512
14 CFR Ch. I (1–1–24 Edition)
§ 27.605
§ 27.605
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-
fication.
(b) Each new aircraft fabrication
method must be substantiated by a
test program.
(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 1425); sec. 6(c) of the Dept.
of Transportation Act (49 U.S.C. 1655(c)))
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–16, 43 FR 50599, Oct. 30,
1978]
§ 27.607
Fasteners.
(a) Each removable bolt, screw, nut,
pin, or other fastener whose loss could
jeopardize the safe operation of the
rotorcraft must incorporate two 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. 27–4, 33 FR 14533, Sept. 27, 1968]
§ 27.609
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.
§ 27.610
Lightning and static elec-
tricity protection.
(a) The rotorcraft must be protected
against catastrophic effects from light-
ning.
(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-
craft.
(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 so as not to endanger the rotor-
craft.
(d) The electrical 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
and maintenance personnel using nor-
mal precautions;
(3) Provide an electrical return path,
under both normal and fault condi-
tions, on rotorcraft having grounded
electrical systems; and
(4) Reduce to an acceptable level the
effects of static electricity on the func-
tioning of essential electrical and elec-
tronic equipment.
[Amdt. 27–21, 49 FR 44433, Nov. 6, 1984, as
amended by Amdt. 27–37, 64 FR 45094, Aug. 18,
1999; Amdt. 27–46, 76 FR 33135, June 8, 2011]
§ 27.611
Inspection provisions.
There must be means to allow the
close examination of each part that re-
quires—
(a) Recurring inspection;
(b) Adjustment for proper alignment
and functioning; or
(c) Lubrication.
§ 27.613
Material strength properties
and design values.
(a) Material strength properties must
be based on enough tests of material
meeting specifications to establish de-
sign values on a statistical basis.
(b) Design values must be chosen to
minimize the probability of structural
failure due to material variability. Ex-
cept as provided in paragraphs (d) and
(e) of this section, compliance with
this paragraph must be shown by se-
lecting design values that assure mate-
rial strength with the following prob-
ability—
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513
Federal Aviation Administration, DOT
§ 27.621
(1) Where applied loads are eventu-
ally distributed through a single mem-
ber within an assembly, the failure of
which would result in loss of structural
integrity of the component, 99 percent
probability with 95 percent confidence;
and
(2) For redundant structure, those in
which the failure of individual ele-
ments would result in applied loads
being safely distributed to other load-
carrying members, 90 percent prob-
ability with 95 percent confidence.
(c) The strength, detail design, and
fabrication of the structure must mini-
mize the probability of disastrous fa-
tigue failure, particularly at points of
stress concentration.
(d) Design values may be those con-
tained in the following publications
(available from the Naval Publications
and Forms Center, 5801 Tabor Avenue,
Philadelphia, Pennsylvania 19120) or
other values approved by the Adminis-
trator:
(1) MIL-HDBK-5, ‘‘Metallic Materials
and Elements for Flight Vehicle Struc-
ture’’.
(2) MIL-HDBK-17, ‘‘Plastics for
Flight Vehicles’’.
(3) ANC-18, ‘‘Design of Wood Aircraft
Structures’’.
(4) MIL-HDBK-23, ‘‘Composite Con-
struction for Flight Vehicles’’.
(e) Other design values may be used if
a selection of the material is made in
which a specimen of each individual
item is tested before use and it is de-
termined that the actual strength
properties of that particular item will
equal or exceed those used in design.
(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. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–16, 43 FR 50599, Oct. 30,
1978; Amdt. 27–26, 55 FR 8000, Mar. 6, 1990]
§ 27.619
Special factors.
(a) The special factors prescribed in
§§ 27.621 through 27.625 apply to each
part of the structure whose strength
is—
(1) Uncertain;
(2) Likely to deteriorate in service
before normal replacement; or
(3) Subject to appreciable variability
due to—
(i) Uncertainties in manufacturing
processes; or
(ii) Uncertainties in inspection meth-
ods.
(b) For each part to which §§ 27.621
through 27.625 apply, the factor of safe-
ty prescribed in § 27.303 must be multi-
plied by a special factor equal to—
(1) The applicable special factors pre-
scribed in §§ 27.621 through 27.625; or
(2) Any other factor great enough to
ensure that the probability of the part
being understrength because of the un-
certainties specified in paragraph (a) of
this section is extremely remote.
§ 27.621
Casting factors.
(a)
General. The factors, tests, and in-
spections specified in paragraphs (b)
and (c) of this section must be applied
in addition to those necessary to estab-
lish foundry quality control. The in-
spections must meet approved speci-
fications. Paragraphs (c) and (d) of this
section apply to structural castings ex-
cept castings that are pressure tested
as parts of hydraulic or other fluid sys-
tems and do not support structural
loads.
(b)
Bearing stresses and surfaces. The
casting factors specified in paragraphs
(c) and (d) of this section—
(1) Need not exceed 1.25 with respect
to bearing stresses regardless of the
method of inspection used; and
(2) Need not be used with respect to
the bearing surfaces of a part whose
bearing factor is larger than the appli-
cable casting factor.
(c)
Critical castings. For each casting
whose failure would preclude continued
safe flight and landing of the rotorcraft
or result in serious injury to any occu-
pant, the following apply:
(1) Each critical casting must—
(i) Have a casting factor of not less
than 1.25; and
(ii) Receive 100 percent inspection by
visual, radiographic, and magnetic par-
ticle (for ferromagnetic materials) or
penetrant (for nonferromagnetic mate-
rials) inspection methods or approved
equivalent inspection methods.
(2) For each critical casting with a
casting factor less than 1.50, three sam-
ple castings must be static tested and
shown to meet—
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