(3)
Remove electrical power if no longer required.
5C8
Jun 20/85 34-26-41 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
FLIGHT DIRECTOR CONTROL PANEL - REMOVAL/INSTALLATION
EFFECTIVITY
Airplanes with Collins FD-110 Flight Director System
1. General
A. The flight director control panel is located on the pilots lightshield and held in place by four fasteners.
2. Remove Flight Director Control Panel
A. Open appropriate flight director AC and DC circuit breakers on P6 or P18 panel.
B. Loosen fasteners securing panel to mounting.
C. Withdraw panel from mounting and disconnect electrical connector(s).
3. Install Flight Director Control Panel
A. Connect electrical connector(s) to control panel.
B. Secure control panel to mounting.
C. Close circuit breakers opened in par. 2.A.
4. Test Control Panel
A. The following tests are provided to check flight director control panel operation. For a quick check of control panel after installation, perform Control Panel Power-On Test (par. C). For a more complete check-out of the control panel, perform Control Panel Mode Selection Test (par. D).
B. Prepare to Test
(1)
Provide external electrical power.
(2)
Close following circuit breakers on P6 and P18 circuit breaker panels:
(a)
FLT DIR 1 and 2, AC and DC
(b)
VHF NAV 1 and 2, VOR/LOC G/S
(c)
VERT GYRO 1 and 2
(d)
COMPASS 1 and 2
(e)
INST XFMR 1 and 2
(f)
INST XFR
(3)
Open LRRA systems circuit breakers on P6 and P18 circuit breaker panels.
(4)
Position flight instrument transfer switches to NORMAL.
C. Control Panel Power-On Test
(1)
Position mode selector to OFF. Check ADI V-bars are out of view.
(2)
Position mode selector to HDG. Check F/D APD for green HDG SEL annunciation.
(3)
If no further test are required, remove external electrical power.
5C8
Jun 20/85 34-26-51 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
D. Control Panel Mode Selection Test
(1)
Perform prepare to test procedure (par. B).
(2)
Position mode selector to HDG. Check F/D APD for green HDG SEL annunciation.
(3)
Rotate left COURSE knob left and right of airplane heading. Check captains HSI course pointer follows course commands.
(4)
Rotate right COURSE knob left and right of airplane heading. Check F/O's HSI course pointer follows course commands.
(5)
Rotate HEADING knob left and right of airplane heading. Check on both ADI'S, V-bars follow heading commands, also HSI heading marker follows heading command.
(6)
Return HEADING knob to airplane heading. Check ADI V-bars are centered and HSI heading marker is under lubber line.
(7)
Rotate PITCH CMD knob 10 degrees above and below 0. Check on both ADI'S, V-bars follow pitch commands.
(8)
Return PITCH CMD knob to zero. Check ADI V-bars are centered.
(9)
Position ALT HOLD ON/OFF to ON, check F/D APD for green ALT HOLD annunciation.
(10)
Rotate PITCH CMD 10 degrees up and return to zero. Check on both ADI'S, V-bars remain centered.
(11)
Position mode selector to MAN GS. Check for following:
(a)
ALT HOLD switch - Returns to OFF
(b)
ALT HOLD annunciations -ALT HOLD extinguish
VOR/LOC green
GS green
(12)
Momentarily press left thrust lever GO-AROUND switch. Check for following:
(a)
Mode selector - Rotates to GA position.
(b)
F/D APD - annunciations GA green.
(c)
ADI V-bars -display pitch-up command
(13)
Position mode selector to VOR/LOC. Check F/D APD for green HDG and amber VOR/LOC annunciations.
(14)
Position mode selector to OFF.
(15)
Return all switches and controls to normal.
(16)
Remove electrical power if no longer required.
5A5
34-26-51 Page 402 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/03
FLIGHT INSTRUMENT ACCESSORY UNIT - REMOVAL/INSTALLATION
1. General
A. The flight instrument accessory unit is installed on electronic shelf E1-2. The accessory unit is held in the rack mounting by a lever latch assembly. Correct adjustment of the lever latch assembly is necessary to assure proper electrical connector engagement.
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