Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes, 33344-33346 [05-10949]
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Federal Register / Vol. 70, No. 109 / Wednesday, June 8, 2005 / Rules and Regulations
TABLE 4.—MATERIAL INCORPORATED BY REFERENCE—TEMPORARY CHANGES—Continued
Dassault temporary
change
Date
Dassault airplane flight manual
122 ....................................
September 23, 2003 ..............................................
Falcon 2000 ...........................................................
This incorporation by reference was
approved by the Director of the Federal
Register in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. To get copies of this
service information, contact Dassault Falcon
Jet, P.O. Box 2000, South Hackensack, New
Jersey 07606. To inspect copies of this
service information, go to the FAA, Transport
Airplane Directorate, 1601 Lind Avenue,
SW., Renton, Washington; or to the National
Archives and Records Administration
(NARA). For information on the availability
of this material at the NARA, call (202) 741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Note 2: The subject of this AD is addressed
in French airworthiness directive 2003–
409(B), dated October 29, 2003.
Effective Date
(g) This amendment becomes effective on
July 13, 2005.
Issued in Renton, Washington, on May 26,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–11052 Filed 6–7–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20720; Directorate
Identifier 2005–CE–17–AD; Amendment 39–
14108; AD 2005–11–06]
RIN 2120–AA64
Airworthiness Directives; Pilatus
Aircraft Ltd. Models PC–12 and PC–12/
45 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
Discussion
SUMMARY: The FAA adopts a new
airworthiness directive (AD) for certain
Pilatus Aircraft Ltd. (Pilatus) Models
PC–12 and PC–12/45 airplanes. This AD
requires you to insert a temporary
revision into the Limitations Section of
the Pilot Operating Handbook (POH).
This AD also requires you to replace the
pitch actuator with an improved design
pitch actuator and make the necessary
wiring and circuit breaker changes, as
applicable. Installing the improved
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design pitch actuator terminates the
need for the temporary revision in the
POH. This AD results from mandatory
continuing airworthiness information
(MCAI) issued by the airworthiness
authority for Switzerland. We are
issuing this AD to prevent an out-of-trim
condition from occurring when the flaps
are at a 40-degree flight phase and the
pilot disconnects the autopilot. This
condition could lead to reduced ability
to control the airplane.
DATES: This AD becomes effective on
July 18, 2005.
As of July 18, 2005, the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in the regulation.
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
6208; facsimile: +41 41 619 7311; email: SupportPC12@pilatus-aircraft.com
or from Pilatus Business Aircraft Ltd.,
Product Support Department, 11755
Airport Way, Broomfield, Colorado
80021; telephone: (303) 465–9099;
facsimile: (303) 465–6040.
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–2005–20720; Directorate Identifier
2005–CE–17–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:
What events have caused this AD?
The Federal Office for Civil Aviation
(FOCA), which is the airworthiness
authority for Switzerland, recently
notified FAA that an unsafe condition
may exist on certain Pilatus Models PC–
12 and PC–12/45 airplanes. The FOCA
reports that an abrupt nose down pitch
condition occurred on a PC–12 airplane.
Investigation revealed that the pilot
disconnected the autopilot when the
flaps were at a 40-degree selection.
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Document
DTM537.
Pilatus has determined that the pitch
actuator sense circuitry becomes overactive during a 40-degree flight phase.
Therefore, Pilatus designed a new pitch
actuator that modifies sense output
signals and removes the flap in motion
signal to the autopilot.
What is the potential impact if FAA
took no action? This condition, if not
corrected, could result in an out-of-trim
condition when the flaps are at a 40degree flight phase and the pilot
disconnects the autopilot. This
condition could lead to reduced ability
to control the airplane.
Has FAA taken any action to this
point? 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 certain
Pilatus Models PC–12 and PC–12/45
airplanes. This proposal was published
in the Federal Register as a notice of
proposed rulemaking (NPRM) on April
13, 2005 (70 FR 19342). The NPRM
proposed to require you to insert the
temporary revision into the Limitations
Section of the Pilot Operating Handbook
(POH). The NPRM also proposed to
require you to replace the pitch actuator
with an improved design pitch actuator
and make the necessary wiring and
circuit breaker changes, as applicable.
