68074 Federal Register / Vol. 65, No. 220 / Tuesday, November 14, 2000 / Rules and Regulations

Applicability: Model CL–600–2B16 (CL–

604) series airplanes, serial numbers 5301

through 5374 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 (e) 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 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, accomplish the

following:

General Visual Inspection

(a) Do a general visual inspection to detect

gaps between the vane bracket(s), part

number (P/N) 600–14306–1 and –2, and the

adjacent skin, per paragraph ‘‘2.

Accomplishment Instructions,’’ of

Bombardier Alert Service Bulletin A604–27–

006, dated April 18, 2000; at the time

specified in paragraph (a)(1), (a)(2), or (a)(3)

of this AD, as applicable.

(1) For airplanes having serial numbers

5301 through 5334 inclusive: Within 30 days

after the effective date of this AD.

(2) For airplanes having serial numbers

5335 through 5354 inclusive: Within 90 days

after the effective date of this AD.

(3) For airplanes having serial numbers

5355 through 5374 inclusive: Within 180

days after the effective date of this AD.

Note 2: For the purposes of this AD, a

general visual inspection is defined as ‘‘A

visual examination of an interior or exterior

area, installation, or assembly to detect

obvious damage, failure, or irregularity. This

level of inspection is made under normally

available lighting conditions such as

daylight, hangar lighting, flashlight, or droplight, and may require removal or opening of

access panels or doors. Stands, ladders, or

platforms may be required to gain proximity

to the area being checked.’’

Corrective Actions if Any Gap Is Found

(b) If any gap is found during the general

visual inspection required by paragraph (a) of

this AD, before further flight, perform a nondestructive inspection to detect cracks of the

vane bracket, per paragraph ‘‘2.

Accomplishment Instructions,’’ of

Bombardier Alert Service Bulletin A604–27–

006, dated April 18, 2000.

(1) If any crack is detected, before further

flight, replace the cracked vane bracket with

a new vane bracket per the service bulletin.

(2) If no crack is detected and if the gap

is up to 0.100 inch (2.54 mm), eliminate the

gap by filling the gap with liquid shim or

installing a solid shim, as applicable, per the

service bulletin.

(3) If no crack is detected and if the gap

is more than 0.100 inch (2.54 mm), before

further flight, repair in accordance with a

method approved by the Manager, New York

Aircraft Certification Office (ACO), FAA; or

the Transport Canada Civil Aviation, (or its

delegated agent). For a repair method to be

approved by the Manager, New York ACO, as

required by this paragraph, the Manager’s

approval letter must specifically reference

this AD.

Replacement of Six Flap Vane Actuator

Beams

(c) Replace the six flap vane actuator

beams with new beams, per paragraph ‘‘2.

Accomplishment Instructions,’’ of

Bombardier Alert Service Bulletin A604–27–

006, dated April 18, 2000; at the time

specified in paragraph (a)(1), (a)(2), or (a)(3)

of this AD, as applicable.

(1) For airplanes having serial numbers

5301 through 5334 inclusive: Within 30 days

after the effective date of this AD.

(2) For airplanes having serial numbers

5335 through 5354 inclusive: Within 90 days

after the effective date of this AD.

(3) For airplanes having serial numbers

5355 through 5374 inclusive: Within 180

days after the effective date of this AD.

Return of Parts

(d) Within 30 days after doing the

replacement required by paragraph (c) of this

AD, forward any cracked vane bracket and

any two of the six removed flap vane actuator

assemblies to Bombardier, per paragraph ‘‘2.

Accomplishment Instructions,’’ of

Bombardier Alert Service Bulletin A604–27–

006, dated April 18, 2000. Data, such as the

station location of the flap actuator beam

assembly, the number of flight hours and

landings of the airplane at removal, must be

submitted along with the flap vane actuator

beam assemblies. Information collection

requirements contained in this regulation

have been approved by the Office of

Management and Budget (OMB) under the

provisions of the Paperwork Reduction Act of

1980 (44 U.S.C. 3501 et seq.) and have been

assigned OMB Control Number 2120–0056.

Alternative Methods of Compliance

(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, New York

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

New York ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

Special Flight Permits

(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 airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(g) Except as provided in paragraph (b)(3)

of this AD, the actions shall be done in

accordance with Bombardier Alert Service

Bulletin A604–27–006, dated April 18, 2000.

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 Bombardier, Inc., Canadair, Aerospace

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

Quebec H3C 3G9, Canada. Copies may be

inspected 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.

Note 4: The subject of this AD is addressed

in Canadian airworthiness directive CF–

2000–18, dated July 11, 2000.

Effective Date

(h) This amendment becomes effective on

November 29, 2000.

Issued in Renton, Washington, on

November 3, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–28830 Filed 11–13–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–113–AD; Amendment

39–11975; AD 2000–23–05]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace Model BAC 1–11 401/AK

and 410/AQ Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all British Aerospace

Model BAC 1–11 401/AK and 410/AQ

airplanes, that requires replacement of

certain landing gear brake accumulators

with improved accumulators. The

actions specified by this AD are

intended to prevent loss of hydraulic

pressure and possible structural damage

Federal Register / Vol. 65, No. 220 / Tuesday, November 14, 2000 / Rules and Regulations 68075

to the airplane due to failure of the

accumulator. This action is intended to

address the identified unsafe condition.

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 British Aerospace, Service

Support, Airbus Limited, P.O. Box 77,

Bristol BS99 7AR, England. 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 all British

Aerospace Model BAC 1–11 401/AK

and 410/AQ airplanes was published in

the Federal Register on September 19,

2000 (65 FR 56506). That action

proposed to require replacement of

certain landing gear brake accumulators

with improved accumulators.

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 13 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 1

work hour per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Required parts will cost approximately

$9,940 per airplane. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be

$130,000, or $10,000 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. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

Regulatory Impact

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

adding the following new airworthiness

directive:

2000–23–05 British Aerospace Airbus

Limited: (Formerly British Aerospace

Commercial Aircraft Limited, British

Aerospace Aircraft Group): Amendment

39–11975. Docket 2000–NM–113–AD.

Applicability: All Model BAC 1–11 401/AK

and 410/AQ airplanes, 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 loss of hydraulic pressure and

possible structural damage to the airplane

due to failure of the landing gear brake

accumulator, accomplish the following:

Replacement

(a) Within 10 months after the effective

date of this AD, replace any Parker landing

gear brake accumulator having part number

(P/N) 1356–653562 with an accumulator

having P/N 1356–653562M2, in accordance

with British Aerospace Service Bulletin 32-

PM6054, dated February 2000.

Note 2: The British Aerospace service

bulletin references Parker Service Bulletin

1356–653562–32–100, dated September 23,

1999, as an additional source of service

information for accomplishment of the

replacement.

Spares

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

Parker landing gear brake accumulator

having P/N 1356–653562 shall be installed

on any airplane.

Alternative Methods of Compliance

(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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(d) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

68076 Federal Register / Vol. 65, No. 220 / Tuesday, November 14, 2000 / Rules and Regulations

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(e) The replacement shall be done in

accordance with British Aerospace Service

Bulletin 32–PM6054, dated February 2000.

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 British Aerospace, Service Support,

Airbus Limited, P.O. Box 77, Bristol BS99

7AR, England. 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.

Effective Date

(f) This amendment becomes effective on

December 19, 2000.

Issued in Renton, Washington, on

November 3, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–28829 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–26–AD; Amendment

39–11974; AD 2000–23–04]

RIN 2120–AA64

Airworthiness Directives; Aerospatiale

Model ATR42–500 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Aerospatiale Model

ATR42–500 series airplanes, that

requires revising the Airworthiness

Limitations Section of the Instructions

for Continued Airworthiness to

incorporate life limits for certain items

and inspections to detect fatigue

cracking in certain structures. This

amendment is prompted by issuance of

a new revision of the ‘‘Time Limits’’

section of the ATR42–400/500

Maintenance Planning Document,

which specifies new inspections and

compliance times for inspection and

replacement actions. The actions

specified by this AD are intended to

ensure that fatigue cracking of certain

structural elements is detected and

corrected; such fatigue cracking could

adversely affect the structural integrity

of these airplanes.

DATES: Effective December 19, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Aerospatiale, 316 Route de

Bayonne, 31060 Toulouse, Cedex 03,

France. 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 all Aerospatiale

Model ATR42–500 series airplanes was

published in the Federal Register on

August 29, 2000 (65 FR 52369). That

action proposed to require revising the

Airworthiness Limitations Section of

the Instructions for Continued

Airworthiness to incorporate life limits

for certain items and inspections to

detect fatigue cracking in certain

structures.

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 8 airplanes of

U.S. registry will be affected by this AD,

that it will take approximately 1 work

hour per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour. Based

on these figures, the cost impact of the

required AD on U.S. operators is

estimated to be $480, or $60 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. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

Regulatory Impact

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, 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:

2000–23–04 Aerospatiale: Amendment 39–

11974. Docket 2000–NM–26–AD.

Applicability: All Model ATR42–500 series

airplanes, certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability