## 37523 Federal Register / Vol. 74, No. 144 / Wednesday, July 29, 2009 / Rules and Regulations

It was found one occurrence of a fuel booster pump circuit br[e]aker opening during an engine maintenance servicing. An inspection inside the fuel tank revealed the fuel booster pump[’]s electrical harness chafing against its body, causing the loss of the electrical wiring protection and resulting in a short circuit. Further in-tank inspections have showed other fuel booster pump electrical harnesses chafing either with the pump body and/or with adjacent fuel lines, causing damage to the harness protective layers and resulting * * * [in a] possible ignition source inside the fuel tank.


### * * * * * The corrective actions include revising the Limitations section of the airplane flight manual (AFM) to include a minimum fuel quantity, adding a minimum fuel quantity limitation for operation of the fuel booster pump, inspecting the fuel booster pump electrical harness of the left- and right-hand fuel tanks for damage, replacing any fuel booster pump assembly having a damaged electrical harness, installing clamps on the tank structure, and installing tie down straps for the fuel booster pump electrical harness.
Actions and Compliance

(f) Unless already done, do the following actions.

(1) Within 30 days after the effective date of this AD, insert in the Limitations section of the AFM a copy of this AD or the following statement:

The minimum fuel quantity inside each tank must be 300 kg (662 pounds) or 370 liters (97.75 gallons).

(2) As of the effective date of this AD, any fuel tank defueling or other maintenance action which demands use of the fuel booster pumps is limited to a minimum fuel quantity of no less than 300 kilograms (662 pounds) or 370 liters (97.75 gallons) inside the respective tank.

(3) Within 4,000 flight hours, or 24 months, or at the next scheduled or unscheduled fuel tank opening after the effective date of this AD, whichever occurs first, do the following actions:

(i) Inspect the fuel booster pump electrical harness of the left- and right-hand fuel tanks for damage on its external protection, in accordance with paragraph 3.F. (Part I) of the Accomplishment Instructions of Embraer Service Bulletin 120–28–0016, dated January 9, 2008. If any damaged fuel booster pump electrical harness is found, before further flight, replace the affected fuel booster pump assembly with another fuel booster pump assembly bearing the same part number, in accordance with the Accomplishment Instructions of Embraer Service Bulletin 120– 28–0016, dated January 9, 2008.

(ii) Install clamps and tie down straps on the tank structure and attach each fuelbooster pump electrical harness to the leftand right-hand fuel tanks to avoid eventual chafing against the pump body, adjacent fuel lines, structure or any other part, and to prevent damage to the harness protective layers, in accordance with paragraph 3.G. (Part II) of the Accomplishment Instructions of Embraer Service Bulletin 120–28–0016, dated January 9, 2008. (4) After complying with the actions in paragraphs (f)(3)(i) and (f)(3)(ii) of this AD, the limitations imposed by paragraphs (f)(1) and (f)(2) of this AD are no longer required, and the AFM revision required by paragraph (f)(1) of this AD may be removed from the AFM.

FAA AD Differences

Note: This AD differs from the MCAI and/ or service information as follows: No differences.

Other FAA AD Provisions

(g) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1405; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

(3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056.

Related Information

(h) Refer to MCAI Brazilian Airworthiness Directive 2008–05–01, effective June 13, 2008; and Embraer Service Bulletin 120–28– 0016, dated January 9, 2008; for related information.
Material Incorporated by Reference

(i) You must use Embraer Service Bulletin 120–28–0016, dated January 9, 2008, 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 Empresa Brasileira de Aeronautica S.A. (EMBRAER), Technical Publications Section (PC 060), Av. Brigadeiro Faria Lima, 2170—Putim—12227–901 Sa  ̃ o Jose dos Campos—SP—BRASIL; telephone: +55 12 3927–5852 or +55 12 3309–0732; fax: +55 12 3927–7546; e-mail: distrib@embraer.com.br; Internet: http:// www.flyembraer.com. (3) 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.

(4) 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 July 13,
2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–17534 Filed 7–28–09; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2009–0211; Directorate Identifier 2008–NM–028–AD; Amendment**  **39–15980 AD 2009–15–17]**

**RIN 2120–AA64**



### Airworthiness Directives; Airbus Model **A330–200, A330–300, A340–200, and A340–300 Series Airplanes** 

**AGENCY** 

### : Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for the products listed above. 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:

* * * * *

[B]ogie beam internal paint has been degraded, leading to a loss of cadmium plating and thus allowing development of corrosion pitting.

