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(a) Repeat step (1) using F/O components and VG-2 instead of VG-1.
H. ALTERNATE VHF NAV
(1) Both sides:
(a)
Apply greater than 2-dot fly-left localizer signal and 2-dot fly-up glide slope signal. Set VHF NAV switch to BOTH ON 2. Open the VHF NAV-1 VOR/LOC and G/S circuit breakers. Check that both APD's VOR/LOC and GS annunciations are green and V-bars indicate pitch up and fly left command.
(b)
Close VHF NAV circuit breakers.
(c)
Turn the VHF NAV transfer switch to BOTH ON 1. Open VHF NAV-2 VOR/LOC and G/S circuit breakers. Check for same indication as in (a).
(d)
Close VHF NAV circuit breakers. Return VHF NAV transfer switch to normal.
6. Restore Airplane to Normal
A. Turn all systems off and remove test equipment.
B. Open attitude reference system circuit breakers and install vertical gyros.
C. Close attitude reference system circuit breakers and verify that the system indicates attitude of airplane.
D. Determine if there is further need for electrical power, if not, remove power.
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34-26-0 Page 510 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jan 20/83
FLIGHT DIRECTOR SYSTEM - DESCRIPTION AND OPERATION
EFFECTIVITY
Airplanes with Sperry SP177 Auto Flight Control System
1. General
A. The flight director system is totally integrated with the autopilot system to form one of four independent systems which together comprise the auto flight control systems (AFCS). The AFCS consists of: the autopilot/flight director system; the yaw damper system; the mach trim system, and the auto throttle system. For additional information on each of these, refer to the following:
(1)
Auto Flight Description and Operation (22-00).
(2)
Autopilot/Flight Director System (22-11-01).
(3)
Yaw Damper System (22-12-00).
(4)
Mach Trim System (22-21-00).
(5)
Auto Throttle System (22-31-00).
May 15/81 34-26-01 Page 1
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
ATTITUDE DIRECTOR INDICATOR - REMOVAL/INSTALLATION
1. General
A. Two attitude director indicators (ADI, FDI, or HDI) 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).
B. Each indicator is clamp mounted on the panel and is electrically connected to the flight director system thru multipin connectors on the back.
2. ADI Removal/Installation (Airplanes with Collins FD-110 Flight Director System)
A. Remove Indicator
(1)
Open following listed circuit breakers on P18 or P6 circuit breaker panel (system 1 for CAPT ADI, system 2 for F/0 ADI): ADI FLT DIR VHF NAV (VOR/LOC, G/S) VERT GYRO RADIO ALTM
(2)
Loosen clamp and pull out indicator.
(3)
Disconnect electrical connectors.
B. Install Indicator
(1)
Connect electrical connectors, push in indicator, and tighten clamp.
(2)
Close circuit breakers opened in step A. (1).
C. Test Indicator
(1)
The following tests are provided to check attitude director indicator operation. For a quick check of indicator after installation perform Indicator Self-Test in par.
(2)
. For a more complete check of the indicator perform Indicator Command, V-Bar and Warning Flag Test in par. (3).
(2)
Indicator Self-Test
(a)
On appropriate ADI, press and hold TEST switch. Check ATT flag appears and horizon sphere rotates left 15 to 25 degrees and down 5 to 15 degrees.
(b)
Release TEST switch. Check horizon sphere returns to display airplane attitude and ATT flag retracts from view.
(c)
If no further tests are required, remove electrical power.
(3)
Indicator Command V-Bar and Warning Flag Test
(a)
Prepare to test. 1) Provide external electrical power. 2) Check all circuit breakers for flight director, VOR/ILS navigation, compass, and
attitude reference systems are closed and all systems are operational. 3) Tune VHF NAV receivers to a localizer frequency other than local VOR/TAC station. 4) Open circuit breakers for appropriate LRRA system.
(b)
Test
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