58290 Federal Register / Vol. 75, No. 185 / Friday, September 24, 2010 / Rules and Regulations 

(7) * * * 

(iii) Short-term, small amount Loans 

(STS loans). (A) Notwithstanding the 

provisions in § 701.21(c)(7)(ii), a Federal 

credit union may charge an interest rate 

of 1000 basis points above the 

maximum interest rate as established by 

the Board, provided the Federal credit 

union is making a closed-end loan in 

accordance with the following 

conditions: 

(1) The principal of the loan is not 

less than $200 or more than $1000; 

(2) The loan has a minimum maturity 

term of one month and a maximum 

maturity term of six months; 

(3) The Federal credit union does not 

make more than three STS loans in any 

rolling six-month period to any one 

borrower and makes no more than one 

short-term, small amount loan at a time 

to a borrower; 

(4) The Federal credit union must not 

roll-over any STS loan; 

(A) The prohibition against roll-overs 

does not apply to an extension of the 

loan term within the maximum loan 

terms in paragraph (c)(7)(iii)(3) provided 

the Federal credit union does not charge 

any additional fees or extend any new 

credit. 

(B) [Reserved] 

(5) The Federal credit union fully 

amortizes the loan; 

(6) The Federal credit union sets a 

minimum length of membership 

requirement of at least one month; 

(7) The Federal credit union charges 

an application fee to all members 

applying for a new loan that reflects the 

actual costs associated with processing 

the application, but in no case may the 

application fee exceed $20; and 

(8) The Federal credit union includes, 

in its written lending policies, a limit on 

the aggregate dollar amount of loans 

made under this section of a maximum 

of 20% of net worth and implements 

appropriate underwriting guidelines to 

minimize risk; for example, requiring a 

borrower to verify employment by 

producing at least two recent pay stubs. 

(B) STS Loan Program Guidance and 

Best Practices. In developing a 

successful STS loan program, a Federal 

credit union should consider how the 

program will help benefit a member’s 

financial well-being while considering 

the higher degree of risk associated with 

this type of lending. The guidance and 

best practices are intended to help 

Federal credit unions minimize risk and 

develop a successful program, but are 

not an exhaustive checklist and do not 

guarantee a successful program with a 

low degree of risk. 

(1) Program Features. Several features 

that may increase the success of an STS 

loan program and enhance member 

benefit include adding a savings 

component, financial education, 

reporting of members’ payment of STS 

loans to credit bureaus, or electronic 

loan transactions as part of an STS 

program. In addition, although a Federal 

credit union cannot require members to 

authorize a payroll deduction, a Federal 

credit union should encourage or 

incentivize members to utilize payroll 

deduction. 

(2) Underwriting. Federal credit 

unions need to develop minimum 

underwriting standards that account for 

a member’s need for quickly available 

funds, while adhering to principles of 

responsible lending. Underwriting 

standards should address required 

documentation for proof of employment 

or income, including at least two recent 

paycheck stubs. FCUs should be able to 

use a borrower’s proof of recurring 

income as the key criterion in 

developing standards for maturity 

lengths and loan amounts so a borrower 

can manage repayment of the loan. For 

members with established accounts, 

FCUs should only need to review a 

member’s account records and proof of 

recurring income or employment. 

(3) Risk Avoidance. Federal credit 

unions need to consider risk avoidance 

strategies, including: requiring members 

to participate in direct deposit and 

conducting a thorough evaluation of the 

Federal credit union’s resources and 

ability to engage in an STS loan 

program. 

* * * * * 

[FR Doc. 2010–23610 Filed 9–23–10; 8:45 am] 

BILLING CODE 7535–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0364; Directorate 

Identifier 2009–NE–27–AD; Amendment 39– 

16446; AD 2010–20–11] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211 Trent 700 and Trent 800 

Series Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This 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. The MCAI describes the unsafe 

condition as: 

In completing a review of Engine Manual 

repair/acceptance limits for titanium 

compressor shafts, Rolls-Royce has found the 

specified limits to be incorrect such that the 

shot peened surface layer at life critical 

features (the axial dovetail slots) may have 

been inadvertently removed in-service. 

Removal of the shot peened layer results in 

increased vulnerability of the part to tensile 

stresses, which could reduce the life of the 

shaft to below the published life limits. 

We are issuing this AD to prevent 

failure of the intermediate-pressure (IP) 

and high-pressure (HP) shaft, which 

could result in an overspeed condition, 

possible uncontained disc failure and 

damage to the airplane. 

DATES: This AD becomes effective 

October 29, 2010. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue, SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: james.lawrence@faa.gov; 

telephone (781) 238–7176; fax (781) 

238–7199. 

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 was published in the Federal 

Register on April 7, 2010 (75 FR 17630). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

In completing a review of Engine Manual 

repair/acceptance limits for titanium 

compressor shafts, Rolls-Royce has found the 

specified limits to be incorrect such that the 

shot peened surface layer at life critical 

features (the axial dovetail slots) may have 

been inadvertently removed in-service. 

