Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations 40681 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (v)(5) and (v)(6) of this AD. 

(v) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on October 2, 2017. 

(i) Airbus Service Bulletin A320–34–1415, 

Revision 04, dated July 30, 2015. 

(ii) Airbus Service Bulletin A320–34–1444, 

Revision 01, dated March 17, 2011. 

(iii) Airbus Service Bulletin A320–34– 

1564, Revision 01, dated August 26, 2013. 

(iv) Airbus Service Bulletin A320–34– 

1610, Revision 01, dated July 30, 2015. 

(v) Thales Service Bulletin C16291A–34– 

007, Revision 04, dated October 11, 2012. 

(vi) Thales Service Bulletin C16291A–34– 

007, Revision 03, dated April 10, 2012. 

(vii) Thales Service Bulletin C16291A–34– 

007, Revision 02, dated December 16, 2011. 

(viii) Thales Service Bulletin C16291A–34– 

007, Revision 01, dated December 03, 2009. 

(4) The following service information was 

approved for IBR on November 6, 2013, 

Amendment 39–17591 (78 FR 60667, October 

2, 2013). 

(i) Airbus Mandatory Service Bulletin 

A320–34–1564, including Appendix 01, 

dated January 25, 2013. 

(ii) Reserved. 

(5) 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. 

(6) You may view this service information 

at the FAA, Transport Standards Branch, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on August 

2, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–16860 Filed 8–25–17; 8:45 am] 

BILLING CODE P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0652; Product 

Identifier 2017–NE–18–AD; Amendment 39– 

18997; AD 2017–17–07] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Rolls-Royce plc (RR) Trent XWB–75, 

Trent XWB–79, Trent XWB–79B, and 

Trent XWB–84 turbofan engines. This 

AD requires inspection of the 

intermediate-pressure (IP) turbine stage 

2 locking plates. This AD was prompted 

by a report of several IP turbine stage 2 

locking plates cracked during module 

assembly. We are issuing this AD to 

correct the unsafe condition on these 

products. 

DATES: This AD becomes effective 

September 12, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 12, 2017. 

We must receive comments on this 

AD by October 12, 2017. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Mail: U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: 202–493–2251. 

For service information identified in 

this AD, contact Rolls-Royce plc, 

Corporate Communications, P.O. Box 

31, Derby, England, DE24 8BJ; phone: 

011–44–1332–242424; fax: 011–44– 

1332–249936; email: http://www.rollsroyce.com/contact/civil_team.jsp; 

Internet: https://customers.rollsroyce.com/public/rollsroycecare. You 

may view this service information at the 

FAA, Engine and Propeller Standards 

Branch, Policy and Innovation Division, 

1200 District Avenue, Burlington, MA 

01803. 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–2017– 

0652. 

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–2017– 

0652; or in person at the Docket 

Operations office 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), regulatory evaluation, any 

comments received, and other 

information. The address for the Docket 

Office (phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Robert Green, Aerospace Engineer, FAA, 

ECO Branch, Compliance and 

Airworthiness Division, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7754; fax: 781–238–7199; 

email: robert.green@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2017–0652; 

Directorate Identifier 2017–NE–18–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2017– 

0088, dated May 16, 2017 (referred to 

hereinafter as ‘‘the MCAI’’), to correct an 


asabaliauskas on DSKBBXCHB2PROD with RULES
40682 Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations 

unsafe condition for the specified 

products. The MCAI states: 

During module assembly, cracking was 

observed on several intermediate pressure 

(IP) turbine stage 2 locking plates from one 

particular supplier. These locking plates form 

part of the IP turbine stage 2 assembly, 

providing axial retention of the IP turbine 

stage 2 blades onto the disk, and constitute 

a seal for the local air system. These locking 

plates are pre-bent during manufacture and 

are pressed flat during installation such that 

they fit between grooves in the IP stage 2 disk 

and blades. There are 16 locking plates, Part 

Number (P/N) KH12922 or P/N KH16183, 

installed on an IP turbine stage 2 assembly. 

It is possible that parts, manufactured by this 

supplier, may have cracked during module 

assembly, without those cracks being 

detectable prior to release to service of an 

engine. Propagation of cracks during engine 

operation may lead to loss of a locking plate. 

Missing locking plates will allow hot gas 

ingestion which will locally overheat the 

blade retention features of the disk. 

This condition, if not detected and 

corrected, could lead to accelerated fatigue of 

the blade retention features of the disk and 

release of one or more IP turbine stage 2 

blades, possibly resulting in high energy 

uncontained debris release from the engine, 

with consequent damage to, and reduced 

control of, the aeroplane. 

You may obtain further information 

by examining the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0652. 

Related Service Information Under 1 

CFR Part 51 

RR has issued Alert Non-Modification 

Service Bulletin (NMSB) Trent XWB 

72–AJ738, dated April 11, 2017. The 

NMSB describes procedures to inspect 

the IP turbine stage 2 locking plates. 

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. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of EASA, and is 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with the European 

Community, EASA has notified us of 

the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all 

information provided by EASA and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

products of the same type design. This 

AD requires inspection of the IP turbine 

stage 2 locking plates. 

FAA’s Determination of the Effective 

Date 

No domestic operators use this 

product. Therefore, we find that notice 

and opportunity for prior public 

comment are unnecessary and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Costs of Compliance 

We estimate that this AD affects 0 

engine installed on airplanes of U.S. 

registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on 

U.S. operators 

Inspection ................................ 3 work-hours × $85 per hour = $255 ..................................... $0 $255 $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. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to engines, propellers, and 

associated appliances to the Manager, 

Engine and Propeller Standards Branch, 

Policy and Innovation Division. 

