68876 Federal Register / Vol. 65, No. 221 / Wednesday, November 15, 2000 / Rules and Regulations

bulletin (SB) No. Sp 72–1063, dated May

1999.

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, Engine

Certification Office (ECO). Operators shall

submit their request through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, ECO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the ECO.

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 aircraft to a

location where the requirements of this AD

can be accomplished.

(d) The rework shall be done in accordance

with the following Rolls-Royce service

bulletin: (SB) No. Sp 72–1063, dated May

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 Rolls-Royce plc, PO Box 31, Derby,

England, DE248BJ; telephone No. 011–44–

1332–242–424; fax No. 011–44–1332–245–

418. Copies may be inspected at the FAA,

New England Region, Office of the Regional

Counsel, 12 New England Executive Park,

Burlington, MA; or at the Office of the

Federal Register, 800 North Capitol Street,

NW., Suite 700, Washington, DC.

Effective Date of This AD

(e) This amendment becomes effective on

December 20, 2000.

Issued in Burlington, Massachusetts, on

November 6, 2000.

Donald Plouffe,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 00–28960 Filed 11–14–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–104–AD; Amendment

39–11977; AD 2000–23–07]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300, A300–600, and A310 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Airbus Model

A300 and all Model A300–600 and

A310 series airplanes, that currently

requires performing a pitch trim system

test to detect any continuity defect in

the autotrim function, and follow-on

corrective actions, if necessary. This

amendment requires repetitive

inspections of the autotrim function to

detect such defects, and corrective

actions, if necessary. This amendment

also expands the applicability to

include additional airplanes. 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 a sudden change in pitch due to

an out-of-trim condition combined with

an autopilot disconnect, which could

result in reduced controllability of the

airplane.

DATES: Effective December 20, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

20, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. 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)

by superseding AD 2000–02–04,

amendment 39–11522 (65 FR 3799,

January 25, 2000), which is applicable

to certain Airbus Model A300 and all

Model A300–600 and A310 series

airplanes, was published in the Federal

Register on June 12, 2000 (65 FR 36801).

The action proposed to supersede AD

2000–02–04 to continue to require

performing a pitch trim system test to

detect any continuity defect in the

autotrim function, and follow-on

corrective actions, if necessary. The

action also proposed to require

repetitive inspections of the autotrim

function to detect such defects, and

corrective actions, if necessary.

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.

Request To Revise Applicability

The manufacturer, Airbus, requests

that the applicability of the proposed

AD be revised to exclude Model A300–

600 series airplanes on which Airbus

Modification 12277 has been

accomplished during production. In

addition, since the issuance of the

proposed AD, the Direction Ge ́ne ́rale de

l’Aviation Civile (DGAC), which is the

airworthiness authority for France,

issued French airworthiness directive

2000–115–304(B) R2, dated July 12,

2000, as revised by Erratum, dated

August 9, 2000, to exclude those

airplanes from the applicability. The

FAA concurs with the commenter’s

request, and has revised the

applicability of this final rule

accordingly.

Request To Revise Reporting

Requirement

The Air Transport Association (ATA)

of America, on behalf of one of its

members, requests that the reporting

requirement specified in the proposed

AD be revised to require that inspection

findings be reported to Airbus on a

monthly basis, rather than 10 days

following each inspection. The

commenter states that since any

necessary corrective actions would

occur immediately as a result of the

inspection findings, monthly reporting

would not affect the safe operation of

the airplane. For certain airlines,

monthly reporting would greatly

simplify the administrative tasks

associated with ongoing reporting.

The FAA concurs partially. The FAA

agrees that corrective actions, if

necessary, would be required prior to

further flight; therefore, extension of the

compliance time in question will not

affect the safe operation of the airplane.

However, the FAA considers that

requiring report submittals on a

monthly basis could lead to possible

misinterpretation as to the specific

deadline for submission of each report.

In light of this, the FAA has revised

the final rule to require submission of

each report within 30 days after

accomplishing each inspection (for

inspections accomplished after the

effective date of this AD), or within 30

days after the effective date of the AD

(for inspections accomplished prior to

the effective date of this AD). Operators

are provided with additional time to

Federal Register / Vol. 65, No. 221 / Wednesday, November 15, 2000 / Rules and Regulations 68877

submit each report, and may choose to

combine submittals of all reports for the

past 30 days, which would reduce the

administrative burden. Paragraph (b) of

this AD has been revised accordingly.

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 changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Interim Action

This is considered to be interim

action for Model A300–600 and A310

series airplanes. The manufacturer has

advised that it currently is developing a

modification that will positively address

the unsafe condition addressed by this

AD. Once this modification is

developed, approved, and available, the

FAA may consider additional

rulemaking for these airplanes.

Cost Impact

There are approximately 120

airplanes of U.S. registry that will be

affected by this AD. The inspection that

is required by this AD will take

approximately 1 work hour per airplane

to accomplish, at an average labor rate

of $60 per work hour. Based on these

figures, the cost impact of the required

action on U.S. operators is estimated to

be $7,200, or $60 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 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

removing amendment 39–11522 (65 FR

3799, January 25, 2000), and by adding

a new airworthiness directive (AD),

amendment 39–11977, to read as

follows:

2000–23–07 Airbus Industrie: Amendment

39–11977. Docket 2000–NM–104–AD.