Removal of the shot peened layer results in 

increased vulnerability of the part to tensile 

stresses, which could reduce the life of the 

shaft to below the published life limits. The 

acceptable limits for material loss on these 

surfaces have now been corrected in the 

Engine Manual. 

This AD identifies shafts for which such 

dressing operations have been known to have 

been carried out and requires that an 

inspection for compliance with the corrected 

Engine Manual limits be accomplished and 

that the shafts be dispositioned accordingly. 


hsrobinson on DSK69SOYB1PROD with RULES
Federal Register / Vol. 75, No. 185 / Friday, September 24, 2010 / Rules and Regulations 58291 

Comments 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Requests To Change Paragraphs (e)(1) 

and (e)(2) of the Proposed AD 

Two commenters, The Boeing 

Company and American Airlines, ask us 

to change paragraphs (e)(1) and (e)(2) of 

the proposed AD to clarify the focused 

inspections and to include a reference to 

Rolls-Royce (RR) Alert NonModification Service Bulletin (NMSB) 

RB.211–72–AG086. 

The Boeing Company asks us to 

change paragraph (e)(2) to include a 

reference to RR Alert NMSB RB.211–72– 

AG086. They state that guidance on fullfocused inspections and acceptance 

limits can be found in either the current 

applicable RR engine manual or RR 

Alert NMSB RB.211–72–AG086. The 

Boeing Company feels that the 

information contained in the engine 

manual is not as clear or as accessible 

as in the RR Alert NMSB and that 

including the RR Alert NMSB, as an 

additional source of guidance, will 

assist the operators in conducting the 

associated inspections properly. 

We agree. We changed paragraph 

(e)(2) to include a reference to RR Alert 

NMSB RB.211–72–AG086. 

American Airlines, asks us to change 

paragraph (e)(1) to include a 

requirement for ‘‘all applicable focus 

inspection subtasks of the IP and HP 

compressor shafts * * *’’ American 

Airlines states that the Rolls-Royce 

Time Limits Manual and the applicable 

Engine Inspection Tasks do not use 

‘‘full-focused inspection’’ terminology 

(as used in the NPRM). American 

Airlines believes that the AD 

terminology should be consistent with 

the manuals. 

We agree. We changed paragraph 

(e)(1) to state ‘‘Perform a one-time, 

piece-part, full inspection, including all 

applicable focus inspection Subtasks, of 

the IP and HP compressor shafts, listed 

by part number and serial number in 

Table 1 of this AD, before exceeding the 

compliance period specified in Table 1 

of this AD.’’ 

Conclusion 

We reviewed the available data, 

including the comment[s] received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD would affect about 

12 products of U.S. registry. We also 

estimate that it would take about 8 

work-hours per product to comply with 

this AD. The average labor rate is $85 

per work-hour. Required parts would 

cost about $15,000 per product. Based 

on these figures, we estimate the cost of 

the AD on U.S. operators to be $188,160. 

Our cost estimate is exclusive of 

possible warranty coverage. 

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 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 this AD: 

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 AD and placed it in the AD docket. 

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 provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, 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 AD: 

2010–20–11 Rolls-Royce plc: Amendment 

39–16446. Docket No. FAA–2010–0364; 

Directorate Identifier 2009–NE–27–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 29, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Rolls-Royce plc 

model (RR) RB211 Trent 768–60, 772–60, 

772B–60, 875–17, 877–17, 884–17, 884B–17, 

892–17, 892B–17, and 895–17 turbofan 

engines that have a compressor shaft listed 

by part number and serial number in Table 

1 of this AD. These engines are installed on, 

but not limited to, Airbus A330 series and 

Boeing 777 series airplanes. 

Reason 

(d) This AD results from a review of engine 

manual repair/acceptance limits for titanium 

compressor shafts by RR. We are issuing this 

AD to prevent failure of the intermediatepressure (IP) and high-pressure (HP) shaft, 

which could result in an overspeed 

condition, possible uncontained disc failure 

and damage to the airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) Perform a one-time, piece-part, full 

inspection, including all applicable focus 


hsrobinson on DSK69SOYB1PROD with RULES
58292 Federal Register / Vol. 75, No. 185 / Friday, September 24, 2010 / Rules and Regulations 

inspection Subtasks, of the IP and HP 

compressor shafts listed by part number and 

serial number in Table 1 of this AD before 

exceeding the compliance period specified in 

Table 1 of this AD. 

(2) Guidance on full and focused 

inspections and acceptance limits can be 

found in the current, applicable RR engine 

manual and RR Alert Non-Modification 

Service Bulletin (NMSB) RB.211–72–AG086. 

TABLE 1—LIST OF AFFECTED SHAFTS

Engine series Affected component Part no. Shaft serial no. 

