38122 Federal Register / Vol. 63, No. 135 /Wednesday, July 15, 1998 / Proposed Rules

Service Bulletin 767–57A0054, Revision 2,

dated April 18, 1998.

(1) Install the existing 4330M steel fuse

pins in accordance with the Accomplishment

Instructions of the alert service bulletin.

Repeat the detailed visual inspections

required by paragraph (a) of this AD

thereafter at intervals not to exceed 48

months. Or

(2) Install newer-type 15–5PH CRES fuse

pins in accordance with the Accomplishment

Instructions of the alert service bulletin.

Accomplishment of this installation

constitutes terminating action for the

repetitive inspection requirements of

paragraphs (a), (b)(1), and (d)(1) of this AD.

(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, Seattle

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Seattle ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(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.

Issued in Renton, Washington, on July 8,

1998.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–18777 Filed 7–14–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–159–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320–111, –211, and –231 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

certain Airbus Model A320 series

airplanes. This proposal would require

modification of certain fastener holes on

the outer frames of the fuselage, and

installation of new, improved fasteners.

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 prevent fatigue cracking of

certain fastener holes on the outer

frames of the fuselage, which could

result in reduced structural integrity of

the airplane.

DATES: Comments must be received by

August 14, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97–NM–

159–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 97–NM–159–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.

97–NM–159–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 certain Airbus

Model A320 series airplanes. The DGAC

advises that it has received a report

indicating that cracking was detected

during fatigue testing of a test article

after 78,000 simulated flights. This

cracking was found at the fastener holes

located at fuselage frame 35 between

left-and right-hand stringers 30 and 31.

Such fatigue cracking, if not corrected,

could result in reduced structural

integrity of the airplane.

Explanation of Relevant Service

Information

Airbus has issued Service Bulletin

A320–53–1137, dated June 24, 1997,

which describes procedures for a

modification that entails removing

existing fasteners located at fuselage

frame 35 between the left- and righthand stringers 30 and 31, performing a

rotating probe inspection of the fastener

holes to detect any cracking, modifying

the fastener holes, and installing new,

improved fasteners. Accomplishment of

the actions specified in the service

bulletin is intended to adequately

address the identified unsafe condition.

The DGAC classified this service

bulletin as mandatory and issued

French airworthiness directive 98–154–

113(B), dated April 8, 1998, in order to

assure the continued airworthiness of

these airplanes in France.

FAA’s Conclusions

This airplane model is manufactured

in France and is 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
Federal Register / Vol. 63, No. 135 /Wednesday, July 15, 1998 / Proposed Rules 38123

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 service bulletin described

previously, except as discussed below.

Differences Between Proposed Rule and

Service Bulletin

Operators should note that, although

the service bulletin specifies that the

manufacturer may be contacted for

disposition of certain repair conditions,

this proposal would require the repair of

those conditions to be accomplished in

accordance with a method approved by

either the FAA or the Direction Ge ́ne ́rale

de l’Aviation Civile (or its delegated

agent).

Cost Impact

The FAA estimates that 9 airplanes of

U.S. registry would be affected by this

proposed AD, that it would take

approximately 6 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Required parts

would cost approximately $390 per

airplane. Based on these figures, the cost

impact of the proposed AD on U.S.

operators is estimated to be $6,750, or

$750 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 97–NM–159–AD.

Applicability: Model A320–111, –211,

and –231 series airplanes, on which

Airbus Modification 20903 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 (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 prevent fatigue cracking of certain

fastener holes on the outer frames of the

fuselage, which could result in reduced

structural integrity of the airplane,

accomplish the following:

(a) Prior to the accumulation of 20,000 total

flight cycles, or within 4,000 flight cycles

after the effective date of this AD, whichever

occurs later, remove the existing fasteners

located at fuselage frame 35 between the leftand right-hand stringers 30 and 31, and

perform a rotating probe inspection to detect

fatigue cracking of the fastener holes, in

accordance with Airbus Service Bulletin

A320–53–1137, dated June 24, 1997.

(1) If no cracking is detected, prior to

further flight, modify the fastener holes and

install new, improved fasteners, in

accordance with the service bulletin.

(2) If any cracking is detected, 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).

(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. 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.

(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 98–154–

113(B), dated April 8, 1998.

Issued in Renton, Washington, on July 8,

1998.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–18776 Filed 7–14–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–227–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 727–200 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

Boeing Model 727–200 series airplanes.

This proposal would require repetitive

inspections to detect cracks in certain

areas between the upper and lower sills

of the number 1 cargo door, and repair,