[Federal Register Volume 77, Number 174 (Friday, September 7, 2012)]
[Proposed Rules]
[Pages 55163-55166]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-22063]


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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]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) for certain Airbus Model A330-200, A330-300, A340-200, and A340-
300 series airplanes; and Model A340-541 airplanes and Model A340-642 
airplanes. That NPRM proposed to require performing a detailed 
inspection 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. That NPRM 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 action 
revises that NPRM by adding repetitive inspections and expanding the 
applicability. We are proposing 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. Since these actions impose an 
additional burden over that proposed in the NPRM, we are reopening the 
comment period to allow the public the chance to comment on these 
proposed changes.

DATES: We must receive comments on this proposed AD by October 22, 
2012.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed 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 [email protected]; Internet http://www.airbus.com. You may review copies of the referenced 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.

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 this proposed AD, 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.

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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-0111; 
Directorate Identifier 2011-NM-089-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We proposed to amend 14 CFR part 39 with an earlier NPRM for the 
specified products, which was published in the Federal Register on 
February 10, 2012 (77 FR 7007). That earlier NPRM proposed to require 
actions intended to address the unsafe condition for the products 
listed above.
    Since that NPRM (77 FR 7007, February 10, 2012) was issued, we have 
determined that repetitive inspections of the bogie pivot pin are 
necessary to address the identified unsafe condition, and we have 
expanded the applicability to include all Airbus Model A330-200, A330-
200 Freighter, A330-300, A340-200, and A340-300 series airplanes; and 
Model A340-541 and Model A340-642 airplanes.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2012-0053, dated March 30, 2012 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The 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.

[[Page 55164]]

    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 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.

Relevant Service Information

    Airbus has issued the following service bulletins:
     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).
     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).
     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).
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

Comments

    We gave the public the opportunity to comment on the original NPRM 
(77 FR 7007, February 10, 2012). We received no comments on that NPRM 
or on the determination of the cost to the public.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.
    Certain changes described above expand the scope of the earlier 
NPRM (77 FR 7007, February 10, 2012). As a result, we have determined 
that it is necessary to reopen the comment period to provide additional 
opportunity for the public to comment on this proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 29 products of U.S. registry. We also estimate that 
it would take about 22 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on 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.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
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);
    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 proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Airbus: Docket No. FAA-2012-0111; Directorate Identifier 2011-NM-
089-AD.

(a) Comments Due Date

    We must receive comments by October 22, 2012.

(b) Affected ADs

    None.

[[Page 55165]]

(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 if any Pivot Pin Bush is 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 if Any Bogie Pivot Pin is 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 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 if Any Bogie Pivot Pin Is Found Corroded or the 
Base Metal Is Found Cracked During the Non-Destructive Test

    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 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) does not terminate the repetitive inspections in 
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 
[email protected]; at the applicable time specified in 
paragraph (l)(1) or (l)(2) of this AD. The report must include the 
inspection results and 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, 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:

[[Page 55166]]

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: [email protected]. 
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

    (1) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2012-0053, dated March 30, 2012, and the service 
information specified in paragraphs (o)(1)(i) through (o)(1)(iii) of 
this AD, for related information.
    (i) 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).
    (ii) 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).
    (iii) 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).
    (2) 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 [email protected]; 
Internet http://www.airbus.com. You may review copies of the 
referenced 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.

    Issued in Renton, Washington, on August 31, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-22063 Filed 9-6-12; 8:45 am]
BILLING CODE 4910-13-P