22432 Federal Register / Vol. 66, No. 87 / Friday, May 4, 2001 / Rules and Regulations

hours time-in-service (TIS), certificated in

any category.

Note 1: This AD applies to each helicopter

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 helicopters 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 within 25 hours TIS,

unless accomplished previously.

To prevent the blade spar elliptical

centering plug (centering plug) from

disbonding and moving out of position, loss

of tail rotor control, and subsequent loss of

control of the helicopter, accomplish the

following:

(a) Inspect the centering plug for

disbonding of the polyurethane filler that

fills the space between the aluminum

centering plug and the graphite spar in

accordance with the Accomplishment

Instructions, paragraph 3.A.(1) and (2), of

Sikorsky Aircraft Corporation Alert Service

Bulletin No. 76–65–35B (153B), Revision B,

dated October 2, 1997 (ASB).

Note 2: The 500-hours TIS repetitive

inspections contained in the

Accomplishment Instructions, paragraph

3.D., of Sikorsky Aircraft Corporation Alert

Service Bulletin 76–65–35A, Revision A,

dated February 29, 1984, are not required by

this AD.

(1) If the inspection of the centering plug

reveals disbonding of 1⁄2-inch or less in

length, install a retaining pad, P/N 76102–

05004–111, in accordance with the

Accomplishment Instructions, paragraph

3.C., of the ASB.

(2) For disbonds greater than 1⁄2-inch in

length, repair the blade assembly in

accordance with the Accomplishment

Instructions, paragraph 3.B.(1), of the ASB

except you are not required to contact

Sikorsky Worldwide Customer Service. If

blades are found with polyurethane filler

excessively cracked or deteriorated to extent

of breaking away from the spar or aluminum

plug by 0.005-inch or greater, replace the

blade with an airworthy blade.

(3) For spars with complete spar to

centering plug disbond in which the

polyurethane filler is intact and remains fully

bonded to the centering plug, repair the blade

assembly in accordance with the

Accomplishment Instructions, paragraph

3.B.(2), of the ASB.

(4) For spars with complete polyurethane

filler to centering plug disbond in which the

polyurethane filler is intact and remains fully

bonded to the spar, repair the blade assembly

in accordance with the Accomplishment

Instructions, paragraph 3.B.(3) of the ASB.

(b) Install a retaining pad, P/N 76102–

05004–111, in accordance with the

Accomplishment Instructions, paragraph

3.C., of the ASB.

(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, Boston

Aircraft Certification Office, FAA. Operators

shall submit their requests through an FAA

Principal Maintenance Inspector, who may

concur or comment and then send it to the

Manager, Boston Aircraft Certification Office.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Boston Aircraft

Certification Office.

(d) Special flight permits may be issued in

accordance with 14 CFR 21.197 and 21.199

to operate the helicopter to a location where

the requirements of this AD can be

accomplished if a retaining pad has been

installed.

(e) The inspections, modifications, and

repair shall be done in accordance with the

Accomplishment Instructions, paragraphs

3.A.(1), 3.A.(2), 3.B.(1), 3.B.(2), 3.B.(3), and

3.C., of Sikorsky Aircraft Corporation Alert

Service Bulletin No. 76–65–35B (153B),

Revision B, dated October 2, 1997. 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

Sikorsky Aircraft Corporation, Attn: Manager,

Commercial Tech Support, 6900 Main Street,

Stratford, Connecticut 06614, phone (203)

386–3001, fax (203) 386–5983. Copies may be

inspected at the FAA, Office of the Regional

Counsel, Southwest Region, 2601 Meacham

Blvd., Room 663, Fort Worth, Texas; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment becomes effective on

June 8, 2001.

Issued in Fort Worth, Texas, on April 20,

2001.

Larry M. Kelly,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 01–10730 Filed 5–3–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–352–AD; Amendment

39–12214; AD 2001–09–09]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A330 and A340 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A330 and A340 series airplanes. This

action requires a one-time inspection to

verify the proper configuration of the

drive assemblies for the low-pressure

and, for certain airplanes, the cross-feed

fuel valves; and corrective action, if

necessary. This action is necessary to

prevent failure of the low-pressure and/

or cross-feed fuel valves, which could

result in the inability to shut off the fuel

supply to the engine and exacerbate an

engine fire, or the inability to cross-feed

fuel when required. This action is

intended to address the identified

unsafe condition.

DATES: Effective May 21, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 21,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

June 4, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket 2000–NM–352–

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-anmiarcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2000–NM–352–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:

Todd Thompson, Aerospace Engineer,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–1175;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: The

Direction Generale de l’Aviation Civile

(DGAC), which is the airworthiness

authority for France, notified the FAA

Federal Register / Vol. 66, No. 87 / Friday, May 4, 2001 / Rules and Regulations 22433

that an unsafe condition may exist on

certain Airbus Model A330 and A340

series airplanes. The DGAC advises that

an operator of a Model A340 series

airplane experienced an engine

shutdown less than a minute after

engine startup. Subsequent inspection

of the low-pressure fuel valve drive of

the engine revealed that a thrust washer

was missing from the drive assembly.

