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, 40888-40891 [E6-11333]
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40888
Federal Register / Vol. 71, No. 138 / Wednesday, July 19, 2006 / Rules and Regulations
Actions
Compliance
(ii) The upper and lower wing skins for
damage; and
(iii) The inboard fuel tank area to determine
if the inboard fuel tank ventilating system
is installed.
(2) If any crack damage is found:
(i) Correct the crack damage designated as
repairable in the service bulletin.
(ii) For other crack damage, obtain a repair
scheme from the manufacturer through
FAA at the address specified in paragraph (f) of this AD and incorporate this
repair scheme.
(3) If wing distortion is found, obtain a repair
scheme from the manufacturer through FAA
at the address specified in paragraph (f) of
this AD and incorporate this repair scheme.
(4) If the inboard fuel tank ventilating system is
not installed, install the inboard fuel tank ventilating system.
(B) For Group 2 Airplanes: Within the next 90
days or 100 hours TIS, whichever occurs
first, after August 23, 2006 (the effective
date of this AD), unless already done.
Alternative Methods of Compliance
(AMOCs)
(f) The Manager, Standards Office, ATTN:
Doug Rudolph, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4059; facsimile: (816)
329–4090, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
(g) AMOCs approved for AD 2003–13–04
are approved for this AD.
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Related Information
(h) Swiss AD Numbers HB 2003–092, dated
February 17, 2003, and HB 2005–289,
effective date August 23, 2005, also address
the subject of this AD.
Material Incorporated by Reference
(i) You must do the actions required by this
AD following the instructions in Pilatus
Aircraft Ltd. PC–6 Service Bulletin No. 57–
002, dated November 27, 2002, and Pilatus
Aircraft Ltd. PC–6 Service Bulletin No. 118,
dated December 1972.
(1) As of August 15, 2003 (68 FR 37394,
June 24, 2003), the Director of the Federal
Register previously approved the
incorporation by reference of Pilatus Aircraft
Ltd. PC–6 Service Bulletin No. 57–002, dated
November 27, 2002; and Pilatus Aircraft Ltd.
PC–6 Service Bulletin No. 118, dated
December 1972, in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
(2) To get a copy of this service
information, contact Pilatus Aircraft Ltd.,
Customer Liaison Manager, CH–6371 Stans,
Switzerland; telephone: +41 41 619 63 19;
facsimile: +41 41 619 6224. To review copies
of this service information, go to the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, go to: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html or call (202) 741–6030. To
view the AD docket, go to the Docket
Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW.,
VerDate Aug<31>2005
16:10 Jul 18, 2006
Jkt 208001
Procedures
Before further flight after the inspections required in paragraph (e)(1) of this AD.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 57–002, dated November 27,
2002.
Before further flight after the inspections required in paragraph (e)(1) of this AD.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 57–002, dated November 27,
2002.
Before further flight after the inspections required in paragraph (e)(1) of this AD.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 118, dated December 1972.
Nassif Building, Room PL–401, Washington,
DC 20590–001 or on the Internet at https://
dms.dot.gov. The docket number is FAA–
2006–24093; Directorate Identifier 2006–CE–
19–AD.
Issued in Kansas City, Missouri, on July 11,
2006.
Steven W. Thompson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–11339 Filed 7–18–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24092; Directorate
Identifier 2006–CE–18–AD; Amendment 39–
14682; AD 2006–15–02]
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), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) that
supersedes AD 2003–09–01, which
applies to certain Pilatus Aircraft Ltd
(Pilatus) Model PC–6 airplanes. AD
2003–09–01 currently requires you to
inspect and correct, as necessary, the
aileron control bellcrank assemblies at
the wing and fuselage locations. Since
we issued AD 2003–09–01, the FAA
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
determined the action should also apply
to all the models of the PC–6 airplanes
listed in the type certificate data sheet
of Type Certificate (TC) No. 7A15 that
were produced in the United States
through a licensing agreement between
Pilatus and Fairchild Republic
Company (also identified as Fairchild
Industries, Fairchild Heli Porter, or
Fairchild-Hiller Corporation). In
addition, the intent of the applicability
of AD 2003–09–01 was to apply to all
the affected serial numbers of the
airplane models listed in TC No. 7A15.
