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e-CFR=20 Data is current as of November 12, 2010


Title 14:=20 Aeronautics and Space

Browse=20 Previous | Browse=20 Next

PART 26=97CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR = TRANSPORT=20 CATEGORY AIRPLANES
Section Contents

Subpart=20 A=97General

=A7 26.1 &nb= sp; Purpose=20 and scope.
=A7 26.3 &nb= sp; Definitions.
=A7 26.5 &nb= sp; Applicability=20 table.

Subpart=20 B=97Enhanced Airworthiness Program for Airplane=20 Systems

=A7 26.11 &n= bsp; Electrical=20 wiring interconnection systems (EWIS) maintenance=20 program.

Subpart=20 C [Reserved]


Subpart=20 D=97Fuel Tank Flammability

=A7 26.31 &n= bsp; Definitions.
=A7 26.33 &n= bsp; Holders=20 of type certificates: Fuel tank flammability.
=A7 26.35 &n= bsp; Changes=20 to type certificates affecting fuel tank = flammability.
=A7 26.37 &n= bsp; Pending=20 type certification projects: Fuel tank = flammability.
=A7 26.39 &n= bsp; Newly=20 produced airplanes: Fuel tank flammability.

Subpart=20 E=97Aging Airplane Safety=97Damage Tolerance Data for Repairs and=20 Alterations

=A7 26.41 &n= bsp; Definitions.
=A7 26.43 &n= bsp; Holders=20 of and applicants for type = certificates=97Repairs.
=A7 26.45 &n= bsp; Holders=20 of type certificates=97Alterations and repairs to=20 alterations.
=A7 26.47 &n= bsp; Holders=20 of and applicants for a supplemental type = certificate=97Alterations and=20 repairs to alterations.
=A7 26.49 &n= bsp; Compliance=20 plan.

Authority:   49 U.S.C. 106(g), = 40113,=20 44701, 44702 and 44704.

Source:   Docket No. = FAA=962004=9618379, 72=20 FR 63409, Nov. 8, 2007, unless otherwise noted.

Subpart A=97General
=20 top
=A7 26.1   Purpose and scope.
=20 top

(a) This part establishes requirements for support of the = continued=20 airworthiness of and safety improvements for transport category = airplanes.=20 These requirements may include performing assessments, developing = design=20 changes, developing revisions to Instructions for Continued = Airworthiness=20 (ICA), and making necessary documentation available to affected = persons.=20 Requirements of this part that establish standards for design = changes and=20 revisions to the ICA are considered airworthiness = requirements.

(b) Except as provided in paragraph (c) of this section, this = part=20 applies to the following persons, as specified in each subpart of = this=20 part:

(1) Holders of type certificates and supplemental type=20 certificates.

(2) Applicants for type certificates and supplemental type = certificates=20 and changes to those certificates (including service bulletins = describing=20 design changes).

(3) Persons seeking design approval for airplane repairs, = alterations,=20 or modifications that may affect airworthiness.

(4) Holders of type certificates and their licensees producing = new=20 airplanes.

(c) An applicant for approval of a design change is not = required to=20 comply with any applicable airworthiness requirement of this part = if the=20 applicant elects or is required to comply with a corresponding = amendment=20 to part 25 of this chapter that is adopted concurrently or after = that=20 airworthiness requirement.

(d) For the purposes of this part, the word =93type = certificate=94 does not=20 include supplemental type certificates.

=A7 26.3   Definitions.
=20 top

For the purposes of this part:

FAA Oversight Office is the aircraft certification = office or=20 office of the Transport Airplane Directorate with oversight = responsibility=20 for the relevant type certificate, supplemental type certificate, = or=20 manufacturer, as determined by the Administrator.

=A7 26.5   Applicability table.
=20 top

Table 1 of this section provides an overview of the = applicability of=20 this part. It provides guidance in identifying what sections apply = to=20 various types of entities. The specific applicability of each = subpart and=20 section is specified in the regulatory text.

Table 1=97Applicability of Part 26 = Rules

   Applicable = sections
Subpart B Subpart D Subpart E
EAPAS/FTS Fuel tank = flammability Damage tolerance = data
Effective = date of=20 rule December 10, 2007 December 26, 2008 January 11, = 2008
Existing1TC=20 Holders 26.11 26.33 26.43, 26.45, = 26.49
Pending1TC=20 Applicants 26.11 26.37 26.43, 26.45
Existing1STC=20 Holders N/A 26.35 26.47, 26.49
Pending1STC/ATC=20 Applicants 26.11 26.35 26.45, 26.47, = 26.49
Future2STC/ATC=20 Applicants 26.11 26.35 26.45, 26.47, = 26.49
Manufacturers N/A 26.39 N/A

1As of the effective date of the = identified=20 rule.

2Application made after the = effective date=20 of the identified rule.

