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, 1990-1993 [2010-33333]
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<![CDATA[
1990
Federal Register / Vol. 76, No. 8 / Wednesday, January 12, 2011 / Rules and Regulations
TABLE 6—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE
Document
Date
Manual
Shorts Advance Amendment Bulletin 1/2004 ....
July 13, 2004 ....................................................
Shorts
Shorts
Shorts
Shorts
Shorts
Shorts
Shorts
Shorts
14.
Shorts
15.
Shorts
Shorts
Shorts
Shorts
Shorts
Shorts
Advance Amendment Bulletin 1/2004 ....
Advance Amendment Bulletin 1/2004 ....
Advance Amendment Bulletin 1/2004 ....
Temporary Revision TR330–AMM–13 ...
Temporary Revision TR330–AMM–14 ...
Temporary Revision TR360–AMM–33 ...
Temporary Revision TR360–AMM–34 ...
Temporary Revision TRSD360S–AMM–
July 13, 2004 ....................................................
July 13, 2004 ....................................................
July 13, 2004 ....................................................
June 21, 2004 ..................................................
June 21, 2004 ..................................................
July 27, 2004 ....................................................
July 27, 2004 ....................................................
July 29, 2004 ....................................................
Shorts Airplane Flight Manuals (AFMs)
SBH.3.2, SBH.3.3, SBH.3.6, SBH.3.7,
SBH.3.8, and SB.3.9.
Shorts AFMs SB.4.3, SB.4.6, and SB.4.8.
Shorts AFM SB.5.2.
Shorts AFM SB.6.2.
SD3–30 AMM.
SD3–30 AMM.
SD3–60 AMM.
SD3–60 AMM.
SD3–60 SHERPA AMM.
Temporary Revision TRSD360S–AMM–
July 29, 2004 ....................................................
SD3–60 SHERPA AMM.
Temporary Revision TRSD3S–AMM–15
Temporary Revision TRSD3S–AMM–16
Service Bulletin SD330–28–37 ..............
Service Bulletin SD360–28–23 ..............
Service Bulletin SD360 SHERPA–28–3
Service Bulletin SD3 SHERPA–28–2 ....
July 28, 2004 ....................................................
July 28, 2004 ....................................................
June 2004 ........................................................
June 2004 ........................................................
June 2004 ........................................................
June 2004 ........................................................
SD3 SHERPA AMM.
SD3 SHERPA AMM.
None.
None.
None.
None.
DEPARTMENT OF TRANSPORTATION
leading to failure of the wing structure and
subsequent loss of control of the aircraft.
To address this problem, FOCA published
AD TM–L Nr. 80.627–6/Index 72–2 and HB–
2006–400 and EASA published AD 2007–
0114 to require specific inspections and to
obtain a fleet status. Since the issuance of AD
2007–0114, the reported data proved that it
was necessary to establish and require
repetitive inspections.
EASA published Emergency AD 2007–
0241–E to extend the applicability and to
require repetitive eddy current and visual
inspections of the upper wing strut fitting for
evidence of cracks, wear and/or corrosion
and examination of the spherical bearing and
replacement of cracked fittings. Collected
data received in response to Emergency AD
2007–0241–E resulted in the issuance of
EASA AD 2007–0241R1 that permitted
extending the intervals for the repetitive
eddy current and visual inspections from 100
Flight Hours (FH) to 300 FH and from 150
Flight Cycles (FC) to 450 FC, respectively. In
addition, oversize bolts were introduced by
Pilatus PC–6 Service Bulletin (SB) 57–005 R1
and the fitting replacement procedure was
adjusted accordingly.
Based on fatigue test results, EASA AD
2007–0241R2 was issued to extend the
repetitive inspection interval to 1100 FH or
12 calendar months, whichever occurs first,
and to delete the related flight cycle intervals
and the requirement for the ‘‘Mild Corrosion
Severity Zone’’. In addition, some editorial
changes have been made for reasons of
standardization and readability.
Revision 3 of this AD referred to the latest
revision of the PC–6 Aircraft Maintenance
Manual (AMM) Chapter 5 limitations which
have included the same repetitive inspection
intervals and procedures already mandated
in the revision 2 of AD 2007–0241. Besides
the inspections, in the latest revision of the
PC–6 AMM, the replacement procedures for
the fittings were included.
Additionally, EASA AD 2007–0241R3
introduced the possibility to replace the wing
strut fitting with a new designed wing strut
(3) For service information identified in
this AD, contact Short Brothers PLC,
Airworthiness, P.O. Box 241, Airport Road,
Belfast, BT3 9DZ Northern Ireland; telephone
+44(0)2890–462469; fax +44(0)2890–468444;
e-mail
michael.mulholland@aero.bombardier.com;
Internet https://www.bombardier.com.
(4) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
(5) You may also review copies of the
service information that is incorporated by
reference 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 Renton, Washington, on
November 10, 2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2011–30 Filed 1–11–11; 8:45 am]
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BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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:
SUMMARY:
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,
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Federal Register / Vol. 76, No. 8 / Wednesday, January 12, 2011 / Rules and Regulations
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 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 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: https://www.pilatusaircraft.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:
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Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on October 7, 2010 (75 FR
62005), and proposed to revise AD
2009–18–03, Amendment 39–15999 (74
FR 43636, August 27, 2009).
Since we issued AD 2009–18–03,
Pilatus has updated their maintenance
programs with new requirements and
limitations. Another AD action, AD
2011–01–14, requires the incorporation
of the updated maintenance
requirements into the airworthiness
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16:46 Jan 11, 2011
Jkt 223001
limitations section of the instructions
for continued airworthiness. Those
updated maintenance requirements
include the repetitive inspections for
the wing strut fittings and the spherical
bearings currently included in AD
2009–18–03.
The NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states that:
Findings of corrosion, wear and cracks in
the upper wing strut fittings on some PC–6
aircraft have been reported in the past. It is
possible that the spherical bearing of the
wing strut fittings installed in the underwing
can be loose in the fitting or cannot rotate
because of corrosion. In this condition, the
joint cannot function as designed and fatigue
cracks may then develop. Undetected cracks,
wear and/or corrosion in this area could
cause failure of the upper attachment fitting,
leading to failure of the wing structure and
subsequent loss of control of the aircraft.
To address this problem, FOCA published
AD TM–L Nr. 80.627–6/Index 72–2 and HB–
2006–400 and EASA published AD 2007–
0114 to require specific inspections and to
obtain a fleet status. Since the issuance of AD
2007–0114, the reported data proved that it
was necessary to establish and require
repetitive inspections.
EASA published Emergency AD 2007–
0241–E to extend the applicability and to
require repetitive eddy current and visual
inspections of the upper wing strut fitting for
evidence of cracks, wear and/or corrosion
and examination of the spherical bearing and
replacement of cracked fittings. Collected
data received in response to Emergency AD
2007–0241–E resulted in the issuance of
EASA AD 2007–0241R1 that permitted
extending the intervals for the repetitive
eddy current and visual inspections from 100
Flight Hours (FH) to 300 FH and from 150
Flight Cycles (FC) to 450 FC, respectively. In
addition, oversize bolts were introduced by
Pilatus PC–6 Service Bulletin (SB) 57–005 R1
and the fitting replacement procedure was
adjusted accordingly.
Based on fatigue test results, EASA AD
2007–0241R2 was issued to extend the
repetitive inspection interval to 1100 FH or
12 calendar months, whichever occurs first,
and to delete the related flight cycle intervals
and the requirement for the ‘‘Mild Corrosion
Severity Zone’’. In addition, some editorial
changes have been made for reasons of
standardization and readability.
Revision 3 of this AD referred to the latest
revision of the PC–6 Aircraft Maintenance
Manual (AMM) Chapter 5 limitations which
have included the same repetitive inspection
intervals and procedures already mandated
in the revision 2 of AD 2007–0241. Besides
the inspections, in the latest revision of the
PC–6 AMM, the replacement procedures for
the fittings were included.
Additionally, EASA AD 2007–0241R3
introduced the possibility to replace the wing
strut fitting with a new designed wing strut
fitting. With this optional part replacement,
in the repetitive inspection procedure the
1100 FH interval is deleted so that only
calendar defined intervals of inspections
remained applicable.
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1991
The aim of this new revision is to only
mandate the initial inspection requirement
and consequently to limit its applicability to
aeroplanes which are not already in
compliance with EASA AD 2007–0241R3.
All aeroplanes which are in compliance with
EASA AD 2007–0241R3 have to follow the
repetitive inspection requirements as
described in Pilatus PC–6 AMM Chapter 04–
00–00, Document Number 01975, Revision
12 and the Airworthiness Limitations (ALS)
Document Number 02334 Revision 1
mandated by EASA AD 2010–0176.
Therefore the repetitive inspection
requirements corresponding paragraphs have
been deleted in this new EASA AD revision.
The paragraph numbers of EASA AD 2007–
0241R numbering has been maintained for
referencing needs.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received.
Request for Clarification on
Applicability
Pilatus Aircraft commented that there
is no consistency between FAA
Directorate Identifier 2010–CE–047–AD
and FAA Directorate Identifier 2009–
CE–034–AD regarding the applicability
of airplanes in regards to the
manufacturer serial numbers (MSN) on
the Fairchild PC–6 airplanes.
The FAA agrees that the applicability
of airplanes needs corrected. We will
change the applicability to clarify that
some specific MSNs can also be
identified as Fairchild Republic
Company PC–6 airplanes, Fairchild
Industries PC–6 airplanes, Fairchild
Heli Porter PC–6 airplanes, or FairchildHiller Corporation PC–6 airplanes.
Conclusion
We reviewed the available data,
including the comment received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
We determined that these changes will
not increase the economic burden on
any operator or increase the scope of the
AD.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
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Federal Register / Vol. 76, No. 8 / Wednesday, January 12, 2011 / Rules and Regulations
MCAI in order to follow FAA policies.
Any such differences are highlighted in
a NOTE within the AD.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD Docket.
Subject
(d) Air Transport Association of America
(ATA) Code 57: Wings.
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 $85 per work-hour.
Based on these figures, we estimate
the cost of this AD on U.S. operators to
be $29,750, or $595 per product.
In addition, we estimate that any
necessary follow-on actions will take
about 30 work-hours and require parts
costing $5,000, for a cost of $7,550 per
product. We have no way of
determining the number of products
that may need these actions.
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.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Findings of corrosion, wear and cracks in
the upper wing strut fittings on some PC–6
aircraft have been reported in the past. It is
possible that the spherical bearing of the
wing strut fittings installed in the underwing
can be loose in the fitting or cannot rotate
because of corrosion. In this condition, the
joint cannot function as designed and fatigue
cracks may then develop. Undetected cracks,
wear and/or corrosion in this area could
cause failure of the upper attachment fitting,
leading to failure of the wing structure and
subsequent loss of control of the aircraft.
To address this problem, FOCA published
AD TM–L Nr. 80.627–6/Index 72–2 and HB–
2006–400 and EASA published AD 2007–
0114 to require specific inspections and to
obtain a fleet status. Since the issuance of AD
2007–0114, the reported data proved that it
was necessary to establish and require
repetitive inspections.
EASA published Emergency AD 2007–
0241–E to extend the applicability and to
require repetitive eddy current and visual
inspections of the upper wing strut fitting for
evidence of cracks, wear and/or corrosion
and examination of the spherical bearing and
replacement of cracked fittings. Collected
data received in response to Emergency AD
2007–0241–E resulted in the issuance of
EASA AD 2007–0241R1 that permitted
extending the intervals for the repetitive
eddy current and visual inspections from 100
Flight Hours (FH) to 300 FH and from 150
Flight Cycles (FC) to 450 FC, respectively. In
addition, oversize bolts were introduced by
Pilatus PC–6 Service Bulletin (SB) 57–005 R1
and the fitting replacement procedure was
adjusted accordingly.
Based on fatigue test results, EASA AD
2007–0241R2 was issued to extend the
repetitive inspection interval to 1100 FH or
12 calendar months, whichever occurs first,
and to delete the related flight cycle intervals
and the requirement for the ‘‘Mild Corrosion
Severity Zone’’. In addition, some editorial
changes have been made for reasons of
standardization and readability.
Revision 3 of this AD referred to the latest
revision of the PC–6 Aircraft Maintenance
Manual (AMM) Chapter 5 limitations which
have included the same repetitive inspection
intervals and procedures already mandated
in the revision 2 of AD 2007–0241. Besides
the inspections, in the latest revision of the
PC–6 AMM, the replacement procedures for
the fittings were included.
Additionally, EASA AD 2007–0241R3
introduced the possibility to replace the wing
strut fitting with a new designed wing strut
fitting. With this optional part replacement,
in the repetitive inspection procedure the
1100 FH interval is deleted so that only
calendar defined intervals of inspections
remained applicable.
The aim of this new revision is to only
mandate the initial inspection requirement
and consequently to limit its applicability to
aeroplanes which are not already in
Authority for This Rulemaking
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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.
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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 39–15999 (74 FR
43636, August 27, 2009) and adding the
following new AD:
■
2009–18–03 R1 Pilatus Aircraft Limited:
Amendment 39–16570; Docket No.
FAA–2009–0622; Directorate Identifier
2009–CE–034–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective February 16, 2011.
Affected ADs
(b) This AD revises AD 2009–18–03,
Amendment 39–15999.
Applicability
(c) This AD applies to Pilatus Aircraft Ltd.
Models PC–6, PC–6–H1, PC–6–H2, PC–6/350,
PC–6/350–H1, PC–6/350–H2, PC–6/A, PC–6/
A–H1, PC–6/A–H2, PC–6/B–H2, PC–6/B1–
H2, PC–6/B2–H2, PC–6/B2–H4, PC–6/C–H2,
and PC–6/C1–H2 airplanes, all manufacturer
serial number (MSN) 101 through 999, and
MSN 2001 through 2092, certificated in any
category.
Note 1: For MSN 2001–2092, these
airplanes are also identified as Fairchild
Republic Company PC–6 airplanes, Fairchild
Industries PC–6 airplanes, Fairchild Heli
Porter PC–6 airplanes, or Fairchild-Hiller
Corporation PC–6 airplanes.
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Federal Register / Vol. 76, No. 8 / Wednesday, January 12, 2011 / Rules and Regulations
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compliance with EASA AD 2007–0241R3.
All aeroplanes which are in compliance with
EASA AD 2007–0241R3 have to follow the
repetitive inspection requirements as
described in Pilatus PC–6 AMM Chapter 04–
00–00, Document Number 01975, Revision
12 and the Airworthiness Limitations (ALS)
Document Number 02334 Revision 1
mandated by EASA AD 2010–0176.
Therefore the repetitive inspection
requirements corresponding paragraphs have
been deleted in this new EASA AD revision.
The paragraph numbers of EASA AD 2007–
0241R numbering has been maintained for
referencing needs.
This AD requires actions that are intended to
address the unsafe condition described in the
MCAI.
Actions and Compliance
(f) Unless already done, do the following
actions:
(1) For affected airplanes that have not had
both wing strut fittings replaced within the
last 100 hours time-in-service (TIS) before
September 26, 2007 (the effective date of AD
2007–19–14), or have not been inspected
using an eddy current inspection method
following Pilatus Aircraft Ltd. Pilatus PC–6
Service Bulletin No. 57–004, dated April 16,
2007, within the last 100 hours TIS before
September 26, 2007 (the effective date of AD
2007–19–14): Before further flight after either
September 26, 2007 (the effective date of AD
2007–19–14), or October 1, 2009 (the
effective date of AD 2009–18–03), visually
inspect the upper wing strut fittings and
examine the spherical bearings following the
Pilatus Aircraft Ltd. Pilatus PC–6 Service
Bulletin No. 57–005, REV No. 2, dated May
19, 2008.
(2) For all affected airplanes: Within 25
hours TIS after September 26, 2007 (the
effective date of AD 2007–19–14), or within
30 days after September 26, 2007 (the
effective date of AD 2007–19–14), whichever
occurs first, visually and using eddy current
methods, inspect the upper wing strut fittings
and examine the spherical bearings following
Pilatus Aircraft Ltd. Pilatus PC–6 Service
Bulletin No. 57–005, REV No. 2, dated May
19, 2008.
(3) You may also take ‘‘unless already
done’’ credit for any inspection specified in
paragraphs (f)(1) or (f)(2) of this AD if done
before October 1, 2009 (the effective date
retained from AD 2009–18–03) following
Pilatus Aircraft Ltd. Pilatus PC–6 Service
Bulletin No. 57–005, dated August 30, 2007;
or Pilatus Aircraft Ltd. Pilatus PC–6 Service
Bulletin No. 57–005, REV No. 1, dated
November 19, 2007.
(4) For all affected airplanes: If during any
inspection required by paragraphs (f)(1) or
(f)(2) of this AD you find cracks in the upper
wing strut fitting or the spherical bearing is
not in conformity, before further flight,
replace the cracked upper wing strut fitting
and/or the nonconforming spherical bearing
following Chapter 57–00–02 of Pilatus
Aircraft Ltd. Pilatus PC–6 Aircraft
Maintenance Manual, dated November 30,
2008.
Note 1: AD 2011–01–14 requires the
incorporation of the updated maintenance
requirements into the airworthiness
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limitations section of the instructions for
continued airworthiness. Those updated
maintenance requirements include the
repetitive inspections for the wing strut
fittings and the spherical bearings. This
revised AD removes those repetitive
inspections.
FAA AD Differences
Note 2: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
Attn: Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4059; fax: (816) 329–
4090. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, a federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave., SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
Related Information
(h) Refer to MCAI EASA AD No.: 2007–
0241R4, dated August 31, 2010; Pilatus
Aircraft Ltd. Pilatus PC–6 Service Bulletin
No. 57–005, REV No. 2, dated May 19, 2008;
Pilatus Aircraft Ltd. Pilatus PC–6 Service
Bulletin No. 57–005, REV No. 1, dated
November 19, 2007; Pilatus Aircraft Ltd.
Pilatus PC–6 Service Bulletin No. 57–005,
dated August 30, 2007; Pilatus Aircraft Ltd.
Pilatus PC–6 Service Bulletin No. 57–004,
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
1993
dated April 16, 2007; and Chapter 57–00–02
of Pilatus Aircraft Ltd. Pilatus PC–6 Aircraft
Maintenance Manual, dated November 30,
2008, for related information.
Material Incorporated by Reference
(h) You must use Pilatus Aircraft Ltd.
Pilatus PC–6 Service Bulletin No. 57–005,
REV No. 2, dated May 19, 2008; and Chapter
57–00–02 of Pilatus Aircraft Ltd. Pilatus PC–
6 Aircraft Maintenance Manual, dated
November 30, 2008 (referenced as revision 9
in EASA AD No.: 2007–0241R3), to do the
actions required by this AD, unless the AD
specifies otherwise.
(1) On October 1, 2009 (74 FR 43636,
August 27, 2009), the Director of the Federal
Register previously approved the
incorporation by reference of Pilatus Aircraft
Ltd. Pilatus PC–6 Service Bulletin No. 57–
005, REV No. 2, dated May 19, 2008; and
Chapter 57–00–02 of Pilatus Aircraft Ltd.
Pilatus PC–6 Aircraft Maintenance Manual,
dated November 30, 2008 (referenced as
revision 9 in EASA AD No.: 2007–0241R3).
(2) For service information identified in
this AD, contact PILATUS AIRCRAFT LTD.,
Customer Service Manager, CH–6371
STANS, Switzerland; telephone: +41 (0) 41
619 65 01; fax: +41 (0) 41 619 65 76; Internet:
https://www.pilatus-aircraft.com.
(3) You may review copies of the
referenced service information at the FAA,
Small Airplane Directorate, 901 Locust,
Kansas City, Missouri 64106. For information
on the availability of this material at the
FAA, call 816–329–4148.
(4) You may also review copies of the
service information incorporated by reference
for this AD at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call (202) 741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Kansas City, Missouri, on
December 28, 2010.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2010–33333 Filed 1–11–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0549; Directorate
Identifier 2010–NM–109–AD; Amendment
39–16573; AD 2011–01–16]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model DC–9–81 (MD–81),
DC–9–82 (MD–82), DC–9–83 (MD–83),
DC–9–87 (MD–87), and MD–88
Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
E:\FR\FM\12JAR1.SGM
12JAR1
]]>Agencies
[Federal Register Volume 76, Number 8 (Wednesday, January 12, 2011)]
[Rules and Regulations]
[Pages 1990-1993]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-33333]
-----------------------------------------------------------------------
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 extending the intervals for the
repetitive eddy current and visual inspections from 100 Flight Hours
(FH) to 300 FH and from 150 Flight Cycles (FC) to 450 FC,
respectively. In addition, oversize bolts were introduced by Pilatus
PC-6 Service Bulletin (SB) 57-005 R1 and the fitting replacement
procedure was adjusted accordingly.
Based on fatigue test results, EASA AD 2007-0241R2 was issued to
extend the repetitive inspection interval to 1100 FH or 12 calendar
months, whichever occurs first, and to delete the related flight
cycle intervals and the requirement for the ``Mild Corrosion
Severity Zone''. In addition, some editorial changes have been made
for reasons of standardization and readability.
Revision 3 of this AD referred to the latest revision of the PC-
6 Aircraft Maintenance Manual (AMM) Chapter 5 limitations which have
included the same repetitive inspection intervals and procedures
already mandated in the revision 2 of AD 2007-0241. Besides the
inspections, in the latest revision of the PC-6 AMM, the replacement
procedures for the fittings were included.
Additionally, EASA AD 2007-0241R3 introduced the possibility to
replace the wing strut fitting with a new designed wing strut
[[Page 1991]]
fitting. With this optional part replacement, in the repetitive
inspection procedure the 1100 FH interval is deleted so that only
calendar defined intervals of inspections remained applicable.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective February 16, 2011.
As of October 1, 2009 (74 FR 43636, August 27, 2009), the Director
of the Federal Register approved the incorporation by reference of
Pilatus Aircraft Ltd. Pilatus PC-6 Service Bulletin No. 57-005, REV No.
2, dated May 19, 2008; and Chapter 57-00-02 of Pilatus Aircraft Ltd.
Pilatus PC-6 Aircraft Maintenance Manual, dated November 30, 2008
(referenced as revision 9 in EASA AD No.: 2007-0241R3) listed in this
AD.
ADDRESSES: You may examine the AD docket on the Internet at 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 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:
https://www.pilatus-aircraft.com. You may review copies of the
referenced service information at the FAA, Small Airplane Directorate,
901 Locust, Kansas City, Missouri 64106. For information on the
availability of this material at the FAA, call 816-329-4148.
FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, 901
Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-
4059; fax: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on October 7, 2010 (75
FR 62005), and proposed to revise AD 2009-18-03, Amendment 39-15999 (74
FR 43636, August 27, 2009).
Since we issued AD 2009-18-03, Pilatus has updated their
maintenance programs with new requirements and limitations. Another AD
action, AD 2011-01-14, requires the incorporation of the updated
maintenance requirements into the airworthiness limitations section of
the instructions for continued airworthiness. Those updated maintenance
requirements include the repetitive inspections for the wing strut
fittings and the spherical bearings currently included in AD 2009-18-
03.
The NPRM proposed to correct an unsafe condition for the specified
products. The MCAI states that:
Findings of corrosion, wear and cracks in the upper wing strut
fittings on some PC-6 aircraft have been reported in the past. It is
possible that the spherical bearing of the wing strut fittings
installed in the underwing can be loose in the fitting or cannot
rotate because of corrosion. In this condition, the joint cannot
function as designed and fatigue cracks may then develop. Undetected
cracks, wear and/or corrosion in this area could cause failure of
the upper attachment fitting, leading to failure of the wing
structure and subsequent loss of control of the aircraft.
To address this problem, FOCA published AD TM-L Nr. 80.627-6/
Index 72-2 and HB-2006-400 and EASA published AD 2007-0114 to
require specific inspections and to obtain a fleet status. Since the
issuance of AD 2007-0114, the reported data proved that it was
necessary to establish and require repetitive inspections.
EASA published Emergency AD 2007-0241-E to extend the
applicability and to require repetitive eddy current and visual
inspections of the upper wing strut fitting for evidence of cracks,
wear and/or corrosion and examination of the spherical bearing and
replacement of cracked fittings. Collected data received in response
to Emergency AD 2007-0241-E resulted in the issuance of EASA AD
2007-0241R1 that permitted extending the intervals for the
repetitive eddy current and visual inspections from 100 Flight Hours
(FH) to 300 FH and from 150 Flight Cycles (FC) to 450 FC,
respectively. In addition, oversize bolts were introduced by Pilatus
PC-6 Service Bulletin (SB) 57-005 R1 and the fitting replacement
procedure was adjusted accordingly.
Based on fatigue test results, EASA AD 2007-0241R2 was issued to
extend the repetitive inspection interval to 1100 FH or 12 calendar
months, whichever occurs first, and to delete the related flight
cycle intervals and the requirement for the ``Mild Corrosion
Severity Zone''. In addition, some editorial changes have been made
for reasons of standardization and readability.
Revision 3 of this AD referred to the latest revision of the PC-
6 Aircraft Maintenance Manual (AMM) Chapter 5 limitations which have
included the same repetitive inspection intervals and procedures
already mandated in the revision 2 of AD 2007-0241. Besides the
inspections, in the latest revision of the PC-6 AMM, the replacement
procedures for the fittings were included.
Additionally, EASA AD 2007-0241R3 introduced the possibility to
replace the wing strut fitting with a new designed wing strut
fitting. With this optional part replacement, in the repetitive
inspection procedure the 1100 FH interval is deleted so that only
calendar defined intervals of inspections remained applicable.
The aim of this new revision is to only mandate the initial
inspection requirement and consequently to limit its applicability
to aeroplanes which are not already in compliance with EASA AD 2007-
0241R3. All aeroplanes which are in compliance with EASA AD 2007-
0241R3 have to follow the repetitive inspection requirements as
described in Pilatus PC-6 AMM Chapter 04-00-00, Document Number
01975, Revision 12 and the Airworthiness Limitations (ALS) Document
Number 02334 Revision 1 mandated by EASA AD 2010-0176. Therefore the
repetitive inspection requirements corresponding paragraphs have
been deleted in this new EASA AD revision. The paragraph numbers of
EASA AD 2007-0241R numbering has been maintained for referencing
needs.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received.
Request for Clarification on Applicability
Pilatus Aircraft commented that there is no consistency between FAA
Directorate Identifier 2010-CE-047-AD and FAA Directorate Identifier
2009-CE-034-AD regarding the applicability of airplanes in regards to
the manufacturer serial numbers (MSN) on the Fairchild PC-6 airplanes.
The FAA agrees that the applicability of airplanes needs corrected.
We will change the applicability to clarify that some specific MSNs can
also be identified as Fairchild Republic Company PC-6 airplanes,
Fairchild Industries PC-6 airplanes, Fairchild Heli Porter PC-6
airplanes, or Fairchild-Hiller Corporation PC-6 airplanes.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting the
AD with the changes described previously. We determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the
[[Page 1992]]
MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect 50 products of U.S. registry.
We also estimate that it will take about 7 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour.
Based on these figures, we estimate the cost of this AD on U.S.
operators to be $29,750, or $595 per product.
In addition, we estimate that any necessary follow-on actions will
take about 30 work-hours and require parts costing $5,000, for a cost
of $7,550 per product. We have no way of determining the number of
products that may need these actions.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD Docket.
Examining the AD Docket
You may examine the AD docket on the Internet at 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 39-15999 (74 FR
43636, August 27, 2009) and adding the following new AD:
2009-18-03 R1 Pilatus Aircraft Limited: Amendment 39-16570; Docket
No. FAA-2009-0622; Directorate Identifier 2009-CE-034-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective February
16, 2011.