This AD retains all the actions of AD
2003–09–01, adds those Fairchild
Republic Company airplanes to the
applicability of this AD, and lists the
individual specific airplane models. We
are issuing this AD to detect and correct
increased friction in the aileron control
bellcrank assemblies, which could
result in failure of the aileron flightcontrol system. Such failure could lead
to problems in controlling flight.
DATES: This AD becomes effective on
August 23, 2006.
As of June 17, 2003 (68 FR 22582,
April 29, 2003), the Director of the
Federal Register previously approved
the incorporation by reference of Pilatus
Service Bulletin No. 27–001, dated June
5, 2002, in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
ADDRESSES: To get the service
information identified in this AD,
contact Pilatus Aircraft Ltd., Customer
Liaison Manager, CH–6371 Stans,
Switzerland; telephone: +41 41 619 63
19; facsimile: +41 41 619 6224.
To view the AD docket, go to the
Docket Management Facility; U.S.
Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
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Federal Register / Vol. 71, No. 138 / Wednesday, July 19, 2006 / Rules and Regulations
001 or on the Internet at https://
dms.dot.gov. The docket number is
FAA–2006–24092; Directorate Identifier
2006–CE–18–AD.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; facsimile: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
Discussion
On May 3, 2006, we issued a proposal
to amend part 39 of the Federal Aviation
Regulations (14 CFR part 39) to include
an AD that would apply to all the
models of the PC–6 airplanes listed in
the type certificate data sheet of TC No.
7A15 that were produced in the United
States through a licensing agreement
between Pilatus and Fairchild Republic
Company (also identified as Fairchild
Industries, Fairchild Heli Porter, or
Fairchild-Hiller Corporation) airplanes.
This proposal was published in the
Federal Register as a notice of proposed
rulemaking (NPRM) on May 9, 2006 (71
FR 26891). The NPRM proposed to
supersede AD 2003–09–01 (68 FR
22582, April 29, 2003), add those
Fairchild Republic Company airplanes
to the applicability of this proposed AD,
and would list the individual specific
airplane models. The NPRM proposed
to retain all of the actions of AD 2003–
09–01 for inspecting and correcting, as
necessary, the aileron control bellcrank
assemblies at the wing and fuselage
locations.
Comments
We provided the public the
opportunity to participate in developing
this AD. We received one comment in
favor of the proposed AD.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed except for
minor editorial corrections. We have
determined that these minor
corrections:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 49
airplanes in the U.S. registry.
We estimate the following costs to do
the inspection and modifications:
Labor cost
Parts cost
Total cost per
airplane
7 work-hours × $80 per hour = $560 .......................................................................
$300
$860
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 AD.
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Regulatory Findings
15:11 Jul 18, 2006
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
VerDate Aug<31>2005
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a summary of the costs
to comply with this AD (and other
information as included in the
Regulatory Evaluation) and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2006–24092;
Directorate Identifier 2006–CE–18–AD’’
in your request.
Jkt 208001
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
PO 00000
Authority: 49 U.S.C. 106(g), 40113, 44701.
Frm 00015
Fmt 4700
Sfmt 4700
40889
§ 39.13
Total cost on U.S.
operators
$860 × 49 = $42,140.
[Amended]
2. FAA amends § 39.13 by removing
Airworthiness Directive (AD) 2003–09–
01, Amendment 39–13130 (68 FR
22582, April 29, 2003), and by adding
the following new AD:
I
2006–15–02 Pilatus Aircraft Ltd.:
Amendment 39–14682; Docket No. FAA–
2006–24092; Directorate Identifier 2006–
CE–18–AD.
Effective Date
(a) This AD becomes effective on August
23, 2006.
Affected ADs
(b) This AD supersedes AD 2003–09–01,
Amendment 39–13130.
Applicability
(c) This AD affects the following 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 that are certificated in any
category:
(1) Group 1 (maintains the actions from AD
2003–09–01): All manufacturer serial
numbers (MSN) up to and including 939.