[Doc. No. FAA=962005=9622997, 74 FR 31618, July 2, 2009]

Subpart B=97Enhanced Airworthiness Program for Airplane=20 Systems
=20 top
=A7 26.11   Electrical wiring = interconnection=20 systems (EWIS) maintenance program.
=20 top

(a) Except as provided in paragraph (g) of this section, this = section=20 applies to transport category, turbine-powered airplanes with a = type=20 certificate issued after January 1, 1958, that, as a result of the = original certification, or later increase in capacity, have=97

(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=20 paragraph (d) of this section must develop Instructions for = Continued=20 Airworthiness (ICA) for the representative airplane's EWIS in = accordance=20 with part 25, Appendix H paragraphs H25.5(a)(1) and (b) of this = subchapter=20 in effect on December 10, 2007 for each affected type design, and = submit=20 those ICA for review and approval by the FAA Oversight Office. For = purposes of this section, the =93representative airplane=94 is the = configuration of each model series airplane that incorporates all=20 variations of EWIS used in production on that series airplane, and = all=20 TC-holder-designed modifications mandated by airworthiness = directive as of=20 the effective date of this rule. Each person specified in = paragraph (d) of=20 this section must also review any fuel tank system ICA developed = by that=20 person to comply with SFAR 88 to ensure compatibility with the = EWIS ICA,=20 including minimizing redundant requirements.

(c) Applicants for amendments to type certificates and = supplemental=20 type certificates, as identified in paragraph (d) of this section, = must:

(1) Evaluate whether the design change for which approval is = sought=20 necessitates a revision to the ICA required by paragraph (b) of = this=20 section to comply with the requirements of Appendix H, paragraphs=20 H25.5(a)(1) and (b). If so, the applicant must develop and submit = the=20 necessary revisions for review and approval by the FAA Oversight=20 Office.

(2) Ensure that any revised EWIS ICA remain compatible with any = fuel=20 tank system ICA previously developed to comply with SFAR 88 and = any=20 redundant requirements between them are minimized.

(d) The following persons must comply with the requirements of=20 paragraph (b) or (c) of this section, as applicable, before the = dates=20 specified.

(1) Holders of type certificates (TC): December 10, 2009.

(2) Applicants for TCs, and amendments to TCs (including = service=20 bulletins describing design changes), if the date of application = was=20 before December 10, 2007 and the certificate was issued on or = after=20 December 10, 2007: December 10, 2009 or the date the certificate = is=20 issued, whichever occurs later.

(3) Unless compliance with =A725.1729 of this subchapter is = required or=20 elected, applicants for amendments to TCs, if the application was = filed on=20 or after December 10, 2007: December 10, 2009, or the date of = approval of=20 the certificate, whichever occurs later.

(4) Applicants for supplemental type certificates (STC), = including=20 changes to existing STCs, if the date of application was before = December=20 10, 2007 and the certificate was issued on or after December 10, = 2007:=20 June 7, 2010, or the date of approval of the certificate, = whichever occurs=20 later.

(5) Unless compliance with =A725.1729 of this subchapter is = required or=20 elected, applicants for STCs, including changes to existing STCs, = if the=20 application was filed on or after December 10, 2007, June 7, 2010, = or the=20 date of approval of the certificate, whichever occurs later.

(e) Each person identified in paragraphs (d)(1), (d)(2), and = (d)(4) of=20 this section must submit to the FAA Oversight Office for approval = a=20 compliance plan by March 10, 2008. The compliance plan must = include the=20 following information:

(1) A proposed project schedule, identifying all major = milestones, for=20 meeting the compliance dates specified in paragraph (d) of this=20 section.

(2) A proposed means of compliance with this section, = identifying all=20 required submissions, including all compliance items as mandated = in part=20 25, Appendix H paragraphs H25.5(a)(1) and (b) of this subchapter = in effect=20 on December 10, 2007, and all data to be developed to substantiate = compliance.

(3) A proposal for submitting a draft of all compliance items = required=20 by paragraph (e)(2) of this section for review by the FAA = Oversight Office=20 not less than 60 days before the compliance time specified in = paragraph=20 (d) of this section.

(4) A proposal for how the approved ICA will be made available = to=20 affected persons.

(f) Each person specified in paragraph (e) must implement the=20 compliance plan, or later approved revisions, as approved in = compliance=20 with paragraph (e) of this section.

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

(1) Lockheed L=96188

(2) Bombardier CL=9644

(3) Mitsubishi YS=9611

(4) British Aerospace BAC 1=9611

(5) Concorde

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

(7) VFW=97Vereinigte Flugtechnische Werk VFW=96614

(8) Illyushin Aviation IL 96T

(9) Bristol Aircraft Britannia 305

(10) Handley Page Herald Type 300

(11) Avions Marcel Dassault=97Breguet Aviation Mercure 100C

(12) Airbus Caravelle

(13) Lockheed L=96300

[Amdt. 26=960, 72 FR 63409, Nov. 8, 2007; 72 FR 68618, Dec. 5,=20 2007]

Subpart C [Reserved]
=20 top
Subpart D=97Fuel Tank Flammability
=20 top

Source:   Docket No. = FAA=962005=9622997, 73=20 FR 42499, July 21, 2008, unless otherwise noted.

=A7 26.31   Definitions.
=20 top

For purposes of this subpart=97

(a) Fleet Average Flammability Exposure has the meaning = defined=20 in Appendix N of part 25 of this chapter.

(b) Normally Emptied means a fuel tank other than a Main = Fuel=20 Tank. Main Fuel Tank is defined in 14 CFR 25.981(b).

