Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes, 19342-19345 [05-7382]
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<![CDATA[
19342
§ 39.13
Federal Register / Vol. 70, No. 70 / Wednesday, April 13, 2005 / Proposed Rules
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
GROB-WERKE: Docket No. FAA–2005–
20589; Directorate Identifier 2005–CE–
12–AD.
When Is the Last Date I Can Submit
Comments on This Proposed AD?
(a) We must receive comments on this
proposed airworthiness directive (AD) by
May 13, 2005.
What Other ADs Are Affected by This
Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects Model G120A airplanes,
all serial numbers, 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
Germany. We are issuing this AD to detect
and correct cracks and damage in the nose
landing gear (NLG) assembly, which could
result in failure of the NLG. This failure
could lead to a hard landing and/or loss of
control of the airplane during landing
operations.
What Must I Do To Address This Problem?
(e) To address this problem, you must do
the following:
Actions
Compliance
Procedures
(1) Inspect the nose landing gear (NLG) assembly for cracks or damaged (defective)
welding seams. Pay special attention to the
NLG swivel tube and the engine truss in the
area of the NLG attachment.
(2) If you find cracks or defects during any inspection required in paragraph (e)(1) of this
AD, replace the cracked or defective part.
Initially inspect within the next 50 hours timein-service (TIS) after the effective date of
this AD, unless already done. Repetitively
inspect thereafter at intervals not to exceed
50 hours TIS.
Replace before further flight after the inspection in which cracks and/or defects are
found. After you replace the cracked or defective part, continue with the repetitive inspections required paragraph (e)(1) of this
AD at the 50 hours TIS intervals.
Follow GRUB Service Bulletin No. MSB1121–
055 dated November 26, 2004.
Note: The compliance time in this AD is
different than the compliance time in GROB
Service Bulletin No. MSB1121–055 dated
November 26, 2004. The compliance time in
this AD takes precedence over the
compliance time in the service information.
Issued in Kansas City, Missouri, on April
6, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–7384 Filed 4–12–05; 8:45 am]
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 Karl Schletzbaum,
Aerospace Engineer, FAA, Small Airplane
Directorate, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone: (816) 329–
4146; facsimile: (816) 329–4090.
BILLING CODE 4910–13–P
Is There Other Information That Relates to
This Subject?
(g) German AD Number D–2004–514,
effective date: December 9, 2004, also
addresses the subject of this AD.
AGENCY:
May I Get Copies of the Documents
Referenced in This AD?
(h) To get copies of the documents
referenced in this AD, contact GROB Luftund Raumfahrt, Lettenbachstrasse 9, D–
86874 Tussenhausen-Mattsies, Federal
Republic of Germany; telephone: 011 49 8268
998139; facsimile: 011 49 8268 998200. 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, or on the Internet at https://dms.dot.gov.
This is docket number FAA–2005–20589;
Directorate Identifier 2005–CE–12–AD.
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Pilatus Aircraft Ltd. (Pilatus)
Models PC–12 and PC–12/45 airplanes.
This proposed AD would require you to
insert a temporary revision into the
Limitations Section of the Pilot
Operating Handbook (POH). This
proposed AD would also 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 terminates the need for the
temporary revision in the POH. This
proposed AD results from mandatory
continuing airworthiness information
(MCAI) issued by the airworthiness
authority for Switzerland. We are
issuing this proposed 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: We must receive any comments
on this proposed AD by May 13, 2005.
ADDRESSES: Use one of the following to
submit comments on this proposed AD:
• DOT Docket Web Site: Go to http:/
/dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide Rulemaking Web
Site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
001.
• Fax: 1–202–493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
To get the service information
identified in this proposed AD, contact
Pilatus Aircraft Ltd., Customer Liaison
Manager, CH–6371 Stans, Switzerland;
telephone: +41 41 619 6208; facsimile:
+41 41 619 7311; e-mail:
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15:00 Apr 12, 2005
Jkt 205001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20720; Directorate
Identifier 2005–CE–17–AD]
RIN 2120–AA64
Airworthiness Directives; Pilatus
Aircraft Ltd. Models PC–12 and PC–12/
45 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
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Follow GROB Service Bulletin No. MSB1121–
055 dated November 26, 2004.
