PWS 2.0_l_CFR Title 14 Part 121.1111 EWIS Maint.pdf

9/30/2021 eCFR :: 14 CFR Part 121 Subpart AA -- Continued Airworthiness and Safety Improvements https://www.ecfr.gov/current/title-14/chapter-I/subchapter-G/part-121?toc=1 1/14

Displaying title 14, up to date as of 9/28/2021. Title 14 was last amended 9/23/2021.

Title 14

Subpart AA - Continued Airworthiness and Safety Improvements

Source: Amdt. 121-336, 72 FR 63411, Nov. 8, 2007, unless otherwise noted.

§ 121.1101 Purpose and de�inition.

[Amdt. 121-336, 72 FR 63411, Nov. 8, 2007, as amended by Docket FAA-2018-0119, Amdt. 121-380, 83 FR 9173, Mar. 5, 2018]

§ 121.1103 [Reserved]

§ 121.1105 Aging airplane inspections and records reviews.

(a) This subpart requires persons holding an air carrier or operating certi�cate 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.

(b) [Reserved]

(a) Applicability. This section applies to all airplanes operated by a certi�cate holder under this part, except for those airplanes operated between any point within the State of Alaska and any other point within the State of Alaska.

(b) Operation after inspection and records review. After the dates speci�ed in this paragraph, a certi�cate holder may not operate an airplane under this part unless the Administrator has noti�ed the certi�cate holder that the Administrator has completed the aging airplane inspection and records review required by this section. During the inspection and records review, the certi�cate holder must demonstrate to the Administrator that the maintenance of age-sensitive parts and components of the airplane has been adequate and timely enough to ensure the highest degree of safety.

(1) Airplanes exceeding 24 years in service on December 8, 2003; initial and repetitive inspections and records reviews.

For an airplane that has exceeded 24 years in service on December 8, 2003, no later than December 5, 2007, and thereafter at intervals not to exceed 7 years.

(2) Airplanes exceeding 14 years in service but not 24 years in service on December 8, 2003; initial and repetitive inspections and records reviews. For an airplane that has exceeded 14 years in service but not 24 years in service on December 8, 2003, no later than December 4, 2008, and thereafter at intervals not to exceed 7 years.

Subpart AA Continued Airworthiness and Safety Improvements 121.1101 – 121.1119 § 121.1101 Purpose and de�nition.

§ 121.1103 [Reserved] § 121.1105 Aging airplane inspections and records reviews.

§ 121.1107 Repairs assessment for pressurized fuselages.

§ 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.

§ 121.1117 Flammability reduction means.

§ 121.1119 Fuel tank vent explosion protection.

ENHANCED CONTENT - TABLE OF CONTENTS

https://www.federalregister.gov/citation/72-FR-63411 https://www.federalregister.gov/citation/72-FR-63411 https://www.federalregister.gov/citation/83-FR-9173 https://www.ecfr.gov/current/title-14/part-119 https://www.ecfr.gov/current/title-14/chapter-I/subchapter-G/part-121/subpart-AA?toc=1 https://www.ecfr.gov/current/title-14/chapter-I/subchapter-G/part-121?toc=1 2/14

[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]

§ 121.1107 Repairs assessment for pressurized fuselages.

(3) Airplanes not exceeding 14 years in service on December 8, 2003; initial and repetitive inspections and records reviews. For an airplane that has not exceeded 14 years in service on December 8, 2003, no later than 5 years after the start of the airplane's 15th year in service and thereafter at intervals not to exceed 7 years.

(c) Unforeseen schedule con�ict. In the event of an unforeseen scheduling con�ict for a speci�c airplane, the Administrator may approve an extension of up to 90 days beyond an interval speci�ed in paragraph (b) of this section.

(d) Airplane and records availability. The certi�cate holder must make available to the Administrator each airplane for which an inspection and records review is required under this section, in a condition for inspection speci�ed 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 �ight 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 speci�c 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) Noti�cation to Administrator. Each certi�cate 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.

(a) No certi�cate 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 �ight cycle implementation time speci�ed below, or May 25, 2001, whichever occurs later, unless operations speci�cations 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 Certi�cation Service o�ce for the type certi�cate for the affected airplane.

(1) For the Airbus Model A300 (excluding the -600 series), the �ight cycle implementation time is:

(i) Model B2: 36,000 �ights.

(ii) Model B4-100 (including Model B4-2C): 30,000 �ights above the window line, and 36,000 �ights below the window line.

(iii) Model B4-200: 25,500 �ights above the window line, and 34,000 �ights below the window line.

