55156 Federal Register / Vol. 62, No. 205 / Thursday, October 23, 1997 / Rules and Regulations

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.

(d) The installation required by this AD

shall be done in accordance with Extra

Flugzeugbau, GmbH. EA–300 Service

Bulletin No. 300–1–97, Issue B, dated June

11, 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 Flugzeugbau, GmbH., Schwarze Heide

21, 46569 Hu ̈nxe, Germany. 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.

(e) This amendment (39–10174)

becomes effective on November 24,

1997.

Issued in Kansas City, Missouri, on

October 16, 1997.

Mary Ellen A. Schutt,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 97–27933 Filed 10–22–97; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 84–CE–18–AD; Amendment 39–

10172; AD 84–23–06 R1]

RIN 2120–AA64

Airworthiness Directives; Pilatus

Britten-Norman Ltd. Models BN–2, BN–

2A, BN–2B, BN–2T, and BN–2A MK.

111 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment revises

airworthiness directive (AD) 84–23–06,

which currently requires repetitively

inspecting the upper mounting brackets,

bolts, and bushings on wing mounted

engines for cracks, wear, and

insufficient fit on certain Pilatus BrittenNorman Ltd. (Pilatus) Models BN–2,

BN–2A, BN–2B, BN–2T, and BN–2A

MK. 111 series airplanes, and replacing

any cracked, worn, or ill-fitting part.

This action retains the same action

required in AD 84–23–06, except the

action is only applicable to the BN–2A

MK. 111 series airplanes. This action is

the result of a terminating modification,

now available to the Pilatus Models BN–

2, BN–2A, BN–2B, BN–2T airplanes,

which removes them from the

applicability of AD 84–23–06. The

actions specified by this AD are

intended to prevent failure of the upper

mounting brackets on wing mounted

engines, which could possibly cause

structural failure of the airplane.

DATES: Effective November 24, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

24, 1997.

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 44–19–

83–872511; facsimile 44–19–83–873246.

This information may also be examined

at the Federal Aviation Administration

(FAA), Central Region, Office of the

Regional Counsel, Attention: Rules

Docket 84–CE–18–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, Project Officer, Small

Airplane Directorate, Aircraft

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 BN–2, BN–2A, BN–2B,

BN–2T, and BN–2A MK. 111 series was

published in the Federal Register on

March 10, 1997 (62 FR 10756). The

proposed AD would revise AD 84–23–

06 by deleting the Pilatus BN–2, BN–2A,

BN–2B, BN–2T series airplanes from the

AD, and by retaining the following for

the Pilatus BN–2A MK. 111 series

airplanes:

(1) Visually inspecting the upper

engine mounting bracket lugs for cracks

extending radially from the bolt holes in

the doubler;

(2) Inspecting for elongation of the

bolt holes, distortion, delamination,

cracks, flaking, and corrosion;

(3) Inspecting the bolts for correct

bearing length, and loose and fretted

bushings; and

(4) Correcting any discrepancies

found.

Accomplishment of this action will be

in accordance with Pilatus BrittenNorman Ltd. Service Bulletin (SB) BN–

2/SB.61, Issue 5, dated December 9,

1981, which is also referenced in the

Notice of Proposed Rulemaking (NPRM)

Docket 96–CE–17–AD for a terminating

action applicable to the Pilatus BN–2,

BN–2A, BN–2B and BN–2T series

airplanes.

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 9 airplanes in

the U.S. registry will be affected by this

AD, that it will take approximately 2

workhours per airplane to accomplish

this action and the average labor rate is

approximately $60 an hour. There are

no parts required for the initial

inspection. Based on these figures, the

total cost impact for the initial

inspection of this AD on U.S. operators

is estimated to be $1,080 or $120 per

airplane. This figure is based on the

initial inspection cost and does not

include workhours for repetitive

inspections because the FAA does not

have the information to determine the

number of repetitive inspections that

would be incurred over the life of the

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
Federal Register / Vol. 62, No. 205 / Thursday, October 23, 1997 / Rules and Regulations 55157

‘‘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)

84–23–06, Amendment 39–4942, (49 FR

43621, October 31, 1984), and adding a

new AD to read as follows:

84–23–06 R1. Pilatus Britten-Norman LTD.:

Amendment 39–10172; Docket No. 84–

CE–18–AD; Revises AD 84–23–06,

Amendment 39–4942.

Applicability: BN–2A MK. 111 Series

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 (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.

