Code of Federal Regulations - Title 14

630

14 CFR Ch. I (1–1–14 Edition)

§ 26.37

Pending type certification

projects: Fuel tank flammability.

(a)

Applicability. This section applies

to any new type certificate for a trans-
port category airplane, if the applica-
tion was made before December 26,
2008, and if the certificate was not
issued before December 26, 2008. This
section applies only if the airplane
would 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) If the application was made on or

after June 6, 2001, the requirements of
14 CFR 25.981 in effect on December 26,
2008, apply.

[Doc. No. FAA–2005–22997, 73 FR 42499, July
21, 2008, as amended by Amdt. 26–3, 74 FR
31619, July 2, 2009]

§ 26.39

Newly produced airplanes: Fuel

tank flammability.

(a)

Applicability: This section applies

to Boeing model airplanes specified in
Table 1 of this section, including pas-
senger and cargo versions of each
model, when application is made for
original certificates of airworthiness or
export airworthiness approvals after
December 27, 2010.

ABLE

Model—Boeing

747 Series
737 Series
777 Series
767 Series

(b) Any fuel tank meeting all of the

criteria stated in paragraphs (b)(1),
(b)(2) and (b)(3) of this section must
have flammability reduction means
(FRM) or ignition mitigation means
(IMM) that meet the requirements of 14
CFR 25.981 in effect on December 26,
2008.

(1) The fuel tank is Normally

Emptied.

(2) Any portion of the fuel tank is lo-

cated within the fuselage contour.

(3) The fuel tank exceeds a Fleet Av-

erage Flammability Exposure of 7 per-
cent.

an Fleet Average Flammability Expo-
sure of 7 percent must have an IMM
that meets 14 CFR 25.981(d) in effect on

December 26, 2008, or an FRM that
meets all of the requirements of Appen-
dix M to this part, except instead of
complying with paragraph M25.1 of
that appendix, the Fleet Average Flam-
mability Exposure may not exceed 7
percent.

[Doc. No. FAA–2005–22997, 73 FR 42499, July
21, 2008, as amended by Amdt. 26–3, 74 FR
31619, July 2, 2009]

Subpart E—Aging Airplane Safe-

ty—Damage Tolerance Data
for Repairs and Alterations

OURCE

: Docket No. FAA–2005–21693, 72 FR

70505, Dec. 12, 2007, unless otherwise noted.

§ 26.41

Definitions.

Affects (or Affected) means structure

has been physically repaired, altered,
or modified, or the structural loads
acting on the structure have been in-
creased or redistributed.

Baseline structure means structure

that is designed under the original type
certificate or amended type certificate
for that airplane model.

Damage Tolerance Evaluation (DTE)

means a process that leads to a deter-
mination of maintenance actions nec-
essary to detect or preclude fatigue
cracking that could contribute to a
catastrophic failure. As applied to re-
pairs and alterations, a DTE includes
the evaluation both of the repair or al-
teration and of the fatigue critical
structure affected by the repair or al-
teration.

Damage Tolerance Inspection (DTI)

means the inspection developed as a re-
sult of a DTE. A DTI includes the areas
to be inspected, the inspection method,
the inspection procedures, including
acceptance and rejection criteria, the
threshold, and any repeat intervals as-
sociated with those inspections. The
DTI may specify a time limit when a
repair or alteration needs to be re-
placed or modified. If the DTE con-
cludes that DT-based supplemental
structural inspections are not nec-
essary, the DTI contains a statement
to that effect.

DT data mean DTE documentation

and the DTI.

DTE documentation means data that

identify the evaluated fatigue critical

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