(2) For all models of the British Aerospace BAC 1-11, the �ight cycle implementation time is 60,000 �ights.

(3) For all models of the Boeing 707, the �ight cycle implementation time is 15,000 �ights.

(4) For all models of the Boeing 720, the �ight cycle implementation time is 23,000 �ights.

(5) For all models of the Boeing 727, the �ight cycle implementation time is 45,000 �ights.

(6) For all models of the Boeing 737, the �ight cycle implementation time is 60,000 �ights.

(7) For all models of the Boeing 747, the �ight cycle implementation time is 15,000 �ights.

https://www.federalregister.gov/citation/67-FR-72761 https://www.federalregister.gov/citation/70-FR-5532 https://www.federalregister.gov/citation/70-FR-23936 https://www.federalregister.gov/citation/72-FR-63412 https://www.ecfr.gov/current/title-14/section-121.1105#p-121.1105(b) https://www.ecfr.gov/current/title-14/chapter-I/subchapter-G/part-121?toc=1 3/14

[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]

§ 121.1109 Supplemental inspections.

[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]

§ 121.1111 Electrical wiring interconnection systems (EWIS) maintenance program.

(8) For all models of the McDonnell Douglas DC-8, the �ight cycle implementation time is 30,000 �ights.

(9) For all models of the McDonnell Douglas DC-9/MD-80, the �ight cycle implementation time is 60,000 �ights.

(10) For all models of the McDonnell Douglas DC-10, the �ight cycle implementation time is 30,000 �ights.

(11) For all models of the Lockheed L-1011, the �ight cycle implementation time is 27,000 �ights.

(12) For the Fokker F-28 Mark 1000, 2000, 3000, and 4000, the �ight cycle implementation time is 60,000 �ights.

(b) [Reserved]

(a) Applicability. Except as speci�ed in paragraph (b) of this section, this section applies to transport category, turbine powered airplanes with a type certi�cate issued after January 1, 1958, that as a result of original type certi�cation or later increase in capacity have -

(1) A maximum type certi�cated passenger seating capacity of 30 or more; or

(2) A maximum payload capacity of 7,500 pounds or more.

(b) Exception. This section does not apply to an airplane operated by a certi�cate holder under this part between any point within the State of Alaska and any other point within the State of Alaska.

(c) General requirements. After December 20, 2010, a certi�cate holder may not operate an airplane under this part unless the following requirements have been met:

(1) Baseline Structure. The certi�cate holder's maintenance program for the airplane includes FAA-approved damage-tolerance-based inspections and procedures for airplane structure susceptible 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, alterations, and modi�cations. The maintenance program for the airplane includes a means for addressing the adverse effects repairs, alterations, and modi�cations 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 Certi�cation Service o�ce.

(3) Changes to maintenance program. The changes made to the maintenance program required by paragraphs (c)(1) and (c)(2) of this section, and any later revisions to these changes, must be submitted to the Principal Maintenance Inspector for review and approval.

(a) Except as provided in paragraph (f) of this section, this section applies to transport category, turbine-powered airplanes with a type certi�cate issued after January 1, 1958, that, as a result of original type certi�cation or later increase in capacity, have -

(1) A maximum type-certi�cated passenger capacity of 30 or more, or

(2) A maximum payload capacity of 7500 pounds or more.

(b) After March 10, 2011, no certi�cate holder may operate an airplane identi�ed in paragraph (a) of this section unless the maintenance program for that airplane includes inspections and procedures for electrical wiring interconnection systems (EWIS).

(c) The proposed EWIS maintenance program changes must be based on EWIS Instructions for Continued Airworthiness (ICA) that have been developed in accordance with the provisions of Appendix H of part 25 of this chapter applicable to each affected airplane (including those ICA developed for supplemental type certi�cates installed on each airplane) and https://www.federalregister.gov/citation/65-FR-24125 https://www.federalregister.gov/citation/65-FR-50744 https://www.federalregister.gov/citation/66-FR-23130 https://www.federalregister.gov/citation/69-FR-45942 https://www.federalregister.gov/citation/72-FR-63412 https://www.federalregister.gov/citation/83-FR-9173 https://www.federalregister.gov/citation/70-FR-5532 https://www.federalregister.gov/citation/72-FR-63412 https://www.federalregister.gov/citation/72-FR-70508 https://www.federalregister.gov/citation/83-FR-9173 https://www.ecfr.gov/current/title-14/section-121.1109#p-121.1109(b) https://www.ecfr.gov/current/title-14/section-121.1109#p-121.1109(c)(1) https://www.ecfr.gov/current/title-14/section-121.1109#p-121.1109(c)(1) https://www.ecfr.gov/current/title-14/section-121.1109#p-121.1109(c)(2) https://www.ecfr.gov/current/title-14/section-121.1111#p-121.1111(f) https://www.ecfr.gov/current/title-14/section-121.1111#p-121.1111(a) https://www.ecfr.gov/current/title-14/part-25 https://www.ecfr.gov/current/title-14/chapter-I/subchapter-G/part-121?toc=1 4/14

