Federal Register / Vol. 65, No. 204 / Friday, October 20, 2000 / Rules and Regulations 62999

Revision 1, as required by this AD, are

acceptable for compliance with the

inspections in accordance with Lockheed

Service Bulletin 093–53–249, Revision 3,

required by AD 94–05–01.

(b) The following service bulletins listed in

Table II of Lockheed Service Bulletin 093–

51–040, Revision 1, dated October 1, 1997,

and Revision 2, dated October 21, 1999, are

excluded from the requirements of paragraph

(a) of this AD.

(1) The structural inspections specified in

Lockheed Service Bulletins 093–53–268,

Revision 1, dated July 2, 1996, and 093–53–

272, Revision 1, dated March 17, 1997, are

not required by this AD. The inspections

specified in these service bulletins are

required by AD 99–08–20, amendment 39–

11128.

(2) The structural inspections specified in

Lockheed Service Bulletin 093–53–258,

Revision 1, dated April 4, 1996, are not

required by this AD. Inspections equivalent

to those specified in that bulletin are

required by AD 95–17–03, amendment 39–

9332.

(3) The structural inspections specified in

Lockheed Service Bulletin 093–57–203,

Revision 5, dated April 22, 1996, are not

required by this AD. Inspections equivalent

to those specified in that bulletin are

required by AD 98–10–14, amendment 39–

10526.

Corrective Action

(c) If any cracking is detected during any

inspection required by paragraph (a) of this

AD, prior to further flight, accomplish the

actions specified in paragraph (c)(1), (c)(2),

(c)(3), or (c)(4) of this AD.

(1) Repair in accordance with the

applicable service bulletin referenced in

Table I or II of Lockheed Service Bulletin

093–51–040, Revision 1, dated October 1,

1997, or Revision 2, dated October 21, 1999.

(2) Repair in accordance with the

applicable section of the Lockheed L–1011

Structural Repair Manual.

(3) Accomplish the terminating

modification in accordance with the

applicable service bulletin referenced in

Table I or II of Lockheed Service Bulletin

093–51–040, Revision 1, dated October 1,

1997, or Revision 2, dated October 21, 1999.

(4) Repair in accordance with a method

approved by the Manager, Atlanta Aircraft

Certification Office (ACO), FAA.

Terminating Action

(d) Except as provided by paragraph (e) of

this AD, install the terminating modification

referenced in each service bulletin listed in

Table II of Lockheed Service Bulletin 093–

51–040, Revision 1, dated October 1, 1997, or

Revision 2, dated October 21, 1999; in

accordance with the applicable service

bulletin listed under ‘‘Service Bulletin

Number, Revision, and Date’’ in Table II of

Lockheed Service Bulletin 093–51–040,

Revision 1 or Revision 2. Except as provided

by paragraph (f) of this AD, install each

modification at the later of the times

specified in paragraphs (d)(1) and (d)(2) of

this AD. Such installation constitutes

terminating action for the applicable

structural inspection required by paragraph

(a) of this AD.

(1) Prior to the threshold specified in the

applicable service bulletin listed in Table II

of Lockheed Service Bulletin 093–51–040,

Revision 1 or Revision 2.

(2) Within 5 years or 5,000 flight cycles

after the effective date of this AD, whichever

occurs first.

Note 4: Installation of the terminating

modifications specified in Lockheed Service

Bulletin 093–53–268, Revision 1, dated July

2, 1996, and Lockheed Service Bulletin 093–

53–272, dated November 12, 1996, does not

constitute terminating action for the

repetitive inspection requirements of AD 99–

08–20, amendment 39–11128.

(e) Overhaul of the main landing gear

actuator in accordance with Lockheed

Service Bulletin 093–32–238, Revision 3,

dated April 11, 1996, as listed in Table II of

Lockheed Service Bulletin 093–51–040,

Revision 1, dated October 1, 1997, is not

required by paragraph (d) of this AD.

(f) At the later of the times specified in

paragraphs (f)(1) and (f)(2) of this AD: Install

the terminating modification listed in

Lockheed Service Bulletin 093–57–215, as

referenced in Table II of Lockheed Service

Bulletin 093–51–040, Revision 1, dated

October 1, 1997, or Revision 2, dated October

21, 1999. Such installation constitutes

terminating action for the inspections

required by AD 98–10–14, amendment 39–

10526.

