43636 Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations 

Related Information 

(k) European Aviation Safety Agency AD 

2009–0110, dated May 7, 2009, also 

addresses the subject of this AD. 

(l) Contact Stephen Sheely, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: stephen.k.sheely@faa.gov; 

telephone (781) 238–7750; fax (781) 238– 

7199, for more information about this AD. 

Material Incorporated by Reference 

(m) You must use CFM International, S.A. 

SB No. CFM56–5B S/B 72–0620, Revision 2, 

dated December 1, 2008 to perform the 

inspections required by this AD. The Director 

of the Federal Register approved the 

incorporation by reference of this service 

bulletin in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. Contact CFM 

International, Technical Publications 

Department, 1 Neumann Way, Cincinnati, 

OH 45215; telephone (513) 552–2800; fax 

(513) 552–2816, 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. 

Issued in Burlington, Massachusetts, on 

August 17, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–20284 Filed 8–26–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0622; Directorate 

Identifier 2009–CE–034–AD; Amendment 

39–15999; AD 2009–18–03] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Models PC–6, PC–6–H1, 

PC–6–H2, PC–6/350, PC–6/350–H1, PC– 

6/350–H2, PC–6/A, PC–6/A–H1, PC–6/ 

A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/ 

B2–H2, PC–6/B2–H4, PC–6/C–H2, and 

PC–6/C1–H2 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing 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: 

Findings of corrosion, wear and cracks in 

the upper wing strut fittings on some PC–6 

aircraft have been reported in the past. It is 

possible that the spherical bearing of the 

wing strut fittings installed in the underwing 

can be loose in the fitting or cannot rotate 

because of corrosion. In this condition, the 

joint cannot function as designed and fatigue 

cracks may then develop. Undetected cracks, 

wear and/or corrosion in this area could 

cause failure of the upper attachment fitting, 

leading to failure of the wing structure and 

subsequent loss of control of the aircraft. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

October 1, 2009. 

On October 1, 2009, the Director of 

the Federal Register approved the 

incorporation by reference of Pilatus 

Aircraft Ltd. Pilatus PC–6 Service 

Bulletin No. 57–005, REV No. 2, dated 

May 19, 2008, and Chapter 57–00–02 of 

Pilatus Aircraft Ltd. Pilatus PC–6 

Aircraft Maintenance Manual, dated 

November 30, 2008 (referenced as 

revision 9 in European Aviation Safety 

Agency (EASA) AD No.: 2007–0241R3), 

listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

Docket 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: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090. 

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 July 8, 2009 (74 FR 32471), 

and proposed to supersede AD 2007– 

19–14, Amendment 39–15205 (72 FR 

53920, September 21, 2007). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Findings of corrosion, wear and cracks in 

the upper wing strut fittings on some PC–6 

aircraft have been reported in the past. It is 

possible that the spherical bearing of the 

wing strut fittings installed in the underwing 

can be loose in the fitting or cannot rotate 

because of corrosion. In this condition, the 

joint cannot function as designed and fatigue 

cracks may then develop. Undetected cracks, 

wear and/or corrosion in this area could 

cause failure of the upper attachment fitting, 

leading to failure of the wing structure and 

subsequent loss of control of the aircraft. 

To address this problem, FOCA published 

AD TM–L Nr. 80.627–6/Index 72–2 and HB– 

2006–400 and EASA published AD 2007– 

0114 to require specific inspections and to 

obtain a fleet status. Since the issuance of AD 

2007–0114, the reported data proved that it 

was necessary to establish and require 

repetitive inspections. 

EASA published Emergency AD 2007– 

0241–E to extend the applicability and to 

require repetitive eddy current and visual 

inspections of the upper wing strut fitting for 

evidence of cracks, wear and/or corrosion 

and examination of the spherical bearing and 

replacement of cracked fittings. Collected 

data received in response to Emergency AD 

2007–0241–E resulted in the issuance of 

EASA AD 2007–0241R1 that permitted 

extending the intervals for the repetitive 

eddy current and visual inspections from 100 

Flight Hours (FH) to 300 FH and from 150 

Flight Cycles (FC) to 450 FC, respectively. In 

addition, oversize bolts were introduced by 

Pilatus PC–6 Service Bulletin (SB) 57–005 R1 

and the fitting replacement procedure was 

adjusted accordingly. 

