Federal Register / Vol. 63, No. 111 /Wednesday, June 10, 1998 /Rules and Regulations 31609

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 the following new airworthiness

directive:

98–12–27 British Aerospace Regional

Aircraft [Formerly Jetstream Aircraft

Limited; British Aerospace (Commercial

Aircraft) Limited]: Amendment 39–

10581. Docket 98–NM–53–AD.

Applicability: BAe Model ATP airplanes,

constructor’s numbers 2002 through 2067

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 (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 detect and correct cracking of the

splined operating shaft of the internal door

handle on the forward passenger door, rear

passenger door, and rear baggage door, which

could result in failure of the internal door

handle, inability to operate the door during

an emergency evacuation, and consequent

injury to airplane occupants; accomplish the

following:

(a) Prior to the accumulation of 2,000 flight

cycles on the splined operating shaft of the

internal door handle on the forward

passenger door, rear passenger door, and rear

baggage door; or within 60 days after the

effective date of this AD; whichever occurs

later: Accomplish either paragraph (a)(1) or

(a)(2) of this AD.

(1) Perform a magnetic particle inspection

to detect cracking of the splined operating

shaft of the internal door handle on the

forward passenger door, rear passenger door,

and rear baggage door, in accordance with

British Aerospace Regional Aircraft BAe ATP

Alert Service Bulletin ATP–A52–30, dated

March 19, 1997.

(i) If any crack is found, prior to further

flight, accomplish the actions required by

paragraph (a)(2).

(ii) If no crack is found, repeat the actions

required by paragraph (a) of this AD at

intervals not to exceed 1,000 flight cycles.

(2) Replace the existing splined operating

shaft with a new splined operating shaft, in

accordance with the alert service bulletin.

Repeat the actions required by paragraph (a)

of this AD within 2,000 flight cycles after the

replacement, and thereafter at intervals not to

exceed 1,000 flight cycles.

(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,

International Branch, ANM–116, FAA,

Transport Airplane Directorate. Operators

shall submit their request 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.

(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 airplane to

a location where the requirements of this AD

can be accomplished.

(d) The actions shall be done in accordance

with British Aerospace Regional Aircraft BAe

ATP Alert Service Bulletin ATP–A52–30,

dated March 19, 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 AI(R) American Support, Inc.,

13850 Mclearen Road, Herndon, Virginia

20171. Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Note 3: The subject of this AD is addressed

in British airworthiness directive 004–03–97.

(e) This amendment becomes effective on

July 15, 1998.

Issued in Renton, Washington, on June 3,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–15253 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–10–AD; Amendment

39–10576; AD 98–12–22]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron Canada Model 407

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Bell Helicopter Textron

Canada (BHTC) Model 407 helicopters

that requires shimming the tail rotor

drive system bearing supports (bearing

supports). This amendment is prompted

by reports of cracked bearing hangar

support arms in the area of the fillet

radius. The actions specified by this AD

are intended 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.

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 Bell Helicopter Textron Canada,

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

JON1LO, telephone (800) 463–3036, fax

(514) 433–0272. 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.

Jurgen Priester, Aerospace Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Certification Office, 2601 Meacham
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