[Amdt. 121-336, 72 FR 63411, Nov. 8, 2007, as amended by Docket FAA-2018-0119, Amdt. 121-380, 83 FR 9173, Mar. 5, 2018]

§ 121.1113 Fuel tank system maintenance program.

that have been approved by the responsible Aircraft Certi�cation Service o�ce.

(1) For airplanes subject to § 26.11 of this chapter, the EWIS ICA must comply with paragraphs H25.5(a)(1) and (b).

(2) For airplanes subject to § 25.1729 of this chapter, the EWIS ICA must comply with paragraph H25.4 and all of paragraph H25.5.

(d) After March 10, 2011, before returning an airplane to service after any alterations for which EWIS ICA are developed, the certi�cate holder must include in the airplane's maintenance program inspections and procedures for EWIS based on those ICA.

(e) The EWIS maintenance program changes identi�ed in paragraphs (c) and (d) of this section and any later EWIS revisions must be submitted to the Principal Inspector for review and approval.

(f) This section does not apply to the following airplane models:

(1) Lockheed L-188

(2) Bombardier CL-44

(3) Mitsubishi YS-11

(4) British Aerospace BAC 1-11

(5) Concorde

(6) deHavilland D.H. 106 Comet 4C

(7) VFW-Vereinigte Flugtechnische Werk VFW-614

(8) Illyushin Aviation IL 96T

(9) Bristol Aircraft Britannia 305

(10) Handley Page Herald Type 300

(11) Avions Marcel Dassault - Breguet Aviation Mercure 100C

(12) Airbus Caravelle

(13) Lockheed L-300

(a) Except as provided in paragraph (g) of this section, this section applies to transport category, turbine-powered airplanes with a type certi�cate issued after January 1, 1958, that, as a result of original type certi�cation or later increase in capacity, have -

(1) A maximum type-certi�cated passenger capacity of 30 or more, or

(2) A maximum payload capacity of 7500 pounds or more.

(b) For each airplane on which an auxiliary fuel tank is installed under a �eld approval, before June 16, 2008, the certi�cate holder must submit to the responsible Aircraft Certi�cation Service o�ce proposed maintenance instructions for the tank that meet the requirements of Special Federal Aviation Regulation No. 88 (SFAR 88) of this chapter.

(c) After December 16, 2008, no certi�cate holder may operate an airplane identi�ed in paragraph (a) of this section unless the maintenance program for that airplane has been revised to include applicable inspections, procedures, and limitations for fuel tanks systems.

(d) The proposed fuel tank system maintenance program revisions must be based on fuel tank system Instructions for Continued Airworthiness (ICA) that have been developed in accordance with the applicable provisions of SFAR 88 of this chapter or § 25.1529 and part 25, Appendix H, of this chapter, in effect on June 6, 2001 (including those developed for auxiliary fuel tanks, if any, installed under supplemental type certi�cates or other design approval) and that have been approved by the responsible Aircraft Certi�cation Service o�ce.

https://www.federalregister.gov/citation/72-FR-63411 https://www.federalregister.gov/citation/83-FR-9173 https://www.ecfr.gov/current/title-14/section-26.11 https://www.ecfr.gov/current/title-14/section-25.1729 https://www.ecfr.gov/current/title-14/section-121.1111#p-121.1111(c) https://www.ecfr.gov/current/title-14/section-121.1111#p-121.1111(d) https://www.ecfr.gov/current/title-14/section-121.1113#p-121.1113(g) https://www.ecfr.gov/current/title-14/section-121.1113#p-121.1113(a) https://www.ecfr.gov/current/title-14/section-25.1529 https://www.ecfr.gov/current/title-14/chapter-I/subchapter-G/part-121?toc=1 5/14

[Amdt. 121-336, 72 FR 63411, Nov. 8, 2007, as amended by Docket FAA-2018-0119, Amdt. 121-380, 83 FR 9173, Mar. 5, 2018]

§ 121.1115 Limit of validity.

