[Federal Register Volume 64, Number 123 (Monday, June 28, 1999)]
[Unknown Section]
[Pages 34526-34528]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-16277]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-CE-122-AD; Amendment 39-11211; AD 99-14-03]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and
PC-12/45 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes Airworthiness Directive (AD) 98-13-
08, which currently requires replacing and re-routing the power return
cables on the starter generator and the generator 2 on certain Pilatus
Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. AD 98-13-
08 also requires inserting a temporary revision to the pilot operating
handbook (POH), and installing a placard near the standby magnetic
compass. This AD retains the actions currently required by AD 98-13-08
on all airplanes affected by that AD, and requires replacing the
temporary revision to the POH and the placard near the standby magnetic
compass with an improved procedural POH revision and placard. This AD
also requires the placard and the temporary revision to the POH for
additional manufacturer serial number Models PC-12 and PC-12/45
airplanes; and requires accomplishing improved Standby Magnetic Compass
Swing procedures and incorporating a temporary revision to the
maintenance manual on all of the affected airplanes. This AD is the
result of mandatory continuing airworthiness information (MCAI) issued
by the airworthiness authority for Switzerland. The actions specified
by this AD are intended to prevent directional deviation on the standby
magnetic compass caused by modifications made to the airplane since
manufacture, which could result in flight-path deviation during
critical phases of flight.
DATES: Effective August 17, 1999.
The incorporation by reference of Pilatus PC-12 Maintenance Manual
Temporary Revision No. 34-03, dated July 16, 1998, as specified in
Pilatus Service Bulletin No. 34-006, dated September 3, 1998, as listed
in the regulations is approved by the Director of the Federal Register
as of August 17, 1999.
The incorporation by reference of Pilatus PC XII Service Bulletin
No. 24-002, Rev. No. 1, dated September 20, 1996, as listed in the
regulations was previously approved by the Director of Federal Register
as of July 31, 1998 (63 FR 32975, July 17, 1998).
ADDRESSES: Service information that applies to this AD may be obtained
from Pilatus Aircraft Ltd., Marketing Support Department, CH-6370
Stans, Switzerland; telephone: +41 41-6196 233; facsimile: +41 41-6103
351. This information may also be examined at the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 98-CE-122-AD, Room 1558, 601 E. 12th
Street, Kansas City, Missouri 64106; or at the Office of the Federal
Register, 800 North Capitol Street, NW, suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Roman T. Gabrys, Aerospace Engineer,
FAA, Small Airplane Directorate, 1201 Walnut, suite 900, Kansas City,
Missouri 64106; telephone: (816) 426-6934; facsimile: (816) 426-2169.
SUPPLEMENTARY INFORMATION:
Events Leading to the Issuance of This AD
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 was published in the Federal
Register as a notice of proposed rulemaking (NPRM) on April 14, 1999
(64 FR 18382). The NPRM proposed to supersede AD 98-13-08, Amendment
39-10596 (63 FR 32975, June 17, 1998). AD 98-13-08 currently requires
replacing and re-routing the power return cables on the starter
generator and generator 2; inserting a temporary revision to the POH;
and installing a placard near the standby magnetic compass, using at
least \1/8\inch letters, with the following words:
``STANDBY COMPASS FOR CORRECT READING CHECK: WINDSHIELD DE-ICE LH & RH
HEAVY & COOLING SYSTEM OFF.''
The NPRM proposed to retain the actions currently required by AD
98-13-08 on all airplanes affected by that AD (manufacturer serial
numbers 101 through 147), and would require replacing the temporary
revision to the POH and the placard near the standby magnetic compass
with an improved procedural POH revision and placard. The NPRM also
proposed to require the placard and the temporary revision to the POH
for additional manufacturer serial number Models PC-12 and PC-12/45
airplanes; and would require accomplishing improved Standby Magnetic
Compass Swing procedures and incorporating a temporary revision
[[Page 34527]]
to the maintenance manual on all of the affected airplanes. The placard
will incorporate the following language:
``STANDBY COMPASS FOR CORRECT READING SWITCH: AVIONICS ON NAV &
INSTRUMENT LIGHTING AS REQUIRED WINDSHIELD DE-ICE LH & RH OFF AUXILIARY
HEATING SYSTEMS OFF AUXILIARY COOLING SYSTEM OFF''
Accomplishment of the proposed replacement and re-routing of the
power return cables as specified in the NPRM would be required in
accordance with Pilatus PC XII Service Bulletin No. 24-002, Rev. No. 1,
dated September 20, 1996.
