(2)  
Test Harnesses

NOTE:  Quality of test cabling must be controlled, especially in regard to stray capacitance. Stray capacitance for test cables shall be less than 0.1 pf.
(a)  
F72731-82 or Gull Airborne 467-177-007, -008

(b)  
P/N 464534, Simmonds Precision Products Inc.

(c)  
P/N 101-00542, Barfield Instrument Corp.

(3)  
Five gallon container

(4)  
Leading Edge Flap Actuator Locks - F80048-89 (Preferred), F80048-90 (Preferred), F80048-84 (Alternate), and F80048-36 (Alternate)

C.  Prepare Fuel Quantity Indicating System for Adjustment
(1)  
Provide electrical power (AMM 24-22-0/201).

(2)  
Extend flaps and install leading edge flap locks (AMM 27-81-0/201).

WARNING:  REFER TO AMM 27-81-0/201 FOR LOCK INSTALLATION PROCEDURE. FLAPS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONS.
580 
May 01/00  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  28-41-0 Page 511 

D.  Adjust Fuel Quantity Indicating System
(1)  Adjust indicators to read zero.
(a)  
Open EP GRD FUELING and fuel QTY circuit breakers on circuit breaker panel P6.

(b)  
Disconnect tank and compensator unit bussing plug for applicable tank (Fig. 501).

(c)  
Connect test harness into airplane circuit (Fig 502, Detail B).

NOTE: Test harness wire connections are identified as follows:
WM - No. 1 and 2 main tanks WC - Center tank
(d)  
Connect system tester to test harness.

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

(f)  
Warm up system for five minutes.

(g)  
Adjust system tester compensator unit variable capacitor (COMP) and tank unit variable capacitor (PROB) to the respective EMPTY capacitance values stamped or imprinted on nameplate at rear of indicator. 1) If EMPTY capacitance values do not appear on nameplate or are considered

obsolete, use nominal values as shown in Table 1.
FUEL TANK  NOMINAL EMPTY CAPACITANCE VALUES 
TESTER SETTING TANK UNIT (PROB)  TESTER SETTING COMPENSATOR UNIT (COMP) 
No. 1, 2 Center Tank (Integral)  458.2 pf 164.2 pf  39.0 pf 39.0 pf 

TABLE 1
(h)  
On center instrument P2, adjust applicable fuel quantity indicator to read zero ±25 pounds by means of empty adjustment screw at rear of indicator.

NOTE: Due to gear train backlash, adjust to zero in an increasing quantity direction.

(i)  
Press to test indicator test button; indicator pointer or dial shall move downscale. Release test button indicator pointer or dial shall return to adjusted zero position ±25 pounds.

(j)  
If any indicator pointer or dial does not return to adjusted zero position after press-to-test operation, repeat steps (h) and (i).

NOTE:  Because of indicator construction, it is usually impossible to adjust indicators to read zero exactly, but only within tolerances specified.

(k)  
Open fueling station access door.

558 
28-41-0 Page 512  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Oct 20/85 

(1)  Corresponding fueling quantity indicators on fueling control panel P15 should read as shown in Table 2.
FUEL QUANTITY INDICATOR - P15 PANEL 
FUEL TANK  READING 
Fuel Tank No. 1, 2  Zero +100 lbs 
Center Tank (Integral)  Zero +130 lbs 

TABLE 2
NOTE:  The fueling quantity indicators on fueling control panel cannot be "empty" adjusted due to their use as repeaters.
(2)  
Check indicator adjustment

(a)  
Place fueling quantity indicator test switch to TEST GAGE position and check that indicators respond as follows: 1) Fueling quantity pointers shall move downscale. 2) Fuel quantity indicator pointers may or may not move when original reading is

zero. Movement, if any, may be upscale or downscale.

(b)  
Release test switch and check that indicators respond as follows: 1) Fuel and fueling indicator pointers return to original position + 50 pounds.

(3)  
Adjust indicators to read full.

581 
May 15/79  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  28-41-0 Page 513 

(a)  Adjust system tester compensator unit variable capacitor (COMP) and tank unit variable capacitor (PROBE) to the respective full capacitance values as shown in Table 3.
SYSTEM TESTER NOMINAL FULL SUBSTITUTION VALUES 
　
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(164)