4656 Federal Register / Vol. 66, No. 12 / Thursday, January 18, 2001 / Rules and Regulations

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–292–AD; Amendment

39–12079; AD 2001–01–09]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A330–301, –321, and –322 Series

Airplanes; and Model A340–211, –212,

–213, –311, –312, and –313 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to all Airbus Model A330–

301, –321, and –322 series airplanes;

and Model A340–211, –212, –213, –311,

–312, and –313 series airplanes. The

existing AD requires repetitive

replacements of the yaw damper

actuator installed on active position

with a new or overhauled actuator. This

action adds a requirement, for certain

airplanes, to install upgraded flight

control primary computers, which

terminates the requirement for the

repetitive actuator replacements for

those airplanes. This action is necessary

to prevent hydraulic leakage from the

yaw damper actuator installed on active

position, due to premature wear of the

dynamic seals between the actuator

piston and the piston bearing. Hydraulic

leakage could lead to the complete loss

of the green hydraulic circuit, which

could result in reduced controllability

of the airplane. This action is intended

to address the identified unsafe

condition.

DATES: Effective February 2, 2001.

The incorporation by reference of

certain publications, as listed in the

regulations, is approved by the Director

of the Federal Register as of February 2,

2001.

The incorporation by reference of

certain other publications, as listed in

the regulations, was approved

previously by the Director of the Federal

Register as of January 24, 2000 (64 FR

71004, December 20, 1999).

Comments for inclusion in the Rules

Docket must be received on or before

February 20, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

292–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays. Comments may be

submitted via fax to (425) 227–1232.

Comments may also be sent via the

Internet using the following address: 9-

anm-iarcomment@faa.gov. Comments

sent via fax or the Internet must contain

‘‘Docket No. 2000-NM–292-AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

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 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.

FOR FURTHER INFORMATION CONTACT: Dan

Rodina, Aerospace Engineer,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue SW., Renton, Washington

98055–4056; telephone (425) 227–2125;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: On

December 10, 1999, the FAA issued AD

99–26–12, amendment 39–11471 (64 FR

71004, December 20, 1999). That AD is

applicable to all Airbus Model A330–

301, –321, and –322 series airplanes;

and Model A340–211, –212, –213, –311,

–312, and –313 series airplanes. That

AD requires repetitive replacements of

the yaw damper actuator installed on

active position with a new or

overhauled actuator. That AD was

prompted by issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The requirements of that AD are

intended to prevent hydraulic leakage

from the yaw damper actuator installed

on active position due to premature

wear of the dynamic seals between the

actuator piston and the piston bearing.

Hydraulic leakage could lead to

complete loss of the green hydraulic

circuit, which could result in reduced

controllability of the airplane.

Actions Since Issuance of Previous Rule

As described in the proposed NPRM

to AD 99–26–12, hydraulic fluid leakage

from the yaw damper actuator has been

attributed to premature wear of certain

dynamic seals. Investigation revealed a

link between the leakage and small

inputs sent by the flight control primary

computers (FCPC).

In the preamble to AD 99–26–12, the

FAA specified that the actions required

by that AD were considered ‘‘interim

action’’ and that the manufacturer was

developing a modification to positively

address the unsafe condition. The FAA

indicated that it may consider further

rulemaking action once the modification

was developed, approved, and available.

The manufacturer now has developed

such a modification for Model A330

series airplanes, and the FAA has

determined that further rulemaking

action is indeed necessary; this

proposed AD follows from that

determination.

A similar modification has been

developed for Model A340 series

airplanes. There currently are no such

airplanes on the U.S. Register. The A340

modification will be included in the

FAA Required Modification List for

these airplanes. Actions identified on

this list must be accomplished before

the airplane may be imported into the

United States.

Explanation of Relevant Service

Information

Airbus has issued the following

service bulletins for Model A330 series

airplanes:

Service bulletin Revision

level Date

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

A330–27–3071 Original .. November 19,

1999.

A330–27–3055 02 .......... March 24,

2000.

