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14 CFR Ch. I (1–1–14 Edition)
§ 26.45
existing repairs that affect fatigue
critical baseline structure identified
under paragraph (b)(1) of this section
and § 26.45(b)(2);
(ii) A process that will enable opera-
tors to obtain the DTI for repairs iden-
tified under paragraph (e)(1)(i) of this
section; and
(iii) An implementation schedule for
repairs covered by the repair evalua-
tion guidelines. The implementation
schedule must identify times when ac-
tions must be taken as specific num-
bers of airplane flight hours, flight cy-
cles, or both.
(2) Submit the repair evaluation
guidelines to the FAA Oversight Office
for review and approval.
(3) Upon approval, make the guide-
lines available to persons required to
comply with §§ 121.1109 and 129.109 of
this chapter.
(4) If the guidelines direct the oper-
ator to obtain assistance from the
holder of a type certificate, make such
assistance available in accordance with
the implementation schedule.
(f)
Compliance times. Holders of type
certificates must submit the following
to the FAA Oversight Office or its
properly authorized designees for re-
view and approval by the specified
compliance time:
(1) The identified list of fatigue crit-
ical baseline structure required by
paragraph (b)(2) of this section must be
submitted no later than 180 days after
January 11, 2008 or before issuance of
the type certificate, whichever occurs
later.
(2) For published repair data that are
current as of January 11, 2008, the DT
data required by paragraph (c)(3) of
this section must be submitted by June
30, 2009.
(3) For repair data published after
January 11, 2008, the DT data required
by paragraph (c)(3) of this section must
be submitted before FAA approval of
the repair data.
(4) For unpublished repair data devel-
oped after January 11, 2008, the DT
data required by paragraph (d)(1) of
this section must be submitted within
12 months of the airplane’s return to
service or in accordance with a sched-
ule approved by the FAA Oversight Of-
fice.
(5) The repair evaluation guidelines
required by paragraph (e)(1) of this sec-
tion must be submitted by December
30, 2009.
(g)
Exceptions. The requirements of
this section do not apply to the fol-
lowing transport category airplane
models:
(1) Convair CV–240, 340, 440, if modi-
fied to include turbine engines.
(2) Vickers Armstrong Viscount,
TCDS No. A–814.
(3) Douglas DC–3, if modified to in-
clude turbine engines, TCDS No. A–618.
(4) Bombardier CL–44, TCDS No.
1A20.
(5) Mitsubishi YS–11, TCDS No.
A1PC.
(6) British Aerospace BAC 1–11, TCDS
No. A5EU.
(7) Concorde, TCDS No. A45EU.
(8) deHavilland D.H. 106 Comet 4C,
TCDS No. 7A10.
(9) deHavilland DHC–7, TCDS No.
A20EA.
(10) VFW-Vereinigte Flugtechnische
Werk VFW–614, TCDS No. A39EU.
(11) Illyushin Aviation IL 96T, TCDS
No. A54NM.
(12) Bristol Aircraft Britannia 305,
TCDS No. 7A2.
(13) Handley Page Herald Type 300,
TCDS No. A21N.
(14) Avions Marcel Dassault—Breguet
Aviation Mercure 100C, TCDS No.
A40EU.
(15) Airbus Caravelle, TCDS No. 7A6.
(16) Lockheed L–300, TCDS No. A2S0.
(17) Boeing 707–100/–200, TCDS No.
4A21.
(18) Boeing 707–300/–400, TCDS No.
4A26.
(19) Boeing 720, TCDS No. 4A28.
[Doc. No. FAA–2005–21693, 72 FR 70505, Dec.
12, 2007, as amended by Amdt. 26–4, 75 FR
11734, Mar. 12, 2010]
§ 26.45
Holders of type certificates—Al-
terations and repairs to alterations.
(a)
Applicability. This section applies
to transport category airplanes subject
to § 26.43.
(b)
Fatigue critical alteration structure.
For existing and future alteration data
developed by the holder of a type cer-
tificate, the holder must—
(1) Review alteration data and iden-
tify all alterations that affect fatigue
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