Federal Register / Vol. 63, No. 106 /Wednesday, June 3, 1998 /Rules and Regulations 30119

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:

98–11–30 Empresa Brasileira De

Aeronautica S.A. (Embraer):

Amendment 39–10555. Docket 97–NM–

279–AD.

Applicability: Model EMB–145 series

airplanes, serial numbers 145004 through

145018 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 structural failure of the main

landing gear (MLG) due to fatigue cracking of

the strut bushing seat, accomplish the

following:

(a) Prior to the accumulation of 2,000 total

flight cycles, or within 100 flight cycles after

the effective date of this AD, whichever

occurs later, accomplish paragraphs (a)(1),

(a)(2), and (a)(3) of this AD.

(1) Perform a one-time liquid penetrant

inspection to detect cracking of the flanged

bushing seats of the MLG, in accordance with

EMBRAER Service Bulletin 145–32–0012,

dated September 1, 1997. If any crack is

found, prior to further flight, repair in

accordance with a method approved by the

Manager, Atlanta Aircraft Certification Office

(ACO), FAA, Small Airplane Directorate.

(2) Perform a one-time inspection of the

bushing holes using a bore micrometer to

determine the dimension of the holes, in

accordance with EMBRAER Service Bulletin

145–32–0012, dated September 1, 1997. Prior

to further flight, accomplish paragraph

(a)(2)(i) or (a)(2)(ii) of this AD, as applicable.

(i) If the dimension of the bushing hole is

less than 49.2 mm, perform the applicable

corrective actions specified in the service

bulletin.

(ii) If the dimension of the bushing hole is

greater than or equal to 49.2 mm, repair in

accordance with a method approved by the

Manager, Atlanta ACO.

(3) Replace the plain bearing of the MLG

shock absorber with a new bearing in

accordance with EMBRAER Service Bulletin

145–32–0009, dated September 1, 1997.

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

person shall install a plain bearing having

part number ABC24VG (NMB) on the shock

absorber of the MLG of 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, Atlanta

Aircraft Certification Office (ACO), FAA,

Small 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, Atlanta ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

(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 actions shall be done in accordance

with EMBRAER Service Bulletin 145–32–

0012, dated September 1, 1997, and

EMBRAER Service Bulletin 145–32–0009,

dated September 1, 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 Empresa Brasileira de

Aeronautica S.A. (EMBRAER), P.O. Box

343—CEP 12.225, Sao Jose dos Campos—SP,

Brazil. Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

FAA, Small Airplane Directorate, Atlanta

Aircraft Certification Office, One Crown

Center, 1895 Phoenix Boulevard, suite 450,

Atlanta, Georgia; or at the Office of the

Federal Register, 800 North Capitol Street,

NW., suite 700, Washington, DC.

Note 3: The subject of this AD is addressed

in Brazilian airworthiness directive 97–10–

02, dated October 13, 1997.

(f) This amendment becomes effective on

July 8, 1998.

Issued in Renton, Washington, on May 22,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–14220 Filed 6–2–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–43–AD; Amendment

39–10553; AD 98–11–28]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace Model BAe Avro 146–RJ

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain British Aerospace

Model BAe Avro 146–RJ series

airplanes, that requires a one-time

inspection of certain electrical wires in

the electrical equipment bay to

determine if ERMA terminal lugs are

installed; and replacement with new

parts, if necessary. 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

electrical circuit terminal lugs, which

could result in electrical system failure,

and consequent reduced controllability

of the airplane.

DATES: Effective July 8, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 8, 1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from AI(R) American Support, Inc.,

13850 Mclearen Road, Herndon,

Virginia 20171. This information may be
30120 Federal Register / Vol. 63, No. 106 /Wednesday, June 3, 1998 /Rules and Regulations

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

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 British

Aerospace Model BAe Avro 146–RJ

series airplanes was published in the

Federal Register on April 2, 1998 (63 FR

16175). That action proposed to require

a one-time inspection of certain

electrical wires in the electrical

equipment bay to determine if ERMA

terminal lugs are installed; and

replacement with new parts, if

necessary.