Supersedes AD 2000–02–04,

Amendment 39–11522.

Applicability: This AD applies to the

airplanes listed in Table 1. of this AD,

certificated in any category:

TABLE 1.—APPLICABILITY

Airbus model Description

A300 B2–203 airplanes and A300–B4–203 airplanes ............................. In a forward facing cockpit version, as listed in Airbus Service Bulletin

A300–22A0115, Revision 02, dated March 7, 2000.

A310 series airplanes ............................................................................... All.

A300–600 series airplanes ....................................................................... On which Airbus Modification 12277 has not been accomplished during

production.

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 (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 prevent a sudden change in pitch due

to an out-of-trim condition combined with an

autopilot disconnect, which could result in

reduced controllability of the airplane,

accomplish the following:

Repetitive Inspections

(a) At the applicable time specified by

paragraph (a)(1) or (a)(2) of this AD: Perform

an inspection of the autotrim function by

testing the flight control computer (FCC)/

flight augmentation computer (FAC) integrity

in logic activation of the autotrim, in

accordance with Airbus Service Bulletin

A300–22A6042, Revision 01 (for Model

A300–600 series airplanes); A300–22A0115,

Revision 02 (for Model A300 series

airplanes); or A310–22A2053, Revision 01

(for Model A310 series airplanes); all dated

March 7, 2000; as applicable. If any

discrepancy is found, prior to further flight,

perform all applicable corrective actions

(including trouble-shooting, replacing the

FCC and/or FAC, retesting, checking the

wires between certain FCC and FAC pins,

and repairing damaged wires) in accordance

with the applicable service bulletin. Repeat

the inspection thereafter at intervals not to

exceed 500 flight hours.

(1) For airplanes on which the pitch trim

system test has been performed in

accordance with the requirements of AD

2000–02–04, amendment 39–11522: Inspect

within 500 flight hours after accomplishment

of the test required by that AD, or within 20

days after the effective date of this AD,

whichever occurs later.

(2) For all other airplanes: Inspect within

20 days after the effective date of this AD.

Reporting Requirement

(b) For all inspections required by

paragraph (a) of this AD: At the applicable

time specified by paragraph (b)(1) or (b)(2) of

this AD, submit a report of the inspection

results (both positive and negative findings)

to AI/SE–D32 Technical Data and

68878 Federal Register / Vol. 65, No. 221 / Wednesday, November 15, 2000 / Rules and Regulations

Documentation Services, Airbus Industrie

Customer Services Directorate, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex

France; fax (+33) 5 61 93 28 06.

(1) For inspections accomplished after the

effective date of this AD: Submit the report

within 30 days after performing the

inspection.

(2) For inspections accomplished prior to

the effective date of this AD: Submit the

report within 30 days after the effective date

of this AD.

Alternative Methods of Compliance

(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, 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

(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.

Incorporation by Reference

(e) The actions shall be done in accordance

with Airbus Service Bulletin A300–22A6042,

Revision 01, including Appendix 01, dated

March 7, 2000; Airbus Service Bulletin

A300–22A0115, Revision 02, including

Appendix 01, dated March 7, 2000; or Airbus

Service Bulletin A310–22A2053, Revision 01,

including Appendix 01, dated March 7, 2000;

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 Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. 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 French airworthiness directive 2000–115–

304(B) R2, dated July 12, 2000, as revised by

Erratum, dated August 9, 2000.

(f) This amendment becomes effective on

December 20, 2000.

Issued in Renton, Washington, on

November 6, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–28967 Filed 11–14–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–114–AD; Amendment

39–11978; AD 2000–23–08]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 and A300–600 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A310 and A300–600 series airplanes,

that requires replacement of the flight

control computers (FCC) with new,

improved FCC’s having updated

software installed. This amendment also

requires, for some airplanes,

modification of the wiring of the FCC’s.

The actions specified by this AD are

intended to prevent autopilot reversions

in certain flight conditions, which could

result in misunderstanding by the flight

crew and consequent reduced ability to

take appropriate action. This action is

intended to address the identified

unsafe condition.

DATES: Effective December 20, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

20, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. 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,

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 Airbus

Model A310 and A300–600 series

airplanes was published in the Federal

Register on August 25, 2000 (65 FR

51775). That action proposed to require

replacement of the flight control

computers (FCC) with new, improved

FCC’s having updated software

installed. That action also proposed to

require, for some airplanes,

modification of the wiring of the FCC’s.

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 116 airplanes

of U.S. registry will be affected by this

proposed AD.

It will take as much as 17 work hours

per airplane to accomplish the required

replacements, at an average labor rate of

$60 per work hour. Required parts will

cost as much as $5,064 per airplane.

Based on these figures, the cost impact

of the required replacements on U.S.

operators is estimated to be as much as

$705,744, or $6,084 per airplane.

It will take approximately 1 work

hour per airplane to accomplish the

required modification of the wiring, at

an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of the required modification on

U.S. operators is estimated to be $6,960,

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. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

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.