Federal Register / Vol. 65, No. 2 / Tuesday, January 4, 2000 / Rules and Regulations 207

is $60 per work hour. Required parts

will cost approximately $104 per

airplane. Based on these figures, the cost

impact of the AD on U.S. operators is

estimated to be $29,584, or $344 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:

99–27–05 Boeing: Amendment 39–11486.

Docket 97–NM–241–AD.

Applicability: Model 767–200, –300, and

–300F series airplanes, line numbers 1

through 607 inclusive; equipped with part

number S160T300-series carbon brakes;

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 (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 failure of the brake housing in

the torque rod region, which could reduce

the braking capability of the airplane and/or

prevent the extension of a main landing gear,

accomplish the following:

Replacement

(a) Within 360 days after the effective date

of this AD, replace the hydraulic reducer

fitting in the return port of the alternate brake

selector valve with a new restrictor fitting, in

accordance with Boeing Service Bulletin

767–32–0152, dated June 6, 1996; Revision 1,

dated June 27, 1996; or Revision 2, dated July

10, 1997.

Alternative Methods of Compliance

(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, Seattle

Aircraft Certification Office (ACO), 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, Seattle ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permits

(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.

Incorporation by Reference

(d) The replacement shall be done in

accordance with Boeing Service Bulletin

767–32–0152, dated June 6, 1996; Boeing

Service Bulletin 767–32–0152, Revision 1,

dated June 27, 1996; or Boeing Service

Bulletin 767–32–0152, Revision 2, dated July

10, 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 Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington 98124–

2207. 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.

(e) This amendment becomes effective on

February 8, 2000.

Issued in Renton, Washington, on

December 22, 1999.

Vi L. Lipski,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–11 Filed 1–3–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–31–AD; Amendment

39–11492; AD 99–27–11]

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 to all British Aerospace

Model BAC 1–11 200 and 400 series

airplanes, that requires replacing the

thrust reverser control unit selector

valve with a new or modified valve and

inspecting for proper rigging of the

thrust reverser cable drums and thrust

reverser control unit selector valve

detent, and corrective actions, if

necessary. This amendment also

requires revising the Airplane Flight

Manual to provide the flight crew with

procedures to address uncontrolled

operation of the thrust reverser system.

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 provide the flight crew with

procedures in the event of

uncommanded deployment of the thrust

reverser, and to prevent uncommanded

deployment of the thrust reverser in

flight or on the ground, which could

result in reduced controllability of the

airplane.

208 Federal Register / Vol. 65, No. 2 / Tuesday, January 4, 2000 / Rules and Regulations

DATES: Effective February 8, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February 8,

2000.

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 September 15,

1999 (64 FR 50023). That action

proposed to require replacing the thrust

reverser control unit selector valve with

a new or modified valve and inspecting

for proper rigging of the thrust reverser

cable drums and thrust reverser control

unit selector valve detent, and

corrective actions, if necessary. That

action also proposed to require revising

the Airplane Flight Manual (AFM) to

provide the flight crew with procedures

to address uncontrolled operation of the

thrust reverser system.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Clarification of Paragraph (c)

The commenter proposes adding

clarification in paragraph (c) of the

proposed AD to distinguish Advance

Amendment Bulletin 16 (which applies

to Model 200 series airplanes) from

Advance Amendment Bulletin 12

(which applies to Model 400 series

airplanes). The FAA concurs with this

proposed change to distinguish between

Advanced Amendment Bulletins 16 and

12 and the appropriate airplane series,

and has revised paragraph (c) of the

final rule accordingly.

Correction to British Airworthiness

Directive Number

This same commenter states that the

correct number of the British

airworthiness directive (identified as

‘‘002–09–08’’ in the Explanation of

Relevant Service Information of the

proposed AD) should be ‘‘002–09–98.’’

The FAA agrees that the number was

incorrectly identified in the referenced

section of the proposed AD. However,

the Explanation of Relevant Service

Information section is not restated

within the final rule; therefore, no

change to the final rule is necessary.

British airworthiness directive 002–09–

98 is correctly identified in NOTE 3 of

the proposal and this final rule.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the change

described previously. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

Cost Impact

The FAA estimates that 16 airplanes

of U.S. registry will be affected by this

AD.

It will take approximately 6 work

hours per airplane to accomplish the

inspections, at an average labor rate of

$60 per work hour. Based on these

figures, the cost impact of the

inspections required by this AD on U.S.

operators is estimated to be $5,760, or

$360 per airplane.

