Federal Aviation Administration, DOT

Section 129.111

(7) For all models of the Boeing 747,
the flight cycle implementation time is
15,000 flights.
(8) For all models of the McDonnell
Douglas DC-8, the flight cycle implementation time is 30,000 flights.
(9) For all models of the McDonnell
Douglas DC-9/MD-80, the flight cycle
implementation time is 60,000 flights.
(10) For all models of the McDonnell
Douglas DC-10, the flight cycle implementation time is 30,000 flights.
(11) For all models of the Lockheed
L-1011, the flight cycle implementation
time is 27,000 flights.
(12) For the Fokker F-28 Mark 1000,
2000, 3000, and 4000, the flight cycle implementation time is 60,000 flights.
(b) [Reserved]
[Doc. No. 29104, 65 FR 24126, Apr. 25, 2000; 65
FR 35703, June 5, 2000, as amended by Amdt.
129-30, 66 FR 23131, May 7, 2001; Amdt. 129-35,
67 FR 72834, Dec. 9, 2002; Amdt. 129-39, 69 FR
45942, July 30, 2004. Redesignated and amended by Amdt. 129-43, 72 FR 63413, Nov. 8, 2007;
Docket FAA-2018-0119, Amdt. 129-53, 83 FR
9174, Mar. 5, 2018]

Section 129.109 Supplemental inspections for
U.S.-registered aircraft.
(a) Applicability. This section applies
to U.S.-registered, transport category,
turbine powered airplanes with a type
certificate issued after January 1, 1958
that as a result of original type certification or later increase in capacity
have - 
(1) A maximum type certificated passenger seating capacity of 30 or more;
or
(2) A maximum payload capacity of
7,500 pounds or more.
(b) General requirements. After December 20, 2010, a certificate holder may
not operate an airplane under this part
unless the following requirements have
been met:
(1) Baseline Structure. The certificate
holder-s maintenance program for the
airplane includes FAA-approved damage-tolerance-based inspections and
procedures for airplane structure susceptible to fatigue cracking that could
contribute to a catastrophic failure.
For the purpose of this section, this
structure is termed  - fatigue critical
structure. - 
(2) Adverse effects of repairs, alterations, and modifications. The maintenance program for the airplane in-

cludes a means for addressing the adverse effects repairs, alterations, and
modifications may have on fatigue
critical structure and on inspections
required by paragraph (b)(1) of this section. The means for addressing these
adverse effects must be approved by
the responsible Aircraft Certification
Service office.
(3) Changes to maintenance program.
The changes made to the maintenance
program required by paragraph (b)(1)
and (b)(2) of this section, and any later
revisions to these changes, must be
submitted to the Principal Maintenance Inspector for review and approval.
[Doc. No. FAA-1999-5401, 70 FR 5532, Feb. 2,
2005. Redesignated by Amdt. 129-43, 72 FR
63413, Nov. 8, 2007; Amdt. 129-44, 72 FR 70508,
Dec. 12, 2007; Docket FAA-2018-0119, Amdt.
129-53, 83 FR 9174, Mar. 5, 2018]

Section 129.111 Electrical
wiring
interconnection systems (EWIS) maintenance program.
(a) Except as provided in paragraph
(f) of this section, this section applies
to transport category, turbine-powered
airplanes with a type certificate issued
after January 1, 1958, that, as a result
of original type certification or later
increase in capacity, have - 
(1) A maximum type-certificated passenger capacity of 30 or more, or
(2) A maximum payload capacity of
7500 pounds or more.
(b) After March 10, 2011, no foreign
person or foreign air carrier may operate a U.S.-registered airplane identified in paragraph (a) of this section unless the maintenance program for that
airplane includes inspections and procedures for EWIS.
(c) The proposed EWIS maintenance
program changes must be based on
EWIS Instructions for Continued Airworthiness (ICA) that have been developed in accordance with the provisions
of Appendix H of part 25 of this chapter
applicable to each affected airplane (including those ICA developed for supplemental type certificates installed on
each airplane) and that have been approved by the responsible Aircraft Certification Service office.
(1) For airplanes subject to Section 26.11 of
this chapter, the EWIS ICA must comply with paragraphs H25.5(a)(1) and (b).

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