## 31386 Federal Register / Vol. 78, No. 101 / Friday, May 24, 2013 / Rules and Regulations

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–1163; Directorate Identifier 2011–NM–246–AD; Amendment**  **39–17456; AD 2013–10–03]**

**RIN 2120–AA64**



### Airworthiness Directives; Airbus **Airplanes**

**AGENCY** 

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

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are superseding an existing airworthiness directive (AD) for
all Airbus Model A330–200 and –300 series airplanes; and Model A340–200, –300, –500, and –600 series airplanes. That AD currently requires a one-time detailed inspection of both main landing gear (MLG) bogie beams in the region of the bogie stop pad for detection of deformation and damage, and corrective actions if necessary. This
new AD adds Model A330–200 Freighter series airplanes to the applicability. For certain airplanes, this new AD also adds repetitive inspections for damage and corrosion of the sliding piston sub-assembly, with new related investigative and corrective actions. This AD was prompted by reports of corroded bogie stop pads, including some with cracking. We are issuing this
AD to detect and correct deformation or damage under the bogie stop pad of both MLG bogie beams, which could result in a damaged bogie beam and consequent
detachment of the beam from the airplane or collapse of the MLG and departure of the airplane from the

runway.

**DATES** 

### : This AD becomes effective June

28, 2013.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 28, 2013.

The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of March 4, 2010 (75 FR 4477, January 28, 2010).

**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 November 16, 2012 (77 FR 68711), and proposed to supersede AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010). That NPRM proposed to correct an unsafe condition for the specified products. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community has issued EASA Airworthiness Directive 2011–0211, dated October 31, 2011 (referred to after this as ‘‘the MCAI’’), to supersede EASA AD 2008–0223, dated December 15, 2008 (referred to in the existing AD),
and correct an unsafe condition for the specified products. The MCAI states:

During a scheduled maintenance inspection on the MLG [main landing gear], the bogie stop pad was found deformed and cracked. Upon removal of the bogie stop pad for replacement, the bogie beam was also
found cracked.

Laboratory investigation indicates that an overload event has occurred and no fatigue propagation of the crack was evident.

A second bogie beam crack has subsequently been found on another aeroplane, located under a bogie stop pad which only had superficial paint damage.

This condition, if not detected and corrected, could result in the aeroplane departing the runway or to the bogie detaching from the aeroplane or gear collapses, which would all constitute unsafe conditions at speeds above 30 knots.

As a precautionary measure, EASA AD 2008–0223 [which corresponds to FAA AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010] required one-time detailed inspections under the bogie stop pad of both MLG bogie beams and, in case deformation or damage is detected, to apply the associated repair.

Numerous bogie stop pad were found
corroded and a few cracked as a result of the one-time inspection required by EASA AD 2008–0223 on A330, A340–200 and A340– 300 aeroplanes.

For the reasons describe above, this [EASA] AD, which supersedes EASA AD

2008–0223: —retains the initial inspection requirement

of EASA AD 2008–0223 for A330, A340– 200 and A340–300 aeroplanes. —introduces a repetitive detailed visual

inspection for A330, A340–200 and A340– 300 aeroplanes. —retains the requirement of EASA AD 2008–

0223 for A340–500 and A340–600 aeroplanes, for which further mandatory requirements might follow in future depending on the results of the one-time mandatory inspection in place. 

### The required actions include repetitive detailed inspections for damage andcorrosion of the sliding piston subassembly, with new related investigative
and corrective actions. Related investigative actions include a test for indications of corrosion and damage to the bogie assembly base material, and a magnetic particle inspection for cracks, corrosion, and damage of the bogie
beam. Corrective actions include repairing affected parts. You may obtain further information by examining the
MCAI in the AD docket.

Revised Service Information

Since we issued the NPRM (77 FR 68711, November 16, 2012), we have reviewed the following revised service
information. No additional work is specified by these revisions.

