4564 Federal Register / Vol. 63, No. 20 / Friday, January 30, 1998 /Rules and Regulations

(1) The combined thrust, torque and

gyroscopic loads resulting from the

engine and propeller at maximum

continuous power for the first 5

minutes, and

(2) The airplane normal inertial limit

loads that result from the following:

(i) A maneuver load factor equal to

that obtained from a constant altitude

30° bank, combined with

(ii) The positive and negative vertical

design gust load factors that occur at the

design maneuvering speed and the

minimum flying weight, and

(iii) A factor-of-safety equal to one.

Issued in Kansas City, Missouri on January

22, 1998.

Marvin Nuss,

Assistant Manager, Small Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–2399 Filed 1–29–98; 8:45 am]

BILLING CODE 4910–13–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–256–AD; Amendment

39–10294; AD 98–03–02]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model CL–600–1A11 and CL–600–2A12

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Bombardier Model

CL–600–1A11 and CL–600–2A12 series

airplanes, that requires replacement of

the anti-noise filter on the standby and

auxiliary power unit (APU) fuel pump

assemblies with a new filter. 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 electrical arcing between the

internal wiring and casing of the antinoise filter on the standby and APU fuel

pump assemblies, and consequent

increased risk of fuel tank explosion or

fire.

DATES: Effective March 6, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 6,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Bombardier, Inc., Canadair,

Aerospace Group, P.O. Box 6087,

Station A, Montreal, Quebec H3C 3G9,

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:

Wing Chan, Aerospace Engineer,

Systems and Equipment 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) 256–7511; 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 Bombardier

Model CL–600–1A11 and CL–600–2A12

series airplanes was published in the

Federal Register on November 19, 1997

(62 FR 61706). That action proposed to

require replacement of the anti-noise

filter on the standby and auxiliary

power unit (APU) fuel pump assemblies

with a new filter.

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 84 Model CL–

600–1A11 and CL–600–2A12 series

airplanes of U.S. registry will be affected

by this AD, that it will take

approximately 20 work hours per

airplane to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $5,689 per

airplane. Based on these figures, the cost

impact of the AD on U.S. operators is

estimated to be $578,676, or $6,889 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:

98–03–02 Bombardier, Inc. (Formerly

Canadair): Amendment 39–10294.

Docket 97–NM–256–AD.

Applicability: Model CL–600–1A11 series

airplanes, as listed in Bombardier Canadair

Challenger Alert Service Bulletin A600–0644,
Federal Register / Vol. 63, No. 20 / Friday, January 30, 1998 /Rules and Regulations 4565

Revision 01, dated March 31, 1995; and

Model CL–600–2A12 series airplanes, as

listed in Bombardier Canadair Challenger

Alert Service Bulletin A601–0441, Revision

01, dated March 31, 1995; 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 electrical arcing between the

internal wiring and casing of the anti-noise

filter on the standby and auxiliary power unit

(APU) fuel pump assemblies, and consequent

increased risk of fuel tank explosion or fire,

accomplish the following:

(a) Within 100 flight hours after the

effective date of this AD, replace the antinoise filter on the standby and auxiliary

power unit (APU) fuel pump assemblies with

a new filter, in accordance with Part B of

Bombardier Canadair Challenger Alert

Service Bulletin A600–0644, Revision 01,

dated March 31, 1995 (for Model CL–600–

1A11 series airplanes), or Bombardier

Canadair Challenger Alert Service Bulletin

A601–0441, Revision 01, dated March 31,

1995 (for Model CL–600–2A12 series

airplanes); as applicable.

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

person shall install on any airplane a fuel

pump having part number (P/N) 600–62966–

25 or 600–62966–27 with an anti-noise filter

having P/N 160–151501 (prior to revision H

stamped on the part) installed.

(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, 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.

(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 replacement shall be done in

accordance with Bombardier Canadair

Challenger Alert Service Bulletin A600–0644,

Revision 01, dated March 31, 1995;

Bombardier Canadair Challenger Alert

Service Bulletin A601–0441, Revision 01,

dated March 31, 1995; as applicable. 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

Bombardier, Inc., Canadair, Aerospace

Group, P.O. Box 6087, Station A, Montreal,

Quebec H3C 3G9, Canada. Copies may be

inspected 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; 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 Canadian airworthiness directive CF–97–

02, dated February 25, 1997.

(f) This amendment becomes effective on

March 6, 1998.

Issued in Renton, Washington, on January

21, 1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–1973 Filed 1–29–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–301–AD; Amendment

39–10296; AD 98–03–04]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A330 and A340 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A330 and A340 series airplanes. This

action requires revising the Airplane

Flight Manual (AFM) to prohibit use of

the autobrake during landing on

contaminated runways. This action also

requires replacement of the brake and

steering control unit (BSCU) with a new

BSCU, which eliminates the need for

the AFM revision. For certain airplanes,

this action also requires installation of

new brakes. This amendment is

prompted by the issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified in this AD are

intended to prevent insufficient braking

capability, which could increase the

potential for landing overrun.

DATES: Effective February 17, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February

17, 1998.

Comments for inclusion in the Rules

Docket must be received on or before

March 2, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97–NM–

301–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD 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; 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: 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 A330 and A340

series airplanes. The DGAC advises that

some operators reported braking

discrepancies at low taxi speed.

Investigation has revealed anomalies in

the standard of software associated with

the brake and steering control unit

(BSCU), which could result in

insufficient braking capability. This

condition, if not corrected, could

increase the potential for landing

overrun.

Explanation of Relevant Service

Information

Airbus has released A330 Flight

Manual Temporary Revision 4.03.00/05,

dated July 12, 1996, and A340 Flight

Manual Temporary Revision 4.03.00/13,

dated July 12, 1996. These temporary

revisions describe a revision to the

Limitations Section of the Airplane

Flight Manual (AFM) to prohibit use of

the autobrake during landing on

contaminated runways.

Airbus also has issued Service

Bulletins A330–32–3062, Revision 2 (for

Model A330 series airplanes), and

A340–32–4087, Revision 2 (for Model

A340 series airplanes), both dated May