### 74668 Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Proposed Rules

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 FAA-approved 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 (o) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2010–0070, dated April 14, 2010; and the service information specified in Table 1 of this AD; as applicable; for related information.



### TABLE 

### 1—S ERVICE 

### I NFORMATION

Document Revision Date

Airbus All Operators Telex A300–25A6215 .................................................................. 02 ................................................. March 2, 2009. Airbus All Operators Telex A310–25A2203 .................................................................. 02 ................................................. March 2, 2009. Airbus Mandatory Service Bulletin A300–25–6217 ....................................................... Original ........................................ August 31, 2009. Airbus Mandatory Service Bulletin A310–25–2205 ....................................................... Original ........................................ August 31, 2009. EADS SOGERMA Alert Service Bulletin A2510112–25–764 ....................................... 1 ................................................... February 17, 2009. EADS SOGERMA Inspection Service Bulletin A2510112–25–807 .............................. Original ........................................ February 20, 2009.

Issued in Renton, Washington, on November 18, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–30135 Filed 11–30–10; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–1156; Directorate Identifier 2010–NM–128–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Model 777–200, –200LR,**  **–300, and –300ER Series Airplanes**

**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 777–200, –200LR, –300, and –300ER series airplanes. This proposed AD would require repetitive detailed inspections for disbonding and tearing and measurements for wear of the internal diameter (ID) of the Karon-lined bushings of the bulkhead support jackscrew fitting and of the jackscrew fitting of the horizontal stabilizer; repetitive installations of the horizontal stabilizer trim actuator (HSTA); and if necessary, replacement of the bushings with new bushings and all applicable related investigative and corrective actions. This proposed AD results from a report indicating that a Karon-lined bushing with the liner broken into five pieces was found during a scheduled inspection of the HSTA components; the broken liner had worn and disbonded from the bushing. We are proposing this AD to detect and correct discrepancies of the HSTA attachment locations, which could result in reduced structural integrity of the horizontal stabilizer and consequent loss of controllability of the airplane.

**DATES :**  We must receive comments on this proposed AD by January 18, 2011.

**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 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1, fax 206–766–5680; e-mail me.boecom@boeing.com ; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. 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; 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 regulatory evaluation, any comments received, and other information. The street address for the Docket 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 :**  Duong Tran, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6452; fax (425) 917–6590.

**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–2010–1156; Directorate Identifier 2010–NM–128–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 because of 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.


### 74669 Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Proposed Rules

Discussion

We received a report indicating that a Karon-lined bushing with the liner broken into five pieces was found during a scheduled inspection of the horizontal stabilizer trim actuator (HSTA) components; the broken liner had worn and disbonded from the bushing. The broken liner was found on a 777–200 airplane that had accumulated 35,145 total flight hours and 5,335 total flight cycles. Analysis by the manufacturer revealed that the broken liner was one of 149 bushings on which an early manufacturing process was used; that process has since been improved. Further investigation and analysis by the manufacturer shows that Karon-lined bushings in the HSTA and HSTA attachment locations on the airplane structure using both the early and the improved process are susceptible to wear in service. The analysis also shows that the wear may cause excessive joint clearance which could lead to fatigue cracking of the pins. This condition, if not corrected, could result in reduced structural integrity of the horizontal stabilizer and consequent loss of controllability of the airplane.

Relevant Service Information

We have reviewed Boeing Alert Service Bulletin 777–55A0017, dated May 20, 2010, which describes procedures for:

• Repetitive detailed inspections for disbonding and tearing and measurements for wear of the internal diameter (ID) of the Karon-lined bushings of the bulkhead support jackscrew fitting; and replacement of the bushings with new bushings if necessary: The replacement includes related investigative and corrective actions, if necessary. The related investigative actions include a surface high-frequency eddy current inspection for cracking of the inner surface of the hole, and measurement of the ID, of the intermediate sleeve. The corrective action for cracking of the intermediate sleeve or measurements outside the ID specified in the service bulletin is replacement of the intermediate sleeve, including related investigative and corrective actions if necessary. The related investigative actions include a surface high-frequency eddy current inspection for cracking of the inner surface of the hole, and measurement of the ID of the hole of the bulkhead support jackscrew fitting. The corrective action for cracking of the bulkhead support jackscrew fitting or measurements outside the ID specified in the service bulletin is contacting Boeing.

• Repetitive detailed inspections for disbonding and tearing and measurements for wear of the internal diameter (ID) of the Karon-lined bushings of the jackscrew fitting of the horizontal stabilizer; and replacement of the bushings with new bushings if
necessary.

