This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

51459 

Vol. 77, No. 165 

Friday, August 24, 2012 

DEPARTMENT OF AGRICULTURE 

Farm Service Agency 

7 CFR Part 782 

Suspension of End-Use Certificate 

Program Requirements 

AGENCY: Farm Service Agency, USDA. 

ACTION: Final rule. 

SUMMARY: This final rule suspends 

indefinitely the Farm Service Agency 

(FSA) regulation requiring end-use 

certificates and tracking of wheat 

produced in Canada that enters the 

United States. This action is being taken 

in response to the discontinuation of 

Canada’s end-use certificate program. 

As a result of these changes, importers 

and end-users of Canadian produced 

wheat are no longer required to provide 

FSA end-use certificates or 

consumption and resale reports on 

wheat produced in Canada. 

DATES: Effective August 31, 2012. 

FOR FURTHER INFORMATION CONTACT: 

Helen Linden, Farm Service Agency, 

Commodity Operations Division, 

telephone (202) 690–4321, or email 

Helen.linden@wdc.usda.gov. 

SUPPLEMENTARY INFORMATION: Section 

321(f) of the North American Free Trade 

Agreement (NAFTA) Implementation 

Act requires the Secretary of Agriculture 

to: 

(1) Establish end-use certificates for 

imports of wheat and barley from a 

foreign country that requires end-use 

certificates for imports of U.S. produced 

wheat or barley; and 

(2) Suspend end-use certificate 

requirements if the foreign countries 

that have similar requirements 

terminate such requirements. Canada 

was the only country requiring end-use 

certificates, and wheat was the only 

commodity subject to end-use certificate 

requirements. 

FSA regulations regarding the U.S. 

end-use certificate program were 

implemented in 7 CFR part 782, End 

Use Certificate Program. These 

regulations provide, in part, that the 

provisions of the regulations will be 

suspended 30 calendar days following 

the date Canada eliminates its end-use 

certificate requirement. 

Canada announced that effective 

August 1, 2012, it will no longer require 

end-use certificates on U.S. produced 

wheat entering Canada. Therefore, by 

the statutory and regulatory authorities 

mentioned above, effective August 31, 

2012, FSA is suspending the End-Use 

Certificate filing requirements in 7 CFR 

part 782. Accordingly, beginning August 

31, 2012, importers and end-users of 

Canadian wheat will no longer be 

required to file either the End-Use 

Certificate for Wheat (FSA–750) or the 

End-Use Certificate Program Canadian 

Wheat Consumption and Resale Report 

(FSA–751). 

List of Subjects in 7 CFR Part 782 

Administrative practice and 

procedure, Barley, Reporting and 

recordkeeping requirements, Wheat. 

PART 782—[SUSPENDED] 

■ Accordingly, under the authority of 7 

U.S.C. 6932, 15 U.S.C. 714b and 714c 

and 19 U.S.C. 3391, the Farm Security 

administration suspends indefinitely 7 

CFR part 782. 

Signed on August 3, 2012. 

Juan M. Garcia, 

Administrator, Farm Service Agency. 

[FR Doc. 2012–20983 Filed 8–23–12; 8:45 am] 

BILLING CODE 3410–05–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0079; Directorate 

Identifier 2012–NE–06–AD; Amendment 39– 

17148; AD 2012–16–01] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Division Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Pratt & 

Whitney Division PW4052, PW4152, 

PW4056, PW4156A, PW4060, 

PW4060A, PW4060C, PW4062, 

PW4062A, PW4158, PW4460, PW4462, 

PW4164, PW4164C, PW4164C/B, 

PW4168, and PW4168A turbofan 

engines with certain high-pressure 

turbine (HPT) stage 1 front hubs 

installed. This AD was prompted by 

Pratt & Whitney’s updated low-cyclefatigue analysis that indicated certain 

HPT stage 1 front hubs could initiate a 

crack prior to the published life limit. 

This AD requires removing the affected 

HPT stage 1 front hubs from service 

using a drawdown plan. We are issuing 

this AD to prevent failure of the HPT 

stage 1 front hub, which could lead to 

an uncontained engine failure and 

damage to the airplane. 

DATES: This AD is effective September 

28, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of September 28, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Pratt & 

Whitney, 400 Main St., East Hartford, 

CT 06108; phone: 860–565–7700; fax: 

860–565–1605. 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. 

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 address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

James Gray, Aerospace Engineer, Engine 

Certification Office, FAA, 12 New 

England Executive Park, Burlington, 

MA; phone: 781–238–7742; fax: 781– 

238–7199; email: james.e.gray@faa.gov. 


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51460 Federal Register / Vol. 77, No. 165 / Friday, August 24, 2012 / Rules and Regulations 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM published in the Federal 

Register on March 23, 2012 (77 FR 

16967). That NPRM proposed to require 

removing the affected HPT stage 1 front 

hubs from service using a drawdown 

plan. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Support for the NPRM 

One commenter, The Boeing 

Company, supported the contents of the 

proposed AD (77 FR 16967, March 23, 

2012), as written. 

Request To Modify Applicability 

Commenters United Airlines, United 

Parcel Service Co. (UPS), Pratt & 

Whitney (P&W), and MNG Airlines 

requested that part numbers (P/Ns) 

52L301 and 51L201–021 be added to the 

applicability paragraphs (c)(1) and (c)(2) 

of the proposed AD (77 FR 16967, 

March 23, 2012). The commenters noted 

that the applicability of the proposed 

AD is inconsistent since it includes 

some assembly P/Ns and some detail 

P/Ns. 

We agree. We revised the applicability 

paragraphs of this AD to include the 

referenced P/Ns for consistency. 

Request To Change Compliance Time 

Commenters UPS, MNG Airlines, and 

Onur Air requested that the compliance 

time be changed to ‘‘at next piece-part 

exposure after the effective date of this 

AD or before accumulating the number 

of cycles listed in this AD, whichever 

occurs later.’’ MNG Airlines indicated 

that its engines would lose 1,382 flight 

cycles, which would cost more than 

$1,000,000 and force early shop visits. 

Onur Air noted that its engines would 

lose 1,300 cycles and it would cause 

stub life problems on other life limited 

parts. UPS also expressed its concern 

over the increased shop burden from a 

hub life reduction. 

We do not agree. We determined that 

removal of the HPT stage 1 front hubs 

according to the compliance times in 

paragraph (f) of this AD provides an 

acceptable level of safety for the fleet. 

This acceptable level of safety would 

not be maintained if all HPT stage 1 

front hubs were allowed to remain in 

service until the next piece-part 

exposure above the number of cycles 

listed in this AD. For this reason, we 

also cannot adjust the compliance time 

to account for potential stub life 

problems that might occur in the other 

rotors. We did not change the AD. 

Request To Reference the PW4000 

Engine Manual Chapter 05 Life Limits 

Commenters MNG Airlines and P&W 

requested that the phrase ‘‘former life 

limits cannot be exceeded’’ be added to 

compliance paragraphs (f)(1)(ii) and 

(f)(2)(ii) of the proposed AD (77 FR 

16967, March 23, 2012), or that some 

other reference to the PW4000 Engine 

Manual Chapter 05 life limits be added 

when the stage 1 front hub is operating 

during the 1,000 cycle drawdown. 

United commented that a reference to 

the reduced life limits be included in 

Chapter 05 of the Airworthiness 

Limitations Section (ALS) of the 

PW4000 Engine Manual. 

We do not agree. The Chapter 05 life 

limits cannot be exceeded. For those 

hubs beneath the Chapter 05 life limit, 

this AD requires removal according to 

the drawdown schedule in the AD, 

which is before the Chapter 05 limit is 

reached. This AD’s requirements are 

independent from the Chapter 05 life 

limits in the ALS of the PW4000 Engine 

Manual. We did not change the AD. 

Request Revisions to Service 

Information To Be Incorporated by 

Reference 

P&W, UPS, and United requested 

revisions to the service information that 

is incorporated by reference in the AD. 

P&W requested that the AD reference 

the new P&W Alert Service Bulletin 

(ASB) No. PW4ENG A72–821, dated 

July 6, 2012 and P&W ASB No. PW4G– 

100–A72–246, dated June 28, 2012, 

which address the unsafe condition and 

contain the affected part numbers by 

serial number for the PW4000–94’’ and 

PW4000–100’’ engines. UPS also asked 

that the AD be revised to note that any 

subsequent revision of the service 

bulletin (SB) can be used for 

compliance. 

We agree in part. Our proposed AD 

(77 FR 16967, March 23, 2012), 

referenced the P/N-serial number (S/N) 

tables of affected parts in the old SBs. 

We agree that we should use the new 

P&W SBs. We changed paragraph (c) of 

this AD to incorporate the P/N–S/N 

tables from the new P&W ASBs, 

specifically from P&W ASB No. 

PW4ENG A72–821, dated July 6, 2012 

and P&W ASB No. PW4G–100–A72– 

246, dated June 28, 2012. 

We disagree that the AD should be 

revised to incorporate future revisions 

of an ASB because we do not know the 

contents of SBs not yet published. We 

did not change the AD based on UPS’s 

comment. 

Request To Modify Compliance 

Wording 

P&W requested that the phrase ‘‘or at 

the next piece-part exposure after the 

effective date of this AD, whichever 

occurs first’’ be removed from the 

compliance paragraphs (f)(1)(ii) and 

(f)(2)(ii). P&W indicated that, based on 

the proposed AD, operators may not be 

able to run HPT stage 1 front hubs, 

identified in paragraphs (c)(1)(i) and 

(c)(1)(ii), that are exposed at piece-part 

between 17,000 and 18,000 cycles-sincenew (CSN) and HPT stage 1 front hubs, 

identified in paragraphs (c)(2) and (c)(3), 

that are exposed between 12,700 and 

13,700 CSN, to the full 1,000 cycle 

drawdown. 

We partially agree. We agree that the 

AD if adopted as proposed could have 

forced removal of HPT stage 1 front 

hubs prior to reaching 18,000 CSN and 

13,700 CSN, respectively. We disagree 

that we should remove the at piece-part 

exposure wording from paragraphs 

(f)(1)(ii) and (f)(2)(ii) of the AD, because 

HPT stage 1 front hubs that are exposed 

at piece-part after 18,000 CSN and 

13,700 CSN should not go back into 

service, even if they have not 

accumulated an additional 1,000 cycles 

in service. We therefore, revised 

paragraphs (f)(1)(ii) and (f)(2)(ii) of the 

proposed AD (77 FR 16967, March 23, 

2012), to clarify that these HPT stage 1 

front hubs should be removed at the 

next piece-part exposure above 18,000 

CSN and 13,700 CSN, respectively, 

rather than at the next piece-part 

exposure after the effective date of the 

AD. This change is consistent with the 

installation prohibition for HPT stage 1 

front hubs in paragraph (g) of this AD. 

Request for Allowance for Mixed-Model 

Management 

United asked that the AD include an 

allowance for mixed-model 

management. 

We do not agree. The AD does not 

restrict use of mixed-model 

management. If an operator uses mixedmodel management, then 18,000 CSN 

and 13,700 CSN should be used in the 

calculation for the respective engine 

models included in paragraph (c) of this 

AD. We did not change the AD. 

Request To Add Credit for Prior 

Compliance 

FedEx Express (FedEx) asked that the 

AD include credit for compliance to 

prior SBs. 


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We do not agree. Operators can take 

credit for previous actions based on 

paragraph (e) of this AD. We did not 

change the AD. 

Request To Clarify Requirements for 

P/N 51L901 

FedEx asked that the AD requirements 

for stage 1 front hub, P/N 51L901, be 

clarified. FedEx claimed that the 

relevant service information section of 

the AD and its applicability are 

contradictory. 

