[4910-13-P]DEPARTMENTOFTRANSPORTATIONFederalAviationAdministration14CFRPart39[DocketNo.FAA-2014-0462;DirectorateIdentifier2014-NE-06-AD]RIN2120-AA64AirworthinessDirectives;Rolls-RoyceCorporationTurbopropandTurbofanEnginesAGENCY:FederalAviationAdministration(FAA),DOT.ACTION:Noticeofproposedrulemaking(NPRM).SUMMARY:Weproposetoadoptanewairworthinessdirective(AD)forcertainRollsRoyceCorporation(RRC)AE2100seriesturbopropenginesandAE3007Aand3007Cseriesturbofanengines.ThisproposedADwaspromptedbyreportsofpittinginthewheelboresandsubsequentRRCanalysisthatconcludedthatlowerlifelimitsareneededfortheaffectedturbinewheels.ThisproposedADwouldreducetheapprovedlifelimitsoftheaffectedturbinewheels.ThisproposedADwouldalsorequireaneddycurrentinspection(ECI)ofcertainRRCengineswithaffectedturbinewheels.WeareproposingthisADtopreventuncontainedfailureoftheturbinewheels,damagetotheengine,anddamagetotheairplane.DATES:WemustreceivecommentsonthisproposedADby[INSERTDATE60DAYSAFTERDATEOFPUBLICATIONINTHEFederalRegister].ADDRESSES:Youmaysendcomments,usingtheproceduresfoundin14CFR11.43and11.45,byanyofthefollowingmethods:•FederaleRulemakingPortal:Gotohttp://www.regulations.gov.Followtheinstructionsforsubmittingcomments.•Fax:202-493-2251.• Mail: U.S. Department

of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W
l 2-l40, 1200 New Jersey Avenue SE., Washington,
DC 20590.

• Hand Delivery: Deliver
to Mail address above between

9 a.m. and 5 p.m.

, Monday through Friday, except Federal holidays. For service information identified

in this proposed AD, contact Rolls-Royce Corporation, 450 South Meridian Street, Mail Code NB-01-06, Indianapo

l is, IN 46225

, phone: 317-230-1667; email: CMSEindyOSD@rolls-royce.com;
Internet: www.rollsroyce.com. You may view this service information

at the FAA

, Engine

& Propeller Directorate,

12 New England Executive Park, Bur

l ington, MA. For information

on the availability

of this material

at the FAA

,call 781-238-7125. Exa minin g t h e A D Do c ke t You may examine the AD docket on the Internet

at http://www.regulations.gov

by searching for and locating Docket No. F AA-20 14-0462;
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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527)

is in the ADDRESSES section. Comments will be available

in the AD docket

s hortly after receipt. FOR FURTHER INFORMATION CONTACT: Kyri Zaroyiannis, Aerospace Engineer, Chicago Aircraft Certification Office, Small Airplane Directorate

,FAA

, 2300 E. Devon Ave., Des Plaines

,IL 60018

; phone: 847-294-7836;
fax: 847-294-7834

; email: kyri .zaroyiannis@faa.
gov.

2SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views

,or arguments about this proposal. Send your comments

to an address listed under the ADDRESSES section. Include

" Docket No. FAA-2014-0462; Directorate Identifier 2014-NE-06-AD"

at the beginning
of your comments. We specifically invite comments
on the overall regulatory, economic, environmental,
and energy aspects of this proposed AD. We will consider
all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we re ceive, without change,
to http: // www.regulations.gov, including any personal information you provide. We will also post

a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion In s pection

s during the manufacturing process revealed higher than normal pitting in the bore of certain turbine wheels due to a permanganate cleaning process. Analysis and subsequent testing by RRC of these affected turbine wheels indicated that these wheels, because of the potential for pitting
in the wheel bores

,could not be operated safely up to their published life limits

.For RRC AE 2100 series turboprop eng ine s, the affected turbine whee

l s are identified

as
1 51 stage gas generator turbine wheels and as 4 1 h stage turbine wheels. For the RRC AE 3007 A and 3007C series turbofan engines

