Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations 37017

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:

2000–11–19 Boeing: Amendment 39–11767.

Docket 98–NM–313–AD.

Applicability: Model 767–200 and –300

series airplanes, as listed in Boeing Alert

Service Bulletin 767–25A0260, dated July 9,

1998; certificated in any category; except

Model 767 series airplanes that have

undergone conversion to freighter

configurations, and on which the off-wing

escape system has been removed or

deactivated.

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 non-deployment of an escape

slide during an emergency evacuation, which

could slow down the evacuation of the

airplane and result in injury to passengers or

flightcrew; and to detect damaged disconnect

housings in the off-wing escape slide

compartments, which could result in

unexpected deployment of an escape slide

during maintenance, and consequent injury

to maintenance personnel; accomplish the

following:

Inspections

(a) Prior to the accumulation of 6,000 total

flight hours, or within 18 months after the

effective date of this AD, whichever occurs

later, perform a detailed visual inspection to

detect wear or damage of the door latches

and disconnect housings in the off-wing

escape slide compartments, in accordance

with Boeing Alert Service Bulletin 767–

25A0260, dated July 9, 1998. Repeat the

inspection thereafter at intervals not to

exceed 6,000 flight hours or 18 months,

whichever occurs later.

Note 2: Boeing Alert Service Bulletin 767–

25A0260, dated July 9, 1998, allows

repetitive inspections of a door latch having

part number H2052–11 or H2052–115,

provided that the latch is not worn or

damaged. However, replacement of any latch

having part number H2052–11 or H2052–115

with a new latch having part number H2052–

13 is described as part of a modification of

the escape slide compartment door latching

mechanism that is specified in Boeing Alert

Service Bulletin 767–25A0174, dated August

15, 1991. Accomplishment of that

modification is required by AD 92–16–17,

amendment 39–8327, and AD 95–08–11,

amendment 39–9200. Therefore, operators

should note that any latch having part

number H2052–11 or H2052–115 found

during an inspection required by paragraph

(a) of this AD is already required to be

replaced in accordance with AD 92–16–17 or

AD 95–08–11, as applicable.

Note 3: Inspections and corrective actions

accomplished prior to the effective date of

this AD in accordance with the Validation

Copy of Boeing Alert Service Bulletin 767–

25A0260, dated April 28, 1998, are

considered acceptable for compliance with

the applicable action specified in this AD.

Replacement

(b) If any part is found to be worn or

damaged during the inspections performed in

accordance with paragraph (a) of this AD,

prior to further flight, replace the worn or

damaged part with a new part, and perform

an adjustment of the off-wing escape slide

system, in accordance with Boeing Alert

Service Bulletin 767–25A0260, dated July 9,

1998.

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, 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 4: 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

(d) 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

(e) The actions shall be done in accordance

with Boeing Alert Service Bulletin 767–

25A0260, dated July 9, 1998. 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.

Effective Date

(f) This amendment becomes effective on

July 18, 2000.

Issued in Renton, Washington, on June 1,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14312 Filed 6–12–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–331–AD; Amendment

39–11769; AD 2000–11–21]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A319, A320, and A321 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A319, A320, and A321 series airplanes,

that requires a one-time general visual

inspection to determine the part number

and serial number of the spoiler

servocontrol, and corrective action, 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 prevent failure of the spoiler

servocontrol piston rod, which could

result in reduced controllability of the

airplane.

DATES: Effective July 18, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

37018 Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations

of the Federal Register as of July 18,

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 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 Airbus

Model A319, A320, and A321 series

airplanes was published in the Federal

Register on December 22, 1999 (64 FR

71696). That action proposed to require

a one-time general visual inspection to

determine the part number and serial

number of the spoiler servocontrol, and

corrective action, 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.

The Air Transport Association (ATA)

of America, on behalf of two of its

members, states that both members

support the intent of the proposed AD.

One member is already accomplishing

the relevant service bulletin. The other

member is carrying out the one-time

inspection of the affected aircraft to

ensure the correct spoiler servocontrols

are installed on their aircraft.

Request to Revise the Compliance Time

for the Corrective Actions

One commenter requests that the

proposed AD be revised to allow more

flexibility in accomplishing the

corrective actions specified in the

proposal. The commenter states that

there will be times when replacement

spoiler servos are unavailable due to the

large number of spoiler servocontrol

units that are affected in the Airbus

fleet. With this in mind, the commenter

suggests revising paragraph (a) of the

proposed AD to read as follows:

‘‘At the time specified in paragraph (a)(1)

or (a)(2), accomplish the inspection and

corrective action per SB A320–27–1127 or

A320–27–1126 as applicable.’’

The FAA does not concur.

Discussions with the manufacturer have

not identified a supply problem with

the spoiler servocontrols. Additionally,

sufficient time has elapsed since the

issuance of the service bulletins and

notice of proposed rulemaking (NPRM)

for operators to make the necessary

planning and logistical supply

arrangements in advance in order to

comply with this amendment.

Therefore, no change has been made to

the final rule.

Request to Revise the Compliance Time

for the Inspection

One commenter requests that the

proposed AD be revised to require the

one-time general visual inspection to

determine the part number and serial

number of the spoiler servocontrol to be

accomplished within 18 months for

Airbus Model A319 series airplanes.

