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System Description
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WHITE MESSAGE Require immediate crew attention. These messages are accompanied by flashing master warning, triple chime attenson with or without voice message or dedicated tone. Require immediate crew awareness and future crew action may be required in the form of alternate system selection or performance limitation. These message are accompanied by flashing master caution and a single chime. Indicate safe or normal system operation which require crew awareness, over and above the dark cockpit philosophy. Indicate minor failures or reduction in systems capability, which require no crew action.

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Overview

The refuel/defuel system supplies the function for gravity refuelling, manual or automatic pressure refueling, and suction defueling operations.

Gravity refuelling is done through a gravity filler cap and port found on the top of each wing. Pressure refueling and suction defuelling is done through a refuel/defuel adapter connected to the refuel/defuel manifold. Two shutoff valves (SOVs) are installed on the refuel/defuel manifold to control the fuel flow to the wing tanks. A high level sensor in each tank prevents the wing tanks from being overfilled in the event of an automatic refuel failure. Grounding receptacles are supplied for electrically bonding the aircraft to the ground equipment.

Refuel/Defuel Control Panel

The refuel/defuel control panel controls pressure refueling and defueling operations on the aircraft. The control panel is above the refuel /defuel adapter on the right side of the aircraft forward of the wing root.

The power switch energizes the refuel/defuel system. A power indication lamp comes on when the system is energized. A striker plate on the access panel pushes the power switch to the off position when the access door is closed if personnel do not turn the switch off. When the LAMP TEST button is pushed, the lamps on the control panel are turned on to make sure they are serviceable.

The fuel selector rotary switch permits selection of automatic or manual refuel, aircraft defuel, and system test. Selection of FUEL AUTO permits the total required fuel load to be preselected and controlled automatically through the fuel quantity computer. The INC/DEC toggle switch increases or decreases fuel quantity selection, which is shown on the display above the switch. An ON/OFF toggle switch starts/stops the automatic refuel/defuel operation.

Note:
The refuel/defuel control-panel shows the quantity in imperial (Lbs) or in metric (Kg) if the optional metric control-panel is installed (SB 350-28-001).

Selection of FUEL MANUAL permits manual refuel of the aircraft with the SOV ON/OFF toggle switches. SOV OP and CL indicator lamps show when the refuel/defuel SOV is open (OP) or closed (CL). Two displays show the quantity of fuel in the left and right tank. The H LEVEL DETECTOR lamps above the displays indicate when the left or right high-level detector senses the tank is full.

Selection of DEFUEL permits suction defuel of the aircraft with the SOV ON/OFF toggle switches.

Selection of OFF on the rotary switch shuts down the refuel/defuel operation.

The refuel/defuel control panel also shows the engine oil level.

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refuel_defuel

Refuel/Defuel Adapter

The refuel/defuel adapter is found behind an access panel aft of the right wing root fairing below the refuel/defuel control panel. It is a manually operated poppet valve with a double sealing function. A refueling nozzle connects to the refuel/defuel adapter for refueling.

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Refuel/Defuel Manifold

The refuel/defuel manifold is on the front spar of the right wing tank between Ribs 0 and 1. It consists of a body, two refuel/defuel shutoff valves, two restrictors, a 0.03 inch diameter pressure relief orifice, and two flap valves. The restrictors are sized to provide a total refuel rate of 125 U.S. gal/min at 50 psig (473.16 L/min at 344.74 kPa) applied at the refuel/defuel adapter. The pressure relief orifice reduces the pressure between the shutoff valves and the adapter. The flap valves permit the removal and installation of the refuel/defuel shutoff valves without defueling the aircraft.

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Refuel/Defuel Shutoff Valve

Two refuel/defuel SOVs are in the refuel/defuel manifold. Each SOV consists of a control solenoid, valve position switch, piston, and spring. It also has a manual override to refuel without electrical power. Fuel flows from the adapter into the refuel/defuel manifold housing and through the two SOVs, and then out of the refuel/defuel manifold housing through two ports that are connected to the tanks by 1.5 inch (38.10 mm) tubing. Access to the refuel/defuel shutoff valves is through the wing-to-fuselage fairing.

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System Operation

The usual mode of operation for the refuel/defuel control panel is automatic, with the selection of FUEL AUTO on the refuel/defuel control panel. The total aircraft fuel quantity is selected on the 5-digit display and the tank switches are set to ON to start the refuel operation. The fuel quantity computer closes the refuel/defuel SOVs automatically when the fuel is at the set quantity. During refuel, digital fuel quantity indications and status information about the refuel/defuel SOVs (open or closed) and high-level sensors (wet or dry) are shown on the refuel/defuel control panel.

When the manual mode is selected, the personnel control the fuel load. They monitor the left and right tank fuel quantity displays and operate the SOV ON/OFF switches when needed.

When the operator removes the cap and connects the refueling nozzle to the refuel/defuel adapter, it pushes the poppet that opens the passage in the valve body. Fuel enters each wing tank at the lowest point, at Rib 0 and outboard of Rib 2, to fill the collector tank and the section of tank inboard of Rib 11. The fuel then spills over Rib 11 to fill the outboard section, until the wing tank is full. When the refueling nozzle is removed, the spring pushes the poppet and the plunger back into position and closes the adapter.

The DEFUEL mode on the refuel/defuel control panel is used to defuel the aircraft. The refuel/defuel SOVs close when there is no power available. Selection of DEFUEL opens the SOVs, which allows removal of fuel from the tanks. Maximum defuel pressure is limited to -8 psi. A manual override allows personnel to manually defuel the aircraft without electrical power. The manual override must be continuously held open. It cannot be locked open.

Gravity refuel of the aircraft is done through the gravity filler port on the forward side of the wing top between Ribs 12 and 13.

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11/13/15

System Interface

The refuel/defuel system has interfaces with the systems/components that follow:

  • Servicing the Fuel System
  • Replenishing the Oil System
  • Wing Tank
  • Fuel Management and Quantity Gauging System
  • Fuel Indication System

System Test

A test sequence is completed before aircraft refuel/defuel starts. Upon selection of TEST on the fuel selector rotary switch on the refuel/defuel control panel, the fuel quantity computer starts a controlled test sequence to make sure the refuel/defuel system operates correctly.

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10/16/20

Component Location Index

Component Location Index
IDENT DESCRIPTION LOCATION IPC REF
PL41 REFUEL/DEFUEL CONTROL PANEL ZONE(S) 181CR 28-23-01
     - REFUEL/DEFUEL ADAPTER ZONE(S) 181CR 28-23-05
A59 REFUEL/DEFUEL MANIFOLD ZONE(S) 181BL 28-23-09
     - REFUEL/DEFUEL SHUTOFF VALVE (LH) ZONE(S) 181BL 28-23-13
     - REFUEL/DEFUEL SHUTOFF VALVE (RH) ZONE(S) 181BL 28-23-13

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