30660 Federal Register / Vol. 63, No. 108 / Friday, June 5, 1998 / Proposed Rules

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 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing Airworthiness Directive (AD)

96–12–03 R1, Amendment 39–10109 (62

FR 44535, August 22, 1997), and by

adding a new AD to read as follows:

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

AD; Revises AD 96–12–03 R1,

Amendment 39–10109.

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, P/N

2–2107–1, or P/N 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 one of the

following service bulletins (SB):

Service Bulletins

—Aviat SB No. 25, dated April 3, 1996,

Revised November 12, 1996, Revised

November 11, 1997;

—Aviat SB No. 25, dated April 3, 1996,

Revised November 12, 1996; or

—Aviat SB No. 25, dated April 3, 1996.

Airplanes Affected

—Models S–1S, S–1T, S–2, S–2A, and S–2S

airplanes, all serial numbers.

—Model S–2B airplanes, serial numbers 5000

through 5336.

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 as indicated in the

body of this AD.

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) Within 50 hours time-in-service (TIS)

after October 3, 1997 (the effective date of AD

96–12–03 R1), unless already accomplished

(compliance with either AD 96–12–03 R1 or

AD 96–12–03), and thereafter at intervals not

to exceed 50 hours TIS, inspect the aft lower

fuselage wing attach fitting on both wings for

cracks. Accomplish these inspections in

accordance with the ACCOMPLISHMENT

INSTRUCTIONS section of one of the

following SB’s:

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

Revised November 12, 1996, Revised

November 11, 1997;

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

Revised November 12, 1996; or

(3) 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 one of the SB’s referenced in

paragraphs (a)(1), (a)(2), and (a)(3) of this AD.

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 one of the SB’s

referenced in paragraphs (a)(1), (a)(2), and

(a)(3) of this AD 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.

(1) The request shall be forwarded through

an appropriate FAA Maintenance Inspector,

who may add comments and then send it to

the Manager, Denver ACO.

(2) Alternative methods of compliance

approved in accordance with AD 96–12–03

R1 or 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 document referred

to herein upon request to Aviat Aircraft, Inc.,

P.O. Box 1240, Afton, Wyoming 83110; or

may examine this document at the FAA,

Central Region, Office of the Regional

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

Kansas City, Missouri 64106.

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

R1, Amendment 39–10109.

Issued in Kansas City, Missouri, on May

29, 1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–14906 Filed 6–4–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–SW–55–AD]

Airworthiness Directives; Agusta

S.p.A. Model A109C and A109K2

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

Agusta S.p.A. Model A109C and

A109K2 helicopters. This proposal

would require removing the main rotor

pitch link assemblies, measuring the

radial play of the upper and lower

spherical bearings (bearings), and

replacing any unairworthy bearings.

This proposal is prompted by four

reports of increased vibration of the

helicopters caused by wear in the

bearings of the main rotor pitch change

link assembly. The actions specified by

the proposed AD are intended to detect

unairworthy bearings on the pitch

change link assembly and to prevent

increased vibration and subsequent

reduced controllability of the helicopter.

DATES: Comments must be received on

or before July 6, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 97–SW–55–

AD, 2601 Meacham Blvd., Room 663,

Fort Worth, Texas 76137. Comments

may be inspected at this location

between 9:00 a.m. and 3:00 p.m.,

Monday through Friday, except Federal

holidays.

FOR FURTHER INFORMATION CONTACT: Mr.

Shep Blackman, Aerospace Engineer,

FAA, Rotorcraft Directorate, Rotorcraft
Federal Register / Vol. 63, No. 108 / Friday, June 5, 1998 / Proposed Rules 30661

Standards Staff, 2601 Meacham Blvd.,

Fort Worth, Texas 76137, telephone

(817) 222–5296, fax (817) 222–5961.

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

summarizing 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. 97–SW–55–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, Office of the Regional Counsel,

Southwest Region, Attention: Rules

Docket No. 97–SW–55–AD, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas 76137.

Discussion

The Registro Aeronautico Italiano

(RAI), which is the airworthiness

authority for Italy, recently notified the

FAA that an unsafe condition may exist

on Agusta Model A109C and A109K2

helicopters. The RAI advises that there

have been instances of increased

vibration in Agusta Model A109C

helicopters, which necessitated an AD

requiring compliance in accordance

with Agusta Bollettino Technico

Telegraphico No. 109–9, dated March

23, 1995.

Agusta has issued Agusta Bollettino

Technico Telegraphico Nos. 109–9 and

109K–2, both dated March 23, 1995,

which specify a procedure to measure

the radial play of both the upper and

lower spherical bearings of the main

rotor pitch change link assemblies. The

RAI classified these service bulletins as

mandatory and issued RAI AD’s 95–082

and 95–083, both dated March 28, 1995,

to assure the continued airworthiness of

these helicopters in Italy.

This helicopter model is

manufactured in Italy and is type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the RAI has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the RAI,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Since an unsafe condition has been

identified that is likely to exist or

develop on other Agusta Model A109C

and A109K2 helicopters of the same

type design registered in the United

States, the proposed AD would require

inspection of the main rotor pitch link

assemblies Part Number (P/N) 109–

0110–71, and if the radial play of the

spherical bearings exceeds 0.2

millimeters, or .008 inches, replacement

of the affected bearings prior to further

flight

The FAA estimates that 3 helicopters

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 3 work hours per

helicopter to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Required parts

would cost approximately $1,122 for the

upper bearing and $995 for the lower

bearing per helicopter. Based on these

figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $6,891.

