72200 Federal Register / Vol. 77, No. 234 / Wednesday, December 5, 2012 / Rules and Regulations 

Rulemaking Procedure 

Because this amendment constitutes a 

minor technical correction to the NRC’s 

regulations and the authority citation for 

the prior technical corrections 

rulemaking, the Commission finds that 

the notice and comment provisions of 

the Administrative Procedure Act are 

unnecessary and is exercising its 

authority under 5 U.S.C. 553(b)(3)(B) to 

publish these amendments as a final 

rule. These amendments do not require 

action by any person or entity regulated 

by the NRC. Also, the final rule does not 

change the substantive responsibilities 

of any person or entity regulated by the 

NRC. 

List of Subjects in 10 CFR Part 171 

Annual charges, Byproduct material, 

Holders of certificates, Registrations, 

Approvals, Intergovernmental relations, 

Non-payment penalties, Nuclear 

materials, Nuclear power plants and 

reactors, Source material, Special 

nuclear material. 

For the reasons set out in the 

preamble and under the authority of the 

Atomic Energy Act of 1954, as amended; 

the Energy Reorganization Act of 1974, 

as amended; and 5 U.S.C. 552 and 553, 

10 CFR part 171 is corrected by making 

the following correcting amendment. 

PART 171—ANNUAL FEES FOR 

REACTOR LICENSES AND FUEL 

CYCLE LICENSES AND MATERIAL 

LICENSES, INCLUDING HOLDERS OF 

CERTIFICATES OF COMPLIANCE, 

REGISTRATIONS, AND QUALITY 

ASSURANCE PROGRAM APPROVALS 

AND GOVERNMENT AGENCIES 

LICENSED BY THE NRC 

■ 1. Revise the authority citation for part 

171 to read as follows: 

Authority: Consolidated Omnibus Budget 

Reconciliation Act sec. 7601 Pub. L. 99–272, 

as amended by sec. 5601, Pub. L. 100–203 as 

amended by sec. 3201, Pub. L. 101–239, as 

amended by sec. 6101, Pub. L. 101–508, as 

amended by sec. 2903a, Pub. L. 102–486 (42 

U.S.C. 2213, 2214), and as amended by Title 

IV, Pub. L. 109–103 (42 U.S.C. 2214); Atomic 

Energy Act sec. 161(w), 223, 234 (42 U.S.C. 

2201(w), 2273, 2282); Energy Reorganization 

Act sec. 201 (42 U.S.C. 5841); Government 

Paperwork Elimination Act sec. 1704 (44 

U.S.C. 3504 note); Energy Policy Act of 2005 

sec. 651(e), Pub. L. 109–58 (42 U.S.C. 2014, 

2021, 2021b, 2111). 

For the Nuclear Regulatory Commission. 

Dated at Rockville, Maryland, this 29th day 

of November, 2012. 

Cindy Bladey, 

Chief, Rules, Announcements, and Directives 

Branch, Division of Administrative Services, 

Office of Administration. 

[FR Doc. 2012–29348 Filed 12–4–12; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1220; Directorate 

Identifier 2012–NM–208–AD; Amendment 

39–17277; AD 2012–24–07] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 787–8 

airplanes. This AD requires ensuring 

that lockwire is installed correctly on 

the engine fuel feed manifold couplings. 

This AD also requires inspecting the 

assembly of the engine fuel feed 

manifold rigid and full flexible 

couplings. This AD was prompted by 

reports of fuel leaks due to improperly 

assembled engine fuel feed manifold 

couplings. We are issuing this AD to 

detect and correct improperly 

assembled couplings, which could 

result in fuel leaks and consequent fuel 

exhaustion, engine power loss or 

shutdown, or leaks on hot engine parts 

that could lead to a fire. 

DATES: This AD is effective December 5, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 5, 2012. 

We must receive comments on this 

AD by January 22, 2013. 

