Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Proposed Rules 11717 

the Federal credit union’s assets may be 

made to its members from cash funds 

available on authorization by the board 

of directors or liquidating agent. 

Payment of a partial distribution may 

exclude member accounts of less than 

$25.00 and must not exceed the insured 

amount of any account, as determined 

under part 745 of this chapter. 

(b) After all assets of the Federal 

credit union have been converted to 

cash or found to be worthless and all 

loans and debts owing to it have been 

collected or found to be uncollectible 

and all obligations of the Federal credit 

union have been paid, with the 

exception of shares due its members, the 

books shall be closed and the pro rata 

distribution to the members shall be 

computed. The computation shall be 

based on the total amount in each share 

account as of the liquidation date or the 

date on which all share drafts have 

cleared, whichever is later. 

(c) Payments must be made to 

members promptly after the pro rata 

distribution has been computed. The 

Federal credit union may mail a check 

to a member at his or her last known 

address, deliver the check personally to 

the member, or make the payment by 

wire or any other electronic means 

approved by a member. 

* * * * * 

[FR Doc. 2014–04231 Filed 2–28–14; 8:45 am] 

BILLING CODE 7535–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0121; Directorate 

Identifier 2013–NM–151–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2008–14– 

17, for certain Airbus Model A330–200 

and A340–300 series airplanes. AD 

2008–14–17 currently requires a high 

frequency eddy current (HFEC) 

inspection, corrective actions if 

necessary, and modifications. Since we 

issued AD 2008–14–17, it has been 

determined from a fatigue and damage 

tolerance evaluation that the 

compliance time needs to be revised. 

This proposed AD would require the 

same actions as those required by AD 

2008–14–17, but with a reduced 

compliance time. We are proposing this 

AD to detect and correct damage of the 

upper shell structure at the skin and 

frame interface, which could result in 

reduced structural integrity of the 

airframe. 

DATES: We must receive comments on 

this proposed AD by April 17, 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, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS, 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. 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 by searching for 

and locating Docket No. FAA–2014– 

0121; 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 MCAI, 

the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1138; 

fax (425) 227–1149. 

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–2014–0121; Directorate Identifier 

2013–NM–151–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 based on 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 June 27, 2008, we issued AD 

2008–14–17, Amendment 39–15612 (73 

FR 40958, July 17, 2008). AD 2008–14– 

17 requires actions intended to address 

an unsafe condition on certain Airbus 

Model A330–200 and A340–300 series 

airplanes. 

Since we issued AD 2008–14–17, 

Amendment 39–15612 (73 FR 40958, 

July 17, 2008), it has been determined 

from a fatigue and damage tolerance 

evaluation that the compliance time of 

the HFEC inspection for cracking, and 

modification of the upper shell structure 

of the fuselage needs to be revised. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0158, 

dated July 22, 2013 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

During fatigue tests (EF3) on an A340–600 

aeroplane, multiple damage was found in the 

upper side shell structure at skin and frame 

(FR) 84 and 85 interface, from stringer 6 to 

15 Left-Hand (LH) and Right Hand (RH). This 

damage occurred between 58 341 and 72 891 

simulated flight cycles (FC). 

Due to the higher Design Service Goal and 

different design (e.g. skin thickness) for 

A330–200 and A340–300 aeroplanes, the 

damage assessment concluded that these 

aeroplanes can potentially be impacted. 

This condition, if not detected and 

corrected, could result in reduced structural 

integrity of the airframe. 

Prompted by these findings, EASA issued 

[an] AD * * * to require a one-time 

inspection and a modification to improve the 

upper shell structure. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

11718 Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Proposed Rules 

EASA AD 2007–0269R1 [(http://

ad.easa.europa.eu/blob/easa_ad_2007_

0269R1_superseded.pdf/AD_2007–0269R1_

2)], which corresponds to FAA AD 2008–14– 

17, Amendment 39–15612 (73 FR 40958) was 

issued to clarify the fact that the [EASA] AD 

was not applicable to A340–300 aeroplanes 

on which both Airbus Mod 44205 and Mod 

45012 have been embodied in production. 

Since that [EASA] AD was issued, in the 

frame of a new fatigue and damage tolerance 

evaluation, taking into account the aeroplane 

utilization, the threshold and intervals were 

reassessed. This reassessment concluded 

that, in that specific case, the threshold for 

modifying the aeroplane must be reduced. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2007–0269R1, which is superseded, but 

requires these actions within the new 

thresholds. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating it in Docket No. FAA– 

2014–0121. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A330–53–3152, Revision 03, 

dated December 22, 2011. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This 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 the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an 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 

affects 7 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection and Modification [retained actions from AD 

2008–14–17, Amendment 39–15612 (73 FR 40958, 

July 17, 2008)].

300 work-hours × $85 per hour = 

$25,500.

$72,730 $98,230 $687,610 

This proposed AD adds no additional 

economic burden. 

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 

Airworthiness Directive (AD) 2008–14– 

17, Amendment 39–15612 (73 FR 

40958, July 17, 2008), and adding the 

following new AD: 

Airbus: Docket No. FAA–2014–0121; 

Directorate Identifier 2013–NM–151–AD. 

(a) Comments Due Date 

We must receive comments by April 17, 

2014. 

(b) Affected ADs 

This AD supersedes AD 2008–14–17, 

Amendment 39–15612 (73 FR 40958, July 17, 

2008). 

(c) Applicability 

This AD applies to the airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Airbus Model A330–201, –202, –203, 

–223, and –243 airplanes, all manufacturer 

serial numbers (MSN), on which Airbus 

modification 44205 has been embodied in 

production, except those on which Airbus 

modification 52974 or modification 53223 

has been embodied in production. 

