Federal Register / Vol. 63, No. 74 / Friday, April 17, 1998 /Rules and Regulations 19175

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–130–AD; Amendment

39–10471; AD 98–08–22]

RIN 2120–AA64

Airworthiness Directives; Pilatus

Aircraft Ltd. Model PC–7 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Pilatus Aircraft Ltd.

(Pilatus) Model PC–7 airplanes. This AD

requires inspecting the elevator and

rudder attachment brackets for cracks

and/or corrosion, and repairing or

replacing any cracked or corrosiondamaged parts, as applicable. 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 failure

of the elevator and rudder attachment

brackets because of cracks or corrosion

damage, which could result in the

elevator and/or rudder separating from

the airplane with consequent loss of

airplane control.

DATES: Effective May 31, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 31,

1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

Pilatus Aircraft Ltd., Customer Liaison

Manager, CH–6371 Stans, Switzerland;

telephone: +41 41 619 6509; facsimile:

+41 41 610 3351. This information may

also be examined at the Federal

Aviation Administration (FAA), Central

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 97–CE–

130–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: Mr.

Roman T. Gabrys, Aerospace Engineer,

FAA, Small Airplane Directorate,

Airplane Certification Service, FAA,

1201 Walnut, suite 900, Kansas City,

Missouri 64106; telephone: (816) 426–

6932; 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 PC–7 airplanes

was published in the Federal Register

as a notice of proposed rulemaking

(NPRM) on January 20, 1998 (63 FR

2911). The NPRM proposed to require

inspecting the elevator and rudder

attachment brackets for cracks and/or

corrosion, and repairing or replacing

any cracked or corrosion-damaged parts,

as applicable. Accomplishment of the

proposed action as specified in the

NPRM would be in accordance with

Pilatus Service Bulletin No. 55–002,

dated November 7, 1997.

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 8 airplanes in

the U.S. registry will be affected by this

AD, that it will take approximately 7

workhours per airplane to accomplish

the inspection required by this AD, and

that the average labor rate is

approximately $60 an hour. Inspection

kits cost approximately $106 per

airplane. Based on these figures, the

total cost impact of this AD on U.S.

operators is estimated to be $4,208, or

$526 per airplane.

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.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive

(AD) to read as follows:

98–08–22 Pilatus Aircraft Ltd.: Amendment

39–10471; Docket No. 97–CE–130–AD.

Applicability: Model PC–7 airplanes, serial

numbers MSN 001 through MSN 612,

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 (d) 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 failure of the elevator and

rudder attachment brackets because of cracks
19176 Federal Register / Vol. 63, No. 74 / Friday, April 17, 1998 /Rules and Regulations

or corrosion damage, which could result in

the elevator and/or rudder separating from

the airplane with consequent loss of airplane

control, accomplish the following:

(a) Within the next 100 hours time-inservice after the effective date of this AD,

inspect the elevator and rudder attachment

brackets for cracks and/or corrosion in

accordance with Pilatus Service Bulletin No.

55–002, dated November 7, 1997.

(b) If cracked or corrosion-damaged parts

are found during the inspection required by

paragraph (a) of this AD, prior to further

flight, repair or replace any cracked or

corrosion-damaged parts, as specified in and

in accordance with Pilatus Service Bulletin

No. 55–002, dated November 7, 1997.

(c) 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.

(d) An alternative method of compliance or

adjustment of the compliance time 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.

(e) Questions or technical information

related to Pilatus Service Bulletin No. 55–

002, dated November 7, 1997, should be

directed to Pilatus Aircraft Ltd., Customer

Liaison Manager, CH–6371 Stans,

Switzerland; telephone: +41 41 619 6509;

facsimile: +41 41 610 3351. 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.

(f) The inspection, repair, and replacement

required by this AD shall be done in

accordance with Pilatus Service Bulletin No.

55–002, dated November 7, 1997. This

incorporation by reference was approved by

the Director of the Federal Register in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51. Copies may be obtained from Pilatus

Aircraft Ltd., Customer Liaison Manager,

CH–6371 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.

(g) This amendment becomes effective on

May 31, 998.

Issued in Kansas City, Missouri, on April

8, 1998.

Marvin R. Nuss,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–10058 Filed 4–16–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–74–AD; Amendment 39–

10469; AD 98–08–20]

RIN 2120–AA64

Airworthiness Directives; AlliedSignal

Aerospace Bendix/King Model KSA

470 Autopilot Servo Actuators, Part

Numbers 065–0076–10 Through 065–

0076–15

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain AlliedSignal

Aerospace Bendix/King Model KSA 470

autopilot servo actuators, part numbers

065–0076–10 through 065–0076–15,

that are installed on aircraft. This AD

requires replacing the autopilot servo

actuator with a modified actuator. This

is the result of two reports of the

affected autopilot servo actuators

containing loose roll pins within the

servo housing. Loose roll pins could fall

out, become lodged in the output shaft

clutch mechanism, and prevent this

mechanism from disengaging. The

actions specified by this AD are

intended to prevent such an occurrence,

which could result in increased effort by

the pilot to control the aircraft and

possible loss of control of the affected

flight control axis.

EFFECTIVE DATE: June 2, 1998.

ADDRESSES: Service information

identified in this AD may be obtained

from AlliedSignal Aerospace,

Commercial Avionics Systems, 400 N.

Rogers Road, Olathe, Kansas 66062–

1212. This information may also be

examined at the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 97–CE–74

AD, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106.

FOR FURTHER INFORMATION CONTACT: Mr.

Joel Ligon, Aerospace Engineer, Wichita

Aircraft Certification Office, FAA, 1801

Airport Road, Mid-Continent Airport,

Wichita, Kansas 67209; telephone: (316)

946–4138; facsimile: (316) 946–4407.

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 AlliedSignal Aerospace

Bendix/King Model KSA 470 autopilot

servo actuators, part numbers 065–

0076–10 through 065–0076–15, that are

installed on aircraft was published in

the Federal Register as a notice of

proposed rulemaking (NPRM) on

December 19, 1997 (62 FR 66565). The

NPRM proposed to require replacing the

autopilot servo actuator with a modified

actuator. Accomplishment of the

proposed action as specified in the

NPRM would be in accordance with

Bendix/King Service Bulletin No. SB

KSA 470–3, dated May 1997.

The NPRM was the result of two

reports of the affected autopilot servo

actuators containing loose roll pins

within the servo housing. Loose roll

pins could fall out, become lodged in

the output shaft clutch mechanism, and

prevent this mechanism from

disengaging.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the one

comment received. No comments were

received on the FAA’s determination of

the cost to the public.

Comment Disposition

The commenter states that the

reference to the Raytheon 350 series

aircraft in the proposal is incorrect. The

commenter explains that the Raytheon

350 series is actually a Raytheon 300

series aircraft. The commenter requests

that the FAA reference these aircraft

accordingly.

The FAA concurs that these aircraft

should be referenced as Raytheon 300

series instead of Raytheon 350 series.

Since the Raytheon 300 series is already

referenced in the AD, the FAA will

remove all reference to the Raytheon

350 series in the final rule.

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 the

change referenced above and minor

editorial corrections. The FAA has

determined that this change and the

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 500 of the

affected servo actuators could be

installed on aircraft in the U.S. registry.

This replacement will take

approximately 2 workhours per aircraft

to accomplish, at an average labor rate