We do not agree. We reviewed the 

P/N references and find no 

contradictions between the two 

sections. We did not change the AD. 

Revision to Cost of Compliance 

In reviewing our cost of compliance 

estimate made in the NPRM (77 FR 

16967, March 23, 2012), we found that 

our estimate was wrong. Specifically, 

we found that we based our estimate on 

the number of engines installed on 

airplanes worldwide rather than just on 

the U.S. fleet. Therefore, we changed 

our estimate to reflect U.S. operators 

only. This change reduced the number 

of engines affected from 954 to 289 and 

the total cost estimate from $23,049,537 

to $6,981,578. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We also determined that these changes 

will not increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Costs of Compliance 

We estimate that this AD would affect 

289 engines installed on airplanes of 

U.S. registry. About 183 engines use a 

20,000 CSN life limit for the HPT stage 

1 front hub. For these engines, we 

estimate the lost part life to have a value 

of about $25,400 per engine. About 106 

engines use a 15,000 CSN life limit. For 

these engines, we estimate the lost life 

to have a value of about $22,013 per 

engine. Based on these figures, we 

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

operators is $6,981,578. 

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): 

2012–16–01 Pratt & Whitney Division: 

Amendment 39–17148; Docket No. 

FAA–2012–0079; Directorate Identifier 

2012–NE–06–AD. 

(a) Effective Date 

This AD is effective September 28, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the following Pratt & 

Whitney Division turbofan engines: 

(1) PW4052, PW4152, and PW4056 

turbofan engines, including models with any 

dash number suffix, with a high-pressure 

turbine (HPT) stage 1 front hub part number 

(P/N) listed in Table 1 to paragraph (c) of this 

AD installed. 

(2) PW4156A, PW4060, PW4060A, 

PW4060C, PW4062, PW4062A, PW4158, 

PW4460, and PW4462 turbofan engines, 

including models with any dash number 

suffix, with an HPT stage 1 front hub P/N 

listed in Table 1 to paragraph (c) of this AD 

installed. 

TABLE 1 TO PARAGRAPH (C) 

P/N 51L601 ................................................................................... All serial numbers (S/Ns). 

P/N 52L401 ................................................................................... With a S/N not listed in Table 5 of the Accomplishment Instructions of Pratt & 

Whitney Alert Service Bulletin (ASB) No. PW4ENG A72–821, dated July 6, 

2012. 

P/N 51L201, P/N 51L201–001, P/N 51L201–021 ........................ All S/Ns. 

P/N 51L901, P/N 52L301 .............................................................. With an S/N not listed in Table 7 of the Accomplishment Instructions of Pratt & 

Whitney ASB No. PW4ENG A72–821, dated July 6, 2012. 

(3) PW4164, PW4164C, PW4164C/B, 

PW4168, and PW4168A turbofan engines 

with an HPT stage 1 front hub, P/N 51L901, 

installed with an S/N not listed in Table 3 

of the Accomplishment Instructions of Pratt 

& Whitney ASB No. PW4G–100–A72–246, 

dated June 28, 2012. 

(d) Unsafe Condition 

This AD was prompted by Pratt & 

Whitney’s updated low-cycle-fatigue analysis 

that indicated certain HPT stage 1 front hubs 

could initiate a crack prior to the published 


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51462 Federal Register / Vol. 77, No. 165 / Friday, August 24, 2012 / Rules and Regulations 

life limit. This AD requires removing the 

affected HPT stage 1 front hubs from service 

using a drawdown plan. We are issuing this 

AD to prevent failure of the HPT stage 1 front 

hub, which could lead to an uncontained 

engine failure and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Removal of HPT Stage 1 Front Hubs From 

Service 

(1) For HPT stage 1 front hubs listed in 

paragraph (c)(1) of this AD, do the following: 

(i) If the HPT stage 1 front hub has 

accumulated 17,000 or fewer cycles-sincenew (CSN) on the effective date of this AD, 

remove the HPT stage 1 front hub from 

service before accumulating 18,000 CSN. 

