Airworthiness Directives; Airbus Industrie Model A300, A300-600, and A310 Series Airplanes

DEPARTMENT OF TRANSPORTATION

14 CFR Part 39

[Docket No. 94-NM-63-AD; Amendment 39-8931; AD 94-10-51]

Airworthiness Directives; Airbus Industrie Model A300, A300-600,

and A310 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment

adopting Airworthiness Directive (AD) T94-10-51 that was sent

previously to all known U.S. owners and operators of certain Airbus

Model A300, A300-600, and A310 series airplanes by individual

telegrams. This AD requires a detailed visual inspection to detect

cracks, delamination, or discoloration of the bus bar of certain aft

fixed side cockpit windows; and deactivation of the window heating

system and repetitive detailed visual inspections, or replacement of

the window with a modified window, if necessary. This amendment is

prompted by a report of fracture of a fixed cockpit window that led to

electrical arcing in the bus bar area of the window heating system on a

Model A300 series airplane. The actions specified by this AD are

intended to prevent decompression of the fuselage during flight due to

failure of a window.

DATES: Effective June 28, 1994, to all persons except those persons to

whom it was made immediately effective by telegraphic AD T94-10-51,

issued May 3, 1994, which contained the requirements of this amendment.

The incorporation by reference of certain publications listed in

the regulations is approved by the Director of the Federal Register as

of June 28, 1994.

Comments for inclusion in the Rules Docket must be received on or

before August 12, 1994.

ADDRESSES: Submit comments in triplicate to the Federal Aviation

Administration (FAA), Transport Airplane Directorate, ANM-103,

Attention: Rules Docket No. 94-NM-63-AD, 1601 Lind Avenue, SW., Renton,

Washington 98055-4056.

The applicable service information 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; or at the

Office of the Federal Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Sam Grober, Aerospace Engineer,

Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)

227-1187; fax (206) 227-1320.

SUPPLEMENTARY INFORMATION: On May 3, 1994, the FAA issued telegraphic

AD T94-10-51, which is applicable to certain Airbus Industrie Model

A300, A300-600, and A310 series airplanes. That action was prompted by

a report of fracture of a fixed cockpit window on the right-hand aft

side of the cockpit of a Model A300 series airplane. Embrittlement of

the fixed cockpit window and simultaneous rupture of the two main plies

of the window have been attributed to electrical arcing in the bus bar

area of the window heating system. This condition, if not corrected,

could result in decompression of the fuselage during flight.

Since the subject windows installed on Model A300-600 and A310

series airplanes are similar in design to those on Model A300 series

airplanes, the FAA has determined that these airplanes are also subject

to the addressed unsafe condition.

Airbus Industrie has issued All Operators Telex (AOT) 56-01,

Revision 1, dated April 29, 1994, that describes procedures for a

detailed visual inspection to detect discoloration (black or brown

burnt spots) of the bus bar of certain aft fixed side windows; and

either deactivation of the window heating system coupled with

repetitive detailed visual inspections, or replacement of the window

with a modified window, if necessary. The Direction Generale de

l'Aviation Civile (DGAC), which is the airworthiness authority for

France, classified this AOT as mandatory and issued French telegraphic

airworthiness directive N 94-104-160(B), dated April 26, 1994, in order

to assure the continued airworthiness of these airplanes in France.

These airplane models are manufactured in France and are type

certificated for operation in the United States under the provisions of

Sec. 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.

Since the unsafe condition described is likely to exist or develop

on other airplanes of the same type design registered in the United

States, the FAA issued telegraphic AD T94-10-51 to require a detailed

visual inspection to detect cracks, delamination, or discoloration

(black or brown burnt spots) of the bus bar of certain aft fixed side

windows; and either deactivation of the window heating system and

repetitive detailed visual inspections, or replacement of the window

with a modified window, if necessary. The actions are required to be

accomplished in accordance with the AOT described previously.

Since it was found that immediate corrective action was required,

notice and opportunity for prior public comment thereon were

impracticable and contrary to the public interest, and good cause

existed to make the AD effective immediately by individual telegrams

issued on May 3, 1994, to all known U.S. owners and operators of

certain Airbus Model A300, A300-600, and A310 series airplanes. These

conditions still exist, and the AD is hereby published in the Federal

Register as an amendment to Sec. 39.13 of the Federal Aviation

Regulations (14 CFR 39.13) to make it effective as to all persons.

Comments Invited

Although this action is in the form of a final rule that involves

requirements affecting flight safety and, thus, was not preceded by

notice and an opportunity for public comment, comments are invited on

this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All

communications received on or before the closing date for comments will

be considered, and this rule may be amended in light of the comments

received. Factual information that supports the commenter's ideas and

suggestions is extremely helpful in evaluating the effectiveness of the

AD action and determining whether additional rulemaking action would be

needed.