Based on fatigue test results, EASA AD 

2007–0241R2 was issued to extend the 

repetitive inspection interval to 1 100 FH or 

12 calendar months, whichever occurs first, 

and to delete the related flight cycle intervals 

and the requirement for the ‘‘Mild Corrosion 

Severity Zone’’. In addition, some editorial 

changes have been made for reasons of 

standardization and readability. 

Revision 3 of this AD refers to the latest 

revision of the PC–6 Aircraft Maintenance 

Manual (AMM) Chapter 5 limitations which 

includes the same repetitive inspection 

intervals and procedures already mandated 

in the revision 2 of AD 2007–0241. Besides 

the inspections, the latest revision of the PC– 

6 AMM contains the replacement procedures 

for the fittings. 

Additionally, it is possible to replace the 

wing strut fitting with a new designed wing 

strut fitting. With this optional part 

replacement, in the repetitive inspection 

procedure the 1 100 FH interval is deleted so 

that only calendar defined intervals of 

inspections remain applicable. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 


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Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations 43637 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

50 products of U.S. registry. We also 

estimate that it will take about 7 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Based on these figures, we estimate 

the cost of the proposed AD on U.S. 

operators to be $28,000, or $560 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 30 work-hours and require parts 

costing $5,000, for a cost of $7,400 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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 

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 Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains the NPRM, 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. 

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 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 

removing Amendment 39–15205 (72 FR 

53920, September 21, 2007) and adding 

the following new AD: 

2009–18–03 Pilatus Aircraft Ltd.: 

Amendment 39–15999; Docket No. 

FAA–2009–0622; Directorate Identifier 

2009–CE–034–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 1, 2009. 

Affected ADs 

(b) This AD supersedes AD 2007–19–14, 

Amendment 39–15205. 

Applicability 

(c) This AD applies to Models PC–6, PC– 

6–H1, PC–6–H2, PC–6/350, PC–6/350–H1, 

PC–6/350–H2, PC–6/A, PC–6/A–H1, PC–6/ 

A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/B2– 

H2, PC–6/B2–H4, PC–6/C–H2, and PC–6/C1– 

H2 airplanes, manufacturer serial numbers 

(MSN) 101 through 999 and MSN 2001 

through 2092, certificated in any category. 

Note 1: These airplanes are also identified 

as Fairchild Republic Company PC–6 

airplanes, Fairchild Industries PC–6 

airplanes, Fairchild Heli Porter PC–6 

airplanes, or Fairchild-Hiller Corporation 

PC–6 airplanes. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Findings of corrosion, wear and cracks in 

the upper wing strut fittings on some PC–6 

aircraft have been reported in the past. It is 

possible that the spherical bearing of the 

wing strut fittings installed in the underwing 

can be loose in the fitting or cannot rotate 

because of corrosion. In this condition, the 

joint cannot function as designed and fatigue 

cracks may then develop. Undetected cracks, 

wear and/or corrosion in this area could 

cause failure of the upper attachment fitting, 

leading to failure of the wing structure and 

subsequent loss of control of the aircraft. 

To address this problem, FOCA published 

AD TM–L Nr. 80.627–6/Index 72–2 and HB– 

2006–400 and EASA published AD 2007– 

0114 to require specific inspections and to 

obtain a fleet status. Since the issuance of AD 

2007–0114, the reported data proved that it 

was necessary to establish and require 

repetitive inspections. 

EASA published Emergency AD 2007– 

0241–E to extend the applicability and to 

require repetitive eddy current and visual 

inspections of the upper wing strut fitting for 

evidence of cracks, wear and/or corrosion 

and examination of the spherical bearing and 

replacement of cracked fittings. Collected 

data received in response to Emergency AD 

2007–0241–E resulted in the issuance of 

EASA AD 2007–0241R1 that permitted 

extending the intervals for the repetitive 

eddy current and visual inspections from 100 

Flight Hours (FH) to 300 FH and from 150 

Flight Cycles (FC) to 450 FC, respectively. In 

addition, oversize bolts were introduced by 

Pilatus PC–6 Service Bulletin (SB) 57–005 R1 

and the fitting replacement procedure was 

adjusted accordingly. 

