Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ Airplanes, 29123-29126 [E9-13567]

Download as PDF Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations Subject (d) Air Transport Association (ATA) of America Code 26: Fire protection. cprice-sewell on PRODPC61 with RULES Reason (e) The mandatory continuing airworthiness information (MCAI) states: During receipt of spare parts at the final assembly line, it was discovered that lugs of the assembly nut, part number (P/N) A2621005000200, had been inverted (wrong orientation of the braking pin) during manufacturing process at the supplier. The assembly nut P/N A2621005000200 is part of the engine fire-extinguishing piping assembly. It connects the extinguisher discharge head with the piping. The lugs function is to prevent the connection untwisting once it has been hand-tightened with the correct torque. This lug inversion could give the illusion of correct torque whereas the affected parts are not properly connected. Loose connection could lead to loss of the fire extinguishing system integrity and therefore inability to ensure the adequate agent concentration. In combination with an engine fire event, it could result in a temporary uncontrolled engine fire, which constitutes an unsafe condition. To restore connection integrity, this Airworthiness Directive (AD) requires a onetime general visual inspection of the affected nut assembly to detect and correct any wrong orientation of lugs. The corrective actions include a temporary repair (restoration) and replacing the fire extinguisher bottle nut assembly with the braking pin in the inverted position, if necessary. Actions and Compliance (f) Unless already done, do the following actions: (1) Within 900 flight hours after the effective date of this AD, perform a general visual inspection to detect any wrong orientation of the lugs of the fire extinguisher bottle nut assembly of both engines, and do all applicable corrective actions specified in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–26–3043, dated October 7, 2008. (i) Before further flight, if the correct nut assembly is available, replace the fire extinguisher bottle nut assembly. (ii) Before further flight, if the correct nut assembly is not available, do the temporary repair; and within 900 flight hours after doing the repair, replace the fire extinguisher bottle nut assembly with the correct one. (2) Submit a report of the findings of the inspection required by paragraph (f)(1) of this AD using Appendix 01 of Airbus Mandatory Service Bulletin A330–26–3043, dated October 7, 2008, at the applicable time specified in paragraph (f)(2)(i) or (f)(2)(ii) of this AD. Send the report to Airbus Department SEEE6, Airbus Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France, Attn: SDC32 Technical Data and Documentation Services; fax 33 5 61 93 28 06; e-mail sb.reporting@airbus.com. VerDate Nov<24>2008 14:33 Jun 18, 2009 Jkt 217001 (i) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (ii) If the inspection was accomplished prior to the effective date of this AD: Submit the report within 30 days after the effective date of this AD. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. 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. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2008– 0196, dated October 27, 2008; and Airbus Mandatory Service Bulletin A330–26–3043, including Appendices 01, 2, and 3, dated October 7, 2008; for related information. Material Incorporated by Reference (i) You must use Airbus Mandatory Service Bulletin A330–26–3043, including Appendices 01, 2, and 3, dated October 7, 2008, to do the actions required by this AD, unless the AD specifies otherwise. (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 Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80, e-mail airworthiness.A330–A340@airbus.com; Internet https://www.airbus.com. PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 29123 (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 June 11, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–14308 Filed 6–18–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0133; Directorate Identifier 2008–NM–107–AD; Amendment 39–15933; AD 2009–12–10] RIN 2120–AA64 Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 and Avro 146–RJ Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to all BAE Systems (Operations) Limited Model BAe 146 and Avro 146–RJ airplanes. That AD currently requires repetitive inspections for corrosion of frames 15, 18, 41, and 43 and applicable related investigative and corrective actions. The existing AD also provides an optional action that would extend the repetitive inspection interval. This new AD also requires a high frequency eddy current inspection for corrosion of the outer frame flanges and door hinge bosses of frames 15, 18, 41, and 43. This AD results from a report indicating that corrosion has been detected in the outer frame flanges and door hinge bosses during scheduled maintenance. We are issuing this AD to prevent reduced structural integrity of the airplane. DATES: This AD becomes effective July 24, 2009. The Director of the Federal Register approved the incorporation by reference E:\FR\FM\19JNR1.SGM 19JNR1 29124 Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations of a certain publication listed in the AD as of July 24, 2009. ADDRESSES: For service information identified in this AD, contact BAE Systems Regional Aircraft, 13850 McLearen Road, Herndon, Virginia 20171; telephone 703–736–1080; e-mail raebusiness@baesystems.com; Internet https://www.baesystems.com/Businesses/ RegionalAircraft/index.htm. 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 address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: interval. In addition, the NPRM proposed to require a high frequency eddy current (HFEC) inspection for corrosion of the outer frame flanges and door hinge bosses of frames 15, 18, 41, and 43. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2006–12–09, amendment 39–14634 (71 FR 33602, June 12, 2006). The existing AD applies to all BAE Systems (Operations) Limited Model BAe 146 and Avro 146–RJ airplanes. That NPRM was published in the Federal Register on February 18, 2009 (74 FR 7565). That NPRM proposed to continue to require repetitive inspections for corrosion of frames 15, 18, 41, and 43 and applicable related investigative and corrective actions. The NPRM also proposed to continue to provide an optional action that would extend the repetitive inspection We provided the public the opportunity to participate in the development of this AD. No comments have been received on the NPRM or on the determination of the cost to the public. Comments Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this AD. ESTIMATED COSTS Action Average labor rate per hour Work hours HFEC inspection, per inspection cycle (required by AD 2006–12–09) .................................................................... Detailed Inspection, per inspection cycle (required by AD 2006–12–09) .................................................................... HFEC inspection, per inspection cycle (new action) ........... $80 $400 1 $400 3 5 80 80 240 400 1 1 240 400 cprice-sewell on PRODPC61 with RULES Regulatory Findings 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. 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 this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under 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. 14:33 Jun 18, 2009 Jkt 217001 PO 00000 Frm 00014 Fleet cost 5 Authority for This Rulemaking VerDate Nov<24>2008 Number of U.S.-registered airplanes Cost per airplane Fmt 4700 Sfmt 4700 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 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 removing amendment 39–14634 (71 FR 33602, June 12, 2006) and by adding the following new airworthiness directive (AD): ■ 2009–12–10 BAE Systems (Operations) Limited (Formerly British Aerospace E:\FR\FM\19JNR1.SGM 19JNR1 Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations Regional Aircraft): Amendment 39– 15933. Docket No. FAA–2009–0133; Directorate Identifier 2008–NM–107–AD. Effective Date (a) This AD becomes effective July 24, 2009. Affected ADs (b) This AD supersedes AD 2006–12–09. Applicability (c) This AD applies to all BAE Systems (Operations) Limited Model BAe 146–100A, –200A, and –300A series airplanes; and Model Avro 146–RJ70A, 146–RJ85A, and 146–RJ100A airplanes; certificated in any category. Subject (d) Air Transport Association (ATA) of America Code 53: Fuselage. Unsafe Condition (e) This AD results from a report indicating that corrosion has been detected in the outer frame flanges and door hinge bosses during scheduled maintenance. We are issuing this AD to prevent reduced structural integrity of the airplane. Compliance (f) 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 Requirements of AD 2006– 12–09 cprice-sewell on PRODPC61 with RULES (g) Use high-frequency eddy current (HFEC) and detailed methods to inspect for signs of corrosion (including cracks, blistering, or flaking paint) of frames 15, 18, 41, and 43, in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53–182, dated March 16, 2005, except as required by paragraph (k) of this AD. Inspect at the applicable time specified in 1.D. ‘‘Compliance’’ of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53–182, dated March 16, 2005. Application of corrosion-preventive treatment, in accordance with BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53–182, dated March 16, 2005; or Revision 1, dated August 6, 2007; extends the repetitive inspection interval, as specified in Table 2 in 1.D. ‘‘Compliance’’ of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53–182, dated March 16, 2005. Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ VerDate Nov<24>2008 14:33 Jun 18, 2009 Jkt 217001 Corrective Action (h) If any discrepancy is found during any inspection required by paragraph (g) of this AD: Before further flight, perform applicable related investigative/corrective actions in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53– 182, dated March 16, 2005, except as required by paragraphs (i) and (k) of this AD. AD: Before further flight, perform applicable related investigative/corrective actions in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53– 182, Revision 1, dated August 6, 2007, except as required by paragraph (n) of this AD. Exceptions to Service Bulletin Specifications (i) If BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53–182, dated March 16, 2005, specifies to contact the manufacturer for appropriate action, before further flight, repair per a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the Civil Aviation Authority (or its delegated agent); or European Aviation Safety Agency (EASA) (or its delegated agent). (j) Where BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53– 182, dated March 16, 2005, specifies a compliance time after the issuance of the service bulletin, this AD requires compliance within the specified compliance time after July 17, 2006 (the effective date of AD 2006– 12–09). Where BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53– 182, dated March 16, 2005, specifies a compliance time ‘‘since date of construction’’ of the airplane, this AD requires compliance since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness. (n) If BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53–182, Revision 1, dated August 6, 2007, specifies to contact the manufacturer for appropriate action, before further flight, repair per a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA (or its delegated agent). (o) Where BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53– 182, Revision 1, dated August 6, 2007, specifies a compliance time after the issuance of the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. Where BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53–182, Revision 