Airworthiness Directives:
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
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.
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
