473
Federal Aviation Administration, DOT
§ 26.21
issued on or after December 10, 2007:
December 10, 2009 or the date the cer-
tificate is issued, whichever occurs
later.
(3) Unless compliance with § 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 applica-
tion 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 § 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 responsible
Aircraft Certification Service office for
approval a compliance plan by March
10, 2008. The compliance plan must in-
clude the following information:
(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 responsible Aircraft Cer-
tification Service office not less than
60 days before the compliance time
specified in paragraph (d) of this sec-
tion.
(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 Safe-
ty—Widespread Fatigue Dam-
age
S
OURCE
: Docket 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
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14 CFR Ch. I (1–1–24 Edition)
§ 26.21
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—
(i) All model variations and deriva-
tives approved under the type certifi-
cate; and
(ii) All structural modifications to
and replacements for the airplane
structural configurations specified in
paragraph (b)(1)(i) of this section, man-
dated by airworthiness directives as of
January 14, 2011.
(2) If the LOV depends on perform-
ance of maintenance actions for which
service information has not been man-
dated by airworthiness directive as of
January 14, 2011, submit the following
to the responsible Aircraft Certifi-
cation Service office:
(i) For those maintenance actions for
which service information has been
issued as of the applicable compliance
date specified in paragraph (c) of this
section, a list identifying each of those
actions.
(ii) For those maintenance actions
for which service information has not
been issued as of the applicable compli-
ance date specified in paragraph (c) of
this section, a list identifying each of
those actions and a binding schedule
for providing in a timely manner the
necessary service information for those
actions. Once the responsible Aircraft
Certification Service office approves
this schedule, each person identified in
paragraph (c) of this section must com-
ply with that schedule.
(3) Unless previously accomplished,
establish an Airworthiness Limitations
section (ALS) for each airplane struc-
tural configuration evaluated under
paragraph (b)(1) of this section.
(4) Incorporate the applicable LOV
established under paragraph (b)(1) of
this section into the ALS for each air-
plane structural configuration evalu-
ated under paragraph (b)(1) and submit
it to the responsible Aircraft Certifi-
cation Service office for approval.
(c)
Persons who must comply and com-
pliance dates. The following persons
must comply with the requirements of
paragraph (b) of this section by the
specified date.
(1) Holders of type certificates (TC)
of airplane models identified in Table 1
of this section: No later than the appli-
cable date identified in Table 1 of this
section.
(2) Applicants for TCs, if the date of
application was before January 14, 2011:
No later than the latest of the fol-
lowing dates:
(i) January 14, 2016;
(ii) The date the certificate is issued;
or
(iii) The date specified in the plan ap-
proved under § 25.571(b) for completion
of the full-scale fatigue testing and
demonstrating that widespread fatigue
damage will not occur in the airplane
structure.
(3) Applicants for amendments to
TCs, with the exception of amendments
to TCs specified in paragraphs (c)(6) or
(c)(7) of this section, if the original TC
was issued before January 14, 2011: No
later than the latest of the following
dates:
(i) January 14, 2016;
(ii) The date the amended certificate
is issued; or
(iii) The date specified in the plan ap-
proved under § 25.571(b) for completion
of the full-scale fatigue testing and
demonstrating that widespread fatigue
damage will not occur in the airplane
structure.
(4) Applicants for amendments to
TCs, with the exception of amendments
to TCs specified in paragraphs (c)(6) or
(c)(7) of this section, if the application
for the original TC was made before
January 14, 2011 but the TC was not
issued before January 14, 2011: No later
than the latest of the following dates:
(i) January 14, 2016;
(ii) The date the amended certificate
is issued; or
(iii) The date specified in the plan ap-
proved under § 25.571(b) for completion
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Federal Aviation Administration, DOT
§ 26.21
of the full-scale fatigue testing and
demonstrating that widespread fatigue
damage will not occur in the airplane
structure.
(5) Holders of either supplemental
type certificates (STCs) or amend-
ments to TCs that increase maximum
takeoff gross weights from 75,000
pounds or less to greater than 75,000
pounds: No later than July 14, 2012.
(6) Applicants for either STCs or
amendments to TCs that increase max-
imum takeoff gross weights from 75,000
pounds or less to greater than 75,000
pounds: No later than the latest of the
following dates:
(i) July 14, 2012;
(ii) The date the certificate is issued;
or
(iii) The date specified in the plan ap-
proved under § 25.571(b) for completion
of the full-scale fatigue testing and
demonstrating that widespread fatigue
damage will not occur in the airplane
structure.
(7) Applicants for either STCs or
amendments to TCs that decrease max-
imum takeoff gross weights from
greater than 75,000 pounds to 75,000
pounds or less, if the date of applica-
tion was after January 14, 2011: No
later than the latest of the following
dates:
(i) July 14, 2012;
(ii) The date the certificate is issued;
or
(iii) The date specified in the plan ap-
proved under § 25.571(b) for completion
of the full-scale fatigue testing and
demonstrating that widespread fatigue
damage will not occur in the airplane
structure.
(d)
Compliance plan. Each person
identified in paragraph (e) of this sec-
tion must submit a compliance plan
consisting of the following:
(1) A proposed project schedule, iden-
tifying all major milestones, for meet-
ing the compliance dates specified in
paragraph (c) of this section.
(2) A proposed means of compliance
with paragraphs (b)(1) through (b)(4) of
this section.
(3) A proposal for submitting a draft
of all compliance items required by
paragraph (b) of this section for review
by the responsible Aircraft Certifi-
cation Service office not less than 60
days before the compliance date speci-
fied in paragraph (c) of this section, as
applicable.
(4) A proposal for how the LOV will
be distributed.
