Federal Register / Vol. 63, No. 20 / Friday, January 30, 1998 /Rules and Regulations 4565

Revision 01, dated March 31, 1995; and

Model CL–600–2A12 series airplanes, as

listed in Bombardier Canadair Challenger

Alert Service Bulletin A601–0441, Revision

01, dated March 31, 1995; certificated in any

category.

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 electrical arcing between the

internal wiring and casing of the anti-noise

filter on the standby and auxiliary power unit

(APU) fuel pump assemblies, and consequent

increased risk of fuel tank explosion or fire,

accomplish the following:

(a) Within 100 flight hours after the

effective date of this AD, replace the antinoise filter on the standby and auxiliary

power unit (APU) fuel pump assemblies with

a new filter, in accordance with Part B of

Bombardier Canadair Challenger Alert

Service Bulletin A600–0644, Revision 01,

dated March 31, 1995 (for Model CL–600–

1A11 series airplanes), or Bombardier

Canadair Challenger Alert Service Bulletin

A601–0441, Revision 01, dated March 31,

1995 (for Model CL–600–2A12 series

airplanes); as applicable.

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

person shall install on any airplane a fuel

pump having part number (P/N) 600–62966–

25 or 600–62966–27 with an anti-noise filter

having P/N 160–151501 (prior to revision H

stamped on the part) installed.

(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, New York

Aircraft Certification Office (ACO), FAA,

Engine and Propeller Directorate. 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.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

(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.

(e) The replacement shall be done in

accordance with Bombardier Canadair

Challenger Alert Service Bulletin A600–0644,

Revision 01, dated March 31, 1995;

Bombardier Canadair Challenger Alert

Service Bulletin A601–0441, Revision 01,

dated March 31, 1995; 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

Bombardier, Inc., Canadair, Aerospace

Group, P.O. Box 6087, Station A, Montreal,

Quebec H3C 3G9, Canada. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the FAA Engine and

Propeller Directorate, New York Aircraft

Certification Office, 10 Fifth Street, Third

Floor, Valley Stream, New York; 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 Canadian airworthiness directive CF–97–

02, dated February 25, 1997.

(f) This amendment becomes effective on

March 6, 1998.

Issued in Renton, Washington, on January

21, 1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–1973 Filed 1–29–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–301–AD; Amendment

39–10296; AD 98–03–04]

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 revising the Airplane

Flight Manual (AFM) to prohibit use of

the autobrake during landing on

contaminated runways. This action also

requires replacement of the brake and

steering control unit (BSCU) with a new

BSCU, which eliminates the need for

the AFM revision. For certain airplanes,

this action also requires installation of

new brakes. This amendment is

prompted by the issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified in this AD are

intended to prevent insufficient braking

capability, which could increase the

potential for landing overrun.

DATES: Effective February 17, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February

17, 1998.

Comments for inclusion in the Rules

Docket must be received on or before

March 2, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97–NM–

301–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

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:

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: The

Direction Ge ́ne ́rale de l’Aviation Civile

(DGAC), which is the airworthiness

authority for France, notified the FAA

that an unsafe condition may exist on

certain Airbus Model A330 and A340

series airplanes. The DGAC advises that

some operators reported braking

discrepancies at low taxi speed.

Investigation has revealed anomalies in

the standard of software associated with

the brake and steering control unit

(BSCU), which could result in

insufficient braking capability. This

condition, if not corrected, could

increase the potential for landing

overrun.

Explanation of Relevant Service

Information

Airbus has released A330 Flight

Manual Temporary Revision 4.03.00/05,

dated July 12, 1996, and A340 Flight

Manual Temporary Revision 4.03.00/13,

dated July 12, 1996. These temporary

revisions describe a revision to the

Limitations Section of the Airplane

Flight Manual (AFM) to prohibit use of

the autobrake during landing on

contaminated runways.

Airbus also has issued Service

Bulletins A330–32–3062, Revision 2 (for

Model A330 series airplanes), and

A340–32–4087, Revision 2 (for Model

A340 series airplanes), both dated May
4566 Federal Register / Vol. 63, No. 20 / Friday, January 30, 1998 /Rules and Regulations

27, 1997. These service bulletins

describe procedures for installation of

an improved S6D standard BSCU,

which will improve braking capability.

Additionally, Airbus has issued

Service Bulletins A330–32–3061,

Revision 1, dated May 6, 1997 (for

Model A330 series airplanes), and

A340–32–4086, Revision 2, dated June

13, 1997 (for Model A340 series

airplanes). These service bulletins,

applicable to airplanes equipped with

Bendix brakes, describe procedures for

installation of improved Bendix brakes,

which will reduce susceptibility to

braking discrepancies at low taxi speed.

For airplanes equipped with Bendix

brakes, Airbus Service Bulletin A330–

32–3061 must be accomplished prior to

or concurrently with the

accomplishment of Airbus Service

Bulletin A330–32–3062; and Airbus

Service Bulletin A330–32–4086 must be

accomplished prior to or concurrently

with the accomplishment of Airbus

Service Bulletin A330–32–4087.

