### 73265 Federal Register / Vol. 77, No. 237 / Monday, December 10, 2012 / Rules and Regulations

Oversight Committee, the division also oversees and coordinates FHFA activities that involve certain data analysis, and analysis affecting housing finance and financial markets.

(4) Division of Federal Home Loan Bank Regulation. The division supports and implements the responsibilities of the Deputy Director described in paragraph (d) of this section, including overseeing and directing all Bank supervisory activities, developing examination findings, preparing reports of examination, and preparing the sections of the annual report to Congress that describe the condition and performance of the Banks. The division monitors and assesses the financial condition and performance of the Banks and the OF and monitors and assesses their compliance with regulations, the amount of risk they assume, and the quality of their risk management through annual on-site examinations, periodic visits, and ongoing off-site monitoring and analysis.

(5) Office of Inspector General. The office is headed by a presidentially appointed and Senate-confirmed Inspector General who serves under the general supervision of the Director. The office carries out activities and responsibilities established in the Inspector General Act of 1978.

(6) Office of General Counsel. The office advises and supports the Director and FHFA staff on legal matters related to the functions, activities, and operations of FHFA and the regulated entities; it supports supervision functions, development and promulgation of regulations and orders, and enforcement actions. The office manages the Freedom of Information, Privacy Act and ethics programs. The Designated Agency Ethics Official advises, counsels, and trains FHFA employees on ethical standards and conflicts of interest, and manages the agency’s financial disclosure program.

(7) Office of the Ombudsman. The office is responsible for considering complaints and appeals from the regulated entities, the OF and any person that has a business relationship with a regulated entity or the OF concerning any matter relating to FHFA’s regulation and supervision of that entity or the OF.

(8) Office of Minority and Women Inclusion. The office is responsible for all matters of FHFA relating to diversity in management, employment, and business activities, and for supervising the diversity requirements applicable to the regulated entities and the OF.

(f) Other Offices and Departments. The Director may from time to time establish other Offices and Divisions of the agency as the Director deems necessary or appropriate to carry out FHFA’s mission, such as an Office of Conservatorship Operations during such period as regulated entities are under FHFA’s conservatorship; an Office of Strategic Initiatives to manage such strategic initiatives as the Director may identify; and a Division of Supervision Policy and Support to facilitate consistent supervision and examination policies across all regulated entities. The Director may also establish other Offices and positions as the Director deems necessary and appropriate to support the operations of a federal agency, such as a Chief Operating Officer, a Chief Financial Officer, an Office of Information Technology, and such other offices, departments, and positions as are necessary and appropriate or may be required by

statute.

(g) Additional information. Current information on the organization of FHFA may be obtained by mail from the Office of Congressional Affairs and Communications, 400 Seventh Street, SW., Washington, DC 20024. Such information, as well as other FHFA information, also may be obtained electronically by accessing FHFA’s Web
site located at www.FHFA.gov.

**§ 1200.3 Official logo and seal.**

This section describes and displays the logo adopted by the Director as the official symbol representing FHFA. It is displayed on correspondence, selected documents, and signage. The logo serves as the official seal to certify and
authenticate official documents of the

agency.

(a) Description. The logo is a disc consisting of three polygons each drawn in a manner resembling a silhouette of a pitched roof house and with
distinctive eaves under its roof. Each polygon is placed one in front of the other, two of which are diminished in size from the polygon behind it. Placed in the center of the smallest polygon is the acronym for the organization, ‘‘FHFA.’’ The polygons are encircled by a designation scroll having an outer and inner border of plain heavy lines and containing the words ‘‘FEDERAL

HOUSING FINANCE AGENCY’’ in capital letters with serifs, with two mullets on the extreme left and right of
the scroll.

(b) Display. FHFA’s official logo and seal appears below: **Chapter XVII—Office of Federal Housing Enterprise Oversight, Department of**  **Housing and Urban Development**

**PART 1700—[REMOVED]**

■ 3. Remove part 1700.

Dated: December 3, 2012. Edward J. DeMarco, Acting Director, Federal Housing Finance Agency.

[FR Doc. 2012–29695 Filed 12–7–12; 8:45 am]

**BILLING CODE 8070–01–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2008–1243; Directorate Identifier 2007–SW–03–AD; Amendment 39–**  **17267; AD 2012–23–11]**

**RIN 2120–AA64**

**Airworthiness Directives; Erickson Air Crane Incorporated Helicopters** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for Erickson Air-Crane Incorporated (Erickson) Model S–64F helicopters. This AD requires inspecting for cracking or working rivets in each left and right splice fitting (transition fitting), the pylon bulkhead assembly-canted (bulkhead assembly), and the pylon steel strap (strap). This AD was prompted by several reports of cracking in the transition fittings, the bulkhead assembly, and the pylon. The actions specified by this AD are intended to detect cracking in the rotary rudder boom or pylon due to fatigue, and to prevent failure from static overload and subsequent loss of control of the helicopter.

