35790 Federal Register / Vol. 63, No. 126 /Wednesday, July 1, 1998 /Rules and Regulations

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

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 final

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, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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 a new airworthiness directive

(AD) to read as follows:

98–14–03 AlliedSignal Inc.: Amendment

39–10637; Docket No. 97–CE–30–AD.

Applicability: AlliedSignal KT 76A Air

Traffic Control (ATC) transponders; part

number (P/N) 066–1062-00/10/02; serial

numbers 93,000 through 109,999, as installed

on, but not limited to the following airplanes

(all serial numbers), certificated in any

category:

Cessna Aircraft Company: 172, 182, R182,

T182, 06, P206, U206, TP206, 210, T210,

P210, 310, 310, T310, and 421 series

airplanes.

Twin Commander Aircraft Company: 500,

520, 560, 680, 681, 685, 690, 695, and 720

series airplanes.

The New Piper Aircraft Corporation: PA–31,

PA–32, and PA–34 series airplanes.

Raytheon Aircraft Company: E33, F33, G33,

35, J35, K35, L35, K35, M35, P35, S35, V35,

36, A26, B36, D55, E55, 56, A56, 58, 58A,

95, B95, D95, and E95 series airplanes.

Mooney Aircraft Corporation: M20 series

airplanes.

McDonnell Douglas Helicopter Company:

Model 500N rotorcraft.

Note 1: This AD applies to each aircraft

equipped with a transponder that is

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

aircraft 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 (d) 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 12

calendar months after the effective date of

this AD, unless already accomplished.

To prevent the transmission of misleading

encoding altimeter information between

affected aircraft caused by the inability of the

affected ATC transponders to coordinate with

ground-based air traffic control (ATC) radar

sites and nearby Traffic Alert and Collision

Avoidance System (TCAS)-equipped aircraft,

accomplish the following:

(a) Replace the two resistor network

modules, M401 and RM402, with new glasscoated parts in accordance with the

MODIFICATION PROCEDURE section of

AlliedSignal Service Bulletin SB KT 76A–7,

dated July 1996. When accomplished, this

replacement is referred to as Mod 7.

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

person may install an AlliedSignal KT 76A

ATC transponder; part number (P/N) 066–

1062–00/10/02; serial numbers 93,000

through 109,999, in an aircraft without first

incorporating Mod 7 as specified in

paragraph (a) of this AD.

(c) Special flight permits may be issued in

accordance with §§ 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.

(d) 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 (ACO), 1801 Airport

Road, Room 100, Mid-Continent Airport,

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 ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(e) The replacement required by this AD

shall be done in accordance with

AlliedSignal Service Bulletin SB KT 76A–7,

dated July 1996. This incorporation by

reference was approved by the Director of the

Federal Register in accordance with 5 U.S.C.

552(a) and 1 CFR part 51. Copies may be

obtained from AlliedSignal Inc., General

Aviation Avionics, 400 N. Rogers Road,

Olathe, Kansas 66062–1212. Copies may be

inspected at the FAA, Central Region, Office

of the Regional Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri, or at the

Office of the Federal Register, 800 North

Capitol Street, NW, suite 700, Washington,

DC.

(f) This amendment becomes effective on

August 16, 1998.

Issued in Kansas City, Missouri, on June

23, 1998.

Marvin R. Nuss,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–17301 Filed 6–30–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–103–AD; Amendment

39–10639; AD 98–14–05]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328–100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Dornier Model

328–100 series airplanes, that requires

modification of the ground cooling fan.

This amendment is prompted by

issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by this 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: Effective August 5, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 5,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from FAIRCHILD DORNIER, DORNIER

Luftfahrt GmbH, P.O. Box 1103, D–

82230 Wessling, Germany. This

information may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601
Federal Register / Vol. 63, No. 126 /Wednesday, July 1, 1998 /Rules and Regulations 35791

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Dornier

Model 328–100 series airplanes was

published in the Federal Register on

May 5, 1998 (63 FR 24758). That action

proposed to require modification of the

ground cooling fan.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Explanation of Changes Made to this

Final Rule

In the proposal, the FAA

inadvertently omitted reference to the

Price/Material Information Sheet, dated

July 16, 1997, of Dornier Service

Bulletin SB–328–21–227, dated July 16,

1997. Therefore, the FAA has revised

the final rule accordingly.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule with the change

previously described. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

Cost Impact

The FAA estimates that 50 airplanes

of U.S. registry will be affected by this

AD. It will take approximately 1 work

hour per airplane to accomplish the

required actions, at average labor rate of

$60 per work hour. Required parts will

be supplied by the manufacturer at no

cost to operators. Based on these figures,

the cost impact of the 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 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 adopted herein will

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 final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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:

98–14–05 Dornier Luftfahrt GmbH:

Amendment 39–10639. 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

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,

including Price/Material Information Sheet,

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.

(e) The modification shall be done in

accordance with Dornier Service Bulletin

SB–328–21–227, dated July 16, 1997,

including Price/Material Information Sheet,

dated July 16, 1997. This incorporation by

reference was approved by the Director of the

Federal Register in accordance with 5 U.S.C.

552(a) and 1 CFR part 51. Copies may be

obtained from FAIRCHILD DORNIER,

DORNIER Luftfahrt GmbH, P.O. Box 1103, D–

82230 Wessling, Germany. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Note 4: The subject of this AD is addressed

in German airworthiness directive 97–243,

dated August 28, 1997.

(f) This amendment becomes effective on

August 5, 1998.
35792 Federal Register / Vol. 63, No. 126 /Wednesday, July 1, 1998 /Rules and Regulations

Issued in Renton, Washington, on June 24,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–17419 Filed 6–30–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–336–AD; Amendment

39–10638; AD 98–14–04]

RIN 2120–AA64

Airworthiness Directives; de Havilland

Model DHC–8–100, –200, and –300

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain de Havilland

Model DHC–8–100, –200, and –300

series airplanes, that requires

modification of the lever assembly of

the roll disconnect system. This

amendment is prompted by mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified by this AD are

intended to prevent uncommanded

disconnects of the roll control system,

which could result in a limited degree

of roll control and consequent reduced

controllability of the airplane.

DATES: Effective August 5, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 5,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Bombardier, Inc., Bombardier

Regional Aircraft Division, Garratt

Boulevard, Downsview, Ontario M3K

1Y5, Canada. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

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;

or at the Office of the Federal Register,

800 North Capitol Street, NW., suite

700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Anthony E. Gallo, Aerospace Engineer,

Systems and Flight Test 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) 256–7510; fax

(516) 568–2716.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain de

Havilland Model DHC–8–100, –200, and

–300 series airplanes was published in

the Federal Register on April 27, 1998

(63 FR 20552). That action proposed to

require modification of the lever

assembly of the roll disconnect system.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 180 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 2

work hours per airplane to accomplish

the required modification, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

AD on U.S. operators is estimated to be

$21,600, or $120 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the 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 adopted herein will

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 final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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:

98–14–04 De Havilland, Inc.: Amendment

39–10638. Docket 97–NM–336–AD.

Applicability: Model DHC–8–100, –200,

and –300 series airplanes on which

Bombardier Modification 8/2376 was not

accomplished during production; serial

numbers 003 through 294 inclusive, and 296

through 433 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

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 (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 uncommanded disconnects of

the roll control system, which could result in

a limited degree of roll control and

consequent reduced controllability of the

airplane; accomplish the following: