Federal Register / Vol. 65, No. 220 / Tuesday, November 14, 2000 / Rules and Regulations 68071

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(f) The actions shall be done in accordance

with Raytheon Aircraft Service Bulletin SB

24–3212, dated August 1999; or Raytheon

Aircraft Service Bulletin SB 24–3213,

Revision 1, dated February 2000; as

applicable. 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 Raytheon Aircraft Company, 9709 East

Central, Wichita, Kansas 67206. Copies may

be inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Wichita Aircraft

Certification Office, 1801 Airport Road,

Room 100, Mid-Continent Airport, Wichita,

Kansas; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Effective Date

(g) This amendment becomes effective on

December 19, 2000.

Issued in Renton, Washington, on

November 1, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–28479 Filed 11–13–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–14–AD; Amendment

39–11967; AD 2000–22–19]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France Model SA330F, G, and J

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD)

that applies to Eurocopter France Model

SA330F, G, and J helicopters and

requires inspecting the tail rotor blade

(blade) skin for cracks and replacing, as

necessary, the blade. This amendment

requires skin bonding and eddy current

inspections of the blade skin for cracks

and would reference a more recent

service bulletin (SB). This amendment

is prompted by improved inspection

methods and by the manufacturer

revising the SB referenced in the current

AD. The actions specified by this AD are

intended to prevent fatigue cracking of

a blade, failure of a blade, and

subsequent loss of control of the

helicopter.

DATES: Effective December 19, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

19, 2000.

ADDRESSES: The service information

referenced in this AD 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; or at the Office

of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Jim

Grigg, Aviation Safety Engineer, FAA,

Rotorcraft Directorate, Regulations

Group, Fort Worth, Texas 76193–0111,

telephone (817) 222–5490, fax (817)

222–5961.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 80–12–04,

Amendment 39–3790 (45 FR 37180,

June 2, 1980), which applies to

Eurocopter France Model SA330F, G,

and J helicopters, was published in the

Federal Register on August 10, 2000 (65

FR 48936). That action proposed to

require skin bonding and eddy current

inspections of the blade skin for cracks

and referenced a more recent SB.

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 4 helicopters

of U.S. registry will be affected by this

AD, that it will take approximately 1.5

work hours per helicopter to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Based on these figures, the total cost

impact of the AD on U.S. operators is

estimated to be $360.

The regulations adopted herein will

not have a substantial direct effect 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, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

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

removing Amendment 39–3790 (45 FR

37180, June 2, 1980), and by adding a

new airworthiness directive (AD),

Amendment 39–11967, to read as

follows:

2000–22–19 Eurocopter France:

Amendment 39–11967. Docket No. 2000-

SW–14–AD. Supersedes AD 80–12–04,

Amendment 39–3790, Docket No. 20384.

Applicability: Model SA330F, G, and J

helicopters with a tail rotor blade (blade),

part number (P/N) 330A12–0000-(all dash

numbers), 330A12–0000-(all dash numbers),

330A12–0006-(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

otherwise 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 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.

68072 Federal Register / Vol. 65, No. 220 / Tuesday, November 14, 2000 / Rules and Regulations

Compliance: Required as indicated, unless

accomplished previously.

To prevent fatigue cracking of a blade,

failure of a blade, and subsequent loss of

control of the helicopter, accomplish the

following:

(a) Within 30 hours time-in-service (TIS),

and thereafter at intervals not to exceed 15

hours TIS for blades equipped with deicing

systems or 30 hours TIS for blades without

deicing systems, conduct skin bonding and

eddy current inspections on each affected

blade for skin bonding and a crack. Inspect

in accordance with paragraph 1.C of

Aerospatiale Service Bulletin 05.71R4, dated

December 18, 1990. Replace any blade failing

the skin bonding inspection or eddy current

inspection before further flight.

(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, Regulations

Group, 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, Regulations Group.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Regulations Group.

(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 inspection shall be done in

accordance with paragraph 1.C of

Aerospatiale Service Bulletin 05.71R4, dated

December 18, 1990. 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, telephone (972)

641–3460, fax (972) 641–3527. 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

December 19, 2000.

Issued in Fort Worth, Texas, on October 30,

2000.

Mark R. Schilling,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 00–28722 Filed 11–13–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–315–AD; Amendment

39–11972; AD 2000–23–02]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model CL–600–2B16 (CL–604) Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Bombardier Model

CL–600–2B16 (CL–604) series airplanes.

This action requires, among other

actions, a general visual inspection to

detect gaps between the vane bracket(s)

and the adjacent skin; corrective

actions, if necessary; and replacement of

the six flap vane actuator beams with

new beams. This action is necessary to

detect and correct corrosion of the

inboard flap actuator beam assembly

and gaps between the vane brackets and

adjacent skin, which could compromise

the structural integrity of the flap

systems and reduce the controllability

of the airplane in the event that a flap

vane actuator or a flap vane bracket fails

during flight. This action is intended to

address the identified unsafe condition.

DATES: Effective November 29, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

29, 2000.

Comments for inclusion in the Rules

Docket must be received on or before

December 14, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

315–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays. Comments may be

submitted via fax to (425) 227–1232.

Comments may also be sent via the

Internet using the following address: 9-

anm-iarcomment@faa.gov. Comments

sent via the Internet must contain

‘‘Docket No. 2000–NM–315–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via fax or

the Internet as attached electronic files

must be formatted in Microsoft Word 97

for Windows or ASCII text.

The service information referenced in

this AD may be obtained from

Bombardier, Inc., Canadair, Aerospace

Group, P.O. Box 6087, Station A,

Montreal, Quebec H3C 3G9, Canada.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington; or at the FAA,

New York Aircraft Certification Office,

10 Fifth Street, Third Floor, Valley

Stream, New York; or at the Office of the

Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT:

Serge Napoleon, Aerospace Engineer,

Airframe and Propulsion Branch, ANE–

171, FAA, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York;

telephone (516) 256–7512; fax (516)

568–2716.

SUPPLEMENTARY INFORMATION: Transport

Canada Civil Aviation (TCCA), which is

the airworthiness authority for Canada,

recently notified the FAA that an unsafe

condition may exist on certain

Bombardier Model CL–600–2B16 (CL–

604) series airplanes. TCCA advises that

it has received a report that, during a

visual inspection of the flap systems,

corrosion was found in the inboard flap

actuator beam assembly, part number

(P/N) 600–14250–25, as well as gaps

between the vane brackets, P/N’s 600–

14306–1 and –2, and adjacent skin. Both

of these discrepancies have been

attributed to deficiencies in the

manufacturing process. These

conditions, if not corrected, could

compromise the structural integrity of

the flap systems and could reduce the

controllability of the airplane in the

event that a flap vane actuator or a flap

vane bracket fails during flight.

Explanation of Relevant Service

Information

Bombardier has issued Alert Service

Bulletin A604–27–006, dated April 18,

2000. The service bulletin describes

procedures for a general visual

inspection to detect gaps between the

vane bracket(s) and the adjacent skin;

corrective actions, if necessary;

replacement of the six flap vane actuator

beams with new beams; and returning

certain parts to the airplane

manufacturer. The corrective actions

involve performing a non-destructive

inspection to detect cracks of the vane

brackets; replacing any cracked vane

bracket with a new vane bracket;

eliminating the gap by filling the gap

with liquid shim or installing a solid

shim, as applicable; and repairing the