14 CFR 129.107 - Repairs assessment for pressurized fuselages.

§ 129.107 Repairs assessment for pressurized fuselages.
(a) No foreign air carrier or foreign persons operating a U.S. registered airplane may operate an Airbus Model A300 (excluding −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 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 FAA Aircraft Certification Office (ACO), or office of the Transport Airplane Directorate, having cognizance over 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 60,00 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 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]

Title 14 published on 2014-01-01

no entries appear in the Federal Register after this date.

Title 14 published on 2014-01-01

The following are ALL rules, proposed rules, and notices (chronologically) published in the Federal Register relating to 14 CFR 129 after this date.

  • 2014-08-15; vol. 79 # 158 - Friday, August 15, 2014
    1. 79 FR 48098 - Fuel Tank Vent Fire Protection
      GPO FDSys XML | Text
      DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration
      Notice of proposed rulemaking (NPRM).
      Send comments on or before November 13, 2014.
      14 CFR Parts 25, 121, and 129