(1) Prior to the threshold specified in

Lockheed Service Bulletin 093–57–203,

Revision 5, dated April 22, 1996.

(2) Within 2 years or 2,000 flight cycles

after the effective date of this AD, whichever

occurs first.

Alternative Methods of Compliance

(g) 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, Atlanta

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Atlanta ACO.

Note 5: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

Special Flight Permits

(h) Special flight permits may be issued in

accordance with §§ 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

(i) Except as provided by paragraphs (c)(2)

and (c)(4) of this AD, the actions shall be

done in accordance with Lockheed Service

Bulletin 093–51–040, Revision 1, dated

October 1, 1997; or Lockheed Service

Bulletin 093–51–040, Revision 2, dated

October 21, 1999. 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 Lockheed Martin Aircraft &

Logistics Center, 120 Orion Street,

Greenville, South Carolina 29605. Copies

may be inspected at the FAA, Transport

Airplane Directorate, 1601 Lind Avenue,

SW., Renton, Washington; at the FAA,

Atlanta Aircraft Certification Office, One

Crown Center, 1895 Phoenix Boulevard, suite

450, Atlanta, Georgia; or at the Office of the

Federal Register, 800 North Capitol Street,

NW., suite 700, Washington, DC.

Effective Date

(j) This amendment becomes effective on

November 24, 2000.

Issued in Renton, Washington, on October

11, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–26590 Filed 10–19–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–123–AD; Amendment

39–11937; AD 2000–21–05]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace BAe Model ATP Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all British Aerospace BAe

Model ATP airplanes. This action

requires repetitive inspections to detect

damage of the torque link apex joint of

the left-and right-hand main landing

gear (MLG); and replacement of nuts,

pins, and bolts with new parts, if

necessary. This action is necessary to

prevent separation of the top and

bottom torque links, and consequent

loss of directional control of the MLG.

This action is intended to address the

identified unsafe condition.

DATES: Effective November 6, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

6, 2000.

Comments for inclusion in the Rules

Docket must be received on or before

November 20, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

123–AD, 1601 Lind Avenue, SW.,

63000 Federal Register / Vol. 65, No. 204 / Friday, October 20, 2000 / Rules and Regulations

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays. Comments may be

submitted via fax to (425) 227–1232.

Comments may also be sent via the

Internet using the following address: 9-

an-iarcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2000–NM–123–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

The service information referenced in

this AD may be obtained from British

Aerospace Regional Aircraft American

Support, 13850 Mclearen Road,

Herndon, Virginia 20171. This

information may be examined 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.

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: The Civil

Aviation Authority (CAA), which is the

airworthiness authority for the United

Kingdom, notified the FAA that an

unsafe condition may exist on all British

Aerospace BAe Model ATP airplanes.

The CAA advises that it received reports

of failures of the torque links of the

main landing gear (MLG). The failures

have occurred at the bolt assembly (apex

joint) that attaches the top link to the

bottom link. The failures are caused by

wear in the threads of the pin and nut

of the bolt assembly. This wear is

caused by lateral oscillatory loading of

the joint coupled with its normal

movement as the MLG oleo compresses

and extends. Excessive wear in the

threads can result in loss of the nut and

separation of the joint when the

attachment pin migrates from its bushes

in the torque links. Separation of the top

and bottom torque links could result in

loss of directional control of the MLG.

Explanation of Relevant Service

Information

British Aerospace has issued Service

Bulletin ATP–32–99, dated February 21,

2000. The service bulletin references

Messier-Dowty Service Bulletin 200–

32–263, including Appendix A, dated

February 1, 2000, as an additional

source of service information for

accomplishment of the recommended

actions. The Messier-Dowty service

bulletin describes procedures for

repetitive inspections to detect damage

of the torque link apex joint of the leftand right-hand MLG; and replacement

of nuts, pins, and bolts with new parts,

if necessary.

The CAA classified the British

Aerospace service bulletin as mandatory

and issued British airworthiness

directive 008–02–2000 in order to

assure the continued airworthiness of

these airplanes in the United Kingdom.

FAA’s Conclusions

This airplane model is manufactured

in the United Kingdom and is type

certificated for operation in the United

States under the provisions of § 21.29 of

the Federal Aviation Regulations (14

CFR 21.19) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the CAA has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the CAA,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, this AD is being issued to

prevent separation of the top and

bottom torque links, and consequent

loss of directional control of the MLG.

