G42624
Measuring Stick Assembly 500
28-41-11 Figure 801 Oct 20/93
Page 802
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
TANK UNITS AND COMPENSATOR UNITS - REMOVAL/INSTALLATION
1. General
A. The removal/installation of the tank units and compensator units are basically the same; the differences are in locations and access openings, shown in Fig. 401.
2. Remove Tank Unit or Compensator Unit (Fig. 401)
A. Defuel and purge applicable fuel tank (Ref 28-23-0, 28-10-0, Maintenance Practices).
B. Open GRD FUELING and FUEL QTY circuit breakers on P6 panel.
C. Obtain access to tank or compensator unit through applicable fuel tank access panel opening and rib access openings (Ref 28-11-11, 28-11-31).
D. Disconnect leads and loosen wire clamp on unit.
E. Remove unit mounting screws and remove unit.
CAUTION: HANDLE UNITS WITH CARE. DROPPING CAN DAMAGE CAPACITANCE CHARACTERISTICS OF UNIT.
3. Install Tank Unit or Compensator Unit (Fig. 401)
A. Position tank or compensator unit and install mounting screws.
B. Connect leads and tighten clamp on unit. Tighten screws/nut to following torque ranges:
H1 Z (COAX) 15-16 pound-inches LOW Z (TANK) 19-23 pound-inches Wire Clamp 7-9 pound-inches
C. After installation, check each terminal to ensure that the screw firmly holds the terminal from turning.
NOTE: It is necessary for unit leads to have a drip loop as shown in illustration. Water droplets tend to accumulate on lead and run down on unit terminals. Drip loop is used to prevent this.
D. Install fuel tank access panel (Ref 28-11-11, 28-11-31).
E. Perform adjustments of related components (Ref 28-41-0 or 28-41-05, A/T).
532
Jun 20/83 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 28-41-21 Page 401
F95189
Tank Unit and Compensator Unit Installation 538
28-41-21 Figure 401 Apr 01/97
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
TANK UNIT AND COMPENSATOR UNIT - ADJUSTMENT/TEST
1. Tank Unit and Compensator Unit Test
A. Equipment and Materials
(1)
System Tester
(a)
Model GTF-2, P/N 361-012-001, Gull Airborne Instruments, Inc., 55 Engineers Road, Smithtown, New York, 11787
(b)
P/N 472090-007, 472090-009, or PSD 40-1, Simmonds Precision Products Inc., Panton Road, Vergennes, Vermont, 05491
(c)
Model 8000, Barfield Instrument Corp., Miami, Flordia 33142
(2)
Test Harness
(a)
F72731-81 (tanks, 1, 2, and center on ALL EXCEPT airplanes with AFCS, and tanks 1 and 2 on airplanes with AFCS)
(b)
F72731-102 (center tank on airplanes with AFCS)
(3)
Leading Edge Flap Actuator Locks - F80048-36
B. Test Tank Unit and Compensator Unit Resistance and Capacitance
(1)
Defuel airplane or defuel applicable fuel tank only, and drain sump fuel (Ref 28-23-0 MP).
(2)
For testing tank No. 1 or 2 units, extend flaps and install leading edge flap locks (Ref 27-81-0 MP).
WARNING: REFER TO 27-81-0 MP FOR LOCK INSTALLATION PROCEDURE. FLAPS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONNEL.
(3)
Open EP GRD FUELING and fuel QTY circuit breakers on aft overhead panel (P6) and maintain open position for duration of test.
CAUTION: DO NOT APPLY ELECTRICAL POWER WITH OPEN CIRCUIT BETWEEN TANK UNITS AND FUEL QUANTITY INDICATORS. OPEN CIRCUITED TANK UNITS DRIVE QUANTITY INDICATOR POINTERS AGAINST STOP, AND CONTINUED RUNNING WILL DAMAGE INDICATOR CLUTCH.
(4)
At wing front spar or rear of center tank, remove applicable bussing plug from bulkhead receptacle (Ref 28-41-41 R/I).
CAUTION: BE EXTREMELY CAREFUL WITH CONNECTOR PINS AND/OR SOCKETS. CONNECTOR RECEPTACLE IS PART OF TANK WIRING HARNESS. DAMAGE TO RECEPTACLE WILL NECESSITATE REMOVAL OF COMPLETE ASSEMBLY.
(5)
Connect kit test harness adapter plug to tank and compensator unit receptacle and secure plug with two bolts (Fig. 501).
(6)
Connect system tester to test harness (Fig. 501).
(7)
Measure insulation resistance of each tank unit and compensator unit. Resistance shall not be less than shown in Fig. 502, Table A.
(8)
Measure capacitance of each tank unit and compensator unit. Capacitance should be as shown in Fig. 502, Table B.
(9)
Remove test harness adapter plug bolts and remove plug.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 燃油 FUEL(174)
