3088 Federal Register / Vol. 77, No. 14 / Monday, January 23, 2012 / Rules and Regulations 

credibility of the resolution plan and the 

ability of the CIDI to implement the 

resolution plan. The FDIC will rely to 

the fullest extent possible on 

examinations conducted by or on behalf 

of the appropriate Federal banking 

agency for the relevant company. 

(2) Within a reasonable period of 

time, as determined by the FDIC, 

following its Initial Submission Date, 

the CIDI shall demonstrate its capability 

to produce promptly, in a time frame 

and format acceptable to the FDIC, the 

information and data underlying its 

resolution plan. The FDIC shall consult 

with the appropriate Federal banking 

agency for the CIDI before finding that 

the CIDI’s capability to produce the 

information and data underlying its 

resolution plan is unacceptable. 

(3) Notwithstanding the general 

requirements of paragraph (c)(1) of this 

section, on a case-by-case basis, the 

FDIC may extend, on its own initiative 

or upon written request, the 

implementation and updating time 

frames for all or part of the requirements 

of this section. 

(4) FDIC may, on its own initiative or 

upon written request, exempt a CIDI 

from one or more of the requirements of 

this section. 

(e) No limiting effect on FDIC. No 

resolution plan provided pursuant to 

this section shall be binding on the 

FDIC as supervisor, deposit insurer or 

receiver for a CIDI or otherwise require 

the FDIC to act in conformance with 

such plan. 

(f) Form of Resolution Plans; 

Confidential Treatment of Resolution 

Plans. (1) Each resolution plan of a CIDI 

shall be divided into a Public Section 

and a Confidential Section. Each CIDI 

shall segregate and separately identify 

the Public Section from the Confidential 

Section. The Public Section shall 

consist of an executive summary of the 

resolution plan that describes the 

business of the CIDI and includes, to the 

extent material to an understanding of 

the CIDI: 

(i) The names of material entities; 

(ii) A description of core business 

lines; 

(iii) Consolidated financial 

information regarding assets, liabilities, 

capital and major funding sources; 

(iv) A description of derivative 

activities and hedging activities; 

(v) A list of memberships in material 

payment, clearing and settlement 

systems; 

(vi) A description of foreign 

operations; 

(vii) The identities of material 

supervisory authorities; 

(viii) The identities of the principal 

officers; 

(ix) A description of the corporate 

governance structure and processes 

related to resolution planning; 

(x) A description of material 

management information systems; and 

(xi) A description, at a high level, of 

the CIDI’s resolution strategy, covering 

such items as the range of potential 

purchasers of the CIDI, its material 

entities and core business lines. 

(2) The confidentiality of resolution 

plans shall be determined in accordance 

with applicable exemptions under the 

Freedom of Information Act (5 U.S.C. 

552(b)) and the FDIC’s Disclosure of 

Information Rules (12 CFR part 309). 

(3) Any CIDI submitting a resolution 

plan or related materials pursuant to 

this section that desires confidential 

treatment of the information submitted 

pursuant to 5 U.S.C. 552(b)(4) and the 

FDIC’s Disclosure of Information Rules 

(12 CFR part 309) and related policies 

may file a request for confidential 

treatment in accordance with those 

rules. 

(4) To the extent permitted by law, 

information comprising the Confidential 

Section of a resolution plan will be 

treated as confidential. 

(5) To the extent permitted by law, the 

submission of any nonpublicly available 

data or information under this section 

shall not constitute a waiver of, or 

otherwise affect, any privilege arising 

under Federal or state law (including 

the rules of any Federal or state court) 

to which the data or information is 

otherwise subject. Privileges that apply 

to resolution plans and related materials 

are protected pursuant to Section 18(x) 

of the FDI Act, 12 U.S.C. 1828(x). 

Dated at Washington, DC this 17th day of 

January, 2012. 

By order of the Board of Directors. 

Federal Deposit Insurance Corporation. 

Robert E. Feldman, 

Executive Secretary. 

