----------------------------------------------------------------------------
COMPONENT | PWR.CONS. | VOLTAGE | BUSBAR | C/B
----------------------------------------------------------------------------FDIMU | 30 W | 115 V AC | 202XP NORM | 5TV DAR | 50 W | 115 V AC | 202XP NORM | 5TV
| | 28 V DC | 204PP NORM | 9TU ----------------------------------------------------------------------------
**ON A/C 151-199, 201-210,
(Ref. Fig. 003A)
The DMU is connected to the 115 V AC bus via the circuit breaker 4TV (AIDS). The maximum of power consumption and the busbar connections are as listed below. The DAR is connected to the 115 V AC bus via the circuit breaker 4TV and 28 V DC bus via circuit breaker 9TU.
----------------------------------------------------------------------------COMPONENT | PWR.CONS. | VOLTAGE | BUSBAR | C/B
----------------------------------------------------------------------------DMU | 40 W | 115 V AC | 202XP NORM | 4TV DAR | 50 W | 115 V AC | 202XP NORM | 4TV
| | 28 V DC | 204PP NORM | 9TU ----------------------------------------------------------------------------
R **ON A/C 106-149, 151-199, 201-299, 301-399, 401-499,
5. Interface
_________
R **ON A/C 106-149, 211-299, 301-399, 401-499,
A. Architecture of Inputs The FDIMU is connected to various source systems to collect the whole parameter set. The block diagram of input sources (Ref. 31-37-00) shows the connection of the FDIMU to its related sources.
B. FDIMU (DMU-Part) Input Sources
(1) The following systems are connected to the FDIMU (DMU-PART):
(a) Air Conditioning (ATA 21)
-Pressure Controller (11HL, 12HL)
-Zone Controller (8HK)
-Pack Controller (7HH, 27HH).
R 1EFF : 106-149, 151-199, 201-299, 301-399, 1 31-36-00Page 17 1401-499, 1Config-2 Aug 01/05 1 1 1CES 1
R AIDS - Power Supply Figure 003A
R 1EFF : 1 1 1CES 151-199, 201-210, 1 111 Page 1831-36-00 Config-2 May 01/05
(b) Auto Flight (ATA 22)
-Multipurpose Control and Display Unit (3CA1, 3CA2)
-
Flight Control Unit (2CA)
-
Flight Augmentation Computer (1CC1, 1CC2)
-
Flight Management, Guidance and Envelope Computer (1CA1, 1CA2).
(c) Communication (ATA23)
-Aircraft Communications Addressing and Reporting Management Unit (1RB1).
(d) Flight Controls (ATA 27)
-Flight Control Data Concentrator (3CE1, 3CE2)
-Slat and Flap Control Computer (21CV, 22CV).
(e) Fuel (ATA 28)
-Fuel Quantity Unit (3QT).
(f) Indication/Recording (ATA 31)
-Display Management Computer (1WT1, 1WT2)
-Flight Warning Computer (1WW1, 1WW2)
-System Data Acquisition Concentrator (1WV1, 1WV2)
-Flight Data Interface Unit (2TU).
(g) Landing Gear (ATA 32)
-Break System Control Unit 1, 2 (10GG)
-Landing Gear Control and Interface Unit (5GA1, 5GA2).
(h) Navigation (ATA 34)
-Ground Proximity Warning Computer (1WZ)
-Air Data/inertial Reference Unit (1FP1, 1FP2).
(i) Pneumatic (ATA 36)
-Bleed Monitoring Computer (1HA1, 1HA2).
(j) Onboard Maintenance System (ATA 45)
-Central Fault Display Interface Unit (1TM1)
-Printer (2TP).
(k) Airborne Auxiliary Power (ATA 49)
-Electronic Control Box (59KD).
(l) Engine Fuel and Control (ATA 73)
-Engine Vibration Monitoring Unit (2EV)
-Electronic Engine Control/Engine Control Unit Eng 1, Eng 2 (4000KS).
R 1EFF : 106-149, 211-299, 301-399, 401-499, 1 31-36-00Page 19 1 1 Config-2 Aug 01/05 1 1 1CES 1
C. Summary of Input/Output Data The connection between the related computers and the FDIMU (DMU-part) is shown in the AIDS Inputs - Schematic. The summary of the input pin assignment is shown:
-
For FDIMU (DMU-part) bus outputs - Table 1
-
For FDIMU (DMU-part) bus inputs - Table 2
-
For FDIMU ETHERNET provision - Table 3
-
For FDIMU (DMU-part) DITS inputs - Table 4
-
For FDIMU (DMU-part) discrete inputs - Table 5
-
For FDIMU (DMU-part) discrete outputs - Table 6
-
For FDIMU power supply and ground pins - Table 7
-
For FDIMU test connector pin assignment - Table 8.
R 1EFF : 106-149, 211-299, 301-399, 401-499, 1 31-36-00Page 20 1 1 Config-2 Aug 01/05 1 1 1CES 1
-------------------------------------------------------------------------------
| CONNECTOR | PIN | TYPE | SPEED | DESTINATION | PORT NO |
| | HI | LO | | HI | LO | | |
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