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2006.2 Aircraft-fueling systems.
Aircraft-fueling systems shall be designed and constructed in accordance with NFPA 407.
Exception: Aircraft fueling systems may be designed and constructed as a full service automotive liquid motor vehicle fuel-dispensing facility in accordance with FC Chapter 23, subject to such conditions as the commissioner may require.
2006.3 Design of aircraft-fueling vehicles.
Aircraft-fueling vehicles shall be designed in accordance with FC 2006 and NFPA 407.
2006.3.1 Transfer apparatus.
Aircraft-fueling vehicles shall be equipped and maintained with an approved transfer apparatus.
2006.3.1.1 Internal combustion type.
Where such transfer apparatus is operated by an individual unit of the internal-combustion-motor type, such power unit shall be located as remotely as practicable from pumps, piping, meters, air eliminators, water separators, hose reels, and similar equipment, and shall be housed in a separate compartment from any of the aforementioned items. The fuel tank in connection therewith shall be suitably designed and installed, and the maximum fuel capacity shall not exceed 5 gallons (19 L) where the tank is installed on the engine. The exhaust pipe, muffler and tail pipe shall be shielded.
2006.3.1.2 Gear operated.
Where operated by gears or chains, the gears, chains, shafts, bearings, housing and all parts thereof shall be of an approved design and shall be installed and maintained in an approved manner.
2006.3.1.3 Vibration isolation.
Flexible connections for the purpose of eliminating vibration are allowed if the material used therein is designed, installed, operated and maintained in an approved manner, provided such connections do not exceed 24 inches (610 mm) in length.
2006.3.2 Pumps.
Pumps of a positive-displacement type shall be provided with a bypass relief valve set at a pressure of not more than 35 percent in excess of the normal working pressure of such unit. Such units shall be equipped and maintained with a pressure gauge on the discharge side of the pump.
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