Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Rules and Regulations 4165 

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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (j) of this AD. Information may be 

emailed to: 9–ANM-Seattle-ACO–AMOCRequests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane and the 

approval must specifically refer to this AD. 

(4) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (i)(4)(i) and (i)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(j) Related Information 

For more information about this AD, 

contact Eric Lin, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6412; fax: 425– 

917–6590; email: Eric.Lin@faa.gov. 

(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 the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on January 28, 2016 (80 FR 

80234, December 24, 2015). 

(i) Boeing Alert Service Bulletin 777– 

53A0078, dated December 5, 2014. 

(ii) Reserved. 

(4) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206 766 5680; 

Internet https://www.myboeingfleet.com. 

(5) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(6) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://www.archives.

gov/federal-register/cfr/ibr-locations.html. 

Issued in Renton, Washington, on January 

19, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–01441 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–2015–3585; Directorate 

Identifier 2015–NE–22–AD; Amendment 39– 

18384; AD 2015–28–01] 

RIN 2120–AA64 

Airworthiness Directives; Engine 

Alliance Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Engine Alliance (EA) GP7270 turbofan 

engines. This AD was prompted by the 

manufacturer informing us that the 

inspection criteria and repair 

procedures in the maintenance manual 

for aft bolt holes of the high-pressure 

compressor (HPC) cone shaft on the 

affected engines is incorrect. This AD 

requires inspection of the HPC cone 

shaft and repair of affected parts, if 

needed. 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. 

DATES: This AD is 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: For 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. 

You may view this service information 

at the FAA, Engine & Propeller 

Directorate, 1200 District Avenue, 

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–2015– 

3585; 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 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: 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. 

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 certain EA GP7270 turbofan 

engines. The NPRM published in the 

Federal Register on October 1, 2015 (80 

FR 59081). The NPRM was prompted by 

the manufacturer informing us that the 

inspection criteria and repair 

procedures in the maintenance manual 

for aft bolt holes of the HPC cone shaft, 

also referred to as the ‘‘HPC forward 

stubshaft,’’ for the affected engines is 

incorrect. The NPRM proposed to 

require inspection of the HPC cone shaft 

and repair of affected parts, if needed. 

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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (80 FR 59081, 

October 1, 2015) and the FAA’s 

response to each comment. 

Request To Add Engine Models 

EA requested that we expand the 

applicability to include the GP7272 and 

GP7277 engine models. 

We disagree. There are no GP7272 or 

GP7277 engines in service nor have any 

been delivered. New engines would be 

delivered with corrected service 

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4166 Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Rules and Regulations 

information and would not be impacted 

by this AD. We did not change this AD. 

Request To Change the Unsafe 

Condition Statement 

EA requested that the unsafe 

condition statement be changed from 

‘‘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.’’ to ‘‘We are 

issuing this AD to prevent a hazardous 

engine condition.’’ The reason for this 

request is that no HPC cone shaft 

failures have occurred in the field. 

We disagree. The unsafe condition 

statement describes the condition we 

are trying to prevent and is the 

justification for this AD. It does not 

describe what has occurred in the past. 

We did not change this AD. 

Request To Change Various Paragraphs 

EA requested that we revise the part 

nomenclature in the Applicability, 

Compliance, and Installation 

Prohibition paragraphs and in the 

unsafe condition statement to include 

both ‘‘cone shaft’’ and ‘‘forward 

stubshaft.’’ The part is referenced as a 

‘‘cone shaft’’ in this AD and engine and 

component manuals; however, it is 

referred to as a ‘‘forward stubshaft’’ in 

the service bulletins (SBs). 

We disagree. The part nomenclature 

listed in the airworthiness limitations 

section and engine maintenance manual 

is ‘‘cone shaft.’’ The Discussion section 

of this AD explains that the terms ‘‘cone 

shaft’’ and ‘‘forward stubshaft’’ are 

synonymous. We consider including 

both terms throughout this AD 

unnecessary. We did not change this 

AD. 

Request To Revise the Compliance 

EA requested that the Compliance 

paragraph be revised to include the 

word ‘‘pits’’ when describing the 

inspection criteria. 

We agree. We revised paragraph (e)(1) 

and (f)(1) of this AD from ‘‘. . . nicks, 

dents, and scratches . . .’’ to ‘‘. . . 

nicks, dents, pits, and scratches. . . .’’ 

Request To Change the Compliance 

EA requested that we replace ‘‘Do not 

reinstall the HPC cone shaft if the aft 

bolt hole has a nick, dent, or scratch that 

is greater than 0.002 inch in depth’’ in 

paragraph (e)(1) of this AD with 

‘‘Comply with the Accomplishment 

Instructions in EA SB No. EAGP7–72– 

330 if the aft bolt hole has a nick, dent, 

pit, or scratch that is greater than the 

serviceable limit.’’ 

We disagree. The current engine 

manual has an approved repair 

procedure for damage that is more 

severe than the installation 

requirements of this AD. It is not 

necessary to restate what is already 

allowed by the engine manual. We did 

not change this AD. 

Request To Change Service Information 

EA requested that the phrase ‘‘or 

later’’ be used when referring to SBs. 

We disagree. We are only authorized 

to mandate use of SBs that we have 

reviewed and which are published. 

Since future revisions of SBs are not yet 

published, we are not authorized to 

mandate their use. We did not change 

this AD. 

Request To Change the Installation 

Prohibition 

EA requested that we change the 

Installation Prohibition paragraph to 

read: ‘‘After the effective date of this 

AD, do not install an HPC cone shaft 

onto an engine: (1) that has accumulated 

more than 9,000 cycles since new that 

has not complied with this AD on an 

applicable part, and (2) has a nick, dent, 

or scratch in an HPC cone shaft aft bolt 

hole that is greater than the serviceable 

limit.’’ 

We disagree. The intent of the 

Installation Prohibition paragraph is to 

mandate the new serviceable limit of 

0.002 inch for damage to the inner 

diameter of the bolt holes for the entire 

GP7270 fleet. Any parts with damage 

beyond this limit may be repaired using 

the approved procedures listed in the 

engine manual, provided that you 

include shot peening as required by 

paragraph (f)(2) of this AD. We did not 

change this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously. 

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 

EA has issued SB No. EAGP7–72–329, 

dated July 21, 2015 and SB No. EAGP7– 

72–330, dated July 21, 2015. The service 

information describes procedures for 

shotpeening the HPC forward stubshaft 

and inspecting the HPC forward 

stubshaft bolt-hole inner diameter 

respectively. 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 final rule. 

Costs of Compliance 

We estimate that this AD affects zero 

engines installed on airplanes of U.S. 

registry. 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 $0. 

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 14 CFR part 39 as 

follows: 

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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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