### 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


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

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 beforeaccumulating 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.


### 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