Federal Register / Vol. 76, No. 201 / Tuesday, October 18, 2011 / Proposed Rules 64285 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) RB211-Trent 700 Series Engines—Rear 

Balance Land Inspections 

(1) On-Wing Inspections 

Perform on-wing inspections as follows: 

(i) Within 625 cycles-in-service (CIS) after 

the effective date of this AD, borescope 

inspect the IP compressor rotor shaft rear 

balance land. Use RR Alert Service Bulletin 

(ASB) No. RB.211–72–AG270, Revision 4, 

dated March 21, 2011, sections 3.A.(2)(a) 

through 3.A.(2)(c) and 3.A.(3)(a) through 

3.A.(3)(c), or 3.B.(2)(a) through 3.B.(2)(c) and 

3.B.(4)(a) through 3.B.(4)(c), to do the 

inspection. 

(ii) Thereafter, repeat the inspection within 

every 625 cycles-since-last inspection (CSLI). 

You may count CSLI from the last borescope 

inspection or the last eddy current 

inspection, whichever has occurred last. 

(2) In-Shop Inspections 

At each shop visit, eddy current inspect 

(ECI) and visually inspect the IP compressor 

rotor shaft rear balance land, and visually 

inspect the balance weights. Use RR ASB No. 

RB.211–72–AG085, Revision 2, dated July 7, 

2011, sections 3.A. through 3.D.(3)(b)(v), 

except paragraphs 3.D.(3)(a)(ii) and 

3.D.(3)(b)(iii) to do the inspections. 

(3) RB211-Trent 800 Series Engines—Rear 

Balance Land Inspections 

(1) On-Wing Inspections 

(i) Within 475 CIS after the effective date 

of this AD, borescope inspect the IP 

compressor rotor shaft rear balance land. Use 

RR ASB No. RB.211–72–AG264, Revision 5, 

dated March 21, 2011, sections 3.B.(2)(a) 

through 3.B.(2)(c) and 3.B.(4)(a) through 

3.B.(4)(c) to do the inspection. 

(ii) Thereafter, repeat the inspection within 

every 475 CSLI. You may count CSLI from 

the last borescope inspection or the last eddy 

current inspection, whichever has occurred 

last. 

(2) In-Shop Inspections 

At each shop visit, ECI and visually inspect 

the IP compressor rotor rear shaft balance 

land, and visually inspect the balance 

weights. Use RR ASB No. RB.211–72–AG085, 

Revision 2, dated July 7, 2011, sections 3.A. 

through 3.D.(3)(b)(v), except paragraphs 

3.D.(3)(a)(ii) and 3.D.(3)(b)(iii), to do the 

inspections. 

(h) RB211-Trent 500 Series Engines—InShop Rear Balance Land Inspections 

At each shop visit, ECI the IP compressor 

rotor shaft and visually inspect the balance 

weights. Use RR ASB No. RB.211–72–AF260, 

Revision 5, dated July 7, 2011 sections 3.A. 

through 3.B.(3)(a)(iii) to do the visual 

inspection, or RR SB No. RB.211–72–G448, 

Revision 3, dated July 7, 2011 section 3.D.(1) 

through 3.D.(14) to do the ECI. 

(i) Definition 

For the purposes of this AD, a shop visit 

is defined as introduction of an engine into 

a shop, and disassembly sufficient to expose 

the IP compressor module rear face. 

(j) Optional Terminating Action for RB211- 

Trent 700 and RB211-Trent 800 Engines 

(1) Modifying an RB211-Trent 700 engine 

as specified in RR SB No. RB.211–72–G402, 

Revision 2, dated July 7, 2011, or RR SB No. 

RB.211–72–G402, Revision 1, dated January 

11, 2011, is terminating action for paragraph 

(f)(2) of this AD. 

(2) Modifying an RB211-Trent 800 engine 

as specified in RR SB No. RB.211–72–G401, 

Revision 2, dated July 5, 2011, or SB No. 

RB.211–72–G401, Revision 1, dated January 

11, 2011, is terminating action for paragraph 

(h)(2) of this AD. 

(k) Previous Credit 

(1) For RB211-Trent 700 series engines: 

(i) On-wing inspections done before the 

effective date of this AD using RR ASB No. 

