52182 Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Rules and Regulations 

(i) Bombardier Service Bulletin 601R–35– 

018, dated May 21, 2013. 

(ii) Reserved. 

(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 August 

17, 2015. 

Kevin Hull, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–20959 Filed 8–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0455; Directorate 

Identifier 2014–NM–006–AD; Amendment 

39–18247; AD 2015–17–14] 

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 A319, A320, and A321 

series airplanes. This AD was prompted 

by reports that during a full scale fatigue 

test, several broken frames in certain 

areas of the cargo compartment have 

been found, especially on the cargo floor 

support fittings and open tack holes on 

the left-hand side. This AD requires a 

rototest inspection of the open tack 

holes and rivet holes at the cargo floor 

support fittings of the fuselage, 

including doing all applicable related 

investigative actions, and repair if 

necessary. We are issuing this AD to 

detect and correct cracking in the open 

tack holes and rivet holes at the cargo 

floor support fittings of the fuselage, 

which could affect the structural 

integrity of the airplane. 

DATES: This AD becomes effective 

October 2, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 2, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0455; 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, 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.airwortheas@airbus.com; Internet http://

www.airbus.com. You may view this 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2015–0455. 

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 A319, A320, 

and A321 series airplanes. The NPRM 

published in the Federal Register on 

July 23, 2014 (79 FR 42716). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0310, dated December 

20, 2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for all Airbus 

Model A319, A320, and A321 series 

airplanes. The MCAI states: 

During a full scale fatigue test, several 

broken frames in the cargo compartment area 

between Frame (FR) 50 and FR 63, have been 

found, especially on the cargo floor support 

fittings and open tack holes on [the] left hand 

side. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

For the reason described above, this 

[EASA] AD requires repetitive inspections of 

the frames in the cargo compartment area and 

of the cargo floor support fittings and open 

tack holes on the left hand (LH) side, and 

depending on findings, the accomplishment 

of applicable corrective action(s). This 

[EASA] AD also requires a modification, 

which constitutes terminating action for the 

repetitive inspections required by this 

[EASA] AD. 

The actions in this AD include a rototest 

inspection for cracking of the open tack 

holes and rivet holes at the cargo floor 

support fittings of the fuselage; 

modification of the fuselage, including 

doing all applicable related investigative 

actions; and repair if necessary. Related 

investigative actions include rotating 

probe inspections for cracking of the 

holes. You may examine the MCAI in 

the AD docket on the Internet at http:// 

www.regulations.gov/

#!documentDetail;D=FAA-2014-0455- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 42716, 

July 23, 2014) and the FAA’s response 

to each comment. 

Requests To Remove Service 

Information Not Applicable to the U.S. 

Fleet 

Delta Air Lines (DAL), United 

Airlines (UAL), and US Airways 

requested that certain service 

information be removed from the NPRM 

(79 FR 42716, July 23, 2014) as it is not 

applicable to the U.S. fleet. 

DAL stated that Airbus Service 

Bulletin A320–53–1261, dated 

December 21, 2012, which provides a 

terminating modification for the 

repetitive inspections specified in the 

NPRM (79 FR 42716, July 23, 2014), is 

one of eight structural modification 

service bulletins required to operate 

Model A320 airplanes beyond 48,000 

flight cycles/96,000 flight hours 

(referred to as extended service goal 

(ESG)). DAL stated that Airbus Service 

Bulletin A320–53–1261, dated 

December 21, 2012, does not affect DAL 

or any other U.S. operator, since Airbus 

only recognizes airplane effectivity for 

those operators that have accomplished 

this service bulletin (which can only be 

purchased from Airbus) through ESG 

embodiment. 

