[Federal Register Volume 64, Number 120 (Wednesday, June 23, 1999)]
[Proposed Rules]
[Pages 33445-33447]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-15927]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-CE-119-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 inspecting
all flap actuators in the internal gear system to assure that correct
end-play and backlash measurements exist, and accomplishing any
corrective adjustments as necessary. The proposed AD would also require
incorporating a temporary revision into the Pilot's Operating Handbook
(POH) in order to update operating procedures for the flap actuators;
and would require incorporating temporary revisions to the maintenance
manual in order to make the proposed inspection part of the future
maintenance program. 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 premature wear of the internal gear system caused
by excessive backlash in the flight control flap actuators, which could
eventually result in loss of actuator output with possible reduced or
loss of airplane control.
DATES: Comments must be received on or before July 28, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 98-CE-119-AD, Room 1558, 601 E. 12th
Street, 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, 1201 Walnut, suite 900,
Kansas City, Missouri 64106; telephone: (816) 426-6932; facsimile:
(816) 426-2169.
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. 98-CE-119-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. 98-CE-119-AD, Room 1558, 601 E. 12th Street, 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 excessive backlash
found in the flap actuators of the internal gear system. Excessive
backlash will lead to premature wear of the gear.
This condition, if not detected and corrected, could result in
internal failure of the internal gear system with loss of actuator
output and possible reduced or loss of airplane control.
Relevant Service Information
Pilatus has issued Service Bulletin No. 27-005, November 18, 1998,
which specifies procedures for:
--Inspecting all flap actuators in the internal gear system to assure
that correct end-play and backlash measurements exist;
--Incorporating both Temporary Revision No. 27-04, and Temporary
Revision No. 04-01, both dated November 18, 1998; into the Pilatus PC-
12 Maintenance Manual; and
--Incorporating PC-12 Pilot's Operating Handbook, Pilatus Report No.
01973-001, Temporary Revision No. 4, Flap Actuators, dated November 18,
1998.
The FOCA of Switzerland classified this service bulletin as
mandatory and issued Swiss AD HB 98-460, dated November 23, 1998, 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.
[[Page 33446]]
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 that incorporate a certain flight control flap
actuator and that are registered in the United States, the FAA is
proposing AD action. The proposed AD would require inspecting all flap
actuators in the internal gear system to assure that correct end-play
and backlash measurements exist, and accomplishing any corrective
adjustments as necessary. The proposed AD would also require
incorporating the temporary revision into the POH in order to update
operating procedures for the flap actuators; and would require
incorporating temporary revisions to the maintenance manual in order to
make the proposed inspection part of the future maintenance program.
The affected airplanes could incorporate one of the following
flight control flap actuators:
--Pilatus part number (P/N) 978.71.20.302--Actuator, Linear (951D100-
5);
--Pilatus P/N 978.71.20.303--Actuator, Linear (951D100-7); and
--Pilatus P/N 978.71.20.304--Actuator, Linear (951D100-9).
Accomplishment of the proposed inspection would be in accordance
with Pilatus Service Bulletin No. 27-005, November 18, 1998. The
proposed adjustments, if necessary, would be accomplished in accordance
with the maintenance manual.
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 6
workhours per airplane to accomplish the proposed action, and that the
average labor rate is approximately $60 an hour. The manufacturer will
provide parts free-of-charge to the owners/operators of the affected
aircraft. Based on these figures, the total cost impact of the proposed
AD on U.S. operators is estimated to be $24,840, or $360 per airplane.
Incorporating the proposed POH and maintenance manual revisions may
be performed by 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), and must be entered into the aircraft
records showing compliance with the proposed AD in accordance with
section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). The
only cost impact the proposed POH and maintenance manual revision
requirements impose is the time it would take each owner/operator of
the affected airplanes to incorporate this information into the POH and
maintenance manual.
Regulatory Impact
The regulations proposed herein 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. Therefore, in
accordance with Executive Order 12612, it is determined that this
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
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. 98-CE-119-AD.
Applicability: Models PC-12 and PC-12/45 airplanes, manufacturer
serial numbers (MSN) 101 through MSN 236; certificated in any
category, that have one of the following flight control flap
actuators installed:
--Pilatus part number (P/N) 978.71.20.302--Actuator, Linear
(951D100-5);
--Pilatus P/N 978.71.20.303--Actuator, Linear (951D100-7); and
--Pilatus P/N 978.71.20.304-- Actuator, Linear (951D100-9).
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 (f) 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 premature wear of the internal gear system caused by
excessive backlash in the flight control flap actuators, which could
eventually result in loss of actuator output with possible reduced
or loss of airplane control, accomplish the following:
(a) Within the next 50 hours time-in-service (TIS) after the
effective date of this AD, inspect all flap actuators in the
internal gear system to assure that correct end-play and backlash
measurements exist, in accordance with the ACCOMPLISHMENT
INSTRUCTIONS section of Pilatus Service Bulletin No. 27-005,
November 18, 1998. Prior to further flight, perform any corrective
adjustments, as necessary, in accordance with the maintenance
manual.
(b) As of the effective date of this AD, no person may install,
on any airplane, a flap actuator that has not been inspected and
adjusted (as necessary) as required by paragraph (a) this AD.
(c) Prior to further flight after the inspection and possible
modification required by paragraph (a) of this AD, accomplish the
following:
(1) Insert Pilatus Report No. 01973-001, Temporary Revision No.
4, Flap Actuators, dated November 18, 1998, into the Pilot's
Operating Handbook (POH).
(2) Insert Temporary Revision No. 27-04, and Temporary Revision
No. 04-01, both dated November 18, 1998; into the Pilatus PC-12
Maintenance Manual.
(d) Accomplishment of the POH revision and maintenance manual
insertions, as required by paragraph (c) of this AD, may be
[[Page 33447]]
performed by 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), and must be entered into the aircraft
records showing compliance with this AD in accordance with section
43.9 of the Federal Aviation Regulations (14 CFR 43.9).
(e) 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.
(f) 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, 1201 Walnut,
suite 900, 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.
(g) Questions or technical information related to Pilatus
Service Bulletin No. 27-005, dated November 18, 1998, 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, Room 1558, 601 E.
12th Street, Kansas City, Missouri 64106.
Note 3: The subject of this AD is addressed in Swiss AD HB 98-
460, dated November 23, 1998.
Issued in Kansas City, Missouri, on June 16, 1999.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 99-15927 Filed 6-22-99; 8:45 am]
BILLING CODE 4910-13-U
