Source: https://www.federalregister.gov/documents/2010/02/25/2010-3470/airworthiness-directives-bae-systems-operations-limited-model-atp-airplanes
Timestamp: 2018-09-26 02:42:44
Document Index: 427929451

Matched Legal Cases: ['arts 50', 'art 43', 'art 50', 'arts 50', 'art 43', 'art 50', 'arts 1', '§\u200939']

8467-8471 (5 pages)
Docket No. FAA-2010-0130
Directorate Identifier 2009-NM-087-AD
Amendment 39-16214
AD 2010-05-05
Restatement of Requirements of AD 2006-18-09, With Revised Compliance Method
Restatement of Requirements of AD 2007-15-08, With Revised Compliance Method
https://www.federalregister.gov/d/2010-3470 https://www.federalregister.gov/d/2010-3470
A review of the results of the final fuselage fatigue test identified the need for additional and revised safety-related fatigue- and environmental inspections for the fuselage. These additional tasks were introduced by Service Bulletin (SB) ATP-51-002 * * *.
As it was determined that these inspections were necessary to maintain the structural integrity of the aeroplane, EASA AD 2006-0090 [which corresponds to FAA AD 2007-15-08] was issued * * *.
Since the original Issue of the SB, three revisions have been published. Revision 1 of the SB included only editorial changes. Revision 2 of the SB corrected the fuselage frame designations in Parts 50 and 50A and extended the allowable time before initial inspection. In addition, the repeat inspection interval in Part 43 of the SB was reduced. In the latest Revision 3 of the SB, the grace period for the initial inspection in Part 50 has been clarified.
The unsafe condition is fatigue cracking of certain structural elements, which could result in reduced structural integrity of the airplane and consequent rapid decompression of the airplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of March 12, 2010.
On September 21, 2006 (71 FR 52418, September 6, 2006), the Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD.
Todd Thompson, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1175; fax (425) 227-1149.
On July 15, 2007, we issued AD 2007-15-08, Amendment 39-15137 (72 FR 40230, July 24, 2007). That AD required actions intended to address an unsafe condition on the products listed above.
Since we issued AD 2007-15-08, the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2009-0074, dated March 31, 2009 (referred to after this as “the MCAI”), to correct an unsafe condition for the specified products. The MCAI states:
A review of the results of the final fuselage fatigue test identified the need for additional and revised safety-related fatigue- and environmental inspections for the fuselage. These additional tasks were introduced by Service Bulletin (SB) ATP-51-002, which supplemented and in some cases revised those previously published in the Aircraft Maintenance Manual (AMM) Chapter 05-10-17 and the Maintenance Review Board Report (MRBR).
As it was determined that these inspections were necessary to maintain the structural integrity of the aeroplane, EASA AD 2006-0090 [which corresponds to FAA AD 2007-15-08] was issued to require the inspections and, depending on findings, corrective actions as defined in BAE Systems (Operations) Limited SB ATP-51-002 (the SB) at original issue.
Since the original Issue of the SB, three revisions have been published. Revision 1 of the SB included only editorial changes. Revision 2 of the SB corrected the fuselage frame designations in Parts 50 and 50A and extended the allowable time before initial Start Printed Page 8468inspection. In addition, the repeat inspection interval in Part 43 of the SB was reduced. In the latest Revision 3 of the SB, the grace period for the initial inspection in Part 50 has been clarified.
Fatigue tasks in Parts 1 through 50 of the SB, i.e. those without an “A” suffix, have now been replicated in AMM Chapter 05-10-17 and MRBR Section 6. In addition, environmental tasks, those identified with an “A” suffix, have now been replicated in MRBR Section 6.
For the reasons described above, this AD retains the requirements of EASA AD 2006-0090, which is superseded, and requires the accomplishment of the inspections and, depending on findings, corrective actions as defined in BAE Systems (Operations) Limited SB ATP-51-002 at Revision 3.
The unsafe condition is fatigue cracking of certain structural elements, which could result in reduced structural integrity of the airplane and consequent rapid decompression of the airplane. The corrective actions include repairing cracking and corrosion, and depending on findings, repairing or replacing damaged components. You may obtain further information by examining the MCAI in the AD docket.
