曝光臺 注意防騙 網(wǎng)曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

F.  The PDCS provides flight guidance data to the autothrottle system in the form of optimum airspeed and thrust settings to achieve the most efficient and economical mode of operation for the airplane. Controls for this system are mounted on the CDU, which is located on the forward electronic panel. The CDU is used extensively by the autothrottle system to display self-test (BITE) information, including test pass/fail results, of the autothrottle computer.
G.  Various autothrottle interlocks must be satisfied before the A/T ARM-OFF switch will latch in the engaged position. The autothrottle system will disengage with the loss of internal valid signal, loss of interfacing system valid signal, operation of either A/T disengage switch on the forward thrust levers, or operation of the A/T ARM-OFF switch to OFF. A disengage warning light is located on the captain's and first officer's flight mode annunciators.
H.  A number of externally generated signals are used for system computation and control (Fig. 3). These signals, together with signal sources, are given in the following list:
(1)  
Vertical gyro No. 1 provides pitch and roll attitude plus VG valid logic.

(2)  
Digital air data computer No. 1 provides altitude, MACH, CAS (computed airspeed), and DADC valid logic.

(3)  
Low range radio altimeter No. 1 provides altitude during landing.

(4)  
ALPHA vane No. 1 provides angle of attack used to compute minimum speed.

(5)  
Logic in the landing gear accessory box provides a landing gear up/down discrete and an in-air/on-ground discrete.

(6)  
Longitudinal accelerometer provides longitudinal acceleration. This component is part of the autothrottle system.

(7)  
Flap position sensor provides flap position information.

(8)  
Engine pressure ratio transmitters provide actual EPR and valid signals.

(9)  
Thrust lever linear velocity displacement transducers (left and right) provide engine thrust lever position. The transducers are part of the autothrottle system.

580 
Oct 20/85  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  22-31-01 Page 7 

H20241
Autothrottle System Interface Diagram  580 
22-31-01  Figure 3  Oct 20/85 
Page 8 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

(10)
AFCS mode control panel provides autothrottle engage logic and ARINC 429 digital data. This data, which is generated in the AFCS computer, consists of IAS select, mach select, and selected AFCS modes. The digital data is transmitted in binary form.

(11)
Performance data computer provides ARINC 429 digital data consisting of target EPR, EPR limit, climb EPR limit, cruise EPR limit, go around EPR limit, target airspeed, total air temperature (TAT), outside air temperature (OAT) in TO (take off mode) flight mode select, and system discrete (34-18-0). The data is transmitted in binary form.

(12)
AFCS computers A and B provide glide slope engage logic. In addition, computer A provides flare engage logic.

(13)
Throttle servos (left and right), part of the autothrottle drive assemblies, provide tachometer feedback signals.

I.  Electrical power (115 volts ac, and 28 volts dc) for the autothrottle system is provided by No. 1 electronic power bus via circuit breakers A/T SYST AC and A/T SYST DC, respectively, located on load control center P18.
2.  Autothrottle Computer
A.  The autothrottle computer is a digital computer with memory and a BITE system. It is housed in a 1/2 - ATR long case located on electronic equipment rack E1, shelf No. 2 or 3. Rack mounted swivel bolts are used to lock the unit into position in the rack. Four electrical connectors are located on the back of the unit. Solid state logic and computation circuits are used throughout for signal processing.
B.  All computations for thrust lever commands are processed in the central processor section. The computer also contains the servo power amplifiers and all system monitor logic.
C.  A BITE TEST switch and an alpha-numerical test result readout are provided on the front panel of the autothrottle computer. The BITE tests are initiated by pressing the momentary action 'TEST' pushbutton. Test in progress (0 to 9 and A to F) and pass/fail indications are provided by the alpha/numerical display. Initial operation of the pushbutton produces a continuous display of letter E followed by numeral 7 as a check on the correct operation of the display. Subsequent operation of the pushbutton initiates each BITE TEST in sequence.
5B8 
Oct 20/85  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  22-31-01 Page 9 
　
中國航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 AUTO FLIGHT 自動飛行 2(81)