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 


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Federal Register / Vol. 76, No. 212 / Wednesday, November 2, 2011 / Rules and Regulations 67595 

4110T53P06) installed. This AD 

requires daily visual inspections of the 

fuel filter differential pressure switch 

for fuel leaks and for excessive cracking 

of the switch mounting flanges due to 

stress-corrosion. This AD also requires 

the installation of a collar kit over the 

fuel filter differential pressure switch as 

terminating action to the daily 

inspections. This AD was prompted by 

reports of 47 fuel filter differential 

pressure switches found with stresscorrosion cracking of the mounting 

flanges. We are issuing this AD to 

prevent unrecoverable in-flight engine 

shutdown, engine bay fire due to fuel 

leakage, and forced landing or accident. 

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, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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 GE-Aviation, M/D Rm. 

285, One Neumann Way, Cincinnati, 

OH 45215, phone: (513) 552–3272; 

email: geae.aoc@ge.com. 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. 

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. 

FOR FURTHER INFORMATION CONTACT: 

Walter Meibaum, Aerospace Engineer, 

Engine & Propeller Directorate, FAA, 

12 New England Executive Park, 

Burlington, MA 01803; phone: (781) 

238–7119; fax: (781) 238–7199; email: 

walter.meibaum@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Since March of 2011, we have 

received reports of 47 fuel filter 

differential pressure switches found 

with cracked mounting flanges. The 

pressure switch, P/N TD028VF0H7Y5, 

is part of the fuel filter assembly, P/N 

4110T53P06. Investigation has revealed 

that the two cap screws securing the 

switch to the fuel filter assembly, apply 

a bending stress to the aluminum 

mounting flanges of the switch. This 

bending stress, coupled with 

contaminants in the operating 

environment, can lead to stresscorrosion cracking of the mounting 

flanges on the switch. This condition, if 

not corrected, could result in 

unrecoverable in-flight engine 

shutdown, engine bay fire due to fuel 

leakage, and forced landing or accident. 

Relevant Service Information 

We reviewed GE Alert Service 

Bulletin (ASB) No. CT7–8–S/B 73– 

A0007, dated July 8, 2011, and ASB No. 

CT7–8–S/B 73–A0008, dated August 17, 

2011. The service information describes 

procedures for performing daily visual 

inspections of the fuel filter differential 

pressure switch for fuel leaks and for 

excessive cracking of the switch 

mounting flanges, and for installing a 

collar kit over the fuel filter differential 

pressure switch as terminating action to 

the daily inspections. The collar kit will 

retain the pressure switch from 

separating from the filter head of the 

fuel filter assembly due to cracks in the 

pressure switch flanges, and will 

prevent the pressure switch from 

leaking. 

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. 

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 about 20% of the affected 

fuel filter differential pressure switches 

in service have been found cracked. 

Many of the affected engines are used 

on Sikorsky S–92 helicopters in offshore 

applications. 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–2011–0942 and Directorate 

Identifier 2011–NE–29–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 

80 engines installed on helicopters of 

U.S. registry. We also estimate that it 

would take about 0.1 work-hour per 

engine to perform a daily visual 

inspection and about 0.1 hour to install 

a collar over the fuel filter differential 

pressure switch. The average labor rate 

is $85 per work-hour. Required parts 

would cost about $200 per engine. 

Based on these figures, we estimate the 

total cost of the AD for one visual 

inspection and installation of the collar 

to U.S. operators to be $17,360. 

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: 


sroberts on DSK5SPTVN1PROD with RULES
67596 Federal Register / Vol. 76, No. 212 / Wednesday, November 2, 2011 / Rules and Regulations 

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): 

2011–21–17 General Electric Company: 

Amendment 39–16840; Docket No. 

FAA–2011–0942; Directorate Identifier 

2011–NE–29–AD. 

(a) Effective Date 

This AD is effective November 17, 2011. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to General Electric 

Company (GE) CT7–8A, CT7–8A1, CT7–8E, 

and CT7–8F5 turboshaft engines, with fuel 

filter differential pressure switch, part 

number (P/N) TD028VF0H7Y5 (part of fuel 

filter assembly, P/N 4110T53P06), installed. 

(d) Unsafe Condition 

This AD was prompted by reports of 47 

fuel filter differential pressure switches 

found with stress-corrosion cracking of the 

mounting flanges. We are issuing this AD to 

prevent unrecoverable in-flight engine 

shutdown, engine bay fire due to fuel 

leakage, and forced landing or accident. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Starting on the effective date of this AD, 

perform daily visual inspections of the fuel 

filter differential pressure switch for leaks 

and excessive cracking of the mounting 

flanges. 

(2) Visually inspect in accordance with 

paragraph 3, Accomplishment Instructions, 

of GE Alert Service Bulletin (ASB) No. CT7– 

8–S/B 73–A0007, dated July 8, 2011. 

(f) Mandatory Terminating Action 

(1) As mandatory terminating action to the 

daily visual inspections, within 4 months 

after the effective date of this AD, install 

collar kit, P/N 59TC02800K1T, over the fuel 

filter differential pressure switch. 

(2) Install the collar kit in accordance with 

paragraph 3, Accomplishment Instructions of 

GE ASB No. CT7–8–S/B 73–A0008, dated 

August 17, 2011. 

(g) Special Flight Permits 

Special flight permits are prohibited. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. 

(i) Related Information 

For more information about this AD, 

contact Walter Meibaum, Aerospace 

Engineer, Engine & Propeller Directorate, 

FAA, 12 New England Executive Park, 

Burlington, MA 01803; phone: (781) 238– 

7119; fax: (781) 238–7199; email: 

walter.meibaum@faa.gov. 

(j) 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) General Electric Company Alert Service 

Bulletin No. CT7–8–S/B 73–A0007, dated 

July 8, 2011, approved for IBR as of 

November 17, 2011. 

(2) General Electric Company Alert Service 

Bulletin No. CT7–8–S/B 73–A0008, dated 

August 17, 2011, approved for IBR as of 

November 17, 2011. 

(3) For service information identified in 

this AD, contact GE-Aviation, M/D Rm. 285, 

One Neumann Way, Cincinnati, OH 45215, 

phone: (513) 552–3272; email: 

geae.aoc@ge.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 4, 2011. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–28353 Filed 11–1–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2011–0431; Airspace 

Docket No. 11–AGL–11] 

Amendment of Class E Airspace; 

Spearfish, SD 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action amends Class E 

airspace at Spearfish, SD, to 

accommodate new Area Navigation 

(RNAV) Standard Instrument Approach 

Procedures at Black Hills Airport— 

Clyde Ice Field, and updates the 

geographic coordinates of the airport. 

There also is a minor correction to the 

coordinates of controlled airspace 1,200 

feet above the surface, and a minor 

change in the airport name. The FAA is 

taking this action to enhance the safety 

and management of Instrument Flight 

Rule (IFR) operations at the airport. 

DATES: Effective date: 0901 UTC, 

February 9, 2012. The Director of the 

Federal Register approves this 

incorporation by reference action under 

1 CFR part 51, subject to the annual 


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