(2) Airbus Model A340–311, –312, and 

–313 airplanes, all MSN on which Airbus 

modification 44205 has been embodied in 

production, except those on which Airbus 

modification 52974 or modification 53223 or 

modification 45012 has been embodied in 

production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a determination 

from a fatigue and damage tolerance 

evaluation that the compliance time of the 

high frequency eddy current (HFEC) 

inspection for cracking, and modification of 

the upper shell structure of the fuselage 

needs to be revised. We are issuing this AD 

to detect and correct damage of the of the 

upper shell structure at the skin and frame 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Proposed Rules 11719 

interface, which could result in reduced 

structural integrity of the airframe. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection With Reduced 

Compliance Times and Revised Service 

Information 

This paragraph restates the requirements of 

paragraph (f)(1) of AD 2008–14–17, 

Amendment 39–15612 (73 FR 40958, July 17, 

2008), with reduced compliance times and 

revised service information. For Airbus 

Model A330–200 series airplanes, as 

identified in paragraph (c) of this AD, on 

which Modification 45012 has been 

embodied in production: Within the 

applicable compliance times specified in 

paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of 

this AD, do the HFEC inspection for cracking, 

and corrective actions as applicable; and 

modify the upper shell structure of the 

fuselage; in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–53–3152, 

Revision 3, dated December 22, 2011. Do all 

applicable corrective actions before further 

flight. 

(1) For airplanes pre-modification 48827 

with short range utilization: At the later of 

the times specified in paragraph (g)(1)(i) or 

(g)(1)(ii) of this AD. 

(i) Prior to 24,400 total flight cycles or 

85,400 total flight hours, whichever occurs 

first. 

(ii) Within 12 months after the effective 

date of this AD without exceeding 25,400 

total flight cycles. 

(2) For airplanes pre-modification 48827 

with long range utilization: At the later of the 

times specified in paragraph (g)(2)(i) or 

(g)(2)(ii) of this AD. 

(i) Prior to 18,900 total flight cycles or 

122,900 total flight hours, whichever occurs 

first. 

(ii) Within 12 months after the effective 

date of this AD without exceeding 25,400 

total flight cycles. 

(3) For airplanes post-modification 48827 

with short range utilization: At the later of 

the times specified in paragraph (g)(3)(i) or 

(g)(3)(ii) of this AD. 

(i) Prior to 16,400 total flight cycles or 

57,400 total flight hours, whichever occurs 

first. 

(ii) Within 12 months after the effective 

date of this AD without exceeding 17,100 

total flight cycles or 94,700 total flight hours, 

whichever occurs first. 

(4) For airplanes post-modification 48827 

with long range utilization: At the later of the 

times specified in paragraph (g)(4)(i) or 

(g)(4)(ii) of this AD. 

(i) Prior to 12,700 total flight cycles or 

82,700 total flight hours, whichever occurs 

first. 

(ii) Within 12 months after the effective 

date of this AD without exceeding 17,100 

total flight cycles or 94,700 total flight hours, 

whichever occurs first. 

(h) Retained Modification With Revised 

Formatting 

This paragraph restates the requirements of 

paragraph (f)(2) of AD 2008–14–17, 

Amendment 39–15612 (73 FR 40958, July 17, 

2008). For Airbus Model A330–200 and 

A340–300 series airplanes as identified in 

paragraph (c) of this AD, on which 

Modification 45012 has not been embodied 

in production: At the later of the compliance 

times specified in paragraphs (h)(1) and 

(h)(2) of this AD, modify the upper shell 

structure of the fuselage, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3157 or Airbus 

Service Bulletin A340–53–4163, both dated 

July 5, 2006, as applicable. 

(1) For the airplanes identified in 

paragraphs (h)(1)(i) and (h)(1)(ii) of this AD. 

(i) For Model A330–200 series airplanes, 

prior to 6,600 total flight cycles. 

(ii) For Model A340–300 series airplanes, 

prior to 14,000 total flight cycles. 

(2) Within 90 days after August 21, 2008 

(the effective date of AD 2008–14–17, 

Amendment 39–15612 (73 FR 40958, July 17, 

2008)). 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using the service information 

specified in paragraph (i)(1), (i)(2), or (i)(3) of 

this AD. 

(1) Airbus Mandatory Service Bulletin 

A330–53–3152, dated April 10, 2007. 

(2) Airbus Mandatory Service Bulletin 

A330–53–3152, Revision 1, dated May 5, 

2009. 

(3) Airbus Mandatory Service Bulletin 

A330–53–3152, Revision 2, dated July 27, 

2011. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1138; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or by the DAH with a 

State of Design Authority’s design 

organization approval, as applicable). You 

are required to ensure the product is 

airworthy before it is returned to service. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0158, dated July 22, 2013, for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2014–0121. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.com. You may 

view this service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on February 

14, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–04501 Filed 2–28–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0953; Directorate 

Identifier 2013–NE–32–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Rolls-Royce plc (RR) RB211 Trent 875– 

17, 877–17, 884–17, 884B–17, 892–17, 

892B–17, and 895–17 turbofan engines. 

The proposed AD was prompted by 

thin-walled low pressure (LP) turbine 

bearing support and exhaust case 

assemblies having been delivered into 

service. This proposed AD would 

require inspection of the affected LP 

turbine bearing support and exhaust 

case assembly and, if necessary, its 

replacement with a part eligible for 

installation. We are proposing this AD 

to prevent failure of the LP turbine 

mstockstill on DSK4VPTVN1PROD with PROPOSALS