30874 Federal Register / Vol. 65, No. 94 / Monday, May 15, 2000 / Rules and Regulations

May 21, 1997; and Mitsubishi MU–2 Service

Bulletin (SB) No. 232, dated July 2, 1997.

(2) Install a trim-in-motion alerting system

and automatic autopilot disconnect system.

Use the procedures contained in Test

Instrumentation, Inc. Document No. MU2–

1001, Rev. C, dated June 15, 1997; Test

Instrumentation, Inc. Document No. MU2–

4001, Rev. C, dated June 30, 1997; and

Mitsubishi MU–2 SB No. 231, dated July 2,

1997.

(3) Install an auto-ignition (re-light) system.

Use the procedures contained in Mitsubishi

MU–2 SB No. 226, which incorporates the

following pages:

Pages

Revision

level

Date

2 through 11, 13

through 23, 27

through 57,

and 59 through

93.

A January 13,

1997.

1, 12, 24, 25, 26,

and 58.

B October 27,

1997.

(e) Can I comply with this AD in any other

way?

(1) You may use an alternative method of

compliance or adjust the compliance time if:

(i) Your alternative method of compliance

provides an equivalent level of safety; and

(ii) The Manager of one of the following

approves your alternative. Submit your

request through an FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager.

(A) Los Angeles Aircraft Certification

Office, FAA, 3960 Paramount Blvd.,

Lakewood, California 90712; or

(B) Fort Worth Airplane Certification

Office, FAA, 2601 Meacham Boulevard, Fort

Worth, Texas 76193–0150.

(2) 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 (e)(1) 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 you have not eliminated the

unsafe condition, specific actions you

propose to address it.

(f) Where can I get information about any

already-approved alternative methods of

compliance? Contact one of the following:

(1) Small Airplane Directorate, FAA, 901

Locust, Room 301, Kansas City, Missouri

64106; telephone: (816) 329–4121; facsimile:

(816) 426–4090;

(2) Los Angeles Aircraft Certification

Office, FAA, 3960 Paramount Blvd.,

Lakewood, California 90712; telephone: (562)

627–5222; facsimile: (562) 627–5228; or

(3) Fort Worth Airplane Certification

Office, FAA, 2601 Meacham Boulevard, Fort

Worth, Texas 76193–0150; telephone: (817)

222–5147; facsimile: (817) 222–5960.

(g) What if I need to fly the airplane to

another location to comply with this AD? The

FAA can issue a special flight permit under

sections 21.197 and 21.199 of the Federal

Aviation Regulations (14 CFR 21.197 and

21.199) to operate your airplane to a location

where you can accomplish the requirements

of this AD.

(h) Are any service bulletins incorporated

into this AD by reference?

(1) You must accomplish the actions

required by this AD in accordance with the

following:

(i) Mitsubishi MU–2 SB No. 226, which

incorporates the following pages:

Pages

Revision

level

Date

2 through 11, 13

through 23, 27

through 57,

and 59 through

93.

A January 13,

1997.

1, 12, 24, 25, 26,

and 58.

B October 27,

1997.

(ii) Mitsubishi MU–2 SB No. 231, dated

July 2, 1997;

(iii) Mitsubishi MU–2 SB No. 232, dated

July 2, 1997;

(iv) Test Instrumentation, Inc. Document

No. MU2–1001, Rev. C, dated June 15, 1997,

and attachments;

(v) Test Instrumentation, Inc. Document

No. MU2–4001, Rev. C, dated June 30, 1997,

and attachments; and

(vi) Test Instrumentation, Inc. Document

No. MU2–5001, Rev. E., dated May 21, 1997,

and attachments.

(2) The Director of the Federal Register

approved this incorporation by reference

under 5 U.S.C. 552(a) and 1 CFR part 51.

(3) You can get copies from Mitsubishi

Heavy Industries America, Inc., 15303 Dallas

Parkway, suite 685, LB–77, Dallas, Texas.

You can look at copies at FAA, Central

Region, Office of the Regional Counsel, 901

Locust, Room 506, Kansas City, Missouri, or

at the Office of the Federal Register, 800

North Capitol Street, NW, suite 700,

Washington, DC.

(i) When does this amendment become

effective? This amendment becomes effective

on July 24, 2000.

Issued in Kansas City, Missouri, on May 5,

2000.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 00–11863 Filed 5–12–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–103–AD; Amendment

39–11726; AD 2000–10–02]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A319, A320, A321, A330, and A340

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Airbus Model A319,

A320, A321, A330, and A340 series

airplanes, that requires repetitive

inspections to detect missing and

incorrectly installed parts of the footrest

actuator assembly, and replacement of

discrepant parts with new parts. This

AD also provides for optional

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 detachment of the

footrest assembly actuator, which could

result in partial blockage of the rudder

pedals and reduced controllability of

the airplane.

