622
14 CFR Ch. I (1–1–14 Edition)
§ 26.21
date of approval of the certificate,
whichever occurs later.
(5) Unless compliance with § 25.1729 of
this subchapter is required or elected,
applicants for STCs, including changes
to existing STCs, if the application was
filed on or after December 10, 2007,
June 7, 2010, or the date of approval of
the certificate, whichever occurs later.
(e) Each person identified in para-
graphs (d)(1), (d)(2), and (d)(4) of this
section must submit to the FAA Over-
sight Office for approval a compliance
plan by March 10, 2008. The compliance
plan must include the following infor-
mation:
(1) A proposed project schedule, iden-
tifying all major milestones, for meet-
ing the compliance dates specified in
paragraph (d) of this section.
(2) A proposed means of compliance
with this section, identifying all re-
quired submissions, including all com-
pliance items as mandated in part 25,
Appendix H paragraphs H25.5(a)(1) and
(b) of this subchapter in effect on De-
cember 10, 2007, and all data to be de-
veloped to substantiate compliance.
(3) A proposal for submitting a draft
of all compliance items required by
paragraph (e)(2) of this section for re-
view by the FAA Oversight Office not
less than 60 days before the compliance
time specified in paragraph (d) of this
section.
(4) A proposal for how the approved
ICA will be made available to affected
persons.
(f) Each person specified in paragraph
(e) must implement the compliance
plan, or later approved revisions, as ap-
proved in compliance with paragraph
(e) of this section.
(g) This section does not apply to the
following airplane models:
(1) Lockheed L–188
(2) Bombardier CL–44
(3) Mitsubishi YS–11
(4) British Aerospace BAC 1–11
(5) Concorde
(6) deHavilland D.H. 106 Comet 4C
(7) VFW—Vereinigte Flugtechnische
Werk VFW–614
(8) Illyushin Aviation IL 96T
(9) Bristol Aircraft Britannia 305
(10) Handley Page Herald Type 300
(11) Avions Marcel Dassault—Breguet
Aviation Mercure 100C
(12) Airbus Caravelle
(13) Lockheed L–300
[Amdt. 26–0, 72 FR 63409, Nov. 8, 2007; 72 FR
68618, Dec. 5, 2007]
Subpart C—Aging Airplane Safe-
ty—Widespread Fatigue Dam-
age
S
OURCE
: Doc. No. FAA–2006–24281, 75 FR
69782, Nov. 15, 2010, unless otherwise noted.
§ 26.21
Limit of validity.
(a)
Applicability. Except as provided
in paragraph (g) of this section, this
section applies to transport category,
turbine-powered airplanes with a max-
imum takeoff gross weight greater
than 75,000 pounds and a type certifi-
cate issued after January 1, 1958, re-
gardless of whether the maximum
takeoff gross weight is a result of an
original type certificate or a later de-
sign change. This section also applies
to transport category, turbine-powered
airplanes with a type certificate issued
after January 1, 1958, if a design change
approval for which application is made
after January 14, 2011 has the effect of
reducing the maximum takeoff gross
weight from greater than 75,000 pounds
to 75,000 pounds or less.
(b)
Limit of validity. Each person iden-
tified in paragraph (c) of this section
must comply with the following re-
quirements:
(1) Establish a limit of validity of the
engineering data that supports the
structural maintenance program (here-
after referred to as LOV) that cor-
responds to the period of time, stated
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—
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