Service Bulletins A330–27–3068 and

A330–27–3071 describe procedures for

obtaining new software standards for

the FCPCs by replacing or

reprogramming the on-board replaceable

modules, or by replacing the FCPCs

with new, improved FCPCs. The actions

specified by these service bulletins are

intended to prevent premature wear and

subsequent leakage of the active and

damping yaw actuators.

Revision 02 of Service Bulletin A330–

27–3055 was issued to, among other

things, add a detailed visual inspection

of the FCPC part numbers and revise

certain repair procedures for replacing

the yaw damper actuator. The actions

otherwise are the same as those

described in Revision 01 of the service

bulletin, which was referred to in AD

99–26–12 as the appropriate source of

service information for replacing the

yaw damper actuator.

The DGAC classified the service

bulletins as mandatory and issued

French airworthiness directive 2000–

076–115(B) R1, dated March 22, 2000, to

ensure the continued airworthiness of

Federal Register / Vol. 66, No. 12 / Thursday, January 18, 2001 / Rules and Regulations 4657

affected Model A330 series airplanes in

France.

FAA’s Conclusions

These airplane models are

manufactured in France and are type

certificated for operation in the United

States under the provisions of § 21.29 of

the Federal Aviation Regulations (14

CFR 21.19) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the DGAC has kept the FAA informed

of the situation described above. The

FAA has examined the findings of the

DGAC, reviewed all available

information, and determined that AD

action is necessary for products of this

type design that are certificated for

operation in the United States.

Explanation of Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, this AD is being issued to

prevent hydraulic leakage from the yaw

damper actuator installed on active

position, which could lead to complete

loss of the green hydraulic circuit and

consequent reduced controllability of

the airplane. This AD supersedes AD

99–26–12 to continue to require

repetitive replacements of the yaw

damper actuator installed on active

position with a new or overhauled yaw

damper actuator. This AD adds a

requirement, for affected Model A330

series airplanes, to install upgraded

FCPCs, which terminates the

requirement for repetitive actuator

replacements for those airplanes. The

actions are required to be accomplished

in accordance with the service bulletins

described previously.

Cost Impact

None of the airplanes affected by this

action are on the U.S. Register. All

airplanes included in the applicability

of this rule currently are operated by

non-U.S. operators under foreign

registry; therefore, they are not directly

affected by this AD action. However, the

FAA considers that this rule is

necessary to ensure that the unsafe

condition is addressed in the event that

any of these subject airplanes are

imported and placed on the U.S.

Register in the future.

Should an affected airplane be

imported and placed on the U.S.

Register in the future, it would require

approximately 2 work hours to

accomplish the required actions, at an

average labor rate of $60 per work hour.

Required parts would cost

approximately $390 per airplane. Based

on these figures, the cost impact of this

AD is estimated to be $510 per airplane.

Determination of Rule’s Effective Date

Since this AD action does not affect

any airplane that is currently on the

U.S. register, it has no adverse economic

impact and imposes no additional

burden on any person. Therefore, prior

notice and public procedures hereon are

unnecessary and the amendment may be

made effective in less than 30 days after

publication in the Federal Register.

Comments Invited

Although this action is in the form of

a final rule and was not preceded by

notice and opportunity for public

comment, comments are invited on this

rule. Interested persons are invited to

comment on this rule by submitting

such written data, views, or arguments

as they may desire. Communications

shall identify the Rules Docket number

and be submitted in triplicate to the

address specified under the caption

ADDRESSES. All communications

received on or before the closing date

for comments will be considered, and

this rule may be amended in light of the

comments received. Factual information

that supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the AD is being requested.

• Include justification (e.g., reasons or

data) for each request.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 2000–NM–292–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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

removing amendment 39–11471 (64 FR

71004, December 20, 1999), and by

adding a new airworthiness directive

(AD), amendment 39–12079, to read as

follows:

2001–01–09 Airbus Industrie: Amendment

39–12079. Docket 2000–NM–292–AD.

Supersedes AD 99–26–12, Amendment

39–11471.

Applicability: The following airplanes,

certificated in any category: Model A330–

301, –321, and –322 series airplanes;

excluding those on which Airbus

Modification 46964 or 47221 has been

installed; and Model A340–211, –212, –213,

–311, –312, and –313 series airplanes.

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