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A
737-300/400/500MAINTENANCE MANUAL
(2) Altitude bias is provided to the Autopilot during altitude hold. The bias provides speed control through the elevators, minimizing throttle activity.
L. AIRPLANES WITHOUT EFIS;
Fast/Slow Drive
(1) The Autothrottle provides fast/slow commands to the pilots, through the F/S pointer on the ADI's. The fast/slow command is derived from the airspeed error signal. When the A/T is not engaged, the fast/slow command is compensated by longitudinal acceleration, and has the versine signal added.
M. Monitor and Test
(1)
The A/T computer provides a continuous self-test of the system validity. If a computer failure is detected, the Autothrottle automatically disengages.
(2)
A/T BITE is accessed through the FMC control display unit. As the BITE routines, stored in the A/T computer, are accessed, instructions and test results are displayed on the FMC CDU.
14. Autothrottle System - Power Distribution (Fig. 5)________________________________________
A. The Autothrottle system requires 28 volt dc, 115 volt ac and 26 volt ac. The Autothrottle computer provides 28 volt dc for the engage interlock circuit and 26 volt ac, 400 Hz excitation for the Power Lever Angle Synchros.
B. Figure 5 shows all circuit breakers associated with the Autothrottle system. Reference numbers identify interface connections with other Autothrottle figures. For example: the Autothrottle dc circuit breaker provides 28 volt dc to the Autothrottle computer, the A/T servo actuators, and the Flight Mode Annunciators (Autoflight Status Annunciators) - as shown on this illustration. The Autothrottle dc circuit breaker also provides 28 volt dc for distribution on Figs. 10, 14, and 16.
15. Autothrottle Data Inputs________________________
A. ARINC 429 Digital Inputs (Fig. 6)
(1) The majority of the input data and command discretes are provided to the Autothrottle through six ARINC 429 digital data buses. Fig. 6 identifies the interfacing data buses, and the words on each bus that are used by the Autothrottle. The discrete words from the DFCS mode control panel and the Flight Management Computer are further defined by tables that follow.
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M1113 POWER LEVER ANGLE SYNCHRO -
2 AIRPLANES WITH EFIS ENGINE 2 (FUEL CONTROL BOX)
Autothrottle System - Power DistributionFigure 5
A 737-300/400/500MAINTENANCE MANUAL
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OCTAL LABEL INPUT DATA WORDS SOURCE BUS
3MCP 01FMC L-3DADC R-3DADC L-3IRU R-3IRU
102102077076075 FMC SELECTED ALTSELECTED ALTTARGET AIRSPEEDTARGET MACHGROSS WEIGHT XXX XX
211206205204203 BARO CORRECTED ALT 1TATCASMACHALT XXXXX XXXXX
250245220213212 CONT N1 LIMITFMC MIN SPEEDBARO CORRECTED ALT 2SATALT RATE XXX XX XX
272270255254253 DFCS DISCRETE-1DFCS DISCRETE-2GA N1 LIMITCLIMB N1 LIMITCRUISE N1 LIMIT XX XXX
324323312275274 GROUND SPEEDDFCS DISCRETE-3PITCH ANGLEFLT PATH ACCELFMC DISCRETE X X XXX XXX
341333332331325 TARGET N1NORMAL ACCELLAT ACCELLONG ACCELROLL ANGLE X XXXX XXXX
365361357 INERTIAL VERT ACCELFLT PATH ANGLE RATEBITE TEST WORD X X X X
ARINC 429 Digital Inputs
Figure 6
D301 D1647
MODE SELECT
4292 A57
MCP-3
ARM
XMTR
1 A56
MCP SPDFMC SPD M198 DFCS MCP
N1 (P7 GLARE SHIELD) RETARD 2
ARINC 429
D2179A
RECEIVERS
429 G9A38 DISCRETE LOGIC
FMC-01
XMTR
H9 A37
FLARE ARMFLARE ENGAM1175 FMC
G/S ENGAGE(E1-2) V NAVACTIVE ALT REFBARO CORR CMD
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