Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-6 Airplanes, 47039-47041 [E8-18236]
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Federal Register / Vol. 73, No. 157 / Wednesday, August 13, 2008 / Rules and Regulations
hsrobinson on PROD1PC76 with RULES
Alternative Methods of Compliance
(AMOCs)
(v)(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. 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.
(3) An AMOC that provides an acceptable
level of safety shall be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved previously in
accordance with AD 94–15–06 for airplane
line numbers 630 through 814 inclusive are
approved as AMOCs for the corresponding
provisions of this AD if the AMOC does not
involve using the existing sliding probe
HFEC skin inspection method specified in
Boeing Service Bulletin 747–53A2312,
Revision 2, dated October 8, 1992, or an
earlier version. In addition, the provisions of
paragraph (r) of this AD must be applied to
AMOCs approved previously in accordance
with AD 94–15–06, where applicable.
(5) AMOCs approved previously in
accordance with AD 94–15–06 for airplane
line numbers 201 through 629 inclusive are
approved as AMOCs for the corresponding
provisions of this AD. In addition, the
provisions of paragraph (r) of this AD must
be applied to AMOCs approved previously in
accordance with AD 94–15–06, where
applicable.
Material Incorporated by Reference
(w) You must use Boeing Alert Service
Bulletin 747–53A2312, dated June 12, 1989;
Boeing Service Bulletin 747–53A2312,
Revision 1, including ‘‘Addendum,’’ dated
March 29, 1990; Boeing Service Bulletin 747–
53A2312, including the ‘‘Addendum,’’
Revision 2, dated October 8, 1992; or Boeing
Service Bulletin 747–53A2312, Revision 3,
dated February 8, 2007; as applicable; to
perform the actions that are required by this
AD, unless the AD specifies otherwise. (The
document number and date of Boeing Alert
Service Bulletin 747–53A2312, dated June
12, 1989, are identified only on the first page
of the document; no other page of the
document contains this information.)
(1) The Director of the Federal Register
approved the incorporation by reference of
Boeing Alert Service Bulletin 747–53A2312,
dated June 12, 1989; Boeing Service Bulletin
747–53A2312, Revision 1, including
‘‘Addendum,’’ dated March 29, 1990; and
Boeing Service Bulletin 747–53A2312,
Revision 3, dated February 8, 2007; in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
VerDate Aug<31>2005
15:55 Aug 12, 2008
Jkt 214001
(2) On August 24, 1994 (59 FR 37659, July
25, 1994), the Director of the Federal Register
approved the incorporation by reference of
Boeing Service Bulletin 747–53A2312,
including the ‘‘Addendum,’’ Revision 2,
dated October 8, 1992.
(3) Contact Boeing Commercial Airplanes,
P.O. Box 3707, Seattle, Washington 98124–
2207, for a copy of this service information.
You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on July 23,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–17776 Filed 8–12–08; 8:45 am]
BILLING CODE 4910–13–P
47039
This AD becomes effective
September 17, 2008.
On September 17, 2008, the Director
of the Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; fax: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
DATES:
Discussion
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0626 Directorate
Identifier 2008–CE–035–AD; Amendment
39–15637; AD 2008–16–19]
RIN 2120–AA64
Airworthiness Directives; Pilatus
Aircraft Ltd. Model PC–6 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
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:
This Airworthiness Directive (AD) is
prompted due to the discovery of loose selflocking stop nuts Part Number (P/N)
938.07.65.105 in the tail landing gear fastener
assemblies of some PC–6 aircraft.
It is believed that this occurrence could
also exist in other fastener assemblies using
nuts P/N 938.07.65.105 at various identified
locations in the aircraft.
If left uncorrected, the identified
assemblies may become loose and not
function as designed and could lead to
hazardous situations.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
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Sfmt 4700
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 June 9, 2008 (73 FR 32497).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
This Airworthiness Directive (AD) is
prompted due to the discovery of loose selflocking stop nuts Part Number (P/N)
938.07.65.105 in the tail landing gear fastener
assemblies of some PC–6 aircraft.
It is believed that this occurrence could
also exist in other fastener assemblies using
nuts P/N 938.07.65.105 at various identified
locations in the aircraft.
If left uncorrected, the identified
assemblies may become loose and not
function as designed and could lead to
hazardous situations.
In order to prevent those conditions, the
present AD requires you to replace selflocking stop nuts P/N 938.07.65.105 from the
Tail Landing Gear Assembly, the Parachute
Cable Assembly, the Water Tank Assembly,
the Cable Tensioner Assembly, the Fuel
Filter Assembly, the Hydraulic Pump
Assembly and the Engine Mounts Assembly
in accordance with Pilatus PC–6 Service
Bulletin No. 53–002 Revision 2.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
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13AUR1
47040
Federal Register / Vol. 73, No. 157 / Wednesday, August 13, 2008 / Rules and Regulations
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow FAA policies.
Any such differences are highlighted in
a NOTE within the AD.
Costs of Compliance
Based on the service information, 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 basic
requirements of this AD. The average
labor rate is $80 per work-hour.
Required parts will cost about $310 per
product.
Based on these figures, we estimate
the cost of this AD to the U.S. operators
to be $43,500, or $870 per product.
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.
hsrobinson on PROD1PC76 with RULES
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.
VerDate Aug<31>2005
15:55 Aug 12, 2008
Jkt 214001
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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
2008–16–19 Pilatus Aircraft Ltd.:
Amendment 39–15637; Docket No.
FAA–2008–0626; Directorate Identifier
2008–CE–035–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective September 17, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to 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,
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Fmt 4700
Sfmt 4700
manufacturer serial numbers (MSN) MSN
101 through MSN 949 and MSN 2001
through MSN 2092, certificated in any
category.
Note 1: These airplanes may also be
identified as Fairchild Republic Company
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 53: Fuselage.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
This Airworthiness Directive (AD) is
prompted due to the discovery of loose selflocking stop nuts Part Number (P/N)
938.07.65.105 in the tail landing gear fastener
assemblies of some PC–6 aircraft.
It is believed that this occurrence could
also exist in other fastener assemblies using
nuts P/N 938.07.65.105 at various identified
locations in the aircraft.
If left uncorrected, the identified
assemblies may become loose and not
function as designed and could lead to
hazardous situations.
In order to prevent those conditions, the
present AD requires you replace self-locking
stop nuts P/N 938.07.65.105 from the Tail
Landing Gear Assembly, the Parachute Cable
Assembly, the Water Tank Assembly, the
Cable Tensioner Assembly, the Fuel Filter
Assembly, the Hydraulic Pump Assembly
and the Engine Mounts Assembly in
accordance with Pilatus PC–6 Service
Bulletin No. 53–002 Revision 2.
Actions and Compliance
(f) Unless already done, do the following
actions:
(1) Within the next 12 months after
September 17, 2008 (the effective date of this
AD), inspect and modify the fastener
assemblies as instructed in paragraph 3 of
Pilatus Aircraft Ltd. Pilatus PC–6 Service
Bulletin No. 53–002, Revision No. 2, dated
September 24, 2007.
(2) As of September 17, 2008 (the effective
date of this AD), no person shall install on
any PC–6 series aircraft, water tank
assemblies and hydraulic pump assemblies,
unless they have been previously modified
following paragraph 4 of Pilatus Aircraft Ltd.
Pilatus PC–6 Service Bulletin No. 53–002,
Revision No. 2, dated September 24, 2007.
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;
E:\FR\FM\13AUR1.SGM
13AUR1
Federal Register / Vol. 73, No. 157 / Wednesday, August 13, 2008 / Rules and Regulations
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.: 2008–0083,
dated May 5, 2008; and Pilatus Aircraft Ltd.
Pilatus PC–6 Service Bulletin No. 53–002,
Revision No. 2, dated September 24, 2007, for
related information.
Material Incorporated by Reference
hsrobinson on PROD1PC76 with RULES
(i) You must use Pilatus Aircraft Ltd.
Pilatus PC–6 Service Bulletin No. 53–002,
Revision No. 2, dated September 24, 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.,
Customer Liaison Manager, CH–6371
STANS, Switzerland; telephone: +41 41 619
65 80; fax: +41 41 619 65 76; e-mail:
fodermatt@pilatus-aircraft.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: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on August
1, 2008.
James E. Jackson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–18236 Filed 8–12–08; 8:45 am]
BILLING CODE 4910–13–P
VerDate Aug<31>2005
15:55 Aug 12, 2008
Jkt 214001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0685 Directorate
Identifier 2008–CE–037–AD; Amendment
39–15638; AD 2008–16–20]
RIN 2120–AA64
Airworthiness Directives; Diamond
Aircraft Industries GmbH Model DA 42
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
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:
The original designed bellcrank for the
aileron control system in the wing needed to
be installed with slightly bent rod ends
during production of the aircraft to avoid
friction and possible chafing. In addition to
being a nonpreferable production practice,
this creates the risk of replacement parts
being installed during subsequent in-service
maintenance without being bent or not being
bent correctly. This condition, if not detected
and corrected, could lead to chafing damage
of the aileron control system and consequent
loss of control of the aircraft.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
September 17, 2008.
On September 17, 2008, the Director
of the Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Sarjapur Nagarajan, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4145; fax: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
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47041
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 June 23, 2008 (73 FR 35361).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
The original designed bellcrank for the
aileron control system in the wing needed to
be installed with slightly bent rod ends
during production of the aircraft to avoid
friction and possible chafing. In addition to
being a nonpreferable production practice,
this creates the risk of replacement parts
being installed during subsequent in-service
maintenance without being bent or not being
bent correctly. This condition, if not detected
and corrected, could lead to chafing damage
of the aileron control system and consequent
loss of control of the aircraft.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow FAA policies.
Any such differences are highlighted in
a NOTE within the AD.
Costs of Compliance
Based on the service information, we
estimate that this AD will affect 156
products of U.S. registry. We also
estimate that it will take about 3 workhours per product to comply with basic
requirements of this AD. The average
labor rate is $80 per work-hour.
Required parts will cost about $0 per
product (warranty credit given by
manufacturer) per product. Where the
service information lists required parts
costs that are covered under warranty,
we have assumed that there will be no
E:\FR\FM\13AUR1.SGM
13AUR1
]]>Agencies
[Federal Register Volume 73, Number 157 (Wednesday, August 13, 2008)]
[Rules and Regulations]
[Pages 47039-47041]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-18236]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0626 Directorate Identifier 2008-CE-035-AD;
Amendment 39-15637; AD 2008-16-19]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-6
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new 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:
This Airworthiness Directive (AD) is prompted due to the
discovery of loose self-locking stop nuts Part Number (P/N)
938.07.65.105 in the tail landing gear fastener assemblies of some
PC-6 aircraft.
It is believed that this occurrence could also exist in other
fastener assemblies using nuts P/N 938.07.65.105 at various
identified locations in the aircraft.
If left uncorrected, the identified assemblies may become loose
and not function as designed and could lead to hazardous situations.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective September 17, 2008.
On September 17, 2008, the Director of the Federal Register
approved the incorporation by reference of certain publications listed
in this AD.
ADDRESSES: You may examine the AD docket on the Internet at https://
www.regulations.gov or in person at Document Management Facility, U.S.
Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC
20590.
FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4059; fax: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on June 9, 2008 (73 FR
32497). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
This Airworthiness Directive (AD) is prompted due to the
discovery of loose self-locking stop nuts Part Number (P/N)
938.07.65.105 in the tail landing gear fastener assemblies of some
PC-6 aircraft.
It is believed that this occurrence could also exist in other
fastener assemblies using nuts P/N 938.07.65.105 at various
identified locations in the aircraft.
If left uncorrected, the identified assemblies may become loose
and not function as designed and could lead to hazardous situations.
In order to prevent those conditions, the present AD requires
you to replace self-locking stop nuts P/N 938.07.65.105 from the
Tail Landing Gear Assembly, the Parachute Cable Assembly, the Water
Tank Assembly, the Cable Tensioner Assembly, the Fuel Filter
Assembly, the Hydraulic Pump Assembly and the Engine Mounts Assembly
in accordance with Pilatus PC-6 Service Bulletin No. 53-002 Revision
2.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
[[Page 47040]]
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
Based on the service information, 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 basic requirements of
this AD. The average labor rate is $80 per work-hour. Required parts
will cost about $310 per product.
Based on these figures, we estimate the cost of this AD to the U.S.
operators to be $43,500, or $870 per product.
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 adding the following new AD:
2008-16-19 Pilatus Aircraft Ltd.: Amendment 39-15637; Docket No.
FAA-2008-0626; Directorate Identifier 2008-CE-035-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective
September 17, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to 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) MSN 101 through MSN 949 and MSN
2001 through MSN 2092, certificated in any category.
Note 1: These airplanes may also be identified as Fairchild
Republic Company 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 53:
Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
This Airworthiness Directive (AD) is prompted due to the
discovery of loose self-locking stop nuts Part Number (P/N)
938.07.65.105 in the tail landing gear fastener assemblies of some
PC-6 aircraft.
It is believed that this occurrence could also exist in other
fastener assemblies using nuts P/N 938.07.65.105 at various
identified locations in the aircraft.
If left uncorrected, the identified assemblies may become loose
and not function as designed and could lead to hazardous situations.
In order to prevent those conditions, the present AD requires
you replace self-locking stop nuts P/N 938.07.65.105 from the Tail
Landing Gear Assembly, the Parachute Cable Assembly, the Water Tank
Assembly, the Cable Tensioner Assembly, the Fuel Filter Assembly,
the Hydraulic Pump Assembly and the Engine Mounts Assembly in
accordance with Pilatus PC-6 Service Bulletin No. 53-002 Revision 2.
Actions and Compliance
(f) Unless already done, do the following actions:
(1) Within the next 12 months after September 17, 2008 (the
effective date of this AD), inspect and modify the fastener
assemblies as instructed in paragraph 3 of Pilatus Aircraft Ltd.
Pilatus PC-6 Service Bulletin No. 53-002, Revision No. 2, dated
September 24, 2007.
(2) As of September 17, 2008 (the effective date of this AD), no
person shall install on any PC-6 series aircraft, water tank
assemblies and hydraulic pump assemblies, unless they have been
previously modified following paragraph 4 of Pilatus Aircraft Ltd.
Pilatus PC-6 Service Bulletin No. 53-002, Revision No. 2, dated
September 24, 2007.
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;
[[Page 47041]]
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.:
2008-0083, dated May 5, 2008; and Pilatus Aircraft Ltd. Pilatus PC-6
Service Bulletin No. 53-002, Revision No. 2, dated September 24,
2007, for related information.
Material Incorporated by Reference
(i) You must use Pilatus Aircraft Ltd. Pilatus PC-6 Service
Bulletin No. 53-002, Revision No. 2, dated September 24, 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., Customer Liaison Manager, CH-6371 STANS,
Switzerland; telephone: +41 41 619 65 80; fax: +41 41 619 65 76; e-
mail: fodermatt@pilatus-aircraft.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: https://www.archives.gov/federal-
register/cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on August 1, 2008.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-18236 Filed 8-12-08; 8:45 am]
BILLING CODE 4910-13-P
