Federal Register / Vol. 76, No. 212 / Wednesday, November 2, 2011 / Rules and Regulations 67591 

NCUA and must agree to examination 

by NCUA. 

§ 705.9 Reporting and monitoring. 

(a) General. NCUA’s policy is to 

monitor Participating Credit Unions to 

assure that loan and technical assistance 

grant funds awarded under this Part 

have been used in accordance with their 

intended purposes and to determine 

whether anticipated outcomes have 

been achieved. Particular emphasis will 

be placed on reviewing loan funds 

earmarked for programs or initiatives 

proposed by the Participating Credit 

Union to determine if the funds have 

been used as represented and whether 

the program or initiative has had the 

impact anticipated by the Participating 

Credit Union. 

(b) Reporting. A Participating Credit 

Union must complete and submit all 

required reports, at such times and in 

such formats as NCUA will direct. Such 

reports must describe how the 

Participating Credit Union has used the 

loan or technical assistance grant 

proceeds and the results it has obtained, 

in relation to the programs, policies, or 

initiatives identified by the Participating 

Credit Union in its application. In 

addition, the Participating Credit 

Union’s board of directors must report 

on the progress of providing needed 

community services to the Participating 

Credit Union’s members once a year, 

either at the annual meeting or in a 

written report sent to all members. The 

Participating Credit Union must also 

submit to NCUA the written report or a 

summary of the report given at the 

annual meeting. NCUA may request 

additional information as it determines 

appropriate. 

(c) Monitoring. At its discretion, for 

verification purposes and as part of its 

evaluation of the effectiveness of the 

loan and technical assistance grant 

programs, NCUA may elect to review 

information concerning Participating 

Credit Unions to which it already has 

access, including information obtained 

through the examination process and 

data contained in Call Reports. 

§ 705.10 Technical assistance grants. 

Technical assistance grants may be 

funded in such amounts, and in 

accordance with such terms and 

conditions, as NCUA may establish. In 

general, technical assistance grants are 

provided on a reimbursement basis, to 

cover expenditures approved in advance 

by NCUA and supported by receipts 

evidencing payment by the Participating 

Credit Union. 

(a) Permissible uses of technical 

assistance grant funds. Section 705.4(a) 

and (b) of this part also apply to 

technical assistance grants made under 

this section. Those sections provide 

examples and other information with 

respect to the permissible use of CDRLF 

funds. In addition, technical assistance 

grants generally should enhance and 

support the Participating Credit Union’s 

internal capacity to serve its members 

and better enable it to provide financial 

services to the community in which the 

Participating Credit Union is located. 

(b) Appeals of technical assistance 

grant reimbursement denials. Pursuant 

to NCUA Interpretative Ruling and 

Policy Statement 11–1, any Participating 

Credit Union may appeal a denial of a 

technical assistance grant 

reimbursement to NCUA’s Supervisory 

Review Committee. All appeals of 

technical assistance grant 

reimbursements must be submitted to 

the Supervisory Review Committee 

within 30 days from the date of the 

denial. The decisions of the Supervisory 

Review Committee are final and may 

not be appealed to the NCUA Board. 

PART 741—REQUIREMENTS FOR 

INSURANCE 

■ 4. The authority citation for part 741 

continues to read as follows: 

Authority: 12 U.S.C. 1757, 1766(a), 1781— 

1790, and 1790d; 31 U.S.C. 3717. 

§ 741.207 [Amended] 

■ 5. Section 741.207 is amended by 

removing the citation ‘‘§ 705.3’’ and 

adding in its place the citation 

‘‘§ 705.2’’. 

[FR Doc. 2011–28335 Filed 11–1–11; 8:45 am] 

BILLING CODE 7535–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0273; Directorate 

Identifier 2011–NE–08–AD; Amendment 39– 

16845; AD 2011–22–03] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Corporation Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for RollsRoyce Corporation (RRC) AE 3007A, AE 

3007A1/1, AE 3007A1, AE 3007A1/3, 

AE 3007A1E, AE 3007A1P, and AE 

3007A3 turbofan engines. This AD 

requires initial and repetitive eddy 

current inspections (ECI) of certain 6ththrough-13th stage compressor wheel 

knife edge seals, and initial and 

repetitive ECIs of the compressor wheel 

outer circumference, for cracks. This AD 

was prompted by reports of low-cycle 

fatigue cracks found during shop visits, 

in the 6th-through-13th stage 

compressor wheels having chromecarbide coated or uncoated knife edge 

seals. We are issuing this AD to prevent 

uncontained failure of the 6th-through13th stage compressor wheel, leading to 

damage to the airplane. 

DATES: This AD is effective November 

17, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 17, 2011. 

We must receive comments on this 

AD by December 19, 2011. 

