Subpart A—General
Federal Aviation Administration, DOT § 26.5 as critical as the specific ice accretion de- Subpart A—General fined for that flight phase. Configuration dif- ferences and their effects on ice accretions § 26.1 Purpose and scope.
must be taken into account.
(f) The ice accretion that has the most ad- (a) This part establishes require- verse effect on handling qualities may be ments for support of the continued air- used for airplane performance tests provided worthiness of and safety improvements any difference in performance is conserv- for transport category airplanes. These atively taken into account.
requirements may include performing [Amdt. 25–140, 79 FR 65528, Nov. 4, 2014] assessments, developing design changes, developing revisions to In- PART 26—CONTINUED AIRWORTHI- structions for Continued Airworthiness (ICA), and making necessary docu- NESS AND SAFETY IMPROVE- mentation available to affected per- MENTS FOR TRANSPORT CAT- sons. Requirements of this part that EGORY AIRPLANES establish standards for design changes and revisions to the ICA are considered Subpart A—General airworthiness requirements.
Sec.
(b) Except as provided in paragraph 26.1 Purpose and scope.
(c) of this section, this part applies to 26.3 [Reserved] the following persons, as specified in 26.5 Applicability table.
each subpart of this part: (1) Holders of type certificates and Subpart B—Enhanced Airworthiness supplemental type certificates.
Program for Airplane Systems (2) Applicants for type certificates 26.11 Electrical wiring interconnection sys- and supplemental type certificates and tems (EWIS) maintenance program.
changes to those certificates (including service bulletins describing design Subpart C—Aging Airplane Safety— changes).
Widespread Fatigue Damage (3) Persons seeking design approval 26.21 Limit of validity.
for airplane repairs, alterations, or 26.23 Extended limit of validity.
modifications that may affect air- worthiness.
Subpart D—Fuel Tank Flammability (4) Holders of type certificates and their licensees producing new air- 26.31 Definitions.
26.33 Holders of type certificates: Fuel tank planes.
flammability.
(c) An applicant for approval of a de- 26.35 Changes to type certificates affecting sign change is not required to comply fuel tank flammability.
with any applicable airworthiness re- 26.37 Pending type certification projects: quirement of this part if the applicant Fuel tank flammability.
elects or is required to comply with a 26.39 Newly produced airplanes: Fuel tank corresponding amendment to part 25 of flammability.
this chapter that is adopted concur- Subpart E—Aging Airplane Safety—Dam- rently or after that airworthiness re- age Tolerance Data for Repairs and quirement.
Alterations (d) For the purposes of this part, the word ‘‘type certificate’’ does not in- 26.41 Definitions.
clude supplemental type certificates.
26.43 Holders of and applicants for type cer- tificates—Repairs.
§ 26.3 [Reserved] 26.45 Holders of type certificates—Alter- ations and repairs to alterations.
§ 26.5 Applicability table.
26.47 Holders of and applicants for a supple- mental type certificate—Alterations and Table 1 of this section provides an repairs to alterations.
overview of the applicability of this 26.49 Compliance plan.
part. It provides guidance in identi- A UTHORITY : 49 U.S.C. 106(g), 40113, 44701, fying what sections apply to various 44702 and 44704.
types of entities. The specific applica- bility of each subpart and section is S OURCE : Docket No. FAA–2004–18379, 72 FR 63409, Nov. 8, 2007, unless otherwise noted. specified in the regulatory text.
Section 2
14 CFR Ch. I (1–1–25 Edition) § 26.11 T ABLE 1—A PPLICABILITY OF P ART 26 R ULES Applicable sections Subpart E dam- Subpart C widespread Subpart D fuel tank Subpart B EAPAS/FTS age fatigue damage flammability tolerance data Effective date of rule .................. December 10, 2007 .... January 14, 2011 ........ December 26, 2008 .... January 11, Existing TC Holders ................. 26.11 ........................... 26.21 ........................... 26.33 ........................... 26.43, 26.45, 26.49 Pending TC Applicants ............ 26.11 ........................... 26.21 ........................... 26.37 ........................... 26.43, 26.45 Future TC applicants ............... N/A .............................. N/A .............................. N/A .............................. 26.43 Existing STC Holders .............. N/A .............................. 26.21 ........................... 26.35 ........................... 26.47, 26.49 Pending STC/ATC applicants .. 26.11 ........................... 26.21 ........................... 26.35 ........................... 26.45, 26.47, 26.49 Future STC/ATC applicants ..... 26.11 ........................... 26.21 ........................... 26.35 ........................... 26.45, 26.47, 26.49 Manufacturers ............................ N/A .............................. N/A .............................. 26.39 ........................... N/A As of the effective date of the identified rule.
Application made after the effective date of the identified rule.
[Doc. No. FAA–2006–24281, 75 FR 69782, Nov. 15, 2010] this rule. Each person specified in para- Subpart B—Enhanced Airworthi- graph (d) of this section must also re- ness Program for Airplane view any fuel tank system ICA devel- Systems oped by that person to comply with SFAR 88 to ensure compatibility with § 26.11 Electrical wiring interconnec- tion systems (EWIS) maintenance the EWIS ICA, including minimizing program.
redundant requirements.
(c) Applicants for amendments to (a) Except as provided in paragraph type certificates and supplemental (g) of this section, this section applies type certificates, as identified in para- to transport category, turbine-powered graph (d) of this section, must: airplanes with a type certificate issued (1) Evaluate whether the design after January 1, 1958, that, as a result change for which approval is sought ne- of the original certification, or later cessitates a revision to the ICA re- increase in capacity, have— quired by paragraph (b) of this section (1) A maximum type-certificated pas- to comply with the requirements of Ap- senger capacity of 30 or more or pendix H, paragraphs H25.5(a)(1) and (2) A maximum payload capacity of (b). If so, the applicant must develop 7,500 pounds or more.
and submit the necessary revisions for (b) Holders of, and applicants for, review and approval by the responsible type certificates, as identified in para- Aircraft Certification Service office.
graph (d) of this section must develop (2) Ensure that any revised EWIS ICA Instructions for Continued Airworthi- remain compatible with any fuel tank ness (ICA) for the representative air- system ICA previously developed to plane’s EWIS in accordance with part comply with SFAR 88 and any redun- 25, Appendix H paragraphs H25.5(a)(1) dant requirements between them are and (b) of this subchapter in effect on minimized.
December 10, 2007 for each affected type design, and submit those ICA for re- (d) The following persons must com- view and approval by the responsible ply with the requirements of paragraph Aircraft Certification Service office. (b) or (c) of this section, as applicable, For purposes of this section, the ‘‘rep- before the dates specified.
resentative airplane’’ is the configura- (1) Holders of type certificates (TC): tion of each model series airplane that December 10, 2009.
incorporates all variations of EWIS (2) Applicants for TCs, and amend- used in production on that series air- ments to TCs (including service bul- plane, and all TC-holder-designed letins describing design changes), if the modifications mandated by airworthi- date of application was before Decem- ness directive as of the effective date of ber 10, 2007 and the certificate was Federal Aviation Administration, DOT § 26.21 issued on or after December 10, 2007: proved in compliance with paragraph December 10, 2009 or the date the cer- (e) of this section.
tificate is issued, whichever occurs (g) This section does not apply to the later. following airplane models: (3) Unless compliance with § 25.1729 of (1) Lockheed L–188 this subchapter is required or elected, (2) Bombardier CL–44 applicants for amendments to TCs, if (3) Mitsubishi YS–11 the application was filed on or after (4) British Aerospace BAC 1–11 December 10, 2007: December 10, 2009, or (5) Concorde the date of approval of the certificate, (6) deHavilland D.H. 106 Comet 4C whichever occurs later.
(7) VFW—Vereinigte Flugtechnische (4) Applicants for supplemental type Werk VFW–614 certificates (STC), including changes (8) Illyushin Aviation IL 96T to existing STCs, if the date of applica- (9) Bristol Aircraft Britannia 305 tion was before December 10, 2007 and (10) Handley Page Herald Type 300 the certificate was issued on or after (11) Avions Marcel Dassault—Breguet December 10, 2007: June 7, 2010, or the Aviation Mercure 100C date of approval of the certificate, (12) Airbus Caravelle whichever occurs later.
(13) Lockheed L–300 (5) Unless compliance with § 25.1729 of this subchapter is required or elected, [Amdt. 26–0, 72 FR 63409, Nov. 8, 2007; 72 FR applicants for STCs, including changes 68618, Dec. 5, 2007, as amended by Doc. No.
to existing STCs, if the application was FAA–2018–0119, Amdt. 26–7, 83 FR 9170, Mar. 5, filed on or after December 10, 2007, 2018] June 7, 2010, or the date of approval of the certificate, whichever occurs later.
Subpart C—Aging Airplane Safe- (e) Each person identified in para- ty—Widespread Fatigue Dam- graphs (d)(1), (d)(2), and (d)(4) of this age section must submit to the responsible Aircraft Certification Service office for S OURCE : Docket No. FAA–2006–24281, 75 FR approval a compliance plan by March 69782, Nov. 15, 2010, unless otherwise noted.
10, 2008. The compliance plan must in- clude the following information: § 26.21 Limit of validity.
(1) A proposed project schedule, iden- (a) Applicability. Except as provided tifying all major milestones, for meet- in paragraph (g) of this section, this ing the compliance dates specified in section applies to transport category, paragraph (d) of this section.
turbine-powered airplanes with a max- (2) A proposed means of compliance imum takeoff gross weight greater with this section, identifying all re- than 75,000 pounds and a type certifi- quired submissions, including all com- cate issued after January 1, 1958, re- pliance items as mandated in part 25, gardless of whether the maximum Appendix H paragraphs H25.5(a)(1) and takeoff gross weight is a result of an (b) of this subchapter in effect on De- original type certificate or a later de- cember 10, 2007, and all data to be de- sign change. This section also applies veloped to substantiate compliance.
to transport category, turbine-powered (3) A proposal for submitting a draft airplanes with a type certificate issued of all compliance items required by after January 1, 1958, if a design change paragraph (e)(2) of this section for re- approval for which application is made view by the responsible Aircraft Cer- after January 14, 2011 has the effect of tification Service office not less than reducing the maximum takeoff gross 60 days before the compliance time weight from greater than 75,000 pounds specified in paragraph (d) of this sec- to 75,000 pounds or less.
tion.
(4) A proposal for how the approved (b) Limit of validity. Each person iden- ICA will be made available to affected tified in paragraph (c) of this section persons. must comply with the following re- (f) Each person specified in paragraph quirements: (e) must implement the compliance (1) Establish a limit of validity of the plan, or later approved revisions, as ap- engineering data that supports the 14 CFR Ch. I (1–1–25 Edition) § 26.21 structural maintenance program (here- (4) Incorporate the applicable LOV after referred to as LOV) that cor- established under paragraph (b)(1) of responds to the period of time, stated this section into the ALS for each air- as a number of total accumulated plane structural configuration evalu- flight cycles or flight hours or both, ated under paragraph (b)(1) and submit during which it is demonstrated that it to the responsible Aircraft Certifi- widespread fatigue damage will not cation Service office for approval.
occur in the airplane. This demonstra- (c) Persons who must comply and com- tion must include an evaluation of air- pliance dates. The following persons plane structural configurations and be must comply with the requirements of supported by test evidence and analysis paragraph (b) of this section by the at a minimum and, if available, service specified date.
experience, or service experience and (1) Holders of type certificates (TC) teardown inspection results, of high- of airplane models identified in Table 1 time airplanes of similar structural de- of this section: No later than the appli- sign, accounting for differences in op- cable date identified in Table 1 of this erating conditions and procedures. The section.
airplane structural configurations to (2) Applicants for TCs, if the date of be evaluated include— application was before January 14, 2011: (i) All model variations and deriva- No later than the latest of the fol- tives approved under the type certifi- lowing dates: cate; and (i) January 14, 2016; (ii) All structural modifications to (ii) The date the certificate is issued; and replacements for the airplane or structural configurations specified in (iii) The date specified in the plan ap- paragraph (b)(1)(i) of this section, man- proved under § 25.571(b) for completion dated by airworthiness directives as of of the full-scale fatigue testing and January 14, 2011. demonstrating that widespread fatigue (2) If the LOV depends on perform- damage will not occur in the airplane ance of maintenance actions for which structure.
service information has not been man- (3) Applicants for amendments to dated by airworthiness directive as of TCs, with the exception of amendments January 14, 2011, submit the following to TCs specified in paragraphs (c)(6) or to the responsible Aircraft Certifi- (c)(7) of this section, if the original TC cation Service office: was issued before January 14, 2011: No (i) For those maintenance actions for later than the latest of the following which service information has been dates: issued as of the applicable compliance (i) January 14, 2016; date specified in paragraph (c) of this (ii) The date the amended certificate section, a list identifying each of those is issued; or actions. (iii) The date specified in the plan ap- (ii) For those maintenance actions proved under § 25.571(b) for completion for which service information has not of the full-scale fatigue testing and been issued as of the applicable compli- demonstrating that widespread fatigue ance date specified in paragraph (c) of damage will not occur in the airplane this section, a list identifying each of structure.
those actions and a binding schedule (4) Applicants for amendments to for providing in a timely manner the TCs, with the exception of amendments necessary service information for those to TCs specified in paragraphs (c)(6) or actions. Once the responsible Aircraft (c)(7) of this section, if the application Certification Service office approves for the original TC was made before this schedule, each person identified in January 14, 2011 but the TC was not paragraph (c) of this section must com- issued before January 14, 2011: No later ply with that schedule. than the latest of the following dates: (3) Unless previously accomplished, (i) January 14, 2016; establish an Airworthiness Limitations (ii) The date the amended certificate section (ALS) for each airplane struc- is issued; or tural configuration evaluated under (iii) The date specified in the plan ap- paragraph (b)(1) of this section. proved under § 25.571(b) for completion Federal Aviation Administration, DOT § 26.21 of the full-scale fatigue testing and fied in paragraph (c) of this section, as demonstrating that widespread fatigue applicable.
damage will not occur in the airplane (4) A proposal for how the LOV will structure. be distributed.
(5) Holders of either supplemental (e) Compliance dates for compliance type certificates (STCs) or amend- plans. The following persons must sub- ments to TCs that increase maximum mit the compliance plan described in takeoff gross weights from 75,000 paragraph (d) of this section to the re- pounds or less to greater than 75,000 sponsible Aircraft Certification Service pounds: No later than July 14, 2012. office by the specified date.
(6) Applicants for either STCs or (1) Holders of type certificates: No amendments to TCs that increase max- later than April 14, 2011.
imum takeoff gross weights from 75,000 (2) Applicants for TCs and amend- pounds or less to greater than 75,000 ments to TCs, with the exception of pounds: No later than the latest of the amendments to TCs specified in para- following dates: graphs (e)(4), (e)(5), or (e)(6) of this sec- (i) July 14, 2012; tion, if the date of application was be- (ii) The date the certificate is issued; fore January 14, 2011 but the TC or TC or amendment was not issued before Jan- (iii) The date specified in the plan ap- uary 14, 2011: No later than April 14, proved under § 25.571(b) for completion 2011.
of the full-scale fatigue testing and (3) Holders of either supplemental demonstrating that widespread fatigue type certificates or amendments to TCs damage will not occur in the airplane that increase maximum takeoff gross structure. weights from 75,000 pounds or less to (7) Applicants for either STCs or greater than 75,000 pounds: No later amendments to TCs that decrease max- than April 14, 2011.
imum takeoff gross weights from (4) Applicants for either STCs or greater than 75,000 pounds to 75,000 amendments to TCs that increase max- pounds or less, if the date of applica- imum takeoff gross weights from 75,000 tion was after January 14, 2011: No pounds or less to greater than 75,000 later than the latest of the following pounds, if the date of application was dates: before January 14, 2011: No later than (i) July 14, 2012; April 14, 2011.
(ii) The date the certificate is issued; (5) Applicants for either STCs or or amendments to TCs that increase max- (iii) The date specified in the plan ap- imum takeoff gross weights from 75,000 proved under § 25.571(b) for completion pounds or less to greater than 75,000 of the full-scale fatigue testing and pounds, if the date of application is on demonstrating that widespread fatigue or after January 14, 2011: Within 90 damage will not occur in the airplane days after the date of application.
structure. (6) Applicants for either STCs or (d) Compliance plan. Each person amendments to TCs that decrease max- identified in paragraph (e) of this sec- imum takeoff gross weights from tion must submit a compliance plan greater than 75,000 pounds to 75,000 consisting of the following: pounds or less, if the date of applica- (1) A proposed project schedule, iden- tion is on or after January 14, 2011: tifying all major milestones, for meet- Within 90 days after the date of appli- ing the compliance dates specified in cation.
paragraph (c) of this section. (f) Compliance plan implementation.
(2) A proposed means of compliance Each affected person must implement with paragraphs (b)(1) through (b)(4) of the compliance plan as approved in this section. compliance with paragraph (d) of this (3) A proposal for submitting a draft section.
of all compliance items required by (g) Exceptions. This section does not paragraph (b) of this section for review apply to the following airplane models: by the responsible Aircraft Certifi- (1) Bombardier BD–700.
cation Service office not less than 60 (2) Bombardier CL–44.
days before the compliance date speci- (3) Gulfstream GV.
14 CFR Ch. I (1–1–25 Edition) § 26.23 (4) Gulfstream GV–SP. (10) Lockheed 300–50A01 (USAF C141A).
(5) British Aerospace, Aircraft Group, (11) Boeing 707.
and Societe Nationale Industrielle (12) Boeing 720.
Aerospatiale Concorde Type 1.
(13) deHavilland D.H. 106 Comet 4C.
(6) British Aerospace (Commercial (14) Ilyushin Aviation IL–96T.
Aircraft) Ltd., Armstrong Whitworth (15) Bristol Aircraft Britannia 305.
Argosy A.W. 650 Series 101.
(16) Avions Marcel Dassault-Breguet (7) British Aerospace Airbus, Ltd., Aviation Mercure 100C.
BAC 1–11.
(17) Airbus Caravelle.
(8) BAE Systems (Operations) Ltd., (18) D & R Nevada, LLC, Convair BAe 146.
Model 22.
(9) BAE Systems (Operations) Ltd., (19) D & R Nevada, LLC, Convair Avro 146.
Model 23M.
T ABLE 1—C OMPLIANCE DATES FOR AFFECTED AIRPLANES Compliance date— Airplane model (months after January (all existing models) 14, 2011) Airbus: Boeing: Bombardier: Embraer: Fokker: Lockheed: McDonnell Douglas: Type certificated as of January 14, 2011.
[Doc. No. FAA–2006–24281, 75 FR 69782, Nov.
§ 26.23 Extended limit of validity.
15, 2010, as amended at 77 FR 30878, May 24, (a) Applicability. Any person may 2012; Doc. No. FAA–2018–0119, Amdt. 26–7, 83 apply to extend a limit of validity of FR 9169, Mar. 5, 2018] the engineering data that supports the Federal Aviation Administration, DOT § 26.33 structural maintenance program (here- reaches the proposed extended LOV.
after referred to as LOV) approved These maintenance actions must be under § 25.571 of this subchapter, § 26.21, documented as airworthiness limita- or this section. Extending an LOV is a tion items in the ALS and submitted to major design change. The applicant the responsible Aircraft Certification must comply with the relevant provi- Service office for approval.
sions of subparts D or E of part 21 of [Docket No. FAA–2006–24281, 75 FR 69782, this subchapter and paragraph (b) of Nov. 15, 2010, as amended by Doc. No. FAA– this section.
2018–0119, Amdt. 26–7, 83 FR 9169, Mar. 5, 2018] (b) Extended limit of validity. Each per- son applying for an extended LOV must Subpart D—Fuel Tank comply with the following require- Flammability ments: (1) Establish an extended LOV that S OURCE : Docket No. FAA–2005–22997, 73 FR corresponds to the period of time, stat- 42499, July 21, 2008, unless otherwise noted.
ed as a number of total accumulated flight cycles or flight hours or both, § 26.31 Definitions.
during which it is demonstrated that For purposes of this subpart— widespread fatigue damage will not (a) Fleet Average Flammability Expo- occur in the airplane. This demonstra- sure has the meaning defined in Appen- tion must include an evaluation of air- dix N of part 25 of this chapter.
plane structural configurations and be (b) Normally Emptied means a fuel supported by test evidence and analysis tank other than a Main Fuel Tank.
at a minimum and, if available, service Main Fuel Tank is defined in 14 CFR experience, or service experience and 25.981(b).
teardown inspection results, of high- time airplanes of similar structural de- § 26.33 Holders of type certificates: sign, accounting for differences in op- Fuel tank flammability.
erating conditions and procedures. The airplane structural configurations to (a) Applicability. This section applies be evaluated include— to U.S. type certificated transport cat- (i) All model variations and deriva- egory, turbine-powered airplanes, other tives approved under the type certifi- than those designed solely for all-cargo cate for which approval for an exten- operations, for which the State of Man- sion is sought; and ufacture issued the original certificate (ii) All structural modifications to of airworthiness or export airworthi- and replacements for the airplane ness approval on or after January 1, structural configurations specified in 1992, that, as a result of original type paragraph (b)(1)(i) of this section, man- certification or later increase in capac- dated by airworthiness directive, up to ity have: the date of approval of the extended (1) A maximum type-certificated pas- LOV. senger capacity of 30 or more, or (2) Establish a revision or supple- (2) A maximum payload capacity of ment, as applicable, to the Airworthi- 7,500 pounds or more.
ness Limitations section (ALS) of the (b) Flammability Exposure Analysis. (1) Instructions for Continued Airworthi- General. Within 150 days after Decem- ness required by § 25.1529 of this sub- ber 26, 2008, holders of type certificates chapter, and submit it to the respon- must submit for approval to the re- sible Aircraft Certification Service of- sponsible Aircraft Certification Service fice for approval. The revised ALS or office a flammability exposure analysis supplement to the ALS must include of all fuel tanks defined in the type de- the applicable extended LOV estab- sign, as well as all design variations lished under paragraph (b)(1) of this approved under the type certificate section. that affect flammability exposure. This (3) Develop the maintenance actions analysis must be conducted in accord- determined by the WFD evaluation per- ance with Appendix N of part 25 of this formed in paragraph (b)(1) of this sec- chapter.
tion to be necessary to preclude WFD (2) Exception. This paragraph (b) does from occurring before the airplane not apply to— 14 CFR Ch. I (1–1–25 Edition) § 26.33 (i) Fuel tanks for which the type cer- office design changes and service in- tificate holder has notified the FAA structions for installation of fuel tank under paragraph (g) of this section that IMM that comply with 14 CFR 25.981(c) it will provide design changes and serv- in effect on December 26, 2008.
ice instructions for Flammability Re- (e) Instructions for Continued Air- duction Means or an Ignition Mitiga- worthiness (ICA). No later than Decem- tion Means (IMM) meeting the require- ber 27, 2010, holders of type certificates ments of paragraph (c) of this section. required by paragraph (c) of this sec- (ii) Fuel tanks substantiated to be tion to make design changes must sub- conventional unheated aluminum wing mit for approval by the responsible tanks. Aircraft Certification Service office, (c) Design Changes. For fuel tanks critical design configuration control with a Fleet Average Flammability Ex- limitations (CDCCL), inspections, or posure exceeding 7 percent, one of the other procedures to prevent increasing following design changes must be the flammability exposure of any tanks made. equipped with FRM above that per- (1) Flammability Reduction Means mitted under paragraph (c)(1) of this (FRM). A means must be provided to section and to prevent degradation of reduce the fuel tank flammability. the performance of any IMM provided (i) Fuel tanks that are designed to be under paragraph (c)(2) of this section.
Normally Emptied must meet the These CDCCL, inspections, and proce- flammability exposure criteria of Ap- dures must be included in the Air- pendix M of part 25 of this chapter if worthiness Limitations Section (ALS) any portion of the tank is located with- of the ICA required by 14 CFR 25.1529 or in the fuselage contour. paragraph (f) of this section. Unless (ii) For all other fuel tanks, the FRM shown to be impracticable, visible must meet all of the requirements of means to identify critical features of Appendix M of part 25 of this chapter, the design must be placed in areas of except, instead of complying with para- the airplane where foreseeable mainte- graph M25.1 of this appendix, the Fleet nance actions, repairs, or alterations Average Flammability Exposure may may compromise the critical design not exceed 7 percent. configuration limitations. These visi- (2) Ignition Mitigation Means (IMM). A ble means must also be identified as a means must be provided to mitigate CDCCL.
the effects of an ignition of fuel vapors (f) Airworthiness Limitations. Unless within the fuel tank such that no dam- previously accomplished, no later than age caused by an ignition will prevent December 27, 2010, holders of type cer- continued safe flight and landing. tificates affected by this section must (d) Service Instructions. No later than establish an ALS of the maintenance December 27, 2010, holders of type cer- manual or ICA for each airplane con- tificates required by paragraph (c) of figuration evaluated under paragraph this section to make design changes (b)(1) of this section and submit it to must meet the requirements specified the responsible Aircraft Certification in either paragraph (d)(1) or (d)(2) of Service office for approval. The ALS this section. The required service in- must include a section that contains structions must identify each airplane the CDCCL, inspections, or other pro- subject to the applicability provisions cedures developed under paragraph (e) of paragraph (a) of this section. of this section.
(1) FRM. The type certificate holder (g) Compliance Plan for Flammability must submit for approval by the re- Exposure Analysis. Within 90 days after sponsible Aircraft Certification Service December 26, 2008, each holder of a type office design changes and service in- certificate required to comply with structions for installation of fuel tank paragraph (b) of this section must sub- flammability reduction means (FRM) mit to the responsible Aircraft Certifi- meeting the criteria of paragraph (c) of cation Service office a compliance plan this section. consisting of the following: (2) IMM. The type certificate holder (1) A proposed project schedule for must submit for approval by the re- submitting the required analysis, or a sponsible Aircraft Certification Service determination that compliance with Federal Aviation Administration, DOT § 26.35 paragraph (b) of this section is not re- supplemental type certificate or an quired because design changes and amendment to a type certificate was service instructions for FRM or IMM made before December 26, 2008 and if will be developed and made available as the approval was not issued before De- required by this section. cember 26, 2008; and (2) A proposed means of compliance (3) If an application for a supple- with paragraph (b) of this section, if mental type certificate or an amend- applicable. ment to a type certificate is made on (h) Compliance Plan for Design or after December 26, 2008, any of the Changes and Service Instructions. Within following design changes: 210 days after December 26, 2008, each (i) Installation of a fuel tank de- holder of a type certificate required to signed to be Normally Emptied, comply with paragraph (d) of this sec- (ii) Changes to existing fuel tank ca- tion must submit to the responsible pacity, or Aircraft Certification Service office a (iii) Changes that may increase the compliance plan consisting of the fol- flammability exposure of an existing lowing: fuel tank for which FRM or IMM is re- (1) A proposed project schedule, iden- quired by § 26.33(c).
tifying all major milestones, for meet- (b) Flammability Exposure Analysis —(1) ing the compliance dates specified in General. By the times specified in para- paragraphs (d), (e) and (f) of this sec- graphs (b)(1)(i) and (b)(1)(ii) of this sec- tion. tion, each person subject to this sec- (2) A proposed means of compliance tion must submit for approval a flam- with paragraphs (d), (e) and (f) of this mability exposure analysis of the aux- section. iliary fuel tanks or other affected fuel (3) A proposal for submitting a draft tanks, as defined in the type design, to of all compliance items required by the responsible Aircraft Certification paragraphs (d), (e) and (f) of this sec- Service office. This analysis must be tion for review by the responsible Air- conducted in accordance with Appendix craft Certification Service office not N of part 25 of this chapter.
less than 60 days before the compliance (i) Holders of supplemental type cer- times specified in those paragraphs.
tificates and field approvals: Within 12 (4) A proposal for how the approved months of December 26, 2008, service information and any necessary (ii) Applicants for supplemental type modification parts will be made avail- certificates and for amendments to able to affected persons.
type certificates: Within 12 months (i) Each affected type certificate after December 26, 2008, or before the holder must implement the compliance certificate is issued, whichever occurs plans, or later revisions, as approved later.
under paragraph (g) and (h) of this sec- (2) Exception. This paragraph does not tion.
apply to— (i) Fuel tanks for which the type cer- [Doc. No. FAA–2005–22997, 73 FR 42499, July tificate holder, supplemental type cer- 21, 2008, as amended by Amdt. 26–3, 74 FR tificate holder, or field approval holder 31619, July 2, 2009; Doc. No. FAA–2018–0119, Amdt. 26–7, 83 FR 9169, Mar. 5, 2018] has notified the FAA under paragraph (f) of this section that it will provide § 26.35 Changes to type certificates af- design changes and service instructions fecting fuel tank flammability.
for an IMM meeting the requirements (a) Applicability. This section applies of § 25.981(c) in effect December 26, 2008; to holders and applicants for approvals and of the following design changes to any (ii) Fuel tanks substantiated to be airplane subject to 14 CFR 26.33(a): conventional unheated aluminum wing (1) Any fuel tank designed to be Nor- tanks.
mally Emptied if the fuel tank instal- (c) Impact Assessment. By the times lation was approved pursuant to a sup- specified in paragraphs (c)(1) and (c)(2) plemental type certificate or a field ap- of this section, each person subject to proval before December 26, 2008; paragraph (a)(1) of this section holding (2) Any fuel tank designed to be Nor- an approval for installation of a Nor- mally Emptied if an application for a mally Emptied fuel tank on an airplane 14 CFR Ch. I (1–1–25 Edition) § 26.35 model listed in Table 1 of this section, CDCCL. Any fuel tank modified as re- and each person subject to paragraph quired by this paragraph must also be (a)(3)(iii) of this section, must submit evaluated as required by paragraph (b) for approval to the responsible Aircraft of this section.
Certification Service office an assess- (2) Applicants subject to paragraph ment of the fuel tank system, as modi- (a)(2), or (a)(3)(i) of this section must fied by their design change. The assess- comply with the requirements of 14 ment must identify any features of the CFR 25.981, in effect on December 26, design change that compromise any 2008.
critical design configuration control (3) Applicants subject to paragraph limitation (CDCCL) applicable to any (a)(3)(ii) of this section must comply airplane on which the design change is with the requirements of 14 CFR 26.33.
eligible for installation.
(e) Compliance Times for Design (1) Holders of supplemental type cer- Changes and Service Instructions. The tificates and field approvals: Before following persons subject to this sec- June 26, 2011.
tion must comply with the require- (2) Applicants for supplemental type ments of paragraph (d) of this section certificates and for amendments to at the specified times.
type certificates: Before June 26, 2011 (1) Holders of supplemental type cer- or before the certificate is issued, tificates and field approvals: Before De- whichever occurs later.
cember 26, 2012.
(2) Applicants for supplemental type T ABLE 1 certificates and for amendments to type certificates: Before December 26, Model—Boeing 2012, or before the certificate is issued, whichever occurs later.
747 Series (f) Compliance Planning. By the appli- 737 Series cable date specified in Table 2 of this 777 Series section, each person subject to para- 767 Series graph (a)(1) of this section must submit 757 Series for approval by the responsible Aircraft Certification Service office compliance Model—Airbus plans for the flammability exposure analysis required by paragraph (b) of A318, A319, A320, A321 Series this section, the impact assessment re- A300, A310 Series quired by paragraph (c) of this section, A330, A340 Series and the design changes and service in- structions required by paragraph (d) of (d) Design Changes and Service Instruc- this section. Each person’s compliance tions. By the times specified in para- plans must include the following: graph (e) of this section, each person (1) A proposed project schedule for subject to this section must meet the submitting the required analysis or im- requirements of paragraphs (d)(1) or pact assessment.
(d)(2) of this section, as applicable.
(2) A proposed means of compliance (1) For holders and applicants subject with paragraph (d) of this section.
to paragraph (a)(1) or (a)(3)(iii) of this section, if the assessment required by (3) For the requirements of paragraph paragraph (c) of this section identifies (d) of this section, a proposal for sub- any features of the design change that mitting a draft of all design changes, if compromise any CDCCL applicable to any are required, and Airworthiness any airplane on which the design Limitations (including CDCCLs) for re- change is eligible for installation, the view by the responsible Aircraft Cer- holder or applicant must submit for ap- tification Service office not less than proval by the responsible Aircraft Cer- 60 days before the compliance time tification Service office design changes specified in paragraph (e) of this sec- and service instructions for Flamma- tion.
bility Impact Mitigation Means (4) For the requirements of paragraph (FIMM) that would bring the design (d) of this section, a proposal for how change into compliance with the the approved service information and Federal Aviation Administration, DOT § 26.41 any necessary modification parts will be made available to affected persons.
T ABLE 2—C OMPLIANCE PLANNING DATES Flammability exposure anal- Design changes and service Impact assessment plan ysis plan instructions plan STC and Field Approval Hold- March 26, 2009 ...................... February 26, 2011 .................. August 26, 2011.
ers.
(g) Each person subject to this sec- (b) Any fuel tank meeting all of the tion must implement the compliance criteria stated in paragraphs (b)(1), plans, or later revisions, as approved (b)(2) and (b)(3) of this section must under paragraph (f) of this section. have flammability reduction means (FRM) or ignition mitigation means [Doc. No. FAA–2005–22997, 73 FR 42499, July (IMM) that meet the requirements of 14 21, 2008, as amended by Amdt. 26–3, 74 FR CFR 25.981 in effect on December 26, 31619, July 2, 2009; Doc. No. FAA–2018–0119, Amdt. 26–7, 83 FR 9170, Mar. 5, 2018] 2008.
(1) The fuel tank is Normally § 26.37 Pending type certification Emptied.
projects: Fuel tank flammability.
(2) Any portion of the fuel tank is lo- (a) Applicability. This section applies cated within the fuselage contour.
to any new type certificate for a trans- (3) The fuel tank exceeds a Fleet Av- port category airplane, if the applica- erage Flammability Exposure of 7 per- tion was made before December 26, cent.
2008, and if the certificate was not (c) All other fuel tanks that exceed issued before December 26, 2008. This an Fleet Average Flammability Expo- section applies only if the airplane sure of 7 percent must have an IMM would have— that meets 14 CFR 25.981(d) in effect on (1) A maximum type-certificated pas- December 26, 2008, or an FRM that senger capacity of 30 or more, or meets all of the requirements of Appen- (2) A maximum payload capacity of dix M to this part, except instead of 7,500 pounds or more.
complying with paragraph M25.1 of (b) If the application was made on or that appendix, the Fleet Average Flam- after June 6, 2001, the requirements of mability Exposure may not exceed 7 14 CFR 25.981 in effect on December 26, percent.
2008, apply.
[Doc. No. FAA–2005–22997, 73 FR 42499, July [Doc. No. FAA–2005–22997, 73 FR 42499, July 21, 2008, as amended by Amdt. 26–3, 74 FR 21, 2008, as amended by Amdt. 26–3, 74 FR 31619, July 2, 2009] 31619, July 2, 2009] § 26.39 Newly produced airplanes: Fuel Subpart E—Aging Airplane Safe- tank flammability.
ty—Damage Tolerance Data (a) Applicability: This section applies for Repairs and Alterations to Boeing model airplanes specified in Table 1 of this section, including pas- S OURCE : Docket No. FAA–2005–21693, 72 FR senger and cargo versions of each 70505, Dec. 12, 2007, unless otherwise noted.
model, when application is made for original certificates of airworthiness or § 26.41 Definitions.
export airworthiness approvals after Affects (or Affected) means structure December 27, 2010.
has been physically repaired, altered, or modified, or the structural loads T ABLE 1 acting on the structure have been in- Model—Boeing creased or redistributed.
Baseline structure means structure 747 Series 737 Series that is designed under the original type 777 Series certificate or amended type certificate 767 Series for that airplane model.
14 CFR Ch. I (1–1–25 Edition) § 26.43 Damage Tolerance Evaluation (DTE) tural repair manuals and service bul- means a process that leads to a deter- letins (or equivalent types of docu- mination of maintenance actions nec- ments).
essary to detect or preclude fatigue § 26.43 Holders of and applicants for cracking that could contribute to a type certificates—Repairs.
catastrophic failure. As applied to re- pairs and alterations, a DTE includes (a) Applicability. Except as specified the evaluation both of the repair or al- in paragraph (g) of this section, this teration and of the fatigue critical section applies to transport category, structure affected by the repair or al- turbine powered airplane models with a teration.
type certificate issued after January 1, Damage Tolerance Inspection (DTI) 1958, that as a result of original type means the inspection developed as a re- certification or later increase in capac- sult of a DTE. A DTI includes the areas ity have— to be inspected, the inspection method, (1) A maximum type certificated pas- the inspection procedures, including senger seating capacity of 30 or more; acceptance and rejection criteria, the or threshold, and any repeat intervals as- (2) A maximum payload capacity of sociated with those inspections. The 7,500 pounds or more.
DTI may specify a time limit when a (b) List of fatigue critical baseline struc- repair or alteration needs to be re- ture. For airplanes specified in para- placed or modified. If the DTE con- graph (a) of this section, the holder of cludes that DT-based supplemental or applicant for a type certificate structural inspections are not nec- must— essary, the DTI contains a statement (1) Identify fatigue critical baseline to that effect.
structure for all airplane model vari- DT data mean DTE documentation ations and derivatives approved under and the DTI.
the type certificate; and DTE documentation means data that (2) Develop and submit to the respon- identify the evaluated fatigue critical sible Aircraft Certification Service of- structure, the basic assumptions ap- fice for review and approval, a list of plied in a DTE, and the results of a the structure identified under para- DTE.
graph (b)(1) of this section and, upon Fatigue critical structure means air- approval, make the list available to plane structure that is susceptible to persons required to comply with § 26.47 fatigue cracking that could contribute and §§ 121.1109 and 129.109 of this chap- to a catastrophic failure, as determined ter.
in accordance with § 25.571 of this chap- (c) Existing and future published repair ter. Fatigue critical structure includes data. For repair data published by a structure, which, if repaired or altered, holder of a type certificate that is cur- could be susceptible to fatigue crack- rent as of January 11, 2008 and for all ing and contribute to a catastrophic later published repair data, the holder failure. Such structure may be part of of a type certificate must— the baseline structure or part of an al- (1) Review the repair data and iden- teration.
tify each repair specified in the data Implementation schedule consists of that affects fatigue critical baseline documentation that establishes the structure identified under paragraph timing for accomplishing the necessary (b)(1) of this section; actions for developing DT data for re- (2) Perform a DTE and develop the pairs and alterations, and for incor- DTI for each repair identified under porating those data into an operator’s paragraph (c)(1) of this section, unless continuing airworthiness maintenance previously accomplished; program. The documentation must (3) Submit the DT data to the respon- identify times when actions must be sible Aircraft Certification Service of- taken as specific numbers of airplane fice or its properly authorized des- flight hours, flight cycles, or both.
ignees for review and approval; and Published repair data mean instruc- tions for accomplishing repairs, which (4) Upon approval, make the DTI are published for general use in struc- available to persons required to comply Federal Aviation Administration, DOT § 26.43 with §§ 121.1109 and 129.109 of this chap- assistance available in accordance with ter. the implementation schedule.
(f) Compliance times. Holders of type (d) Future repair data not published.
certificates must submit the following For repair data developed by a holder to the responsible Aircraft Certifi- of a type certificate that are approved cation Service office or its properly au- after January 11, 2008 and are not pub- thorized designees for review and ap- lished, the type certificate holder must proval by the specified compliance accomplish the following for repairs time: specified in the repair data that affect (1) The identified list of fatigue crit- fatigue critical baseline structure: ical baseline structure required by (1) Perform a DTE and develop the paragraph (b)(2) of this section must be DTI.
submitted no later than 180 days after (2) Submit the DT data required in January 11, 2008 or before issuance of paragraph (d)(1) of this section for re- the type certificate, whichever occurs view and approval by the responsible later.