If not corrected, this situation under higher speed could result in the aircraft departing the runway or in the bogie [beam] detaching from the aircraft or [main landing] gear collapses, which would constitute an unsafe condition.


### * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.

**DATES** 

### : This AD becomes effective September 2, 2009.


## 37524 Federal Register / Vol. 74, No. 144 / Wednesday, July 29, 2009 / Rules and Regulations

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 2, 2009.

**ADDRESSES** 

### : You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC.

**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** 

### :

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on March 10, 2009 (74 FR 10199). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

The operator of an A330 aircraft (which has a common bogie beam with the A340) has reported a fracture of the RH (right-hand) MLG (main landing gear) Bogie Beam whilst turning during low speed taxi maneuvers. The bogie [beam] fractured aft of the pivot point and remained attached to the sliding tube by the brake torque reaction rods. After this RH bogie [beam] failure, the aircraft continued for approximately 40 meters on the forks of the sliding member before coming to rest on the taxiway without any passenger injury.

The preliminary investigations revealed that this event was due to corrosion pitting occurring on the bore of the bogie beam. Investigations are ongoing to determine why bogie beam internal paint has been degraded, leading to a loss of cadmium plating and thus allowing development of corrosion pitting.

If not corrected, this situation under higher speed could result in the aircraft departing the runway or in the bogie [beam] detaching from the aircraft or [main landing] gear collapses, which would constitute an unsafe condition.

To enable early detection and repair of any corrosion of the internal surfaces, EASA (European Aviation Safety Agency) AD 2007– 0314 required a one-time inspection on all MLG Bogie Beams except Enhanced MLG Bogie Beams and the reporting of the results to AIRBUS.

The Revision 1 of AD 2007–0314 aimed to clarify the compliance time of the inspection and to extend the reporting period.

The present AD which supersedes the AD 2007–0314R1:
—Takes over the AD 2007–0314R1

requirements and —Reduces the inspection threshold from 6 to

4.5 years due to significant findings on the inspected aircraft. 

### Required actions include applying protective treatments to the bogie beam and corrective actions. Corrective actions include repair of any damaged or corroded surfaces or surfacetreatments, and contacting MessierDowty for repair instructions and doing the repair. You may obtain further information by examining the MCAI in the AD docket.

Comments

We gave the public the opportunity to participate in developing this AD. We considered the comments received. Request To Revise References to the French Export Certificate in the NPRM

Airbus requests that we revise the phrase ‘‘French export certificate of airworthiness’’ that is specified in paragraphs (f)(2), (f)(2)(i), (f)(3), and (f)(3)(i) of the NPRM. Airbus states that there is no more ‘‘French’’ export airworthiness certificate and states that it has been replaced with the EASA export airworthiness certificate. We agree to revise paragraphs (f)(2), (f)(2)(i), (f)(3), and (f)(3)(i) of this AD for the reason provided by the commenter. We have replaced the phrase ‘‘French export certificate of airworthiness’’ with ‘‘French or EASA export certificate of airworthiness.’’ Request To Revise Compliance Time Specified in Paragraphs (f)(3)(i) and (f)(3)(ii) of the NPRM

Airbus requests that we revise the compliance time specified in paragraphs (f)(3)(i) and (f)(3)(ii) of the NPRM to include the additional phrase ‘‘or at the next scheduled bogie beam overhaul, whichever occurs first.’’

We disagree with revising the compliance time, ‘‘within 18 months after the effective date of this AD,’’ specified in paragraphs (f)(3)(i) and (f)(3)(ii) of this AD to include the additional phrase. The requested change would shorten the compliance time for certain operators. In developing an appropriate compliance time, we considered the safety implications and normal maintenance schedules for timely accomplishment of the required actions. We determined that the compliance time represents an appropriate interval in which the actions required by this AD can be done, in a timely manner within the fleet, while still maintaining an adequate level of safety. Operators are always permitted to accomplish the requirements of an AD at a time earlier than the specified compliance time. If additional data are presented that would justify a shorter compliance time, we might consider further rulemaking on this issue. We have not revised this AD in this regard.

New Relevant Service Information

Airbus and Messier-Dowty have issued the service information described in the following table.



### N EW 

### S ERVICE 

### I NFORMATION

Service Bulletin Revision Date

Airbus Mandatory Service Bulletin A330–32–3225, including Appendix 1 ................................................. 01 October30, 2008. Airbus Mandatory Service Bulletin A340–32–4268, including Appendix 1 ................................................. 01 October30, 2008. Messier-Dowty Service Bulletin A33/34–32–271, including Appendixes A and B ...................................... 1 November 16, 2007. Messier-Dowty Service Bulletin A33/34–32–272, including Appendixes A, B, C, and D ........................... 1 September 22, 200 8.