Installing the improved design pitch
actuator would terminate the need for
the temporary revision in the POH.
Comments
Was the public invited to comment?
We provided the public the opportunity
to participate in developing this AD.
The following presents the comments
received on the proposal and FAA’s
response to each comment:
Comment Issue: Change the Compliance
Time for Replacing the Pitch Actuator
What is the commenter’s concern?
Two commenters state the requirement
to replace the pitch actuator within 6
months after the effective date of the AD
may place an unnecessary burden on
both the operators and service centers.
The Pilatus PC–12 fleet consists of
over 500 airplanes worldwide. Because
of material quantity constraints, the
logistics associated with replacing the
pitch actuator within six months would
be nearly impossible for all operators.
Extensive flight-testing identified the
unsafe condition associated with
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Federal Register / Vol. 70, No. 109 / Wednesday, June 8, 2005 / Rules and Regulations
operation of the autopilot with 40degree flaps.
The AD requires inserting a temporary
revision into the Pilot Operating
Handbook (POH) prohibiting the use of
the autopilot with the flaps at the 40degree position, which removes the risk
of a major out of trim condition.
The commenters request the
compliance time for replacing the pitch
actuator be changed from ‘‘Within the
next 6 months after the effective date of
this AD, unless already done,’’ to
‘‘Before December 31, 2006.’’
What is FAA’s response to the
concern? We partially agree with the
commenters.
Since it has been identified through
flight-testing that the unsafe condition
can be avoided by inserting Temporary
Revision No. 11 or No. 40 into the
Limitation Section of the POH, we agree
to extend the compliance time for
replacing the pitch actuator.
Extending the compliance time will
allow the owners/operators more time to
get the pitch actuator replaced and
allows the supplier to meet the demand
for parts in a timely manner. However,
we rarely use a specific calendar date to
express compliance time and only then
when engineering analysis establishes a
direct relationship between the date and
either the compliance ‘‘threshold’’ or
the ‘‘grace period.’’
Basically, the commenters are
requesting an additional 12 months to
replace the pitch actuator.
Therefore, we will change the final
rule AD action and increase the
compliance time for replacing the pitch
actuator to ‘‘Within the next 18 months
after the effective date of this AD, unless
already done.’’
Conclusion
What is FAA’s final determination on
this issue? We have carefully reviewed
the available data and determined that
air safety and the public interest require
adopting the AD as proposed except for
the changes discussed above and minor
editorial corrections. We have
determined that these changes and
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.
Changes to 14 CFR Part 39—Effect on
the AD
How does the revision to 14 CFR part
39 affect this AD? On July 10, 2002, the
FAA published a new version of 14 CFR
part 39 (67 FR 47997, July 22, 2002),
which governs the FAA’s AD system.
This regulation now includes material
that relates to altered products, special
flight permits, and alternative methods
of compliance. This material previously
was included in each individual AD.
Since this material is included in 14
CFR part 39, we will not include it in
future AD actions.
Costs of Compliance
How many airplanes does this AD
impact? We estimate that this AD affects
330 airplanes in the U.S. registry.
What is the cost impact of this AD on
owners/operators of the affected
airplanes? We estimate the following
costs to incorporate the Pilot Operating
Handbook (POH) Temporary Revision:
Total cost
per Airplane
Labor cost
Parts cost
1 work hour × $65 per hour = $65. ................................................................
Not applicable ....................................
Pilatus will provide warranty credit
for replacing the pitch actuator to the
extent stated in the service information.
Authority for This Rulemaking
What authority does FAA have for
issuing this rulemaking action? 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
Will this AD impact various entities?
We have determined that this AD will
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15:35 Jun 07, 2005
Jkt 205250
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.
Will this AD involve a significant rule
or regulatory action? 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–2005–20720;
Directorate Identifier 2005–CE–17–AD’’
in your request.
PO 00000
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33345
$65
Total cost
on U.S.
operators
$21,450
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 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
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
I 2. FAA amends § 39.13 by adding a
new AD to read as follows:
2005–11–06 Pilatus Aircraft Ltd.:
Amendment 39–14108; Docket No.
FAA–2005–20720; Directorate Identifier
2005–CE–17–AD.
When Does This AD Become Effective?
(a) This AD becomes effective on July 18,
2005.
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Federal Register / Vol. 70, No. 109 / Wednesday, June 8, 2005 / Rules and Regulations
What Other ADs Are Affected By This
Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects Models PC–12 and PC–
12/45 airplanes, Manufacturers Serial
Numbers (MSN) 101 through 620, that are
certificated in any category.
What Is the Unsafe Condition Presented in
This AD?
(d) This AD is the result of mandatory
continuing airworthiness information (MCAI)
issued by the airworthiness authority for
Switzerland. The actions specified in this AD
are intended to prevent an out-of-trim
condition from occurring when the flaps are
at a 40-degree flight phase and the pilot
disconnects the autopilot. This condition
could lead to reduced ability to control the
airplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do
the following:
Actions
Compliance
Procedures
(1) Insert Temporary Revision No. 11 (Report
No. 02211) or No. 40 (Report No. 01973–
001) into the Limitations Section of the PC–
12 Pilot’s Operating Handbook (POH).
Within the next 90 days after July 18, 2005
(the effective date of this AD), unless already done.
(2) Replace the pitch actuator, part number (P/
N) 985.92.03.161, with an improved design
pitch actuator, P/N 985.92.03.164; and make
the associated wiring and circuit breaker
changes (as applicable).
(3) Remove the Temporary Revision to the
POH specified in paragraph (e)(1) of this AD
after the pitch actuator is replaced as required in paragraph (e)(2) of this AD.
Within the next 18 months after July 18, 2005
(the effective date of this AD), unless already done.
The owner/operator holding at least a private
pilot certificate as authorized by section
43.7 of the Federal Aviation Regulations
(14 CFR 43.7) may modify the POH as
specified in paragraph (e)(1) of this AD.
Make an entry into the aircraft records
showing compliance with this portion of the
AD following section 43.9 of the Federal
Aviation Regulations (14 CFR 43.9).
Follow Pilatus PC12 Service Bulletin No. 22–
004, dated December 21, 2004.
(4) Do not install a P/N 985.92.03.161 pitch actuator.
As of July 18, 2005 (the effective date of this
AD).
May I Request an Alternative Method of
Compliance?
(f) You may request a different method of
compliance or a different compliance time
for this AD by following the procedures in 14
CFR 39.19. Unless FAA authorizes otherwise,
send your request to your principal
inspector. The principal inspector may add
comments and will send your request to the
Manager, Standards Office, Small Airplane
Directorate, FAA. For information on any
already approved alternative methods of
compliance, 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.
Is There Other Information That Relates to
This Subject?
(g) Swiss AD Number HB–2005–128,
effective date March 29, 2005, also addresses
the subject of this AD.
Does This AD Incorporate Any Material by
Reference?
(h) You must do the actions required by
this AD following the instructions in Pilatus
PC12 Service Bulletin No. 22–004, dated
December 21, 2004. The Director of the
Federal Register approved the incorporation
by reference of this service bulletin in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. To get a copy of this service
information, contact Pilatus Aircraft Ltd.,
Customer Liaison Manager, CH–6371 Stans,
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15:35 Jun 07, 2005
Jkt 205250
Before further flight after the pitch actuator is
replaced with an improved design pitch actuator.
Switzerland; telephone: +41 41 619 6208;
facsimile: +41 41 619 7311; e-mail:
SupportPC12@pilatus-aircraft.com or from
Pilatus Business Aircraft Ltd., Product
Support Department, 11755 Airport Way,
Broomfield, Colorado 80021; telephone: (303)
465–9099; facsimile: (303) 465–6040. 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–
2005–20720; Directorate Identifier 2005–CE–
17–AD.
