Federal Register / Vol. 62, No. 203 / Tuesday, October 21, 1997 / Rules and Regulations 54575

U.S. pork trade with Spain has been

very small. The interim rule could result

in less pork being imported into the

United States from Spain.

Among the potential entities that may

be affected by the interim rule are U.S.

producers, consumers, and importers.

Since the amount of pork imported from

Spain has been so small compared to

the amount produced domestically and

total pork imports, no impact on

consumer and producer prices is

expected. Also, there should be little or

no impact on importers. Because the

amount of pork imported from Spain

has been so small, importers should

easily find replacements from other

approved sources.

Further, if pork imports from Spain

were not restricted and hog cholera was

introduced into the United States from

Spain, the economic impact on

consumers, tax payers, and exporters

could be great. Consumers would be

affected by increased costs and reduced

availability of pork. The cost to tax

payers to eradicate or contain the

disease would be considerable.

Exporters would likely face restrictions

on exporting pork to traditional foreign

markets. Affected producers would face

increased production costs. The benefits

of avoiding the potential cost of a

disease outbreak outweighs by far the

minimal impact of this rule on

consumers, producers, and importers of

pork products.

Under these circumstances, the

Administrator of the Animal and Plant

Health Inspection Service has

determined that this action will not

have a significant economic impact on

a substantial number of small entities.

List of Subjects in 9 CFR Part 94

Animal diseases, Imports, Livestock,

Meat and meat products, Milk, Poultry

and poultry products, Reporting and

recordkeeping requirements.

PART 94—RINDERPEST, FOOT-ANDMOUTH DISEASE, FOWL PEST (FOWL

PLAQUE), EXOTIC NEWCASTLE

DISEASE, AFRICAN SWINE FEVER,

HOG CHOLERA, AND BOVINE

SPONGIFORM ENCEPHALOPATHY:

PROHIBITED AND RESTRICTED

IMPORTATIONS

Accordingly, we are adopting as a

final rule, without change, the interim

rule that amended 9 CFR 94 and that

was published at 62 FR 28619–28620 on

May 27, 1997.

Authority: 7 U.S.C. 147a, 150ee, 161, 162,

and 450; 19 U.S.C. 1306; 21 U.S.C. 111, 114a,

134a, 134b, 134c, 134f, 136, and 136a; 31

U.S.C. 9701; 42 U.S.C. 4331 and 4332; 7 CFR

2.22, 2.80, and 371.2(d).

Done in Washington, DC, this 15th day of

October 1997.

Craig A. Reed,

Acting Administrator, Animal and Plant

Health Inspection Service.

[FR Doc. 97–27812 Filed 10–20–97; 8:45 am]

BILLING CODE 3410–34–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 86–CE–23–AD; Amendment 39–

10171; AD 86–07–02 R1]

RIN 2120–AA64

Airworthiness Directives; Pilatus

Britten-Norman Ltd. (Formerly BrittenNorman) BN2A MK. 111 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment revises

Airworthiness Directive (AD) 86–07–02,

which currently requires repetitively

inspecting the junction of the torque

link lug and upper case of the main

landing gear (MLG) torque link

assemblies for cracks on Pilatus BrittenNorman Ltd. (Pilatus Britten-Norman)

BN–2A, BN–2B, BN–2T, and BN2A MK.

111 series airplanes, and replacing any

part found cracked with a like part. This

AD removes from the applicability the

BN–2A, BN–2B, and BN–2T series

airplanes, and retains the repetitive

inspection and replacement (if

necessary) requirements of AD 86–07–

02 for the BN2A MK. 111 series

airplanes. This AD results from the

Federal Aviation Administration’s

determination that additional AD action

needs to be taken on the BN–2A, BN–

2B, and BN–2T series airplanes. This

additional action will be addressed in a

separate AD. The actions specified by

this AD are intended to prevent failure

of the main landing gear caused by

cracks in the torque link area, which

could lead to loss of control of the

airplane during landing operations.

DATES: Effective November 28, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

28, 1997.

ADDRESSES: Service information that

applies to this AD may be obtained from

Fairey Hydraulics Limited, Claverham,

Bristol, England; or Pilatus BrittenNorman 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. 86–CE–23–

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.

S.M. Nagarajan, Aerospace Engineer,

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 Pilatus Britten-Norman BN2A

MK. 111 series airplanes was published

in the Federal Register as a notice of

proposed rulemaking on May 27, 1997

(62 FR 28644). The NPRM proposed to

revise AD 86–07–02 by removing the

BN–2A, BN–2B, and BN–2T series

airplanes from the applicability of that

AD. The NPRM proposed to retain the

requirement of repetitively inspecting

the junction of the torque link lug and

upper case of the MLG torque link

assemblies for the BN2A MK. 111 series

airplanes. The FAA is issuing a separate

AD action for the BN–2A, BN–2B, and

BN–2T series airplanes to require a

modification that, when incorporated,

would eliminate the repetitive

inspection requirement currently

required by AD 86–07–02.

