[Federal Register Volume 77, Number 39 (Tuesday, February 28, 2012)]
[Proposed Rules]
[Pages 11793-11796]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-4644]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0185; Directorate Identifier 2011-NM-001-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Airbus Model A300 B4-103, B4-203, and B4-2C airplanes, and 
Model B4-600, B4-600R, and F4-600R series airplanes, and Model C4-605R 
Variant F airplanes (collectively called A300-600 series airplanes). 
This proposed AD was prompted by reports of cracking in the forward lug 
of the main landing gear (MLG) rib 5 aft bearing attachment. This 
proposed AD would require repetitive inspections for cracking of the 
left-hand (LH) and right-hand (RH) wing MLG rib 5 aft bearing forward 
lugs and repair if necessary. We are proposing this AD to detect and 
correct cracking of the LH and RH wing MLG rib 5 aft bearing forward 
lugs which, if not corrected,

[[Page 11794]]

could affect the structural integrity of the MLG attachment, which 
could result in MLG collapse during landing or rollout with consequent 
damage to the airplane and injury to occupants.

DATES: We must receive comments on this proposed AD by April 13, 2012.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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.
    <bullet> 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--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; email: <a href="/cdn-cgi/l/email-protection#18797b7b776d766c3679716a6f776a6c70357d796b5879716a7a6d6b367b7775"><span class="__cf_email__" data-cfemail="4e2f2d2d213b203a602f273c39213c3a26632b2f3d0e2f273c2c3b3d602d2123">[email protected]</span></a>; 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: 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: 

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-2012-0185; 
Directorate Identifier 2011-NM-001-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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2010-0250, dated November 29, 2010 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    During routine visual inspection, a crack has been found in the 
wing MLG [main landing gear] rib 5 aft bearing forward lug on two 
A310 in-service aeroplanes. Laboratory examination of cracked ribs 
confirmed that the crack was due to the presence of pitting 
corrosion in the forward lug hole. Also on both aeroplanes medium to 
heavy corrosion was found in the forward lugs on the opposite wing 
after removal of the bushes. Similarly to A310 aeroplanes, A300 and 
A300-600 aeroplanes are concerned by this situation which, if not 
detected, could affect the structural integrity of the MLG 
attachment.
    The aim of the [EASA] Emergency Airworthiness Directive (EAD) 
2006-0372-E [which corresponds to FAA AD 2007-03-18, Amendment 39-
14929 (72 FR 5919, February 8, 2007)] was to mandate, for A300 and 
A300-600 aeroplanes, repetitive detailed visual inspections (DVI) of 
wing MLG rib 5 aft bearing forward lugs for detection of through 
cracks.
    Since then, in order to ensure the detection of any crack in the 
forward lug of the RH [right-hand] and LH [left-hand] MLG rib 5 aft 
bearing attachment at an early stage, Airbus has developed a new 
inspection by means of ultrasonic method. Due to the early crack 
detection possibility, this new means of inspection also enables 
extension of the inspection interval.
    For technical reasons, this new means of inspection is only 
applicable to A300B4, C4, and F4 and A300-600 aeroplane series (not 
to A300B2 aeroplane series).
    For these reasons, this new [EASA] AD * * * adds new inspection 
program requirements [a revised detailed inspection, optional 
ultrasonic inspections, and repair if necessary].

As an option, a modification which includes installing bushings with an 
increased interference fit in the aft bearing forward lugs terminates 
the repetitive inspections. You may obtain further information by 
examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued the following service bulletins:
    <bullet> Mandatory Service Bulletin A300-57-0249, Revision 02, 
dated June 18, 2010 (for Model A300-B4-103, B4-2C, and B4-203 
airplanes).
    <bullet> Mandatory Service Bulletin A300-57-0251, including 
Appendix 01, dated August 8, 2007 (for Model A300 B4-103, B4-203 and 
B4-2C airplanes).
    <bullet> Service Bulletin A300-57-6106, Revision 02, dated June 18, 
2010 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-622R, 
F4-605R, F4-622R, and C4-605R airplanes).
    <bullet> Mandatory Service Bulletin A300-57-6107, including 
Appendix 01, dated August 8, 2007 (for Model A300 B4-601, B4-603, B4-
605R, B4-620, B4-622, B4-622R, C4-605R, F4-605R, and F4-622R 
airplanes).

The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

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.

Differences Between This AD and the MCAI or Service Information

    Although the MCAI allows further flight after cracks are found 
during compliance with the required action, paragraph (i) of this AD 
requires that you repair the cracks before further flight.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 165 products of U.S. registry. We also estimate that 
it would take about 3 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor

[[Page 11795]]

rate is $85 per work-hour. Based on these figures, we estimate the cost 
of the proposed AD on U.S. operators to be $42,075, or $255 per 
product.
    In addition, we estimate that any necessary follow-on actions would 
take about 52 work-hours and require parts costing $4,590, for a cost 
of $9,010 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-2012-0185; Directorate Identifier 2011-NM-
001-AD.