• Repetitively installing either a known serviceable or overhauled HSTA. FAA’s Determination and Requirements of This Proposed AD

We are proposing this AD because we evaluated all relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Difference Between the Proposed AD and Service Information. ’’ Difference Between the Proposed AD and Service Information

The service bulletin specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways:

• Using a method that we approve; or

• Using data that meet the certification basis of the airplane, and that have been approved by an Authorized Representative for the Boeing Commercial Airplanes Organization Designation Authorization whom we have authorized to make those findings. Costs of Compliance

We estimate that this proposed AD would affect 145 airplanes of U.S. registry. We also estimate that it would take about 7 work-hours per product to comply with the detailed inspection, measurement, and installation in this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD to the U.S. operators to be $86,275, or $595 per product. 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), 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.

You can find our regulatory evaluation and the estimated costs of compliance in the AD Docket. 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. The FAA amends § 39.13 by adding the following new AD:
The Boeing Company: Docket No. FAA– 2010–1156; Directorate Identifier 2010– NM–128–AD.


### 74670 Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Proposed Rules

Comments Due Date

(a) We must receive comments by January 18, 2011.

Affected ADs

(b) None.
Applicability

(c) This AD applies to The Boeing Company Model 777–200, –200LR, –300, and –300ER series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 777–55A0017, dated May 20, 2010. Subject

(d) Air Transport Association (ATA) of America Code 55: Stabilizers.

Unsafe Condition

(e) This AD results from a report indicating that a Karon-lined bushing with the liner broken into five pieces was found during a scheduled inspection of the horizontal stabilizer trim actuator (HSTA) components; the broken liner had worn and disbonded from the bushing. The Federal Aviation Administration is issuing this AD to detect and correct discrepancies of the HSTA attachment locations, which could result in reduced structural integrity of the horizontal stabilizer and consequent loss of controllability of the airplane.
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.
Inspection/Related Investigative and Corrective Actions

(g) Before the accumulation of 32,000 total flight cycles, or within 24 months after the effective date of this AD, whichever occurs later: Do a detailed inspection for disbonding and tearing, and a measurement for wear of the internal diameter (ID) of the Karon-lined bushings of the bulkhead support jackscrew fitting and of the jackscrew fitting of the horizontal stabilizer; replace bushings with new bushings, as applicable; do all applicable related investigative and corrective actions; and install either a known serviceable or overhauled HSTA. Do the actions in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777–55A0017, dated May 20, 2010, except as provided by paragraph (h) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the actions required by this paragraph thereafter at intervals not to exceed 16,000 flight cycles.
Exceptions to Corrective Actions

(h) If, during any inspection or measurement required by this AD, any damage is found, or the inner diameter is greater than the allowable hole diameter, and Part 1, Step 3.B.2.a.(1)(a)1)a) of the Accomplishment Instructions of Boeing Alert Service Bulletin 777–55A0017, dated May 20, 2010, specifies to contact Boeing for appropriate action: Before further flight, do the repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD.
Alternative Methods of Compliance (AMOCs)

(i)(1) The Manager, Seattle Aircraft Certification Office (ACO), 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: Duong Tran, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6452; fax (425) 917–6590. Or information may be e-mailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.

(2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. 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.

(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and the approval must specifically refer to this AD.

Issued in Renton, Washington, on November 15, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–30138 Filed 11–30–10; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–1161; Directorate Identifier 2010–NM–152–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Empresa Brasileira de Aeronautica S.A.**  **(EMBRAER) Model ERJ 170 and ERJ 190 Airplanes** 

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

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

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed 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:

It has been found occurrence of screw unitsmanufactured with metallographic nonconformity that may increase their susceptibility to brittle fracture. The screw failure may result in loss of the related balance washer causing a possible ram air turbine (RAT) imbalance event, which may result in RAT structural failure, which associated with an electrical emergency situation, could result in loss of power to airplane flight controls hydraulic back-up system.
* * * * * Loss of power to the hydraulic back-up system for airplane flight controls could reduce the ability of the flightcrew to maintain the safe flight and landing of the airplane. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.

**DATES :**  We must receive comments on this proposed AD by January 18, 2011.

**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 W12–40, 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 Empresa Brasileira de Aeronautica S.A. (EMBRAER), Technical Publications Section (PC 060), Av. Brigadeiro Faria Lima, 2170–Putim–12227–901 Sa  ̃ o Jose dos Campos–SP–BRASIL; telephone: +55 12 3927–5852 or +55 12 3309–0732; fax: +55 12 3927–7546; e-mail: distrib@embraer.com.br; Internet: http:// www.flyembraer.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. 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; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday,