## 72565 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations

(c) Applicability

This AD applies to Reims Aviation S.A. Model F406 airplanes, serial numbers 0001 through 0098, certificated in any category.

(d) Subject

Air Transport Association of America (ATA) Code 27: Flight Controls.

(e) Reason

This AD was prompted by 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 detachment of the pilot’s rudder control pedal in flight. We are issuing this AD to detect and correct cracking of the pilot rudder control pedal which, if not corrected, could result in detachment of the pedal with possible loss of airplane directional control.

(f) Actions and Compliance

Unless already done, do the actions in paragraphs (f)(1) through (f)(4) of this AD.

(1) Before further flight after August 18, 2015 (the effective date retained from AD 2015–16–07), do a visual inspection and a dye or fluorescent penetrant inspection of the rudder control pedal torque tubes, LH (Part Number (P/N) 5115260–1) and RH (P/N 5115260–2), following the instructions of
PART A of ASI AVIATION Service Bulletin No.: F406–104, dated July 28, 2015.

(2) If no crack is detected during the inspection required by paragraph (f)(1) of this AD, within 100 hours time-in-service (TIS) after August 18, 2015 (the effective date retained from AD 2015–16–07), do a magnetic particle inspection of the rudder control pedal torque tubes, LH (P/N 5115260–1) and RH (P/N 5115260–2), following the instructions of PART B of ASI AVIATION Service Bulletin No.: F406–104, dated July 28, 2015.

(3) If any crack is detected on a rudder control pedal torque tube during the inspection required by paragraph (f)(1) or (f)(2) of this AD, before further flight, replace the affected part with a serviceable part following the instructions of ASI AVIATION Service Bulletin No.: F406–104, dated July

28, 2015.

(4) For the purpose of this AD, a serviceable part is:

(i) A rudder control pedal torque tube (LH P/N 5115260–1 or RH P/N 5115260–2) that has had a magnetic particle inspection following the instructions of PART B of ASI AVIATION Service Bulletin No.: F406–104, dated July 28, 2015, and no cracks were found; or

(ii) A new rudder control pedal torque tube (LH P/N 5115260–1 or RH P/N 5115260–2) that has never been installed on an airplane.

(5) You may install a rudder control pedal torque tube P/N 5115260–1 (LH) or P/N 5115260–2 (RH) on an airplane, provided it is a serviceable part.

(g) Other FAA AD Provisions

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: Albert J. Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4119; fax: (816) 329–4090; email: albert.mercado@faa.gov. 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, 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.

(h) Related Information

Refer to MCAI European Aviation Safety Agency (EASA) AD No.: 2015–0159–E, dated July 31, 2015, and EASA AD No.: 2015– 0159R1, dated August 24, 2015, for related information. You may examine the MCAI on
the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–

2015–3398.

(i) 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 August 18, 2015 (80 FR 49127).

(i) ASI AVIATION Service Bulletin No.: F406–104, dated July 28, 2015.

(ii) Reserved. (4) For service information identified in this AD, contact ASI Aviation, Ae  ́ rodrome de Reims Prunay, 51360 Prunay, FRANCE; telephone: +33 3 26 48 46 65; fax: +33 3 26 49 18 57; email: none; Internet: http://asiaviation.fr/asi-aviation-support/1.html (requires user name and password).

(5) You may view this service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. It
is also available on the Internet at http:// www.regulations.gov by searching for locating Docket No. FAA–2015–3398.

(6) 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 Kansas City, Missouri, on November 6, 2015.
Melvin Johnson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–29200 Filed 11–19–15; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0427; Directorate Identifier 2013–NM–218–AD; Amendment**  **39–18316; AD 2015–22–11]**

**RIN 2120–AA64**



### Airworthiness Directives; Lockheed **Martin Corporation/Lockheed Martin Aeronautics Company Airplanes** 

**AGENCY** 

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

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are superseding Airworthiness Directive (AD) 2011–09– 04 for all Lockheed Martin Corporation/ Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. AD 2011–09–04 required repetitive inspections for damage to the lower surface of the center wing box (CWB), and corrective actions if necessary. This new AD adds related investigative actions, and corrective actions if necessary. This AD was prompted by an evaluation by the design approval holder (DAH) that indicated that the CWB is subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking of the lower surface of the CWB, which could result in structural failure of the wings.

**DATES** 

### : This AD is effective December

28, 2015.

