Federal Register / Vol. 65, No. 103 / Friday, May 26, 2000 / Rules and Regulations 34069

WING SPAR PART NUMBERS

INCORPORATED

Wing spar parts Part Nos.

Upper Spar Cap Angles.2–1610–015 and 2–

1610–016.

Lower Spar Cap Angles.2–1610–075 and 2–

1610–076.

Upper Spar Doublers 2–1610–061 and 2–

1610–081 and 2–

1610–065.

WING SPAR PART NUMBERS

INCORPORATED

Wing spar parts Part Nos.

Lower Spar Doublers 2–1610–063 and 2–

1610–083.

(b) Who must comply with this AD?

This AD applies to anyone who wishes

to operate any of the above airplanes on

the U.S. Register .

(c) What problem does this AD

address? The actions of this AD are

intended to detect and correct cracks in

the wing spars, which could result in

loss of the wing with consequent loss of

control of the airplane.

(d) What actions must I accomplish to

address this problem? To address this

problem, you must accomplish the

following:

Action When Procedures

(1) Inspect the left and right wing upper and

lower spar doublers for cracks.

At whichever of the following that occurs first:

(i) Within the next 50 hours time-in-service

(TIS) after June 20, 2000 (the effective date

of this AD); or.

(ii) On or before June 20, 2001 (12 months

after the effective date of this AD).

In accordance with the Inspection section of

Revo, Inc. Service Bulletin B–79 R1—Revised January 5, 2000.

(2) Replace any cracked wing spar doubler

with a new part that incorporates the same

part number (or FAA-approved equivalent

part number).

Prior to further flight after the required inspection.In accordance with the applicable maintenance manual.

(3) Incorporate Modification Kit B–79 ................ Prior to further flight after the required inspection.In accordance with the Kit Installation section

of Revo, Inc. Service Bulletin B–79 R1—

Revised January 5, 2000.

(e) What if I need to replace a wing

on my airplane? After the effective date

of this AD, you may not install a wing

on any of the affected airplanes, unless

one of the following exists:

(1) The wing is new from the factory;

or

(2) The inspection, applicable

replacement, and kit incorporation

requirements of this AD have been

accomplished at the time of installation.

(f) Can I comply with this AD in any

other way? You may use an alternative

method of compliance or adjust the

compliance time if:

(1) Your alternative method of

compliance provides an equivalent level

of safety; and

(2) The Manager, Boston Aircraft

Certification Office (ACO), approves

your alternative. Submit your request

through an FAA Principal Maintenance

Inspector, who may add comments and

then send it to the Manager, Boston

ACO.

Note: This AD applies to each airplane

identified in paragraph (a) of this AD,

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 (f)

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 you have not

eliminated the unsafe condition, specific

actions you propose to address it.

(g) Where can I get information about

any already-approved alternative

methods of compliance? Contact Mr.

Richard B. Noll, Aerospace Engineer,

FAA, Boston Aircraft Certification

Office, 12 New England Executive Park,

Burlington, Massachusetts 01803;

telephone: (781) 238–7160; facsimile:

(781) 238–7199.

(h) What if I need to fly the airplane

to another location to comply with this

AD? The FAA can issue a special flight

permit under sections 21.197 and

21.199 of the Federal Aviation

Regulations (14 CFR 21.197 and 21.199)

to operate your airplane to a location

where you can accomplish the

requirements of this AD.

(i) Are any service bulletins

incorporated into this AD by reference?

Actions required by this AD must be

done in accordance Revo, Inc. Service

Bulletin B–79 R1—Revised January 5,

2000. The Director of the Federal

Register approved this incorporation by

reference under 5 U.S.C. 552(a) and 1

CFR part 51. You can get copies from

REVO, Incorporated, P.O. Box 312, One

High Street, Sanford, Maine 04073. You

can look at copies at FAA, Central

Region, Office of the Regional Counsel,

901 Locust, Room 506, Kansas City,

Missouri; or at the Office of the Federal

Register, 800 North Capitol Street, NW,

suite 700, Washington, DC.

(j) When does this amendment

become effective? This amendment

becomes effective on June 20, 2000.

