25180 Federal Register / Vol. 63, No. 88/Thursday, May 7, 1998 / Proposed Rules

engine mount lug area. This condition,

if not corrected, could result in TEC

structural failure under abnormal

operating conditions, which could

result in reduced main mount load

capability, which could result in an

engine separating from the wing and

subsequent loss of control of the aircraft.

The FAA has reviewed and approved

the technical contents PW Alert Service

Bulletin (ASB) No. JT9D–A6322,

Revision 1, dated March 19, 1998, and

ASB No. JT9D–7R4–A72–546, Revision

1, dated March 19, 1998, that describe

procedures for acid etch inspections of

the TEC wall between and on either side

of the ‘‘R’’ and ‘‘S’’ rails in the engine

mount lug area (top quadrant of the

case) for the presence of weld material,

and if that material is detected, removal

from service and replacement with

serviceable parts.

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the proposed AD would

require, at the next removal of the TEC

from the low pressure turbine case ‘‘P’’

flange for maintenance after the

effective date of this AD, a one-time acid

etch inspection of TEC wall between

and on either side of the ‘‘R’’ and ‘‘S’’

rails in the engine mount lug area (top

quadrant of the case) for the presence of

weld material, and if that material is

detected, removal from service and

replacement with serviceable parts. The

actions would be required to be

accomplished in accordance with the

ASBs described previously.

There are approximately 2,720

engines of the affected design in the

worldwide fleet. The FAA estimates that

1,125 engines installed on aircraft of

U.S. registry would be affected by this

proposed AD, that it would take

approximately 1.4 work hours per

engine to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $94,500.

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 the following new airworthiness

directive:

Pratt & Whitney: Docket No. 98–ANE–21–

AD.

Applicability: Pratt & Whitney (PW)

Models JT9D–7, –7A, –7H, –7AH, –7F, –7J,

–20, –20J, –7Q, –7Q3, –59A, –70A, and

–7R4D turbofan engines. These engines are

installed on but not limited to Boeing 747

and 767 series, McDonnell Douglas DC–10

series, and Airbus Industrie A300 and A310

series aircraft.

Note 1: This airworthiness directive (AD)

applies to each engine 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 engines 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 (b)

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, unless

accomplished previously.

To prevent turbine exhaust case (TEC)

structural failure under abnormal operating

conditions, which could result in reduced

main mount load capability, which could

result in an engine separating from the wing

and subsequent loss of control of the aircraft,

accomplish the following:

(a) At the next removal of the TEC from the

low pressure turbine case ‘‘P’’ flange for

maintenance after the effective date of this

AD, accomplish the following in accordance

with PW Alert Service Bulletin (ASB) No.

JT9D–A6322, Revision 1, dated March 19,

1998, or ASB No. JT9D–7R4–A72–546,

Revision 1, dated March 19, 1998, as

applicable:

(1) Perform a one-time acid etch inspection

of TEC wall between and on either side of the

‘‘R’’ and ‘‘S’’ rails in the engine mount lug

area (top quadrant of the case) for the

presence of weld material.

(2) If weld material is found, remove from

service the TEC and replace with a

serviceable part.

(b) 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, Engine

Certification Office. Operators shall submit

their request through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

(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 aircraft to

a location where the inspection requirements

of this AD can be accomplished.

Issued in Burlington, Massachusetts, on

April 29, 1998.

Thomas A. Boudreau,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 98–12062 Filed 5–6–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–SW–43–AD]

Airworthiness Directives; Eurocopter

France 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 Model SA 330F, G,

and J helicopters. This proposal would

require removal and replacement of

each tail rotor electrical bonding braid

(bonding braid). This proposal is

prompted by one in-service report of
Federal Register / Vol. 63, No. 88/Thursday, May 7, 1998 / Proposed Rules 25181

failure of a bonding braid. The actions

specified by the proposed AD are

intended to prevent failure of a bonding

braid due to fatigue, resulting impact

with the tail rotor blades, and

subsequent loss of control of the

helicopter.

DATES: Comments must be received on

or before June 8, 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–43–

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.

The service information referenced in

the proposed rule may be obtained from

American Eurocopter Corporation, 2701

Forum Drive, Grand Prairie, Texas

75053–4005, telephone (972) 641–3460,

fax (972) 641–3527. This information

may be examined at the FAA, Office of

the Regional Counsel, Southwest

Region, 2601 Meacham Blvd., Room

663, Fort Worth, Texas.

