40854 Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 / Proposed Rules

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:

De Havilland Inc.: Docket 98–NM–172–AD.

Applicability: Model DHC–8–102, –103,

–106, –201, –202, –301, –311, and –315 series

airplanes; serial numbers 3 through 519

inclusive, excluding serial number 462;

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 chafing of electrical wires,

which could result in an uncommanded

shutdown of an engine during flight,

accomplish the following:

(a) Within 36 months after the effective

date of this AD, perform a one-time visual

inspection to detect chafing of electrical

wires in the cable trough below the cabin

floor; install additional tie-mounts and tiewraps; and apply sealant to rivet heads

(reference de Havilland Modification 8/

2705); in accordance with de Havilland

Service Bulletin 8–53–66, dated March 27,

1998. If any chafing is detected during the

inspection required by this paragraph, prior

to further flight, repair in accordance with

the service bulletin.

(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, 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.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

(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 Canadian airworthiness directive CF–98–

08, dated March 26, 1998.

Issued in Renton, Washington, on July 24,

1998.

S. R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–20436 Filed 7–30–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–162–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

replacement of certain landing gear

proximity sensor electrical units (PSEU)

with improved units. 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 the failure

of normal extension and retraction of

the landing gear, which could result in

collapse of the main landing gear upon

landing.

DATES: Comments must be received by

August 31, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

162–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 98–NM–162–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–162–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 has advised that it has

received several reports of occurrences

in which normal extension and

retraction of the landing gear was not

possible. Further investigation revealed

that the failure of landing gear to extend

and retract properly was due to a

manufacturing defect of certain ELDEC

landing gear proximity sensor electrical
Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 / Proposed Rules 40855

units (PSEU), which can cause certain

control circuits within the PSEU to shut

off intermittently. Such failures of

normal extension and retraction of the

landing gear, if not corrected, could

result in collapse of the main landing

gear upon landing.

Explanation of Relevant Service

Information

The manufacturer has issued Dornier

Service Bulletin SB–328–32–248,

Revision 1, dated April 22, 1998, which

describes procedures for replacement of

certain landing gear PSEU’s with

improved PSEU’s that are not

susceptible to the intermittent shutoff of

certain control circuits. The Dornier

service bulletin references Crane ELDEC

Corporation Service Bulletin 8–700–31–

02, Revision 1, December 11, 1997, as an

additional source of service information

to accomplish the replacement.

Accomplishment of the actions

specified in the Dornier service bulletin

is intended to adequately address the

identified unsafe condition. The LBA

classified this service bulletin as

mandatory and issued German

airworthiness directive 1998–137, dated

March 26, 1998, in order to assure the

continued 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 the 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, that it would take

approximately 1 work hour per airplane

to accomplish the proposed

replacement, and that the average labor

rate is $60 per work hour. Required

parts would be supplied by the

manufacturer at no cost to the operators.

Based on these figures, the cost impact

of the proposed 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

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 98–NM–

162–AD.

Applicability: Model 328–100 series

airplanes, equipped with landing gear

proximity sensor electrical units (PSEU)

having part number (P/N) 8–700–03 or 8–

700–04; 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 the failure of normal extension

and retraction of the landing gear, which

could result in collapse of the main landing

gear upon landing, accomplish the following:

(a) Within 12 months after the effective

date of this AD, replace the landing gear

PSEU’s having P/N 8–700–03 or 8–700–04

with PSEU’s having P/N 8–700–04 Mod A or

8–700–05, in accordance with Dornier

Service Bulletin SB–328–32–248, Revision 1,

dated April 22, 1998.

Note 2: Dornier Service Bulletin SB–328–

32–248, Revision 1, dated April 22, 1998,

references Crane ELDEC Corporation Service

Bulletin 8–700–31–02, Revision 1, December

11, 1997, as an additional source of service

information to accomplish the actions

required by this AD.

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

person shall install a landing gear PSEU

having P/N 8–700–03 or 8–700–04 on any

airplane.

(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, 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.

(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.
40856 Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 / Proposed Rules

Note 4: The subject of this AD is addressed

in German airworthiness directive 1998–137,

dated March 26, 1998.

Issued in Renton, Washington, on July 24,

1998.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–20435 Filed 7–30–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–339–AD]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace (Jetstream) Model 4101

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to all British

Aerospace (Jetstream) Model 4101

airplanes, that currently requires

repetitive functional testing of the main

entrance door, cleaning and lubricating

of the ‘‘speed’’ lock and ‘‘G’’ lock

systems, and repair, if necessary. This

action would add a requirement for

replacement of the ‘‘G’’ lock rollers with

new, improved ‘‘G’’ lock rollers. 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 inability of the

main entrance door to open, which

could delay or impede passengers

exiting the airplane, or rescue personnel

from entering the airplane during an

emergency.

DATES: Comments must be received by

August 31, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97–NM–

339–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

AI(R) American Support, Inc., 13850

Mclearen Road, Herndon, Virginia

20171. 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 97–NM–339–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.

97–NM–339–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On September 3, 1997, the FAA

issued AD 97–19–02, amendment 39–

10122 (62 FR 47362, September 9,

1997), applicable to all British

Aerospace (Jetstream) Model 4101

airplanes, to require repetitive

functional testing of the main entrance

door, cleaning and lubricating of the

‘‘speed’’ lock and ‘‘G’’ lock systems, and

repair, if necessary. That action was

prompted by reports of flightcrews and

ground crews being unable to open the

main entrance door. The requirements

of that AD are intended to prevent

inability of the main entrance door to

open, which could delay or impede

passengers exiting the airplane, or

rescue personnel from entering the

airplane during an emergency.

Actions Since Issuance of Previous Rule

In the preamble to AD 97–19–02, the

FAA specified that the actions required

by that AD were considered ‘‘interim

action’’ and that once a modification is

developed, approved, and available, the

FAA may consider additional

rulemaking action. The manufacturer

now has developed such a modification,

and the FAA has determined that

further rulemaking action is indeed

necessary; this proposed AD follows

from that determination.

Explanation of Relevant Service

Information

British Aerospace Regional Aircraft

has issued Jetstream Alert Service

Bulletins J41–A–52–059, dated

September 12, 1997, and Revision 2,

dated January 23, 1998, which describe

procedures for replacement of the ‘‘G’’

lock rollers with rollers having

increased diameters. The installation of

‘‘G’’ lock rollers with increased

diameters provides a means to prevent

jamming of the main entrance door by

increasing the mechanism clearance

when the door handle is operated. The

Civil Aviation Authority (CAA), which

is the airworthiness authority for the

United Kingdom, classified these alert

service bulletins as mandatory and

issued British airworthiness directive

001–09–97 in order to assure the

continued airworthiness of these

airplanes in the United Kingdom.

FAA’s Conclusions

This airplane model is manufactured

in the United Kingdom 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 CAA has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the CAA,

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.