Aircraft Certification Service office or (2) For published repair data that are its properly authorized designees.
current as of January 11, 2008, the DT (3) Upon approval, make the approved data required by paragraph (c)(3) of DTI available to persons required to this section must be submitted by June comply with §§ 121.1109 and 129.109 of 30, 2009.
this chapter.
(3) For repair data published after (e) Repair evaluation guidelines. Ex- January 11, 2008, the DT data required cept for airplane models whose type by paragraph (c)(3) of this section must certificate is issued after January 11, be submitted before FAA approval of 2008, holders of a type certificate for the repair data.
each airplane model subject to this sec- (4) For unpublished repair data devel- tion must— oped after January 11, 2008, the DT (1) Develop repair evaluation guide- data required by paragraph (d)(1) of lines for operators’ use that include— this section must be submitted within (i) A process for conducting surveys 12 months of the airplane’s return to of affected airplanes that will enable service or in accordance with a sched- identification and documentation of all ule approved by the responsible Air- existing repairs that affect fatigue craft Certification Service office.
critical baseline structure identified (5) The repair evaluation guidelines under paragraph (b)(1) of this section required by paragraph (e)(1) of this sec- and § 26.45(b)(2); tion must be submitted by December (ii) A process that will enable opera- 30, 2009.
tors to obtain the DTI for repairs iden- (g) Exceptions. The requirements of tified under paragraph (e)(1)(i) of this this section do not apply to the fol- section; and lowing transport category airplane (iii) An implementation schedule for models: repairs covered by the repair evalua- (1) Convair CV–240, 340, 440, if modi- tion guidelines. The implementation fied to include turbine engines.
schedule must identify times when ac- (2) Vickers Armstrong Viscount, tions must be taken as specific num- TCDS No. A–814.
bers of airplane flight hours, flight cy- (3) Douglas DC–3, if modified to in- cles, or both.
clude turbine engines, TCDS No. A–618.
(2) Submit the repair evaluation (4) Bombardier CL–44, TCDS No.
guidelines to the responsible Aircraft 1A20.
Certification Service office for review (5) Mitsubishi YS–11, TCDS No.
and approval.
A1PC.
(3) Upon approval, make the guide- (6) British Aerospace BAC 1–11, TCDS lines available to persons required to No. A5EU.
comply with §§ 121.1109 and 129.109 of (7) Concorde, TCDS No. A45EU.
this chapter.
(8) deHavilland D.H. 106 Comet 4C, (4) If the guidelines direct the oper- TCDS No. 7A10.
ator to obtain assistance from the (9) deHavilland DHC–7, TCDS No.
holder of a type certificate, make such A20EA.
14 CFR Ch. I (1–1–25 Edition) § 26.45 (10) VFW-Vereinigte Flugtechnische ical baseline structure that is affected Werk VFW–614, TCDS No. A39EU. by the alteration; (11) Illyushin Aviation IL 96T, TCDS (2) Submit the DT data developed in No. A54NM.
accordance with paragraphs (c)(1) of (12) Bristol Aircraft Britannia 305, this section to the responsible Aircraft TCDS No. 7A2. Certification Service office or its prop- (13) Handley Page Herald Type 300, erly authorized designees for review TCDS No. A21N. and approval; and (14) Avions Marcel Dassault—Breguet (3) Upon approval, make the DTI Aviation Mercure 100C, TCDS No. available to persons required to comply A40EU. with §§ 121.1109 and 129.109 of this chap- (15) Airbus Caravelle, TCDS No. 7A6. ter.
(d) DT Data for Repairs Made to Alter- (16) Lockheed L–300, TCDS No. A2S0.
ations. For existing and future repair (17) Boeing 707–100/–200, TCDS No.
data developed by a holder of a type 4A21.
certificate, the type certificate holder (18) Boeing 707–300/–400, TCDS No.
must— 4A26.
(1) Review the repair data, and iden- (19) Boeing 720, TCDS No. 4A28.
tify each repair that affects any fa- [Doc. No. FAA–2005–21693, 72 FR 70505, Dec.
tigue critical alteration structure iden- 12, 2007, as amended by Amdt. 26–4, 75 FR tified under paragraph (b)(2) of this sec- 11734, Mar. 12, 2010; Doc. No. FAA–2018–0119, tion; Amdt. 26–7, 83 FR 9170, Mar. 5, 2018] (2) For each repair identified under § 26.45 Holders of type certificates—Al- paragraph (d)(1) of this section, unless terations and repairs to alterations.
previously accomplished, perform a DTE and develop DTI; (a) Applicability. This section applies (3) Submit the DT data developed in to transport category airplanes subject accordance with paragraph (d)(2) of to § 26.43.
this section to the responsible Aircraft (b) Fatigue critical alteration structure.
Certification Service office or its prop- For existing and future alteration data erly authorized designees for review developed by the holder of a type cer- and approval; and tificate, the holder must— (4) Upon approval, make the DTI (1) Review alteration data and iden- available to persons required to comply tify all alterations that affect fatigue with §§ 121.1109 and 129.109 of this chap- critical baseline structure identified ter.
under § 26.43(b)(1); (e) Compliance times. Holders of type (2) For each alteration identified certificates must submit the following under paragraph (b)(1) of this section, to the responsible Aircraft Certifi- identify any fatigue critical alteration cation Service office or its properly au- structure; thorized designees for review and ap- (3) Develop and submit to the respon- proval by the specified compliance sible Aircraft Certification Service of- time: fice for review and approval a list of (1) The list of fatigue critical alter- the structure identified under para- ation structure identified under para- graph (b)(2) of this section; and graph (b)(3) of this section must be sub- (4) Upon approval, make the list re- mitted— quired in paragraph (b)(3) of this sec- tion available to persons required to (i) No later than 360 days after Janu- comply with §§ 121.1109 and 129.109 of ary 11, 2008, for alteration data ap- this chapter. proved before January 11, 2008.