[FR Doc. 2012–1136 Filed 1–20–12; 8:45 am] 

BILLING CODE P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0599; Directorate 

Identifier 2011–NE–19–AD; Amendment 39– 

16922; AD 2012–01–10] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for General 

Electric Company (GE) CF34–10E series 

turbofan engines. This AD was 

prompted by a report of heavy wear 

found on the seating surface of the 

center vent duct (CVD) (commonly 

referred to as center vent tube) support 

ring and on the inside diameter of the 

fan drive shaft at the mating location. 

This AD requires removing from service 

all CVD support assemblies and any fan 

drive shaft on the affected engines if 

wear is found on either the CVD support 

ring or the fan drive shaft. We are 

issuing this AD to prevent fan drive 

shaft failure, leading to uncontained 

engine failure and damage to the 

airplane. 

DATES: This AD is effective February 27, 

2012. 

ADDRESSES: For service information 

identified in this AD, contact GE– 

Aviation, M/D Rm. 285, One Neumann 

Way, Cincinnati, OH 45215, phone: 

(513) 552–3272; email: 

geae.aoc@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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: (800) 647–5527) 

is Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: John 

Frost, Aerospace Engineer, Engine 

Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: (781) 238–7756; fax: (781) 

238–7199; email: john.frost@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 the specified products. That 

NPRM published in the Federal 

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Federal Register / Vol. 77, No. 14 / Monday, January 23, 2012 / Rules and Regulations 3089 

Register on October 18, 2011 (76 FR 

64287). That NPRM proposed to require 

removing from service all CVD support 

assemblies and any fan drive shaft on 

the affected engines if wear is found on 

either the CVD support ring or the 

inside diameter of the fan drive shaft. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Request To Include an Engine Serial 

Number (S/N) 

One commenter, Embraer Aircraft 

Maintenance Services, requests that we 

include engine S/N 994187 in the 

applicability. They cite the GE All 

Operators Wire they received as being 

accurate with the affected engine S/Ns, 

which includes S/N 994187. 

We agree. We added S/N 994187. 

Request To Allow Previous Credit 

One commenter, GE, requests that we 

allow previous credit for engines with 

records of prior CVD support assembly 

replacement and fan drive shaft 

inspection per the Engine Manual, 

before the effective date of the AD. 

We agree that previous credit should 

be allowed. Paragraph (e) of the AD 

requires compliance before 

accumulating 11,500 total cycles-inservice on the engine, unless already 

done. We did not change the AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

Costs of Compliance 

We estimate that this AD will affect 

71 GE CF34–10E series turbofan engines 

installed on airplanes of U.S. registry. 

We also estimate that it will take about 

8 work-hours per engine to perform a 

replacement of the CVD support 

assembly and visual inspections, and 

that the average labor rate is $85 per 

work-hour. A replacement CVD support 

assembly costs about $3,080. We 

estimate that two fan drive shafts will 

fail inspection and require replacement. 

A replacement fan drive shaft costs 

about $126,900. We estimate that no 

additional labor costs would be incurred 

to perform the required part 

replacements as the replacements are 

done at time of scheduled engine shop 

visit. Based on these figures, we 

estimate the total cost of the AD to U.S. 

operators to be $520,760. 

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 

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): 

2012–01–10 General Electric Company: 

Amendment 39–16922; Docket No. 

FAA–2011–0599; Directorate Identifier 

2011–NE–19–AD. 

(a) Effective Date 

This AD is effective February 27, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to General Electric 

Company (GE) CF34–10E series turbofan 

engines, serial number (S/N) 994116, and 

S/Ns 994118 through 994187, inclusive. 

(d) Unsafe Condition 

This AD was prompted by a report of 

heavy wear found on the seating surface of 

the center vent duct (CVD) (commonly 

referred to as center vent tube) support ring 

and on the inside diameter of the fan drive 

shaft at the mating location. The wear is 

caused by relative motion between the CVD 

support assembly (consisting of self-locking 

nut, part number (P/N) 2226M57G03, 

threaded sleeve, P/N 2226M55P03, and 

support ring, P/N 2226M56P01) and the fan 

drive shaft, during engine operation. We are 

issuing this AD to prevent fan drive shaft 

failure, leading to uncontained engine failure 

and damage to the airplane. 

