Federal Register / Vol. 63, No. 136 /Thursday, July 16, 1998 /Rules and Regulations 38293

Issued in Renton, Washington, on July 8,

1998.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–18769 Filed 7–15–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94–NM–94–AD; Amendment

39–10657; AD 98–15–06]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320 and Model A321 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A320 and Model A321 series airplanes,

that requires repetitive inspections to

verify proper installation of the plain

bushings of the upper and lower

connection links on the forward and aft

passenger/crew doors, and correction of

discrepancies. This amendment also

requires installation of shouldered

bushings on the frame segment used for

attachment of the connection links or

modification of the frame segment

bushing (as applicable), which

terminates the repetitive inspection

requirements. This amendment is

prompted by a report that, during an

emergency evacuation of in-service

airplanes, the left aft passenger/crew

door jammed against the fuselage

structure in a nearly closed position due

to bushing migration. The actions

specified by this AD are intended to

prevent jamming of the passenger/crew

door, which could delay or impede the

evacuation of passengers during an

emergency.

DATES: Effective August 20, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 20,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

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: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Airbus

Model A320 and A321 series airplanes

was published as a supplemental notice

of proposed rulemaking (NPRM) in the

Federal Register on February 25, 1997

(62 FR 8408). That action proposed to

require repetitive inspections to verify

proper installation of the plain bushings

of the upper and lower connection links

on the forward and aft passenger/crew

doors, and correction of discrepancies.

That action also proposed to require

replacement of the shouldered bushing

on the locking mechanism with a new

oversized bushing or modification of the

frame segment bushing (as applicable),

which terminates the repetitive

inspection requirements.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Request to Revise Applicability

One commenter, Airbus, requests that

the applicability of the supplemental

NPRM be revised to specify that the AD

applies to (1) airplanes on which Airbus

Modification 24497 has not been

installed in production; and (2)

airplanes on which Airbus Service

Bulletin A320–52–1027, Revision 2,

dated February 18, 1993, Revision 3,

dated December 10, 1993, or Airbus

Service Bulletin A320–52–1064,

Revision 1, dated September 8, 1995,

has not been installed.

Airbus advises that installation of

Airbus Modification 22422 in

production is not equivalent to

accomplishment of Airbus Service

Bulletin A320–52–1027. (The

applicability of the supplemental NPRM

incorrectly equates Modification 22422

to Airbus Service Bulletin A320–52–

1027.) The commenter adds that

airplanes on which Airbus Service

Bulletin A320–52–1027 has been

accomplished are not affected by the

requirements of the supplemental

NPRM. The commenter states further

that Airbus Service Bulletin A320–52–

1064 must be accomplished on

airplanes on which Airbus Modification

22422 was installed in production.

The FAA concurs with the

commenter’s request. Installation of

shouldered bushings on the segment

frame is necessary in order to provide a

full solution and adequately address the

identified unsafe condition. Airbus

Modification 22422 installed in

production added interference fit plain

bushings, in place of plain bushings.

However, several occurrences of

migration of the bushings were reported

on those airplanes having Modification

22422 installed in production.

Subsequently, Airbus has developed a

further modification of the frame

segment bushing, which entails

removing the plain bushings and

installing shouldered bushings on the

frame used for attachment of the

connection links. Airbus Modification

24497 accomplishes this installation for

airplanes in production, using

interference fit shouldered bushings.

(For retrofit solutions, installation of the

shouldered bushings is accomplished

with Loctite sealant rather than

interference fit).

Airbus Service Bulletin A320–52–

1027 is the retrofit solution equivalent

to Modification 24497, to be

accomplished on those airplanes in a

pre-Modification 22422 configuration.

For those airplanes on which

Modification 22422 was installed in

production, installation of shouldered

bushings is also necessary, and is to be

accomplished in accordance with the

procedures described in Airbus Service

Bulletin A320–52–1064.

Accomplishment of the retrofit solution

described in A320–52–1027 or A320–

52–1064, as applicable, would terminate

the repetitive inspection requirements

of this AD. The FAA has revised the

applicability and paragraphs (a), (b), (c),

and (d) of the final rule to clarify the

effectivity of the AD.

