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

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—SERVICE INFORMATION

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—MATERIAL INCORPORATED BY REFERENCE

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 CoˆteVertu 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 


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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: 


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

(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 also 

estimate 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 


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