Comments are specifically invited on the overall regulatory,

economic, environmental, and energy aspects of the rule that might

suggest a need to modify the 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 that

summarizes each FAA-public contact concerned with the substance of this

AD 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 94-NM-63-AD.'' The postcard will be date stamped and

returned to the commenter.

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.

The FAA has determined that this regulation is an emergency

regulation that must be issued immediately to correct an unsafe

condition in aircraft, and is not a ``significant regulatory action''

under Executive Order 12866. It has been determined further that this

action involves an emergency regulation under DOT Regulatory Policies

and Procedures (44 FR 11034, February 26, 1979). If it is determined

that this emergency regulation otherwise would be significant under DOT

Regulatory Policies and Procedures, a final regulatory evaluation will

be prepared and placed in the Rules Docket. A copy of it, if filed, 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. 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 adding the following new

airworthiness directive:

94-10-51 Airbus Industrie: Amendment 39-8931. Docket 94-NM-63-AD.

Applicability: Model A300, A300-600, and A310 series airplanes;

as listed in Airbus Industrie All Operators Telex (AOT) 56-01,

Revision 1, dated April 29, 1994; certificated in any category.

Compliance: Required as indicated, unless accomplished

previously.

To prevent decompression of the fuselage during flight,

accomplish the following:

(a) Within 15 days after the effective date of this AD, perform

a detailed visual inspection to detect cracks, delamination, or

discoloration (black or brown burnt spots) of the bus bar of the aft

fixed windows, in accordance with Airbus Industrie AOT 56-01,

Revision 1, dated April 29, 1994.

(b) If any crack or delamination is found during the inspection

required by paragraph (a) of this AD, prior to further flight,

replace the affected window with a modified window, in accordance

with Airbus Industrie AOT 56-01, Revision 1, dated April 29, 1994.

(c) If no cracks, delamination, or discoloration is found during

the inspection required by paragraph (a) of this AD, accomplish

either paragraph (c)(1) or (c)(2) of this AD in accordance with

Airbus Industrie AOT 56-01, Revision 1, dated April 29, 1994.

(1) Within 7 days after accomplishing the inspection required by

paragraph (a) of this AD, and thereafter at intervals not to exceed

7 days, repeat the inspection required by paragraph (a) of this AD;

or

(2) Prior to further flight, deactivate the side window heating

system in accordance with the AOT.

(d) If any discoloration is found during the inspections

required by paragraph (a) or (c) of this AD, and that discoloration

measures less than 10mm in diameter, accomplish paragraphs (d)(1),

(d)(2), and (d)(3) of this AD in accordance with Airbus Industrie

AOT 56-01, Revision 1, dated April 29, 1994.

(1) Prior to further flight, deactivate the side window heating

system on the affected side, in accordance with the AOT.

(2) 7 days after deactivating the window heating system, inspect

the affected window to detect cracks or delamination formation

around the discolored area, in accordance with the AOT.

(3) If any crack or delamination is found during the repeat

inspection required by paragraph (d)(2) of this AD, prior to further

flight, replace the window with a modified window, in accordance

with the AOT.

(e) If any discoloration is found during the inspection required

by paragraph (a) or (c) of this AD, and that discoloration measures

10mm or more in diameter, accomplish paragraphs (e)(1), (e)(2), and

(e)(3) of this AD, in accordance with Airbus Industrie AOT 56-01,

Revision 1, dated April 29, 1994.

(1) Prior to further flight, deactivate the side window heating

system on the affected side, in accordance with the AOT.

(2) Thereafter, at daily intervals, inspect the affected window

to detect cracks or delamination formation around the discoloration

area, in accordance with the AOT.

(3) If any crack or delamination is found during the inspections

required by paragraph (e)(2) of this AD, prior to further flight,

replace the window with a modified window in accordance with the

AOT.

(f) Replacement of the aft fixed side window in accordance with

Airbus Industrie AOT 56-01, Revision 1, dated April 29, 1994,

constitutes terminating action for the requirements of this AD.

(g) 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.

(h) Special flight permits may be issued in accordance with

Secs. 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.

(i) The inspections, deactivation, and replacement, shall be

done in accordance with Airbus Industrie All Operators Telex (AOT)

56-01, Revision 1, dated April 29, 1994. 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.

(j) This amendment becomes effective on June 28, 1994, to all

persons except those persons to whom it was made immediately

effective by telegraphic AD T94-10-51, issued May 3, 1994, which

contained the requirements of this amendment.

Issued in Renton, Washington, on May 31, 1994.

Darrell M. Pederson,

Acting Manager, Transport Airplane Directorate, Aircraft Certification

Service.

[FR Doc. 94-13625 Filed 6-10-94; 8:45 am]

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