D728A(TP) D2295A
D2295A
SLAT 1 MID EXTEND 3 SLAT 5 MID EXTEND 47SLAT 3 MID EXTEND 39SLAT 1 INTRANSIT 2SLAT 3 INTRANSIT 38SLAT 5 INTRANSIT 46
SLAT 2 FULL EXTEND 37SLAT 6 FULL EXTEND 52SLAT 4 FULL EXTEND 45SLAT 6 MID EXTEND 50SLAT 4 MID EXTEND 44SLAT 2 MID EXTEND 36SLAT 2 INTRANSIT 35SLAT 4 INTRANSIT 43SLAT 6 INTRANSIT 49
SLAT 3 FULL EXTEND 41SLAT 5 FULL EXTEND 48SLAT 1 FULL EXTEND 6
D728B(BP)
FLAP 3 EXTENDED 53FLAP 1 EXTENDED 48FLAP 1 INTRANSIT 47
FLAP 3 INTRANSIT 52
FLAP 4 EXTENDED 57
FLAP 2 EXTENDED 51FLAP 2 INTRANSIT 49FLAP 4 INTRANSIT 55
M229 LE FLAPS/SLATS POSNIND MODULE (E3-2)
D1458ATR DEPLOY (L-IN) 46
TR DEPLOY (L-OUT) 47
TR UNLOCK (L-OUT) 48TR UNLOCK (L-IN) 49D1458BTR DEPLOY (R-OUT) 46
TR DEPLOY (R-IN) 47
TR UNLOCK (R-IN) 48
TR UNLOCK (R-OUT) 49
M528 ENG ACCESSUNIT (E3-2)
D3412B2
R371 ENG 1 LOW IDLE
D776
A
S128 CABIN PRESSURE SWITCH
D2870
4
S811 ALT BRAKE SELECTVALVE PRESS SWITCH
D367
B
M424 F/O CONTROL
COLUMN SHAKER
D1671B14M1924 FCC-A
D742
3
M237 COMPARTMENTOVERHEAT CONTROL UNIT
D2618
7
3
8E11 LANDING GEAR LOGIC SHELF
D3414B2
R372 ENG 2 LOW IDLE
D281
A
M232 CAPTAIN'S CONTROLCOLUMN SHAKER
D1649B1718
M916 A/T COMPUTER
D1655B14M1923 FCC-B
D998
11
D1002
11
D1000
11
M279 FIRE DETECTIONACCESSORY UNIT
Flight Data Recorder System - Discrete Input Schematic
Figure 7 (Sheet 2)
A 737-300/400/500MAINTENANCE MANUAL
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. BEJ 101-999 ú
31-24-01
ú ú 05A Page 17 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A53644
A
737-300/400/500MAINTENANCE MANUAL
5) EFIS transfer relay 6) Engine accessory unit 7) Flight control module 8) HF transceivers 9) Hydraulic system low pressure switches 10) IRS transfer relay 11) Landing gear logic shelf 12) Leading edge flaps/slats position indicator module 13) Light shield panel lights 14) Marker beacon receiver 15) Stabilizer trim cutout relay 16) VHF transceivers
B. Functional Description
(1)
The flight recorder system is turned on automatically by the ground power sensing relay as soon as the airplane has lift-off or by the engine oil pressure switches when any of the engines is operating. It can also be turned on by placing the flight recorder TEST NORMAL switch in the TEST position.
(2)
During operation, all data is processed by the FDAU. The FDAU provides data to the FDR as a serial digital data stream.
(3)
Monitor or BITE (Built-in Test Equipment) circuits in the FDAU and the FDR provide status signals to actuate fault indicators on the front panel of the FDAU in the event of malfunction.
(4)
The FDAU accepts all input parameter signals and performs the functions of preconditioning, multiplexing and conversion to place them in standard digital format for recording. The FDAU accepts analog, digital, and discrete parameter signals. The parameter signals are preconditioned to adjust scale factors, biases and other signal characteristics to a normalized level so that resolution will be retained during analog to digital conversion. The input signals are multiplexed (time shared) in the FDAU and formatted for transmission to the FDR.
(5)
The FDAU clock generator generates the synchronizing signal (clock) for the functions of multiplexing and analog-to-digital conversion in the FDAU and recording in the FDR.
C. DFDR Functions
(1)
Airplane power (115v ac, 400 Hz) is applied through the flight recorder rear connector. The Power Supply board converts airplane power to voltage levels required by the DFDR.
(2)
The flight data acquisition unit provides ARINC 573 data to the DFDR. The data is supplied through the flight recorder rear connector to Airframe wiring Interface circuit board. Airframe wiring Interface circuit board, shifts the data levels for use by the recorder system controller. The recorder system controller sends the data to the Read/Write Interface thru the Transport Interface. The Read/Write Interface conditions the data stream, providing a current source sufficient to drive the write heads of the tape transport.
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