Accomplishment of Airbus Service

Bulletin A330–32–3062 or A340–32–

4087, as applicable, eliminates the need

for the AFM revision. Accomplishment

of the actions specified in the service

bulletins is intended to adequately

address the identified unsafe condition.

The DGAC classified these service

bulletins and the temporary revisions as

mandatory and issued French

airworthiness directives 97–086–

046(B)(R1) and 97–142–048(B), both

dated July 2, 1997 (for Model A330

series airplanes); and 97–087–056(B),

dated March 12, 1997 (for Model A340

series airplanes); in order to assure 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 section

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 requires accomplishment

of the actions specified in the service

information described previously.

Cost Impact

None of the airplanes affected by this

action is 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, estimated costs

are provided as follows.

It would require approximately 1

work hour to accomplish the temporary

revision of the AFM, at an average labor

rate of $60 per work hour. Based on

these figures, the cost impact of the

temporary revision of the AFM required

by this AD would be $60 per airplane.

It would require approximately 3

work hours to install an improved

BSCU, at an average labor rate of $60

per work hour. Required parts would be

provided by the manufacturer at no cost

to the operators. Based on these figures,

the cost impact of the BSCU installation

required by this AD would be $180 per

airplane.

For airplanes equipped with Bendix

brakes, it would require approximately

8 work hours to install new Bendix

brakes, at an average labor rate of $60

per work hour. Required parts would be

provided by the manufacturer at no cost

to the operators. Based on these figures,

the cost impact of the brake installation

required by this AD would be $480 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.

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 Number 97–NM–301–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

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.
Federal Register / Vol. 63, No. 20 / Friday, January 30, 1998 /Rules and Regulations 4567

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:

98–03–04 Airbus Industrie: Amendment

39–10296. Docket 97–NM–301–AD.

Applicability: Model A330 and A340 series

airplanes on which Airbus Modification

45006 has not been installed, certificated in

any category.

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 (e) 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 insufficient braking capability,

which could increase the potential for

landing overrun, accomplish the following:

(a) Within 30 days after the effective date

of this AD, revise the Limitations Section of

the FAA-approved Airplane Flight Manual

(AFM) in accordance with paragraph (a)(1) or

(a)(2) of this AD, as applicable. This action

may be accomplished by inserting a copy of

this AD into the applicable AFM.

(1) For Model A330 series airplanes: Revise

the AFM to include the following:

‘‘AUTOBRAKE

Do not use the autobrake on contaminated

runway (runway covered with more than 3

millimeters of water or slush or snow or ice)

and on suspected slippery runway (for

example, runway having heavy rubber

traces).

On contaminated runway or on suspected

slippery runway:

—Apply manual braking only after the nose

landing gear is on ground.

—Increase the landing distance by 4% (1%

on icy runway).’’

Note 2: This AFM revision also may be

accomplished by inserting into the

Limitations Section of the AFM a copy of

Airbus A330 Flight Manual Temporary

Revision 4.03.00/05, dated July 12, 1996.

(2) For Model A340 series airplanes: Revise

the AFM to include the following:

‘‘AUTOBRAKE

Do not use the autobrake on contaminated

runway (runway covered with more than 3

millimeters of water or slush or snow or ice)

and on suspected slippery runway (for

example, runway having heavy rubber

traces).

On contaminated runway or on suspected

slippery runway:

—Apply manual braking only after the nose

landing gear is on ground.

—Increase the landing distance by 5% (1%

on icy runway).’’

Note 3: This AFM revision also may be

accomplished by inserting into the

Limitations Section of the AFM a copy of

Airbus A340 Flight Manual Temporary

Revision 4.03.00/13, dated July 12, 1996.

(b) For airplanes equipped with Bendix

brakes: Prior to or concurrently with the

accomplishment of paragraph (c) of this AD,

replace existing Bendix brakes with new

Bendix brakes in accordance with paragraph

(b)(1) or (b)(2) of this AD, as applicable.

(1) For Model A330 series airplanes: Install

Bendix brakes having increased zero torque

pressure, in accordance with Airbus Service

Bulletin A330–32–3061, Revision 1, dated

May 6, 1997.

(2) For Model A340 series airplanes: Install

Bendix brakes having increased zero torque

pressure, in accordance with Airbus Service

Bulletin A340–32–4086, Revision 2, dated

June 13, 1997.

(c) Within 6 months after the effective date

of this AD, replace the existing brake and

steering control unit (BSCU) with a BSCU

having part number C2029336D6D6D, in

accordance with paragraph (c)(1) or (c)(2) of

this AD, as applicable. Accomplishment of

this modification constitutes terminating

action for the requirements of paragraph (a)

of this AD; after the modification has been

accomplished, the temporary AFM limitation

may be removed.

(1) For Model A330 series airplanes:

Replace the BSCU with a modified BSCU, in

accordance with Airbus Service Bulletin

A330–32–3062, Revision 2, dated May 27,

1997.

