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
35794 Federal Register / Vol. 63, No. 126 /Wednesday, July 1, 1998 /Rules and Regulations

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:

98–14–06 British Aerospace Regional

Aircraft [Formerly Jetstream Aircraft

Limited; British Aerospace (Commercial

Aircraft) Limited]: Amendment 39–

10640. Docket 98–NM–113–AD.

Applicability: BAe Model ATP airplanes,

as listed in British Aerospace Alert Service

Bulletin ATP–32–85, Revision 1, dated

March 20, 1998; 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 spring strut

assembly of the forward door of the main

landing gear (MLG), which could result in

the inability to extend the MLG, accomplish

the following:

(a) Within 600 flight hours after the

effective date of this AD, perform a visual

inspection for discrepancies of the fork end

of the spring strut assembly of the forward

door of the MLG, on the left and right sides

of the airplane; in accordance with British

Aerospace Alert Service Bulletin ATP–32–85,

Revision 1, dated March 20, 1998.

(1) If no discrepancy is detected, repeat the

visual inspection thereafter at intervals not to

exceed 1,500 flight hours until the actions

specified by paragraph (b) of this AD are

accomplished.

(2) If any discrepancy is detected, prior to

further flight, replace the existing spring strut

assembly with a new or serviceable part, in

accordance with the alert service bulletin.

Repeat the visual inspection thereafter at

intervals not to exceed 1,500 flight hours

until the actions specified by paragraph (b)

of this AD are accomplished.

(b) Within 18 months after the effective

date of this AD, replace the spring strut

assembly of the forward door of the MLG

with an improved spring strut assembly, on

the left and right sides of the airplane; in

accordance with British Aerospace Service

Bulletin ATP–32–87, dated January 29, 1998.

This replacement constitutes terminating

action for the requirements of this AD.

(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 request 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 replacement shall be done in

accordance with British Aerospace Service

Bulletin ATP–32–87, dated January 29, 1998.

The inspection shall be done in accordance

with British Aerospace Alert Service Bulletin

ATP–32–85, Revision 1, dated March 20,

1998, which contains the following effective

pages:

Page No. shown on

page

Revision

level

shown on

page

Date

shown on

page

1–3, 6, 7, 10 ............. 1 ............. March 20,

1998.

4, 5, 8, 9, 11 ............. Original .. January

26,

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 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.

(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. 98–17417 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–ANE–33–AD; Amendment

39–10636; AD 98–14–02]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney Canada PW100 Series

Turboprop Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Pratt & Whitney Canada

(PWC) PW100 series turboprop engines,

that requires removal of the existing fuel

manifold tubes, lock plates, and

preformed packing; installation of

improved fuel manifold transfer tubes,

improved lock plates, and improved

preformed packing; and, after

installation, the performance of a leak

check. This amendment is prompted by

reports of engine fuel leaks which

resulted in either inflight engine

shutdowns or fire warnings. The actions

specified by this AD are intended to

prevent engine fuel leaks, which can

result in inflight engine shutdowns or

fire warnings.

DATES: Effective August 31, 1998.