36440 Federal Register / Vol. 79, No. 124 / Friday, June 27, 2014 / Proposed Rules 

§ 1653.36 Payment. 

(a) Payment pursuant to a qualifying 

levy or criminal restitution order will be 

made 30 days after the TSP decision 

letter. 

(b) In no case will payment exceed the 

participant’s calculated entitlement. 

(c) The entire amount of a restitution 

order or levy entitlement must be 

disbursed at one time. A series of 

payments will not be made. A payment 

pursuant to a restitution order or levy 

extinguishes all rights to any further 

payment under that order or levy, even 

if the entire amount of the entitlement 

cannot be paid. Any further award must 

be contained in a separate restitution 

order or levy. 

(d) If a participant has funds in more 

than one type of account, payment will 

be made from each account in the 

following order, until the amount of the 

levy or restitution order is reached: 

(1) Civilian account; 

(2) Uniformed services account; 

(3) Beneficiary participant account. 

(e) Payment will be made pro rata 

from the participant’s traditional and 

Roth balances. The distribution from the 

traditional balance will be further prorated between the tax-deferred balance 

and tax-exempt balance. The payment 

from the Roth balance will be further 

pro-rated between contributions in the 

Roth balance and earnings in the Roth 

balance. In addition, all payments will 

be distributed pro rata from all TSP 

Funds in which the participant’s 

account is invested. All pro-rated 

amounts will be based on the balances 

in each fund or source of contributions 

on the day the disbursement is made. 

(f) The payment is taxable to the 

participant and is subject to ten percent 

Federal income tax withholding. The 

tax withholding will be taken from the 

payee’s entitlement and the gross 

amount of the payment (i.e., the net 

payment distributed to the payee plus 

the amount withheld from the payment 

for taxes) will be reported to the IRS as 

income to the participant. 

(g) A properly paid levy or restitution 

order cannot be returned to the TSP. 

[FR Doc. 2014–14937 Filed 6–26–14; 8:45 am] 

BILLING CODE 6760–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0929; Directorate 

Identifier 2013–CE–031–AD] 

RIN 2120–AA64 

Airworthiness Directives; DG 

Flugzeugbau GmbH Gliders 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for any DG 

Flugzeugbau GmbH Model DG–1000T 

glider equipped with a Solo 

Kleinmotoren Model 2350 C engine that 

would revise AD 2013–22–14. This 

proposed AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as engine shaft 

failure and consequent propeller 

detachment. We are issuing this 

proposed AD to require actions to 

address the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by August 11, 2014. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590, 

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

through Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Solo 

Kleinmotoren GmbH, Postfach 60 01 52, 

D 71050 Sindelfingen, Germany; 

telephone: +49 07031–301–0; fax: +49 

07031–301–136; email: aircraft@sologermany.com; Internet: http://

aircraft.solo-online.com/. You may view 

this referenced service information at 

the FAA, Small Airplane Directorate, 

901 Locust, Kansas City, Missouri 

64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2013– 

0929; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Jim 

Rutherford, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 

329–4090; email: jim.rutherford@

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–2013–0929; Directorate Identifier 

2013–CE–031–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 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 proposed AD. 

Discussion 

On October 24, 2013, we issued AD 

2013–22–14, Amendment 39–17646 (78 

FR 65869, November 4, 2013) (‘‘AD 

2013–22–14’’). That AD required actions 

intended to address an unsafe condition 

on any DG Flugzeugbau GmbH Model 

DG–1000T glider equipped with a Solo 

Kleinmotoren Model 2350 C engine and 

was based on mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country. 

Since we issued AD 2013–22–14, the 

manufacturer of the Solo Kleinmotoren 


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Federal Register / Vol. 79, No. 124 / Friday, June 27, 2014 / Proposed Rules 36441 

Model 2350 C engine has developed an 

engine modification to restore engine 

operation. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD No.: 2013– 

0217R1, dated May 5, 2014 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

An occurrence of Solo 2350 C engine shaft 

failure and consequent propeller detachment 

was reported. The preliminary investigation 

revealed that the failed shaft was earlier 

modified in accordance with an approved 

method. 

This condition, if not corrected, could lead 

to additional cases of release of the propeller 

from the engine, possibly resulting in damage 

to the sailplane, or injury to persons on the 

ground. 

To address this potential unsafe condition, 

EASA issued Emergency AD 2013–0217–E to 

prohibit operation of the engine. 

Since that AD was issued, Solo 

Kleinmotoren GmbH developed a 

modification consisting of installing an 

improved eccenter axle-pulley assembly, 

allowing to resume operation of the engine. 

For the reason described above, this AD is 

revised to incorporate the optional 

modification, cancelling the operational 

restriction. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2013–0929. 

Relevant Service Information 

Solo Kleinmotoren GmbH issued 

Technische Mitteilung Service Bulletin 

Nr. 4603–14, dated April 28, 2014. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of the Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 2 products of U.S. registry. 

We also estimate that it would take 

about .5 work-hour per product to 

comply with the proposed retained 

requirement of placing a copy of AD 

2013–22–14 into the Limitations section 

of the aircraft flight manual, which 

prohibits engine operation. The average 

labor rate is $85 per work-hour. 

Based on these figures, we estimate 

the cost of this proposed retained 

requirement on U.S. operators to be $85, 

or $42.50 per product. 

In addition, we estimate that the 

optional engine modification would 

take about 1.5 work-hours and require 

parts costing $100, for a cost of $227.50. 

If both products of U.S. registry 

incorporated the engine modification, 

the cost of the proposed modification on 

U.S. operators would be $455. 

If the engine modification is done, it 

would also take about .5 work-hour per 

product to remove the engine operation 

restriction (copy of AD 2013–22–14) 

from the Limitations section of the 

aircraft flight manual. The average labor 

rate is $85 per work-hour, for a cost of 

$42.50 per product. 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. 

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 

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), 

(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. 

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. Amend § 39.13 by removing 

Amendment 39–17646 (78 FR 65869, 

November 4, 2013), and adding the 

following new AD: 

DG Flugzeugbau GmbH: Docket No. FAA– 

2013–0929; Directorate Identifier 2013– 

CE–031–AD. 

(a) Comments Due Date 

We must receive comments by August 11, 

2014. 

(b) Affected ADs 

This AD revises AD 2013–22–14, 

Amendment 39–17646 (78 FR 65869, 

November 4, 2013) (‘‘AD 2013–22–14’’). 

(c) Applicability 

This AD applies to DG Flugzeugbau GmbH 

Model DG–1000T gliders, all serial numbers, 

that are: 

(1) Equipped with a Solo Kleinmotoren 

Model 2350 C engine; and 

(2) certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 72: Engine. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as engine 

shaft failure and consequent propeller 

detachment. We are issuing this AD to 


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36442 Federal Register / Vol. 79, No. 124 / Friday, June 27, 2014 / Proposed Rules 

prevent engine shaft failure and propeller 

detachment, which could result in damage to 

the glider and injury to persons on the 

ground. 

(f) Actions and Compliance 

Unless already done, do the following 

actions in paragraphs (f)(1) through (f)(4) of 

this AD. 

(1) As of November 25, 2013 (the effective 

date retained from AD 2013–22–14), do not 

operate the engine unless the engine is 

modified following instructions that are 

approved by the FAA specifically for AD 

2013–22–14. Contact the FAA office 

identified in paragraph (g)(1) of this AD to get 

more information about obtaining such 

instructions. 

(2) As of November 25, 2013 (the effective 

date retained from AD 2013–22–14), place a 

copy of AD 2013–22–14 or this AD into the 

Limitations section of the aircraft flight 

manual (AFM). 

(3) To remove the prohibited engine 

operation requirement in paragraph (f)(1) of 

this AD, modify the engine as specified in the 

Actions paragraph of Solo Kleinmotoren 

GmbH Technische Mitteilung Service 

Bulletin Nr. 4603–14, dated April 28, 2014, 

unless already modified with FAA-approved 

instructions as specified in paragraph (f)(1) of 

this AD. 

Note 1 to paragraph (f)(3) of this AD: This 

service information contains German to 

English translation. The European Aviation 

Safety Agency (EASA) used the English 

translation in referencing the document. For 

enforceability purposes, we will refer to the 

Solo Kleinmotoren GmbH service 

information as the title appears on the 

document. 