• Airbus Mandatory Service Bulletin A330–32–3220, Revision 02, dated December 13, 2012 (for Model A330– 200 and –300 series airplanes).

• Airbus Mandatory Service Bulletin A330–32–3248, Revision 01, including Appendix 1, dated December 13, 2012 (for Model A330–200, –200 Freighter, and –300 series airplanes).

We have revised paragraphs (i) and (j)
of this AD to refer to the revised service information, added a new paragraph (l) to give credit for earlier revisions of this service information, and re-identified subsequent paragraphs accordingly.

Comments

We gave the public the opportunity to participate in developing this AD. We
considered the comment received.

Request To Remove or Revise Reporting Requirement

Delta Air Lines, Inc. (Delta) asked that the compliance time for the reporting requirement specified in the NPRM (77 FR 68711, November 16, 2012) be extended from 30 to 180 days. Delta stated that, unless we plan to rescind or
revise this AD in the near future based on the findings, paragraph (l)(1) of the NPRM (paragraph (m)(1) of the final rule) should be removed. Delta also recommended that the reporting be mandated only for positive findings— not positive and negative findings—and specifically for those findings that are beyond the repair limits identified in the applicable component maintenance
manual. Delta stated that this would allow findings to be batched together for a grouped report and would preclude undue compliance issues related to late reporting.


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We do not agree to remove the reporting requirement in paragraph (m) of this AD. The reporting requirement is included in the requirements in the EASA AD, and our AD follows those requirements in order to ensure that the unsafe condition is adequately addressed. Reporting of both positive and negative findings is necessary to determine the scope of the problem. Reporting all findings will allow the
manufacturer to conduct statistical analyses and apply the results to
calculate more accurate life limits for the affected parts. We have made no change to the AD in this regard.

In addition, we do not agree to extend the compliance time for the reporting requirement to 180 days; however, we will extend it to 90 days to be consistent with the compliance time for the reporting requirement in the EASA AD referred to in this AD. We have changed the compliance time for the reporting requirement in paragraph (m) of this AD accordingly.

Conclusion

We reviewed the available data, including the comment received, 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

Based on the service information, we
estimate that this AD affects about 67 products of U.S. registry.

The actions that are required by AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010), and retained in this AD take about 2 work-hours per product, at an average labor rate of $85 per work hour. Based on these figures, the estimated cost of the currently required actions is $170 per product.

We estimate that it will take about 16 work-hours per product to comply with the new basic requirements of this AD.The average labor rate is $85 per workhour. Based on these figures, we
estimate the cost of the AD on U.S. operators to be $91,120, or $1,360 per product.

We have received no definitive data that will enable us to provide cost
estimates for the on-condition actions specified in 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 that 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);

3. Will not affect intrastate aviation in Alaska; and

4. 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 (77 FR 68711, November 16, 2012), 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.

**§ 39.13 [Amended]**

■ 

### 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010), and adding the following new AD:

2013–10–03 Airbus: Amendment 39–17456. Docket No. FAA–2012–1163; Directorate
Identifier 2011–NM–246–AD.

(a) Effective Date

This airworthiness directive (AD) becomes effective June 28, 2013.

(b) Affected ADs

This AD supersedes AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010).

(c) Applicability

This AD applies to all Airbus Model A330–
201, –202, –203, –223, –223F, –243, –243F,
–301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; Model A340–211, –212, –213, –311, –312, –313 airplanes; and Model A340–541 and –642 airplanes; certificated in any category; all serial
numbers.

(d) Subject

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

(e) Reason

This AD was prompted by reports of corroded bogie stop pads, some with cracking. We are issuing this AD to detect and correct deformation or damage under the bogie stop pad of both main landing gear (MLG) bogie beams, which could result in a damaged bogie beam and consequent detachment of the beam from the airplane or collapse of the MLG and departure of the airplane from the runway.