=A7 26.33   Holders of type certificates: = Fuel tank=20 flammability.
=20 top

(a) Applicability . This section applies to U.S. type=20 certificated transport category, turbine-powered airplanes, other = than=20 those designed solely for all-cargo operations, for which the = State of=20 Manufacture issued the original certificate of airworthiness or = export=20 airworthiness approval on or after January 1, 1992, that, as a = result of=20 original type certification or later increase in capacity = have:

(1) A maximum type-certificated passenger capacity of 30 or = more,=20 or

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

(b) Flammability Exposure Analysis . (1) General = . Within=20 150 days after December 26, 2008, holders of type certificates = must submit=20 for approval to the FAA Oversight Office a flammability exposure = analysis=20 of all fuel tanks defined in the type design, as well as all = design=20 variations approved under the type certificate that affect = flammability=20 exposure. This analysis must be conducted in accordance with = Appendix N of=20 part 25 of this chapter.

(2) Exception . This paragraph (b) does not apply = to=97

(i) Fuel tanks for which the type certificate holder has = notified the=20 FAA under paragraph (g) of this section that it will provide = design=20 changes and service instructions for Flammability Reduction Means = or an=20 Ignition Mitigation Means (IMM) meeting the requirements of = paragraph (c)=20 of this section.

(ii) Fuel tanks substantiated to be conventional unheated = aluminum wing=20 tanks.

(c) Design Changes . For fuel tanks with a Fleet Average = Flammability Exposure exceeding 7 percent, one of the following = design=20 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=20 flammability exposure criteria of Appendix M of part 25 of this = chapter if=20 any portion of the tank is located within the fuselage = contour.

(ii) For all other fuel tanks, the FRM must meet all of the=20 requirements of Appendix M of part 25 of this chapter, except, = instead of=20 complying with paragraph M25.1 of this appendix, the Fleet Average = Flammability Exposure may not exceed 7 percent.

(2) Ignition Mitigation Means (IMM) . A means must be = provided=20 to mitigate the effects of an ignition of fuel vapors within the = fuel tank=20 such that no damage caused by an ignition will prevent continued = safe=20 flight and landing.

(d) Service Instructions . No later than December 27, = 2010,=20 holders of type certificates required by paragraph (c) of this = section to=20 make design changes must meet the requirements specified in either = paragraph (d)(1) or (d)(2) of this section. The required service=20 instructions must identify each airplane subject to the = applicability=20 provisions of paragraph (a) of this section.

(1) FRM . The type certificate holder must submit for = approval=20 by the FAA Oversight Office design changes and service = instructions for=20 installation of fuel tank flammability reduction means (FRM) = meeting the=20 criteria of paragraph (c) of this section.

(2) IMM . The type certificate holder must submit for = approval=20 by the FAA Oversight Office design changes and service = instructions for=20 installation of fuel tank IMM that comply with 14 CFR 25.981(c) in = effect=20 on December 26, 2008.

(e) Instructions for Continued Airworthiness (ICA) . No = later=20 than December 27, 2010, holders of type certificates required by = paragraph=20 (c) of this section to make design changes must submit for = approval by the=20 FAA Oversight Office, critical design configuration control = limitations=20 (CDCCL), inspections, or other procedures to prevent increasing = the=20 flammability exposure of any tanks equipped with FRM above that = permitted=20 under paragraph (c)(1) of this section and to prevent degradation = of the=20 performance of any IMM provided under paragraph (c)(2) of this = section.=20 These CDCCL, inspections, and procedures must be included in the=20 Airworthiness Limitations Section (ALS) of the ICA required by 14 = CFR=20 25.1529 or paragraph (f) of this section. Unless shown to be=20 impracticable, visible means to identify critical features of the = design=20 must be placed in areas of the airplane where foreseeable = maintenance=20 actions, repairs, or alterations may compromise the critical = design=20 configuration limitations. These visible means must also be = identified as=20 a CDCCL.

(f) Airworthiness Limitations . Unless previously = accomplished,=20 no later than December 27, 2010, holders of type certificates = affected by=20 this section must establish an ALS of the maintenance manual or = ICA for=20 each airplane configuration evaluated under paragraph (b)(1) of = this=20 section and submit it to the FAA Oversight Office for approval. = The ALS=20 must include a section that contains the CDCCL, inspections, or = other=20 procedures developed under paragraph (e) of this section.

(g) Compliance Plan for Flammability Exposure Analysis . = Within=20 90 days after December 26, 2008, each holder of a type certificate = required to comply with paragraph (b) of this section must submit = to the=20 FAA Oversight Office a compliance plan consisting of the = following:

(1) A proposed project schedule for submitting the required = analysis,=20 or a determination that compliance with paragraph (b) of this = section is=20 not required because design changes and service instructions for = FRM or=20 IMM will be developed and made available as required by this = section.

(2) A proposed means of compliance with paragraph (b) of this = section,=20 if applicable.

(h) Compliance Plan for Design Changes and Service = Instructions=20 . Within 210 days after December 26, 2008, each holder of a = type=20 certificate required to comply with paragraph (d) of this section = must=20 submit to the FAA Oversight Office a compliance plan consisting of = the=20 following:

(1) A proposed project schedule, identifying all major = milestones, for=20 meeting the compliance dates specified in paragraphs (d), (e) and = (f) of=20 this section.

(2) A proposed means of compliance with paragraphs (d), (e) and = (f) of=20 this section.