Issued in Kansas City, Missouri, on May
25, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–10949 Filed 6–7–05; 8:45 am]
BILLING CODE 4910–13–P
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The owner/operator holding at least a private
pilot certificate as authorized by section
43.7 of the Federal Aviation Regulations
(14 CFR 43.7) may modify the POH as
specified in paragraph (e)(3) of this AD.
Make an entry into the aircraft records
showing compliance with this portion of the
AD following section 43.9 of the Federal
Aviation Regulations (14 CFR 43.9).
Not applicable.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2005–20673; Airspace
Docket No. 05–AEA–06]
Amendment of Class E Airspace;
Newburgh, NY
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This action amends Class E
airspace at Newburgh, NY. The
development of multiple area navigation
(RNAV) Standard Instrument Approach
Procedures (SIAP) for numerous airports
within the Newburgh, NY geographical
area with approved Instrument Flight
Rules (IFR) operations and the resulting
overlap of designated Class E–5 airspace
have made this action necessary. This
action consolidates the Class E–5
airspace designations for ten airports
and results in the rescission of four
Class E–5 descriptions through separate
rulemaking action. The area will be
depicted on aeronautical charts for pilot
reference.
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]]>Agencies
[Federal Register Volume 70, Number 109 (Wednesday, June 8, 2005)]
[Rules and Regulations]
[Pages 33344-33346]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-10949]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20720; Directorate Identifier 2005-CE-17-AD;
Amendment 39-14108; AD 2005-11-06]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and
PC-12/45 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain
Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes.
This AD requires you to insert a temporary revision into the
Limitations Section of the Pilot Operating Handbook (POH). This AD also
requires you to replace the pitch actuator with an improved design
pitch actuator and make the necessary wiring and circuit breaker
changes, as applicable. Installing the improved design pitch actuator
terminates the need for the temporary revision in the POH. This AD
results from mandatory continuing airworthiness information (MCAI)
issued by the airworthiness authority for Switzerland. We are issuing
this AD to prevent an out-of-trim condition from occurring when the
flaps are at a 40-degree flight phase and the pilot disconnects the
autopilot. This condition could lead to reduced ability to control the
airplane.
DATES: This AD becomes effective on July 18, 2005.
As of July 18, 2005, the Director of the Federal Register approved
the incorporation by reference of certain publications listed in the
regulation.
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 6208; facsimile: +41 41 619 7311; e-
mail: SupportPC12@pilatus-aircraft.com or from Pilatus Business
Aircraft Ltd., Product Support Department, 11755 Airport Way,
Broomfield, Colorado 80021; telephone: (303) 465-9099; facsimile: (303)
465-6040.
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-2005-20720; Directorate
Identifier 2005-CE-17-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
What events have caused this AD? The Federal Office for Civil
Aviation (FOCA), which is the airworthiness authority for Switzerland,
recently notified FAA that an unsafe condition may exist on certain
Pilatus Models PC-12 and PC-12/45 airplanes. The FOCA reports that an
abrupt nose down pitch condition occurred on a PC-12 airplane.
Investigation revealed that the pilot disconnected the autopilot
when the flaps were at a 40-degree selection.
Pilatus has determined that the pitch actuator sense circuitry
becomes over-active during a 40-degree flight phase. Therefore, Pilatus
designed a new pitch actuator that modifies sense output signals and
removes the flap in motion signal to the autopilot.
What is the potential impact if FAA took no action? This condition,
if not corrected, could result in an out-of-trim condition when the
flaps are at a 40-degree flight phase and the pilot disconnects the
autopilot. This condition could lead to reduced ability to control the
airplane.
Has FAA taken any action to this point? 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 certain Pilatus Models PC-12 and PC-
12/45 airplanes. This proposal was published in the Federal Register as
a notice of proposed rulemaking (NPRM) on April 13, 2005 (70 FR 19342).
The NPRM proposed to require you to insert the temporary revision into
the Limitations Section of the Pilot Operating Handbook (POH). The NPRM
also proposed to require you to replace the pitch actuator with an
improved design pitch actuator and make the necessary wiring and
circuit breaker changes, as applicable. Installing the improved design
pitch actuator would terminate the need for the temporary revision in
the POH.
Comments
Was the public invited to comment? We provided the public the
opportunity to participate in developing this AD. The following
presents the comments received on the proposal and FAA's response to
each comment:
Comment Issue: Change the Compliance Time for Replacing the Pitch
Actuator
What is the commenter's concern? Two commenters state the
requirement to replace the pitch actuator within 6 months after the
effective date of the AD may place an unnecessary burden on both the
operators and service centers.
The Pilatus PC-12 fleet consists of over 500 airplanes worldwide.
Because of material quantity constraints, the logistics associated with
replacing the pitch actuator within six months would be nearly
impossible for all operators.
Extensive flight-testing identified the unsafe condition associated
with
[[Page 33345]]
operation of the autopilot with 40-degree flaps.
The AD requires inserting a temporary revision into the Pilot
Operating Handbook (POH) prohibiting the use of the autopilot with the
flaps at the 40-degree position, which removes the risk of a major out
of trim condition.
The commenters request the compliance time for replacing the pitch
actuator be changed from ``Within the next 6 months after the effective
date of this AD, unless already done,'' to ``Before December 31,
2006.''
What is FAA's response to the concern? We partially agree with the
commenters.
Since it has been identified through flight-testing that the unsafe
condition can be avoided by inserting Temporary Revision No. 11 or No.
40 into the Limitation Section of the POH, we agree to extend the
compliance time for replacing the pitch actuator.
Extending the compliance time will allow the owners/operators more
time to get the pitch actuator replaced and allows the supplier to meet
the demand for parts in a timely manner. However, we rarely use a
specific calendar date to express compliance time and only then when
engineering analysis establishes a direct relationship between the date
and either the compliance ``threshold'' or the ``grace period.''
Basically, the commenters are requesting an additional 12 months to
replace the pitch actuator.
Therefore, we will change the final rule AD action and increase the
compliance time for replacing the pitch actuator to ``Within the next
18 months after the effective date of this AD, unless already done.''
Conclusion
What is FAA's final determination on this issue? We have carefully
reviewed the available data and determined that air safety and the
public interest require adopting the AD as proposed except for the
changes discussed above and minor editorial corrections. We have
determined that these changes and 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.
Changes to 14 CFR Part 39--Effect on the AD
How does the revision to 14 CFR part 39 affect this AD? On July 10,
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997,
July 22, 2002), which governs the FAA's AD system. This regulation now
includes material that relates to altered products, special flight
permits, and alternative methods of compliance. This material
previously was included in each individual AD. Since this material is
included in 14 CFR part 39, we will not include it in future AD
actions.
Costs of Compliance
How many airplanes does this AD impact? We estimate that this AD
affects 330 airplanes in the U.S. registry.
What is the cost impact of this AD on owners/operators of the
affected airplanes? We estimate the following costs to incorporate the
Pilot Operating Handbook (POH) Temporary Revision:
------------------------------------------------------------------------
Total cost Total cost
Labor cost Parts cost per on U.S.
Airplane operators
------------------------------------------------------------------------
1 work hour x $65 per hour = Not applicable. $65 $21,450
$65..
------------------------------------------------------------------------
Pilatus will provide warranty credit for replacing the pitch
actuator to the extent stated in the service information.
Authority for This Rulemaking
What authority does FAA have for issuing this rulemaking action?
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
Will this AD impact various entities? 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.
Will this AD involve a significant rule or regulatory action? 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-2005-20720; Directorate Identifier 2005-CE-17-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 adding a new AD to read as follows:
2005-11-06 Pilatus Aircraft Ltd.: Amendment 39-14108; Docket No.
