FAA 14 CFR PART 26-2011 Continued airworthiness and safety improvements for transport category airplanes《运输分类飞机的持续适航性和安全改进》.pdf

1、616 14 CFR Ch. I (1111 Edition) Pt. 26 TABLE 2.FLIGHT LENGTH DISTRIBUTIONContinued Flight length (NM) Airplane maximum rangenautical miles (NM) From To 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 9200 9400 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.2 9400 9600 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0

2、.1 9600 9800 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.1 9800 10000 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.1 (c) Overnight Temperature Drop. For air-planes on which FRM is installed, the over-night temperature drop for this appendix is defined using: (1) A temperature at the beginning of the overnight pe

3、riod that equals the landing temperature of the previous flight that is a random value based on a Gaussian distribu-tion; and (2) An overnight temperature drop that is a random value based on a Gaussian distribu-tion. (3) For any flight that will end with an overnight ground period (one flight per d

4、ay out of an average number of flights per day, depending on utilization of the particular airplane model being evaluated), the landing outside air temperature (OAT) is to be cho-sen as a random value from the following Gaussian curve: TABLE 3.LANDING OUTSIDE AIR TEMPERATURE Parameter Landing outsid

5、e air temperature F Mean Temperature 58.68 negative 1 std dev . 20.55 positive 1 std dev 13.21 (4) The outside ambient air temperature (OAT) overnight temperature drop is to be chosen as a random value from the following Gaussian curve: TABLE 4.OUTSIDE AIR TEMPERATURE (OAT) DROP Parameter OAT drop t

6、emperature F Mean Temp . 12.0 1 std dev 6.0 (d) Number of Simulated Flights Required in Analysis. In order for the Monte Carlo analysis to be valid for showing compliance with the fleet average and warm day flam-mability exposure requirements, the appli-cant must run the analysis for a minimum numbe

7、r of flights to ensure that the fleet av-erage and warm day flammability exposure for the fuel tank under evaluation meets the applicable flammability limits defined in Table 5 of this appendix. TABLE 5.FLAMMABILITY EXPOSURE LIMIT Minimum number of flights in Monte Carlo analysis Maximum acceptable

8、Monte Carlo average fuel tank flammability exposure (percent) to meet 3 percent requirements Maximum acceptable Monte Carlo average fuel tank flammability exposure (percent) to meet 7 percent part 26 requirements 10,000 2.91 6.79 100,000 2.98 6.96 1,000,000 . 3.00 7.00 Doc. No. FAA200522997, 73 FR 4

9、2495, July 21, 2008 PART 26CONTINUED AIRWORTHI-NESS AND SAFETY IMPROVE-MENTS FOR TRANSPORT CAT-EGORY AIRPLANES Subpart AGeneral Sec. 26.1 Purpose and scope. 26.3 Definitions. 26.5 Applicability table. Subpart BEnhanced Airworthiness Program for Airplane Systems Sec. 26.11 Electrical wiring interconn

10、ection sys-tems (EWIS) maintenance program. Subpart CAging Airplane Safety Widespread Fatigue Damage 26.21 Limit of validity. 26.23 Extended limit of validity. Subpart DFuel Tank Flammability 26.31 Definitions. 26.33 Holders of type certificates: Fuel tank flammability. 26.35 Changes to type certifi

11、cates affecting fuel tank flammability. 26.37 Pending type certification projects: Fuel tank flammability. VerDate Mar2010 14:10 Mar 01, 2011 Jkt 223043 PO 00000 Frm 00626 Fmt 8010 Sfmt 8010 Y:SGML223043.XXX 223043wwoods2 on DSK1DXX6B1PROD with CFRProvided by IHSNot for ResaleNo reproduction or netw

12、orking permitted without license from IHS-,-,-617 Federal Aviation Administration, DOT 26.5 26.39 Newly produced airplanes: Fuel tank flammability. Subpart EAging Airplane SafetyDam-age Tolerance Data for Repairs and Alterations 26.41 Definitions. 26.43 Holders of and applicants for type cer-tificat

13、esRepairs. 26.45 Holders of type certificatesAlter-ations and repairs to alterations. 26.47 Holders of and applicants for a supple-mental type certificateAlterations and repairs to alterations. 26.49 Compliance plan. AUTHORITY: 49 U.S.C. 106(g), 40113, 44701, 44702 and 44704. SOURCE: Docket No. FAA2

14、00418379, 72 FR 63409, Nov. 8, 2007, unless otherwise noted. Subpart AGeneral 26.1 Purpose and scope. (a) This part establishes require-ments for support of the continued air-worthiness of and safety improvements for transport category airplanes. These requirements may include performing assessments

15、, developing design changes, developing revisions to In-structions for Continued Airworthiness (ICA), and making necessary docu-mentation available to affected per-sons. Requirements of this part that establish standards for design changes and revisions to the ICA are considered airworthiness requir

16、ements. (b) Except as provided in paragraph (c) of this section, this part applies to the following persons, as specified in each subpart of this part: (1) Holders of type certificates and supplemental type certificates. (2) Applicants for type certificates and supplemental type certificates and cha

17、nges to those certificates (including service bulletins describing design changes). (3) Persons seeking design approval for airplane repairs, alterations, or modifications that may affect air-worthiness. (4) Holders of type certificates and their licensees producing new air-planes. (c) An applicant

18、for approval of a de-sign change is not required to comply with any applicable airworthiness re-quirement of this part if the applicant elects or is required to comply with a corresponding amendment to part 25 of this chapter that is adopted concur-rently or after that airworthiness re-quirement. (d

19、) For the purposes of this part, the word type certificate does not include supplemental type certificates. 26.3 Definitions. For the purposes of this part: FAA Oversight Office is the aircraft certification office or office of the Transport Airplane Directorate with oversight responsibility for the

20、 rel-evant type certificate, supplemental type certificate, or manufacturer, as determined by the Administrator. 26.5 Applicability table. Table 1 of this section provides an overview of the applicability of this part. It provides guidance in identi-fying what sections apply to various types of enti

21、ties. The specific applica-bility of each subpart and section is specified in the regulatory text. TABLE 1APPLICABILITY OF PART 26 RULES Applicable sections Subpart B Subpart D Subpart E EAPAS/FTS Fuel tank flammability Damage tolerance data Effective date of rule December 10, 2007 December 26, 2008

22、 January 11, 2008 Existing1TC Holders 26.11 26.33 26.43, 26.45, 26.49 Pending1TC Applicants . 26.11 26.37 26.43, 26.45 Existing1STC Holders N/A 26.35 26.47, 26.49 Pending1STC/ATC Applicants . 26.11 26.35 26.45, 26.47, 26.49 Future2STC/ATC Applicants 26.11 26.35 26.45, 26.47, 26.49 Manufacturers N/A

23、26.39 N/A 1As of the effective date of the identified rule. 2Application made after the effective date of the identified rule. VerDate Mar2010 14:10 Mar 01, 2011 Jkt 223043 PO 00000 Frm 00627 Fmt 8010 Sfmt 8010 Y:SGML223043.XXX 223043wwoods2 on DSK1DXX6B1PROD with CFRProvided by IHSNot for ResaleNo

24、reproduction or networking permitted without license from IHS-,-,-618 14 CFR Ch. I (1111 Edition) 26.5 Doc. No. FAA200522997, 74 FR 31618, July 2, 2009 EFFECTIVE DATE NOTE: By Doc. No. FAA- 2006-24282, Nov. 15, 2010, 26.5 was revised, ef-fective Jan. 14, 2011. For the convenience of the user, the re

25、vised text is set forth as fol-lows: 26.5 Applicability table. Table 1 of this section provides an over-view of the applicability of this part. It pro-vides guidance in identifying what sections apply to various types of entities. The spe-cific applicability of each subpart and sec-tion is specified

26、 in the regulatory text. VerDate Mar2010 14:10 Mar 01, 2011 Jkt 223043 PO 00000 Frm 00628 Fmt 8010 Sfmt 8003 Y:SGML223043.XXX 223043wwoods2 on DSK1DXX6B1PROD with CFRProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-619 Federal Aviation Administration,

27、 DOT 26.5 TABLE1APPLICABILITYOFPART26 RULESApplicable sections Subpart B EAPAS/FTS Subpart C widespread fatigue damage Subpart D fuel tank flammability Subpart E damage tolerance data Effective date of ruleDecember 10, 2007January 14, 2011December 26, 2008January 11, 2008 Existing1TC Holders.26.11.2

28、6.21.26.33.26.43, 26.45, 26.49 Pending1TC Applicants26.11.26.21.26.37.26.43, 26.45 Future2TC applicants.N/AN/A.N/A26.43 Existing1STC Holders.N/A26.21.26.35.26.47, 26.49 Pending1STC/ATC applicants26.11.26.21.26.35.26.45, 26.47, 26.49 Future2STC/ATC applicants.26.11.26.21.26.35.26.45, 26.47, 26.49 Man

29、ufacturersN/AN/A26.39.N/A 1As of the effective date of the identified rule. 2Application made after the effective date of the identified rule. VerDate Mar2010 14:10 Mar 01, 2011 Jkt 223043 PO 00000 Frm 00629 Fmt 8010 Sfmt 8003 Y:SGML223043.XXX 223043wwoods2 on DSK1DXX6B1PROD with CFRProvided by IHSN

30、ot for ResaleNo reproduction or networking permitted without license from IHS-,-,-620 14 CFR Ch. I (1111 Edition) 26.11 Subpart BEnhanced Airworthi-ness Program for Airplane Systems 26.11 Electrical wiring interconnec-tion systems (EWIS) maintenance program. (a) Except as provided in paragraph (g) o

31、f this section, this section applies to transport category, turbine-powered airplanes with a type certificate issued after January 1, 1958, that, as a result of the original certification, or later increase in capacity, have (1) A maximum type-certificated pas-senger capacity of 30 or more or (2) A

32、maximum payload capacity of 7,500 pounds or more. (b) Holders of, and applicants for, type certificates, as identified in para-graph (d) of this section must develop Instructions for Continued Airworthi-ness (ICA) for the representative air-planes EWIS in accordance with part 25, Appendix H paragrap

