cfr_sections
Data license: Public Domain (U.S. Government data) · Data source: Federal Register API & Regulations.gov API
16 rows where part_number = 26 and title_number = 14 sorted by section_id
This data as json, CSV (advanced)
Suggested facets: subpart, subpart_name, amendment_citations
| section_id ▼ | title_number | title_name | chapter | subchapter | part_number | part_name | subpart | subpart_name | section_number | section_heading | agency | authority | source_citation | amendment_citations | full_text |
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| 14:14:1.0.1.3.14.1.121.1 | 14 | Aeronautics and Space | I | C | 26 | PART 26—CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES | A | Subpart A—General | § 26.1 Purpose and scope. | FAA | (a) This part establishes requirements for support of the continued airworthiness of and safety improvements for transport category airplanes. These requirements may include performing assessments, developing design changes, developing revisions to Instructions for Continued Airworthiness (ICA), and making necessary documentation available to affected persons. Requirements of this part that establish standards for design changes and revisions to the ICA are considered airworthiness requirements. (b) Except as provided in paragraph (c) of this section, this part applies to the following persons, as specified in each subpart of this part: (1) Holders of type certificates and supplemental type certificates. (2) Applicants for type certificates and supplemental type certificates and changes to those certificates (including service bulletins describing design changes). (3) Persons seeking design approval for airplane repairs, alterations, or modifications that may affect airworthiness. (4) Holders of type certificates and their licensees producing new airplanes. (c) An applicant for approval of a design change is not required to comply with any applicable airworthiness requirement of this part if the applicant elects or is required to comply with a corresponding amendment to part 25 of this chapter that is adopted concurrently or after that airworthiness requirement. (d) For the purposes of this part, the word “type certificate” does not include supplemental type certificates. | ||||
| 14:14:1.0.1.3.14.1.121.2 | 14 | Aeronautics and Space | I | C | 26 | PART 26—CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES | A | Subpart A—General | § 26.3 [Reserved] | FAA | |||||
| 14:14:1.0.1.3.14.1.121.3 | 14 | Aeronautics and Space | I | C | 26 | PART 26—CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES | A | Subpart A—General | § 26.5 Applicability table. | FAA | [Doc. No. FAA-2006-24281, 75 FR 69782, Nov. 15, 2010] | Table 1 of this section provides an overview of the applicability of this part. It provides guidance in identifying what sections apply to various types of entities. The specific applicability of each subpart and section is specified in the regulatory text. Table 1—Applicability of Part 26 Rules 1 As of the effective date of the identified rule. 2 Application made after the effective date of the identified rule. | |||
| 14:14:1.0.1.3.14.2.121.1 | 14 | Aeronautics and Space | I | C | 26 | PART 26—CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES | B | Subpart B—Enhanced Airworthiness Program for Airplane Systems | § 26.11 Electrical wiring interconnection systems (EWIS) maintenance program. | FAA | [Amdt. 26-0, 72 FR 63409, Nov. 8, 2007; 72 FR 68618, Dec. 5, 2007, as amended by Doc. No. FAA-2018-0119, Amdt. 26-7, 83 FR 9170, Mar. 5, 2018] | (a) Except as provided in paragraph (g) of this section, this section applies to transport category, turbine-powered airplanes with a type certificate issued after January 1, 1958, that, as a result of the original certification, or later increase in capacity, have— (1) A maximum type-certificated passenger capacity of 30 or more or (2) A maximum payload capacity of 7,500 pounds or more. (b) Holders of, and applicants for, type certificates, as identified in paragraph (d) of this section must develop Instructions for Continued Airworthiness (ICA) for the representative airplane's EWIS in accordance with part 25, Appendix H paragraphs H25.5(a)(1) and (b) of this subchapter in effect on December 10, 2007 for each affected type design, and submit those ICA for review and approval by the responsible Aircraft Certification Service office. For purposes of this section, the “representative airplane” is the configuration of each model series airplane that incorporates all variations of EWIS used in production on that series airplane, and all TC-holder-designed modifications mandated by airworthiness directive as of the effective date of this rule. Each person specified in paragraph (d) of this section must also review any fuel tank system ICA developed by that person to comply with SFAR 88 to ensure compatibility with the EWIS ICA, including minimizing redundant requirements. (c) Applicants for amendments to type certificates and supplemental type certificates, as identified in paragraph (d) of this section, must: (1) Evaluate whether the design change for which approval is sought necessitates a revision to the ICA required by paragraph (b) of this section to comply with the requirements of Appendix H, paragraphs H25.5(a)(1) and (b). If so, the applicant must develop and submit the necessary revisions for review and approval by the responsible Aircraft Certification Service office. (2) Ensure that any revised EWIS ICA remain compatible with any fuel tank system ICA previously developed to comply with SFAR 88 and an… | |||