(ii) If the HPT stage 1 front hub has 

accumulated more than 17,000 CSN on the 

effective date of this AD, remove the HPT 

stage 1 front hub from service before 

accumulating an additional 1,000 cycles-inservice (CIS) or at the next piece-part 

exposure above 18,000 CSN, whichever 

occurs first. 

(2) For HPT stage 1 front hubs listed in 

paragraphs (c)(2) and (c)(3) of this AD, do the 

following: 

(i) If the HPT stage 1 front hub has 

accumulated 12,700 or fewer CSN on the 

effective date of this AD, remove the HPT 

stage 1 front hub from service before 

accumulating 13,700 CSN. 

(ii) If the HPT stage 1 front hub has 

accumulated more than 12,700 CSN on the 

effective date of this AD, remove the HPT 

stage 1 front hub from service before 

accumulating an additional 1,000 CIS or at 

the next piece-part exposure above 13,700 

CSN, whichever occurs first. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

install into any engine any HPT stage 1 front 

hubs listed in paragraph (c)(1) of this AD that 

are at piece-part exposure and exceed 18,000 

CSN, or any HPT stage 1 front hubs listed in 

paragraphs (c)(2) and (c)(3) of this AD that 

are at piece-part exposure and exceed 13,700 

CSN. 

(h) Definition 

For the purpose of this AD, piece-part 

exposure means that the part is completely 

disassembled and removed from the engine. 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(j) Related Information 

For more information about this AD, 

contact James Gray, Aerospace Engineer, 

Engine Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA; 

phone: 781–238–7742; fax: 781–238–7199; 

email: james.e.gray@faa.gov. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the following service information 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise: 

(i) Pratt & Whitney Alert Service Bulletin 

(ASB) No. PW4ENG A72–821, dated July 6, 

2012. 

(ii) Pratt & Whitney ASB No. PW4G–100– 

A72–246, dated June 28, 2012. 

(3) For service information identified in 

this AD, contact Pratt & Whitney, 400 Main 

St., East Hartford, CT 06108; phone: 860– 

565–7700; fax: 860–565–1605. 

(4) You may review 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. 

(5) You may also review 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 NARA, call 

202–741–6030, or go to: http:// 

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

Issued in Burlington, Massachusetts, on 

July 26, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–20842 Filed 8–23–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0603; Directorate 

Identifier 2012–NE–17–AD; Amendment 39– 

17160; AD 2012–16–13] 

RIN 2120–AA64 

Airworthiness Directives; BRPPowertrain GmbH & Co KG Rotax 

Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for BRPPowertrain GmbH & Co KG Rotax 912 

F2; 912 F3; 912 F4; 912 S2; 912 S3; and 

912 S4 reciprocating engines. This AD 

requires replacing the pressure side fuel 

hose on certain fuel pumps and 

inspecting the carburetors connected to 

those fuel pumps for contamination 

within 5 flight hours after the effective 

date of this AD. This AD was prompted 

by reports of fuel pumps having 

pressure side fuel hoses not meeting the 

design specification. We are issuing this 

AD to prevent pressure side fuel hose 

deterioration and contamination of the 

carburetor, which could result in an inflight engine shutdown, forced landing 

and damage to the airplane. 

DATES: This AD becomes effective 

September 10, 2012. 

We must receive comments on this 

AD by October 9, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of BRP-Powertrain GmbH & Co KG, 

Rotax Aircraft Engines Alert Service 

Bulletin No. ASB–912–061R1, dated 

May 31, 2012, listed in the AD as of 

September 10, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• 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 BRP-Powertrain GmbH 

& Co KG, Welser Strasse 32, A–4623 

Gunskirchen, Austria, or go to: http:// 

www.rotax-aircraft-engines.com. You 

may view this 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. 

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 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 & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

email: alan.strom@faa.gov; phone: 781– 

238–7143; fax: 781–238–7199. 

SUPPLEMENTARY INFORMATION: 


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