Federal Register / Vol. 63, No. 14 /Thursday, January 22, 1998 / Proposed Rules 3273

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:

SAAB aircraft AB: Docket 97–NM–306–AD.

Applicability: Model SAAB 2000 series

airplanes having serial numbers -003 through

-040 inclusive, 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 (c) 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 collapse of the main landing

gear (MLG) due to fatigue cracking of the

MLG trunnion fittings, accomplish the

following:

(a) Prior to the accumulation of 12,000 total

flight cycles, or within 100 flight cycles after

the effective date of this AD, whichever

occurs later, replace the MLG trunnion

fittings with reinforced trunnion fittings in

accordance with Saab Service Bulletin 2000–

57–010, dated February 25, 1997.

(b) As of the effective date of this AD, no

person shall install any MLG trunnion fitting

having part number 7357451–503 or –504 on

any airplane.

(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,

International Branch, ANM–116, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(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.

Note 3: The subject of this AD is addressed

in Swedish airworthiness directive SAD No.

1–108, dated February 27, 1997.

Issued in Renton, Washington, on January

14, 1998.

Gilbert L. Thompson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–1425 Filed 1–21–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–SW–07–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 Model SA 330F, G,

and J helicopters. This proposal would

require visually inspecting the

intermediate gearbox (IGB) fairing safety

stop (safety stop) for cracks, crazing, or

edge wear, and if cracks, crazing, or

edge wear exceeds the established

limits, replacing the safety stop; and,

inspecting to ensure that the inclined

drive shaft fairing hinge pin is properly

locked. A terminating action is provided

in the AD by installing an additional

safety stop on the IGB fairing. This

proposal is prompted by one report of

an accident involving the loss of the

inclined drive shaft fairing. The actions

specified by the proposed AD are

intended to prevent loss of the inclined

drive shaft fairing and impact with the

tail rotor, and subsequent loss of control

of the helicopter.

DATES: Comments must be received by

March 23, 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–07–

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. 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.

Mike Mathias, Aerospace Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Standards Staff, 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
3274 Federal Register / Vol. 63, No. 14 /Thursday, January 22, 1998 / Proposed Rules

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 97–SW–07–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–07–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 SA 330F, G, and J helicopters.

The DGAC advises that there was one

reported accident that was caused by

the loss of the inclined drive shaft

fairing.

Eurocopter France has issued

Eurocopter France SA 330 Service

Bulletin No. 54.20, Revision 1, dated

February 27, 1996, which specifies

visually inspecting the safety stop for

wear, cracks or crazing, and determining

if the edge has ruptured locally, and

replacing the safety stop. The DGAC

classified this service bulletin as

mandatory and issued DGAC AD 96–

095–076(B), dated April 24, 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

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 visually inspecting the safety

stop for cracks, crazing, or edge wear

that exceeds the limits stated in Note II

of the Accomplishment Instructions of

Eurocopter France SA 330 Service

Bulletin No. 54.20, Revision 1, dated

February 27, 1996, and if cracks,

crazing, or edge wear exceeds the

established limits, replacing the safety

stop; and, inspecting to ensure that the

inclined drive shaft fairing hinge pin is

properly locked. Both inspections are

required within 7 calendar days after

the effective date of the AD, and upon

completion of the last flight of each day.

Installing an additional safety stop

(right-angle clip) on the IGB fairing

within 60 calendar days after the

effective date of the AD is terminating

action for the requirements of this AD.

The actions would be required to be

accomplished in accordance with the

service bulletin described previously.

The FAA estimates that 1 helicopter

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 1 work hour to perform

the inspection, and two work hours to

install the safety stop, and that the

average labor rate is $60 per work hour.

Required parts would cost

approximately $50 per helicopter. Based

on these figures, the total cost impact of

the proposed AD on U.S. operators is

estimated to be $230.

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–07–

AD.

Applicability: Model SA 330 F, G, and J

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 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 loss of the inclined drive shaft

fairing hinge pin (hinge pin), that could

result in loss of the inclined drive shaft

fairing, impact with the tail rotor, and

subsequent loss of control of the helicopter,

accomplish the following:

(a) Within 7 calendar days after the

effective date of this AD, and thereafter, upon

the completion of the last flight of each day,

visually inspect the intermediate gearbox

(IGB) fairing safety stop (safety stop) and the

hinge pin in accordance with the

Accomplishment Instructions of Eurocopter

France SA 330 Service Bulletin No. 54.20,

Revision 1, dated February 27, 1996.

(1) Inspect the IGB fairing safety stop, part

number (P/N) 330A24–2086–20, for cracks or

crazing, and edge wear that exceeds the

limits stated in Note II of the

Accomplishment Instructions of Eurocopter

France SA 330 Service Bulletin No. 54.20,

Revision 1, dated February 27, 1996, and if

cracks, crazing, or edge wear that exceeds the

established limits is detected, remove the

safety stop and replace it with an airworthy

safety stop; and,

(2) Inspect the hinge pin to ensure it is

properly locked.

(b) Within 60 calendar days after the

effective date of this AD, install an additional

safety stop, P/N 330A24–2119–21, to prevent

the hinge pin from backing out of its hole in
Federal Register / Vol. 63, No. 14 /Thursday, January 22, 1998 / Proposed Rules 3275

case of a locking arm failure, in accordance

with Accomplishment Instructions of

Eurocopter France SA 330 Service Bulletin

No. 54.20, Revision 1, dated February 27,

1996.

(c) Installation of an airworthy additional

safety stop, P/N 330A24–2119–21,

constitutes terminating action for the

requirements of this AD.

(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, 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.

(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 3: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

(France) AD 96–095–076(B), dated April 24,

1996.

Issued in Fort Worth, Texas, on January 14,

1998.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 98–1428 Filed 1–21–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–ANE–46–AD]

RIN 2120–AA64

Airworthiness Directives; CFM

International CFM56–2, –2A, –2B, –3,

–3B, and –3C Series Turbofan Engines

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 CFM

International (CFMI) CFM56–2, –2A,

–2B, –3, –3B, and –3C series turbofan

engines. This proposal would require a

one-time eddy current inspection (ECI)

for cracks or gouges in certain high

pressure turbine rotor (HPTR) disks.

This proposal is prompted by a report

of a HPTR disk found to have a crack

in a rim bolt hole during a routine shop

manual ECI. The actions specified by

the proposed AD are intended to

prevent the potential for an uncontained

failure of the HPTR disk, which could

result in an inflight engine shutdown,

aborted takeoff, or damage to the

aircraft.

DATES: Comments must be received by

March 23, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

97–ANE–46–AD, 12 New England

Executive Park, Burlington, MA 01803–

5299. Comments may be inspected at

this location between 8:00 a.m. and 4:30

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

CFM International, Technical

Publications Department, 1 Neumann

Way, Cincinnati, OH 45215; telephone

(513) 552–2981, fax (513) 552–2816.

This information may be examined at

the FAA, New England Region, Office of

the Assistant Chief Counsel, 12 New

England Executive Park, Burlington,

MA.

FOR FURTHER INFORMATION CONTACT:

Glorianne Messemer, Aerospace

Engineer, Engine Certification Office,

FAA, Engine and Propeller Directorate,

12 New England Executive Park,

Burlington, MA 01803–5299; telephone

(781) 238–7132; fax (781) 238–7199.

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 Number 97–ANE–46–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, New England Region, Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 97–ANE–46–AD, 12

New England Executive Park,

Burlington, MA 01803–5299.

Discussion

This proposed airworthiness directive

(AD) is applicable to CFM International

(CFMI) CFM56–2, –2A, –2B, –3, –3B,

and –3C series turbofan engines. The

Federal Aviation Administration (FAA)

received a report of a high pressure

turbine rotor (HPTR) disk found to have

a crack in a rim bolt hole during a

routine shop manual eddy current

inspection (ECI). Investigation revealed

that the crack initiated from a gouge in

the bolt hole. The gouge is the result of

a drill break that occurred when the rim

bolt hole was being manufactured. A

review of manufacturing records

indicates that a total of 276 HPTR disks

have documented drill breaks that

occurred during manufacture of the

HPTR disk. This condition, if not

corrected, could result in an

uncontained failure of the HPTR disk,

which could result in an inflight engine

shutdown, aborted takeoff, or damage to

the aircraft.

The FAA has reviewed and approved

the technical contents of CFM56–2

Service Bulletin (SB) No. 72–817, dated

January 14, 1997, CFM56–2A SB No.

72–419, Revision 1, dated January 31,

1997, CFM56–2B SB No. 72–561,

Revision 1, dated January 31, 1997, and

CFM56–3/–3B/–3C SB No. 72–843,

dated January 14, 1997, that describe

procedures for ECI for cracks or gouges

in HPTR disks.

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 a one-time ECI for cracks or

gouges in certain HPTR disks. The

calendar end-dates listed in the

compliance section of this AD were

based upon risk analysis. The actions

would be required to be accomplished

in accordance with the SBs described

previously.

There are approximately 276 engines

of the affected design in the worldwide