31610 Federal Register / Vol. 63, No. 111 /Wednesday, June 10, 1998 /Rules and Regulations

Blvd., Fort Worth, Texas 76137, (817)

222–5159, fax (817) 222–5960.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to BHTC helicopters

was published in the Federal Register

on April 1, 1998 (63 FR 15790). That

action proposed to require shimming

the bearing supports within the next 25

hours time-in-service.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed except for small

editorial change. The FAA has

determined that these changes will

neither increase the scope of the AD nor

increase the economic burden on any

operator.

The FAA estimates that 160

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 4 work hours per

helicopter to accomplish the shimming

of the bearing support, and that the

average labor rate is $60 per work hour.

Required parts will cost approximately

$30 per helicopter. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$43,200.

The regulations adopted herein will

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 final rule does

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)

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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:

AD 98–12–22 Bell Helicopter Textron

Canada: Amendment 39–10576. Docket

No. 98-SW–10-AD.

Applicability: Model 407 helicopters, serial

numbers 53000, 53002 through 53065, 53067,

and 53069 through 53075, 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 25 hours

time-in-service, unless accomplished

previously.

To prevent failure of the bearing supports,

which could result in excessive tail rotor

drive system vibration, loss of tail rotor drive,

and subsequent loss of control of the

helicopter, accomplish the following:

(a) Shim the tail rotor drive system bearing

supports in accordance with the

Accomplishment Instructions contained in

Bell Helicopter Textron Alert Service

Bulletin No. 407-97–7, dated February 27,

1997.

(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

Certification Office, 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

Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft 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 helicopter

to a location where the requirements of this

AD can be accomplished.

(d) The shimming shall be done in

accordance with Bell Helicopter Textron

Alert Service Bulletin No. 407–97–7, dated

February 27, 1997. This incorporation by

reference was approved by the Director of the

Federal Register in accordance with 5 U.S.C.

552(a) and 1 CFR part 51. Copies may be

obtained from Bell Helicopter Textron

Canada, 12,800 Rue de l’Avenir, Mirabel,

Quebec JON1LO, telephone (800) 463–3036,

fax (514) 433–0272. Copies may be inspected

at the FAA, Office of the Regional Counsel,

Southwest Region, 2601 Meacham Blvd.,

Room 663, Fort Worth, Texas; or at the Office

of the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

(e) This amendment becomes effective on

July 15, 1998.

Note 3: The subject of this AD is addressed

in Transport Canada (Canada) AD No. CF–

97–08, dated May 30, 1997.

Issued in Fort Worth, Texas, on June 2,

1998.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 98–15264 Filed 6–9–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–SW–02–AD; Amendment

39–10575; AD 98–12–21]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France Model SA. 315B Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Eurocopter France Model

SA. 315B helicopters that requires an

initial and repetitive visual inspections

and modification, if necessary, of the

horizontal stabilizer spar tube (spar

tube). This amendment is prompted by

an in-service report of fatigue cracks

that initiated from corrosion pits. The

actions specified by this AD are
Federal Register / Vol. 63, No. 111 /Wednesday, June 10, 1998 /Rules and Regulations 31611

intended to prevent fatigue failure of the

spar tube, separation and impact of the

horizontal stabilizer with the main or

tail rotor and subsequent loss of control

of the helicopter.

DATES: Effective July 15, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 15,

1998.

ADDRESSES: The service information

referenced in this AD 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; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Richard Monschke, Aerospace Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Standards Staff, 2601 Meacham Blvd.,

Fort Worth, Texas 76137, telephone

(817) 222–5116, fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to Eurocopter France

Model SA. 315B helicopters was

published in the Federal Register on

April 21, 1998 (63 FR 19670). That

action proposed to require an initial and

repetitive visual inspections and

modification, if necessary, of the

horizontal stabilizer spar tube (spar

tube).

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed.

The FAA estimates that 28 helicopters

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 0.5 work hour per

helicopter to accomplish the inspections

and 3 work hours per helicopter to

accomplish the modification, and that

the average labor rate is $60 per work

hour. Required parts would cost

approximately $1100 per helicopter.

Based on these figures, the total cost

impact of the proposed AD on U.S.

operators is estimated to be $1310 per

helicopter.

The regulations adopted herein will

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 final rule does

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)

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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:

AD 98–12–21 Eurocopter France:

Amendment 39–10575. Docket No. 98–

SW–02–AD.

Applicability: Model SA. 315B helicopters

with horizontal stabilizers, part number (P/N)

315A35–10–000–1, 315A35–10–000–2, or

higher 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 (e) 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 a fatigue failure of the

horizontal stabilizer spar tube (spar tube),

impact of the horizontal stabilizer with the

main or tail rotor and subsequent loss of

control of the helicopter, accomplish the

following:

(a) Before further flight:

(1) Inspect the aircraft records and the

horizontal stabilizer installation to determine

whether Modification 072214 (installation of

the spar tube without play) or Modification

072215 (adding two half-shells on the spar)

has been accomplished.

(2) If Modification 072214 has not been

installed, comply with paragraphs 2.A.,

2.B.1), 2.B.2)a), and 2.B.2)b) of the

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
31612 Federal Register / Vol. 63, No. 111 /Wednesday, June 10, 1998 /Rules and Regulations

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.

(g) The modification shall be done in

accordance with Eurocopter France Service

Bulletin No. 55.01, Revision 3, dated April

25, 1997. This incorporation by reference was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from American Eurocopter Corporation, 2701

Forum Drive, Grand Prairie, Texas 75053–

4005. Copies may be inspected at the FAA,

Office of the Regional Counsel, Southwest

Region, 2601 Meacham Blvd., Room 663, Fort

Worth, Texas; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(h) This amendment becomes effective on

July 15, 1998.

Note 4: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

(France) AD 96–277–337(B)R1, dated May 21,

1997.

Issued in Fort Worth, Texas, on June 2,

1998.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 98–15263 Filed 6–9–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–45–AD; Amendment

39–10580; AD 98–12–26]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F.28 Mark 1000, 2000, 3000, and

4000 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Fokker Model F.28

Mark 1000, 2000, 3000, and 4000 series

airplanes, that requires a one-time

inspection to determine the torque

values of the coupling fitting attachment

bolts at fuselage station 10790, and

corrective action, if necessary. This

amendment is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by this AD are intended to

prevent loss of the coupling fitting

attachment bolts between the center

wing section and the fuselage, and

consequent reduced structural integrity

of the airplane.

DATES: Effective July 15, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 15,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Fokker Services B.V., Technical

Support Department, P. O. Box 75047,

1117 ZN Schiphol Airport, the

Netherlands. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Fokker

Model F.28 Mark 1000, 2000, 3000, and

4000 series airplanes was published in

the Federal Register on April 6, 1998

(63 FR 16711). That action proposed to

require a one-time inspection to

determine the torque values of the

coupling fitting attachment bolts at

fuselage station 10790, and corrective

action, if necessary.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 27 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 128

work hours per airplane to accomplish

the required inspection, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $207,360, or $7,680 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

Regulatory Impact

The regulations adopted herein will

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 final rule does

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)

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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.