10960 Federal Register / Vol. 66, No. 35 / Wednesday, February 21, 2001 / Rules and Regulations

(4) For Model A300–600 series airplanes

on which Airbus Modification 5890 is

installed: Perform the HFEC inspection at the

applicable time specified in paragraph

(a)(4)(i) or (a)(4)(ii) of this AD.

(i) For airplanes that have accumulated

fewer than 10,000 total flight cycles as of the

effective date of this AD: Perform the onetime HFEC inspection at the later of the times

specified in paragraph (a)(4)(i)(A) and

(a)(4)(i)(B) of this AD.

(A) Prior to the accumulation of 6,500 total

flight cycles or 16,700 total flight hours,

whichever occurs earlier.

(B) Within 1,500 flight cycles after the

effective date of this AD.

(ii) For airplanes that have accumulated

10,000 or more total flight cycles as of the

effective date of this AD: Perform the HFEC

inspection within 500 flight cycles after the

effective date of this AD.

Disposition of Certain Crack Findings

(b) Where Airbus AOT A300–53A0350 (for

Model A300 series airplanes) or A300–600–

53A6123 (for Model A300–600 series

airplanes), both dated October 25, 1999,

specifies to contact Airbus in case of certain

crack findings, this AD requires that a repair

be accomplished in accordance with a

method approved by either the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate; or the

Direction Ge ́ne ́rale de l’Aviation Civile

(DGAC) (or its delegated agent). For a repair

method to be approved by the Manager,

International Branch, ANM–116, as required

by this paragraph, the Manager’s approval

letter must specifically reference this AD.

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. 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.

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

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) Except as required by paragraph (b) of

this AD, the actions shall be done in

accordance with Airbus All Operators Telex

A300–53A0350, dated October 25, 1999; or

Airbus All Operators Telex A300–600–

53A6123, dated October 25, 1999; 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 Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

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 French airworthiness directive 1999–515–

298(B), dated December 29, 1999.

Effective Date

(f) This amendment becomes effective on

March 28, 2001.

Issued in Renton, Washington, on February

9, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–3852 Filed 2–20–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–102–AD; Amendment

39–12120; AD 2001–04–02]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model DHC–8–100, –200, and –300

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Bombardier Model

DHC–8–100, –200, and –300 series

airplanes, that requires inspection to

determine the orientation of the Wiggins

fuel couplers of the fuel tank vent line

and scavenge line in the right wing at

station 249, and follow-on corrective

actions. This amendment is necessary to

prevent contact between the nuts of the

Wiggins fuel couplers and the stiffener

on the access panel of the upper surface

of the right wing, which could

compromise the lightning protection of

the fuel tank of the right wing in the

event of a lightning strike, and could

result in possible fuel tank explosion.

This action is intended to address the

identified unsafe condition.

DATES: Effective March 28, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 28,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Bombardier, Inc., Bombardier

Regional Aircraft Division, 123 Garratt

Boulevard, Downsview, Ontario M3K

1Y5, Canada. 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 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

11581; telephone (516) 256–7512; fax

(516) 568–2716.

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 Bombardier

Model DHC–8–100, –200, and –300

series airplanes was published in the

Federal Register on November 7, 2000

(65 FR 66657). That action proposed to

require inspection to determine the

orientation of the Wiggins fuel couplers

of the fuel tank vent line and scavenge

line in the right wing at station 249, and

follow-on corrective actions.

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 195 airplanes

of U.S. registry will be affected by this

AD.

It will take approximately 1 work

hour per airplane to accomplish the

actions (inspection) specified in Part A

of of Bombardier Alert Service Bulletin

A8–28–32, at an average labor rate of

$60 per work hour. Based on these

figures, the cost impact of these required

actions on U.S. operators is estimated to

be $11,700, or $60 per airplane.

It will take approximately 2 work

hours per airplane to accomplish the

actions (rework) specified in Part B of

the alert service bulletin, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of these

Federal Register / Vol. 66, No. 35 / Wednesday, February 21, 2001 / Rules and Regulations 10961

required actions on U.S. operators is

estimated to be $23,400, or $120 per

airplane.

The cost impact figures discussed

above are 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:

2001–04–02 Bombardier, Inc. (Formerly de

Havilland, Inc.): Amendment 39–12120.

Docket 2000–NM–102–AD.

Applicability: Model DHC–8–100, –200,

and –300 series airplanes having serial

numbers 003 through 540 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 (d) 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 contact between the nuts of the

Wiggins fuel couplers and the stiffener on the

access panel of the upper surface of the right

wing, which could compromise the lightning

protection of the fuel tank of the right wing

in the event of a lightning strike, and could

result in possible fuel tank explosion,

accomplish the following:

General Visual or X-ray Inspection

(a) Within 90 days after the effective date

of this AD: Perform a one-time general visual

or X-ray inspection to determine the

orientation of the Wiggins fuel couplers of

the fuel tank vent line and scavenge line in

the right wing at station 249, in accordance

with Part A of the Accomplishment

Instructions of Bombardier Alert Service

Bulletin A8–28–32, dated January 14, 2000.

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.’’

