Document ID: FAA-2009-0622-0009
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Pilatus Aircraft Ltd. Models PC-6, PC-6 H1, PC-6 H2, PC-6/350, PC-6/350 H1, et al. Airplanes
Posted Date: 2011-01-12T05:00Z

[Federal Register Volume 76, Number 8 (Wednesday, January 12, 2011)]
[Rules and Regulations]
[Pages 1990-1993]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-33333]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0622; Directorate Identifier 2009-CE-034-AD; 
Amendment
[39-16570; AD 2009-18-03 R1]
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.

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SUMMARY: We are revising 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.
    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 1100 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 referred to the latest revision of the PC-
6 Aircraft Maintenance Manual (AMM) Chapter 5 limitations which have 
included the same repetitive inspection intervals and procedures 
already mandated in the revision 2 of AD 2007-0241. Besides the 
inspections, in the latest revision of the PC-6 AMM, the replacement 
procedures for the fittings were included.
    Additionally, EASA AD 2007-0241R3 introduced the possibility to 
replace the wing strut fitting with a new designed wing strut

[[Page 1991]]

fitting. With this optional part replacement, in the repetitive 
inspection procedure the 1100 FH interval is deleted so that only 
calendar defined intervals of inspections remained applicable.

We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective February 16, 2011.
    As of October 1, 2009 (74 FR 43636, August 27, 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 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 service information identified in this AD, contact PILATUS 
AIRCRAFT LTD., Customer Service Manager, CH-6371 STANS, Switzerland; 
telephone: +41 (0) 41 619 65 01; fax: +41 (0) 41 619 65 76; Internet: 
http://www.pilatus-aircraft.com. You may review copies of the 
referenced service information at the FAA, Small Airplane Directorate, 
901 Locust, Kansas City, Missouri 64106. For information on the 
availability of this material at the FAA, call 816-329-4148.

FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, 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 October 7, 2010 (75 
FR 62005), and proposed to revise AD 2009-18-03, Amendment 39-15999 (74 
FR 43636, August 27, 2009).
    Since we issued AD 2009-18-03, Pilatus has updated their 
maintenance programs with new requirements and limitations. Another AD 
action, AD 2011-01-14, requires the incorporation of the updated 
maintenance requirements into the airworthiness limitations section of 
the instructions for continued airworthiness. Those updated maintenance 
requirements include the repetitive inspections for the wing strut 
fittings and the spherical bearings currently included in AD 2009-18-
03.
    The NPRM proposed to correct an unsafe condition for the specified 
products. The MCAI states that:

    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 1100 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 referred to the latest revision of the PC-
6 Aircraft Maintenance Manual (AMM) Chapter 5 limitations which have 
included the same repetitive inspection intervals and procedures 
already mandated in the revision 2 of AD 2007-0241. Besides the 
inspections, in the latest revision of the PC-6 AMM, the replacement 
procedures for the fittings were included.
    Additionally, EASA AD 2007-0241R3 introduced the possibility to 
replace the wing strut fitting with a new designed wing strut 
fitting. With this optional part replacement, in the repetitive 
inspection procedure the 1100 FH interval is deleted so that only 
calendar defined intervals of inspections remained applicable.
    The aim of this new revision is to only mandate the initial 
inspection requirement and consequently to limit its applicability 
to aeroplanes which are not already in compliance with EASA AD 2007-
0241R3. All aeroplanes which are in compliance with EASA AD 2007-
0241R3 have to follow the repetitive inspection requirements as 
described in Pilatus PC-6 AMM Chapter 04-00-00, Document Number 
01975, Revision 12 and the Airworthiness Limitations (ALS) Document 
Number 02334 Revision 1 mandated by EASA AD 2010-0176. Therefore the 
repetitive inspection requirements corresponding paragraphs have 
been deleted in this new EASA AD revision. The paragraph numbers of 
EASA AD 2007-0241R numbering has been maintained for referencing 
needs.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received.

Request for Clarification on Applicability

    Pilatus Aircraft commented that there is no consistency between FAA 
Directorate Identifier 2010-CE-047-AD and FAA Directorate Identifier 
2009-CE-034-AD regarding the applicability of airplanes in regards to 
the manufacturer serial numbers (MSN) on the Fairchild PC-6 airplanes.
    The FAA agrees that the applicability of airplanes needs corrected. 
We will change the applicability to clarify that some specific MSNs can 
also be 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.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting the 
AD with the changes described previously. We determined that these 
changes will not increase the economic burden on any operator or 
increase the scope of the AD.

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

[[Page 1992]]

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 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour.
    Based on these figures, we estimate the cost of this AD on U.S. 
operators to be $29,750, or $595 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 30 work-hours and require parts costing $5,000, for a cost 
of $7,550 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

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-15999 (74 FR 
43636, August 27, 2009) and adding the following new AD:

2009-18-03 R1 Pilatus Aircraft Limited: Amendment 39-16570; Docket 
No. FAA-2009-0622; Directorate Identifier 2009-CE-034-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective February 
16, 2011.

Affected ADs

    (b) This AD revises AD 2009-18-03, Amendment 39-15999.

Applicability

    (c) This AD applies to 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, all manufacturer serial number (MSN) 101 
through 999, and MSN 2001 through 2092, certificated in any 
category.

    Note 1: For MSN 2001-2092, 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 1100 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 referred to the latest revision of the PC-
6 Aircraft Maintenance Manual (AMM) Chapter 5 limitations which have 
included the same repetitive inspection intervals and procedures 
already mandated in the revision 2 of AD 2007-0241. Besides the 
inspections, in the latest revision of the PC-6 AMM, the replacement 
procedures for the fittings were included.
    Additionally, EASA AD 2007-0241R3 introduced the possibility to 
replace the wing strut fitting with a new designed wing strut 
fitting. With this optional part replacement, in the repetitive 
inspection procedure the 1100 FH interval is deleted so that only 
calendar defined intervals of inspections remained applicable.
    The aim of this new revision is to only mandate the initial 
inspection requirement and consequently to limit its applicability 
to aeroplanes which are not already in

[[Page 1993]]

compliance with EASA AD 2007-0241R3. All aeroplanes which are in 
compliance with EASA AD 2007-0241R3 have to follow the repetitive 
inspection requirements as described in Pilatus PC-6 AMM Chapter 04-
00-00, Document Number 01975, Revision 12 and the Airworthiness 
Limitations (ALS) Document Number 02334 Revision 1 mandated by EASA 
AD 2010-0176. Therefore the repetitive inspection requirements 
corresponding paragraphs have been deleted in this new EASA AD 
revision. The paragraph numbers of EASA AD 2007-0241R numbering has 
been maintained for referencing needs.

This AD requires actions that are intended to address the unsafe 
condition described in the MCAI.

Actions and Compliance

    (f) Unless already done, do the following actions:
    (1) For affected 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 either September 26, 2007 (the effective date 
of AD 2007-19-14), or October 1, 2009 (the effective date of AD 
2009-18-03), 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 affected 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) You may also take ``unless already done'' credit for any 
inspection specified in paragraphs (f)(1) or (f)(2) of this AD if 
done before October 1, 2009 (the effective date retained from AD 
2009-18-03) 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.
    (4) For all affected airplanes: If during any inspection 
required by paragraphs (f)(1) or (f)(2) 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.

    Note 1: AD 2011-01-14 requires the incorporation of the updated 
maintenance requirements into the airworthiness limitations section 
of the instructions for continued airworthiness. Those updated 
maintenance requirements include the repetitive inspections for the 
wing strut fittings and the spherical bearings. This revised AD 
removes those repetitive inspections.

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): 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.
    (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, a federal agency may not conduct or sponsor, and a person 
is not required to respond to, nor shall a person be subject to a 
penalty for failure to comply with a collection of information 
subject to the requirements of the Paperwork Reduction Act unless 
that collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 5 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

Related Information

    (h) Refer to MCAI EASA AD No.: 2007-0241R4, dated August 31, 
2010; 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, for related information.

Material Incorporated by Reference

    (h) 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) On October 1, 2009 (74 FR 43636, August 27, 2009), the 
Director of the Federal Register previously 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).
    (2) For service information identified in this AD, contact 
PILATUS AIRCRAFT LTD., Customer Service Manager, CH-6371 STANS, 
Switzerland; telephone: +41 (0) 41 619 65 01; fax: +41 (0) 41 619 65 
76; Internet: http://www.pilatus-aircraft.com.
    (3) You may review copies of the referenced service information 
at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, 
Missouri 64106. For information on the availability of this material 
at the FAA, call 816-329-4148.
    (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 December 28, 2010.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010-33333 Filed 1-11-11; 8:45 am]
BILLING CODE 4910-13-P