30300 Federal Register / Vol. 66, No. 109 / Wednesday, June 6, 2001 / Rules and Regulations

Airport, Wichita, Kansas 67209; telephone:

(316) 946–4152; facsimile: (316) 946–4407.

(j) What if I need to fly the airplane to

another location to comply with this AD? The

FAA can issue a special flight permit under

sections 21.197 and 21.199 of the Federal

Aviation Regulations (14 CFR 21.197 and

21.199) to operate your airplane to a location

where you can accomplish the requirements

of this AD.

(k) Are any service bulletins incorporated

into this AD by reference? Actions required

by this AD must be done in accordance with

Raytheon Mandatory Service Bulletin SB 34–

3267, Issued: March, 1999, Raytheon

Mandatory Service Bulletin SB 34–3268,

Issued: April, 2000, Raytheon Mandatory

Service Bulletin SB 34–3269, Issued: January

2000, and Raytheon Mandatory Service

Bulletin SB 34–3269, Revision 1, Revised:

October, 2000. The Director of the Federal

Register approved this incorporation by

reference under 5 U.S.C. 552(a) and 1 CFR

part 51. You can get copies from the

Raytheon Aircraft Company, P.O. Box 85,

Wichita, Kansas 67201–0085. You can look at

copies at the FAA, Central Region, Office of

the Regional Counsel, 901 Locust, Room 506,

Kansas City, Missouri, or at the Office of the

Federal Register, 800 North Capitol Street,

NW, suite 700, Washington, DC.

(l) When does this amendment become

effective? This amendment becomes effective

on July 20, 2001.

Issued in Kansas City, Missouri, on May

21, 2001.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 01–13581 Filed 6–5–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–CE–82–AD; Amendment 39–

12243; AD 2001–11–02]

RIN 2120–AA64

Airworthiness Directives; Pilatus

Aircraft LTD Models PC–12 and PC–12/

45 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

Airworthiness Directive (AD) 99–17–08,

which currently requires modifying the

generator 2 excitation by removing

certain diodes and installing a new 5-

amp circuit breaker and suppression

filter on certain Pilatus Aircraft Ltd.

(Pilatus) Models PC–12 and PC–12/45

airplanes. This AD is the result of the

Federal Aviation Administration’s

determination that the A250 voltage

spike suppression filter in the

modification kit can cause the circuit

breaker 235 to trip because of overload.

In extreme circumstances, this can lead

to overheating of wiring. This AD

requires you to modify the generator 2

excitation by removing certain diodes

and installing a new 5-amp circuit

breaker and suppression filter of

improved design in accordance with

revised procedures. 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 damage

to electrical components if generator 2

is not switched off before engine

shutdown and it overheats. This could

result in loss of electrical power to

certain critical airplane components.

DATES: This AD becomes effective on

July 23, 2001.

The Director of the Federal Register

approved the incorporation by reference

of Pilatus Service Bulletin No. 24–014,

dated October 27, 1999, as of July 23,

2001.

The Director of the Federal Register

previously approved the incorporation

by reference of Pilatus Service Bulletin

No. 24–012, dated February 19, 1999, as

of October 4, 1999 (64 FR 45149, August

19, 1999).

ADDRESSES: You may get the service

information referenced in this AD from

Pilatus Aircraft Ltd., Customer Liaison

Manager, CH–6371 Stans, Switzerland;

telephone: +41 41 619 65 09; facsimile:

+41 41 610 33 51. You may examine this

information at the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 99–CE–82–

AD, 901 Locust, Room 506, 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:

Doug Rudolph, Aerospace Engineer,

FAA, Small Airplane Directorate, 901

Locust, Room 301, Kansas City,

Missouri 64106; telephone: (816) 329–

4059; facsimile: (816) 329–4090.

SUPPLEMENTARY INFORMATION:

Discussion

Has FAA Taken Any Action to This

Point?

The FAA issued AD 99–17–08,

Amendment 39–11256 (64 FR 45149,

August 19, 1999), against Pilatus models

PC–12 and PC–12/45 airplanes, to

prevent damage to electrical

components if generator 2 is not

switched off before engine shutdown

and it overheats. This could result in

loss of electrical power to certain

critical airplane components.

AD 99–17–08 requires that you do the

following on the affected airplanes:

—modify the generator 2 excitation by

removing certain diodes; and

—install a new 5-amp circuit breaker

and suppression filter.

AD 99–17–08 was the result of

mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for Switzerland.

What Has Happened Since AD 99–17–

08 To Begin This Action?

The Federal Office for Civil Aviation

(FOCA), which is the airworthiness

authority for Switzerland, notified the

FAA of the need to change AD 99–17–

08. The FOCA reports that after

installation of the modification kit in

accordance with Pilatus Service Bulletin

SB 24–012 and turning on electrical

power on one of the affected airplanes,

the circuit breaker CB 235 tripped.