BAE SYSTEMS (Operations) Limited has issued Service Bulletin ATP-51-002, Revision 3, dated April 3, 2008. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.
This AD retains all requirements of AD 2007-15-08. Since AD 2007-15-08 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this AD, as listed in the following table:
Requirement in AD 2007-15-08
This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include “Docket No. FAA-2010-0130; Directorate Identifier 2009-NM-087-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.
2. The FAA amends § 39.13 by removing Amendment 39-15137 (
2010-05-05 BAE Systems (Operations) Limited: Amendment 39-16214. Docket No. FAA-2010-0130; Directorate Identifier 2009-NM-087-AD.
(b) This AD supersedes AD 2007-15-08, Amendment 39-15137.
This AD requires revisions to certain operator maintenance documents to include new and revised inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (q) of this AD. The request should include a description of changes to the required inspections that will ensure the continued damage tolerance of the affected structure. The FAA has provided guidance for this determination in Advisory Circular (AC) 25-1529.
(d) Air Transport Association (ATA) of America Code: 51: Standard Practices/Procedures.
The unsafe condition is fatigue cracking of certain structural elements, which could result in reduced structural integrity of the airplane and consequent rapid decompression of the airplane. The corrective actions include repairing cracking and corrosion, and depending on findings, repairing or replacing damaged components.
(g) Within 30 days after February 7, 2001 (the effective date of AD 2000-26-10, Amendment 39-12060, which was superseded by AD 2005-19-03, which was superseded by AD 2007-15-08), revise the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness according to a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. Doing the revision specified in paragraph (h) of this AD replaces Chapters 27, 32, 53, and 54 listed in Section 05-10-11 and Chapters 52, 53, 54, 55, and 57 listed in Section 05-10-17 that are in effect on February 7, 2001, with Chapters 27, 32, 53, and 54 listed in Section 05-10-11, “Mandatory Life Limitations (Airframe)”; and Chapters 52, 53, 54, 55, and 57 listed in Section 05-10-17, “Structurally Significant Items (SSIs)”; both dated July 15, 2004; of the British Aerospace ATP Aircraft Maintenance Manual (AMM). Doing the revision specified in paragraph (l) of this AD replaces Sections 05-10-12, 05-10-15, and 05-10-17 with the corresponding sections specified in paragraph (l) of this AD.
Guidance on revising the ALS can be found in Section 05-00-00, dated August 15, 1997, of the British Aerospace ATP AMM, dated October 15, 1999. This section references other chapters of the AMM. The applicable revision level of the referenced chapters is that in effect on February 7, 2001.
(h) Within 30 days after September 28, 2005 (the effective date of AD 2005-19-03, Amendment 39-14268, which was superseded by AD 2006-18-09), revise the ALS of the Instructions for Continued Airworthiness according to a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. Doing the revision specified in paragraph (i) of this AD replaces certain Chapter 52 and 53 tasks listed in Section 05-10-17, “Structurally Significant Items (SSIs),” dated July 15, 2004, of the British Aerospace ATP AMM, with the corresponding Chapter 52 and 53 tasks listed in BAE SYSTEMS (Operations) Limited Service Bulletin ATP-51-002, dated December 20, 2005. Doing the revision specified in paragraph (l) of this AD replaces Chapters 52, 53, 54, 55, and 57 listed in Section 05-10-17 with the corresponding Section 05-10-17 specified in paragraph (l) of this AD.
Guidance on revising the ALS can be found in Chapters 27, 32, 53, and 54 listed in Section 05-10-11, “Mandatory Life Limitations (Airframe)”; and the tasks for Chapters 52, 53, 54, 55, and 57 listed in Section 05-10-17, “Structurally Significant Items (SSIs)”; both dated July 15, 2004; of the British Aerospace ATP AMM. These chapters replace the corresponding chapters in Section 05-00-00, dated August 15, 1997, of the British Aerospace ATP AMM as specified in paragraph (g) of this AD.
