Federal Aviation Administration, DOT

Section 26.45

(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; Doc. No. FAA-2018-0119,
Amdt. 26-7, 83 FR 9170, Mar. 5, 2018]

spaschal on DSK3GDR082PROD with CFR

Section 26.45 Holders of type certificates - Alterations and repairs to alterations.
(a) Applicability. This section applies
to transport category airplanes subject
to Section 26.43.
(b) Fatigue critical alteration structure.
For existing and future alteration data
developed by the holder of a type certificate, the holder must - 
(1) Review alteration data and identify all alterations that affect fatigue
critical baseline structure identified
under Section 26.43(b)(1);
(2) For each alteration identified
under paragraph (b)(1) of this section,
identify any fatigue critical alteration
structure;
(3) Develop and submit to the responsible Aircraft Certification Service office for review and approval a list of
the structure identified under paragraph (b)(2) of this section; and
(4) Upon approval, make the list required in paragraph (b)(3) of this section available to persons required to
comply with SectionSection 121.1109 and 129.109 of
this chapter.
(c) DT Data. For existing and future
alteration data developed by the holder
of a type certificate that affect fatigue
critical baseline structure identified
under Section 26.43(b)(1), unless previously accomplished, the holder must - 
(1) Perform a DTE and develop the
DTI for the alteration and fatigue crit-

ical baseline structure that is affected
by the alteration;
(2) Submit the DT data developed in
accordance with paragraphs (c)(1) of
this section to the responsible Aircraft
Certification Service office or its properly authorized designees for review
and approval; and
(3) Upon approval, make the DTI
available to persons required to comply
with SectionSection 121.1109 and 129.109 of this chapter.
(d) DT Data for Repairs Made to Alterations. For existing and future repair
data developed by a holder of a type
certificate, the type certificate holder
must - 
(1) Review the repair data, and identify each repair that affects any fatigue critical alteration structure identified under paragraph (b)(2) of this section;
(2) For each repair identified under
paragraph (d)(1) of this section, unless
previously accomplished, perform a
DTE and develop DTI;
(3) Submit the DT data developed in
accordance with paragraph (d)(2) of
this section to the responsible Aircraft
Certification Service office or its properly authorized designees for review
and approval; and
(4) Upon approval, make the DTI
available to persons required to comply
with SectionSection 121.1109 and 129.109 of this chapter.
(e) Compliance times. Holders of type
certificates must submit the following
to the responsible Aircraft Certification Service office or its properly authorized designees for review and approval by the specified compliance
time:
(1) The list of fatigue critical alteration structure identified under paragraph (b)(3) of this section must be submitted - 
(i) No later than 360 days after January 11, 2008, for alteration data approved before January 11, 2008.
(ii) No later than 30 days after March
12, 2010 or before initial approval of the
alteration data, whichever occurs
later, for alteration data approved on
or after January 11, 2008.
(2) For alteration data developed and
approved before January 11, 2008, the
DT data required by paragraph (c)(2) of

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