(a) Comments Due Date

    We must receive comments by April 13, 2012.

(b) Affected ADs

    This AD affects AD 2007-03-18, Amendment 39-14929 (72 FR 5919, 
February 8, 2007).

(c) Applicability

    This AD applies to Airbus Model A300 B4-2C, B4-103, B4-203 
airplanes; Model B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, 
F4-605R and F4-622R airplanes; and Model A300 C4-605R Variant F 
airplanes; certificated in any category; all serial numbers except 
for airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of 
this AD.
    (1) Airplanes on which LH (left-hand) and RH (right-hand) wing 
main landing gear (MLG) rib 5 forward lugs have oversized 
interference fit bushings installed per drawing R57240221.
    (2) Model A300 B4-103, B4-203, and B4-2C airplanes on which 
Airbus Mandatory Service Bulletin A300-57-0249 has been done in 
service on the LH and RH wing.
    (3) Model A300-600 series airplanes on which Airbus Service 
Bulletin A300-57-6106 has been done in service on the LH and RH 
wing.

(d) Subject

    Air Transport Association (ATA) of America Code 57: Wings.

(e) Reason

    This AD was prompted by reports of cracking in the forward lug 
of the MLG rib 5 aft bearing attachment. We are issuing this AD to 
detect and correct cracking of the LH and RH wing MLG rib 5 aft 
bearing forward lugs which, if not corrected, could affect the 
structural integrity of the MLG attachment, which could result in 
MLG collapse during landing or rollout with consequent damage to the 
airplane and injury to occupants.

(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) Inspections

    Except as provided by paragraph (h) of this AD, before the 
accumulation of 12,000 total flight cycles since new, or within 
12,000 flight cycles since the most recent MLG rib 5 replacement, if 
applicable, or within 10 days after the effective date of this AD, 
whichever occurs latest, do a detailed inspection or an ultrasonic 
inspection for cracking of the LH and RH MLG rib 5 aft bearing 
forward lugs, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A300-57-0251, including Appendix 
01, dated August 8, 2007 (for Model A300 B4-103, B4-203, and B4-2C 
airplanes); or Airbus Mandatory Service Bulletin A300-57-6107, 
including Appendix 01, dated August 8, 2007 (for Model A300-600 
series airplanes). Repeat the applicable inspections thereafter at 
the applicable interval specified in paragraph (g)(1) or (g)(2) of 
this AD, until the modification specified in paragraph (j) of this 
AD is accomplished.
    (1) Repeat the detailed inspections at intervals not to exceed 
100 flight cycles.
    (2) Repeat the ultrasonic inspections at intervals not to exceed 
675 flight cycles.

(h) Exception

    For airplanes on which an inspection required by AD 2007-03-18, 
Amendment 39-14929 (72 FR 5919, February 8, 2007), has been done as 
of the effective date of this AD: Within 100 flight cycles after 
doing the most recent inspection required by AD 2007-03-18, or 
within 10 days after the effective date of this AD, whichever occurs 
later, do a detailed or ultrasonic inspection as specified in 
paragraph (g) of this AD. Repeat the applicable inspection 
thereafter at the times specified in paragraph (g) of this AD.

(i) Repair

    If any cracking is detected during any detailed or ultrasonic 
inspection of the LH and RH MLG rib 5 aft bearing forward lugs 
required by paragraph (g) of this AD, before further flight, repair 
using a method approved by either the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or the European 
Aviation Safety Agency (EASA) (or its delegated agent).

(j) Optional Terminating Modification

    Performing the applicable actions specified in paragraphs 
(j)(1), (j)(2), (j)(3) and (j)(4) of this AD, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-57-0249, Revision 02, dated June 18, 2010 (for Model A300 B4-
103, B4-203, and B4-2C airplanes); or Airbus Service Bulletin A300-
57-6106, Revision 02, dated June 18, 2010 (for Model A300-600 series 
airplanes); terminates the repetitive inspections required by this 
AD.
    (1) Perform a general visual inspection and dye penetrant flaw 
detection inspection for corrosion and damage of the bore and 
spotfaces of the lug.
    (2) Determine that the diameter of the bore of the lug 
(dimension Y) is within the tolerance specified in the 
Accomplishment Instructions of Airbus Mandatory Service

[[Page 11796]]

