19672 Federal Register / Vol. 63, No. 76 /Tuesday, April 21, 1998 / Proposed Rules

Accomplishment Instructions of Eurocopter

France Service Bulletin No. 55.01, Revision

3, dated April 25, 1997 (service bulletin). If

the fit and dimensions of the components

specified in paragraph 2.B.2)a) exceed the

tolerances in the applicable structural repair

manual, replace with airworthy parts.

(3) If Modification 072215 has not been

installed, first comply with paragraphs 2.A.,

2.B.1), and 2.B.3), and then comply with

paragraph 2.B.2)c) of the Accomplishment

Instructions of the service bulletin.

Note 2: Modification kit P/N 315A–07–

0221571 contains the necessary materials to

accomplish this modification.

(b) Before the first flight of each day:

(1) Visually inspect the installation of the

half-shells, the horizontal stabilizer supports,

and the horizontal stabilizer for corrosion or

cracks. Repair any corroded parts in

accordance with the applicable maintenance

manual. Replace any cracked components

with airworthy parts before further flight.

(2) Confirm that there is no play in the

horizontal stabilizer supports by lightly

shaking the horizontal stabilizer. If play is

detected, comply with paragraphs 2.A. and

2.B.2)a) of the service bulletin. If the fit and

dimensions of the components specified in

paragraph 2.B.2)a) exceed the tolerances in

the applicable structural repair manual,

replace with airworthy parts before further

flight.

(c) At intervals not to exceed 400 hours

time-in-service (TIS) or four calendar

months, whichever occurs first, inspect and

lubricate the spar tube attachment bolts.

(d) Within 90 calendar days and thereafter

at intervals not to exceed 24 calendar

months, visually inspect the inside of the

horizontal spar tube in accordance with

paragraph 2.A. and 2.B.)1) of the service

bulletin.

(1) If corrosion is found inside the tube,

other than in the half-shell area, replace the

tube with an airworthy tube within the next

500 hours TIS or 18 calendar months,

whichever occurs first.

(2) If corrosion is found inside the tube in

the half-shell area, apply a protective

treatment as described in paragraph 2.B.1)b)

of the service bulletin.

(e) 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, Rotorcraft

Standards Staff, FAA, Rotorcraft Directorate.

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.

(f) 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 Direction Generale De L’Aviation Civile

(France) AD 96–277–037(B)R1, dated May 21,

1997.

Issued in Fort Worth, Texas, on April 14,

1998.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 98–10465 Filed 4–20–98; 8:45 am]

BILLING CODE 4910–13–V

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–SW–38–AD]

Airworthiness Directives; Eurocopter

France Model SA 330F, G, and J

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 (Eurocopter) Model

SA 330F, G, and J helicopters. This

proposal would require initial and

repetitive inspections of each tail rotor

shaft flapping hinge retainer (retainer)

for cracks and replacement of a retainer

if a crack is discovered. This proposal

is prompted by a report of high

vibrations occurring on a helicopter

while it was in service due to a cracked

retainer. The actions specified by the

proposed AD are intended to detect

cracks in the retainers that, if left

undetected, could lead to high tail rotor

vibrations, loss of tail rotor control, and

subsequent loss of control of the

helicopter.

DATES: Comments must be received on

or before May 21, 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–38–

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,

FAA, Rotorcraft Directorate, Rotorcraft

Standards Staff, 2601 Meacham Blvd.,

Fort Worth, Texas 76137, telephone

(817) 222–5123, (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–38–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–38–AD, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas 76137.

Discussion

The Direction Generale De L’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

recently notified the FAA that an unsafe

condition may exist on Eurocopter

Model SA 330F, G, and J helicopters.

The DGAC advises that cracking of the

retainers could lead to high tail rotor

vibrations, loss of tail rotor control, and

subsequent loss of control of the

helicopter.

Eurocopter France has issued

Eurocopter France Service Bulletin No.

05.84, Revision 1, dated January 29,

1996, which specifies visually checking

the entire outside surface of the five

flapping hinge retainers for cracks. If it

cannot be determined by the visual

inspection that no crack is present, the

service bulletin also specifies that a dyepenetrant crack detection inspection be

performed. The DGAC classified this

service bulletin as mandatory and

issued DGAC AD 96–076–075(AB)R1,
Federal Register / Vol. 63, No. 76 /Tuesday, April 21, 1998 / Proposed Rules 19673

dated November 5, 1997, 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 § 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 certificated for

operation in the United States.

Since an unsafe condition has been

identified that is likely to exist or

develop on other Eurocopter Model SA

330F, G, and J helicopters of the same

type design registered in the United

States, the proposed AD would require

a dye penetrant inspection of the

retainers for cracks prior to the first

flight of each day.

The FAA estimates that 4 helicopter

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 0.5 work hour per

helicopter to accomplish each dyepenetrant inspection, 2.0 work hours to

replace the retainers on each helicopter,

if necessary, and that the average labor

rate is $60 per work hour. Required

parts would cost approximately

$56,900. Based on these figures, the

total cost impact of the proposed AD on

U.S. operators is estimated to be

$252,080, assuming that the retainers on

the tail rotor blades are replaced on all

4 helicopters and each helicopter is dye

penetrant inspected 200 times per year.

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:

Eurocopter France: Docket No. 97–SW–38–

AD.

Applicability: Model SA 330F, G, and J

helicopters with tail rotor head assembly,

part number 330 A 33 0000 all dash numbers,

or 330 A 33 0001 all dash numbers, installed,

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 is affected, the

owner/operator must use the authority

provided in paragraph (c) 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 detect cracks on a tail rotor shaft

flapping hinge retainer (retainer) that could

lead to high tail rotor vibrations, loss of tail

rotor control, and subsequent loss of control

of the helicopter, accomplish the following:

(a) Before further flight, and thereafter

before the first flight of each day, perform a

dye-penetrant inspection of each retainer for

cracks.

(b) If a crack is found on any retainer,

replace it with an airworthy retainer before

further flight.

Note 2: Eurocopter Service Bulletin No.

05.84, Revision No. 1, dated January 29,

1996, pertains to the subject of this AD.

(c) 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, Rotorcraft

Standards Staff, Rotorcraft Directorate, FAA.

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.

(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 helicopter

to a location where the requirements of this

AD can be accomplished.

Note 4: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

(France) AD 96–076–075(AB)R1, dated

November 5, 1997.

Issued in Fort Worth, Texas, on April 14,

1998.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 98–10462 Filed 4–20–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–65–AD]

RIN 2120–AA64

Airworthiness Directives; Empresa

Brasileira de Aeronautica, S.A.

(EMBRAER) Model EMB–145 Series

Airplanes

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

certain EMBRAER Model EMB–145

series airplanes. This proposal would

require replacement of the horizontal

stabilizer anti-icing valve with a new

anti-icing valve. This proposal also

would require reinforcement of the

insulation over the anti-icing ducts of

the horizontal stabilizer thermal antiicing system. This proposal is prompted

by issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by the proposed AD

are intended to prevent failure of the