(f) Compliance

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

(g) Retained One-Time Inspection and Corrective Actions, With Revised Service
Information

This paragraph restates the requirements of paragraph (f)(1) of AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010), with revised service information.
For Model A330–200 and –300 series airplanes, and Model A340–200, –300, –500, and –600 series airplanes, except as required


## 31388 Federal Register / Vol. 78, No. 101 / Friday, May 24, 2013 / Rules and Regulations

by paragraph (i) of this AD: At the applicable compliance time specified in paragraph (g)(1), (g)(2), (g)(3), (g)(4), (g)(5), or (g)(6) of this AD, perform one-time detailed inspections of both MLG bogie beams in the region of the bogie stop pad for detection of deformation and damage, and apply the applicable corrective actions, in accordance with the Accomplishment Instructions of the applicable service bulletin specified in paragraph (g)(7) of this AD. Do all applicable corrective actions before further flight.

(1) Airplanes with 22 months or less and 2,500 flight cycles or less from the first flight with the original bogie beam as of March 4, 2010 (the effective date of AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010)): Not earlier than 2,500 flight cycles or 22 months on the original bogie beam, whichever occurs first, but not later than 40 months from first flight.

(2) Airplanes with 22 months or less and 2,500 flight cycles or less from the installation date of a new bogie beam in service as of March 4, 2010 (the effective date of AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010)): Not earlier than 2,500 flight cycles or 22 months from the installation date of the new bogie beam, whichever occurs first, but not later than 40
months from the installation date of a new bogie beam in service.

(3) Airplanes with 22 months or less and 2,500 flight cycles or less from the installation date of an overhauled bogie beam in service as of March 4, 2010 (the effective date of AD 2010–02–10, Amendment 39– 16181 (75 FR 4477, January 28, 2010)): Not earlier than 2,500 flight cycles or 22 months
from the installation date of the overhauled bogie beam in service, whichever occurs first,
but not later than 40 months from the installation date of the overhauled bogie
beam in service.

(4) Airplanes with more than 22 months or more than 2,500 flight cycles from the first flight with the original bogie beam, as of March 4, 2010 (the effective date of AD 2010– 02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010)): Within 18 months after March 4, 2010 (the effective date of AD 2010– 02–10).

(5) Airplanes with more than 22 months or more than 2,500 flight cycles from the installation date of a new bogie beam in service, as of March 4, 2010 (the effective date of AD 2010–02–10, Amendment 39– 16181 (75 FR 4477, January 28, 2010)): Within 18 months after March 4, 2010 (the effective date of AD 2010–02–10).

(6) Airplanes with more than 22 months or more than 2,500 flight cycles from the installation date of an overhauled bogie beam in service, as of March 4, 2010 (the effective date of AD 2010–02–10, Amendment 39– 16181 (75 FR 4477, January 28, 2010)): Within 18 months after March 4, 2010 (the effective date of AD 2010–02–10).

(7) Use the applicable service information to accomplish the actions required by paragraph (g) of this AD.

(i) For Model A330–200 and –300 series airplanes: Airbus Mandatory Service Bulletin A330–32–3220, dated October 10, 2008; Revision 01, dated October 5, 2011; or Revision 02, dated December 13, 2012. (ii) For Model A340–200 and –300 series airplanes: Airbus Mandatory Service Bulletin A340–32–4264, dated October 10, 2008.

(iii) For Model A340–500 and –600 series airplanes: Airbus Mandatory Service Bulletin A340–32–5087, dated October 10, 2008.

(h) Retained Reporting Requirement

This paragraph restates the requirements of paragraph (f)(2) of AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010). Report the results of the inspection required by paragraph (g) of this AD, including no findings, to Airbus, Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France; Attn:
SEDCC1 Technical Data and Documentation Services; fax (+33) 5 61 93 28 06; email sb.reporting@airbus.com ; at the applicable time specified in paragraph (h)(1) or (h)(2) of
this AD.

(1) If the inspection is done on or after March 4, 2010 (the effective date of AD 2010– 02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010)): Submit the report within 30 days after doing the inspection.

(2) If the inspection was done prior to March 4, 2010 (the effective date of AD 2010– 02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010)): Submit the report within 30 days after March 4, 2010 (the effective date of AD 2010–02–10).

(i) New Inspections of Beams That Have Not Been Inspected As of the Effective Date of
This AD

For bogie beams on which the inspection required by paragraph (g) of this AD has not been accomplished as of the effective date of this AD: At the later of the times specified in paragraphs (i)(1) and (i)(2) of this AD, perform one-time detailed inspections of both MLG bogie beams in the region of the bogie stop pad for detection of deformation and damage, and apply the applicable corrective actions, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (i)(3) of this AD. Do all applicable corrective actions before further flight.

(1) At the applicable time specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD.

(i) For bogie beams that have not been overhauled: Not earlier than 2,500 flight cycles or 22 months, whichever occurs first, on a bogie beam since its first flight on an airplane since new, but not later than 40 months since its first flight on an airplane

since new.

(ii) For bogie beams that have been overhauled: Not earlier than 2,500 flight cycles or 22 months, whichever occurs first, on a bogie beam since its first flight on an airplane after its most recent overhaul, but not later than 40 months since its first flight on an airplane after its most recent overhaul.

(2) Within 90 days after the effective date
of this AD.

(3) Use the applicable service information specified in paragraph (i)(3)(i), (i)(3)(ii), or (i)(3)(iii) of this AD, to accomplish the actions required by paragraph (i) of this AD.

(i) For Model A330–200 and –300 series airplanes: Airbus Mandatory Service Bulletin A330–32–3220, Revision 02, dated December

13, 2012. (ii) For Model A340–200 and –300 series airplanes: Airbus Mandatory Service Bulletin A340–32–4264, dated October 10, 2008.

(iii) For Model A340–500 and –600 series airplanes: Airbus Mandatory Service Bulletin A340–32–5087, dated October 10, 2008.

(j) New Repetitive Inspections

Except for bogie beams that have been inspected as specified in Airbus Mandatory
Service Bulletin A340–32–5087: At the later of the times specified in paragraphs (j)(1) and (j)(2) of this AD, do the detailed inspection of both MLG bogie beams in the bogie stop pad area for damage and corrosion, and all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–32–3248, Revision 01, dated December 13, 2012 (for Model A330–200, –200 Freighter, and –300 series airplanes); or Airbus Mandatory Service Bulletin A340–32–4286, dated October 5, 2011 (for Model A340–200 and –300 series airplanes); except as required by paragraph (k) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at intervals not to exceed 2,500 flight cycles or 24 months, whichever is first.

(1) Within 2,500 flight cycles or 24 months, whichever occurs first, accumulated by a MLG bogie beam since its first flight after the most recent accomplishment of Airbus Mandatory Service Bulletin A330–32–3220 or A340–32–4264, as applicable.

(2) Within 3 months after the effective date
of this AD.

(k) Service Information Exception

If any cracking of the bogie beam is detected during any inspection or repair required by paragraph (j) of this AD, or any repair required by paragraph (j) of this AD is beyond the maximum repair allowance specified in the applicable service information required by paragraph (j) of this AD: Before further flight, repair using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent).

(l) Credit for Previous Actions

This paragraph provides credit for the actions specified in paragraphs (i) and (j) of this AD, if those actions were performed before the effective date of this AD using Airbus Mandatory Service Bulletin A330–32– 3220, dated October 10, 2008, or Airbus Mandatory Service Bulletin A330–32–3220, Revision 01, dated October 5, 2011; or Airbus Mandatory Service Bulletin A330–32–3248, dated October 5, 2011; as applicable; which are not incorporated by reference in this AD.

(m) New Reporting Requirement

Report the results of the initial inspection required by paragraph (j) of this AD, including both positive and negative findings, to Airbus, Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France; Attn: SEDCC1 Technical Data and Documentation Services; fax (+33) 5 61 93 28 06; email sb.reporting@airbus.com; at the applicable


## 31389 Federal Register / Vol. 78, No. 101 / Friday, May 24, 2013 / Rules and Regulations

time specified in paragraph (m)(1) or (m)(2)
of this AD.

