Federal Register / Vol. 79, No. 160 / Tuesday, August 19, 2014 / Rules and Regulations 48957 

(for Model CL–215–6B11 (CL–415 Variant) 

airplanes); and continue with the installation 

of the bolt and PLI washer, in accordance 

with paragraph 2.G. of the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin 215–A3173, dated April 11, 2012 

(for Model CL–215–6B11 (CL–215T Variant) 

airplanes); or Bombardier Alert Service 

Bulletin 215–A4453, dated April 10, 2012 

(for Model CL–215–6B11 (CL–415 Variant) 

airplanes). 

(2) Repair the bushing in accordance with 

paragraph 2.F. of the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin 215–A3173, dated April 11, 2012 

(for Model CL–215–6B11 (CL–215T Variant) 

airplanes); or Bombardier Alert Service 

Bulletin 215–A4453, dated April 10, 2012 

(for Model CL–215–6B11 (CL–415 Variant) 

airplanes); and continue with the installation 

of the bolt and PLI washer, in accordance 

with paragraph 2.G. of the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin 215–A3173, dated April 11, 2012 

(for Model CL–215–6B11 (CL–215T Variant) 

airplanes); or Bombardier Alert Service 

Bulletin 215–A4453, dated April 10, 2012 

(for Model CL–215–6B11 (CL–415 Variant) 

airplanes). 

(i) Replacement of Repaired Bushing 

For any bushing that has been repaired as 

specified in paragraph (h)(2) of this AD: 

Within 5,000 flight hours after accomplishing 

the repair or at the next engine removal, 

whichever occurs first, replace the bushing 

with P/N 85410265–103, in accordance with 

paragraph 2.E. of the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin 215–A3173, dated April 11, 2012 

(for Model CL–215–6B11 (CL–215T Variant) 

airplanes); or Bombardier Alert Service 

Bulletin 215–A4453, dated April 10, 2012 

(for Model CL–215–6B11 (CL–415 Variant) 

airplanes); and continue with the installation 

of the bolt and PLI washer, in accordance 

with paragraph 2.G. of the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin 215–A3173, dated April 11, 2012 

(for Model CL–215–6B11 (CL–215T Variant) 

airplanes); or Bombardier Alert Service 

Bulletin 215–A4453, dated April 10, 2012 

(for Model CL–215–6B11 (CL–415 Variant) 

airplanes). 

(j) Airplanes for Which No Further Action Is 

Required 

(1) For airplanes on which a general visual 

inspection specified in paragraph (g) of this 

AD is done and it is determined that nacelle 

strut bushings having P/N 85410265–103 are 

installed in the airplane: No further actions 

are required by this AD, provided the actions 

specified in paragraph (g)(1) of this AD have 

been done. 

(2) For airplanes on which nacelle strut 

bushings having P/N 85410265–103 are 

installed as specified in paragraph (h)(1) or 

(i) of this AD: No further actions are required 

by this AD. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531. 

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, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

Transport Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(l) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–06, dated 

February 27, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0120-0002. 

(m) 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) Bombardier Alert Service Bulletin 215– 

A3173, dated April 11, 2012. 

(ii) Bombardier Alert Service Bulletin 215– 

A4453, dated April 10, 2012. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.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 July 30, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–18863 Filed 8–18–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1158; Directorate 

Identifier 2011–NM–232–AD; Amendment 

39–17501; AD 2013–13–13] 

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 A310 series airplanes; 

and Model A300 B4–600, B4–600R, and 

F4–600R series airplanes, and Model 

A300 C4–605R Variant F airplanes 

(collectively called A300–600 series 

airplanes). This AD was prompted by 

the revision of certain airworthiness 

limitation items (ALI) documents, 

which require more restrictive 

maintenance requirements and 

airworthiness limitations. This AD 

requires revising the maintenance or 

inspection program to incorporate the 

limitations section. We are issuing this 

AD to prevent fatigue cracking, damage, 

or corrosion in principal structural 

elements, which could result in reduced 

structural integrity of the airplane. 

