31380 Federal Register / Vol. 63, No. 110 /Tuesday, June 9, 1998 / Proposed Rules

New Requirements of This AD

(e) Within 6 months after the effective

date of this AD, install new MLG shock

strut upper and lower attachment pins

in accordance with Canadair Regional

Jet Service Bulletin S.B. 601R–32–065,

dated November 11, 1996.

Accomplishment of this installation

constitutes terminating action for the

repetitive inspections required by

paragraphs (b) and (c) of this AD.

Note 4: The Canadair service bulletin

references Messier-Dowty Service Bulletin

M–DT 17002–32–12, dated November 6,

1996, as an additional source of service

information to accomplish the installation.

(f)(1) 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, New York

Aircraft Certification Office (ACO), FAA,

Engine and Propeller Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, New York ACO.

(2) Alternative methods of compliance,

approved previously in accordance with AD

96–22–14, amendment 39–9803, are

approved as alternative methods of

compliance with this AD.

Note 5: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

(g) 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 6: The subject of this AD is addressed

in Canadian airworthiness directive CF–96–

12R1, dated January 29, 1997.

Issued in Renton, Washington, on June 3,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–15252 Filed 6–8–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–151–AD]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB 2000 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 Saab Model SAAB 2000 series

airplanes. This proposal would require

a one-time inspection for cracking of the

rear pressure bulkhead; and installation

of a reinforcement angle on the rear

pressure bulkhead; or repair, 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 prevent cracking of the

rear pressure bulkhead, which could

result in sudden loss of cabin pressure

and the inability to withstand fail-safe

loads.

DATES: Comments must be received by

July 9, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

151–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

Saab Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈ping,

Sweden. 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–151–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–151–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Luftfartsverket (LFV), which is

the airworthiness authority for Sweden,

notified the FAA that an unsafe

condition may exist on certain Saab

Model SAAB 2000 series airplanes. The

LFV advises that, during full-scale

fatigue testing on a test article, a crack

was detected on the radius of the lower

forward flange that connects the rear

pressure bulkhead to the fuselage skin.

The crack occurred when the test article

reached 68,000 simulated flights. The

LFV further advises that reinforcement

of the lower forward flange area that

connects the rear pressure bulkhead to

the fuselage skin is required to meet the

design life of the airplane. Such

cracking, if not corrected, could result

in sudden loss of cabin pressure and the

inability to withstand fail-safe loads.

Explanation of Relevant Service

Information

The manufacturer has issued SAAB

Service Bulletin 2000–53–026, dated

February 27, 1998, which describes

procedures for a one-time inspection to

detect cracking of the rear pressure

bulkhead in the area of the lower

forward flange that connects to the

fuselage skin. Additionally, for

airplanes on which no cracking is

found, the service bulletin describes

procedures for installation of a

reinforcement angle on the rear pressure

bulkhead in the area of the lower

forward flange that connects to the

fuselage skin. Accomplishment of the

actions specified in the service bulletin

is intended to adequately address the

identified unsafe condition. The LFV

classified this service bulletin as

mandatory and issued Swedish

airworthiness directive 1–122, dated

March 2, 1998, in order to assure the
Federal Register / Vol. 63, No. 110 /Tuesday, June 9, 1998 / Proposed Rules 31381

continued airworthiness of these

airplanes in Sweden.

FAA’s Conclusions

This airplane model is manufactured

in Sweden 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 LFV has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the LFV,

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, except as discussed below.

Differences Between Proposed Rule and

Service Bulletin

Operators should note that although

the service bulletin specifies that the

manufacturer may be contacted for

disposition of cracks, this proposal

would require the repair of those cracks

be accomplished in accordance with a

method approved by either the Manager,

International Branch, ANM–116, FAA

Transport Directorate; or the LFV (or its

delegated agent). In light of the type of

repair that would be required to address

the identified unsafe condition, and in

consonance with existing bilateral

airworthiness agreements, the FAA has

determined that, for this proposed AD,

a repair approved by either the FAA or

the LFV (or its delegated agent) would

be acceptable for compliance with this

proposed AD.

Cost Impact

The FAA estimates that 3 airplanes of

U.S. registry would be affected by this

proposed AD.

It would take approximately 6 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 $1,080, or

$360 per airplane.

The proposed installation would take

approximately 10 work hours per

airplane, at an average labor rate of $60

per work hour. Based on these figures,

the cost impact of the installation

proposed by this AD on U.S. operators

is estimated to be $1,800, or $600 per

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:

SAAB Aircraft AB: Docket 98–NM–151–AD.

Applicability: Model SAAB 2000 series

airplanes, manufacturer serial numbers 004

through 050 inclusive, 052, 053, and 054;

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 (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 cracking on the rear pressure

bulkhead, which could result in sudden loss

of cabin pressure and the inability to

withstand fail-safe loads, accomplish the

following:

(a) Within 4,000 flight cycles after the

effective date of this AD, perform a one-time

visual inspection for cracking on the rear

pressure bulkhead in the area of the lower

forward flange that connects to the fuselage

skin, in accordance with SAAB Service

Bulletin 2000–53–026, dated February 27,

1998.

(1) If no crack is detected, prior to further

flight, install a reinforcement angle on the

rear pressure bulkhead in the area of the

lower forward flange that connects to the

fuselage skin, in accordance with the service

bulletin. After accomplishment of the

installation, no further action is required by

this AD.

(2) If any crack is detected, prior to further

flight, repair in accordance with a method

approved by either the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, or the

Luftfartsverket (or its delegated agent).

(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. 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 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.

(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 3: The subject of this AD is addressed

in Swedish airworthiness directive 1–122,

dated March 2, 1998.
31382 Federal Register / Vol. 63, No. 110 /Tuesday, June 9, 1998 / Proposed Rules

Issued in Renton, Washington, on June 3,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–15248 Filed 6–8–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–113–AD]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328–100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Supplemental notice of

proposed rulemaking; reopening of

comment period.

SUMMARY: This document revises an

earlier proposed airworthiness directive

(AD), applicable to certain Dornier

Model 328–100 series airplanes, that

would have required repetitive

inspections to detect cracking of the

support beam of the main landing gear

(MLG) fairing; and permanent repair of

any cracking found, which would

terminate the repetitive inspections.

This new action revises the proposed

rule by adding a requirement for

installation of reinforcement parts for

the longitudinal beam of the MLG

fairing, which also would terminate the

repetitive inspections. This new action

also limits the applicability of the

proposed rule. This proposal is

prompted by issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified by this new

proposed AD are intended to prevent

cracking of the support beam of the

MLG fairing, which could result in

reduced structural integrity of the lower

part of the MLG fairing, and consequent

separation of part of the fairing from the

airplane and possible damage to the

airplane or injury to persons on the

ground.

DATES: Comments must be received by

July 6, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 96–NM–

113–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

FAIRCHILD DORNIER, 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:

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 96–NM–113–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.

96–NM–113–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to add an airworthiness

directive (AD), applicable to certain

Dornier Model 328–100 series airplanes,

was published as a notice of proposed

rulemaking (NPRM) in the Federal

Register on April 9, 1997 (62 FR 17129).

That NPRM would have required

repetitive inspections to detect cracking

of the support beam of the main landing

gear (MLG) fairing; and permanent

repair of any cracking found, which

would terminate the repetitive

inspections. That NPRM was prompted

by reports of cracking of the support

beam of the MLG fairing. That

condition, if not corrected, could result

in reduced structural integrity of the

lower part of the MLG fairing, and

consequent separation of part of the

fairing from the airplane and possible

damage to the airplane or injury to

persons on the ground.

Disposition of Comments

Due consideration has been given to

the comments received in response to

the NPRM.

Request To Cite Additional Service

Information

One commenter, the manufacturer,

requests that the FAA revise the

proposal to reference Dornier Service

Bulletin SB–328–53–184, Revision 1,

dated July 2, 1997. That service bulletin

describes procedures for installation of

reinforcement parts for the longitudinal

beam of the MLG fairing, which would

eliminate the need for the repetitive

inspections. The effectivity listing of the

service bulletin limits accomplishment

of the installation of reinforcement parts

to those airplanes on which the

installation was not accomplished in

production. Accomplishment of the

action specified in the service bulletin

is intended to adequately address the

identified unsafe condition. The

Luftfahrt-Bundesamt (LBA), which is

the airworthiness authority for

Germany, classified the original release

of this service bulletin, dated January

10, 1997, as mandatory and issued

German airworthiness directive 97–073,

dated March 27, 1997, in order to assure

the continued airworthiness of these

airplanes in Germany.

The FAA concurs with the

commenter’s request. The FAA finds

that accomplishment of the terminating

action is necessary within 3,000 hours

time-in-service, as specified in the

German airworthiness directive. The

FAA has revised this supplemental

NPRM accordingly. Additionally, the

cost impact information, below, has

been revised to reflect any additional

costs to operators.