453 

Federal Aviation Administration, DOT 

Pt. 25, App. L 

in accordance with the tasks defined in the 
proposed Instructions for Continued Air-
worthiness to establish its condition for con-
tinued safe operation. Each engine must also 
undergo a gas path inspection. These inspec-
tions must be conducted in a manner to iden-
tify 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 main-
tain a problem tracking and resolution sys-
tem. The system must: 

(i) Contain a process for prompt reporting 

to the FAA office responsible for the design 
approval of each occurrence reportable under 
§ 21.4(a)(6) encountered during the phases of 

airplane and engine development used to as-
sess Early ETOPS eligibility. 

(ii) Contain a process for notifying the 

FAA office responsible for the design ap-
proval 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 airplane- 
engine 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 ad-

dress . . . 

(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. 

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

Problems in changed systems only. 

(f) 

Acceptance criteria. 

The type and fre-

quency of failures and malfunctions on 
ETOPS significant systems that occur dur-
ing the airplane flight test program and the 
airplane demonstration flight test program 
specified in section K25.3.2(d) of this appen-
dix must be consistent with the type and fre-
quency of failures and malfunctions that 
would be expected to occur on currently cer-
tificated airplanes approved for ETOPS. 

K25.3.3

Combined service experience and 

Early ETOPS method. 

An applicant for ETOPS type design ap-

proval 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 com-
bination; 

(b) The Early ETOPS requirements of sec-

tion 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] 

A

PPENDIX

L 

TO

P

ART

25—HIRF E

NVI

-

RONMENTS

AND

E

QUIPMENT

HIRF 

T

EST

L

EVELS

 

This appendix specifies the HIRF environ-

ments and equipment HIRF test levels for 
electrical and electronic systems under 
§ 25.1317. The field strength values for the 

HIRF environments and equipment HIRF 
test levels are expressed in root-mean-square 
units measured during the peak of the modu-
lation cycle. 

(a) HIRF environment I is specified in the 

following table: 

T

ABLE

I.—HIRF E

NVIRONMENT

I 

Frequency 

Field strength 

(volts/meter) 

Peak Average 

10 kHz–2 MHz ...................................

50 

50 

2 MHz–30 MHz .................................

100 

100 

30 MHz–100 MHz .............................

50 

50 

100 MHz–400 MHz ...........................

100 

100 

400 MHz–700 MHz ...........................

700 

50 

700 MHz–1 GHz ................................

700 

100 

1 GHz–2 GHz ....................................

2,000 

200 

2 GHz–6 GHz ....................................

3,000 

200 

6 GHz–8 GHz ....................................

1,000 

200 

8 GHz–12 GHz ..................................

3,000 

300 

12 GHz–18 GHz ................................

2,000 

200 

18 GHz–40 GHz ................................

600 

200 

In this table, the higher field strength applies at the fre-

quency band edges. 

(b) HIRF environment II is specified in the 

following table: 

T

ABLE

II.–HIRF E

NVIRONMENT

II 

Frequency 

Field strength 

(volts/meter) 

Peak Average 

10 kHz–500 kHz ................................

20 

20 

500 kHz–2 MHz .................................

30 

30 

2 MHz–30 MHz .................................

100 

100 

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