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Federal Register / Vol. 70, No. 70 / Wednesday, April 13, 2005 / Proposed Rules
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 comments to this
proposed AD, go to https://dms.dot.gov.
This is docket number 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:
Comments Invited
How do I comment on this proposed
AD? We invite you to submit any
written relevant data, views, or
arguments regarding this proposal. Send
your comments to an address listed
under ADDRESSES. Include the docket
number, ‘‘FAA–2005–20720; Directorate
Identifier 2005–CE–17–AD’’ at the
beginning of your comments. We will
post all comments we receive, without
change, to https://dms.dot.gov, including
any personal information you provide.
We will also post a report summarizing
each substantive verbal contact with
FAA personnel concerning this
proposed rulemaking. Using the search
function of our docket Web site, anyone
can find and read the comments
received into any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). This is
docket number FAA–2005–20720;
Directorate Identifier 2005-CE–17-AD.
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78) or you may visit
https://dms.dot.gov.
Are there any specific portions of this
proposed AD I should pay attention to?
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this proposed AD. If you contact us
through a nonwritten communication
and that contact relates to a substantive
part of this proposed AD, we will
summarize the contact and place the
summary in the docket. We will
consider all comments received by the
closing date and may amend this
proposed AD in light of those comments
and contacts.
Docket Information
Where can I go to view the docket
information? You may view the AD
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15:00 Apr 12, 2005
Jkt 205001
docket that contains the proposal, any
comments received, and any final
disposition in person at the DMS Docket
Offices between 9 a.m. and 5 p.m.
(eastern standard time), Monday
through Friday, except Federal holidays.
The Docket Office (telephone 1–800–
647–5227) is located on the plaza level
of the Department of Transportation
NASSIF Building at the street address
stated in ADDRESSES. You may also view
the AD docket on the Internet at
https://dms.dot.gov. The comments will
be available in the AD docket shortly
after the DMS receives them.
Discussion
What events have caused this
proposed 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 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.
Is there service information that
applies to this subject? Pilatus has
issued PC12 Service Bulletin No. 22–
004, dated December 21, 2004; and
Temporary Revision No. 11 (Report No.
02211) or No. 40 (Report No. 01973–
001).
What are the provisions of this service
information? The service bulletin
includes procedures for:
—Replacing the pitch actuator, part
number (P/N) 985.92.03.161, with an
improved design pitch actuator, P/N
985.92.03.164; and
—Making the associated wiring and
circuit breaker changes, as applicable.
What action did the FOCA take? The
FOCA classified this service bulletin as
mandatory and issued Swiss AD
Number HB–2005–128, effective date
March 29, 2005, to ensure the continued
airworthiness of these airplanes in
Switzerland.
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19343
Did the FOCA inform the United
States under the bilateral airworthiness
agreement? These Pilatus PC–12 and
PC–12/45 airplanes are manufactured in
Switzerland and are type-certificated for
operation in the United States under the
provisions of section 21.29 of the
Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral
airworthiness agreement.
Under this bilateral airworthiness
agreement, the FOCA has kept us
informed of the situation described
above.
FAA’s Determination and Requirements
of This Proposed AD
What has FAA decided? We have
examined the FOCA’s findings,
reviewed all available information, and
determined that AD action is necessary
for products of this type design that are
certificated for operation in the United
States.
Since the unsafe condition described
previously is likely to exist or develop
on Pilatus Models PC–12 and PC–12/45
airplanes of the same type design that
are registered in the United States, we
are proposing AD action 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 would this proposed AD
require? This proposed AD would
require you to insert the applicable
temporary revision into the Pilot
Operating Handbook (POH) and
incorporate the actions in the
previously-referenced service bulletin.
The POH revision is no longer necessary
when the improved design pitch
actuator referenced in the service
information is installed.
How does the revision to 14 CFR part
39 affect this proposed AD? On July 10,
2002, we published a new version of 14
CFR part 39 (67 FR 47997, July 22,
2002), which governs 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 would this
proposed AD impact? We estimate that
this proposed AD affects 330 airplanes
in the U.S. registry.