| 14:14:1.0.1.3.14.3.121.1 | 14 | Aeronautics and Space | I | C | 26 | PART 26—CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES | C | Subpart C—Aging Airplane Safety—Widespread Fatigue Damage | § 26.21 Limit of validity. | FAA | [Doc. No. FAA-2006-24281, 75 FR 69782, Nov. 15, 2010, as amended at 77 FR 30878, May 24, 2012; Doc. No. FAA-2018-0119, Amdt. 26-7, 83 FR 9169, Mar. 5, 2018] | (a) Applicability. Except as provided in paragraph (g) of this section, this section applies to transport category, turbine-powered airplanes 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 transport category, turbine-powered airplanes with a type certificate issued after January 1, 1958, if a design change approval for which application is made after January 14, 2011 has the effect of reducing the maximum takeoff gross weight from greater than 75,000 pounds to 75,000 pounds or less. (b) Limit of validity. Each person identified in paragraph (c) of this section must comply with the following requirements: (1) Establish a limit of validity of the engineering data that supports the structural maintenance program (hereafter referred to as LOV) that corresponds to the period of time, stated as a number of total accumulated flight cycles or flight hours or both, during which it is demonstrated that widespread fatigue damage will not occur in the airplane. This demonstration must include an evaluation of airplane structural configurations and be supported by test evidence and analysis at a minimum and, if available, service experience, or service experience and teardown inspection results, of high-time airplanes of similar structural design, accounting for differences in operating conditions and procedures. The airplane structural configurations to be evaluated include— (i) All model variations and derivatives approved under the type certificate; and (ii) All structural modifications to and replacements for the airplane structural configurations specified in paragraph (b)(1)(i) of this section, mandated by airworthiness directives as of January 14, 2011. (2) If the LOV depends on performance of maintenance actions for which service information has not been mandated by airworthiness directive … | |||
| 14:14:1.0.1.3.14.3.121.2 | 14 | Aeronautics and Space | I | C | 26 | PART 26—CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES | C | Subpart C—Aging Airplane Safety—Widespread Fatigue Damage | § 26.23 Extended limit of validity. | FAA | [Docket No. FAA-2006-24281, 75 FR 69782, Nov. 15, 2010, as amended by Doc. No. FAA-2018-0119, Amdt. 26-7, 83 FR 9169, Mar. 5, 2018] | (a) Applicability. Any person may apply to extend a limit of validity of the engineering data that supports the structural maintenance program (hereafter referred to as LOV) approved under § 25.571 of this subchapter, § 26.21, or this section. Extending an LOV is a major design change. The applicant must comply with the relevant provisions of subparts D or E of part 21 of this subchapter and paragraph (b) of this section. (b) Extended limit of validity. Each person applying for an extended LOV must comply with the following requirements: (1) Establish an extended LOV that corresponds to the period of time, stated as a number of total accumulated flight cycles or flight hours or both, during which it is demonstrated that widespread fatigue damage will not occur in the airplane. This demonstration must include an evaluation of airplane structural configurations and be supported by test evidence and analysis at a minimum and, if available, service experience, or service experience and teardown inspection results, of high-time airplanes of similar structural design, accounting for differences in operating conditions and procedures. The airplane structural configurations to be evaluated include— (i) All model variations and derivatives approved under the type certificate for which approval for an extension is sought; and (ii) All structural modifications to and replacements for the airplane structural configurations specified in paragraph (b)(1)(i) of this section, mandated by airworthiness directive, up to the date of approval of the extended LOV. (2) Establish a revision or supplement, as applicable, to the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness required by § 25.1529 of this subchapter, and submit it to the responsible Aircraft Certification Service office for approval. The revised ALS or supplement to the ALS must include the applicable extended LOV established under paragraph (b)(1) of this section. (3) Develop the maintenance actions determined by the WFD… | |||
