(b)
Conform to approved speci.cations(such asindustry or military speci.cations, or Technical Standard Orders) that ensure their having the strength and other pro-perties assumedinthedesigndata[;and
(c)
Take into account the e.ects of environmental conditions, such as temperature and humidity, expected in service.]
Amdt. 25-46, E.. 12/1/78
FAR 25.605 : Fabrication methods.
[(a)] The methods of fabrication used must produce a consistently sound structure. If afabricationprocess(such asgluing, spot welding, orheattreating) requires close control to reach this objective, the process must be performed under an approved process speci.cation.
(b) [Eachnew aircraft fabrication method must be substantiated by a test program.]
Amdt. 25-46, E.. 12/1/78
FAR25.607 :[Fasteners.]
(a)
[Eachremovablebolt, screw, nut,pin, or other removablefastener mustincorporate two separate locking devices if–
(1)
Its loss could preclude continued .ight and landing within the design limita-tions of the airplane using normal pilot skill and strength; or
(2)
Its loss could result in reduction in pitch, yaw, or roll control capability or response below that required by Subpart B of this chapter.
(b)
The fasteners speci.ed in paragraph (a) of this section and their locking devices may not be adversely a.ected by the environmental conditions associated with the particular installation.
(c)
No self-locking nut may be used on any bolt subject to rotation in operation unless a nonfriction locking device is used in addition to the self-locking device.]
Amdt. 25-23, E.. 5/8/70
FAR 25.609 : Protection of structure.
Eachpart of the structure must–
(a)
Be suitably protected against deterioration or loss of strength in service due to any cause, including–
(1)
Weathering;
(2)
Corrosion; and
(3)
Abrasion; and
(b)
Have provisions for ventilation and drainage where necessary for protection.
FAR25.611 :[Accessibilityprovisions.]
[Meansmustbeprovidedto allowinspection(including inspection ofprincipal struc-tural elements and control systems), replacement of parts normally requiring replace-ment, adjustment, and lubrication as necessary for continued airworthiness. The inspec-tion means for each item must be practicable for the inspection interval for the item. Nondestructive inspection aids may be used to inspect structural elements where it is impracticable toprovide means for direct visual inspection if it is shown that the inspec-tion is e.ective and the inspection procedures are speci.ed in the maintenance manual required by Sec. 25.1529.] Amdt. 25-23, E.. 5/8/70
FAR 25.613 : Material strength properties and design values.
(a)
Material strength properties must be based on enough tests of material meeting approved speci.cations to establish design values on a statistical basis.
(b)
[Design values must be chosen to minimize the probability of structural failures due to material variability. Except as provided in paragraph (e) of this section, compliance with this paragraph must be shown by selecting design values which assure material strength withthefollowingprobability :
(1)
Where appliedloads are eventuallydistributedthrough a single member within an assembly, the failure of which would result in loss of structural integrity of the component,99percentprobability with95percent con.dence.
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 3(71)