FOR FURTHER INFORMATION CONTACT:

Mr. Robert McCallister, Aerospace

Engineer, FAA, Rotorcraft Directorate,

Rotorcraft Standards Staff, 2601

Meacham Blvd., Fort Worth, Texas

76137, telephone (817) 222–5121, 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–43–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–43–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

France Model SA 330F, G, and J

helicopters. The DGAC advises that, in

order to improve the in-service

resistance of the bonding braids and to

limit the risks of their impacting the

blades, the bonding braids and their

attachment clamps were to be removed

and replaced before September 1, 1995.

Eurocopter France has issued

Eurocopter France Service Bulletin SA

330 No. 65.73 R3, dated June 22, 1995.

The DGAC classified this service

bulletin as mandatory and issued AD

95–153–072(B), dated July 19, 1995, 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 tot

his 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 France

Model SA 330F, G, and J helicopters of

the same type design registered in the

United States, the proposed AD would

require replacing the bonding braids.

The actions would be required to be

accomplished in accordance with the

service bulletin described previously.

The FAA estimates that 2 helicopters

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 2 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 $250 per

helicopter. Based on these figures, the

total cost impact of the proposed AD on

U.S. operators is estimated to be $740.

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–43–

AD.

Applicability: Model SA330F, G, and J

helicopters with tail rotor electrical bonding
25182 Federal Register / Vol. 63, No. 88/Thursday, May 7, 1998 / Proposed Rules

braids, part number (P/N) 332A031.1276.00,

that have not been modified in accordance

with AMS 332A07–66–003 or AMS 33207–

66–072, 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 (b) 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 within the next 60

calendar days, unless accomplished

previously.

To prevent failure of a tail rotor electrical

bonding braid (bonding braid) due to fatigue,

resulting impact with the tail rotor blades,

and subsequent loss of control of the

helicopter, accomplish the following:

(a) Remove the bonding braids, P/N

332A31.1276.00, and replace them with

airworthy bonding braids, P/N

332A31.1276.01 in accordance with

paragraphs B and C of the Operating

Procedure of Eurocopter France Service

Bulletin SA 330 No. 65.73 R3, dated June 22,

1995.

(b) 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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft Standards Staff.

(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 helicopter

to a location where the requirements of this

AD can be accomplished.

Note 3: The subject of this AD is addressed

in Direction Generale L’Aviation Civile

(France) AD 95–153–072(B), dated July 19,

1995.

Issued in Fort Worth, Texas, on April 29,

1998.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 98–12113 Filed 5–6–98; 8:45 am]

BILLING CODE 4910–13–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–SW–36–AD]

Airworthiness Directives; Eurocopter

France Model AS 332C, L, and L1

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 332C, L,

and L1 helicopters. This proposal would

require replacing main rotor blades with

modified main rotor blades. This

proposal is prompted by reports of an

investigation that found broken braids

on main rotor blade de-icers. The

actions specified by the proposed AD

are intended to prevent loss of the deicing capabilities of the main rotor

blades, adverse performance during

flight in icing conditions, and

subsequent loss of control of the

helicopter.

DATES: Comments must be received by

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–36–

Ad, 2601 Meacham Blvd., Room 663,

Forth 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.

The service information referenced in

the proposed rule may be obtained from

American Eurocopter Corporation, 2701

Forum Drive, Grand Prairie, Texas

75053–4005, telephone (972) 641–3460,

fax (972) 641–3527. This information

may be examined at the FAA, Office of

the Regional Counsel, Southwest

Region, 2601 Meacham Blvd., Room

663, Forth Worth, Texas.

FOR FURTHER INFORMATION CONTACT: Mr.

Robert McCallister, Aerospace Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Standards Staff, 2601 Meacham Blvd.,

Forth Worth, Texas 76137, telephone

(817) 222–5121, fax (812) 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–36–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–36–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

France AS 332C, L, and L1 helicopters.

The DGAC advises that replacing the deicers on these helicopters is necessary to

prevent loss of the de-icing function due

to damaged electric return braids.

Eurocopter France has issued Telex

Service Number (No.) 10002, dated

January 17, 1994, which specifies

modification of the main rotor blade

within specified time intervals. The

DGAC classified the Technical Directive

No. 230 referenced in the telex as

mandatory and issued AD 95–029–

054(B) 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