
[Federal Register: February 25, 2010 (Volume 75, Number 37)]
[Rules and Regulations]               
[Page 8467-8471]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr25fe10-3]                         

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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).
------------------------------------------------------------------------

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 raebusiness@baesystems.com; 
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