Issued in Kansas City, Missouri, on May

17, 2000.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 00–13084 Filed 5–25–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–99–AD; Amendment

39–11739; AD 2000–10–15]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

two existing airworthiness directives

(AD), applicable to certain Airbus

Model A320 series airplanes, that

currently require modification of the

rear spar web of the wing and cold

expansion of certain attachment holes

for the forward pintle fitting and certain

holes at the actuating cylinder

anchorage of the main landing gear

(MLG). This amendment adds a

requirement for repetitive inspections to

detect fatigue cracking in certain areas

of the rear spar of the wing, and

corrective action, if necessary. This

34070 Federal Register / Vol. 65, No. 103 / Friday, May 26, 2000 / Rules and Regulations

amendment also provides for optional

terminating action for the requirements

of this AD. 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 detect and correct fatigue

cracking, which may lead to reduced

structural integrity of the wing and the

MLG.

DATES: Effective June 30, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 30,

2000.

The incorporation by reference of

certain other publications was approved

previously by the Director of the Federal

Register as of June 11, 1993 (58 FR

27923, May 12, 1993), and February 14,

1994 (59 FR 1903, January 13, 1994).

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,

Transport Airplane Directorate, 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)

by superseding AD 93–08–15,

amendment 39–8563 (58 FR 27923, May

12, 1993), and AD 93–25–13,

amendment 39–8777 (59 FR 1903,

January 13, 1994), which are both

applicable to certain Airbus Model

A320 series airplanes, was published in

the Federal Register on February 10,

2000 (65 FR 6566). The action proposed

to continue to require modification of

the wing rear spar web and cold

expansion of certain attachment holes

for the forward pintle fitting and certain

holes at the actuating cylinder

anchorage of the MLG. The AD

proposed to add a requirement for

repetitive ultrasonic inspections to

detect fatigue cracking in certain areas

of the wing rear spar, and repair of

cracking. The AD also proposed to

provide for optional terminating action

for the inspections proposed by this AD.

Comments Received

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Support for the Proposal

One commenter concurs with the

proposed AD. Another commenter states

that Airbus Production Modification

24591 is installed on its airplanes;

therefore, it is not affected by the

proposed AD.

Inspection Threshold for Certain

Airplanes

One commenter requests that the

proposed AD be revised to allow

‘‘Group 2’’ airplanes to accomplish the

initial inspection of the wing rear spar

within 12,000 flight cycles after

accomplishment of Airbus Service

Bulletin A320–57–1060. The commenter

defines ‘‘Group 1’’ airplanes as

manufacturer’s serial numbers (MSN)

002 through 021, on which Airbus

Service Bulletins A320–57–1004 and

A320–57–1060 are accomplished as

retrofit. ‘‘Group 2’’ airplanes are defined

as MSN’s 022 through 051, on which

Airbus Modification 20740 (equivalent

to A320–57–1004) has been

accomplished in production, and Airbus

Service Bulletin A320–57–1060 as

retrofit.

The commenter notes that ‘‘Group 1’’

airplanes are granted 12,000 flight

cycles after accomplishment of A320–

57–1060, yet ‘‘Group 2’’ airplanes are

required to undergo inspection prior to

accumulation of 17,300 total flight

cycles, regardless of when modification

per A320–57–1060 was accomplished.

The commenter states that ‘‘Group 1’’

and ‘‘Group 2’’ airplanes are in the same

configuration and will have a similar

fatigue life; therefore, both should have

the same inspection threshold.

The FAA does not concur. Although

the FAA acknowledges that ‘‘Group 1’’

and ‘‘Group 2’’ airplanes may be in a

similar modification configuration, the

design configuration of these airplanes

is different. ‘‘Group 1’’ airplanes are

composed of Model A320–100 series

airplanes, and ‘‘Group 2’’ airplanes are

composed of Model A320–200 series

airplanes. Model A320–200 series

airplanes are equipped with a center

fuel tank (not installed on Model A320–

100 series airplanes) that increases the

airplanes’ weight. For this reason, it is

necessary that ‘‘Group 2’’ airplanes be

inspected for cracking prior to

accumulation of 17,300 total flight

cycles, regardless of when Service

Bulletin A320–57–1060 is

accomplished. No change is made to the

final rule.

