
[Federal Register Volume 76, Number 202 (Wednesday, October 19, 2011)]
[Rules and Regulations]
[Pages 64798-64801]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-26082]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0478; Directorate Identifier 2010-NM-138-AD; 
Amendment 39-16832; AD 2011-21-09]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-103, B4-203, and 
B4-2C Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are superseding an existing airworthiness directive (AD) 
that applies to the products listed above. This AD results from 
mandatory continuing airworthiness information (MCAI) originated by an 
aviation authority of another country to identify and correct an unsafe 
condition on an aviation product. The MCAI describes the unsafe 
condition as:

    One operator reported a failure of the MLG [main landing gear] 
retraction actuator sliding rod. This incident occurred at a number 
of operating flight cycles lower than the limit value imposed by the 
MLG manufacturer.
    This condition, if not detected and corrected, results in 
undampened extension of the MLG, leading to higher than usual loads 
on the MLG attachment. Higher loads affect the structural integrity 
of the MLG and could lead to MLG failure.
* * * * *
We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective November 23, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 23, 
2011.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on June 8, 2011 (76 FR 
33176), and proposed to supersede AD 2007-25-15, Amendment 39-15297 (72 
FR 69601, December 10, 2007). That NPRM proposed to correct an unsafe 
condition for the specified products. The MCAI states:

    One operator reported a failure of the MLG [main landing gear] 
retraction actuator sliding rod. This incident occurred at a number 
of operating flight cycles lower than the limit value imposed by the 
MLG manufacturer.
    This condition, if not detected and corrected, results in 
undampened extension of the MLG, leading to higher than usual loads 
on the MLG attachment. Higher loads affect the structural integrity 
of the MLG and could lead to MLG failure.
    To address and correct this unsafe condition, EASA issued AD 
2006-0075 (now at Revision 2) [which corresponds to FAA AD 2007-25-
15 (72 FR 69601, December 10, 2007)] to require repetitive 
inspections of the retraction actuator sliding rod as installed on 
A300, A300-600 and A300-600ST aeroplanes and, depending on findings, 
repair or replacement of the affected parts.
    Since this event, studies have been performed by Airbus, the 
consequences of which are that for A300 aeroplanes, a new inspection 
program (new threshold and interval) has been established.
    For the reason described above, this new [EASA] AD retains the 
requirements of AD

[[Page 64799]]

2006-0075R2, which is superseded and requires the accomplishment of 
the repetitive inspections and associated corrective actions at the 
new intervals. In addition, the Airbus A300 Aircraft Maintenance 
Manual (AMM) Chapter 12-22-32 (associated to Maintenance Planning 
Document (MPD) task 321112-0505-1) has been revised to introduce a 
greasing action at the level of the pick-up jack fitting. 
Consequently, this AD also requires the repetitive lubrication task.
    For A300-600 and A300-600ST aeroplanes, the analyses have shown 
that, due to design differences, the loads induced on the MLG 
attachments are within acceptable margins. For that reason, this AD 
does not apply to those aeroplanes which were previously included in 
the applicability of EASA AD 2006-0075R2.

You may obtain further information by examining the MCAI in the AD 
docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received.

Request To Change Proposed Compliance Time

    The Air Line Pilots Association, International (ALPA) stated it 
supports the intent and language of the subject NPRM (76 FR 33176, June 
8, 2011), but requested the compliance time be changed in paragraph (g) 
of the NPRM to ``not to exceed 1000 flight hours or 12 months, 
whichever occurs first, under any circumstances.''
    We disagree with this request because the unsafe condition is 
flight-cycle dependent, and the commenter did not provide any 
supporting data to justify a change in the compliance time. We have not 
changed the AD in this regard.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting the 
AD as proposed.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect 3 products of U.S. registry. 
We also estimate that it will take about 6 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD to the U.S. operators to be $1,530, or $510 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 6 work-hours and require parts costing $0, for a cost of 
$510 per product. We have no way of determining the number of products 
that may need these actions.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We 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 this AD:
    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 and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains the NPRM (76 FR 33176, June 8, 2011), 
the regulatory evaluation, any comments received, and other 
information. The street address for the Docket Operations office 
(telephone (800) 647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    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 removing Amendment 39-15297 (72 FR 
69601, December 10, 2007) and adding the following new AD:

2011-21-09 Airbus: Amendment 39-16832. Docket No. FAA-2011-0475; 
Directorate Identifier 2010-NM-138-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
23, 2011.

