10236 Federal Register / Vol. 62, No. 44 / Thursday, March 6, 1997 / Proposed Rules

Limited, Claverham, Bristol, England; or

Pilatus Britten-Norman Limited, Bembridge,

Isle of Wight, United Kingdom PO35 5PR, as

applicable; or may examine these documents

at the FAA, Central Region, Office of the

Assistant Chief Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri 64106.

Issued in Kansas City, Missouri, on

February 24, 1997.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 97–5471 Filed 3–5–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–CE–23–AD]

RIN 2120–AA64

Airworthiness Directives; Aviat

Aircraft, Inc. Models S–1S, S–1T, S–2,

S–2A, S–2S, and S–2B Airplanes

(formerly known as Pitts Models S–1S,

S–1T, S–2, S–2A, S–2S, and S–2B

Airplanes)

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

revise AD 96–12–03, which applies to

Aviat Aircraft, Inc. (Aviat) Models S–1S,

S–1T, S–2, S–2A, S–2S, and S–2B

airplanes that are equipped with aft

lower fuselage wing attach fittings

incorporating either part number (P/N)

76090, 2–2107–1, or 1–210–102. That

AD currently requires repetitively

inspecting the aft lower fuselage wing

attach fitting on both wings for cracks,

and modifying any cracked aft lower

fuselage wing attach fitting. Modifying

both aft lower fuselage wing attach

fittings eliminates the repetitive

inspection requirement of AD 96–12–03.

Aviat recently started incorporating

modified aft lower fuselage wing attach

fittings on newly manufactured

airplanes. The proposed AD would

retain the requirements of AD 96–12–03,

but would exempt airplanes that had the

modified aft lower fuselage wing attach

fittings incorporated at manufacture.

The actions specified by the proposed

AD are intended to prevent possible inflight separation of the wing from the

airplane caused by a cracked fuselage

wing attach fitting.

DATES: Comments must be received on

or before June 4, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Assistant Chief Counsel,

Attention: Rules Docket No. 96–CE–23–

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

Kansas City, Missouri 64106. Comments

may be inspected at this location

between 8 a.m. and 4 p.m., Monday

through Friday, holidays excepted.

Service information that applies to the

proposed AD may be obtained from

Aviat Aircraft, Inc., P.O. Box 1240

(postal service delivery), 672 South

Washington Street (express mail), Afton,

Wyoming 83110. This information also

may be examined at the Rules Docket at

the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

Roger Caldwell, Aerospace Engineer,

FAA, Denver Aircraft Certification

Office, 26805 E. 68th Avenue, Room

214, Denver, Colorado 80249; telephone

(303) 342–1086; facsimile (303) 342–

1088.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications

should identify the Rules Docket

number and be submitted in triplicate to

the address specified above. All

communications received on or before

the closing date for comments, specified

above, will be considered before taking

action on the proposed rule. The

proposals contained in this notice may

be changed in light of the comments

received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 96–CE–23–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Central Region, Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 96–CE–23–AD, Room

1558, 601 E. 12th Street, Kansas City,

Missouri 64106.

Events Leading to the Proposed AD

AD 96–12–03, Amendment 39–9645

(61 FR 28730, June 6, 1996), applies to

Aviat Models S–1S, S–1T, S–2, S–2A,

S–2S, and S–2B airplanes that are

equipped with aft lower fuselage wing

attach fittings incorporating either part

number (P/N) 76090, 2–2107–1, or 1–

210–102. The AD currently requires

repetitively inspecting the aft lower

fuselage wing attach fitting on both

wings for cracks, and modifying any

cracked aft lower fuselage wing attach

fitting. Modifying both aft lower

fuselage wing attach fittings eliminates

the repetitive inspection requirement of

AD 96–12–03. Accomplishment of the

actions required by AD 96–12–03 is in

accordance with Aviat Service Bulletin

(SB) No. 25, dated April 3, 1996.

Aviat recently started incorporating

modified aft lower fuselage wing attach

fittings on newly manufactured Models

S–1S, S–1T, S–2, S–2A, S–2S, and S–2B

airplanes. In addition, Aviat revised SB

No. 25 (Revised November 12, 1996) to

include this airplane serial number

effectivity change.

The FAA’s Determination

After examining the circumstances

and reviewing all available information

related to the incidents described above,

the FAA has determined that (1) those

airplanes with modified aft lower

fuselage wing attach fittings

incorporated at manufacture should be

exempt from AD 96–12–03; and (2) AD

action should be taken to prevent

possible in-flight separation of the wing

from the airplane caused by a cracked

fuselage wing attach fitting.

Explanation of the Provisions of the

Proposed AD

Since an unsafe condition has been

identified that is likely to exist or

develop in other Aviat Models S–1S, S–

1T, S–2, S–2A, S–2S, and S–2B

airplanes of the same type design that

are equipped with aft lower fuselage

wing attach fittings incorporating either

P/N 76090, 2–2107–1, or 1–210–102, the

FAA is proposing to revise AD 96–12–

03. The proposed AD would retain the

requirements of AD 96–12–03, but

would exempt airplanes that had the

modified aft lower fuselage wing attach

fittings incorporated at manufacture.