(3) A proposal for submitting a draft of all compliance items = required=20 by paragraphs (d), (e) and (f) of this section for review by the = FAA=20 Oversight Office not less than 60 days before the compliance times = specified in those paragraphs.

(4) A proposal for how the approved service information and any = necessary modification parts will be made available to affected=20 persons.

(i) Each affected type certificate holder must implement the = compliance=20 plans, or later revisions, as approved under paragraph (g) and (h) = of this=20 section.

[Doc. No. FAA=962005=9622997, 73 FR 42499, July 21, 2008, as = amended by=20 Amdt. 26=963, 74 FR 31619, July 2, 2009]

=A7 26.35   Changes to type certificates = affecting=20 fuel tank flammability.
=20 top

(a) Applicability . This section applies to holders and=20 applicants for approvals of the following design changes to any = airplane=20 subject to 14 CFR 26.33(a):

(1) Any fuel tank designed to be Normally Emptied if the fuel = tank=20 installation was approved pursuant to a supplemental type = certificate or a=20 field approval before December 26, 2008;

(2) Any fuel tank designed to be Normally Emptied if an = application for=20 a supplemental type certificate or an amendment to a type = certificate was=20 made before December 26, 2008 and if the approval was not issued = before=20 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=20 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 = =A726.33(c).

(b) Flammability Exposure Analysis =97(1) General = . By the=20 times specified in paragraphs (b)(1)(i) and (b)(1)(ii) of this = section,=20 each person subject to this section must submit for approval a=20 flammability exposure analysis of the auxiliary fuel tanks or = other=20 affected fuel tanks, as defined in the type design, to the FAA = Oversight=20 Office. This analysis must be conducted in accordance with = Appendix N of=20 part 25 of this chapter.

(i) Holders of supplemental type certificates and field = approvals:=20 Within 12 months of December 26, 2008,

(ii) Applicants for supplemental type certificates and for = amendments=20 to type certificates: Within 12 months after December 26, 2008, or = before=20 the certificate is issued, whichever occurs later.

(2) Exception . This paragraph does not apply to=97

(i) Fuel tanks for which the type certificate holder, = supplemental type=20 certificate holder, or field approval holder has notified the FAA = under=20 paragraph (f) of this section that it will provide design changes = and=20 service instructions for an IMM meeting the requirements of = =A725.981(c) in=20 effect December 26, 2008; and

(ii) Fuel tanks substantiated to be conventional unheated = aluminum wing=20 tanks.

(c) Impact Assessment . By the times specified in = paragraphs=20 (c)(1) and (c)(2) of this section, each person subject to = paragraph (a)(1)=20 of this section holding an approval for installation of a Normally = Emptied=20 fuel tank on an airplane model listed in Table 1 of this section, = and each=20 person subject to paragraph (a)(3)(iii) of this section, must = submit for=20 approval to the FAA Oversight Office an assessment of the fuel = tank=20 system, as modified by their design change. The assessment must = identify=20 any features of the design change that compromise any critical = design=20 configuration control limitation (CDCCL) applicable to any = airplane on=20 which the design change is eligible for installation.

(1) Holders of supplemental type certificates and field = approvals:=20 Before June 26, 2011.

(2) Applicants for supplemental type certificates and for = amendments to=20 type certificates: Before June 26, 2011 or before the certificate = is=20 issued, whichever occurs later.

Table 1

Model=97Boeing
747 = Series
737 = Series
777 = Series
767 = Series
757 = Series
Model=97Airbus
A318, A319, = A320, A321=20 Series
A300, A310 = Series
A330, A340=20 Series

(d) Design Changes and Service Instructions . By the = times=20 specified in paragraph (e) of this section, each person subject to = this=20 section must meet the requirements of paragraphs (d)(1) or (d)(2) = of this=20 section, as applicable.

(1) For holders and applicants subject to paragraph (a)(1) or=20 (a)(3)(iii) of this section, if the assessment required by = paragraph (c)=20 of this section identifies any features of the design change that=20 compromise any CDCCL applicable to any airplane on which the = design change=20 is eligible for installation, the holder or applicant must submit = for=20 approval by the FAA Oversight Office design changes and service=20 instructions for Flammability Impact Mitigation Means (FIMM) that = would=20 bring the design change into compliance with the CDCCL. Any fuel = tank=20 modified as required by this paragraph must also be evaluated as = required=20 by paragraph (b) of this section.

(2) Applicants subject to paragraph (a)(2), or (a)(3)(i) of = this=20 section must comply with the requirements of 14 CFR 25.981, in = effect on=20 December 26, 2008.

(3) Applicants subject to paragraph (a)(3)(ii) of this section = must=20 comply with the requirements of 14 CFR 26.33.

(e) Compliance Times for Design Changes and Service = Instructions=20 . The following persons subject to this section must comply = with the=20 requirements of paragraph (d) of this section at the specified = times.

(1) Holders of supplemental type certificates and field = approvals:=20 Before December 26, 2012.

(2) Applicants for supplemental type certificates and for = amendments to=20 type certificates: Before December 26, 2012, or before the = certificate is=20 issued, whichever occurs later.

(f) Compliance Planning . By the applicable date = specified in=20 Table 2 of this section, each person subject to paragraph (a)(1) = of this=20 section must submit for approval by the FAA Oversight Office = compliance=20 plans for the flammability exposure analysis required by paragraph = (b) of=20 this section, the impact assessment required by paragraph (c) of = this=20 section, and the design changes and service instructions required = by=20 paragraph (d) of this section. Each person's compliance plans must = include=20 the following:

(1) A proposed project schedule for submitting the required = analysis or=20 impact assessment.

(2) A proposed means of compliance with paragraph (d) of this=20 section.

(3) For the requirements of paragraph (d) of this section, a = proposal=20 for submitting a draft of all design changes, if any are required, = and=20 Airworthiness Limitations (including CDCCLs) for review by the FAA = Oversight Office not less than 60 days before the compliance time=20 specified in paragraph (e) of this section.

(4) For the requirements of paragraph (d) of this section, a = proposal=20 for how the approved service information and any necessary = modification=20 parts will be made available to affected persons.

Table 2=97Compliance Planning = Dates

   Flammability exposure = analysis=20 plan Impact assessment = plan Design changes and = service=20 instructions plan
STC and Field = Approval=20 Holders March 26, 2009 February 26, 2011 August 26,=20 2011.

(g) Each person subject to this section must implement the = compliance=20 plans, or later revisions, as approved under paragraph (f) of this = section.

[Doc. No. FAA=962005=9622997, 73 FR 42499, July 21, 2008, as = amended by=20 Amdt. 26=963, 74 FR 31619, July 2, 2009]

=A7 26.37   Pending type certification = projects:=20 Fuel tank flammability.
=20 top

(a) Applicability . This section applies to any new type = certificate for a transport category airplane, if the application = was made=20 before December 26, 2008, and if the certificate was not issued = before=20 December 26, 2008. This section applies only if the airplane would = have=97

(1) A maximum type-certificated passenger capacity of 30 or = more,=20 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=20 requirements of 14 CFR 25.981 in effect on December 26, 2008, = apply.

[Doc. No. FAA=962005=9622997, 73 FR 42499, July 21, 2008, as = amended by=20 Amdt. 26=963, 74 FR 31619, July 2, 2009]

=A7 26.39   Newly produced airplanes: Fuel = tank=20 flammability.
=20 top

(a) Applicability: This section applies to Boeing model=20 airplanes specified in Table 1 of this section, including = passenger and=20 cargo versions of each model, when application is made for = original=20 certificates of airworthiness or export airworthiness approvals = after=20 December 27, 2010.

Table 1

Model=97Boeing
747 = Series
737 = Series
777 = Series
767=20 Series

(b) Any fuel tank meeting all of the criteria stated in = paragraphs=20 (b)(1), (b)(2) and (b)(3) of this section must have flammability = reduction=20 means (FRM) or ignition mitigation means (IMM) that meet the = requirements=20 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=20 percent.

(c) All other fuel tanks that exceed an Fleet Average = Flammability=20 Exposure of 7 percent must have an IMM that meets 14 CFR 25.981(d) = in=20 effect on December 26, 2008, or an FRM that meets all of the = requirements=20 of Appendix M to this part, except instead of complying with = paragraph=20 M25.1 of that appendix, the Fleet Average Flammability Exposure = may not=20 exceed 7 percent.

[Doc. No. FAA=962005=9622997, 73 FR 42499, July 21, 2008, as = amended by=20 Amdt. 26=963, 74 FR 31619, July 2, 2009]

Subpart E=97Aging Airplane Safety=97Damage Tolerance Data for = Repairs and=20 Alterations
=20 top

Source:   Docket No. = FAA=962005=9621693, 72=20 FR 70505, Dec. 12, 2007, unless otherwise noted.

=A7 26.41   Definitions.
=20 top

Affects (or Affected) means structure has been = physically=20 repaired, altered, or modified, or the structural loads acting on = the=20 structure have been increased or redistributed.

Baseline structure means structure that is designed = under the=20 original type certificate or amended type certificate for that = airplane=20 model.

Damage Tolerance Evaluation (DTE) means a process that = leads to=20 a determination of maintenance actions necessary to detect or = preclude=20 fatigue cracking that could contribute to a catastrophic failure. = As=20 applied to repairs and alterations, a DTE includes the evaluation = both of=20 the repair or alteration and of the fatigue critical structure = affected by=20 the repair or alteration.

Damage Tolerance Inspection (DTI) means the inspection = developed=20 as a result of a DTE. A DTI includes the areas to be inspected, = the=20 inspection method, the inspection procedures, including acceptance = and=20 rejection criteria, the threshold, and any repeat intervals = associated=20 with those inspections. The DTI may specify a time limit when a = repair or=20 alteration needs to be replaced or modified. If the DTE concludes = that=20 DT-based supplemental structural inspections are not necessary, = the DTI=20 contains a statement to that effect.

DT data mean DTE documentation and the DTI.

DTE documentation means data that identify the evaluated = fatigue=20 critical structure, the basic assumptions applied in a DTE, and = the=20 results of a DTE.

Fatigue critical structure means airplane structure that = is=20 susceptible to fatigue cracking that could contribute to a = catastrophic=20 failure, as determined in accordance with =A725.571 of this = chapter. Fatigue=20 critical structure includes structure, which, if repaired or = altered,=20 could be susceptible to fatigue cracking and contribute to a = catastrophic=20 failure. Such structure may be part of the baseline structure or = part of=20 an alteration.