Terminating Modification for Certain

Airplanes

One commenter requests that

modification in accordance with Airbus

Service Bulletin A320–57–1089 be

considered as terminating action to all

inspection requirements if

accomplished prior to the initial

inspection interval, or to repetitive

inspections if accomplished after the

initial inspection interval. The

commenter states that terminating

action credit is allowed under paragraph

(e) of the proposed AD only if

accomplished prior to 12,000 total flight

cycles. The commenter states that

accomplishment of the terminating

modification includes a non-destructive

test inspection of the inner rear spar at

each hole location. Since this inspection

during the modification will ensure that

the inner rear spar is free of defects,

terminating action to the follow-on

inspection requirements should also be

provided.

The FAA notes that terminating

modification to the inspection

requirements of the AD is already

provided for in paragraph (e) of the

proposed AD, and considers that

clarification of the provisions for

terminating modification is necessary.

As stated in the second sentence of

paragraph (e) of the AD, the threshold

of 12,000 total flight cycles is required

only if modification per Service Bulletin

A320–57–1089 is chosen in lieu of

accomplishing the modifications

required by paragraphs (a) and (b) of the

AD. However, the modification also

constitutes acceptable terminating

action for the ultrasonic inspection

requirements of the AD, as stated in the

first sentence of paragraph (e) of the AD.

Paragraph (e) has been revised to more

clearly specify the terminating action

provisions of the AD.

Cost Estimate for Terminating

Modification

Two commenters request that the

proposed AD be revised to provide

correct cost estimates for the optional

modification described in Airbus

Service Bulletin A320–57–1089. The

commenters state that the service

bulletin lists the labor cost as 980 work

hours, yet the proposed AD provides an

estimate of 750 work hours.

The FAA acknowledges that the

service bulletin estimate specifies

additional work hours (for access and

close) that are not included in the

proposed AD. However, the cost impact

information in an AD typically

describes only the ‘‘direct’’ costs of

Federal Register / Vol. 65, No. 103 / Friday, May 26, 2000 / Rules and Regulations 34071

specific actions, and does not include

incidental costs, such as the time

required to gain access and close up;

planning time; or time necessitated by

other administrative actions. Because

incidental costs may vary significantly

from operator to operator, they are

almost impossible to calculate.

Additionally, since this is an optional

modification, operators may choose not

to incur such costs, or may minimize

costs by accomplishing the modification

during scheduled maintenance. No

change is made to the final rule.

Additional Changes to the AD

To clarify actions for airplanes on

which modifications have been installed

in production and those on which

service bulletins have been

accomplished as retrofit, the FAA has

revised paragraph (c)(2) of the AD to

refer to certain modifications as ‘‘Airbus

Production Modification * * *.’’

Additionally, a heading has been

included to specify the actions required

by paragraphs (c) and (d) of the AD.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

There are approximately 126

airplanes of U.S. registry that will be

affected by this AD.

It takes approximately 60 work hours

per airplane to accomplish the

modification of the rear spar web of the

wing, as required by AD 93–08–15 and

retained in this AD, at an average labor

rate of $60 per work hour. Based on

these figures, the total cost impact of the

modification on U.S. operators is

estimated to be $3,600 per airplane.

It takes approximately 600 work hours

per airplane to accomplish the cold

expansion of certain holes associated

with the MLG, as required by AD 93–

25–13 and retained in this AD, at an

average labor rate of $60 per work hour.

Required parts are provided by the

manufacturer at no cost to the operators.

Based on these figures, the total cost

impact of the cold expansion on U.S.

operators is estimated to be $36,000 per

airplane.

The new inspection that is required

by this new AD will take approximately

24 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 $181,440, or

$1,440 per airplane, per inspection

cycle.

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.

Should an operator elect to

accomplish the optional terminating

action specified in this AD, it would

take approximately 750 work hours, at

an average labor rate of $60 per work

hour. The required parts would cost

$27,036; $30,595; or $32,727; depending

on the airplane configuration. Based on

these figures, the cost per airplane of the

optional terminating action provided by

this AD is estimated to be $72,036;

$75,595; or $77,727.