(4) Prior to further flight after modifying 

the engine as specified in paragraph (f)(1) or 

paragraph (f)(3) of this AD, remove the 

engine operation restriction (copy of AD 

2013–22–14) from the Limitations section of 

the AFM. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Jim Rutherford, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 329– 

4090; email: jim.rutherford@faa.gov. Before 

using any approved AMOC on any glider to 

which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(h) Related Information 

Refer to MCAI EASA AD No.: 2013– 

0217R1, dated May 5, 2014, for related 

information. You may examine the MCAI on 

the Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2013–0929. For service information related to 

this AD, contact Solo Kleinmotoren GmbH, 

Postfach 60 01 52, D 71050 Sindelfingen, 

Germany; telephone: +49 07031–301–0; fax: 

+49 07031–301–136; email: aircraft@sologermany.com; Internet: http://aircraft.soloonline.com. You may view this referenced 

service information at the FAA, Small 

Airplane Directorate, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the FAA, call 

(816) 329–4148. 

Issued in Kansas City, Missouri, on June 

19, 2014. 

Timothy Smyth, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–15058 Filed 6–26–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0742; Directorate 

Identifier 2013–CE–012–AD] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Proposed rule; withdrawal. 

SUMMARY: This document withdraws a 

notice of proposed rulemaking (NPRM) 

that would have applied to certain Piper 

Aircraft, Inc. Models PA–28–140, PA– 

28–150, PA–28–160, PA–28–180, PA– 

28R–180, and PA–28R–200 airplanes. 

The proposed airworthiness directive 

(AD) would have superseded AD 71– 

21–08, Amendment 39–1312, which 

currently requires replacement of the 

fuel selector valve cover. This proposed 

AD would have added additional 

airplanes to the AD’s applicability 

section and changed the compliance 

time of the required actions. Since 

issuance of the NPRM, the FAA has reevaluated this airworthiness concern 

and determined that an unsafe 

condition does not exist that would 

warrant AD action. This withdrawal 

does not prevent the FAA from 

initiating future rulemaking on this 

subject. 

DATES: As of June 27, 2014, the 

proposed rule published August 20, 

2013 (78 FR 51121), is withdrawn. 

FOR FURTHER INFORMATION CONTACT: Gary 

Wechsler, Aerospace Engineer, Atlanta 

Aircraft Certification Office, FAA, 1701 

Columbia Avenue, College Park, Georgia 

30337; telephone: (404) 474–5575; fax: 

(404) 474–5606; email: gary.wechsler@

faa.gov. 

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 Piper Aircraft, Inc. Models PA– 

28–140, PA–28–150, PA–28–160, PA– 

28–180, PA–28R–180, and PA–28R–200 

airplanes. That NPRM published in the 

Federal Register on August 20, 2013 (78 

FR 51121). That NPRM proposed to 

supersede AD 71–21–08, Amendment 

39–1312 (36 FR 19572, October 8, 1971), 

by adding airplanes to and changing the 

compliance time of AD 71–21–08 fuel 

selector valve cover replacement 

requirements. 

Because of the comments received on 

the NPRM (78 FR 51121, August 20, 

2013), the FAA re-evaluated the data 

collected on the safety concern and 

concluded that: 

• There was evidence of pilot 

inexperience and an absence of fuel 

selector valve maintenance (in 

accordance with Piper Service Bulletin 

355, dated June 5, 1972) in the Piper 

PA–28–180 crash of December 28, 2011; 

and 

• The low frequency of PA–28 series 

safety events due to the inadvertent 

selection of the ‘‘OFF’’ position of fuel 

selector valves, since AD 71–21–08 was 

published on October 13, 1971, does not 

warrant AD action. 

To mitigate the safety concern from 

recurring, the FAA may take other 

airworthiness action such as a special 

airworthiness information bulletin 

(SAIB) to recommend the actions 

contained in the proposed rule and 

capture the concerns identified by the 

public during the NPRM (78 FR 51121, 

August 20, 2013) comment period. 

Withdrawal of this NPRM (78 FR 

51121, August 20, 2013) constitutes 

only such action and does not preclude 

the agency from issuing future 

rulemaking on this issue, nor does it 

commit the agency to any course of 

action in the future. 

Regulatory Findings 

Since this action only withdraws an 

NPRM, it is neither a proposed nor a 

final rule and therefore, is not covered 

under Executive Order 12866, the 

Regulatory Flexibility Act, or DOT 

Regulatory Policies and Procedures (44 

FR 11034, February 26, 1979). 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS