ENGINE FIRE EXTINGUISHING SYSTEM – TROUBLE SHOOTING
1. General
A. Whenever the fire protection module (P8-1) is removed and replaced, a test must be performed on the engine fire extinguishing system (Ref 26-21-0, A/T).
2. Equipment and Materials
A. Ohmmeter incapable of supplying more than 35 milliamperes.
WARNING: CURRENT FLOW EXCEEDING 35 MILLIAMPERES MAY DETONATE THE BOTTLE DISCHARGE SQUIB.
3. Trouble Charts
With all IND LIGHTS, SEC 1, and SEC 5 circuit breakers on P6-3 closed.
RIGHT OR LEFT BOTTLE DISCH LIGHT IS ON – Pressure is low. Replace respective bottle.
T52380
554
May 20/82 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 26-21-0 Page 101
500
26-21-0 Page 102 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 20/82
ENGINE FIRE EXTINGUISHING SYSTEM - ADJUSTMENT/TEST
1. Engine Fire Extinguishing System Test
A. Tubing Leakage Test
NOTE: This test should be performed when discharge tubing has been disturbed.
(1)
Equipment and Materials
(a)
Source of dry compressed air - regulated to 35 (±5) psig equipped with a pressure gage
(b)
Leak Detection Bubble Solution - TDL 28B
(c)
Electrical power source - 28 volts dc
(2)
Prepare for Test
(a)
Disconnect bottle discharge lines from bottle discharge plugs.
WARNING: BOTTLE DISCHARGE PLUG CONNECTOR MUST BE DISCONNECTED. OPERATION OF FIRE SWITCH WILL DETONATE EXPLOSIVE CHARGE IF CONNECTOR IS NOT REMOVED FROM DISCHARGE PLUG.
(b)
Cap right bottle discharge line.
(c)
Cap or plug fire extinguishing discharge lines at No. 1 and 2 engines.
(d)
Disconnect electrical connectors D590 and D592 at engine selector valves.
(e)
Connect supply of compressed air to left bottle discharge line.
(3)
Test for Leakage
(a)
Supply pressure to discharge lines.
(b)
Actuate both engine selector valves to open by applying 28 volts dc to electrical connector of each solenoid. Do not energize solenoids for more than 15 seconds at a time.
CAUTION: ENERGIZING SOLENOIDS FOR MORE THAN APPROXIMATELY 15 SECONDS WILL DAMAGE SOLENOIDS.
(c)
Apply bubble solution to tubing connections and seals. There shall be no leakage.
(d)
If engine selector valves close prior to end of test, repeat steps (b) and (c) until test is complete.
(4)
Restore Airplane to Normal
(a)
Disconnect air source and remove plug from discharge lines.
(b)
Connect electrical connectors D590 and D592 to engine selector valves.
(c)
Remove cap or plug from engine No. 1 and 2 discharge lines.
501
May 01/00 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 26-21-0 Page 501
B. Tubing Continuity and Electrical Circuit Test
(1)
Equipment and Materials
(a)
Test box, Boeing F80229
(b)
Source of compressed air - regulated to 35(+5) psig, equipped with a pressure gage.
(2)
Prepare for Test
(a)
Disconnect electrical connectors D582 and D584.
WARNING: ALL BOTTLE DISCHARGE PLUG CONNECTORS MUST BE DISCONNECTED. OPERATION OF FIRE SWITCH WILL DETONATE EXPLOSIVE CHARGES IF CONNECTORS ARE NOT REMOVED FROM DISCHARGE PLUGS.
(b)
Install shunt plug to fire extinguisher bottle squibs.
(c)
Disconnect connectors D586 and D588 at bottle pressure switches.
(d)
Check that EXTINGUISHER BOTTLES RIGHT and EXTINGUISHER BOTTLES LEFT circuit breakers on panel P6-2 and all IND LIGHTS, SEC 1, and SEC 5 circuit breakers on P6-3 are closed.
(e)
Disconnect both discharge lines from bottle discharge plugs.
(f)
Connect test box to each electrical connector D582 and D584.
(g)
Connect source of compressed air to fwd bottle discharge hose.
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 防火 FIRE PROTECTION(64)
