Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Proposed Rules 24407 

(ii) Debts arising under the tariff laws 

of the United States; 

(iii) Any case where collection of a 

debt by salary offset is explicitly 

provided for or prohibited by another 

statute (e.g., travel advances in 5 U.S.C. 

5705 and employee training expenses in 

5 U.S.C. 4108); or 

(iv) Any other debt excluded by the 

FCCS or 31 CFR part 285. 

* * * * * 

(3) Compromise, suspension, or 

termination of collection actions. This 

subpart does not preclude the 

compromise, suspension, or termination 

of collection actions, where appropriate, 

as provided in the FCCS (31 CFR 900.4) 

or the use of alternative dispute 

resolution methods if they are not 

inconsistent with agency-specific laws 

and regulations. 

3. In § 550.1103, the definition of 

‘‘FCCS’’ is revised to read as follows: 

§ 550.1103 Definitions. 

* * * * * 

FCCS means the Federal Claims 

Collections Standards published in 31 

CFR parts 900 through 904. 

* * * * * 

4. In § 550.1104, paragraphs (d)(3), (i), 

and (j) are revised to read as follows: 

§ 550.1104 Agency regulations. 

* * * * * 

(d) * * * 

(3) The frequency and amount of the 

intended deduction (stated as a fixed 

dollar amount or as a percentage of pay, 

not to exceed 15 percent of disposable 

pay except as provided in paragraph (i) 

of this section) and the intention to 

continue the deductions until the debt 

is paid in full or otherwise resolved; 

* * * * * 

(i) Limitation on amount of 

deductions. Prescribe the limitations on 

the amount of the deduction. 

Ordinarily, the size of installment 

deductions must bear a reasonable 

relationship to the size of the debt and 

the employee’s ability to pay (see the 

FCCS). However, the amount deducted 

for any period may not exceed 15 

percent of the disposable pay from 

which the deduction is made, unless the 

employee has agreed in writing to the 

deduction of a greater amount or a 

higher deduction has been ordered by a 

court under section 124 of Public Law 

97–276 (96 Stat.1195). 

(j) Duration of deductions. Prescribe 

the duration of deductions. Ordinarily, 

debts must be collected in one lump 

sum where possible. However, if the 

employee is financially unable to pay in 

one lump sum or the amount of the debt 

exceeds 15 percent of disposable pay (or 

other applicable limitation as provided 

in paragraph (i) of this section) for an 

officially established pay interval, 

collection must be made in installments. 

Such installment deductions must be 

made over a period not greater than the 

anticipated period of active duty or 

employment, as the case may be, except 

as provided in paragraphs (l) and (m) of 

this section. 

* * * * * 

5. Section 550.1106 is revised to read 

as follows: 

§ 550.1106 Time limit on collection of 

debts. 

Agencies may initiate salary offset to 

collect a debt without time limitations 

on any debt outstanding after the 

Government’s right to collect the debt 

first accrued. (See § 550.1108 for 

requirement when debts are delinquent 

over 180 days.) 

* * * * * 

[FR Doc. 2011–10626 Filed 4–29–11; 8:45 am] 

BILLING CODE 6325–39–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0392; Directorate 

Identifier 2011–NE–12–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company CT7–8, CT7–8A, 

CT7–8A1, CT7–8E, and CT7–8F5 

Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD would require the installation of an 

accessory gearbox (AGB) axis-A oil 

slinger nut to the axis-A shaft assembly. 

This proposed AD was prompted by 

four reports of unrecoverable engine 

stalls, during hover in a left-roll 

attitude. We are proposing this AD to 

prevent an unrecoverable engine stall, 

leading to a helicopter forced landing or 

accident. 

DATES: We must receive comments on 

this proposed AD by June 16, 2011. 

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: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact GE-Aviation, 

M/D Rm. 285, One Neumann Way, 

Cincinnati, OH 45215; telephone: 513– 

552–3272; e-mail: geaeaoc@ge.com. You 

may review copies of the referenced 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Walter Meibaum, Aerospace Engineer, 

Engine & Propeller Directorate, FAA, 

12 New England Executive Park, 

Burlington, MA 01803; phone: 781– 

238–7119; fax: 781–238–7199; e-mail: 

walter.meibaum@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2011–0392; Directorate Identifier 2011– 

NE–12–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. 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
24408 Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Proposed Rules 

Discussion 

We received four reports of General 

Electric Company (GE) CT7–8 series 

turboshaft helicopter engines 

experiencing unrecoverable engine 

stalls, during hover in a left-roll 

attitude. Investigation revealed that 

during a prolonged left roll, excessive 

return oil from the AGB may return to 

the A-sump and exceed the sump’s 

scavenging capability. The sump then 

floods, leading to over-heated oil, which 

preheats the air entering the engine’s 

compressor. This preheated air causes 

inlet thermal distortion. This condition, 

if not corrected, could result in an 

unrecoverable engine stall, leading to a 

helicopter forced landing or accident. 

Relevant Service Information 

We reviewed GE Aircraft Engines 

CT7–8 Turboshaft Engine Service 

Bulletin (SB) No. CT7–8 S/B 72–0033, 

dated February 11, 2011. The SB 

describes procedures for installing the 

AGB axis-A oil slinger nut to the axisA shaft assembly. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other engines of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require the 

installation of an AGB axis-A oil slinger 

nut to the axis-A shaft assembly. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 80 engines installed on 

helicopters of U.S. registry. We also 

estimate that it would take about one 

work-hour per engine to perform the 

actions required by this proposed AD, 

and that the average labor rate is $85 per 

work-hour. Required parts would cost 

about $700 per engine. Based on these 

figures, we estimate the total cost of the 

proposed AD to U.S. operators to be 

$62,800. 

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. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

General Electric Company: Docket No. FAA– 

2011–0392; Directorate Identifier 2011– 

NE–12–AD. 

Comments Due Date 

(a) We must receive comments by June 16, 

2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the following 

General Electric Company (GE) turboshaft 

engines: 

(1) CT7–8, all engine serial numbers 

(S/Ns). 

(2) CT7–8A, engine S/Ns 947565 and 

below. 

(3) CT7–8A1, engine S/Ns 530017 and 

below. 

(4) CT7–8E, engine S/Ns 953068 and 

below, and S/Ns 953070 and 953072. 

(5) CT7–8F5, engine S/Ns 731005 and 

below, and S/Ns 731007, 731008, 817021, 

and 817022. 

Unsafe Condition 

(d) This AD was prompted by four reports 

of unrecoverable engine stalls, during hover 

in a left-roll attitude. We are issuing this AD 

to prevent an unrecoverable engine stall, 

leading to a helicopter forced landing or 

accident. 

Compliance 

(e) Comply with this AD at the next engine 

shop visit, the next 1,500-hour helicopter 

inspection, or before operation after next 

engine installation, whichever occurs first, 

unless already done. 

Installation of Accessory Gearbox (AGB) 

Axis-A Oil Slinger Nut 

(f) Install the AGB axis-A oil slinger nut to 

the axis-A shaft assembly. Use 

Accomplishment Instructions, paragraphs 

3.A. through 3.C. of GE Aircraft Engines 

CT7–8 Turboshaft Engine Service Bulletin 

No. CT7–8 S/B 72–0033, dated February 11, 

2011, to do the installation. 

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) For more information about this AD, 

contact Walter Meibaum, Aerospace 

Engineer, Engine & Propeller Directorate, 

FAA, 12 New England Executive Park, 

Burlington, MA 01803; phone: 781–238– 

7119; fax: 781–238–7199; e-mail: 

walter.meibaum@faa.gov. 

(i) For service information identified in 

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

One Neumann Way, Cincinnati, OH 45215; 

telephone: 513–552–3272; e-mail: 

geaeaoc@ge.com. You may review copies of 

the referenced 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. 

Issued in Burlington, Massachusetts, on 

April 25, 2011. 

Peter A. White, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–10522 Filed 4–29–11; 8:45 am] 

BILLING CODE 4910–13–P 


emcdonald on DSK2BSOYB1PROD with PROPOSALS