,the affected turbine wheels are identified

as high-pressure turbine (HPT) stage

1 and stage

2 wheels. Operation
of the affected wheels above the new lower limits represents
an unsafe condition. We are also proposing
an ECI for certain RRC AE 3007A engines with affected turbine wheels because our risk anal ysis shows that these engines are operated
in a more 3stringent environment and therefore require periodic inspections

to ensure these engine

s are operated safe ly. This condition,

if not corrected, could result in uncontained failure of the turbine wheels, damage
to the engine, and damage
to the airplane. Relevant Service Information We reviewed RRC Alert Service Bulletin (AS B) No. AE 210002-A-72-085, dated July 25

, 2013; RRC ASB No. AE 210003-A-72-277, dated July 25, 2013; RRC ASB No. AE 2100P -A-72 -019, dated July 25, 2013; RRC ASB No. AE 3007A-A-72- 407

, Revi

s i on

1 ,dated August 29, 2014; RRC ASB No. AE 3007A-A-72-408, Revision 1, dated August 29, 2014; and RRC ASB No. AE 3007C-A-72-316, dated December

6. 2013. RRC ASB No. AE 3007A-A-72-408 provides instructions

on performing

an ECI of affected HPT stage

2 wheels. The other RRC ASBs list the lower approved life limits of the affected turbine wheels. FAA's Determination We are proposing this AD because we evaluated
all the relevant information and determined
the unsafe condition described previously

is likely to exist or develop

in other products of the same type design. Proposed AD Requirements Thi
s propo se d AD would require an ECI of certain RRC engines with affected turbine wheels, and reduce the life limits of the affected turbine wheels. Costs of Compliance We estimate that this proposed AD would affect 664 engines installed on airplanes
of U.S. registry. We also estimate that it would take about

1 hour to perform
an ECI in the bore of the turbine wheel for affected engines. The average labor rate is $85 per work-hour. We estimate the pro-rated replacement cost would be $30,688 for a 1 51 stage gas generator turbine wheel; $63 ,6 93 for an HPT stage

1 wheel; $13,941 for an 4HPT stage

2 wheel; and $13,186 for a 4Lh stage turbine wheel. We also estimate that these parts would be replaced during an engine shop visit at no additional labor cost. Based on these figures, we estimate the total cost of the AD to U.S. operators

to be $11,317,969. 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have

a substantial direct effect on the States

,on the relationship between the national Government and the State

s . or on the distribution
of power and responsibilities among the various levels of government. For the reasons discussed above

,I certify this proposed regulation: ( 1) Is not
a "significant regulatory action" under Executive Order 12866, (2)

I s not
a "s ignificant rule

" und e r the DOT Regulatory Policies and Procedur
es ( 44 FR 110 3 4, Fe bruary 26

, 1979 ),

5(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 n egat ive

,on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects

in 14 CFR Part 39 Air tran sporta tion

, Aircraft, Aviation safety, Incorporation

by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated

to me by the Administrator,

the FAA proposes

to amend 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): Roll-Royce Corporation (Formerly Allison Engine Company): Docket No. FAA-2014-0462; Directorate Identifier 2014 -NE-06-AD. (a) Comments Due Date We must receive comments
by [INSERT DATE 60 DAYS AFTER DATE OF PUBLICATION

IN THE Federal Register]. (b) Affected ADs None.

6(c) Applicability This AD applies
to all Rolls-Royce Corporation (RRC) AE 21 OOD2, 21 OOD2A, 2100D3, and 2100P turboprop engines and AE 3007Al, Al/1, Al/3, AlE, AlP, A2, A3

, C, C 1 ,and C2 turbofan engines: (1) With an installed

1 51 stage gas generator turbine wheel

, part number (PIN) 23079946, 23088906,

or 23089692

,all serial numbers (SINs) listed in Table

2 and Table 3 ofRRC Alert Service Bulletin (ASB) No. AE 2100D2-A-72-085, dated July 25, 2013

; and in Table

2 and Table

3 ofRRC ASB No

.AE 2100D3-A-72-277

,dated July 25,2013. (2) With an installed high-pres

s ure turbine (HPT) stage

1 or HPT stage

2 wheel

, P IN 23 079946

, 2308 8906

, 23088784, 23084520, 23084781, 23088817,

or 23088818,

all SINs
li sted in Table

1 through Table

7 of RRC ASB No. AE 3007 A-A-72-407, Revision 1 ,dated August 29,2014, except those SINs excluded by Table

