### 69611 Federal Register / Vol. 75, No. 219 / Monday, November 15, 2010 / Proposed Rules

Compliance

(f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

Actions

(g) Within 30 days after the effective date of this AD, revise the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness (ICA) by incorporating Task Number C36–20–133–03 specified in Bombardier Temporary Revision (TR) 2A–50, dated November 17, 2009; and Task Number C30–10–133–01 specified in Bombardier TR 2A–49, dated November 17, 2009; into Appendix A, ‘‘Certification Maintenance Requirements, ’’ of Part 2 of the Bombardier CL–600–2B19 Maintenance Requirements Manual (MRM). For these tasks, the initial compliance time starts at the applicable time specified in paragraphs (g)(1) and (g)(2) of this AD. Thereafter, except as provided by paragraph (h) of this AD, no alternative functional check of the thermal switch or detailed visual inspection of the piccolo tube may be approved.

Note 1: The actions required by paragraph (g) of this AD may be done by inserting a copy of Bombardier TR 2A–49 and TR 2A– 50, both dated November 17, 2009, into the Appendix A of Part 2 of the Bombardier CL– 600–2B19 MRM. When these TRs have been included in Appendix A of Part 2 of the general revisions of the MRM, the general revisions may be inserted in the MRM, provided that the relevant information in the general revision is identical to that in Bombardier TR 2A–49 and TR 2A–50, both dated November 17, 2009.

(1) For Task Number C36–20–133–03, the initial compliance time is before the accumulation of 15,000 total flight hours or within 7 months after the effective date of this AD, whichever occurs later.

(2) For Task Number C30–10–133–01, the initial compliance time is before the accumulation of 15,000 total flight hours on the piccolo tube or within 7 months after the effective date of this AD, whichever occurs later.

FAA AD Differences

Note 2: This AD differs from the MCAI and/or service information as follows: No differences.

Other FAA AD Provisions

(h) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York, 11590; telephone 516–228–7300; fax 516– 794–5531. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards 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 or other source, use these actions if they are FAA-approved.Corrective actions are considered FAAapproved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

(3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq. ), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056.

Related Information

(i) Refer to MCAI Canadian Airworthiness Directive CF–2010–12, dated May 26, 2010; and Bombardier TR 2A–49, dated November 17, 2009, and Bombardier TR 2A–50, dated November 17, 2009 to Appendix A,

‘‘Certification Maintenance Requirements, ’’ of Part 2 of the Bombardier CL–600–2B19 MRM; for related information.

Issued in Renton, Washington, on November 3, 2010. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–28604 Filed 11–12–10; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0960; Directorate Identifier 98–ANE–09–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Rolls-Royce plc RB211–Trent 768, 772, and 772B**  **Turbofan Engines**

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

**ACTION :**  Notice of proposed rulemaking (NPRM); rescission.

**SUMMARY :**  We propose to rescind an airworthiness directive (AD) for the products listed above. The existing AD, AD 98–09–27, resulted from aircraft certification testing which revealed that stresses on the thrust reverser hinge were higher than had been anticipated during engine certification, and the United Kingdom Civil Aviation Authority, issuing AD 008–03–97.

Since we issued AD 98–09–27, we discovered that its requirements were duplicated in airplane-level AD 2001– 09–14, issued by the FAA Transport Airplane Directorate. This proposal to rescind the engine-level AD allows the public the opportunity to comment on the FAA’s determination of the duplication of requirements in another AD, before we rescind the engine-level AD.

**DATES :**  We must receive comments on this proposed AD by December 30,
2010.

**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: Docket Management Facility, 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. 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 proposed 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; e-mail: alan.strom@faa.gov; telephone (781) 238–7143; fax (781) 238–7199.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD rescission. Send your comments to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2010–0960; Directorate Identifier 98–ANE–09–AD ’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD rescission. We will consider all comments received by the closing date and may amend this proposed AD rescission based on those
comments.


### 69612 Federal Register / Vol. 75, No. 219 / Monday, November 15, 2010 / Proposed Rules

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 with FAA personnel concerning this proposed AD rescission. Using the search function of the Web site, anyone can find and read the comments in any of our dockets, including, if provided, the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78).

Discussion

On April 23, 1998, the FAA Engine & Propeller Directorate issued engine AD 98–09–27 (63 FR 24911, May 6, 1998). On April 30, 2001, the FAA Transport Airplane Directorate issued airplane AD 2001–09–14 (66 FR 23838, May 10, 2001). Those ADs both require the same initial and repetitive visual inspections of Rolls-Royce plc RB211–Trent 768 and 772 series turbofan engine thrust reverser hinge lugs and attachment ribs for cracks, and, if necessary, removal from service and replacement with serviceable parts.

Since we issued engine AD 98–09–27 and airplane AD 2001–09–14, we determined that duplicate ADs to address the same unsafe condition were
unnecessary. FAA’s Determination and Requirements of This Proposed AD Rescission

We are proposing this AD rescission of AD 98–09–27 because we evaluated all information and determined that two FAA ADs with the same requirements are not necessary. 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 rescission would not have federalism implications under Executive Order 13132. This proposed AD rescission 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 rescission of a 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); 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 proposed AD rescission and placed it in the AD docket. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, 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. The FAA amends § 39.13 by rescinding airworthiness directive (AD) 98–09–27, Amendment 39–10508 (63 FR 24911, May 6, 1998): Rolls-Royce plc: Docket No. FAA–2010– 0960; Directorate Identifier 98–ANE–09– AD.

Comments Due Date

(a) We must receive comments by December 30, 2010.

Affected ADs

(b) This AD rescinds AD 98–09–27.
Applicability

(c) This AD applies to Rolls-Royce plc RB211–Trent 768, 772, and 772B turbofan engines. These engines are installed on, but not limited to, Airbus A330–341 and A330– 342 series airplanes. Issued in Burlington, Massachusetts, on November 5, 2010. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2010–28583 Filed 11–12–10; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–1111; Directorate Identifier 2010–NM–129–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Model 747–200B, –300, –400,**  **–400D, and –400F Series Airplanes Powered by Pratt and Whitney 4000 or**  **General Electric CF6–80C2 Series 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 Model 747–200B, –300, –400, –400D, and –400F series airplanes. This proposed AD would require an inspection to determine the part number of the door and to determine if the correct mid-pivot access door is installed, and the installation of a marker on the mid-pivot access door, and if necessary, repetitive ultrasonicinspections for cracking of the midpivot bolt assembly and eventual replacement of the mid-pivot bolt assembly. This proposed AD results from a report that the left and right spring beam mid-pivot bolt assembly access doors for the No. 1 strut were inadvertently installed in the incorrect position during strut modification. We are proposing this AD to detect and correct incorrectly installed mid-pivot bolt assemblies on the spring beam on the outboard struts. Incorrectly installed bolt assemblies could lead to fatigue cracking and consequent fracturing of the mid-pivot bolt assembly, which could lead to loss of the spring beam load path and the possible separation of a strut and engine from the airplane during flight.

**DATES :**  We must receive comments on this proposed AD by December 30,
2010.

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