DATES: Effective June 19, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 19,

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) to

include an airworthiness directive (AD)

Federal Register / Vol. 65, No. 94 / Monday, May 15, 2000 / Rules and Regulations 30875

that is applicable to all Airbus Model

A319, A320, A321, A330, and A340

series airplanes was published in the

Federal Register on July 14, 1999 (64 FR

37915). That action proposed to require

repetitive inspections to detect missing

and incorrectly installed parts of the

footrest actuator assembly, and

replacement of discrepant parts with

new parts. That AD also would provide

for optional terminating action for the

repetitive inspections.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Explanation of Changes Made to This

Final Rule

1. The notice of proposed rulemaking

(NPRM) references All Operator Telex

(AOT) 25–14 (for Model A319, A320,

and A321 series airplanes) and AOT 25–

13 (for Model A330 and A340 series

airplanes); both dated December 17,

1998, as the appropriate sources of

service information for accomplishment

of the actions specified by paragraph (a)

of the NPRM. Instead, this amendment

requires that the actions specified by

that paragraph be accomplished in

accordance with Airbus Service Bulletin

A320–25–1220 and A320–25–1225, both

dated November 19, 1999 (for Model

A319, A320, and A321 series airplanes);

A330–25–3105, dated October 22, 1999,

and A330–25–3110, dated December 23,

1999 (for Model A330 series airplanes);

and A340–25–4131, dated October 22,

1999, and A340–25–4136, dated

December 23, 1999 (for Model A340

series airplanes); as applicable. The

inspection procedures specified by

those service bulletins are similar to the

procedures specified by AOT 25–13 and

25–14; however, the service bulletins

also include graphics to show the areas

of inspection and replacement (repair).

Note 2 has been added to this AD to give

credit to operators for accomplishment

of the actions specified in the AOT’s

prior to the effective date of this AD.

2. Note 4 of the proposed rule has

been renumbered as NOTE 6 in the final

rule, and two references to French

airworthiness directives have been

changed to reflect later revision

numbers.

Support for the Proposed Rule

The Air Transport Association (ATA)

of America states that one of its

members concurs with the proposal and

offers no further comments.

Requests To Include Terminating

Action

• One commenter states that Airbus

Service Bulletin A320–25–1225

includes procedures for the installation

of a new footrest actuator, Modification

28472, and that such a modification

should be considered terminating action

for the repetitive inspections.

The FAA acknowledges the

commenter’s request and has

determined that the installation of

Modification 28472 during production

or the accomplishment of Airbus

Service Bulletin A320–25–1225, or the

installation of Modification 47376

during production or the

accomplishment of Airbus Service

Bulletin A330–25–3110 or A340–25–

4136, constitutes optional terminating

action for the repetitive inspections

required by this AD. In light of this, the

FAA has added a new paragraph (c) to

the final rule to include this new option.

• Another commenter states that it is

in the process of issuing a request for

funding to remove the footrest from the

seat, and that ‘‘it is our expectation that

this will be terminating action.’’

The FAA acknowledges the

commenter’s statement and points out

that paragraph (b) of the proposed rule

provides for optional terminating action

for the repetitive inspection

requirements of this AD. Therefore, no

change to the final rule is necessary in

this regard.

Request to Credit Operators With Prior

Accomplishment of Inspections

One commenter states that operators

were notified of a proposed rule

mandating repetitive inspections of the

cockpit footrest actuator assembly. The

first inspection (detailed visual) was

required at 500 flight hours after the

effective date of the proposed AD,

followed by a repeat inspection at

intervals not to exceed 15 months. The

commenter also states that AOT 25–14,

dated December 17, 1998, specifies a

production quality control check and

that the manufacturer issued two

messages to specify that all airplanes

undergoing production quality checks

may take credit for accomplishing the

inspections specified at 500 flight hours.

For this reason, the commenter requests

that all airplanes that have

accomplished such a check be excluded

from the detailed visual inspection

within 500 flight hours after the

effective date of this AD, and only be

required to accomplish that inspection

at intervals not to exceed 15 months.

The commenter considers that such a

policy will not impair the safety of the

airplanes.

The FAA concurs and considers that

such a check during production would

detect any discrepancy, such as a

missing or broken retaining clip, and

preclude the necessity for the initial

inspection at 500 flight hours. For that

reason, Note 3, preceding paragraph (a)

of this AD, has been added to provide

credit for prior accomplishment of the

initial detailed visual inspection

required by that paragraph.