Request to Extend Compliance Time

One commenter requests that the

compliance time for accomplishing the

initial detailed visual inspection be

extended from the proposed 450 flight

hours to 460 flight hours, and that the

repetitive interval be extended from the

proposed 900 flight hours to 920 flight

hours. The commenter states that such

an extension will allow the inspection

to be accomplished during a regularly

scheduled ‘‘A’’ and ‘‘2A’’ check, and

thereby eliminate any additional

expenses that would be associated with

special scheduling. The FAA does not

concur. In developing an appropriate

compliance time for this action, the
38294 Federal Register / Vol. 63, No. 136 /Thursday, July 16, 1998 /Rules and Regulations

FAA considered the safety implications,

parts availability, and normal

maintenance schedules for timely

accomplishment of the detailed visual

inspection. Since maintenance

schedules vary from operator to

operator, there would be no assurance

that the detailed visual inspection will

be accomplished during a regularly

scheduled ‘‘A’’ or ‘‘2A’’ check.

However, under the provisions of

paragraph (e) of the final rule, the FAA

may approve requests for adjustments to

the compliance time if data are

submitted to substantiate that such an

adjustment would provide an acceptable

level of safety.

Correction to the Supplemental NPRM

In paragraph (c) and in the Discussion

section of the supplemental NPRM, the

FAA made incorrect reference to the

modification involving shouldered

bushings, which would be required to

be accomplished in accordance with

Airbus Service Bulletin A320–57–1027,

Revision 3, dated December 10, 1993.

Although the supplemental NPRM

specifies ‘‘replacement of the

shouldered bushing on the locking

mechanism with a new oversized

bushing (Kit No. 521027A02)’’, the

modification entails installation of

shouldered bushings on the frame

segment used for attachment of the

connection links, as the service bulletin

specifies in reference to Kit No.

521027A02. Applicable portions of the

preamble and paragraph (c) of this final

rule have been revised to correctly

describe the installation of shouldered

bushings.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

The FAA estimates that 94 Airbus

Model A320 and Model A321 series

airplanes of U.S. registry will be affected

by this AD.

It will take approximately 6 work

hours per airplane to accomplish the

required detailed visual inspection, at

an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of the detailed visual inspection

required by this AD on U.S. operators is

estimated to be $33,840, or $360 per

airplane, per inspection cycle.

For certain airplanes, it will take

approximately 72 work hours per

airplane to accomplish the required

modification, at an average labor rate of

$60 per work hour. Required parts will

be supplied by the manufacturer at no

cost to the operators. Based on these

figures, the cost impact of the

modification required by this AD on

U.S. operators is estimated to be $4,320

per airplane.

For certain other airplanes, it will take

approximately 53 work hours per

airplane to accomplish the required

modification, at an average labor rate of

$60 per work hour. Required parts will

be supplied by the manufacturer at no

cost to the operators. Based on these

figures, the cost impact of the

modification required by this AD on

U.S. operators is estimated to be $3,180

per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the 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 adopted herein will

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 final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

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

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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:

98–15–06 Airbus Industrie: Amendment

39–10657. Docket 94–NM–94–AD.

Applicability: Model A320 and Model

A321 series airplanes, as listed below,

certificated in any category:

• On which Airbus Modification 24497

has not been installed in production. Or

• On which Airbus Service Bulletin A320–

52–1027, Revision 2, dated February 18,

1993, Revision 3, dated December 10, 1993,

or Airbus Service Bulletin A320–52–1064,

Revision 1, dated September 8, 1995; has not

been accomplished.

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 (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 prevent jamming of the passenger/crew

door, which could delay or impede the

evacuation of passengers during an

emergency, accomplish the following:

(a) For Model A320 series airplanes

on which Airbus Modification 22422

has not been installed in production:

Within 450 flight hours after the

effective date of this AD, perform a

detailed visual inspection to verify

proper installation of the plain bushings

of the upper and lower connection links

on the forward and aft passenger/crew

doors, in accordance with Airbus

Service Bulletin A320–52–1047, dated

April 25, 1994.

(1) If all bushings are installed properly,

repeat the inspection thereafter at intervals

not to exceed 900 flight hours until the

modification required by paragraph (c) of this

AD is accomplished.

(2) If any bushing has migrated, prior to

further flight, remove the passenger/crew

door and visually inspect the bushing to
Federal Register / Vol. 63, No. 136 /Thursday, July 16, 1998 /Rules and Regulations 38295

detect damage, in accordance with the

service bulletin.

