38120 Federal Register / Vol. 63, No. 135 /Wednesday, July 15, 1998 / Proposed Rules

effective date of this AD: Inspect prior to the

accumulation of 25,500 total flight cycles, or

within 1,000 flight cycles after the effective

date of this AD, whichever occurs first.

(4) For airplanes that have accumulated

25,000 or more total flight cycles as of the

effective date of this AD: Inspect within 500

flight cycles after the effective date of this

AD.

(b) If no crack is detected during any

inspection required by paragraph (a) of this

AD, repeat the HFEC inspection thereafter at

intervals not to exceed 3,000 flight cycles.

(c) If any crack is detected during any

inspection required by paragraph (a) of this

AD, prior to further flight, repair in

accordance with Boeing Alert Service

Bulletin 747–53A2414, dated August 7, 1997.

Note 2: The alert service bulletin

emphasizes the importance of performing an

open hole HFEC inspection of the inner

chord of the frame within 6.0 inches of the

web or doubler crack (as applicable), if the

inner chord of the frame is not replaced

concurrently with the web and doubler

repair.

(d) Accomplishment of the repair or

preventative modification specified in Boeing

Alert Service Bulletin 747–53A2414, dated

August 7, 1997, constitutes terminating

action for the repetitive inspection

requirements of this AD for that repaired/

modified edge frame web and doubler.

(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

Aircraft Certification Office (ACO), 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, Seattle ACO.

Note 3: 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. 98–18778 Filed 7–14–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–51–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 767 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 Boeing Model 767 series

airplanes. This proposal would require

detailed visual inspections to detect

corrosion or chrome plating cracks on

the fuse pins, load distribution plates,

and bushings of the outboard support of

the main landing gear (MLG) beam. This

proposal also would require either

installation of the existing fuse pins and

repetitive inspections; or installation of

newer-type fuse pins, which would

constitute terminating action for the

repetitive inspections. This proposal is

prompted by a report indicating that

corrosion was found on a fuse pin in the

outboard support of the MLG beam. The

actions specified by the proposed AD

are intended to detect and correct such

corrosion and cracking, which could

result in the failure of a fuse pin and,

consequently, lead to collapse of the

MLG.

DATES: Comments must be received by

August 31, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97–NM–

51–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

Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington

98124–2207. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

James G. Rehrl, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington; telephone (425) 227–2783;

fax (425) 227–1181.

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–51–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–51–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received a report of

corrosion on a fuse pin in the outboard

support of the main landing gear (MLG)

beam on a Boeing Model 767 series

airplane. At the time the corrosion was

detected, the airplane had accumulated

23,637 total flight hours and 5,652 total

flight cycles. Investigation revealed that

the chrome plating on the fuse pin did

not have a sufficient bond to the base

metal, which allowed the chrome plate

to crack and peel from the base metal.

This cracking in the chrome plate

allowed moisture to accumulate in the

subject area and, consequently, caused

corrosion on the base metal of the fuse

pin. Such cracking and corrosion, if not

detected and corrected, could result in
Federal Register / Vol. 63, No. 135 /Wednesday, July 15, 1998 / Proposed Rules 38121

failure of a fuse pin and, consequently,

lead to collapse of the MLG.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Alert Service Bulletin 767–

57A0054, Revision 2, dated April 18,

1996, which describes procedures for

detailed visual inspections to detect

corrosion or chrome plating cracks on

the fuse pins of the outboard support of

the MLG beam. The alert service

bulletin also describes procedures for

either installation of existing 4330M

steel fuse pins and repetitive detailed

visual inspections; or installation of

newer-type 15–5PH CRES fuse pins,

which would eliminate the need for the

repetitive inspections. The alert service

bulletin also describes procedures for

inspections of the load distribution

plates and fuse pin bushings to detect

corrosion. These latter parts make up a

portion of the MLG outboard support

fitting assembly into which the fuse

pins are installed. Accomplishment of

the actions specified in the alert service

bulletin is intended to adequately

address the identified unsafe condition.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the proposed AD would

require accomplishment of the actions

specified in the alert service bulletin

described previously, except as

discussed below.

Differences Between the Proposed Rule

and the Relevant Service Information

Operators should note that, although

the alert service bulletin specifies that

the manufacturer may be contacted for

disposition of certain repair conditions,

this proposal would require that the

repair of those conditions to be

accomplished in accordance with a

method approved by the FAA.

Also, whereas the alert service

bulletin uses the term ‘‘close visual

inspection,’’ this proposal uses the more

common term ‘‘detailed visual

inspection.’’ For the purpose of this

proposal, the two terms are considered

to be synonymous.

Cost Impact

There are approximately 609 Boeing

Model 767 series airplanes of the

affected design in the worldwide fleet.

The FAA estimates that 151 airplanes of

U.S. registry would be affected by this

proposed AD, that it would take

approximately 4 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the cost impact of this proposed

AD on U.S. operators is estimated to be

$36,240, or $240 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:

Boeing: Docket 97–NM–51–AD.

Applicability: Model 767 series airplanes,

line numbers 1 through 609 inclusive,

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 (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 detect and correct cracking and

corrosion of the fuse pins, load distribution

plates, and bushings in the outboard support

of the main landing gear (MLG) beam, which

could result in the failure of a fuse pin and,

consequently, lead to collapse of the MLG,

accomplish the following:

(a) Within 4 years of service since the MLG

was new, or within 18 months after the

effective date of this AD, whichever occurs

later, perform detailed visual inspections of

the fuse pins of the MLG outboard support

beam to detect corrosion or chrome plating

cracks on the fuse pin, and of the load

distribution plates and bushings of the MLG

outboard support beam to detect corrosion; in

accordance with the Accomplishment

Instructions of Boeing Alert Service Bulletin

767–57A0054, Revision 2, dated April 18,

1996.

(b) If any corrosion or plating crack of a

fuse pin is found during any inspection

required by paragraph (a) of this AD, prior to

further flight, accomplish either paragraph

(b)(1) or (b)(2) of this AD.

(1) Install a new or serviceable 4330M steel

fuse pin in accordance with the

Accomplishment Instructions of Boeing Alert

Service Bulletin 767–57A0054, Revision 2,

dated April 18, 1996. Repeat the detailed

visual inspections required by paragraph (a)

of this AD thereafter at intervals not to

exceed 48 months. Or

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

pin in accordance with the Accomplishment

Instructions of Boeing Alert Service Bulletin

767–57A0054, Revision 2, dated April 18,

1996. Accomplishment of this installation

constitutes terminating action for the

repetitive inspection requirements of

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

(c) If any corrosion of a load distribution

plate or bushing is found during any

inspection required by paragraph (a) or (b) of

this AD, prior to further flight, repair in

accordance with a method approved by the

Manager, Seattle Aircraft Certification Office

(ACO), FAA, Transport Airplane Directorate.

(d) If no corrosion or plating crack is found

on the fuse pins, load distribution plates, or

bushings, prior to further flight, accomplish

the requirements of either paragraph (d)(1) or

(d)(2) of this AD in accordance with the

Accomplishment Instructions of Boeing Alert
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