Accomplishment of the proposed AD

would be in accordance with Aviat SB

No. 25, dated April 3, 1996, Revised

November 12, 1996.

Cost Impact

The FAA estimates that 500 airplanes

in the U.S. registry would be affected by

the proposed AD, that it would take

approximately 2 workhours per airplane
Federal Register / Vol. 62, No. 44 / Thursday, March 6, 1997 / Proposed Rules 10237

to accomplish the proposed initial

inspection, and that the average labor

rate is approximately $60 an hour. Parts

to accomplish the repetitive inspections

cost approximately $100 per airplane.

Based on these figures, the total cost

impact of the proposed AD on U.S.

operators is estimated to be $110,000.

These figures do not take into account

the cost of repetitive inspections. The

FAA has no way of determining how

many repetitive inspections each

owner/operator may incur over the life

of the airplane.

In addition, AD 96–12–03 currently

requires the same inspections as the

proposed AD for all 500 of the affected

airplanes. The only difference is that

newly manufactured airplanes would be

exempt from the actions because they

have modified aft lower fuselage wing

attach fittings incorporated at

manufacture. Therefore, the cost impact

of the proposed AD for operators of all

affected airplanes is the same as AD 96–

12–03.

Regulatory Impact

The regulations proposed herein

would 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

proposal would 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) if

promulgated, 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 draft

regulatory evaluation prepared for this

action has been placed 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, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13, is amended by

removing Airworthiness Directive (AD)

96–12–03, Amendment 39-9645, and by

adding a new AD to read as follows:

Aviat Aircraft, Inc.: Docket No. 96–CE–23–

AD. Revises AD 96–12–03, Amendment

39–9645.

Applicability: The following airplane

models and serial numbers, certificated in

any category, that are equipped with aft

lower fuselage wing attach fittings

incorporating part number (P/N) 76090, 2–

2107–1, or 1-210–102, and where these aft

lower fuselage wing attach fittings on both

wings have not been modified in accordance

with the ACCOMPLISHMENT

INSTRUCTIONS section of Aviat Service

Bulletin (SB) No. 25, dated April 3, 1996,

Revised November 12, 1996; or Aviat SB No.

25, dated April 3, 1996:

—Models S–1S, S–1T, S–2, S–2A, and S–

2S airplanes, all serial numbers.

—Model S–2B airplanes, serial numbers

5000 through 5348.

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 (e) 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 initially within the

next 50 hours time-in-service (TIS) after the

effective date of this AD, unless already

accomplished (compliance with AD 96–12–

03), and thereafter at intervals not to exceed

50 hours TIS.

To prevent possible in-flight separation of

the wing from the airplane caused by a

cracked aft lower fuselage wing attach fitting,

accomplish the following:

(a) Inspect the aft lower fuselage wing

attach fitting on both wings for cracks in

accordance with the ACCOMPLISHMENT

INSTRUCTIONS section of Aviat SB No. 25,

dated April 3, 1996, Revised November 12,

1996; or Aviat SB No. 25, dated April 3,

1996.

(b) If any cracked aft lower fuselage wing

attach fitting is found during any inspection

required by this AD, prior to further flight,

modify the cracked aft lower fuselage wing

attach fitting in accordance with the

ACCOMPLISHMENT INSTRUCTIONS

section of Aviat SB No. 25, dated April 3,

1996, Revised November 12, 1996; or Aviat

SB No. 25, dated April 3, 1996. Repetitive

inspections are no longer necessary on an aft

lower fuselage wing attachment fitting that

was found cracked and has the referenced

modification incorporated.

(c) Modifying the aft lower fuselage wing

attach fitting on both wings in accordance

with the ACCOMPLISHMENT

INSTRUCTIONS section of Aviat SB No. 25,

dated April 3, 1996, Revised November 12,

1996; or Aviat SB No. 25, dated April 3,

1996, is considered terminating action for the

repetitive inspection requirement of this AD.

(d) 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.

(e) 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, Denver Aircraft Certification Office,

26805 E. 68th Avenue, Room 214, Denver,

Colorado 80249. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Denver ACO. Alternative methods of

compliance approved in accordance with AD

96–12–03 are considered approved for this

AD.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Denver ACO.

(f) All persons affected by this directive

may obtain copies of the service bulletin

referred to herein upon request to Aviat

Aircraft, Inc., P.O. Box 1240 (postal service

delivery), 672 South Washington Street

(express mail), Afton, Wyoming 83110; or

may examine this service bulletin at the

FAA, Central Region, Office of the Assistant

Chief Counsel, Room 1558, 601 E. 12th

Street, Kansas City, Missouri 64106.

(g) This amendment revises AD 96–12–03,

Amendment 39–9645. Issued in Kansas City,

Missouri, on February 24, 1997.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 97–5470 Filed 3–5–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 97–NM–17–AD]

RIN 2120–AA64

Airworthiness Directives; Gulfstream

Aerospace Corporation Model G–159

(G–I) Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).