FAA-2005-20720; Directorate Identifier 2005-CE-17-AD.
When Does This AD Become Effective?
(a) This AD becomes effective on July 18, 2005.
[[Page 33346]]
What Other ADs Are Affected By This Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects Models PC-12 and PC-12/45 airplanes,
Manufacturers Serial Numbers (MSN) 101 through 620, that are
certificated in any category.
What Is the Unsafe Condition Presented in This AD?
(d) This AD is the result of mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for
Switzerland. The actions specified in this AD are intended to
prevent an out-of-trim condition from occurring when the flaps are
at a 40-degree flight phase and the pilot disconnects the autopilot.
This condition could lead to reduced ability to control the
airplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Insert Temporary Within the next 90 The owner/operator
Revision No. 11 (Report No. days after July 18, holding at least a
02211) or No. 40 (Report 2005 (the effective private pilot
No. 01973-001) into the date of this AD), certificate as
Limitations Section of the unless already done. authorized by
PC-12 Pilot's Operating section 43.7 of the
Handbook (POH). Federal Aviation
Regulations (14 CFR
43.7) may modify
the POH as
specified in
paragraph (e)(1) of
this AD. Make an
entry into the
aircraft records
showing compliance
with this portion
of the AD following
section 43.9 of the
Federal Aviation
Regulations (14 CFR
43.9).
(2) Replace the pitch Within the next 18 Follow Pilatus PC12
actuator, part number (P/N) months after July Service Bulletin
985.92.03.161, with an 18, 2005 (the No. 22-004, dated
improved design pitch effective date of December 21, 2004.
actuator, P/N this AD), unless
985.92.03.164; and make the already done.
associated wiring and
circuit breaker changes (as
applicable).
(3) Remove the Temporary Before further The owner/operator
Revision to the POH flight after the holding at least a
specified in paragraph pitch actuator is private pilot
(e)(1) of this AD after the replaced with an certificate as
pitch actuator is replaced improved design authorized by
as required in paragraph pitch actuator. section 43.7 of the
(e)(2) of this AD. Federal Aviation
Regulations (14 CFR
43.7) may modify
the POH as
specified in
paragraph (e)(3) of
this AD. Make an
entry into the
aircraft records
showing compliance
with this portion
of the AD following
section 43.9 of the
Federal Aviation
Regulations (14 CFR
43.9).
(4) Do not install a P/N As of July 18, 2005 Not applicable.
985.92.03.161 pitch (the effective date
actuator. of this AD).
------------------------------------------------------------------------
May I Request an Alternative Method of Compliance?
(f) You may request a different method of compliance or a
different compliance time for this AD by following the procedures in
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to
your principal inspector. The principal inspector may add comments
and will send your request to the Manager, Standards Office, Small
Airplane Directorate, FAA. For information on any already approved
alternative methods of compliance, 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.
Is There Other Information That Relates to This Subject?
(g) Swiss AD Number HB-2005-128, effective date March 29, 2005,
also addresses the subject of this AD.
Does This AD Incorporate Any Material by Reference?
(h) You must do the actions required by this AD following the
instructions in Pilatus PC12 Service Bulletin No. 22-004, dated
December 21, 2004. The Director of the Federal Register approved the
incorporation by reference of this service bulletin in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this
service information, contact Pilatus Aircraft Ltd., Customer Liaison
Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 6208;
facsimile: +41 41 619 7311; e-mail: SupportPC12@pilatus-aircraft.com
or from Pilatus Business Aircraft Ltd., Product Support Department,
11755 Airport Way, Broomfield, Colorado 80021; telephone: (303) 465-
9099; facsimile: (303) 465-6040. 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-2005-20720;
Directorate Identifier 2005-CE-17-AD.
Issued in Kansas City, Missouri, on May 25, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-10949 Filed 6-7-05; 8:45 am]
BILLING CODE 4910-13-P
