Federal Register / Vol. 63, No. 152 / Friday, August 7, 1998 /Rules and Regulations 42205

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. 32–

018, dated March 6, 1998, should be directed

to Pilatus Aircraft Ltd., Customer Liaison

Manager, CH–6371 Stans, Switzerland;

telephone: +41 41 619 6233; 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 64106.

(f) The replacements required by this AD

shall be done in accordance with Pilatus

Service Bulletin No. 32–018, dated March 6,

1998. 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.

Note 3: The subject of this AD is addressed

in Swiss AD HB 98–069, dated March 23,

1998.

(g) This amendment becomes effective on

September 21, 1998.

Issued in Kansas City, Missouri, on July 28,

1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–20838 Filed 8–6–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–112–AD; Amendment

39–10690; AD 98–16–14]

RIN 2120–AA64

Airworthiness Directives; Pilatus

Britten-Norman Ltd. BN–2, BN–2A, BN–

2B, and BN–2T Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to all Pilatus Britten-Norman

Ltd. (Pilatus Britten-Norman) BN–2,

BN–2A, BN–2B, and BN–2T series

airplanes. This AD requires replacing

the attachment bolts, nuts and washers

of the lower fitting of the main landing

gear (MLG), and adjusting the torque

values of the nuts. This AD is the result

of mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for the United

Kingdom. The actions specified by this

AD are intended to prevent the bolts

that attach the lower fitting of the MLG

to the nacelle from becoming

threadbound, which could result in

structural failure of the MLG with

consequent loss of control of the

airplane during takeoff, taxi, or landing

operations.

DATES: Effective September 21, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of September

21, 1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

Pilatus Britten-Norman Limited,

Bembridge, Isle of Wight, United

Kingdom PO35 5PR; telephone: 44–1983

872511; facsimile: 44–1983 873246.

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–112-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.

Roger Chudy, Aerospace Engineer,

Small Airplane Directorate, Aircraft

Certification Service, 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 all Pilatus Britten-Norman BN–

2, BN-2A, BN–2B, and BN–2T series

airplanes was published in the Federal

Register as a notice of proposed

rulemaking (NPRM) on March 19, 1998

(63 FR 13379). The NPRM proposed to

require replacing the washers on the

attachment bolts of the lower fitting of

the MLG. Accomplishment of the

proposed action as specified in the

NPRM would be in accordance with

Pilatus Britten-Norman Service Bulletin

BN2/SB.231, Initial Issue, dated October

17, 1996.

The NPRM was the result of

mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for the United

Kingdom.

After issuance of the NPRM, Pilatus

Britten-Norman informed the FAA that

Service Bulletin BN2/SB.231 has been

revised to the Issue 2 status (dated

October 1, 1997). This revision changes

the procedures to specify replacing the

attachment bolts and nuts of the lower

fitting of the MLG instead of re-using

the existing bolts and nuts. This service

information also specifies procedures to

adjust the torque loading values of the

bolts.

In addition, the FAA has realized that

the Model BN–2T–4R airplanes were

inadvertently omitted from the

proposed AD. At that time, the FAA

determined that the Model BN–2T–4R

airplanes are of similar type design to

those currently listed in the NPRM.

This prompted the FAA to issue a

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD that would apply to all

Pilatus Britten-Norman BN–2, BN–2A,

BN–2B, BN–2T, and BN–2T–4R series

airplanes. This proposal was published

in the Federal Register as a

supplemental NPRM on May 28, 1998

(63 FR 29159). The supplemental NPRM

proposed to also require replacing the

attachment bolts and nuts of the lower

fitting of the MLG and adjusting the

torque values of the nuts.

Accomplishment of the proposed action

as specified in the supplemental NPRM

would be in accordance with the service

information previously referenced.

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.

Comment Disposition

Pilatus Britten-Norman states that the

proposed AD should not apply to the

Model BN–2T–4R airplanes. These

airplanes utilize a different type wing

and an uprated landing gear

construction from the rest of the affected

models.

After re-examining all information

related to this subject, the FAA concurs

and has removed the Model BN-2T–4R

airplanes from 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 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.
42206 Federal Register / Vol. 63, No. 152 / Friday, August 7, 1998 /Rules and Regulations

Cost Impact

The FAA estimates that 80 airplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

3 workhours per airplane to accomplish

this action, and that the average labor

rate is approximately $60 an hour. Parts

cost approximately $10 per airplane.

Based on these figures, the total cost

impact of this AD on U.S. operators is

estimated to be $15,200, or $190 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:

98–16–14 Pilatus Britten-Norman Ltd:

Amendment 39–10690; Docket No. 97-

CE–112–AD.

Applicability: Models BN–2, BN–2A, BN–

2A–3, BN–2A–6, N–2A–8, BN–2A–2, BN–

2A–9, BN–2A–20, BN–2A–21, BN–2A–26,

BN–2A–27, BN–2B–20, BN–2B–21, BN–2B–

26, BN–2B–27, and BN–2T airplanes, all

serial numbers, 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 (c) 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 within the next 50

landings after the effective date of this AD,

unless already accomplished.

Note 2: The compliance time of this AD is

presented in landings instead of hours timein-service (TIS). If the number of landings is

unknown, hours TIS may be used by

multiplying the number of hours TIS by 1.5.

To prevent the bolts that attach the lower

fitting of the main landing gear (MLG) to the

nacelle from becoming threadbound, which

could result in structural failure of the MLG

with consequent loss of control of the

airplane during takeoff, taxi, or landing

operations, accomplish the following:

(a) Replace the attachment bolts, nuts, and

washers of the lower fitting of the MLG, in

accordance with Pilatus Britten-Norman

Service Bulletin No. BN2/SB.231, Issue 2,

dated October 1, 1997.

(b) 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

an be accomplished.

(c) 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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane

Directorate.

(d) Questions or technical information

related to Pilatus Britten-Norman Service

Bulletin BN2/SB.231, Issue 2, dated October

1, 1997, should be directed to Pilatus BrittenNorman Limited, Bembridge, Isle of Wight,

United Kingdom PO35 5PR; telephone: 44–

1983 872511; facsimile: 44–1983 873246.

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.

(e) The replacement required by this AD

shall be done in accordance with Pilatus

Britten-Norman Service Bulletin No. BN2/

SB.231, Issue 2, dated October 1, 997. 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

Britten-Norman Limited, Bembridge, Isle of

Wight, United Kingdom PO35 5PR. Copies

may be inspected at the FAA, Central Region,

ffice 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 4: The subject of this AD is addressed

in British AD No. 008–10–96, dated January

31, 1997.

(f) This amendment becomes effective on

September 21, 1998.

Issued in Kansas City, Missouri, on July 28,

1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–20837 Filed 8–6–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–208–AD; Amendment

39–10693; AD 98–16–17]

RIN 2120–AA64

Airworthiness Directives; Cessna

Model 750 Citation X Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to all Cessna Model 750

Citation X series airplanes. This action

requires repetitive in-flight functional

tests to verify proper operation of the

secondary horizontal stabilizer pitch

trim system, and repair, if necessary.

This amendment is prompted by reports

of simultaneous failures of the primary

and secondary horizontal stabilizer

pitch trim system during flight, due to

internal water contamination and

corrosion damage in the system

actuator. The actions specified in this

AD are intended to detect and correct