Document ID: FAA-2012-0111-0006
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2013-04-10T04:00Z

[Federal Register Volume 78, Number 69 (Wednesday, April 10, 2013)]
[Rules and Regulations]
[Pages 21227-21229]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-08047]

[[Page 21227]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0111; Directorate Identifier 2011-NM-089-AD; 
Amendment 39-17407; AD 2013-07-03]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A330-200, A330-200 Freighter, A330-300, A340-200, and 
A340-300 series airplanes; and Model A340-541 airplanes and Model A340-
642 airplanes. This AD was prompted by reports of cracks in the bogie 
pivot pin caused by material heating due to friction between the bogie 
pivot pin and bush, leading to chrome detachment and chrome dragging on 
the bogie pivot pin. This AD requires repetitive detailed inspections 
for degradation of the bogie pivot pins and for any cracks and damage 
of the pivot pin bushes of the main and central landing gear; a 
magnetic particle inspection of the affected bogie pivot pins for 
corrosion and base metal cracks; and repairing or replacing bogie pivot 
pins and pivot pin bushes, if necessary. We are issuing this AD to 
detect and correct cracks and damage to the main and central landing 
gear, which could result in the collapse of the landing gear and 
adversely affect the airplane's continued safe flight and landing.

DATES: This AD becomes effective May 15, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of May 15, 2013.

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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-1138; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to include an AD that would apply to the specified 
products. That SNPRM was published in the Federal Register on September 
7, 2012 (77 FR 55163). That SNPRM proposed to correct an unsafe 
condition for the specified products. The Mandatory Continuing 
Airworthiness Information (MCAI) states:

    During removals of A330/340 Main Landing Gear (MLG) Bogie Beams 
and A340-500/600 Center Landing Gear (CLG) Bogie Beams, cracks in 
the bogie pivot pin were found.
    Investigations indicated that these findings were the result of 
material heating, caused by friction between bogie pivot pin and 
bush, leading to chrome detachment and stress corrosion cracking.
    This condition, if not detected and corrected, could lead to 
collapse of the main or center landing gear, possibly resulting in 
damage to the aeroplane and/or injury to occupants.
    As a precautionary measure, EASA [European Aviation Safety 
Agency] issued AD 2011-0040 to require a one-time [detailed] 
inspection of the MLG (all types of A330 and A340 aeroplanes) and 
CLG (A340-500/600 aeroplanes only) to detect degradation or cracking 
of the bogie pivot pin [and to detect cracks and damage of the 
bushes], as applicable to aeroplane model, and the reporting of 
inspections results.
    Following issuance of EASA AD 2011-0040, several operators 
reported finding chrome detachment or chrome dragging on bogie pivot 
pin. New cases of cracks were also reported. It has been confirmed 
as well that, due to similar design, the enhanced MLG bogie pivot 
pin (Airbus modification 54500) could also be affected by this 
condition.
    Prompted by these findings, Airbus have developed an inspection 
programme consisting of repetitive inspections of the bogie pivot 
pin and applicable corrective actions.
    For the reasons described above, this [EASA] AD, which 
supersedes EASA AD 2011-0040 and extends the applicability to all 
A330 and A340 aeroplanes, requires accomplishment of repetitive 
inspections of the MLG and CLG (for A340-500 and A340-600 
aeroplanes) bogie pivot pins and pivot pin bushes, and corrective 
actions, depending on findings.

Required actions also include, for certain airplanes, a magnetic 
particle inspection of the bogie pivot pin for corrosion and base metal 
cracks. The corrective actions include replacing any cracked or damaged 
pivot pin bush with a new or serviceable pivot pin bush, and replacing 
any corroded or cracked bogie pin with a new bogie pin. 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 have considered the comments received.

Request To Change the Compliance Time

    Delta Air Lines, Inc. (DAL) requested that the initial compliance 
time in paragraph (g) of the SNPRM (77 FR 55163, September 7, 2012) be 
changed from ``* * * first flight of the airplane,'' to ``* * * first 
flight of the new or overhauled landing gear,'' in two locations in 
that paragraph. The commenter did not provide rationale for this 
request.
    We disagree with DAL's request. Our compliance time coincides with 
EASA AD 2012-0053, dated March 30, 2012, which specifically states, 
``Accomplishment of an overhaul of the landing gear does not substitute 
the accomplishment of an inspection as required by paragraph (1) of 
this [EASA] AD.'' The inspections required by this final rule are not 
equivalent to what is accomplished during landing gear overhaul. 
However, if the inspections required by this final rule are positively 
verified to have been accomplished during overhaul, the overhaul date 
may be used to determine the next repetitive inspection date. We have 
not changed this final rule in this regard.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed--except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
SNPRM (77 FR 55163, September 7, 2012) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM (77 FR 55163, September 7, 2012).

