title-14-part-26-sec26-23

476

14 CFR Ch. I (1–1–24 Edition)

§ 26.23

(4) Gulfstream GV–SP.
(5) British Aerospace, Aircraft Group,

and Societe Nationale Industrielle
Aerospatiale Concorde Type 1.

(6) British Aerospace (Commercial

Aircraft) Ltd., Armstrong Whitworth
Argosy A.W. 650 Series 101.

(7) British Aerospace Airbus, Ltd.,

BAC 1–11.

(8) BAE Systems (Operations) Ltd.,

BAe 146.

(9) BAE Systems (Operations) Ltd.,

Avro 146.

(10) Lockheed 300–50A01 (USAF

C141A).

(11) Boeing 707.
(12) Boeing 720.
(13) deHavilland D.H. 106 Comet 4C.
(14) Ilyushin Aviation IL–96T.
(15) Bristol Aircraft Britannia 305.
(16) Avions Marcel Dassault-Breguet

Aviation Mercure 100C.

(17) Airbus Caravelle.
(18) D & R Nevada, LLC, Convair

Model 22.

(19) D & R Nevada, LLC, Convair

Model 23M.

ABLE

1—C

OMPLIANCE

ATES FOR

FFECTED

IRPLANES

Airplane model

(all existing

models)

Compliance date—

(months after January

14, 2011)

Airbus:

A300 Series ....................................................................................................................................

A310 Series, A300–600 Series ......................................................................................................

A318 Series ....................................................................................................................................

A319 Series ....................................................................................................................................

A320 Series ....................................................................................................................................

A321 Series ....................................................................................................................................

A330–200, –200 Freighter, –300 Series ........................................................................................

A340–200, –300, –500, –600 Series ..............................................................................................

A380–800 Series ............................................................................................................................

Boeing:

717 ..................................................................................................................................................

727 (all series) ................................................................................................................................

737 (Classics): 737–100, –200, –200C, –300, –400, –500 ...........................................................

737 (NG): 737–600, –700, –700C, –800, –900, –900ER ..............................................................

747 (Classics): 747–100, –100B, –100B SUD, –200B, –200C, –200F, –300, 747SP, 747SR .....

747–400: 747–400, –400D, –400F .................................................................................................

757 ..................................................................................................................................................

767 ..................................................................................................................................................

777–200, –300 ................................................................................................................................

777–200LR, 777–300ER, 777F ......................................................................................................

Bombardier:

CL–600: 2D15 (Regional Jet Series 705), 2D24 (Regional Jet Series 900) .................................

Embraer:

ERJ 170 ..........................................................................................................................................

ERJ 190 ..........................................................................................................................................

Fokker:

F.28 Mark 0070, Mark 0100 ...........................................................................................................

Lockheed:

L–1011 ............................................................................................................................................

188 ..................................................................................................................................................

382 (all series) ................................................................................................................................

McDonnell Douglas:

DC–8, –8F .......................................................................................................................................

DC–9 ...............................................................................................................................................

MD–80 (DC–9–81, –82, –83, –87, MD–88) ...................................................................................

MD–90 .............................................................................................................................................

DC–10 .............................................................................................................................................

MD–10 .............................................................................................................................................

MD–11, –11F ..................................................................................................................................

All Other Airplane Models Listed on a Type Certificate as of January 14, 2011 ..........................

Type certificated as of January 14, 2011.

[Doc. No. FAA–2006–24281, 75 FR 69782, Nov.
15, 2010, as amended at 77 FR 30878, May 24,
2012; Doc. No. FAA–2018–0119, Amdt. 26–7, 83
FR 9169, Mar. 5, 2018]

§ 26.23

Extended limit of validity.

