(m)  
Open GRD FUELING and FUEL QTY circuit breakers on circuit breaker panel P6.

(n)  
Disconnect system tester from test set harness.

(o)  
Disconnect test set harness from subsystem circuit.

(p)  
Reconnect fuel quantity indicator connector plug to receptacle on tank and compensator unit plug.

(q)  
Repeat steps D.(3)(a) thru D.(5)(p) for remaining fuel tanks.

581 
May 01/01  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  28-41-05/80 Page 509 

(6)  
Check system empty adjustment.

(a)  
Close GRD FUELING and FUEL QTY circuit breakers on panel P6.

(b)  
Record fuel quantity and fuel weight readings. Compare these readings with corresponding indicator actual zero adjustment readings of step D.(1)(f). Both sets of readings should agree +50 pounds for fuel quantity indicators.

(c)  
Record fueling quantity indicator actual fuel weight readings. Compare these readings with corresponding indicator readings of step D.(1)(i). Both sets of readings shall agree (+50 lbs).

(d)  
If fuel weight readings in steps D.(6)(b) and D.(6)(c) do not agree, repeat steps D.(1)(c) thru D.(6)(c).

(e)  
Open GRD FUELING and FUEL QTY circuit breakers on panel P6.

(7)  
Record empty and full capacitance adjustment on indicators.

(a)  
Remove fuel quantity indicator from center instrument panel (P2) and disconnect plug.

(b)  
Remove previous capacitance data on indicator.

(c)  
Record EMPTY and FULL capacitance on indicator in space provided. 1) Use EMPTY capacitance data for corresponding indicator recorded for step D.(4)(f).

2  Obtain FULL capacitance data by summation of empty capacitance in step 1) above, and added capacitance shown in Table 3.

(d)  
Mark data using rubber stamp and Cado pencil or Speedry Type A ink.

(e)  
Hold indicator and turn rear cover of indicator counterclockwise.

(f)  
Tighten two cover locking screws.

(g)  
Lockwire screws and seal lockwire with sealing wax.

(h)  
Connect electrical plug to indicator.

(i)  
Replace indicator into panel and tighten indicator clamp screw.

(j)  
Repeat steps (a) thru (i) for other indicators.

(k)  
Remove fueling quantity indicator from fueling control panel and repeat steps (e) thru (i).

(l)  
Repeat step (k) for other fueling quantity indicators.

E.  Restore System To Normal
(1)  
Close FUELING AND EXT PWR CONTROL circuit breaker on panel P6.

(2)  
Remove leading edge flap locks (AMM 27-81-0/201).

WARNING:  LEADING EDGE FLAPS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONNEL

(3)  
Remove electrical power if no longer required (AMM 24-22-0/201).

581 
28-41-0 Page 510  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jan 20/82 

3.  Adjustment of Fuel Quantity Indicating System -Wet Tank Method (Alternate)
A.  General
(1)  
In this adjustment method (wet tank), empty capacitance substitution values are set into tester, after tank and compensator units are disconnected from indicator/tester circuit, and indicators are zero adjusted and rechecked. Tester is then reset to substitute capacitance values equivalent to indicator nominal full readings, corresponding weight readings are read on indicators, indicators are full adjusted as necessary and rechecked. It is preferable to use actual EMPTY and FULL capacitance substitution data if recorded on space provided on back of quantity indicator but if this data is missing, use nominal values provided on following pages.

(2)  
This method requires that fuel quantity system equipment installed inside tank (tank unit(s), compensator unit(s), wiring bundle, etc.) be disconnected in order to zero and full adjust indicators and therefore constitutes a possible error. Also, additional (stray) capacitance imposed by test equipment cannot be determined and accounted for, thus increasing chance of error. To ensure system integrity, use this method only when unable to use empty tank method (par. 2).

B.  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 PSD40-1, Simmonds Precision Products Inc., Panton Road, Vergennes, Vermont 05491

(c)  
Model 8000, Barfield Instrument Corp., Miami, Florida 33142
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊 燃油 FUEL(163)