RB.211–72–AG270, Revision 1, dated 

December 14, 2009, or Revision 2, dated 

December 21, 2010, or Revision 3, dated 

February 25, 2011, meet the inspection 

requirements in paragraph (f) of this AD. 

(ii) In-shop inspections done before the 

effective date of this AD using RR ASB No. 

RB.211–72–AG085, Revision 1, dated 

September 27, 2010, meet the inspection 

requirements in paragraph (g) of this AD. 

(2) For RB211-Trent 800 series engines: 

(i) On-wing inspections done before the 

effective date of this AD using RR ASB No. 

RB.211–72–AG264, Revision 3, dated 

December 21, 2010, or Revision 4, dated 

February 25, 2011, meet the inspection 

requirements in paragraph (h) of this AD. 

(ii) In-shop inspections done before the 

effective date of this AD using RR ASB No. 

RB.211–72–AG085, Revision 1, dated 

September 27, 2010, meet the inspection 

requirements in paragraph (i) of this AD. 

(3) For RB211-Trent 500 series engines: 

(i) In-shop visual inspections done before 

the effective date of this AD using RR ASB 

No. RB.211–72–AF260, Revision 4, dated 

July 28, 2009, meet the inspection 

requirements in paragraph (j) of this AD. 

(ii) In-shop ECIs done before the effective 

date of this AD using RR ASB No. RB.211– 

72–G448, Revision 2, dated December 23, 

2010, meet the ECI requirements in 

paragraph (j) of this AD. 

(l) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures in 14 CFR 39.19 to request an 

AMOC. 

(m) Related Information 

(1) For more information about this AD, 

contact Alan Strom, Aerospace Engineer, 

Engine Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA; 

phone: 781–238–7143; fax: 781–238–7199; 

e-mail: alan.strom@faa.gov. 

(2) For service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, 

England, DE248BJ; phone: 011–44–1332– 

242424; fax: 011–44–1332–245418; or e-mail 

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

civil_team.jsp. You may review copies of the 

referenced service information at the FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803. For information on the availability of 

this material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

October 6, 2011. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–26821 Filed 10–17–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0948; Directorate 

Identifier 2009–NE–30–AD] 

RIN 2120–AA64 

Airworthiness Directives; Thielert 

Aircraft Engines GmbH (TAE) Models 

TAE 125–02–99 and TAE 125–01 

Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to revise an 

existing airworthiness directive (AD) for 

the products listed above. This 

proposed AD results from mandatory 

continuing airworthiness information 

(MCAI) issued by an aviation authority 

of another country to identify and 

correct an unsafe condition on an 

aviation product and from a comment 

received from the European Aviation 

Safety Agency (EASA) on AD 2010–06– 

12, (75 FR 12439, March 16, 2010). The 

MCAI describes the unsafe condition as: 

As a consequence of occurrences and 

service experience, Thielert Aircraft Engines 

GmbH has introduced a new rail pressure 

control valve part number (P/N) 05–7320– 

E000702 and has amended the Airworthiness 

Limitation Section (ALS) of the Operation & 

Maintenance Manual OM–02–02 to include a 

replacement of the rail pressure control 

valve. Failure of this part could result in inflight shutdowns of the engine(s). 

TAE has also amended the ALS of the 

Operation & Maintenance Manual OM– 

02–01 to include a replacement of the 

rail pressure valve. We are proposing 

this AD to prevent engine in-flight 

shutdown, possibly resulting in reduced 

control of the aircraft. 

DATES: We must receive comments on 

this proposed AD by November 17, 

2011. 

ADDRESSES: You may send comments by 

any of the following methods: 


srobinson on DSK4SPTVN1PROD with PROPOSALS
64286 Federal Register / Vol. 76, No. 201 / Tuesday, October 18, 2011 / Proposed Rules 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

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. 

Contact Thielert Aircraft Engines 

GmbH, Platanenstrasse 14 D–09350, 

Lichtenstein, Germany, phone: +49– 

37204–696–0; fax: +49–37204–696–55; 

e-mail: info@centurion-engines.com for 

the service information identified in this 

proposed AD. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (phone: 800–647–5527) is the 

same as the Mail address provided in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7143; fax: 781–238– 

7199; e-mail: alan.strom@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2009–0948; Directorate Identifier 

2009–NE–30–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 based on 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 proposed AD. 