(2) Group 2: MSN 2001 through 2092.
Note: 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.
Unsafe Condition
(d) This AD results from mandatory
continuing airworthiness information (MCAI)
issued by the airworthiness authority for
Switzerland that requires retaining the
E:\FR\FM\19JYR1.SGM
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40890
Federal Register / Vol. 71, No. 138 / Wednesday, July 19, 2006 / Rules and Regulations
actions of AD 2003–09–01 and adding MSN
2001 through 2092 for all the models of the
PC–6 airplanes listed in the type certificate
data sheet of Type Certificate No. 7A15. We
are issuing this AD to detect and correct
increased friction in the aileron control
bellcrank assemblies, which could result in
failure of the aileron flight-control system.
Such failure could lead to problems in
controlling flight.
Compliance
(e) To address this problem, you must do
the following:
Compliance
Procedures
(1) Inspect, before removal of the wing
bellcrank assemblies, part numbers (P/N)
6132.0071.51 and 6132.0071.52, for installed
circlips, P/N N237.
(i) If circlips are installed, do the actions required in paragraphs (e)(5) and (e)(6) of
this AD.
(ii) If circlips are not installed, perform all
actions required by paragraphs (e)(3),
(e)(4), (e)(5), (e)(6), and (e)(7) of this AD.
(2) Inspect, before removal of the fuselage
bellcrank assembly, P/N 6232.0118.00, for
the circlip installed on the housing to prevent
axial movement of the bellcrank on its bearing and the flange of the housing to the rear.
If the fuselage bellcrank assembly has either
no circlip and/or it is not installed as required,
perform the actions in paragraphs (e)(8) and
(e)(9) of this AD.
(3) Remove the wing bellcrank assemblies, P/
Ns 6132.0071.51 and 6132.0071.52, and inspect for worn or damaged bearings. Replace worn or damaged bearings.
(4) Stake and lock the bearing in the housing of
the wing bellcranks, P/Ns 6132.0071.51 and
6132.0071.52.
(5) Inspect the wing bellcranks control-cable attachment bolts for correct type and for signs
of rub damage on the heads. Replace bolts
that are damaged and/or have a total length
(including head) of more than 21.5 mm (0.85
in.).
(6) Inspect the wing bellcranks support plate for
signs of rub damage caused by the bolts. If
damage is found:
(i) Obtain a repair scheme from the manufacturer through FAA at the address
specified in paragraph (f) of this AD.
(ii) Incorporate this repair scheme.
(7) Reinstall wing bellcrank assemblies .............
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Actions
(A) For Group 1 Airplanes: Within the next
100 hours time-in-service (TIS) after June
17, 2003 (the effective date of AD 2003–
09–01), unless already done.
(B) For Group 2 Airplanes: Within the next
100 hours TIS after August 23, 2006 (the
effective date of this AD), unless already
done.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002.
Before further flight after the inspection required in paragraph (e)(1) of this AD.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002.
Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of
this AD, as applicable.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002.
Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of
this AD, as applicable.
Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of
this AD, as applicable.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002.
Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of
this AD.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002.
Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of
this AD.
Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of
this AD.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002.
Before further flight after the inspections required in paragraphs (e)(1), (e)(2), and
(e)(8) of this AD.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002.
(8) Remove the fuselage bellcrank assembly,
P/N 6232.0118.00, and inspect the housing
for wear, damage, and signs of axial movement of the bearing in the housing. Replace
worn or damaged bearings. If any signs of
axial movement of a bearing are found:
(i) Obtain a repair scheme from the manufacturer through FAA at the address
specified in paragraph (f) of this AD.
(ii) Incorporate this repair scheme.
(9) Reinstall the fuselage bellcrank assembly.
Ensure that the fuselage bellcrank assembly
is installed so that the surface of the
bellcrank with the flange of the housing is installed to the rear. The effect of this is to lock
the bellcrank on the bearing tube and thus
prevent movement.
(10) Do not install any bellcrank assemblies, P/
Ns
6132.0071.51,
6132,0071.52,
and
6232.0118.00 (or FAA-approved equivalent
part numbers), unless the aileron assembly
has been inspected, modified, and installed.
VerDate Aug<31>2005
15:11 Jul 18, 2006
Jkt 208001
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002.
(A) For Group 1 Airplanes: As of June 17, Follow Pilatus Aircraft Ltd. PC–6 Service Bul2003 (the effective date of AD 2003–09–01).
letin No. 27–001, dated June 5, 2002.
(B) For Group 2 Airplanes: As of August 23,
2006 (the effective date of this AD), unless
already done.
PO 00000
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E:\FR\FM\19JYR1.SGM
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Federal Register / Vol. 71, No. 138 / Wednesday, July 19, 2006 / Rules and Regulations
(f) Axial movement of serviceable bearings
in the housings of the wing bellcranks is
permitted provided no wear or damage to the
bearing is found.
(g) Any sign of axial movement of a bearing
in the housing of the fuselage bellcrank
assembly requires that you obtain a repair
scheme from the manufacturer through FAA
at the address specified in paragraph (i) of
this AD and incorporate the repair scheme.
(h) 14 CFR 21.303 allows for replacement
parts through parts manufacturer approval
(PMA). The phrase ‘‘or FAA-approved
equivalent part number’’ in this AD is
intended to signify those parts that are PMA
approved through identicality to the design
of the part under the type certificate and
replacement parts to correct the unsafe
condition under PMA (other than
identicality). If parts are installed that are
identical to the unsafe parts, then the
corrective actions of the AD affect these parts
also. In addition, equivalent replacement
parts to correct the unsafe condition under
PMA (other than identicality) may also be
installed provided they meet current
airworthiness standards, which include those
actions cited in this AD.
Alternative Methods of Compliance
(AMOCs)
(i) The Manager, Standards Office, ATTN:
Doug Rudolph, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4059; facsimile: (816)
329–4090, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
(j) AMOCs approved for AD 2003–09–01
are approved for this AD.
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Related Information
(k) Swiss AD Number HB 2005–289,
effective date August 23, 2005, also addresses
the subject of this AD.
Material Incorporated by Reference
(l) You must do the actions required by this
AD following the instructions in Pilatus
Aircraft Ltd. PC–6 Service Bulletin No. 27–
001, dated June 5, 2002.
(1) As of June 17, 2003 (68 FR 22582, April
29, 2003), the Director of the Federal Register
previously approved the incorporation by
reference of Pilatus Service Bulletin No. 27–
001, dated June 5, 2002, in accordance with
5 U.S.C. 552(a) and 1 CFR part 51.
(2) To get a copy of this service
information, contact Pilatus Aircraft Ltd.,
Customer Liaison Manager, CH–6371 Stans,
Switzerland; telephone: +41 41 619 63 19;
facsimile: +41 41 619 6224. To review copies
of this service information, go to the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, go to: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html or call (202) 741–6030. To
view the AD docket, go to the Docket
Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW.,
Nassif Building, Room PL–401, Washington,
DC 20590–001 or on the Internet at https://
dms.dot.gov. The docket number is FAA–
VerDate Aug<31>2005
15:11 Jul 18, 2006
Jkt 208001
2006–24092; Directorate Identifier 2006–CE–
18–AD.
Issued in Kansas City, Missouri, on July 10,
2006.
Steven W. Thompson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–11333 Filed 7–18–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
National Highway Traffic Safety
Administration
23 CFR Part 1350
[Docket No. NHTSA–2006–23700]
RIN 2127–AJ86
Motorcyclist Safety Grant Program
National Highway Traffic
Safety Administration (NHTSA),
Department of Transportation (DOT).
ACTION: Final rule.
AGENCY:
This final rule implements
the Motorcyclist Safety grant program
authorized under section 2010 of the
Safe, Accountable, Flexible, Efficient
Transportation Equity Act: A Legacy for
Users (SAFETEA–LU) for fiscal years
2006 through 2009. Eligibility for the
section 2010 grants is based on six
statutorily-specified grant criteria. To
receive an initial section 2010 grant, a
State must demonstrate compliance
with at least one of the six grant criteria.
To receive a grant in subsequent fiscal
years, a State must demonstrate
compliance with at least two of the six
grant criteria. This final rule establishes
the requirements a State must meet and
the procedures it must follow to receive
a section 2010 Motorcyclist Safety grant,
beginning in fiscal year 2006.
DATES: This final rule becomes effective
on July 19, 2006.
FOR FURTHER INFORMATION CONTACT: For
program issues: Marti Miller, Regional
Operations and Program Delivery,
National Highway Traffic Safety
Administration, 400 Seventh Street,
SW., Washington, DC 20590; Telephone:
(202) 366–2121. For legal issues: Allison
Rusnak, Office of the Chief Counsel,
National Highway Traffic Safety
Administration, 400 Seventh Street,
SW., Washington, DC 20590; Telephone:
(202) 366–1834.
SUPPLEMENTARY INFORMATION:
SUMMARY:
Table of Contents
I. Background
II. Section 2010 Statutory Requirements
III. Section 2010 Administrative
Requirements
PO 00000
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40891
IV. Notice of Proposed Rulemaking
V. Comments
A. In General
B. Comments Regarding Programmatic
Criteria
1. Motorcycle Rider Training Courses
2. Motorcyclists Awareness Program
3. Reduction of Fatalities and Crashes
Involving Motorcycles and Reduction of
Fatalities and Accidents Involving
Impaired Motorcyclists
4. Impaired Driving Program
C. Comments Regarding Administrative
Issues
VI. Statutory Basis for This Action
VII. Regulatory Analyses and Notices
A. Executive Order 12866 and DOT
Regulatory Policies and Procedures
B. Regulatory Flexibility Act
C. Executive Order 13132 (Federalism)
D. Executive Order 12988 (Civil Justice
Reform)
E. Paperwork Reduction Act
F. Unfunded Mandates Reform Act
G. National Environmental Policy Act
H. Executive Order 13175 (Consultation
and Coordination With Indian Tribes)
I. Regulatory Identifier Number (RIN)
J. Privacy Act
I. Background
An estimated 128,000 motorcyclists
have died in traffic crashes since the
enactment of the Highway Safety Act of
1966. There are nearly 6 million
motorcycles 1 registered in the United
States. Motorcycles made up more than
2 percent of all registered vehicles in the
United States in 2004 and accounted for
an estimated 0.3 percent of all vehicle
miles traveled. Per vehicle mile traveled
in 2004, motorcyclists were about 34
times more likely to die and 8 times
more likely to be injured in a motor
vehicle traffic crash than passenger car
occupants. Motorcycle rider fatalities
reached a high of 5,144 in 1980. After
dropping to a low of 2,116 in 1997,
motorcycle rider fatalities have
increased for 7 consecutive years,
reaching a total of 4,008 in 2004, the last
full year for which data are available—
an increase of 89 percent. Preliminary
2005 Fatality Analysis Reporting System
(FARS) data show a projected increase
of 7.7% in motorcycle fatalities.
Impaired motorcycle operation
contributes considerably to motorcycle
fatalities and injuries. In fatal crashes in
2004, a higher percentage of motorcycle
operators than any other type of motor
vehicle operator had blood alcohol
concentration (BAC) levels of .08 grams
1 For the purposes of the section 2010 grants,
NHTSA proposed in the NPRM that the term
‘‘motorcycle’’ would have the same meaning as in
49 CFR 571.3, ‘‘a motor vehicle with motive power
having a seat or saddle for the use of the rider and
designed to travel on not more than three wheels
in contact with the ground.’’ NHTSA received no
comments on the meaning of the term
‘‘motorcycle.’’ Therefore, we retain the definition
without change in this final rule.