Bulletin A300-57-0249, Revision 02, dated June 18, 2010 (for Model 
A300 B4-103, B4-203, and B4-2C airplanes); or Airbus Service 
Bulletin A300-57-6106, Revision 02, dated June 18, 2010 (for Model 
A300-600 series airplanes).
    (3) If damage or corrosion is detected during any inspection 
specified in paragraph (j)(1) of this AD, or if dimension Y is 
outside the tolerance specified in the Accomplishment Instructions 
of Airbus Mandatory Service Bulletin A300-57-0249, Revision 02, 
dated June 18, 2010 (for Model A300 B4-103, B4-203, and B4-2C 
airplanes); or Airbus Service Bulletin A300-57-6106, Revision 02, 
dated June 18, 2010 (for Model A300-600 series airplanes); repair 
using a method approved by either the Manager, International Branch, 
ANM 116, Transport Airplane Directorate, FAA; or the European 
Aviation Safety Agency (EASA) (or its delegated agent).
    (4) Install bushings with an increased interference fit in the 
aft bearing forward lugs, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A300-57-0249, 
Revision 02, dated June 18, 2010 (for Model A300 B4-103, B4-203, and 
B4-2C airplanes); or Airbus Service Bulletin A300-57-6106, Revision 
02, dated June 18, 2010 (for Model A300-600 series airplanes).

(k) Terminating Action for AD 2007-03-18, Amendment 39-14929 (72 FR 
5919, February 8, 2007)

    Doing the inspection required by paragraph (g) of this AD 
terminates the requirements of AD 2007-03-18, Amendment 39-14929 (72 
FR 5919, February 8, 2007), for that airplane.

(l) Reporting

    Submit a report (including both positive and negative findings), 
using the applicable report sheet attached to Airbus Mandatory 
Service Bulletin A300-57-0251, including Appendix 01, dated August 
8, 2007 (for Model A300 B4-103, B4-203, and B4-2C airplanes); or 
Airbus Mandatory Service Bulletin A300-57-6107, including Appendix 
01, August 8, 2007 (for Model A300-600 series airplanes); of the 
first inspection required by paragraph (g) of this AD. Submit the 
report to Airbus, Customer Services Directorate, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex France, Attn: SEDCC1 Technical 
Data and Documentation Services; fax: (+33) 5 61 93 28 06; email: 
<a href="/cdn-cgi/l/email-protection#7d0e1f530f180d120f0914131a3d1c140f1f080e531e1210"><span class="__cf_email__" data-cfemail="8ffceda1fdeaffe0fdfbe6e1e8cfeee6fdedfafca1ece0e2">[email protected]</span></a>; at the applicable time specified in 
paragraph (l)(1) or (l)(2) of this AD.
    (1) If the inspection was done on or 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.

(m) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using the applicable service bulletins 
specified in paragraphs (m)(1), (m)(2), (m)(3), and (m)(4) of this 
AD.
    (1) Airbus Service Bulletin A300-57-0249, dated May 22, 2007 
(for Model A300 B4-2C, B4-103, and B4-203 airplanes).
    (2) Airbus Service Bulletin A300-57-0249, Revision 01, dated 
December 19, 2007 (for Model A300 B4-2C, B4-103, and B4-203 
airplanes).
    (3) Airbus Service Bulletin A300-57-6106, dated May 22, 2007 
(Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-622R, F4-
605R, F4-622R, and Model A300 C4-605R Variant F airplanes).
    (4) Airbus Service Bulletin A300-57-6106, Revision 01, dated 
January 28, 2008 (Model A300 B4-601, B4-603, B4-605R, B4-620, B4-
622, B4-622R, F4-605R, F4-622R, and Model A300 C4-605R Variant F 
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: 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 emailed to: <a href="/cdn-cgi/l/email-protection#2910046867640418181f046864666a047b6c787c6c7a7d7a694f4848074e465f"><span class="__cf_email__" data-cfemail="ffc6d2beb1b2d2cecec9d2beb2b0bcd2adbaaeaabaacabacbf999e9ed1989089">[email protected]</span></a>. 
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 EASA Airworthiness Directive 2010-0250, dated 
November 29, 2010, and the service information in paragraphs (o)(1), 
(o)(2), (o)(3), and (o)(4) of this AD, for related information.
    (1) Airbus Mandatory Service Bulletin A300-57-0249, Revision 02, 
dated June 18, 2010.
    (2) Airbus Mandatory Service Bulletin A300-57-0251, including 
Appendix 01, dated August 8, 2007.
    (3) Airbus Service Bulletin A300-57-6106, Revision 02, dated 
June 18, 2010.
    (4) Airbus Mandatory Service Bulletin A300-57-6107, including 
Appendix 01, August 8, 2007.

    Issued in Renton, Washington, on February 13, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-4644 Filed 2-27-12; 8:45 am]
BILLING CODE 4910-13-P


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