1, dated August 6, 2007, specifies a compliance time ‘‘since date of construction’’ of the airplane, this AD requires compliance since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness. New Requirements of This AD Repetitive Inspections 29125 New Service Bulletin (k) As of the effective date of this AD: Do the actions required by paragraphs (g) and (h) of this AD in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53–182, Revision 1, dated August 6, 2007, except as required by paragraph (n) of this AD. Additional Inspection Areas (l) At the applicable compliance time specified in paragraph (g) of this AD, except as provided by paragraph (o) of this AD; or within six months after the effective date of this AD; whichever occurs later: Do an HFEC inspection for corrosion of the outer frame flanges and door hinge bosses of frames 15, 18, 41, and 43, in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53–182, Revision 1, dated August 6, 2007 (‘‘the service bulletin’’). Repeat the inspection thereafter at the applicable time specified in paragraph 1.D., ‘‘Compliance,’’ of the service bulletin. Application of corrosion-preventive treatment, in accordance with the Accomplishment Instructions of the service bulletin, extends the repetitive inspection interval, as specified in Table 2 in paragraph 1.D., ‘‘Compliance,’’ of the service bulletin. Corrective Action for Additional Inspection (m) If any discrepancy is found during any inspection required by paragraph (l) of this PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 Exceptions to BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53– 182, Revision 1 No Reporting (p) Although BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53– 182, dated March 16, 2005; and Revision 1, dated August 6, 2007; specify to submit information to the manufacturer, this AD does not include such a requirement. Alternative Methods of Compliance (AMOCs) (q) 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: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. 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 (r) European Aviation Safety Agency Airworthiness Directive 2008–0092 R1, dated May 15, 2008, also addresses the subject of this AD. Material Incorporated by Reference (s) You must BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53– 182, Revision 1, dated August 6, 2007; as E:\FR\FM\19JNR1.SGM 19JNR1 29126 Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations applicable; to do the actions required by this AD, unless the AD specifies otherwise. (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 BAE Systems Regional Aircraft, 13850 McLearen Road, Herndon, Virginia 20171; telephone 703–736–1080; email raebusiness@baesystems.com; Internet https://www.baesystems.com/Businesses/ RegionalAircraft/index.htm. (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 June 2, 2009. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–13567 Filed 6–18–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION to the pin can be jammed when it is pulled by a pilot or a passenger. This condition, if not corrected, would lead, in case of an emergency procedure due to decompression to a risk of generator fault with subsequent lack of oxygen on crew and/ or passenger. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective July 9, 2009. On July 9, 2009, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. We must receive comments on this AD by July 20, 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. Federal Aviation Administration Examining the AD Docket 14 CFR Part 39 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: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4119; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: [Docket No. FAA–2009–0557; Directorate Identifier 2009–CE–031–AD; Amendment 39–15944; AD 2009–13–05] RIN 2120–AA64 Airworthiness Directives; SOCATA Model TBM 700 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: cprice-sewell on PRODPC61 with RULES SUMMARY: During a SOCATA flight test, it has been noted some difficulties for the pilot to release oxygen. After investigation it has been found that, due to the design of the oxygen generator release pin, one of the mask’s lanyard linked VerDate Nov<24>2008 14:33 Jun 18, 2009 Jkt 217001 Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued Emergency AD No. 2009–0096–E, dated April 21, 2009, (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 During a SOCATA flight test, it has been noted some difficulties for the pilot to release oxygen. After investigation it has been found that, due to the design of the oxygen generator release pin, one of the mask’s lanyard linked to the pin can be jammed when it is pulled by a pilot or a passenger. This condition, if not corrected, would lead, in case of an emergency procedure due to decompression to a risk of generator fault with subsequent lack of oxygen on crew and/ or passenger. For the reason described above, SOCATA has released Pilot Operating Handbook (POH) Temporary Revision (TR) 03 which asks, in case of failure to release oxygen, to pull on the other mask lanyard in order to activate the oxygen generator. A SOCATA modification enabling to solve this issue is under preparation. Once this modification release, this AD is expected to be revised to confirm the acceptability of that modification. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information SOCATA has issued SOCATA TBM 700 A & B Pilot Operating Handbook (POH), Temporary Revision No. 3, dated March 2009. The actions described in page 3.13.5 of this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of the AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all information provided by the State of Design Authority and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might have also required different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are described in a E:\FR\FM\19JNR1.SGM 19JNR1