Affected ADs

    (b) This AD supersedes AD 2007-25-15, Amendment 39-15297 (72 FR 
69601, December 10, 2007).

Applicability

    (c) This AD applies to Airbus Model A300 B4-103, B4-203, and B4-
2C airplanes; certificated in any category; equipped with main 
landing gear (MLG) retraction actuator having part number (P/N) 
C23129 fitted with sliding rod P/N C69029-2 or C69029-3.

Subject

    (d) Air Transport Association (ATA) of America Code 32: Landing 
gear.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    One operator reported a failure of the MLG [main landing gear] 
retraction actuator sliding rod. This incident occurred at a number 
of operating flight cycles lower than

[[Page 64800]]

the limit value imposed by the MLG manufacturer.
    This condition, if not detected and corrected, results in 
undampened extension of the MLG, leading to higher than usual loads 
on the MLG attachment. Higher loads affect the structural integrity 
of the MLG and could lead to MLG failure.
* * * * *

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Revised Compliance Times for Inspection of MLG Retraction Actuator and 
Corrective Actions

    (g) At the applicable time specified in paragraphs (g)(1), 
(g)(2), and (g)(3) of this AD: Remove the MLG retraction actuator 
having P/N C23129 and do a detailed and high frequency eddy current 
inspection for defects that exceed the criteria defined in Messier-
Dowty Special Inspection Service Bulletin 470-32-806, dated October 
27, 2005, of the retraction actuator sliding rods having P/N C69029-
2 or C69029-3, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A300-32-0450, Revision 02, dated 
July 28, 2009.
    (1) For airplanes on which the retraction actuator sliding rod 
has accumulated 12,000 or fewer total flight cycles as of the 
effective date of this AD: Inspect at the later of the times 
specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
    (i) Before the accumulation of 12,000 total flight cycles on the 
retraction actuator sliding rod.
    (ii) Within 2,000 flight cycles or 24 months after the effective 
date of this AD, whichever occurs first.
    (2) For airplanes on which the retraction actuator sliding rod 
has accumulated more than 12,000 total flight cycles, and 22,000 or 
fewer total flight cycles, as of the effective date of this AD: 
Inspect at the earliest of the times specified in paragraphs 
(g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD.
    (i) Before the accumulation of 23,000 total flight cycles on the 
retraction actuator sliding rod.
    (ii) Within 2,000 flight cycles after the effective date of this 
AD.
    (iii) Within 24 months after the effective date of this AD.
    (3) For airplanes on which the retraction actuator sliding rod 
has accumulated more than 22,000 total flight cycles as of the 
effective date of this AD: Inspect within 1,000 flight cycles or 12 
months after the effective date of this AD, whichever occurs first.
    (h) Thereafter, repeat the inspections required by paragraph (g) 
of this AD at intervals not to exceed 12,000 flight cycles.
    (i) If, during any inspection required by paragraph (g) or (h) 
of this AD, any defect is detected that exceeds the criteria defined 
in Messier-Dowty Special Inspection Service Bulletin 470-32-806, 
dated October 27, 2005, before further flight, replace the affected 
sliding rod with a serviceable unit in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-32-0450, Revision 02, dated July 28, 2009.
    (j) Before the accumulation of 32,000 flight cycles on any 
retraction actuator sliding rod, it must be replaced with a 
serviceable unit in accordance with the Accomplishment Instructions 
of Airbus Mandatory Service Bulletin A300-32-0450, Revision 02, 
dated July 28, 2009. Parts removed from an airplane as required by 
this paragraph must be returned to Messier-Dowty within 30 days 
after removing the part from the airplane.
    (k) As of the effective date of this AD, any MLG retraction 
actuator sliding rod having P/N C69029-2 or C69029-3 that has 
accumulated less than 32,000 total flight cycles, may be installed 
on any airplane, provided that the inspections required by 
paragraphs (g) and (h) of this AD are accomplished at the compliance 
times specified in paragraphs (g) and (h) of this AD and all 
applicable replacements required by paragraphs (i) and (j) of this 
AD are done.