**DATES :**  This AD is effective January 14,

2013.


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The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of January 14, 2013.

**ADDRESSES :**  For service information identified in this AD, contact Erickson Air-Crane Incorporated, ATTN: Chris Erickson/Compliance Officer, 3100 Willow Springs Rd., P.O. Box 3247, Central Point, OR 97502; telephone (541) 664–5544; fax (541) 664–2312; email cerickson@ericksonaircrane.com. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

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, any incorporated-by-reference service information, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800– 647–5527) is U.S. Department of Transportation, Docket Operations Office, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

**FOR FURTHER INFORMATION CONTACT :**  Michael Kohner, Aviation Safety Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5170; email 7-avs-asw-170@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

On November 26, 2008, at 73 FR 71952, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 to include an AD that would apply to Erickson Model S–64F helicopters with a transition fitting, part number (P/N) 6420–66341–101, –102, –103, or –104; bulkhead assembly, P/N
6420–66340–041, –043, or –044; or a strap, P/N 6420–66301–119 or –127, installed. That NPRM proposed to require inspecting for cracking or working rivets in each transition fitting, the bulkhead assembly, the strap, and the attaching rotary rudder boom and pylon structure, and repairing or replacing any cracked or damaged part with an airworthy part. The NPRM also proposed to require, for any part where you could not visually determine that a crack does not exist, inspecting using a 10-power or higher magnifying glass. If you could not determine that a crack does not exist in the part after inspecting it with a 10-power or higher magnifying glass, the NPRM proposed to require performing a fluorescent particle inspection (FPI) of any part other than a strap, and performing a magnetic particle inspection (MPI) of any strap. The NPRM also proposed to require replacing any loose or working rivet. The proposed requirements were intended to detect cracking in the rotary rudder boom or pylon due to fatigue, and to prevent failure from static overload and subsequent loss of control of the helicopter.

Comments

After our NPRM (73 FR 71952, November 26, 2008) was published, we received comments from one

commenter.

Request

A commenter from Erickson AirCrane asked that we delete the bulkhead assembly, P/N 6420–66340–041, from the applicability and compliance section of the NPRM (73 FR 71952, November 26, 2008) since that P/N is not used on Erickson Model S–64F helicopters. We agree and have revised this AD accordingly.

The commenter also asked that we delete the words ‘‘other than a strap’’ from the requirement to perform an FPI on a part other than a strap if you cannot determine that a crack does not exist, and delete the entire requirement to perform an MPI of the strap if you cannot determine that a crack does not exist. The commenter states that an MPI cannot be performed on the strap when it is installed on a helicopter; instead an FPI of the strap would need to be performed with the other parts. We partially agree. We agree that an MPI cannot be performed on the strap while it is installed on the helicopter because the strap is attached to the aluminum pylon section. An MPI for the strap was initially proposed in the NPRM (73 FR 71952, November 26, 2008) because this would be the type of inspection normally used for a steel part. Instead of changing the MPI on the strap to an FPI as requested, after further review, we determined that deleting this inspection, as well as the magnifying glass inspection and certain FPIs that were proposed in the NPRM, will not impact the overall level of safety. These inspections were included in the event a visual inspection was insufficient to determine whether a crack exists. If any additional inspections are necessary to determine if a crack exists, a qualified individual performing the inspection must make this determination.

FAA’s Determination

We have reviewed the relevant information, considered the comments received, and determined that an unsafe condition exists and is likely to exist or develop on other products of the same type design and that air safety and the public interest require adopting the AD requirements as proposed with the changes described previously and minor editorial changes. We have also revised the estimated costs of complying with this AD to reflect an average labor rate of $85 per work-hour instead of $80 per work-hour. These changes are consistent with the intent of the proposals in the NPRM (73 FR 71952, November 26, 2008) and will not increase the economic burden on any operator nor increase the scope of the AD.

Related Service Information

We have reviewed Erickson Service Bulletin (SB) No. 64B20–6, Revision A, dated December 12, 2007, which describes procedures for inspecting the transition fittings, the bulkhead assembly, the strap, and the attaching rotary rudder boom and pylon structure for cracking or working rivets. We have also reviewed Erickson SB No. 64F General-3, Revision C, dated December 12, 2007, which summarizes a listing of a portion of the Model S–64F helicopter components, their part numbers, and the corresponding SBs to use when performing the structural inspections.

