Airworthiness Directives; Airbus Model A300 Airplanes, 55118-55121 [E9-25772]

Download as PDF 55118 Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations the operator must request approval for an alternative method of compliance according to paragraph (o) of this AD. The request should include a description of changes to the required inspections that will ensure the continued operational safety of the airplane. Subject (d) Air Transport Association (ATA) of America Code 28: Fuel. Unsafe Condition (e) This AD results from fuel system reviews conducted by the manufacturer. The Federal Aviation Administration is issuing this AD to reduce the potential of ignition sources inside fuel tanks, which in combination with flammable fuel vapors, could result in fuel tank fire or explosions and consequent loss of the airplane. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless already done. Revision to the Airworthiness Limitations Section To Incorporate Inspections (g) Within 30 days after the effective date of this AD, revise the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate the inspections specified in Section 2.2.3 of the Goodrich A300–600 Instructions for Continued Airworthiness, Document T3012– 0005–0101, Revision B, dated June 12, 2008. pwalker on DSK8KYBLC1PROD with RULES Inspection for Correct Separation (h) Within 6 months after the effective date of this AD, do a general visual inspection for tank unit separation and compensator separation of the center, inner, and outer fuel tanks, and trim fuel tanks of the tank units, in accordance with Section 2.2.3 of the Goodrich A300–600 Instructions for Continued Airworthiness, Document T3012– 0005–0101, Revision B, dated June 12, 2008. If incorrect separation is found, before further flight, correct the separation in accordance with the Airplane Maintenance Manual for the corresponding inspection specified in Section 2.2.3 of the Goodrich A300–600 Instructions for Continued Airworthiness, Document T3012–0005–0101, Revision B, dated June 12, 2008. A review of airplane maintenance records is acceptable in lieu of this inspection if the requirement of Table 6 in Section 10.1 of the Goodrich A300–600 Instructions for Continued Airworthiness, Document T3012–0005–0101, Revision B, dated June 12, 2008, can be conclusively determined to have been done from that review. Revision to the ALS To Incorporate CDCCLs (i) Within 30 days after the effective date of this AD, revise the ALS of the Instructions for Continued Airworthiness to incorporate the CDCCLs, as defined in Section 10.1 of the Goodrich A300–600 Instructions for Continued Airworthiness, Document T3012–0005–0101, Revision B, dated June 12, 2008. (j) Except as provided by paragraph (o) of this AD: After accomplishing the actions specified in paragraphs (g) and (i) of this AD, VerDate Nov<24>2008 16:23 Oct 26, 2009 Jkt 220001 no alternative inspection, inspection intervals, or CDCCLs may be used. Note 2: Notwithstanding any other maintenance or operational requirements, components that have been identified as airworthy or installed on the affected airplanes before the revision of the Airworthiness Limitations Section of the Instructions for Continuing Airworthiness, as required by paragraph (i) of this AD, do not need to be reworked in accordance with the CDCCLs. However, once the Airworthiness Limitations Section of the Instructions for Continuing Airworthiness has been revised, future maintenance actions on these components must be done in accordance with the CDCCLs. Actions Done According to Previous Service Information (k) Inspections are acceptable for compliance with the requirements of paragraph (h) of this AD, if done before the effective date of this AD, in accordance with Goodrich Service Bulletin 300723–0101–28– 01, dated April 15, 2004. (l) Inspections are also acceptable for compliance with the requirements of paragraph (h) of this AD, if done before the effective date of this AD, in accordance with Goodrich Service Bulletin 300723–0101–28– 01, Revision 1, dated July 1, 2004. Acceptable Methods of Compliance for AD 2004–05–05 (m) Doing the inspections in Section 2.2.3 of the Goodrich A300–600 Instructions for Continued Airworthiness, Document T3012– 0005–0101, Revision B, dated June 12, 2008, is considered an acceptable method of compliance with paragraphs (b) and (c) of AD 2004–05–05. (n) Doing the inspections in accordance with Goodrich Service Bulletin 300723– 0101–28–01, Revision 1, dated July 1, 2004, is an acceptable method of compliance with paragraphs (b) and (c) of AD 2004–05–05. Alternative Methods of Compliance (AMOCs) (o)(1) The Manager, Boston Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Marc Ronell, Aerospace Engineer, ANE–150, FAA, Boston ACO, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone (781) 238–7776; fax (781) 238– 7170. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. Material Incorporated by Reference (p) You must use Goodrich A300–600 Instructions for Continued Airworthiness, Document T3012–0005–0101, Revision B, PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 dated June 12, 2008, to do the actions required by this AD, unless the AD specifies otherwise. (The List of Effective Pages section of this document does not include pages iii, 6, 15, and 16 of this document. Those pages are also at Revision B, dated June 12, 2008.) (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Goodrich Corporation, Sensors and Integrated Systems (Formerly Fuel and Utility Systems), 100 Panton Road, Vergennes, Vermont 05491–1008; telephone 802–877–4476; e-mail sis.techpubsvt@goodrich.com; Internet https:// www.goodrich.com/TechPubs. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on September 18, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–24011 Filed 10–26–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0997; Directorate Identifier 2009–NM–158–AD; Amendment 39–16062; AD 2007–22–03 R1] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. SUMMARY: The FAA is revising an existing airworthiness directive (AD), which applies to all Airbus Model A300 airplanes. That AD currently requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This AD clarifies the intended effect of the AD on spare and on-airplane fuel tank system components. This AD E:\FR\FM\27OCR1.SGM 27OCR1 Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations pwalker on DSK8KYBLC1PROD with RULES results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors caused by latent failures, alterations, repairs, or maintenance actions, could result in fuel tank explosions and consequent loss of the airplane. DATES: This AD is effective November 12, 2009. On November 28, 2007 (72 FR 60240, October 24, 2007), the Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD. We must receive any comments on this AD by December 11, 2009. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Airbus SAS–EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com; Internet https://www.airbus.com. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: VerDate Nov<24>2008 16:23 Oct 26, 2009 Jkt 220001 Discussion On October 15, 2007, we issued AD 2007–22–03, amendment 39–15239 (72 FR 60240, October 24, 2007). That AD applied to all Airbus Model A300 airplanes. That AD required revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. Critical design configuration control limitations (CDCCLs) are limitation requirements to preserve a critical ignition source prevention feature of the fuel tank system design that is necessary to prevent the occurrence of an unsafe condition. The purpose of a CDCCL is to provide instruction to retain the critical ignition source prevention feature during configuration change that may be caused by alterations, repairs, or maintenance actions. A CDCCL is not a periodic inspection. Actions Since AD Was Issued Since we issued that AD, we have determined that it is necessary to clarify the AD’s intended effect on spare and on-airplane fuel tank system components, regarding the use of maintenance manuals and instructions for continued airworthiness. Section 91.403(c) of the Federal Aviation Regulations (14 CFR 91.403(c)) specifies the following: No person may operate an aircraft for which a manufacturer’s maintenance manual or instructions for continued airworthiness has been issued that contains an airworthiness limitation section unless the mandatory * * * procedures * * * have been complied with. Some operators have questioned whether existing components affected by the new CDCCLs must be reworked. We did not intend for the AD to retroactively require rework of components that had been maintained using acceptable methods before the effective date of the AD. Owners and operators of the affected airplanes therefore are not required to rework affected components identified as airworthy or installed on the affected airplanes before the required revisions of the airworthiness limitations section. But once the CDCCLs are incorporated into the airworthiness limitations section, future maintenance actions on components must be done in accordance with those CDCCLs. FAA’s Determination and Requirements of This AD The affected product has been approved by the aviation authority of another country, and are approved for operation in the United States. We are PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 55119 issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. This new AD retains the requirements of the existing AD, and adds a new note to clarify the intended effect of the AD on spare and on-airplane fuel tank system components. Costs of Compliance This revision imposes no additional economic burden. The current costs for this AD are repeated for the convenience of affected operators, as follows: This AD affects about 30 airplanes of U.S. registry. The required actions take about 2 work hours per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the AD for U.S. operators is $4,800, or $160 per airplane. FAA’s Justification and Determination of the Effective Date This revision merely clarifies the intended effect on spare and on-airplane fuel tank system components, and makes no substantive change to the AD’s requirements. For this reason, it is found that notice and opportunity for prior public comment for this action are unnecessary, and good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2009–0997; Directorate Identifier 2009– NM–158–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue E:\FR\FM\27OCR1.SGM 27OCR1 55120 Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 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 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, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: pwalker on DSK8KYBLC1PROD with RULES ■ 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. VerDate Nov<24>2008 16:23 Oct 26, 2009 Jkt 220001 § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–15239 (72 FR 60240, October 24, 2007) and adding the following new AD: ■ 2007–22–03 R1 Airbus: Amendment 39– 16062. Docket No. FAA–2009–0997; Directorate Identifier 2009–NM–158–AD. Effective Date (a) This airworthiness directive (AD) is effective November 12, 2009. Affected ADs (b) This AD revises AD 2007–22–03, Amendment 39–15239. Applicability (c) This AD applies to all Airbus Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4– 2C, B4–103, and B4–203 airplanes, certificated in any category, except Airbus Model A300–600 airplanes. Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections and critical design configuration control limitations (CDCCLs). Compliance with the operator maintenance documents 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 and CDCCLs, the operator may not be able to accomplish the inspections and CDCCLs 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 (j)(1) of this AD. The request should include a description of changes to the required inspections and CDCCLs that will preserve the critical ignition source prevention feature of the affected fuel system. For all tasks identified in Section 1 of Document 95A.1928/05, the initial compliance times start from the later of the times specified in paragraphs (f)(1) and (f)(2) of this AD, and the repetitive inspections must be accomplished thereafter at the intervals specified in Section 1 of Document 95A.1928/05, except as provided by paragraph (g) of this AD. (1) November 28, 2007. (2) The date of issuance of the original French standard airworthiness certificate or the date of issuance of the original French export certificate of airworthiness. Note 2: Airbus Operator Information Telex SE 999.0079/07, Revision 01, dated August 14, 2007, identifies the applicable sections of the Airbus A300 Airplane Maintenance Manual necessary for accomplishing the tasks specified in Section 1 of Document 95A.1928/05. Initial Compliance Time for Task 28–18–00– 03–1 (g) For Task 28–18–00–03–1 identified in Section 1 of Document 95A.1928/05, ‘‘Maintenance/Inspection Tasks,’’ of Airbus A300 Fuel Airworthiness Limitations, Document 