Airworthiness Directives; Airbus Model A330, A340-200, and A340-300 Series Airplanes

[Federal Register Volume 69, Number 149 (Wednesday, August 4, 2004)]
[Rules and Regulations]
[Pages 46979-46981]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-17623]



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Federal Register / Vol. 69, No. 149 / Wednesday, August 4, 2004 / 
Rules and Regulations

[[Page 46979]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18669; Directorate Identifier 2004-NM-83-AD; 
Amendment 39-13757; AD 2004-16-01]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330, A340-200, and A340-
300 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Model A330, A340-200, and A340-300 series airplanes. 
This AD requires repetitive inspections for cracking of the chromed 
area of the left and right piston rods for the main landing gear (MLG) 
retraction actuators, and related investigative and corrective actions 
if necessary. This AD is prompted by reports of the piston rods for the 
MLG retraction actuators rupturing during flight. We are issuing this 
AD to detect and correct corrosion pitting and cracking of the piston 
rods for the MLG retraction actuators, which could result in rupture of 
a piston rod, non-damped extension of the MLG, high loads on the fully 
extended MLG, and consequent reduced structural integrity of the MLG.

DATES: Effective August 19, 2004.
    The incorporation by reference of certain publications listed in 
the AD is approved by the Director of the Federal Register as of August 
19, 2004.
    We must receive comments on this AD by October 4, 2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD.
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401, 
Washington, DC 20590.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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 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.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., room PL-401, on 
the plaza level of the Nassif Building, Washington, DC.

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 located 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 Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2797; 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 A330, A340-200, and A340-300 series airplanes. The DGAC 
advises that it has received a report of the flightcrew on a Model A330 
series airplane doing a free-fall extension of the main landing gear 
(MLG) during approach. Investigation revealed a rupture of the piston 
rod for the left MLG retraction actuator. It was determined that 
corrosion and cracking caused the rupture. Additional reports indicate 
that cracking was found on the chromed area of several piston rods; the 
cracking started from a line of corrosion pitting in the rod bores. 
These conditions, if not corrected, could result in rupture of a piston 
rod, non-damped extension of the MLG, and high loads on the fully 
extended MLG, which could result in reduced structural integrity of the 
MLG.
    The MLG system on Model A340-200 and A340-300 series airplanes is 
identical to the MLG system on the affected Model A330 series 
airplanes. Therefore, Model A340-200 and A340-300 series airplanes may 
be subject to the same unsafe condition identified on the Model A330 
series airplanes.

Relevant Service Information

    Airbus has issued Service Bulletin A330-32-3173, Revision 01 (for 
Model A330 series airplanes); and A340-32-4212, Revision 01 (for Model 
A340-200 and -300 series airplanes); both dated June 16, 2004. The 
service bulletins describe procedures for repetitive detailed visual 
inspections for cracking of the chromed area of the left and right 
piston rods for the MLG retraction actuators. If any cracking is found, 
the corrective actions include replacing the

[[Page 46980]]

affected MLG retraction actuator with a new actuator before the next 
flight.
    The service bulletins also describe procedures for related 
investigative actions. Those procedures include repetitive ultrasonic 
inspections for corrosion pitting and cracking of the inner surface of 
the piston rods for the MLG retraction actuators. If any corrosion 
pitting or cracking is found, the corrective actions include replacing 
the affected MLG retraction actuator with a new actuator. The 
compliance time for the corrective action depends on the results of the 
ultrasonic inspection, and is either before the next flight, or within 
the next 10 landings.
    The service bulletins also include procedures for reporting the 
results of both the detailed visual and ultrasonic inspections to 
Airbus.
    The DGAC mandated these service bulletins and issued French 
airworthiness directives F-2004-086 and F-2004-087, both dated June 23, 
2004, to ensure the continued airworthiness of these airplanes in 
France.
    Both of the Airbus service bulletins reference Messier-Dowty 
Service Bulletin A33/34-32-222, including Appendices A and B, dated 
December 6, 2003, as an additional source of service information for 
the detailed visual and ultrasonic inspections.

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 
detect and correct corrosion pitting and cracking of the piston rods 
for the MLG retraction actuators, which could result in rupture of the 
piston rods, non-damped extension of the MLG, high loads on the fully 
extended MLG, and consequent reduced structural integrity of the MLG.
    This AD requires doing the actions specified in the Airbus service 
information described previously, except as discussed under 
``Differences Between the AD and French Airworthiness Directives.'' 
This AD also requires sending certain inspection results to the 
manufacturer.

Interim Action

    We consider this AD to be interim action. The inspection reports 
that are required by this AD will enable the manufacturer to obtain 
better insight into the nature, cause, and extent of the corrosion/
cracking, and eventually to develop final action to address the unsafe 
condition. Once final action has been identified, we may consider 
further rulemaking.

Differences Between the AD and French Airworthiness Directives

    The French airworthiness directives do not include compliance times 
for airplanes equipped with piston rods that have been in service less 
than 36 months, as of the effective date of the French airworthiness 
directives. However, the FAA AD includes compliance times for these 
airplanes. Because this AD is an interim action, we have determined 
that it is necessary to address airplanes equipped with piston rods 
that are close to having 36 months in service, as of the effective date 
of the AD. This difference has been coordinated with the DGAC.

Clarification of Inspection Terminology

    The Airbus service bulletins specify to do a ``detailed visual 
inspection'' of the chromed area of the piston rods for the MLG 
retraction actuators. This AD instead requires a ``detailed 
inspection,'' which is defined in Note 1 of this AD.

