Section 121.1109
Section 121.1109

14 CFR Ch. I (1-1-19 Edition)
Supplemental inspections.

(a) Applicability. Except as specified
in paragraph (b) 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 seating capacity of 30 or more;
or
(2) A maximum payload capacity of
7,500 pounds or more.
(b) Exception. This section does not
apply to an airplane operated by a certificate holder under this part between
any point within the State of Alaska
and any other point within the State of
Alaska.
(c) 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 includes a means for addressing the adverse effects repairs, alterations, and
modifications may have on fatigue
critical structure and on inspections
required by paragraph (c)(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 paragraphs (c)(1)
and (c)(2) of this section, and any later
revisions to these changes, must be
submitted to the Principal Mainte-

nance Inspector for review and approval.
[Doc. No. FAA-1999-5401, 70 FR 5532, Feb. 2,
2005. Redesignated by Amdt. 121-336, 72 FR
63412, Nov. 8, 2007; Amdt. 121-337, 72 FR 70508,
Dec. 12, 2007; Docket FAA-2018-0119, Amdt.
121-380, 83 FR 9173, Mar. 5, 2018]

Section 121.1111 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 certificate holder may operate an airplane
identified in paragraph (a) of this section unless the maintenance program
for that airplane includes inspections
and procedures for electrical wiring
interconnection systems (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).
(2) For airplanes subject to Section 25.1729 of
this chapter, the EWIS ICA must comply with paragraph H25.4 and all of
paragraph H25.5.
(d) After March 10, 2011, before returning an airplane to service after any
alterations for which EWIS ICA are developed, the certificate holder must include in the airplane-s maintenance
program inspections and procedures for
EWIS based on those ICA.
(e) The EWIS maintenance program
changes identified in paragraphs (c)
and (d) of this section and any later
EWIS revisions must be submitted to

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