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 amendments 39–8563 (58 FR

27923, May 12, 1993) and 39–8777 (59

FR 1903, January 13, 1994), and by

adding a new airworthiness directive

(AD), amendment 39–11739, to read as

follows:

2000–10–15 Airbus Industrie: Amendment

39–11739. Docket 98–NM–99–AD.

Supersedes AD 93–08–15, Amendment

39–8563; and AD 93–25–13, Amendment

39–8777.

Applicability: Model A320 series airplanes,

certificated in any category, except those on

which Airbus Modification 24591 (Airbus

Service Bulletin A320–57–1089, dated

December 22, 1996; Revision 01, dated April

17, 1997; or Revision 02, dated November 6,

1998) 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 (f)(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 detect and correct fatigue cracking in

certain areas of the rear spar of the wing,

which may lead to reduced structural

integrity of the wing and the main landing

gear (MLG), accomplish the following:

Restatement of Actions Required by AD 93–

08–15

(a) For airplanes having manufacturer’s

serial numbers (MSN) 003 through 008

inclusive, and 010 through 021 inclusive:

Prior to the accumulation of 12,000 total

flight cycles, or within 500 flight cycles after

June 11, 1993 (the effective date of AD 93–

08–15, amendment 39–8563), whichever

occurs later, modify the inner rear spar web

of the wing in accordance with Airbus

Service Bulletin A320–57–1004, Revision 1,

dated September 24, 1992, or Revision 2,

dated June 14, 1993.

Restatement of Actions Required by AD 93–

25–13

(b) For airplanes having MSN’s 002

through 051 inclusive: Prior to the

accumulation of 12,000 total flight cycles, or

within 2,000 flight cycles after February 14,

1994 (the effective date of AD 93–25–13,

34072 Federal Register / Vol. 65, No. 103 / Friday, May 26, 2000 / Rules and Regulations

amendment 39–8777), whichever occurs

later, accomplish the requirements of

paragraphs (b)(1) and (b)(2) of this AD in

accordance with Airbus Service Bulletin

A320–57–1060, dated December 8, 1992; or

Revision 2, dated December 16, 1994.

(1) Perform a cold expansion of all the

attachment holes for the forward pintle

fitting of the MLG, except for the holes that

are for taper-lok bolts.

(2) Perform a cold expansion of the holes

at the actuating cylinder anchorage of the

MLG.

Note 2: Accomplishment of the cold

expansion in accordance with Airbus Service

Bulletin A320–57–1060, Revision 1, dated

April 26, 1993, is also acceptable for

compliance with the requirements of

paragraph (b) of this AD.

New Actions Required by This AD

Ultrasonic Inspections and Corrective

Action

(c) For all airplanes: Perform an ultrasonic

inspection to detect cracking of the rear spar

of the wing, in accordance with Airbus

Service Bulletin A320–57–1088, Revision 02,

dated July 29, 1999; at the applicable time

specified by paragraph (c)(1) or (c)(2) of this

AD. Repeat the inspection thereafter at

intervals not to exceed 3,600 flight cycles.

(1) For airplanes on which the actions

specified by Airbus Service Bulletin A320–

57–1004, Revision 2, dated June 14, 1993, or

earlier version; and Airbus Service Bulletin

A320–57–1060, Revision 02, dated December

16, 1994, or earlier version; have been

accomplished: Perform the inspection of all

applicable fastener holes within 12,000 flight

cycles after accomplishment of the service

bulletins, or within 750 flight cycles after the

effective date of this AD, whichever occurs

later.

(2) For airplanes on which the actions

specified by Airbus Production Modification

20740 and Airbus Service Bulletin A320–57–

1060, Revision 2, dated December 16, 1994,

or earlier version, have been accomplished;

or on which Airbus Production Modifications

20740, 20741, and 20796 have been

accomplished: Perform the inspections at the

locations and applicable times specified by

paragraphs (c)(2)(i) and (c)(2)(ii) of this AD.

(i) Perform the inspection of left and right

fastener holes 52 to 55, 82, 83, 87, and 88;

located in the rear spar of the wing; prior to

the accumulation of 17,300 total flight cycles,

or within 750 flight cycles after the effective

date of this AD, whichever occurs later. If

any cracking is found, prior to further flight,

accomplish the requirements of paragraph

(c)(2)(ii) of this AD.

