(c)
Make sure there is wire clearance and protection from chafing against the edges of the backshell connectors and screws on the backs of the fueling quantity indicators. 1) If it is necessary, loosen and turn the backshell connectors to give clearance
from the wires, and then tighten them.
(d)
Install protective sleeves around wires where the wires are routed close to sharp edges and objects on the back of the fueling control panel (SWPM 20-10-18).
CAUTION: DO NOT SHRINK THE SLEEVES WITH HEAT. THE TEFLON WRAPPING SLEEVE USED IN THIS APPLICATION IS A NON-SHRINKABLE TYPE. HEAT CAN DAMAGE THE WIRE INSULATION UNDER THE SLEEVE.
1) Where it is necessary, replace the Teflon wrapping sleeve and add a new sleeve to protect the wires from chafing.
2) For more protection, wires that are routed near sharp edges can be wrapped with one more layer of Teflon sleeve.
(8)
Re-install the fueling control panel.
(a)
Put the fueling control panel in position between the support members for the leading edge.
(b)
Install the screws in the fueling control panel to attach it.
(9)
Install the bonding jumpers to the fueling control panel.
(10)
Do a check of the electrical bond between the fueling control panel and the airplane structure (SWPM 20-20-00).
(a) Make sure the resistance is 0.001 ohm or less.
(11)
Install the pins and washers that attach the linkages to the access door.
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28-41-61 Page 402 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/03
B. Install the Fueling Quantity Indicator
(1)
Remove the tag and connect the electrical connector to the correct installation location as identified by the tag, of the indicator being installed.
(2)
Remove the DO-NOT CLOSE tags and close these circuit breakers:
(a) On the circuit breaker panel, P6:
1) QTY
2) EP GND FUELING
(3)
Do the fueling quantity indicator FULL adjustment on non-precalibrated indicators (AMM 28-41-0/501).
(4)
Install the fueling quantity indicator in the P15 panel.
(5)
Tighten the clamp screw on the fueling quantity indicator.
(6)
Close the access door for the refueling control panel.
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May 01/03 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 28-41-61 Page 403
FUEL SUMMATION UNIT -ADJUSTMENT/TEST
1. General
A. The fuel summation unit (FSU) on P23 panel totalizes fuel quantity signals from the fuel tanks.
B. System adjustment or calibration consists of adjusting the FSU to obtain an empty tank and full tank fuel quantity readout on the control display unit (CDU) of the performance data computer system (PDCS) (Ref Chapter 34).
C. Total fuel quantity readout is obtained from the readings of the fuel quantity indicator(s), therefore accuracy of CDU readout is no better than the accuracy of the individual fuel quantity indicators. If there is any doubt as to the accuracy of any of fuel quantity indicators, perform fuel quantity indicator system adjustment checks (Ref 28-41-05 A/T) prior to performing any adjustment checks of this section.
2. Equipment and Materials
A. System Tester (One of following)
(1)
Model GTF-2, P/N 361-012-001, Gull Airborne Instruments Inc., 55 Engineers Road, Smithtown, New York 11787.
(2)
P/N 472090-007, 472090-009 or PSD 40-1, Simmonds Precision Products Inc., Panton Road, Vergennes, Vermont 05491
(3)
Model 8000, Barfield Instrument Corp., Miami, Florida 33142
B. Test Harness (One of following)
NOTE: Quality of test cabling must be controlled, especially in regard to stray capacitance. Stray capacitance for test cables shall be less than 0.2 pf.
(1)
F72731-82
(2)
467-177-007, -008 Gull Airborne
(3)
P/N 464534, Simmonds
(4)
P/N 101-00542, Barfield
C. Leading Edge Flap Actuator Locks -F80048
5C1
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3. Fuel Summation Unit - Adjustment
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