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.

Conclusion

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 1 airplane of

U.S. registry will be affected by this AD,

that it will take approximately 4 work

hours per airplane to accomplish the

required inspection, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of this AD on the single U.S. operator

is estimated to be $240.

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:

98–11–28 British Aerospace Regional

Aircraft (Formerly British Aerospace

Regional Aircraft Limited, Avro

International Aerospace Division;

British Aerospace, PLC; British

Aerospace Commercial Aircraft

Limited): Amendment 39–10553. Docket

98–NM–43–AD.

Applicability: Model BAe Avro 146–RJ85A

series airplanes, serial numbers E2296,

E2297, E2299, E2300, E2302, E2303, E2304,

E2305, E2306, and E2307; and Model Avro

146–RJ100A series airplanes, serial numbers

E3298, E3301, and E3308; 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 electrical circuit

terminal lugs, which could result in electrical

system failure, and consequent reduced

controllability of the airplane, accomplish

the following:

(a) Within 6 months after the effective date

of this AD, perform a one-time visual

inspection of the electrical wires, having part

numbers (P/N) MD0011N and MD0012N, in

the electrical equipment bay and hydraulic

equipment bay, to determine if any ERMA

terminal lug having P/N ERMA 12115/2 is

installed, in accordance with British

Aerospace Service Bulletin SB.24–120, dated

September 18, 1997. If any ERMA terminal

lug is found, prior to further flight, remove

the lug and replace with an AMP terminal

lug having P/N AMP 323064, in accordance

with the service bulletin.

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

person shall install an ERMA terminal lug, P/

N ERMA 12115/2, 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 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.

(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 inspection and replacement shall

be done in accordance with British

Aerospace Service Bulletin SB.24–120, dated

September 18, 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 AI(R) American Support, Inc.,

13850 Mclearen Road, Herndon, Virginia

20171. 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 3: The subject of this AD is addressed

in British airworthiness directive 007–09–97.

(f) This amendment becomes effective on

July 8, 1998.
Federal Register / Vol. 63, No. 106 /Wednesday, June 3, 1998 /Rules and Regulations 30121

Issued in Renton, Washington, on May 22,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–14219 Filed 6–2–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–60–AD; Amendment

39–10550; AD 98–11–25]

RIN 2120–AA64

Airworthiness Directives; de Havilland

Model DHC–8–311 and –315 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–8–311 and –315 series

airplanes, that requires replacement of

the nitrogen cylinder assemblies that

inflate the airplane’s ditching dams with

improved nitrogen cylinder assemblies.

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

ditching dams to inflate fully during an

emergency water landing, which could

result in water entering the airplane.

DATES: Effective July 8, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 8, 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: Ezra

Sasson, 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–

7520; 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–8–311 and –315

series airplanes was published in the

Federal Register on April 2, 1998 (63 FR

16169). That action proposed to require

replacement of the nitrogen cylinder

assemblies that inflate the airplane’s

ditching dams with improved nitrogen

cylinder assemblies.

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.

Conclusion

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 2 airplanes of

U.S. registry will be affected by this AD,

that it will take approximately 4 work

hours per airplane to accomplish the

required modification, and that the

average labor rate is $60 per work hour.

Required parts will be provided by the

manufacturer of the nitrogen cylinder

assembly at no cost to the operator.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $480, or $240 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:

98–11–25 De Havilland Inc.: Amendment

39–10550. Docket 98–NM–60–AD.

Applicability: Model DHC–8–311 and –315

series airplanes in the medium and high

gross weight configuration, on which

Bombardier Change Request CR803SO00001,

CR803SO00002, CR803CH00046,

CR803CH00079, CR803CH00105,

CR825CH00847, or CR803CH00051 has been

incorporated; 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 failure of the ditching dams to

inflate fully during an emergency water

landing, which could result in water entering

the airplane, accomplish the following: