Federal Register / Vol. 65, No. 229 / Tuesday, November 28, 2000 / Rules and Regulations 70777

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 95–105–

026 (B), dated May 24, 1995.

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. 00–29607 Filed 11–27–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–359–AD; Amendment

39–12000; AD 2000–23–27]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model DHC–8–102, –103, and –301

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Bombardier Model

DHC–8–102, –103, and –301 series

airplanes, that currently requires a onetime inspection for wear and breakage of

wire segments of the individual lighting

units of the ceiling and sidewall lights,

and replacement of any damaged

wiring. The existing AD also requires

installation of teflon spiral wrap on the

wiring of the ceiling and sidewall lights.

This amendment adds a requirement for

a one-time inspection to determine if

teflon spiral wrap is installed on the

wiring of the lavatory lighting system,

and installation, if necessary. This

amendment is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by this AD are intended to

prevent the possibility of a fire on an

airplane due to such chafing and

consequent short circuiting,

overheating, and smoking of the wires

on the aircraft structure.

DATES: Effective January 2, 2001.

The incorporation by reference of

Bombardier Service Bulletin S.B. 8–33–

35, Revision B, dated September 25,

1998, as listed in the regulations, is

approved by the Director of the Federal

Register as of January 2, 2001.

The incorporation by reference of de

Havilland Service Bulletin S.B. 8–33–

35, dated September 1, 1995, as listed in

the regulations, was approved

previously by the Director of the Federal

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

June 1, 1998).

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 Office of the

Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT:

Luciano Castracane, Aerospace

Engineer, New York Aircraft

Certification Office, Systems & Flight

Test Branch (ANE–172), FAA, 10 Fifth

Street, Third Floor, Valley Stream, New

York 11581; telephone (516) 256–7535;

fax (516) 568–2716.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 98–11–21,

amendment 39–10546 (63 FR 29546,

July 6, 1998), which is applicable to

certain Bombardier Model DHC–8–102,

–103, and –301 series airplanes, was

published in the Federal Register on

August 23, 2000 (65 FR 51256). The

action proposed to continue to require

a one-time inspection for wear and

breakage of wire segments of the

individual lighting units of the ceiling

and sidewall lights, and replacement of

any damaged wiring. The action also

proposed to continue to require

installation of teflon spiral wrap on the

wiring of the ceiling and sidewall lights.

Additionally, the action proposed to

add a requirement for a one-time

inspection to determine if teflon spiral

wrap is installed on the wiring of the

lavatory lighting system, and

installation, if necessary.

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

There are approximately 73 airplanes

of U.S. registry that will be affected by

this AD.

The actions that are currently

required by AD 98–11–21 take

approximately 30 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts cost approximately $250

per airplane. Based on these figures, the

cost impact of the currently required

actions on U.S. operators is estimated to

be $149,650, or $2,050 per airplane.

The new inspection that is required

by this AD will take approximately 2

work hours per airplane to accomplish,

at an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of the new requirements of this

AD on U.S. operators is estimated to be

$8,760, 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

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