(i) If the bushing housings are not

damaged, prior to further flight, reinstall the

bushing in accordance with the service

bulletin. Repeat the detailed visual

inspections of the bushings thereafter at

intervals not to exceed 450 flight hours until

the modification required by paragraph (c) of

this AD is accomplished.

(ii) If any bushing housing is damaged,

prior to further flight, ream the door structure

and install an oversize shouldered bushing,

in accordance with the service bulletin. If the

damage is not completely removed after

reaming, prior to further flight, repair the

bushing housing in accordance with a

method approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate.

(b) For Model A320 and Model A321 series

airplanes on which Airbus Modification

22422 has been installed in production:

Within 450 flight hours after the effective

date of this AD, perform a detailed visual

inspection to verify proper installation of the

plain bushings of the upper and lower

connection links (2 bushings per door), in

accordance with Airbus All Operators Telex

AOT 52–07, dated July 28, 1994, or Airbus

Service Bulletin A320–52–1066, dated March

6, 1995.

(1) If the bushings are installed properly,

repeat the detailed visual inspection

thereafter at intervals not to exceed 900 flight

hours, until the modification required by

paragraph (d) of this AD is accomplished.

(2) If any bushing is found to be

improperly installed, prior to further flight,

modify the frame segment bushings in

accordance with Airbus Service Bulletin

A320–52–1064, Revision 1, dated September

8, 1995. Accomplishment of the modification

constitutes terminating action for the

requirements of this AD.

(c) For Model A320 series airplanes on

which Airbus Modification 22422 has not

been installed in production: Within 3,500

flight hours after the effective date of this AD,

install shouldered bushings on the frame

segment used for attachment of the

connection links (Kit No. 521027A02), in

accordance with Airbus Service Bulletin

A320–52–1027, Revision 3, dated December

10, 1993. Accomplishment of this

modification constitutes terminating action

for the repetitive inspection requirements of

paragraph (a) of this AD.

Note 2: Replacement in accordance with

Airbus Service Bulletin A320–52–1027,

Revision 2, dated February 18, 1993, is

considered acceptable for compliance with

the requirements of paragraph (c) of this AD.

(d) For Model A320 and Model A321 series

airplanes on which Airbus Modification

22422 has been installed in production:

Within 15 months after the effective date of

this AD, modify the frame segment bushing

in accordance with Airbus Service Bulletin

A320–52–1064, Revision 1, dated September

8, 1995. Accomplishment of the modification

constitutes terminating action for the

repetitive detailed visual inspection

requirements of paragraph (b) 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,

International Branch, ANM–116, 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, International Branch,

ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(f) Special flight permits may be issued in

accordance with §§ 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.

(g) Except for the repair action provided in

paragraph (a)(2)(ii), the actions shall be done

in accordance with the following Airbus

Service Bulletins and All Operators Telex

(AOT), which contain the specified list of

effective pages:

Service bulletin and AOT referenced and date Page No. Rrevision level

shown on page Date shown on page

Service Bulletin A320–52–1047, April 25, 1994 ............................. 1–15 ............................................ Original ............. April 25, 1994.

AOT 52–07, July 28, 1994 .............................................................. 1–2 .............................................. Original ............. July 28, 1994.

Service Bulletin A320–52–1066, March 6, 1995. ........................... 1–13 ............................................ Original ............. March 6, 1995.

Service Bulletin A320–52–1064, Revision 1, September 8, 1995. 1–4, 8, 21 ....................................

5–7, 9–20 ....................................

1 .......................

Original .............

September 8, 1995.

November 28, 1994.

Service Bulletin A320–53–1027, Revision 3, December 10, 1993 1–6, 8, 11, 18, 19 .......................

37–42 ..........................................

3 ....................... December 10, 1993.

7, 12, 14–17, 20–36 .................... 1 ....................... September 25, 1992

9, 10 ............................................ Original ............. January 30, 1992.

13 ................................................ 2 ....................... February 18, 1993.

This incorporation by reference was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Note 4: The subject of this AD is addressed

in French airworthiness directive 93–207–

048(B), dated December 8, 1993.

(h) This amendment becomes effective on

August 20, 1998.

Issued in Renton, Washington, on July 8,

1998.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–18768 Filed 7–15–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–92–AD; Amendment 39–

10664; AD 98–15–13]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Aircraft Company 90, 100, 200, and 300

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Raytheon Aircraft

Company (Raytheon) 90, 100, 200, and

300 series airplanes (formerly known as

Beech Aircraft Corporation 90, 100, 200,