Airworthiness Directives; Airbus Model A330-200, A330-300, A340-200, and A340-300 Series Airplanes; and A340-541 and A340-642 Airplanes, 69288-69291 [05-22588]

Download as PDF 69288 Federal Register / Vol. 70, No. 219 / Tuesday, November 15, 2005 / Proposed Rules We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. Comments Due Date (a) The FAA must receive comments on this AD action by December 15, 2005. List of Subjects in 14 CFR Part 39 Applicability (c) This AD applies to BAE Systems (Operations) Limited Model BAe 146–100A, –200A, and –300A series airplanes, certificated in any category, on which Modification HCM00301A or B has been done, and on which Modification HCM0169A has not been done. Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): BAE Systems (Operations) Limited (Formerly British Aerospace Regional Aircraft): Docket No. FAA–2005–22974; Directorate Identifier 2005–NM–180–AD. Affected ADs (b) None. Unsafe Condition (d) This AD results from a report of chafing along the seal/fuselage contact area under the wing-to-fuselage fairing access panels on both sides of the fuselage. We are issuing this AD to ensure the structural integrity of the fuselage. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspection (f) Before the airplane accumulates 1,000 total flight cycles, or within 500 flight cycles after the effective date of this AD, whichever occurs later: Inspect, using a dial test indicator, to measure the depth of any chafing or scoring in the skin along the full length of the fairing from forward to aft ends at the point of contact between the seal and fuselage on both sides of the fuselage. Do applicable related investigative/corrective actions in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Service Bulletins ISB.53–005, Revision 2, dated February 16, 2004, and ISB.53–067, Revision 3, dated June 27, 2005, except as required by paragraph (g) of this AD. Do related investigative/corrective actions and repeat the inspection to measure the chafing/scoring at the times specified in the service bulletins, as applicable. Exceptions to Service Bulletin Specifications (g) Where the service bulletins referenced in this AD specify to contact the manufacturer for repair instructions: Before further flight, repair using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the Civil Aviation Authority (or its delegated agent). (h) Although the service bulletins referenced in this AD specify to submit certain information to the manufacturer, this AD does not include that requirement. Credit for Earlier Accomplishment (i) Inspections and applicable investigative and corrective actions done before the effective date of this AD are acceptable for compliance with the requirements of paragraph (f) of this AD if done in accordance with one of the service bulletin versions identified in Table 1 of this AD, as applicable. TABLE 1.—CREDIT SERVICE BULLETINS BAE Systems (Operations) limited service bulletin Revision level ISB.53–005 ....................................................................... Original ............................................................................. Revision 1 ........................................................................ Original ............................................................................. Revision 1 ........................................................................ Revision 2 ........................................................................ ISB.53–067 ....................................................................... Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Issued in Renton, Washington, on November 7, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–22587 Filed 11–14–05; 8:45 am] BILLING CODE 4910–13–U Date August 15, 1984. April 19, 1984. December 23, 1987. February 16, 1990. February 16, 2004. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22973; Directorate Identifier 2004–NM–67–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330–200, A330–300, A340–200, and A340–300 Series Airplanes; and A340– 541 and A340–642 Airplanes Related Information Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: (k) British airworthiness directive G–2005– 0020, dated July 6, 2005, also addresses the subject of this AD. SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all Airbus Model A330–200, A330–300, VerDate Aug<31>2005 14:04 Nov 14, 2005 Jkt 208001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 E:\FR\FM\15NOP1.SGM 15NOP1 Federal Register / Vol. 70, No. 219 / Tuesday, November 15, 2005 / Proposed Rules A340–200, and A340–300 series airplanes; and A340–541 and A340–642 airplanes. This proposed AD would require operators to revise the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate new information. This information includes, for all affected airplanes, decreased life limit values for certain components; and for Model A330–200 and –300 series airplanes, new inspections, compliance times, and new repetitive intervals to detect fatigue cracking, accidental damage, or corrosion in certain structures. This proposed AD results from a revision to subsection 9–1 of the Airbus A330 and A340 Maintenance Planning Documents (MPD) for Life Limits/Monitored parts, and subsection 9–2 of the Airbus A330 MPD for Airworthiness Limitations Items. We are proposing this AD to ensure the continued structural integrity of these airplanes. DATES: We must receive comments on this proposed AD by December 15, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • By fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer International Branch, ANM–116, FAA, International