Implementation schedule consists of documentation that=20 establishes the timing for accomplishing the necessary actions for = developing DT data for repairs and alterations, and for = incorporating=20 those data into an operator's continuing airworthiness maintenance = program. The documentation must identify times when actions must = be taken=20 as specific numbers of airplane flight hours, flight cycles, or = both.

Published repair data mean instructions for = accomplishing=20 repairs, which are published for general use in structural repair = manuals=20 and service bulletins (or equivalent types of documents).

=A7 26.43   Holders of and applicants for = type=20 certificates=97Repairs.
=20 top

(a) Applicability. Except as specified in paragraph (g) = of this=20 section, this section applies to transport category, turbine = powered=20 airplane models with a type certificate issued after January 1, = 1958, that=20 as a result of original type certification or later increase in = capacity=20 have=97

(1) A maximum type certificated passenger seating capacity of = 30 or=20 more; or

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

(b) List of fatigue critical baseline structure. For = airplanes=20 specified in paragraph (a) of this section, the holder of or = applicant for=20 a type certificate must=97

(1) Identify fatigue critical baseline structure for all = airplane model=20 variations and derivatives approved under the type certificate; = and

(2) Develop and submit to the FAA Oversight Office for review = and=20 approval, a list of the structure identified under paragraph = (b)(1) of=20 this section and, upon approval, make the list available to = persons=20 required to comply with =A726.47 and =A7=A7121.1109 and 129.109 of = this=20 chapter.

(c) Existing and future published repair data. For = repair data=20 published by a holder of a type certificate that is current as of = January=20 11, 2008 and for all later published repair data, the holder of a = type=20 certificate must=97

(1) Review the repair data and identify each repair specified = in the=20 data that affects fatigue critical baseline structure identified = under=20 paragraph (b)(1) of this section;

(2) Perform a DTE and develop the DTI for each repair = identified under=20 paragraph (c)(1) of this section, unless previously = accomplished;

(3) Submit the DT data to the FAA Oversight Office or its = properly=20 authorized designees for review and approval; and

(4) Upon approval, make the DTI available to persons required = to comply=20 with =A7=A7121.1109 and 129.109 of this chapter.

(d) Future repair data not published. For repair data = developed=20 by a holder of a type certificate that are approved after January = 11, 2008=20 and are not published, the type certificate holder must accomplish = the=20 following for repairs specified in the repair data that affect = fatigue=20 critical baseline structure:

(1) Perform a DTE and develop the DTI.

(2) Submit the DT data required in paragraph (d)(1) of this = section for=20 review and approval by the FAA Oversight Office or its properly = authorized=20 designees.

(3) Upon approval, make the approved DTI available to persons = required=20 to comply with =A7=A7121.1109 and 129.109 of this chapter.

(e) Repair evaluation guidelines. Except for airplane = models=20 whose type certificate is issued after January 11, 2008, holders = of a type=20 certificate for each airplane model subject to this section = must=97

(1) Develop repair evaluation guidelines for operators' use = that=20 include=97

(i) A process for conducting surveys of affected airplanes that = will=20 enable identification and documentation of all existing repairs = that=20 affect fatigue critical baseline structure identified under = paragraph=20 (b)(1) of this section and =A726.45(b)(2);

(ii) A process that will enable operators to obtain the DTI for = repairs=20 identified under paragraph (e)(1)(i) of this section; and

(iii) An implementation schedule for repairs covered by the = repair=20 evaluation guidelines. The implementation schedule must identify = times=20 when actions must be taken as specific numbers of airplane flight = hours,=20 flight cycles, or both.

(2) Submit the repair evaluation guidelines to the FAA = Oversight Office=20 for review and approval.

(3) Upon approval, make the guidelines available to persons = required to=20 comply with =A7=A7121.1109 and 129.109 of this chapter.

(4) If the guidelines direct the operator to obtain assistance = from the=20 holder of a type certificate, make such assistance available in = accordance=20 with the implementation schedule.

(f) Compliance times. Holders of type certificates must = submit=20 the following to the FAA Oversight Office or its properly = authorized=20 designees for review and approval by the specified compliance = time:

(1) The identified list of fatigue critical baseline structure = required=20 by paragraph (b)(2) of this section must be submitted no later = than 180=20 days after January 11, 2008 or before issuance of the type = certificate,=20 whichever occurs later.

(2) For published repair data that are current as of January = 11, 2008,=20 the DT data required by paragraph (c)(3) of this section must be = submitted=20 by June 30, 2009.

(3) For repair data published after January 11, 2008, the DT = data=20 required by paragraph (c)(3) of this section must be submitted = before FAA=20 approval of the repair data.

(4) For unpublished repair data developed after January 11, = 2008, the=20 DT data required by paragraph (d)(1) of this section must be = submitted=20 within 12 months of the airplane's return to service or in = accordance with=20 a schedule approved by the FAA Oversight Office.

(5) The repair evaluation guidelines required by paragraph = (e)(1) of=20 this section must be submitted by December 30, 2009.

(g) Exceptions. The requirements of this section do not = apply to=20 the following transport category airplane models:

(1) Convair CV=96240, 340, 440, if modified to include turbine=20 engines.

