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14 CFR Ch. I (1–1–18 Edition) 

§ 29.1045 

barrel temperature recorded during the 
cooling test. 

(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) of the 
Dept. of Transportation Act (49 U.S.C. 
1655(c))) 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–12, 41 FR 55473, Dec. 20, 
1976; Amdt. 29–15, 43 FR 2327, Jan. 16, 1978; 
Amdt. 29–26, 53 FR 34218, Sept. 2, 1988] 

§ 29.1045

Climb cooling test proce-

dures. 

(a) Climb cooling tests must be con-

ducted under this section for— 

(1) Category A rotorcraft; and 
(2) Multiengine category B rotorcraft 

for which certification is requested 
under the category A powerplant in-
stallation requirements, and under the 
requirements of § 29.861(a) at the steady 
rate of climb or descent established 
under § 29.67(b). 

(b) The climb or descent cooling tests 

must be conducted with the engine in-
operative that produces the most ad-
verse cooling conditions for the re-
maining engines and powerplant com-
ponents. 

(c) Each operating engine must— 
(1) For helicopters for which the use 

of 30-minute OEI power is requested, be 
at 30-minute OEI power for 30 minutes, 
and then at maximum continuous 
power (or at full throttle when above 
the critical altitude); 

(2) For helicopters for which the use 

of continuous OEI power is requested, 
be at continuous OEI power (or at full 
throttle when above the critical alti-
tude); and 

(3) For other rotorcraft, be at max-

imum continuous power (or at full 
throttle when above the critical alti-
tude). 

(d) After temperatures have sta-

bilized in flight, the climb must be— 

(1) Begun from an altitude not great-

er than the lower of— 

(i) 1,000 feet below the engine critcal 

altitude; and 

(ii) 1,000 feet below the maximum al-

titude at which the rate of climb is 150 
f.p.m; and 

(2) Continued for at least five min-

utes after the occurrence of the highest 
temperature recorded, or until the 
rotorcraft reaches the maximum alti-

tude for which certification is re-
quested. 

(e) For category B rotorcraft without 

a positive rate of climb, the descent 
must begin at the all-engine-critical 
altitude and end at the higher of— 

(1) The maximum altitude at which 

level flight can be maintained with one 
engine operative; and 

(2) Sea level. 
(f) The climb or descent must be con-

ducted at an airspeed representing a 
normal operational practice for the 
configuration 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 speeds established under 
§ 29.67(a)(2) or § 29.67(b). The climb cool-
ing test may be conducted in conjunc-
tion with the takeoff cooling test of 
§ 29.1047. 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–26, 53 FR 34218, Sept. 2, 
1988] 

§ 29.1047

Takeoff cooling test proce-

dures. 

(a)  Category A. For each category A 

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 and must be 
conducted with one engine inoperative. 

(3) The operating engines must be at 

the greatest power for which approval 
is sought (or at full throttle when 
above the critical altitude) for the 
same period as this power is used in de-
termining the takeoff climbout path 
under § 29.59. 

(4) At the end of the time interval 

prescribed in paragraph (b)(3) of this 
section, the power must be changed to 
that used in meeting § 29.67(a)(2) and 
the climb must be continued for— 

(i) Thirty minutes, if 30-minute OEI 

power is used; or 

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