(e) After December 16, 2008, before returning an aircraft to service after any alteration for which fuel tank ICA are developed under SFAR 88 or under § 25.1529 in effect on June 6, 2001, the certi�cate holder must include in the maintenance program for the airplane inspections and procedures for the fuel tank system based on those ICA.

(f) The fuel tank system maintenance program changes identi�ed in paragraphs (d) and (e) of this section and any later fuel tank system revisions must be submitted to the Principal Inspector for review and approval.

(g) This section does not apply to the following airplane models:

(1) Bombardier CL-44

(2) Concorde

(3) deHavilland D.H. 106 Comet 4C

(4) VFW-Vereinigte Flugtechnische Werk VFW-614

(5) Illyushin Aviation IL 96T

(6) Bristol Aircraft Britannia 305

(7) Handley Page Herald Type 300

(8) Avions Marcel Dassault - Breguet Aviation Mercure 100C

(9) Airbus Caravelle

(10) Lockheed L-300

(a) Applicability. This section applies to certi�cate holders operating any transport category, turbine-powered airplane with a maximum takeoff gross weight greater than 75,000 pounds and a type certi�cate issued after January 1, 1958, regardless of whether the maximum takeoff gross weight is a result of an original type certi�cate or a later design change. This section also applies to certi�cate holders operating any transport category, turbine-powered airplane with a type certi�cate 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 certi�cate holder may operate an airplane identi�ed in paragraph (a) of this section after the applicable date identi�ed 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 -

(1) Include an LOV approved under § 25.571 or § 26.21 of this chapter, as applicable, except as provided in paragraph

(f) of this section; and

(2) Be clearly distinguishable within its maintenance program.

(c) Operation of airplanes excluded from § 26.21. No certi�cate holder may operate an airplane identi�ed 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 -

(1) Include an LOV approved under § 25.571 or § 26.21 of this chapter, as applicable, except as provided in paragraph

(f) of this section; and

(2) Be clearly distinguishable within its maintenance program.

(d) Extended limit of validity. No certi�cate holder may operate an airplane beyond the LOV, or extended LOV, speci�ed in paragraph (b)(1), (c), (d), or (f) of this section, as applicable, unless the following conditions are met:

(1) An ALS must be incorporated into its maintenance program that -

(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.

https://www.federalregister.gov/citation/72-FR-63411 https://www.federalregister.gov/citation/83-FR-9173 https://www.ecfr.gov/current/title-14/section-25.1529 https://www.ecfr.gov/current/title-14/section-121.1113#p-121.1113(d) https://www.ecfr.gov/current/title-14/section-121.1113#p-121.1113(e) https://www.ecfr.gov/current/title-14/section-25.571 https://www.ecfr.gov/current/title-14/section-26.21 https://www.ecfr.gov/current/title-14/section-121.1115#p-121.1115(a) https://www.ecfr.gov/current/title-14/section-26.21 https://www.ecfr.gov/current/title-14/section-25.571 https://www.ecfr.gov/current/title-14/section-26.21 https://www.ecfr.gov/current/title-14/section-121.1115#p-121.1115(f) https://www.ecfr.gov/current/title-14/section-26.21 https://www.ecfr.gov/current/title-14/section-26.21#p-26.21(g) https://www.ecfr.gov/current/title-14/section-26.21 https://www.ecfr.gov/current/title-14/section-25.571 https://www.ecfr.gov/current/title-14/section-26.21 https://www.ecfr.gov/current/title-14/section-121.1115#p-121.1115(f) https://www.ecfr.gov/current/title-14/section-121.1115#p-121.1115(b)(1) https://www.ecfr.gov/current/title-14/section-121.1115#p-121.1115(c) https://www.ecfr.gov/current/title-14/section-121.1115#p-121.1115(d) https://www.ecfr.gov/current/title-14/section-121.1115#p-121.1115(f) https://www.ecfr.gov/current/title-14/section-26.23 https://www.ecfr.gov/current/title-14/section-26.23 https://www.ecfr.gov/current/title-14/chapter-I/subchapter-G/part-121?toc=1 6/14

Table 1 - Airplanes Subject to § 26.21

Airbus - Existing Models Only:

A300 B2-1A, B2-1C, B2K-3C, B2-203 30 48,000 FC

A300 B4-2C, B4-103 30 40,000 FC

A300 B4-203 30 34,000 FC

A300-600 Series 60 30,000

FC/67,500

FH

A310-200 Series 60 40,000

FC/60,000

FH

A310-300 Series 60 35,000

FC/60,000

FH

A318 Series 60 48,000

FC/60,000

FH

A319 Series 60 48,000

FC/60,000

FH

A320-100 Series 60 48,000

FC/48,000

FH

A320-200 Series 60 48,000

FC/60,000

FH

(2) The extended LOV and the airworthiness limitation items pertaining to widespread fatigue damage must be clearly distinguishable within its maintenance program.

