## 27409 Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations

having P/N 2844–19 and re-identifying the safety valves, in accordance with Paragraph 2.C., ‘‘ Part B—Modification—Replacement, ’’ of the Accomplishment Instructions of Bombardier Service Bulletin A100–21–08, dated June 18, 2009, terminates the repetitive cleanings required by paragraph (j) of this AD.

FAA AD Differences

Note 2: This AD differs from the MCAI and/or service information as follows: This AD does not require the replacement of the safety valve cabin pressure-sensing port plugs and the re-identification of the safety valves required in Part V of MCAI Canadian Airworthiness Directive CF–2010–06, dated February 24, 2010. The planned compliance times for these actions would not allow enough time to provide notice and opportunity for prior public comment on the merits of those actions. Therefore, we are considering further rulemaking to address these issues. Other FAA AD Provisions (l) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office, 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 FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to ensure 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

(m) Refer to MCAI Canadian Airworthiness Directive CF–2010–06, dated February 24, 2010; and the service information specified in Table 1 of this AD; as applicable; for related information.



### TABLE 

### 1—S ERVICE 

### I NFORMATION

Document Date

Bombardier Service Bulletin A100–21–08 ......................................................................................... ...................................... June 18, 2009. Bombardier Service Bulletin 100–25–14 .......................................................................................... ....................................... June 30, 2008. Bombardier Service Bulletin 100–25–21 .......................................................................................... ....................................... June 30, 2008. Bombardier Temporary Revision 5–2–53, dated October 1, 2009, to Section 5–10–40, ‘‘ Certification Maintenance Requirements, ’’ in Part 2 of Chapter 5 of Bombardier Challenger 300 BD–100 Time Limits/Maintenance Checks. October 1, 2009.

Material Incorporated by Reference

(n) You must use the service information contained in Table 2 of this AD to do the actions required by this AD, unless the AD specifies otherwise.



### TABLE 

### 2—M ATERIAL 

### I NCORPORATED BY 

### R EFERENCE

Document Date

Bombardier Service Bulletin A100–21–08 ......................................................................................... ...................................... June 18, 2009. Bombardier Service Bulletin 100–25–14 .......................................................................................... ....................................... June 30, 2008. Bombardier Service Bulletin 100–25–21 .......................................................................................... ....................................... June 30, 2008. Bombardier Temporary Revision 5–2–53, dated October 1, 2009, to Section 5–10–40, ‘‘ Certification Maintenance Requirements, ’’ in Part 2 of Chapter 5 of Bombardier Challenger 300 BD–100 Time Limits/Maintenance Checks. October 1, 2009.

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

(2) For service information identified in this AD, contact Bombardier, Inc., 400 Co ˆ teVertu Road West, Dorval, Que  ́ bec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; e-mail thd.crj@aero.bombardier.com; Internet http:// www.bombardier.com

.

(3) You may review copies of the 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.

(4) You may also review copies of the 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/ code

_ of

_ federal

_regulations/ ibr

_locations.html. Issued in Renton, Washington, on May 3,

2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2010–11074 Filed 5–14–10; 8:45 am]

**BILLING CODE 4910–13–P** 

### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0060; Directorate Identifier 2010–SW–06–AD; Amendment 39–**  **16282; AD 2010–10–03]**

**RIN 2120–AA64**



### Airworthiness Directives; Sikorsky **Aircraft Corporation (Sikorsky) Model S–92A Helicopters** 

**AGENCY** 

### : Federal Aviation Administration, DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : This amendment adopts a new airworthiness directive (AD) for the Sikorsky Model S–92A helicopters. The


## 27410 Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations

AD requires replacing the main gearbox(MGB) filter bowl assembly with a twopiece MGB filter bowl assembly and replacing the existing mounting studs. The AD also requires inspecting the MGB lube system filters, the housing, the housing threads, and the lockring counterbore and repairing or replacing them as necessary. This amendment is prompted by tests indicating that an existing MGB filter bowl assembly can fail under certain loading conditions including those associated with a damaged MGB filter or mounting stud resulting from high frequency maintenance tasks. Testing of the improved MGB filter bowl assembly demonstrates a significant increase in strength and durability over the existing filter bowl. The actions specified by this AD are intended to prevent failure of the MGB filter bowl assembly due to failure of the mounting studs or the filter bowl, loss of oil from the MGB, failure of the MGB, and subsequent loss of control of the helicopter.