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 Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H– 

65, Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206– 

766–5680; Internet https:// 

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

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: 

Sherry Vevea, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6514; fax: 

425–917–6590; email: 

sherry.vevea@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We have received reports of fuel leaks 

on two different in-service airplanes, 

and the subsequent discovery of several 

improperly assembled engine fuel feed 

manifold couplings on in-service and 

production airplanes. The improper 

coupling installations, which occurred 

during production, have included 

couplings with missing or improperly 

installed lockwire, parts within the 

couplings installed in the wrong 

locations, incorrect parts installed in the 

couplings, and couplings that have extra 

parts installed. These conditions, if not 

corrected, could result in fuel leaks, 

which could lead to fuel exhaustion, 

engine power loss or shutdown, or leaks 

on hot engine parts that could lead to a 

fire. 


tkelley on DSK3SPTVN1PROD with 
Federal Register / Vol. 77, No. 234 / Wednesday, December 5, 2012 / Rules and Regulations 72201 

Relevant Service Information 

We reviewed Boeing Multi Operator 

Message MOM–MOM–12–0838– 

01B(R2), including Attachment A, dated 

November 25, 2012. For information on 

the procedures and compliance times, 

see this service information at http:// 

www.regulations.gov by searching for 

Docket No. FAA–2012–1220. 

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, 

except as discussed under ‘‘Differences 

Between the AD and the Service 

Information.’’ 

The phrase ‘‘related investigative 

actions’’ might be used in this AD. 

‘‘Related investigative actions’’ are 

follow-on actions that (1) are related to 

the primary actions, and (2) further 

investigate the nature of any condition 

found. Related investigative actions in 

an AD could include, for example, 

inspections. 

In addition, the phrase ‘‘corrective 

actions’’ might be used in this AD. 

‘‘Corrective actions’’ are actions that 

correct or address any condition found. 

Corrective actions in an AD could 

include, for example, repairs. 

Differences Between the AD and the 

Service Information 

For engine fuel feed manifold 

couplings that have not been previously 

inspected, Boeing Multi Operator 

Message MOM–MOM–12–0838– 

01B(R2), including Attachment A, dated 

November 25, 2012, recommends 

accomplishment of all actions specified 

in Action 1) within 7 days. This AD, 

however, requires only that operators 

ensure the correct lockwire installation 

within 7 days; the compliance time for 

the remaining actions is 21 days. We 

have determined that the additional 

time for the remaining actions is 

warranted, based on the assurance that 

the lockwire is installed correctly. 

In addition, for engine fuel feed 

manifold full flexible couplings that 

have been previously inspected, Boeing 

Multi Operator Message MOM–MOM– 

12–0838–01B(R2), including 

Attachment A, dated November 25, 

2012, specifies that operators do not 

need to re-inspect these couplings if 

review of the airplane maintenance 

records conclusively demonstrates that 

the corresponding actions are equivalent 

to steps 1 through 6 of Action 1) of 

Boeing Multi Operator Message MOM– 

MOM–12–0838–01B(R2), including 

Attachment A, dated November 25, 

2012. We have determined that the 

potential for not identifying incorrect 

parts during prior inspection of the full 

flexible coupling warrants re-inspecting 

these couplings; this AD therefore 

requires inspection of these full flexible 

couplings. 

These differences have been 

coordinated with Boeing. 

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 improperly assembled 

engine fuel feed manifold couplings 

could result in fuel leaks and 

consequent fuel exhaustion, engine 

power loss or shutdown, or leaks on hot 

engine parts that could lead to a fire. 

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–2012–1220 and Directorate 

Identifier 2012–NM–208–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 affects 3 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Coupling inspection, o-ring replacement, retainer ring installation, blade seal inspection, and lockwire installation.10 work-hours × $85 per hour 

= $850.

$54 $904 $2,712 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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 


tkelley on DSK3SPTVN1PROD with 
72202 Federal Register / Vol. 77, No. 234 / Wednesday, December 5, 2012 / Rules and Regulations 

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): 

2012–24–07 The Boeing Company: 

Amendment 39–17277; Docket No. 

FAA–2012–1220; Directorate Identifier 

2012–NM–208–AD. 

