Federal Aviation Administration, DOT

Pt. 25, App. L

in accordance with the tasks defined in the
proposed Instructions for Continued Airworthiness to establish its condition for continued safe operation. Each engine must also
undergo a gas path inspection. These inspections must be conducted in a manner to identify abnormal conditions that could result in
an IFSD or diversion. The applicant must
identify, track and resolve any abnormal
conditions in accordance with the problem
tracking and resolution system specified in
section K25.3.2(e) of this appendix.
(e) Problem tracking and resolution system.
(1) The applicant must establish and maintain a problem tracking and resolution system. The system must:
(i) Contain a process for prompt reporting
to the FAA office responsible for the design
approval of each occurrence reportable under
Section 21.4(a)(6) encountered during the phases of

airplane and engine development used to assess Early ETOPS eligibility.
(ii) Contain a process for notifying the
FAA office responsible for the design approval of each proposed corrective action
that the applicant determines necessary for
each problem identified from the occurrences
reported under section K25.3.2(h)(1)(i) of this
appendix. The timing of the notification
must permit appropriate FAA review before
taking the proposed corrective action.
(2) If the applicant is seeking ETOPS type
design approval of a change to an airplaneengine combination previously approved for
ETOPS, the problem tracking and resolution
system need only address those problems
specified in the following table, provided the
applicant obtains prior authorization from
the FAA:

If the change does not require a new airplane type certificate
and . . .

Then the Problem Tracking and Resolution System must address . . .

(i) Requires a new engine type certificate ..................................

All problems applicable to the new engine installation, and for
the remainder of the airplane, problems in changed systems
only.
Problems in changed systems only.

(ii) Does not require a new engine type certificate .....................

(f) Acceptance criteria. The type and frequency of failures and malfunctions on
ETOPS significant systems that occur during the airplane flight test program and the
airplane demonstration flight test program
specified in section K25.3.2(d) of this appendix must be consistent with the type and frequency of failures and malfunctions that
would be expected to occur on currently certificated airplanes approved for ETOPS.
K25.3.3 Combined service experience and
Early ETOPS method.
An applicant for ETOPS type design approval using the Early ETOPS method must
comply with the following requirements:
(a) A service experience requirement of
less than 15,000 engine-hours for the world
fleet of the candidate airplane-engine combination;
(b) The Early ETOPS requirements of section K25.3.2 of this appendix, except for the
airplane demonstration specified in section
K25.3.2(d) of this appendix; and
(c) The flight test requirement of section
K25.3.1(c) of this appendix.
[Doc. No. FAA-2002-6717, 72 FR 1873, Jan. 16,
2007, as amended by Doc. No. FAA-2018-0119,
Amdt. 25-145, 83 FR 9169, Mar. 5, 2018]

HIRF environments and equipment HIRF
test levels are expressed in root-mean-square
units measured during the peak of the modulation cycle.
(a) HIRF environment I is specified in the
following table:

TABLE I. - HIRF ENVIRONMENT I
Frequency

Peak
10 kHz-2 MHz ...................................
2 MHz-30 MHz .................................
30 MHz-100 MHz .............................
100 MHz-400 MHz ...........................
400 MHz-700 MHz ...........................
700 MHz-1 GHz ................................
1 GHz-2 GHz ....................................
2 GHz-6 GHz ....................................
6 GHz-8 GHz ....................................
8 GHz-12 GHz ..................................
12 GHz-18 GHz ................................
18 GHz-40 GHz ................................

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50
100
50
100
50
100
200
200
200
300
200
200

(b) HIRF environment II is specified in the
following table:

TABLE II.-HIRF ENVIRONMENT II
Frequency

Field strength
(volts/meter)
Peak

10 kHz-500 kHz ................................
500 kHz-2 MHz .................................
2 MHz-30 MHz .................................

20
30
100

453

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Average

50
100
50
100
700
700
2,000
3,000
1,000
3,000
2,000
600

In this table, the higher field strength applies at the frequency band edges.

APPENDIX L TO PART 25 - HIRF ENVIRONMENTS AND EQUIPMENT HIRF
TEST LEVELS
This appendix specifies the HIRF environments and equipment HIRF test levels for
electrical and electronic systems under
Section 25.1317. The field strength values for the

Field strength
(volts/meter)

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Average
20
30
100