Accomplishment of the proposed

inspections as specified in the NPRM

would be in accordance with Fairey

Hydraulics Limited Service Bulletin

(SB) 32–7, Issue 3, dated January 30,

1990; and Fairey Hydraulics Limited SB

32–10, Issue 2, dated November 10,

1992.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposed AD 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 AD as proposed except for minor

editorial corrections. The FAA has
54576 Federal Register / Vol. 62, No. 203 / Tuesday, October 21, 1997 / Rules and Regulations

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 9 airplanes in

the U.S. registry will be affected by this

AD, that it will take approximately 1

workhour per airplane to accomplish

the initial inspection, and that the

average labor rate is approximately $60

an hour. Based on these figures, the total

cost impact of this AD on U.S. operators

is estimated to be $540 or $60 per

airplane. This figure only takes into

account the cost of the initial inspection

and does not take into account the cost

of any repetitive inspections. The FAA

has no way of determining the number

of repetitive inspections each of the

owners/operators will incur over the life

of the affected airplanes.

In addition, the inspections are

currently required by AD 86–07–02 on

the 9 affected airplanes. This AD does

not require any additional actions over

that already required by AD 86–07–02.

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

removing Airworthiness Directive (AD)

86–07–02, Amendment 39–5382, and by

adding a new AD to read as follows:

86–07–02 R1 Pilatus Britten-Norman Ltd:

Amendment 39–10171; Docket No. 86–

CE–23–AD. Revises AD 86–07–02,

Amendment 39–5382.

Applicability: Models BN2A MK. 111,

BN2A MK. 111–2, and BN2A MK. 111–3

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 prior to further

flight after the effective date of this AD (see

Note 2) or within 100 hours time-in-service

(TIS) after the last inspection accomplished

in accordance with AD 86–07–02, whichever

occurs later, and thereafter at intervals not to

exceed 100 hours TIS.

Note 2: The ‘‘prior to further flight after the

effective date of this AD’’ compliance time

was the original initial compliance time of

AD 86–07–02, and is being retained to

provide credit and continuity for alreadyaccomplished and future inspections.

To prevent failure of the main landing gear

caused by cracks in the torque link assembly

area, which could lead to loss of control of

the airplane during landing operations,

accomplish the following:

(a) Inspect the junction of the torque link

lug and upper case for cracks (using a 10-

power magnifying glass or by dye penetrant

methods) in accordance with Fairey

Hydraulics Limited Service Bulletin (SB) 32–

7, Issue 3, dated January 30, 1990; or Fairey

Hydraulics SB 32–10, Issue 2, dated

November 10, 1992, as applicable. Pilatus

Britten-Norman SB BN–2/SB. 173, Issue 3,

dated November 16, 1990, references Fairey

Hydraulic Limited SB 32–7; and Pilatus

Britten-Norman SB BN–2/SB.209, Issue 1,

dated November 30, 1992, references Fairey

Hydraulic Limited SB 32–10.

(b) If cracked parts are found during any

of the inspections required by this AD, prior

to further flight, replace the cracked parts

with airworthy parts in accordance with the

applicable maintenance manual.

(c) If the landing gear is replaced, only

equal pairs of the same manufacturer are

approved as replacement parts. Mixing of

different manufacturer landing gears is not

authorized.

(d) The intervals between the repetitive

inspections required by this AD may be

adjusted up to 10 percent of the specified

interval to allow accomplishing these actions

along with other scheduled maintenance on

the airplane.

(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 inspection 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, 1201

Walnut, suite 900, Kansas City, Missouri

64106.

(1) The request should 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 for AD 86–07–02 are considered

approved as alternative methods of

compliance for this AD.

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) The inspections required by this AD

shall be done in accordance with Fairey

Hydraulics Limited Service Bulletin 32–7,

Issue 3, dated January 30, 1990, or Fairey

Hydraulics Service Bulletin 32–10, Issue 2,

dated November 10, 1992, as applicable. 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 Fairey

Hydraulics Limited, Claverham, Bristol,

England; or Pilatus Britten-Norman Limited,

Bembridge, Isle of Wight, United Kingdom

PO35 5PR. 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.

(h) This amendment (39–10171) revises AD

86–07–02, Amendment 39–5382.

(i) This amendment (39–10171) becomes

effective on November 28, 1997.

Issued in Kansas City, Missouri, on

October 14, 1997.

Mary Ellen Schutt,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 97–27785 Filed 10–20–97; 8:45 am]

BILLING CODE 4910–13–U