Using the search function of the Web 

site, anyone can find and read the 

comments in any of our dockets, 

including, if provided, the name of the 

individual who sent the comment (or 

signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78). 

Discussion 

On March 8, 2010, the FAA issued AD 

2010–06–12, (75 FR 12439, March 16, 

2010). That AD requires initial and 

repetitive replacements of the rail 

pressure control valve. 

Actions Since AD 2010–06–12 Was 

Issued 

Since we issued AD 2010–06–12, (75 

FR 12439, March 16, 2010), EASA, 

which is the Technical Agent for the 

Member States of the European 

Community, informed us that our AD is 

more restrictive than their EASA AD 

2008–0128, dated July 9, 2009. 

Specifically, our paragraph (e)(3), which 

currently states: 

‘‘For TAE 125–01 reciprocating 

engines, within 100 flight hours after 

the effective date of this AD, replace the 

existing rail pressure control valve with 

a rail pressure control valve, P/N 02– 

7320–04100R3’’ should state: 

‘‘For TAE 125–01 reciprocating 

engines, before 600 flight hours timesince-new, or within 100 flight hours 

after the effective date of this AD, 

whichever occurs later, replace the 

existing rail pressure control valve with 

a rail pressure control valve, P/N 02– 

7320–04100R3.’’ 

We agree. We made the suggested 

change in this proposed AD. We also 

deleted the AD Differences paragraph 

(f)(2), which stated: ‘‘For the TAE 125– 

01 reciprocating engines, we changed 

initial compliance time from within the 

next 3 months to within 100 flight hours 

after the effective date of this AD.’’ The 

remainder of this proposed AD is 

unchanged. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of Germany 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. We are proposing 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 proposed AD 

would require initial and repetitive 

replacements of the rail pressure control 

valve. 

Differences Between This Proposed AD 

and the MCAIs or Service Information 

We have reviewed the MCAIs and 

related service information and, in 

general, agree with their substance. But 

we have found it necessary to reduce 

the initial compliance time for TAE 

125–02–99 engines from within 110 

flight hours to within 100 flight hours. 

We also have found it necessary to 

specify the repetitive replacement 

compliance time for the rail pressure 

control valve of within every 600 flight 

hours for both models of engines. The 

MCAIs instruct the operators to follow 

Thielert Maintenance Manual, Chapter 

5, Airworthiness Limitations, for the 

repetitive compliance time, which 

requires replacement of the rail pressure 

control valve within every 600 flight 

hours. In making these changes, we do 

not intend to differ substantively from 

the information provided in the MCAI 

and related service information. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 370 TAE 125–01 and TAE 

125–02–99 reciprocating engines 

installed on products of U.S. registry. 

We also estimate that it would take 

about 1.5 work-hours per engine to 

comply with this proposed AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about $500 

per engine. Based on these figures, we 

estimate the cost of the proposed AD for 

initial replacement, on U.S. operators to 

be $232,175. 

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 


srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 76, No. 201 / Tuesday, October 18, 2011 / Proposed Rules 64287 

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 States, 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. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, 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 

removing Amendment 39–16236, and 

adding the following new AD: 

Thielert Aircraft Engines GmbH: Docket No. 

FAA–2009–0948; Directorate Identifier 

2009–NE–30–AD. 

Comments Due Date 

(a) We must receive comments by 

November 17, 2011. 

Affected Airworthiness Directives (ADs) 

(b) This AD revises AD 2010–06–12, 

Amendment 39–16236. 

Applicability 

(c) This AD applies to Thielert Aircraft 

Engines GmbH (TAE) models TAE 125–01 

and TAE 125–02–99 reciprocating engines 

installed in, but not limited to, Cessna 172 

and (Reims-built) F172 series (European 

Aviation Safety Agency (EASA) 

Supplemental Type Certificate (STC) No. 

EASA.A.S.01527); Piper PA–28 series (EASA 

STC No. EASA.A.S. 01632); APEX (Robin) 

DR 400 series (EASA STC No. A.S.01380); 

and Diamond Aircraft Industries Models 

DA40 and DA42 airplanes. 