(2) Vickers Armstrong Viscount, TCDS No. A=96814.

(3) Douglas DC=963, if modified to include turbine engines, = TCDS No.=20 A=96618.

(4) Bombardier CL=9644, TCDS No. 1A20.

(5) Mitsubishi YS=9611, TCDS No. A1PC.

(6) British Aerospace BAC 1=9611, TCDS No. A5EU.

(7) Concorde, TCDS No. A45EU.

(8) deHavilland D.H. 106 Comet 4C, TCDS No. 7A10.

(9) deHavilland DHC=967, TCDS No. A20EA.

(10) VFW-Vereinigte Flugtechnische Werk VFW=96614, TCDS No. = A39EU.

(11) Illyushin Aviation IL 96T, TCDS No. A54NM.

(12) Bristol Aircraft Britannia 305, TCDS No. 7A2.

(13) Handley Page Herald Type 300, TCDS No. A21N.

(14) Avions Marcel Dassault=97Breguet Aviation Mercure 100C, = TCDS No.=20 A40EU.

(15) Airbus Caravelle, TCDS No. 7A6.

(16) Lockheed L=96300, TCDS No. A2S0.

(17) Boeing 707=96100/=96200, TCDS No. 4A21.

(18) Boeing 707=96300/=96400, TCDS No. 4A26.

(19) Boeing 720, TCDS No. 4A28.

[Doc. No. FAA=962005=9621693, 72 FR 70505, Dec. 12, 2007, as = amended by=20 Amdt. 26=964, 75 FR 11734, Mar. 12, 2010]

=A7 26.45   Holders of type = certificates=97Alterations=20 and repairs to alterations.
=20 top

(a) Applicability. This section applies to transport = category=20 airplanes subject to =A726.43.

(b) Fatigue critical alteration structure. For existing = and=20 future alteration data developed by the holder of a type = certificate, the=20 holder must=97

(1) Review alteration data and identify all alterations that = affect=20 fatigue critical baseline structure identified under = =A726.43(b)(1);

(2) For each alteration identified under paragraph (b)(1) of = this=20 section, identify any fatigue critical alteration structure;

(3) Develop and submit to the FAA Oversight Office for review = and=20 approval a list of the structure identified under paragraph (b)(2) = of this=20 section; and

(4) Upon approval, make the list required in paragraph (b)(3) = of this=20 section available to persons required to comply with = =A7=A7121.1109 and=20 129.109 of this chapter.

(c) DT Data. For existing and future alteration data = developed=20 by the holder of a type certificate that affect fatigue critical = baseline=20 structure identified under =A726.43(b)(1), unless previously = accomplished,=20 the holder must=97

(1) Perform a DTE and develop the DTI for the alteration and = fatigue=20 critical baseline structure that is affected by the = alteration;

(2) Submit the DT data developed in accordance with paragraphs = (c)(1)=20 of this section to the FAA Oversight Office or its properly = authorized=20 designees for review and approval; and

(3) Upon approval, make the DTI available to persons required = to comply=20 with =A7=A7121.1109 and 129.109 of this chapter.

(d) DT Data for Repairs Made to Alterations. For = existing and=20 future repair data developed by a holder of a type certificate, = the type=20 certificate holder must=97

(1) Review the repair data, and identify each repair that = affects any=20 fatigue critical alteration structure identified under paragraph = (b)(2) of=20 this section;

(2) For each repair identified under paragraph (d)(1) of this = section,=20 unless previously accomplished, perform a DTE and develop DTI;

(3) Submit the DT data developed in accordance with paragraph = (d)(2) of=20 this section to the FAA Oversight Office or its properly = authorized=20 designees for review and approval; and

(4) Upon approval, make the DTI available to persons required = to comply=20 with =A7=A7121.1109 and 129.109 of this chapter.

(e) Compliance times. Holders of type certificates must = submit=20 the following to the FAA Oversight Office or its properly = authorized=20 designees for review and approval by the specified compliance = time:

(1) The list of fatigue critical alteration structure = identified under=20 paragraph (b)(3) of this section must be submitted=97

(i) No later than 360 days after January 11, 2008, for = alteration data=20 approved before January 11, 2008.

(ii) No later than 30 days after March 12, 2010 or before = initial=20 approval of the alteration data, whichever occurs later, for = alteration=20 data approved on or after January 11, 2008.

(2) For alteration data developed and approved before January = 11, 2008,=20 the DT data required by paragraph (c)(2) of this section must be = submitted=20 by June 30, 2009.

(3) For alteration data approved on or after January 11, 2008, = DT data=20 required by paragraph (c)(2) of this section must be submitted = before=20 initial approval of the alteration data.

(4) For repair data developed and approved before January 11, = 2008, the=20 DT data required by paragraph (d)(2) of this section must be = submitted by=20 June 30, 2009.

(5) For repair data developed and approved after January 11, = 2008, the=20 DT data required by paragraph (d)(2) of this section must be = submitted=20 within 12 months after initial approval of the repair data and = before=20 making the DT data available to persons required to comply with = =A7=A7121.1109=20 and 129.109 of this chapter.

