40852 Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 / Proposed Rules

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:

Airbus Industrie: Docket 98–NM–169–AD.

Applicability: Model A300 series airplanes,

as listed in Airbus Industrie Service Bulletin

A300–53–301, Revision 1, dated February 20,

1997; 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 detect and correct corrosion on the

fuselage skin panels that surround the

emergency exits immediately aft of the wing,

which could result in reduced structural

integrity of the fuselage pressure vessel,

accomplish the following:

(a) Within 18 months after the effective

date of this AD, perform a visual inspection

to detect corrosion on the fuselage skin

panels that surround the emergency exits

immediately aft of the wing, between frames

55 to 58, and from stringers 13 to 31, left and

right; in accordance with Airbus Industrie

Service Bulletin A300–53–301, dated

September 28, 1995, or Revision 1, dated

February 20, 1997.

(1) If no corrosion is detected, repeat the

inspection thereafter at intervals not to

exceed 18 months on all areas on the fuselage

skin panels that do not have a doubler

installed or areas that have not been partially

or completely replaced.

(2) If any corrosion is detected, prior to

further flight, accomplish rework and

perform a residual thickness measurement, in

accordance with the service bulletin.

(i) If the measurement does not exceed the

allowable limits specified by the

Accomplishment Instructions of the service

bulletin, repeat the inspection thereafter at

intervals not to exceed 18 months.

(ii) If the measurement does exceed the

allowable limits specified by the

Accomplishment Instructions of the service

bulletin, prior to further flight, repair using

a doubler, or replace the affected areas of the

skin panel the installation of a new skin

panel (partially or completely), in accordance

with the service bulletin. Accomplishment of

either action constitutes terminating action

for the repetitive inspections required by this

AD for the repaired area or the replaced

panel sections only.

Note 2: Inspections, repairs, and

replacements of the fuselage skin panels that

surround the emergency exits immediately

aft of the wing that have been accomplished

prior to the effective date of this AD, in

accordance with Airbus Industrie Service

Bulletin A300–53–301, dated September 28,

1995, are considered acceptable for

compliance with the applicable action

specified in this proposed AD.

(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 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.

(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 French airworthiness directive 97–357–

231(B), dated November 19, 1997.

Issued in Renton, Washington, on July 24,

1998.

D. L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–20437 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–172–AD]

RIN 2120–AA64

Airworthiness Directives; de Havilland

Model DHC–8–102, –103, –106, –201,

–202, –301, –311, and –315 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 de Havilland Model DHC–8–102,

–103, –106, –201, –202, –301, –311, and

–315 series airplanes. This proposal

would require a one-time inspection to

detect chafing of electrical wires in the

cable trough below the cabin floor;

repair, if necessary; installation of

additional tie-mounts and tie-wraps;

and application of sealant to rivet heads.

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 chafing of electrical

wires, which could result in an

uncommanded shutdown of an engine

during flight.

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–

172–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

Bombardier, Inc., Bombardier Regional

Aircraft Division, Garratt Boulevard,

Downsview, Ontario M3K 1Y5, Canada.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington; or at the FAA,

Engine and Propeller Directorate, New

York Aircraft Certification Office, 10

Fifth Street, Third Floor, Valley Stream,

New York.

FOR FURTHER INFORMATION CONTACT:

Peter Cuneo, Senior Aerospace

Engineer, Systems and Flight Test
Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 / Proposed Rules 40853

Branch, ANE–172, FAA, Engine and

Propeller Directorate, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York

11581; telephone (516) 256–7506; fax

(516) 568–2716.

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–172–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–172–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

Transport Canada Aviation (TCA),

which is the airworthiness authority for

Canada, notified the FAA that an unsafe

condition may exist on certain de

Havilland Model DHC–8–102, –103,

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

series airplanes. TCA advises that a

Model DHC–8 series airplane

experienced an uncommanded

shutdown of an engine during flight,

due to a short circuit between adjacent

electrical wires in a cable trough below

the cabin floor. The short circuit

resulted in a 28-volt signal being

applied to the fuel shut-off valve, which

stopped the flow of fuel to the engine.

Investigation revealed that the short

circuit was caused by chafing of

electrical wires on the sharp edges of

the rivets in the cable trough. This

condition, if not corrected, could result

in an uncommanded shutdown of an

engine during flight.

Explanation of Relevant Service

Information

Bombardier has issued de Havilland

Service Bulletin 8–53–66, dated March

27, 1998, which describes procedures

for a one-time visual inspection to

detect chafing of electrical wires in the

cable trough below the cabin floor;

repair, if necessary; installation of

additional tie-mounts and tie-wraps;

and application of sealant to rivet heads.

Accomplishment of the actions

specified in the service bulletin is

intended to adequately address the

identified unsafe condition. TCA

classified this service bulletin as

mandatory and issued Canadian

airworthiness directive CF–98–08, dated

March 26, 1998, in order to assure the

continued airworthiness of these

airplanes in Canada.

FAA’s Conclusions

This airplane model is manufactured

in Canada 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,

TCA has kept the FAA informed of the

situation described above. The FAA has

examined the findings of TCA, 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 225 airplanes

of U.S. registry would be affected by this

proposed AD.

For the 210 Model DHC–8–102, –103,

–106, –201, and –202 series airplanes

affected, it would take approximately 70

work hours per airplane to accomplish

the proposed actions, 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 proposed AD for these airplanes

on U.S. operators is estimated to be

882,000, or $4,200 per airplane.

For the 15 Model DHC–8–301, –311,

and –315 series airplanes affected, it

would take approximately 100 work

hours per airplane to accomplish the

proposed actions, 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 proposed AD for these airplanes

on U.S. operators is estimated to be

$90,000, or $6,000 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
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