What would be the cost impact of this
proposed AD on owners/operators of the
affected airplanes? We estimate the
following costs to incorporate the
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19344
Federal Register / Vol. 70, No. 70 / Wednesday, April 13, 2005 / Proposed Rules
proposed Pilot Operating Handbook
(POH) Temporary Revision:
Labor cost
Parts cost
Total cost
per airplane
Total cost
on U.S.
operators
1 work hour × $65 per hour = $65 ............................................
Not applicable ..................................................
$65
$21,450
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
Would this proposed AD impact
various entities? We have determined
that this proposed AD would not have
federalism implications under Executive
Order 13132. This proposed AD would
not have a substantial direct effect on
the States, on the relationship between
the national Government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
Would this proposed AD involve a
significant rule or regulatory action? For
the reasons discussed above, I certify
that this proposed 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 proposed 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 ‘‘AD Docket FAA–2005–20720;
Directorate Identifier 005–CE–17–AD’’
in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
proposes to amend 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Pilatus Aircraft Ltd.: Docket No. FAA–2005–
20720; Directorate Identifier 2005–CE–
17–AD.
When Is the Last Date I Can Submit
Comments on This Proposed AD?
(a) We must receive comments on this
proposed airworthiness directive (AD) by
May 13, 2005.
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 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).
Within the next 6 months after 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 the portion of the AD following section 43.9 of Federal Aviation
Regulations (14 CFR 43.9).
Follow Pilatus PC12 Service Bulletin No. 22–
004, dated December 21, 2004.
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19345
Actions
Compliance
Procedures
(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.
Before further flight after the pitch actuator is
replaced with an improved design pitch actuator.
(4) Do not install a P/N 985.92.03.161 pitch actuator.
As of the effective date of this AD ...................
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 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.
May I Request an Alternative Method of
Compliance?
DEPARTMENT OF TRANSPORTATION
(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.
Federal Aviation Administration
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.
May I Get Copies of the Documents
Referenced in this AD?
(h) To get copies of the documents
referenced 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, or on the Internet at https://dms.dot.gov.
This is docket number FAA–2005–20720;
Directorate Identifier 2005–CE–17–AD.
Issued in Kansas City, Missouri, on April
6, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–7382 Filed 4–12–05; 8:45 am]
BILLING CODE 4910–13–P
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14 CFR Part 39
[Docket No. FAA–2005–20917; Directorate
Identifier 2004–NM–85–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–100, –200B, –200F, –200C,
–100B, –300, –100B SUD, –400, –400D,
and –400F Series Airplanes; and Model
747SR Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede two existing airworthiness
directives (AD) for certain Boeing
transport category airplanes. One AD
currently requires doing certain
inspections to detect cracks and
corrosion around the lower bearing of
the actuator attach fittings of the
inboard and outboard flaps; repairing if
necessary; and either overhauling the
fittings or replacing them, which when
done on certain actuator attach fittings
ends the repetitive inspections. The
other AD currently requires certain
other inspections to detect
discrepancies of the fittings of the flaps,
and follow-on and corrective actions if
necessary, which ends the repetitive
inspections of the first AD. For certain
airplanes, this proposed AD would
require new inspections for
discrepancies of the attach fittings of the
flaps, and follow-on and corrective
actions if necessary, which ends the
repetitive inspections of both existing
ADs. For all airplanes, this proposed AD
would require repetitive overhaul/
replacements of the fittings of both the
inboard and outboard flaps. This
proposed AD is prompted by reports of
cracks of the attach fittings of the
trailing edge flaps. We are proposing
this AD to prevent cracking and other
damage of the actuator attach fittings of
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Sfmt 4702
the trailing edge flaps, which could
result in abnormal operation or
retraction of a trailing edge flap, and
possible loss of controllability of the
airplane.
DATES: We must receive comments on
this proposed AD by May 31, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web Site: Go to http:
//dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide Rulemaking Web
Site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: room PL–401 on the
plaza level of the Nassif Building, 400
Seventh Street SW., Washington, DC,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
You can get the service information
identified in this proposed AD from
Boeing Commercial Airplanes, P.O. Box
3707, Seattle, Washington 98124–2207.
