(b)
If the type design includes critical parts, a critical parts list shall be established. Proceduresshallbe established tode.nethecriticaldesigncharacteristics,identify processesthat a.ectthose characteristics, andidentify thedesign change andpro-cess change controls necessary for showing compliance with the quality assurance requirements of part 21 of this chapter.]

Amdt. 27-38, E.. 10/25/99
FAR 27.603 : Materials
The suitability and durability of materials used for parts, the failure of which could adversely a.ect safety, must–
(a)
[Be establishedon the basis of experience or tests;

(b)
Meet approved speci.cations 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. 27-16, E.. 12/1/78
FAR 27.605 : Fabrication methods
[(a) ] The methods of fabrication used must produce consistently sound structures. If afabricationprocess(such asgluing, spot welding, orheat-treating) requires close control to reach this objective, the process must be performed according to an approvedprocess speci.cation.
(b)
[Eachnew aircraft fabrication method must be substantiated by a test program.] Amdt. 27-16, E.. 12/1/78

FAR27.607 :[Fasteners.]

(a)
[Eachremovablebolt, screw, nut,pin, or otherfastener whoseloss couldjeopardize the safe operation of the rotorcraft must incorporate two separate locking devices. The fastener and its locking devices may not be adversely a.ected by the environ-mental conditions associated with the particular installation.

(b)
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. 27-4, E.. 10/27/68
′
Elodie Roux. Septembre 2003
Subpart D : Design and Construction
FAR 27.609 : 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 to prevent the accu-mulation of corrosive, .ammable, or noxious .uids.

FAR27.610:[Lightning and staticelectricityprotection.]

(a)
The rotorcraft must be protected against catastrophic e.ects from lightning.

(b)
For metallic components, compliance with paragraph (a) of this section may be shown by–

(1)
Electrically bonding the components properly to the airframe; or

(2)
Designing the components so that a strike will not endanger the rotorcraft.

(c)
For nonmetallic components, compliance withparagraph(a) ofthis section may be shown by–

(1)
Designing the components to minimize the e.ect of a strike; or

(2)
Incorporating acceptable means of diverting the resulting electrical current so as not to endanger the rotorcraft.

(d)
[The electricalbondingandprotectionagainstlightning and staticelectricity must–

(1)
Minimize the accumulation of electrostatic charge;

(2)
Minimize the risk of electric shock to crew, passengers, and service and main-tenance personnel using normal precautions;

(3)
Provide an electrical return path, under both normal and fault conditions, on rotorcrafthavinggrounded electrical systems; and

(4)
Reduce to an acceptable level the e.ects of lightning and static electricity on thefunctioning of essential electrical and electronic equipment.]

Amdt. 27-37, E.. 10/18/99
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 4(86)