(a) Effective Date 

This AD is effective December 5, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 787–8 airplanes, certificated in any 

category, serial numbers 34485, 34486, 

34488, 34490, 34493, 34494, 34497, 34502, 

34506 through 34508 inclusive, 34514, 

34515, 34521, 34744 through 34747 

inclusive, 34822, 34824, 34829, 34832, 34834 

through 34838 inclusive, 35938, 36276 

through 36278 inclusive, 38319, 38320, 

38330, 38466, 38471, 40748, and 40899. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by reports of fuel 

leaks due to improperly assembled engine 

fuel feed manifold couplings. We are issuing 

this AD to detect and correct improperly 

assembled couplings, which could result in 

fuel leaks and consequent fuel exhaustion, 

engine power loss or shutdown, or leaks on 

hot engine parts that could lead to a fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Except as provided by paragraph (h) of this 

AD: Do the actions specified in paragraphs 

(g)(1) and (g)(2) of this AD, in accordance 

with Action 1) of Boeing Multi Operator 

Message MOM–MOM–12–0838–01B(R2), 

including Attachment A, dated November 25, 

2012. 

(1) Within 7 days after the effective date of 

this AD, ensure that the lockwire installation 

on the rigid and full flexible couplings is 

correct. 

(2) Within 21 days after the effective date 

of this AD, inspect the rigid and full flexible 

couplings for correct assembly, including 

replacement of the o-rings with new o-rings, 

confirmation that the proper retainer rings 

are installed in the full flexible coupling, a 

general visual inspection for damage of the 

blade seals, and all applicable corrective 

actions. Do all applicable corrective actions 

before further flight. 

(h) Requirements Based on Previous 

Accomplishment 

(1) For airplanes on which the fuel 

couplings have been inspected before the 

effective date of this AD as specified in 

‘‘Method 1: AMM Method’’ of Boeing Multi 

Operator Message MOM–MOM–12–0838– 

01B, dated November 11, 2012, which is not 

incorporated by reference in this AD; or 

Boeing Multi Operator Message MOM– 

MOM–12–0838–01B(R1), dated November 

14, 2012, which is not incorporated by 

reference in this AD: A review of the airplane 

maintenance records is acceptable for 

compliance with the requirements of 

paragraph (g)(1) of this AD, if the records 

conclusively demonstrate that lockwire was 

installed correctly using a method equivalent 

to step 6.a. of Action 1) of Boeing Multi 

Operator Message MOM–MOM–12–0838– 

01B(R2), including Attachment A, dated 

November 25, 2012. 

(2) For airplanes on which the fuel 

couplings have been inspected before the 

effective date of this AD as specified in 

‘‘Method 2: Non-Invasive Method’’ of Boeing 

Multi Operator Message MOM–MOM–12– 

0838–01B, dated November 11, 2012, which 

is not incorporated by reference in this AD; 

or Boeing Multi Operator Message MOM– 

MOM–12–0838–01B(R1), dated November 

14, 2012, which is not incorporated by 

reference in this AD: The actions specified in 

paragraph (g)(1) of this AD are not required. 

(3) For airplanes on which the rigid fuel 

couplings have been inspected before the 

effective date of this AD as specified in 

‘‘Method 1: AMM Method’’ or ‘‘Method 2: 

Non-Invasive Method’’ of Boeing Multi 

Operator Message MOM–MOM–12–0838– 

01B, dated November 11, 2012, which is not 

incorporated by reference in this AD; or 

Boeing Multi Operator Message MOM– 

MOM–12–0838–01B(R1), dated November 

14, 2012, which is not incorporated by 

reference in this AD: The actions specified in 

paragraph (g)(2) of this AD are not required 

for the rigid fuel couplings only. However, 

the actions specified in paragraph (g)(2) of 

this AD are required for the full flexible 

couplings, even if inspected prior to the 

effective date of this AD as specified in 

Boeing Multi Operator Message MOM– 

MOM–12–0838–01B, dated November 11, 

2012, which is not incorporated by reference 

in this AD; or Boeing Multi Operator Message 

MOM–MOM–12–0838–01B(R1), dated 

November 14, 2012, which is not 

incorporated by reference in this AD. 

