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D633A101-GUN Oct 10/2002
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
26-11-00-001
FIRE PROTECTION - ENGINE FIRE DETECTION - INTRODUCTION
FIRE PROTECTION - ENGINE FIRE DETECTION - INTRODUCTION
EFFECTIVITY
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D633A101-GUN Feb 10/2003
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
26-11-00-001
General Description
These are the components for engine overheat and fire:
* Engine overheat/fire detector (loop A and loop B)
* Engine and APU fire detection module
* Glareshield, P7 panel
* Engine and APU fire control panel
* Aural warning unit.
Overheat/fire detectors on the engine send signals to the
engine and APU fire detection module. This module will supply
aural and visual indications in the flight compartment.
The engine and APU fire detection module gives visual
indications for detector faults on the module and the engine
and APU fire control panel panel.
Overheat/fire test
You use the TEST switch on the engine and APU fire control
panel. In the OVHT/FIRE position, the indications in the flight
compartment are the same as for the real fire condition. If the
test fails, use the engine and APU fire detection module to
isolate the fault.
NOTE: During the engine overheat/fire test, the APU fire and
wheel well fire circuits are also tested.
Fault/inop test
You use the TEST switch on the engine and APU fire control
panel. In the FAULT/INOP position, the indications in the flight
compartment are the same as a real fault condition. If the test
fails, use the engine and APU fire detection module to isolate
the fault.
NOTE: During engine fault test, the APU fire detector fault
circuit is tested.
Single Loop Operation
If an engine overheat/fire detector fails to operate, the engine
and APU fire detection module automatically changes to single
loop operation. In the single loop mode, only one loop must
detect an overheat or fire condition for the engine and APU fire
detection module to give the alarm condition.
There is no indication in the flight compartment of single loop
operation until you do the OVHT/FIRE test.
FIRE PROTECTION - ENGINE FIRE DETECTION - GENERAL DESCRIPTION
EFFECTIVITY
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Page 4
D633A101-GUN Oct 10/2002
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
26-11-00-006
FIRE PROTECTION - ENGINE FIRE DETECTION - GENERAL DESCRIPTION
FIRE PROTECTION - ENGINE FIRE DETECTION - GENERAL DESCRIPTION
EFFECTIVITY
GUN ALL 26-11-00
Page 5
D633A101-GUN Feb 10/2003
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
26-11-00-006
Purpose
The engine fire detectors monitor for high temperatures in the
engine area.
General Description
Each engine has eight detectors. The detectors monitor four
sections of the engine. In each section, two detectors attach to a
support tube and make an assembly. An assembly has one
detector from loop A and one from loop B.
Physical Description
The engine fire detectors have these parts:
* Overheat, fire, and fault pressure switches
* Resistors
* Terminal stud
* A stainless steel, gas charged tube.
Location
These are the locations of the engine fire detectors:
* Two on the upper fan case section
* Two on the lower fan case section
* Two on the left core section
* Two on the right core section.
Detector Characteristics
This table shows the temperature characteristics of the
detectors.
Detector Location Overheat Fire
Upper Fan Case 345F (174C) 580F (304C)
Lower Fan Case 345F (174C) 580F (304C)
Left Core Section 650F (343C) 850F (454C)
Right Core section 650F (343C) 850F (454C)
Operation
The three pressure switches sense these conditions:
* Overheat
* Fire
* Fault (loss of gas pressure).
Gas pressure in the sense tube holds the fault pressure switch
in the closed position. The other two pressure switches close
when the gas pressure increases because of an overheat or fire
condition.
The overheat and fire signals go to the engine and the APU fire
detection module. This module supplies overheat or fire
indication in the flight compartment.
If the pressure in the sense tube decreases, the fault switch
opens. This switch sends the fault signal to the engine and APU
　
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