The proposed Standby Magnetic Compass Swing procedures as specified
in the NPRM would be accomplished in accordance with PC-12 Maintenance
Manual Temporary Revision No. 34-03, dated July 16, 1998, as specified
in Pilatus Service Bulletin No. 34-006, dated September 3, 1998.
The NPRM was the result of mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for
Switzerland.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposed rule or the FAA's determination of the cost to the public.
The FAA's Determination
After careful review of all available information related to the
subject presented above, the FAA has determined that air safety and the
public interest require the adoption of the rule as proposed except for
minor editorial corrections. The FAA has determined that these minor
corrections will not change the meaning of the AD and will not add any
additional burden upon the public than was already proposed.
Cost Impact
The FAA estimates that 70 airplanes in the U.S. registry will be
affected by this AD.
Approximately 40 of these airplanes are affected by the power
return cable replacement and re-routing requirements that are being
retained from AD 98-13-08. The FAA estimates that it will take
approximately 12 workhours per airplane to accomplish these actions,
and that the average labor rate is approximately $60 an hour. Pilatus
will provide parts at no cost to the owners/operators of the affected
airplanes. Based on these figures, the cost impact of the replacement
and re-routing requirements on U.S. operators is $28,800, or $720 per
airplane. This AD imposes no additional replacement and re-routing cost
impact upon U.S. operators of the affected airplanes over that
currently required by AD 98-13-08.
Accomplishing the improved Standby Magnetic Compass Check Swing
procedures will be required for approximately 70 airplanes and will
take approximately 3 workhours per airplane to accomplish at an average
labor rate of $60 per hour. Based on these figures, the cost impact on
U.S. operators to accomplish the improved Standby Magnetic Compass
Check Swing procedures will be $12,600, or $180 per airplane.
The POH revision and placard requirements will be required for
approximately 70 airplanes. Incorporating the POH revisions and
fabricating and installing a placard may be performed by the owner/
operator holding at least a private pilot certificate as authorized by
Sec. 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). The only cost impact the placard and POH revision
requirements impose is the time it will take each owner/operator of the
affected airplanes to incorporate this information into the POH and
fabricate and install the placard.
Regulatory Impact
The regulations adopted herein will 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 final
rule does 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) 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 final evaluation prepared for this
action is contained 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, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to 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
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 removing Airworthiness Directive
(AD) 98-13-08, Amendment 39-10596 (63 FR 32975, June 17, 1998), and by
adding a new AD to read as follows:
99-14-03 Pilatus Aircraft LTD.: Amendment 39-11211; Docket No. 98-
CE-122-AD, Supersedes AD 98-13-08, Amendment 39-10596.
Applicability: Models PC-12 and PC-12/45 airplanes, manufacturer
serial numbers 101 through 230, 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 (g) 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 directional deviation on the standby magnetic compass
caused by modifications made to the airplane since manufacture,
which could result in flight-path deviation during critical phases
of flight, accomplish the following:
(a) For airplanes incorporating manufacturer serial numbers 101
through 147, within the next 100 hours time-in-service (TIS) after
July 31, 1998 (the effective date of AD 98-13-08), accomplish the
following:
(1) Replace the starter generator cable and the generator 2
power return cables with new cables of improved design and re-route
these cables, in accordance with the Accomplishment Instructions
section in Pilatus PC XII Service Bulletin (SB) No. 24-002, Rev. No.
1, dated September 20, 1996.
[[Page 34528]]
(2) Remove the temporary revision titled ``Electrical Cables,''
dated March 7, 1996, from the Pilot Operating Handbook (POH) and
insert a temporary revision titled ``Electrical Cables'' Rev. 1,
dated July 12, 1996. Accomplish this action in accordance with the
Accomplishment Instructions section in Pilatus PC XII SB No. 24-002,
Rev. No. 1, dated September 20, 1996.
(b) For airplanes incorporating manufacturer serial numbers 101
through 147, within the next 50 hours TIS after the effective date
of this AD, replace the placard installed near the standby magnetic
compass that is required by AD 98-13-08, with a new placard that
incorporates the following words (using at least \1/8\inch letters):
STANDBY COMPASS FOR CORRECT READING SWITCH: AVIONICS ON NAV &
INSTRUMENT LIGHTING AS REQUIRED WINDSHIELD DE-ICE LH & RH OFF AUXILIARY
HEATING SYSTEMS OFF AUXILIARY COOLING SYSTEM OFF
This placard is referenced in Pilatus Service Bulletin No. 34-
006, dated September 3, 1998.
