Federal Aviation Administration, DOT

Section 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 established. Procedures shall be established to define the critical design
characteristics, identify processes that
affect those characteristics, and identify 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]

Section 29.603

Materials.

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

The suitability and durability of materials used for parts, the failure of
which could adversely affect safety,
must - 
(a) Be established on the basis of experience 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 temperature and humidity, expected in
service.
(Secs. 313(a), 601, 603, 604, and 605 of the Federal Aviation Act of 1958 (49 U.S.C. 1354(a),
1421, 1423, 1424), and 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. 29-12, 41 FR 55471, Dec. 20,
1976; Amdt. 29-17, 43 FR 50599, Oct. 30, 1978]

Section 29.605

Fabrication methods.

(a) The methods of fabrication used
must produce consistently sound structures. If a fabrication process (such as
gluing, spot welding, or heat-treating)
requires close control to reach this objective, the process must be performed
according to an approved process specification.
(b) Each new aircraft fabrication
method must be substantiated by a
test program.

spaschal on DSK3GDR082PROD with CFR

Section 29.607 Fasteners.
(a) Each removable bolt, screw, nut,
pin, or other fastener whose loss could
jeopardize the safe operation of the
rotorcraft must incorporate two separate locking devices. The fastener and
its locking devices may not be adversely affected by the environmental
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.

(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,
1978]

Section 29.609 Protection of structure.
Each part 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 accumulation of corrosive,
flammable, or noxious fluids.
Section 29.610 Lightning and static electricity protection.
(a) The rotorcraft structure must be
protected against catastrophic effects
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 with paragraph (a) of this
section may be shown by - 
(1) Designing the components to minimize the effect of a strike; or
(2) Incorporating acceptable means of
diverting the resulting electrical current to not endanger the rotorcraft.
(d) The electric bonding and protection against lightning and static electricity must - 
(1) Minimize the accumulation of
electrostatic charge;
(2) Minimize the risk of electric
shock to crew, passengers, and service

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