H61644
Standby Artificial Horizon System Component Location 5C1
34-25-01 Figure 1 Jun 20/85
Page 2
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
STANDBY ARTIFICIAL HORIZON SYSTEM ADJUSTMENT/TEST
EFFECTIVITY
GJ B-2509, B-2510 and B-2524
1. Standby Artificial Horizon System Test
A. General
(1) The standby artificial horizon indicator is a back-up for the attitude reference system.
B. Test
(1)
Close STANDBY HORIZON circuit breaker located on load control panel P18. Power failure "OFF" warning flag should retract from view.
(2)
After power has been applied for at least 30 seconds, gently pull the caging knob to erect gyro. After a few seconds the attitude display will align close to the airplane attitude. Gently release the caging knob quickly without letting it knock abruptly against the indicator face.
(3)
After five minutes check that indication has stabilized to within 士 1 degree of airplane attitude as compared with aircraft primary attitude reference system or inclinometer.
(4)
Turn caging knob until airplane symbol and horizon bar are aligned, if necessary.
(5)
Open circuit breaker and observe that "OFF" flag appears.
5C8
Feb 20/89 34-25-01 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
FLIGHT DIRECTOR SYSTEM - DESCRIPTION AND OPERATI0N
EFFECTIVITY
Airplanes with Collins FD-110 Flight Director System
1. General
A. The flight director systems furnish the means to select a desired flight path, along with lateral (bank) and vertical (pitch) steering commands, which if followed, will enable intercept and tracking of the desired flight path. The desired flight path may be a magnetic heading, go-around after aborted approach, VOR or localizer (LOC)/glide slope (GS) approach beams. In addition, altitude information obtained from the air data computer is converted to pitch steering command information and utilized in holding the airplane at a desired altitude. Time base glide slope gain programming is available to reduce pitch steering commands as the airplane descends the glide path.
B. Two systems are installed, captain's (No. 1) and first officer's (No. 2). Each is comprised of the following units: attitude director indicator (ADI), horizontal situation indicator (HSI), steering computer and flight director annunciators. A single flight director control panel is common to both systems. Location of the components is shown in Fig. 1.
C. Each flight director computer receives input signals from its associated VOR/ILS navigation system (GS, or VOR/LOC deviation signals) (Ref 34-31-0), attitude reference system (bank and pitch displacement/error signals) (Ref 34-22-0), and the air data computer (altitude hold and rate error signals) (Ref 34-12-0). Pitch and roll signals are received from the vertical gyro (Ref 34-22-0). Each computer receives heading and course error signals and manual pitch commands from the flight director control panel. The computer uses various combinations of these signals, depending upon the mode selected, to develop the bank and pitch steering commands. Bank steering commands are developed from heading and course error signals from the flight director control panel, VOR/LOC deviation signals from the VOR/ILS system and roll attitude reference system. Pitch steering commands are developed from altitude error signals from the ADC, manual pitch commands from the flight director control panel, glide slope deviation signals from the VOR/ILS system and pitch attitude signals from the attitude reference system. The bank and pitch steering commands are displayed by the steering command display system (V-bar command indicators) in the ADI. The V-bars are servo-operated and move to indicate the desired attitude in bank and pitch. The pilot then maneuvers the airplane to align the V-bars against the miniature airplane symbol. When the V-bars are aligned with the airplane symbol, the real airplane will be in the correct attitude to intercept, or remain on the desired flight path. A block diagram of the systems is shown in Fig. 2.
5C8
Feb 20/86 34-26-0 Page 1
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
H24580 H24660
Flight Director System Component Location 563
34-26-0 Figure 1 (Sheet 1) Feb 15/77
Page 2
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
5C4 Flight Director System Component Location
Jan 20/83 Figure 1 (Sheet 2) 34-26-0
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