Costs of Compliance

We estimate that this AD will affect 7 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. It will take about 0.75 work-hour to visually inspect the transition fittings, skin panels, the bulkhead assembly, strap, and pylon exterior in the strap area; we estimate 30 of these visual inspections per year. It will take about 0.50 work-hour to visually inspect the pylon interior in the strap area; we estimate 4 of these visual inspectionsper year. It will take about 0.75 workhour to visually and fluorescent penetrant inspect the skin panels at the transition fitting; we estimate performing these inspections 1 time per year. It will take about 40 work-hours to repair a pylon structural assembly. The average labor rate is $85 per work-hour and the cost for required parts to repair a pylon structural assembly is approximately $50,000. Based on these figures, we estimate the annual cost of the inspections will be $2,146 per helicopter and $15,024 for the fleet on


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U.S. operators. The estimated cost to repair a pylon structural assembly, including the cost for replacement parts and labor, is $53,400.

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 to the extent that it justifies making a regulatory distinction; 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.

We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket.

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):

2012–23–11 Erickson Air-Crane Incorporated: Amendment 39–17267; Docket No. FAA–2008–1243; Directorate Identifier 2007–SW–03–AD.

(a) Applicability

This AD applies to Erickson Air-Crane Incorporated (Erickson) Model S–64F helicopters with a left or right splice fitting (transition fitting), part number (P/N) 6420– 66341–101, –102, –103, or –104; pylon bulkhead assembly-canted (bulkhead assembly), P/N 6420–66340–043 or –044; or a pylon steel strap (strap), P/N 6420–66301– 119 or –127, installed, certificated in any category.

(b) Unsafe Condition

This AD defines the unsafe condition as cracking in the rotary rudder boom or pylon due to fatigue, failure from static overload, and subsequent loss of control of the helicopter.

(c) Effective Date

This AD becomes effective January 14,

2013.
(d) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.

(e) Required Actions

(1) Within 20 hours time-in-service (TIS), and thereafter at intervals not to exceed 20 hours (TIS):

(i) Visually inspect each transition fitting, P/N 6420–66341–101, –102, –103, or –104, for a crack or working rivets on the inboard face of the rotary rudder boom and pylon, paying particular attention to the fastener attachment holes, as depicted in Figure 1, Detail A, of the Accomplishment Instructions in Erickson Air-Crane Incorporated Service Bulletin No. 64B20–6, Revision A, dated December 12, 2007 (SB).

(ii) Visually inspect the outboard face of each rotary rudder boom and pylon skin panel (skin panel) that attaches to the transition fittings for a crack or working rivets in the transition fitting attachment areas, paying particular attention to the fastener attachment holes, as shown in Figure 1, Detail B, of the Accomplishment Instructions in the SB.

(iii) Visually inspect the forward and aft sides of each bulkhead assembly, P/N 6420– 66340–043 or –044, for a crack. Pay particular attention to the circled areas shown in Figure 2 of the Accomplishment Instructions in the SB.

(iv) Visually inspect the upper 12 inches of each strap, P/N 6420–66301–119 or –127, for a crack or for working rivets as shown in Figure 3 of the Accomplishment Instructions in the SB.

(v) Visually inspect the pylon for a crack or working rivets on each side of the upper 12 inches of the strap, and also 6 inches above the end of the strap as shown in Figure 3 of the Accomplishment Instructions in the
SB.

(2) For any pylon with a strap installed, within 155 hours TIS, and thereafter at intervals not to exceed 155 hours TIS, remove the inspection access covers, P/N 6420–66304–109 and P/N 6420–66303–125, on the forward and aft sides of the pylon and visually inspect the left-hand cap angle (longeron), P/N 6420–66304–136, and the interior area of the pylon adjacent to the upper 12 inches of the strap, as well as 6 inches above the end of the strap, for a crack or working rivets, as shown in Figure 3 of the Accomplishment Instructions in the SB.

(3) At each transition fitting replacement, which is required at intervals not to exceed 8,300 hours TIS:

(i) With each transition fitting removed, visually inspect both sides of each skin panel for a crack in the areas to which the transition fitting attaches, paying particular attention to the fastener attachment holes, as depicted in Details A and B, Figure 1, of the Accomplishment Instructions in the SB.

(ii) Perform a fluorescent penetrant inspection of each skin panel for a crack in the areas around the fastener holes where the transition fittings attach to the rotary rudder boom and pylon.

(4) If there is a crack, before further flight, replace any cracked part with an airworthy part, or repair the cracked part if the damage is within the maximum repair damage limits.

Note to paragraph (e)(4) of this AD: The maximum repair damage limitations are stated in the applicable Component and Repair Overhaul Manual.