It will take approximately 1 work

hour per airplane to accomplish the

replacement, at an average labor rate of

$60 per work hour. Required parts will

cost approximately $16,000 per

airplane. Based on these figures, the cost

impact of the replacement required by

this AD on U.S. operators is estimated

to be $256,960, or $16,060 per airplane.

It will take approximately 1 work

hour per airplane to accomplish the

AFM revision, at an average labor rate

of $60 per work hour. Based on these

figures, the cost impact of the AFM

revision required by this AD on U.S.

operators is estimated to be $960, or $60

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:

99–27–11 British Aerospace Airbus

Limited (Formerly British Aerospace

Commercial Aircraft Limited, British

Aerospace Aircraft Group): Amendment

39–11492. Docket 99–NM–31–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

Federal Register / Vol. 65, No. 2 / Tuesday, January 4, 2000 / Rules and Regulations 209

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 (e) 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 provide the flight crew with procedures

in the event of uncommanded deployment of

the thrust reverser and to prevent

uncommanded deployment of the thrust

reverser in flight or on the ground, which

could result in reduced controllability of the

airplane, accomplish the following:

(a) Within 30 days after the effective date

of this AD, perform an inspection for proper

rigging of the thrust reverser cable drums, in

accordance with British Aerospace Alert

Service Bulletin 76–A–PM6043, Issue No. 1,

dated September 18, 1998. If any drum is

found to be improperly rigged, prior to

further flight, accomplish the adjustments

specified in paragraph 3, ‘‘Adjustments,’’ of

the alert service bulletin.

(b) Prior to further flight after

accomplishing the inspection required by

paragraph (a) of this AD, perform an

inspection for proper rigging of the thrust

reverser selector valve detent, in accordance

with Rolls-Royce Spey Service Bulletin

Sp78–131, dated September 1998. If any

discrepancy is found, prior to further flight,

accomplish the adjustments specified in

paragraph 3, ‘‘Adjustments,’’ of the service

bulletin.

(c) Within 30 days after the effective date

of this AD, revise the Emergency and

Abnormal Procedures Sections of the FAAapproved Airplane Flight Manual (AFM) by

inserting, into the applicable sections of the

AFM, British Aerospace Advance

Amendment Bulletin No. 12 (for Model 400

series airplanes) or No. 16 (for Model 200

series airplanes), as applicable; both dated

August 19, 1997.

(d) Within 12 months after the effective

date of this AD, replace the thrust reverser

control unit selector valve with a new or

modified selector valve in accordance with

British Aerospace Service Bulletin 78–

PM6047, Revision 1, dated November 27,

1998.

Alternative Methods of Compliance

(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.

Special Flight Permits

(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.

Incorporation by Reference

(g) The actions shall be done in accordance

with British Aerospace Alert Service Bulletin

76–A–PM6043, Issue No. 1, dated September

18, 1998; Rolls-Royce Spey Service Bulletin

Sp78–131, dated September 1998; British

Aerospace Service Bulletin 78–PM6047,

Revision 1, dated November 27, 1998; British

Aerospace Advance Amendment Bulletin No.

12, dated August 19, 1997; and British

Aerospace Advance Amendment Bulletin No.

16, dated August 19, 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 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 directives 002–09–98

and 005–11–98.

(h) This amendment becomes effective on

February 8, 2000.

Issued in Renton, Washington, on

December 23, 1999.

Vi L. Lipski,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–10 Filed 1–3–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–200–AD; Amendment

39–11489; AD 99–27–08]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB SF340A and SAAB 340B Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Saab Model SAAB

SF340A and SAAB 340B series

airplanes, that requires repetitive

inspections of the control quadrant for

loose screws, and replacement of the

control quadrant with a modified part,

which constitutes terminating action for

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 the power levers from binding

due to the backing out of screws that

secure the solenoid bracket within the

flight idle stop assembly, which could

result in the malfunction of the flight

idle stop mechanism and the override

function, and the inability to move the

power levers aft of flight idle.

DATES: Effective February 8, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February 8,

2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Saab Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈ping,

Sweden. 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 Saab Model

SAAB SF340A and SAAB 340B series

airplanes was published in the Federal

Register on September 13, 1999 (64 FR

49418). That action proposed to require

repetitive inspections of the control

quadrant for loose screws, and

replacement of the control quadrant

with a modified part, which would

terminate action for the repetitive

inspections.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Restatement of Unsafe Condition

One commenter, the manufacturer,

requests that the proposed AD be

revised to restate the identified unsafe

condition. The commenter states that

malfunction of the automatic flight idle