1 , Table 2, Table 4, and Table

5 ofRRC ASB No. AE 3007A-A-72-407

, Revision

1, dated August 29,2014. (3) With an in s talled HPT stage

2 wheel, PIN 23084520
or 23088818,
all SINs listed in Table

1 and Table

2 of RRC ASB No. AE 3007C-A-72-316, dated December

6, 2013, except tho se SINs excluded by Table

1 o fRRC ASB No. AE 3007C -A-72-316

, dated Decemb

e r 6, 2013. (4) With an installed

4 1 h stage turbine wheel, PIN 23083536

,all SINs listed in Table

2 ofRRC AS B No. AE 2100P-A-72-019, dated Jul y 25,2013. (d) Unsafe Condition This AD was prompted
by reports of pitting in the wheel bores and su b sequent RRC analysis that co nclud

e d that lower life limit

s are needed
fo r the affec ted turbine wheels. We
a r e issuing this AD to pr eve nt uncontained failure of the turbine wheels, damage
to the engine, and damage
to the airp

l ane. (e) Compliance Comply

w i th this AD within the compliance tim es specified, unless already done. 7(1) For all RRC AE 3007Al, Al/1, Al/3, AlE, AlP, and A3 series engines with an HPT stage

2 wheel PIN and SIN identified

in RRC ASB No. AE 3007 A-A-72-408, Revision

1 ,dated August 29,2014,

at each shop visit after the effective date of this AD, eddy current inspect the bore of the affected HPT stage
2 wheels. Use RRC ASB AE 3007A-A-72-408, Revision

1, August 29,2014,

to do the inspection. Do not return to service any wheel that fai
l s the inspection required by this AD. (2) Thirty days after the effective date of this AD, do not return to service any engine that has
a turbine wheel with

a PIN and an SIN listed in any of the following RR ASBs whose wheel life exceeds the new life limits identified

in the RR ASBs: RRC ASB No. AE 2100D2-A-72-085, dated July 25, 2013; RRC ASB No. AE 21 0003-A-72-277, dated Ju
l y 25, 2013; RRC ASB No. AE 2100P-A-72-019

,dated July 25, 2013; RRC ASB No. AE 3007A-A-72-407, Revision

1, dated August 29, 2014; or RRC ASB No. AE 3007C-A-72-316, dated December

6, 2013. (f) Installation Prohibition Thirty days after the effective date of this AD, do not install an affected wheel, as identified

in paragraph
(c) of this AD, into any RRC AE 3007C2 engine. (g) Definition For the purpose of this AD, an "e ngine shop visit" is the induction
of an engine into the shop for maintenance involving the separation
of pairs of major mating engine flanges, except that the separation
of engine flanges solely for the purposes
of transportation without subsequent engine maintenance

is not an engine shop visit. (h) Alternative Methods
of Compliance (AMOCs) The Manager, Chicago Aircraft Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. 8(i) Related Information (1) For more information about this AD, contact Kyri Zaroyiannis, Aerospace Engineer, Chicago Aircraft Certification Office, Small Airplane Directorate, FAA, 2300 E. Devon Ave., Des Plaines, IL 60018; phone: 847-294-7836;
fax: 847-294-7834; email

: kyri .zaroyiannis@faa.
gov. (2) RRC ASB No. AE 2100D2-A-72-085, dated July 25, 2013; RRC ASB No. AE 2100D3-A-72-277, dated July 25, 2013; RRC ASB No. AE 2100P-A-72-019, dated July 25, 2013; RRC ASB No. AE 3007A-A-72-407, Revision

1, dated August 29, 2014; RRC ASB No. AE 3007A-A-72-408, Revision

1, dated August 29, 2014; and RRC ASB No. AE 3007C-A-72-316, dated December

6, 2013, which are not incorporated

by reference in this AD, can be obtained from RRC using the contact information

in paragraph (i)(3) of this AD. (3) For service information identified in this AD, contact Rolls-Royce Corporation, 450 South Meridian Street, Mail Code NB-0 1-06, Indianapolis

,IN 46225

, phone: 317-230-1667; email: CMSEindyOSD@rolls-royce.com;
Internet: www.rollsroyce. com. (4) 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. I ssued in Burlington, Massachusetts,

on September 25, 2014. Colleen M. D' Alessandro, Assistant Directorate Manager

, Engine

& Propeller Directorate

, Aircraft Certification Service.

9