24758 Federal Register / Vol. 63, No. 86 /Tuesday, May 5, 1998 / Proposed Rules

Model Serial No.

B200 ............................... BB–1158, BB–1167, BB–1193 through BB–1263, BB–1265 through BB–1286, BB–1287, BB–1288, BB–1290 through

BB–1300, BB–1302 through BB–1425, BB–1427 through BB–1447, BB–1449, BB–1450, BB–1453, BB–1455, BB–

1456, and BB–1458 through BB–1559.

B200C ............................ BL–124 through BL–140.

B200CT (FW–II) ............. FG–1 and FG–2.

200T/B200T .................... BT–31 through BT–38.

300 ................................. FA–1 through FA–230 and FF–1 through FF–19.

B300 ............................... FL–1 through FL–159.

B300C ............................ FM–1 through FM–9 and FN–1.

A200CT (C–12D) ........... BP–46 through BP–51.

A200CT (C–12F) ............ BP–52 through BP–63.

A200CT (RC–12K) ......... FE–1 through FE–9.

A200CT (RC–12N) ......... FE–10 through FE–24.

A200CT (RC–12P) ......... FE–25 through FE–31, FE–33, FE–35.

A200CT (RC–12Q) ......... FE–32, FE–34, FE–36.

B200C (C–12F) .............. BP–64 through BP–71, BL–73 through BL–112, and BL–118 through BL–123.

B200C (UC–12F) ........... BU–1 through BU–10.

B200CT (RC–12F) ......... BU–11 and BU–12.

B200C (UC–12M) ........... BV–1 through BV–10.

B200C (RC–12M) ........... BV–11 and BV–12.

B200C (C–12R) .............. BW–1 through BW–29.

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 within the next 200

hours time-in-service (TIS) after the effective

date of this AD, unless already accomplished.

To prevent failure of the actuator clevis rod

in the main landing gear, which could result

in loss of control of the airplane during

landing operations, accomplish the

following:

(a) Replace the left and right main landing

gear actuator clevis assembly with a new

MLG actuator clevis assembly of improved

design in accordance with the

Accomplishment Instructions section in

Raytheon Aircraft Mandatory Service

Bulletin No. 2728, Issued: June, 1997,

Revision No. 1, February, 1998.

(b) 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.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Wichita Aircraft

Certification Office, 1801 Airport Road,

Room 100, Wichita, Kansas 67209. The

request shall be forwarded through an

appropriate FAA Maintenance Inspector,

who may add comments and then send it to

the Manager, Wichita Aircraft Certification

Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita Aircraft

Certification Office.

(d) All persons affected by this directive

may obtain copies of the document referred

to herein upon request to the Raytheon

Aircraft Company, P.O. Box 85, Wichita,

Kansas 67201–0085; or may examine this

document at the FAA, Central Region, Office

of the Regional Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri 64106.

Issued in Kansas City, Missouri, on April

29, 1998.

James E. Jackson,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–11887 Filed 5–4–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–103–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

modification of the ground cooling fan.

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

ground cooling fan, which could result

in smoke in the flight deck and cabin

and consequent inability of the flight

crew to perform duties or possible

passenger injury due to smoke

inhalation.

DATES: Comments must be received by

June 4, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

103–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
Federal Register / Vol. 63, No. 86 /Tuesday, May 5, 1998 / Proposed Rules 24759

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–103–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–103–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

reports of smoke in the flight deck and

cabin. The cause of the smoke has been

attributed to an overheating condition

caused by oil contamination of the heat

exchangers and the failure of the ground

cooling fans to dispel the smoke from

the flight deck and cabin. This

condition, if not corrected, could result

in inability of the flight crew to perform

duties or possible passenger injury due

to smoke inhalation.

Explanation of Relevant Service

Information

Dornier has issued Service Bulletin

SB–328–21–227, dated July 16, 1997,

which describes procedures for

modification of the ground cooling fan.

The modification involves incorporation

of a modified check valve and rotation

of the valve 90 degrees from its present

position. (The service bulletin

references EG&G Rotron Service

Bulletin 011389500–21–1, dated April

30, 1997, as an additional source of

service information to accomplish the

modification.) 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 97–243, dated

August 28, 1997, 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. It would take

approximately 1 work hour per airplane

to accomplish the proposed

modification, at an average labor rate of

$60 per work hour. Required parts

would be supplied by the manufacturer

at no cost to 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–

103–AD.

Applicability: Model 328–100 series

airplanes, serial numbers 3005 through 3095

inclusive, 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
24760 Federal Register / Vol. 63, No. 86 /Tuesday, May 5, 1998 / Proposed Rules

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 ground cooling

fan, which could result in smoke in the flight

deck and cabin and consequent inability of

the flight crew to perform duties or possible

passenger injury due to smoke inhalation,

accomplish the following:

(a) Within 3 months after the effective date

of this AD, modify the ground cooling fan

and rotate the modified check valve, in

accordance with Dornier Service Bulletin

SB–328–21–227, dated July 16, 1997.

Note 2: The service bulletin references

EG&G Rotron Service Bulletin 011389500–

21–1, dated April 30, 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 on any airplane a ground

cooling fan, part number 011389500, unless

it has been modified in accordance with

Dornier Service Bulletin SB–328–21–227,

dated July 16, 1997.

(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.

Note 4: The subject of this AD is addressed

in German airworthiness directive 97–243,

dated August 28, 1997.

Issued in Renton, Washington, on April 29,

1998.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–11888 Filed 5–4–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–18–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320 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 Airbus Model A320 series

airplanes. This proposal would require

repetitive inspections to detect fatigue

cracking of the front spar vertical

stringers on the wings; and repair, if

necessary. This proposal also provides

for an optional terminating action for

the repetitive inspections. 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 cracking of the front spar vertical

stringers on the wings, which could

result in reduced structural integrity of

the airframe.

DATES: Comments must be received by

June 4, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

18–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:

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–18–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–18–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

notified the FAA that an unsafe

condition may exist on certain Airbus

Model A320 series airplanes. The DGAC

advises that, during full-scale fatigue

testing on a Model A320 test article,

fatigue cracking occurred at 116,151

simulated flights on the front vertical

stringer on the wing at frame 36. Such

fatigue cracking, if not detected and

corrected in a timely manner, could

result in reduced structural integrity of

the airframe.

Explanation of Relevant Service

Information

Airbus has issued Service Bulletin

A320–57–1016, Revision 1, dated

December 6, 1995, which describes

procedures for repetitive eddy current