## 50877 Federal Register / Vol. 75, No. 159 / Wednesday, August 18, 2010 / Rules and Regulations

lever for cracking in accordance with the Accomplishment Instructions, paragraph 2.B.1.a., in Eurocopter Emergency Alert Service Bulletin (EASB) No. 05.00.62, Revision 1, dated April 23, 2010, for Model AS350 helicopters or EASB No. 05.00.57, Revision 1, dated April 23, 2010, for Model AS355 helicopters.

(b) If a crack is found, before further flight, remove and replace the cracked TGB control lever with an airworthy TGB control lever in accordance with the Accomplishment Instructions, paragraph 2.B.2., in the EASB appropriate for your model helicopter.

(c) Either of the following options constitutes a terminating action for the inspection requirements of this AD:

(1) Replace a TGB control lever with an airworthy TGB control lever that is marked with an ‘‘X ’’ near the P/N; or

(2) Strip the rework area ‘‘ B ’’ as shown inFigure 4 of each EASB and perform a dyepenetrant inspection on that area for a crack. If no crack is found, rework and mark the TGB control lever in accordance with paragraph 2.B.3.b. of the EASB appropriate for your model helicopter, except you are not required to contact Eurocopter France. If a crack is found, before further flight, remove and replace the cracked TGB control lever with an airworthy TGB control lever in accordance with the Accomplishment Instructions, paragraph 2.B.2., in the EASB.

Note 1: One Eurocopter EASB contains four different service bulletin numbers but only portions of 2 EASBs are being incorporated.

Note 2: Installing a reinforced TGB control lever, P/N 350A33–1524–00 or P/N 350A33– 1526–00, that does not need to be marked with an ‘‘X ’’ constitutes compliance with paragraph (c) of this AD.

(d) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Safety Management Group, FAA, ATTN: J.R. Holton, Jr., Aviation Safety Engineer, ASW– 112, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–4964, fax (817) 222–5961, for information about previously approved alternative methods of compliance.

(e) 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 paragraph (a) of this AD can be accomplished.

(f) The Joint Aircraft System/Component (JASC) Code is 6720: Tail Rotor Control System.

(g) Inspecting, replacing the control lever or removing, reworking, and replacing the control lever shall be done in accordance with the specified portions of Eurocopter Emergency Alert Service Bulletin (EASB) No. 05.00.62, Revision 1, dated April 23, 2010, for Model AS350 helicopters or EASB No. 05.00.57, Revision 1, dated April 23, 2010, for Model AS355 helicopters. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005, telephone (800) 232–0323, fax (972) 641–3710, or at http://www.Eurocopter.com . Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas, or 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/ code

_ of

_ federal

_regulations/ ibr

_locations.html. (h) This amendment becomes effective on September 2, 2010, to all persons except those persons to whom it was made immediately effective by Emergency AD 2010–11–51, issued May 11, 2010, which contained the requirements of this amendment.

Note 3: The subject of this AD is addressed in European Aviation Safety Agency (France) Emergency AD No. 2010–0082–E, dated April 27, 2010.

Issued in Fort Worth, Texas, on August 2,
2010. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010–19818 Filed 8–17–10; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0521; Directorate Identifier 2009–NE–21–AD; Amendment 39–**  **16405; AD 2010–17–13]**

**RIN 2120–AA64**



### Airworthiness Directives; Rolls-Royce **plc RB211–524C2 Series Turbofan Engines** 

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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:

A number of LPT casings have been found cracked during engine shop visit. Cracking of the LPT casing reduces the capability of the casing to contain debris in the event of an LPT stage 1 blade failure. Therefore, blade failure in an engine featuring a cracked LPT casing may result in release of uncontained high energy debris.

For the reason described above, this AD requires repetitive inspections and corrective actions, depending on findings. 

### We are issuing this AD to detect cracks in the low-pressure turbine (LPT) casings, which could result in the release of uncontained high-energy debris in the event of a stage 1 blade failure. Uncontained high-energy debris could result in damage to the airplane.