You may examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Gary
Oltman, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98055–4056; telephone (425) 917–6443;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Docket Management System (DMS)
The FAA has implemented new
procedures for maintaining AD dockets
electronically. As of May 17, 2004, new
AD actions are posted on DMS and
assigned a docket number. We track
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]]>Agencies
[Federal Register Volume 70, Number 70 (Wednesday, April 13, 2005)]
[Proposed Rules]
[Pages 19342-19345]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-7382]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20720; Directorate Identifier 2005-CE-17-AD]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and
PC-12/45 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45
airplanes. This proposed AD would require you to insert a temporary
revision into the Limitations Section of the Pilot Operating Handbook
(POH). This proposed AD would also 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 terminates the need for the temporary
revision in the POH. This proposed AD results from mandatory continuing
airworthiness information (MCAI) issued by the airworthiness authority
for Switzerland. We are issuing this proposed 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: We must receive any comments on this proposed AD by May 13,
2005.
ADDRESSES: Use one of the following to submit comments on this proposed
AD:
DOT Docket Web Site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide Rulemaking Web Site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-001.
Fax: 1-202-493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
To get the service information identified in this proposed AD,
contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans,
Switzerland; telephone: +41 41 619 6208; facsimile: +41 41 619 7311; e-
mail:
[[Page 19343]]
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 comments to this proposed AD, go to https://dms.dot.gov.
This is docket number 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:
Comments Invited
How do I comment on this proposed AD? We invite you to submit any
written relevant data, views, or arguments regarding this proposal.
Send your comments to an address listed under ADDRESSES. Include the
docket number, ``FAA-2005-20720; Directorate Identifier 2005-CE-17-AD''
at the beginning of your comments. We will post all comments we
receive, without change, to https://dms.dot.gov, including any personal
information you provide. We will also post a report summarizing each
substantive verbal contact with FAA personnel concerning this proposed
rulemaking. Using the search function of our docket Web site, anyone
can find and read the comments received into any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
This is docket number FAA-2005-20720; Directorate Identifier 2005-CE-
17-AD. You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78) or you
may visit https://dms.dot.gov.
Are there any specific portions of this proposed AD I should pay
attention to? We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of this
proposed AD. If you contact us through a nonwritten communication and
that contact relates to a substantive part of this proposed AD, we will
summarize the contact and place the summary in the docket. We will
consider all comments received by the closing date and may amend this
proposed AD in light of those comments and contacts.
Docket Information
Where can I go to view the docket information? You may view the AD
docket that contains the proposal, any comments received, and any final
disposition in person at the DMS Docket Offices between 9 a.m. and 5
p.m. (eastern standard time), Monday through Friday, except Federal
holidays. The Docket Office (telephone 1-800-647-5227) is located on
the plaza level of the Department of Transportation NASSIF Building at
the street address stated in ADDRESSES. You may also view the AD docket
on the Internet at https://dms.dot.gov. The comments will be available
in the AD docket shortly after the DMS receives them.
Discussion
What events have caused this proposed 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.
Is there service information that applies to this subject? Pilatus
has issued PC12 Service Bulletin No. 22-004, dated December 21, 2004;
and Temporary Revision No. 11 (Report No. 02211) or No. 40 (Report No.
01973-001).
What are the provisions of this service information? The service
bulletin includes procedures for:
--Replacing the pitch actuator, part number (P/N) 985.92.03.161, with
an improved design pitch actuator, P/N 985.92.03.164; and
--Making the associated wiring and circuit breaker changes, as
applicable.
What action did the FOCA take? The FOCA classified this service
bulletin as mandatory and issued Swiss AD Number HB-2005-128, effective
date March 29, 2005, to ensure the continued airworthiness of these
airplanes in Switzerland.