Branch, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2797; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under VerDate Aug<31>2005 14:04 Nov 14, 2005 Jkt 208001 Include ‘‘Docket No. FAA– 2005–22973; Directorate Identifier 2004–NM–67–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments submitted by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of our docket Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You can review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit https:// dms.dot.gov. ADDRESSES. Examining the Docket You can examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. Discussion ´ ´ The Direction Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, notified us that an unsafe condition may exist on all Airbus Model A330–200, A330–300, A340–200, and A340–300 series airplanes; and A340–541 and A340–642 airplanes. The DGAC advises that Airbus A300 Maintenance Planning Document (MPD) subsection 9–2, ‘‘Airworthiness Limitations Items,’’ has been revised to reference Issue 12, dated November 1, 2003, of the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness. Issue 12 results from the completion of fatigue and damage tolerance evaluations and introduces, for Model A330 series airplanes, new inspections, compliance times, and repetitive intervals to detect fatigue cracking, accidental damage, or PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 69289 corrosion in certain structures of the airplane. The DGAC also advises that the list of life limited/monitored parts given in Section 9–1 of the Airbus A330 and A340 MPDs has been revised. The revision provides mandatory replacement times approved under section 25.571 of the Joint Aviation Requirements and the Federal Aviation Regulations (14 CFR 25.571), and applies to all Airbus Model A330–200, A330–300, A340–200, and A340–300 series airplanes; and A340–541 and A340–642 airplanes. The DGAC advises that certain life limits must be imposed for various components on these airplanes to prevent the onset of fatigue cracking, and that the limits for certain components have decreased in these new revisions. Incorporating these revisions into the Airworthiness Limitations section of the Instructions for Continued Airworthiness is intended to ensure the continued structural integrity of these airplanes. Relevant Service Information Airbus has issued Document AI/SE– M4/95A.0089/97, ‘‘A330 Airworthiness Limitation Items’’ (ALI), Issue 12, dated November 1, 2003, of the Airbus A330 MPD, Section 9–2. The ALI document contains items related to evaluations of fatigue and damage tolerance arising from fatigue-critical and flight-cycle accidental damage, and a requirement to control corrosion. Issue 12 specifies new inspections, compliance times, and repetitive intervals to detect fatigue cracking, accidental damage, or corrosion in certain structures. Airbus has also issued Section 9–1, ‘‘Life Limits/Monitored Parts,’’ Revision 05, dated April 7, 2005, of the Airbus A330 and A340 MPDs. The MPDs include the airworthiness limits for Airbus Model A330–200, A330–300, A340–200, and A340–300 series airplanes; and A340–541 and A340–642 airplanes. Revision 05 increases the life limits of certain components of the MLG and nose landing gear (NLG) for Model A340–541 and A340–642 airplanes, and decreases the existing life limits for other MLG and NLG components for other Airbus Model A330–200, A330– 300, A340–200, and A340–300 series airplanes. Accomplishing the actions specified in these documents is intended to adequately address the unsafe condition. The DGAC mandated these documents and issued French airworthiness directives F–2004–024, dated February 18, 2004; F–2005–069, dated April 27, 2005; and F–2005–070, dated April 27, 2005; to ensure the E:\FR\FM\15NOP1.SGM 15NOP1 69290 Federal Register / Vol. 70, No. 219 / Tuesday, November 15, 2005 / Proposed Rules continued airworthiness of these airplanes in France. Explanation of Action Taken by the FAA In accordance with airworthiness standards requiring ‘‘damage tolerance assessments’’ for transport category airplanes (section 25.1529 of the Federal Aviation Regulations (14 CFR 25.1529), and the Appendices referenced in that section), all products certificated to comply with that section must have Instructions for Continued Airworthiness (or, for some products, maintenance manuals) that include an ALS. That section must set forth: • Mandatory replacement times for structural components, • Structural inspection intervals, and • Related approved structural inspection procedures necessary to show compliance with the damagetolerance requirements. Compliance with the terms specified in the ALS is required by sections 43.16 (for persons maintaining products) and 91.403 (for operators) of the Federal Aviation Regulations (14 CFR 43.16 and 91.403). In order to require compliance with these inspection intervals and life limits, we must engage in rulemaking, namely the issuance of an AD. For products certificated to comply with the referenced part 25 requirements, it is within our authority to issue an AD requiring a revision to the ALS that includes reduced life limits, or new or different structural inspection requirements. These revisions then are mandatory for operators under section 91.403(c) of the Federal Aviation Regulations (14 CFR 91.403), which prohibits operation of an airplane for which airworthiness limitations have been issued unless the inspection intervals specified in those limitations have been complied with. After that document is revised, as required, and the AD has been fully complied with, the life limit or structural inspection change remains enforceable as a part of the airworthiness limitations. (This is