(4) 
 5-Gallon Container

(5)  
Rubber Stamp Set (numerals)

(6)  
Cado Pencil or Speedry Type A Ink

(7)  
Leading Edge Flap Actuator Locks - F80048-36

C.  Prepare Fuel Quantity Indicating System for Adjustment
(1)  
Supply 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.

(3)  
Defuel airplane for adjustment of entire system, or defuel applicable fuel tank, and drain sump fuel (AMM 28-23-0/201).

WARNING:  TO PREVENT POSSIBILITY OF EXPLOSION, DO NOT REMOVE ANY FUEL TANK ACCESS PANELS WHILE ELECTRICAL POWER IS BEING USED.

(4)  
Open FUELING & EXT PWR CONTROL circuit breaker on circuit breaker panel P6.

(5)  
Check that GRD FUELING and BUS PROTECTION PANEL circuit breakers on circuit breaker panel P6 are closed.

(6)  
On center instrument panel, loosen fuel quantity indicator clamp screws and remove indicator from panel far enough to obtain access to rear cover locking screws.

(7)  
Remove lockwire and loosen screws.

(8)  
Obtain access to indicator adjustment screws by holding indicator and turning rear cover clockwise.

(9)  
Replace indicator into center instrument panel, but do not tighten clamp screw.

(10)
Repeat steps (6) thru (9) for other fuel quantity indicators.

(11)
Repeat steps (6) thru (9) for fueling quantity indicators on fueling control panel P15.

(12)
Close fueling station access door.

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Jun 20/85  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  28-41-0 Page 503 

D.  Adjust Fuel Quantity Indicating System (Fig. 501)
(1)  Adjust system to read zero.
(a)  
Close FUELING & EXT PWR CONTROL circuit breaker on panel P6.

(b)  
Warm up system for 5 minutes.

(c)  
On center instrument panel, adjust each fuel quantity indicator to read zero + 25 lbs (kgs) by means of empty adjustment screw at rear of indicator.

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

(d)  
Press-to-test indicator test button; indicator pointer shall move down scale. Release test button; indicator pointer shall return to adjusted zero position + 25 lbs (kgs).

(e)  
If any indicator pointer does not return to adjusted zero position after press-to-test operation, repeat steps (c) and (d).

(f)  
Record fuel quantity indicator actual fuel weight readings.

NOTE:  Because of indicator construction, it is usually impossible to adjust indicators to read zero exactly, but only within tolerances specified. To perform adjustment/test to greatest accuracy possible, it is necessary to record the actual fuel weight readings for determination of empty and full capacitance values.

(g)  
Open fueling station access door.

(h)  
Corresponding fueling quantity indicators on fueling control panel should read as shown in Table 1.

INDICATOR  READING 
FUEL TANK No. 1 & 2  ZERO + 100 LBS 
CENTER TANK  ZERO + 100 LBS 

TABLE 1
NOTE:  The fueling quantity indicators on fueling control panel cannot be empty adjusted due to their use as repeaters.
(i)  Record fueling quantity indicator actual weight readings.
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28-41-0 Page 504  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jan 20/82 

(2)  
Check system adjustment.

(a)  
Place fueling quantity indicator test switch to TEST GAGES position and check that indicators respond as follows: 1) Fueling quantity indicator 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 lbs.

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

(3)  
Determine stray capacitance introduced by test harness:

(a)  
Disconnect fuel quantity indicator connector on tank and compensator bussing plug at front wing spar (tank 1 or 2), rear wing spar (center wing tank)(Fig. 501).

(b)  
Connect test harness into (subsystem) circuit (Fig. 502, Detail A).
　
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