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A
737-300/400/500MAINTENANCE MANUAL
 4) Adapter cables (fabricated locally):
 a)  Adapter cables - 50 ohm, unshielded, with polarized BNC plug (Amphenol 14625) to connect to the Lo-Z receptacles of the test unit and polarized BNC jack (Kings LC-33-02) to connect to the tee connector, two are necessary.
 NOTE: Shielded cables on Lo-Z connections can
____ cause EMI problems.
 b)  Adapter cable - 50 ohm, with BNC plug (Amphenol 31-202) to connect to the Hi Z receptacle on the test unit and a BNC receptacle (AMP 330885) to connect to the tee connector.
 5)  Ground cable
 B.  References
 (1)
AMM 24-22-00/201, Manual Control

 (2)
AMM 27-81-00/201, Leading Edge Flaps and Slats

 (3)
AMM 28-23-00/201, Defueling

 (4)
AMM 28-41-81/401, Fuel Summation Unit

 C.  Access
 (1)  
Location Zones
 101 Control Cabin, Left
 217 Right Main Wheel Well
 303 Left Wing Inboard Leading Edge
 402 Right Wing Outboard Leading Edge
 403 Right Wing Inboard Leading Edge

 (2)  
Access Panels
 6540 Refueling Station Access Door

 

 D. Prepare for the System Test ú ú S 865-030-002 ú (1) Supply electrical power (AMM 24-22-00/201).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH SIMMONDS DIGITAL FUEL ú
 28-41-02 QUANTITY INDICATORS ú CONFIG 2
 ú 01.1 Page 518 (SIMMONDS SYSTEM TESTER) ú Jul 12/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 S 865-060-002
 WARNING:_______ MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE LE AND TE FLAPS AND FLAP DRIVE MECHANISMS BEFORE YOU MOVE THE FLAPS. THE FLAPS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
 ú  (2)  Extend the leading edge flaps (AMM 27-81-00/201).
 S 495-032-002
 WARNING:_______ YOU MUST CAREFULLY DO THE STEPS IN THE TASK BELOW TO INSTALL THE LE FLAP SAFETY LOCKS. THE LE FLAPS CAN MOVE QUICKLY IF YOU DO NOT INSTALL THE SAFETY LOCKS CORRECTLY. CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT. THIS
 ú  (3)  Install locks on the leading edge flaps (AMM 27-81-00/201).
 ú  (4)  S 655-033-002Remove all fuel from the fuel tank, and the fuel in the sumps(AMM 28-23-00/201).
 ú ú  NOTE:____ If you do the trim for only one tank system, you can movethe fuel into the other tanks.
 (5)  S 865-034-002Open these circuit breakers and attach DO-NOT-CLOSE tags: (a) P6 Main Power Distribution Panel 1) QTY 2) EP GND FUELING
 (6)  S 015-035-002Remove the fuel quantity indicator from the pilots' panel.
 ú ú ú  (7) (8)  S 035-036-002Disconnect the electrical connector from the rear of the indicator.S 485-037-002Connect the test equipment (Fig. 504). (a) Connect the test harness to the airplane wire bundle. (b) Connect the test harness to the test unit.
 (9)  S 015-055-002Do this task:  Fuel Summation Unit Removal (AMM 28-41-81/401).

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH SIMMONDS DIGITAL FUEL ú
 28-41-02 QUANTITY INDICATORS ú CONFIG 2
 ú 01.1 Page 519 (SIMMONDS SYSTEM TESTER) ú Jul 12/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
FUNCTION MEASURE SWITCH
DO NOT

TO
CONNECT TO
COMPENSATOR
FUEL
AND TANK
QUANTITY
UNITS
INDICATOR
SIMMONDS PSD60-1 SYSTEM TESTER
SIMMONDS PSD40-1 SYSTEM TESTER
TANK  ADAPTER CABLES 
WING  PSD40-502-3 
CENTER  PSD40-502 

Test Equipment Set-Up for Resistance Measurement
Figure 504 (Sheet 1)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH SIMMONDS DIGITAL FUEL ú
 28-41-02 QUANTITY INDICATORS ú CONFIG 2
　
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