「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : ALL ∞∞28-24-00∞∞∞∞∞∞∞∞∞∞Page 306
 Feb 01/98 CES

 LP Fuel Valve Closed (Eng/Master Switch On, Eng/Fire Pushbutton Operated)
 Figure 306

 「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : ALL ∞∞28-24-00∞∞∞∞∞∞∞∞∞∞Page 307
 Feb 01/98 CES

 REFUEL/DEFUEL SYSTEM - FAULT ISOLATION PROCEDURES
_________________________________________________
 TASK 28-25-00-810-801
 Refuel Valve Fails To Close On The Completion of a Refuel
 WARNING : OBEY THE FUEL SAFETY PROCEDURES.

_______
 CAUTION : DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM SAFE PRESSURE

_______
 OF 50psi (3.45bar).

 1. Possible Causes
_______________
 - VALVE-REFUEL, L WING TK (7QU)

 - VALVE-REFUEL, R WING TK (8QU)

 - VALVE-REFUEL, CTR TK (10QU) R - refuel valve solenoid R - aircraft wiring
 2. Job Set-up Information
______________________
 A. Fixtures, Tools, Test and Support Equipment
 -------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific multimeter
 B. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
R  ESPM 20-00-00
R  AMM 28-25-00-710-003 AMM 28-25-51-000-001 AMM 28-25-51-000-002 AMM 28-25-51-000-003  Operational Test of the Refuel SystemRemoval of the Refuel Valve 7QU, (8QU)Removal of the Refuel Valve 10QU Removal of the Solenoid Valve
R  AMM 28-25-51-400-001 AMM 28-25-51-400-002 AMM 28-25-51-400-003  Installation of the Refuel Valve 7QU, (8QU)Installation of the Refuel Valve 10QU Installation of the Solenoid Valve 
R  ASM 28-25/01
 3. Fault Confirmation__________________ 
R  A. Test 

R (1) Not applicable, the fault is evident. Do the fault isolation.
 「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : ALL ∞∞28-25-00∞∞∞∞∞∞∞∞∞∞Page 201
 Feb 01/05 CES

 4. Fault Isolation
_______________

R  A. Procedure 
R  NOTE : If the fuel tanker or fuel hydrant hose end pressure is more than____ 
R  the maximum safe pressure it can cause:
 - a refuel valve that has been commanded to shut, to be held open
 - damage to the refuel gallery.
 (1) Do a check of the fuel tanker or fuel hydrant hose end pressure.
 (2) If the fuel pressure is more than 50psi (3.45bar):
 - change the fuel pressure if possible or
 - get another source of fuel supplied at the correct pressure.
 (3) If the fault continues:
 - disconnect the electrical supply connector from the related
 refuel-valve. 
R  (4) Do a test, with a multimeter, to see if 28VDC is between pin A (+) 
R  and pin C (-). 
R  (5) If 28VDC is not detected in step (4): 
R  (a) Replace: 
R  1 The related refuel valve solenoid (Ref. AMM TASK 28-25-51-000-_ 
R  003) and (Ref. AMM TASK 28-25-51-400-003). 
R  2 If the fault continues, replace the applicable:_ 
R  - VALVE-REFUEL, L WING TK (7QU) (VALVE-REFUEL, R WING TK 
R  (8QU)), (Ref. AMM TASK 28-25-51-000-001) and (Ref. AMM TASK
 28-25-51-400-001) 
R  - VALVE-REFUEL, CTR TK (10QU), (Ref. AMM TASK 28-25-51-000-
R  002) and (Ref. AMM TASK 28-25-51-400-002). 
R  (b) Do the operational test of the refuel system (Ref. AMM TASK 28-
R  25-00-710-003), or continue the refuel. 
R  (6) If 28VDC is detected in step (4), do a check of the related aircraft 
R  wiring (Ref. ASM 28-25/01) (to locate the source of the 28VDC) 
R  between: 
R  - the refuel valve electrical supply connector, pin A and the 
R  RELAY/REFUEL-VALVE CONTROL, terminal A2. 
R 
R  (a) Repair all unserviceable wiring and connectors (Ref. ESPM 20-00-
R  00). 
R 
　
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