(e) Principal Maintenance Inspector approval. Certi�cate holders must submit the maintenance program revisions required by paragraphs (b), (c), and (d) of this section to the Principal Maintenance Inspector for review and approval.

(f) Exception. For any airplane for which an LOV has not been approved as of the applicable compliance date speci�ed in paragraph (c) or Table 1 of this section, instead of including an approved LOV in the ALS, an operator must include the applicable default LOV speci�ed in Table 1 or Table 2 of this section, as applicable, in the ALS.

Airplane model Compliance date -months after January 14, Default

LOV

[�ight cycles (FC) or �ight hours (FH)] https://www.ecfr.gov/current/title-14/section-26.21 https://www.ecfr.gov/current/title-14/section-121.1115#p-121.1115(b) https://www.ecfr.gov/current/title-14/section-121.1115#p-121.1115(c) https://www.ecfr.gov/current/title-14/section-121.1115#p-121.1115(d) https://www.ecfr.gov/current/title-14/chapter-I/subchapter-G/part-121?toc=1 7/14

A321 Series 60 48,000

FC/60,000

FH

A330-200, -300 Series (except WV050 family) (non enhanced)

60 40,000

FC/60,000

FH

A330-200, -300 Series WV050 family (enhanced) 60 33,000

FC/100,000

FH

A330-200 Freighter Series 60 See NOTE.

A340-200, -300 Series (except WV 027 and WV050 family) (non enhanced)

60 20,000

FC/80,000

FH

A340-200, -300 Series WV 027 (non enhanced) 60 30,000

FC/60,000

FH

A340-300 Series WV050 family (enhanced) 60 20,000

FC/100,000

FH

A340-500, -600 Series 60 16,600

FC/100,000

FH

A380-800 Series 72 See NOTE.

Boeing - Existing Models Only:

717 60 60,000

FC/60,000

FH

727 (all series) 30 60,000 FC

737 (Classics): 737-100, -200, -200C, -300, -400, -500 30 75,000 FC

737 (NG): 737-600, -700, -700C, -800, -900, -900ER 60 75,000 FC

747 (Classics): 747-100, -100B, -100B SUD, -200B, -200C, -200F, -300, 747SP, 747SR

30 20,000 FC

747-400: 747-400, -400D, -400F 60 20,000 FC

Airplane model Compliance date -months after January 14, Default

LOV

[�ight cycles (FC) or �ight hours (FH)] https://www.ecfr.gov/current/title-14/chapter-I/subchapter-G/part-121?toc=1 8/14

757 60 50,000 FC

767 60 50,000 FC

777-200, -300 60 40,000 FC

777-200LR, 777-300ER 72 40,000 FC

777F 72 11,000 FC

Bombardier - Existing Models Only:

CL-600: 2D15 (Regional Jet Series 705), 2D24 (Regional Jet Series 900)

72 60,000 FC

Embraer - Existing Models Only:

ERJ 170 72 See NOTE.

ERJ 190 72 See NOTE.

Fokker - Existing Models Only:

F.28 Mark 0070, Mark 0100 30 90,000 FC

Lockheed - Existing Models Only:

L-1011 30 36,000 FC

188 30 26,600 FC

382 (all series) 30 20,000

FC/50,000

FH

McDonnell Douglas - Existing Models Only:

DC-8, -8F 30 50,000

FC/50,000

FH

DC-9 (except for MD-80 models) 30 100,000

FC/100,000

FH

MD-80 (DC-9-81, -82, -83, -87, MD-88) 30 50,000

FC/50,000

FH

Airplane model Compliance date -months after January 14, Default

LOV

[�ight cycles (FC) https://www.ecfr.gov/current/title-14/chapter-I/subchapter-G/part-121?toc=1 9/14

MD-90 60 60,000

FC/90,000

FH

DC-10-10, -15 30 42,000

FC/60,000

FH

DC-10-30, -40, -10F, -30F, -40F 30 30,000

FC/60,000

FH

MD-10-10F 60 42,000

FC/60,000

FH

MD-10-30F 60 30,000

FC/60,000

FH

MD-11, MD-11F 60 20,000

FC/60,000

FH

Maximum Takeoff Gross Weight Changes:

All airplanes whose maximum takeoff gross weight has been decreased to 75,000 pounds or below after January 14, 2011, or increased to greater than 75,000 pounds at any time by an amended type certi�cate or supplemental type certi�cate

30, or within 12 months after the LOV is approved, or before operating the airplane, whichever occurs latest

Not applicable.

