Federal Register / Vol. 79, No. 158 / Friday, August 15, 2014 / Rules and Regulations 48021 

dated July 3, 2014: Retorque within 6,000 

flight cycles or 7,500 flight hours, whichever 

occurs first after replacement of the pylon 

outboard and inboard lower link fittings 

required by paragraph (h) of this AD, and 

thereafter at intervals not to exceed 6,000 

flight cycles or 7,500 flight hours, whichever 

occurs first. 

(ii) For airplanes identified as Group 3 in 

Embraer Service Bulletin 190–54–0015, dated 

July 3, 2014, and Model ERJ 190–100 STD, 

–100 LR, –100 IGW, –200 STD, –200 LR, and 

–200 IGW airplanes having serial numbers 

19000586 and subsequent: Retorque within 

6,000 flight cycles or 7,500 flight hours, 

whichever occurs first after the effective date 

of this AD, and thereafter at intervals not to 

exceed 6,000 flight cycles or 7,500 flight 

hours, whichever occurs first. 

(2) For Model ERJ 190–100 ECJ airplanes: 

Retorque as specified in paragraph (i)(2)(i) or 

(i)(2)(ii) of this AD, as applicable, in 

accordance with Parts III and IV of the 

Accomplishment Instructions of Embraer 

Service Bulletin 190LIN–54–0006, dated July 

3, 2014. 

(i) For airplanes identified as Groups 1 and 

2 in Embraer Service Bulletin 190LIN–54– 

0006, dated July 3, 2014: Retorque within 

2,000 flight cycles or 7,500 flight hours, 

whichever occurs first after replacement of 

the pylon outboard and inboard lower link 

fittings required by paragraph (h) of this AD, 

and thereafter at intervals not to exceed 2,000 

flight cycles or 7,500 flight hours, whichever 

occurs first. 

(ii) For airplanes identified as Group 3 in 

Embraer Service Bulletin 190LIN–54–0006, 

dated July 3, 2014, and Model ECJ airplanes 

having serial numbers 19000572 and 

subsequent: Retorque within 2,000 flight 

cycles or 7,500 flight hours, whichever 

occurs first after the effective date of this AD, 

and thereafter at intervals not to exceed 2,000 

flight cycles or 7,500 flight hours, whichever 

occurs first. 

(j) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install, at the inboard or 

outboard lower link fitting on any airplane, 

a lock assembly identified in Embraer Service 

Bulletin 190–54–0013, dated November 27, 

2012; or Embraer Service Bulletin 190LIN– 

54–0004, dated December 20, 2012. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information specified in paragraphs (k)(1) 

through (k)(5) of this AD, as applicable. This 

service information is not incorporated by 

reference in this AD. 

(1) Embraer Alert Service Bulletin 190–54– 

A015, dated June 23, 2014. 

(2) Embraer Alert Service Bulletin 190–54– 

A015, Revision 01, dated June 26, 2014. 

(3) Embraer Alert Service Bulletin 190–54– 

A015, Revision 02, dated June 27, 2014. 

(4) Embraer Alert Service Bulletin 190LIN– 

54–A006, dated June 23, 2014. 

(5) Embraer Alert Service Bulletin 190LIN– 

54–A006, Revision 01, dated June 26, 2014. 

(l) 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: 

Kathrine Rask, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; telephone 425– 

227–2180; fax 425–227–1149. Information 

may be emailed to 9-ANM-116-AMOCREQUESTS@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 

ANAC; or ANAC’s authorized Designee. If 

approved by the ANAC Designee, the 

approval must include the Designee’s 

authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Brazilian 

Airworthiness Directive 2014–07–01, dated 

July 10, 2014, for related information. You 

may examine the MCAI on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2014–0531. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (n)(3) and (n)(4) of this AD. 

(n) 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) Embraer Alert Service Bulletin 190–54– 

A015, Revision 03, dated June 27, 2014. 

(ii) Embraer Alert Service Bulletin 190LIN– 

54–A006, Revision 02, dated June 27, 2014. 

