Code of Federal Regulations - Title 14

803

Federal Aviation Administration, DOT

§ 29.1309

not employ any pumps, filters, or other
components subject to degradation or
failure which may adversely affect fuel
pressure at the engine;

(22) A means to indicate to the

flightcrew the failure of any fuel pump
installed to show compliance with
§ 29.955;

(23) Warning or caution devices to

signal to the flightcrew when ferro-
magnetic particles are detected by the
chip detector required by § 29.1337(e);
and

(24) For auxiliary power units, an in-

dividual indicator, warning or caution
device, or other means to advise the
flightcrew that limits are being exceed-
ed, if exceeding these limits can be haz-
ardous, for—

(i) Gas temperature;
(ii) Oil pressure; and
(iii) Rotor speed.
(25) For rotorcraft for which a 30-sec-

ond/2-minute OEI power rating is re-
quested, a means must be provided to
alert the pilot when the engine is at
the 30-second and 2-minute OEI power
levels, when the event begins, and
when the time interval expires.

(26) For each turbine engine utilizing

30-second/2-minute OEI power, a device
or system must be provided for use by
ground personnel which—

(i) Automatically records each usage

and duration of power at the 30-second
and 2-minute OEI levels;

(ii) Permits retrieval of the recorded

data;

(iii) Can be reset only by ground

maintenance personnel; and

(iv) Has a means to verify proper op-

eration of the system or device.

(b) For category A rotorcraft—
(1) An individual oil pressure indi-

cator for each engine, and either an
independent warning device for each
engine or a master warning device for
the engines with means for isolating
the individual warning circuit from the
master warning device;

(2) An independent fuel pressure

warning device for each engine or a
master warning device for all engines
with provision for isolating the indi-
vidual warning device from the master
warning device; and

(3) Fire warning indicators.
(c) For category B rotorcraft—

(1) An individual oil pressure indi-

cator for each engine; and

(2) Fire warning indicators, when fire

detection is required.

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–3, 33 FR 970, Jan. 26,
1968; Amdt. 29–10, 39 FR 35463, Oct. 1, 1974;
Amdt. 29–26, 53 FR 34219, Sept. 2, 1988; Amdt.
29–34, 59 FR 47768, Sept. 16, 1994; Amdt. 29–40,
61 FR 21908, May 10, 1996; 61 FR 43952, Aug. 27,
1996]

§ 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

VerDate Mar<15>2010

10:12 Mar 18, 2014

Jkt 232046

PO 00000

Frm 00813

Fmt 8010

Sfmt 8010

Y:\SGML\232046.XXX

232046

pmangrum on DSK3VPTVN1PROD with CFR