All Other Airplane Models (TCs and amended TCs) not Listed in Table 2

72, or within 12 months after the LOV is approved, or before operating the airplane, whichever occurs latest

Not applicable.

Type certi�cated as of January 14, 2011.

Note: Airplane operation limitation is stated in the Airworthiness Limitation section.

Note:

Airplane operation limitation is stated in the Airworthiness Limitation section.

Airplane model Compliance date -months after January 14, Default

LOV

[�ight cycles (FC) https://www.ecfr.gov/current/title-14/chapter-I/subchapter-G/part-121?toc=1 10/14

Table 2 - Airplanes Excluded from § 26.21

Airbus:

Caravelle 15,000 FC/24,000 FH

Avions Marcel Dassault:

Breguet Aviation Mercure 100C 20,000 FC/16,000 FH

Boeing:

Boeing 707 (-100 Series and -200 Series) 20,000 FC

Boeing 707 (-300 Series and -400 Series) 20,000 FC

Boeing 720 30,000 FC

Bombardier:

CL-44D4 and CL-44J 20,000 FC

BD-700 15,000 FH

Bristol Aeroplane Company:

Britannia 305 10,000 FC

British Aerospace Airbus, Ltd.:

BAC 1-11 (all models) 85,000 FC

British Aerospace (Commercial Aircraft) Ltd.:

Armstrong Whitworth Argosy A.W. 650 Series 101 20,000 FC

BAE Systems (Operations) Ltd.:

BAe 146-100A (all models) 50,000 FC

BAe 146-200-07 50,000 FC

BAe 146-200-07 Dev 50,000 FC

BAe 146-200-11 50,000 FC

BAe 146-200-07A 47,000 FC

BAe 146-200-11 Dev 43,000 FC

BAe 146-300 (all models) 40,000 FC

Avro 146-RJ70A (all models) 40,000 FC

Avro 146-RJ85A and 146-RJ100A (all models) 50,000 FC

Airplane model Default LOV

[�ight cycles (FC) or �ight hours (FH)] https://www.ecfr.gov/current/title-14/section-26.21 https://www.ecfr.gov/current/title-14/chapter-I/subchapter-G/part-121?toc=1 11/14

D & R Nevada, LLC:

Convair Model 22 1,000 FC/1,000 FH

Convair Model 23M 1,000 FC/1,000 FH deHavilland Aircraft Company, Ltd.:

D.H. 106 Comet 4C 8,000 FH

Gulfstream:

GV 40,000 FH

GV-SP 40,000 FH

Ilyushin Aviation Complex:

IL-96T 10,000 FC/30,000 FH

Lockheed:

300-50A01 (USAF C 141A) 20,000 FC

[Doc. No. FAA-2006-24281, 75 FR 69785, Nov. 15, 2010, as amended by Amdt. 121-360, 77 FR 30878, May 24, 2012; Admt. 121-360A, 77 FR 55105, Sept. 7, 2012]

§ 121.1117 Flammability reduction means.

Table 1

747 Series A318, A319, A320, A321 Series

737 Series A330, A340 Series

777 Series

767 Series

(a) Applicability. Except as provided in paragraph (o) of this section, this section applies to transport category, turbine-powered airplanes with a type certi�cate issued after January 1, 1958, that, as a result of original type certi�cation or later increase in capacity have:

(1) A maximum type-certi�cated passenger capacity of 30 or more, or

(2) A maximum payload capacity of 7,500 pounds or more.

(b) New Production Airplanes. Except in accordance with § 121.628, no certi�cate holder may operate an airplane identi�ed in Table 1 of this section (including all-cargo airplanes) for which the State of Manufacture issued the original certi�cate of airworthiness or export airworthiness approval after December 27, 2010 unless an Ignition Mitigation Means (IMM) or Flammability Reduction Means (FRM) meeting the requirements of § 26.33 of this chapter is operational.

Airplane model Default LOV

[�ight cycles (FC) or �ight hours (FH)]

Model - Boeing Model - Airbus https://www.federalregister.gov/citation/75-FR-69785 https://www.federalregister.gov/citation/77-FR-30878 https://www.federalregister.gov/citation/77-FR-55105 https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(o) https://www.ecfr.gov/current/title-14/section-121.628 https://www.ecfr.gov/current/title-14/section-26.33 https://www.ecfr.gov/current/title-14/chapter-I/subchapter-G/part-121?toc=1 12/14

(c) Auxiliary Fuel Tanks. After the applicable date stated in paragraph (e) of this section, no certi�cate holder may operate any airplane subject to § 26.33 of this chapter that has an Auxiliary Fuel Tank installed pursuant to a �eld approval, unless the following requirements are met:

(1) The certi�cate holder complies with 14 CFR 26.35 by the applicable date stated in that section.

