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,
Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations 34573

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 Dornier

Model 328–100 series airplanes was

published in the Federal Register on

April 21, 1998 (63 FR 19689). That

action proposed to require 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. That

action also proposed to require

replacement of power relays 32HB and

36HB on relay panel 22VE with new

parts.

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 50 airplanes

of U.S. registry will be affected by this

AD.

It will take approximately 2 work

hours per airplane to accomplish the

required inspection and application of

sealant to the contact points, at an

average labor rate of $60 per work hour.

The cost of the sealant will be minimal.

Based on this figure, the cost impact of

the required inspection and

modification on U.S. operators is

estimated to be $120 per airplane.

It will take approximately 1 work

hour per airplane to accomplish the

required installation of a high capacity

fuse on the circuit breaker panels, at an

average labor rate of $60 per work hour.

Required parts will be provided by the

manufacturer at no cost to the operators.

Based on this figure, the cost impact of

the required installation on U.S.

operators is estimated to be $60 per

airplane.

It will take approximately 5 work

hours per airplane to accomplish the

required replacement of the relays, at an

average labor rate of $60 per work hour.

Required parts will be provided by the

manufacturer at no cost to the operators.

Based on this figure, the cost impact of

the required replacement on U.S.

operators is estimated to be $300 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

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:

98–13–27 Dornier Luftfahrt GmbH:

Amendment 39–10618. Docket 98-NM–

89-AD.

Applicability: Model 328–100 series

airplanes equipped with circuit breaker

panels 10VE up to and including serial

number 131, and 11VE up to and including

serial number 133; and Model 328–100 series

airplanes, serial numbers 3005 through 3095

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 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, accomplish the

following:

(a) For Model 328–100 series airplanes

equipped with circuit breaker panels 10VE

up to and including serial number 131, and

11VE up to and including serial number 133:

Within 14 days after the effective date of this

AD, perform a one-time visual inspection to

detect discrepancies of circuit breaker panels

10VE and 11VE at the back lighting contact

points, in accordance with Dornier Alert

Service Bulletin ASB–328–31–016, dated

April 2, 1997.

(1) If no discrepancy is detected, prior to

further flight, modify the contact points by

applying additional sealant in accordance

with the alert service bulletin.

(2) If any discrepancy is detected, prior to

further flight, replace the damaged circuit

breaker panel with a new or serviceable

panel and modify the contact points by

applying additional sealant, in accordance

with the alert service bulletin.

(b) For Model 328–100 series airplanes,

serial numbers 3005 through 3095 inclusive:

Within 90 days after the effective date of this

AD, install a jiffy junction fitted with a high

capacity fuse on circuit breaker panels 10VE

and 11VE, in accordance with version 1 or

version 2, as applicable, of the

Accomplishment Instructions of Dornier

Service Bulletin SB–328–31–226, dated June

16, 1997, including Price/Material

Information Sheet.

(c) For Model 328–100 series airplanes,

serial numbers 3005 through 3089 inclusive:

Within 90 days after the effective date of this

AD, replace relays 32HB and 36HB, part
34574 Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations

number (P/N) DON405M520U5NL, on relay

panel 22VE with new relays, P/N 2504MY1,

in accordance with Dornier Service Bulletin

SB–328–21–218, dated July 2, 1997,

including Price/Material Information Sheet.

(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, 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.

(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) The actions shall be done in accordance

with Dornier Alert Service Bulletin ASB–

328–31–016, dated April 2, 1997; Dornier

Service Bulletin SB–328–31–226, dated June

16, 1997, including Price/Material

Information Sheet; or Dornier Service

Bulletin SB–328–21–218, dated July 2, 1997,

including Price/Material Information Sheet,

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 FAIRCHILD DORNIER,

DORNIER Luftfahrt GmbH, P.O. Box 1103, D–

82230 Wessling, Germany. 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 German airworthiness directives 97–136,

dated May 22, 1997; 97–330, dated November

20, 1997; and 97–323, dated November 20,

1997.

(g) 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. 98–16449 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–83–AD; Amendment

39–10615; AD 98–13–24]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model CL–600–2B19 (Regional Jet

Series 100) Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Bombardier Model

CL–600–2B19 (Regional Jet Series 100)

airplanes, that currently requires a

revision to the Airplane Flight Manual

(AFM) to prohibit the use of mach trim

and to add speed restrictions if the

autopilot is disengaged or inoperative.

That AD also requires installation of an

associated placard. This amendment

adds requirements for replacement of

the horizontal stabilizer trim control

unit (HSTCU) with a new HSTCU, and

reactivation of the mach trim engage/

disengage switch/light (if deactivated).

Accomplishment of these actions

terminates the requirements of the

existing AD. This amendment also

limits the applicability of the existing

AD. 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 deficiencies of the

HSTCU, which could result in a noseup trim runaway when a single

component in the mach trim circuit

fails.

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 Bombardier, Inc., Canadair,

Aerospace Group, P.O. Box 6087,

Station Centre-ville, 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:

Peter Cuneo, 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) 256–7506; fax

(516) 568–2716.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 95–13–04,

amendment 39–9325 (60 FR 38668, July

28, 1995), which is applicable to certain

Bombardier Model CL–600–2B19

(Regional Jet Series 100) airplanes, was

published in the Federal Register on

April 14, 1998 (63 FR 18160). The

action proposed to continue to require

a revision to the AFM to prohibit the

use of mach trim and to add speed

restrictions if the autopilot is

disengaged or inoperative, and to

require installation of an associated

placard. The action proposed to add

requirements for replacement of the

horizontal stabilizer trim control unit

(HSTCU) with a new HSTCU, and

reactivation of the mach trim engage/

disengage switch/light (if deactivated).

Accomplishment of these actions would

terminate the requirements of the

existing AD. That AD also proposed to

limit the applicability of the existing

AD.

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.

Corrections to the Proposal

In paragraph (b) of the proposed rule,

the FAA inadvertently referenced

Bombardier Service Bulletin S.B. 601R–

27–053, dated May 27, 1996; and

Revision A, dated August 26, 1996; for

accomplishment of the proposed

actions. Paragraph (b) of this final rule

has been revised to reference only

Bombardier Service Bulletin S.B. 601R–

27–053, Revision B, dated February 21,

1997. In addition, NOTE 3 has been

added to reference the original issue and

Revision A of the service bulletin as

acceptable means of compliance for

operators that have accomplished the

applicable actions prior to the issuance

of this AD.

The FAA has become aware of a

typographical error that appeared in

paragraph (d)(2) of the proposal. The AD