[Federal Register Volume 64, Number 225 (Tuesday, November 23, 1999)]
[Proposed Rules]
[Pages 65666-65668]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-30521]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-CE-64-AD]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and
PC-12/45 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to adopt a new airworthiness directive
(AD) that would apply to certain Pilatus Aircraft Ltd. (Pilatus) Models
PC-12 and PC-12/45 airplanes. The proposed AD would require replacing
the stick pusher capstan and the stick pusher servo with parts of
improved design. The proposed AD is the result of mandatory continuing
airworthiness information (MCAI) issued by the airworthiness authority
for Switzerland. The actions specified by the proposed AD are intended
to prevent improper operation of the stick pusher system caused by the
existing design configuration, which could result in loss of control of
the airplane during a stall.
DATES: Comments must be received on or before December 23, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 99-CE-64-AD, 901 Locust, Room 506, Kansas
City, Missouri 64106. Comments may be inspected at this location
between 8 a.m. and 4 p.m., Monday through Friday, holidays excepted.
Service information that applies to the proposed AD may be obtained
from Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans,
Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 610 33 51.
This information also may be examined at the Rules Docket at the
address above.
FOR FURTHER INFORMATION CONTACT: Mr. Roman T. Gabrys, Aerospace
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone: (816) 329-4141; facsimile: (816) 329-
4090.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report that summarizes each FAA-public contact concerned
with the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 99-CE-64-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Central Region, Office of the Regional Counsel, Attention:
Rules Docket No. 99-CE-64-AD, 901 Locust, Room 506, Kansas City,
Missouri 64106.
Discussion
The Federal Office for Civil Aviation (FOCA), which is the
airworthiness authority for Switzerland, recently notified the FAA that
an unsafe condition may exist on certain Pilatus Models PC-12 and PC-
12/45 airplanes. The FOCA of Switzerland reports high tolerances found
in the current stick pusher system design. These tolerances were found
during Pilatus's follow-on testing of the Models PC-12 and PC-12/45
airplanes.
The stick pusher system is incorporated to meet certification stall
requirements. Higher tolerances can lead to a higher control column
force than was provided for during the original design of the aircraft.
Higher control forces will not allow the stick pusher system to operate
properly in preventing a stall. This condition, if not corrected in a
timely manner, could result in loss of control of the airplane during a
stall.
[[Page 65667]]
Relevant Service Information
Pilatus has issued Service Bulletin No. 22-003, dated June 24,
1999, which specifies replacing the stick pusher capstan and the stick
pusher servo with parts of improved design. The procedures to
accomplish these actions are included in the applicable maintenance
manual.
The FOCA of Switzerland classified this service bulletin as
mandatory and issued Swiss AD HB 99-406, dated August 16, 1999, in
order to assure the continued airworthiness of these airplanes in
Switzerland.
The FAA's Determination
This airplane model is manufactured in Switzerland and is 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. Pursuant to this
bilateral airworthiness agreement, the FOCA of Switzerland has kept the
FAA informed of the situation described above.
The FAA has examined the findings of the FOCA of Switzerland;
reviewed all available information, including the service information
referenced above; and determined that AD action is necessary for
products of this type design that are certificated for operation in the
United States.
Explanation of the Provisions of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Pilatus PC-12 and PC-12/45 airplanes of the
same type design registered in the United States, the FAA is proposing
AD action. The proposed AD would require replacing the stick pusher
capstan and the stick pusher servo with parts of improved design.
Accomplishment of the proposed action would be required in accordance
with the applicable maintenance manual, as specified in Pilatus Service
Bulletin No. 22-003, dated June 24, 1999.
Cost Impact
The FAA estimates that 69 airplanes in the U.S. registry would be
affected by the proposed AD, that it would take approximately 8
workhours per airplane to accomplish the proposed action, and that the
average labor rate is approximately $60 an hour. Pilatus will provide
parts free of charge until March 2000. Based on these figures, the
total cost impact of the proposed AD on U.S. operators is estimated to
be $33,120, or $480 per airplane.
Regulatory Impact
The proposed rule does not have Federalism implications as defined
in Exectutive Order No. 13132. This means it would not have substantial
direct effects 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. The FAA has
not consulted with state authorities prior to publication of this
proposed rule.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated,
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. A copy of the draft regulatory evaluation
prepared for this action has been placed in the Rules Docket. A copy of
it may be obtained by contacting the Rules Docket at the location
provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
Pilatus Aircraft Ltd.: Docket No. 99-CE-64-AD.
Applicability: Models PC-12 and PC-12/45 airplanes, manufacturer
serial number (MSN) 101 through MSN 180, certificated in any
category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
modified, altered, or repaired in the area subject to the
requirements of this AD. For airplanes that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (d) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated in the body of this AD, unless
already accomplished.
To prevent improper operation of the stick pusher system caused
by the existing design configuration, which could result in the loss
of control of the airplane during a stall, accomplish the following:
(a) Within the next 50 hours time-in-service (TIS) after the
effective date of this AD, replace the stick pusher capstan and
stick pusher servo with parts of improved design, in accordance with
the applicable maintenance manual, as specified in Pilatus Service
Bulletin No. 22-003, dated June 24, 1999. The new part numbers (P/N)
are as follows:
(1) Stick Pusher Capstan: P/N 978.61.11.124 (or FAA-approved
equivalent part number); and
(2) Stick Pusher Servo: P/N 978.61.11.103 (or FAA-approved
equivalent part number).
(b) As of the effective date of this AD, no person may install,
on any of the affected airplanes, a stick pusher capstan or stick
pusher servo that is not of the part number specified in paragraphs
(a)(1) and (a)(2) of this AD, respectively.
(c) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
(d) An alternative method of compliance or adjustment of the
compliance times that provides an equivalent level of safety may be
approved by the Manager, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106. The request shall be
forwarded through an appropriate FAA Maintenance Inspector, who may
add comments and then send it to the Manager, Small Airplane
Directorate.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Small Airplane Directorate.
(e) Questions or technical information related to Pilatus
Service Bulletin No. 22-003, dated June 24, 1999, should be directed
to Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans,
Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 610 33
51. This service information may be examined at the FAA, Central
Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas
City, Missouri 64106.
Note 3: The subject of this AD is addressed in Swiss AD HB 99-
406, dated August 16, 1999.
[[Page 65668]]
Issued in Kansas City, Missouri, on November 15, 1999.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-30521 Filed 11-22-99; 8:45 am]
BILLING CODE 4910-13-P
