Federal Register / Vol. 63, No. 91 /Tuesday, May 12, 1998 / Proposed Rules 26111

1994 (including Appendix 1, Revision 1,

dated August 3, 1994). If any cracking is

detected during any eddy current inspection,

prior to further flight, repair in accordance

with a method approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, or the

Direction Ge ́ne ́rale de l’Aviation Civile or (its

delegated agent).

(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. 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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(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.

Note 3: The subject of this AD is addressed

in French airworthiness directive 97–374–

238(B), dated December 3, 1997.

Issued in Renton, Washington, on May 5,

1998.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–12514 Filed 5–11–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–93–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A319, A320, and A321 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to all

Airbus Model A319, A320, and A321

series airplanes. This proposal would

require repetitive inspections for

discrepancies of the lock bolt for the

pintle pin on the main landing gear

(MLG), and follow-on corrective actions,

if necessary. This proposal is prompted

by issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by the proposed AD

are intended to detect and correct a

rotated, damaged, or missing lock bolt,

which could result in disengagement of

the pintle pin from the bearing, and

consequent collapse of the MLG during

landing.

DATES: Comments must be received by

June 11, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

93–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.

The service information referenced in

the proposed rule 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.

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:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed 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 above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed 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

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 98–NM–93–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–114, Attention: Rules Docket No.

98–NM–93–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

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

A319, A320, and A321 series airplanes.

The DGAC advises that it has received

two reports indicating that the forward

pintle pin of the main landing gear

(MLG) had migrated forward toward the

wing rear spar. In both instances, the

lock bolt and associated MLG barrel

bushings securing the pintle pin were

missing, which allowed the pintle pin to

migrate forward, although further

movement was prevented by the

incrementally tapered diameter of the

pintle pin. Initial investigations have

indicated that the probable cause of

migration of the pintle pin was due to

ineffective lubrication of the bearing of

the forward pintle pin, which caused

excess load on the lock bolt. The DGAC

further advises that backward migration

of the pintle pin also could occur,

which would allow the pintle pin to

become disengaged and separate from

the pintle pin bearing. Such

discrepancies of the pintle pin, if not

corrected, could result in collapse of the

MLG during landing.

Explanation of Relevant Service

Information

The manufacturer has issued Airbus

All Operator Telex (AOT) 32–17,

Revision 01, dated November 6, 1997,

which describes procedures for

repetitive detailed visual inspections for

discrepancies (rotation, wear, missing or

broken parts) of the lock bolt for the

pintle pin of the MLG, and follow-on

corrective actions, if necessary. The

corrective actions include replacement

of a discrepant lock bolt with a new or

serviceable part, followed by

relubrication of the pintle spherical

bearing. The DGAC classified this AOT

as mandatory and issued French

airworthiness directive 97–385–112(B),

dated December 17, 1997, in order to

assure the airworthiness of these

airplanes in France.
26112 Federal Register / Vol. 63, No. 91 /Tuesday, May 12, 1998 / Proposed Rules

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 21.29) 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

Proposed 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 proposed AD would require

accomplishment of the actions specified

in the AOT described previously.

Interim Action

This is considered to be interim

action until final action is identified, at

which time the FAA may consider

further rulemaking.

Cost Impact

The FAA estimates that 120 airplanes

of U.S. registry would be affected by this

proposed AD. It would take

approximately 1 work hour per airplane

to accomplish the proposed inspection,

at an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of the inspection proposed by

this AD on U.S. operators is estimated

to be $7,200, or $60 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted.

Regulatory Impact

The regulations proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Airbus Industrie: Docket 98–NM–93–AD.

Applicability: All Model A319, A320, and

A321 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 a rotated, damaged,

or missing lock bolt, which could result in

disengagement of the pintle pin from the

bearing, and consequent collapse of the main

landing gear (MLG) during landing,

accomplish the following:

(a) Perform a detailed visual inspection to

detect discrepancies (rotation, damage, and

absence) of the lock bolt for the pintle pin on

the MLG, in accordance with Airbus All

Operator Telex (AOT) 32–17, Revision 01,

dated November 6, 1997, at the latest of the

times specified in paragraphs (a)(1), (a)(2),

and (a)(3), of this AD. If any discrepancy is

detected, prior to further flight, perform

corrective actions, as applicable, in

accordance with the AOT. Repeat the

inspection thereafter at intervals not to

exceed 1,000 flight cycles or 15 months,

whichever occurs first.

(1) Within 30 months since the airplane’s

date of manufacture or prior to the

accumulation of 2,000 total flight cycles,

whichever occurs first.

(2) Within 15 months or 1,000 flight cycles

after the last gear replacement or

accomplishment of Airbus Industrie Service

Bulletin A320–32–1119, dated June 13, 1994,

whichever occurs first.

(3) Within 500 flight cycles after the

effective date of this AD.

(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 request through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(c) 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.

Note 3: The subject of this AD is addressed

in French airworthiness directive 97–385–

112(B), dated December 17, 1997.

Issued in Renton, Washington, on May 5,

1998.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–12511 Filed 5–11–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–123–AD]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328–100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).