(a)

Applicability. Any person may

apply to extend a limit of validity of
the engineering data that supports the

VerDate Sep<11>2014

09:06 Jun 28, 2024

Jkt 262046

PO 00000

Frm 00486

Fmt 8010

Sfmt 8010

Y:\SGML\262046.XXX

262046

jspears on DSK121TN23PROD with CFR

477

Federal Aviation Administration, DOT

§ 26.33

structural maintenance program (here-
after referred to as LOV) approved
under § 25.571 of this subchapter, § 26.21,
or this section. Extending an LOV is a
major design change. The applicant
must comply with the relevant provi-
sions of subparts D or E of part 21 of
this subchapter and paragraph (b) of
this section.

(b)

Extended limit of validity. Each per-

son applying for an extended LOV must
comply with the following require-
ments:

(1) Establish an extended LOV that

corresponds to the period of time, stat-
ed as a number of total accumulated
flight cycles or flight hours or both,
during which it is demonstrated that
widespread fatigue damage will not
occur in the airplane. This demonstra-
tion must include an evaluation of air-
plane structural configurations and be
supported by test evidence and analysis
at a minimum and, if available, service
experience, or service experience and
teardown inspection results, of high-
time airplanes of similar structural de-
sign, accounting for differences in op-
erating conditions and procedures. The
airplane structural configurations to
be evaluated include—

(i) All model variations and deriva-

tives approved under the type certifi-
cate for which approval for an exten-
sion is sought; and

(ii) All structural modifications to

and replacements for the airplane
structural configurations specified in
paragraph (b)(1)(i) of this section, man-
dated by airworthiness directive, up to
the date of approval of the extended
LOV.

(2) Establish a revision or supple-

ment, as applicable, to the Airworthi-
ness Limitations section (ALS) of the
Instructions for Continued Airworthi-
ness required by § 25.1529 of this sub-
chapter, and submit it to the respon-
sible Aircraft Certification Service of-
fice for approval. The revised ALS or
supplement to the ALS must include
the applicable extended LOV estab-
lished under paragraph (b)(1) of this
section.

(3) Develop the maintenance actions

determined by the WFD evaluation per-
formed in paragraph (b)(1) of this sec-
tion to be necessary to preclude WFD
from occurring before the airplane

reaches the proposed extended LOV.
These maintenance actions must be
documented as airworthiness limita-
tion items in the ALS and submitted to
the responsible Aircraft Certification
Service office for approval.

[Docket No. FAA–2006–24281, 75 FR 69782,
Nov. 15, 2010, as amended by Doc. No. FAA–
2018–0119, Amdt. 26–7, 83 FR 9169, Mar. 5, 2018]

Subpart D—Fuel Tank

Flammability

OURCE

: Docket No. FAA–2005–22997, 73 FR

42499, July 21, 2008, unless otherwise noted.

§ 26.31

Definitions.

For purposes of this subpart—
(a)

Fleet Average Flammability Expo-

sure has the meaning defined in Appen-
dix N of part 25 of this chapter.

(b)

Normally Emptied means a fuel

tank other than a Main Fuel Tank.
Main Fuel Tank is defined in 14 CFR
25.981(b).

§ 26.33

Holders of type certificates:

Fuel tank flammability.

(a)

Applicability. This section applies

to U.S. type certificated transport cat-
egory, turbine-powered airplanes, other
than those designed solely for all-cargo
operations, for which the State of Man-
ufacture issued the original certificate
of airworthiness or export airworthi-
ness approval on or after January 1,
1992, that, as a result of original type
certification or later increase in capac-
ity have:

(1) A maximum type-certificated pas-

senger capacity of 30 or more, or

(2) A maximum payload capacity of

7,500 pounds or more.

(b)

Flammability Exposure Analysis. (1)

General. Within 150 days after Decem-
ber 26, 2008, holders of type certificates
must submit for approval to the re-
sponsible Aircraft Certification Service
office a flammability exposure analysis
of all fuel tanks defined in the type de-
sign, as well as all design variations
approved under the type certificate
that affect flammability exposure. This
analysis must be conducted in accord-
ance with Appendix N of part 25 of this
chapter.

(2)

Exception. This paragraph (b) does

not apply to—