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That portion of the system from the main quick disconnect to the engine, which distributes fuel to the engine burner section and the thrust augmentor. Includes items such as plumbing, pumps, temperature regulators, valves, filters, manifold, nozzles, etc. Does not include the main or thrust augmentor fuel control.
When the airplane manufacturer selects a “maximum continuous power” less than the rated "maximum continuous power” listed in the Engine Type Data Sheet, the maximum continuous power listed in the Airplane Type Data Sheet is used to show compliance with the applicable airworthiness standards and is the value shown in the Pilot＇s Operating Handbook.
Wires and wire bundles must be supported by clamps or plastic cable straps. Clamps and other primary support devices must be constructed of materials that are compatible with their installation and environment, in terms of temperature, exposure to ultraviolet (UV) light, and wire bundle mechanical loads. They should be spaced at intervals not exceeding 24 inches. Clamps on wire bundles should be selected so that they have a snug fit without pinching wires.
A review of test results applicable to the design was made. The loading conditions together with the resulting margins of safety were evaluated. The resulting data were used to determine if the component should be considered for incorporation into the CAP.
For reciprocating engines, those units and components which deliver metered fuel and air to the engine. The fuel portion includes the carburetor, master control from the inlet side to the discharge nozzle(s), injection pumps, carburetor, injection nozzles and fuel primer.
Engine fuel systems include coordinator or equivalent, engine driven fuel pump and filter assembly, main and thrust augmentor fuel controls, electronic temperature datum control, temperature datum valve, fuel manifold, fuel nozzles, fuel enrichment system, speed sensitive switch, relay box assembly, solenoid drip valve, burner drain valve, etc.
The drain and vent system consists of lines collecting and carrying waste fluids and vapor overboard from the engine and nacelle accessories. Drains are provided to carry fluids from any point where lines and accessories may leak and where fluids may accumulate in a cavity. Fluid from forward and aft sumps, oil-fuel heat exchanger, VBV, and VSV are discharged overboard through drains. In addition, some drain lines serve as vents to carry air and vapor from the engine and accessory cavities.
Airplane certification conditions include one engine becoming inoperative and windmilling (or, in airplanes with autofeathering devices, feathered), not more than a 5° bank toward the operative engine, takeoff power on the operative engine, landing gear up, flaps in the takeoff position, and the most critical C.G.
Flight Controls System refers to those units and components which furnish a means of manually controlling the flight attitude characteristics of the aircraft, including items such as hydraulic boost system, rudder pedals, control column linkages, control cables, tab controls, mounting brackets, etc.
This Section of the Pilot＇s Operating Handbook shall contain the appropriate Supplements (operating information) necessary to safely and efficiently operate the airplane when equipped with the various optional system and equipment not provided with the standard airplane.
