentarily.
(2)
Tune appropriate VOR/ILS nav system to 108.1 MHz.
(3)
On test set, position mode selector to G/S XTAL and AVG/PEAK LOC switch to PEAK LOC.
NOTE: The PEAK LOC and G/S XTAL selector positions on the NAV 401L test set provide simultaneous localizer and glide slope test signals.
5C8
Jun 20/85 34-26-31 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(4)
On test set, position LOC and GS deviation controls for a two dot left and two dot up indication on HSI.
(5)
Position flight director mode selector to AUTO APP. Verify F/D APD amber VOR/LOC annunciator comes on.
(6)
Rotate heading selector left and right of airplane heading. Verify ADI V-bars follow heading commands.
(7)
Rotate pitch command knob士100. Verify ADI V-bars follow pitch commands.
(8)
On test set, slowly reduce LOC deviation until F/D APD green VOR/LOC annunciator comes on (localizer capture). Check following:
(a)
HSI course deviation display indicates between 1 and 2 dots.
(b)
Amber F/D APD glide slope annunciator comes on.
(9)
Rotate heading selector left and right of airplane heading. Verify ADI V-bars do not follow heading commands.
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