Reason 

(d) As a consequence of occurrences and 

service experience, Thielert Aircraft Engines 

GmbH has introduced a new rail pressure 

control valve part number (P/N) 05–7320– 

E000702 and has amended the Airworthiness 

Limitation Section (ALS) of the Operation & 

Maintenance Manual OM–02–02 to include a 

replacement of the rail pressure control 

valve. Failure of this part could result in inflight shutdowns of the engine(s). 

TAE has also amended the ALS of the 

Operation & Maintenance Manual OM–02–01 

to include a replacement of the rail pressure 

valve. This AD results from mandatory 

continuing airworthiness information 

(MCAIs) issued by an aviation authority of 

another country to identify and correct an 

unsafe condition on an aviation product and 

from a comment received from EASA on AD 

2010–06–12. We are issuing this AD to 

prevent engine in-flight shutdown, possibly 

resulting in reduced control of the aircraft. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

TAE 125–02–99 Reciprocating Engines 

(1) For TAE 125–02–99 reciprocating 

engines, within 100 flight hours after the 

effective date of this AD, replace the existing 

rail pressure control valve with a rail 

pressure control valve P/N 05–7320– 

E000702, and modify the Vrail plug to make 

it compatible with the replacement rail 

pressure control valve. 

(2) Guidance on the valve replacement and 

rail modification specified in paragraph (e)(1) 

of this AD can be found in Thielert Repair 

Manual RM–02–02, Chapter 73–10.08, and 

Chapter 39–40.08, respectively. 

TAE 125–01 Reciprocating Engines 

(3) For TAE 125–01 reciprocating engines, 

before 600 flight hours time-since-new, or 

within 100 flight hours after the effective 

date of this AD, whichever occurs later, 

replace the existing rail pressure control 

valve with a rail pressure control valve, P/N 

02–7320–04100R3. 

(4) Guidance on the valve replacement 

specified in paragraph (e)(3) of this AD can 

be found in Thielert Repair Manual RM–02– 

01, Chapter 29.0. 

TAE 125–02–99 and TAE 125–01 Engines, 

Repetitive Replacements of Rail Pressure 

Control Valves 

(5) Thereafter, for affected TAE 125–02–99 

and TAE 125–01 engines, replace the rail 

pressure control valve with the same P/N 

valve within every 600 flight hours. 

FAA AD Differences 

(f) This AD differs from the Mandatory 

Continuing Airworthiness Information 

(MCAI) and/or service information as 

follows: 

(1) For the TAE 125–02–99 reciprocating 

engines, we reduced the initial compliance 

time from within 110 flight hours to within 

100 flight hours after the effective date of this 

AD. 

(2) The MCAIs instruct the operators to 

follow Thielert Maintenance Manual, 

Chapter 5, Airworthiness Limitations, for the 

repetitive compliance time for the rail 

pressure control valve, which, in the manual, 

is 600 flight hours. We found it necessary to 

specify the repetitive replacement 

compliance time in this AD, to within every 

600 flight hours. 

Alternative Methods of Compliance 

(AMOCs) 

(g) 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. 

Related Information 

(h) Refer to MCAI EASA AD 2008–0128, 

dated July 9, 2008, EASA AD 2008–0215, 

dated December 5, 2008, Thielert Service 

Bulletin No. TAE 125–1008 P1, Revision 1, 

dated September 29, 2008, and Thielert 

Repair Manual RM–02–02, for related 

information. Contact Thielert Aircraft 

Engines GmbH, Platanenstrasse 14 D–09350, 

Lichtenstein, Germany, telephone: +49– 

37204–696–0; fax: +49–37204–696–55; 

e-mail: info@centurion-engines.com, for a 

copy of this service information. 

(i) Contact Alan Strom, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; telephone 781–238–7143; fax 781– 

238–7199; e-mail: alan.strom@faa.gov, for 

more information about this AD. 

Issued in Burlington, Massachusetts, on 

October 6, 2011. 

Peter A. White, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–26822 Filed 10–17–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0599; Directorate 

Identifier 2011–NE–19–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company CF34–10E Series 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for General 

Electric Company (GE) CF34–10E series 

turbofan engines. This proposed AD was 


srobinson on DSK4SPTVN1PROD with PROPOSALS