(i) No Reporting Requirement 

Boeing Multi Operator Message MOM– 

MOM–12–0838–01B(R2), including 

Attachment A, dated November 25, 2012, 

specifies reporting to Boeing any anomalies 

found during inspection of the assembly of 

the rigid and full flexible couplings, 

including anomalies of the lockwire 

installation. This AD does not require any 

report. 

(j) Special Flight Permit 

Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the airplane can be 

modified, provided the lockwire is correctly 

installed on the engine fuel feed manifold 

rigid and full flexible couplings in 

accordance with paragraph (g)(1) of this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(l) Related Information 

(1) For more information about this AD, 

contact Sherry Vevea, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6514; fax: 425–917–6590; 

email: sherry.vevea@faa.gov. 


tkelley on DSK3SPTVN1PROD with 
Federal Register / Vol. 77, No. 234 / Wednesday, December 5, 2012 / Rules and Regulations 72203 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. You 

may review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Multi Operator Message MOM– 

MOM–12–0838–01B(R2), including 

Attachment A, dated November 25, 2012. 

The document number and issue date are 

identified on page 1 of Boeing Multi Operator 

Message MOM–MOM–12–0838–01B(R2), 

including Attachment A, dated November 25, 

2012, and on each page of Attachment A; no 

other page of this document contains this 

information. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this 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 Renton, Washington, on 

November 28, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–29405 Filed 12–4–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1245; Directorate 

Identifier 2012–NE–41–AD; Amendment 39– 

17279; AD 2012–24–09] 

RIN 2120–AA64 

Airworthiness Directives; Lycoming 

Engines and Continental Motors, Inc. 

Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Lycoming Engines TSIO–540–AK1A, 

and Continental Motors, Inc. TSIO–360– 

MB, TSIO–360–SB, and TSIO–360–RB 

reciprocating engines, with certain 

Hartzell Engine Technologies (HET) 

turbochargers, model TA0411, part 

number (P/N) 466642–0001; 466642– 

0002; 466642–0006; 466642–9001; 

466642–9002; or 466642–9006, or with 

certain HET model TA0411 

turbochargers overhauled or repaired 

since August 29, 2012. This AD requires 

removing the affected turbochargers 

from service before further flight. This 

AD was prompted by a report of a 

turbocharger turbine wheel that failed a 

static strength test at its manufacturing 

facility. We are issuing this AD to 

prevent turbocharger turbine wheel 

failure, reduction or complete loss of 

engine power, loss of engine oil, oil fire, 

and damage to the airplane. 

DATES: This AD is effective December 

20, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 20, 2012. 

We must receive comments on this 

AD by January 22, 2013. 

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 Hartzell Engine 

Technologies, LLC, 2900 Selma 

Highway, Montgomery, AL 36108, 

phone: 334–386–5400; fax: 334–386– 

5450; internet: http:// 

www.hartzellenginetech.com. You may 

view this service information at the 

FAA, 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: 

Christopher Richards, Aerospace 

Engineer, Chicago Aircraft Certification 

Office, FAA, 2300 E. Devon Ave., Des 

Plaines, IL 60018; phone: 847–294– 

7156; fax: 847–294–7834; email: 

christopher.j.richards@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received a report of an HET 

turbocharger turbine wheel that failed a 

static strength test at its manufacturing 

facility. Subsequent tests showed that 

nearly all turbine wheels, P/N 410188– 

0019, had significant cracking under the 

surface of a critical weld joint between 

the turbine wheel head and shaft that 

occurred during manufacturing. HET 

has identified by serial number (S/N) 

the turbochargers shipped from the 

factory with this unsafe condition. HET 

has also identified the S/N range of 

affected turbine wheels. Some of the 

affected turbine wheels became 

available for overhaul or field repair 

since August 29, 2012, and may have 

been installed. This condition, if not 

corrected, could result in turbocharger 

turbine wheel failure, reduction or 

complete loss of engine power, loss of 

engine oil, oil fire, and damage to the 

airplane. 

Relevant Service Information 

We reviewed HET Alert Service 

Bulletin (ASB) No. 048, dated November 

16, 2012. The ASB lists the known serial 

numbers of affected turbochargers. 


tkelley on DSK3SPTVN1PROD with