(5) If any loose or working rivets are found, before further flight, remove the rivets and visually inspect the fastener holes and surrounding area for a crack or any other damage. Replace any part that is cracked with an airworthy part; replace any damaged part with damage exceeding the maximum repair damage limits with an airworthy part; or repair any damaged part that is within the maximum repair damage limits. Also, replace any loose or working rivets.

(f) Special Flight Permits

Special flight permits may be issued in
accordance with 14 CFR 21.197 and 21.199 to operate the helicopter to a location where the inspection requirements of this AD can be accomplished. No special flight permits will be issued to accomplish replacements or repairs, or if a crack is suspected.

(g) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Rotorcraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Michael Kohner, Aviation Safety Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5170;
email 7-avs-asw-170@faa.gov.


### 73268 Federal Register / Vol. 77, No. 237 / Monday, December 10, 2012 / Rules and Regulations

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC.

(h) Additional Information

Erickson Air-Crane Service Bulletin No. 64F General-3, Revision C, dated December 12, 2007, which is not incorporated by reference, contains additional information about the subject of this AD. For this service information, contact Erickson Air-Crane Incorporated, ATTN: Chris Erickson/ Compliance Officer, 3100 Willow Springs Rd., P.O. Box 3247, Central Point, OR 97502; telephone (541) 664–5544; fax (541) 664– 2312; email cerickson@ericksonaircrane.com

. You may also review this service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

(i) Subject

Joint Aircraft Service Component (JASC) Code: 5302, Rotorcraft Tail Boom.

(j) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.

(i) Erickson Air-Crane Incorporated Service Bulletin No. 64B20–6, Revision A, dated December 12, 2007.

(ii) Reserved. (3) For Erickson Air-Crane Incorporated service information identified in this AD, contact Erickson Air-Crane Incorporated, ATTN: Chris Erickson/Compliance Officer, 3100 Willow Springs Rd., P.O. Box 3247, Central Point, OR 97502; telephone (541) 664–5544; fax (541) 664–2312; email
cerickson@ericksonaircrane.com

.

(4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the availability of this material at the FAA, call (817) 222–5110.

(5) You may view this service information that is incorporated by reference at the
National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: http://www.archives.gov/federal-register/cfr/ibrlocations.html

.

Issued in Fort Worth, Texas, on November

13, 2012. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 2012–28434 Filed 12–7–12; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–1117; Directorate Identifier 2012–NE–25–AD; Amendment 39–**  **17275; AD 2012–24–05]**

**RIN 2120–AA64**

**Airworthiness Directives; Rolls-Royce plc Turbofan Engines** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule; request for

comments.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-Trent 900 series turbofan engines. This AD requires inspection of the low pressure turbine (LPT) bearing housing end cover assembly in certain engines and, if necessary, its replacement. This AD was prompted by a Trent 900 engine experiencing a high intermediate pressure vibration fault, along with other fluctuating engine parameters, while in flight. We are issuing this AD to prevent fracture of the oil transfer tube, which could result in uncontained failure of the engine and damage to the airplane.

**DATES :**  This AD becomes effective December 26, 2012.

We must receive comments on this AD by January 24, 2013.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of December 26, 2012.

**ADDRESSES :**  You may send comments by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically.

• Mail: U.S. Department of Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, Room W12–140, Washington, DC

20590–0001.

• Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

• Fax: (202) 493–2251. For service information identified in this AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ; phone: 011–44–1332–242424; fax: 011–44– 1332–245418 or email from http:// www.rolls-royce.com/contact/ civil

_team.jsp, or download the publication from https:// www.aeromanager.com. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803. 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 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 the same as the Mail address provided in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Alan Strom, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7143; fax: 781–238– 7199; email: alan.strom@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive AD No. 2012– 0145, dated August 6, 2012 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

During a revenue service flight, a Trent 900 engine experienced a high Intermediate Pressure (IP/N2) vibration fault along with several other fluctuating engine parameters, including Low Pressure (LP/N1) faults. The flight crew decided to throttle back the engine to idle and performed an air turn back. The other engines continued to operate normally and an uneventful landing was
made.

The results of an initial investigation revealed that the LP system was seized. Removal of the Low Pressure Turbine (LPT) bearing housing end cover revealed that the oil transfer tube assembly had fractured because the spherical seat between the oil transfer tube and the end cover was missing (not installed).

This non-conformity caused the fracture of the oil transfer tube, leading to reduced oil flow and subsequent damage to the LP and IP bearings. Rolls-Royce has identified that other Trent 900 engines could potentially be
affected.

The in-service event engine was assembled at the factory by RR. After the in-service event, RR inspected all LPT bearing housing end cover assemblies