(1) If the inspection is done on or after the effective date of this AD: Submit the report within 90 days after doing the inspection.

(2) If the inspection was done prior to the effective date of this AD: Submit the report within 90 days after the effective date of this

AD.

(n) Other FAA AD Provisions

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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it 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. Information may be emailed to: 9- ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. AMOCs approved previously in accordance with AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010), are approved as AMOCs for the corresponding provisions of 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: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information collection is 2120–0056. Public reporting for
this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing, and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer,

AES–200. (o) Special Flight Permits
Special flight permits, as described in
Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed if any crack is found during any inspection required by this

AD.

(p) Related Information

(1) Refer to mandatory continued airworthiness information (MCAI) EASA Airworthiness Directive 2011–0211, dated October 31, 2011, and the service information specified in paragraphs (p)(1)(i) through (p)(1)(vii) of this AD, for related information.

(i) Airbus Mandatory Service Bulletin A330–32–3220, dated October 10, 2008.

(ii) Airbus Mandatory Service Bulletin A330–32–3220, Revision 01, dated October 5,

2011.

(iii) Airbus Mandatory Service Bulletin A330–32–3220, Revision 02, dated December

13, 2012.

(iv) Airbus Mandatory Service Bulletin A330–32–3248, Revision 01, including Appendix 01, dated December 13, 2012.

(v) Airbus Mandatory Service Bulletin A340–32–4264, dated October 10, 2008.

(vi) Airbus Mandatory Service Bulletin A340–32–4286, dated October 5, 2011.

(vii) Airbus Mandatory Service Bulletin A340–32–5087, dated October 10, 2008.

(2) For service information identified in this AD, contact Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;

Internet http://www.airbus.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

(q) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.

(3) The following service information was approved for IBR on June 28, 2013.

(i) Airbus Mandatory Service Bulletin A330–32–3220, Revision 01, dated October 5,

2011.

(ii) Airbus Mandatory Service Bulletin A330–32–3220, Revision 02, dated December

13, 2012.

(iii) Airbus Mandatory Service Bulletin A330–32–3248, Revision 01, including Appendix 01, dated December 13, 2012.

(iv) Airbus Mandatory Service Bulletin A340–32–4286, dated October 5, 2011.

(4) The following service information was approved for IBR on March 4, 2010 (75 FR 4477, January 28, 2010).

(i) Airbus Mandatory Service Bulletin A330–32–3220, dated October 10, 2008.

(ii) Airbus Mandatory Service Bulletin A340–32–4264, dated October 10, 2008.

(iii) Airbus Mandatory Service Bulletin A340–32–5087, dated October 10, 2008. (5) For service information identified in this AD, contact Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;

Internet http://www.airbus.com.

(6) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

(7) You may view this 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/cfr/ibrlocations.html.

Issued in Renton, Washington, on May 13,

2013. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2013–11903 Filed 5–23–13; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0855; Directorate Identifier 2011–NM–136–AD; Amendment**  **39–17452; AD 2013–09–10]**

**RIN 2120–AA64**



### Airworthiness Directives; The Boeing **Company Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are superseding an existing airworthiness directive (AD) for all The Boeing Company Model 737– 100, –200, –200C, –300, –400, and –500 series airplanes. That AD currently requires repetitive inspections to detect cracking of the lower corners of the door
frame and cross beam of the forward cargo door, and corrective actions if necessary. That AD also requires
eventual modification of the outboard
radius of the lower corners of the door
frame and reinforcement of the cross beam of the forward cargo door, which terminates the existing repetitive inspections. This new AD revises the compliance times for the preventive modification; adds certain inspections
for cracks in the number 5 cross beam of the forward cargo door; and adds inspections of the number 4 cross beam
if cracks are found in the number 5 cross beam, and corrective actions if necessary. For certain airplanes, this