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-2004-18669; 
Directorate Identifier 2004-NM-83-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:

[[Page 46981]]

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):

2004-16-01 Airbus: Amendment 39-13757. Docket No. FAA-2004-18669; 
Directorate Identifier 2004-NM-83-AD.

Effective Date

    (a) This AD becomes effective August 19, 2004.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A330, A340-200, and A340-300 
series airplanes; certificated in any category; equipped with a 
piston rod, part number (P/N) 114256309 or 114256321, for the main 
landing gear (MLG) retraction actuators.

Unsafe Condition

    (d) This AD was prompted by reports of the piston rods for the 
MLG retraction actuators rupturing during flight. We are issuing 
this AD to detect and correct corrosion pitting and cracking of the 
piston rods for the MLG retraction actuators, which could result in 
rupture of a piston rod, non-damped extension of the MLG, high loads 
on the fully extended MLG, and consequent reduced structural 
integrity of the MLG.

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.

Repetitive Detailed Inspections and Corrective Actions

    (f) Before each MLG retraction actuator has been in service 36 
months, or within 14 days after the effective date of this AD, 
whichever is later: Do a detailed inspection for cracking of the 
chromed area of the left and right piston rod of the MLG retraction 
actuators. Do the inspection in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-32-3173, Revision 01 
(for Model A330 series airplanes); or A340-32-4212, Revision 01 (for 
Model A340-200 and -300 series airplanes); both dated June 16, 2004; 
as applicable. Repeat the inspection thereafter at intervals not to 
exceed 7 days.


    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''


    (g) If any cracking is found during any inspection required by 
paragraph (f) of this AD: Before further flight, replace the MLG 
retraction actuator with a new or serviceable part in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A330-32-3173, Revision 01 (for Model A330 series airplanes); or 
A340-32-4212, Revision 01 (for Model A340-200 and -300 series 
airplanes); both dated June 16, 2004; as applicable.

Related Investigative and Corrective Actions

    (h) If no cracking is found during the initial detailed 
inspection required by paragraph (f) of this AD: At the later of the 
times specified in paragraphs (h)(1) and (h)(2) of this AD, do an 
ultrasonic inspection for corrosion pitting or cracking of the inner 
surface of the piston rods for the MLG retraction actuators. Do the 
ultrasonic inspection in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-32-3173, Revision 01 
(for Model A330 series airplanes); or A340-32-4212, Revision 01 (for 
Model A340-200 and -300 series airplanes); both dated June 16, 2004; 
as applicable. Any corrective action must be done at the times 
specified in Figure 2 of the applicable service bulletin.
    (1) Before each MLG retraction actuator has been in service 36 
months.
    (2) Within 1,400 flight hours, 250 flight cycles, or 4 months 
after the effective date of this AD, whichever is first.


    Note 2: Airbus Service Bulletins A330-32-3173, Revision 01; and 
A340-32-4212, Revision 01; reference Messier-Dowty Service Bulletin 
A33/34-32-222, including Appendices A and B, dated December 6, 2003, 
as an additional source of service information for doing the 
detailed and ultrasonic inspections.


    (i) Repeat the ultrasonic inspection thereafter at intervals not 
to exceed 1,400 flight hours, 250 flight cycles, or 4 months after 
the most recent ultrasonic inspection, whichever is first.

Reporting Requirement

    (j) Submit a report of the results (both positive and negative) 
for any ultrasonic inspection required by paragraph (h) of this AD, 
and only negative findings for any detailed inspection required by 
paragraph (f) of this AD. Submit the report to Airbus Customer 
Services Directorate, Attention: SDC32 Technical Data and 
Documentation Services, fax +33+ 5 61 93 28 06, or via your resident 
customer support office. Submit the report at the applicable time 
specified in paragraph (j)(1) or (j)(2) of this AD. The report must 
include the inspection results, a description of any discrepancies 
found, the airplane serial number, and the period of time the 
affected piston rod has been in service. Under the provisions of the 
Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office 
of Management and Budget (OMB) has approved the information 
collection requirements contained in this AD and has assigned OMB 
Control Number 2120-0056.
    (1) If the inspection is done after the effective date of this 
AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

Parts Installation

    (k) As of the effective date of this AD, no person may install a 
piston rod, part number (P/N) 114256309 or 114256321, for the main 
landing gear (MLG) retraction actuators, on any airplane, unless the 
part has been inspected in accordance with paragraphs (f) and (h) of 
this AD and found free of cracking.

Ultrasonic Inspections Done Per Airbus All Operator's Telex (AOT)

    (l) Ultrasonic inspections done in accordance with Airbus AOT 
A330-32A3172 (for Model A330 series airplanes); or A340-32A4211 (for 
Model A340-200 and -300 series airplanes); both dated May 22, 2003; 
are acceptable for compliance with the initial ultrasonic inspection 
required by paragraph (h) of this AD.

Alternative Methods of Compliance (AMOCs)

    (m) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.

Related Information

    (n) French airworthiness directives F-2004-086 and F-2004-087, 
both dated June 23, 2004, also address the subject of this AD.

Material Incorporated by Reference

    (o) You must use Airbus Service Bulletin A330-32-3173, Revision 
01, dated June 16, 2004; or Airbus Service Bulletin A340-32-4212, 
Revision 01, dated June 16, 2004; as applicable; to perform the 
actions that are required by this AD, unless the AD specifies 
otherwise. 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.

    Issued in Renton, Washington, on July 23, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-17623 Filed 8-3-04; 8:45 am]
BILLING CODE 4910-13-P

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