Action for Airplanes Having Correctly

Oriented Fuel Couplers

(b) For airplanes on which the orientation

of all Wiggins fuel couplers is found to be

correct, as specified in Bombardier Alert

Service Bulletin A8–28–32, dated January 14,

2000: Within 5,000 flight hours after the

effective date of this AD, rework the stiffener

on the access panel of the upper surface of

the right wing in accordance with Part B of

the Accomplishment Instructions of the alert

service bulletin.

Actions for Airplanes Having an Incorrectly

Oriented Fuel Coupler

(c) For airplanes on which the orientation

of any Wiggins fuel coupler is incorrect, as

specified in Bombardier Alert Service

Bulletin A8–28–32, dated January 14, 2000:

Prior to further flight, remove the incorrectly

oriented Wiggins fuel coupler, and perform a

one-time detailed visual inspection to detect

damage of the fuel coupler, in accordance

with Part A of the Accomplishment

Instructions of the alert service bulletin.

Note 3: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

(1) If no damage is found: Prior to further

flight, reinstall the Wiggins fuel coupler in

the correct orientation, as specified in the

alert service bulletin, and rework the stiffener

on the access panel of the upper surface of

the right wing, in accordance with Part B of

the Accomplishment Instructions of the alert

service bulletin. No further action is required

by this AD.

(2) If any damage is found, prior to further

flight, blend out the damage and perform a

detailed visual inspection of the fuel coupler

for cracks, in accordance with the alert

service bulletin.

(i) If no crack is found, and blending CAN

be accomplished to meet the limits specified

in the Accomplishment Instructions of the

alert service bulletin: Prior to further flight,

reinstall the Wiggins fuel coupler in the

correct orientation, as specified in the alert

service bulletin, and rework the stiffener on

the access panel of the upper surface of the

right wing, in accordance with Part B of the

Accomplishment Instructions of the alert

service bulletin. No further action is required

by this AD.

(ii) If any crack is found, or if blending

CANNOT be accomplished to meet the limits

specified in the Accomplishment

Instructions of the alert service bulletin: Prior

to further flight, replace the Wiggins fuel

coupler with a new or serviceable coupler in

the correct orientation, as specified in the

alert service bulletin, and rework the stiffener

on the access panel of the upper surface of

the right wing, in accordance with Part B of

the Accomplishment Instructions of the alert

service bulletin. No further action is required

by this AD.

Alternative Methods of Compliance

(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, New York

Aircraft Certification Office (ACO), FAA.

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 4: Information concerning the

existence of approved alternative methods of

10962 Federal Register / Vol. 66, No. 35 / Wednesday, February 21, 2001 / Rules and Regulations

compliance with this AD, if any, may be

obtained from the New York ACO.

Special Flight Permits

(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 airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(f) The actions shall be done in accordance

with Bombardier Alert Service Bulletin A8–

28–32, dated January 14, 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., Bombardier Regional

Aircraft Division, 123 Garratt Boulevard,

Downsview, Ontario M3K 1Y5, 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 5: The subject of this AD is addressed

in Canadian airworthiness directive CF–

2000–05, dated February 28, 2000.

Effective Date

(g) This amendment becomes effective on

March 28, 2001.

Issued in Renton, Washington, on February

9, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–3851 Filed 2–20–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–253–AD; Amendment

39–12119; AD 2001–04–01]

RIN 2120–AA64

Airworthiness Directives; BAe

Systems (Operations) Limited Model

BAe 146 and Model Avro 146–RJ

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all BAe Systems

(Operations) Limited Model BAe 146

and Model Avro 146–RJ series airplanes,

that requires repetitive non-destructive

testing inspections to detect cracking at

the fuselage end of the inner sidestays

of the main landing gear (MLG) by the

anti-rotation pin, and replacement of the

sidestay with a new sidestay, if

necessary. This amendment is necessary

to detect and correct fatigue cracking of

the inner sidestays of the MLG, which

could result in failure of the MLG. This

action is intended to address the

identified unsafe condition.

DATES: Effective March 28, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 28,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from British Aerospace Regional

Aircraft American Support, 13850

Mclearen Road, Herndon, Virginia

20171. 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 BAe 146 and Model

Avro 146–RJ series airplanes was

published in the Federal Register on

October 30, 2000 (65 FR 64632). That

action proposed to require repetitive

non-destructive testing inspections to

detect cracking at the fuselage end of the

inner sidestays of the main landing gear

by the anti-rotation pin, and

replacement of the sidestay with a new

sidestay, if necessary.

Manufacturer Name Change

Since the issuance of the proposed

AD, the manufacturer has notified the

FAA that it has changed its name from

British Aerospace to BAe Systems

(Operations) Limited. The final rule has

been changed to reflect the recent

company name change.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the change

described previously. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

Cost Impact

The FAA estimates that 60 Model BAe

146 and Model Avro 146–RJ series

airplanes, of U.S. registry will be

affected by this AD. It will take

approximately 1 work hour per airplane

to accomplish the required inspection,

at an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of the AD on U.S. operators is

estimated to be $3,600, or $60 per

airplane, per inspection cycle.

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.