738
14 CFR Ch. I (1–1–24 Edition)
§ 33.97
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, op-
eration, and vibration tests prescribed
in this subpart must be run with the
reverser installed. In complying with
this section, the power control lever
must be moved from one extreme posi-
tion to the other in not more than one
second except, if regimes of control op-
erations are incorporated necessitating
scheduling of the power-control lever
motion in going from one extreme posi-
tion to the other, a longer period of
time is acceptable but not more than
three seconds. In addition, the test pre-
scribed in paragraph (b) of this section
must be made. This test may be sched-
uled 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; Amdt. No. 33–35, 87 FR 75711, Dec. 9,
2022; 88 FR 2813, Jan. 18, 2023]
§ 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
in an IFSD, loss of thrust control, or
other power loss in the applicant’s
other relevant type designs approved
within the past 10 years, to the extent
that adequate service data is available
within that 10-year period. An appli-
cant without adequate service data
must show experience with and knowl-
edge of problem mitigating design
practices equivalent to that gained
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Federal Aviation Administration, DOT
§ 33.201
from actual service experience in a
manner acceptable to the FAA.
(c) Except as specified in paragraph
(f) of this section, the applicant must
conduct a simulated ETOPS mission
cyclic endurance test in accordance
with an approved test plan on an en-
gine that substantially conforms to the
type design. The test must:
(1) Include a minimum of 3,000 rep-
resentative service start-stop mission
cycles and three simulated diversion
cycles at maximum continuous thrust
or power for the maximum diversion
time for which ETOPS eligibility is
sought. Each start-stop mission cycle
must include the use of take-off, climb,
cruise, descent, approach, and landing
thrust or power and the use of thrust
reverse (if applicable). The diversions
must be evenly distributed over the du-
ration of the test. The last diversion
must be conducted within 100 cycles of
the completion of the test.
(2) Be performed with the high speed
and low speed main engine rotors inde-
pendently unbalanced to obtain a min-
imum of 90 percent of the rec-
ommended field service maintenance
vibration levels. For engines with three
main engine rotors, the intermediate
speed rotor must be independently un-
balanced to obtain a minimum of 90
percent of the recommended produc-
tion acceptance vibration level. The re-
quired peak vibration levels must be
verified during a slow acceleration and
deceleration run of the test engine cov-
ering the main engine rotor operating
speed ranges.
(3) Include a minimum of three mil-
lion vibration cycles for each 60 rpm
incremental step of the typical high-
speed rotor start-stop mission cycle.
The test may be conducted using any
rotor speed step increment from 60 to
200 rpm provided the test encompasses
the typical service start-stop cycle
speed range. For incremental steps
greater than 60 rpm, the minimum
number of vibration cycles must be lin-
early increased up to ten million cycles
for a 200 rpm incremental step.
(4) Include a minimum of 300,000 vi-
bration cycles for each 60 rpm incre-
mental step of the high-speed rotor ap-
proved operational speed range be-
tween minimum flight idle and cruise
power not covered by paragraph (c)(3)
of this section. The test may be con-
ducted using any rotor speed step in-
crement from 60 to 200 rpm provided
the test encompasses the applicable
speed range. For incremental steps
greater than 60 rpm the minimum
number of vibration cycles must be lin-
early increased up to 1 million for a 200
rpm incremental step.
(5) Include vibration surveys at peri-
odic intervals throughout the test. The
equivalent value of the peak vibration
level observed during the surveys must
meet the minimum vibration require-
ment of § 33.201(c)(2).
(d) Prior to the test required by para-
graph (c) of this section, the engine
must be subjected to a calibration test
to document power and thrust charac-
teristics.
(e) At the conclusion of the testing
required by paragraph (c) of this sec-
tion, the engine must:
(1) Be subjected to a calibration test
at sea-level conditions. Any change in
power or thrust characteristics must
be within approved limits.
(2) Be visually inspected in accord-
ance with the on-wing inspection rec-
ommendations and limits contained in
the Instructions for Continued Air-
worthiness submitted in compliance
with § 33.4.
(3) Be completely disassembled and
inspected—
(i) In accordance with the applicable
inspection recommendations and limits
contained in the Instructions for Con-
tinued Airworthiness submitted in
compliance with § 33.4;
(ii) With consideration of the causes
of IFSD, loss of thrust control, or other
power loss identified by paragraph (b)
of this section; and
(iii) In a manner to identify wear or
distress conditions that could result in
an IFSD, loss of thrust control, or
other power loss not specifically iden-
tified by paragraph (b) of this section
or addressed within the Instructions
for Continued Airworthiness.