### We referred to earlier revisions of the service bulletins in the NPRM, as described in the following table.



### S ERVICE 

### I NFORMATION 

### S PECIFIED IN THE 

### NPRM

Service Bulletin Date

Airbus Mandatory Service Bulletin A330–32–3225, including Appendix 01 .......................................................... ................. November 21, 2007.


## 37525 Federal Register / Vol. 74, No. 144 / Wednesday, July 29, 2009 / Rules and Regulations

S ERVICE 

### I NFORMATION 

### S PECIFIED IN THE 

### NPRM—Continued

Service Bulletin Date

Airbus Mandatory Service Bulletin A340–32–4268, including Appendix 01 .......................................................... ................. November 21, 2007. Messier-Dowty Service Bulletin A33/34–32–271, including Appendix A ............................................................. ................... September 13, 2007. Messier-Dowty Service Bulletin A33/34–32–272, including Appendixes A, B, C, and D .............................................. ......... November 16, 2007.



### The new service information does not add work for airplanes on which the actions specified in the earlier revisions of the service bulletins have been accomplished.

Revision 01 of Airbus Mandatory Service Bulletins A330–32–3225 and A340–32–4268 revises references to Messier-Dowty Service Bulletin A33/ 34–32–272. We have revised paragraphs (f)(1) and (h) of this AD to refer to Revision 01 of Airbus Mandatory Service Bulletins A330–32–3225 and A340–32–4268. We have also added Airbus Mandatory Service Bulletins A330–32–3225 and A340–32–4268, both dated November 21, 2007, to paragraph (f)(6) of this AD to give credit for actions done in accordance with these service bulletins before the effective date of this AD.

Revision 1 of Messier-Dowty Service Bulletin A33/34–32–271 provides a new illustration and updates the procedures. We have revised paragraphs (f)(5) and (h) of this AD to refer to Revision 1 of Messier-Dowty Service Bulletin A33/ 34–32–271. We have also added Messier-Dowty Service Bulletin A33/ 34–32–271, including Appendix A, dated September 13, 2007, to paragraph (f)(6) of this AD to give credit for actions done in accordance with that service bulletin before the effective date of this AD.

Revision 1 of Messier-Dowty Service Bulletin A33/34–32–272 provides new illustrations and updates the procedures. We have revised paragraphs (f)(1)(i), (f)(1)(ii), and (h), and Note 1 ofthis AD to refer to Revision 1 of MessierDowty Service Bulletin A33/34–32–272. We have also added Messier-Dowty Service Bulletin A33/34–32–272, including Appendixes A, B, C, and D, dated November 16, 2007, to paragraph (f)(6) of this AD to give credit for actions done in accordance with that service bulletin before the effective date of this AD.

Conclusion

We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of the AD.

Differences Between This AD and the MCAI or Service Information

We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.

We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD.
Costs of Compliance

We estimate that this AD will affect 29 products of U.S. registry. We alsoestimate that it will take about 22 workhours per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $51,040, or $1,760 per product.
Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of 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. 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 the NPRM, 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. 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.


## 37526 Federal Register / Vol. 74, No. 144 / Wednesday, July 29, 2009 / Rules and Regulations

**§ 39.13 [Amended]**

■ 

### 2. The FAA amends § 39.13 by adding the following new AD:

2009–15–17 Airbus: Amendment 39–15980. Docket No. FAA–2009–0211; Directorate Identifier 2008–NM–028–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective September 2, 2009.

Affected ADs

(b) None.
Applicability

(c) This AD applies to Airbus Model A330– 200, A330–300, A340–200, and A340–300 series airplanes; certificated in any category; all certified models; all serial numbers, except those on which Airbus modification 54500 has been embodied in production or Airbus Service Bulletin A330–32–3212 has been embodied in service.
Subject

(d) Air Transport Association (ATA) of America Code 32: Landing Gear.

Reason

(e) The mandatory continuing airworthiness information (MCAI) states:

The operator of an A330 aircraft (which has a common bogie beam with the A340) has reported a fracture of the RH (right-hand) MLG (main landing gear) Bogie Beam whilst turning during low speed taxi maneuvers. The bogie [beam] fractured aft of the pivot point and remained attached to the sliding tube by the brake torque reaction rods. After this RH bogie [beam] failure, the aircraft continued for approximately 40 meters on the forks of the sliding member before coming to rest on the taxiway without any passenger injury.

The preliminary investigations revealed that this event was due to corrosion pitting occurring on the bore of the bogie beam. Investigations are ongoing to determine why bogie beam internal paint has been degraded, leading to a loss of cadmium plating and thus allowing development of corrosion pitting.

If not corrected, this situation under higher speed could result in the aircraft departing the runway or in the bogie [beam] detaching from the aircraft or [main landing] gear collapses, which would constitute an unsafe condition.

To enable early detection and repair of any corrosion of the internal surfaces, EASA (European Aviation Safety Agency) AD 2007– 0314 required a one-time inspection on all MLG Bogie Beams except Enhanced MLG Bogie Beams and the reporting of the results to AIRBUS.

The Revision 1 of AD 2007–0314 aimed to clarify the compliance time of the inspection and to extend the reporting period.

The present AD which supersedes the AD 2007–0314R1:
—Takes over the AD 2007–0314R1

requirements and —Reduces the inspection threshold from 6 to 4.5 years due to significant findings on the inspected aircraft. Required actions include applying protective treatments to the bogie beam and corrective actions. Corrective actions include repair of any damaged or corroded surfaces or surface treatments, and contacting Messier-Dowty for repair instructions and doing the repair.
Actions and Compliance

(f) Unless already done, do the following actions.

(1) At the applicable compliance time specified in paragraph (f)(2) or (f)(3) of this AD: Clean the internal bore and perform a detailed visual inspection of internal surfacesof the MLG bogie beam (right-hand and lefthand) for any damage to the protective treatments or any corrosion, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–32– 3225 or A340–32–4268, both Revision 01, both dated October 30, 2008; as applicable.

(i) If no damage and corrosion is found, before further flight, apply the protective treatments of the bogie beam, in accordance with the Accomplishment Instructions of Messier-Dowty Service Bulletin A33/34–32– 272, Revision 1, including Appendixes A, B, C, and D, dated September 22, 2008.

(ii) If any damage or corrosion is found, before further flight, do all applicable corrective actions and apply the protective treatments of the bogie beam, in accordance with the Accomplishment Instructions of Messier-Dowty Service Bulletin A33/34–32– 272, Revision 1, including Appendixes A, B, C, and D, dated September 22, 2008.

(2) For airplanes with 54 months or less time-in-service since the date of issuance of the original French airworthiness certificate or the date of issuance of the original French or EASA export certificate of airworthiness as of the effective date of this AD: At the latest of the applicable times specified in paragraphs (f)(2)(i), (f)(2)(ii), and (f)(2)(iii) of this AD, do the actions required by paragraph (f)(1) of this AD.

(i) Not before 54 months since the date of issuance of the original French airworthiness certificate or the date of issuance of the original French or EASA export certificate of airworthiness, but no later than 72 months since the date of issuance of the original French airworthiness certificate or the date of issuance of the original French or EASA export certificate of airworthiness.

(ii) Not before 54 months since the installation of a new bogie beam in-service before the effective date of this AD, but no later than 72 months since the installation of a new bogie beam in-service before the effective date of this AD.

(iii) Not before 54 months since the last overhaul of a bogie beam before the effective date of this AD, but no later than 72 months since the last overhaul of a bogie beam before the effective date of this AD.

(3) For airplanes with more than 54 months time-in-service since the date of issuance of the original French airworthiness certificate or the date of issuance of the original French or EASA export certificate of airworthiness as of the effective date of this AD: At the applicable time specified in paragraph (f)(3)(i), (f)(3)(ii), f)(3)(iii), (f)(3)(iv), or (f)(3)(v) of this AD, do the actions required by paragraph (f)(1) of this AD.

(i) For airplanes on which the bogie beam has not been replaced or overhauled since the date of issuance of the original French airworthiness certificate or the date of issuance of the original French or EASA export certificate of airworthiness as of the effective date of this AD: Within 18 months after the effective date of this AD.

(ii) For airplanes on which the bogie beam has been replaced in-service with a new bogie beam and the new bogie beam has more than 54 months time-in-service as of the effective date of this AD: Within 18 months after the effective date of this AD.

(iii) For airplanes on which the bogie beam has been replaced in-service with a new bogie beam and the new bogie beam has 54 months or less time-in-service as of the effective date of this AD: Not before 54 months since the installation of a new bogie beam in-service before the effective date of this AD, but no later than 72 months sincethe installation of a new bogie beam inservice before the effective date of this AD.