Agencies

[Federal Register Volume 74, Number 117 (Friday, June 19, 2009)]
[Rules and Regulations]
[Pages 29123-29126]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-13567]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0133; Directorate Identifier 2008-NM-107-AD; 
Amendment 39-15933; AD 2009-12-10]
RIN 2120-AA64


Airworthiness Directives; BAE Systems (Operations) Limited Model 
BAe 146 and Avro 146-RJ Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to all BAE Systems (Operations) Limited Model BAe 
146 and Avro 146-RJ airplanes. That AD currently requires repetitive 
inspections for corrosion of frames 15, 18, 41, and 43 and applicable 
related investigative and corrective actions. The existing AD also 
provides an optional action that would extend the repetitive inspection 
interval. This new AD also requires a high frequency eddy current 
inspection for corrosion of the outer frame flanges and door hinge 
bosses of frames 15, 18, 41, and 43. This AD results from a report 
indicating that corrosion has been detected in the outer frame flanges 
and door hinge bosses during scheduled maintenance. We are issuing this 
AD to prevent reduced structural integrity of the airplane.

DATES: This AD becomes effective July 24, 2009.
    The Director of the Federal Register approved the incorporation by 
reference

[[Page 29124]]

of a certain publication listed in the AD as of July 24, 2009.

ADDRESSES: For service information identified in this AD, contact BAE 
Systems Regional Aircraft, 13850 McLearen Road, Herndon, Virginia 
20171; telephone 703-736-1080; e-mail raebusiness@baesystems.com; 
Internet https://www.baesystems.com/Businesses/RegionalAircraft/index.htm.

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 address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1175; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2006-12-09, amendment 
39-14634 (71 FR 33602, June 12, 2006). The existing AD applies to all 
BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ 
airplanes. That NPRM was published in the Federal Register on February 
18, 2009 (74 FR 7565). That NPRM proposed to continue to require 
repetitive inspections for corrosion of frames 15, 18, 41, and 43 and 
applicable related investigative and corrective actions. The NPRM also 
proposed to continue to provide an optional action that would extend 
the repetitive inspection interval. In addition, the NPRM proposed to 
require a high frequency eddy current (HFEC) inspection for corrosion 
of the outer frame flanges and door hinge bosses of frames 15, 18, 41, 
and 43.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been received on the NPRM or 
on the determination of the cost to the public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