| 14:14:1.0.1.3.14.4.121.1 | 14 | Aeronautics and Space | I | C | 26 | PART 26—CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES | D | Subpart D—Fuel Tank Flammability | § 26.31 Definitions. | FAA | For purposes of this subpart— (a) Fleet Average Flammability Exposure has the meaning defined in Appendix N of part 25 of this chapter. (b) Normally Emptied means a fuel tank other than a Main Fuel Tank. Main Fuel Tank is defined in 14 CFR 25.981(b). | ||||
| 14:14:1.0.1.3.14.4.121.2 | 14 | Aeronautics and Space | I | C | 26 | PART 26—CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES | D | Subpart D—Fuel Tank Flammability | § 26.33 Holders of type certificates: Fuel tank flammability. | FAA | [Doc. No. FAA-2005-22997, 73 FR 42499, July 21, 2008, as amended by Amdt. 26-3, 74 FR 31619, July 2, 2009; Doc. No. FAA-2018-0119, Amdt. 26-7, 83 FR 9169, Mar. 5, 2018] | (a) Applicability. This section applies to U.S. type certificated transport category, turbine-powered airplanes, other than those designed solely for all-cargo operations, for which the State of Manufacture issued the original certificate of airworthiness or export airworthiness approval on or after January 1, 1992, that, as a result of original type certification or later increase in capacity have: (1) A maximum type-certificated passenger capacity of 30 or more, or (2) A maximum payload capacity of 7,500 pounds or more. (b) Flammability Exposure Analysis. (1) General. Within 150 days after December 26, 2008, holders of type certificates must submit for approval to the responsible Aircraft Certification Service office a flammability exposure analysis of all fuel tanks defined in the type design, as well as all design variations approved under the type certificate that affect flammability exposure. This analysis must be conducted in accordance with Appendix N of part 25 of this chapter. (2) Exception. This paragraph (b) does not apply to— (i) Fuel tanks for which the type certificate holder has notified the FAA under paragraph (g) of this section that it will provide design changes and service instructions for Flammability Reduction Means or an Ignition Mitigation Means (IMM) meeting the requirements of paragraph (c) of this section. (ii) Fuel tanks substantiated to be conventional unheated aluminum wing tanks. (c) Design Changes. For fuel tanks with a Fleet Average Flammability Exposure exceeding 7 percent, one of the following design changes must be made. (1) Flammability Reduction Means (FRM). A means must be provided to reduce the fuel tank flammability. (i) Fuel tanks that are designed to be Normally Emptied must meet the flammability exposure criteria of Appendix M of part 25 of this chapter if any portion of the tank is located within the fuselage contour. (ii) For all other fuel tanks, the FRM must meet all of the requirements of Appendix M of part 25 of this chapter, except, instead… | |||
| 14:14:1.0.1.3.14.4.121.3 | 14 | Aeronautics and Space | I | C | 26 | PART 26—CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES | D | Subpart D—Fuel Tank Flammability | § 26.35 Changes to type certificates affecting fuel tank flammability. | FAA | [Doc. No. FAA-2005-22997, 73 FR 42499, July 21, 2008, as amended by Amdt. 26-3, 74 FR 31619, July 2, 2009; Doc. No. FAA-2018-0119, Amdt. 26-7, 83 FR 9170, Mar. 5, 2018] | (a) Applicability. This section applies to holders and applicants for approvals of the following design changes to any airplane subject to 14 CFR 26.33(a): (1) Any fuel tank designed to be Normally Emptied if the fuel tank installation was approved pursuant to a supplemental type certificate or a field approval before December 26, 2008; (2) Any fuel tank designed to be Normally Emptied if an application for a supplemental type certificate or an amendment to a type certificate was made before December 26, 2008 and if the approval was not issued before December 26, 2008; and (3) If an application for a supplemental type certificate or an amendment to a type certificate is made on or after December 26, 2008, any of the following design changes: (i) Installation of a fuel tank designed to be Normally Emptied, (ii) Changes to existing fuel tank capacity, or (iii) Changes that may increase the flammability exposure of an existing fuel tank for which FRM or IMM is required by § 26.33(c). (b) Flammability Exposure Analysis —(1) General. By the times specified in paragraphs (b)(1)(i) and (b)(1)(ii) of this section, each person subject to this section must submit for approval a flammability exposure analysis of the auxiliary fuel tanks or other affected fuel tanks, as defined in the type design, to the responsible Aircraft Certification Service office. This analysis must be conducted in accordance with Appendix N of part 25 of this chapter. (i) Holders of supplemental type certificates and field approvals: Within 12 months of December 26, 2008, (ii) Applicants for supplemental type certificates and for amendments to type certificates: Within 12 months after December 26, 2008, or before the certificate is issued, whichever occurs later. (2) Exception. This paragraph does not apply to— (i) Fuel tanks for which the type certificate holder, supplemental type certificate holder, or field approval holder has notified the FAA under paragraph (f) of this section that it will provide design changes and service ins… | |||