(2) The certi�cate holder installs Flammability Impact Mitigation Means (FIMM), if applicable, that is approved by the responsible Aircraft Certi�cation Service o�ce.

(3) Except in accordance with § 121.628, the FIMM, if applicable, is operational.

(d) Retro�t. Except as provided in paragraphs (j), (k), and (l) of this section, after the dates speci�ed in paragraph (e) of this section, no certi�cate holder may operate an airplane to which this section applies unless the requirements of paragraphs (d)(1) and (d)(2) of this section are met.

(1) IMM, FRM or FIMM, if required by §§ 26.33, 26.35, or 26.37 of this chapter, that are approved by the responsible Aircraft Certi�cation Service o�ce, are installed within the compliance times speci�ed in paragraph (e) of this section.

(2) Except in accordance with § 121.628, the IMM, FRM or FIMM, as applicable, are operational.

(e) Compliance Times. Except as provided in paragraphs (k) and (l) of this section, the installations required by paragraph (d) of this section must be accomplished no later than the applicable dates speci�ed in paragraph (e)(1), (e)(2), or (e)(3) of this section.

(1) Fifty percent of each certi�cate holder's �eet identi�ed in paragraph (d)(1) of this section must be modi�ed no later than December 26, 2014.

(2) One hundred percent of each certi�cate holder's �eet identi�ed in paragraph (d)(1) of this section must be modi�ed no later than December 26, 2017.

(3) For those certi�cate holders that have only one airplane of a model identi�ed in Table 1 of this section, the airplane must be modi�ed no later than December 26, 2017.

(f) Compliance After Installation. Except in accordance with § 121.628, no certi�cate holder may -

(1) Operate an airplane on which IMM or FRM has been installed before the dates speci�ed in paragraph (e) of this section unless the IMM or FRM is operational, or

(2) Deactivate or remove an IMM or FRM once installed unless it is replaced by a means that complies with paragraph

(d) of this section.

(g) Maintenance Program Revisions. No certi�cate holder may operate an airplane for which airworthiness limitations have been approved by the responsible Aircraft Certi�cation Service o�ce in accordance with §§ 26.33, 26.35, or 26.37 of this chapter after the airplane is modi�ed in accordance with paragraph (d) of this section unless the maintenance program for that airplane is revised to include those applicable airworthiness limitations.

(h) After the maintenance program is revised as required by paragraph (g) of this section, before returning an airplane to service after any alteration for which airworthiness limitations are required by §§ 25.981, 26.33, or 26.37 of this chapter, the certi�cate holder must revise the maintenance program for the airplane to include those airworthiness limitations.

(i) The maintenance program changes identi�ed in paragraphs (g) and (h) of this section must be submitted to the operator's Principal Maintenance Inspector responsible for review and approval prior to incorporation.

(j) The requirements of paragraph (d) of this section do not apply to airplanes operated in all-cargo service, but those airplanes are subject to paragraph (f) of this section.

(k) The compliance dates speci�ed in paragraph (e) of this section may be extended by one year, provided that -

(1) No later than March 26, 2009, the certi�cate holder noti�es its responsible Flight Standards o�ce or Principal Inspector that it intends to comply with this paragraph;

(2) No later than June 24, 2009, the certi�cate holder applies for an amendment to its operations speci�cation in accordance with § 119.51 of this chapter and revises the manual required by § 121.133 to include a requirement for the airplane models speci�ed in Table 2 of this section to use ground air conditioning systems for actual gate times of more than 30 minutes, when available at the gate and operational, whenever the ambient temperature exceeds 60 degrees Fahrenheit; and

(3) Thereafter, the certi�cate holder uses ground air conditioning systems as described in paragraph (k)(2) of this section on each airplane subject to the extension.