The reason for the missing washer is

unknown. The absence of the washer

allowed excessive movement of the

spindle in the drive assembly, which

caused the spindle to disconnect from

the actuator. Because the actuator was

not connected to the spindle of the drive

assembly, the fuel valve could not be

operated. Failure of the low-pressure

fuel valve, if not corrected, could result

in the inability to shut off the fuel

supply to the engine and exacerbate an

engine fire.

The subject low-pressure fuel valves

are installed on certain Model A330 and

A340 series airplanes. Therefore, those

Model A330 series airplanes are also

subject to the unsafe condition

identified in this AD.

Failure of the cross-feed valves could

result in the inability to cross-feed fuel

when required only on Model A330

series airplanes flying under extended

range twin-engine operations (ETOPS).

Relevant Service Information

Airbus has issued Service Bulletins

A330–28A3069 (for Model A330 series

airplanes) and A340–28A4087 (for

Model A340 series airplanes), both

dated July 27, 2000. The service

bulletins describe procedures for a onetime inspection to verify the proper

configuration of the drive assemblies for

the low-pressure and cross-feed fuel

valves. If the washer is missing, the

service bulletins provide procedures for

installing a new thrust washer. If

excessive movement of the drive

spindle is detected, the service bulletins

provide procedures for inspecting the

drive assembly to detect damage and

wear and replacing unserviceable parts

with serviceable parts. These actions are

intended to adequately address the

unsafe condition. The DGAC classified

the service bulletins as mandatory and

issued French airworthiness directives

2000–406–125(B) and 2000–405–152(B),

both dated September 20, 2000, to

ensure the continued airworthiness of

these 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 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 that may be registered in the

United States at some time in the future,

this AD is being issued to prevent

failure of the low-pressure and/or crossfeed fuel valves, which could result in

the inability to shut off the fuel supply

to the engine and exacerbate an engine

fire, or the inability to cross-feed fuel

when required. This AD requires the

actions specified in 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 16 work hours to

accomplish the required actions, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of this AD would be $960 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 2000–NM–352–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

22434 Federal Register / Vol. 66, No. 87 / Friday, May 4, 2001 / Rules and Regulations

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:

2001–09–09 Airbus Industrie: Amendment

39–12214. Docket 2000–NM–352–AD.

Applicability: The following airplanes,

certificated in any category, listed in the

following table:

TABLE 1—APPLICABILITY

Model/series Having serial numbers— Equipped with—

A330–202, –223, –243, –301, –321, –322,

–323, –341, –342, –343.

0012 through 0314 inclusive, 0316 through

0319 inclusive, 0321, 0322, 0325 through

0328 inclusive.

Low-pressure fuel valves having part number

(P/N) HTE900212 or HTE900160, and having a cross-feed valve having P/N

HTE900162.

A340–211, –212, –213, –311, –312, –313 ........ 0002 through 0327 inclusive ............................ Low-pressure fuel valves having P/N

HTE900212 or HTE900160.

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 (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 failure of the low-pressure and/

or cross-feed fuel valves, which could result

in the inability to shut off the fuel supply to

the engine and exacerbate an engine fire, or

the inability to cross-feed fuel when required,

accomplish the following:

Inspection

(a) Within 1,450 flight hours after the

effective date of this AD, perform a one-time

detailed visual inspection of the drive

assemblies for the low-pressure and crossfeed fuel valves to detect discrepancies

(incorrect configuration including a missing

thrust washer and excessive movement of the

drive spindle), in accordance with Airbus

Service Bulletin A330–28A3069 (for Model

A330 series airplanes) or A340–28A4087 (for

Model A340 series airplanes), both dated July

27, 2000; as applicable. If any discrepancy is

found: Prior to further flight, perform

applicable corrective actions (including

inserting a new washer, inspecting the drive

assembly to detect damage and wear,

repairing cracking, and replacing

unserviceable parts with serviceable parts) in

accordance with the applicable service

bulletin.

Note 2: 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.’’

Spares

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

person may install on any airplane a lowpressure fuel valve having P/N HTE900212 or

HTE900160, unless that valve has been

inspected and applicable corrective actions

have been performed in accordance with the

requirements of 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, 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 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 actions shall be done in accordance

with Airbus Service Bulletin A330–28A3069,

dated July 27, 2000; and Airbus Service

Bulletin A340–28A4087, dated July 27, 2000;

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–

406–125(B) and 2000–405–152(B), both dated

September 20, 2000.

Effective Date

(f) This amendment becomes effective on

May 21, 2001.

Issued in Renton, Washington, on April 24,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–10726 Filed 5–3–01; 8:45 am]

BILLING CODE 4910–13–U