Federal Register / Vol. 63, No. 111 /Wednesday, June 10, 1998 /Rules and Regulations 31613

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

98–12–26 Fokker Services B.V.:

Amendment 39–10580. Docket 98–NM–

45–AD.

Applicability: Model F.28 Mark 1000,

2000, 3000, and 4000 series airplanes; serial

numbers 11003 through 11201 inclusive,

11991, and 11992; on which Fokker Service

Bulletin F28/53–125, dated January 23, 1993,

has been accomplished; 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 (b) 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 loss of the coupling fitting

attachment bolts between the center wing

section and the fuselage, and consequent

reduced structural integrity of the airplane,

accomplish the following:

(a) Within 3,000 flight cycles or 1 year after

the effective date of this AD, whichever

occurs later, perform a one-time inspection to

determine the torque values of the coupling

fitting attachment bolts between the fuselage

and the center wing section at fuselage

station number 10790, in accordance with

Part 1 of the Accomplishment Instructions of

Fokker Service Bulletin F28/53–143, dated

August 30, 1996.

(1) If the torque values are within the limits

specified by the service bulletin, no further

action is required by this AD.

(2) If the torque value of any bolt is outside

the limits specified by the service bulletin,

prior to further flight, re-torque the bolt in

accordance with the service bulletin.

(b) 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.

(c) 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.

(d) The actions shall be done in accordance

with Fokker Service Bulletin F28/53–143,

dated August 30, 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 Fokker Services B.V.,

Technical Support Department, P.O. Box

75047, 1117 ZN Schiphol Airport, the

Netherlands. 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 Dutch airworthiness directive 1996–119

(A), dated September 30, 1996.

(e) This amendment becomes effective on

July 15, 1998.

Issued in Renton, Washington, on June 3,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–15251 Filed 6–9–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–312–AD; Amendment

39–10579; AD 98–12–25]

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, that requires

a one-time inspection to detect

corrosion, wear, or damage of the

operating mechanism of the forward

door of the main landing gear (MLG);

operational inspections to ensure

smooth operation of the MLG operating

mechanism; and follow-on actions. 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 partial seizure of the forward

door of the MLG operating mechanism,

which could result in the inability to

lower or retract the MLG.

DATES: Effective July 15, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 15,

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 April 6, 1998 (63 FR 16713). That

action proposed to require a one-time

inspection to detect corrosion, wear, or

damage of the operating mechanism of

the forward door of the main landing

gear (MLG); operational inspections to

ensure smooth operation of the MLG

operating mechanism; and follow-on

actions.

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, that it will take approximately 8

work hours per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $4,800, or $480 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.
31614 Federal Register / Vol. 63, No. 111 /Wednesday, June 10, 1998 /Rules and Regulations

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:

98–12–25 British Aerospace Regional

Aircraft [Formerly Jetstream Aircraft

Limited; British Aerospace (Commercial

Aircraft) Limited]: Amendment 39–

10579. Docket 97–NM–312–AD.

Applicability: BAe Model ATP airplanes,

constructor’s numbers 2001 through 2063

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 (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 as indicated, unless

accomplished previously.

To prevent partial seizure of the forward

door of the main landing gear (MLG)

operating mechanism, which could result in

the inability to lower or retract the MLG,

accomplish the following:

(a) Within 300 flight hours or within 90

days after the effective date of this AD,

whichever occurs first, perform a one-time

visual inspection to detect corrosion, wear, or

damage of the operating mechanism of the

forward door of the MLG; and clean,

degrease, and relubricate the door operating

mechanism; in accordance with British

Aerospace Service Bulletin ATP–32–84,

Revision 1, dated September 26, 1997.

(1) If no corrosion, wear, or damage is

detected during the inspection required by

paragraph (a) of this AD, no further action is

required by this AD.

(2) If any corrosion, damage, or worn

component is detected during the inspection

required by paragraph (a) of this AD,

accomplish the requirements of paragraphs

(a)(2)(i) and (a)(2)(ii) of this AD, as

applicable.

(i) If any corrosion or damage is detected,

prior to further flight, repair in accordance

with a method approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate.

(ii) If any worn component is detected,

within 600 flight hours after performing the

inspection required by paragraph (a) of this

AD, replace the component with a new or

serviceable part in accordance with the

service bulletin.

(b) Within 300 flight hours after

accomplishing the inspection required by

paragraph (a) of this AD, perform an

operational inspection to ensure smooth

operation of the spring strut of the forward

door of the MLG, and relubricate the

operating spring and sliding tube of the

forward door ‘A’ frame, in accordance with

British Aerospace Service Bulletin ATP–32–

84, Revision 1, dated September 26, 1997.

(1) Repeat the operational inspections

thereafter at intervals not to exceed 300 flight

hours, until the accumulation of 1,500 flight

hours after the accomplishment of the

inspection required by paragraph (a) of this

AD.

(2) Following the accomplishment of all

inspections required by paragraph (b)(1) of

this AD, repeat the operational inspections

and relubrication required by paragraph (b)

of this AD at intervals not to exceed 1,500

flight hours.

(c) If any discrepancy is detected during

any operational inspection and relubrication

required by paragraph (b) of this AD, prior to

further flight, replace any discrepant part

with a new or serviceable part in accordance

with a method approved by the Manager,

International Branch, ANM–116.

(d) 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. 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.

(e) 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.

(f) Except as provided by paragraphs

(a)(2)(i) and (c) of this AD, the actions shall

be done in accordance with British

Aerospace Service Bulletin ATP–32–84,

Revision 1, dated September 26, 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.

(g) This amendment becomes effective on

July 15, 1998.

Issued in Renton, Washington, on June 3,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–15249 Filed 6–9–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–182–AD; Amendment

39–10578; AD 98–12–24]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 Series Airplanes Equipped With

General Electric Model CF6–80A3

Series Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Airbus Model

A310 series airplanes. This action

requires a one-time inspection to detect