Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Rules and Regulations 4167 

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): 

2015–28–01 Engine Alliance: Amendment 

39–18384; Docket No. FAA–2015–3585; 

Directorate Identifier 2015–NE–22–AD. 

(a) Effective Date 

This AD is effective March 1, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Engine Alliance (EA) 

GP7270 turbofan engines with a highpressure compressor (HPC) cone shaft, part 

number 382–100–907–0, installed. 

(d) Unsafe Condition 

This AD was prompted by the 

manufacturer informing us that the 

inspection and repair criteria in the 

maintenance manual for aft bolt holes of the 

HPC cone shaft on the affected engines is 

incorrect. We are issuing this AD to prevent 

failure of the HPC cone shaft, which could 

lead to uncontained engine failure and 

damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) For HPC cone shafts with serial 

numbers listed in EA Service Bulletin (SB) 

No. EAGP7–72–330, dated July 21, 2015, 

inspect the inner diameter of the HPC cone 

shaft aft bolt holes for nicks, dents, pits, and 

scratches before accumulating 9,000 cycles 

since new (CSN). Do not reinstall the HPC 

cone shaft if the aft bolt hole has any nicks, 

dents, pits, or scratches that are greater than 

0.002 inch in depth. 

(2) For HPC cone shafts with serial 

numbers listed in EA SB No. EAGP7–72–329, 

dated July 21, 2015, shot peen the HPC cone 

shaft aft bolt holes before accumulating 9,000 

CSN. Use paragraph 1 of the 

Accomplishment Instructions in EA SB No. 

EAGP7–72–329 to do the shot peening. 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install an HPC cone shaft on any engine with 

the following: 

(1) any nicks, dents, pits, or scratches in an 

HPC cone shaft aft bolt hole that is greater 

than 0.002 inch in depth; or 

(2) any repair of an HPC cone shaft aft bolt 

hole that did not include shot peening. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. You may email your request to: 

ANE–AD–AMOC@faa.gov. 

(h) Related Information 

For more information about this AD, 

contact Kyle Gustafson, Aerospace Engineer, 

Engine & Propeller Directorate, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: 781–238–7183; fax: 781–238–7199; 

email: kyle.gustafson@faa.gov. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Engine Alliance (EA) Service Bulletin 

(SB) No. EAGP7–72–329, dated July 21, 2015. 

(ii) EA SB No. EAGP7–72–330, dated July 

21, 2015. 

(3) For EA service information identified in 

this AD, contact Engine Alliance, 400 Main 

St., East Hartford, CT 06108, M/S 169–10; 

phone: 800–565–0140; email: help24@

pw.utc.com; Internet: 

sp.engineallianceportal.com. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 1200 

District Avenue, Burlington, MA. For 

information on the availability of this 

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

(5) You may view this service information 

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/ibr-locations.html. 

Issued in Burlington, Massachusetts, on 

January 13, 2016. 

Gaetano Sciortino, 

Acting Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2016–01268 Filed 1–25–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1429; Directorate 

Identifier 2014–NM–246–AD; Amendment 

39–18382; AD 2016–02–03] 

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 certain 

Airbus Model A319–113, A319–114, 

A320–211, and A320–212 airplanes. 

This AD was prompted by a report that 

the aft mount pylon bolts of the CFM56– 

5 engines may have been installed using 

the wrong torque values. This AD 

requires identification of engines that 

were installed using the wrong torque 

values and re-torque of the four aft 

mount pylon bolts of those engines. We 

are issuing this AD to detect and correct 

improper torque of the aft mount pylon 

bolts, which, if combined with any 

maintenance damage, could lead to aft 

engine mount failure, possibly resulting 

in engine detachment and consequent 

reduced control of the airplane. 

DATES: This AD becomes effective 

March 1, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 1, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://www.

regulations.gov/#!docketDetail;D=FAA–

2015–1429; 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 final rule, 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. 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– 

1429. 

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. 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Airbus Model A319– 

113, A319–114, A320–211, and A320– 

212 airplanes. The NPRM published in 

the Federal Register on June 15, 2015 

(80 FR 34101). The NPRM was 

prompted by a report that the aft mount 

pylon bolts of the CFM56–5 engines 

may have been installed using the 

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4168 Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Rules and Regulations 

wrong torque values. The NPRM 

proposed to require identification of 

engines that were installed using the 

wrong torque values and re-torque of the 

four aft mount pylon bolts of those 

engines. We are issuing this AD to 

detect and correct improper torque of 

the aft mount pylon bolts, which, if 

combined with any maintenance 

damage, could lead to aft engine mount 

failure, possibly resulting in engine 

detachment and consequent reduced 

control of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2014–0258, 

dated November 28, 2014 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A319–113, 

A319–114, A320–211, and A320–212 

airplanes. The MCAI states: 

In the Aircraft Maintenance Manual 

(AMM) revision dated May 2013, a wrong 

torque value was added in AMM task 71–00– 

00–400–040–A01 ‘‘Installation of the power 

plant with Engine Positioner TWW75E’’. 

Temporary Revisions (TR) dated March 2014 

were published by Airbus to correct the 

information and with AMM revision dated 

May 2014, Task 71–00–00–400–040–A01 was 

corrected to include the correct values. 

Notwithstanding those actions, static and 

fatigue analyses have concluded that this 

undertorque scenario negatively impacts the 

assembly performance, reducing the aft 

mount capability. 

This condition, if not corrected and if 

combined with any maintenance damage, 

could lead to aft engine mount failure, 

possibly resulting in engine detachment and 

consequent reduced control of the aeroplane. 

For the reasons described above, this 

[EASA] AD requires identification of 

CFM56–5 engines (those listed in TCDS 

EASA.E.067 [http://easa.europa.eu/

document-library/typecertificates/easae067]) 

that were installed by using the wrong torque 

data of AMM instructions mentioned above 

and re-torque of the four aft mount pylon 

bolts of those engines. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/#!documentDetail;

D=FAA–2015–1429–0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (80 FR 34101, 

June 15, 2015) and the FAA’s response 

to each comment. 

Request to Revise Paragraph (h) of the 

Proposed AD (80 FR 34101, June 15, 

2015) 

Delta Air Lines, Inc. (DAL) requested 

that we revise paragraph (h) of the 

proposed AD (80 FR 34101, June 15, 

2015), by revising the wording to refer 

to the Aircraft Maintenance Manual 

(AMM), dated May 2013 instead of 

Airbus Service Bulletin A320–71–1063, 

including Appendix 01, dated August 

13, 2014. DAL pointed out that 

paragraph (h) of the proposed AD 

required engine installation in 

accordance with Airbus Service Bulletin 

A320–71–1063, including Appendix 01, 

dated August 13, 2014. DAL also 

mentioned that Airbus Service Bulletin 

A320–71–1063, including Appendix 01, 

dated August 13, 2014, only has 

requirements for inspection and retorque of the aft engine mount pylon 

bolts. 

We agree to revise paragraph (h) of 

this AD because Airbus Service Bulletin 

A320–71–1063, including Appendix 01, 

dated August 13, 2014, does not contain 

installation instructions. We have 

revised paragraph (h) of this AD to 

specify that no person may install a 

CFM56–5 engine, on any airplane, 

unless accomplishing the actions 

specified in paragraph (g) of this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

with the change described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 

34101, June 15, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 34101, 

June 15, 2015). 

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 

Airbus has issued Airbus Service 

Bulletin A320–71–1063, including 

Appendix 01, dated August 13, 2014. 

The service information describes 

procedures to detect and correct 

improper torque of the aft mount pylon 

bolts. 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. 

Costs of Compliance 

We estimate that this AD affects 126 

airplanes of U.S. registry. 

We also estimate that it will take 

about 2 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $21,420, or $170 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-2015-1429; 

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 

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Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Rules and Regulations 4169 

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): 

2016–02–03 Airbus: Amendment 39– 

18382. Docket No. FAA–2015–1429; 

Directorate Identifier 2014–NM–246–AD. 

(a) Effective Date 

This AD becomes effective March 1, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category, all manufacturer 

serial numbers. 

(1) Airbus Model A319–113 and –114 

airplanes. 

(2) Airbus Model A320–211 and –212 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Powerplant. 

(e) Reason 

This AD was prompted by a report that the 

aft mount pylon bolts of the CFM56–5 

engines may have been installed using the 

wrong torque values. We are issuing this AD 

to detect and correct improper torque of the 

aft mount pylon bolts, which, if combined 

with any maintenance damage, could lead to 

aft engine mount failure, possibly resulting in 

engine detachment and consequent reduced 

control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection for Incorrect Torque Values 

Within 6 months or 1,500 flight cycles, 

whichever occurs first after the effective date 

of this AD, inspect to determine the method 

used to install the engines, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–71–1063, 

including Appendix 01, dated August 13, 

2014. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the method used to install the 

engines can be conclusively determined from 

that review. For any engine replaced as 

specified in the Airbus A318/A319/A320/

A321 Aircraft Maintenance Manual (AMM), 

Task 71–00–00–400–040–A01, ‘‘Installation 

of the Power Plant with Engine Positioner 

TWW 75E,’’ dated May 2013: Within 6 

months or 1,500 flight cycles, whichever 

occurs first after the effective date of this AD, 

re-torque the 4 aft mount pylon bolts 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). 

Note 1 to paragraph (g) of this AD: 

Additional guidance for the re-torque can be 

found in Airbus A318/A319/A320/A321 

AMM Task 71–00–00–400–040–A01, 

‘‘Installation of the Power Plant with Engine 

Positioner TWW 75E,’’ dated May 2014. 

(h) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install a CFM56–5 engine, on any 

airplane, unless the inspection, and, as 

applicable, the re-torque, is done as specified 

in paragraph (g) of this AD. 

(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, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–227–1405; fax: 425–227– 

1149. Information may be emailed to: 9-116- 

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 EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2014–0258, dated November 28, 2014, for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

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

Detail;D=FAA-2015-1429-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(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 A320–71–1063, 

including Appendix 01, dated August 13, 

2014. 

(ii) Reserved. 

(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/ibr-locations.html. 

Issued in Renton, Washington, on January 

11, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–01108 Filed 1–25–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1991; Directorate 

Identifier 2014–NM–251–AD; Amendment 

39–18381; AD 2016–02–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A318–111 and –112 

airplanes; Model A319–111, –112, and 

–115 airplanes; Model A320–214 

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