792 

14 CFR Ch. I (1–1–14 Edition) 

§ 29.1049 

(ii) At least 5 minutes after the oc-

currence of the highest temperature re-
corded, if continuous OEI power or 
maximum continuous power is used. 

(5) The speeds must be those used in 

determining the takeoff flight path 
under § 29.59. 

(b) 

Category B. For each category B 

rotorcraft, cooling must be shown dur-
ing takeoff and subsequent climb as 
follows: 

(1) Each temperature must be sta-

bilized while hovering in ground effect 
with— 

(i) The power necessary for hovering; 
(ii) The appropriate cowl flap and 

shutter settings; and 

(iii) The maximum weight. 
(2) After the temperatures have sta-

bilized, a climb must be started at the 
lowest practicable altitude with take-
off power. 

(3) Takeoff power must be used for 

the same time interval as takeoff 
power is used in determining the take-
off flight path under § 29.63. 

(4) At the end of the time interval 

prescribed in paragraph (a)(3) of this 
section, the power must be reduced to 
maximum continuous power and the 
climb must be continued for at least 
five minutes after the occurance of the 
highest temperature recorded. 

(5) The cooling test must be con-

ducted at an airspeed corresponding to 
normal operating practice for the con-
figuration being tested. However, if the 
cooling provisions are sensitive to 
rotorcraft speed, the most critical air-
speed must be used, but need not ex-
ceed the speed for best rate of climb 
with maximum continuous power. 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–1, 30 FR 8778, July 13, 
1965; Amdt. 29–26, 53 FR 34219, Sept. 2, 1988] 

§ 29.1049

Hovering cooling test proce-

dures. 

The hovering cooling provisions must 

be shown— 

(a) At maximum weight or at the 

greatest weight at which the rotorcraft 
can hover (if less), at sea level, with 
the power required to hover but not 
more than maximum continuous 
power, in the ground effect in still air, 
until at least five minutes after the oc-
currence of the highest temperature re-
corded; and 

(b) With maximum continuous power, 

maximum weight, and at the altitude 
resulting in zero rate of climb for this 
configuration, until at least five min-
utes after the occurrence of the highest 
temperature recorded. 

I

NDUCTION

S

YSTEM

 

§ 29.1091

Air induction. 

(a) The air induction system for each 

engine and auxiliary power unit must 
supply the air required by that engine 
and auxiliary power unit under the op-
erating conditions for which certifi-
cation is requested. 

(b) Each engine and auxiliary power 

unit air induction system must provide 
air for proper fuel metering and mix-
ture distribution with the induction 
system valves in any position. 

(c) No air intake may open within 

the engine accessory section or within 
other areas of any powerplant compart-
ment where emergence of backfire 
flame would constitute a fire hazard. 

(d) Each reciprocating engine must 

have an alternate air source. 

(e) Each alternate air intake must be 

located to prevent the entrance of rain, 
ice, or other foreign matter. 

(f) For turbine engine powered rotor-

craft and rotorcraft incorporating aux-
iliary power units— 

(1) There must be means to prevent 

hazardous quantities of fuel leakage or 
overflow from drains, vents, or other 
components of flammable fluid systems 
from entering the engine or auxiliary 
power unit intake system; and 

(2) The air inlet ducts must be lo-

cated or protected so as to minimize 
the ingestion of foreign matter during 
takeoff, landing, and taxiing. 

(Secs. 313(a), 601, 603, 604, Federal Aviation 
Act of 1958 (49 U.S.C. 1354(a), 1421, 1423, 1424), 
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. 29–3, 33 FR 969, Jan. 26, 
1968; Amdt. 29–17, 43 FR 50601, Oct. 30, 1978] 

§ 29.1093

Induction system icing pro-

tection. 

(a) 

Reciprocating engines. Each recip-

rocating engine air induction system 
must have means to prevent and elimi-
nate icing. Unless this is done by other 
means, it must be shown that, in air 

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