882 

14 CFR Ch. I (1–1–14 Edition) 

§ 33.97 

the complete engine under the max-
imum conditions of engine accelera-
tion/deceleration rate, speed, torque, 
and temperature as specified by the ap-
plicant. The propeller must be stopped 
prior to brake release. 

(c) One hundred engine starts and 

stops with the propeller brake engaged. 

(d) The tests required by paragraphs 

(a), (b), and (c) of this section must be 
performed on the same engine, but this 
engine need not be the same engine 
used for the tests required by § 33.87. 

(e) The tests required by paragraphs 

(a), (b), and (c) of this section must be 
followed by engine disassembly to the 
extent necessary to show compliance 
with the requirements of § 33.93(a) and 
§ 33.93(b). 

[Amdt. 33–11, 51 FR 10346, Mar. 25, 1986] 

§ 33.97

Thrust reversers. 

(a) If the engine incorporates a re-

verser, the endurance calibration, oper-
ation, and vibration tests prescribed in 
this subpart must be run with the re-
verser installed. In complying with this 
section, the power control lever must 
be moved from one extreme position to 
the other in not more than one second 
except, if regimes of control operations 
are incorporated necessitating sched-
uling of the power-control lever motion 
in going from one extreme position to 
the other, a longer period of time is ac-
ceptable but not more than three sec-
onds. In addition, the test prescribed in 
paragraph (b) of this section must be 
made. This test may be scheduled as 
part of the endurance run. 

(b) 175 reversals must be made from 

flight-idle forward thrust to maximum 
reverse thrust and 25 reversals must be 
made from rated takeoff thrust to max-
imum reverse thrust. After each rever-
sal the reverser must be operated at 
full reverse thrust for a period of one 
minute, except that, in the case of a re-
verser intended for use only as a brak-
ing means on the ground, the reverser 
need only be operated at full reverse 
thrust for 30 seconds. 

[Doc. No. 3025, 29 FR 7453, June 10, 1964, as 
amended by Amdt. 33–3, 32 FR 3737, Mar. 4, 
1967] 

§ 33.99

General conduct of block tests. 

(a) Each applicant may, in making a 

block test, use separate engines of 
identical design and construction in 
the vibration, calibration, endurance, 
and operation tests, except that, if a 
separate engine is used for the endur-
ance test it must be subjected to a cali-
bration check before starting the en-
durance test. 

(b) Each applicant may service and 

make minor repairs to the engine dur-
ing the block tests in accordance with 
the service and maintenance instruc-
tions submitted in compliance with 
§ 33.4. If the frequency of the service is 
excessive, or the number of stops due 
to engine malfunction is excessive, or a 
major repair, or replacement of a part 
is found necessary during the block 
tests or as the result of findings from 
the teardown inspection, the engine or 
its parts must be subjected to any addi-
tional tests the Administrator finds 
necessary. 

(c) Each applicant must furnish all 

testing facilities, including equipment 
and competent personnel, to conduct 
the block tests. 

[Doc. No. 3025, 29 FR 7453, June 10, 1964, as 
amended by Amdt. 33–6, 39 FR 35470, Oct. 1, 
1974; Amdt. 33–9, 45 FR 60181, Sept. 11, 1980] 

Subpart G—Special Requirements: 

Turbine Aircraft Engines 

S

OURCE

: Docket No. FAA–2002–6717, 72 FR 

1877, Jan. 16, 2007, unless otherwise noted. 

§ 33.201

Design and test requirements 

for Early ETOPS eligibility. 

An applicant seeking type design ap-

proval for an engine to be installed on 
a two-engine airplane approved for 
ETOPS without the service experience 
specified in part 25, appendix K, K25.2.1 
of this chapter, must comply with the 
following: 

(a) The engine must be designed 

using a design quality process accept-
able to the FAA, that ensures the de-
sign features of the engine minimize 
the occurrence of failures, malfunc-
tions, defects, and maintenance errors 
that could result in an IFSD, loss of 
thrust control, or other power loss. 

(b) The design features of the engine 

must address problems shown to result 

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