[Federal Register Volume 69, Number 82 (Wednesday, April 28, 2004)]
[Rules and Regulations]
[Pages 23090-23093]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-9241]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2004-NM-57-AD; Amendment 39-13590; AD 2004-09-01]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, C4-
605R Variant F, and F4-600R (Collectively Called A300-600) Series 
Airplanes; and Model A310 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Airbus Model A300 B4-600, B4-600R, C4 605R 
Variant F, and F4-600R (collectively called A300-600) series airplanes; 
and Model A310 series airplanes. This action requires a one-time 
inspection for damage of the integrated drive generator electrical 
harness and pyramid arm, and repair if necessary. This action is 
necessary to prevent electrical arcing within the engine pylon, which 
could result in loss of the relevant alternating current (AC) bus bar, 
reduced structural integrity of the engine pylon, and consequent loss 
of control of the airplane. This action is intended to address the 
identified unsafe condition.

DATES: Effective May 13, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 13, 2004.
    Comments for inclusion in the Rules Docket must be received on or 
before May 28, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2004-NM-57-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via the Internet must contain 
``Docket No. 2004-NM-57-AD'' in the subject line and need not be 
submitted in triplicate. Comments sent via fax or the Internet as 
attached electronic files must

[[Page 23091]]

be formatted in Microsoft Word 97 or 2000 or ASCII text.
    The service information referenced in this AD may be obtained from 
Airbus, 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: Tony Jopling, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2190; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The Direction G[eacute]n[eacute]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 A300 B4-600, B4-600R, C4-605R Variant F, and F4-600R 
(collectively called A300-600) series airplanes; and Model A310 series 
airplanes. The DGAC advises that an operator found structural damage on 
the forward pyramid arm of an engine pylon during a scheduled 
maintenance check. Investigation revealed that the damage was caused by 
chafing of the integrated drive generator (IDG) electrical harness 
against the structure of the pyramid arm. This condition, if not 
corrected, could result in loss of the relevant alternating current 
(AC) bus bar, reduced structural integrity of the engine pylon, and 
consequent loss of control of the airplane.

Explanation of Relevant Service Information

    Airbus has issued All Operators Telex (AOT) A300-54A6037, dated 
February 19, 2004 (for Model A300-600 series airplanes); and AOT A310-
54A2038, dated February 19, 2004 (for Model A310 series airplanes). 
These AOTs describe procedures for inspecting for damage of the IDG 
harness and pyramid arm, and related investigative and corrective 
actions if necessary.
    The inspection involves:
     Determining if the IDG electrical harness 
bracket on the pylon forward pyramid arm is attached, and if the 
retaining fasteners are in place and secured.
     Determining if there is contact between the IDG 
electrical harness and the pyramid arms.
     Determining if there is damage (chafing marks) 
on the pylon forward pyramid arms; and/or damage (chafing or fretting) 
to the IDG electrical harness, especially at the junction between the 4 
convoluted conduits that protect each feeder cable, and at the large 
conduit that protects the 4 cables together.
    The related investigative and corrective actions depend on the 
results of the inspection and include the following:
     If there is no damage found, no further action 
is specified by the AOT.
     If the bracket on the pylon forward pyramid arm 
is not attached and/or the fasteners are not in place and secured, the 
corrective action is to repair the bracket and/or fasteners.
     If there is fretting at the convoluted conduits 
(with or without contact between the IDG electrical harness and the 
pyramid arms), the related investigative and corrective actions are to 
inspect the feeder cables for damage, repair the cables if necessary 
per the limits defined in the Airbus electrical standard practices 
manual, and apply self-adhesive protective tape to the IDG electrical 
harness at possible contact points.
     If there is any contact between the IDG 
electrical harness and the pyramid arms, without damage to the harness 
or the arms, and without fretting at the convoluted conduits, the 
related corrective action is to apply self-adhesive protective tape to 
the harness at possible contact points.
     If there is any damage to the pyramid arms found 
during any inspection, the AOTs recommend contacting Airbus before 
further flight for disposition of repairs.
    The DGAC classified these AOTs as mandatory and issued French 
airworthiness directive F-2004-039, dated March 17, 2004, to ensure the 
continued airworthiness of these airplanes in France.

FAA's Conclusions

    These airplane models are manufactured in France and are 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.

Explanation of Requirements of 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, this AD is being issued to prevent loss of the 
relevant AC bus bar, reduced structural integrity of the engine pylon, 
and consequent loss of control of the airplane. This AD requires a one-
time inspection for damage of the IDG electrical harness and pyramid 
arm, and repair if necessary. The actions are required to be 
accomplished in accordance with the AOTs described previously, except 
as discussed below.

