[Federal Register Volume 74, Number 129 (Wednesday, July 8, 2009)]
[Proposed Rules]
[Pages 32471-32474]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-16142]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 74, No. 129 / Wednesday, July 8, 2009 /
Proposed Rules
[[Page 32471]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0622; Directorate Identifier 2009-CE-034-AD]
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: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above that would supersede an existing AD. This
proposed AD results from mandatory continuing airworthiness information
(MCAI) originated 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.
The proposed AD would require actions that are intended to address
the unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by August 7, 2009.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
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.
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 this proposed 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, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4059; fax: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0622;
Directorate Identifier 2009-CE-034-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On September 13, 2007, we issued AD 2007-19-14, Amendment 39-15205
(72 FR 53920; September 21, 2007), which superseded AD 2007-15-09,
Amendment 39-15138 (72 FR 41436; July 30, 2007), issued on July 19,
2007. AD 2007-15-09 superseded AD 2007-03-08, Amendment 39-14919 (72 FR
4635; February 1, 2007), issued January 24, 2007. Those ADs required
actions intended to address an unsafe condition on the products listed
above.
Since we issued AD 2007-19-14, Pilatus has developed new wing strut
fittings that require repetitive visual and eddy current inspections.
In addition, fatigue test results show the eddy current repetitive
inspection interval for the old wing strut fittings can be extended to
1,100 hours time-in-service (TIS) or 12 calendar months, whichever
occurs first.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued AD
No.: 2007-0241R3, dated May 6, 2009 (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 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
[[Page 32472]]
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.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Pilatus Aircraft Ltd. has issued 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,
dated November 30, 2008 (referenced as revision 9 in EASA AD No.: 2007-
0241R3). 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 Proposed 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 proposing this AD because
we evaluated all information and determined the unsafe condition exists
and is likely to exist or develop on other products of the same type
design.
Differences Between This Proposed 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 proposed 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 proposed AD.
Costs of Compliance
We estimate that this proposed AD will affect 50 products of U.S.
registry. We also estimate that it would take about 7 work-hours per
product to comply with the basic requirements of this proposed 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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 proposed 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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing Amendment 39-15205 (72 FR
53920; September 21, 2007), and adding the following new AD:
Pilatus Aircraft Ltd.: Docket No. FAA-2009-0622; Directorate
Identifier 2009-CE-034-AD.
Comments Due Date
(a) We must receive comments by August 7, 2009.
Affected ADs
(b) This AD supersedes AD 2007-19-14, Amendment 39-15205 (72 FR
53920; September 21, 2007).
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.
[[Page 32473]]
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 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 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 paragraph (f)(1), (f)(2), or (f)(3) of this
AD if done before 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
paragraph (f)(1), (f)(2), or (f)(3) of this AD you find the
following conditions, before further flight, replace the specified
part 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):
(i) Cracks in the upper wing strut fitting; or
(ii) The spherical bearing is not in conformity.
(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: 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 European Aviation Safety Agency (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
[[Page 32474]]
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. Issued in
Kansas City, Missouri, on July 1, 2009.
Scott A. Horn,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-16142 Filed 7-7-09; 8:45 am]
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