analogous to ADs that require changes to the Limitations Section of the Airplane Flight Manual.) Requiring a revision of the airworthiness limitations, rather than requiring individual inspections, is advantageous for operators because it allows them to record AD compliance status only once—at the time they make the revision—rather than after every inspection. It also has the advantage of keeping all airworthiness limitations, whether imposed by original certification or by AD, in one place within the operator’s maintenance program, thereby reducing the risk of non-compliance because of oversight or confusion. FAA’s Determination and Requirements of the Proposed AD These airplane models are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. We have examined the DGAC’s findings, evaluated all pertinent information, and determined that we need to issue an AD for products of this type design that are certificated for operation in the United States. Therefore, we are proposing this AD, which would require operators to revise the ALS of the Instructions for Continued Airworthiness to incorporate new inspections, compliance times, and repetitive intervals to detect fatigue cracking, accidental damage, or corrosion in certain structures. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this proposed AD. ESTIMATED COSTS Action Work hours Revise the ALS ......................... Average labor rate per hour 1 $65 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on VerDate Aug<31>2005 14:04 Nov 14, 2005 Jkt 208001 Cost per airplane Parts None ......................................... products identified in this rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Number of U.S.-registered airplanes $65 Fleet cost 20 $1,300 under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: E:\FR\FM\15NOP1.SGM 15NOP1 Federal Register / Vol. 70, No. 219 / Tuesday, November 15, 2005 / Proposed Rules Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2005–22973; Directorate Identifier 2004–NM–67–AD. Comments Due Date (a) The Federal Aviation Administration must receive comments on this AD action by December 15, 2005. Affected ADs (b) None. Applicability (c) This AD applies to all Airbus Model A330–201, –202, –203, –223, and –243 airplanes; A330–301, –321, –322, –323, –341, –342, –343 airplanes; A340–211, –212, and –213 airplanes; A340–311, –312, and –313 airplanes; A340–541 airplanes; and A340– 642 airplanes; certificated in any category. Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (h) of this AD. The request should include a description of changes to the required inspections that will ensure the continued damage tolerance of the affected structure. The FAA has provided guidance for this determination in Advisory Circular (AC) 25–1529. Unsafe Condition (d) This AD results from a revision to subsection 9–1 of the Airbus A330 and A340 Maintenance Planning Documents (MPD) for Life Limits/Monitored parts, and subsection 9–2 of the Airbus A330 MPD for Airworthiness Limitations Items. We are issuing this AD to ensure the continued structural integrity of these airplanes. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (i) French airworthiness directives F– 2004–024, dated February 18, 2004; F–2005– 069, dated April 27, 2005; and F–2005–070, dated April 27, 2005; also address the subject of this AD. Issued in Renton, Washington, on November 7, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–22588 Filed 11–14–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22873; Directorate Identifier 2005–NM–197–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier Model CL–600–2B19 (Regional Jet Series 100 & 440) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Airworthiness Limitations Revision (f) Within 3 months after the effective date of this AD, revise the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness by incorporating into the ALS the documents in paragraph (f)(1) and (f)(2) of this AD, as applicable. (1) Document AI/SE–M4/95A.0089/97, ‘‘Airworthiness Limitations Items,’’ Issue 12, dated November 1, 2003, Section 9–2 of the Airbus A330 Maintenance Planning Document (MPD). VerDate Aug<31>2005 (2) Section 9–1, ‘‘Life Limits/Monitored parts,’’ Revision 05, dated April 7, 2005, of the Airbus A330 and A340 MPDs. (g) Except as provided by paragraph (h) of this AD: After the actions in paragraph (f) of this AD have been accomplished, no alternative inspections or inspection intervals may be approved for the structural elements specified in the documents listed in paragraph (f) of this AD. 14:04 Nov 14, 2005 Jkt 208001 SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Bombardier Model CL–600– 2B19 (Regional Jet Series 100 & 440) airplanes. This proposed AD would require replacing the Camloc fasteners on the sidewall of the center pedestal. This proposed AD results from reports of the Camloc fasteners on the sidewall of the center pedestal disengaging and interfering with an inboard rudder pedal. We are proposing this AD to PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 69291 prevent these fasteners from disengaging and interfering with an inboard rudder pedal, which could reduce directional controllability of the airplane. DATES: We must receive comments on this proposed AD by December 15, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Daniel Parrillo, Aerospace Engineer, Systems and Flight Test Branch, ANE– 172, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New York 11590; telephone (516) 228–7305; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2005–22873; Directorate Identifier 2005–NM–197–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web E:\FR\FM\15NOP1.SGM 15NOP1

