Airworthiness directives: BAE Systems (Operations) Ltd.,
[Federal Register: December 20, 2007 (Volume 72, Number 244)]
[Proposed Rules]
[Page 72270-72272]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20de07-16]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. FAA-2007-0368; Directorate Identifier 2007-NM-050-AD]
RIN 2120-AA64
Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146-100A, -200A, and -300A Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated 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:
Cracking has been found on the centre fuselage top aft longeron at Rib `0,' on an in-service aircraft. * * *
This condition could result in reduced structural integrity of the airplane. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by January 22, 2008.
ADDRESSES:
Federal eRulemaking Portal: Go to http://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 W12-40, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at http://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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations 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: Todd Thompson, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 227-1175; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2007-0368; Directorate Identifier 2007-NM-050-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments.
We will post all comments we receive, without change, to http://www.regulations.gov , including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2006-0215, dated July 14, 2006 (referred to after this as ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states:
Cracking has been found on the centre fuselage top aft longeron at Rib `0' on an in-service aircraft. Subsequent investigation has indicated that the currently defined threshold and repeat inspection period must be reduced, and the area of inspection expanded for the BAe 146 series 100 and 200. For the BAe146 series 300, only the repeat inspection period must be reduced, and the area of inspection expanded.
Cracking on the center fuselage top aft longeron at Rib `0,' could result in reduced structural integrity of the airplane. Corrective actions include repetitive inspections of the center fuselage top aft longeron for cracking and repair/replacement if necessary. You may obtain further information by examining the MCAI in the AD docket.
Relevant Service Information
BAE Systems (Operations) Limited has issued Service Bulletin ISB.53-173, Revision 2, dated March 28, 2006. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed 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 the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an 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 also have proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD would affect about 1 product of U.S. registry. We also estimate that it would take about 8 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $640, or $640 per product.
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
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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 determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed regulation:
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Is not a ``significant regulatory action'' under Executive Order 12866;
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Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and
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Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
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The FAA amends Sec. 39.13 by adding the following new AD:
BAE Systems (Operations) Limited (Formerly British Aerospace Regional Aircraft): Docket No. FAA-2007-0368; Directorate Identifier 2007-NM-050-AD.
Comments Due Date
(a) We must receive comments by January 22, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all BAE Systems (Operations) Limited Model BAE 146-100A, -200A, and -300A series airplanes; certificated in any category.
Subject
(d) Air Transport Association (ATA) of America Code 53: Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI) states:
Cracking has been found on the centre fuselage top aft longeron at Rib `0' on an in-service aircraft. Subsequent investigation has indicated that the currently defined threshold and repeat inspection period must be reduced, and the area of inspection expanded for the BAe146 series 100 and 200. For the BAe146 series 300, only the repeat inspection period must be reduced, and the area of inspection expanded.
Cracking on the center fuselage top aft longeron at Rib `0' could result in reduced structural integrity of the airplane. Corrective actions include repetitive inspections of the center fuselage top aft longeron for cracking and repair/replacement if necessary.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) For all BAE 146-100A and BAE 146-200A series airplanes pre- mod HCM01709B or HCM01709C that have not been inspected in accordance with Maintenance Review Board Report (MRBR) SSI/SII Task No. 53-20-140A (Maintenance Planning Document (MPD) task 532040-SDI- 10000-3) or BAE Systems (Operations) Limited Service Bulletin ISB.53-173 Revision 1, dated May 19, 2004, as of the effective date of this AD: Do the actions in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD at the applicable compliance time, and do all applicable repairs and replacements before further flight.
(i) Inspect and repair cracking of the forward six bolt bores between the subframe and frame 30 in accordance with paragraph 2.B of BAE Systems (Operations) Limited Service Bulletin ISB.53-173, Revision 2, dated March 28, 2006, before the accumulation of 17,000 total flight cycles, or within 500 flight cycles after the effective date of this AD, whichever occurs later. If the damage exceeds limits specified in the structural repair manual (SRM), before further flight, contact BAE Systems and repair. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles, except as provided by paragraph (f)(3) of this AD.
(ii) Inspect and repair cracking of the remaining fastener bores between the sub-frame and frame 30 in accordance with paragraph 2.B of BAE Systems (Operations) Limited Service Bulletin ISB.53-173, Revision 2, dated March 28, 2006, before the accumulation of 17,000 total flight cycles, or within 4,000 flight cycles after the effective date of this AD, whichever occurs later. If the damage exceeds limits specified in the SRM, before further flight, contact BAE Systems and repair. Repeat the inspection thereafter at intervals not to exceed 11,900 flight cycles, except as provided by paragraph (f)(3) of this AD.