Differences Among the French Airworthiness Directive, the AOTs, and 
This AD

    The French airworthiness directive and the AOTs do not define the 
type of inspection for the IDG electrical harness and pyramid arm. This 
AD calls the inspection a ``detailed inspection.'' Note 1 of this AD 
defines this inspection.
    Although the French airworthiness directive and the AOTs specify to 
report inspection results to the manufacturer, this AD does not include 
such a requirement.
    Where the French airworthiness directive and the AOTs specify to 
contact Airbus for disposition of repairs if there is any damage to the 
pyramid arms, this AD requires operators to repair per a method 
approved by either the FAA or the DGAC (or its delegated agent). In 
light of the type of repair that would be required to address the 
unsafe condition, and consistent with existing bilateral airworthiness 
agreements, we have determined that, for this AD, a repair approved by 
either the FAA or the DCAG would be acceptable for compliance with this 
AD.

Interim Action

    We consider this AD interim action. If final action is identified 
later, we may consider further rulemaking then.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

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

[[Page 23092]]

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.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, 
discuss a request to change the compliance time and a request to change 
the service bulletin reference as two separate issues.
     For each issue, state what specific change to 
the AD is being requested.
     Include justification (e.g., reasons or data) 
for each request.
    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 rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2004-NM-57-AD.'' The postcard will be date stamped and 
returned to the commenter.

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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it 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

0
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

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2004-09-01 Airbus: Amendment 39-13590. Docket 2004-NM-57-AD.

    Applicability: Model A300 B4-600, B4-600R, C4-605R Variant F, 
and F4-600R (collectively called A300-600) series airplanes; and 
Model A310 series airplanes; certificated in any category; equipped 
with GE CF6-80C2 engines.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent loss of the relevant alternating current (AC) bus 
bar, reduced structural integrity of the engine pylon, and 
consequent loss of control of the airplane, accomplish the 
following:

All Operators Telex Reference

    (a) The term ``All Operators Telex,'' or ``AOT,'' as used in 
this AD, means the following AOTs, as applicable:
    (1) For Model A300 B4-600, B4-600R, C4 605R Variant F, and F4-
600R (collectively called A300-600) series airplanes: Airbus AOT 
A300-54A6037, dated February 19, 2004; and
    (2) For Model A310 series airplanes: Airbus AOT A310-54A2038, 
dated February 19, 2004.

Inspection

    (b) At the applicable time in paragraph (b)(1) or (b)(2) of this 
AD, do a one-time detailed inspection for discrepancies of the 
integrated drive generator (IDG) harness, harness bracket, retaining 
fasteners, and pyramid arm, in accordance with the applicable AOT.
    (1) For airplanes on which Airbus Modification 07591 has not 
been incorporated as of the effective date of this AD: Within 10 
days after the effective date of this AD.
    (2) For airplanes on which Airbus Modification 07591 has been 
incorporated as of the effective date of this AD: Within 600 flight 
hours after the effective date of this AD.


    Note 1: For the purposes of this AD, a detailed 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.''

No Further Action if No Discrepancies Are Found

    (c) If there are no discrepancies found during the inspection 
required by paragraph (b) of this AD, no further action is required 
by this AD.

Related Investigative and Corrective Actions for Damaged Electrical 
Harness

    (d) If any discrepancy in the IDG electrical harness, fretting 
at the convoluted conduits, or contact between the IDG electrical 
harness and the pyramid arms is found during the inspection required 
by paragraph (b) of this AD: Before further flight, do the 
applicable related investigative actions and corrective actions in 
accordance with the applicable AOT.

Corrective Action for Damaged Electrical Harness Bracket, Retaining 
Fasteners, or Pyramid Arm

    (e) If any discrepancy in the electrical harness bracket, 
retaining fasteners, or pyramid arm is found during the inspection 
required by paragraph (b) of this AD: Before further flight, repair 
in accordance with a method approved by either the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) 
(or its delegated agent).

No Reporting Requirement

    (f) Although the referenced AOTs describe procedures for 
submitting certain information to the manufacturer, this AD does not 
require those actions.

Alternative Methods of Compliance

    (g) In accordance with 14 CFR 39.19, the Manager, International 
Branch, ANM-116, is authorized to approve alternative methods of 
compliance for this AD.

Incorporation by Reference

    (h) Unless otherwise specified in this AD, the actions shall be 
done in accordance with Airbus All Operators Telex (AOT) A300-
54A6037, dated February 19, 2004; or A310-54A2038, dated February 
19, 2004; 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, 1 Rond Point Maurice Bellonte,

[[Page 23093]]

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 2: The subject of this AD is addressed in French 
airworthiness directive F-2004-039, dated March 17, 2004.

Effective Date

    (i) This amendment becomes effective on May 13, 2004.

    Issued in Renton, Washington, on April 16, 2004.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-9241 Filed 4-27-04; 8:45 am]
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