**DATES** 

### : This AD becomes effective September 22, 2010.

**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** 

### : Alan Strom, Aerospace Engineer, Engine Certification Office, FAA, Engine and 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** 

### :

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 May 19, 2010 (75 FR 27973). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

A number of LPT casings have been found cracked during engine shop visit. Cracking of the LPT casing reduces the capability of the casing to contain debris in the event of an LPT stage 1 blade failure. Therefore, blade failure in an engine featuring a cracked LPT casing may result in release of uncontained high energy debris.



### Comments

We gave the public the opportunity to participate in developing this AD. We considered the comment received. The commenter supports the NPRM.

Conclusion

We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance

Based on the service information, we estimate that this AD will affect about 10 products of U.S. registry. We alsoestimate that it will take about 10 workhours per product to comply with this AD. The average labor rate is $85 per work-hour. Required parts will cost about $25,000 per product. Based on these figures, we estimate the cost of the AD on U.S. operators to be $258,500.


## 50878 Federal Register / Vol. 75, No. 159 / Wednesday, August 18, 2010 / Rules and Regulations

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 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 provided in the

**ADDRESSES** 

### section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, 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 AD: 2010–17–13 Rolls-Royce plc (Formerly Rolls-Royce Limited): Amendment 39– 16405. Docket No. FAA–2010–0521; Directorate Identifier 2009–NE–21–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective September 22, 2010.

Affected ADs

(b) None. Applicability

(c) This AD applies to Rolls-Royce plc (RR) model RB211–524C2–19 and RB211–524C2– B–19 turbofan engines. These engines are installed on, but not limited to, Boeing 747 series airplanes.

Reason

(d) A number of LPT casings have been found cracked during engine shop visit. Cracking of the LPT casing reduces the capability of the casing to contain debris in the event of an LPT stage 1 blade failure. Therefore, blade failure in an engine with a cracked LPT casing may result in release of uncontained high-energy debris.

We are issuing this AD to detect cracks in the low-pressure turbine (LPT) casings, which could result in the release of uncontained high-energy debris in the eventof a stage 1 blade failure. Uncontained highenergy debris could result in damage to the airplane.
Actions and Compliance

(e) Unless already done, do the following actions: Initial Inspection Requirements

(1) Perform a fluorescent penetrant inspection (FPI) before the life of the LPT casing has reached 4,500 cycles-since-new (CSN) or within 4,500 cycles-since-last inspection (CSLI) or within 500 cycles after the effective date of this AD, whichever occurs later. You can find guidance on performing the FPI in RR Alert Service Bulletin (ASB) RB.211–72–AG076, dated November 13, 2008.
Repetitive Inspection Requirements

(2) Thereafter, perform an FPI at intervals not exceeding 4,500 CSLI. You can find guidance on performing the FPI in RollsRoyce plc ASB RB.211–72–AG076, dated November 13, 2008.

Remove Parts With Cracks

(3) Remove cracked LPT casings, found using paragraphs (e)(1) or (e)(2) of this AD, from service before further flight.
Alternative Methods of Compliance (AMOCs)

(f) The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.

Related Information

(g) Refer to MCAI EASA AD 2009–0083, dated April 16, 2009, and Rolls-Royce plc ASB No. RB.211–72–AG076, dated November 13, 2008, for related information. Contact Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom; telephone 011 44 1332 242424; fax 011 44 1332 249936, for a copy of this service information.

(h) Contact Alan Strom, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: alan.strom@faa.gov; telephone (781) 238–7143; fax (781) 238–7199, for more information about this AD.
Material Incorporated by Reference

(i) None. Issued in Burlington, Massachusetts, on August 6, 2010. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2010–20353 Filed 8–17–10; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0433; Directorate Identifier 2009–NM–117–AD; Amendment**  **39–16388; AD 2010–16–11]**

**RIN 2120–AA64**



### Airworthiness Directives; McDonnell **Douglas Corporation Model MD–90–30 Airplanes** 

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for certain Model MD–90–30 airplanes. This AD requires inspecting for corrosion of the retract cylinder support fitting for the main landing gear (MLG) and the mating bore for the support fitting in the MLG trunnion fitting, performing corrective actions if necessary, and replacing cadmium-plated retract cylinder