(2) For all BAe 146-100A and BAe 146-200A series airplanes pre- mod HCM01709B or HCM01709C that have been inspected in accordance with MRBR SSI/SII Task No. 53-20-140A (MPD task 532040-SDI-10000-3) or BAE Systems (Operations) Limited Service Bulletin ISB.53-173 Revision 1, May 19, 2004, as of the effective date of this AD: Do the actions in paragraphs (f)(2)(i), (f)(2)(ii), and (f)(2)(iii) of this AD at the applicable compliance time, and do all applicable repairs and replacements before further flight.
(i) Do an ultrasonic inspection and repair cracking of the forward six bolt bores between the subframe and frame 30 in accordance with paragraph 2.B and Appendix 2 of BAE Systems (Operations) Limited Service Bulletin ISB.53-173, Revision 2, dated March 28, 2006, before the accumulation of 5,400 flight cycles since last inspection, or within 500 flight cycles after the effective date of this AD, whichever occurs later. If the damage exceeds limits specified in the SRM, before further flight, contact BAE Systems and repair. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles, except as provided by paragraph (f)(3) of this AD.
(ii) Do a high frequency eddy current inspection and repair cracking of the forward six bolt bores between the subframe and frame 30 in accordance with paragraph 2.B and Appendix 3 of BAE Systems (Operations) Limited Service Bulletin ISB.53-173, Revision 2, dated March 28, 2006, within 4,000 flight cycles after the effective date of this AD. If the damage exceeds limits specified in the SRM, before further flight, contact BAE systems and repair. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles, except as provided by paragraph (f)(3) of this AD.
(iii) Do a rotating eddy current inspection and repair cracking of the remaining fastener bores between the sub-frame and frame 30 in accordance with paragraph 2.B of BAE Systems (Operations) Limited Service Bulletin ISB.53-173, Revision 2, dated March 28, 2006, and Nondestructive Test Manual (NTM) Part 6 20-00-03, within 4,000 flight cycles after the effective date of this AD. If the damage exceeds limits specified in the SRM, before further flight, contact BAE Systems and repair. Repeat the inspection thereafter at intervals not to exceed 11,900 flight cycles, except as provided by paragraph (f)(3) of this AD.
(3) For all BAe 146-100A and BAe 146-200A series airplanes pre- mod HCM01709B or HCM01709C that have had a replacement aft longeron installed: Prior to the accumulation of 17,000 flight cycles after the
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aft longeron replacement, or within 500 flight cycles after the effective date of this AD, whichever occurs later, inspect for cracking of the forward six bolt bores and the fastener bores between the sub-frame and frame 30, and repair any crack before further flight in accordance with paragraph 2.B of BAE Systems (Operations) Limited Service Bulletin ISB.53-173, Revision 2, dated March 28, 2006. If the damage exceeds limits specified in the SRM, before further flight, contact BAE Systems and repair. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles for the forward six bolt bores, and 11,900 flight cycles for the remaining fastener bores between the sub-frame and frame 30. Replacing the longeron terminates the repetitive inspection requirements of paragraph (f)(1) and (f)(2) of this AD; post- replacement inspections must be done in accordance with this paragraph.
Note 1: The threshold for an aircraft is reset if a replacement longeron is fitted.
(4) For all BAe 146-300A series airplanes pre-mod HCM01709A that have not been inspected in accordance with MRBR SSI/SII Task No. 53- 20-140A (MPD (Maintenance Planning Document) task 532040-SDI-10000- 3) or BAE Systems (Operations) Limited Service Bulletin ISB.53-173, Revision 1, dated May 19, 2004, as of the effective date of this AD: Do the actions in paragraphs (f)(4)(i) and (f)(4)(ii) of this AD at the applicable compliance time, and do all applicable repairs and replacements before further flight.
(i) Inspect and repair cracking of the forward six bolt bores between the subframe and frame 30 in accordance with paragraph 2.B of BAE Systems (Operations) Limited Service Bulletin ISB.53-173, Revision 2, dated March 28, 2006, prior to the accumulation of 24,000 total flight cycles, or within 500 flight cycles after the effective date of this AD, whichever occurs later. If the damage exceeds limits specified in the SRM, before further flight, contact BAE Systems and repair. Repeat the inspection thereafter at intervals not to exceed 4,000 flight cycles, except as provided by paragraph (f)(6) of this AD.
