4658 Federal Register / Vol. 66, No. 12 / Thursday, January 18, 2001 / Rules and Regulations

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 (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 hydraulic leakage from the yaw

damper actuator, which could lead to

complete loss of the green hydraulic circuit

and consequent reduced controllability of the

airplane, accomplish the following:

Restatement of Requirements of AD 99–26–

12

Repetitive Replacement

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

flight hours, or within 500 flight hours after

January 24, 2000 (the effective date of AD 99–

26–12, amendment 39–11471), whichever

occurs later, replace the yaw damper actuator

installed on active position with a new or

overhauled yaw damper actuator in

accordance with Airbus Service Bulletin

A330–27–3055, Revision 01, dated July 1,

1998, or Revision 02, dated March 24, 2000

(for Model A330 series airplanes); or A340–

27–4063, Revision 01, dated July 1, 1998 (for

Model A340 series airplanes); as applicable.

Thereafter, repeat the replacement at

intervals not to exceed 6,500 flight hours. For

Model A330 series airplanes, after the

effective date of this AD, only Revision 02 of

Service Bulletin A330–27–3055 may be used.

Note 2: Replacement of yaw dampers

accomplished prior to January 24, 2000, in

accordance with Airbus Service Bulletin

A330–27–3055, dated August 26, 1997 (for

Model A330 series airplanes), or Airbus

Service Bulletin A340–27–4063, dated

August 26, 1997 (for Model A340 series

airplanes); as applicable; is an acceptable

method of compliance for the initial

replacement required by paragraph (a) of this

AD.

New Requirements of This AD

Terminating Action

(b) For Model A330 series airplanes:

Within 18 months after the effective date of

this AD, install 3 upgraded flight control

primary computers (FCPC), in accordance

with Airbus Service Bulletin A330–27–3071,

dated November 19, 1999, or A330–27–3068,

dated July 29, 1999; as applicable.

Accomplishment of the installation

terminates the requirements of this AD for

Model A330 series airplanes.

Spares

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

person may install an FCPC, part number

LA2K01500A40000 or LA2K1A100D20000,

on any Model A330 series airplane.

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,

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 any approved alternative

methods of compliance with this AD may be

obtained from the International Branch,

ANM–116.

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 the following Airbus service bulletins,

as applicable:

Service bulletin number Revision level Date

A330–27–3055 .................................................. Revision 01 ....................................................... July 1, 1998

A330–27–3055 .................................................. Revision 02 ....................................................... March 24, 2000

A340–27–4063 .................................................. Revision 01 ....................................................... July 1, 1998

A330–27–3071 .................................................. Original ............................................................. November 19, 1999

A330–27–3068 .................................................. Original ............................................................. July 29, 1999

(1) The incorporation by reference of

Airbus Service Bulletin A330–27–3055,

Revision 02, dated March 24, 2000; Airbus

Service Bulletin A330–27–3071, dated

November 19, 1999; and Airbus Service

Bulletin A330–27–3068, dated July 29, 1999;

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

Airbus Service Bulletin A330–27–3055,

Revision 01, dated July 1, 1998; and Airbus

Service Bulletin A340–27–4063, Revision 01,

dated July 1, 1998; was approved previously

by the Director of the Federal Register as of

January 24, 2000 (64 FR 71004, December 20,

1999).

(3) Copies of any of these service bulletins

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 1998–

100–067(B) R2, dated May 19, 1999; 98–104–

083(B), dated February 25, 1998; and 2000–

076–115(B) R1, dated March 22, 2000.

Effective Date

(g) This amendment becomes effective on

February 2, 2001.

Issued in Renton, Washington, on January

9, 2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–1233 Filed 1–17–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–72–AD; Amendment

39–12077; AD 2001–01–07]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300 B2, A300 B4, A300 B4–600, A300

B4–600R, A300 F4–600R, and A310

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A300 B2, A300 B4, A300 B4–600, A300

B4–600R, A300 F4–600R, and A310

series airplanes, that requires

modification of the escape slides. The

actions specified by this AD are

Federal Register / Vol. 66, No. 12 / Thursday, January 18, 2001 / Rules and Regulations 4659

intended to prevent deflation of the

escape slide after deployment, which

could result in a delay during an

emergency evacuation. This action is

intended to address the identified

unsafe condition.

