[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