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, 43636-43638 [E9-20386]

Download as PDF 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: https:// 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 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. srobinson on DSKHWCL6B1PROD with RULES AGENCY: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) SUMMARY: VerDate Nov<24>2008 16:19 Aug 26, 2009 Jkt 217001 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 https:// 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 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 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. E:\FR\FM\27AUR1.SGM 27AUR1 Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations 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. 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. srobinson on DSKHWCL6B1PROD with RULES 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. Examining the AD Docket You may examine the AD docket on the Internet at https:// 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. 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 VerDate Nov<24>2008 16:19 Aug 26, 2009 Jkt 217001 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. PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 43637 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 E:\FR\FM\27AUR1.SGM 27AUR1 43638 Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations srobinson on DSKHWCL6B1PROD with RULES 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 VerDate Nov<24>2008 16:19 Aug 26, 2009 Jkt 217001 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. PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 (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: https://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 E:\FR\FM\27AUR1.SGM 27AUR1

Agencies

[Federal Register Volume 74, Number 165 (Thursday, August 27, 2009)]
[Rules and Regulations]
[Pages 43636-43638]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-20386]


-----------------------------------------------------------------------

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 https://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.

[[Page 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 work-hours 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 https://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 39-15205 (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

[[Page 43638]]

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: https://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
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