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. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this AD, contact Rolls-Royce 

Corporation, P.O. Box 420, Indianapolis, 

IN 46206; phone: (317) 230–3774; fax: 

(317) 230–6084; email: 

indy.pubs.services@rolls-royce.com. 

You may review copies of the 

referenced 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; 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 Office (phone: (800) 647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 


sroberts on DSK5SPTVN1PROD with RULES
67592 Federal Register / Vol. 76, No. 212 / Wednesday, November 2, 2011 / Rules and Regulations 

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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received reports of low-cycle 

fatigue cracks found during shop visits, 

in the 6th-through-13th stage 

compressor wheels having chromecarbide coated or uncoated knife edge 

seals, on RRC AE 3007A, AE 3007A1/1, 

AE 3007A1, AE 3007A1/3, AE 3007A1E, 

AE 3007A1P, and AE 3007A3 turbofan 

engines. These cracks can deteriorate 

the integrity of the compressor wheel by 

lengthening into the outer 

circumference of the wheel. This 

condition, if not corrected, could result 

in uncontained failure of the 6ththrough-13th stage compressor wheel, 

leading to damage to the airplane. 

Relevant Service Information 

We reviewed RRC Alert Service 

Bulletin (ASB) No. AE 3007A–A–72– 

386, Revision 4, dated June 27, 2011, 

which describes procedures for 

performing a one-time comprehensive 

ECI of the compressor wheel outer 

circumference, for cracks. We also 

reviewed RRC ASB No. AE 3007A–A– 

72–390, Revision 3, dated June 27, 2011, 

which describes procedures for initial 

and repetitive inspections of affected 

6th-through-13th stage compressor 

wheel knife edge seals and the 

compressor wheel outer circumference, 

for cracks. 

FAA’s Determination 

We are issuing 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. 

AD Requirements 

This AD requires accomplishing the 

actions specified in the service 

information described previously. The 

AD also requires sending the inspection 

results to AE Service Data, Rolls-Royce 

Corporation, Attn: AE Service Data 

Manager, P.O. Box 420, Speed Code 

U17, Indianapolis, IN 46206–0420, 

email: cra.rel.data@rolls-royce.com. 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because our risk assessment 

indicates these parts, uninspected, pose 

an unacceptable level of risk to the 

traveling public. Therefore, we find that 

notice and opportunity for prior public 

comment are impracticable and that 

good cause exists for making this 

amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2011–0273 and Directorate 

Identifier 2011–NE–08–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 we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD will affect 

1,402 RRC AE 3007A, AE 3007A1/1, AE 

3007A1, AE 3007A1/3, AE 3007A1E, AE 

3007A1P, and AE 3007A3 turbofan 

engines installed on 616 airplanes of 

U.S. registry. We also estimate that it 

will take about 6 hours to perform one 

inspection of the affected 6th-through13th stage compressor wheel knife edge 

seals and the compressor wheel outer 

circumference, for each engine. The 

average labor rate is $85 per work-hour. 

We anticipate required parts costs to be 

$35,546,000. Based on these figures, we 

estimate the total cost of the AD to U.S. 

operators to be $36,259,926. 

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, 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): 

2011–22–03 Rolls-Royce Corporation 

(Formerly Allison Engine Company): 

Amendment 39–16845; Docket No. 

FAA–2011–0273; Directorate Identifier 

2011–NE–08–AD. 

(a) Effective Date 

This AD is effective November 17, 2011. 


sroberts on DSK5SPTVN1PROD with RULES
Federal Register / Vol. 76, No. 212 / Wednesday, November 2, 2011 / Rules and Regulations 67593 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce 

Corporation (RRC) AE 3007A, AE 3007A1/1, 

AE 3007A1, AE 3007A1/3, AE 3007A1E, AE 

3007A1P, and AE 3007A3 turbofan engines, 

with any of the 6th-through-13th stage 

compressor wheel part numbers (P/Ns) in 

Table 1 of this AD installed. 

TABLE 1—6TH-THROUGH-13TH STAGE COMPRESSOR WHEEL P/NS AFFECTED BY THIS AD 

Compressor wheel stage 

Wheel P/Ns with 

chrome-carbide coated 

knife seals 

Wheel P/Ns with uncoated knife 

seals 

6th ........................................................................................................................ 23074717 23062666, 23071261, 23071396 

7th ........................................................................................................................ 23074719, 23074217 23062667, 23071262, 23071397 

8th ........................................................................................................................ 23074721 23061628, 23071263 

9th ........................................................................................................................ 23074722 23061629, 23071264 

10th ...................................................................................................................... 23074723 23061630, 23071265 

11th ...................................................................................................................... 23074724 23061631, 23066231 

12th ...................................................................................................................... 23074725 23061632, 23071267 

13th ...................................................................................................................... 23074213, 23074726 23061633, 23071268 

