804
14 CFR Ch. I (1–1–14 Edition)
§ 29.1316
action. Systems, controls, and associ-
ated monitoring and warning means
must be designed to minimize crew er-
rors which could create additional haz-
ards.
(d) Compliance with the require-
ments of paragraph (b)(2) of this sec-
tion must be shown by analysis and,
where necessary, by appropriate
ground, flight, or simulator tests. The
analysis must consider—
(1) Possible modes of failure, includ-
ing malfunctions and damage from ex-
ternal sources;
(2) The probability of multiple fail-
ures and undetected failures;
(3) The resulting effects on the rotor-
craft and occupants, considering the
stage of flight and operating condi-
tions; and
(4) The crew warning cues, corrective
action required, and the capability of
detecting faults.
(e) For Category A rotorcraft, each
installation whose functioning is re-
quired by this subchapter and which re-
quires a power supply is an ‘‘essential
load’’ on the power supply. The power
sources and the system must be able to
supply the following power loads in
probable operating combinations and
for probable durations:
(1) Loads connected to the system
with the system functioning normally.
(2) Essential loads, after failure of
any one prime mover, power converter,
or energy storage device.
(3) Essential loads, after failure of—
(i) Any one engine, on rotorcraft with
two engines; and
(ii) Any two engines, on rotorcraft
with three or more engines.
(f) In determining compliance with
paragraphs (e)(2) and (3) of this section,
the power loads may be assumed to be
reduced under a monitoring procedure
consistent with safety in the kinds of
operations authorized. Loads not re-
quired for controlled flight need not be
considered for the two-engine-inoper-
ative condition on rotorcraft with
three or more engines.
(g) In showing compliance with para-
graphs (a) and (b) of this section with
regard to the electrical system and to
equipment design and installation,
critical environmental conditions must
be considered. For electrical genera-
tion, distribution, and utilization
equipment required by or used in com-
plying with this subchapter, except
equipment covered by Technical Stand-
ard Orders containing environmental
test procedures, the ability to provide
continuous, safe service under foresee-
able environmental conditions may be
shown by environmental tests, design
analysis, or reference to previous com-
parable service experience on other air-
craft.
(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); 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. 29–14, 42 FR 36972, July 18,
1977; Amdt. 29–24, 49 FR 44438, Nov. 6, 1984;
Amdt. 29–40, 61 FR 21908, May 10, 1996; Amdt.
29–53, 76 FR 33136, June 8, 2011]
§ 29.1316
Electrical and electronic sys-
tem lightning protection.
(a) Each electrical and electronic
system that performs a function, for
which failure would prevent the contin-
ued safe flight and landing of the rotor-
craft, must be designed and installed so
that—
(1) The function is not adversely af-
fected during and after the time the
rotorcraft is exposed to lightning; and
(2) The system automatically recov-
ers normal operation of that function
in a timely manner after the rotorcraft
is exposed to lightning.
(b) Each electrical and electronic
system that performs a function, for
which failure would reduce the capa-
bility of the rotorcraft or the ability of
the flightcrew to respond to an adverse
operating condition, must be designed
and installed so that the function re-
covers normal operation in a timely
manner after the rotorcraft is exposed
to lightning.
[Doc. No. FAA–2010–0224, Amdt. 29–53, 76 FR
33136, June 8, 2011]
§ 29.1317
High-intensity Radiated
Fields (HIRF) Protection.
(a) Except as provided in paragraph
(d) of this section, each electrical and
electronic system that performs a func-
tion whose failure would prevent the
continued safe flight and landing of the
rotorcraft must be designed and in-
stalled so that—
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