Agencies

[Federal Register Volume 70, Number 219 (Tuesday, November 15, 2005)]
[Proposed Rules]
[Pages 69288-69291]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-22588]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22973; Directorate Identifier 2004-NM-67-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-200, A330-300, A340-
200, and A340-300 Series Airplanes; and A340-541 and A340-642 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for all Airbus Model A330-200, A330-300,

[[Page 69289]]

A340-200, and A340-300 series airplanes; and A340-541 and A340-642 
airplanes. This proposed AD would require operators to revise the 
Airworthiness Limitations section of the Instructions for Continued 
Airworthiness to incorporate new information. This information 
includes, for all affected airplanes, decreased life limit values for 
certain components; and for Model A330-200 and -300 series airplanes, 
new inspections, compliance times, and new repetitive intervals to 
detect fatigue cracking, accidental damage, or corrosion in certain 
structures. This proposed AD results from a revision to subsection 9-1 
of the Airbus A330 and A340 Maintenance Planning Documents (MPD) for 
Life Limits/Monitored parts, and subsection 9-2 of the Airbus A330 MPD 
for Airworthiness Limitations Items. We are proposing this AD to ensure 
the continued structural integrity of these airplanes.

DATES: We must receive comments on this proposed AD by December 15, 
2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     By fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer 
International Branch, ANM-116, FAA, International Branch, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (425) 227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-22973; 
Directorate Identifier 2004-NM-67-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments submitted by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of our 
docket Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You can review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit https://dms.dot.gov.

Examining the Docket

    You can examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the DMS receives them.

