spaschal on DSK3GDR082PROD with CFR

Section 26.31

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

structural maintenance program (hereafter referred to as LOV) approved
under Section 25.571 of this subchapter, Section 26.21,
or this section. Extending an LOV is a
major design change. The applicant
must comply with the relevant provisions of subparts D or E of part 21 of
this subchapter and paragraph (b) of
this section.
(b) Extended limit of validity. Each person applying for an extended LOV must
comply with the following requirements:
(1) Establish an extended LOV that
corresponds 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 demonstration must include an evaluation of airplane 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 hightime airplanes of similar structural design, accounting for differences in operating conditions and procedures. The
airplane structural configurations to
be evaluated include - 
(i) All model variations and derivatives approved under the type certificate for which approval for an extension is sought; and
(ii) All structural modifications to
and replacements for the airplane
structural configurations specified in
paragraph (b)(1)(i) of this section, mandated by airworthiness directive, up to
the date of approval of the extended
LOV.
(2) Establish a revision or supplement, as applicable, to the Airworthiness Limitations section (ALS) of the
Instructions for Continued Airworthiness required by Section 25.1529 of this subchapter, and submit it to the responsible Aircraft Certification Service office for approval. The revised ALS or
supplement to the ALS must include
the applicable extended LOV established under paragraph (b)(1) of this
section.
(3) Develop the maintenance actions
determined by the WFD evaluation performed in paragraph (b)(1) of this section to be necessary to preclude WFD
from occurring before the airplane

reaches the proposed extended LOV.
These maintenance actions must be
documented as airworthiness limitation 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
SOURCE: Docket No. FAA-2005-22997, 73 FR
42499, July 21, 2008, unless otherwise noted.

Section 26.31

Definitions.

For purposes of this subpart - 
(a) Fleet Average Flammability Exposure has the meaning defined in Appendix 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).
Section 26.33 Holders of type certificates:
Fuel tank flammability.
(a) Applicability. This section applies
to U.S. type certificated transport category, turbine-powered airplanes, other
than those designed solely for all-cargo
operations, for which the State of Manufacture issued the original certificate
of airworthiness or export airworthiness approval on or after January 1,
1992, that, as a result of original type
certification or later increase in capacity have:
(1) A maximum type-certificated passenger 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 December 26, 2008, holders of type certificates
must submit for approval to the responsible Aircraft Certification Service
office a flammability exposure analysis
of all fuel tanks defined in the type design, as well as all design variations
approved under the type certificate
that affect flammability exposure. This
analysis must be conducted in accordance with Appendix N of part 25 of this
chapter.
(2) Exception. This paragraph (b) does
not apply to - 

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