(2) For Model A340 series airplanes:

Replace the BSCU with a modified BSCU, in

accordance with Airbus Service Bulletin

A330–32–4087, Revision 2, dated May 27,

1997.

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

person shall install a BSCU having P/N

C2029335B5B5B on any airplane.

(e) 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 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(f) 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.

(g) The replacements shall be done in

accordance with the following Airbus service

bulletins, as applicable, which contain the

specified effective pages:

Service bulletin referenced and date Page No. Revision level

shown on page

Date shown on

page

A330–32–3061, Revision 1, May 6, 1997 .................................................................................. 1–4 1 ....................... May 6, 1997.

5–8 Original ............. Oct. 22, 1996.

A330–32–3062, Revision 2, May 27, 1997 ................................................................................ 1–8 2 ....................... May 27, 1997.

A340–32–4086, Revision 2, June 13, 1997 ............................................................................... 1, 2 2 ....................... June 13, 1997.

3–8 1 ....................... Feb. 10, 1997.

A340–32–4087, Revision 2, May 27, 1997 ................................................................................ 1–8 2 ....................... May 27, 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 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 5: The subject of this AD is addressed

in French airworthiness directives 97–086–

046(B)(R1) and 97–142–048(B), both dated

July 2, 1997; and 97–087–056(B), dated

March 12, 1997.
4568 Federal Register / Vol. 63, No. 20 / Friday, January 30, 1998 /Rules and Regulations

(h) This amendment becomes effective on

February 17, 1998.

Issued in Renton, Washington, on January

21, 1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–1970 Filed 1–29–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–320–AD; Amendment

39–10297; AD 98–03–05]

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 all Airbus Model A330

and A340 series airplanes. This action

requires removal of three electric motordriven hydraulic pumps (EHP) and

associated wiring, and installation of

placards in the flight deck. This

amendment is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified in this AD are intended to

prevent operation of the EHP, which

could result in fire in the wheel well

area, and consequent damage to airplane

structure or injury to airplane

occupants.

DATES: Effective February 17, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February

17, 1998.

Comments for inclusion in the Rules

Docket must be received on or before

March 2, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97–NM–

320–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

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:

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: The

Direction Ge ́ne ́rale de l’Aviation Civile

(DGAC), which is the airworthiness

authority for France, notified the FAA

that an unsafe condition may exist on

all Airbus Model A330 and A340 series

airplanes. The DGAC advises that it has

received several reports of fires in the

wheel well area. The cause of the fires

has been attributed to use of the electric

motor-driven hydraulic pumps (EHP).

The DGAC had previously issued

French airworthiness directives to

require electrical isolation of the three

EHP in order to address the unsafe

condition. However, since that time, the

DGAC has received one additional

report of an on-ground fire in the wheel

well. The investigation into the cause of

this incident has not yet concluded;

however, deliberate or inadvertent

operation of the EHP is believed to be

related to the incident. This condition,

if not corrected, could result in fire in

the wheel well area, and consequent

damage to airplane structure or injury to

airplane occupants.

Explanation of Relevant Service

Information

Airbus has issued All Operators Telex

(AOT) 29–21, Revision 1, dated January

8, 1997, which describes procedures for

the disconnection and electrical

isolation of all EHP’s, and the

installation of certain system

‘inoperative’ placards in the flight deck.

Airbus also has issued Service

Bulletins A330–29–3041, dated

February 25, 1997 (for Model A330

series airplanes), and A340–29–4041,

dated February 26, 1997 (for Model

A340 series airplanes), which describe

procedures for removal of the three

EHP’s and associated wiring to permit

installation of alternative pumps, or

installation of provisions that would

allow use of dedicated ground support

equipment. Accomplishment of the

actions specified in the AOT and service

bulletins described previously is

intended to adequately address the

identified unsafe condition.

The DGAC classified the AOT and

service bulletins as mandatory and

issued French airworthiness directives

97–017–043(B)R2, dated June 18, 1997,

as revised by ERRATUM, dated July 2,

1997; and 97–018–059(B)R2, dated June

18, 1997, as revised by ERRATUM,

dated July 2, 1997; in order to assure 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 section

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, the AD requires accomplishment

of the actions specified in the AOT and

service bulletins described previously.

Differences Between This AD and the

French AD’s

This AD differs from the parallel

French airworthiness directives in that

it requires a single method of preventing

operation of the three EHP’s. The DGAC

AD’s provide three methods of

compliance: describing procedures for

disconnection and electrical isolation of

the three EHP’s; removal of the three

EHP’s with installation of placards in

the flight deck; or removal of the three

EHP’s and subsequent installation of

replacement EHP’s. However, the FAA

has determined that removal of the

EHP’s is the most effective method of

addressing the unsafe condition;

therefore, this AD requires the removal

of the three EHP’s and installation of

placards in the flight deck. Operators

should note that such removal of the

three EHP’s allows the option of using

ground support equipment, or installing

alternative pumps, as described in the

French airworthiness directives.

Cost Impact

None of the Model A330 and A340

series 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;