Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations 37029

will not have a significant economic

impact, positive or negative, on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (14 CFR

part 39) as follows:

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: (49 U.S.C. 106(g), 40113,

44701.)

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

2000–11–26 Airbus Industrie: Amendment

39–11775. Docket 2000–NM–53–AD.

Applicability: All Model A330 and A340

series airplanes, 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 (b) 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 corrosion of the

retraction links of the main landing gear

(MLG), which could result in reduced

structural integrity and possible collapse of

the MLG, accomplish the following:

Repetitive Ultrasonic Inspections

(a) Within 36 months time-in-service on

any new retraction link, or within 2 months

after the effective date of this AD, whichever

occurs later, perform an ultrasonic inspection

to detect corrosion of the retraction links leftand right-hand of the MLG, in accordance

with Airbus Service Bulletin A330–32–3105,

Revision 01, dated December 14, 1999 (for

Model A330 series airplanes), or Airbus

Service Bulletin A340–32–4148, Revision 01,

dated December 14, 1999 (for Model A340

series airplanes), as applicable.

(1) If no corrosion is detected, or if

corrosion is detected that is within the limits

specified in the applicable service bulletin,

repeat the inspection thereafter at intervals

not to exceed 6 months.

(2) If any corrosion is detected that is

outside the limits specified in the applicable

service bulletin, replace the affected

retraction link with a new retraction link at

the time specified and in accordance with the

procedures specified in the applicable

service bulletin. Thereafter, repeat the

inspection specified in paragraph (a) on any

new retraction links, at the time specified in

paragraph (a) of this AD.

Note 2: The Airbus service bulletins

reference Messier-Dowty Service Bulletins

A33/34–32–151, Revision 3, including

Appendix A, and A33/34–32–152, Revision

3, including Appendix A, each dated January

11, 2000, as additional sources of service

information for accomplishing the repetitive

inspections.

Note 3: Although the inspection schedule

of this AD applies to both left-and right-hand

retraction links of the MLG, replacement of

a retraction link, prior to scheduled

replacement, would result in subsequent

staggered inspections for the remainder of the

retraction links.

Alternative Methods of Compliance

(b) 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.

Special Flight Permits

(c) 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

(d) The actions shall be done in accordance

with Airbus Service Bulletin A330–32–3105,

Revision 01, dated December 14, 1999; or

Airbus Service Bulletin A340–32–4148,

Revision 01, dated December 14, 1999; as

applicable. This incorporation by reference

was approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Note 5: The subject of this AD is addressed

in French airworthiness directives 2000–

013–107(B) R1, dated February 9, 2000, and

2000–015–132(B), dated January 12, 2000.

(e) This amendment becomes effective on

July 18, 2000.

Issued in Renton, Washington, on June 2,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14433 Filed 6–12–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–139–AD; Amendment

39–11776; AD 2000–11–27]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A319, A320, and A321 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Airbus Model

A319, A320, and A321 series airplanes.

This action requires a one-time

ultrasonic inspection to detect

disbonding of the skin attachments at

the stringers and spars of the vertical

stabilizer, and repair, if necessary. This

action is necessary to detect and correct

disbonding of the vertical stabilizer

structure, which could result in reduced

structural integrity of the spar boxes of

the vertical stabilizer.

DATES: Effective June 28, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 28,

2000.

Comments for inclusion in the Rules

Docket must be received on or before

July 13, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

139–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

37030 Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations

location between 9 a.m. and 3 p.m.,

Monday through Friday, except Federal

holidays. Comments may also be sent

via the Internet using the following

address: 9-anm-iarcomment@faa.gov.

Comments sent via the Internet must

contain ‘‘Docket No. 2000–NM–139–

AD’’ in the subject line and need not be

submitted in triplicate.

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 Geu ́neu ́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 A319, A320, and A321 series

airplanes. The DGAC advises that

localized disbonding has been detected

on the skin attachments at the stringers

and spars of the spar boxes of the

vertical stabilizer. During the

manufacturing process, pre-cured parts

(attachments of the stringers, spars, and

ribs) are installed on the skin panel

before the final curing process. A peel

ply is used to protect the contact

surfaces of the attachment angles of the

skin panels of the vertical stabilizer

until the pre-cured parts are ready for

installation. Investigation revealed that,

after the peel ply was removed from the

attachment angles, a residue of polymer

finish contaminated the contact surfaces

of some pre-cured parts. This

contamination reduced the adhesive

strength of the bond and, in some cases,

caused debonding (disbonding) of the

skin attachments. This condition, if not

detected and corrected, could result in

reduced structural integrity of the spar

boxes of the vertical stabilizer.

Explanation of Relevant Service

Information

The manufacturer has issued Airbus

Service Bulletin A320–55A1027, dated

May 12, 2000, which describes

procedures for a one-time ultrasonic

inspection to detect disbonding of the

skin attachments at the stringers and

spars of the vertical stabilizer, left-and

right-hand sides, and repair, if

necessary. If any disbonding (damage) is

detected and the area of damage is

greater than 300 square millimeters

(mm2), or if multiple damage is detected

on one specific component (stringerspar attachment), the repair involves

installing additional fasteners in the

affected areas. The amount of damage

determines the number of additional

fasteners to be installed in the affected

area.

Additionally, Airbus Service Bulletin

A320–55A1027 references Airbus

Service Bulletin A320–55–1026,

Revision 01, dated May 20, 1999, which,

for certain airplanes, describes

procedures for prior or concurrent

modification of the vertical stabilizer to

ensure proper reinforcement of the

structure-skin attachments.

The DGAC classified Airbus Service

Bulletin A320–55–A1027 as mandatory

and issued French airworthiness

directive T2000–208–148(B) R1, dated

May 17, 2000, 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 § 21.29 of

the Federal Aviation Regulations (14

CFR 21.29) 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 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 detect

and correct disbonding of the vertical

stabilizer structure, which could result

in reduced structural integrity of the

spar boxes of the vertical stabilizer. This

AD requires a one-time ultrasonic

inspection to detect disbonding of the

skin attachments at the stringers and

spars of the vertical stabilizer, and

repair, if necessary. The actions are

required to be accomplished in

accordance with the service bulletin

described previously.

Interim Action

This is considered interim action. The

manufacturer has advised that it is

currently developing a repetitive

inspection program to positively

address the unsafe condition addressed

by this AD. Once this repetitive

inspection program is developed,

approved, and available, the FAA may

consider additional rulemaking.

Determination of Rule’s Effective Date

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an 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

Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations 37031

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–139–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.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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:

2000–11–27 Airbus Industrie: Amendment

39–11776. Docket 2000–NM–139–AD.

Applicability: Model A319, A320, and

A321 series airplanes; certificated in any

category; as listed in Airbus Service Bulletin

A320–55A1027, dated May 12, 2000.

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 detect and correct disbonding of the

vertical stabilizer structure, which could

result in reduced structural integrity of the

spar boxes of the vertical stabilizer,

accomplish the following:

Ultrasonic Inspection

(a) Within 60 days after the effective date

of this AD, perform a one-time ultrasonic

inspection to detect disbonding (damage) of

the skin attachments at the stringers and

spars of the vertical stabilizer, left-and righthand sides, in accordance with Airbus

Service Bulletin A320–55A1027, dated May

12, 2000.

(1) If no damage is detected or if a single

area of damage is less than or equal to an area

of 300 square millimeters (mm2), no further

action is required by this AD.

(2) If any damage is detected and the area

of damage is greater than 300 mm2, or if

multiple damage is detected on one specific

component (stringer/spar attachment), prior

to further flight, accomplish applicable

repairs in accordance with the service

bulletin.

Modification (for Certain Airplanes)

(b) For airplanes with manufacturer’s serial

numbers listed in paragraph B of the

Planning Information of Airbus Service

Bulletin A320–55A1027, dated May 12, 2000:

Prior to or concurrent with the ultrasonic

inspection required by paragraph (a) of this

AD, modify the vertical stabilizer to ensure

proper reinforcement of the structure/skin

attachments, in accordance with Airbus

Service Bulletin A320–55–1026, Revision 01,

dated May 20, 1999.

Note 2: Accomplishment of the

modification required by paragraph (b) of this

AD, prior to the effective date of this AD, in

accordance with Airbus Service Bulletin

A320–55–1026 dated March 29, 1999, is

considered acceptable for compliance with

the applicable requirement 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

A320–55A1027, dated May 12, 2000, and

Airbus Service Bulletin A320–55–1026,

Revision 01, dated May 20, 1999. This

incorporation by reference was approved by

the Director of the Federal Register in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51.

Copies may be obtained from Airbus

Industrie, 1 Rond Point Maurice Bellonte,

31707 Blagnac Cedex, France. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Note 4: The subject of this AD is addressed

in French airworthiness directive T2000–

208–148(B) R1, dated May 17, 2000.

(f) This amendment becomes effective on

June 28, 2000.

Issued in Renton, Washington, on June 2,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14432 Filed 6–12–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–38–AD; Amendment

39–11779; AD 2000–12–01]

RIN 2120–AA64

Airworthiness Directives;

Airworthiness Directives; CFM

International (CFMI) CFM56–2, –2A,

–2B, –3, –3B, –3C, –5, –5B, –5C, and

–7B Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain CFM International

(CFMI) CFM56 series turbofan engines,