Affected ADs
(b) This AD revises AD 2009-18-03, Amendment 39-15999.
Applicability
(c) This AD applies to Pilatus Aircraft Ltd. Models PC-6, PC-6-
H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1,
PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2,
and PC-6/C1-H2 airplanes, all manufacturer serial number (MSN) 101
through 999, and MSN 2001 through 2092, certificated in any
category.
Note 1: For MSN 2001-2092, these airplanes are also identified
as Fairchild Republic Company PC-6 airplanes, Fairchild Industries
PC-6 airplanes, Fairchild Heli Porter PC-6 airplanes, or Fairchild-
Hiller Corporation PC-6 airplanes.
Subject
(d) Air Transport Association of America (ATA) Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Findings of corrosion, wear and cracks in the upper wing strut
fittings on some PC-6 aircraft have been reported in the past. It is
possible that the spherical bearing of the wing strut fittings
installed in the underwing can be loose in the fitting or cannot
rotate because of corrosion. In this condition, the joint cannot
function as designed and fatigue cracks may then develop. Undetected
cracks, wear and/or corrosion in this area could cause failure of
the upper attachment fitting, leading to failure of the wing
structure and subsequent loss of control of the aircraft.
To address this problem, FOCA published AD TM-L Nr. 80.627-6/
Index 72-2 and HB-2006-400 and EASA published AD 2007-0114 to
require specific inspections and to obtain a fleet status. Since the
issuance of AD 2007-0114, the reported data proved that it was
necessary to establish and require repetitive inspections.
EASA published Emergency AD 2007-0241-E to extend the
applicability and to require repetitive eddy current and visual
inspections of the upper wing strut fitting for evidence of cracks,
wear and/or corrosion and examination of the spherical bearing and
replacement of cracked fittings. Collected data received in response
to Emergency AD 2007-0241-E resulted in the issuance of EASA AD
2007-0241R1 that permitted extending the intervals for the
repetitive eddy current and visual inspections from 100 Flight Hours
(FH) to 300 FH and from 150 Flight Cycles (FC) to 450 FC,
respectively. In addition, oversize bolts were introduced by Pilatus
PC-6 Service Bulletin (SB) 57-005 R1 and the fitting replacement
procedure was adjusted accordingly.
Based on fatigue test results, EASA AD 2007-0241R2 was issued to
extend the repetitive inspection interval to 1100 FH or 12 calendar
months, whichever occurs first, and to delete the related flight
cycle intervals and the requirement for the ``Mild Corrosion
Severity Zone''. In addition, some editorial changes have been made
for reasons of standardization and readability.
Revision 3 of this AD referred to the latest revision of the PC-
6 Aircraft Maintenance Manual (AMM) Chapter 5 limitations which have
included the same repetitive inspection intervals and procedures
already mandated in the revision 2 of AD 2007-0241. Besides the
inspections, in the latest revision of the PC-6 AMM, the replacement
procedures for the fittings were included.
Additionally, EASA AD 2007-0241R3 introduced the possibility to
replace the wing strut fitting with a new designed wing strut
fitting. With this optional part replacement, in the repetitive
inspection procedure the 1100 FH interval is deleted so that only
calendar defined intervals of inspections remained applicable.
The aim of this new revision is to only mandate the initial
inspection requirement and consequently to limit its applicability
to aeroplanes which are not already in
[[Page 1993]]
compliance with EASA AD 2007-0241R3. All aeroplanes which are in
compliance with EASA AD 2007-0241R3 have to follow the repetitive
inspection requirements as described in Pilatus PC-6 AMM Chapter 04-
00-00, Document Number 01975, Revision 12 and the Airworthiness
Limitations (ALS) Document Number 02334 Revision 1 mandated by EASA
AD 2010-0176. Therefore the repetitive inspection requirements
corresponding paragraphs have been deleted in this new EASA AD
revision. The paragraph numbers of EASA AD 2007-0241R numbering has
been maintained for referencing needs.
This AD requires actions that are intended to address the unsafe
condition described in the MCAI.
Actions and Compliance
(f) Unless already done, do the following actions:
(1) For affected airplanes that have not had both wing strut
fittings replaced within the last 100 hours time-in-service (TIS)
before September 26, 2007 (the effective date of AD 2007-19-14), or
have not been inspected using an eddy current inspection method
following Pilatus Aircraft Ltd. Pilatus PC-6 Service Bulletin No.
57-004, dated April 16, 2007, within the last 100 hours TIS before
September 26, 2007 (the effective date of AD 2007-19-14): Before
further flight after either September 26, 2007 (the effective date
of AD 2007-19-14), or October 1, 2009 (the effective date of AD
2009-18-03), visually inspect the upper wing strut fittings and
examine the spherical bearings following the Pilatus Aircraft Ltd.