Costs of Compliance

    We estimate that this AD will affect 29 products of U.S. registry. 
We also estimate that it will take about 22 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 $54,230, or $1,870 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 6 work-hours and require parts costing $21,222, for a cost 
of $21,732 per product. We have no way of determining the number of 
products that may need these actions.

[[Page 21228]]

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 that 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);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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 SNPRM (77 FR 55163, September 7, 
2012), 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 adding the following new AD:

2013-07-03 Airbus: Amendment 39-17407. Docket No. FAA-2012-0111; 
Directorate Identifier 2011-NM-089-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective May 15, 
2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
243, -223F, -243F, -301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes; Model A340-211, -212, -213, -311, -312, and -313 
airplanes; and Model A340-541 and Model A340-642 airplanes; 
certificated in any category; all manufacturer serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of cracks in the bogie pivot pin 
caused by material heating due to friction between the bogie pivot 
pin and bush, leading to chrome detachment and chrome dragging on 
the bogie pivot pin. We are issuing this AD to detect and correct 
cracks and damage to the main and central landing gear, which could 
result in the collapse of the landing gear and adversely affect the 
airplane's continued safe flight and landing.

(f) Compliance

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

(g) Detailed Inspection

    Within 26 months after the effective date of this AD or 26 
months after the first flight of the airplane, whichever occurs 
later, but no earlier than 12 months after the first flight of the 
airplane: Do a detailed inspection for degradation (i.e., loss of 
chromium plate, loose chromium, sharp edges) of the bogie pivot pins 
and for any cracks and damage of the pivot pin bushes of the main 
landing gear, and, as applicable, the central landing gear, in 
accordance with the Accomplishment Instructions of the applicable 
service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of 
this AD. Repeat the inspection thereafter at intervals not to exceed 
26 months. Accomplishment of an overhaul of the landing gear does 
not substitute the accomplishment of the inspection as required by 
this paragraph.
    (1) Airbus Mandatory Service Bulletin A330-32-3240, Revision 02, 
including Appendices 01 and 02, dated December 2, 2011 (for Model 
A330-200 series airplanes, Model A330-200 Freighter series 
airplanes, and Model A330-300 series airplanes).
    (2) Airbus Mandatory Service Bulletin A340-32-4281, Revision 01, 
including Appendices 01 and 02, dated December 2, 2011 (for Model 
A340-200 series airplanes and Model A340-300 series airplanes).
    (3) Airbus Mandatory Service Bulletin A340-32-5096, Revision 01, 
including Appendices 01 and 02, dated December 2, 2011 (for Model 
A340-541 airplanes and Model A340-642 airplanes).

(h) Corrective Action for Any Pivot Pin Bush Found Cracked or Damaged

    If, during any inspection required by paragraph (g) of this AD, 
any pivot pin bush is found cracked or damaged: Before further 
flight, repair or replace the pivot pin bush with a new or 
serviceable pivot pin bush, in accordance with the Accomplishment 
Instructions of the applicable service bulletin specified paragraph 
(h)(1), (h)(2), or (h)(3) of this AD.
    (1) Airbus Mandatory Service Bulletin A330-32-3240, Revision 02, 
including Appendices 01 and 02, dated December 2, 2011 (for Model 
A330-200 series airplanes, Model A330-200 Freighter series 
airplanes, and Model A330-300 series airplanes).
    (2) Airbus Mandatory Service Bulletin A340-32-4281, Revision 01, 
including Appendices 01 and 02, dated December 2, 2011 (for Model 
A340-200 series airplanes and Model A340-300 series airplanes).
    (3) Airbus Mandatory Service Bulletin A340-32-5096, Revision 01, 
including Appendices 01 and 02, dated December 2, 2011 (for Model 
A340-541 airplanes and Model A340-642 airplanes).

(i) Corrective Action for Any Bogie Pivot Pin Found With Degraded 
Chrome Plating

    If, during any inspection required by paragraph (g) of this AD, 
degraded chrome plating on any bogie pivot pin is found: Before 
further flight, do a non-destructive test (magnetic particle 
inspection) of the affected bogie pivot pin for corrosion and base 
metal cracks, in accordance with the Accomplishment Instructions of 
the applicable service bulletin specified paragraph (i)(1), (i)(2), 
or (i)(3) of this AD.
    (1) Airbus Mandatory Service Bulletin A330-32-3240, Revision 02, 
including Appendices 01 and 02, dated December 2, 2011 (for Model 
A330-200 series airplanes, Model A330-200 Freighter series 
airplanes, and Model A330-300 series airplanes).
    (2) Airbus Mandatory Service Bulletin A340-32-4281, Revision 01, 
including

[[Page 21229]]

Appendices 01 and 02, dated December 2, 2011 (for Model A340-200 
series airplanes and Model A340-300 series airplanes).
    (3) Airbus Mandatory Service Bulletin A340-32-5096, Revision 01, 
including Appendices 01 and 02, dated December 2, 2011 (for Model 
A340-541 airplanes and Model A340-642 airplanes).

