spaschal on DSK3GDR082PROD with CFR

Pt. 25, App. K

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

appendix before conducting the airplane systems assessment specified in K25.3.1(b), and
the flight test specified in section K25.3.1(c)
of this appendix.
(a) Service experience. The world fleet for
the airplane-engine combination must accumulate a minimum of 250,000 engine-hours.
The FAA may reduce this number of hours if
the applicant identifies compensating factors that are acceptable to the FAA. The
compensating factors may include experience on another airplane, but experience on
the candidate airplane must make up a significant portion of the total required service
experience.
(b) Airplane systems assessment. The applicant must conduct an airplane systems assessment. The applicant must show that the
airplane systems comply with the Section 25.1309(b)
using available in-service reliability data for
ETOPS significant systems on the candidate
airplane-engine combination. Each cause or
potential cause of a relevant design, manufacturing, operational or maintenance problem occurring in service must have a corrective action or actions that are shown to be
effective in preventing future occurrences.
Each corrective action must be identified in
the CMP document specified in section
K25.1.6 of this appendix. A corrective action
is not required if the problem would not significantly impact the safety or reliability of
the airplane system involved. A relevant
problem is a problem with an ETOPS group
1 significant system that has or could result
in an IFSD or diversion. The applicant must
include in this assessment relevant problems
with similar or identical equipment installed
on other types of airplanes to the extent
such information is reasonably available.
(c) Airplane flight test. The applicant must
conduct a flight test to validate the
flightcrew-s ability to safely conduct an
ETOPS diversion with an inoperative engine
and worst-case ETOPS significant system
failures and malfunctions that could occur in
service. The flight test must validate the airplane-s flying qualities and performance
with the demonstrated failures and malfunctions.
K25.3.2 Early ETOPS method.
An applicant for ETOPS type design approval using the Early ETOPS method must
comply with the following requirements:
(a) Maintenance and operational procedures.
The applicant must validate all maintenance
and operational procedures for ETOPS significant systems. The applicant must identify, track and resolve any problems found
during the validation in accordance with the
problem tracking and resolution system
specified in section K25.3.2(e) of this appendix.
(b) New technology testing. Technology new
to the applicant, including substantially new
manufacturing techniques, must be tested to

substantiate its suitability for the airplane
design.
(c) APU validation test. If an APU is needed
to comply with this appendix, one APU of
the type to be certified with the airplane
must be tested for 3,000 equivalent airplane
operational cycles. Following completion of
the test, the APU must be disassembled and
inspected. The applicant must identify,
track, and resolve each cause or potential
cause of an inability to start or operate the
APU in flight as intended in accordance with
the problem tracking and resolution system
specified in section K25.3.2(e) of this appendix.
(d) Airplane demonstration. For each airplane-engine combination to be approved for
ETOPS, the applicant must flight test at
least one airplane to demonstrate that the
airplane, and its components and equipment
are capable of functioning properly during
ETOPS flights and diversions of the longest
duration for which the applicant seeks approval. This flight testing may be performed
in conjunction with, but may not substitute
for the flight testing required by Section 21.35(b)(2).
(1) The airplane demonstration flight test
program must include:
(i) Flights simulating actual ETOPS including flight at normal cruise altitude, step
climbs, and, if applicable, APU operation.
(ii) Maximum duration flights with maximum duration diversions.
(iii) Maximum duration engine-inoperative
diversions distributed among the engines installed on the airplanes used for the airplane
demonstration flight test program. At least
two one engine-inoperative diversions must
be conducted at maximum continuous thrust
or power using the same engine.
(iv) Flights under non-normal conditions
to validate the flightcrew-s ability to safely
conduct an ETOPS diversion with worst-case
ETOPS significant system failures or malfunctions that could occur in service.
(v) Diversions to airports that represent
airports of the types used for ETOPS diversions.
(vi) Repeated exposure to humid and inclement weather on the ground followed by a
long duration flight at normal cruise altitude.
(2) The airplane demonstration flight test
program must validate the adequacy of the
airplane-s flying qualities and performance,
and the flightcrew-s ability to safely conduct
an ETOPS diversion under the conditions
specified in section K25.3.2(d)(1) of this appendix.
(3) During the airplane demonstration
flight test program, each test airplane must
be operated and maintained using the applicant-s recommended operating and maintenance procedures.
(4) At the completion of the airplane demonstration, each ETOPS significant system
must undergo an on-wing inspection or test

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