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Federal Aviation Administration, DOT 

§ 29.610 

have been identified which must be 
controlled to ensure the required level 
of integrity. 

(b) If the type design includes critical 

parts, a critical parts list shall be es-
tablished. Procedures shall be estab-
lished to define the critical design 
characteristics, identify processes that 
affect those characteristics, and iden-
tify the design change and process 
change controls necessary for showing 
compliance with the quality assurance 
requirements of part 21 of this chapter. 

[Doc. No. 29311, 64 FR 46232, Aug. 24, 1999] 

§ 29.603


The suitability and durability of ma-

terials used for parts, the failure of 
which could adversely affect safety, 

(a) Be established on the basis of ex-

perience or tests; 

(b) Meet approved specifications that 

ensure their having the strength and 
other properties assumed in the design 
data; and 

(c) Take into account the effects of 

environmental conditions, such as tem-
perature and humidity, expected in 

(Secs. 313(a), 601, 603, 604, and 605 of the Fed-
eral Aviation Act of 1958 (49 U.S.C. 1354(a), 
1421, 1423, 1424), and sec. 6(c), Dept. of Trans-
portation Act (49 U.S.C. 1655(c))) 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–12, 41 FR 55471, Dec. 20, 
1976; Amdt. 29–17, 43 FR 50599, Oct. 30, 1978] 

§ 29.605

Fabrication methods. 

(a) The methods of fabrication used 

must produce consistently sound struc-
tures. If a fabrication process (such as 
gluing, spot welding, or heat-treating) 
requires close control to reach this ob-
jective, the process must be performed 
according to an approved process speci-

(b) Each new aircraft fabrication 

method must be substantiated by a 
test program. 

(Secs. 313(a), 601, 603, 604, Federal Aviation 
Act of 1958 (49 U.S.C. 1354(a), 1421, 1423, 1424), 
sec. 6(c), Dept. of Transportation Act (49 
U.S.C. 1655(c))) 

[Doc. No. 5084, 29 FR 16150. Dec. 3, 1964, as 
amended by Amdt. 29–17, 43 FR 50599, Oct. 30, 

§ 29.607


(a) Each removable bolt, screw, nut, 

pin, or other fastener whose loss could 
jeopardize the safe operation of the 
rotorcraft must incorporate two sepa-
rate locking devices. The fastener and 
its locking devices may not be ad-
versely affected by the environmental 
conditions associated with the par-
ticular installation. 

(b) No self-locking nut may be used 

on any bolt subject to rotation in oper-
ation unless a nonfriction locking de-
vice is used in addition to the self-lock-
ing device. 

[Amdt. 29–5, 33 FR 14533, Sept. 27, 1968] 

§ 29.609

Protection of structure. 

Each part of the structure must— 
(a) Be suitably protected against de-

terioration or loss of strength in serv-
ice due to any cause, including— 

(1) Weathering; 
(2) Corrosion; and 
(3) Abrasion; and 
(b) Have provisions for ventilation 

and drainage where necessary to pre-
vent the accumulation of corrosive, 
flammable, or noxious fluids. 

§ 29.610

Lightning and static elec-

tricity protection. 

(a) The rotorcraft structure must be 

protected against catastrophic effects 
from lightning. 

(b) For metallic components, compli-

ance with paragraph (a) of this section 
may be shown by— 

(1) Electrically bonding the compo-

nents properly to the airframe; or 

(2) Designing the components so that 

a strike will not endanger the rotor-

(c) For nonmetallic components, 

compliance with paragraph (a) of this 
section may be shown by— 

(1) Designing the components to min-

imize the effect of a strike; or 

(2) Incorporating acceptable means of 

diverting the resulting electrical cur-
rent to not endanger the rotorcraft. 

(d) The electric bonding and protec-

tion against lightning and static elec-
tricity must— 

(1) Minimize the accumulation of 

electrostatic charge; 

(2) Minimize the risk of electric 

shock to crew, passengers, and service 

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