656 

14 CFR Ch. I (1–1–24 Edition) 

§ 29.1307 

(4) For each Category A rotorcraft 

for which OEI Training Mode is re-
quested, a means must be provided to 
indicate to the pilot the simulation of 
an engine failure, the annunciation of 
that simulation, and a representation 
of the OEI power being provided. 

(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; Amdt. 29–59, 88 FR 8739, Feb. 10, 2023] 

§ 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. 

(c) Hand fire extinguishers. 
(d) A windshield wiper or equivalent 

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. 

The equipment, systems, and instal-

lations whose functioning is required 
by this subchapter must be designed 
and installed to ensure that they per-
form their intended functions under 
any foreseeable operating condition. 
For any item of equipment or system 
whose failure has not been specifically 
addressed by another requirement in 
this chapter, the following require-
ments also apply: 

(a) The design of each item of equip-

ment, system, and installation must be 
analyzed separately and in relation to 
other rotorcraft systems and installa-
tions to determine and identify any 
failure that would affect the capability 
of the rotorcraft or the ability of the 
crew to perform their duties in all op-
erating conditions. 

(b) Each item of equipment, system, 

and installation must be designed and 
installed so that: 

(1) The occurrence of any cata-

strophic failure condition is extremely 
improbable; 

(2) The occurrence of any major fail-

ure condition is no more than improb-
able; and 

(3) For the occurrence of any other 

failure condition in between major and 
catastrophic, the probability of the 
failure condition must be inversely 
proportional to its consequences. 

(c) A means to alert the crew in the 

event of a failure must be provided 
when an unsafe system operating con-
dition exists and to enable them to 
take corrective action. Systems, con-
trols, and associated monitoring and 
crew alerting means must be designed 
to minimize crew errors that could cre-
ate additional hazards. 

(d) Compliance with the require-

ments of this section must be shown by 
analysis and, where necessary, by 
ground, flight, or simulator tests. The 
analysis must account for: 

(1) Possible modes of failure, includ-

ing malfunctions and misleading data 
and input from external sources; 

(2) The effect of multiple failures and 

latent failures; 

(3) The resulting effects on the rotor-

craft and occupants, considering the 
stage of flight and operating condi-
tions; and 

(4) The crew alerting cues and the 

corrective action required. 

[Amdt. 29–59, 88 FR 8739, Feb. 10, 2023] 

§ 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 

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