The Director of the Federal Register approved the incorporation by reference


## 72566 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations

of a certain publication listed in this AD as of December 28, 2015.

The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of June 22, 2011 (76 FR 28626, May 18, 2011).

**ADDRESSES** 

### : For service information identified in this AD, contact Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, Airworthiness Office, Dept. 6A0M, Zone 0252, Column P–58, 86 S. Cobb Drive, Marietta, GA 30063; telephone 770–494–5444; fax 770–494–5445; email ams.portal@
lmco.com ; Internet http://
www.lockheedmartin.com/ams/tools/
TechPubs.html. You may view this
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. It is also available on the Internet

at http://www.regulations.gov by searching for and locating Docket No.

FAA–2014–0427.

Examining the AD Docket

You may examine the AD docket on
the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0427; or in person at the Docket 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 (phone: 800–647–5527) is Docket 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**

### : Carl Gray, Aerospace Engineer, Airframe Branch, ACE–117A, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, GA 30337; telephone 404–474–5554; fax 404–474–5605; email: carl.w.gray@ faa.gov.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2011–09–04, Amendment 39–16666 (76 FR 28626, May 18, 2011). AD 2011–09–04 applied to all Lockheed Martin Corporation/ Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. The NPRM published in the Federal Register on July 1, 2014 (79 FR 37248). The NPRM was prompted by an evaluation by the DAH that indicated that the CWB is subject to WFD. The NPRM proposed to continue to require repetitive inspections for any damage of the lower surface of the CWB, and corrective actions if necessary. The NPRM also proposed to require replacement of the CWB, and to add, for the repetitive inspections, concurrent related investigative actions, and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking of the lower surface of the CWB, which could result in structural failure of the wings.

Actions Since Issuance of the NPRM (79 FR 37248, July 1, 2014)

The CWB replacement, proposed in the NPRM (79 FR 37248, July 1, 2014), has been removed from this final rule, and is instead required by AD 2015–18– 02, Amendment 39–18260 (80 FR 52941, September 2, 2015). We determined that the proposed compliance time for the CWB replacement would not adequately address the unsafe condition, because the risk of undetected WFD rises rapidly for CWBs that have accumulated 50,000 total flight hours. Therefore, for airplanes over the 50,000-flight-hour threshold, AD 2015–18–02 provides a shorter grace period than that proposed in the NPRM. In this AD, we have removed paragraph (k) of the proposed AD and Note 1 to paragraph (k) of the proposed AD, and redesignated subsequent paragraphs accordingly.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments to the NPRM (79 FR 37248, July 1, 2014) related to the proposed inspection requirements, and the FAA’s response
to those comments. Since this AD does not include the CWB replacement proposed in paragraph (k) of the NPRM,
this AD does not address comments regarding the CWB replacement. Those
comments are addressed in AD 2015– 18–02, Amendment 39–18260 (80 FR 52941, September 2, 2015).

Support for the NPRM (79 FR 37248, July 1, 2014)

Lynden Air Cargo (Lynden) stated that it concurs that the proposed inspections are beneficial and enhance safety.

Request To Revise Proposed Applicability

Lynden questioned whether the FAA considered the safety risk factor for ‘‘restricted category type certificated Model C–130A through H airplanes’’ and whether those airplanes should be included in the applicability.

We did consider the safety risk factor for those airplanes. The FAA issued restricted-category type certificates only
for Model C–130A and C–130B airplanes, and these are low-usage airplanes. The wings on Model C–130A airplanes are different from those of other models; the CWBs have previously been replaced on all Model C–130A airplanes. There are no civil registered Model C–130B airplanes in service. We might consider further rulemaking for Model C–130 airplanes. We have not changed this AD regarding this issue.

Request To Revise Repair Approval
Procedures

Safair requested that we revise the NPRM (79 FR 37248, July 1, 2014) to authorize the DAH or designated engineering representative (DER) to develop and approve repairs under international operator support agreements with the state-of-registration
civil authorities.

We agree with the commenter’s request. We have revised paragraphs (h), (i)(1)(ii), (j), and (k)(1) of this AD to require that certain repairs, alternative compliance times, and inspection methods be approved in accordance with the procedures specified in paragraph (m) of this AD, which allows DER approval for repairs as specified in new paragraph (m)(3) of this AD.

Request To Require a Report of Inspection Findings

Noting that the NPRM (79 FR 37248, July 1, 2014) would not require inspection reports, Safair suggested that Lockheed build a database of inspection findings. The commenter asserted that
the data would not be collected unless
mandated.

