70778 Federal Register / Vol. 65, No. 229 / Tuesday, November 28, 2000 / Rules and Regulations

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 39–10546 (63 FR

29546, July 6, 1998), and by adding a

new airworthiness directive (AD),

amendment 39–12000, to read as

follows:

2000–23–27 Bombardier, Inc. (Formerly de

Havilland, Inc.): Amendment 39–12000.

Docket 99–NM–359–AD. Supersedes AD

98–11–21, Amendment 39–10546.

Applicability: Model DHC–8–102, –103,

and –301 series airplanes; certificated in any

category; serial numbers 002 though 010

inclusive, 012 through 201 inclusive, 203

through 209 inclusive, 211 through 215

inclusive, 217 through 220 inclusive, 222,

and 223; except those airplanes on which de

Havilland Modification 8/1114 or 8/1110 has

been accomplished.

Note 1: This AD applies to each airplane

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 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)(1) 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 the possibility of a fire on an

airplane due to chafing of the electrical

wiring of the cabin ceiling lighting system,

accomplish the following:

Restatement of Requirements of AD 98–11–

21

Inspection for Wire Wear and Breakage

(a) Within 1,000 hours time-in-service or 6

months after July 6, 1998 (the effective date

of AD 98–11–21, amendment 39–10546),

whichever occurs first: Accomplish the

requirements of paragraphs (a)(1) and (a)(2)

of this AD in accordance with de Havilland

Service Bulletin S.B. 8–33–35, dated

September 1, 1995, or Bombardier Service

Bulletin S.B. 8–33–35, Revision ‘B’, dated

September 25, 1998.

(1) Perform a one-time inspection for wear

and breakage of wire segments of the

individual lighting units of the ceiling and

sidewall lights. Prior to further flight, replace

any damaged wiring.

(2) Install teflon spiral wrap on the wiring

of the ceiling and sidewall lights

(Modification 8/2158).

Note 2: Accomplishment of the actions

required by paragraph (a) of this AD in

accordance with Bombardier Service Bulletin

S.B. 8–33–35, Revision ‘A’, dated July 28,

1998, is acceptable for compliance with that

paragraph.

New Requirements of This AD

Inspection for Installed Teflon Spiral Wrap

(b) Within 1,000 hours time-in-service or 6

months after the effective date of this AD,

whichever occurs first: Perform a one-time

inspection to determine if teflon spiral wrap

is installed on the wiring of the lavatory

lighting system, in accordance with

Bombardier Service Bulletin S.B. 8–33–35,

Revision ‘B’, dated September 25, 1998.

(1) If teflon spiral wrap is not installed,

prior to further flight, install teflon spiral

wrap on the wiring of the lavatory lighting

system in accordance with the service

bulletin.

(2) If teflon spiral wrap is installed, no

further action is required by this paragraph.

Alternative Methods of Compliance

(c)(1) 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.

(2) Alternative methods of compliance,

approved previously in accordance with AD

98–11–21, amendment 39–10546, are

approved as alternative methods of

compliance with this AD.

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

(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) The actions shall be done in accordance

with de Havilland Service Bulletin S.B. 8–

33–35, dated September 1, 1995; or

Bombardier Service Bulletin S.B. 8–33–35,

Revision ‘B’, dated September 25, 1998.

(1) The incorporation by reference of

Bombardier Service Bulletin S.B. 8–33–35,

Revision ‘B’, dated September 25, 1998, is

approved by the Director of the Federal

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

and 1 CFR part 51.

(2) The incorporation by reference of de

Havilland Service Bulletin S.B. 8–33–35,

dated September 1, 1995, was approved

previously by the Director of the Federal

Register as of July 6, 1998 (63 FR 29546, June

1, 1998).

(3) 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

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–95–

18R1, dated January 8, 1999.

Effective Date

(f) This amendment becomes effective on

January 2, 2001.

Issued in Renton, Washington, on

November 14, 2000.

Donald L. Riggin,

Acting Manager,, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–29606 Filed 11–27–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–79–AD; Amendment

39–11996; AD 2000–23–23]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A330 and A340 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A330 and A340 series airplanes, that

requires modification of the rib 1/wing

center spar attachment. This

amendment is necessary to prevent

fatigue cracking at the rib 1/center spar

angle and bottom corner fitting, which

could result in reduced structural

capability of the wing. This action is

Federal Register / Vol. 65, No. 229 / Tuesday, November 28, 2000 / Rules and Regulations 70779

intended to address the identified

unsafe condition.

