10168 Federal Register / Vol. 74, No. 45 / Tuesday, March 10, 2009 / Rules and Regulations 

inspection of the stick-pusher servo-cables 

installation and adjustment of the stickpusher cable tension, as necessary. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within 150 hours time-in-service (TIS) 

or 30 days after March 30, 2009 (the effective 

date of this AD), whichever occurs first, 

inspect the stick-pusher servo-cables for 

correct installation, position, and tension in 

accordance with the Accomplishment 

Instructions of PILATUS AIRCRAFT LTD. 

PC12 Service Bulletin No. 27–020, Revision 

No. 1, dated January 30, 2009. 

(2) If any discrepancy is found as a result 

of the inspection required by paragraph (f)(1) 

of this AD, before further flight, do all 

corrective actions in accordance with the 

Accomplishment Instructions of PILATUS 

AIRCRAFT LTD. PC12 Service Bulletin No. 

27–020, Revision No. 1, dated January 30, 

2009. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: The MCAI 

does not supersede the previous MCAI on 

which FAA AD 2008–06–17 was based 

because it was a one-time inspection. For 

consistency within the FAA’s regulatory 

system and to avoid confusion, this AD 

supersedes AD 2008–06–17. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

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: Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4059; fax: (816) 329– 

4090. 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 

(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 

(h) Refer to MCAI European Aviation 

Safety Agency (EASA) AD No.: 2009–0040, 

dated February 20, 2009, and PILATUS 

AIRCRAFT LTD. PC12 Service Bulletin No. 

27–020, Revision No. 1, dated January 30, 

2009, for related information. 

Material Incorporated by Reference 

(i) You must use PILATUS AIRCRAFT 

LTD. PC12 Service Bulletin No. 27–020, 

Revision No. 1, dated January 30, 2009, to do 

the actions required by this AD, unless the 

AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact PILATUS AIRCRAFT LTD., 

Customer Service Manager, CH–6371 

STANS, Switzerland; telephone: +41 (0)41 

619 62 08; fax: +41 (0)41 619 73 11; Internet: 

http://www.pilatus-aircraft.com/, or e-mail: 

SupportPC12@pilatus-aircraft.com. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri on 

February 25, 2009. 

John R. Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–4437 Filed 3–9–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0980; Directorate 

Identifier 2008–NM–008–AD; Amendment 

39–15834; AD 2009–05–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330 Airplanes, and Model A340–200 

and A340–300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Airbus Model 

A330, A340–200, and A340–300 series 

airplanes. That AD currently requires 

repetitive inspections of a certain 

bracket that attaches the flight deck 

instrument panel to the airplane 

structure; related investigative and 

corrective actions if necessary; and 

replacement of the existing bracket with 

a titanium-reinforced bracket, which 

ends the repetitive inspections in the 

existing AD. This new AD adds 

requirements only for airplanes on 

which the existing bracket was replaced 

with a titanium-reinforced bracket in 

accordance with the existing AD. The 

additional requirement is a one-time 

inspection to determine if certain 

fasteners are broken or cracked, and 

corrective actions if necessary. This AD 

results from a report that incorrect 

torque values could damage the bracket. 

We are issuing this AD to prevent a 

cracked bracket. Failure of this bracket, 

combined with failure of the horizontal 

beam, could result in collapse of the left 

part of the flight deck instrument panel, 

and consequent reduced controllability 

of the airplane. 

DATES: This AD becomes effective April 

14, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of April 14, 2009. 

On February 8, 2007 (72 FR 256, 

January 4, 2007), the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the AD. 

ADDRESSES: For service information 

identified in this AD, contact Airbus 

SAS—Airworthiness Office—EAL, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France; fax +33 5 61 93 

45 80, e-mail airworthiness.A330- 

A340@airbus.com. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Document Management Facility 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this AD, the 

regulatory evaluation, any comments 

received, and other information. The 

address for the Docket Office (telephone 

800–647–5527) is the Document 

Management Facility, U.S. Department 

of Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Federal Register / Vol. 74, No. 45 / Tuesday, March 10, 2009 / Rules and Regulations 10169 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2006–26–12, amendment 

39–14870 (72 FR 256, January 4, 2007), 

for certain Airbus Model A330, A340– 

200, and A340–300 series airplanes. AD 

2006–26–12 requires repetitive 

inspections of a certain bracket that 

attaches the flight deck instrument 

panel to the airplane structure; 

replacement of the bracket with a new, 

improved bracket; and related 

investigative and corrective actions if 

necessary. AD 2006–26–12 further 

requires replacement of the existing 

bracket with a titanium-reinforced 

bracket, which ends the repetitive 

inspections. That NPRM was published 

in the Federal Register on September 

17, 2008 (73 FR 53770). That NPRM 

proposed to add requirements only for 

airplanes on which the existing bracket 

was replaced with a titanium-reinforced 

bracket in accordance with the existing 

AD. The additional requirement is a 

one-time inspection to determine if 

certain fasteners are broken or cracked, 

and corrective actions if necessary. 

Explanation of Change to Paragraph (f) 

of This AD 

We have removed the ‘‘Service 

Bulletin Reference’’ paragraph from this 

AD. (That paragraph was identified as 

paragraph (f) in the NPRM.) Instead, we 

have spelled out the service bulletin 

citations throughout this AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We also determined that these changes 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. This AD affects 

about 24 Model A330 series airplanes of 

U.S. registry. There are currently no 

affected Model A340–200 and –300 

series airplanes of U.S. registry. 

However, if one of these airplanes is 

imported and put on the U.S. Register 

in the future, these cost estimates would 

also apply to those airplanes. 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts Cost per airplane Fleet cost 

Inspections (required by AD 2006–26–12) ... 1 $80 $0 $80 per inspection 

cycle.

$1,920 per inspection 

cycle. 

Replacement and investigative actions (required by AD 2006–26–12).9 80 330 $1,050 ....................... $25,200. 

One-time inspection (new action) ................. 2 80 0 $160 .......................... Up to $3,840. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–14870 (72 

FR 256, January 4, 2007) and by adding 

the following new airworthiness 

directive (AD): 

2009–05–10 Airbus: Amendment 39–15834. 

Docket No. FAA–2008–0980; Directorate 

Identifier 2008–NM–008–AD. 

Effective Date 

(a) This AD becomes effective April 14, 

2009. 

Affected ADs 

(b) This AD supersedes AD 2006–26–12. 

Applicability 

(c) This AD applies to all Airbus Model 

A330 airplanes, and Model A340–200 and 

A340–300 series airplanes; certificated in any 

category; except those airplanes identified in 

paragraphs (c)(1), (c)(2), and (c)(3) of this AD. 

(1) Airplanes on which Airbus 

Modification 53446 has been incorporated in 

production. 

10170 Federal Register / Vol. 74, No. 45 / Tuesday, March 10, 2009 / Rules and Regulations 

(2) Model A330 airplanes on which Airbus 

Mandatory Service Bulletin A330–25–3249, 

Revision 01, dated July 10, 2007, has been 

embodied in service. 

(3) Model A340–200 and –300 series 

airplanes on which Airbus Mandatory 

Service Bulletin A340–25–4245, Revision 01, 

dated July 10, 2007, has been embodied in 

service. 

Unsafe Condition 

(d) This AD results from a report that 

incorrect torque values could damage a 

certain bracket that attaches the flight deck 

instrument panel to the airplane structure. 

We are issuing this AD to prevent a cracked 

bracket. Failure of this bracket, combined 

with failure of the horizontal beam, could 

result in collapse of the left part of the flight 

deck instrument panel, and consequent 

reduced controllability of the airplane. 

Compliance 

(e) 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 the Requirements of AD 

2006–26–12 

Initial Inspection 

(f) At the applicable time specified in 

paragraph (f)(1) or (f)(2) of this AD, perform 

a detailed inspection of the bracket having 

part number (P/N) F2511012920000, which 

attaches the flight deck instrument panel to 

the airplane structure, in accordance with 

Airbus Mandatory Service Bulletin A330–25– 

3227 or A340–25–4230, both Revision 01, 

both dated May 3, 2005, as applicable. 

(1) For Model A330 series airplanes: Prior 

to the accumulation of 16,500 total flight 

cycles, or within 60 days after April 25, 2005 

(the effective date of AD 2005–06–08, 

amendment 39–14016, which was 

superseded by AD 2006–26–12), whichever is 

later. 

(2) For Model A340–200 and –300 series 

airplanes: Prior to the accumulation of 9,700 

total flight cycles, or within 2,700 flight 

cycles after April 25, 2005, whichever is 

later. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’ 

No Cracking/Repetitive Inspections 

(g) If no crack is found during the initial 

inspection required by paragraph (f) of this 

AD: Repeat the inspection thereafter at the 

applicable interval specified in paragraph 

(g)(1) or (g)(2) of this AD, in accordance with 

Airbus Mandatory Service Bulletin A330–25– 

3227 or A340–25–4230, both Revision 01, 

both dated May 3, 2005, as applicable, until 

the replacement specified in paragraph (j) of 

this AD has been accomplished. 