This AD requires accomplishment of the

actions specified in the service bulletins

described previously.

Cost Impact

None of the BAe Model ATP airplanes

affected by this action are on the U.S.

Register. All airplanes included in the

applicability of this rule currently are

operated by non-U.S. operators under

foreign registry; therefore, they are not

directly affected by this AD action.

However, the FAA considers that this

rule is necessary to ensure that the

unsafe condition is addressed in the

event that any of these subject airplanes

are imported and placed on the U.S.

Register in the future.

Should an affected airplane be

imported and placed on the U.S.

Register in the future, it would require

approximately 2 work hours to

accomplish the required actions, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of this AD would be $120 per airplane.

Determination of Rule’s Effective Date

Since this AD action does not affect

any airplane that is currently on the

U.S. register, it has no adverse economic

impact and imposes no additional

burden on any person. Therefore, prior

notice and public procedures hereon are

unnecessary and the amendment may be

made effective in less than 30 days after

publication in the Federal Register. 

Comments Invited

Although this action is in the form of

a final rule and was not preceded by

notice and opportunity for public

comment, comments are invited on this

rule. Interested persons are invited to

comment on this rule by submitting

such written data, views, or arguments

as they may desire. Communications

shall identify the Rules Docket number

and be submitted in triplicate to the

address specified under the caption

ADDRESSES. All communications

received on or before the closing date

for comments will be considered, and

this rule may be amended in light of the

comments received. Factual information

that supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the AD is being requested.

• Include justification (e.g., reasons or

data) for each request.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–123–AD.’’

The postcard will be date stamped and

returned to the commenter.

Federal Register / Vol. 65, No. 204 / Friday, October 20, 2000 / Rules and Regulations 63001

Regulatory Impact

The regulations adopted herein will

not have a substantial direct effect 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, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

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:

2000–21–05 British Aerospace Regional

Aircraft [Formerly Jetstream Aircraft

Limited; British Aerospace (Commercial

Aircraft) Limited]: Amendment 39–

11937. Docket 2000–NM–123–AD.

Applicability: All BAe Model ATP

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 (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 separation of the top and

bottom torque links, and consequent loss of

directional control of the main landing gear

(MLG), accomplish the following:

Inspection

(a) Within 800 landings or 4 months after

the effective date of this AD, whichever

occurs first: Perform an inspection to detect

damage of the torque link apex joint of the

left- and right-hand MLG, in accordance with

British Aerospace Service Bulletin ATP–32–

99, dated February 21, 2000, and MessierDowty Service Bulletin 200–32–263,

including Appendix A, dated February 1,

2000. If any damage exceeds the limit

specified in the Messier-Dowty service

bulletin, prior to further flight, replace the

nut, bolt, and pin with new parts, as

applicable, in accordance with that service

bulletin. Repeat the inspection thereafter at

intervals not to exceed 1,000 landings.

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,

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

(c) Special flight permits may be issued in

accordance with §§ 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 actions shall be done in accordance

with British Aerospace Service

Bulletin ATP–32–99, dated February 21,

2000, and Messier-Dowty Service Bulletin

200–32–263, including Appendix A, dated

February 1, 2000. 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 Regional

Aircraft American Support, 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.

Note 3: The subject of this AD is addressed

in British airworthiness directive 008–02–

2000.

Effective Date

(e) This amendment becomes effective on

November 6, 2000.

Issued in Renton, Washington, on October

12, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–26710 Filed 10–19–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–379–AD; Amendment

39–11934; AD 2000–21–02]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A330 and A340 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A330 and A340 series airplanes, that

requires revising the Airplane Flight

Manual to include new flight

operational procedures for the fuel

system; repetitive inspections of the

trim transfer fuel line in the vicinity of

the aft pressure bulkhead located

between frame (FR) 77 and FR86 to

detect any discrepancy; and corrective

actions, if necessary. This amendment

also requires modification of the air

release valve in the fuel trim tank

transfer system, which constitutes

terminating action for the requirements

of this 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 damage to the fuel

trim transfer system, which could cause

rupture of the trim transfer fuel line due

to pressure build-up, and result in fuel

leakage from that fuel line. This action

is intended to address the identified

unsafe condition.

DATES: Effective November 24, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

24, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained