AD 2009-18-03 R1

AD Final Rules - 2009-18-03 R1.pdf
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AD Number:
2009-18-03 R1
Document Type:
AD Final Rules
Docket Number:
FAA-2009-0622
Subject Heading:
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... ...Show more
Subject:
Wings
Status:
Current
Citation:
Federal Register: January 12, 2011 (Volume 76, Number 8)
Citation Publish Date:
01/12/2011
Effective Date:
02/16/2011
Make:
Pilatus Aircraft Limited
Model:
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 ...Show more
Product Type:
Aircraft
Product Subtype:
Small Airplane
Affected AD:
Superseded AD:
2009-18-03
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
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[Federal Register: January 12, 2011 (Volume 76, Number 8)]


[Rules and Regulations]


[Page 1990-1993]


From the Federal Register Online via GPO Access [wais.access.gpo.gov]


[DOCID:fr12ja11-4]


––––––––––––––––––––––––––––––––––


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.


––––––––––––––––––––––––––––––––––


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


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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.


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


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