732 

14 CFR Ch. I (1–1–19 Edition) 

§ 33.87 

(b)(2) of this section, or of the 30 min-
utes at 30-minute OEI power test pe-
riod of paragraph (c)(4) of this section, 
or of the l hour at continuous OEI 
power test period of paragraph (d)(3) of 
this section, must be run at 2

1

⁄

2

-minute 

OEI power. 

(f) 

Rotorcraft Engines for which 30-sec-

ond OEI and 2-minute OEI ratings are de-
sired. 

For each rotorcraft engine for 

which 30-second OEI and 2-minute OEI 
power ratings are desired, and fol-
lowing completion of the tests under 
paragraphs (b), (c), (d), or (e) of this 
section, the applicant may disassemble 
the tested engine to the extent nec-
essary to show compliance with the re-
quirements of § 33.93(a). The tested en-
gine must then be reassembled using 
the same parts used during the test 
runs of paragraphs (b), (c), (d), or (e) of 
this section, except those parts de-
scribed as consumables in the Instruc-
tions for Continued Airworthiness. Ad-
ditionally, the tests required in para-
graphs (f)(1) through (f)(8) of this sec-
tion must be run continuously. If a 
stop occurs during these tests, the in-
terrupted sequence must be repeated 
unless the applicant shows that the se-
verity of the test would not be reduced 
if it were continued. The applicant 
must conduct the following test se-
quence four times, for a total time of 
not less than 120 minutes: 

(1) 

Takeoff power. 

Three minutes at 

rated takeoff power. 

(2) 

30-second OEI power. 

Thirty sec-

onds at rated 30-second OEI power. 

(3) 

2-minute OEI power. 

Two minutes 

at rated 2-minute OEI power. 

(4) 

30-minute OEI power, continuous 

OEI power, or maximum continuous 
power. 

Five minutes at whichever is 

the greatest of rated 30-minute OEI 
power, rated continuous OEI power, or 
rated maximum continuous power, ex-
cept that, during the first test se-
quence, this period shall be 65 minutes. 
However, where the greatest rated 
power is 30-minute OEI power, that 
sixty-five minute period shall consist 
of 30 minutes at 30-minute OEI power 
followed by 35 minutes at whichever is 
the greater of continuous OEI power or 
maximum continuous power. 

(5) 

50 percent takeoff power. 

One 

minute at 50 percent takeoff power. 

(6) 

30-second OEI power. 

Thirty sec-

onds at rated 30-second OEI power. 

(7) 

2-minute OEI power. 

Two minutes 

at rated 2-minute OEI power. 

(8) 

Idle. 

One minute at flight idle. 

(g) 

Supersonic aircraft engines. 

For 

each engine type certificated for use on 
supersonic aircraft the applicant must 
conduct the following: 

(1) 

Subsonic test under sea level ambient 

atmospheric conditions. 

Thirty runs of 

one hour each must be made, con-
sisting of— 

(i) Two periods of 5 minutes at rated 

takeoff augmented thrust each fol-
lowed by 5 minutes at idle thrust; 

(ii) One period of 5 minutes at rated 

takeoff thrust followed by 5 minutes at 
not more than 15 percent of rated take-
off thrust; 

(iii) One period of 10 minutes at rated 

takeoff augmented thrust followed by 2 
minutes at idle thrust, except that if 
rated maximum continuous augmented 
thrust is lower than rated takeoff aug-
mented thrust, 5 of the 10-minute peri-
ods must be at rated maximum contin-
uous augmented thrust; and 

(iv) Six periods of 1 minute at rated 

takeoff augmented thrust each fol-
lowed by 2 minutes, including accelera-
tion and deceleration time, at idle 
thrust. 

(2) 

Simulated supersonic test. 

Each run 

of the simulated supersonic test must 
be preceded by changing the inlet air 
temperature and pressure from that at-
tained at subsonic condition to the 
temperature and pressure attained at 
supersonic velocity, and must be fol-
lowed by a return to the temperature 
attained at subsonic condition. Thirty 
runs of 4 hours each must be made, 
consisting of— 

(i) One period of 30 minutes at the 

thrust obtained with the power control 
lever set at the position for rated max-
imum continuous augmented thrust 
followed by 10 minutes at the thrust 
obtained with the power control lever 
set at the position for 90 percent of 
rated maximum continuous augmented 
thrust. The end of this period in the 
first five runs must be made with the 
induction air temperature at the lim-
iting condition of transient over-
temperature, but need not be repeated 

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