Airworthiness Directives; Airbus Industrie Model A310-200 and A310-300 Series Airplanes

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93-NM-120-AD; Amendment 39-8794; AD 94-01-12]

Airworthiness Directives; Airbus Industrie Model A310-200 and

A310-300 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive

(AD), applicable to all Airbus Industrie Model A310-200 and A310-300

series airplanes, that currently requires inspections and test to

detect broken or missing vespel bushes in the flap universal joint

assemblies, and replacement of universal joint bushes, if necessary.

This amendment adds a terminating modification for the currently

required inspections and tests. This amendment is prompted by the

development of a modification that will improve the integrity of the

flap universal joints. The actions specified by this AD are intended to

prevent rupture of the flap universal joints, subsequent partial loss

of lift in one wing, and reduced controllability of the airplane.

DATES: Effective March 4, 1994.

The incorporation by reference of Airbus Industrie Service Bulletin

A310-27-2059, dated March 1, 1993, as listed in the regulations, is

approved by the Director of the Federal Register as of March 4, 1994.

The incorporation by reference of Airbus Industrie Service Bulletin

A310-27-2054, Revisions 2, dated November 9, 1990, as listed in the

regulations, was approved previously by the Director of the Federal

Register as of September 11, 1991 (56 FR 37462, August 7, 1991).

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:

Stephen Slotte, Aerospace Engineer, Standardization Branch, ANM-113,

FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,

Washington 98055-4056; telephone (206) 227-2797; fax (206) 227-1320.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal

Aviation Regulations by superseding AD 91-16-05, Amendment 39-7095 (56

FR 37462, August 7, 1991), which is applicable to all Airbus Industrie

Model A310-200 and A310-300 series airplanes, was published in the

Federal Register on October 6, 1993 (58 FR 52041). The action proposed

to add a requirement to modify the flap universal joint assemblies.

Installation of this modification would terminate the currently

required inspections and tests to detect broken or missing vespel

bushes in the flap universal joint assemblies.

Interested persons have been afforded an opportunity to participate

in the making of this amendment. Due consideration has been given to

the two comments received.

Both commenters support the proposal.

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 as proposed.

The FAA estimates that 25 airplanes of U.S. registry will be

affected by this AD.

The inspections and tests currently required by AD 91-16-05 take

approximately 5 work hours to accomplish, at an average labor cost of

$55 per work hour. Based on these figures, the total cost impact on

U.S. operators of the actions previously required by AD 91-16-05 is

estimated to be $6,875, or $275 per airplane, per inspection and

testing cycle.

It will take approximately 47 work hours per airplane to accomplish

the modification required by this new AD action, at an average labor

rate of $55 per work hour. Required parts will cost approximately

$1,000 per airplane. Based on these figures, the total additional cost

impact associated with the modification requirements of this AD on U.S.

operators is estimated to be $89,625, or $3,585 per airplane.

The cost figures discussed above are based on assumptions that no

operator has yet accomplished the requirements of this AD action.

The regulations adopted herein will not have substantial direct

effects 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, in

accordance with Executive Order 12612, it is determined that this final

rule does not have sufficient federalism implications to warrant the

preparation of a Federalism Assessment.

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 14 CFR part

39 of the Federal Aviation Regulations as follows:

PART 39--AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.

106(g); and 14 CFR 11.89.

Sec. 39.13 [Amended]

2. Section 39.13 is amended by removing amendment 39-7095 (56 FR

37462, August 7, 1991), and by adding a new airworthiness directive

(AD), amendment 39-8794, to read as follows:

94-01-12 Airbus Industrie: Amendment 39-8794. Docket 93-NM-120-AD.

Supersedes AD 91-17-05, Amendment 39-7095.

Applicability: All Model A310-200 and A310-300 series airplanes,

certificated in any category.

Compliance: Required as indicated, unless accomplished

previously.

To prevent rupture of the flap universal joints, subsequent

partial loss of lift in one wing, and reduced controllability of the

airplane, accomplish the following:

(a) Prior to the accumulation of 5,500 total landings, or within

350 hours time-in-service after September 11, 1991 (the effective

date of AD 91-16-05, Amendment 39-7095), whichever occurs later, and

thereafter at intervals not to exceed 3,500 landings, perform

repetitive visual inspections and electrical continuity tests of the

flap system.

(b) If any universal joint bushes are missing or broken, prior

to further flight, replace the bushes with new bushes in accordance

with Airbus Industrie Service Bulletin A310-27-2054, Revision 2,

dated November 9, 1990. After replacement, repeat the inspections

required by paragraph (a) of this AD at intervals not to exceed

3,500 landings.

(c) Within 3,500 landings after the effective date of this AD,

modify the flap universal joint assemblies (Airbus Industrie

Modification 10091D20285) in accordance with Airbus Industrie

Service Bulletin A310-27-2059, dated March 1, 1993. Accomplishment

of this modification constitutes terminating action for the

inspection and test requirements of this AD.

(d) Modification of the flap universal joint assemblies (Airbus

Industrie Modification 10091D20285) in accordance with Airbus

Industrie Service Bulletin A310-27-2059, dated March 1, 1993,

constitutes terminating action for the inspection and test

requirements of this AD.

(e) 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, Standardization Branch, ANM-113,

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,

Standardization Branch, ANM-113.

Note: Information concerning the existence of approved

alternative methods of compliance with this AD, if any, may be

obtained from the Standardization Branch, ANM-113.

(f) Special flight permits may be issued in accordance with FAR

21.197 and 21.199 to operate the airplane to a location where the

requirements of this AD can be accomplished.

(g) The inspections, testing, and replacement shall be done in

accordance with Airbus Industrie Service Bulletin A310-27-2054,

Revision 2, dated November 9, 1990. The incorporation by reference

of this document was approved previously by the Director of the

Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part

51, as of September 11, 1991 (56 FR 37462, August 7, 1991). The

modification shall be done in accordance with Airbus Industrie

Service Bulletin A310-27-2059, dated March 1, 1993. The

incorporation by reference of this document is approved by the

Director of the Federal Register, in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies of these documents 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.

(h) This amendment becomes effective on March 4, 1994.

Issued in Renton, Washington, on January 4, 1994.

Darrell M. Pederson,

Acting Manager, Transport Airplane Directorate, Aircraft Certification

Service.

[FR Doc. 94-452 Filed 2-1-94; 8:45 am]

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