(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.
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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 - Unpublished Work - See title page for details.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 .10.. 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.

(10)
Vary manual pitch knob. Verify ADI V-bars follow manual pitch commands.

(11)
Rotate course selector left and right of airplane heading. Verify ADI V-bars follow course commands.

(12)
On test set, vary LOC deviation to center, right of center and then back to center. Verify ADI V-bars and expanded localizer pointer follow LOC deviation changes.

(13)
On test set, slowly reduce GS deviation until F/D APD green glide slope annunciator comes on. Verify GS pointers indicate approximately zero deviation.

(14)
On test set, vary GS deviation to below center, above center and back to center. Verify ADI V-bars and GS pointer follow GS deviation changes.

(15)
Rotate manual pitch knob above and below zero. Verify ADI V-bars do not follow manual pitch commands.

(16)
Restore airplane and test set to original configuration.

(17)
Remove electrical power if no longer required.

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APPROACH PROGRESS DISPLAY - REMOVAL/INSTALLATION
EFFECTIVITY
Airplanes with Collins FD-110 Flight Director System
1. General
A.  Two approach progress displays (APD) are installed in the airplane. One is installed on the captain's instrument panel (P1) and one on the first officer's instrument panel (P3). Each APD is held in place by four fasteners.
2.  Remove APD
A.  Open appropriate FLT DIR DC circuit breaker on P6 or P18 circuit breaker panel.
B.  Loosen fasteners securing APD.
C.  Withdraw APD from panel and disconnect electrical connector(s).
3.  Install APD
A.  Connect electrical connector(s) to APD.
B.  Secure APD to instrument panel.
C.  Close circuit breakers opened in par. 2.A. above.
4.  Test after Installation
A.  Prepare to test.
(1)  
Provide external electrical power.

(2)  
Position LIGHTS BRT-DIM-TEST switch, on pilot's center instrument panel, to BRT.

B.  Test APD
(1)  
Press face of F/D APD. Check A/P and F/D APD VOR/LOC and GS annunciators come on amber.

(2)  
Press face of A/P APD. Check all A/P and F/D APD annunciators come on green.
　
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