Federal Register / Vol. 74, No. 123 / Monday, June 29, 2009 / Rules and Regulations 30917 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(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 June 16, 

2009. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–14676 Filed 6–26–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22039; Directorate 

Identifier 2005–NE–33–AD; Amendment 39– 

15950; AD 2009–14–01] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Arrius 2F 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 

Turbomeca S.A. Arrius 2F turboshaft 

engines that have not incorporated 

Turbomeca Modification Tf75. That AD 

currently requires replacing the O-ring 

on the check valve piston in the 

lubrication unit at repetitive intervals. 

This AD requires the same repetitive 

replacements and would require 

incorporating Modification Tf75 as 

terminating action to the repetitive Oring replacements. Modification Tf75 

replaces the check valve piston with a 

piston design not requiring an O-ring. 

This AD results from the European 

Aviation Safety Agency (EASA) and 

Turbomeca S.A. mandating the 

incorporation of Modification Tf75. We 

are issuing this AD to prevent an 

uncommanded in-flight shutdown of the 

engine, which could result in a forced 

autorotation landing and damage to the 

helicopter. 

DATES: This AD becomes effective 

August 3, 2009. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of August 3, 2009. 

ADDRESSES: You can get the service 

information identified in this AD from 

Turbomeca S.A., 40220 Tarnos, France; 

e-mail: noria-dallas@turbomeca.com; 

telephone 33 05 59 74 40 00, fax 33 05 

59 74 45 15, or go to: http:// 

www.turbomeca-support.com. 

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: 

James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: james.lawrence@faa.gov; 

telephone (781) 238–7176; fax (781) 

238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 by 

superseding AD 2005–17–17R1, 

Amendment 39–14940 (72 FR 6925, 

February 14, 2007), with a proposed AD. 

The proposed AD applies to Turbomeca 

S.A. Arrius 2F turboshaft engines that 

have not incorporated Turbomeca 

Modification Tf75. We published the 

proposed AD in the Federal Register on 

January 22, 2009 (74 FR 3978). That 

action proposed to require replacing the 

O-ring on the check valve piston in the 

lubrication unit at repetitive intervals 

and to require incorporating 

Modification Tf75 as terminating action 

to the repetitive O-ring replacements. 

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 (telephone 

(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. 

Change to the Mandatory Terminating 

Action Compliance Time 

Since we issued the proposed AD, we 

realized that there is no direct 

relationship between the mandatory 

terminating action compliance date in 

the proposed AD and the usage rate of 

the affected helicopters. We changed the 

AD to require the terminating action be 

done within 150 flight hours after the 

effective date of this AD. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD with the change 

described previously. We have 

determined that this change will neither 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Costs of Compliance 

We estimate that this AD will affect 

94 Arrius 2F turboshaft engines 

installed on helicopters of U.S. registry. 

We also estimate that it will take about 

one work-hour per engine to perform an 

O-ring replacement, and about one 

work-hour to incorporate Modification 

Tf75. The average labor rate is $80 per 

work-hour. Required parts will cost 

about $16 per engine for O-ring 

replacement, and about $20 per engine 

for incorporating Modification Tf75. 

Based on these figures, we estimate the 

total cost of the AD to U.S. operators to 

be $18,424. 

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 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. 


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30918 Federal Register / Vol. 74, No. 123 / Monday, June 29, 2009 / Rules and Regulations 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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 summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

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 

removing Amendment 39–14940 (72 FR 

6925, February 14, 2007), and by adding 

a new airworthiness directive, 

Amendment 39–15950, to read as 

follows: 

2009–14–01 Turbomeca S.A: Amendment 

39–15950. Docket No. FAA–2005–22039; 

Directorate Identifier 2005–NE–33–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 3, 2009. 

Affected ADs 

(b) This AD supersedes AD 2005–17–17R1, 

Amendment 39–14940. 

Applicability 

(c) This AD applies to Turbomeca S.A. 

Arrius 2F turboshaft engines that have not 

incorporated modification Tf75. These 

engines are installed on, but not limited to, 

Eurocopter EC120B helicopters. 

Unsafe Condition 

(d) This AD results from the European 

Aviation Safety Agency (EASA) and 

Turbomeca S.A. mandating the incorporation 

of Modification Tf75. The actions specified 

in this AD are intended to prevent an 

uncommanded in-flight shutdown of the 

engine, which could result in a forced 

autorotation landing and damage to the 

helicopter. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

O-ring Replacement 

(f) Replace the O-ring on the check valve 

piston in the lubrication unit at the intervals 

specified in Table 1 of this AD. Use the 

Instructions to be Incorporated paragraphs 

2.A. through 2.C.(2) of Turbomeca Alert 

Service Bulletin No. A319 79 4802, Update 

No. 1, dated April 3, 2006, to replace the Oring. 

TABLE 1—COMPLIANCE TIMES FOR O-RING REPLACEMENT

If the class of oil is: Then replace the O-ring by the later of: Thereafter, replace the Oring within: 

(1) HTS or unknown. ........................................................ 300 hours time-since-new (TSN) or 50 hours after 

March 21, 2007 (effective date of AD 2005–17– 

17R1)..

300 hours time-since-last 

replacement (TSR). 

(2) STD. ............................................................................ 450 hours TSN or 50 hours after March 21, 2007 (effective date of AD 2005–17–17R1)..500 hours TSR. 

Mandatory Terminating Action 

(g) Within 150 flight hours after the 

effective date of this AD, do the following 

mandatory terminating action to the 

repetitive O-ring replacements: 

(1) Incorporate Turbomeca Modification 

Tf75 by replacing the check valve piston in 

the lubrication unit, with a check valve 

piston requiring no O-ring. 

(2) Use the Instructions to be Incorporated 

paragraphs 2.A. through 2.B.(1)(r) of 

Turbomeca Mandatory Service Bulletin No. 

319 79 4075, Version B, dated May 14, 2008, 

to replace the check valve piston. 

Alternative Methods of Compliance 

(h) The Manager, Engine Certification 

Office, FAA, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(i) EASA AD 2008–0170, dated September 

25, 2008, also addresses the subject of this 

AD. 

(j) Contact Turbomeca S.A., 40220 Tarnos, 

France; e-mail: noria-dallas@turbomeca.com; 

telephone 33 05 59 74 40 00, fax 33 05 59 

74 45 15, or go to: http://www.turbomecasupport.com, for a copy of the service 

information identified in this AD. 

(k) Contact James Lawrence, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: james.lawrence@faa.gov; 

telephone (781) 238–7176; fax (781) 238– 

7199, for more information about this AD. 

Material Incorporated by Reference 

(l) You must use the service information 

specified in the following Table 2 to perform 

the actions required by this AD. The Director 

of the Federal Register approved the 

incorporation by reference of the documents 

listed in the following Table 2 in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Turbomeca S.A., 40220 Tarnos, 

France; e-mail: noria-dallas@turbomeca.com; 

telephone 33 05 59 74 40 00, fax 33 05 59 

74 45 15, or go to: http://www.turbomecasupport.com, for a copy of this service 

information. You may review copies at the 

FAA, New England Region, 12 New England 

Executive Park, Burlington, MA; 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/cfr/ibrlocations.html. 

TABLE 2—INCORPORATION BY REFERENCE

Turbomeca Alert/Mandatory 

Service Bulletin No. Page Update/version Date 

A319 79 4802, Total Pages: 7 ...... ALL ............................................... Update No. 1 ................................ April 3, 2006. 

319 79 4075, Total Pages: 9 ......... ALL ............................................... Version B ...................................... May 14, 2008. 


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Federal Register / Vol. 74, No. 123 / Monday, June 29, 2009 / Rules and Regulations 30919 

Issued in Burlington, Massachusetts, on 

June 19, 2009. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–15099 Filed 6–26–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1071; Directorate 

Identifier 2008–NM–093–AD; Amendment 

39–15951; AD 2009–14–02] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Boeing Model 

747 airplanes. That AD currently 

requires repetitive inspections to detect 

evidence of wear damage in the area at 

the interface between the vertical 

stabilizer seal and fuselage skin, and 

corrective actions, if necessary. The 

existing AD also provides for an 

optional terminating action for the 

repetitive inspections. For all Boeing 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747–400, 747–400D, 747– 