Based on fatigue test results, EASA AD 

2007–0241R2 was issued to extend the 

repetitive inspection interval to 1 100 FH or 

12 calendar months, whichever occurs first, 

and to delete the related flight cycle intervals 

and the requirement for the ‘‘Mild Corrosion 

Severity Zone’’. In addition, some editorial 

changes have been made for reasons of 

standardization and readability. 

Revision 3 of this AD refers to the latest 

revision of the PC–6 Aircraft Maintenance 

Manual (AMM) Chapter 5 limitations which 

includes the same repetitive inspection 

intervals and procedures already mandated 


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43638 Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations 

in the revision 2 of AD 2007–0241. Besides 

the inspections, the latest revision of the PC– 

6 AMM contains the replacement procedures 

for the fittings. 

Additionally, it is possible to replace the 

wing strut fitting with a new designed wing 

strut fitting. With this optional part 

replacement, in the repetitive inspection 

procedure the 1 100 FH interval is deleted so 

that only calendar defined intervals of 

inspections remain applicable. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) For airplanes that have not had both 

wing strut fittings replaced within the last 

100 hours time-in-service (TIS) before 

September 26, 2007 (the effective date of AD 

2007–19–14), or have not been inspected 

using an eddy current inspection method 

following Pilatus Aircraft Ltd. Pilatus PC–6 

Service Bulletin No. 57–004, dated April 16, 

2007, within the last 100 hours TIS before 

September 26, 2007 (the effective date of AD 

2007–19–14): Before further flight after 

September 26, 2007 (the effective date of AD 

2007–19–14), visually inspect the upper wing 

strut fittings and examine the spherical 

bearings following the Pilatus Aircraft Ltd. 

Pilatus PC–6 Service Bulletin No. 57–005, 

REV No. 2, dated May 19, 2008. 

(2) For all airplanes: Within 25 hours TIS 

after September 26, 2007 (the effective date 

of AD 2007–19–14), or within 30 days after 

September 26, 2007 (the effective date of AD 

2007–19–14), whichever occurs first, visually 

and using eddy current methods, inspect the 

upper wing strut fittings and examine the 

spherical bearings following Pilatus Aircraft 

Ltd. Pilatus PC–6 Service Bulletin No. 57– 

005, REV No. 2, dated May 19, 2008. 

(3) After doing the inspection specified in 

paragraph (f)(2) of this AD or replacing the 

upper wing strut fitting, repetitively do the 

following inspections: 

(i) For all airplanes: at intervals not to 

exceed every 3 calendar months visually 

inspect the upper wing strut fittings and 

examine the spherical bearings following 

Chapter 57–00–02 of Pilatus Aircraft Ltd. 

Pilatus PC–6 Aircraft Maintenance Manual, 

dated November 30, 2008 (referenced as 

revision 9 in European Aviation Safety 

Agency (EASA) AD No.: 2007–0241R3). For 

airplanes equipped with wing strut fitting 

part number (P/N) 6102.0041.00, P/N 

111.35.06.055, P/N 111.35.06.056, P/N 

111.35.06.184, P/N 111.35.06.185, or P/N 

111.35.06.186, you may also do these 

inspections following Pilatus Aircraft Ltd. 

Pilatus PC–6 Service Bulletin No. 57–005, 

REV No. 2, dated May 19, 2008. 

(ii) For airplanes equipped with wing strut 

fitting P/N 6102.0041.00, P/N 111.35.06.055, 

P/N 111.35.06.056, P/N 111.35.06.184, P/N 

111.35.06.185, or P/N 111.35.06.186: at 

intervals not to exceed every 1,100 hours TIS 

or 12 calendar months, whichever occurs 

first, visually and using eddy current 

methods, inspect the upper wing strut fittings 

and examine the spherical bearings following 

Pilatus Aircraft Ltd. Pilatus PC–6 Service 

Bulletin No. 57–005, REV No. 2, dated May 

19, 2008, or Chapter 57–00–02 of Pilatus 

Aircraft Ltd. Pilatus PC–6 Aircraft 

Maintenance Manual, dated November 30, 

2008 (referenced as revision 9 in EASA AD 

No.: 2007–0241R3). 