**DATES** 

### : Effective June 21, 2010.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of June 21,
2010.

**ADDRESSES** 

### : You may get the service information identified in this AD from Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical Support, mailstop s581a, 6900 Main Street, Stratford, CT, telephone (203) 383–4866, e-mail address tsslibrary@sikorsky.com, or at http:// www.sikorsky.com

.

Examining the Docket: You may examine the docket that contains this AD, any comments, and other information on the Internet at http:// www.regulations.gov or at the Docket Operations office, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC.

**FOR FURTHER INFORMATION CONTACT** 

### : Kirk Gustafson, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine and Propeller Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803, telephone (781) 238–7190, fax (781) 238–7170.

**SUPPLEMENTARY INFORMATION** 

### : A proposal to amend 14 CFR part 39 to include an AD for the specified model helicopters was published in the Federal Register on January 27, 2010 (75 FR 4308). That action proposed to require replacing the MGB filter bowl assembly with a two-piece MGB filter bowl assembly and replacing the existing mounting studs. That action also proposed inspecting the MGB lube system filters, the housing, the housing threads, and the lockring counterbore and repairing and replacing them as
necessary.

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposal or the FAA’s determination of the cost to the public. The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

The FAA estimates that this AD will affect 22 helicopters of U.S. registry. The required actions will take about 6 hours to inspect the existing filter bowl assembly and replace the MGB lube system filters, the mounting studs, and to install an improved filter bowl assembly at an average labor rate of $85 per work hour. Required parts will cost about $3,257 per helicopter. Based on these figures, the total cost impact of the AD on U.S. operators is $82,214. Regulatory Findings

We have 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 that the 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 an economic evaluation of the estimated costs to comply with this AD. See the AD docket to examine the economic evaluation. 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. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment

■ 

### Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive to read as follows:
2010–10–03 Sikorsky Aircraft Corporation: Amendment 39–16282. Docket No. FAA–2010–0060; Directorate Identifier 2010–SW–06–AD. Applicability: Model S–92A helicopters, with main gearbox (MGB) filter bowl assembly, part number (P/N) 92351–15802– 101, installed, certificated in any category.

Compliance: Required as indicated, unless done previously.

To prevent failure of the MGB filter bowl assembly due to failure of the mounting studs or the filter bowl, loss of oil from the MGB, failure of the MGB, and subsequent loss of control of the helicopter, do the following:

(a) Within 60 days: (1) Remove the MGB filter bowl assembly by following the Accomplishment Instructions, paragraphs 3.A. (1) through 3.A.(5), of Sikorsky Alert Service Bulletin No. 92–63–022A, dated December 18, 2009 (ASB).

(2) Remove the primary filter element, P/ N 70351–38801–102, from the MGB lube system filter and visually inspect it for damage as depicted in Figures 1, 2, and 3 of the ASB. If the primary filter element has

‘‘ wavy ’’ pleats, internal buckling, or indented dimples, before further flight, replace it with an airworthy filter element.

(3) Visually inspect the secondary filter element, P/N 70351–38801–103, for damage as depicted in Figures 4 and 5 of the ASB. If the secondary filter element has ‘‘ wavy ’’ pleats or an elongated cup, before further flight, replace it with an airworthy filter element.

(4) Replace the MGB lube system filter assembly mounting studs:


## 27411 Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations

(i) Remove the studs by following the Accomplishment Instructions, paragraphs 3.B.(1) through 3.B.(4) of the ASB. Visually inspect the tapped holes for any damage to the threads. Serrations on the entire counter bore (360 degrees) are acceptable. Serrations in the housing must be intact, and mating serrations on the lock ring must line up with serrations on the housing. Visually inspect the housing to determine that the housing threads are free from damage and corrosion. Visually inspect housing lockring counterbore to determine if the housing is airworthy.

(ii) If you find damage or corrosion to the housing threads, the housing, or the lockring counterbore, stop work and contact Kirk Gustafson, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine and Propeller Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803, telephone (781) 238–7190, fax (781) 238–
7170.

