26102 Federal Register / Vol. 63, No. 91 /Tuesday, May 12, 1998 / Proposed Rules

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Boeing: Docket 96–NM–171–AD.

Applicability: Model 747–400, –400D, and

–400F series airplanes; as identified in

Boeing Alert Service Bulletin 747–21A2381,

dated June 27, 1996; 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 (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 prevent loss of control of the cabin

pressurization system, which could result in

rapid depressurization of the airplane and

consequent deleterious physiological effects

on the passengers and crew; and airplane

diversions, which represent an increased risk

to the airplane, passengers, and crew;

accomplish the following:

(a) Within 180 days after the effective date

of this AD: Modify the P212 and P213 panels

of the cabin pressure control system as

specified in paragraph (a)(1) or (a)(2) of this

AD, as applicable, in accordance with Boeing

Alert Service Bulletin 747–21A2381, dated

June 27, 1996.

(1) For Groups 1 through 7 airplanes, as

identified in the alert service bulletin:

Change the wiring in the P212 and P213

panels; replace the existing two-pole relays

with new four-pole relays; and perform a test

of both panels.

(2) For Group 8 airplanes, as identified in

the alert service bulletin: Change the wiring

in the P212 panel; replace the existing twopole relays with new four-pole relays; replace

the existing P213 panel with a new P213

panel; and perform a test of both panels.

(b) For airplanes having line positions 696

through 1021 inclusive: Within 180 days

after the effective date of this AD, accomplish

paragraphs (b)(1) and (b)(2), as applicable, of

this AD; in accordance with Boeing Service

Bulletin 747–24–2193, dated January 25,

1995; as revised by Notices of Status Change

(NSC) 747–24–2193 NSC 1, dated April 13,

1995, 747–24–2193 NSC 2, dated October 5,

1995, 747–24–2193 NSC 3, dated November

22, 1995, 747–24–2193 NSC 4, dated

December 21, 1995, 747–24–2193 NSC 5,

dated May 2, 1996, and 747–24–2193 NSC 6,

dated March 13, 1997; or Alert Service

Bulletin 747–24A2193, Revision 1, dated

June 19, 1997.

(1) For all airplanes: Modify the wiring of

the P5, P6, and P7 panels; modify the wiring

in the W4701 and W4908 wire bundles; and

install diodes in the P6 panel.

(2) For Groups 1 and 2 airplanes identified

in paragraph I. of the Accomplishment

Instructions of the service bulletin or alert

service bulletin: Modify the wiring in the

W4703 wire bundle.

(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, 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.

(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.

Issued in Renton, Washington, on May 5,

1998.

D. L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–12520 Filed 5–11–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–156–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320 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

repetitive inspections to detect cracking

in the inner flange of door frame 66, and

corrective actions, if necessary. This

proposal also would provide for an

optional terminating action for the

repetitive inspections. 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 correct such fatigue

cracking, which could result in reduced

structural integrity of the airplane.

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. 97–NM–

156–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, 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–156–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
Federal Register / Vol. 63, No. 91 /Tuesday, May 12, 1998 / Proposed Rules 26103

FAA, Transport Airplane Directorate,

ANM–114, Attention: Rules Docket No.

97–NM–156–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, during fatigue testing on a

Model A320 test article, between 60,500

and 85,700 flight cycles, three cracks

developed on the inner flange of door

frame 66 at stringer 18 and stringer 20.

The cracks were located around the

edges of the gusset plate attachment

holes of the inner flange of door frame

66, which, during routine visual

inspection, would be hidden by the

gusset plates. 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

A320–53–1071, dated November 7,

1995, as revised by Change Notice 0A,

dated July 5, 1996. This service bulletin

describes procedures for repetitive

rotating probe eddy current inspections

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′. The DGAC

classified this service bulletin as

mandatory and issued French

airworthiness directive 96–234–087(B),

dated October 23, 1996, in order to

assure the continued airworthiness of

these airplanes in France.

Accomplishment of the actions

specified in the service bulletin is

intended to adequately address the

identified unsafe condition.

Airbus also has issued Service

Bulletin A320–53–1072, dated

November 7, 1995, as revised by Change

Notice 0A, dated July 5, 1996. This

service bulletin describes procedures for

modification of the gusset plate

attachment holes. The modification

involves cold working the attachment

holes of the inner flange of door frame

66, left and right, at stringer positions

P18, P20, P22, P18′, P20′, and P22..

Accomplishment of the modification

would eliminate the need for the

repetitive inspections. The DGAC has

approved this service bulletin.

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.

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 Service Bulletin A320–53–1071

described previously, except as

described in the following section. This

proposed AD also would provide for

optional terminating action for the

repetitive inspections.

Operators should note that, in

consonance with the findings of the

DGAC, the FAA has determined that the

repetitive inspections proposed by this

AD can be allowed to continue in lieu

of accomplishment of a terminating

action. In making this determination,

the FAA considers that, in this case,

long-term continued operational safety

will be adequately assured by

accomplishing the repetitive inspections

to detect cracking before it represents a

hazard to the airplane.

Differences Between the Proposed AD

and the Foreign Service Information

The proposed AD would differ from

the previously described Airbus service

bulletins and French airworthiness

directive, which specify that Airbus be

contacted for a repair solution for

cracking detected during an inspection.

In the proposed AD, however, repair of

any crack would be required to be

accomplished in accordance with a

method approved by the FAA.

Also, operators should note that,

unlike the procedures described in

Airbus Service Bulletin A320–53–1071,

this proposed AD would not permit

further flight if cracks are detected

around the edges of the gusset plate

attachment holes of the inner flange of

door frame 66. The FAA has determined

that, because of the safety implications

and consequences associated with such

cracking, any subject attachment hole

that is found to have cracking must be

repaired or modified prior to further

flight.

Cost Impact

The FAA estimates that 132 airplanes

of U.S. registry would be affected by this

proposed AD.

It would take approximately 8 work

hours 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 $63,360, or

$480 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.

Should an operator elect to

accomplish the proposed modification,

it would take approximately 5 work

hours per airplane to accomplish the

actions, at an average labor rate of $60

per work hour. Based on these figures,

the cost impact of the modification

proposed by this AD on U.S. operators

is estimated to be $300 per airplane.

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
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,