| 14:14:1.0.1.3.14.4.121.4 | 14 | Aeronautics and Space | I | C | 26 | PART 26—CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES | D | Subpart D—Fuel Tank Flammability | § 26.37 Pending type certification projects: Fuel tank flammability. | FAA | [Doc. No. FAA-2005-22997, 73 FR 42499, July 21, 2008, as amended by Amdt. 26-3, 74 FR 31619, July 2, 2009] | (a) Applicability. This section applies to any new type certificate for a transport category airplane, if the application was made before December 26, 2008, and if the certificate was not issued before December 26, 2008. This section applies only if the airplane would have— (1) A maximum type-certificated passenger capacity of 30 or more, or (2) A maximum payload capacity of 7,500 pounds or more. (b) If the application was made on or after June 6, 2001, the requirements of 14 CFR 25.981 in effect on December 26, 2008, apply. | |||
| 14:14:1.0.1.3.14.4.121.5 | 14 | Aeronautics and Space | I | C | 26 | PART 26—CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES | D | Subpart D—Fuel Tank Flammability | § 26.39 Newly produced airplanes: Fuel tank flammability. | FAA | [Doc. No. FAA-2005-22997, 73 FR 42499, July 21, 2008, as amended by Amdt. 26-3, 74 FR 31619, July 2, 2009] | (a) Applicability: This section applies to Boeing model airplanes specified in Table 1 of this section, including passenger and cargo versions of each model, when application is made for original certificates of airworthiness or export airworthiness approvals after December 27, 2010. Table 1 (b) Any fuel tank meeting all of the criteria stated in paragraphs (b)(1), (b)(2) and (b)(3) of this section must have flammability reduction means (FRM) or ignition mitigation means (IMM) that meet the requirements of 14 CFR 25.981 in effect on December 26, 2008. (1) The fuel tank is Normally Emptied. (2) Any portion of the fuel tank is located within the fuselage contour. (3) The fuel tank exceeds a Fleet Average Flammability Exposure of 7 percent. (c) All other fuel tanks that exceed an Fleet Average Flammability Exposure of 7 percent must have an IMM that meets 14 CFR 25.981(d) in effect on December 26, 2008, or an FRM that meets all of the requirements of Appendix M to this part, except instead of complying with paragraph M25.1 of that appendix, the Fleet Average Flammability Exposure may not exceed 7 percent. | |||
| 14:14:1.0.1.3.14.5.121.1 | 14 | Aeronautics and Space | I | C | 26 | PART 26—CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES | E | Subpart E—Aging Airplane Safety—Damage Tolerance Data for Repairs and Alterations | § 26.41 Definitions. | FAA | Affects (or Affected) means structure has been physically repaired, altered, or modified, or the structural loads acting on the structure have been increased or redistributed. Baseline structure means structure that is designed under the original type certificate or amended type certificate for that airplane model. Damage Tolerance Evaluation (DTE) means a process that leads to a determination of maintenance actions necessary to detect or preclude fatigue cracking that could contribute to a catastrophic failure. As applied to repairs and alterations, a DTE includes the evaluation both of the repair or alteration and of the fatigue critical structure affected by the repair or alteration. Damage Tolerance Inspection (DTI) means the inspection developed as a result of a DTE. A DTI includes the areas to be inspected, the inspection method, the inspection procedures, including acceptance and rejection criteria, the threshold, and any repeat intervals associated with those inspections. The DTI may specify a time limit when a repair or alteration needs to be replaced or modified. If the DTE concludes that DT-based supplemental structural inspections are not necessary, the DTI contains a statement to that effect. DT data mean DTE documentation and the DTI. DTE documentation means data that identify the evaluated fatigue critical structure, the basic assumptions applied in a DTE, and the results of a DTE. Fatigue critical structure means airplane structure that is susceptible to fatigue cracking that could contribute to a catastrophic failure, as determined in accordance with § 25.571 of this chapter. Fatigue critical structure includes structure, which, if repaired or altered, could be susceptible to fatigue cracking and contribute to a catastrophic failure. Such structure may be part of the baseline structure or part of an alteration. Implementation schedule consists of documentation that establishes the timing for accomplishing the necessary actions for developing DT data for repairs and alterations, and… | ||||
