Document ID: FAA-2007-0004-0044
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Pilatus Aircraft Limited Model PC-6 Series Airplanes
Posted Date: 2007-09-21T04:00Z

[Federal Register: September 21, 2007 (Volume 72, Number 183)]
[Rules and Regulations]               
[Page 53920-53923]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr21se07-4]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-29178; Directorate Identifier 2007-CE-074-AD; 
Amendment 39-15205; AD 2007-19-14]
RIN 2120-AA64

 
Airworthiness Directives; Pilatus Aircraft Limited Model PC-6 
Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above that would supersede existing ADs. This AD 
results from mandatory continuing airworthiness information (MCAI) 
issued by the 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 lead to 
failure on the upper attachment fitting. This could result in the 
failure of the wing structure with subsequent loss of control of the 
aircraft.

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

DATES: This AD becomes effective September 26, 2007.
    On September 26, 2007, the Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in this AD.
    We must receive comments on this AD by October 22, 2007.

ADDRESSES: You may send comments by any of the following methods:
     DOT Docket Web Site: Go to  http://dms.dot.gov and follow 

the instructions for sending your comments electronically.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
     Federal eRulemaking Portal: http://www.regulations.gov. 

Follow the instructions for submitting comments.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov
; or in person at the Docket Management Facility between 9 

a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains this AD, the regulatory evaluation, any comments 
received, and other information. The 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.

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:

[[Page 53921]]

Discussion

    On January 24, 2007, we issued AD 2007-03-08, Amendment 39-14919 
(72 FR 4635; February 1, 2007), and on July 19, 2007, we issued AD 
2007-15-09, Amendment 39-15138 (72 FR 41436; July 30, 2007). Those ADs 
required actions intended to address an unsafe condition on the 
products listed above.
    Since we issued AD 2007-03-08 and AD 2007-15-09, Pilatus reported 
that the right hand (RH) wing strut fitting of aircraft serial number 
903 was found with one lug shoulder completely broken. The aircraft had 
accumulated 297 hours time-in-service since the RH wing strut fitting 
had been replaced in May of 2007. Based on this report, the foreign 
airworthiness authority has issued a new MCAI.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued AD 
No. 2007-0241-E, dated September 5, 2007 (referred to after this as 
``the MCAI''), 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 lead to 
failure on the upper attachment fitting. This could result in the 
failure of the wing structure with subsequent loss of control of the 
aircraft.
    To address this problem the superseded FOCA Airworthiness 
Directives (AD) TM-L Nr. 80.627-6, HB-2006-400 and EASA AD 2007-0114 
were issued to mandate specific inspections and to obtain a fleet 
status. Since the issuance of AD 2007-0114, the data reporting 
proved that it was necessary to establish repetitive inspections.
    Thus, in addition to an extended applicability, the present AD 
mandates repetitive inspections of the upper wing strut fitting for 
cracks, wear and/or corrosion and examination of the spherical 
bearing and replacement of cracked fittings.

    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Pilatus Aircraft Ltd. has issued Service Bulletin No. 57-005, dated 
August 30, 2007. The actions described in this service information are 
intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of the AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with this State of Design Authority, they 
have notified us of the unsafe condition described in the MCAI and 
service information referenced above. We are issuing this AD because we 
evaluated all information provided by the State of Design Authority and 
determined the unsafe condition exists and is likely to exist or 
develop on other products of the same type design.

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 have also required different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
described in a separate paragraph of the AD. These requirements take 
precedence over those copied from the MCAI.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because it is 
possible that fatigue cracks exist on the wing strut fittings installed 
on the wing that are not detected during the inspections published in 
the aircraft maintenance manual or required by any previous service 
bulletin. Undetected cracks in this area could lead to failure of the 
fitting and consequent loss of control. Therefore, we determined that 
notice and opportunity for public comment before issuing this AD are 
impracticable and that good cause exists for making this amendment 
effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2007-29178; Directorate 
Identifier 2007-CE-074-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will 

also post a report summarizing each substantive verbal contact we 
receive about this AD.

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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

[[Page 53922]]

    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

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 39-14919 (72 FR 
4635; February 1, 2007) and Amendment 39-15138 (72 FR 41436; July 30, 
2007); and adding the following new AD:

2007-19-14 Pilatus Aircraft Limited: Amendment 39-15205; Docket No. 
FAA-2007-29178; Directorate Identifier 2007-CE-074-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective 
September 26, 2007.

