26104 Federal Register / Vol. 63, No. 91 /Tuesday, May 12, 1998 / Proposed Rules

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–156–AD.

Applicability: Model A320 series airplanes

on which Airbus Modification 21778

(reference Airbus Service Bulletin A320–53–

1072, dated November 7, 1995, as revised by

Change Notice 0A, dated July 5, 1996) has

not been accomplished, 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 (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 correct fatigue cracking in the inner

flange of door frame 66, left and right, 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 1 year after the

effective date of this AD, whichever occurs

later: Perform a rotating probe eddy current

inspection to detect cracking around the

edges of the gusset plate attachment holes of

the inner flange of door frame 66, left and

right, at stringer positions P18, P20, P22,

P18′, P20′, and P22′, in accordance with

Airbus Service Bulletin A320–53–1071,

dated November 7, 1995, as revised by

Change Notice 0A, dated July 5, 1996. If any

crack is detected, prior to further flight,

repair in accordance with a method approved

by the Manager, International Branch, ANM–

116, FAA, Transport Airplane Directorate.

Repeat the inspection thereafter at intervals

not to exceed 20,000 flight cycles.

(b) Modification of the gusset plate

attachment holes of the inner flange of door

frame 66, left and right (Airbus Modification

21778), in accordance with Airbus Service

Bulletin A320–53–1072, dated November 7,

1995, as revised by Change Notice 0A, dated

July 5, 1996, constitutes terminating action

for the repetitive inspection requirements of

this AD.

(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 96–234–

087(B), dated October 23, 1996.

Issued in Renton, Washington, on May 5,

1998.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–12518 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–37–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 757–200 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

certain Boeing Model 757–200 series

airplanes. This proposal would require

modifications to the attachment

installation of the forward lavatory. This

proposal is prompted by a stress

analysis report indicating that the

forward lavatory could break free from

the upper and/or lower attachments

during an emergency landing. The

actions specified by the proposed AD

are intended to prevent failure of the

attachment installation of the forward

lavatory during an emergency landing,

which could result in injury to the crew

and passengers.

DATES: Comments must be received by

June 26, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

37–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:

Keith Ladderud, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Transport Airplane Directorate, Seattle

Aircraft Certification Office, 1601 Lind

Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2780;

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 98–NM–37–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,
Federal Register / Vol. 63, No. 91 /Tuesday, May 12, 1998 / Proposed Rules 26105

ANM–114, Attention: Rules Docket No.

98–NM–37–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

While reviewing a stress analysis for

the attachment installation of the

forward lavatory on the Boeing Model

757–200 series airplane to add airlinerequested variations, Boeing discovered

a discrepancy with the analysis. The

stress analysis, when corrected,

indicated that the current design was

not strong enough to withstand a 9g

forward emergency landing. As a result,

the upper attachment installation of the

forward lavatory of passenger airplanes

and the lower attachment installation of

the forward lavatory of freighter

airplanes do not meet the certification

requirements for the ultimate load

specifications of the forward lavatory.

Furthermore, the stress analysis report

indicated that the forward lavatory

could break free at the upper and/or

lower attachments during an emergency

landing. Failure of the attachment

installation of the forward lavatory

during an emergency landing could

result in injury to the crew and

passengers.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Service Bulletin 757–25–0181,

dated June 26, 1997, which describes

procedures for installation of a doubler

to the upper attachment installation of

the forward lavatory on passenger

airplanes. The FAA also has reviewed

and approved Boeing Alert Service

Bulletin 757–25A0187, dated September

18, 1997, which describes procedures

for installation of floor panel inserts, a

retention fitting assembly, and a doubler

assembly to the lower attachment

installation of the forward lavatory on

freighter airplanes. Accomplishment of

the modifications specified in the

service bulletins 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

modifications specified in the service

bulletins described previously.

Cost Impact

There are approximately 333

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

225 airplanes of U.S. registry would be

affected by this proposed AD: 164

passenger airplanes and 61 freighter

airplanes.

It would take approximately 10 work

hours per passenger airplane to

accomplish the proposed modification,

at an average labor rate of $60 per work

hour. Required parts would cost

approximately $100 per airplane. Based

on these figures, the cost impact of this

proposed modification on U.S. operators

is estimated to be $114,800, or $700 per

passenger airplane.

It would take approximately 42 work

hours per freighter airplane to

accomplish the proposed modification,

at an average labor rate of $60 per work

hour. Required parts would be provided

by the airplane manufacturer at no cost

to the operators. Based on these figures,

the cost impact of this proposed

modification on U.S. operators is

estimated to be $153,720, or $2,520 per

freighter airplane.

The cost impact figures discussed

above are 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 98–NM–37–AD.

Applicability: Model 757–200 series

airplanes; as listed in Boeing Service Bulletin

757–25–0181, dated June 26, 1997, and

Boeing Alert Service Bulletin 757–25A0187,

dated September 18, 1997; 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 (d) 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 failure of the attachment

installation of the forward lavatory during an

emergency landing, which could result in

injury to the crew and passengers,

accomplish the following:

(a) For passenger airplanes identified in

Boeing Service Bulletin 757–25–0181, dated

June 26, 1997: Within 18 months after the

effective date of this AD, install a doubler to

the upper attachment installation of the

forward lavatory in accordance with Boeing

Service Bulletin 757–25–0181, dated June 26,

1997.

(b) For freighter airplanes identified in

Boeing Alert Service Bulletin 757–25A0187,

dated September 18, 1997: Within 18 months

after the effective date of this AD, install floor

panel inserts, a retention fitting assembly,

and a doubler assembly to the lower

attachment installation of the forward

lavatory, in accordance with Boeing Alert

Service Bulletin 757–25A0187, dated

September 18, 1997.

(c) As of the effective date of this AD, no

person shall install a floor panel, part

number 141N5410–12 or 141N5410–28, on

any airplane.

(d) An alternative method of compliance or

adjustment of the compliance time that
26106 Federal Register / Vol. 63, No. 91 /Tuesday, May 12, 1998 / Proposed Rules

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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(e) 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 May 5,

1998.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–12517 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–44–AD]

RIN 2120–AA64

Airworthiness Directives; Aerospatiale

Model ATR42 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 Aerospatiale Model ATR42

series airplanes. This proposal would

require modification of the electrical

power supply for the standby horizon

indicator. 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 loss of the

standby horizon indicator in the event

of failure of emergency direct current

(DC) power, which could result in

reduced controllability of the airplane

during instrument flight rules

conditions.

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–

44–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

Aerospatiale, 316 Route de Bayonne,

31060 Toulouse, Cedex 03, 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–44–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–44–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

Aerospatiale Model ATR42 series

airplanes. The DGAC advises that an

operator experienced an aborted takeoff

that was attributed to loss of power at

the direct current (DC) emergency

(EMER) bus, which disabled the standby

horizon indicator. The present

configuration does not supply electrical

power for the standby horizon indicator

from two independent sources, which

could result in the loss of the standby

horizon indicator in the event of failure

of emergency DC power. This condition,

if not corrected, could result in reduced

controllability of the airplane during

instrument flight rules conditions.

Explanation of Relevant Service

Information

The manufacturer has issued Avions

de Transport Regional Service Bulletin

ATR42–34–0090, Revision 1, dated

April 22, 1997, which describes

procedures for modifying the electrical

power supply for the standby horizon

indicator. This modification would

involve installation of relays in certain

electrical panels and modification of

wiring, so that power to the standby

horizon indicator can be supplied from

two independent sources.

Accomplishment of the action 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

96–230–066(B), dated October 23, 1996,

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

action is necessary for products of this

type design that are certificated for

operation in the United States.