DATES: This AD becomes effective 

September 23, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 23, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2012-1158 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—EAW, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 


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

account.airworth-eas@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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

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 A300 and 

A310 series airplanes; and Model A300 

B4–600, B4–600R, and F4–600R series 

airplanes, and Model A300 C4–605R 

Variant F airplanes (collectively called 

A300–600 series airplanes). The NPRM 

was intended to supersede AD 2011– 

10–17, Amendment 39–16698 (76 FR 

27875, May 13, 2011). The NPRM 

published in the Federal Register on 

November 7, 2012 (77 FR 66772). The 

NPRM was prompted by the revision of 

certain airworthiness limitation items 

(ALI) documents, which require more 

restrictive maintenance requirements 

and airworthiness limitations. The 

NPRM proposed to require revising the 

maintenance program to incorporate the 

limitations section. We are issuing this 

AD to prevent fatigue cracking, damage, 

or corrosion in principal structural 

elements, which could result in reduced 

structural integrity of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, issued EASA 

Airworthiness Directive 2011–0198, 

dated October 19, 2011 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

all Airbus Model A300 and A310 series 

airplanes; and Model A300 B4–600, B4– 

600R, and F4–600R series airplanes, and 

Model A300 C4–605R Variant F 

airplanes (collectively called A300–600 

series airplanes). The MCAI states: 

The airworthiness limitations applicable to 

the Damage Tolerant Airworthiness 

Limitation Items (DT ALIs) are currently 

listed in Airbus ALI Documents, which are 

referenced in the A300, A310 and A300–600 

Airworthiness Limitations Section (ALS) Part 

2. 

Airbus have recently revised the A300–600 

and A310 ALI Documents, and these issues 

have been approved by EASA. The Airbus 

A300–600 ALI Document issue 13 and 

temporary revision (TR) 13.1 and the A310 

ALI document issue 08 introduce more 

restrictive maintenance requirements and 

airworthiness limitations, which have been 

identified as mandatory actions for continued 

airworthiness. 

EASA AD 2009–0155 [which corresponds 

to FAA AD 2011–10–17, Amendment 39– 

16698 (76 FR 27875, May 13, 2011)] required 

compliance with the maintenance 

requirements and associated airworthiness 

limitations defined in the following 

documents: 

—AIRBUS A300 ALI Document issue 04, 

—AIRBUS A310 ALI Document issue 07, and 

—AIRBUS A300–600 ALI Document issue 

12. 

For the reasons described, this EASA AD 

retains the requirements of EASA AD 2009– 

0155, which is superseded, and requires 

compliance with the airworthiness 

limitations defined in the Airbus A300–600 

ALI Document issue 13 and TR13.1, and the 

A310 ALI document issue 08. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2012-1158- 

0002. 

Actions Since NPRM (77 FR 66772, 

November 7, 2012) 

The NPRM (77 FR 66772, November 

7, 2012) proposed to supersede AD 

2011–10–17, Amendment 39–16698 (76 

FR 27875, May 13, 2011). However, the 

new actions introduced in the NPRM 

and required by this final rule apply 

only to Model A310 and A300–600 

series airplanes. The actions required 

for Model A300 series airplanes that are 

required by AD 2011–10–17 are not 

affected by this AD. AD 2011–10–17 

therefore remains in effect in its entirety 

for Model A300, A300–600, and A310 

series airplanes. The requirements of 

this final rule include only the new 

actions, and apply only to Model A310 

and A300–600 series airplanes. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Request for Clarification of Compliance 

Times 

UPS requested clarification of the 

compliance times for the maintenance 

program revision and the initial 

inspection. UPS noted that operators 

have 3 months to complete both the 

maintenance program revision and the 

initial inspections. UPS stated that the 

current wording indicates that the two 

tasks are to be accomplished 

concurrently, and cannot be 

accomplished until approved by the 

principal maintenance inspector. UPS 

added that concurrent accomplishment 

of the two actions is not feasible and 

requested that accomplishment of these 

two actions be consecutive rather than 

concurrent. 

We agree to provide clarification. The 

commenter’s statement that operators 

have 3 months to complete both the 

maintenance program revision and 

initial inspections is not accurate. As 

specified in paragraph (g) of this AD, 

operators have 3 months to revise the 

maintenance or inspection program, as 

applicable. However, the compliance 

time for the initial inspections is at the 

times in the applicable service 

information identified in paragraphs 

(g)(1), (g)(1)(i)(A), and (g)(2) of this AD, 

or within 3 months after the effective 

date of this AD, whichever occurs later. 

For the service information identified 

in paragraphs (g)(1) and (g)(2) of this 

AD, there are also compliance times 

specified in paragraph 3., ‘‘Special 

Compliance Times,’’ in the ‘‘Record of 

Revisions’’ section of the service 

information, which provide compliance 

times relative to the approval date or 

publication date of the service 

information. We have determined that 

those compliance times should be 

relative to the effective date of this AD; 

therefore, we have added compliance 

time exceptions to paragraphs 

(g)(1)(i)(B) and (g)(2)(i) of this AD. We 

have determined that extending these 

compliance times will provide an 

acceptable level of safety. 

