Federal Register / Vol. 63, No. 152 / Friday, August 7, 1998 /Rules and Regulations 42203

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:

98–16–15 British Aerospace (Operations)

Limited: Amendment 39–10691; Docket

No. 98–CE–03–AD.

Applicability: Model B.121 Series 1, 2, and

3 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 (f) 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 structural failure of the main

spar web area caused by fatigue cracking or

separation of the wing caused by loose nuts

at the wing to fuselage main-spar attachment

fittings, which could result in loss of control

of the airplane, accomplish the following:

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

AD, replace the nuts (with improved design

nuts) at the wing to fuselage main-spar

attachment fittings in accordance with

British Aerospace PUP Mandatory Service

Bulletin No. B121/106, dated January 12,

1998.

(b) Upon accumulating 2,000 hours TIS on

the main spar or within the next 50 hours TIS

after the effective date of this AD, whichever

occurs later, install an inspection opening

and inspect, using eddy current methods, the

area at the main spar web for cracks in

accordance with the ACCOMPLISHMENT

INSTRUCTIONS section of British Aerospace

PUP Mandatory Service Bulletin No. B121/

105, dated January 12, 1998.

Note 2: Accomplishing the installation

inspection opening and initial eddy current

inspection required by this AD in accordance

with British Aerospace PUP Mandatory

Service Bulletin No. B121/102, Revision No.

1, Issued April 16, 1997, is considered

‘‘already accomplished’’ for the requirements

of paragraph (b) of this AD.

(c) Within 800 hours TIS after the initial

inspection required by paragraph (b) of this

AD, and thereafter at intervals not to exceed

800 hours TIS, reinspect the area of the main

spar web as specified in paragraph (b) of this

AD.

(d) If any cracks are found during any

inspection required by this AD, prior to

further flight, accomplish the following:

(1) Obtain a repair or replacement scheme

from the manufacturer through the FAA,

Small Airplane Directorate, at the address

specified in paragraph (f) of this AD; and

(2) Incorporate this scheme and continue to

repetitively inspect as required by paragraph

(c) of this AD, unless specified differently in

the instructions to the repair or replacement

scheme.

(e) 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.

(f) An alternative method of compliance or

adjustment of the initial or repetitive

compliance times that provides an equivalent

level of safety may be approved by the

Manager, Small Airplane Directorate, Aircraft

Certification Service, 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.

(g) Questions or technical information

related to British Aerospace PUP Mandatory

Service Bulletin No. B121/106, dated January

12, 1998, and British Aerospace PUP

Mandatory Service Bulletin No. B121/105,

dated January 12, 1998, should be directed to

British Aerospace (Operations) Limited,

British Aerospace Regional Aircraft,

Prestwick International Airport, Ayrshire,

KA9 2RW, Scotland; telephone: (01292)

479888; facsimile: (01292) 479703. 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.

(h) The replacements, installation, and

inspections required by this AD shall be done

in accordance with British Aerospace PUP

Mandatory Service Bulletin No. B121/106,

dated January 12, 1998, and British

Aerospace PUP Mandatory Service Bulletin

No. B121/105, dated January 12, 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 British

Aerospace (Operations) Limited, British

Aerospace Regional Aircraft, Prestwick

International Airport, Ayrshire, KA9 2RW,

Scotland. 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 4: The subject of this AD is addressed

in British AD 005–01–98, not dated.

(i) 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. 98–20840 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–CE–30–AD; Amendment 39–

10692; AD 98–16–16]

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.

Model PC–7 airplanes. This AD requires

replacing the seal unit on both main

landing gear (MLG) legs and the nose

landing gear (NLG) leg. This AD is the

result of mandatory continuing

airworthiness information (MCAI)

issued by the airworthiness authority for

Switzerland. The actions specified by
42204 Federal Register / Vol. 63, No. 152 / Friday, August 7, 1998 /Rules and Regulations

this AD are intended to prevent MLG or

NLG failure caused by deterioration of

a MLG or NLG leg seal unit, which

could result in damage to the airplane

or airplane control problems during

takeoff, landing, or taxi 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 Aircraft Ltd., Customer Liaison

Manager, CH–6371 Stans, Switzerland;

telephone: +41 41 619 6233; 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. 98–CE–30–

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,

Small Airplane Directorate, Airplane

Certification Service, FAA, 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 Aircraft Ltd.

Model PC–7 airplanes was published in

the Federal Register as a notice of

proposed rulemaking (NPRM) on May

29, 1998 (63 FR 29360). The NPRM

proposed to require replacing the seal

unit on both MLG legs and the NLG leg.

Accomplishment of the proposed action

as specified in the NPRM would be in

accordance with Pilatus Service Bulletin

No. 32–018, dated March 6, 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 5 airplanes in

the U.S. registry will be affected by this

AD, that it will take approximately 8

workhours per airplane to accomplish

this action, and that the average labor

rate is approximately $60 an hour. Parts

cost approximately $932 per airplane.

Based on these figures, the total cost

impact of this AD on U.S. operators is

estimated to be $7,060, or $1,412 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:

98–16–16 Pilatus Aircraft Ltd.: Amendment

39–10692; Docket No. 98–CE–30–AD.

Applicability: Model PC–7 airplanes, all

manufacturer serial numbers (MSN) up to

and including MSN 609, 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 main landing gear (MLG) or

nose landing gear (NLG) failure caused by

deterioration of a MLG or NLG leg seal unit,

which could result in damage to the airplane

or airplane control problems during takeoff,

landing, or taxi operations, accomplish the

following:

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

replace the seal unit on both MLG legs and

the NLG leg in accordance with the

ACCOMPLISHMENT INSTRUCTIONS

section of Pilatus Service Bulletin No. 32–

018, dated March 6, 1998.

(b) As of the effective date of this AD, no

person may install, on an affected airplane,

a MLG leg or NLG leg that does not have an

improved seal unit installed in accordance

with the ACCOMPLISHMENT

INSTRUCTIONS section of Pilatus Service

Bulletin No. 32–018, dated March 6, 1998.

(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.
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.