This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

20921

Vol. 65, No. 76

Wednesday, April 19, 2000

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–77–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Airbus Model A310 series

airplanes. This proposal would require

modification of the position 1 flap screw

jack. This proposal is prompted by

issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by the proposed AD

are intended to prevent fracture of the

lead screw of the position 1 flap screw

jack, which could result in failure of the

tie bar and possible disconnection of the

flap structure from the airplane.

DATES: Comments must be received by

May 19, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

77–AD, 1601 Lind Avenue, SW.,

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.

The service information referenced in

the proposed rule may be obtained from

Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed 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 above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed 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

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–77–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–114, Attention: Rules Docket No.

2000–NM–77–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

notified the FAA that an unsafe

condition may exist on certain Airbus

Model A310 series airplanes. The DGAC

advises that, during routine

maintenance, a fractured lead screw was

detected in a position 1 flap screw jack.

After an inspection of the fleet,

additional occurrences of broken or

cracked lead screws were reported.

Investigation into the fractured lead

screws revealed that the cause was

attributed to interference between the

ball nut and the trunnion fork end due

to the installation of the ball nut being

offset 180 degrees after maintenance.

Such interference between the ball nut

and trunnion fork end could lead to

fracture of the lead screw of the position

1 flap screw jack. This condition, if not

corrected, could result in failure of the

tie bar and possible disconnection of the

flap structure from the airplane.

Explanation of Relevant Service

Information

The manufacturer has issued Airbus

Service Bulletin A310–27–2075,

Revision 02, dated February 8, 2000,

which describes procedures for

modification of the position 1 flap screw

jack. The modification involves the

installation of a bracket, which will

prevent incorrect installation of the ball

nut. The DGAC classified this service

bulletin as mandatory and issued

French airworthiness directive 1999–

510–299(B), dated December 29, 1999,

in order to assure the continued

airworthiness of these airplanes in

France.

The Airbus service bulletin references

Lucas/Liebherr Service Bulletin 537–

27–M537–15, dated May 12, 1994, as an

additional source of service information

for accomplishing the modification

proposed by this AD.

FAA’s Conclusions

This airplane model is manufactured

in France and is type certificated for

operation in the United States under the

provisions of section 21.29 of the

Federal Aviation Regulations (14 CFR

21.29) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the DGAC has kept the FAA informed

of the situation described above. The

FAA has examined the findings of the

DGAC, 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.

20922 Federal Register / Vol. 65, No. 76 / Wednesday, April 19, 2000 / Proposed Rules

Explanation of Requirements of

Proposed 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, the proposed AD would require

modification of the position 1 flap

control screw jack. The actions would

be required to be accomplished in

accordance with the Airbus service

bulletin described previously.

Cost Impact

The FAA estimates that 41 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 2 work hours per

airplane to accomplish the proposed

modification, and that the average labor

rate is $60 per work hour. Required

parts would cost approximately $105

per airplane. Based on these figures, the

cost impact of the proposed

modification AD on U.S. operators is

estimated to be $9,225, or $225 per

airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed 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 proposed herein

would 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 proposal

would not have federalism implications

under Executive Order 13132.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Airbus Industrie: Docket 2000–NM–77–AD.

Applicability: Model A310 series airplanes,

certificated in any category, except those

airplanes on which Airbus Modification

10855 or Airbus Service Bulletin A310–27–

2075 has been accomplished.

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 fracture of the lead screw of the

position 1 flap screw jack, which could result

in failure of the tie bar and possible

disconnection of the flap structure from the

airplane, accomplish the following:

Modification

(a) Within 18 months after the effective

date of this AD, modify the position 1 flap

screw jack in accordance with Airbus Service

Bulletin A310–27–2075, Revision 02, dated

February 8, 2000.

Note 2: Modifications accomplished prior

to the effective date of this AD, in accordance

with Airbus Service Bulletin A310–27–2075,

dated November 18, 1994, or Revision 01,

dated July 20, 1995, are considered

acceptable for compliance with the

modification specified by this AD.

Note 3: The Airbus service bulletin

references Lucas/Liebherr Service Bulletin

537–27–M537–15, dated May 12, 1994, as an

additional source of service information for

accomplishing the applicable action required

by this AD.

Spares

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

person shall install on any airplane a

position 1 flap screw jack having part

number 537G0000–02, unless modified in

accordance with 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 4: 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.

Note 5: The subject of this AD is addressed

in French airworthiness directive 1999–510–

299(B), dated December 29, 1999.

Issued in Renton, Washington, on April 13,

2000.

Charles D. Huber,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–9823 Filed 4–18–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–54–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300, A300–600, and A310 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Airbus Model A300, A300–600,

and A310 series airplanes. This

proposal would require replacement of

the transformer rectifier units (TRU) in

the avionics compartment with new,

improved TRU’s. This proposal is

prompted by issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.