(1) For Model A330 series airplanes: 

Intervals not to exceed 13,800 flight cycles. 

(2) For Model A340–200 and –300 series 

airplanes: Intervals not to exceed 7,000 flight 

cycles. 

Crack Found/Replacement and Repetitive 

Inspections 

(h) If any crack is found during any 

inspection required by paragraph (f) or (g) of 

this AD: Do the actions in paragraphs (h)(1) 

and (h)(2) of this AD, except as provided by 

paragraph (i) of this AD, in accordance with 

Airbus Mandatory Service Bulletin A330–25– 

3227 or A340–25–4230, both Revision 01, 

both dated May 3, 2005, as applicable, until 

accomplishment of the replacement required 

by paragraph (j) of this AD. 

(1) Before further flight: Replace the 

cracked bracket with a new, improved 

bracket having P/N F2511012920095, in 

accordance with Airbus Mandatory Service 

Bulletin A330–25–3227 or A340–25–4230, 

both Revision 01, both dated May 3, 2005, as 

applicable. 

(2) Repeat the inspection of the replaced 

bracket as required by paragraph (f) of this 

AD, at the time specified in paragraph 

(h)(2)(i) or (h)(2)(ii) of this AD. Then, do 

repetitive inspections or replace the bracket 

as specified in paragraph (g) or (h) of this AD, 

as applicable. 

(i) For Model A330 series airplanes: Within 

16,500 flight cycles after replacing the 

bracket. 

(ii) For Model A340–200 and –300 series 

airplanes: Within 9,700 flight cycles after 

replacing the bracket. 

(i) If both flanges of a bracket are found 

broken during any inspection required by 

this AD: Before further flight, replace the 

bracket as specified in paragraph (h) of this 

AD and perform any applicable related 

investigative and corrective actions (which 

may include inspections for damage to 

surrounding structure caused by the broken 

bracket, and corrective actions for any 

damage that is found), in accordance with a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent). 

Replacement of Brackets/Investigative and 

Corrective Actions 

(j) Except as required by paragraph (h)(1) 

of this AD: Within 72 months after February 

8, 2007 (the effective date of AD 2006–26– 

12), replace existing brackets having P/N 

F2511012920000 or P/N F2511012920095 

with titanium-reinforced brackets having P/N 

F2511305220096; and perform any related 

investigative and corrective actions (which 

may include detailed inspections for cracking 

of the bracket or damage to surrounding 

structure caused by a broken bracket, and 

applicable corrective actions for any damage 

that is found); in accordance with Airbus 

Service Bulletin A330–25–3249 or A340–25– 

4245, both dated May 3, 2005; or Airbus 

Mandatory Service Bulletin A330–25–3249 

or A340–25–4245, both Revision 01, both 

dated July 10, 2007; as applicable. After the 

effective date of this AD, use only Revision 

01 of Airbus Mandatory Service Bulletin 

A330–25–3249 or A340–25–4245, both dated 

July 10, 2007; as applicable. If any crack is 

found, before further flight, repair in 

accordance with Airbus Service Bulletin 

A330–25–3249 or A340–25–4245, both dated 

May 3, 2005; or Airbus Mandatory Service 

Bulletin A330–25–3249 or A340–25–4245, 

both Revision 01, both dated July 10, 2007; 

as applicable. After the effective date of this 

AD, use only Revision 01 of Airbus 

Mandatory Service Bulletin A330–25–3249 

or A340–25–4245, both dated July 10, 2007; 

as applicable. Replacement of the affected 

bracket with a titanium-reinforced bracket 

having P/N F2511305220096 ends the 

repetitive inspections required by paragraph 

(g) or (h) of this AD. Although Airbus Service 

Bulletin A330–25–3249 and A340–25–4245, 

both dated May 3, 2005; and Airbus 

Mandatory Service Bulletin A330–25–3249 

and A340–25–4245, both Revision 01, both 

dated July 10, 2007; specify to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

New Requirements of This AD 

One-time Inspection 

(k) For airplanes on which the actions 

required by paragraph (j) of this AD have 

been accomplished before the effective date 

of this AD: At the applicable time in 

paragraph (k)(1) or (k)(2) of this AD, remove 

the fasteners of the titanium-reinforced 

bracket and, if a fastener is broken, do a 

detailed inspection for cracking of the 

horizontal beam. Do all applicable corrective 

actions before further flight. Do all actions in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–25–3249 or A340–25–4245, 

both Revision 01, both dated July 10, 2007, 

as applicable. Where Airbus Mandatory 

Service Bulletin A330–25–3249 or A340–25– 

4245, both Revision 01, both dated July 10, 

2007, specifies to contact Airbus, before 

further flight, repair in accordance with a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the EASA (or 

its delegated agent). 