Affected ADs

    (b) This AD supersedes the following ADs:
    (1) AD 2007-03-08; Amendment 39-14919; and
    (2) AD 2007-15-09; Amendment 39-15138.

Applicability

    (c) This AD applies to:
    (1) 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 (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);
    (2) Manufacturer serial numbers (MSN) 101 through 999 and MSN 
2001 through 2092;
    (3) Airplanes that are equipped with left wing strut fitting 
part number (P/N) 6102.0041.00, P/N 111.35.06.055, P/N 
111.35.06.184, or P/N 111.35.06.185; or equipped with right wing 
strut fitting P/N 6102.0041.00, P/N 111.35.06.056, P/N 
111.35.06.184, or P/N 111.35.06.186, or FAA-approved equivalent part 
numbers; and
    (4) Airplanes that are certificated in any category.

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 lead to 
failure on the upper attachment fitting. This could result in the 
failure of the wing structure with subsequent loss of control of the 
aircraft.
    To address this problem the superseded FOCA Airworthiness 
Directives (AD) TM-L Nr. 80.627-6, HB-2006-400 and EASA AD 2007-0114 
were issued to mandate specific inspections and to obtain a fleet 
status. Since the issuance of AD 2007-0114, the data reporting 
proved that it was necessary to establish repetitive inspections.
    Thus, in addition to an extended applicability, the present AD 
mandates repetitive inspections of the upper wing strut fitting for 
cracks, wear and/or corrosion and examination of the spherical 
bearing and replacement of cracked fittings.

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) since 
September 26, 2007 (the effective date of this AD) or inspected 
using an eddy current inspection method following Pilatus Aircraft 
Ltd. Service Bulletin No. 57-004, dated April 16, 2007, within the 
last 100 hours TIS since September 26, 2007 (the effective date of 
this AD): Before further flight after September 26, 2007 (the 
effective date of this AD), visually inspect the upper wing strut 
fittings and examine the spherical bearings following Pilatus 
Aircraft Ltd. Service Bulletin No. 57-005, dated August 30, 2007.
    (2) For all airplanes: Within 25 hours TIS after September 26, 
2007 (the effective date of this AD) or within 30 days after 
September 26, 2007 (the effective date of this AD), whichever occurs 
first, visually and using eddy current methods, inspect the upper 
wing strut fittings and examine the spherical bearings following 
Pilatus Aircraft Ltd. Service Bulletin No. 57-005, dated August 30, 
2007.
    (3) For all airplanes: After doing the inspection specified in 
paragraph (f)(2) of this AD, repetitively at intervals not to exceed 
100 hours TIS or 3 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. 
Service Bulletin No. 57-005, dated August 30, 2007.
    (4) For all airplanes: If during any inspection required by 
paragraph (f)(1), (f)(2), or (f)(3) of this AD cracks are found in 
the upper wing strut fitting, before further flight, replace the 
wing strut fitting following the Accomplishment Instructions in 
Pilatus Aircraft Ltd. Service Bulletin No. 57-005, dated August 30, 
2007. Replacement of one or both upper wing strut fitting(s) does 
not terminate the repetitive inspection specified in paragraph 
(f)(3) of this AD.
    (5) For all airplanes: If during any inspection required by 
paragraph (f)(1), (f)(2), or (f)(3) of this AD the spherical bearing 
is found not in conformity, before further flight, replace the 
bearing following the Accomplishment Instructions in Pilatus 
Aircraft Ltd. Service Bulletin No. 57-005, dated August 30, 2007.

FAA AD Differences

    Note: 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, 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 European Aviation Safety Agency (EASA) AD No: 
2007-0241-E, dated September 05, 2007; Pilatus Aircraft Ltd. Service 
Bulletin No. 57-005, dated August 30, 2007; and Pilatus Aircraft 
Ltd. Service Bulletin No. 57-004, dated April 16, 2007, for related 
information.

Material Incorporated by Reference

    (i) You must use Pilatus Aircraft Ltd. Service Bulletin No. 57-
005, dated August 30, 2007, 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 this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Pilatus Aircraft Ltd.,

[[Page 53923]]

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 at the FAA, Central Region, Office of 
the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 
64106; 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/ibr-locations.html
.

    Issued in Kansas City, Missouri on September 13, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
 [FR Doc. E7-18476 Filed 9-20-07; 8:45 am]

BILLING CODE 4910-13-P