(h)
All engine cowling, access doors, and other removable items must be designed to ensure that they will not separate from the airplane and contact the pusher pro-peller.]

Amdt. 23-43, E.. 05/10/93
FAR 23.907 : Propeller vibration.
(a)
Each propeller [other than a conventional .xed-pitch wooden propeller ]must be showntohave vibration stresses,in normal operating conditions, thatdo not exceed valuesthathavebeen shownbythepropeller manufacturertobe safefor continuous operation. This must be shown by–

(1)
Measurement of stresses through direct testing of the propeller;

(2)
Comparison with similarinstallationsfor which these measurementshavebeen made; or

(3)
Any other acceptable test method or service experience that proves the safety of the installation.

(b)
Proof of safe vibration characteristics for any type of propeller, except for conven-tional, .xed-pitch, wood propellers must be shown where necessary.

Amdt. 23-51, E.. 03/11/96
FAR23.909 :[Turbocharger systems.]
(a)
Each[turbochargermustbeapproved undertheenginetype certi.cateoritmust be shown that the turbocharger system, while in its normal engine installation and operating in the engine environment–]

(1)
Can withstand, without defect, an endurance test of 150 hours that meets the applicable requirements ofSec.33.49 of this subchapter; and

(2)
Will have no adverse e.ect upon the engine.

(b)
Control system malfunctions, vibrations, and abnormal speeds and temperatures expectedin service may notdamagethe[turbocharger] compressor orturbine.

(c)
Each[ turbocharger] case must be able to contain fragments of a compressor or turbinethatfailsatthehighest speed thatisobtainablewith normal speed control devices inoperative.

(d)
[Each intercooler installation, where provided, must complywith the following–

(1)
The mountingprovisionsof theintercoolermustbedesigned to withstand the loads imposed on the system;

(2)
Itmustbe shown that, under theinstalled vibration environment, theintercoo-ler will notfailina mannerallowingportionsof theintercoolertobeingested by the engine; and

(3)
Air.ow through the intercooler must not discharge directly on any airplane component(e.g., windshield) unless suchdischargeis shownto cause nohazard to the airplane under all operating conditions.

(e)
Engine power, cooling characteristics, operating limits, and procedures a.ected by the turbocharger system installations must be evaluated. Turbocharger operating procedures and limitations must be included in the Airplane Flight Manual in accordance with Sec. 23.1581 of this part.]

Amdt. 23-43, E.. 05/10/93
′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
FAR 23.925 : Propeller clearance.
[Unless smaller clearances are substantiated,propeller clearances withthe airplane at maximum weight, with the most adverse center of gravity, and with the propeller in the most adversepitchposition, may notbelessthanthefollowing :]
(a)
Ground clearance.There mustbe a clearance of atleast seveninches(for each air-plane with nose wheel landing gear) or nine inches (for each airplane with tail wheel landing gear) between each propeller and the ground with the landing gear statically de.ected and in the level, normal takeo., or taxing attitude, whichever ismostcritical.Inaddition,foreach airplanewith conventionallandinggearstruts using .uid or mechanical means for absorbing landing shocks, there must be po-sitive clearance between the propeller and the ground in the level takeo. attitude with the critical tire completely de.ated and the corresponding landing gear strut bottomed. Positive clearance for airplanes using leaf spring struts is shown with a de.ection corresponding to 1.5g.
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 2(54)