(4) Not show wear or distress to the
extent that could result in an IFSD,
loss of thrust control, or other power
loss within a period of operation before
the component, assembly, or system
would likely have been inspected or
functionally tested for integrity while
in service. Such wear or distress must
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14 CFR Ch. I (1–1–24 Edition)
Pt. 33, App. A
have corrective action implemented
through a design change, a change to
maintenance instructions, or oper-
ational procedures before ETOPS eligi-
bility is granted. The type and fre-
quency of wear and distress that occurs
during the engine test must be con-
sistent with the type and frequency of
wear and distress that would be ex-
pected to occur on ETOPS eligible en-
gines.
(f) An alternative mission cycle en-
durance test that provides an equiva-
lent demonstration of the unbalance
and vibration specified in paragraph (c)
of this section may be used when ap-
proved by the FAA.
(g) For an applicant using the simu-
lated ETOPS mission cyclic endurance
test to comply with § 33.90, the test
may be interrupted so that the engine
may be inspected by an on-wing or
other method, using criteria acceptable
to the FAA, after completion of the
test cycles required to comply with
§ 33.90(a). Following the inspection, the
ETOPS test must be resumed to com-
plete the requirements of this section.
A
PPENDIX
A
TO
P
ART
33—I
NSTRUCTIONS
FOR
C
ONTINUED
A
IRWORTHINESS
A
33.1
GENERAL
(a) This appendix specifies requirements
for the preparation of Instructions for Con-
tinued Airworthiness as required by § 33.4.
(b) The Instructions for Continued Air-
worthiness for each engine must include the
Instructions for Continued Airworthiness for
all engine parts. If Instructions for Contin-
ued Airworthiness are not supplied by the
engine part manufacturer for an engine part,
the Instructions for Continued Airworthiness
for the engine must include the information
essential to the continued airworthiness of
the engine.
(c) The applicant must submit to the FAA
a program to show how changes to the In-
structions for Continued Airworthiness made
by the applicant or by the manufacturers of
engine parts will be distributed.
A
33.2
FORMAT
(a) The Instructions for Continued Air-
worthiness must be in the form of a manual
or manuals as appropriate for the quantity
of data to be provided.
(b) The format of the manual or manuals
must provide for a practical arrangement.
A
33.3
CONTENT
The contents of the manual or manuals
must be prepared in the English language.
The Instructions for Continued Airworthi-
ness must contain the following manuals or
sections, as appropriate, and information:
(a)
Engine Maintenance Manual or Section.
(1) Introduction information that includes an
explanation of the engine’s features and data
to the extent necessary for maintenance or
preventive maintenance.
(2) A detailed description of the engine and
its components, systems, and installations.
(3) Installation instructions, including
proper procedures for uncrating,
deinhibiting, acceptance checking, lifting,
and attaching accessories, with any nec-
essary checks.
(4) Basic control and operating information
describing how the engine components, sys-
tems, and installations operate, and informa-
tion describing the methods of starting, run-
ning, testing, and stopping the engine and its
parts including any special procedures and
limitations that apply.
(5) Servicing information that covers de-
tails regarding servicing points, capacities of
tanks, reservoirs, types of fluids to be used,
pressures applicable to the various systems,
locations of lubrication points, lubricants to
be used, and equipment required for serv-
icing.
(6) Scheduling information for each part of
the engine that provides the recommended
periods at which it should be cleaned, in-
spected, adjusted, tested, and lubricated, and
the degree of inspection the applicable wear
tolerances, and work recommended at these
periods. However, the applicant may refer to
an accessory, instrument, or equipment
manufacturer as the source of this informa-
tion if the applicant shows that the item has
an exceptionally high degree of complexity
requiring specialized maintenance tech-
niques, test equipment, or expertise. The rec-
ommended overhaul periods and necessary
cross references to the Airworthiness Limi-
tations section of the manual must also be
included. In addition, the applicant must in-
clude an inspection program that includes
the frequency and extent of the inspections
necessary to provide for the continued air-
worthiness of the engine.
(7) Troubleshooting information describing
probable malfunctions, how to recognize
those malfunctions, and the remedial action
for those malfunctions.
(8) Information describing the order and
method of removing the engine and its parts
and replacing parts, with any necessary pre-
cautions to be taken. Instructions for proper
ground handling, crating, and shipping must
also be included.
(9) A list of the tools and equipment nec-
essary for maintenance and directions as to
their method of use.
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