(j) Corrective Action for Any Bogie Pivot Pin Found Corroded or Found 
With Cracked Base Metal

    If, during the non-destructive test (magnetic particle 
inspection) specified in paragraph (i) of this AD, the bogie pivot 
pin is found corroded or the base metal is found cracked: Before 
further flight, repair or replace the bogie pin with a new or 
serviceable bogie pin, in accordance with the Accomplishment 
Instructions of the applicable service bulletin specified paragraph 
(j)(1), (j)(2), or (j)(3) of this AD.
    (1) Airbus Mandatory Service Bulletin A330-32-3240, Revision 02, 
including Appendices 01 and 02, dated December 2, 2011 (for Model 
A330-200 series airplanes, Model A330-200 Freighter series 
airplanes, and Model A330-300 series airplanes).
    (2) Airbus Mandatory Service Bulletin A340-32-4281, Revision 01, 
including Appendices 01 and 02, dated December 2, 2011 (for Model 
A340-200 series airplanes and Model A340-300 series airplanes).
    (3) Airbus Mandatory Service Bulletin A340-32-5096, Revision 01, 
including Appendices 01 and 02, dated December 2, 2011 (for Model 
A340-541 airplanes and Model A340-642 airplanes).

(k) No Terminating Action

    Accomplishment of the corrective actions required by paragraphs 
(h) and (j) of this AD does not terminate the repetitive inspections 
required by paragraph (g) of this AD.

(l) Reporting Requirement

    Submit a one-time report of the findings (both positive and 
negative) of the inspections required by paragraphs (g) and (i) of 
this AD to Airbus, Customer Services Directorate, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex France, ATTN: SDC32 Technical 
Data and Documentation Services; fax (+33) 5 61 93 28 06; email 
sb.reporting@airbus.com; at the applicable time specified in 
paragraph (l)(1) or (l)(2) of this AD. The report must include the 
inspection results and a description of any discrepancies found.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 90 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 90 days after the effective date of 
this AD.

(m) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (g) through (j) of this AD, if those actions were 
performed before the effective date of this AD using the service 
information specified in paragraphs (m)(1) through (m)(4) of this 
AD, which are not incorporated by reference in this AD.
    (1) Airbus Mandatory Service Bulletin A330-32-3240, including 
Appendix 1, dated December 8, 2010 (for Model A330-200 series 
airplanes, Model A330-200 Freighter series airplanes, and Model 
A330-300 series airplanes).
    (2) Airbus Mandatory Service Bulletin A330-32-3240, including 
Appendix 1, Revision 01, dated May 4, 2011 (for Model A330-200 
series airplanes, Model A330-200 Freighter series airplanes, and 
Model A330-300 series airplanes).
    (3) Airbus Mandatory Service Bulletin A340-32-4281, including 
Appendix 1, dated December 8, 2010 (for Airbus Model A340-200 series 
airplanes and Model A340-300 series airplanes).
    (4) Airbus Mandatory Service Bulletin A340-32-5096, including 
Appendix 1, dated December 8, 2010 (for Model A340-541 airplanes and 
Model A340-642 airplanes).

(n) Other FAA AD Provisions

    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: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149. 
Information may be emailed 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.
    (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.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(o) Related Information

    Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2012-0053, dated March 30, 2012, and the service 
information specified in paragraphs (o)(1) through (o)(3) of this 
AD, for related information.
    (1) Airbus Mandatory Service Bulletin A330-32-3240, Revision 02, 
including Appendices 01 and 02, dated December 2, 2011.
    (2) Airbus Mandatory Service Bulletin A340-32-4281, Revision 01, 
including Appendices 01 and 02, dated December 2, 2011.
    (3) Airbus Mandatory Service Bulletin A340-32-5096, Revision 01, 
including Appendices 01 and 02, dated December 2, 2011.

(p) Material Incorporated by Reference

    (1) The Director of the Federal Registe approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Airbus Mandatory Service Bulletin A330-32-3240, Revision 02, 
including Appendices 01 and 02, dated December 2, 2011.
    (ii) Airbus Mandatory Service Bulletin A340-32-4281, Revision 
01, including Appendices 01 and 02, dated December 2, 2011.
    (iii) Airbus Mandatory Service Bulletin A340-32-5096, Revision 
01, including Appendices 01 and 02, dated December 2, 2011.
    (3) For service information identified in this AD, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@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, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.
    (5) You may view this 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/cfr/ibr-locations.html.

    Issued in Renton, Washington, on March 28, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-08047 Filed 4-9-13; 8:45 am]
BILLING CODE 4910-13-P