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 208 Model

A319, A320, A321, A330, and A340

series airplanes of U.S. registry will be

affected by this AD, that it will take

approximately 3 work hours per

airplane to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be

$37,440, or $180 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

30876 Federal Register / Vol. 65, No. 94 / Monday, May 15, 2000 / Rules and Regulations

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:

2000–10–02 Airbus: Amendment 39–11726.

Docket 99–NM–103–AD.

Applicability: All Model A319, A320,

A321, A330, and A340 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 (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.

Note 2: Inspections and replacement

actions accomplished prior to the effective

date of this amendment, in accordance with

Airbus All Operator Telex (AOT) 25–14 (for

Model A319, A320, and A321 series

airplanes), and AOT 25–13 (for Model A330

and A340 series airplanes), both dated

December 17, 1998, are considered

acceptable for compliance with the initial

inspection and replacement actions specified

by paragraph (a) of this AD.

Note 3: An initial detailed visual

inspection accomplished during production

prior to the effective date of this amendment

is considered acceptable for compliance with

the initial inspection required by paragraph

(a) of this AD.

To prevent detachment of the footrest

assembly actuator, which could result in

partial blockage of the rudder pedals and

reduced controllability of the airplane,

accomplish the following:

Detailed Visual Inspections

(a) Within 500 flight hours after the

effective date of this AD, perform a detailed

visual inspection of the footrest actuator

assembly for discrepancies (including bent

pins and missing or incorrectly installed

retaining rings and pins), in accordance with

Airbus Service Bulletin A320–25–1220,

dated November 19, 1999 (for Model A319,

A320, and A321 series airplanes); A330–25–

3105, dated October 22, 1999 (for Model

A330 series airplanes); or A340–25–4131,

dated October 22, 1999 (for Model A340

series airplanes); as applicable.

(1) If no discrepancy is detected: Repeat

the inspection thereafter at intervals not to

exceed 15 months.

(2) If any discrepancy is detected:

Accomplish the actions of paragraphs (a)(2)(i)

and (a)(2)(ii) of this AD.

(i) Prior to further flight, remove the

actuator system from the footrest assembly

and conduct a detailed visual inspection of

the pins for damage, distortion, or wear in

accordance with the applicable service

bulletin. If any damage, distortion, or wear of

the pin, or any discrepancy of the pin or the

ring is detected, prior to further flight,

replace that pin or ring with a new part in

accordance with the applicable service

bulletin. And

(ii) Repeat the detailed visual inspection of

the footrest actuator assembly thereafter at

intervals not to exceed 15 months.

Note 4: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc. may be used. Surface

cleaning and elaborate access procedures

may be required.’’

Optional Terminating Actions

(b) Removal of the footrest assembly

constitutes terminating action for the

repetitive inspection requirements of this

AD.

(c) Accomplishment of Modification 28472

during production, or Airbus Service Bulletin

A320–25–1225, dated November 19, 1999

(for Model A319, A320, and A321 series

airplanes); or accomplishment of

Modification 47376 during production, or

Airbus Service Bulletin A330–25–3110 or

A340–25–4136, both dated December 23,

1999 (for Model A330 and A340 series

airplanes); as applicable; constitutes

terminating action for the inspection

requirements of this AD.

Alternative Methods of Compliance

(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 5: 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

(e) 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

(f) The actions shall be done in accordance

with Airbus Service Bulletin

A320–25–1220, dated November 19, 1999

(for Model A319, A320, and A321 series

airplanes); Airbus Service Bulletin A320–25–

1225, dated November 19, 1999 (for Model

A319, A320, and A321 series airplanes);

Airbus Service Bulletin A330–25–3105,

dated October 22, 1999 (for Model A330

series airplanes); Airbus Service Bulletin

A330–25–3110, dated December 23, 1999 (for

Model A330 series airplanes); Airbus Service

Bulletin A340–25–4131, dated October 22,

1999 (for Model A340 series airplanes); and

Airbus Service Bulletin A340–25–4136,

dated December 23, 1999 (for Model A340

series airplanes); 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 6: The subject of this AD is addressed

in French airworthiness directives 1999–

047–110(B) R1 (for Model A340 series

airplanes) and 1999–048–090(B) R1 (for

Model A330 series airplanes), both dated

December 15, 1999; and 1999–074–127(B),

R1, dated January 26, 2000 (for Model A319,

A320, and A321 series airplanes).

(g) This amendment becomes effective on

June 19, 2000.

Issued in Renton, Washington, on May 8,

2000.

Vi L. Lipski,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–11949 Filed 5–12–00; 8:45 am]

BILLING CODE 4910–13–U