400F, 747SR, and 747SP series 

airplanes, this new AD requires 

repetitive inspections for wear damage 

and cracks of the fuselage skin in the 

interface area of the vertical stabilizer 

seal and fuselage skin, a detailed 

inspection for wear damage and cracks 

of the surface of any skin repair doubler 

in the area, and corrective actions if 

necessary. For airplanes on which the 

fuselage skin has been blended to 

remove wear damage, this new AD 

requires repetitive external detailed 

inspections or high frequency eddy 

current inspections for cracks of the 

blended area of the fuselage skin, and 

corrective actions if necessary. This AD 

results from reports of wear damage on 

airplanes with fewer than 8,000 total 

flight cycles. In addition, there have 

been three reports of skin wear damage 

on airplanes that applied Boeing 

Material Specifications 10–86 Teflonfilled coating (terminating action per the 

existing AD). We are issuing this AD to 

detect and correct wear damage and 

cracks of the fuselage skin in the 

interface area of the vertical stabilizer 

seal and fuselage skin in sections 46 and 

48, which could cause in-flight 

depressurization of the airplane. 

DATES: This AD becomes effective 

August 3, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of August 3, 2009. 

On February 10, 2003 (68 FR 476, 

January 6, 2003), the Director of the 

Federal Register approved the 

incorporation by reference of Boeing 

Alert Service Bulletin 747–53A2478, 

dated February 7, 2002. 

ADDRESSES: For service information 

identified in this 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. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room, W12– 

140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2002–26–15, amendment 

39–13003 (68 FR 476, January 6, 2003). 

The existing AD applies to certain 

Boeing Model 747 series airplanes. That 

NPRM was published in the Federal 

Register on October 8, 2008 (73 FR 

58903). That NPRM proposed to require, 

for all Boeing Model 747–100, 747– 

100B, 747–100B SUD, 747–200B, 747– 

200C, 747–200F, 747–300, 747–400, 

747–400D, 747–400F, 747SR, and 747SP 

series airplanes, repetitive inspections 

for wear damage and cracks of the 

fuselage skin in the interface area of the 

vertical stabilizer seal and fuselage skin, 

a detailed inspection for wear damage 

and cracks of the surface of any skin 

repair doubler in the area, and 

corrective actions if necessary. For 

airplanes on which the fuselage skin has 

been blended to remove wear damage, 

that NPRM proposed to require 

repetitive external detailed inspections 

or high frequency eddy current (HFEC) 

inspections for cracks of the blended 

area of the fuselage skin, and corrective 

actions if necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the NPRM. 

Request for Change in Applicability 

Boeing requests that the second 

paragraph under ‘‘Relevant Service 

Information’’ of the NPRM be revised to 

list the specific Boeing Model 747 series 

airplanes affected by this rule. The 

commenter states that Boeing Model 

747–8 series airplanes, which are not 

yet FAA type-certificated, should be 

excluded because they are equipped 

with corrosion-resistant steel rubstrips 

on the affected skins, which are a 

baseline configuration on these 

airplanes. 

We find that clarification is necessary. 

The applicability in paragraph (c) of the 

AD identifies specifically affected 

Boeing Model 747 airplanes. However, 

the ‘‘Relevant Service Information’’ 

section is not restated in the final rule. 

Therefore, for clarity, we have specified 

in the Discussion section of this AD the 

specific Boeing Model 747 airplanes 

identified in the AD applicability 

(paragraph (c)) of this AD. 

Request To Delay Issuance of the AD 

Japan Airlines (JAL) requests that we 

delay the issuance of the AD until the 

service bulletin is revised and the repair 

doubler wear limits can be incorporated 

into the final rule. JAL states that the 

NPRM and Boeing Alert Service 

Bulletin 747–53A2478, Revision 1, 

dated March 27, 2008, do not provide 

any wear limits for the repair doublers. 

JAL also states that operators would 

have to contact Boeing for repair 

instructions, replace the repair, or 

replace the repair doubler even if minor 

blending is found. 

We disagree with the request to delay 

issuance of this AD. The wear limits 

provided in the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 747–53A2478, Revision 1, 


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