Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations 34571

Fokker Service Bulletin F28/27–183, dated

November 21, 1994. If any discrepancy is

found, prior to further flight, replace the

actuator with a new or serviceable actuator

in accordance with the service bulletin.

(c) Within 3 years after the effective date

of this AD, replace the horizontal stabilizer

actuator with an actuator that has been

modified and re-marked in accordance with

Part 2 of the Accomplishment Instructions of

Fokker Service Bulletin F28/27–183, dated

November 21, 1994.

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

person shall install a horizontal stabilizer

control unit on any airplane, unless the

horizontal stabilizer actuator has been

modified and re-marked in accordance with

Part 2 of the Accomplishment Instructions of

Fokker Service Bulletin F28/27–183, dated

November 21, 1994.

(e) 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.

(f) 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.

(g) The actions shall be done in accordance

with Fokker Service Bulletin F28/27–180,

dated July 3, 1992, and Fokker Service

Bulletin F28/27–183, dated November 21,

1994.

(1) The incorporation by reference of

Fokker Service Bulletin F28/27–183, dated

November 21, 1994, is approved by the

Director of the Federal Register in accordance

with 5 U.S.C. 552(a) and 1 CFR part 51.

(2) The incorporation by reference of

Fokker Service Bulletin F28/27–180, dated

July 3, 1992, was approved previously by the

Director of the Federal Register as of

September 9, 1992 (57 FR 38432, August 25,

1992).

(3) 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 1992–007/

2(A), dated January 31, 1995.

(h) This amendment becomes effective on

July 30, 1998.

Issued in Renton, Washington, on June 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–16451 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–51–AD; Amendment

39–10617; AD 98–13–26]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace Model BAC 1–11 200 and

400 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all British Aerospace

Model BAC 1–11 200 and 400 series

airplanes, that requires repetitive

detailed visual inspections to detect

cracking in the trunnion fittings located

in the nose landing gear (NLG) bay of

the forward fuselage; and repair, 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 detect and correct cracking

in the trunnion fittings of the NLG,

which could lead to collapse of the NLG

during takeoff and landing, and possible

injury to the flight crew and passengers.

DATES: Effective July 30, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 30,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from British Aerospace, Service

Support, Airbus Limited, P.O. Box 77,

Bristol BS99 7AR, England. 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 all British

Aerospace Model BAC 1–11 200 and

400 series airplanes was published in

the Federal Register on April 21, 1998

(63 FR 19682). That action proposed to

require repetitive detailed visual

inspections to detect cracking in the

trunnion fittings located in the nose

landing gear (NLG) bay of the forward

fuselage; and repair, 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 42 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 1

work hour 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 the inspection required by this AD on

U.S. operators is estimated to be $2,520,

or $60 per airplane, per inspection

cycle.

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
34572 Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations

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:

98–13–26 British Aerospace Airbus Limited

(Formerly British Aerospace

Commercial Aircraft Limited, British

Aerospace Aircraft Group): Amendment

39–10617. Docket 98–NM–51–AD.

Applicability: All Model BAC 1–11 200

and 400 series airplanes, 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 detect and correct cracking in the

trunnion fittings of the nose landing gear

(NLG), which could lead to collapse of the

NLG during takeoff and landing, and possible

injury to the flight crew and passengers,

accomplish the following:

(a) Perform a detailed visual inspection for

cracking on the left- and right-hand trunnion

fittings of the NLG, in the area of the

trunnion cap attachment holes, in accordance

with British Aerospace Alert Service Bulletin

53–A–PM6035, Revision 1, dated March 7,

1996; at the time specified in paragraph (a)(1)

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

(1) For airplanes on which British

Aerospace Modification PM5308 has not

been accomplished: Perform the inspection

within 6 years after the effective date of this

AD, or within 11 years after the last

inspection accomplished in accordance with

the alert service bulletin, whichever occurs

later. Repeat the inspection thereafter at

intervals not to exceed 11 years.

(2) For airplanes on which British

Aerospace Modification PM5308 has been

accomplished: Perform the inspection within

30 months after the effective date of this AD,

or within 5 years after the last inspection

accomplished in accordance with the alert

service bulletin, whichever occurs later.

Repeat the inspection thereafter at intervals

not to exceed 6 years.

(b) If any crack is found during any

inspection required by paragraph (a) of this

AD, prior to further flight, repair the crack in

accordance with a method approved by the

Manager, International Branch, ANM–116,

FAA, Transport Airplane Directorate.

(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. 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 inspections shall be done in

accordance with British Aerospace Alert

Service Bulletin 53–A–PM6035, Revision 1,

dated March 7, 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 British Aerospace, Service

Support, Airbus Limited, P.O. Box 77, Bristol

BS99 7AR, England. 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 004–03–96,

dated April 26, 1996.

(f) This amendment becomes effective on

July 30, 1998.

Issued in Renton, Washington, on June 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–16450 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–89–AD; Amendment

39–10618; AD 98–13–27]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328–100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Dornier Model

328–100 series airplanes, that requires a

one-time inspection to detect

discrepancies of circuit breaker panels

10VE and 11VE; follow-on corrective

actions; modification of the contact

points; and installation of a high

capacity fuse. This amendment also

requires replacement of power relays

32HB and 36HB on relay panel 22VE

with new parts. 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 short

circuits of the contact points and power

relays on the circuit breaker panels,

which could result in increased risk of

smoke and fire damage in the flight

compartment.

DATES: Effective July 30, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 30,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from FAIRCHILD DORNIER, DORNIER

Luftfahrt GmbH, P.O. Box 1103, D–

82230 Wessling, Germany. 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,