656 

14 CFR Ch. I (1–1–19 Edition) 

§ 29.1316 

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— 

(1) The function is not adversely af-

fected during and after the time the 
rotorcraft is exposed to HIRF environ-
ment I, as described in appendix E to 
this part; 

(2) The system automatically recov-

ers normal operation of that function, 
in a timely manner, after the rotor-
craft is exposed to HIRF environment 

I, as described in appendix E to this 
part, unless this conflicts with other 
operational or functional requirements 
of that system; 

(3) The system is not adversely af-

fected during and after the time the 
rotorcraft is exposed to HIRF environ-
ment II, as described in appendix E to 
this part; and 

(4) Each function required during op-

eration under visual flight rules is not 
adversely affected during and after the 
time the rotorcraft is exposed to HIRF 
environment III, as described in appen-
dix E to this part. 

(b) Each electrical and electronic 

system that performs a function whose 
failure would significantly reduce the 
capability of the rotorcraft or the abil-
ity of the flightcrew to respond to an 
adverse operating condition must be 
designed and installed so the system is 
not adversely affected when the equip-
ment providing these functions is ex-
posed to equipment HIRF test level 1 
or 2, as described in appendix E to this 
part. 

(c) Each electrical and electronic sys-

tem that performs such a function 
whose 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 the system is not ad-
versely affected when the equipment 
providing these functions is exposed to 
equipment HIRF test level 3, as de-
scribed in appendix E to this part. 

(d) Before December 1, 2012, an elec-

trical or electronic system that per-
forms a function whose failure would 
prevent the continued safe flight and 
landing of a rotorcraft may be designed 
and installed without meeting the pro-
visions of paragraph (a) provided— 

(1) The system has previously been 

shown to comply with special condi-
tions for HIRF, prescribed under § 21.16, 
issued before December 1, 2007; 

(2) The HIRF immunity characteris-

tics of the system have not changed 
since compliance with the special con-
ditions was demonstrated; and 

(3) The data used to demonstrate 

compliance with the special conditions 
is provided. 

[Doc. No. FAA–2006–23657, 72 FR 44027, Aug. 6, 
2007] 

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