Federal Aviation Administration, DOT

Section 121.1107

specified by the Administrator, together with records containing the following information:
(1) Total years in service of the airplane;
(2) Total time in service of the airframe;
(3) Total flight cycles of the airframe;
(4) Date of the last inspection and
records review required by this section;
(5) Current status of life-limited
parts of the airframe;
(6) Time since the last overhaul of all
structural components required to be
overhauled on a specific time basis;
(7) Current inspection status of the
airplane, including the time since the
last inspection required by the inspection program under which the airplane
is maintained;
(8) Current status of applicable airworthiness directives, including the
date and methods of compliance, and if
the airworthiness directive involves recurring action, the time and date when
the next action is required;
(9) A list of major structural alterations; and
(10) A report of major structural repairs and the current inspection status
for those repairs.
(e) Notification to Administrator. Each
certificate holder must notify the Administrator at least 60 days before the
date on which the airplane and airplane records will be made available
for the inspection and records review.
[Doc. No. FAA-1999-5401, 67 FR 72761, Dec. 6,
2002, as amended by Amdt. 121-284, 70 FR
5532, Feb. 2, 2005; Amdt. 121-310, 70 FR 23936,
May 6, 2005. Redesignated by Amdt. 121-336,
72 FR 63412, Nov. 8, 2007]

Section 121.1107 Repairs assessment for pressurized fuselages.
(a) No certificate holder may operate
an Airbus Model A300 (excluding the
-600 series), British Aerospace Model
BAC 1-11, Boeing Model 707, 720, 727,
737, or 747, McDonnell Douglas Model
DC-8, DC-9/MD-80 or DC-10, Fokker
Model F28, or Lockheed Model L-1011
airplane beyond the applicable flight
cycle implementation time specified
below, or May 25, 2001, whichever occurs later, unless operations specifications have been issued to reference repair assessment guidelines applicable

to the fuselage pressure boundary (fuselage skin, door skin, and bulkhead
webs), and those guidelines are incorporated in its maintenance program.
The repair assessment guidelines must
be approved by the responsible Aircraft
Certification Service office for the type
certificate for the affected airplane.
(1) For the Airbus Model A300 (excluding the -600 series), the flight cycle
implementation time is:
(i) Model B2: 36,000 flights.
(ii) Model B4-100 (including Model
B4-2C): 30,000 flights above the window
line, and 36,000 flights below the window line.
(iii) Model B4-200: 25,500 flights above
the window line, and 34,000 flights
below the window line.
(2) For all models of the British Aerospace BAC 1-11, the flight cycle implementation time is 60,000 flights.
(3) For all models of the Boeing 707,
the flight cycle implementation time is
15,000 flights.
(4) For all models of the Boeing 720,
the flight cycle implementation time is
23,000 flights.
(5) For all models of the Boeing 727,
the flight cycle implementation time is
45,000 flights.
(6) For all models of the Boeing 737,
the flight cycle implementation time is
60,000 flights.
(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 24125, Apr. 25, 2000; 65
FR 50744, Aug. 21, 2000, as amended by Amdt.
121-282, 66 FR 23130, May 7, 2001; ; Amdt. 121-
305, 69 FR 45942, July 30, 2004. Redesignated
and amended by Amdt. 121-336, 72 FR 63412,
Nov. 8, 2007; Docket FAA-2018-0119, Amdt.
121-380, 83 FR 9173, Mar. 5, 2018]

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