(b)
Deleted.
(c)
Wire End Fitting - 35303-10, Fenwal, Inc., Ashland, Mass.
NOTE: The wire end fittings are to be used for attachment of test equipment to the sensing elements during test procedures.
500
May 01/99 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 26-18-11 Page 501
LOOP CONNECTOR AND LOCATION SENSORS AND WIRING RESISTANCE (75oF) SENSORS
D858 Left forward A/C pack D856 Left aft A/C pack 6 ohms max. M274, M355
D854 Aft keel beam D848 Forward keel beam 6 ohms max. M272, M273
D866 Aft end of Section 58 D1070 Forward end of aft cargo compartment 12 ohms max. M275, M276, M347. M348 if installed M574
D832 Inboard left wing D1392 Left engine strut cavity 6 ohms max. M268, M370, M487
D846 Right aft A/C pack D1396 Right engine strut cavity 12 ohms max. M269, M271, M356, M371 & M488
NOTE: The resistance measurements are for the sensing elements and interconnecting airplane wiring, if applicable. Resistance measurements do not include sensor connector resistance.
Sensing Loop Test 500
26-18-11 Figure 501 May 01/00
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
B. Test Sensing Loop (Fig. 501)
(1)
Disconnect wire connectors from a loop.
(2)
Test for center conductor continuity by connecting multimeter to center conductor at each end of the loop. Resistance value should be per Fig. 501.
(3)
Connect connectors to elements, torque jamnuts 50 to 60 pound-inches, and lockwire.
(4)
Repeat steps (1) thru (3) for remaining loops.
C. Restore Airplane to Normal
(1)
Remove wire end fittings from loop connectors.
(2)
Connect connectors to sensing elements, torque jamnuts 50 to 60 pound-inches, and lockwire.
(3)
Install compartment overheat control module on rack in electrical/electronic equipment compartment.
500
May 01/99 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 26-18-11 Page 503
WING AND LOWER AFT BODY OVERHEAT DETECTION SENSING ELEMENT -INSPECTION/CHECK
1. General
A. Physically check each sensing element and electrical connector to determine whether and
faults have occurred to make the element unacceptable.
Wing and Lower Aft Body Overheat Detection Sensing Element Check
A. Check Sensing Element
(1)
Check that all diameter variation have smooth contours and that no abrasions or wear spots are deeper than 0.002 inch.
(2)
Check that no section of element has a diameter of less than 0.070 inch.
NOTE: Smoothly contoured dents and kinks which have not reduced tubing diameter beyond acceptable limits are not cause for replacement.
CAUTION: DO NOT ATTEMPT TO STRAIGHTEN ANY ACCEPTABLE DENT OR KINK, AS STRESSES SET UP IN TUBING MAY CAUSE A POSSIBLE FAILURE.
(3)
Check for any radial marks (nicks or gouges) that are more than 0.005 inch deep or extending more than 50% across seal face of end and electrical connectors.
NOTE: These gouges would prevent an adequate water vapor seal from being made when connectors are metal.
(4)
Check for dirt or other foreign substances on seal face of end connectors.
500
Aug 15/67 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 26-18-11 Page 601
CARGO COMPARTMENT SMOKE DETECTION SYSTEM - DESCRIPTION AND OPERATION
EFFECTIVITY
737-200 Passenger Airplanes Incorporating SB 26A1081
1. General
A. The cargo compartment smoke detection system is used to monitor smoke in the forward and aft cargo compartments. The system includes these parts:
(1)
Smoke Detectors
(2)
Cargo Electronic Units (CEU)
(3)
Cargo Fire Control Panel (P8)
B. The cargo compartment smoke detection system uses 28 volts dc power. The power is supplied through the circuit breakers on the P6 or P18 panel.
2. Component Details (Fig. 1)
A. Cargo Smoke Detector
(1)
Cargo Smoke detectors are installed in the ceiling of the forward and aft cargo compartment. A screen is installed over the smoke detector to keep it from being damaged. The smoke detectors are controlled and monitored by the CEUs. The smoke detectors send alarm signals and status signals to the CEUs.
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