Source: https://www.ecfr.gov/cgi-bin/text-idx?mc=true&node=sp14.3.121.aa&rgn=div6
Timestamp: 2020-04-03 21:32:06
Document Index: 162266144

Matched Legal Cases: ['art 121', '§121', '§121', '§121', '§121', '§121', '§121', '§121', '§121', 'art 119', '§25', '§26', 'art 25', '§26', '§26', '§26', 'art 25', '§26', '§26', '§26']

Title 14 → Chapter I → Subchapter G → Part 121 → Subpart AA
§121.1101 Purpose and definition.
§121.1103 [Reserved]
§121.1105 Aging airplane inspections and records reviews.
§121.1109 Supplemental inspections.
§121.1111 Electrical wiring interconnection systems (EWIS) maintenance program.
§121.1113 Fuel tank system maintenance program.
§121.1115 Limit of validity.
§121.1119 Fuel tank vent explosion protection.
Source: Amdt. 121-336, 72 FR 63411, Nov. 8, 2007, unless otherwise noted.
(a) This subpart requires persons holding an air carrier or operating certificate under part 119 of this chapter to support the continued airworthiness of each airplane. These requirements may include, but are not limited to, revising the maintenance program, incorporating design changes, and incorporating revisions to Instructions for Continued Airworthiness.
(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.
[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]
(a) Applicability. This section applies to certificate holders operating any transport category, turbine-powered airplane with a maximum takeoff gross weight greater than 75,000 pounds and a type certificate issued after January 1, 1958, regardless of whether the maximum takeoff gross weight is a result of an original type certificate or a later design change. This section also applies to certificate holders operating any transport category, turbine-powered airplane with a type certificate issued after January 1, 1958, regardless of the maximum takeoff gross weight, for which a limit of validity of the engineering data that supports the structural maintenance program (hereafter referred to as LOV) is required in accordance with §25.571 or §26.21 of this chapter after January 14, 2011.
(b) Limit of validity. No certificate holder may operate an airplane identified in paragraph (a) of this section after the applicable date identified in Table 1 of this section unless an Airworthiness Limitations section approved under Appendix H to part 25 or §26.21 of this chapter is incorporated into its maintenance program. The ALS must—
(c) Operation of airplanes excluded from §26.21. No certificate holder may operate an airplane identified in §26.21(g) of this chapter after July 14, 2013, unless an Airworthiness Limitations section approved under Appendix H to part 25 or §26.21 of this chapter is incorporated into its maintenance program. The ALS must—
(i) Includes an extended LOV and any widespread fatigue damage airworthiness limitation items approved under §26.23 of this chapter; and
(ii) Is approved under §26.23 of this chapter.
[Docket FAA-2014-0500, Amdt. 121-375, 81 FR 41208, June 24, 2016]