(d) Unsafe Condition 

This AD was prompted by reports of lowcycle fatigue cracks found during shop visits, 

in the 6th-through-13th stage compressor 

wheels having chrome-carbide coated or 

uncoated knife edge seals. We are issuing this 

AD to prevent uncontained failure of the 6ththrough-13th stage compressor wheel, 

leading to damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Initial Inspection 

The initial inspection compliance times for 

the 6th-through-13th stage compressor 

wheels are based on cycles-since-new (CSN) 

and cycles-in-service (CIS) of their 12th and 

13th stage compressor wheels. For engines 

that one or both 12th and 13th stage 

compressor wheels have chrome-carbide 

coated knife edge seals, use the compliance 

times listed in Table 2 of this AD. For 

engines that both 12th and 13th stage 

compressor wheels do not have chromecarbide coated knife edge seals, use the 

compliance times listed in Table 3 of this 

AD. 

(1) Perform a one-time comprehensive 

eddy current inspection (ECI) of the 6ththrough-13th stage compressor wheel knife 

edge seals for cracks, using paragraph 2, 

Accomplishment Instructions, of RRC Alert 

Service Bulletin (ASB) No. AE 3007A–A–72– 

386, Revision 4, dated June 27, 2011 

(Completion of this one-time comprehensive 

ECI relieves you thereafter of the repetitive 

inspection requirements of this AD); or 

(2) Perform an initial ECI of the 6ththrough-13th stage compressor wheel outer 

circumferences for cracks, using paragraph 2, 

Accomplishment Instructions, of RRC ASB 

No. AE 3007A–A–72–390, Revision 3, dated 

June 27, 2011. 

TABLE 2—INITIAL INSPECTION COMPLIANCE TIMES FOR ENGINES, THAT ONE OR BOTH 12TH AND 13TH STAGE

COMPRESSOR WHEELS HAVE CHROME-CARBIDE COATED KNIFE EDGE SEALS

For 12th and or 13th stage 

compressor wheels with the 

following CSN on the effective 

date of this AD 

Initially inspect after the effective date of this AD 

(i) 18,185 or more CSN .................. Within 15 CIS. 

(ii) 16,700 to 18,184 CSN ............... Before accumulating 18,200 CSN. 

(iii) 16,000 to 16,699 CSN .............. Within 1,500 CIS. 

(iv) 15,100 to 15,999 CSN .............. Within 2,000 CIS. 

(v) 14,300 to 15,099 CSN ............... Within 2,800 CIS. 

(vi) 13,000 to 14,299 CSN .............. Within 3,400 CIS. 

(vii) 12,300 to 12,999 CSN ............. Within 4,000 CIS. 

(viii) 11,200 to 12,299 CSN ............ Within 4,600 CIS. 

(ix) 9,700 to 11,199 CSN ................ Within 5,300 CIS. 

(x) Fewer than 9,700 CSN .............. Before accumulating 15,000 CSN or at the next shop visit when the engine has more than 7,000 cycles, 

whichever occurs first. 

TABLE 3—INITIAL INSPECTION COMPLIANCE TIMES FOR ENGINES, THAT BOTH 12TH AND 13TH STAGE COMPRESSOR

WHEELS DO NOT HAVE CHROME-CARBIDE COATED KNIFE EDGE SEALS

For 12th and or 13th stage 

compressor wheels with the 

following CSN on the effective 

date of this AD: 

Initially inspect after the effective date of this AD: 

(i) 18,300 or more CSN .................. Within 200 CIS. 

(ii) 16,000 to 18,299 CSN ............... Within 1,500 CIS. 

(iii) 15,100 to 15,999 CSN .............. Within 2,000 CIS. 

(iv) 14,300 to 15,099 CSN .............. Within 2,800 CIS. 

(v) 13,000 to 14,299 CSN ............... Within 3,400 CIS. 

(vi) 12,300 to 12,999 CSN .............. Within 4,000 CIS. 

(vii) 11,200 to 12,299 CSN ............. Within 4,600 CIS. 

(viii) 9,700 to 11,199 CSN .............. Within 5,300 CIS. 


sroberts on DSK5SPTVN1PROD with RULES
67594 Federal Register / Vol. 76, No. 212 / Wednesday, November 2, 2011 / Rules and Regulations 

TABLE 3—INITIAL INSPECTION COMPLIANCE TIMES FOR ENGINES, THAT BOTH 12TH AND 13TH STAGE COMPRESSOR

WHEELS DO NOT HAVE CHROME-CARBIDE COATED KNIFE EDGE SEALS—Continued 

For 12th and or 13th stage 

compressor wheels with the following CSN on the effective date of 

this AD: 

Initially inspect after the effective date of this AD: 

(ix) Fewer than 9,700 CSN ............. Before accumulating 15,000 CSN or at the next shop visit when the engine has more than 7,000 cycles, 

whichever occurs first. 

(g) Repetitive Inspections 

(1) After passing the initial inspection, 

perform repetitive ECIs of the compressor 

wheel outer circumference, for cracks, within 

every 5,000 cycles-since-last-inspection 

(CSLI), using paragraph 2, Accomplishment 

Instructions, of RRC ASB No. AE 3007A–A– 

72–390, Revision 3, dated June 27, 2011; or 

(2) Perform a one-time comprehensive ECI 

of the 6th-through-13th stage compressor 

wheel knife edge seals for cracks, within 

5,000 CSLI using paragraph 2, 

Accomplishment Instructions, of RRC ASB 

No. AE 3007A–A–72–386, Revision 4, dated 

June 27, 2011. Completion of this one-time 

ECI comprehensive inspection relieves you 

thereafter of the repetitive inspection 

requirements of this AD. 

(h) 6th-Through-13th Stage Compressor 

Wheels Found Cracked 

Remove from service before further flight 

6th-through-13th stage compressor wheels 

that are found cracked. 

(i) Special Flight Permits 

Special Flight Permits are limited to 

essential flight crew only. 

(j) Reporting Requirements 

Report all inspection results within 10 

days, to AE Service Data, Rolls-Royce 

Corporation, Attn: AE Service Data Manager, 

P.O. Box 420, Speed Code U17, Indianapolis, 

IN 46206–0420, email: cra.rel.data@rollsroyce.com. Use the reporting instructions in: 

(1) Paragraph 2.D. of ASB No. AE 3007A– 

A–72–386, Revision 4, dated June 27, 2011. 

(2) Service Bulletin Compliance Form of 

RRC ASB No. AE 3007A–A–72–390, Revision 

3, dated June 27, 2011. 

(k) Paperwork Reduction Act Burden 

Statement 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 5 minutes per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave. SW., Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

(l) Previous Inspection Credit 

(1) If you previously performed an ECI of 

the 6th-through-13th stage compressor 

wheels using RRC ASB No. AE 3007A–A– 

390, Revision 1, dated February 14, 2011 or 

Revision 2, dated June 10, 2011, or Revision 

3, dated June 27, 2011, you met the initial 

inspection requirements of this AD. 

(2) If you previously performed a one-time 

comprehensive ECI of the 6th-through-13th 

stage compressor wheel knife edge seals, 

using RRC ASB No. AE 3007A–A–72–386, 

dated October 20, 2010, or Revision 1, dated 

December 17, 2010, or Revision 2 dated 

January 10, 2011, or Revision 3, dated June 

10, 2011, you met the initial inspection 

requirements of paragraph (f) of this AD. 

Completion of this one-time comprehensive 

inspection relieves you of the repetitive 

inspection requirements of this AD. 

(3) If you previously performed an 

ultrasonic inspection of the compressor 

wheel knife edge seals, using RRC Service 

Bulletin No. AE 3007A–72–382, dated April 

6, 2010, prior to publication of RRC ASB No. 

AE 3007A–A–72–386, dated October 20, 

2010, you met the initial inspection 

requirements of this AD. Completion of this 

one-time ultrasonic inspection relieves you 

of the repetitive inspection requirements of 

this AD. 

(m) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Chicago Aircraft 

Certification Office, may approve AMOCs for 

this AD. Use the procedures found in 14 CFR 

39.19 to make your request. 

(n) Related Information 

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. 

(o) Material Incorporated by Reference 

You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51 of the 

following service information on the date 

specified: 

(1) Rolls-Royce Corporation Alert Service 

Bulletin No. AE 3007A–A–72–386, Revision 

4, dated June 27, 2011, approved for IBR 

November 17, 2011. 

(2) Rolls-Royce Corporation Alert Service 

Bulletin No. AE 3007A–A–72–390, Revision 

3, dated June 27, 2011, approved for IBR 

November 17, 2011. 

(3) For service information identified in 

this AD, contact Rolls-Royce Corporation, 

P.O. Box 420, Indianapolis, IN 46206; phone: 

(317) 230–3774; fax: (317) 230–6084; email: 

indy.pubs.services@rolls-royce.com. 

(4) You may review copies of the 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. 

(5) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call (202) 741– 

6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html. 

Issued in Burlington, Massachusetts, on 

October 25, 2011. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–28352 Filed 11–1–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0942; Directorate 

Identifier 2011–NE–29–AD; Amendment 39– 

16840; AD 2011–21–17] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

General Electric Company (GE) CT7–8A, 

CT7–8A1, CT7–8E, and CT7–8F5 

turboshaft engines with a fuel filter 

differential pressure switch, part 

number (P/N) TD028VF0H7Y5 (part of 

the fuel filter assembly, P/N 


sroberts on DSK5SPTVN1PROD with RULES