Discussion

    The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France, notified us that an 
unsafe condition may exist on all Airbus Model A330-200, A330-300, 
A340-200, and A340-300 series airplanes; and A340-541 and A340-642 
airplanes.
    The DGAC advises that Airbus A300 Maintenance Planning Document 
(MPD) subsection 9-2, ``Airworthiness Limitations Items,'' has been 
revised to reference Issue 12, dated November 1, 2003, of the 
Airworthiness Limitations section (ALS) of the Instructions for 
Continued Airworthiness. Issue 12 results from the completion of 
fatigue and damage tolerance evaluations and introduces, for Model A330 
series airplanes, new inspections, compliance times, and repetitive 
intervals to detect fatigue cracking, accidental damage, or corrosion 
in certain structures of the airplane.
    The DGAC also advises that the list of life limited/monitored parts 
given in Section 9-1 of the Airbus A330 and A340 MPDs has been revised. 
The revision provides mandatory replacement times approved under 
section 25.571 of the Joint Aviation Requirements and the Federal 
Aviation Regulations (14 CFR 25.571), and applies to all Airbus Model 
A330-200, A330-300, A340-200, and A340-300 series airplanes; and A340-
541 and A340-642 airplanes. The DGAC advises that certain life limits 
must be imposed for various components on these airplanes to prevent 
the onset of fatigue cracking, and that the limits for certain 
components have decreased in these new revisions.
    Incorporating these revisions into the Airworthiness Limitations 
section of the Instructions for Continued Airworthiness is intended to 
ensure the continued structural integrity of these airplanes.

Relevant Service Information

    Airbus has issued Document AI/SE-M4/95A.0089/97, ``A330 
Airworthiness Limitation Items'' (ALI), Issue 12, dated November 1, 
2003, of the Airbus A330 MPD, Section 9-2. The ALI document contains 
items related to evaluations of fatigue and damage tolerance arising 
from fatigue-critical and flight-cycle accidental damage, and a 
requirement to control corrosion. Issue 12 specifies new inspections, 
compliance times, and repetitive intervals to detect fatigue cracking, 
accidental damage, or corrosion in certain structures.
    Airbus has also issued Section 9-1, ``Life Limits/Monitored 
Parts,'' Revision 05, dated April 7, 2005, of the Airbus A330 and A340 
MPDs. The MPDs include the airworthiness limits for Airbus Model A330-
200, A330-300, A340-200, and A340-300 series airplanes; and A340-541 
and A340-642 airplanes. Revision 05 increases the life limits of 
certain components of the MLG and nose landing gear (NLG) for Model 
A340-541 and A340-642 airplanes, and decreases the existing life limits 
for other MLG and NLG components for other Airbus Model A330-200, A330-
300, A340-200, and A340-300 series airplanes.
    Accomplishing the actions specified in these documents is intended 
to adequately address the unsafe condition. The DGAC mandated these 
documents and issued French airworthiness directives F-2004-024, dated 
February 18, 2004; F-2005-069, dated April 27, 2005; and F-2005-070, 
dated April 27, 2005; to ensure the

[[Page 69290]]

continued airworthiness of these airplanes in France.

Explanation of Action Taken by the FAA

    In accordance with airworthiness standards requiring ``damage 
tolerance assessments'' for transport category airplanes (section 
25.1529 of the Federal Aviation Regulations (14 CFR 25.1529), and the 
Appendices referenced in that section), all products certificated to 
comply with that section must have Instructions for Continued 
Airworthiness (or, for some products, maintenance manuals) that include 
an ALS. That section must set forth:
     Mandatory replacement times for structural components,
     Structural inspection intervals, and
     Related approved structural inspection procedures 
necessary to show compliance with the damage-tolerance requirements.
    Compliance with the terms specified in the ALS is required by 
sections 43.16 (for persons maintaining products) and 91.403 (for 
operators) of the Federal Aviation Regulations (14 CFR 43.16 and 
91.403).
    In order to require compliance with these inspection intervals and 
life limits, we must engage in rulemaking, namely the issuance of an 
AD. For products certificated to comply with the referenced part 25 
requirements, it is within our authority to issue an AD requiring a 
revision to the ALS that includes reduced life limits, or new or 
different structural inspection requirements. These revisions then are 
mandatory for operators under section 91.403(c) of the Federal Aviation 
Regulations (14 CFR 91.403), which prohibits operation of an airplane 
for which airworthiness limitations have been issued unless the 
inspection intervals specified in those limitations have been complied 
with.
    After that document is revised, as required, and the AD has been 
fully complied with, the life limit or structural inspection change 
remains enforceable as a part of the airworthiness limitations. (This 
is analogous to ADs that require changes to the Limitations Section of 
the Airplane Flight Manual.)
    Requiring a revision of the airworthiness limitations, rather than 
requiring individual inspections, is advantageous for operators because 
it allows them to record AD compliance status only once--at the time 
they make the revision--rather than after every inspection. It also has 
the advantage of keeping all airworthiness limitations, whether imposed 
by original certification or by AD, in one place within the operator's 
maintenance program, thereby reducing the risk of non-compliance 
because of oversight or confusion.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that we need to 
issue an AD for products of this type design that are certificated for 
operation in the United States.
    Therefore, we are proposing this AD, which would require operators 
to revise the ALS of the Instructions for Continued Airworthiness to 
incorporate new inspections, compliance times, and repetitive intervals 
to detect fatigue cracking, accidental damage, or corrosion in certain 
structures.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                          Number of U.S.-
                    Action                       Work    Average labor                Parts                  Cost per       registered      Fleet cost
                                                hours    rate per hour                                       airplane        airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Revise the ALS...............................        1             $65  None............................             $65              20          $1,300
--------------------------------------------------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:


[[Page 69291]]


    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

Airbus: Docket No. FAA-2005-22973; Directorate Identifier 2004-NM-
67-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this AD action by December 15, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Airbus Model A330-201, -202, -203, -
223, and -243 airplanes; A330-301, -321, -322, -323, -341, -342, -
343 airplanes; A340-211, -212, and -213 airplanes; A340-311, -312, 
and -313 airplanes; A340-541 airplanes; and A340-642 airplanes; 
certificated in any category.

    Note 1: This AD requires revisions to certain operator 
maintenance documents to include new inspections. Compliance with 
these inspections is required by 14 CFR 91.403(c). For airplanes 
that have been previously modified, altered, or repaired in the 
areas addressed by these inspections, the operator may not be able 
to accomplish the inspections described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must 
request approval for an alternative method of compliance according 
to paragraph (h) of this AD. The request should include a 
description of changes to the required inspections that will ensure 
the continued damage tolerance of the affected structure. The FAA 
has provided guidance for this determination in Advisory Circular 
(AC) 25-1529.

Unsafe Condition

    (d) This AD results from a revision to subsection 9-1 of the 
Airbus A330 and A340 Maintenance Planning Documents (MPD) for Life 
Limits/Monitored parts, and subsection 9-2 of the Airbus A330 MPD 
for Airworthiness Limitations Items. We are issuing this AD to 
ensure the continued structural integrity of these airplanes.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Airworthiness Limitations Revision

    (f) Within 3 months after the effective date of this AD, revise 
the Airworthiness Limitations section (ALS) of the Instructions for 
Continued Airworthiness by incorporating into the ALS the documents 
in paragraph (f)(1) and (f)(2) of this AD, as applicable.
    (1) Document AI/SE-M4/95A.0089/97, ``Airworthiness Limitations 
Items,'' Issue 12, dated November 1, 2003, Section 9-2 of the Airbus 
A330 Maintenance Planning Document (MPD).
    (2) Section 9-1, ``Life Limits/Monitored parts,'' Revision 05, 
dated April 7, 2005, of the Airbus A330 and A340 MPDs.
    (g) Except as provided by paragraph (h) of this AD: After the 
actions in paragraph (f) of this AD have been accomplished, no 
alternative inspections or inspection intervals may be approved for 
the structural elements specified in the documents listed in 
paragraph (f) of this AD.

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (i) French airworthiness directives F-2004-024, dated February 
18, 2004; F-2005-069, dated April 27, 2005; and F-2005-070, dated 
April 27, 2005; also address the subject of this AD.

    Issued in Renton, Washington, on November 7, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-22588 Filed 11-14-05; 8:45 am]
BILLING CODE 4910-13-P
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