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

(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 


tkelley on DSK3SPTVN1PROD with RULES
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.govby 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 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations 72567 

• 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: 

ESTIMATED 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 per 

hour = $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: 

ON-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 


tkelley on DSK3SPTVN1PROD with RULES
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 AD 

requires 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. 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations 72569 

(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 


tkelley on DSK3SPTVN1PROD with RULES