(c) For airplanes incorporating manufacturer serial numbers 148
through 230, within the next 50 hours TIS after the effective date
of this AD, install a placard with the following words (using at
least 1/8-inch letters) near the standby magnetic compass:
STANDBY COMPASS FOR CORRECT READING SWITCH: AVIONICS ON NAV &
INSTRUMENT LIGHTING AS REQUIRED WINDSHIELD DE-ICE LH & RH OFF AUXILIARY
HEATING SYSTEMS OFF AUXILIARY COOLING SYSTEM OFF
This placard is referenced in Pilatus Service Bulletin No. 34-
006, dated September 3, 1998.
(d) For all affected manufacturer serial number airplanes,
within the next 50 hours TIS after the effective date of this AD,
accomplish the following:
(1) Insert Pilatus Report No. 01973-001, Temporary Revision,
Standby Compass, dated July 16, 1998, into the Pilot Operating
Handbook (POH).
(2) Accomplish the improved Standby Magnetic Compass Check Swing
procedures in accordance with Pilatus PC-12 Maintenance Manual
Temporary Revision No. 34-03, dated July 16, 1998, as specified in
Pilatus Service Bulletin No. 34-006, dated September 3, 1998.
(3) Insert Pilatus PC-12 Maintenance Manual Temporary Revision
No. 34-03, dated July 16, 1998, in chapter 34-21-00 facing page 502
of the maintenance manual. Disregard existing pages 502 through 506.
(e) Accomplishment of the POH revision, maintenance manual
insertions, and placard fabrication and installation, as required by
paragraphs (a)(2), (b), (c), (d)(1), and (d)(3) of this AD, may be
performed by the owner/operator holding at least a private pilot
certificate as authorized by Sec. 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 Sec. 43.9
of the Federal Aviation Regulations (14 CFR 43.9).
(f) Special flight permits may be issued in accordance with
Sec. Sec. 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.
(g) 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.
(1) 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.
(2) Alternative methods of compliance approved in accordance
with AD 98-13-08 are not considered approved as alternative methods
of compliance for this AD.
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.
(h) Questions or technical information related to the service
information referenced in this AD should be directed to Pilatus
Aircraft Ltd., Customer Liaison Manager, CH-6370 Stans, Switzerland;
telephone: +41 41 6196 233; facsimile: +41 41 6103 351. 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.
(i) The replacement and modification of the starter generator
cable and the generator 2 power return cable and the POH revision
replacement required by this AD shall be done in accordance with
Pilatus PC XII Service Bulletin No. 24-002, Rev. No. 1, dated
September 20, 1996. The Standby Magnetic Compass Check Swing
procedures required by this AD shall be done in accordance with
Pilatus PC-12 Maintenance Manual Temporary Revision No. 34-03, dated
July 16, 1998, as specified in Pilatus Service Bulletin No. 34-006,
dated September 3, 1998.
(1) The incorporation by reference of Pilatus PC XII Service
Bulletin No. 24-002, Rev. No. 1, dated September 20, 1996, was
previously approved by the Director of the Federal Register in
accordance with 5 U.S.C.. 552(a) and 1CFR part 51, as of July 31,
1998 (63 FR 32975, July 17, 1998).
(2) The incorporation by reference of Pilatus PC-12 Maintenance
Manual Temporary Revision No. 34-03, dated July 16, 1998, as
specified in Pilatus Service Bulletin No. 34-006, dated September 3,
1998, was approved by the Director of the Federal Register in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(3) Copies may be obtained from Pilatus Aircraft Ltd., Customer
Liaison Manager, CH-6370 Stans, Switzerland. Copies may be inspected
at the FAA, Central Region, Office of the Regional Counsel, Room
1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of
the Federal Register, 800 North Capitol Street, NW, suite 700,
Washington, DC.
Note 3: The subject of this AD is addressed in Swiss AD HB-98-
426, dated November 6, 1998.
(j) This amendment supersedes AD 98-13-08, Amendment 39-10596.
(k) This amendment becomes effective on August 17, 1999.
Issued in Kansas City, Missouri, on June 18, 1999.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 99-16277 Filed 6-25-99; 8:45 am]
BILLING CODE 4910-13-U