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

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                  Number of U.S.-
             Action                 Work hours     Average labor     Cost per       registered      Fleet cost
                                                   rate per hour     airplane        airplanes
----------------------------------------------------------------------------------------------------------------
HFEC inspection, per inspection                5             $80            $400               1            $400
 cycle (required by AD 2006-12-
 09)............................
Detailed Inspection, per                       3              80             240               1             240
 inspection cycle (required by
 AD 2006-12-09).................
HFEC inspection, per inspection                5              80             400               1             400
 cycle (new action).............
----------------------------------------------------------------------------------------------------------------

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 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14634 (71 FR 33602, June 12, 2006) and by adding 
the following new airworthiness directive (AD):

2009-12-10 BAE Systems (Operations) Limited (Formerly British 
Aerospace

[[Page 29125]]

Regional Aircraft): Amendment 39-15933. Docket No. FAA-2009-0133; 
Directorate Identifier 2008-NM-107-AD.

Effective Date

    (a) This AD becomes effective July 24, 2009.

Affected ADs

    (b) This AD supersedes AD 2006-12-09.

Applicability

    (c) This AD applies to all BAE Systems (Operations) Limited 
Model BAe 146-100A, -200A, and -300A series airplanes; and Model 
Avro 146-RJ70A, 146-RJ85A, and 146-RJ100A airplanes; certificated in 
any category.

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Unsafe Condition

    (e) This AD results from a report indicating that corrosion has 
been detected in the outer frame flanges and door hinge bosses 
during scheduled maintenance. We are issuing this AD to prevent 
reduced structural integrity of the airplane.

Compliance

    (f) 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 Requirements of AD 2006-12-09

Repetitive Inspections

    (g) Use high-frequency eddy current (HFEC) and detailed methods 
to inspect for signs of corrosion (including cracks, blistering, or 
flaking paint) of frames 15, 18, 41, and 43, in accordance with the 
Accomplishment Instructions of BAE Systems (Operations) Limited 
Inspection Service Bulletin ISB.53-182, dated March 16, 2005, except 
as required by paragraph (k) of this AD. Inspect at the applicable 
time specified in 1.D. ``Compliance'' of BAE Systems (Operations) 
Limited Inspection Service Bulletin ISB.53-182, dated March 16, 
2005. Application of corrosion-preventive treatment, in accordance 
with BAE Systems (Operations) Limited Inspection Service Bulletin 
ISB.53-182, dated March 16, 2005; or Revision 1, dated August 6, 
2007; extends the repetitive inspection interval, as specified in 
Table 2 in 1.D. ``Compliance'' of BAE Systems (Operations) Limited 
Inspection Service Bulletin ISB.53-182, dated March 16, 2005.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

Corrective Action

    (h) If any discrepancy is found during any inspection required 
by paragraph (g) of this AD: Before further flight, perform 
applicable related investigative/corrective actions in accordance 
with the Accomplishment Instructions of BAE Systems (Operations) 
Limited Inspection Service Bulletin ISB.53-182, dated March 16, 
2005, except as required by paragraphs (i) and (k) of this AD.

Exceptions to Service Bulletin Specifications

    (i) If BAE Systems (Operations) Limited Inspection Service 
Bulletin ISB.53-182, dated March 16, 2005, specifies to contact the 
manufacturer for appropriate action, before further flight, repair 
per a method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or the Civil Aviation Authority 
(or its delegated agent); or European Aviation Safety Agency (EASA) 
(or its delegated agent).
    (j) Where BAE Systems (Operations) Limited Inspection Service 
Bulletin ISB.53-182, dated March 16, 2005, specifies a compliance 
time after the issuance of the service bulletin, this AD requires 
compliance within the specified compliance time after July 17, 2006 
(the effective date of AD 2006-12-09). Where BAE Systems 
(Operations) Limited Inspection Service Bulletin ISB.53-182, dated 
March 16, 2005, specifies a compliance time ``since date of 
construction'' of the airplane, this AD requires compliance since 
the date of issuance of the original standard airworthiness 
certificate or the date of issuance of the original export 
certificate of airworthiness.

