389 

Federal Aviation Administration, DOT 

§ 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 imple-
mentation 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 imple-
mentation 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 im-
plementation 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 amend-
ed by Amdt. 129–43, 72 FR 63413, Nov. 8, 2007; 
Docket FAA–2018–0119, Amdt. 129–53, 83 FR 
9174, Mar. 5, 2018] 

§ 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 certifi-
cation or later increase in capacity 
have— 

(1) A maximum type certificated pas-

senger seating capacity of 30 or more; 
or 

(2) A maximum payload capacity of 

7,500 pounds or more. 

(b) 

General requirements. 

After Decem-

ber 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 dam-
age-tolerance-based inspections and 
procedures for airplane structure sus-
ceptible 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, alter-

ations, and modifications. 

The mainte-

nance program for the airplane in-

cludes a means for addressing the ad-
verse effects repairs, alterations, and 
modifications may have on fatigue 
critical structure and on inspections 
required by paragraph (b)(1) of this sec-
tion. 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 Mainte-
nance Inspector for review and ap-
proval. 

[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] 

§ 129.111

Electrical wiring inter-

connection systems (EWIS) mainte-
nance 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 pas-

senger 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 oper-
ate a U.S.-registered airplane identi-
fied in paragraph (a) of this section un-
less the maintenance program for that 
airplane includes inspections and pro-
cedures for EWIS. 

(c) The proposed EWIS maintenance 

program changes must be based on 
EWIS Instructions for Continued Air-
worthiness (ICA) that have been devel-
oped in accordance with the provisions 
of Appendix H of part 25 of this chapter 
applicable to each affected airplane (in-
cluding those ICA developed for supple-
mental type certificates installed on 
each airplane) and that have been ap-
proved by the responsible Aircraft Cer-
tification Service office. 

(1) For airplanes subject to § 26.11 of 

this chapter, the EWIS ICA must com-
ply with paragraphs H25.5(a)(1) and (b). 

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