The commenter states that, the proposed

AD specifies a fourteen times

differential in the required compliance

threshold (i.e., 2 months versus 28

months) between Airbus Model A320

and A319 series airplanes. The

commenter questions this differential

because Model A320 series airplanes

have been in service longer with an

accumulated average of 17,306 total

flight hours than the Model A319 series

airplanes, which have an accumulated

average of approximately 4,014 total

flight hours. Furthermore, the

commenter states that there are

approximately 2.3 times more Model

A320 series airplanes in service as

Model A319 and A321 series airplanes.

The FAA does not concur. Data

provided by the manufacturer indicates

that an autoland failure of a

servocontrol on a Model A319 or A321

series airplane would result in a greater

maximum transient deviation from the

runway centerline and maximum

transient bank angle without triggering

the excessive deviation warning.

Considering this factor, the FAA has

determined that the compliance times

specified in paragraphs (a)(1) and (a)(2)

of the proposed AD represent the

maximum time in which the affected

airplanes could continue to operate

without compromising safety.

Therefore, no change has been made to

the final rule.

Explanation of Change to the Proposal

The FAA notes that it is necessary to

clarify that the general visual inspection

required by paragraphs (a) and (b) of

this AD may be accomplished in

accordance with Airbus Service Bulletin

A320–27–1126, dated April 26, 1999, or

Revision 01, dated October 6, 1999. This

clarification provides credit for those

operators that may have previously

accomplished the required action in

accordance with that service bulletin.

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

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

The FAA estimates that 210 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 2

work hours per airplane to accomplish

the inspection, at an average labor rate

of $60 per work hour. Based on these

figures, the cost impact of this AD on

U.S. operators is estimated to be

$25,200, or $120 per airplane.

Should an operator be required to

accomplish the modification, it will take

approximately 4 work hours per

airplane, at an average labor rate of $60

per work hour. The cost of required

parts would be free of charge. Based on

these figures, the cost impact of the

modification is estimated to be $240 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 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

Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations 37019

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:

2000–11–21 Airbus Industrie: Amendment

39–11769. Docket 99–NM–331–AD.

Applicability: The following models,

certificated in any category, excluding those

on which Airbus Service Bulletin A320–27–

1126, dated April 26, 1999 (for Model A319

and 321 series airplanes); or A320–27–1127,

dated April 26, 1999, or Revision 01, dated

October 6, 1999 (for Model A320 series

airplanes); has been accomplished:

• Model A319 series airplanes, serial

numbers (S/N) 0546 through 0972 inclusive;

• Model A320 series airplanes, S/N 0002

through 0842 inclusive, 0846 through 0859

inclusive, 0865, 0866, and 0872 through 0960

inclusive; and

• Model A321 series airplanes, S/N 0364

through 0974 inclusive.

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 failure of the servocontrol

piston rod, which could result in reduced

controllability of the airplane, accomplish

the following:

Inspection

(a) At the applicable time specified by

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

a general visual inspection to determine the

part number and serial number for the spoiler

servocontrols, in accordance with Airbus

Service Bulletin A320–27–1126, April 26,

1999, or Revision 01, dated October 6, 1999

(for Model A319 and A321 series airplanes);

or Airbus Service Bulletin A320–27–1127,

dated April 26, 1999, or Revision 01, dated

October 6, 1999 (for Model A320 series

airplanes); as applicable. If the part number

and serial number are identified in paragraph

2.B.(1)(b) of the Accomplishment

Instructions of the applicable service

bulletin, prior to further flight, perform

applicable corrective actions (including

removal, reidentification of the servocontrol,

and replacement of the servocontrol with a

modified part) as specified in the applicable

service bulletin.

(1) For Model A319 and A321 series

airplanes: Inspect within 2 months after the

effective date of this AD.

(2) For Model A320 series airplanes:

Inspect within 28 months after the effective

date of this AD.

Note 2: For the purposes of this AD, a

general visual inspection is defined as: ‘‘A

visual examination of an interior or exterior

area, installation, or assembly to detect

obvious damage, failure, or irregularity. This

level of inspection is made under normally

available lighting conditions such as

daylight, hangar lighting, flashlight, or droplight, and may require removal or opening of

access panels or doors. Stands, ladders, or

platforms may be required to gain proximity

to the area being checked.’’

Spares

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

person shall install on any airplane a spoiler

servocontrol having part number 31077–050,

31077–060, or 31077–110; and S/N 0001 to

3499, except those serial numbers excluded

in paragraph 2.B.(1)(b)1 of the

Accomplishment Instructions in Airbus

Service Bulletin A320–27–1126, dated April

26, 1999, or Revision 01, dated October 6,

1999; unless that servocontrol has been

inspected, and corrective actions have been

performed, in accordance with the

requirements 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 3: 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

A320–27–1126, including Appendices 01

and 02, dated April 26, 1999; Airbus Service

Bulletin A320–27–1126, Revision 01

including Appendices 01 and 02, dated

October 6, 1999; Airbus Service Bulletin

A320–27–1127, including Appendices 01

and 02, dated April 26, 1999; or Airbus

Service Bulletin A320–27–1127, Revision 01

including Appendices 01 and 02, dated

October 6, 1999; 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 4: The subject of this AD is addressed

in French airworthiness directive 1999–362–

139(B), dated September 8, 1999.

(f) This amendment becomes effective on

July 18, 2000.

Issued in Renton, Washington, on June 1,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14311 Filed 6–12–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–128–AD; Amendment

39–11772; AD 2000–11–23]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300, 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 all Airbus Model A300,

A310, and A300–600 series airplanes,

that requires an inspection to detect

damage of the electrical bonding leads

in specified locations of the fuel tanks,

and replacement of any damaged