Compliance period 

(flight cycles in 

service after 

December 4, 2008) 

Trent 800 ........................... 1–8 IP Compressor Shaft .............................................. FK24100 MW0115238 750 

Trent 800 ........................... 1–4 HP Compressor Shaft ............................................ FK32580 MW0115512 750 

Trent 800 ........................... 1–4 HP Compressor Shaft ............................................ FK32580 MW0004708 2000 

Trent 800 ........................... 1–4 HP Compressor Shaft ............................................ FK32580 MW00063868 2500 

Trent 800 ........................... 1–8 IP Compressor Shaft .............................................. FK24100 DN65507 2500 

Trent 800 ........................... 1–8 IP Compressor Shaft .............................................. FK24100 DN65158 2500 

Trent 800 ........................... 1–4 HP Compressor Shaft ............................................ FK32580 MW0125467 3500 

Trent 800 ........................... 1–4 HP Compressor Shaft ............................................ FW11590 DN65189 3500 

Trent 800 ........................... 1–8 IP Compressor Shaft .............................................. FK24100 MW0091518 3500

Trent 800 ........................... 1–8 IP Compressor Shaft .............................................. FK24100 MW0126365 3500

Trent 800 ........................... 1–8 IP Compressor Shaft .............................................. FK24100 DN66422 4750 

Trent 800 ........................... 1–8 IP Compressor Shaft .............................................. FK24100 MW0203314 4750

Trent 700 ........................... 1–8 IP Compressor Shaft .............................................. FK22279 DN63228 3250 

Trent 700 ........................... 1–8 IP Compressor Shaft .............................................. FK26048 MW0026046 4500

Other FAA AD Provisions 

(f) Alternative Methods of Compliance 

(AMOCs): 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 

(g) Refer to MCAI EASA Airworthiness 

Directive 2009–0021 (Corrected February 9, 

2009), dated February 6, 2009, and RR Alert 

NMSB RB.211–72–AG086, for related 

information. 

(h) Contact James Lawrence, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: james.lawrence@faa.gov; 

telephone (781) 238–7176; fax (781) 238– 

7199, for more information about this AD. 

Material Incorporated by Reference 

(i) None. 

Issued in Burlington, Massachusetts, on 

September 17, 2010. 

Robert J. Ganley, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–23831 Filed 9–23–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 47 

[Docket No. FAA–2008–0188; Amdt. No. 47– 

29A] 

RIN 2120–AI89 

Re-Registration and Renewal of 

Aircraft Registration; OMB Approval of 

Information Collection; Correction 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; approval of 

information collection; correction. 

SUMMARY: The FAA is correcting the 

notification of the Office of Management 

and Budget (OMB) approval of 

information collection requirements 

contained in the ‘‘Re-Registration and 

Renewal of Aircraft Registration’’ final 

rule. The final rule was published on 

July 20, 2010. The notification of OMB 

approval of information collection was 

published on August 30, 2010. This 

document corrects the OMB approval 

expiration date referenced in the August 

30, 2010, notification. 

DATES: The final rule, including the 

information collection requirements in 

part 47, published July 20, 2010, at 75 

FR 41968, and August 20, 2010, at 75 FR 

52859, will become effective on October 

1, 2010. The FAA received OMB 

approval for the information collection 

requirements on August 16, 2010. 

FOR FURTHER INFORMATION CONTACT: John 

G. Bent, Civil Aviation Registry, Mike 

Monroney Aeronautical Center, 6500 

South MacArthur Boulevard, Oklahoma 

City, OK 73169; telephone: (405) 954– 

4331. 

SUPPLEMENTARY INFORMATION: 

Background 

On July 20, 2010, the FAA published 

the final rule ‘‘Re-Registration and 

Renewal of Aircraft Registration’’ (75 FR 

41968). 

The final rule contained information 

collection requirements in part 47 that 

had not yet been approved by OMB at 

the time of publication. In accordance 

with the Paperwork Reduction Act, the 

FAA submitted a copy of the new 

information collection requirements to 

OMB for its review. OMB approved the 

collection on August 16, 2010, and 

assigned the information collection 

OMB Control Number 2120–0729, 

which expires on February 29, 2012. In 

the notification of OMB approval 

document that was published on August 

30, 2010, the FAA incorrectly stated that 

the expiration date was February 29, 

2010. The FAA also incorrectly 

referenced docket number FAA–2008– 

0118 instead of docket number FAA– 

2008–0188. The FAA also inadvertently 

included references to parts 13 and 91 

in the heading of the document; 

however, parts 13 and 91 did not 

contain information collection 

requirements. 

In final rule FR Doc. 2010–21561 

published on August 30, 2010 (75 FR 

52859), make the following corrections: 

Corrections to Preamble 

■ 1. On page 52859, in the second 

column, in the third line of the heading, 

remove ‘‘14 CFR Parts 13, 47, and 91’’ 

and add in its place ‘‘14 CFR Part 47.’’ 


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