Section 29.1045

14 CFR Ch. I (1-1-19 Edition)

approved for the engines, and the mixture settings must be those used in
normal operation.
(4) The test procedures must be as
prescribed in SectionSection 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 SectionF
per minute.
(b) Maximum ambient atmospheric temperature. A maximum ambient atmospheric temperature corresponding to
sea level conditions of at least 100 degrees F. must be established. The assumed temperature lapse rate is 3.6 degrees F. per thousand feet of altitude
above sea level until a temperature of
Section69.7 degrees F. is reached, above
which altitude the temperature is considered constant at Section69.7 degrees F.
However, for winterization installations, the applicant may select a maximum ambient atmospheric temperature corresponding to sea level conditions of less than 100 degrees F.
(c) Correction factor (except cylinder
barrels). Unless a more rational correction applies, temperatures of engine
fluids and powerplant components (except cylinder barrels) for which temperature limits are established, must
be corrected by adding to them 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
component or fluid temperature recorded during the cooling test.
(d) Correction factor for cylinder barrel
temperatures. Cylinder barrel temperatures 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.

spaschal on DSK3GDR082PROD with CFR

(Secs. 313(a), 601, 603, 604, and 605 of the Federal 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]

Section 29.1045 Climb cooling test procedures.
(a) Climb cooling tests must be conducted under this section for - 
(1) Category A rotorcraft; and
(2) Multiengine category B rotorcraft
for which certification is requested
under the category A powerplant installation requirements, and under the
requirements of Section 29.861(a) at the steady
rate of climb or descent established
under Section 29.67(b).
(b) The climb or descent cooling tests
must be conducted with the engine inoperative that produces the most adverse cooling conditions for the remaining engines and powerplant components.
(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 altitude); and
(3) For other rotorcraft, be at maximum continuous power (or at full
throttle when above the critical altitude).
(d) After temperatures have stabilized in flight, the climb must be - 
(1) Begun from an altitude not greater than the lower of - 
(i) 1,000 feet below the engine critcal
altitude; and
(ii) 1,000 feet below the maximum altitude at which the rate of climb is 150
f.p.m; and
(2) Continued for at least five minutes after the occurrence of the highest
temperature recorded, or until the
rotorcraft reaches the maximum altitude for which certification is requested.
(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 conducted at an airspeed representing a

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