DATES: Effective February 22, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February

22, 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 A300 B2 and A300 B4 (A300);

Model A300 B4–600, A300 B4–600R,

and A300 F4–600R (A300–600); and

Model A310 series airplanes was

published in the Federal Register on

October 31, 2000 (65 FR 64901). That

action proposed to require modification

of the escape slides.

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 126 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 1

work hour per slide to accomplish the

required actions, and that the average

labor rate is $60 per work hour.

Required parts will cost approximately

$124 to $185 per slide. Each Model

A300 and A300–600 series airplane has

6 escape doors, and each Model A310

series airplane has 4 escape doors.

Based on these figures, the cost impact

of the proposed AD on U.S. operators is

estimated to be between $736 and

$1,470 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:

2001–01–07 Airbus Industrie: Amendment

39–12077. Docket 2000–NM–72–AD.

Applicability: The following airplanes,

certificated in any category:

Model Equipped with any BFGoodrich slide having part

number Excluding airplanes modified in accordance with

A300 B2 series ................................

A300 B4 series

7A1296–001 ..............................................................

7A1296–002 ..............................................................

7A1296–003 ..............................................................

7A1296–004 ..............................................................

7A1298–001 ..............................................................

7A1298–002 ..............................................................

7A1298–003 ..............................................................

7A1298–004 ..............................................................

Airbus Service Bulletin A300–25–0466, Revision 01,

dated December 1, 1999; or BFGoodrich Service

Bulletin 7A1296/7A1298–25–298, dated January

15, 1999.

4660 Federal Register / Vol. 66, No. 12 / Thursday, January 18, 2001 / Rules and Regulations

Model Equipped with any BFGoodrich slide having part

number Excluding airplanes modified in accordance with

A300 B4–600 series ........................ 7A1296–001.

A300 B4–600R series ..................... 7A1296–002.

A300 F4–600R series ..................... 7A1296–003 ..............................................................

7A1296–004 ..............................................................

7A1298–001 ..............................................................

7A1298–002 ..............................................................

7A1298–003 ..............................................................

7A1298–004 ..............................................................

Airbus Service Bulletin A300–25–6146, Revision 01,

dated December 1, 1999; or BFGoodrich Service

Bulletin7A1296/7A1298–25–298, dated January

15, 1999.

A310 series ..................................... 7A1298–001 ..............................................................

7A1298–002 ..............................................................

7A1298–003 ..............................................................

7A1298–004 ..............................................................

Airbus Service Bulletin A310–25–2133, dated June

21, 1999; or BFGoodrich Service Bulletin 7A1296/

7A1298–25–298, dated January 15, 1999.

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) 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 deflation of the escape slide

after deployment, which could result in a

delay during an emergency evacuation,

accomplish the following:

Modification

(a) Within 34 months after the effective

date of this AD, modify the escape slides in

accordance with the applicable Airbus

service bulletin listed in Table 1 of this AD,

as follows:

TABLE 1.—SERVICE BULLETINS

Model Service

bulletin

Revision

level Date

A300 ....................................................................................................................................... A300–25–

0466

01 ................ December 1, 1999.

A300–600 ............................................................................................................................... A300–25–

6146

01 ................ December 1, 1999.

A310 ....................................................................................................................................... A310–25–

2133

Original ........ June 21, 1999.

Note 2: The Airbus service bulletins refer

to BFGoodrich Service Bulletin 7A1296/

7A1298–25–298, dated January 15, 1999, as

an additional source of service information

for modifying the escape slides.

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

person shall install, on any airplane, a

BFGoodrich escape slide having a part

number listed in Table 2 of this AD, unless

that slide has been modified in accordance

with this AD:

TABLE 2.—SLIDE PART NUMBERS

7A1296–001

7A1296–002

7A1296–003

7A1296–004

7A1298–001

7A1298–002

7A12 98–003

7A1298–004

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, 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,

ANM–116.

Special Flight Permits

(d) Special flight permits may be issued in

accordance with §§ 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 modification shall be done in

accordance with Airbus Service Bulletin

A300–25–0466, Revision 01, dated December

1, 1999; Airbus Service Bulletin A300–25–

6146, Revision 01, dated December 1, 1999;

or Airbus Service Bulletin A310–25–2133,

dated June 21, 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 directive 2000–059–

302(B), dated February 9, 2000.

Effective Date

(f) This amendment becomes effective on

February 22, 2001.

Issued in Renton, Washington, on January

9, 2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–1232 Filed 1–17–01; 8:45 am]

BILLING CODE 4910–13–P