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:
Federal Register / Vol. 63, No. 126 /Wednesday, July 1, 1998 /Rules and Regulations 35793

(a) Within 3 months after the effective date

of this AD, modify the lever assembly of the

roll disconnect system, in accordance with

Bombardier Service Bulletin 8–27–79,

Revision ‘‘A,’’ dated March 20, 1998.

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

person shall install on the roll disconnect

system of any airplane a lever assembly

having part number 82710200–001.

(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 modification shall be done in

accordance with Bombardier Service Bulletin

8–27–79, Revision ‘A,’ dated March 20, 1998.

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., Bombardier Regional

Aircraft Division, Garratt Boulevard,

Downsview, Ontario M3K 1Y5, 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–98–

04, dated February 27, 1998.

(f) This amendment becomes effective on

August 5, 1998.

Issued in Renton, Washington, on June 24,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–17418 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–113–AD; Amendment

39–10640; AD 98–14–06]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace BAe Model ATP Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain British Aerospace

BAe Model ATP airplanes. This

amendment requires repetitive

inspections for discrepancies of the

spring strut assembly of the forward

door of the main landing gear (MLG),

and replacement of the existing spring

strut assembly with a new or serviceable

part, if necessary. This amendment also

requires eventual replacement of the

existing spring strut assembly with an

improved part, which, when

accomplished, terminates the repetitive

inspections. 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 spring

strut assembly of the forward door of the

MLG, which, if not corrected, could

result in inability to extend the MLG.

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 AI(R) American Support, Inc.,

13850 Mclearen Road, Herndon,

Virginia 20171. 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

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 BAe Model ATP airplanes

was published in the Federal Register

on May 1, 1998 (63 FR 24136). That

action proposed to require repetitive

inspections for discrepancies of the

spring strut assembly of the forward

door of the main landing gear (MLG),

and replacement of the existing spring

strut assembly with a new or serviceable

part, if necessary. That action also

proposed to require eventual

replacement of the existing spring strut

assembly with an improved part, which,

when accomplished, would terminate

the repetitive inspections.

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 10 airplanes

of U.S. registry will be affected by this

AD.

It will take approximately 4 work

hours (2 work hours per MLG) to

accomplish the required inspection, at

an average labor rate of $60 per work

hour. Based on this figure, the cost

impact of the inspection required by

this AD on U.S. operators is estimated

to be $2,400, or $240 per airplane, per

inspection cycle.

It will take approximately 12 work

hours (6 work hours per MLG) to

accomplish the required modification,

at an average labor rate of $60 per work

hour. Required parts will cost

approximately $2,200 per airplane

($1,100 per MLG). Based on this figure,

the cost impact of the modification

required by this AD on U.S. operators is

estimated to be $29,200, or $2,920 per

airplane.

The cost impact figures discussed

above are 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