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 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 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: 

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): 

2017–17–07 Rolls-Royce plc: Amendment 

39–18997; Docket No. FAA–2017–0652; 

Product Identifier 2017–NE–18–AD. 

(a) Effective Date 

This AD is effective September 12, 2017. 


asabaliauskas on DSKBBXCHB2PROD with RULES
Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations 40683 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce plc (RR) 

Trent XWB–75, Trent XWB–79, Trent XWB– 

79B, and Trent XWB–84 turbofan engines 

with an engine serial number (S/N) listed in 

Appendix 1 of RR Alert Non-Modification 

Service Bulletin (NMSB) Trent XWB 72– 

AJ738, dated April 11, 2017, and with 

intermediate-pressure (IP) turbine stage 2 

locking plates, part number (P/N) KH12922 

or KH16183, installed. 

(d) Subject 

Joint Aircraft System Component (JASC) 

7250, Turbine/Turboprop Engine/Turbine 

Section. 

(e) Reason 

This AD was prompted by a report of 

several IP turbine stage 2 locking plates 

cracked during module assembly. We are 

issuing this AD to prevent failure of the IP 

turbine stage 2 locking plates, uncontained 

release of the IP turbine stage 2 blades, 

damage to the engine, and damage to the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Inspect the IP turbine stage 2 locking 

plates on-wing before exceeding 750 engine 

flight cycles (FCs) since new, or within 100 

engine FCs after the effective date of this AD, 

whichever occurs later. Use the 

Accomplishment Instructions, paragraph 

3.A., of RR Alert NMSB Trent XWB 72– 

AJ738, dated April 11, 2017, to do the 

inspection. 

(2) Thereafter, re-inspect the IP turbine 

stage 2 locking plates at intervals not to 

exceed 750 engine FCs since the last locking 

plate inspection. Use the Accomplishment 

Instructions, paragraph 3.A., of RR Alert 

NMSB Trent XWB 72–AJ738, dated April 11, 

2017, to do the inspection. 

(i) If all IP turbine stage 2 locking plates 

installed on the engine have an S/N 

beginning with 20452, or are not marked 

with an S/N, the repetitive inspection 

required by paragraph (f)(2) of this AD is not 

required. 

(ii) If one or more IP turbine stage 2 locking 

plates are missing, remove the engine from 

service within the compliance times 

specified in the Accomplishment 

Instructions, paragraph 3.A.(3), of RR Alert 

NMSB Trent XWB 72–AJ738, dated April 11, 

2017. 

(3) Inspect the IP turbine stage 2 locking 

plates during the next engine shop visit 

(ESV) after the effective date of this AD. 

(i) Use the Accomplishment Instructions, 

paragraph 3.B., of RR Alert NMSB Trent 

XWB 72–AJ738, dated April 11, 2017, to do 

this inspection. This in-shop inspection may 

be substituted for the on-wing inspection 

required by paragraphs (f)(1) and (2) of this 

AD. 

(ii) If one or more IP turbine stage 2 locking 

plates are missing, use the acceptance criteria 

in the Accomplishment Instructions, 

paragraph 3.B.(3), of RR Alert NMSB Trent 

XWB 72–AJ738 dated April 11, 2017, to 

disposition the engine. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

install an engine unless the IP turbine stage 

2 locking plates were inspected using the 

Accomplishment Instructions, paragraph 3.A. 

or 3.B., of RR Alert NMSB Trent XWB 72– 

AJ738, dated April 11, 2017. 

(h) Definition 

For the purpose of this AD, an ESV is when 

the engine is subject to a serviceability check 

and repair, rebuild, or overhaul. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, FAA, ECO Branch, 

Compliance and Airworthiness Division, 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. 

(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. 

(j) Related Information 

(1) For more information about this AD, 

contact Robert Green, Aerospace Engineer, 

FAA, ECO Branch, Compliance and 

Airworthiness Division, 1200 District 

Avenue, Burlington, MA 01803; phone: 781– 

238–7754; fax: 781–238–7199; email: 

robert.green@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2017–0088, dated May 16, 

2017, for more information. You may 

examine the MCAI in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating it in Docket No. 

FAA–2017–0642. 

(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. 

(i) Rolls-Royce plc (RR) Alert NonModification Service Bulletin Trent XWB 72– 

AJ738, dated April 11, 2017. 

(ii) Reserved. 

(3) For RR service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, 

England, DE24 8BJ; phone: 011–44–1332– 

242424; fax: 011–44–1332–249936; email: 

http://www.rolls-royce.com/contact/civil_

team.jsp; Internet: https://customers.rollsroyce.com/public/rollsroycecare. 

(4) You may view this service information 

at FAA, Engine and Propeller Standards 

Branch, Policy and Innovation Division, 1200 

District Avenue, Burlington, MA 01803. 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/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

August 16, 2017. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2017–18133 Filed 8–25–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0472; Product 

Identifier 2016–NM–148–AD; Amendment 

39–19002; AD 2017–17–12] 

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 A310–203, –221, –222, 

–304, –322, –324, and –325 airplanes. 

This AD was prompted by an evaluation 

by the design approval holder indicating 

that the wing bottom skin at the main 

landing gear (MLG) reinforcing plate is 

subject to widespread fatigue damage 

(WFD). This AD requires a modification 

of the wing bottom skin at the MLG 

reinforcing plate. We are issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective October 2, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 2, 2017. 

ADDRESSES: For service information 

identified in this final rule, 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. You may view this 

referenced service information at the 

FAA, Transport Standards Branch, 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–2017– 

0472. 


asabaliauskas on DSKBBXCHB2PROD with RULES