Request To Extend Grace Period and 

Repetitive Intervals 

UPS requested that the proposed 

grace period and repetitive intervals be 

extended to be equivalent to the 

requirements of AD 2011–10–17, 

Amendment 39–16698 (76 FR 27875, 

May 13, 2011). UPS commented that the 

proposed compliance times are overly 

conservative and are not supported by 

industry data. 

We do not agree with the commenter’s 

request to extend the grace period and 

repetitive intervals. Airbus revised the 

ALIs based upon analysis and data. 

Under the provisions of paragraph (j) of 

this final rule, however, we will 

consider requests for approval of an 

extension of the compliance time if 

sufficient data are submitted to 

substantiate that a different compliance 

time would provide an acceptable level 

of safety. We have not changed this final 

rule in this regard. 

‘‘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 


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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 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. 

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, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the 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 (77 FR 

66772, November 7, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 66772, 

November 7, 2012). 

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 170 

airplanes of U.S. registry. 

We estimate that it will take about 1 

work-hour per product to comply with 

the new basic requirements of this AD. 

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

estimate the cost of this AD on U.S. 

operators to be $14,450, or $85 per 

product. 

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-2012-1158; 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): 

2013–13–13 Airbus Airplanes: Amendment 

39–17501. Docket No. FAA–2012–1158; 

Directorate Identifier 2011–NM–232–AD. 


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(a) Effective Date 

This AD becomes effective September 23, 

2014. 

(b) Affected ADs 

This AD affects AD 2011–10–17, 

Amendment 39–16698 (76 FR 27875, May 13, 

2011). 

(c) Applicability 

This AD applies to all Airbus model 

airplanes identified in paragraphs (c)(1) and 

(c)(2) of this AD, certificated in any category. 

(1) Model A310–203, –204, –221, –222, 

304, –322, –324, and –325 airplanes. 

(2) Model A300 B4–601, B4–603, B4–620, 

B4–622, B4–605R, B4–622R, F4–605R, F4– 

622R, and C4–605R Variant F airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by revisions of 

certain Airbus Airworthiness Limitation 

Items (ALI) documents, which require more 

restrictive maintenance requirements and 

airworthiness limitations. We are issuing this 

AD to prevent fatigue cracking, damage, or 

corrosion in principal structural elements, 

which could result in reduced structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Maintenance or Inspection Program 

Revision 

(1) For Model A300–600 series airplanes: 

Within 3 months after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate the 

structural inspections and inspection 

intervals defined in Airbus A300–600 

Airworthiness Limitation Items Document 

AI/SE–M2/95A.1310/07, Issue 13, dated 

October 2010. The initial compliance time for 

accomplishing the inspections is at the later 

of the times specified in paragraphs (g)(1)(i) 

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

(i) At the applicable times specified in 

Airbus A300–600 Airworthiness Limitation 

Items Document AI/SE–M2/95A.1310/07, 

Issue 13, dated October 2010, except as 

specified in paragraphs (g)(1)(i)(A) and 

(g)(1)(i)(B) of this AD. 

(A) For actions identified in Airbus A300– 

600 Airworthiness Limitation Items 

Document AI/SE–M2/95A.1310/07, Issue 13, 

dated October 2010; and Airbus TR 13.1, 

dated February 2011, to the Airbus A300–600 

Airworthiness Limitation Items Document 

AI/SE–M2/95A.1310/07, Issue 13, dated 

October 2010: Use the applicable compliance 

time specified in Airbus Temporary Revision 

(TR) 13.1, dated February 2011, to the Airbus 

A300–600 Airworthiness Limitation Items 

Document AI/SE–M2/95A.1310/07, Issue 13, 

dated October 2010. 

(B) Where compliance times in paragraph 

3., ‘‘Special Compliance Times,’’ in the 

‘‘Record of Revisions’’ section of Airbus 

A300–600 Airworthiness Limitation Items 

Document AI/SE–M2/95A.1310/07, specify 

‘‘from approval date of A300–600 ALI 

Document Issue 13,’’ ‘‘from date approval of 

A300–600 ALI Document Issue 13,’’ or ‘‘from 

A300–600 ALI Document Issue date of 

publication,’’ for this AD use ‘‘after the 

effective date of this AD’’ for those 

compliance times. 

(ii) Within 3 months after the effective date 

of this AD. 

(2) For Model A310 series airplanes: 

Within 3 months after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate the 

structural inspections and inspection 

intervals defined in Airbus A310 

Airworthiness Limitation Items Document 

AI/SE–M2/95A.1309/07, Issue 8, dated 

October 2010. The initial compliance time for 

accomplishing the inspections is at the later 

of the times specified in paragraph (g)(2)(i) 

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

(i) At the applicable times specified in 

Airbus A310 Airworthiness Limitation Items 

Document AI/SE–M2/95A.1309/07, Issue 8, 

dated October 2010; except where 

compliance times in paragraph 3., ‘‘Special 

Compliance Times,’’ in the ‘‘Record of 

Revisions’’ section of Airbus A310 

Airworthiness Limitation Items Document 

AI/SE–M2/95A.1309/07, Issue 8, dated 

October 2010, specify ‘‘from date of approval 

of ALI Document Issue 8,’’ or ‘‘from date 

approval of the ALI document Issue 8,’’ for 

this AD use ‘‘after the effective date of this 

AD’’ for those compliance times. 

(ii) Within 3 months after the effective date 

of this AD. 

(h) Terminating Action for AD 2011–10–17, 

Amendment 39–16698 (76 FR 27875, May 

13, 2011) 

Accomplishing the revision required by 

paragraph (g) of this AD terminates the 

actions required by paragraph (s) of AD 

2011–10–17, Amendment 39–16698 (76 FR 

27875, May 13, 2011) for that airplane only. 

(i) New Alternative Inspections and 

Inspection Intervals Limitation 

After accomplishing the revision required 

by paragraph (g) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (j) of 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, 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; 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 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2011–0198, dated 

October 19, 2011, for related information. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/#!docketDetail;D=FAA2012-1158-0002. 

(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. 

(i) Airbus A300–600 Airworthiness 

Limitation Items Document AI/SE–M2/

95A.1310/07, Issue 13, dated October 2010. 

(ii) Airbus A310 Airworthiness Limitation 

Items Document AI/SE–M2/95A.1309/07, 

Issue 8, dated October 2010. Page APXD–362 

(which contains Illustration 2 of 2 of Figure 

575141) of this document does not contain an 

issue date or page number. 

(iii) Airbus Temporary Revision 13.1, dated 

February 2011, to Airbus A300–600 

Airworthiness Limitation Items Document 

AI/SE–M2/95A.1310/07, Issue 13, dated 

October 2010. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 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. 


wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 79, No. 160 / Tuesday, August 19, 2014 / Rules and Regulations 48961 

Issued in Renton, Washington, on July 30, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–18906 Filed 8–18–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1327; Directorate 

Identifier 2012–NE–47–AD; Amendment 39– 

17934; AD 2014–16–10] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2013–12– 

01 for all Rolls-Royce plc (RR) model 

RB211 Trent 768–60, 772–60, and 

772B–60 turbofan engines. AD 2013– 

12–01 required a one-time ultrasonic 

inspection (UI) of low-pressure (LP) 

compressor blades with more than 2,500 

flight cycles since new or last 

inspection. This AD requires initial and 

repetitive UIs of the affected LP 

compressor blades. This AD was 

prompted by LP compressor blade 

partial airfoil release events. We are 

issuing this AD to prevent LP 

compressor blade airfoil separations, 

damage to the engine, and damage to the 

airplane. 

DATES: This AD is effective September 

23, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 23, 2014. 

ADDRESSES: For service information 

identified in this AD, contact RollsRoyce plc, P.O. Box 31, Derby DE24 8BJ, 

UK; phone: 44 0 1332 242424; fax: 44 

0 1332 249936. You may view this 

service information at the FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2012– 

1327; 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 mandatory 

continuing airworthiness information, 

regulatory evaluation, any comments 

received, and other information. The 

address for the Docket Office (phone: 

800–647–5527) is 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 FURTHER INFORMATION CONTACT: 

Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7754; fax: 781–238– 

7199; email: robert.green@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2013–12–01, 

Amendment 39–17478 (78 FR 37703, 

June 24, 2013), (‘‘AD 2013–12–01’’). AD 

2013–12–01 applied to the specified 

products. The NPRM published in the 

Federal Register on May 23, 2014 (79 

FR 29694). The NPRM proposed to 

require initial and repetitive UIs of the 

affected LP compressor blades. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 29694, May 23, 2014). 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 56 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 44 hours per engine to 

comply with the initial inspection 

requirements in this AD. The average 

labor rate is $85 per hour. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be 

$209,440. 

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 

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 to the extent that it justifies 

making a regulatory distinction, 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 part 39 of the Federal 

Aviation Regulations (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) 

2013–12–01, Amendment 39–17478 (78 

FR 37703, June 24, 2013), and adding 

the following new AD: 


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