New Requirements of This AD

New Service Bulletin

    (k) As of the effective date of this AD: Do the actions required 
by paragraphs (g) and (h) of this AD in accordance with the 
Accomplishment Instructions of BAE Systems (Operations) Limited 
Inspection Service Bulletin ISB.53-182, Revision 1, dated August 6, 
2007, except as required by paragraph (n) of this AD.

Additional Inspection Areas

    (l) At the applicable compliance time specified in paragraph (g) 
of this AD, except as provided by paragraph (o) of this AD; or 
within six months after the effective date of this AD; whichever 
occurs later: Do an HFEC inspection for corrosion of the outer frame 
flanges and door hinge bosses of frames 15, 18, 41, and 43, in 
accordance with the Accomplishment Instructions of BAE Systems 
(Operations) Limited Inspection Service Bulletin ISB.53-182, 
Revision 1, dated August 6, 2007 (``the service bulletin''). Repeat 
the inspection thereafter at the applicable time specified in 
paragraph 1.D., ``Compliance,'' of the service bulletin. Application 
of corrosion-preventive treatment, in accordance with the 
Accomplishment Instructions of the service bulletin, extends the 
repetitive inspection interval, as specified in Table 2 in paragraph 
1.D., ``Compliance,'' of the service bulletin.

Corrective Action for Additional Inspection

    (m) If any discrepancy is found during any inspection required 
by paragraph (l) of this AD: Before further flight, perform 
applicable related investigative/corrective actions in accordance 
with the Accomplishment Instructions of BAE Systems (Operations) 
Limited Inspection Service Bulletin ISB.53-182, Revision 1, dated 
August 6, 2007, except as required by paragraph (n) of this AD.

Exceptions to BAE Systems (Operations) Limited Inspection Service 
Bulletin ISB.53-182, Revision 1

    (n) If BAE Systems (Operations) Limited Inspection Service 
Bulletin ISB.53-182, Revision 1, dated August 6, 2007, specifies to 
contact the manufacturer for appropriate action, before further 
flight, repair per a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA (or 
its delegated agent).
    (o) Where BAE Systems (Operations) Limited Inspection Service 
Bulletin ISB.53-182, Revision 1, dated August 6, 2007, specifies a 
compliance time after the issuance of the service bulletin, this AD 
requires compliance within the specified compliance time after the 
effective date of this AD. Where BAE Systems (Operations) Limited 
Inspection Service Bulletin ISB.53-182, Revision 1, dated August 6, 
2007, specifies a compliance time ``since date of construction'' of 
the airplane, this AD requires compliance since the date of issuance 
of the original airworthiness certificate or the date of issuance of 
the original export certificate of airworthiness.

No Reporting

    (p) Although BAE Systems (Operations) Limited Inspection Service 
Bulletin ISB.53-182, dated March 16, 2005; and Revision 1, dated 
August 6, 2007; specify to submit information to the manufacturer, 
this AD does not include such a requirement.

Alternative Methods of Compliance (AMOCs)

    (q) 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: Todd 
Thompson, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1175; fax (425) 227-1149. 
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

    (r) European Aviation Safety Agency Airworthiness Directive 
2008-0092 R1, dated May 15, 2008, also addresses the subject of this 
AD.

Material Incorporated by Reference

    (s) You must BAE Systems (Operations) Limited Inspection Service 
Bulletin ISB.53-182, Revision 1, dated August 6, 2007; as

[[Page 29126]]

applicable; to do the actions required by this AD, unless the AD 
specifies otherwise.
    (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 BAE 
Systems Regional Aircraft, 13850 McLearen Road, Herndon, Virginia 
20171; telephone 703-736-1080; e-mail raebusiness@baesystems.com; 
Internet https://www.baesystems.com/Businesses/RegionalAircraft/index.htm.
    (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 June 2, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-13567 Filed 6-18-09; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.