(ii) Except as required by paragraph

(c)(2)(i) of this AD: Perform the inspection of

all fastener holes located in the rear spar of

the wing that are not identified in paragraph

(c)(2)(i) of this AD prior to the accumulation

of 20,000 total flight cycles, or within 200

flight cycles after the effective date of this

AD, whichever occurs later.

Note 3: Accomplishment of the actions

specified by Airbus Service Bulletin A320–

57–1088, dated September 30, 1996, or

Revision 01, dated September 17, 1997, prior

to the effective date of this AD is acceptable

for compliance with the requirements of the

initial inspection required by paragraph (c) of

this AD.

(d) If any crack is found during any

inspection required by paragraph (c) of this

AD: Prior to further flight, repair in

accordance with a method approved by

either the Manager, International Branch,

ANM–116, FAA, Transport Airplane

Directorate; or the Direction G ́en ́erale de

l’Aviation Civile (DGAC) (or its delegated

agent). For a repair method to be approved

by the Manager, International Branch, ANM–

116, as required by this paragraph, the

Manager’s approval letter must specifically

reference this AD.

Optional Terminating Action

(e) Modification of all specified fastener

holes in the rear spar of the wing in

accordance with Airbus Service Bulletin

A320–57–1089, dated December 22, 1996;

Revision 01, dated April 17, 1997; or

Revision 02, dated November 6, 1998;

constitutes terminating action for the

ultrasonic inspections required by paragraph

(c) of this AD. Such modification, if

accomplished prior to the accumulation of

12,000 total flight cycles, also constitutes

terminating action for the actions required by

paragraphs (a) and (b) of this AD.

Alternative Methods of Compliance

(f)(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,

International Branch, ANM–116. 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.

(2) Alternative methods of compliance,

approved previously in accordance with AD

93–25–13; amendment 39–8777, are

approved as alternative methods of

compliance with this AD.

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.

Special Flight Permits

(g) 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

(h) Except as required by paragraph (d) of

the AD, the actions shall be done in

accordance with Airbus Service Bulletin

A320–57–1004, Revision 1, dated September

24, 1992; Airbus Service Bulletin A320–57–

1004, Revision 2, dated June 14, 1993; Airbus

Service Bulletin A320–57–1060, dated

December 8, 1992; Airbus Service Bulletin

A320–57–1060, Revision 2, dated December

16, 1994; or Airbus Service Bulletin A320–

57–1088, Revision 02, including Appendix

01, dated July 29, 1999; as applicable. Airbus

Service Bulletin A320–57–1004, Revision 2,

dated June 14, 1993, contains the following

list of effective pages:

Page No. Revision level shown on page Date shown on page

1, 4, 12, 14, 17–20, 22, 23, 28, 29 ..................................... 2 .......................................................................................... June 14, 1993.

15 ......................................................................................... 1 .......................................................................................... September 24, 1992.

2, 3, 5–11, 13, 16, 21, 24–27, 30 ....................................... Original ................................................................................ July 9, 1991.

(1) The incorporation by reference of

Airbus Service Bulletin A320–57–1004,

Revision 2, dated June 14, 1993; Airbus

Service Bulletin A320–57–1060, Revision 2,

dated December 16, 1994; and Airbus Service

Bulletin A320–57–1088, Revision 02,

including Appendix 01, 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 A320–57–1004,

Revision 1, dated September 24, 1992, was

approved previously by the Director of the

Federal Register as of June 11,1993 (58 FR

27923, May 12, 1993).

(3) The incorporation by reference of

Airbus Service Bulletin A320–57–1060,

dated December 8, 1992, was approved

previously by the Director of the Federal

Register as of February 14, 1994 (59 FR 1903,

January 13, 1994).

(4) 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 directive 1999–264–

135(B), dated June 30, 1999.

(i) This amendment becomes effective on

June 30, 2000.

Issued in Renton, Washington, on May 16,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–12816 Filed 5–25–00; 8:45 am]

BILLING CODE 4910–13–U