DATES: Effective January 2, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 2,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

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,

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 Airbus

Model A330 and A340 series airplanes

was published in the Federal Register

on September 27, 2000 (65 FR 58013).

That action proposed to require

modification of the rib 1/wing center

spar attachment.

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 following information describes

the anticipated cost impact on U.S.

operators for the required modification.

Model

Number of

airplanes on

U.S.

Register

Number of

work hours

Average

labor rate

per work

hour

Cost

of required

parts

Per-airplane

cost

A330 ......................................................................................................... 5 42 $60 $9,950 $12,470

A340 ......................................................................................................... 0 42 60 10,099 12,619

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished the

modification of this AD, and that no

operator would accomplish these

actions in the future if this AD were not

adopted. However, the FAA has been

advised that the 5 airplanes currently on

the U.S. Register have been modified in

accordance with the requirements of

this AD. Therefore, until additional

affected airplanes (unmodified) are

added to the U.S. Register, this AD

imposes no additional cost on U.S.

operators.

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:

2000–23–23 Airbus Industrie: Amendment

39–11996. Docket 2000–NM–79–AD.

Applicability: Model A330 and A340 series

airplanes, certificated in any category;

excluding those on which Airbus

Modification 43021 has been installed.

Note 1: This AD applies to each airplane

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 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 prevent fatigue cracking at the rib 1/

center spar angle and bottom corner fitting,

which could result in reduced structural

capability of the wing, accomplish the

following:

Modification

(a) Modify the rib 1/wing center spar

attachment, as specified by paragraph (a)(1)

or (a)(2), as applicable, of this AD.

(1) For Model A330 series airplanes:

Modify before the accumulation of 9,600 total

flight cycles or 29,900 total flight hours,

whichever occurs first. Do the modification

in accordance with Airbus Service Bulletin

A330–57–3017, including Appendix 01,

Revision 02, dated October 11, 1999.

(2) For Model A340 series airplanes:

Modify before the accumulation of 9,300 total

flight cycles or 37,200 total flight hours,

whichever occurs first. Do the modification

70780 Federal Register / Vol. 65, No. 229 / Tuesday, November 28, 2000 / Rules and Regulations

in accordance with Airbus Service Bulletin

A340–57–4022, including Appendices 01

and 02, dated October 8, 1999.

Note 2: Modification prior to the effective

date of this AD in accordance with Airbus

Service Bulletin A330–57–3017, dated

October 14, 1998, or Revision 01, dated April

9, 1999, is acceptable for compliance with

the requirements of paragraph (a) of this AD.

Alternative Methods of Compliance

(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, Transport

Airplane Directorate, FAA. 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.

Special Flight Permits

(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.

Incorporation by Reference

(d) The actions shall be done in accordance

with Airbus Service Bulletin A330–57–3017,

including Appendix 01, Revision 02, dated

October 11, 1999; and Airbus Service

Bulletin A340–57–4022, including

Appendices 01 and 02, dated October 8,

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 4: The subject of this AD is addressed

in French airworthiness directives 2000–

073–111(B) and 2000–074–136(B), both dated

February 23, 2000.

Effective Date

(e) This amendment becomes effective on

January 2, 2001.

Issued in Renton, Washington, on

November 14, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–29605 Filed 11–27–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–221–AD; Amendment

39–11997; AD 2000–23–24]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB 2000 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Saab Model SAAB

2000 series airplanes, that requires an

inspection to ensure correct installation

of certain self-seal couplings in each

nacelle, and corrective action, if

necessary. This amendment also

requires installation of a new clamp to

the self-seal couplings. This action is

necessary to prevent separation of the

self-seal couplings, which could result

in loss of engine oil pressure and a

flight-crew-commanded engine

shutdown. This action is intended to

address the identified unsafe condition.

DATES: Effective January 2, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 2,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Saab Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈ping,

Sweden. 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 Saab Model

SAAB 2000 series airplanes was

published in the Federal Register on

September 29, 2000 (65 FR 58494). That

action proposed to require an inspection

to ensure correct installation of certain

self-seal couplings in each nacelle, and

corrective action, if necessary. That

action also proposed to require

installation of a new clamp to the selfseal couplings.

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 3 Model

SAAB 2000 series 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 be provided by the vendor at no

charge to operators. Based on these

figures, the cost impact of the required

AD on U.S. operators is estimated to be

$180, 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