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Federal Aviation Administration, DOT

§ 29.1309

§ 29.1307

Miscellaneous equipment.

The following is required miscella-

neous equipment:

(a) An approved seat for each occu-

pant.

(b) A master switch arrangement for

electrical circuits other than ignition.

device for each pilot station.

(e) A two-way radio communication

system.

[Amdt. 29–12, 41 FR 55473, Dec. 20, 1976]

§ 29.1309

Equipment, systems, and in-

stallations.

(a) The equipment, systems, and in-

stallations whose functioning is re-
quired by this subchapter must be de-
signed and installed to ensure that
they perform their intended functions
under any foreseeable operating condi-
tion.

(b) The rotorcraft systems and asso-

ciated components, considered sepa-
rately and in relation to other systems,
must be designed so that—

(1) For Category B rotorcraft, the

equipment, systems, and installations
must be designed to prevent hazards to
the rotorcraft if they malfunction or
fail; or

(2) For Category A rotorcraft—
(i) The occurrence of any failure con-

dition which would prevent the contin-
ued safe flight and landing of the rotor-
craft is extremely improbable; and

(ii) The occurrence of any other fail-

ure conditions which would reduce the
capability of the rotorcraft or the abil-
ity of the crew to cope with adverse op-
erating conditions is improbable.

vided to alert the crew to unsafe sys-
tem operating conditions and to enable
them to take appropriate corrective
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

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