(i) Within 30 days after September 21, 2006 (the effective date of AD 2006-18-09), revise the ALS of the Instructions for Continued Airworthiness by incorporating the new and revised tasks for Chapters 52 and 53 as specified in BAE SYSTEMS (Operations) Limited Service Bulletin ATP-51-002, dated December 20, 2005, into the ALS. The revised Chapter 52 and 53 tasks replace the corresponding Chapter 52 and 53 tasks in Section 05-10-17, “Structurally Significant Items (SSIs),” dated July 15, 2004, of the British Aerospace ATP AMM, as specified in paragraph (h) of this AD.
(j) Except as provided by paragraph (q) of this AD: After the actions specified in paragraphs (g), (h), and (i) of this AD have been accomplished, no alternative inspections or inspection intervals may be approved for the structural elements specified in the documents listed in paragraphs (g), (h), and (i) of this AD.
(k) Although BAE SYSTEMS (Operations) Limited Service Bulletin ATP-51-002, dated December 20, 2005, specifies to submit certain information to the manufacturer, this AD does not include that requirement.
(l) Within 30 days after August 8, 2007 (the effective date of AD 2007-15-08), revise the Start Printed Page 8470ALS of the Instructions for Continued Airworthiness according to a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA.
Guidance on revising the ALS can be found in Section 05-10-12, “Mandatory Life Limitations (Airframe—Structures),” dated January 15, 2007; Section 05-10-15, “Mandatory Life Limitations (Powerplant/Engine/APU—Structures),” dated January 15, 2007; and Section 05-10-17, “Structurally Significant Items (SSIs),” dated January 15, 2007; of the BAE Systems (Operations) Limited ATP AMM. The revised sections replace the corresponding sections specified in paragraphs (g) and (h) of this AD.
(m) Except as provided by paragraph (q) of this AD: After the action specified in paragraph (l) of this AD has been accomplished, no alternative inspections or inspection intervals may be approved for the structural elements specified in the documents listed in paragraph (l) of this AD.
(n) Within 30 days after the effective date of this AD: Revise the ALS of the Instructions for Continued Airworthiness by incorporating the inspections specified in BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ATP-51-002, Revision 3, dated April 3, 2008. Doing this revision terminates the requirements of paragraph (i) of this AD. The revised Chapter 52 and 53 tasks replace the corresponding Chapter 52 and 53 tasks in Section 05-10-17, “Structurally Significant Items (SSIs),” dated July 15, 2004, of the British Aerospace ATP AMM, as specified in paragraph (h) of this AD. Do the initial inspection for fatigue cracking at the applicable time in Part N., “Approval,” of BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ATP-51-002, Revision 3, dated April 3, 2008.
(o) Except as provided by paragraph (q) of this AD: After the action specified in paragraph (n) of this AD has been accomplished, no alternative inspections or inspection intervals may be approved for the structural elements specified in the documents listed in paragraph (n) of this AD.
(p) Submit a report of the findings (both positive and negative) of all of the inspections required by paragraph (n) of this AD to Customer Engineering Liaison, BAE SYSTEMS Regional Aircraft, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland; telephone: +44 (0) 1292 675289; fax: +44 (0) 1292 675432; at the applicable time specified in paragraph (p)(1) or (p)(2) of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane.
(1) Alternative Methods of Compliance (AMOCs): The Manager, 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, 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.
(r) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2009-0074, dated March 31, 2009; and BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ATP-51-002, Revision 3, dated April 3, 2008; for related information.
(s) You must use the service information contained in Table 1 of this AD, as applicable, to do the actions required by this AD, unless the AD specifies otherwise.
BAE SYSTEMS (Operations) Limited Service Bulletin ATP-51-002 3 April 3, 2008.
BAE SYSTEMS (Operations) Limited Service Bulletin ATP-51-002 Original December 20, 2005.
(2) The Director of the Federal Register previously approved the incorporation by reference of the service information contained in Table 3 of this AD on September 21, 2006 (71 FR 52418, September 6, 2006).
[FR Doc. 2010-3470 Filed 2-24-10; 8:45 am]