Pilatus PC-6 Service Bulletin No. 57-005, REV No. 2, dated May 19,
2008.
(2) For all affected airplanes: Within 25 hours TIS after
September 26, 2007 (the effective date of AD 2007-19-14), or within
30 days after September 26, 2007 (the effective date of AD 2007-19-
14), whichever occurs first, visually and using eddy current
methods, inspect the upper wing strut fittings and examine the
spherical bearings following Pilatus Aircraft Ltd. Pilatus PC-6
Service Bulletin No. 57-005, REV No. 2, dated May 19, 2008.
(3) You may also take ``unless already done'' credit for any
inspection specified in paragraphs (f)(1) or (f)(2) of this AD if
done before October 1, 2009 (the effective date retained from AD
2009-18-03) following Pilatus Aircraft Ltd. Pilatus PC-6 Service
Bulletin No. 57-005, dated August 30, 2007; or Pilatus Aircraft Ltd.
Pilatus PC-6 Service Bulletin No. 57-005, REV No. 1, dated November
19, 2007.
(4) For all affected airplanes: If during any inspection
required by paragraphs (f)(1) or (f)(2) of this AD you find cracks
in the upper wing strut fitting or the spherical bearing is not in
conformity, before further flight, replace the cracked upper wing
strut fitting and/or the nonconforming spherical bearing following
Chapter 57-00-02 of Pilatus Aircraft Ltd. Pilatus PC-6 Aircraft
Maintenance Manual, dated November 30, 2008.
Note 1: AD 2011-01-14 requires the incorporation of the updated
maintenance requirements into the airworthiness limitations section
of the instructions for continued airworthiness. Those updated
maintenance requirements include the repetitive inspections for the
wing strut fittings and the spherical bearings. This revised AD
removes those repetitive inspections.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Office, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. Send
information to Attn: Doug Rudolph, Aerospace Engineer, FAA, Small
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4059; fax: (816) 329-4090. Before using
any approved AMOC on any airplane to which the AMOC applies, notify
your appropriate principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, a federal agency may not conduct or sponsor, and a person
is not required to respond to, nor shall a person be subject to a
penalty for failure to comply with a collection of information
subject to the requirements of the Paperwork Reduction Act unless
that collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
Related Information
(h) Refer to MCAI EASA AD No.: 2007-0241R4, dated August 31,
2010; Pilatus Aircraft Ltd. Pilatus PC-6 Service Bulletin No. 57-
005, REV No. 2, dated May 19, 2008; Pilatus Aircraft Ltd. Pilatus
PC-6 Service Bulletin No. 57-005, REV No. 1, dated November 19,
2007; Pilatus Aircraft Ltd. Pilatus PC-6 Service Bulletin No. 57-
005, dated August 30, 2007; Pilatus Aircraft Ltd. Pilatus PC-6
Service Bulletin No. 57-004, dated April 16, 2007; and Chapter 57-
00-02 of Pilatus Aircraft Ltd. Pilatus PC-6 Aircraft Maintenance
Manual, dated November 30, 2008, for related information.
Material Incorporated by Reference
(h) You must use Pilatus Aircraft Ltd. Pilatus PC-6 Service
Bulletin No. 57-005, REV No. 2, dated May 19, 2008; and Chapter 57-
00-02 of Pilatus Aircraft Ltd. Pilatus PC-6 Aircraft Maintenance
Manual, dated November 30, 2008 (referenced as revision 9 in EASA AD
No.: 2007-0241R3), to do the actions required by this AD, unless the
AD specifies otherwise.
(1) On October 1, 2009 (74 FR 43636, August 27, 2009), the
Director of the Federal Register previously approved the
incorporation by reference of Pilatus Aircraft Ltd. Pilatus PC-6
Service Bulletin No. 57-005, REV No. 2, dated May 19, 2008; and
Chapter 57-00-02 of Pilatus Aircraft Ltd. Pilatus PC-6 Aircraft
Maintenance Manual, dated November 30, 2008 (referenced as revision
9 in EASA AD No.: 2007-0241R3).
(2) For service information identified in this AD, contact
PILATUS AIRCRAFT LTD., Customer Service Manager, CH-6371 STANS,
Switzerland; telephone: +41 (0) 41 619 65 01; fax: +41 (0) 41 619 65
76; Internet: https://www.pilatus-aircraft.com.
(3) You may review copies of the referenced service information
at the FAA, Small Airplane Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the availability of this material
at the FAA, call 816-329-4148.
(4) You may also review copies of the service information
incorporated by reference for this AD at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, call (202) 741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Kansas City, Missouri, on December 28, 2010.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010-33333 Filed 1-11-11; 8:45 am]
BILLING CODE 4910-13-P
