[Federal Register Volume 75, Number 37 (Thursday, February 25, 2010)]
[Rules and Regulations]
[Pages 8467-8471]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-3470]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0130; Directorate Identifier 2009-NM-087-AD;
Amendment 39-16214; AD 2010-05-05]
RIN 2120-AA64
Airworthiness Directives; BAE SYSTEMS (Operations) Limited Model
ATP Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above that would supersede an existing AD. This 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:
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.
DATES: This AD becomes effective March 12, 2010.
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.
We must receive comments on this AD by April 12, 2010.
ADDRESSES: You may send comments by any of the following methods:
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 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, 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
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
[[Page 8468]]
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.
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.
Relevant Service Information
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.
FAA's Determination and Requirements of This 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 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.
There are no products of this type currently registered in the
United States. However, this rule is necessary to ensure that the
described unsafe condition is addressed if any of these products are
placed on the U.S. Register in the future.
Differences Between the 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 required 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 AD.
Change to Existing AD
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:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in this
Requirement in AD 2007-15-08 AD
------------------------------------------------------------------------
paragraph (f) paragraph (g).
paragraph (g) paragraph (h).
paragraph (h) paragraph (i).
paragraph (i) paragraph (j).
paragraph (j) paragraph (k).
paragraph (k) paragraph (l).
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FAA's Determination of the Effective Date
Since there are currently no domestic operators of this product,
notice and opportunity for public comment before issuing this AD are
unnecessary.
Comments Invited
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.
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 AD.
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 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 this AD:
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.
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.
[[Page 8469]]
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-15137 (72 FR
40230, July 24, 2007) and adding the following new AD:
2010-05-05 BAE Systems (Operations) Limited: Amendment 39-16214.
Docket No. FAA-2010-0130; Directorate Identifier 2009-NM-087-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective March
12, 2010.
Affected ADs
(b) This AD supersedes AD 2007-15-08, Amendment 39-15137.
Applicability
(c) This AD applies to all BAE Systems (Operations) Limited
Model ATP airplanes, certificated in any category.
Note 1: 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.
Subject
(d) Air Transport Association (ATA) of America Code: 51:
Standard Practices/Procedures.
Reason
(e) The mandatory continued airworthiness information (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
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.
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.
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 2006-18-09, With Revised Compliance
Method
Airworthiness Limitations Revision Specified in AD 2000-26-10
(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.
Note 2: 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.
Airworthiness Limitations Specified in AD 2005-19-03
(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.
Note 3: 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.
New and Revised Airworthiness Limitations in AD 2006-18-09
(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.
No Reporting Required
(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.
Restatement of Requirements of AD 2007-15-08, With Revised Compliance
Method
Revised Limitations
(l) Within 30 days after August 8, 2007 (the effective date of
AD 2007-15-08), revise the
[[Page 8470]]
ALS of the Instructions for Continued Airworthiness according to a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA.
Note 4: 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.
New Requirements of This AD
Actions
(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) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
FAA AD Differences
Note 5: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(q) The following provisions also apply to this AD:
(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.
(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 (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(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.
Material Incorporated by Reference
(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.
Table 1--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
BAE SYSTEMS (Operations) Limited 3................................ April 3, 2008.
Service Bulletin ATP-51-002.
BAE SYSTEMS (Operations) Limited Original......................... December 20, 2005.
Service Bulletin ATP-51-002.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of the service information contained in
Table 2 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.
Table 2--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
BAE SYSTEMS (Operations) Limited Service 3 April 3, 2008.
Bulletin ATP-51-002.
----------------------------------------------------------------------------------------------------------------
(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).
Table 3--Material Previously Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
BAE SYSTEMS (Operations) Limited Original......................... December 20, 2005.
Service Bulletin ATP-51-002.
----------------------------------------------------------------------------------------------------------------
[[Page 8471]]
(3) For service information identified in this AD, contact BAE
SYSTEMS Regional Aircraft, 13850 McLearen Road, Herndon, Virginia
20171; telephone 703-736-1080; e-mail [email protected];
Internet http://www.baesystems.com/Businesses/RegionalAircraft/index.htm.
(4) 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.
(5) 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on February 16, 2010.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-3470 Filed 2-24-10; 8:45 am]
BILLING CODE 4910-13-P