Pylon Fire Detectors - Component Location
Figure 002
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Fan Fire Detectors - Component Location
Figure 003
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Core Fire Detectors - Component Location
Figure 004 (SHEET 1)
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Core Fire Detectors - Component Location
Figure 004 (SHEET 2)
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3. System Description__________________ (Ref. Fig. 005)
The fire detection system is of the electro-pneumatic type. On each engine, there are two continuous loops for the fire detection.
The loops are connected in parallel to a Fire Detection Unit (FDU). The connection is made through an AND logic to avoid spurious FIRE warnings.
In case of failure of one loop, the AND logic becomes an OR logic. The
aircraft can be released in this configuration.
The fire detection loops are monitored by the FDU. The monitoring device indicates the loss of a fire detection loop to the crew members (Flight Warning System).
For one engine, each loop:
-comprises three fire detectors connected in parallel. The detectors are installed in the nacelle and pylon fire zones.
-
is connected to a separate channel of the FDU
-
is connected through the related channel, to four of the eight lamps in a red warning light common to the two loops. This warning light is integral with the ENG 1(2) FIRE pushbutton switch located on the ENG/APU FIRE panel (overhead panel).
The fire detection system can be tested using the TEST pushbutton switch on the ENG/APU FIRE panel.
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Simplified FIRE Warning - Schematic
Figure 005
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4. Power Supply____________
The engine fire and overheat detection system gets the electrical power from the DC system of the aircraft.
A. Circuit Breakers
The system is supplied through these circuit breakers:
-------------------------------------------------------------------------------FIN PANEL/LOCATION DESIGNATION BUS ATA REF. -------------------------------------------------------------------------------7WD1 49VU A06 ENGINE/1/FIRE DET/LOOP A 401PP 26-12-00 8WD1 121VU Q38 ENGINE/ENG1/FIRE DET/LOOP B 202PP 26-12-00 7WD2 121VU Q39 ENGINE/ENG2/FIRE DET/LOOP A 202PP 26-12-00 8WD2 49VU A07 ENGINE/2/FIRE DET/LOOP B 401PP 26-12-00 -------------------------------------------------------------------------------
5. Interface_________
The engine fire detection system has an interface with the following
systems:
-Electrical Power: DC Ancillary Equipment (Ref. 24-68-00),
-Centralized Fault Display Interface Unit (CFDIU) (Ref. 31-32-00),
-Flight Warning Computer (FWC) (Ref. 31-52-00),
-Landing Gear Control and Interface Unit (LGCIU) (Ref. 32-31-00),
-Annunciator Light Test and Dimming (Ref. 33-14-00),
-Functional Interfaces (Ref. 73-25-00).
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6. Component Description
_____________________
R The components of the fire detection system are for one engine:
-an ENG/APU FIRE panel on the overhead panel with:
. one ENG FIRE pushbutton switch,
. one TEST pushbutton switch,
-two fire detection loops installed in parallel in the fire zones and connected to a Fire Detection Unit (FDU). Each fire detection loop comprises three detectors connected in parallel.
- one FDU per engine, which processes signals from the detectors
A. ENG/APU FIRE panel (1WD)
(Ref. Fig. 006)
(1) ENG 1(2) FIRE pushbutton switch
The ENG 1(2) FIRE pushbutton switch can be pushed only if the safety guard is open.
Each pushbutton switch has three main functions:
-indicate the FIRE warning generated by the Fire Detection Unit,
-activate the microswitches involved in the extinguishing procedure, and
-arm the discharge function for bottles 1 and 2.
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