| 14:14:1.0.1.3.14.5.121.2 | 14 | Aeronautics and Space | I | C | 26 | PART 26—CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES | E | Subpart E—Aging Airplane Safety—Damage Tolerance Data for Repairs and Alterations | § 26.43 Holders of and applicants for type certificates—Repairs. | FAA | [Doc. No. FAA-2005-21693, 72 FR 70505, Dec. 12, 2007, as amended by Amdt. 26-4, 75 FR 11734, Mar. 12, 2010; Doc. No. FAA-2018-0119, Amdt. 26-7, 83 FR 9170, Mar. 5, 2018] | (a) Applicability. Except as specified in paragraph (g) of this section, this section applies to transport category, turbine powered airplane models with a type certificate issued after January 1, 1958, that as a result of original type certification or later increase in capacity have— (1) A maximum type certificated passenger seating capacity of 30 or more; or (2) A maximum payload capacity of 7,500 pounds or more. (b) List of fatigue critical baseline structure. For airplanes specified in paragraph (a) of this section, the holder of or applicant for a type certificate must— (1) Identify fatigue critical baseline structure for all airplane model variations and derivatives approved under the type certificate; and (2) Develop and submit to the responsible Aircraft Certification Service office for review and approval, a list of the structure identified under paragraph (b)(1) of this section and, upon approval, make the list available to persons required to comply with § 26.47 and §§ 121.1109 and 129.109 of this chapter. (c) Existing and future published repair data. For repair data published by a holder of a type certificate that is current as of January 11, 2008 and for all later published repair data, the holder of a type certificate must— (1) Review the repair data and identify each repair specified in the data that affects fatigue critical baseline structure identified under paragraph (b)(1) of this section; (2) Perform a DTE and develop the DTI for each repair identified under paragraph (c)(1) of this section, unless previously accomplished; (3) Submit the DT data to the responsible Aircraft Certification Service office or its properly authorized designees for review and approval; and (4) Upon approval, make the DTI available to persons required to comply with §§ 121.1109 and 129.109 of this chapter. (d) Future repair data not published. For repair data developed by a holder of a type certificate that are approved after January 11, 2008 and are not published, the type certificate holder must… | |||
| 14:14:1.0.1.3.14.5.121.3 | 14 | Aeronautics and Space | I | C | 26 | PART 26—CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES | E | Subpart E—Aging Airplane Safety—Damage Tolerance Data for Repairs and Alterations | § 26.45 Holders of type certificates—Alterations and repairs to alterations. | FAA | [Doc. No. FAA-2005-21693, 72 FR 70505, Dec. 12, 2007, as amended by Amdt. 26-4, 75 FR 11734, Mar. 12, 2010; Doc. No. FAA-2018-0119, Amdt. 26-7, 83 FR 9170, Mar. 5, 2018] | (a) Applicability. This section applies to transport category airplanes subject to § 26.43. (b) Fatigue critical alteration structure. For existing and future alteration data developed by the holder of a type certificate, the holder must— (1) Review alteration data and identify all alterations that affect fatigue critical baseline structure identified under § 26.43(b)(1); (2) For each alteration identified under paragraph (b)(1) of this section, identify any fatigue critical alteration structure; (3) Develop and submit to the responsible Aircraft Certification Service office for review and approval a list of the structure identified under paragraph (b)(2) of this section; and (4) Upon approval, make the list required in paragraph (b)(3) of this section available to persons required to comply with §§ 121.1109 and 129.109 of this chapter. (c) DT Data. For existing and future alteration data developed by the holder of a type certificate that affect fatigue critical baseline structure identified under § 26.43(b)(1), unless previously accomplished, the holder must— (1) Perform a DTE and develop the DTI for the alteration and fatigue critical baseline structure that is affected by the alteration; (2) Submit the DT data developed in accordance with paragraphs (c)(1) of this section to the responsible Aircraft Certification Service office or its properly authorized designees for review and approval; and (3) Upon approval, make the DTI available to persons required to comply with §§ 121.1109 and 129.109 of this chapter. (d) DT Data for Repairs Made to Alterations. For existing and future repair data developed by a holder of a type certificate, the type certificate holder must— (1) Review the repair data, and identify each repair that affects any fatigue critical alteration structure identified under paragraph (b)(2) of this section; (2) For each repair identified under paragraph (d)(1) of this section, unless previously accomplished, perform a DTE and develop DTI; (3) Submit the DT data developed in a… | |||