95A.1928/05, Issue 2, dated May 11, 2007 (approved by the EASA on July 6, 2007): The initial compliance time is the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD. Thereafter, Task 28–18– 00–03–1 must be accomplished at the repetitive interval specified in Section 1 of Document 95A.1928/05. (1) Prior to the accumulation of 40,000 total flight hours. (2) Within 72 months or 20,000 flight hours after November 28, 2007, whichever occurs first. Revise ALS To Incorporate CDCCLs Unsafe Condition (d) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors caused by latent failures, alterations, repairs, or maintenance actions, could result in fuel tank explosions and consequent loss of the airplane. (h) Within 12 months after November 28, 2007, revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A300 Fuel Airworthiness Limitations, Document 95A.1928/05, Issue 2, dated May 11, 2007 (approved by the EASA on July 6, 2007), Section 2, ‘‘Critical Design Configuration Control Limitations.’’ 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. (i) Except as provided by paragraph (j) of this AD: After accomplishing the actions specified in paragraphs (f) and (h) of this AD, no alternative inspections, inspection intervals, or CDCCLs may be used. Restatement of AD 2007–22–03, With Certain Revised Compliance Methods New Information Revise Airworthiness Limitations Section (ALS) To Incorporate Fuel Maintenance and Inspection Tasks (f) Within 3 months after November 28, 2007 (the effective date of AD 2007–22–03), revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A300 Fuel Airworthiness Limitations, Document 95A.1928/05, Issue 2, dated May 11, 2007 (approved by the European Aviation Safety Agency (EASA) on July 6, 2007), Section 1, ‘‘Maintenance/Inspection Tasks.’’ Note 3: Notwithstanding any other maintenance or operational requirements, components that have been identified as airworthy or installed on the affected airplanes before the revision of the ALS, as required by paragraphs (f) and (h) of this AD, do not need to be reworked in accordance with the CDCCLs. However, once the ALS has been revised, future maintenance actions on these components must be done in accordance with the CDCCLs. PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 No Alternative Inspections, Inspection Intervals, or CDCCLs Explanation of CDCCL Requirements E:\FR\FM\27OCR1.SGM 27OCR1 Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION (j)(1) The Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. Federal Aviation Administration Related Information (k) European Aviation Safety Agency Airworthiness Directive 2007–0094 R1, dated May 2, 2007, also addresses the subject of this AD. Material Incorporated by Reference pwalker on DSK8KYBLC1PROD with RULES (l) You must use Airbus A300 Fuel Airworthiness Limitations, Document 95A.1928/05, Issue 2, dated May 11, 2007, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register previously approved the incorporation by reference of Airbus A300 Fuel Airworthiness Limitations, Document 95A.1928/05, Issue 2, dated May 11, 2007, on November 28, 2007 (72 FR 60240, October 24, 2007). (2) For service information identified in this AD, contact Airbus SAS—EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airwortheas@airbus.com; Internet https:// www.airbus.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on October 19, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–25772 Filed 10–26–09; 8:45 am] BILLING CODE 4910–13–P VerDate Nov<24>2008 16:23 Oct 26, 2009 Jkt 220001 14 CFR Part 39 [Docket No. FAA–2007–0037; Directorate Identifier 2007–NE–41–AD; Amendment 39– 16052; AD 2009–22–01] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd. & Co. KG. (RRD) Tay 650–15 Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. SUMMARY: We are superseding an existing airworthiness directive (AD) for the products listed above. That AD currently requires initial and repetitive inspections of the low-pressure (LP) turbine discs stage 2 and stage 3 for corrosion, on certain serial number engines. This AD requires the same actions, but extends the applicability to additional engine serial numbers. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Strip results from some of the engines listed in the applicability section of this directive revealed excessively corroded lowpressure turbine disks stage 2 and stage 3. The corrosion is considered to be caused by the environment in which these engines are operated. Following a life assessment based on the strip findings it is concluded that inspections for corrosion attack are required. The action specified by this AD is intended to avoid a failure of a low-pressure turbine disk stage 2 or stage 3 due to potential corrosion problems which could result in uncontained engine failure and damage to the airplane. We are issuing this AD to detect corrosion that could cause the stage 2 or stage 3 disk of the LP turbine to fail and result in an uncontained failure of the engine. DATES: This AD becomes effective November 12, 2009. We must receive comments on this AD by November 27, 2009. The Director of the Federal Register approved the incorporation by reference of Rolls-Royce Deutschland Alert Service Bulletin No. TAY–72–A1524, Revision 2, dated June 13, 2008, listed in the AD as of November 12, 2009. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 55121 the instructions for sending your comments electronically. • Mail: U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: jason.yang@faa.gov; telephone (781) 238–7747; fax (781) 238–7199. Contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlwitz, 15827 Blankenfelde-Mahlow, Germany; telephone 49 (0) 33–7086–1768; fax 49 (0) 33–7086–3356, for the service information referenced in this AD. SUPPLEMENTARY INFORMATION: Discussion On May 5, 2008, the FAA issued AD 2008–10–14 (Amendment 39–15521 (73 FR 29405, May 21, 2008). That AD requires initial and repetitive inspections of the LP turbine discs stage 2 and stage 3 for corrosion on 45 engines by serial number. That AD was the result of MCAI issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. That condition, if not corrected, could result in the stage 2 or stage 3 disk of the LP turbine to fail and result in an uncontained failure of the engine. Since AD 2008–10–14 was issued, RRD identified 34 additional engines by serial number that require the same inspections. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2008– 0122, dated July 1, 2008. That MCAI E:\FR\FM\27OCR1.SGM 27OCR1

