Federal Register / Vol. 62, No. 230 / Monday, December 1, 1997 / Proposed Rules 63475

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–114–AD]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328–100 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 Dornier Model 328–100 series

airplanes. This proposal would require

removal and replacement of the center

screw of the crew seat belt buckle. 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 failure of the center

screw of the crew seat belt buckle,

which could result in injury to the

flightcrew during an emergency landing.

DATES: Comments must be received by

December 31, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

114–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

Dornier Luftfahrt GmbH, P.O. Box 1103,

D–82230, Wessling, Germany. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

FOR FURTHER INFORMATION CONTACT:

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–114–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–103, Attention: Rules Docket No.

97–NM–114–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Luftfahrt-Bundesamt (LBA),

which is the airworthiness authority for

Germany, notified the FAA that an

unsafe condition may exist on certain

Dornier Model 328–100 series airplanes.

The LBA advises that it has received a

report indicating that, during an

inspection, the center fixing screw of

the flight crew restraint system was

found to be loose. Investigation revealed

that, during assembly of the release

buckles, the center fixing screw could

be contaminated, which would prevent

the securing Loctite from curing. This

condition, if not corrected, could result

in injury to the flightcrew during an

emergency landing.

Explanation of Relevant Service

Information

Dornier has issued Service Bulletin

SB–328–25–196, dated November 12,

1996, which describes procedures for

removal and replacement of the center

screw of the crew seat belt buckle. (The

Dornier service bulletin references

Aerospace Restraint Company (ARC)

Service Bulletin 1180002–25–01, dated

October 11, 1996, as an additional

source of service information for

accomplishment of the removal and

replacement.) Accomplishment of the

actions specified in the service bulletin

is intended to adequately address the

identified unsafe condition. The LBA

classified this service bulletin as

mandatory and issued German

airworthiness directive 97–001, dated

January 16, 1997, in order to assure the

airworthiness of these airplanes in

Germany.

FAA’s Conclusions

This airplane model is manufactured

in Germany 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 LBA has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the LBA,

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 actions specified in

the service bulletin described

previously.

Cost Impact

The FAA estimates that 50 airplanes

of U.S. registry would be affected by this

proposed AD. It would take

approximately 1 work hour per airplane

to accomplish the proposed

replacement, at an average labor rate of

$60 per work hour. Required parts

would be provided by the manufacturer

at no cost to the operators. Based on

these figures, the cost impact of the

replacement proposed by this AD on

U.S. operators is estimated to be $3,000,

or $60 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
63476 Federal Register / Vol. 62, No. 230 / Monday, December 1, 1997 / Proposed Rules

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:

Dornier Luftfahrt GmbH: Docket 97–NM–

114–AD.

Applicability: Model 328–100 series

airplanes equipped with Aerospace Restraint

Company (ARC) restraints having part

number (P/N) 1180002–403–100, part serial

number 0101 up to and including 0315

inclusive, 0328, and 0329; 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 failure of the screw of the crew

seat belt buckle, which could result in injury

to the flightcrew during an emergency

landing, accomplish the following:

(a) Within 90 days after the effective date

of this AD, remove and replace the center

screw of the crew seat belt buckle in

accordance with Dornier Service Bulletin

SB–328–25–196, dated November 12, 1996.

Note 2: The Dornier service bulletin

references Aerospace Restraint Company

(ARC) Service Bulletin 1180002–25–01,

dated October 11, 1996, as an additional

source of service information for

accomplishment of the removal and

replacement.

(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, FAA,

Transport Airplane Directorate. Operators

shall submit their request 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.

(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 4: The subject of this AD is addressed

in German airworthiness directive 97–001,

dated January 16, 1997.

Issued in Renton, Washington, on

November 21, 1997.

Stewart R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–31332 Filed 11–28–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–152–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320–111, –211, –212, –214, –231,

–232, and –233 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

Airbus Model A320–111, –211, –212,

–214, –231, –232, and –233 series

airplanes. This proposal would require

repetitive ultrasonic inspections to

detect fatigue cracking in the wing/

fuselage joint cruciform fittings, and

corrective actions, if necessary. 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 detect and correct fatigue

cracks on the wing/fuselage joint

cruciform fittings, which could result in

reduced structural integrity of the wing/

fuselage.

DATES: Comments must be received by

December 31, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

152–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:

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.