| 14:14:1.0.1.3.14.5.121.4 | 14 | Aeronautics and Space | I | C | 26 | PART 26—CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES | E | Subpart E—Aging Airplane Safety—Damage Tolerance Data for Repairs and Alterations | § 26.47 Holders of and applicants for a supplemental type certificate—Alterations and repairs to alterations. | FAA | [Docket No. FAA-2005-21693, 72 FR 70505, Dec. 12, 2007, as amended by Doc. No. FAA-2018-0119, Amdt. 26-7, 83 FR 9170, Mar. 5, 2018] | (a) Applicability. This section applies to transport category airplanes subject to § 26.43. (b) Fatigue critical alteration structure. For existing structural alteration data approved under a supplemental certificate, the holder of the supplemental certificate must— (1) Review the alteration data and identify all alterations that affect fatigue critical baseline structure identified under § 26.43(b)(1); (2) For each alteration identified under paragraph (b)(1) of this section, identify any fatigue critical alteration structure; (3) Develop and submit to the responsible Aircraft Certification Service office for review and approval a list of the structure identified under paragraph (b)(2) of this section; and (4) Upon approval, make the list required in paragraph (b)(3) of this section available to persons required to comply with §§ 121.1109 and 129.109 of this chapter. (c) DT Data. For existing and future alteration data developed by the holder of a supplemental type certificate that affect fatigue critical baseline structure identified under § 26.43(b)(1), unless previously accomplished, the holder of a supplemental type certificate must— (1) Perform a DTE and develop the DTI for the alteration and fatigue critical baseline structure that is affected by the alteration; (2) Submit the DT data developed in accordance with paragraphs (c)(1) of this section to the responsible Aircraft Certification Service office or its properly authorized designees for review and approval; and (3) Upon approval, make the DTI available to persons required to comply with §§ 121.1109 and 129.109 of this chapter. (d) DT Data for Repairs Made to Alterations. For existing and future repair data developed by the holder of a supplemental holder of a supplemental type certificate, the holder of a supplemental type certificate must— (1) Review the repair data, and identify each repair that affects any fatigue critical alteration structure identified under paragraph (b)(2) of this section; (2) For each repair identified und… | |||
| 14:14:1.0.1.3.14.5.121.5 | 14 | Aeronautics and Space | I | C | 26 | PART 26—CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES | E | Subpart E—Aging Airplane Safety—Damage Tolerance Data for Repairs and Alterations | § 26.49 Compliance plan. | FAA | [Docket No. FAA-2005-21693, 72 FR 70505, Dec. 12, 2007, as amended by Doc. No. FAA-2018-0119, Amdt. 26-7, 83 FR 9170, Mar. 5, 2018] | (a) Compliance plan. Except for applicants for type certificates and supplemental type certificates whose applications are submitted after January 11, 2008, each person identified in §§ 26.43, 26.45, and 26.47, must submit a compliance plan consisting of the following: (1) A project schedule identifying all major milestones for meeting the compliance times specified in §§ 26.43(f), 26.45(e), and 26.47(e), as applicable. (2) A proposed means of compliance with §§ 26.43, 26.45, and 26.47, as applicable. (3) A plan for submitting a draft of all compliance items required by this subpart for review by the responsible Aircraft Certification Service office not less than 60 days before the applicable compliance date. (b) Compliance dates for compliance plans. The following persons must submit the compliance plan described in paragraph (a) of this section to the responsible Aircraft Certification Service office for approval on the following schedule: (1) For holders of type certificates, no later than 90 days after January 11, 2008. (2) For holders of supplemental type certificates no later than 180 days after January 11, 2008. (3) For applicants for changes to type certificates whose application are submitted before January 11, 2008, no later than 180 days after January 11, 2008. (c) Compliance Plan Implementation. Each affected person must implement the compliance plan as approved in compliance with paragraph (a) of this section. |
Advanced export
JSON shape: default, array, newline-delimited, object
CREATE TABLE cfr_sections (
section_id TEXT PRIMARY KEY,
title_number INTEGER,
title_name TEXT,
chapter TEXT,
subchapter TEXT,
part_number TEXT,
part_name TEXT,
subpart TEXT,
subpart_name TEXT,
section_number TEXT,
section_heading TEXT,
agency TEXT,
authority TEXT,
source_citation TEXT,
amendment_citations TEXT,
full_text TEXT
);
CREATE INDEX idx_cfr_title ON cfr_sections(title_number);
CREATE INDEX idx_cfr_part ON cfr_sections(part_number);
CREATE INDEX idx_cfr_agency ON cfr_sections(agency);