Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes

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]

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