background image

481 

Federal Aviation Administration, DOT 

§ 26.41 

any necessary modification parts will 
be made available to affected persons. 

T

ABLE

2—C

OMPLIANCE

P

LANNING

D

ATES

 

Flammability exposure anal-

ysis plan 

Impact assessment plan 

Design changes and service 

instructions plan 

STC and Field Approval Hold-

ers.

March 26, 2009 ......................

February 26, 2011 ..................

August 26, 2011. 

(g) Each person subject to this sec-

tion must implement the compliance 
plans, or later revisions, as approved 
under paragraph (f) of this section. 

[Doc. No. FAA–2005–22997, 73 FR 42499, July 
21, 2008, as amended by Amdt. 26–3, 74 FR 
31619, July 2, 2009; Doc. No. FAA–2018–0119, 
Amdt. 26–7, 83 FR 9170, Mar. 5, 2018] 

§ 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. 

T

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. 

(c) All other fuel tanks that exceed 

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 

S

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. 

VerDate Sep<11>2014 

09:06 Jun 28, 2024

Jkt 262046

PO 00000

Frm 00491

Fmt 8010

Sfmt 8010

Y:\SGML\262046.XXX

262046

jspears on DSK121TN23PROD with CFR

background image

482 

14 CFR Ch. I (1–1–24 Edition) 

§ 26.43 

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 
structure, the basic assumptions ap-
plied in a DTE, and the results of a 
DTE. 

Fatigue critical structure means air-

plane structure that is susceptible to 
fatigue cracking that could contribute 
to a catastrophic failure, as determined 
in accordance with § 25.571 of this chap-
ter. Fatigue critical structure includes 
structure, which, if repaired or altered, 
could be susceptible to fatigue crack-
ing and contribute to a catastrophic 
failure. Such structure may be part of 
the baseline structure or part of an al-
teration. 

Implementation schedule consists of 

documentation that establishes the 
timing for accomplishing the necessary 
actions for developing DT data for re-
pairs and alterations, and for incor-
porating those data into an operator’s 
continuing airworthiness maintenance 
program. The documentation must 
identify times when actions must be 
taken as specific numbers of airplane 
flight hours, flight cycles, or both. 

Published repair data mean instruc-

tions for accomplishing repairs, which 
are published for general use in struc-

tural repair manuals and service bul-
letins (or equivalent types of docu-
ments). 

§ 26.43

Holders of and applicants for 

type certificates—Repairs. 

(a) 

Applicability.  Except as specified 

in paragraph (g) of this section, this 
section applies to transport category, 
turbine powered airplane models with a 
type certificate issued after January 1, 
1958, that as a result of original type 
certification or later increase in capac-
ity have— 

(1) A maximum type certificated pas-

senger seating capacity of 30 or more; 
or 

(2) A maximum payload capacity of 

7,500 pounds or more. 

(b) 

List of fatigue critical baseline struc-

ture.  For airplanes specified in para-
graph (a) of this section, the holder of 
or applicant for a type certificate 
must— 

(1) Identify fatigue critical baseline 

structure for all airplane model vari-
ations and derivatives approved under 
the type certificate; and 

(2) Develop and submit to the respon-

sible Aircraft Certification Service of-
fice for review and approval, a list of 
the structure identified under para-
graph (b)(1) of this section and, upon 
approval, make the list available to 
persons required to comply with § 26.47 
and §§ 121.1109 and 129.109 of this chap-
ter. 

(c) 

Existing and future published repair 

data.  For repair data published by a 
holder of a type certificate that is cur-
rent as of January 11, 2008 and for all 
later published repair data, the holder 
of a type certificate must— 

(1) Review the repair data and iden-

tify each repair specified in the data 
that affects fatigue critical baseline 
structure identified under paragraph 
(b)(1) of this section; 

(2) Perform a DTE and develop the 

DTI for each repair identified under 
paragraph (c)(1) of this section, unless 
previously accomplished; 

(3) Submit the DT data to the respon-

sible Aircraft Certification Service of-
fice or its properly authorized des-
ignees for review and approval; and 

(4) Upon approval, make the DTI 

available to persons required to comply 

VerDate Sep<11>2014 

09:06 Jun 28, 2024

Jkt 262046

PO 00000

Frm 00492

Fmt 8010

Sfmt 8010

Y:\SGML\262046.XXX

262046

jspears on DSK121TN23PROD with CFR