[Doc. No. FAA=962005=9621693, 72 FR 70505, Dec. 12, 2007, as = amended by=20 Amdt. 26=964, 75 FR 11734, Mar. 12, 2010]

=A7 26.47   Holders of and applicants for = a=20 supplemental type certificate=97Alterations and repairs to=20 alterations.
=20 top

(a) Applicability. This section applies to transport = category=20 airplanes subject to =A726.43.

(b) Fatigue critical alteration structure. For existing=20 structural alteration data approved under a supplemental = certificate, the=20 holder of the supplemental certificate must=97

(1) Review the alteration data and identify all alterations = that affect=20 fatigue critical baseline structure identified under = =A726.43(b)(1);

(2) For each alteration identified under paragraph (b)(1) of = this=20 section, identify any fatigue critical alteration structure;

(3) Develop and submit to the FAA Oversight Office for review = and=20 approval a list of the structure identified under paragraph (b)(2) = of this=20 section; and

(4) Upon approval, make the list required in paragraph (b)(3) = of this=20 section available to persons required to comply with = =A7=A7121.1109 and=20 129.109 of this chapter.

(c) DT Data. For existing and future alteration data = developed=20 by the holder of a supplemental type certificate that affect = fatigue=20 critical baseline structure identified under =A726.43(b)(1), = unless=20 previously accomplished, the holder of a supplemental type = certificate=20 must=97

(1) Perform a DTE and develop the DTI for the alteration and = fatigue=20 critical baseline structure that is affected by the = alteration;

(2) Submit the DT data developed in accordance with paragraphs = (c)(1)=20 of this section to the FAA Oversight Office or its properly = authorized=20 designees for review and approval; and

(3) Upon approval, make the DTI available to persons required = to comply=20 with =A7=A7121.1109 and 129.109 of this chapter.

(d) DT Data for Repairs Made to Alterations. For = existing and=20 future repair data developed by the holder of a supplemental = holder of a=20 supplemental type certificate, the holder of a supplemental type=20 certificate must=97

(1) Review the repair data, and identify each repair that = affects any=20 fatigue critical alteration structure identified under paragraph = (b)(2) of=20 this section;

(2) For each repair identified under paragraph (d)(1) of this = section,=20 unless previously accomplished, perform a DTE and develop DTI;

(3) Submit the DT data developed in accordance with paragraph = (d)(2) of=20 this section to the FAA Oversight Office or its properly = authorized=20 designees for review and approval; and

(4) Upon approval, make the DTI available to persons required = to comply=20 with =A7=A7121.1109 and 129.109 of this chapter.

(e) Compliance times. Holders of supplemental type = certificates=20 must submit the following to the FAA Oversight Office or its = properly=20 authorized designees for review and approval by the specified = compliance=20 time:

(1) The list of fatigue critical alteration structure required = by=20 paragraph (b)(3) of this section must be submitted no later than = 360 days=20 after January 11, 2008.

(2) For alteration data developed and approved before January = 11, 2008,=20 the DT data required by paragraph (c)(2) of this section must be = submitted=20 by June 30, 2009.

(3) For alteration data developed after January 11, 2008, the = DT data=20 required by paragraph (c)(2) of this section must be submitted = before=20 approval of the alteration data and making it available to persons = required to comply with =A7=A7121.1109 and 129.109 of this = chapter.

(4) For repair data developed and approved before January 11, = 2008, the=20 DT data required by paragraph (d)(2) of this section must be = submitted by=20 June 30, 2009.

(5) For repair data developed and approved after January 11, = 2008, the=20 DT data required by paragraph (d)(2) of this section, must be = submitted=20 within 12 months after initial approval of the repair data and = before=20 making the DT data available to persons required to comply with = =A7=A7121.1109=20 and 129.109 of this chapter.

=A7 26.49   Compliance plan.
=20 top

(a) Compliance plan. Except for applicants for type = certificates=20 and supplemental type certificates whose applications are = submitted after=20 January 11, 2008, each person identified in =A7=A726.43, 26.45, = and 26.47,=20 must submit a compliance plan consisting of the following:

(1) A project schedule identifying all major milestones for = meeting the=20 compliance times specified in =A7=A726.43(f), 26.45(e), and = 26.47(e), as=20 applicable.

(2) A proposed means of compliance with =A7=A726.43, 26.45, and = 26.47, as=20 applicable.

(3) A plan for submitting a draft of all compliance items = required by=20 this subpart for review by the FAA Oversight Office not less than = 60 days=20 before the applicable compliance date.

(b) Compliance dates for compliance plans. The following = persons=20 must submit the compliance plan described in paragraph (a) of this = section=20 to the FAA Oversight Office for approval on the following = schedule:

(1) For holders of type certificates, no later than 90 days = after=20 January 11, 2008.

(2) For holders of supplemental type certificates no later than = 180=20 days after January 11, 2008.

(3) For applicants for changes to type certificates whose = application=20 are submitted before January 11, 2008, no later than 180 days = after=20 January 11, 2008.

(c) Compliance Plan Implementation. Each affected person = must=20 implement the compliance plan as approved in compliance with = paragraph (a)=20 of this section.

Browse=20 Previous | Browse=20 Next

For questions or comments = regarding e-CFR=20 editorial content, features, or design, email ecfr@nara.gov.

For = questions=20 concerning e-CFR programming and delivery issues, email webteam@gpo.gov.

Section = 508 / Accessibility

 

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