(1) For Model A330 series airplanes: Prior 

to the accumulation of 16,500 total flight 

cycles, or within 20 months after the effective 

date of this AD, whichever occurs first. 

(2) For Model A340–200 and –300 series 

airplanes: Prior to the accumulation of 12,400 

total flight cycles, or within 20 months after 

the effective date of this AD, whichever 

occurs first. 

Actions Accomplished According to 

Previous Issue of Service Bulletins 

(l) This AD provides credit for actions 

performed in accordance with the service 

bulletins identified in paragraphs (1)(1) and 

(l)(2) of this AD. 

(1) Accomplishing the actions specified in 

paragraphs (f), (g), and (h) of this AD before 

February 8, 2007, in accordance with Airbus 

Service Bulletin A330–25–3227 or A340–25– 

4230, both including Appendix 01, both 

dated June 17, 2004, as applicable, is 

acceptable for compliance with the 

requirements of those paragraphs. 

(2) Accomplishing the actions specified in 

paragraphs (j) and (k) of this AD before the 

Federal Register / Vol. 74, No. 45 / Tuesday, March 10, 2009 / Rules and Regulations 10171 

effective date of this AD in accordance with 

Airbus Mandatory Service Bulletin A330–25– 

3249 or A340–25–4245, both dated May 3, 

2005, as applicable, is acceptable for 

compliance with the requirements of those 

paragraphs. 

Alternative Methods of Compliance 

(AMOCs) 

(m)(1) The Manager, International Branch, 

ANM–116, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. Send 

information to ATTN: Vladimir Ulyanov, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1138; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) AMOCs approved previously in 

accordance with AD 2006–26–12 are 

approved as AMOCs for the corresponding 

provisions of this AD. 

Related Information 

(n) EASA airworthiness directives 2007– 

0281 and 2007–0282, both dated November 

6, 2007, also address the subject of this AD. 

Material Incorporated by Reference 

(o) You must use the service information 

contained in Table 1 of this AD to do the 

actions required by this AD, as applicable, 

unless the AD specifies otherwise. 

TABLE 1—ALL MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Airbus Mandatory Service Bulletin A330–25–3249 .............................................................................. Revision 01 ................... July 10, 2007. 

Airbus Mandatory Service Bulletin A340–25–4245 .............................................................................. Revision 01 ................... July 10, 2007. 

Airbus Service Bulletin A330–25–3227, excluding Appendix 01 ......................................................... Revision 01 ................... May 3, 2005. 

Airbus Service Bulletin A330–25–3249 ................................................................................................ Original .......................... May 3, 2005. 

Airbus Service Bulletin A340–25–4230, excluding Appendix 01 ......................................................... Revision 01 ................... May 3, 2005. 

Airbus Service Bulletin A340–25–4245 ................................................................................................ Original .......................... May 3, 2005. 

(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 

Airbus Mandatory Service Bulletin A330–25–3249 .............................................................................. Revision 01 ................... July 10, 2007. 

Airbus Mandatory Service Bulletin A340–25–4245 .............................................................................. Revision 01 ................... July 10, 2007. 

(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 February 

8, 2007 (72 FR 256, January 4, 2007). 

TABLE 3—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE

Document Revision Date 

Airbus Service Bulletin A330–25–3227, excluding Appendix 01 ......................................................... Revision 01 ................... May 3, 2005. 

Airbus Service Bulletin A330–25–3249 ................................................................................................ Original .......................... May 3, 2005. 

Airbus Service Bulletin A340–25–4230, excluding Appendix 01 ......................................................... Revision 01 ................... May 3, 2005. 

Airbus Service Bulletin A340–25–4245 ................................................................................................ Original .......................... May 3, 2005. 

(3) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; fax +33 5 61 

93 45 80, e-mail airworthiness.A330- 

A340@airbus.com. 

(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, February 

20, 2009. 

Ali Bahrami 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–4649 Filed 3–9–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 73 

[Docket No. FAA–2009–0108; Airspace 

Docket No. 08–ASW–8] 

RIN 2120–AA66 

Change of Using Agency for Restricted 

Area 6320; Matagorda, TX 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action changes the using 

agency of R–6320, Matagorda, TX, from 

United States Customs Service’’ to 

‘‘Continental North American