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]]>Agencies
[Federal Register Volume 71, Number 138 (Wednesday, July 19, 2006)]
[Rules and Regulations]
[Pages 40888-40891]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-11333]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24092; Directorate Identifier 2006-CE-18-AD;
Amendment 39-14682; AD 2006-15-02]
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), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) that
supersedes AD 2003-09-01, which applies to certain Pilatus Aircraft Ltd
(Pilatus) Model PC-6 airplanes. AD 2003-09-01 currently requires you to
inspect and correct, as necessary, the aileron control bellcrank
assemblies at the wing and fuselage locations. Since we issued AD 2003-
09-01, the FAA determined the action should also apply to all the
models of the PC-6 airplanes listed in the type certificate data sheet
of Type Certificate (TC) No. 7A15 that were produced in the United
States through a licensing agreement between Pilatus and Fairchild
Republic Company (also identified as Fairchild Industries, Fairchild
Heli Porter, or Fairchild-Hiller Corporation). In addition, the intent
of the applicability of AD 2003-09-01 was to apply to all the affected
serial numbers of the airplane models listed in TC No. 7A15. This AD
retains all the actions of AD 2003-09-01, adds those Fairchild Republic
Company airplanes to the applicability of this AD, and lists the
individual specific airplane models. We are issuing this AD to detect
and correct increased friction in the aileron control bellcrank
assemblies, which could result in failure of the aileron flight-control
system. Such failure could lead to problems in controlling flight.
DATES: This AD becomes effective on August 23, 2006.
As of June 17, 2003 (68 FR 22582, April 29, 2003), the Director of
the Federal Register previously approved the incorporation by reference
of Pilatus Service Bulletin No. 27-001, dated June 5, 2002, in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
ADDRESSES: To get the service information identified in this AD,
contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans,
Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224.
To view the AD docket, go to the Docket Management Facility; U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC 20590-
[[Page 40889]]
001 or on the Internet at https://dms.dot.gov. The docket number is FAA-
2006-24092; Directorate Identifier 2006-CE-18-AD.
FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4059; facsimile: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Discussion
On May 3, 2006, we issued a proposal to amend part 39 of the
Federal Aviation Regulations (14 CFR part 39) to include an AD that
would apply to all the models of the PC-6 airplanes listed in the type
certificate data sheet of TC No. 7A15 that were produced in the United
States through a licensing agreement between Pilatus and Fairchild
Republic Company (also identified as Fairchild Industries, Fairchild
Heli Porter, or Fairchild-Hiller Corporation) airplanes. This proposal
was published in the Federal Register as a notice of proposed
rulemaking (NPRM) on May 9, 2006 (71 FR 26891). The NPRM proposed to
supersede AD 2003-09-01 (68 FR 22582, April 29, 2003), add those
Fairchild Republic Company airplanes to the applicability of this
proposed AD, and would list the individual specific airplane models.
The NPRM proposed to retain all of the actions of AD 2003-09-01 for
inspecting and correcting, as necessary, the aileron control bellcrank
assemblies at the wing and fuselage locations.
Comments
We provided the public the opportunity to participate in developing
this AD. We received one comment in favor of the proposed AD.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed
except for minor editorial corrections. We have determined that these
minor corrections:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 49 airplanes in the U.S. registry.
We estimate the following costs to do the inspection and
modifications:
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Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
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7 work-hours x $80 per hour = $560.. $300 $860 $860 x 49 = $42,140.
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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 AD.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD (and
other information as included in the Regulatory Evaluation) and placed
it in the AD Docket. You may get a copy of this summary by sending a
request to us at the address listed under ADDRESSES. Include ``Docket
No. FAA-2006-24092; Directorate Identifier 2006-CE-18-AD'' in your
request.
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 Federal Aviation Administration amends part 39 of the Federal
Aviation Regulations (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. FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2003-09-01, Amendment 39-13130 (68 FR 22582, April 29, 2003), and by
adding the following new AD:
2006-15-02 Pilatus Aircraft Ltd.: Amendment 39-14682; Docket No.
FAA-2006-24092; Directorate Identifier 2006-CE-18-AD.
Effective Date
(a) This AD becomes effective on August 23, 2006.
Affected ADs
(b) This AD supersedes AD 2003-09-01, Amendment 39-13130.
Applicability
(c) This AD affects the following 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 that are certificated in any category:
(1) Group 1 (maintains the actions from AD 2003-09-01): All
manufacturer serial numbers (MSN) up to and including 939.
(2) Group 2: MSN 2001 through 2092.
Note: 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.
Unsafe Condition
(d) This AD results from mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for
Switzerland that requires retaining the
[[Page 40890]]
actions of AD 2003-09-01 and adding MSN 2001 through 2092 for all
the models of the PC-6 airplanes listed in the type certificate data
sheet of Type Certificate No. 7A15. We are issuing this AD to detect
and correct increased friction in the aileron control bellcrank
assemblies, which could result in failure of the aileron flight-
control system. Such failure could lead to problems in controlling
flight.
Compliance
(e) To address this problem, you must do the following:
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Actions Compliance Procedures
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(1) Inspect, before removal (A) For Group 1 Follow Pilatus
of the wing bellcrank Airplanes: Within Aircraft Ltd. PC-6
assemblies, part numbers (P/ the next 100 hours Service Bulletin
N) 6132.0071.51 and time-in-service No. 27-001, dated
6132.0071.52, for installed (TIS) after June June 5, 2002.
circlips, P/N N237. 17, 2003 (the
(i) If circlips are effective date of
installed, do the actions AD 2003-09-01),
required in paragraphs unless already done.
(e)(5) and (e)(6) of this (B) For Group 2
AD. Airplanes: Within
(ii) If circlips are not the next 100 hours
installed, perform all TIS after August
actions required by 23, 2006 (the
paragraphs (e)(3), (e)(4), effective date of
(e)(5), (e)(6), and (e)(7) this AD), unless
of this AD. already done.
(2) Inspect, before removal Before further Follow Pilatus
of the fuselage bellcrank flight after the Aircraft Ltd. PC-6
assembly, P/N 6232.0118.00, inspection required Service Bulletin
for the circlip installed in paragraph (e)(1) No. 27-001, dated
on the housing to prevent of this AD. June 5, 2002.
axial movement of the
bellcrank on its bearing
and the flange of the
housing to the rear. If the
fuselage bellcrank assembly
has either no circlip and/
or it is not installed as
required, perform the
actions in paragraphs
(e)(8) and (e)(9) of this
AD.
(3) Remove the wing Before further Follow Pilatus
bellcrank assemblies, P/Ns flight after the Aircraft Ltd. PC-6
6132.0071.51 and inspections Service Bulletin
6132.0071.52, and inspect required in No. 27-001, dated
for worn or damaged paragraphs (e)(1) June 5, 2002.
bearings. Replace worn or and (e)(2) of this
damaged bearings. AD, as applicable.
(4) Stake and lock the Before further Follow Pilatus
bearing in the housing of flight after the Aircraft Ltd. PC-6
the wing bellcranks, P/Ns inspections Service Bulletin
6132.0071.51 and required in No. 27-001, dated
6132.0071.52. paragraphs (e)(1) June 5, 2002.
and (e)(2) of this
AD, as applicable.
(5) Inspect the wing Before further Follow Pilatus
bellcranks control-cable flight after the Aircraft Ltd. PC-6
attachment bolts for inspections Service Bulletin
correct type and for signs required in No. 27-001, dated
of rub damage on the heads. paragraphs (e)(1) June 5, 2002.
Replace bolts that are and (e)(2) of this
damaged and/or have a total AD, as applicable.
length (including head) of
more than 21.5 mm (0.85
in.).
(6) Inspect the wing Before further Follow Pilatus
bellcranks support plate flight after the Aircraft Ltd. PC-6
for signs of rub damage inspections Service Bulletin
caused by the bolts. If required in No. 27-001, dated
damage is found: paragraphs (e)(1) June 5, 2002.
(i) Obtain a repair scheme and (e)(2) of this
from the manufacturer AD.
through FAA at the address
specified in paragraph (f)
of this AD.
(ii) Incorporate this repair
scheme..
(7) Reinstall wing bellcrank Before further Follow Pilatus
assemblies. flight after the Aircraft Ltd. PC-6
inspections Service Bulletin
required in No. 27-001, dated
paragraphs (e)(1) June 5, 2002.
and (e)(2) of this
AD.