(iii) If you do not find damage to the housing threads, the housing, or the lockring counterbore that requires repair, replace the mounting studs by following the Accomplishment Instructions, paragraphs 3.B.(7) through 3.B.(15) of the ASB.

(5) Install an airworthy, two-piece MGB filter bowl assembly modification kit, P/N 92070–35005–011, as depicted in Figures 8 and 9 of the ASB and by following the Accomplishment Instructions, paragraphs 3.C.(1) through 3.C.(20), of the ASB.

(b) 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, Boston Aircraft Certification Office, Attn: Kirk Gustafson, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine and Propeller Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803, telephone (781) 238–7190, fax (781) 238–7170, for information about previously approved alternative methods of compliance.

(c) The Joint Aircraft System/Component (JASC) Code is 6320: Main Rotor Gearbox.

(d) Inspecting and replacing the MGB filter bowl assembly shall be done by following the specified portions of Sikorsky Alert Service Bulletin No. 92–63–022A, dated December 18, 2009. 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 Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical Support, mailstop s581a, 6900 Main Street, Stratford, CT, telephone (203) 383–4866, e-mail address tsslibrary@sikorsky.com , or at http:// www.sikorsky.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. (e) This amendment becomes effective on June 21, 2010. Issued in Fort Worth, Texas, on April 27,
2010. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010–11069 Filed 5–14–10; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2005–21242; Directorate Identifier 2005–NE–09–AD; Amendment 39–**  **16288; AD 2010–10–09]**

**RIN 2120–AA64**



### Airworthiness Directives; Turbomeca **Arriel 1B, 1D, 1D1, and 1S1 Turboshaft Engines** 

**AGENCY** 

### : Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION** 

### : Final rule.

**SUMMARY** 

### : The FAA is superseding an existing airworthiness directive (AD) for certain Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft engines. That AD requires initial and repetitive relative position checks of the gas generator 2nd stage turbine blades on Turbomeca Arriel 1B (that incorporate Turbomeca Modification (mod) TU 148), Arriel 1D, 1D1, and 1S1 turboshaft engines that do not incorporate mod TU 347. That AD also requires initial and repetitive replacements of 2nd stage turbines on Arriel 1B, 1D, and 1D1 engines. This AD requires lowering the initial and repetitive thresholds for replacement of 2nd stage turbines on Arriel 1B, 1D, and 1D1 engines. This AD results from reports of new cases of failures of 2nd stage turbine blades since we issued AD 2008–07–01. We are issuing this AD to prevent the failure of 2nd stage turbine blades, which could result in an uncommanded in-flight engine shutdown, and a subsequent forced autorotation landing or accident.

**DATES** 

### : This AD becomes effective June 21, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of June 21, 2010.

**ADDRESSES** 

### : You can get the service information identified in this AD from Turbomeca, 40220 Tarnos, France; telephone (33) 05 59 74 40 00, fax (33)
05 59 74 45 15.

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** 

### : Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: kevin.dickert@faa.gov; phone: (781) 238–7117, fax: (781) 238–
7199.

**SUPPLEMENTARY INFORMATION** 

### : The FAA proposed to amend 14 CFR part 39 by superseding AD 2008–07–01, Amendment 39–15442 (73 FR 15866, March 26, 2008), with a proposed AD. The proposed AD applies to Turbomeca Arriel 1B (that incorporate mod TU 148), 1D, 1D1, and 1S1 turboshaft engines that do not incorporate mod TU 347. We published the proposed AD in the Federal Register on March 10, 2010 (75 FR 11072). That action proposed to require lowering the repetitive threshold for relative position checks on Arriel 1B engines. That action also proposed to require lowering the initial and repetitive thresholds for replacement of 2nd stage turbines on Arriel 1B, 1D, and 1D1 engines. 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.

Comments

We provided the public the opportunity to participate in the development of this AD. We received no comments on the proposal or on the determination of the cost to the public.

Conclusion

We have carefully reviewed the available data 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 587 Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft engines installed on products of U.S. registry. We alsoestimate that it will take about 2 workhours per engine to perform one inspection, and about 40 work-hours per engine to replace the gas turbine discs