Agencies

[Federal Register Volume 74, Number 206 (Tuesday, October 27, 2009)]
[Rules and Regulations]
[Pages 55118-55121]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-25772]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0997; Directorate Identifier 2009-NM-158-AD; 
Amendment 39-16062; AD 2007-22-03 R1]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 Airplanes

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

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is revising an existing airworthiness directive (AD), 
which applies to all Airbus Model A300 airplanes. That AD currently 
requires revising the Airworthiness Limitations Section of the 
Instructions for Continued Airworthiness to incorporate new limitations 
for fuel tank systems. This AD clarifies the intended effect of the AD 
on spare and on-airplane fuel tank system components. This AD

[[Page 55119]]

results from fuel system reviews conducted by the manufacturer. We are 
issuing this AD to prevent the potential of ignition sources inside 
fuel tanks, which, in combination with flammable fuel vapors caused by 
latent failures, alterations, repairs, or maintenance actions, could 
result in fuel tank explosions and consequent loss of the airplane.

DATES: This AD is effective November 12, 2009.
    On November 28, 2007 (72 FR 60240, October 24, 2007), the Director 
of the Federal Register approved the incorporation by reference of a 
certain publication listed in the AD.
    We must receive any comments on this AD by December 11, 2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Airbus SAS-
EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 
51; e-mail: account.airworth-eas@airbus.com; Internet https://www.airbus.com.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    On October 15, 2007, we issued AD 2007-22-03, amendment 39-15239 
(72 FR 60240, October 24, 2007). That AD applied to all Airbus Model 
A300 airplanes. That AD required revising the Airworthiness Limitations 
Section of the Instructions for Continued Airworthiness to incorporate 
new limitations for fuel tank systems.
    Critical design configuration control limitations (CDCCLs) are 
limitation requirements to preserve a critical ignition source 
prevention feature of the fuel tank system design that is necessary to 
prevent the occurrence of an unsafe condition. The purpose of a CDCCL 
is to provide instruction to retain the critical ignition source 
prevention feature during configuration change that may be caused by 
alterations, repairs, or maintenance actions. A CDCCL is not a periodic 
inspection.

Actions Since AD Was Issued

    Since we issued that AD, we have determined that it is necessary to 
clarify the AD's intended effect on spare and on-airplane fuel tank 
system components, regarding the use of maintenance manuals and 
instructions for continued airworthiness.
    Section 91.403(c) of the Federal Aviation Regulations (14 CFR 
91.403(c)) specifies the following:

    No person may operate an aircraft for which a manufacturer's 
maintenance manual or instructions for continued airworthiness has 
been issued that contains an airworthiness limitation section unless 
the mandatory * * * procedures * * * have been complied with.

Some operators have questioned whether existing components affected by 
the new CDCCLs must be reworked. We did not intend for the AD to 
retroactively require rework of components that had been maintained 
using acceptable methods before the effective date of the AD. Owners 
and operators of the affected airplanes therefore are not required to 
rework affected components identified as airworthy or installed on the 
affected airplanes before the required revisions of the airworthiness 
limitations section. But once the CDCCLs are incorporated into the 
airworthiness limitations section, future maintenance actions on 
components must be done in accordance with those CDCCLs.

FAA's Determination and Requirements of This AD

    The affected product has been approved by the aviation authority of 
another country, and are approved for operation in the United States. 
We are issuing this AD because we evaluated all pertinent information 
and determined the unsafe condition exists and is likely to exist or 
develop on other products of the same type design. This new AD retains 
the requirements of the existing AD, and adds a new note to clarify the 
intended effect of the AD on spare and on-airplane fuel tank system 
components.

Costs of Compliance

    This revision imposes no additional economic burden. The current 
costs for this AD are repeated for the convenience of affected 
operators, as follows:
    This AD affects about 30 airplanes of U.S. registry. The required 
actions take about 2 work hours per airplane, at an average labor rate 
of $80 per work hour. Based on these figures, the estimated cost of the 
AD for U.S. operators is $4,800, or $160 per airplane.

FAA's Justification and Determination of the Effective Date

    This revision merely clarifies the intended effect on spare and on-
airplane fuel tank system components, and makes no substantive change 
to the AD's requirements. For this reason, it is found that notice and 
opportunity for prior public comment for this action are unnecessary, 
and good cause exists for making this amendment effective in less than 
30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
``Docket No. FAA-2009-0997; Directorate Identifier 2009-NM-158-AD'' at 
the beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
AD. We will consider all comments received by the closing date and may 
amend this AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue

[[Page 55120]]

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 AD will not have federalism 
implications under Executive Order 13132. This AD will 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 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 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends part 39 of the Federal Aviation Regulations (14 CFR part 
39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-15239 (72 FR 
60240, October 24, 2007) and adding the following new AD:

2007-22-03 R1 Airbus: Amendment 39-16062. Docket No. FAA-2009-0997; 
Directorate Identifier 2009-NM-158-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective November 12, 
2009.

Affected ADs

    (b) This AD revises AD 2007-22-03, Amendment 39-15239.

Applicability

    (c) This AD applies to all Airbus Model A300 B2-1A, B2-1C, B2K-
3C, B2-203, B4-2C, B4-103, and B4-203 airplanes, certificated in any 
category, except Airbus Model A300-600 airplanes.

    Note 1: This AD requires revisions to certain operator 
maintenance documents to include new inspections and critical design 
configuration control limitations (CDCCLs). Compliance with the 
operator maintenance documents 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 and CDCCLs, the operator 
may not be able to accomplish the inspections and CDCCLs 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 (j)(1) of this AD. The 
request should include a description of changes to the required 
inspections and CDCCLs that will preserve the critical ignition 
source prevention feature of the affected fuel system.

Unsafe Condition

    (d) This AD results from fuel system reviews conducted by the 
manufacturer. We are issuing this AD to prevent potential of 
ignition sources inside fuel tanks, which, in combination with 
flammable fuel vapors caused by latent failures, alterations, 
repairs, or maintenance actions, could result in fuel tank 
explosions and consequent loss of the airplane.

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.

Restatement of AD 2007-22-03, With Certain Revised Compliance Methods

Revise Airworthiness Limitations Section (ALS) To Incorporate Fuel 
Maintenance and Inspection Tasks

    (f) Within 3 months after November 28, 2007 (the effective date 
of AD 2007-22-03), revise the ALS of the Instructions for Continued 
Airworthiness to incorporate Airbus A300 Fuel Airworthiness 
Limitations, Document 95A.1928/05, Issue 2, dated May 11, 2007 
(approved by the European Aviation Safety Agency (EASA) on July 6, 
2007), Section 1, ``Maintenance/Inspection Tasks.'' For all tasks 
identified in Section 1 of Document 95A.1928/05, the initial 
compliance times start from the later of the times specified in 
paragraphs (f)(1) and (f)(2) of this AD, and the repetitive 
inspections must be accomplished thereafter at the intervals 
specified in Section 1 of Document 95A.1928/05, except as provided 
by paragraph (g) of this AD.
    (1) November 28, 2007.
    (2) The date of issuance of the original French standard 
airworthiness certificate or the date of issuance of the original 
French export certificate of airworthiness.

    Note 2: Airbus Operator Information Telex SE 999.0079/07, 
Revision 01, dated August 14, 2007, identifies the applicable 
sections of the Airbus A300 Airplane Maintenance Manual necessary 
for accomplishing the tasks specified in Section 1 of Document 
95A.1928/05.

Initial Compliance Time for Task 28-18-00-03-1

    (g) For Task 28-18-00-03-1 identified in Section 1 of Document 
95A.1928/05, ``Maintenance/Inspection Tasks,'' of Airbus A300 Fuel 
Airworthiness Limitations, Document 95A.1928/05, Issue 2, dated May 
11, 2007 (approved by the EASA on July 6, 2007): The initial 
compliance time is the later of the times specified in paragraphs 
(g)(1) and (g)(2) of this AD. Thereafter, Task 28-18-00-03-1 must be 
accomplished at the repetitive interval specified in Section 1 of 
Document 95A.1928/05.
    (1) Prior to the accumulation of 40,000 total flight hours.
    (2) Within 72 months or 20,000 flight hours after November 28, 
2007, whichever occurs first.

Revise ALS To Incorporate CDCCLs

    (h) Within 12 months after November 28, 2007, revise the ALS of 
the Instructions for Continued Airworthiness to incorporate Airbus 
A300 Fuel Airworthiness Limitations, Document 95A.1928/05, Issue 2, 
dated May 11, 2007 (approved by the EASA on July 6, 2007), Section 
2, ``Critical Design Configuration Control Limitations.''

No Alternative Inspections, Inspection Intervals, or CDCCLs

    (i) Except as provided by paragraph (j) of this AD: After 
accomplishing the actions specified in paragraphs (f) and (h) of 
this AD, no alternative inspections, inspection intervals, or CDCCLs 
may be used.

New Information

Explanation of CDCCL Requirements

    Note 3: Notwithstanding any other maintenance or operational 
requirements, components that have been identified as airworthy or 
installed on the affected airplanes before the revision of the ALS, 
as required by paragraphs (f) and (h) of this AD, do not need to be 
reworked in accordance with the CDCCLs. However, once the ALS has 
been revised, future maintenance actions on these components must be 
done in accordance with the CDCCLs.


[[Page 55121]]



Alternative Methods of Compliance (AMOCs)

    (j)(1) The Manager, International Branch, ANM-116, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. Send information to ATTN: Dan 
Rodina, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 
98057-3356; telephone (425) 227-2125; fax (425) 227-1149.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.

Related Information

    (k) European Aviation Safety Agency Airworthiness Directive 
2007-0094 R1, dated May 2, 2007, also addresses the subject of this 
AD.

Material Incorporated by Reference

    (l) You must use Airbus A300 Fuel Airworthiness Limitations, 
Document 95A.1928/05, Issue 2, dated May 11, 2007, to do the actions 
required by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register previously approved the 
incorporation by reference of Airbus A300 Fuel Airworthiness 
Limitations, Document 95A.1928/05, Issue 2, dated May 11, 2007, on 
November 28, 2007 (72 FR 60240, October 24, 2007).
    (2) For service information identified in this AD, contact 
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com; 
Internet https://www.airbus.com.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221 or 425-227-1152.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on October 19, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-25772 Filed 10-26-09; 8:45 am]
BILLING CODE 4910-13-P
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