spaschal on DSK3GDR082PROD with CFR

Section 26.21

14 CFR Ch. I (1-1-19 Edition)

issued on or after December 10, 2007:
December 10, 2009 or the date the certificate is issued, whichever occurs
later.
(3) Unless compliance with Section 25.1729 of
this subchapter is required or elected,
applicants for amendments to TCs, if
the application was filed on or after
December 10, 2007: December 10, 2009, or
the date of approval of the certificate,
whichever occurs later.
(4) Applicants for supplemental type
certificates (STC), including changes
to existing STCs, if the date of application was before December 10, 2007 and
the certificate was issued on or after
December 10, 2007: June 7, 2010, or the
date of approval of the certificate,
whichever occurs later.
(5) Unless compliance with Section 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 paragraphs (d)(1), (d)(2), and (d)(4) of this
section must submit to the responsible
Aircraft Certification Service office for
approval a compliance plan by March
10, 2008. The compliance plan must include the following information:
(1) A proposed project schedule, identifying all major milestones, for meeting the compliance dates specified in
paragraph (d) of this section.
(2) A proposed means of compliance
with this section, identifying all required submissions, including all compliance items as mandated in part 25,
Appendix H paragraphs H25.5(a)(1) and
(b) of this subchapter in effect on December 10, 2007, and all data to be developed to substantiate compliance.
(3) A proposal for submitting a draft
of all compliance items required by
paragraph (e)(2) of this section for review by the responsible Aircraft Certification Service 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, as amended by Doc. No.
FAA-2018-0119, Amdt. 26-7, 83 FR 9170, Mar. 5,
2018]

Subpart C - Aging Airplane Safety - Widespread Fatigue Damage
SOURCE: Docket No. FAA-2006-24281, 75 FR
69782, Nov. 15, 2010, unless otherwise noted.

Section 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 maximum takeoff gross weight greater
than 75,000 pounds and a type certificate issued after January 1, 1958, regardless of whether the maximum
takeoff gross weight is a result of an
original type certificate or a later design 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 identified in paragraph (c) of this section
must comply with the following requirements:
(1) Establish a limit of validity of the
engineering data that supports the

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