MIL-T-62032 Trucks, Tank: Fuel Servicing And Aircraft Fuel Servicing, 1,000 To 4,000 Gallon, Diesel And Gasoline Engine Driven, 16,000 To 50,000 Pounds Gvw, 4X2, 4X4, 6X4, And 6X6, Modified CommercialThis specification covers diesel and gasoline engine driven, four-wheel, two- or four-wheel drive, and six-wheel, four- or six-wheel drive, single or dual delivery fuel servicing and aircraft fuel servicing tank trucks, with product capacities from 1,000 to 4,000 gallons, having minimum gross vehicle weights GVW of 16,000 to 50,000 pounds for normal operating conditions. Vehicles procured under this specification are commercial items which are warranted by the manufacturer as specified in acquisition documents.

Pages 1 - 2 - 3 - 4 - 5 - 6 - 7 - 8 - 9 - 10 - 11 - 12 - 13 - 14 - 15 - 16 - 17 - 18 - 19 - 20 - 21 - 22 - 23 - 24 - 25 - 26 - 27 - 28 - 29 - 30 - 31 - 32 - 33 - 34 - 35 - 36 - 37 - 38 - 39 - 40 - 41 - 42 - 43 - 44 - 45 - 46 - 47 - 48 - 49 - 50 - 51 - 52 - 53 - 54 - 55 - 56 - 57 - 58 - 59 - 60 - 61 - 62

MIL-T-62032H

3.8.2.3 Underwing single point pressure servicing nozzle. An underwing single point pressure servicing nozzle conforming to the functional and performance requirements of

MIL-N-5877 (designated type D-l), or a commercial aviation refueling nozzle capable of connection to the International Standard bayonet adapter, shall be furnished for the 2-inch

servicing hose. The underwing nozzle assembly shall permit interchange with the nozzles specified in 3.8.2.1 and 3.8.2.2 by utilizing a dry break coupling as specified in 3.8.1.2.

* 3.8.3 Pump. A power takeoff driven, self-priming, centrifugal, aircraft fuel dispensing type pump shall be provided. The pump internal components shall be of nonferrous materials. The pump shall be capable of producing a vacuum of not less than 18 inches of mercury (Hg) when loading the tank from an outside source. The pump shall be so constructed and positioned that fuel will not enter into any gearbox or transmission. A drain plug or valve shall be provided for completely draining the pump.

3.8.3.1 Power takeoff interlock. A brake interlock shall be provided to prevent truck movement while the power takeoff is engaged. The interlock shall be air operated.

3.8.4 Pumping system operation. The pumping system shall provide the pressure control and flow rates specified herein. For overwing (open port) refueling, the flow rate shall be controllable between zero and 100 gpm by the trigger control of the 1.5 inch overwing nozzle. For pressure (underwing and closed-circuit) refueling, the pumping system shall provide for any servicing rate between zero and the required nominal flow capability for the specified hose and nozzle (as indicated in 3.8.4.2 and 3.8.4.3) based on the aircraft demand. The pumping system shall exhibit no instability in pressure or flow rate under any operating condition. The vacuum

of the pump suction at the maximum refueling rate shall be not more than 7 inches Hg as the tank approaches empty.

3.8.4.1 Overwing (open port) fuel servicing operations. The pumping system shall function as follows:

(a) Refuel from the tank through the filter/separator, the contamination monitor, the meter, the 2-inch servicing hose, and the 1.5 inch overwing nozzle at flow rates from zero to 100 gpm. The flow rate shall be regulated on demand by control of the trigger of the 1.5 inch overwing nozzle;

(b) Defuel from the aircraft through the 1.5 inch overwing nozzle, the 2-inch hose, the meter, the filter/separator, the contamination monitor, and into the tank at flow rates of not less than 60 gpm. (See 3.8.2.1 for nozzle extension required for deep tanks);

hoses (see 3.5.23), the suction stub (see 3.5.21), the filter/separator, the contamination monitor and into the tank at flow rates up to 100 gpm.