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 proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the 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 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, 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 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive to

read as follows:

Agusta S.p.A.: Docket No. 97–SW–55–AD.

Applicability: Model A109C and A109K2

helicopters, certificated in any category.

Note 1: This AD applies to each helicopter

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

helicopters that have been modified, altered,

or repaired so that the performance of the

requirements of this AD. For helicopters that

have been modified, altered, or repaired so

that the performance of the requirements of

this AD is affected, the owner/operator must

use the authority provided in paragraph (d)

to request approval from the FAA. This

approval may address either no action, if the

current configuration eliminates the unsafe

condition, or different actions necessary to

address the unsafe condition described in

this AD. Such a request should include an

assessment of the effect of the changed

configuration on the unsafe condition

addressed by this AD. In no case does the

presence of any modification, alteration, or

repair remove any helicopter from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent main rotor pitch change link

spherical bearing axial play due to wear,

which could result in an increase in the

vibration level and reduced controllability of

the helicopter, accomplish the following:
30662 Federal Register / Vol. 63, No. 108 / Friday, June 5, 1998 / Proposed Rules

(a) Within the next 10 hours time in service

(TIS) and thereafter at intervals not to exceed

100 hours TIS, remove the pitch change link

assembly, part number (P/N) 109–0110–71.

(b) Measure the radial play at both the

upper and lower spherical bearings. If the

radial play of a bearing exceeds 0.2

millimeters, or .008 inches, replace the

affected bearing with an airworthy bearing

prior to further flight.

Note 2: Agusta Bollettino Technico

Telegrafico No. 109–9, dated March 23, 1995,

pertains to the subject of this AD.

(c) Reinstall the pitch change link

assembly.

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, FAA,

Rotorcraft Directorate, Rotorcraft Standards

Staff. Operators shall submit their requests

through an FAA Principal Maintenance

Inspector, who may concur or comment and

then send it to the Manager, Rotorcraft

Standards Staff.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft Standards Staff.

(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 helicopter

to a location where the requirements of this

AD can be accomplished.

Note 4: The subject of this AD is addressed

in Registro Aeronautico Italiano (Italy) AD’s

95–082 and 95–083, both dated March 28,

1995.

Issued in Fort Worth, Texas, on May 28,

1998.

Henry A. Armstrong,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 98–14912 Filed 6–4–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–SW–64–AD]

Airworthiness Directives; Eurocopter

France Model AS–365N, N1, and N2

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

Eurocopter France Model AS–365N, N1,

and N2 helicopters, with certain main

rotor head frequency adapters

(frequency adapters) installed. This

proposal would require inspecting the

frequency adapter to determine if a

certain frequency adapter is installed,

and if so, removing and replacing the

frequency adapter with an airworthy

frequency adapter before further flight.

This proposal is prompted by a report

of disbonding of the metal center

section of a frequency adapter from the

elastomer on a main rotor head, caused

by a lack of adherence during the

production process. The actions

specified by the proposed AD are

intended to prevent increased vibrations

caused by disbonding of the center

section of a frequency adapter from the

elastomer and subsequent reduced

controllability of the helicopter.

DATES: Comments must be received on

or before July 6, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 97–SW–64–

AD, 2601 Meacham Blvd., Room 663,

Fort Worth, Texas 76137. Comments

may be inspected at this location

between 9:00 a.m. and 3:00 p.m.,

Monday through Friday, except Federal

holidays.

FOR FURTHER INFORMATION CONTACT: Mr.

Mike Mathias, Aerospace Engineer,

Rotorcraft Standards Staff, Rotorcraft

Directorate, FAA, 2601 Meacham Blvd.,

Fort Worth, Texas 76137, telephone

(817) 222–5123, fax (817) 222–5961.

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

summarizing 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. 97–SW–64–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, Office of the Regional Counsel,

Southwest Region, Attention: Rules

Docket No. 97–SW–64–AD, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas 76137.

Discussion

The Direction General De L’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

recently notified the FAA that an unsafe

condition may exist on Eurocopter

France Model AS–365N, N1, and N2

helicopters that have been fitted with a

frequency adapter, part number (P/N)

704A33–640–031 (E1T2624–01A), or

delivered in pairs under the P/N

365A31–1858–01, manufactured before

April 1, 1991, with a serial number (S/

N) equal to or less than 8188; or P/N

704A33–640–046 (E1T3023–01), or

delivered in pairs under the P/N

365A31–1858–02, manufactured before

April 1, 1991, with a S/N equal to or

less than 3122. The DGAC advises that

disbonding between the center metal

section and the elastomer of the

frequency adapter may occur.

Eurocopter France has issued

Eurocopter France AS–365 Service

Bulletin, No. 01.00.44, dated May 9,

1996, which specifies a visual

inspection of the frequency adapter face

to determine its P/N, S/N, and date of

manufacture and to remove and replace

certain frequency adapters with an

unaffected frequency adapter. The

DGAC classified this service bulletin as

mandatory and issued AD 96–117–

040(B), dated June 19, 1996, in order to

assure the continued airworthiness of

these helicopters in France.

This helicopter model is

manufactured in France and is type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the DGAC has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the DGAC,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are