(b)
The turbine engine air inlet system may not, as a result of air.ow distortion during normal operation, cause vibration harmful to the engine.
′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
(c) [For governor-controlledengines, it must be shown that there exists no hazardous torsional instability of the drive system associated with critical combinations of power, rotational speed, and control displacement.]
Amdt. 27-11, E.. 2/1/77
65.3 Fuel System
FAR 27.951 : General
(a)
Eachfuel systemmustbeconstructed and arranged toensurea .owoffuel at arate and pressure established for proper engine functioning under any likely operating condition, including the maneuvers for which certi.cation is requested.
(b)
Each fuel system must be arranged so that–
(1)
Nofuelpump candrawfuelfrom morethan onetank at atime; or
(2)
There are means to prevent introducing air into the system.
(c)
[Eachfuelsystem for a turbine engine must be capable of sustained operation throu-ghout its .ow and pressure range with fuel initially saturated with water at 80'F and having 0.75cc of free water per gallon added and cooled to the most critical condition for icing likely to be encountered in operation.]
Amdt. 27-9, E.. 10/31/74
FAR27.952:[Fuel systemcrash resistance.]
[Unless other means acceptable to the Administrator are employed to minimize the hazardoffuel.restooccupantsfollowing anotherwisesurvivableimpact(crashlanding), thefuel systems must incorporate thedesignfeatures of this section.These systems must be shown to be capable of sustaining the static and dynamic deceleration loads of this section, considered as ultimate loads acting alone, measured at the system component’s center of gravity, without structural damage to system components, fuel tanks, or their attachments that would leak fuel to an ignition source.
(a)
Drop test requirements. Each tank, or the most critical tank, must be drop-tested as follows :
(1)
The drop height must be at least 50 feet.
(2)
The drop impact surface must be nondeforming.
(3)
The tank must be .lled with water to 80 percent of the normal, full capacity.
(4)
The tank must be enclosed in a surrounding structure representative of the installation unless it can be established that the surrounding structure is free of projections or other design features likely to contribute to rupture of the tank.
(5)
Thetank mustdrop freely andimpactin ahorizontalposition ±10'.
(6)
After the drop test, there must be no leakage.
(b)
Fuel tank load factors. Except for fuel tanks located so that tank rupture with fuel release to either signi.cant ignition sources, such as engines, heaters, and auxiliary power units, or occupantsis extremelyremote, eachfuel tank mustbedesigned and installed to retain its contents under the following ultimate inertial load factors, acting alone.
(1)
For fuel tanks in the cabin :
(i)
Upward–4g.
(ii)
Forward–16g.
(iii) Sideward–8g.
(iv) Downward–20g.
(2)
For fuel tanks located above or behind the crew or passenger compartment that, if loosened, could injure an occupant in an emergency landing :
(i)
Upward–1.5g.
(ii)
Forward–8g.
(iii) Sideward–2g.
(iv) Downward–4g.
(3)
For fuel tanks in other areas :
(i)
Upward–1.5g.
(ii)
Forward–4g.
(iii) Sideward–2g.
(iv) Downward–4g.
(c) Fuel line self-sealing breakaway couplings. Self-sealing breakaway couplings must be installed unless hazardous relative motion of fuel system components to each other ortolocal rotorcraft structureisdemonstratedtobe extremelyimprobable or unless other means are provided. The couplings or equivalent devices must be installed at all fuel tank-to-fuel line connections, tank-to-tank interconnects, and at other pointsin thefuelsystem wherelocal structuraldeformation couldleadtothe release of fuel.
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本文鏈接地址：FAA規(guī)章 美國聯(lián)邦航空規(guī)章 Federal Aviation Regulations 4(106)
