[Federal Register: July 29, 2004 (Volume 69, Number 145)]
[Rules and Regulations]
[Page 45243-45246]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29jy04-9]
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DEPARTMENT OF TRANSPORTATION (DOT)
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18681; Directorate Identifier 2004-NM-56-AD;
Amendment 39-13748; AD 2004-15-14]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A319-131, -132, and -133;
A320-231, -232, and -233; and A321-131 and -231 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus Model A319-131, -132, and -133; A320-231, -232, and -
233; and A321-131 and -231 series airplanes. This AD requires revising
the airplane flight manual (AFM) to advise the flightcrew of procedures
associated with the intermittent interruption of the electrical power.
Under certain conditions, this AD also requires inspecting for signs of
arcing and performing any necessary corrective actions. This AD also
provides for optional terminating action for the requirements of the
AD. This AD is prompted by reports of fretting and consequent arcing of
the electrical harness of the integrated drive generator (IDG) at the
pin-to-socket connector at the firewall. We are issuing this AD to
prevent transient loss of certain systems and consequent reduced
ability of the flightcrew to cope with adverse flight conditions.
DATES: Effective August 13, 2004.
The incorporation by reference of certain publications listed in
the AD is approved by the Director of the Federal Register as of August
13, 2004.
We must receive comments on this AD by September 27, 2004.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401,
Washington, DC 20590.
[[Page 45244]]
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For the service information identified in this AD, contact Airbus,
1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. You can
examine this information at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Docket Management System (DMS)
The FAA has implemented new procedures for maintaining AD dockets
electronically. As of May 17, 2004, new AD actions are posted on DMS
and assigned a docket number. We track each action and assign a
corresponding directorate identifier. The DMS AD docket number is in
the form ``Docket No. FAA-2004-99999.'' The Transport Airplane
Directorate identifier is in the form ``Directorate Identifier 2004-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier
(``Old Docket Number'') as a cross-reference for searching purposes.
Examining the Dockets
You can examine the AD docket on the Internet at http://dms.dot.gov
, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is on the plaza level of the Nassif Building at the DOT street
address stated in the ADDRESSES section. Comments will be available in
the AD docket shortly after the DMS receives them.
FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2141; 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 of numerous reports of the intermittent
interruption of the electrical power supply. The power interruption has
been attributed to arcing of the electrical harness of the integrated
drive generator (IDG) at the pin-to-socket connector at the firewall.
The affected IDG connectors are installed on Airbus Model A319, A320,
and A321 series airplanes equipped with International Aero Engines
(IAE) Model V2500. In most of the incidents, the generator control unit
(GCU) detected the arcing and shut down the associated IDG with only
minor consequences. However, in some cases, the GCU--because of
intermittent arcing--did not shut down the IDG. Investigation revealed
that the arcing is due to fretting corrosion between the Cannon
connector installed on the nacelle side of the firewall and the Souriau
connector installed on the pylon side of the firewall. The following
events have occurred or could occur during flight as a result of the
intermittent loss of electrical power supply:
Flickering cabin lights;
Flickering primary flight and navigation displays;
Transient disconnection of several systems (autopilot, yaw
damper, auto throttle), triggering warnings from the electronic
centralized aircraft monitoring (ECAM) displays and prompting
diversions to the nearest available airport; and
Loss of IDG power supply on the affected engine.
These conditions, if not corrected, could result in reduced ability
of the flightcrew to cope with adverse flight conditions.
Relevant Service Information
Airbus has issued Temporary Revision (TR) 4.02.00/20 to the A318/
319/320/321 Airplane Flight Manual (AFM). The TR, dated May 3, 2004,
provides background information and operational recommendations
regarding the intermittent interruption of electrical power supply.
Airbus has also issued Service Bulletin A320-71-1030, dated
February 27, 2003. The service bulletin describes procedures for
replacing the IDG harness on the nacelle side of the firewall to
eliminate the pin-to-socket arcing. Specifically, harnesses having
Cannon connectors are replaced with harnesses having Souriau
connectors. The Souriau connector provides a better connection of the
IDG electrical harness at the firewall. Airbus Service Bulletin A320-
71-1030 refers to International Aero Engines Information Bulletin
V2500-NAC-70-0736, dated January 28, 2003, as an additional source of
information for the IDG harness/connector replacement.
The DGAC approved these service documents. The DGAC has issued
French airworthiness directive F-2004-074, dated May 26, 2004, to
ensure the continued airworthiness of these airplanes in France.
FAA's Determination and Requirements of This AD
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. We have examined the DGAC's findings,
evaluated all pertinent information, and determined that AD action is
necessary for products of this type design that are certificated for
operation in the United States.
Therefore, we are issuing this AD to prevent transient loss of the
systems connected to the affected arcing connector and consequent
reduced ability of the flightcrew to cope with adverse flight
conditions. This AD requires revising the AFM to advise the flightcrew
of procedures associated with the intermittent interruption of the
electrical power. Under certain conditions, this AD also requires
inspecting for signs of arcing and performing any necessary corrective
actions. This AD also provides for optional terminating action for the
requirements of the AD. The actions must be done in accordance with the
service information described previously, except as described below.
Differences Between FAA and DGAC Airworthiness Directive
The following differences have been coordinated between the FAA and
the DGAC.
The French airworthiness directive does not require inspecting an
IDG that has been shut down in accordance with the TR or that has been
shut down automatically. We have determined that investigative and
corrective actions (including an inspection for signs of arcing, and
repair or replacement of any discrepant IDG harness/connector with a
new harness/connector) are necessary due to the severity of the problem
to prevent the unsafe condition from recurring. The inspections and
corrective actions must be done in accordance with a method approved by
the FAA.