(e)
Compliance dates for compliance
plans. The following persons must sub-
mit the compliance plan described in
paragraph (d) of this section to the re-
sponsible Aircraft Certification Service
office by the specified date.
(1) Holders of type certificates: No
later than April 14, 2011.
(2) Applicants for TCs and amend-
ments to TCs, with the exception of
amendments to TCs specified in para-
graphs (e)(4), (e)(5), or (e)(6) of this sec-
tion, if the date of application was be-
fore January 14, 2011 but the TC or TC
amendment was not issued before Jan-
uary 14, 2011: No later than April 14,
2011.
(3) Holders of either supplemental
type certificates or amendments to TCs
that increase maximum takeoff gross
weights from 75,000 pounds or less to
greater than 75,000 pounds: No later
than April 14, 2011.
(4) Applicants for either STCs or
amendments to TCs that increase max-
imum takeoff gross weights from 75,000
pounds or less to greater than 75,000
pounds, if the date of application was
before January 14, 2011: No later than
April 14, 2011.
(5) Applicants for either STCs or
amendments to TCs that increase max-
imum takeoff gross weights from 75,000
pounds or less to greater than 75,000
pounds, if the date of application is on
or after January 14, 2011: Within 90
days after the date of application.
(6) Applicants for either STCs or
amendments to TCs that decrease max-
imum takeoff gross weights from
greater than 75,000 pounds to 75,000
pounds or less, if the date of applica-
tion is on or after January 14, 2011:
Within 90 days after the date of appli-
cation.
(f)
Compliance plan implementation.
Each affected person must implement
the compliance plan as approved in
compliance with paragraph (d) of this
section.
(g)
Exceptions. This section does not
apply to the following airplane models:
(1) Bombardier BD–700.
(2) Bombardier CL–44.
(3) Gulfstream GV.
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14 CFR Ch. I (1–1–24 Edition)
§ 26.23
(4) Gulfstream GV–SP.
(5) British Aerospace, Aircraft Group,
and Societe Nationale Industrielle
Aerospatiale Concorde Type 1.
(6) British Aerospace (Commercial
Aircraft) Ltd., Armstrong Whitworth
Argosy A.W. 650 Series 101.
(7) British Aerospace Airbus, Ltd.,
BAC 1–11.
(8) BAE Systems (Operations) Ltd.,
BAe 146.
(9) BAE Systems (Operations) Ltd.,
Avro 146.
(10) Lockheed 300–50A01 (USAF
C141A).
(11) Boeing 707.
(12) Boeing 720.
(13) deHavilland D.H. 106 Comet 4C.
(14) Ilyushin Aviation IL–96T.
(15) Bristol Aircraft Britannia 305.
(16) Avions Marcel Dassault-Breguet
Aviation Mercure 100C.
(17) Airbus Caravelle.
(18) D & R Nevada, LLC, Convair
Model 22.
(19) D & R Nevada, LLC, Convair
Model 23M.
T
ABLE
1—C
OMPLIANCE
D
ATES FOR
A
FFECTED
A
IRPLANES
Airplane model
(all existing
1
models)
Compliance date—
(months after January
14, 2011)
Airbus:
A300 Series ....................................................................................................................................
18
A310 Series, A300–600 Series ......................................................................................................
48
A318 Series ....................................................................................................................................
48
A319 Series ....................................................................................................................................
48
A320 Series ....................................................................................................................................
48
A321 Series ....................................................................................................................................
48
A330–200, –200 Freighter, –300 Series ........................................................................................
48
A340–200, –300, –500, –600 Series ..............................................................................................
48
A380–800 Series ............................................................................................................................
60
Boeing:
717 ..................................................................................................................................................
48
727 (all series) ................................................................................................................................
18
737 (Classics): 737–100, –200, –200C, –300, –400, –500 ...........................................................
18
737 (NG): 737–600, –700, –700C, –800, –900, –900ER ..............................................................
48
747 (Classics): 747–100, –100B, –100B SUD, –200B, –200C, –200F, –300, 747SP, 747SR .....
18
747–400: 747–400, –400D, –400F .................................................................................................
48
757 ..................................................................................................................................................
48
767 ..................................................................................................................................................
48
777–200, –300 ................................................................................................................................
48
777–200LR, 777–300ER, 777F ......................................................................................................
60
Bombardier:
CL–600: 2D15 (Regional Jet Series 705), 2D24 (Regional Jet Series 900) .................................
60
Embraer:
ERJ 170 ..........................................................................................................................................
60
ERJ 190 ..........................................................................................................................................
60
Fokker:
F.28 Mark 0070, Mark 0100 ...........................................................................................................
18
Lockheed:
L–1011 ............................................................................................................................................
18
188 ..................................................................................................................................................
18
382 (all series) ................................................................................................................................
18
McDonnell Douglas:
DC–8, –8F .......................................................................................................................................
18
DC–9 ...............................................................................................................................................
18
MD–80 (DC–9–81, –82, –83, –87, MD–88) ...................................................................................
18
MD–90 .............................................................................................................................................
48
DC–10 .............................................................................................................................................
18
MD–10 .............................................................................................................................................
48
MD–11, –11F ..................................................................................................................................
48
All Other Airplane Models Listed on a Type Certificate as of January 14, 2011 ..........................
60
1
Type certificated as of January 14, 2011.
[Doc. No. FAA–2006–24281, 75 FR 69782, Nov.
15, 2010, as amended at 77 FR 30878, May 24,
2012; Doc. No. FAA–2018–0119, Amdt. 26–7, 83
FR 9169, Mar. 5, 2018]
§ 26.23
Extended limit of validity.
(a)
Applicability. Any person may
apply to extend a limit of validity of
the engineering data that supports the
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