(iii) For airplanes equipped with wing strut 

fitting P/N 111.35.06.193, P/N 111.35.06.194, 

or P/N 111.35.06.195: at intervals not to 

exceed every 12 calendar months, visually 

and using eddy current methods, inspect the 

upper wing strut fittings and examine the 

spherical bearings following Chapter 57–00– 

02 of Pilatus Aircraft Ltd. Pilatus PC–6 

Aircraft Maintenance Manual, dated 

November 30, 2008 (referenced as revision 9 

in EASA AD No.: 2007–0241R3). 

(4) You may also take ‘‘unless already 

done’’ credit for any inspection specified in 

paragraphs (f)(1), (f)(2), or (f)(3) of this AD if 

done before October 1, 2009 (the effective 

date of this AD) following Pilatus Aircraft 

Ltd. Pilatus PC–6 Service Bulletin No. 57– 

005, dated August 30, 2007; or Pilatus 

Aircraft Ltd. Pilatus PC–6 Service Bulletin 

No. 57–005, REV No. 1, dated November 19, 

2007. 

(5) For all airplanes: If during any 

inspection required by paragraphs (f)(1), 

(f)(2), or (f)(3) of this AD you find cracks in 

the upper wing strut fitting or the spherical 

bearing is not in conformity, before further 

flight, replace the cracked upper wing strut 

fitting and/or the nonconforming spherical 

bearing following Chapter 57–00–02 of 

Pilatus Aircraft Ltd. Pilatus PC–6 Aircraft 

Maintenance Manual, dated November 30, 

2008 (referenced as revision 9 in EASA AD 

No.: 2007–0241R3). 

(6) For all airplanes: Replacement of one or 

both upper wing strut fitting(s) does not 

terminate the repetitive inspection specified 

in paragraph (f)(3) of this AD. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): 

(i) The Manager, Standards Office, 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: 

Doug Rudolph, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4059; fax: (816) 329– 

4090. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(ii) AMOCs approved for AD 2007–19–14 

are not approved for 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 

(h) Refer to MCAI EASA AD No.: 2007– 

0241R3, dated May 6, 2009; Pilatus Aircraft 

Ltd. Pilatus PC–6 Service Bulletin No. 57– 

005, REV No. 2, dated May 19, 2008; Pilatus 

Aircraft Ltd. Pilatus PC–6 Service Bulletin 

No. 57–005, REV No. 1, dated November 19, 

2007; Pilatus Aircraft Ltd. Pilatus PC–6 

Service Bulletin No. 57–005, dated August 

30, 2007; Pilatus Aircraft Ltd. Pilatus PC–6 

Service Bulletin No. 57–004, dated April 16, 

2007; and Chapter 57–00–02 of Pilatus 

Aircraft Ltd. Pilatus PC–6 Aircraft 

Maintenance Manual, dated November 30, 

2008 (referenced as revision 9 in EASA AD 

No.: 2007–0241R3), for related information. 

Material Incorporated by Reference 

(i) You must use Pilatus Aircraft Ltd. 

Pilatus PC–6 Service Bulletin No. 57–005, 

REV No. 2, dated May 19, 2008; and Chapter 

57–00–02 of Pilatus Aircraft Ltd. Pilatus PC– 

6 Aircraft Maintenance Manual, dated 

November 30, 2008 (referenced as revision 9 

in EASA AD No.: 2007–0241R3), to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Pilatus Aircraft Ltd. Pilatus PC–6 Service 

Bulletin No. 57–005, REV No. 2, dated May 

19, 2008, and Chapter 57–00–02 of Pilatus 

Aircraft Ltd. Pilatus PC–6 Aircraft 

Maintenance Manual, dated November 30, 

2008 (referenced as revision 9 in EASA AD 

No.: 2007–0241R3), under 5 U.S.C. 552(a) 

and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Pilatus Aircraft Ltd., 

Customer Liaison Manager, CH 6371 STANS, 

Switzerland; telephone: + 41 (0)41 619 6580; 

fax: + 41 (0)41 619 6576; e-mail: 

fodermatt@pilatus aircaft.com. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri, on August 

18, 2009. 

Scott A. Horn, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–20386 Filed 8–26–09; 8:45 am] 

BILLING CODE 4910–13–P 


srobinson on DSKHWCL6B1PROD with RULES