The French airworthiness directive applies to all Model A319, A320,
and A321 series airplanes equipped with IAE V2500 series engines--
regardless of the type of connector installed. This AD, however,
applies to only those airplanes having Cannon connectors on the
[[Page 45245]]
nacelle side of the firewall and Souriau connectors on the pylon side
of the firewall. There have been no reported problems on airplanes
equipped with Souriau connectors on both sides of the firewall.
Therefore, the applicability of this AD excludes production airplanes
that have been equipped with Souriau connectors on both sides of the
firewall on both engines (accomplished via Airbus Modification 32943).
This AD also includes a provision for replacing, on both engines, the
IDG harnesses having Cannon connectors with IDG harnesses having
Souriau connectors; this replacement would terminate the requirements
of this AD.
Interim Action
We consider this AD interim action. We may consider further
rulemaking at a later date to mandate replacement of the subject
connectors, as specified in Airbus Service Bulletin A320-71-1030.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD; therefore, providing notice and opportunity for public comment
before the AD is issued is impracticable, and good cause exists to make
this AD effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any written relevant
data, views, or arguments regarding this AD. Send your comments to an
address listed under ADDRESSES. Include ``Docket No. FAA-2004-18681;
Directorate Identifier 2004-NM-56-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD. We will consider
all comments received by the closing date and may amend the AD in light
of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of our docket
Web site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You can review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you can visit
http://dms.dot.gov.
We are reviewing the writing style we currently use in regulatory
documents. We are interested in your comments on whether the style of
this document is clear, and your suggestions to improve the clarity of
our communications with you. You can get more information about plain
language at http://www/faa.gov/language and http://www.plainlanguage.gov.Regulatory
Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD 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.
For the reasons discussed above, I certify that the 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. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD. See the ADDRESSES section for a location to
examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2004-15-14 Airbus: Amendment 39-13748. Docket No. FAA-2004-18681;
Directorate Identifier 2004-NM-56-AD.
Effective Date
(a) This AD becomes effective August 13, 2004.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A319-131, -132, and -133;
A320-231, -232, and -233; and A321-131 and ``231 series airplanes;
certificated in any category; except those airplanes on which Airbus
Modification 32943 has been incorporated in production.
Unsafe Condition
(d) This AD was prompted by reports of intermittent interruption
of the electrical power supply due to fretting and consequent arcing
of the electrical harness of the integrated drive generator (IDG) at
the pin-to-socket connector at the firewall. The FAA is issuing this
AD to prevent the transient loss of certain systems and the
consequent reduced ability of the flightcrew to cope with adverse
flight conditions.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Revision of Airplane Flight Manual (AFM)
(f) Within 10 days after the effective date of this AD, revise
the Limitations section of the Airbus A318/319/320/321 AFM to
include the information in Temporary Revision (TR) 4.02.00/20, dated
May 3, 2004. This may be done by inserting a copy of the TR into the
AFM. When the TR has been included in general revisions of the AFM,
those general revisions may be inserted into the AFM, provided the
relevant information in the general revisions is identical to that
in the TR.
Post-IDG Shutdown Inspection
(g) If an IDG is shut down by the flightcrew in accordance with
the TR procedures specified in paragraph (f) of this AD, or if an
IDG is shut down automatically, do the actions specified in
paragraph (g)(1) or (g)(2) of this AD.
(1) Before further flight, inspect the firewall connector of the
affected IDG to detect signs of arcing, in accordance with a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA. If any sign of arcing is detected: Before
further flight, either repair the connector or replace the connector
with a new connector, in accordance with a method approved by the
Manager, International Branch, ANM-116.
(2) Operate the airplane with the affected IDG inoperative in
accordance with the provisions and compliance periods specified in
the FAA-approved Master Minimum Equipment List. Before further use
of the affected IDG, do the actions specified in paragraph (g)(1) of
this AD.
Terminating Action
(h) Replacement of the IDG harnesses and connectors on both
engines in accordance
[[Page 45246]]
with Airbus Service Bulletin A320-71-1030, dated February 27, 2003,
terminates the requirements of this AD.
Note 1: Airbus Service Bulletin A320-71-1030 refers to
International Aero Engines Information Bulletin V2500-NAC-70-0736,
dated January 28, 2003, as an additional source of information for
the harness/connector replacement specified in paragraph (h) of this
AD.
Alternative Methods of Compliance (AMOCs)
(i) The Manager, International Branch, ANM-116, has the
authority to approve AMOCs for this AD, if requested in accordance
with the procedures found in 14 CFR 39.19.
Material Incorporated by Reference
(j) Unless this AD specifies otherwise, you must use Temporary
Revision 4.02.00/20, dated May 3, 2004, to the Airbus A318/319/320/
321 Airplane Flight Manual; and Airbus Service Bulletin A320-71-
1030, dated February 27, 2003; as applicable; to perform the actions
that are required by this AD. (Only page 1 of the temporary revision
contains the date of the document.) The Director of the Federal
Register approves the incorporation by reference of these documents
in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. For copies of
the documents, contact Airbus, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France. You can review copies at the Docket
Management Facility, U.S. Department of Transportation, 400 Seventh
Street, SW., room PL-401, Nassif Building, Washington, DC; or at the
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call (202) 741-6030,
or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Related Information
(k) French airworthiness directive F-2004-074, dated May 26,
2004, also addresses the subject of this AD.
Issued in Renton, Washington, on July 16, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service
[FR Doc. 04-16914 Filed 7-28-04; 8:45 am]
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