642 

14 CFR Ch. I (1–1–19 Edition) 

§ 29.1045 

approved for the engines, and the mix-
ture settings must be those used in 
normal operation. 

(4) The test procedures must be as 

prescribed in §§ 29.1045 through 29.1049. 

(5) For the purposes of the cooling 

tests, a temperature is ‘‘stabilized’’ 
when its rate of change is less than 2 

°

F 

per minute. 

(b) 

Maximum ambient atmospheric tem-

perature. 

A maximum ambient atmos-

pheric temperature corresponding to 
sea level conditions of at least 100 de-
grees F. must be established. The as-
sumed temperature lapse rate is 3.6 de-
grees F. per thousand feet of altitude 
above sea level until a temperature of 

¥

69.7 degrees F. is reached, above 

which altitude the temperature is con-
sidered constant at 

¥

69.7 degrees F. 

However, for winterization installa-
tions, the applicant may select a max-
imum ambient atmospheric tempera-
ture corresponding to sea level condi-
tions of less than 100 degrees F. 

(c) 

Correction factor (except cylinder 

barrels). 

Unless a more rational correc-

tion applies, temperatures of engine 
fluids and powerplant components (ex-
cept cylinder barrels) for which tem-
perature limits are established, must 
be corrected by adding to them the dif-
ference between the maximum ambient 
atmospheric temperature and the tem-
perature of the ambient air at the time 
of the first occurrence of the maximum 
component or fluid temperature re-
corded during the cooling test. 

(d) 

Correction factor for cylinder barrel 

temperatures. 

Cylinder barrel tempera-

tures must be corrected by adding to 
them 0.7 times the difference between 
the maximum ambient atmospheric 
temperature and the temperature of 
the ambient air at the time of the first 
occurrence of the maximum cylinder 
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 

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