(iii) Embraer Service Bulletin 190–54– 

0013, dated November 27, 2012. 

(iv) Embraer Service Bulletin 190–54–0015, 

dated July 3, 2014. 

(v) Embraer Service Bulletin 190LIN–54– 

0004, dated December 20, 2012. 

(vi) Embraer Service Bulletin 190LIN–54– 

0006, dated July 3, 2014. 

(3) For service information identified in 

this AD, contact Embraer S.A., Technical 

Publications Section (PC 060), Av. Brigadeiro 

Faria Lima, 2170—Putim—12227–901 Sa ̃o 

Jose dos Campos—SP—Brasil; telephone +55 

12 3927–5852 or +55 12 3309–0732; fax +55 

12 3927–7546; email distrib@embraer.com.br; 

Internet http://www.flyembraer.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 August 

6, 2014. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–19263 Filed 8–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0121; Directorate 

Identifier 2013–NM–151–AD; Amendment 

39–17928; AD 2014–16–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2008–14– 

17 for certain Airbus Model A330–200 

and A340–300 series airplanes. AD 

2008–14–17 required a high frequency 

eddy current (HFEC) inspection, 

corrective actions if necessary, and 

modifications. This new AD requires the 

same actions as those required by AD 

2008–14–17, but with a reduced 

compliance time. This AD was 

prompted by a determination from a 

fatigue and damage tolerance evaluation 

that the compliance time needs to be 

revised. We are issuing this AD to detect 

and correct damage of the upper shell 

structure at the skin and frame interface, 

which could result in reduced structural 

integrity of the airframe. 

DATES: This AD becomes effective 

September 19, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 19, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 


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48022 Federal Register / Vol. 79, No. 158 / Friday, August 15, 2014 / Rules and Regulations 

of certain other publications listed in 

this AD as of August 21, 2008 (73 FR 

40958, July 17, 2008). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0121; 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. 

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 to supersede AD 2008–14–17, 

Amendment 39–15612 (73 FR 40958, 

July 17, 2008). AD 2008–14–17 applied 

to certain Airbus Model A330–200 and 

A340–300 series airplanes. The NPRM 

published in the Federal Register on 

March 3, 2014 (79 FR 11717). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0158, 

dated July 22, 2013 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A330–200 and 

A340–300 series airplanes. The MCAI 

states: 

During fatigue tests (EF3) on an A340–600 

aeroplane, multiple damage was found in the 

upper side shell structure at skin and frame 

(FR) 84 and 85 interface, from stringer 6 to 

15 Left-Hand (LH) and Right Hand (RH). This 

damage occurred between 58 341 and 72 891 

simulated flight cycles (FC). 

Due to the higher Design Service Goal and 

different design (e.g. skin thickness) for 

A330–200 and A340–300 aeroplanes, the 

damage assessment concluded that these 

aeroplanes can potentially be impacted. 

This condition, if not detected and 

corrected, could result in reduced structural 

integrity of the airframe. 

Prompted by these findings, EASA issued 

[an] AD * * * to require a one-time inspection 

and a modification to improve the upper 

shell structure. 

EASA AD 2007–0269R1 [http://

ad.easa.europa.eu/blob/easa_ad_2007_

0269R1_superseded.pdf/AD_2007-0269R1_2, 

which corresponds to FAA AD 2008–14–17, 

Amendment 39–15612 (73 FR 40958)] was 

issued to clarify the fact that the [EASA] AD 

was not applicable to A340–300 aeroplanes 

on which both Airbus Mod 44205 and Mod 

45012 have been embodied in production. 

Since that [EASA] AD was issued, in the 

frame of a new fatigue and damage tolerance 

evaluation, taking into account the aeroplane 

utilization, the threshold and intervals were 

reassessed. This reassessment concluded 

that, in that specific case, the threshold for 

modifying the aeroplane must be reduced. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2007–0269R1, which is superseded, but 

requires these actions within the new 

thresholds. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0121- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 11717, March 3, 2014) or on the 

determination of the cost to the public. 