(ii) Inspect and repair cracking of the remaining fastener bores between the sub-frame and frame 30 in accordance with paragraph 2.B of BAE Systems (Operations) Limited Service Bulletin ISB.53-173, Revision 2, dated March 28, 2006, at the later of 24,000 total flight cycles, or within 4,000 flight cycles after the effective date of this AD. If the damage exceeds limits specified in the SRM, before further flight, contact BAE Systems and repair. Repeat the inspection thereafter at intervals not to exceed 11,900 flight cycles, except as provided by paragraph (f)(6) of this AD.
(5) For all BAe 146-300A series airplanes pre-mod HCM01709A that have been inspected in accordance with MRBR SSI/SII Task No. 53-20- 140A (MPD task 532040-SDI-10000-3) or BAE Systems (Operations) Limited Service Bulletin ISB.53-173, Revision 1, May 19, 2004, as of the effective date of this AD: Do the actions in paragraphs (f)(5)(i), (f)(5)(ii), and (f)(5)(iii) of this AD at the applicable compliance time, and do all applicable repairs and replacements before further flight.
(i) Do an ultrasonic inspection and repair cracking of the forward six bores between the subframe and frame 30 in accordance with paragraph 2.B and Appendix 2 of BAE Systems (Operations) Limited Service Bulletin ISB.53-173, Revision 2, dated March 28, 2006, within 4,000 flight cycles since last inspection, or within 500 flight cycles after the effective date of this AD, whichever occurs later. If the damage exceeds limits specified in the SRM, before further flight, contact BAE Systems and repair. Repeat the inspection thereafter at intervals not to exceed 4,000 flight cycles except as provided by paragraph (f)(6) of this AD.
(ii) Do a high frequency eddy current inspection and repair cracking of the forward six bolt bores between the subframe and frame 30 in accordance with paragraph 2.B and Appendix 3 of BAE Systems (Operations) Limited Service Bulletin ISB.53-173, Revision 2, dated March 28, 2006, within 4,000 flight cycles after the effective date of this AD. If the damage exceeds limits specified in the SRM, before further flight, contact BAE Systems and repair. Repeat the inspection thereafter at intervals not to exceed 4,000 flight cycles, except as provided by paragraph (f)(6) of this AD.
(iii) Do a rotating eddy current inspection and repair cracking of the remaining fastener bores between the sub-frame and frame 30 in accordance with paragraph 2.B of BAE Systems (Operations) Limited Service Bulletin ISB.53-173, Revision 2, dated March 28, 2006, and NTM Part 6 20-00-03 within 4,000 flight cycles after the effective date of this AD. If the damage exceeds limits specified in the SRM, before further flight, contact BAE Systems and repair. Repeat the inspection thereafter at intervals not to exceed 11,900 flight cycles, except as provided by paragraph (f)(6) of this AD.
(6) For all BAe 146-300A series airplanes pre-mod HCM01709A that have had a replacement aft longeron installed: Prior to the accumulation of 24,000 flight cycles after the aft longeron replacement, or within 500 flight cycles after the effective date of this AD, whichever occurs later, inspect for cracking of the fastener bores between the sub-frame and frame 30, and repair any crack before further flight in accordance with paragraph 2.B. of BAE Systems (Operations) Limited Service Bulletin ISB.53-173, Revision 2, March 28, 2006. If the damage exceeds limits specified in the SRM, before further flight, contact BAE Systems and repair. Repeat the inspection thereafter at intervals not to exceed 4,000 flight cycles for the forward six bolt bores, and 11,900 flight cycles for the remaining fastener bores between the sub-frame and frame 30. Replacing the longeron terminates the repetitive inspection requirements of paragraph (f)(4) and (f)(5) of this AD; new inspections must be done in accordance with this paragraph.
Note 2:
The threshold for an aircraft is reset if a replacement longeron is fitted.
FAA AD Differences
Note 3: This AD differs from the MCAI and/ or service information as follows: The MCAI specifies doing repetitive inspections until the airplane enters the life extension program (LEP). This program is not defined by the FAA. Operators of airplanes that enter the LEP may request an alternative method of compliance (AMOC) for the repetitive inspections in accordance with the procedures specified in paragraph (g) of this AD.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) AMOCs: The Manager, ANM-116, Transport Airplane Directorate, International Branch, 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, FAA, Transport Airplane Directorate, 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 appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.
(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 EASA Airworthiness Directive 2006-0215, dated July 14, 2006, and BAe Systems (Operations) Limited Service Bulletin ISB.53-173, Revision 2, dated March 28, 2006, for related information.
Issued in Renton, Washington, on December 12, 2007. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. E7-24699 Filed 12-19-07; 8:45 am]
BILLING CODE 4910-13-P