33、hs H25.5(a)(1) and (b) of this subchapter in effect on December 10, 2007 for each affected type design, and submit those ICA for re-view and approval by the FAA Over-sight Office. For purposes of this sec-tion, the representative airplane is the configuration of each model series airplane that incor

34、porates all vari-ations of EWIS used in production on that series airplane, and all TC-holder- designed modifications mandated by airworthiness directive as of the effec-tive date of this rule. Each person spec-ified in paragraph (d) of this section must also review any fuel tank system ICA develope

35、d by that person to com-ply with SFAR 88 to ensure compat-ibility with the EWIS ICA, including minimizing redundant requirements. (c) Applicants for amendments to type certificates and supplemental type certificates, as identified in para-graph (d) of this section, must: (1) Evaluate whether the des

36、ign change for which approval is sought ne-cessitates a revision to the ICA re-quired by paragraph (b) of this section to comply with the requirements of Ap-pendix H, paragraphs H25.5(a)(1) and (b). If so, the applicant must develop and submit the necessary revisions for review and approval by the F

37、AA Over-sight Office. (2) Ensure that any revised EWIS ICA remain compatible with any fuel tank system ICA previously developed to comply with SFAR 88 and any redun-dant requirements between them are minimized. (d) The following persons must com-ply with the requirements of paragraph (b) or (c) of t

38、his section, as applicable, before the dates specified. (1) Holders of type certificates (TC): December 10, 2009. (2) Applicants for TCs, and amend-ments to TCs (including service bul-letins describing design changes), if the date of application was before Decem-ber 10, 2007 and the certificate was

39、issued on or after December 10, 2007: December 10, 2009 or the date the cer-tificate is issued, whichever occurs later. (3) Unless compliance with 25.1729 of this subchapter is required or elected, applicants for amendments to TCs, if the application was filed on or after December 10, 2007: December

40、 10, 2009, or the date of approval of the certificate, whichever occurs later. (4) Applicants for supplemental type certificates (STC), including changes to existing STCs, if the date of applica-tion was before December 10, 2007 and the certificate was issued on or after December 10, 2007: June 7, 2

41、010, or the date of approval of the certificate, whichever occurs later. (5) Unless compliance with 25.1729 of this subchapter is required or elected, applicants for STCs, including changes to existing STCs, if the application was filed on or after December 10, 2007, June 7, 2010, or the date of app

42、roval of the certificate, whichever occurs later. (e) Each person identified in para-graphs (d)(1), (d)(2), and (d)(4) of this section must submit to the FAA Over-sight Office for approval a compliance plan by March 10, 2008. The compliance plan must include the following infor-mation: (1) A propose

43、d project schedule, iden-tifying all major milestones, for meet-ing the compliance dates specified in paragraph (d) of this section. (2) A proposed means of compliance with this section, identifying all re-quired submissions, including all com-pliance items as mandated in part 25, Appendix H paragra

44、phs H25.5(a)(1) and VerDate Mar2010 14:10 Mar 01, 2011 Jkt 223043 PO 00000 Frm 00630 Fmt 8010 Sfmt 8010 Y:SGML223043.XXX 223043wwoods2 on DSK1DXX6B1PROD with CFRProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-621 Federal Aviation Administration, DOT

45、26.21 (b) of this subchapter in effect on De-cember 10, 2007, and all data to be de-veloped to substantiate compliance. (3) A proposal for submitting a draft of all compliance items required by paragraph (e)(2) of this section for re-view by the FAA Oversight Office not less than 60 days before the

46、compliance time specified in paragraph (d) of this section. (4) A proposal for how the approved ICA will be made available to affected persons. (f) Each person specified in paragraph (e) must implement the compliance plan, or later approved revisions, as ap-proved in compliance with paragraph (e) of

47、 this section. (g) This section does not apply to the following airplane models: (1) Lockheed L188 (2) Bombardier CL44 (3) Mitsubishi YS11 (4) British Aerospace BAC 111 (5) Concorde (6) deHavilland D.H. 106 Comet 4C (7) VFWVereinigte Flugtechnische Werk VFW614 (8) Illyushin Aviation IL 96T (9) Brist

48、ol Aircraft Britannia 305 (10) Handley Page Herald Type 300 (11) Avions Marcel DassaultBreguet Aviation Mercure 100C (12) Airbus Caravelle (13) Lockheed L300 Amdt. 260, 72 FR 63409, Nov. 8, 2007; 72 FR 68618, Dec. 5, 2007 Subpart CAging Airplane Safe-tyWidespread Fatigue Dam-age SOURCE: 75 FR 69782,

49、 Nov. 15, 2010, unless otherwise noted. EFFECTIVE DATE NOTE: At 75 FR 69782, Nov. 15, 2010, subpart C was added, effective Jan. 14, 2011. 26.21 Limit of validity. (a) Applicability. Except as provided in paragraph (g) of this section, this section applies to transport category, turbine-powered airplanes with a max-imum takeoff gross weight greater than 7