(8) Remove the fuselage Before further Follow Pilatus
bellcrank assembly, P/N flight after the Aircraft Ltd. PC-6
6232.0118.00, and inspect inspections Service Bulletin
the housing for wear, required in No. 27-001, dated
damage, and signs of axial paragraphs (e)(1) June 5, 2002.
movement of the bearing in and (e)(2) of this
the housing. Replace worn AD.
or damaged bearings. If any
signs of axial movement of
a bearing are found:
(i) Obtain a repair scheme
from the manufacturer
through FAA at the address
specified in paragraph (f)
of this AD.
(ii) Incorporate this repair
scheme..
(9) Reinstall the fuselage Before further Follow Pilatus
bellcrank assembly. Ensure flight after the Aircraft Ltd. PC-6
that the fuselage bellcrank inspections Service Bulletin
assembly is installed so required in No. 27-001, dated
that the surface of the paragraphs (e)(1), June 5, 2002.
bellcrank with the flange (e)(2), and (e)(8)
of the housing is installed of this AD.
to the rear. The effect of
this is to lock the
bellcrank on the bearing
tube and thus prevent
movement.
(10) Do not install any (A) For Group 1 Follow Pilatus
bellcrank assemblies, P/Ns Airplanes: As of Aircraft Ltd. PC-6
6132.0071.51, 6132,0071.52, June 17, 2003 (the Service Bulletin
and 6232.0118.00 (or FAA- effective date of No. 27-001, dated
approved equivalent part AD 2003-09-01). June 5, 2002.
numbers), unless the (B) For Group 2
aileron assembly has been Airplanes: As of
inspected, modified, and August 23, 2006
installed. (the effective date
of this AD), unless
already done.
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[[Page 40891]]
(f) Axial movement of serviceable bearings in the housings of
the wing bellcranks is permitted provided no wear or damage to the
bearing is found.
(g) Any sign of axial movement of a bearing in the housing of
the fuselage bellcrank assembly requires that you obtain a repair
scheme from the manufacturer through FAA at the address specified in
paragraph (i) of this AD and incorporate the repair scheme.
(h) 14 CFR 21.303 allows for replacement parts through parts
manufacturer approval (PMA). The phrase ``or FAA-approved equivalent
part number'' in this AD is intended to signify those parts that are
PMA approved through identicality to the design of the part under
the type certificate and replacement parts to correct the unsafe
condition under PMA (other than identicality). If parts are
installed that are identical to the unsafe parts, then the
corrective actions of the AD affect these parts also. In addition,
equivalent replacement parts to correct the unsafe condition under
PMA (other than identicality) may also be installed provided they
meet current airworthiness standards, which include those actions
cited in this AD.
Alternative Methods of Compliance (AMOCs)
(i) The Manager, Standards Office, ATTN: Doug Rudolph, Aerospace
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile:
(816) 329-4090, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19.
(j) AMOCs approved for AD 2003-09-01 are approved for this AD.
Related Information
(k) Swiss AD Number HB 2005-289, effective date August 23, 2005,
also addresses the subject of this AD.
Material Incorporated by Reference
(l) You must do the actions required by this AD following the
instructions in Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 27-
001, dated June 5, 2002.
(1) As of June 17, 2003 (68 FR 22582, April 29, 2003), the
Director of the Federal Register previously approved the
incorporation by reference of Pilatus Service Bulletin No. 27-001,
dated June 5, 2002, in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) To get a copy of this service information, contact Pilatus
Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, Switzerland;
telephone: +41 41 619 63 19; facsimile: +41 41 619 6224. To review
copies of this service information, go to the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, go to: https://www.archives.gov/federal_
register/code_of_federal_regulations/ibr_locations.html or call
(202) 741-6030. To view the AD docket, go to the Docket Management
Facility; U.S. Department of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on
the Internet at https://dms.dot.gov. The docket number is FAA-2006-
24092; Directorate Identifier 2006-CE-18-AD.
Issued in Kansas City, Missouri, on July 10, 2006.
Steven W. Thompson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-11333 Filed 7-18-06; 8:45 am]
BILLING CODE 4910-13-P