‘‘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. 

We have become 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 ADmandated 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 the 

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 actions must be 

accomplished using a method approved 

by the FAA, 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. 

We also have decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or ‘‘design approval 

holder (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 throughout this 

AD. 

Conclusion 

We reviewed the available data 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 


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Federal Register / Vol. 79, No. 158 / Friday, August 15, 2014 / Rules and Regulations 48023 

11717, March 3, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 11717, 

March 3, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 7 

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 and Modification [retained actions 

from.

AD 2008–14–17, Amendment 39–15612 (73 

FR 40958, July 17, 2008)].

300 work-hours × $85 per hour = $25,500 .... $72,730 $98,230 $687,610 

The new requirements of this AD add 

no additional economic burden. 

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/#!docket

Detail;D=FAA–2014–0121; 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 

removing Airworthiness Directive (AD) 

2008–14–17, Amendment 39–15612 (73 

FR 40958, July 17, 2008), and adding the 

following new AD: 

2014–16–04 Airbus: Amendment 39–17928. 

Docket No. FAA–2014–0121; Directorate 

Identifier 2013–NM–151–AD. 

(a) Effective Date 

This AD becomes effective September 19, 

2014. 

(b) Affected ADs 

This AD replaces AD 2008–14–17, 

Amendment 39–15612 (73 FR 40958, July 17, 

2008). 

(c) Applicability 

This AD applies to the airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Airbus Model A330–201, –202, –203, 

–223, and –243 airplanes, all manufacturer 

serial numbers (MSNs), on which Airbus 

Modification 44205 has been embodied in 

production, except those on which Airbus 

Modification 52974 or Modification 53223 

has been embodied in production. 

(2) Airbus Model A340–311, –312, and 

–313 airplanes, all MSNs on which Airbus 

Modification 44205 has been embodied in 

production, except those on which Airbus 

Modification 52974, Modification 53223, or 

Modification 45012 has been embodied in 

production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a determination 

from a fatigue and damage tolerance 

evaluation that the compliance time of the 

high frequency eddy current (HFEC) 

inspection for cracking, and modification of 

the upper shell structure of the fuselage 

needs to be revised. We are issuing this AD 

to detect and correct damage of the upper 

shell structure at the skin and frame 

interface, which could result in reduced 

structural integrity of the airframe. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection 

This paragraph restates the requirements of 

paragraph (f)(1) of AD 2008–14–17, 

Amendment 39–15612 (73 FR 40958, July 17, 

2008), with reduced compliance times and 

revised service information. For Airbus 

Model A330–200 series airplanes, as 

identified in paragraph (c) of this AD, on 

which Modification 45012 has been 

embodied in production: Within the 

applicable compliance times specified in 

paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of 

this AD, do the HFEC inspection for cracking, 

and corrective actions as applicable; and 

modify the upper shell structure of the 

fuselage; in accordance with the 


emcdonald on DSK67QTVN1PROD with RULES
48024 Federal Register / Vol. 79, No. 158 / Friday, August 15, 2014 / Rules and Regulations 

Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3152, Revision 3, 

dated December 22, 2011. Do all applicable 

corrective actions before further flight. 

(1) For airplanes pre-modification 48827 

with short range utilization: At the later of 

the times specified in paragraph (g)(1)(i) or 

(g)(1)(ii) of this AD. 

(i) Prior to 24,400 total flight cycles or 

85,400 total flight hours, whichever occurs 

first. 

(ii) Within 12 months after the effective 

date of this AD without exceeding 25,400 

total flight cycles. 

(2) For airplanes pre-modification 48827 

with long range utilization: At the later of the 

times specified in paragraph (g)(2)(i) or 

(g)(2)(ii) of this AD. 

(i) Prior to 18,900 total flight cycles or 

122,900 total flight hours, whichever occurs 

first. 

(ii) Within 12 months after the effective 

date of this AD without exceeding 25,400 

total flight cycles. 

(3) For airplanes post-modification 48827 

with short range utilization: At the later of 

the times specified in paragraph (g)(3)(i) or 

(g)(3)(ii) of this AD. 

(i) Prior to 16,400 total flight cycles or 

57,400 total flight hours, whichever occurs 

first. 

(ii) Within 12 months after the effective 

date of this AD without exceeding 17,100 

total flight cycles or 94,700 total flight hours, 

whichever occurs first. 

(4) For airplanes post-modification 48827 

with long range utilization: At the later of the 

times specified in paragraph (g)(4)(i) or 

(g)(4)(ii) of this AD. 

(i) Prior to 12,700 total flight cycles or 

82,700 total flight hours, whichever occurs 

first. 

(ii) Within 12 months after the effective 

date of this AD without exceeding 17,100 

total flight cycles or 94,700 total flight hours, 

whichever occurs first. 

(h) Retained Modification 

This paragraph restates the requirements of 

paragraph (f)(2) of AD 2008–14–17, 

Amendment 39–15612 (73 FR 40958, July 17, 

2008), with revised paragraph formatting. For 

Airbus Model A330–200 and A340–300 

series airplanes as identified in paragraph (c) 

of this AD, on which Modification 45012 has 

not been embodied in production: At the 

later of the compliance times specified in 

paragraphs (h)(1) and (h)(2) of this AD, 

modify the upper shell structure of the 

fuselage, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3157, or Airbus 

Service Bulletin A340–53–4163, both dated 

July 5, 2006, as applicable. 

(1) For the airplanes identified in 

paragraphs (h)(1)(i) and (h)(1)(ii) of this AD. 

(i) For Model A330–200 series airplanes, 

prior to 6,600 total flight cycles. 

(ii) For Model A340–300 series airplanes, 

prior to 14,000 total flight cycles. 

(2) Within 90 days after August 21, 2008 

(the effective date of AD 2008–14–17, 

Amendment 39–15612 (73 FR 40958, July 17, 

2008)). 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using the service information 

specified in paragraph (i)(1), (i)(2), or (i)(3) of 

this AD. 

(1) Airbus Service Bulletin A330–53–3152, 

dated April 10, 2007, which was 

incorporated by reference in AD 2008–14–17, 

Amendment 39–15612 (73 FR 40958, 

July 17, 2008). 

(2) Airbus Service Bulletin A330–53–3152, 

Revision 1, dated May 5, 2009, which is not 

incorporated by reference in this AD. 

(3) Airbus Service Bulletin A330–53–3152, 

Revision 2, dated July 27, 2011, which is not 

incorporated by reference in this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; fax 425–227–1149. 

Information may be emailed to: 9–ANM–116– 

AMOC–REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0158, dated July 22, 2013, for 

related information. You may examine the 

MCAI in the AD docket on the Internet at 

http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0121-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD is available at the addresses specified 

in paragraphs (l)(5) and (l)(6) of this AD. 

(l) 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. 

(3) The following service information was 

approved for IBR on September 19, 2014. 

(i) Airbus Service Bulletin A330–53–3152, 

Revision 3, dated December 22, 2011. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on August 21, 2008 (73 FR 

40958, July 17, 2008). 

(i) Airbus Service Bulletin A330–53–3157, 

dated July 5, 2006. 

(ii) Airbus Service Bulletin A340–53–4163, 

dated July 5, 2006. 

(5) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.com. 

(6) You may 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. 

(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 July 23, 

2014. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–18461 Filed 8–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0468; Directorate 

Identifier 2012–NM–147–AD; Amendment 

39–17924; AD 2014–15–21] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2006–26– 

06 for certain The Boeing Company 

Model 777–200 and –300 series 

airplanes equipped with Rolls-Royce 

engines. AD 2006–26–06 required 

repetitive inspections to detect cracks of 

the outer V-blades of the thrust reverser, 

and corrective action if necessary. AD 


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