(e) Compliance 

Comply with this AD before accumulating 

11,500 total cycles-in-service on the engine, 

unless already done. 

(f) Removal from Service of CVD Support 

Assembly and Determination of Fan Drive 

Shaft Serviceability 

Visually inspect the seating surface of the 

CVD support ring for wear. 

(1) If there is sign of wear on the CVD 

support ring, remove the CVD support 

assembly and the fan drive shaft from service 

before further flight. 

(2) If there is no sign of wear on the CVD 

support ring, remove the CVD support 

assembly from service and borescope inspect 

the inside diameter of the fan drive shaft at 

the CVD support ring contact area for wear. 

(3) If there is sign of wear on the inside 

diameter of the fan drive shaft, remove the 

fan drive shaft from service before further 

flight. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

return to service any CVD support assembly 

(consisting of self-locking nut, P/N 

2226M57G03, threaded sleeve, P/N 

2226M55P03, and support ring, P/N 

2226M56P01) or fan drive shaft removed 

from service as specified in this AD. 

(h) Definition 

For the purposes of this AD, the phrase 

‘‘sign of wear’’ is defined as any visual 

indication of removal of parent material from 

the CVD seating surface or the fan drive shaft. 

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3090 Federal Register / Vol. 77, No. 14 / Monday, January 23, 2012 / Rules and Regulations 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(j) Related Information 

(1) For more information about this AD, 

contact John Frost, Aerospace Engineer, 

Engine Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: (781) 238–7756; fax: (781) 

238–7199; email: john.frost@faa.gov. 

(2) GE Service Bulletin No. CF34–10E S/B 

72–0188, dated April 12, 2011, pertains to 

the subject of this AD. For service 

information identified in this AD, contact 

GE–Aviation, M/D Rm. 285, One Neumann 

Way, Cincinnati, OH 45215, phone: (513) 

552–3272; email: geae.aoc@ge.com. 

(3) You may review copies of the 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. 

(k) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

January 12, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–1132 Filed 1–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1022; Directorate 

Identifier 2011–NE–20–AD; Amendment 39– 

16919; AD 2012–01–07] 

RIN 2120–AA64 

Airworthiness Directives; BRP— 

POWERTRAIN GMBH & CO KG Rotax 

Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for BRP— 

POWERTRAIN GMBH & CO KG Rotax 

914 F2, 914 F3, and 914 F4 

reciprocating engines. This 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 isolated manufacturing 

deviations reportedly found on the 

threads of a certain batch of fuel 

pressure regulators, part number (P/N) 

887130, installed on Rotax 914 F series 

engines, which could result in fuel 

leakage during engine operation. We are 

issuing this AD to prevent fuel leaks, 

which could result in an in-flight fire 

and damage to the aircraft. 

DATES: This AD becomes effective 

February 27, 2012. 

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: 

Mark Riley, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

email: mark.riley@faa.gov; phone: (781) 

238–7758; 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 September 28, 2011 (76 FR 

59950). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states that: 

Isolated manufacturing deviations have 

been reportedly found on the threads of a 

certain batch of fuel pressure regulators, Part 

Number (P/N) 887130, installed on Rotax 914 

F series engines. 

The corrective action includes replacing 

fuel pressure regulators listed in Table 

1 of this AD with a fuel pressure 

regulator that is not listed in Table 1 of 

this AD, and is eligible for installation. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

The European Aviation Safety Agency 

AD requires replacing the fuel pressure 

regulator within 100 flight hours (FHs) 

or 6 months after the effective date of 

that AD, whichever occurs first. This 

AD requires replacing the fuel pressure 

regulator within 100 FHs after the 

effective date of this AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 75 products of U.S. registry. We 

also estimate that it will take about 2 

work-hours per product to comply with 

this AD. The average labor rate is $85 

per work-hour. Required parts cost 

about $180 per product. Based on these 

figures, we estimate the cost of the AD 

on U.S. operators to be $26,250. 

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 

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