Did the FOCA inform the United States under the bilateral
airworthiness agreement? These Pilatus PC-12 and PC-12/45 airplanes are
manufactured in Switzerland and are type-certificated for operation in
the United States under the provisions of section 21.29 of the Federal
Aviation Regulations (14 CFR 21.29) and the applicable bilateral
airworthiness agreement.
Under this bilateral airworthiness agreement, the FOCA has kept us
informed of the situation described above.
FAA's Determination and Requirements of This Proposed AD
What has FAA decided? We have examined the FOCA's findings,
reviewed all available information, and determined that AD action is
necessary for products of this type design that are certificated for
operation in the United States.
Since the unsafe condition described previously is likely to exist
or develop on Pilatus Models PC-12 and PC-12/45 airplanes of the same
type design that are registered in the United States, we are proposing
AD action 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 would this proposed AD require? This proposed AD would require
you to insert the applicable temporary revision into the Pilot
Operating Handbook (POH) and incorporate the actions in the previously-
referenced service bulletin. The POH revision is no longer necessary
when the improved design pitch actuator referenced in the service
information is installed.
How does the revision to 14 CFR part 39 affect this proposed AD? On
July 10, 2002, we published a new version of 14 CFR part 39 (67 FR
47997, July 22, 2002), which governs 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 would this proposed AD impact? We estimate that
this proposed AD affects 330 airplanes in the U.S. registry.
What would be the cost impact of this proposed AD on owners/
operators of the affected airplanes? We estimate the following costs to
incorporate the
[[Page 19344]]
proposed Pilot Operating Handbook (POH) Temporary Revision:
----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work hour x $65 per hour = $65............. Not applicable................. $65 $21,450
----------------------------------------------------------------------------------------------------------------
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
Would this proposed AD impact various entities? We have determined
that this proposed AD would not have federalism implications under
Executive Order 13132. This proposed AD would not have a substantial
direct effect on the States, on the relationship between the national
Government and the States, or on the distribution of power and
responsibilities among the various levels of government.
Would this proposed AD involve a significant rule or regulatory
action? For the reasons discussed above, I certify that this proposed
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 proposed 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
``AD Docket FAA-2005-20720; Directorate Identifier 005-CE-17-AD'' in
your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 14
CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
Pilatus Aircraft Ltd.: Docket No. FAA-2005-20720; Directorate
Identifier 2005-CE-17-AD.
When Is the Last Date I Can Submit Comments on This Proposed AD?
(a) We must receive comments on this proposed airworthiness
directive (AD) by May 13, 2005.
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 Within the next 90 The owner/operator
No. 11 (Report No. 02211) or days after the holding at least
No. 40 (Report No. 01973-001) effective date of a private pilot
into the Limitations Section of this AD, unless certificate as
the PC-12 Pilot's Operating already done. authorized by
Handbook (POH). 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 the portion
of the AD
following section
43.9 of Federal
Aviation
Regulations (14
CFR 43.9).
(2) Replace the pitch actuator, Within the next 6 Follow Pilatus
part number (P/N) months after the PC12 Service
985.92.03.161, with an improved effective date of Bulletin No. 22-
design pitch actuator, P/N this AD, unless 004, dated
985.92.03.164; and make the already done. December 21,
associated wiring and circuit 2004.
breaker changes (as applicable).
[[Page 19345]]
(3) Remove the Temporary Before further The owner/operator
Revision to the POH specified flight after the holding at least
in paragraph (e)(1) of this AD pitch actuator is a private pilot
after the pitch actuator is replaced with an certificate as
replaced as required in improved design authorized by
paragraph (e)(2) of this AD. pitch actuator. section 43.7 of
the Federal
Aviation
Regulations (14
CFR 43.7) may
modify the POH as
specified in
paragraph (e)(3)
of 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 the Not applicable.
985.92.03.161 pitch actuator. 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.
May I Get Copies of the Documents Referenced in this AD?
(h) To get copies of the documents referenced 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, or on the
Internet at https://dms.dot.gov. This is docket number FAA-2005-
20720; Directorate Identifier 2005-CE-17-AD.
Issued in Kansas City, Missouri, on April 6, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-7382 Filed 4-12-05; 8:45 am]
BILLING CODE 4910-13-P