Lubrication of the MLG Assembly

    (l) Within 1,500 flight hours after the effective date of this 
AD: Clean and lubricate the MLG assembly, in accordance with Task 
321112-0505-1 ``Main Landing Gear Assy,'' of Section 2-32, ``Systems 
and Powerplant Program: Landing Gear,'' of the Airbus A300 
Maintenance Planning Document, Revision 30, dated April 1, 2010. 
Repeat the cleaning and lubrication thereafter at intervals not to 
exceed 1,500 flight hours.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (m) Inspections accomplished before the effective date of this 
AD, in accordance with Airbus Mandatory Service Bulletin A300-32-
0450, dated December 1, 2005; or Airbus Mandatory Service Bulletin 
A300-32-0450, Revision 01, dated May 10, 2006; are acceptable for 
compliance with the corresponding requirements of this AD.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (n) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 227-2125; fax (425) 227-1149. 
Information may be e-mailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office. The AMOC approval letter must specifically reference this 
AD. AMOCs approved previously in accordance with AD 2007-25-15, 
Amendment 39-15297 (72 FR 69601, December 10, 2007), are approved as 
AMOCs for the corresponding provisions of this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

Related Information

    (o) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2010-0102, dated June 8, 2010; Airbus Mandatory Service 
Bulletin A300-32-0450, Revision 02, dated July 28, 2009; Messier-
Dowty Special Inspection Service Bulletin 470-32-806, dated October 
27, 2005; and Task 321112-0505-1, ``Main Landing Gear Assy,'' of 
Section 2-32, ``Systems and Powerplant Program: Landing Gear,'' of 
the Airbus A300 Maintenance Planning Document, Revision 30, dated 
April 1, 2010; for related information.

Material Incorporated by Reference

    (p) You must use Airbus Mandatory Service Bulletin A300-32-0450, 
Revision 02, excluding Appendix 1, dated July, 28, 2009; Messier-
Dowty Special Inspection Service Bulletin 470-32-806, dated October 
27, 2005; and Task 321112-0505-1, ``Main Landing Gear Assy,'' of 
Section 2-32, ``Systems and Powerplant Program: Landing Gear,'' of 
the Airbus A300 Maintenance Planning Document, Revision 30, dated 
April 1, 2010; to do the actions required by this AD, unless the AD 
specifies otherwise. (The revision level of the Airbus A300 
Maintenance Planning Document is identified in only the title page 
and transmittal letter of this document.)
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For Messier-Dowty service information identified in this AD, 
contact Messier Services Americas, Customer Support Center, 45360 
Severn Way, Sterling, Virginia 20166-8910; telephone 703-450-8233; 
fax 703-404-1621; Internet https://techpubs.services/messier-dowty.com.
    (3) For Airbus service information identified in this AD, 
contact Airbus SAS-EAW (Airworthiness Office), 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; e-mail account.airworth-eas@airbus.com; 
Internet http://www.airbus.com.
    (4) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.

[[Page 64801]]

    (5) You may also review copies of the service information that 
is incorporated by reference 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 September 28, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-26082 Filed 10-18-11; 8:45 am]
BILLING CODE 4910-13-P