(ii) No later than 30 days after March (c) DT Data. For existing and future 12, 2010 or before initial approval of the alteration data developed by the holder alteration data, whichever occurs of a type certificate that affect fatigue later, for alteration data approved on critical baseline structure identified or after January 11, 2008.
under § 26.43(b)(1), unless previously ac- complished, the holder must— (2) For alteration data developed and (1) Perform a DTE and develop the approved before January 11, 2008, the DTI for the alteration and fatigue crit- DT data required by paragraph (c)(2) of Federal Aviation Administration, DOT § 26.47 this section must be submitted by June ture identified under § 26.43(b)(1), unless 30, 2009. previously accomplished, the holder of (3) For alteration data approved on a supplemental type certificate must— or after January 11, 2008, DT data re- (1) Perform a DTE and develop the quired by paragraph (c)(2) of this sec- DTI for the alteration and fatigue crit- tion must be submitted before initial ical baseline structure that is affected approval of the alteration data. by the alteration; (4) For repair data developed and ap- (2) Submit the DT data developed in proved before January 11, 2008, the DT accordance with paragraphs (c)(1) of data required by paragraph (d)(2) of this section to the responsible Aircraft this section must be submitted by June Certification Service office or its prop- 30, 2009. erly authorized designees for review (5) For repair data developed and ap- and approval; and proved after January 11, 2008, the DT (3) Upon approval, make the DTI data required by paragraph (d)(2) of available to persons required to comply this section must be submitted within with §§ 121.1109 and 129.109 of this chap- 12 months after initial approval of the ter.
repair data and before making the DT (d) DT Data for Repairs Made to Alter- data available to persons required to ations. For existing and future repair comply with §§ 121.1109 and 129.109 of data developed by the holder of a sup- this chapter. plemental holder of a supplemental type certificate, the holder of a supple- [Doc. No. FAA–2005–21693, 72 FR 70505, Dec.
mental type certificate must— 12, 2007, as amended by Amdt. 26–4, 75 FR (1) Review the repair data, and iden- 11734, Mar. 12, 2010; Doc. No. FAA–2018–0119, tify each repair that affects any fa- Amdt. 26–7, 83 FR 9170, Mar. 5, 2018] tigue critical alteration structure iden- § 26.47 Holders of and applicants for a tified under paragraph (b)(2) of this sec- supplemental type certificate—Al- tion; terations and repairs to alterations.
(2) For each repair identified under (a) Applicability. This section applies paragraph (d)(1) of this section, unless to transport category airplanes subject previously accomplished, perform a to § 26.43. DTE and develop DTI; (b) Fatigue critical alteration structure. (3) Submit the DT data developed in For existing structural alteration data accordance with paragraph (d)(2) of approved under a supplemental certifi- this section to the responsible Aircraft cate, the holder of the supplemental Certification Service office or its prop- certificate must— erly authorized designees for review (1) Review the alteration data and and approval; and identify all alterations that affect fa- (4) Upon approval, make the DTI tigue critical baseline structure identi- available to persons required to comply fied under § 26.43(b)(1); with §§ 121.1109 and 129.109 of this chap- (2) For each alteration identified ter.
under paragraph (b)(1) of this section, (e) Compliance times. Holders of sup- identify any fatigue critical alteration plemental type certificates must sub- structure; mit the following to the responsible (3) Develop and submit to the respon- Aircraft Certification Service office or sible Aircraft Certification Service of- its properly authorized designees for fice for review and approval a list of review and approval by the specified the structure identified under para- compliance time: graph (b)(2) of this section; and (1) The list of fatigue critical alter- (4) Upon approval, make the list re- ation structure required by paragraph quired in paragraph (b)(3) of this sec- (b)(3) of this section must be submitted tion available to persons required to no later than 360 days after January 11, comply with §§ 121.1109 and 129.109 of 2008.
this chapter. (2) For alteration data developed and (c) DT Data. For existing and future approved before January 11, 2008, the alteration data developed by the holder DT data required by paragraph (c)(2) of of a supplemental type certificate that this section must be submitted by June affect fatigue critical baseline struc- 30, 2009.
14 CFR Ch. I (1–1–25 Edition) § 26.49 (3) For alteration data developed (2) For holders of supplemental type after January 11, 2008, the DT data re- certificates no later than 180 days after quired by paragraph (c)(2) of this sec- January 11, 2008.
(3) For applicants for changes to type tion must be submitted before approval certificates whose application are sub- of the alteration data and making it mitted before January 11, 2008, no later available to persons required to comply than 180 days after January 11, 2008.
with §§ 121.1109 and 129.109 of this chap- (c) Compliance Plan Implementation.
ter.
Each affected person must implement (4) For repair data developed and ap- the compliance plan as approved in proved before January 11, 2008, the DT compliance with paragraph (a) of this data required by paragraph (d)(2) of section.
this section must be submitted by June 30, 2009. [Docket No. FAA–2005–21693, 72 FR 70505, Dec.
12, 2007, as amended by Doc. No. FAA–2018– (5) For repair data developed and ap- 0119, Amdt. 26–7, 83 FR 9170, Mar. 5, 2018] proved after January 11, 2008, the DT data required by paragraph (d)(2) of PART 27—AIRWORTHINESS STAND- this section, must be submitted within ARDS: NORMAL CATEGORY 12 months after initial approval of the repair data and before making the DT ROTORCRAFT data available to persons required to comply with §§ 121.1109 and 129.109 of Subpart A—General this chapter.
Sec.
27.1 Applicability.
[Docket No. FAA–2005–21693, 72 FR 70505, Dec.
27.2 Special retroactive requirements.
12, 2007, as amended by Doc. No. FAA–2018– 0119, Amdt. 26–7, 83 FR 9170, Mar. 5, 2018] Subpart B—Flight § 26.49 Compliance plan.
G ENERAL (a) Compliance plan. Except for appli- 27.21 Proof of compliance.
cants for type certificates and supple- 27.25 Weight limits.
27.27 Center of gravity limits.
mental type certificates whose applica- 27.29 Empty weight and corresponding cen- tions are submitted after January 11, ter of gravity.
2008, each person identified in §§ 26.43, 27.31 Removable ballast.
26.45, and 26.47, must submit a compli- 27.33 Main rotor speed and pitch limits.
ance plan consisting of the following: P ERFORMANCE (1) A project schedule identifying all major milestones for meeting the com- 27.45 General.
27.49 Performance at minimum operating pliance times specified in §§ 26.43(f), speed.
26.45(e), and 26.47(e), as applicable.
27.51 Takeoff.
(2) A proposed means of compliance 27.65 Climb: all engines operating.
with §§ 26.43, 26.45, and 26.47, as applica- 27.67 Climb: one engine inoperative.
ble.
27.71 Autorotation performance.
27.75 Landing.
(3) A plan for submitting a draft of 27.87 Height-velocity envelope.
all compliance items required by this subpart for review by the responsible FLIGHT C HARACTERISTICS Aircraft Certification Service office 27.141 General.
not less than 60 days before the appli- 27.143 Controllability and maneuverability.
cable compliance date.
27.151 Flight controls.
(b) Compliance dates for compliance 27.161 Trim control.
plans. The following persons must sub- 27.171 Stability: general.
27.173 Static longitudinal stability.
mit the compliance plan described in 27.175 Demonstration of static longitudinal paragraph (a) of this section to the re- stability.
sponsible Aircraft Certification Service 27.177 Static directional stability.
office for approval on the following schedule: G ROUND AND W ATER H ANDLING C HARACTERISTICS (1) For holders of type certificates, no later than 90 days after January 11, 27.231 General.
2008. 27.235 Taxiing condition.