(iv) For airplanes on which the bogie beam has been overhauled and the overhauledbogie beam has more than 54 months timein-service as of the effective date of this AD: Within 18 months after the effective date of this AD, or at the next scheduled bogie beam overhaul, whichever occurs first.

(v) For airplanes on which the bogie beam has been overhauled and the overhauledbogie beam has 54 months or less time-inservice as of the effective date of this AD: Not before 54 months since the last overhaul of a bogie beam before the effective date of this AD, but no later than 72 months since the last overhaul of a bogie beam before the effective date of this AD.

(4) Within 30 days after accomplishment of the inspection required by paragraph (f)(1) of this AD or within 30 days after the effective date of this AD, whichever occurs later, report the results, including no findings, to Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; e-mail airworthiness.A330-A340@airbus.com

.

(5) Actions accomplished in accordance with Messier-Dowty Service Bulletin A33/ 34–32–271, Revision 1, including Appendixes A and B, dated November 16, 2007, are considered acceptable for compliance with the corresponding requirements of this AD.

(6) Actions accomplished before the effective date of this AD in accordance with the service bulletins specified in Table 1 of this AD are considered acceptable for compliance with the corresponding requirements of this AD.


## 37527 Federal Register / Vol. 74, No. 144 / Wednesday, July 29, 2009 / Rules and Regulations

T ABLE 

### 1—C REDIT 

### S ERVICE 

### I NFORMATION

Service Bulletin Date

Airbus Mandatory Service Bulletin A330–32–3225 ................................................................................. ................................ November 21, 2007. Airbus Mandatory Service Bulletin A340–32–4268 ................................................................................. ................................ November 21, 2007. Messier-Dowty Service Bulletin A33/34–32–271, including Appendix A ............................................................. ................... September 13, 2007. Messier-Dowty Service Bulletin A33/34–32–272, including Appendixes A, B, C, and D .............................................. ......... November 16, 2007.

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service information as follows: The MCAI specifies repair and corrective actions in accordance with Airbus Mandatory Service Bulletin A330–32–3225 or A340–32– 4268, both dated November 21, 2007; however, these Airbus service bulletins do not describe those actions. Paragraphs (f)(1)(i) and (f)(1)(ii) of this AD specify repair and corrective actions in accordance with Messier-Dowty Service Bulletin A33/34–32– 272, Revision 1, including Appendixes A, B, C, and D, dated September 22, 2008.

Other FAA AD Provisions

(g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

(3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056.

Related Information

(h) Refer to EASA Airworthiness Directive 2008–0093, dated May 20, 2008, and the service bulletins specified in Table 2 of this AD, for related information.



### T ABLE 

### 2—S ERVICE 

### I NFORMATION

Service Bulletin Revision Date

Airbus Mandatory Service Bulletin A330–32–3225, including Appendix 1 ................................................. 01 October30, 2008. Airbus Mandatory Service Bulletin A340–32–4268, including Appendix 1 ................................................. 01 October30, 2008. Messier-Dowty Service Bulletin A33/34–32–271, including Appendixes A and B ...................................... 1 November 16, 2007. Messier-Dowty Service Bulletin A33/34–32–272, including Appendixes A, B, C, and D ........................... 1 September 22, 200 8.

Material Incorporated by Reference

(i) You must use the service information contained in Table 3 of this AD to do the actions required by this AD, unless the AD specifies otherwise.



### T ABLE 

### 3—M ATERIAL 

### I NCORPORATED BY 

### R EFERENCE

Service Bulletin Revision Date

Airbus Mandatory Service Bulletin A330–32–3225, including Appendix 1 ................................................. 01 October30, 2008. Airbus Mandatory Service Bulletin A340–32–4268, including Appendix 1 ................................................. 01 October30, 2008. Messier-Dowty Service Bulletin A33/34–32–271, including Appendixes A and B ...................................... 1 November 16, 2007. Messier-Dowty Service Bulletin A33/34–32–272, including Appendixes A, B, C, and D ........................... 1 September 22, 200 8.

(Pages identified as ‘‘intentionally blank’’ in the Messier-Dowty service bulletins identified in Table 3 of this AD are at the revision level and date specified in Table 3 for those documents.)

(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 Airbus 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 ; Internet http://www.airbus.com . For MessierDowty service information identified in this AD, contact Messier Services Americas, Customer Support Center, 45360 Severn Way, Sterling, Virginia 20166–8910; telephone 703–450–8233; fax 703–404–1621;
Internet https://techpubs.services.messierdowty.com

.

(3) 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.

(4) 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 July 2,

2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–17539 Filed 7–28–09; 8:45 am]

**BILLING CODE 4910–13–P**