UAL and US Airways stated that, in 

paragraph (h) of the proposed AD (79 FR 

42716, July 23, 2014), modification of 

the fuselage in accordance with Airbus 


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Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Rules and Regulations 52183 

Service Bulletin A320–53–1261, dated 

December 21, 2012, must be 

accomplished before exceeding 48,000 

total flight cycles or 96,000 total flight 

hours, whichever occurs first. UAL and 

US Airways stated that Airbus Service 

Bulletin A320–53–1261, dated 

December 21, 2012, is not effective for 

all manufacturer serial numbers 

specified in the service information and 

is only applicable to a select number of 

operators. UAL commented that Airbus 

Service Bulletin A320–53–1261, dated 

December 21, 2012, was originally 

related to the ESG modification 

requirements and has not yet been 

revised to match the effective 

manufacturer serial numbers in 

specified Airbus Service Bulletin A320– 

53–1257, dated December 21, 2012. 

We agree with these commenters’ 

requests. Airbus Service Bulletin A320– 

53–1261, dated December 21, 2012, does 

not apply to the U.S. fleet because the 

terminating action is not applicable for 

all manufacturer serial numbers. 

Therefore, we have deleted the 

modification requirement that was 

specified in paragraph (h) of the 

proposed AD (79 FR 42716, July 23, 

2014), and have redesignated 

subsequent paragraphs accordingly. 

Request To Revise Certain Service 

Information 

DAL also requested that the FAA ask 

Airbus to update the Effectivity in 

Airbus Service Bulletin A320–53–1261, 

dated December 21, 2012, along with 

the other structural modification service 

information required for operation 

beyond 48,000 total flight cycles/96,000 

total flight hours. 

We disagree with this request. As we 

stated previously, we have deleted the 

modification requirement that was 

specified in paragraph (h) of the 

proposed AD (79 FR 42716, July 23, 

2014). In addition, we do not agree with 

delaying this action for mitigating safety 

risks addressed in this AD until after the 

release of the manufacturer’s additional 

planned service bulletin(s). We have not 

changed this AD in this regard. 

Request for Separate AD for the 

Structural Modification 

DAL requested that a separate AD be 

issued that would specify all required 

service information for the modification 

in paragraph (h) of the proposed AD (79 

FR 42716, July 23, 2014), which must be 

accomplished prior to operation beyond 

48,000 total flight cycles/96,000 total 

flight hours for affected manufacturer 

serial numbers. 

We disagree with issuing a separate 

AD action that would require all 

modifications associated with 

operations exceeding 48,000 total flight 

cycles/96,000 total flight hours (referred 

to as ESG). ESG is not related to the 

unsafe condition in this AD. ESG is not 

a requirement, but an option to operate 

with an extended operational limit of 

60,000 total flight cycles/120,000 total 

flight hours and is contingent on 

accomplishment of specific 

modifications. This AD is specific to 

mitigating the risks associated with the 

identified unsafe condition, which were 

identified during full scale fatigue 

testing. Choosing the option to operate 

airplanes exceeding 48,000 total flight 

cycles/96,000 total flight hours lies with 

the operator and has no bearing on the 

mitigation of the unsafe condition 

identified in this AD. We have not 

changed this AD in this regard. 

Requests To Identify Actions Required 

for Compliance 

DAL and UAL requested a statement 

in the NPRM (79 FR 42716, July 23, 

2014) to specify the actions that are 

required for compliance (RC) in Airbus 

Service Bulletin A320–53–1257, dated 

December 21, 2012. 

UAL stated that paragraph 3.C. of the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1257, dated 

December 21, 2012, meets the technical 

intent of the inspection in the service 

information as that paragraph specifies 

removal of the affected fasteners, 

accomplishment of the rototest 

inspection, and re-installation of the 

fasteners. UAL stated that the access 

and close-up actions may then be 

specified by the operator as deemed 

necessary. UAL commented that 

paragraph (g) of the proposed AD (79 FR 

42716, July 23, 2014) could specify that 

the inspection be performed in 

accordance with paragraph 3.C. of the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1257, dated 

December 21, 2012. 

DAL stated that the FAA issued 

Advisory Circular (AC) 20–176 in 

December 2011 and AC 20–176A in 

June 2014 (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgAdvisoryCircular.nsf/0/

979ddd1479e1ec6f86257cfc0052d4e9/

$FILE/AC%2020-176A.pdf); and Order 

8110.117A, dated June 18, 2014 (http:// 

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgOrders.nsf/0/

d715cdfc08ac0ddc86257cfc00528297/

$FILE/110.117A.pdf), which provides 

guidance for issuing service information 

related to ADs. DAL commented that 

paragraph 2–10 of AC 20–176A states 

that ‘‘steps that have a direct effect on 

detecting, preventing, resolving, or 

eliminating the unsafe condition in an 

AD should be identified in a SB with 

‘‘RC’’ (Required for Compliance’’). DAL 

stated that there are no ‘‘RC’’ identifiers 

in the work steps of Airbus Service 

Bulletin A320–53–1257, dated 

December 21, 2012. 

DAL also requested that the FAA 

evaluate service bulletins for adherence 

to the guidance provided in AC 20– 

176A, dated June 16, 2014 (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgAdvisoryCircular.nsf/0/

979ddd1479e1ec6f86257cfc0052d4e9/

$FILE/AC%2020-176A.pdf); and Order 

8110.117A, dated June 18, 2014 (http:// 

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgOrders.nsf/0/

d715cdfc08ac0ddc86257cfc00528297/

$FILE/110.117A.pdf), when proposing 

new AD’s. 

We agree with the concept of 

minimizing AD requirements when 

appropriate. The FAA released AC 20– 

176A, dated June 16, 2014 (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgAdvisoryCircular.nsf/0/

979ddd1479e1ec6f86257cfc0052d4e9/

$FILE/AC%2020-176A.pdf); and Order 

8110.117A, dated June 18, 2014 (http:// 

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgOrders.nsf/0/

d715cdfc08ac0ddc86257cfc00528297/

$FILE/110.117A.pdf), which include the 

concept of RC. The FAA has begun 

implementing this concept in ADs when 

we receive service information 

containing RC steps. While some design 

approval holders have implemented the 

RC concept, the implementation is 

voluntary. The FAA does not intend to 

develop or revise AD requirements to 

incorporate the RC concept if it is not 

included in the service information. 

However for this AD, we reviewed 

Airbus Service Bulletin A320–53–1257, 

dated December 21, 2012, and 

determined that the procedures in 

paragraph 3.C., ‘‘Procedure,’’ are 

necessary to address the identified 

unsafe condition. All other steps in the 

Accomplishment Instructions may be 

deviated from using accepted methods 

in accordance with the operator’s 

maintenance or inspection program 

without obtaining approval of an 

alternative method of compliance 

(AMOC), provided the procedures in 

paragraph 3.C., ‘‘Procedures,’’ can be 

done and the airplane can be put back 

in a serviceable condition. We have 

revised paragraph (g) of this AD to refer 

to procedures in paragraph 3.C., 

‘‘Procedures,’’ of the Accomplishment 

Instructions of Airbus Service Bulletin 

A320–53–1257, dated December 21, 

2012. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 


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52184 Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Rules and Regulations 

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 

42716, July 23, 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 42716, 

July 23, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Airbus Service Bulletin 

A320–53–1257, dated December 21, 

2012. The service information describes 

procedures for a rototest inspection of 

the open tack holes and rivet holes at 

the cargo floor support fittings between 

frame (FR) 50 and FR 63 (left-hand side 

only) for Model A320 and A321 series 

airplanes and FR 53 and FR 63 (lefthand side only) for Model A319 series 

airplanes of the fuselage, including 

other actions, and repair if necessary. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section of 

this AD. 

Costs of Compliance 

We estimate that this AD affects 847 

airplanes of U.S. registry. 

We also estimate that it would take 

about 471 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts (for the 

modification) would cost about $6,570 

per product. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $39,474,435, or $46,605 

per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

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-2014-0455; 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): 

2015–17–14 Airbus: Amendment 39–18247. 

Docket No. FAA–2014–0455; Directorate 

Identifier 2014–NM–006–AD. 

(a) Effective Date 

This AD becomes effective October 2, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A319– 

111, –112, –113, –114, –115, –131, –132, and 

–133 airplanes; Model A320–211, –212, –214, 

–231, –232, and –233 airplanes; and Model 

A321–111, –112, –131, –211, –212, –213, 

–231, and –232 airplanes; certificated in any 

category; all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports that, 

during a full scale fatigue test, several broken 

frames in certain areas of the cargo 

compartment have been found, especially on 

the cargo floor support fittings and open tack 

holes on the left-hand (LH) side. We are 

issuing this AD to detect and correct cracking 

in the open tack holes and rivet holes at the 

cargo floor support fittings of the fuselage, 

which could affect the structural integrity of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

At the applicable compliance times 

specified in paragraphs (g)(1) through (g)(3) 

of this AD: Do a rototest inspection for 

cracking of the open tack holes and rivet 

holes at the cargo floor support fittings of the 

fuselage between frame (FR) 50 and FR 63 

left-hand (LH) side only for Model A320 

series airplanes, and A321 series airplanes; 

and between FR 53 and FR 63 LH side only 

for Model A319 series airplanes; in 

accordance with paragraph 3.C., 

‘‘Procedures,’’ of the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1257, dated December 21, 2012. Repeat 

the inspection thereafter at intervals not to 

exceed 5,000 flight cycles or 10,000 flight 

hours, whichever occurs first. 

(1) For airplanes that have equal to or more 

than 45,000 total flight cycles or 90,000 total 

flight hours as of the effective date of this 

AD: Do the rototest inspection within 1,000 

flight cycles or 2,000 flight hours after the 

effective date of this AD, whichever occurs 

first. 

(2) For airplanes that have equal to or more 

than 36,200 total flight cycles or 72,400 total 

flight hours, but less than 45,000 total flight 

cycles or 90,000 total flight hours as of the 


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Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Rules and Regulations 52185 

effective date of this AD: Do the rototest 

inspection within 2,000 flight cycles or 4,000 

flight hours after the effective date of this AD, 

whichever occurs first, but no later than 

before the accumulation of 46,000 total flight 

cycles or 92,000 total flight hours, whichever 

occurs first. 

(3) For airplanes that have less than 36,200 

total flight cycles or 72,400 total flight hours 

as of the effective date of this AD: Do the 

rototest inspection before exceeding 38,200 

total flight cycles or 76,400 total flight hours, 

whichever occurs first. 

(h) Corrective Action 

If any crack is found during any inspection 

required by this AD: Before further flight, 

repair 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 DOAauthorized signature. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0310, dated 

December 20, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0455-0002. 

(k) 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 Service Bulletin A320–53–1257, 

dated December 21, 2012. 

(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 August 

13, 2015. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–20951 Filed 8–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0900; Directorate 

Identifier 2015–NE–12–AD; Amendment 39– 

18251; AD 2015–17–18] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Turbomeca S.A. Arrius 2F turboshaft 

engines with a certain part number oil 

pump installed. This AD requires 

inspection, and if necessary, 

replacement before further flight of the 

oil pump driver assembly and/or the oil 

pump shaft, or the oil pump itself. This 

AD was prompted by cases of 

deterioration of the gas generator front 

bearing due to a link loss between the 

pump driver and the oil pump shaft. We 

are issuing this AD to prevent link loss 

between the pump driver and the oil 

pump shaft, which could lead to an 

engine in-flight shutdown, forced 

landing, and damage to the helicopter. 

DATES: This AD becomes effective 

October 2, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 2, 2015. 

ADDRESSES: For service information 

identified in this AD, contact 

Turbomeca S.A., 40220 Tarnos, France; 

phone: 33 (0)5 59 74 40 00; telex: 570 

042; fax: 33 (0)5 59 74 45 15. 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0900. 

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–2015– 

0900; 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 

(MCAI), the 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: 

Philip Haberlen, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7770; fax: 781–238– 

7199; email: philip.haberlen@faa.gov. 

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 the specified products. The 

NPRM was published in the Federal 

Register on May 21, 2015 (80 FR 29224). 

The NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

A risk of an in-flight shutdown (IFSD) has 

been identified on an ARRIUS 2F engine, due 

to deterioration of gas generator front bearing. 

This could be the result of lack of lubrication, 


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