https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(e) https://www.ecfr.gov/current/title-14/section-26.33 https://www.ecfr.gov/current/title-14/section-26.35 https://www.ecfr.gov/current/title-14/section-121.628 https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(j) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(k) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(l) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(e) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(d)(1) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(d)(2) https://www.ecfr.gov/current/title-14/section-26.33 https://www.ecfr.gov/current/title-14/section-26.35 https://www.ecfr.gov/current/title-14/section-26.37 https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(e) https://www.ecfr.gov/current/title-14/section-121.628 https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(k) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(l) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(d) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(e)(1) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(e)(2) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(e)(3) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(d)(1) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(d)(1) https://www.ecfr.gov/current/title-14/section-121.628 https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(e) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(d) https://www.ecfr.gov/current/title-14/section-26.33 https://www.ecfr.gov/current/title-14/section-26.35 https://www.ecfr.gov/current/title-14/section-26.37 https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(d) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(g) https://www.ecfr.gov/current/title-14/section-25.981 https://www.ecfr.gov/current/title-14/section-26.33 https://www.ecfr.gov/current/title-14/section-26.37 https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(g) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(h) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(d) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(f) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(e) https://www.ecfr.gov/current/title-14/section-119.51 https://www.ecfr.gov/current/title-14/section-121.133 https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(k)(2) https://www.ecfr.gov/current/title-14/chapter-I/subchapter-G/part-121?toc=1 13/14

Table 2

747 Series A318, A319, A320, A321 Series

737 Series A300, A310 Series

777 Series A330, A340 Series

767 Series

757 Series

[Doc. No. FAA-2005-22997, 73 FR 42501, July 21, 2008, as amended by Amdt. 121-345, 74 FR 31619, July 2, 2009; Docket FAA-2018- 0119, Amdt. 121-380, 83 FR 9173, Mar. 5, 2018]

§ 121.1119 Fuel tank vent explosion protection.

(l) For any certi�cate holder for which the operating certi�cate is issued after December 26, 2008, the compliance date speci�ed in paragraph (e) of this section may be extended by one year, provided that the certi�cate holder meets the requirements of paragraph (k)(2) of this section when its initial operations speci�cations are issued and, thereafter, uses ground air conditioning systems as described in paragraph (k)(2) of this section on each airplane subject to the extension.

(m) After the date by which any person is required by this section to modify 100 percent of the affected �eet, no certi�cate holder may operate in passenger service any airplane model speci�ed in Table 2 of this section unless the airplane has been modi�ed to comply with § 26.33(c) of this chapter.

(n) No certi�cate holder may operate any airplane on which an auxiliary fuel tank is installed after December 26, 2017 unless the FAA has certi�ed the tank as compliant with § 25.981 of this chapter, in effect on December 26, 2008.

(o) Exclusions. The requirements of this section do not apply to the following airplane models:

(1) Convair CV-240, 340, 440, including turbine powered conversions.

(2) Lockheed L-188 Electra.

(3) Vickers VC-10.

(4) Douglas DC-3, including turbine powered conversions.

(5) Bombardier CL-44.

(6) Mitsubishi YS-11.

(7) BAC 1-11.

(8) Concorde.

(9) deHavilland D.H. 106 Comet 4C.

(10) VFW - Vereinigte Flugtechnische VFW-614.

(11) Illyushin Aviation IL 96T.

(12) Bristol Aircraft Britannia 305.

(13) Handley Page Herald Type 300.

(14) Avions Marcel Dassault - Breguet Aviation Mercure 100C.

(15) Airbus Caravelle.

(16) Fokker F-27/Fairchild Hiller FH-227.

(17) Lockheed L-300.

Model - Boeing Model - Airbus https://www.federalregister.gov/citation/73-FR-42501 https://www.federalregister.gov/citation/74-FR-31619 https://www.federalregister.gov/citation/83-FR-9173 https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(e) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(k)(2) https://www.ecfr.gov/current/title-14/section-121.1117#p-121.1117(k)(2) https://www.ecfr.gov/current/title-14/section-26.33#p-26.33(c) https://www.ecfr.gov/current/title-14/section-25.981 https://www.ecfr.gov/current/title-14/chapter-I/subchapter-G/part-121?toc=1 14/14

[Docket FAA-2014-0500, Amdt. 121-375, 81 FR 41208, June 24, 2016]

(a) Applicability. This section applies to transport category, turbine-powered airplanes with a type certi�cate issued after January 1, 1958, that have:

(1) A maximum type-certi�cated passenger capacity of 30 or more; or

(2) A maximum payload capacity of 7,500 pounds or more.

(b) New production airplanes. No certi�cate holder may operate an airplane for which the State of Manufacture issued the original certi�cate of airworthiness or export airworthiness approval after August 23, 2018 unless means, approved by the Administrator, to prevent fuel tank explosions caused by propagation of �ames from outside the fuel tank vents into the fuel tank vapor spaces are installed and operational.

https://www.federalregister.gov/citation/81-FR-41208