It is not necessary to require operators to report inspection findings, as the
Atlanta Aircraft Certification Office (ACO) already maintains a database for tracking repairs. The database includes repair reports from the U.S. as well as DER reports for airplanes outside of the U.S. We have not changed this AD in this regard.

Conclusion

We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM (79 FR 37248, July 1, 2014) for correcting the unsafe condition; and


## 72567 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations

• Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 37248, July 1, 2014).

We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1

CFR Part 51

We reviewed Lockheed Service Bulletin 382–57–85 (82–790), Revision 3, dated July 8, 2013, including Appendix A, Revision 3, dated July 8, 2013, and Appendixes B, C, D, E, F, and G, all Revision 1, all dated March 8,
2007. The service information describes procedures for inspecting the lower
surface of the CWB. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified
in the **ADDRESSES** 

### section of this AD.

Costs of Compliance

We estimate that this AD affects 15 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators

Inspection [retained action

from AD 2011–09–04, Amendment 39–16666 (76 FR 28626, May 18, 2011)]. 2,000 work-hours × $85 perhour = $170,000 per inspection cycle. N/A $170,000 per inspection cycle $2,550,000 per inspection cycle.



### We have received no definitive data that would enable us to provide cost estimates for the related investigative actions specified in this AD.

We estimate the following costs to do any necessary repair that would be required. We have no way of determining the number of aircraft that might need this repair:



### O N 

### -CONDITION 

### COSTS

Action Labor cost Parts cost Cost per product

Repair [retained from AD 2011–09–04,

Amendment 39–16666 (76 FR 28626, May 18, 2011)]. 1,000 to 3,000 work-hours × $85 per hour = $85,000 to $255,000. $30,000 $115,000 to $285,000.



### 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),

(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.

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) 2011–09–04, Amendment 39–16666 (76 FR 28626, May 18, 2011), and adding the following new AD:

2015–22–11 Lockheed Martin Corporation/ Lockheed Martin Aeronautics Company: Amendment 39–18316; Docket No. FAA–2014–0427; Directorate Identifier

2013–NM–218–AD.

(a) Effective Date

This AD is effective December 28, 2015.

(b) Affected ADs

This AD replaces AD 2011–09–04, Amendment 39–16666 (76 FR 28626, May 18, 2011).

(c) Applicability

This AD applies to all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes, certificated in any category.

(d) Subject

Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

This AD was prompted by an evaluation by the design approval holder (DAH) that indicated the center wing box (CWB) is subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct


## 72568 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations

fatigue cracking of the lower surface of the CWB, which could result in structural failure of the wings.

(f) Compliance

Comply with this AD within the compliance times specified, unless already
done.

(g) Retained Inspection, With Revised
Service Information

This paragraph restates the actions required by paragraph (g) of AD 2011–09–04, Amendment 39–16666 (76 FR 28626, May 18, 2011), with revised service information. At the time specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, whichever occurs latest: Do a nondestructive inspection of the lower surface of the CWB for any damage, in
accordance with Lockheed Service Bulletin 382–57–85 (82–790), Revision 2, dated August 23, 2007, including Appendixes A, B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007; or Lockheed Service Bulletin 382–57–85 (82–790), Revision 3, dated July 8, 2013, including Appendix A, Revision 3, dated July 8, 2013, and Appendixes B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007. Repeat the inspections thereafter at intervals not to exceed 10,000 flight hours. As of the effective date of this AD, use only Lockheed Service Bulletin 382–57–85 (82– 790), Revision 3, dated July 8, 2013, including Appendix A, Revision 3, dated July 8, 2013, and Appendixes B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007, for the actions required by this paragraph.

(1) Prior to the accumulation of 40,000 total flight hours on the center wing.

(2) Within 365 days after June 22, 2011 (the effective date of AD 2011–09–04, Amendment 39–16666 (76 FR 28626, May 18, 2011)).

(3) Within 10,000 flight hours on the CWB after the accomplishment of the inspection specified in paragraph (g) of this AD, if done before June 22, 2011 (the effective date of AD 2011–09–04, Amendment 39–16666 (76 FR 28626, May 18, 2011)).

(h) Retained Corrective Action, With Revised Repair Instructions

This paragraph restates the actions required by paragraph (h) of AD 2011–09–04, Amendment 39–16666 (76 FR 28626, May 18, 2011), with revised repair instructions. If any damage is found before the effective date of this AD during any inspection required by paragraph (g) of this AD: Before further flight, repair any damage, using a method approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA. If any damage is found as of the effective date of this AD, during any inspection required by paragraph (g) of this AD: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (m) of this

AD.

(i) Retained Exceptions to Service Information Specifications, With Revised Repair Instructions

(1) This paragraph restates the exception specified in paragraph (i) of AD 2011–09–04, Amendment 39–16666 (76 FR 28626, May 18, 2011), with revised repair instructions. Lockheed Service Bulletin 382–57–85 (82– 790), Revision 2, dated August 23, 2007, including Appendixes A, B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007, specifies that operators may adjust thresholds and intervals, use alternative repetitive inspection intervals, and use alternative inspection methods, if applicable. However, this AD requires the applicable approval specified in paragraph (i)(1)(i) or (i)(1)(ii) of
this AD.

(i) Before the effective date of this AD: This AD requires that any alternative methods or intervals be approved by the Manager, Atlanta ACO. For any alternative methods or intervals to be approved by the Manager, Atlanta ACO, as required by this paragraph, the Manager’s approval letter must specifically refer to this AD.

(ii) As of the effective date of this AD, this AD requires that any alternative methods or intervals be approved in accordance with the procedures specified in paragraph (m) of this

AD.

(2) This paragraph restates the exception stated in paragraph (j) of AD 2011–09–04, Amendment 39–16666 (76 FR 28626, May 18, 2011), with no changes. Where Lockheed Service Bulletin 382–57–85 (82–790), Revision 2, dated August 23, 2007, including Appendixes A, B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007, specifies that alternative repetitive inspection intervals may be used for cold-worked holes, this AD does not allow the longer interval. This ADrequires that all cold-worked and non-coldworked holes be reinspected at 10,000-flighthour intervals.

(3) This paragraph restates the exception stated in paragraph (k) of AD 2011–09–04, Amendment 39–16666 (76 FR 28626, May 18, 2011), with no changes. Where Lockheed Service Bulletin 382–57–85 (82–790), Revision 2, dated August 23, 2007, including Appendixes A, B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007, describes procedures for submitting a report of any damages, this AD does not require
such action.

(j) New Inspection and Corrective Actions

As of the effective date of this AD, concurrently with accomplishing the inspection required by paragraph (g) of this AD: Do all applicable related investigative actions, in accordance with Appendix A, Revision 3, dated July 8, 2013, of Lockheed Service Bulletin 382–57–85 (82–790), Revision 3, dated July 8, 2013, including Appendix A, Revision 3, dated July 8, 2013, and Appendixes B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007. If any cracking or damage is found during any related investigative action: Before further flight, repair all cracking and damage, using a method approved in accordance with the procedures specified in paragraph (m) of this

AD.

(k) New Exceptions to Service Information Specifications

(1) Lockheed Service Bulletin 382–57–85 (82–790), Revision 3, dated July 8, 2013, including Appendix A, Revision 3, dated July 8, 2013, and Appendixes B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007, specifies that operators may adjust thresholds and intervals, use alternative repetitive inspection intervals, and use alternative inspection methods. However, this AD requires that any alternative thresholds, intervals, or inspection methods be approved in accordance with the procedures specified in paragraph (m) of this AD.

(2) Where Lockheed Service Bulletin 382– 57–85 (82–790), Revision 3, dated July 8, 2013, including Appendix A, Revision 3, dated July 8, 2013, and Appendixes B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007, describes procedures for submitting a report of any damages, this AD does not require such action.

(l) Credit for Previous Actions

(1) This paragraph restates the credit provided in paragraph (l) of AD 2011–09–04, Amendment 39–16666 (76 FR 28626, May 18, 2011). This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before June 22, 2011 (the effective date of AD 2011–09– 04), using Lockheed Service Bulletin 382– 57–85 (82–790), Revision 1, dated March 8, 2007, which is not incorporated by reference
in this AD.

(2) This paragraph restates the credit provided in paragraph (m) of AD 2011–09– 04, Amendment 39–16666 (76 FR 28626, May 18, 2011). This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before June 22, 2011 (the effective date of AD 2011– 09–04), using Lockheed Service Bulletin 382–57–85 (82–790), dated August 4, 2005, which is not incorporated by reference in this

AD.

(m) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Atlanta ACO, 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 manager of the ACO, send it to the attention of the person identified in paragraph (n)(1) of this AD.

(2) 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.

(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by a Delegated Engineering Representative (DER)
for the Lockheed Martin Aeronautics Company who has been authorized by the Manager, Atlanta ACO, to make those findings. For a repair method to be approved, the repair approval must meet the certification basis of the airplane, and the approval must specifically refer to this AD.

(n) Related Information

(1) For more information about this AD, contact Carl Gray, Aerospace Engineer, Airframe Branch, ACE–117A, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, GA 30337; telephone 404–474–5554; fax 404–474–5605; email: carl.w.gray@faa.gov.


## 72569 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations

(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(5) and (o)(6) of this AD.

(o) 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 December 28, 2015.

(i) Lockheed Service Bulletin 382–57–85 (82–790), Revision 3, dated July 8, 2013, including Appendix A, Revision 3, dated July 8, 2013, and Appendixes B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007.

(ii) Reserved. (4) The following service information was approved for IBR on June 22, 2011 (76 FR 28626, May 18, 2011).

(i) Lockheed Service Bulletin 382–57–85 (82–790), Revision 2, dated August 23, 2007, including Appendixes A, B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007.

(ii) Reserved. (5) For Lockheed Martin Corporation/ Lockheed Martin Aeronautics Company service information identified in this AD, contact Lockheed Martin Corporation/ Lockheed Martin Aeronautics Company, Airworthiness Office, Dept. 6A0M, Zone 0252, Column P–58, 86 S. Cobb Drive, Marietta, GA 30063; telephone 770–494– 5444; fax 770–494–5445; email ams.portal@ lmco.com; Internet http://

www.lockheedmartin.com/ams/tools/

TechPubs.html.

(6) You may view this 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.

(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 October

29, 2015. Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–28464 Filed 11–19–15; 8:45 am]

**BILLING CODE 4910–13–P** 

### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–1043; Directorate Identifier 2013–NM–079–AD; Amendment**  **39–18321; AD 2015–23–05]**

**RIN 2120–AA64**



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

**AGENCY** 

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

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for all Airbus Model A330–200, A330–200 Freighter, and A330–300 series airplanes; and Model A340–200 and A340–300 series airplanes. This AD was prompted by reports of cracked support strut body ends at a certain frame
location of the trimmable horizontal stabilizer (THS). This AD requires repetitive inspections for cracking of the strut ends of the THS support located at a certain frame in the tail cone, and replacement if necessary; and
reinstallation or installation of reinforcing clamps on certain strut ends. We are issuing this AD to detect and correct cracked support strut body ends of the THS, which could lead to the loss of all four THS support struts, making the remaining structure unable to carry limit loads, resulting in the loss of the horizontal tail plane.

**DATES** 

### : This AD becomes effective December 28, 2015.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 28, 2015.

**ADDRESSES** 

### : You may examine the AD
docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-1043 or in person at the Docket 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.

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 view this 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. It is also
available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014–

1043.

**FOR FURTHER INFORMATION CONTACT**

### : Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 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 by adding an AD that would apply to all Airbus Model A330–200, A330–200 Freighter, and A330–300 series airplanes; and Model A340–200 and A340–300 series airplanes. The NPRM published in the Federal Register on January 23, 2015 (80 FR 3510). The NPRM was prompted by reports of cracked support strut body
ends at a certain frame location of the THS. The NPRM proposed to require repetitive inspections for cracking of the strut ends of the THS support located at a certain frame in the tail cone, and replacement if necessary; and
reinstallation or installation of reinforcing clamps on certain strut ends. We are issuing this AD to detect and correct cracked support strut body ends of the THS, which could lead to the loss of all four THS support struts, making the remaining structure unable to carry limit loads, resulting in the loss of the horizontal tail plane.

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0068, dated March 18, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus Model A330–200, A330–200 Freighter, and A330–300 series airplanes; and
Model A340–200 and A340–300 series airplanes. The MCAI states:

During scheduled maintenance on A330 aeroplanes, several Trimmable Horizontal Stabilizer (THS) support struts at frame (FR) 91 were found cracked at strut body ends.

The THS is supported and articulated at FR 91 by four struts to fix the hinges (Y-bolts) and keep the structural integrity in lateral
direction.

Analysis revealed that cracks can reduce ability of the support struts to carry specified
tension loads.

This condition, if not detected and corrected, could lead to the loss of all four