Investigation revealed that the

suppression filter (A250) (part number

524.52.12.358) was shorted. The

suppression diode installed in the filter

was shorted and was the wrong type.

The manufacturer’s A250 voltage spike

suppression filter is inadequate and has

been replaced with an A250 voltage

spike suppression filter of improved

design.

Has FAA Taken Any Action to This

Point?

We issued 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. This

proposal was published in the Federal

Register as a notice of proposed

rulemaking (NPRM) on March 5, 2001

(66 FR 13271). The NPRM proposed to

supersede AD 99–17–08, Amendment

39–11256 (64 FR 45149, August 19,

1999). The NPRM also proposed to

require you to modify the generator 2

excitation by removing certain diodes

and installing a new 5-amp circuit

breaker and suppression filter of

improved design in accordance with

revised procedures.

Was the Public Invited To Comment?

Interested persons were 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.

FAA’s Determination

What Is FAA’s Final Determination on

This Issue?

After careful review of all available

information related to the subject

Federal Register / Vol. 66, No. 109 / Wednesday, June 6, 2001 / Rules and Regulations 30301

presented above, we have determined

that air safety and the public interest

require the adoption of the rule as

proposed except for minor editorial

corrections. We 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

How Many Airplanes Does This AD

Impact?

We estimate that this AD affects 69

airplanes in the U.S. registry.

What Is the Cost Impact of This AD on

Owners/Operators of the Affected

Airplanes?

We estimate the following costs to do

the modification of the generator 2

excitation:

Labor cost Parts cost Total cost

per airplane

Total cost on

U.S. operators

8 workhours × $60 per hour = $480 ............................ Parts will be provided at no cost to the owners/operators of the affected aircraft.$480 $33,120

If the modification of the generator 2 excitation has been done with the manufacturer’s modification kit, then we

estimate the following costs to remove the A250 voltage spike suppression filter and replace it with the new A250

voltage spike suppression filter:

Labor cost Parts cost Total cost

per airplane

Total cost

on U.S.

operators

3 workhours × $60 per hour = $180 ............................ Parts will be provided at no cost to the owners/operators of the affected aircraft.$180 $12,420

Regulatory Impact

Does This AD Impact Various Entities?

The regulations adopted herein will

not have a substantial direct effect 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, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

Does This AD Involve a Significant Rule

or Regulatory Action?

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, under 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.

§ 39.13 [Amended]

2. FAA amends § 39.13 by removing

airworthiness directive (AD) 99–17–08,

Amendment 39–11256 (64 FR 45149,

August 19, 1999), and by adding a new

AD to read as follows:

2001–11–02 Pilatus Aircraft Ltd.:

Amendment 39–12243; Docket No. 99–

CE–82–AD, Supersedes AD 99–17–08,

Amendment 39–11256.

(a) What airplanes are affected by this AD?

This AD affects Models PC–12 and PC–12/45

airplanes, serial numbers 101 through 289,

that are certificated in any category.

(b) Who must comply with this AD?

Anyone who wishes to operate any of the

above airplanes must comply with this AD.

(c) What problem does this AD address?

The actions specified by this AD are intended

to prevent damage to electrical components

if generator 2 is not switched off before

engine shutdown and it overheats. This

could result in loss of electrical power to

certain critical airplane components.

(d) What actions must I accomplish to

address this problem? To address this

problem, you must accomplish the following:

Actions Compliance Procedures

(1) Modify the generator 2 excitation with the

modification kit, part number (P/N)

500.50.12.192, which requires you to:

(i) Remove certain diodes;

(ii) Install a new 5-ramp circuit breaker, P/N

972.55.18.406; and

(iii) Install an A250 voltage spike suppression

filter, P/N 524.52.12.502, which replaces P/N

524.52.358

Within the next 100 hours time-in-service

(TIS) after July 23, 2001 (the effective date

of this AD), unless already done.

Do this action following the ACCOMPLISHMENT INSTRUCTIONS section of Pilatus

Service Bulletin No. 24–012, dated February 19, 1999, and Service Bulletin No.

24–014, dated October 27, 1999.

30302 Federal Register / Vol. 66, No. 109 / Wednesday, June 6, 2001 / Rules and Regulations

Actions Compliance Procedures

(2) If the modification kit, part number

500.50.12.192, is already installed using the

A250 voltage spike suppression filter, part

number 524.52.12.358, replace only this voltage spike suppression filter with a new A250

voltage spike suppression filter, part number

524.52.12.502.

Within the next 100 hours TIS after July 23,

2001 (the effect date of this AD), unless already done.

Do this action following the ACCOMPLISHMENT INSTRUCTIONS section of Pilatus

Service Bulletin No. 24–014, dated October

27, 1999.

(3) Do not install any A250 voltage spike suppression filter, part number 524.52.358, or

FAA-approved equivalent part number.