Note 2: The paragraph structure of this AD

is as follows:

Level 1: (a), (b), (c), etc.

Level 2: (1), (2), (3), etc.

Level 3: (i), (ii), (iii), etc.

Level 2 and Level 3 structures are

designations of the Level 1 paragraph they

immediately follow.

Compliance: Required initially upon the

accumulation of 500 hours time-in-service

(TIS) or within the next 50 hours TIS after

the effective date of this AD, whichever

occurs later, unless already accomplished

(compliance with AD 84–23–06), and

thereafter at intervals not to exceed 500 hours

TIS.

To prevent failure of the upper mounting

brackets on both wing mounted engines,

which could possibly cause structural failure

of the airplane, accomplish the following:

(a) Visually inspect the following areas in

accordance with paragraphs 1 through 6 of

the ‘‘Inspection’’ section of the Pilatus

Britten-Norman (Pilatus) Service Bulletin

(SB) No. BN–2/SB.61, Issue 5, dated

December 9, 1981:

(1) The upper engine to wing mounting

brackets for:

(i) Minimum lug bolt hole-to-edge distance,

elongation of the bolt holes, distortion,

delamination, cracks, flaking, and corrosion;

(ii) The bolts for correct bearing length; and

(iii) Loose and fretted bushings.

(2) Prior to further flight, correct defects in

accordance with the following:

(i) If the lug bolt hole-to-edge distance is

less than the specified minimum (0.2625-

inches), correct in accordance with paragraph

3 of the ‘‘Rectification/Modification’’ section

of Pilatus SB No. BN–2/SB.61, Issue 5, dated

December 9, 1981;

(ii) If the bolt holes are elongated, or if any

bushings are loose or fretted, modify and

correct in accordance with paragraph 4 of the

‘‘Rectification/Modification’’ section of

Pilatus SB No. BN–2/SB.61, Issue 5, dated

December 9, 1981;

(iii) If any mounting bracket is cracked,

modify both brackets on the same engine

installation (left side engine or right side

engine) concurrently (even if only one

bracket is defective) in accordance with

paragraph 1 of the ‘‘Rectification/

Modification’’ section of Pilatus SB No. BN–

2/SB.61, Issue 5, dated December 9, 1981;

(iv) If any lug is distorted or delaminated,

replace the deficient part in accordance with

paragraphs 1 and 2 of the ‘‘Rectification/

Modification’’ section of Pilatus SB No. BN–

2/SB.61, Issue 5, dated December 9, 1981;

(v) If any inspected part is corroded or

flaking, replace the part in accordance

paragraph 1 with the ‘‘Rectification/

Modification’’ section of Pilatus SB No. BN–

2/SB.61, Issue 5, dated December 9, 1981;

and

(vi) If any of the bolts are of incorrect

length or damaged, replace with new units of

the correct length in accordance with

paragraphs 1 and 2 of the ‘‘Rectification/

Modification’’ section of Pilatus SB No. BN–

2/SB.61, Issue 5, dated December 9, 1981.

(b) The intervals between the repetitive

inspections required by this AD may be

adjusted up to 10 percent of the specified

interval to allow for accomplishing these

inspections concurrent with the other

scheduled maintenance of the airplane.

(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 initial or repetitive

compliance times that provides an equivalent

level of safety may be approved by the

Manager, Small Airplane Directorate, Aircraft

Certification Service, FAA, 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.

(e) The inspections, modifications, and

replacements, required by this AD shall be

done in accordance with Pilatus BrittenNorman Service Bulletin No. BN–2/SB.61,

Issue: 5, Date: December 9, 1981. 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 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.

(f) This amendment (39–10172) becomes

effective on November 24, 1997.

Issued in Kansas City, Missouri, on

October 16, 1997.

Mary Ellen A. Schutt,

Acting Manger, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 97–27931 Filed 10–22–97; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 97–AWP–23]

Amendment of Class E Airspace;

Flagstaff, AZ

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This action amends the Class

E airspace areas at Flagstaff, AZ. The

development of a Global Positioning

System (GPS) Standard Instrument

Approach Procedure (SIAP) to Runway

(RWY) 3 has made this action necessary.

The intended effect of this action is to

provide adequate additional controlled

airspace extending upward from 700

feet or more above the surface for

Instrument Flight Rules (IFR) operations

at Flagstaff Pulliam Airport, Flagstaff,

AZ.