Federal Register / Vol. 79, No. 141 / Wednesday, July 23, 2014 / Rules and Regulations 42655 

(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. 

(i) Airbus Service Bulletin A320–57–1149, 

Revision 01, dated February 12, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

(4) You may view this 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. 

(5) 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 June 25, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–16535 Filed 7–22–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1028; Directorate 

Identifier 2013–NM–068–AD; Amendment 

39–17901; AD 2014–14–06] 

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 A318–111 and –112 

airplanes; Model A319–111, –112, –113, 

–114, and –115 airplanes; Model A320– 

111, –211, –212, and –214 airplanes; 

and Model A321–111, –112, –211, –212, 

and –213 airplanes. This AD was 

prompted by reports of broken aft 

engine mount retainers. This AD 

requires inspecting the aft engine mount 

retainers for surface finish, and for 

cracks and failure, and replacement if 

necessary. We are issuing this AD to 

prevent failure of retainer brackets of 

the aft engine mount and consequent 

loss of the locking feature of the nuts of 

the inner and outer pins; loss of the pins 

will result in the aft mount engine link 

no longer being secured to the aft engine 

mount. 

DATES: This AD becomes effective 

August 27, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 27, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://www.

regulations.gov/#!docketDetail;D=FAA2013-1028; 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 Airbus service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. 

For Goodrich Corporation service 

information identified in this AD, 

contact Goodrich Corporation, 

Aerostructures, 850 Lagoon Drive, Chula 

Vista, CA 91910–2098; telephone 619– 

691–2719; email jan.lewis@

goodrich.com; Internet http://www.

goodrich.com/TechPubs. 

You may view this 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. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

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 A318–111 

and –112 airplanes; Model A319–111, 

–112, –113, –114, and –115 airplanes; 

Model A320–111, –211, –212, and –214 

airplanes; and Model A321–111, –112, 

–211, –212, and –213 airplanes. The 

NPRM published in the Federal 

Register on December 18, 2013 (78 FR 

76572). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0050, 

dated March 5, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

During in-service inspections, several aft 

engine mount retainers, fitted on aeroplanes 

equipped with CFM56–5/5B engines, have 

been found broken. 

The results of the investigations highlight 

that two different types of surface finish have 

been applied (respectively bright and dull 

material finishes), and that dull finish 

adversely affects the strength of the retainer 

with regard to fatigue properties of the part. 

The pins which attach the engine link to the 

aft mount are secured by two nuts, which do 

not have a self-locking feature; this function 

is provided by the retainer brackets. In case 

of failure of the retainer bracket, the locking 

feature of the nuts of the inner and outer pins 

is lost; as a result, these nuts could 

subsequently become loose. 

In case of full loss of the nuts, there is the 

potential to also lose the pins, in which case 

the aft mount link will no longer be secured 

to the aft engine mount. The same locking 

feature is used for the three link assemblies 

of the aft mount. 

For the reasons described above, this [EASA] 

AD requires a one-time detailed visual 

inspection (DVI) of the aft engine mount to 

identify the affected dull finish retainers [and 

for cracks and failure] and replace these 

[retainers] with serviceable retainers. This 

[EASA] AD also prohibits installation of any 

dull finish aft engine mount retainers. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/#!documentDetail;

D=FAA-2013-1028-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

The following presents the comment 

received on the NPRM (78 FR 76572, 

December 18, 2013) and the FAA’s 

response to the comment. 

Request To Add Certain Retainer 

Brackets 

Mr. Michael Raphael stated that 

understanding of the issue (cracking or 

failure of the aft engine mount retainer) 

has changed since the preliminary 

discovery with dull brackets, and that 

bright brackets have been detected with 

the same issue. Mr. Raphael explained 

that vibration is the root cause, and the 

dull surface finish (with pitting) is a 

potential aggravating factor. Mr. Raphael 

also stated that EASA and its airplane 

type certificate holder are preparing a 

‘‘phase 2 containment’’ that is based on 

the latest technical findings. 

We infer that the commenter wants us 

to add brackets with the bright surface 

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42656 Federal Register / Vol. 79, No. 141 / Wednesday, July 23, 2014 / Rules and Regulations 

finish to this AD. We acknowledge that 

potential concerns with the bright 

brackets have been identified and are 

being investigated. However, we 

disagree to delay this final rule, since 

we have determined that an unsafe 

condition exists and that expanding the 

applicability of this AD to include 

retainer brackets with a bright surface 

finish would require additional 

rulemaking. We find that delaying this 

action would be inappropriate in light 

of the identified unsafe condition. Once 

we complete a thorough risk assessment 

of brackets with a bright surface, we 

might consider additional rulemaking. 

We have not changed this final rule in 

this regard. 

Changes to This Final Rule 

We have revised paragraphs (i)(2) and 

(j) of this final rule by removing the 

term ‘‘serviceable.’’ These changes are 

made to avoid ambiguity and 

misinterpretation of type of finish on 

the replacement retainer. We do not 

want operators to polish affected 

retainers as a method of compliance 

with this final rule. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In the NPRM (78 FR 76572, December 

18, 2013), we proposed to prevent the 

use of repairs that were not specifically 

developed to correct the unsafe 

condition, by requiring that the repair 

approval provided by the State of 

Design Authority or its delegated agent 

specifically refer to this FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, we proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

proposed AD. 

No comments were provided to the 

NPRM (78 FR 76572, December 18, 

2013) about these proposed changes. 

However, a comment was provided for 

another NPRM, Directorate Identifier 

2012–NM–101–AD (78 FR 78285, 

December 26, 2013), in which the 

commenter stated the following: ‘‘The 

proposed wording, being specific to 

repairs, eliminates the interpretation 

that Airbus messages are acceptable for 

approving minor deviations (corrective 

actions) needed during accomplishment 

of an AD mandated Airbus service 

bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed 

that paragraph and retitled it 

‘‘Contacting the Manufacturer.’’ This 

paragraph now clarifies that for any 

requirement in this AD to obtain 

corrective actions from a manufacturer, 

the action must be accomplished using 

a method approved by the FAA, the 

European Aviation Safety Agency 

(EASA), or Airbus’s EASA DOA. 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

are EASA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

Other commenters to the NPRM 

discussed previously, Directorate 

Identifier 2012–NM–101–AD (78 FR 

78285, December 26, 2013), pointed out 

that in many cases the foreign 

manufacturer’s service bulletin and the 

foreign authority’s MCAI might have 

been issued some time before the FAA 

AD. Therefore, the DOA might have 

provided U.S. operators with an 

approved repair, developed with full 

awareness of the unsafe condition, 

before the FAA AD is issued. Under 

these circumstances, to comply with the 

FAA AD, the operator would be 

required to go back to the 

manufacturer’s DOA and obtain a new 

approval document, adding time and 

expense to the compliance process with 

no safety benefit. 

Based on these comments, we 

removed the requirement that the DAHprovided repair specifically refer to this 

AD. Before adopting such a 

requirement, the FAA will coordinate 

with affected DAHs and verify they are 

prepared to implement means to ensure 

that their repair approvals consider the 

unsafe condition addressed in this AD. 

Any such requirements will be adopted 

through the normal AD rulemaking 

process, including notice-and-comment 

procedures, when appropriate. We also 

have decided not to include a generic 

reference to either the ‘‘delegated agent’’ 

or ‘‘DAH with State of Design Authority 

design organization approval,’’ but 

instead we have provided the specific 

delegation approval granted by the State 

of Design Authority for the DAH in the 

Contacting the Manufacturer paragraph 

of this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

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Federal Register / Vol. 79, No. 141 / Wednesday, July 23, 2014 / Rules and Regulations 42657 

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 (78 FR 

76572, December 18, 2013) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 76572, 

December 18, 2013). 

Costs of Compliance 

We estimate that this AD affects 851 

airplanes of U.S. registry. 

We also estimate that it will take 

about 3 work-hours per inspection cycle 

(for two engines) per product to comply 

with the basic requirements of this AD. 

The average labor rate is $85 per workhour. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $217,005 per inspection 

cycle (for two engines), or $255 per 

inspection cycle per product (for two 

engines). 

In addition, we estimate that any 

necessary follow-on actions will take 

about 1 work-hour and require parts 

costing $10,000, for a cost of $10,085 

per engine. We have no way of 

determining the number of aircraft that 

might need these actions. 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://www.regulations.

gov/#!docketDetail;D=FAA-2013-1028; 

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 street address for the 

Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

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 adding 

the following new airworthiness 

directive (AD): 

2014–14–06 Airbus: Amendment 39–17901. 

Docket No. FAA–2013–1028; Directorate 

Identifier 2013–NM–068–AD. 

(a) Effective Date 

This AD becomes effective August 27, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1) through (c)(4) 

of this AD, certificated in any category, all 

manufacturer serial numbers. 

(1) Airbus Model A318–111 and –112 

airplanes. 

(2) Airbus Model A319–111, –112, –113, 

–114, and –115 airplanes. 

(3) Airbus Model A320–111, –211, –212, 

and –214 airplanes. 

(4) Airbus Model A321–111, –112, –211, 

–212, and –213 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Powerplant. 

(e) Reason 

This AD was prompted by reports of 

broken aft engine mount retainers. We are 

issuing this AD to prevent failure of retainer 

brackets of the aft engine mount and 

consequent loss of the locking feature of the 

nuts of the inner and outer pins. Loss of the 

pins will result in the aft mount engine link 

no longer being secured to the aft engine 

mount. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Within 3 months after the effective date of 

this AD: Do a detailed inspection of the aft 

engine mount retainers for surface finish 

(dull or bright), and for cracks and failure, in 

accordance with Section 4.2.2, ‘‘Inspection 

Requirements,’’ of Airbus Alert Operators 

Transmission (AOT) A71N001–12, Rev. 2, 

dated February 27, 2013, except as specified 

in paragraph (h) of this AD. 

(h) Exception to Paragraph (g) of This AD 

The actions required by paragraph (g) of 

this AD are not required to be done on 

airplanes with manufacturer serial numbers 

4942 and higher, provided a review of 

maintenance records verifies that no aft 

engine mount retainers have been replaced 

since first flight of the airplane. 

(i) Repetitive Inspection and Retainer 

Replacement for Dull Finish Retainers 

If, during the detailed inspection required 

by paragraph (g) of this AD, any installed 

dull finish aft engine mount retainer is found 

without cracks and not failed: Do the actions 

specified in paragraphs (i)(1) and (i)(2) of this 

AD. 

(1) Within 25 flight cycles after doing the 

actions required by paragraph (g) of this AD: 

Repeat the detailed inspection specified in 

paragraph (g) of this AD. 

(2) Within 50 flight cycles after doing the 

first detailed inspection specified in 

paragraph (g) of this AD: Replace all dull 

finish retainers with new retainers, in 

accordance with Section 4.2.3.1, 

‘‘Replacement Procedure,’’ of Airbus AOT 

A71N001–12, Rev. 2, dated February 27, 

2013. 

(j) Replacement of Cracked or Failed 

Retainers 

If, during any detailed inspection specified 

in paragraph (g) of this AD, any installed aft 

engine mount retainer is found cracked or 

failed: Before further flight, replace all 

affected aft engine mount retainers with new 

retainers, in accordance with Section 4.2.3, 

‘‘Replacement Procedure,’’ of Airbus AOT 

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42658 Federal Register / Vol. 79, No. 141 / Wednesday, July 23, 2014 / Rules and Regulations 

A71N001–12, Rev. 2, dated February 27, 

2013. 

(k) Parts Prohibition 

As of the effective date of this AD, no 

person may install any aft engine mount 

retainer with a dull finish on any airplane. 

The instructions of Airbus AOT A71N001– 

12, Rev. 2, dated February 27, 2013; or the 

Accomplishment Instructions of Goodrich 

Service Bulletin RA32071–146, Rev. 2, dated 

July 26, 2012; may be used to verify the 

correct finish of the part. 

(l) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g), (i), and (j) of this 

AD, if those actions were performed before 

the effective date of this AD using Airbus 

AOT A71N001–12, Rev. 1, dated August 9, 

2012, which is not incorporated by reference 

in this AD. 

(m) 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; 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. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(n) Special Flight Permits 

Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the airplane can be 

modified (if the operator elects to do so), 

provided no dull finish aft engine mount 

retainers that are cracked or have failed are 

installed. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0050, dated March 5, 2013, 

for related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov/#!document

Detail;D=FAA-2013-1028-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

paragraphs (p)(3), (p)(4), and (p)(5) of this 

AD. 

(p) 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 this AD specifies otherwise. 

(i) Airbus Alert Operators Transmission 

A71N001–12, Rev. 2, dated February 27, 

2013. The first page of this document 

contains the document number, revision, and 

date; no other page of this document contains 

this information. 

(ii) Goodrich Service Bulletin RA32071– 

146, Rev. 2, dated July 26, 2012. 

(3) For Airbus service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone +33 5 61 93 36 96; fax +33 

5 61 93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

(4) For Goodrich Corporation service 

information identified in this AD, contact 

Goodrich Corporation, Aerostructures, 850 

Lagoon Drive, Chula Vista, CA 91910–2098; 

phone: 619–691–2719; email: jan.lewis@

goodrich.com; Internet: http://

www.goodrich.com/TechPubs. 

(5) You may view this 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. 

(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 Renton, Washington, on July 3, 

2014. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–16536 Filed 7–22–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0292; Directorate 

Identifier 2014–CE–011–AD; Amendment 

39–17904; AD 2014–15–02] 

RIN 2120–AA64 

Airworthiness Directives; GROB– 

WERKE GMBH & CO KG Gliders 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for GROB– 

WERKE GMBH & CO KG Models G102 

STANDARD ASTIR III, G102 CLUB 

ASTIR III, and G102 CLUB ASTIR IIIb 

gliders and BURKHART GROB LUFT— 

UND RAUMFAHRT GmbH & CO KG 

Models G103 TWIN II, G103A TWIN II 

ACRO, G103C TWIN III ACRO, and G 

103 C Twin III SL gliders. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

issued 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 plastic control cable 

pulleys developing cracks due to aging. 

We are issuing this AD to require 

actions to address the unsafe condition 

on these products. 

DATES: This AD is effective August 27, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of August 27, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0292; or in person at Document 

Management Facility, U.S. Department 

of Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

For service information identified in 

this AD, contact Fiberglas-Technik 

Rudolf Lindner GmbH & Co. KG, Steige 

3, D–88487 Walpertshofen, Germany; 

telephone: +49 (0) 7353/22 43; fax: +49 

(0) 7353/30 96; email: info@LTBLindner.com; Web site: http://www.ltblindner.com/home.104.html. You may 

view this referenced 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. 

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