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Federal Aviation Administration, DOT § 121.1107

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Federal Aviation Administration, DOT § 121.1107 Federal Aviation Administration, DOT § 121.1107 specified by the Administrator, to- to the fuselage pressure boundary (fu- gether with records containing the fol- selage skin, door skin, and bulkhead lowing information: webs), and those guidelines are incor- (1) Total years in service of the air- porated in its maintenance program. plane; The repair assessment guidelines must (2) Total time in service of the air- be approved by the responsible Aircraft frame; Certification Service office for the type (3) Total flight cycles of the air- certificate for the affected airplane. frame; (1) For the Airbus Model A300 (ex- (4) Date of the last inspection and cluding the –600 series), the flight cycle records review required by this section; implementation time is: (5) Current status of life-limited (i) Model B2: 36,000 flights. parts of the airframe; (ii) Model B4–100 (including Model (6) Time since the last overhaul of all B4–2C): 30,000 flights above the window structural components required to be line, and 36,000 flights below the win- overhauled on a specific time basis; dow line. (7) Current inspection status of the (iii) Model B4–200: 25,500 flights above airplane, including the time since the the window line, and 34,000 flights last inspection required by the inspec- below the window line. tion program under which the airplane (2) For all models of the British Aero- is maintained; space BAC 1–11, the flight cycle imple- (8) Current status of applicable air- mentation time is 60,000 flights. worthiness directives, including the (3) For all models of the Boeing 707, date and methods of compliance, and if the flight cycle implementation time is the airworthiness directive involves re- 15,000 flights. curring action, the time and date when (4) For all models of the Boeing 720, the next action is required; the flight cycle implementation time is (9) A list of major structural alter- 23,000 flights. ations; and (5) For all models of the Boeing 727, (10) A report of major structural re- the flight cycle implementation time is pairs and the current inspection status 45,000 flights. (6) For all models of the Boeing 737, for those repairs. the flight cycle implementation time is (e) Notification to Administrator. Each 60,000 flights. certificate holder must notify the Ad- (7) For all models of the Boeing 747, ministrator at least 60 days before the the flight cycle implementation time is date on which the airplane and air- 15,000 flights. plane records will be made available (8) For all models of the McDonnell for the inspection and records review. Douglas DC–8, the flight cycle imple- [Doc. No. FAA–1999–5401, 67 FR 72761, Dec. 6, mentation time is 30,000 flights. 2002, as amended by Amdt. 121–284, 70 FR (9) For all models of the McDonnell 5532, Feb. 2, 2005; Amdt. 121–310, 70 FR 23936, Douglas DC–9/MD–80, the flight cycle May 6, 2005. Redesignated by Amdt. 121–336, implementation time is 60,000 flights. 72 FR 63412, Nov. 8, 2007] (10) For all models of the McDonnell Douglas DC–10, the flight cycle imple- § 121.1107 Repairs assessment for pres- surized fuselages. mentation time is 30,000 flights. (11) For all models of the Lockheed (a) No certificate holder may operate L–1011, the flight cycle implementation an Airbus Model A300 (excluding the time is 27,000 flights. –600 series), British Aerospace Model (12) For the Fokker F–28 Mark 1000, BAC 1–11, Boeing Model 707, 720, 727, 2000, 3000, and 4000, the flight cycle im- 737, or 747, McDonnell Douglas Model plementation time is 60,000 flights. DC–8, DC–9/MD–80 or DC–10, Fokker (b) [Reserved] Model F28, or Lockheed Model L–1011 airplane beyond the applicable flight [Doc. No. 29104, 65 FR 24125, Apr. 25, 2000; 65 cycle implementation time specified FR 50744, Aug. 21, 2000, as amended by Amdt. 121–282, 66 FR 23130, May 7, 2001; ; Amdt. 121– below, or May 25, 2001, whichever oc- 305, 69 FR 45942, July 30, 2004. Redesignated curs later, unless operations specifica- and amended by Amdt. 121–336, 72 FR 63412, tions have been issued to reference re- Nov. 8, 2007; Docket FAA–2018–0119, Amdt. pair assessment guidelines applicable 121–380, 83 FR 9173, Mar. 5, 2018] 247 VerDate Sep<11>2014 08:20 May 17, 2019 Jkt 247048 PO 00000 Frm 00257 Fmt 8010 Sfmt 8010 Y:\SGML\247048.XXX 247048.
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