613
Federal Aviation Administration, DOT
Pt. 25, App. L
§ 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 re-
sponsible FAA aircraft certification office of
each proposed corrective action that the ap-
plicant determines necessary for each prob-
lem 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]
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
30 MHz–100 MHz .............................
10
10
100 MHz–200 MHz ...........................
30
10
200 MHz–400 MHz ...........................
10
10
400 MHz–1 GHz ................................
700
40
1 GHz–2 GHz ....................................
1,300
160
2 GHz–4 GHz ....................................
3,000
120
4 GHz–6 GHz ....................................
3,000
160
6 GHz–8 GHz ....................................
400
170
8 GHz–12 GHz ..................................
1,230
230
12 GHz–18 GHz ................................
730
190
18 GHz–40 GHz ................................
600
150
In this table, the higher field strength applies at the fre-
quency band edges.
(c)
Equipment HIRF Test Level 1.
(1) From 10 kilohertz (kHz) to 400 mega-
hertz (MHz), use conducted susceptibility
tests with continuous wave (CW) and 1 kHz
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