As of July 23, 2001 (the effective date of this

AD).

Not Applicable.

(e) Can I comply with this AD in any other

way? You may use an alternative method of

compliance or adjust the compliance time if:

(1) Your alternative method of compliance

provides an equivalent level of safety; and

(2) The Manager, Small Airplane

Directorate, approves your alternative.

Submit your request through an FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Small Airplane Directorate.

(3) Alternative methods of compliance that

were approved in accordance with AD 99–

17–08 are not considered approved as

alternative methods of compliance for this

AD.

Note 1: This AD applies to each airplane

identified in paragraph (a) of this AD,

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 (e)

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 you have not

eliminated the unsafe condition, specific

actions you propose to address it.

(f) Where can I get information about any

already-approved alternative methods of

compliance? Contact Doug Rudolph,

Aerospace Engineer, FAA, Small Airplane

Directorate, 901 Locust, Room 301, Kansas

City, Missouri 64106; telephone: (816) 329–

4059; facsimile: (816) 329–4090.

(g) What if I need to fly the airplane to

another location to comply with this AD? The

FAA can issue a special flight permit under

sections 21.197 and 21.199 of the Federal

Aviation Regulations (14 CFR 21.197 and

21.199) to operate your airplane to a location

where you can accomplish the requirements

of this AD.

(h) Are any service bulletins incorporated

into this AD by reference? Actions required

by this AD must be done in accordance with

Pilatus Service Bulletin No. 24–012, dated

February 19, 1999, and Pilatus Service

Bulletin No. 24–014, dated October 27, 1999.

(1) The Director of the Federal Register

approved this incorporation by reference of

Pilatus Service Bulletin No. 24–014, dated

October 27, 1999, under 5 U.S.C. 552(a) and

1 CFR part 51.

(2) The Director of the Federal Register

previously approved incorporation by

reference of Pilatus Service Bulletin No. 24–

012, dated February 19, 1999, as of October

4, 1999 (64 FR 45149, August 19, 1999).

(3) You can get copies from Pilatus Aircraft

Ltd., Customer Liaison Manager, CH–6371

Stans, Switzerland. You can look at copies at

the FAA, Central Region, Office of the

Regional Counsel, 901 Locust, Room 506,

Kansas City, Missouri, or at the Office of the

Federal Register, 800 North Capitol Street,

NW, suite 700, Washington, DC.

(i) When does this amendment become

effective? This amendment becomes effective

on July 23, 2001.

Note 2: The subject of this AD is addressed

in Swiss AD Numbers HB 99–143, dated

February 19, 1999, and HB 99–542, dated

October 29, 1999.

Issued in Kansas City, Missouri, on May

22, 2001.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 01–13580 Filed 6–5–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–CE–27–AD; Amendment

39–12245; AD 2001–11–04]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Aircraft Company Models 99, 99A, 99A

(FACH), A99, A99A, B99, and C99

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Raytheon Aircraft

Company (Raytheon) Models 99, 99A,

99A (FACH), A99, A99A, B99, and C99

airplanes. This AD requires you to

inspect all main landing gear (MLG)

hydraulic actuators to determine the

end cap part number that is installed,

and replace any actuator that has a part

number 4A125C32 end cap. This AD is

the result of the potential for fatigue

cracks to develop on the MLG hydraulic

actuator end caps. The actions specified

by this AD are intended to eliminate

existing and prevent future fatigue

cracks in the MLG hydraulic actuator

end caps. Such cracks could cause

hydraulic fluid to leak and result in

collapse of one or more gears with

consequent aircraft damage and

passenger injury.

DATES: This AD becomes effective on

July 23, 2001.

The Director of the Federal Register

approved the incorporation by reference

of certain publications listed in the

regulations as of July 23, 2001.

ADDRESSES: You may get the service

information referenced in this AD from

the Raytheon Aircraft Company, PO Box

85, Wichita, Kansas 67201–0085;

telephone: (800) 625–7043 or (316) 676–

4556. You may examine this

information at the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 2000–CE–

27–AD, 901 Locust, Room 506, 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: Paul

C. DeVore, Aerospace Engineer, Wichita

Aircraft Certification Office, FAA, 1801

Airport Road, Mid-Continent Airport,

Wichita, Kansas 67209; telephone: (316)

946–4142; facsimile: (316) 946–4407.

SUPPLEMENTARY INFORMATION:

Discussion

What Events Have Caused This AD?

The FAA has received a report of an

incident on a Raytheon Model C99

airplane where a cracked main landing

gear (MLG) hydraulic actuator end cap

resulted in nose landing gear (NLG)

collapse during landing. The cracked

end cap caused the hydraulic fluid to

leak, which then prevented the landing

gear from locking down. We have

received several other reports of cracks

in the MLG hydraulic actuator end caps

on certain Raytheon 99 series airplanes

of a similar type design.