(3)
Examples of these castings are structural attachment .ttings, parts of .ight control systems, control surface hinges and balance weight attachments, seat, berth, safety belt, and fuel and oil tank supports and attachments, and cabin pressure valves.

(d)
Non-critical castings.For each casting other than those speci.edinparagraph(c) [or(e)]of this section,thefollowing apply :

(1) Except asprovidedin subparagraphs(2) and(3) of thisparagraph, the casting factors and corresponding inspections must meet the following table :
Casting factor  Inspection 
2.0 or more  100 percent visual. 
Less than 2.0 but more than 1.5.  100 percent visual, and magnetic par-ticle or penetrant or equivalent non-destructive inspection methods. 
1.25 through 1.50.  100 percent visual, magnetic particle or penetrant, and radiographic, or appro-ved equivalent non-destructive inspec-tion methods. 

(2)
The percentage of castings inspected by nonvisual methods may be reduced below that speci.ed in paragraph (d)(1) of this section when an approved quality control procedure is established.

(3)
For castings procured to a speci.cation that guarantees the mechanical pro-perties of the material in the casting and provides for demonstration of these properties by test of coupons cut from the castings on a sampling basis–

(i)
A casting factor of1.0 may be used; and

(ii)
Thecastingsmustbeinspectedasprovidedinparagraph(d)(1) ofthis section for casting factors of ”1.25 through 1.50” and tested under para-graph(c)(2) of this section.

(e) [Non-structural castings. Castings used for non-structural purposes do not require evaluation, testing or close inspection.]
Amdt. 23-45, E.. 09/07/93
FAR 23.623 : Bearing factors.
(a)
[Eachpartthathasclearance(free .t),andthatissubjecttopounding orvibration, musthave abearingfactorlarge enough toprovidefor the e.ects of normal relative motion.

(b)
For control surface hinges and control system joints, compliance with the factors prescribed in Secs. 23.657 and 23.693, respectively, meets paragraph (a) of this section.]

Amdt. 23-7, E.. 09/14/69
FAR 23.625 : Fitting factors.
Foreach .tting(apartorterminal usedtojoinonestructural membertoanother), the following apply :
(a)
Foreach.ttingwhosestrengthisnotprovenbylimit and ultimateloadtestsinwhich actual stress conditions are simulated in the .tting and surrounding structures, a .tting factor of at least 1.15 must be applied to each part of–

(1)
The .tting;

(2)
The means of attachment; and

(3)
Thebearing onthejoined members.

(b)
No .ttingfactorneedbeusedforjointdesignsbasedoncomprehensivetestdata (suchas continuousjointsin metalplating, weldedjoints, and scarfjointsin wood).

′
Elodie Roux. Septembre 2003
Subpart D : Design and Construction
(c)
For each integral .tting, the part must be treated as a .tting up to the point at which the section properties become typical of the member.

(d)
[For eachseat, berth, safety belt, and harness, its attachment to the structure must be shown, by analysis, tests, or both, to be able to withstand the inertia forces prescribed in Sec. 23.561 multiplied by a .tting factor of 1.33.]

Amdt. 23-7, E.. 09/14/69
FAR 23.627 : Fatigue strength.
The structure mustbedesigned, asfar aspracticable, to avoidpoints ofstress concen-tration where variable stresses abovethefatiguelimit arelikelyto occurin normal service.
FAR 23.629 : Flutter.
(a)
[It mustbe shownbythe methods ofparagraph(b) and eitherparagraph(c) or(d) of thissection,thattheairplaneisfreefrom .utter,control reversal,anddivergence for any condition of operation within the limit V .n envelope and at all speeds up to the speed speci.ed for the selected method. In addition–]
　
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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 2(24)