AD 2012-07-02

[Federal Register Volume 77, Number 66 (Thursday, April 5, 2012)]
[Rules and Regulations]
[Pages 20515-20517]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2012-7848]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0331; Directorate Identifier 2011-NM-119-AD; 
Amendment 39-17008; AD 2012-07-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A340-500 and -600 series airplanes. This AD requires 
repetitive inspections of the forward and aft attachment fittings and 
of the swan neck for cracks, and replacing the attachment fittings and 
the swan neck with serviceable ones if necessary. This AD was prompted 
by reports of cracks on the forward attachment fittings of the left and 
right sides of the forward hinge of the nose landing gear (NLG) aft 
door. We are issuing this AD to detect and correct cracks of the 
forward attachment fittings and the swan neck, which could lead to the 
in-flight detachment of the NLG aft door and result in injury to 
persons on the ground or damage to the airplane.

DATES: This AD becomes effective April 20, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of the service information listed in the AD as of April 20, 
2012.
    We must receive comments on this AD by May 21, 2012.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. 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,

[[Page 20516]]

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.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a>; 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 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:

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 2011-0088, dated May 13, 2011 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    An operator has reported cracks on the aft hinge forward (FWD) 
fittings (hinge <greek-i>5) of the NLG aft doors (Right Hand (RH) 
side or Left Hand (LH) side). The cracks extended by approximately 
15 millimetres from the upper hole to the edge of the fittings.
    Investigation has revealed that these cracks have initiated due 
to fatigue loads and propagated under bending load.
    Cracks on the NLG aft door fittings, if not corrected, could 
lead to the inflight detachment of the door, possibly resulting in 
injury to persons on the ground or damage to the aeroplane.
    In order to maintain the structural integrity of the NLG aft 
door aft hinge attachment fittings, EASA issued EASA AD 2010-0028 
[which corresponds to FAA AD 2011-08-03, Amendment 39-16653 (71 FR 
20496, April 13, 2011)], which requires repetitive inspections at 
hinge <greek-i>5.
    Additional investigations have shown that inspections are also 
necessary for the hinge <greek-i>4.
    For the reasons described above, this [EASA] AD requires 
repetitive [detailed] inspections of the FWD and AFT attachment 
fittings and [high frequency eddy current inspections] of the swan 
neck at the forward hinge <greek-i>4 and their replacement, as 
necessary.

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

Relevant Service Information

    Airbus has issued Mandatory Service Bulletin A340-52-5017, 
including Appendices 1 and 2, dated February 17, 2011. 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 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 issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.
    There are no products of this type currently registered in the 
United States. However, this rule is necessary to ensure that the 
described unsafe condition is addressed if any of these products are 
placed on the U.S. Register in the future.

Differences Between the AD and the MCAI or Service Information

    Although the MCAI or service information allows further flight 
after cracks are found, paragraph (g) of this AD requires that you 
replace both the forward and aft fittings before further flight if any 
crack is found.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this product, 
notice and opportunity for public comment before issuing this AD are 
unnecessary.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2012-0331; Directorate 
Identifier 2011-NM-119-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to <a href="http://www.regulations.gov">http://www.regulations.gov</a>, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

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.

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,

[[Page 20517]]

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:

2012-07-02 Airbus: Amendment 39-17008. Docket No. FAA-2012-0331; 
Directorate Identifier 2011-NM-119-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective April 20, 
2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A340-541 and -642 airplanes, 
certificated in any category, all manufacturer serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 52: Doors.

(e) Reason

    This AD was prompted by reports of cracks on the forward 
attachment fittings of the left and right sides of the forward hinge 
of the nose landing gear (NLG) aft door. We are issuing this AD to 
detect and correct cracks of the forward attachment fittings and the 
swan neck, which could lead to the in-flight detachment of the NLG 
aft door and result in injury to persons on the ground or damage to 
the airplane.

(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) Repetitive Inspections and Corrective Action of the Forward and Aft 
Attachment Fittings of the Forward Hinge (<greek-i>4) of the NLG Aft 
Door

    Before the accumulation of 4,500 total flight cycles or within 
50 flight cycles after the effective date of this AD, whichever 
occurs later: Do a detailed visual inspection for any cracking of 
the forward attachment fittings of the forward hinge (<greek-i>4) of 
the NLG aft door of the left side and right side doors, in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A340-52-5017, excluding Appendices 1 and 2, dated 
February 17, 2011.
    (1) If no crack is found: Thereafter repeat the inspection 
required in paragraph (g) of this AD at intervals not to exceed 500 
flight cycles.
    (2) If any crack is found during any inspection required in 
paragraph (g) of this AD: Before further flight, replace both the 
forward and aft fittings with serviceable fittings on the forward 
hinge (<greek-i>4) of the affected NLG aft door, in accordance with 
the Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A340-52-5017, excluding Appendices 1 and 2, dated February 17, 2011.

(h) Action Requirement for Part Replacement of the Forward and Aft 
Attachment Fittings of the Forward Hinge (<greek-i>4) of the NLG Aft 
Door

    If any forward and aft attachment fittings of the forward hinge 
(<greek-i>4) of the NLG aft door have been replaced as required in 
paragraph (g)(2) of this AD: Before the accumulation of 4,500 flight 
cycles on the forward fitting, do the inspection required in 
paragraph (g) of this AD.

(i) Repetitive Inspections and Corrective Actions of the Swan Neck of 
the Forward Hinge (<greek-i>4) of the NLG Aft Door

    Before the accumulation of 4,500 total flight cycles or within 
50 flight cycles after the effective date of this AD, whichever 
occurs later: Perform a high frequency eddy current inspection for 
any cracking of the swan neck of the forward hinge (<greek-i>4) of 
the NLG aft door of the left side and right side doors, in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A340-52-5017, excluding Appendices 1 and 2, dated 
February 17, 2011.
    (1) If no crack is found: Thereafter repeat the inspection 
required in paragraph (i) of this AD at intervals not to exceed 500 
flight cycles.
    (2) If any crack is found during any inspection required in 
paragraphs (i) of this AD: Before further flight, replace the swan 
neck with a serviceable swan neck on the forward hinge (<greek-i>4) 
of the affected NLG aft door, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A340-52-5017, 
excluding Appendices 1 and 2, dated February 17, 2011.

(j) Action Requirement for Part Replacement of the Swan Neck of the 
Forward Hinge (<greek-i>4) of the NLG Aft Door

    If any swan neck of the NLG aft door forward hinge (<greek-i>4) 
is replaced as specified in paragraph (i)(2) of this AD: Before the 
accumulation of 4,500 flight cycles on the swan neck, repeat the 
inspection required in paragraph (i) of this AD.

 (k) 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: 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: <a href="/cdn-cgi/l/email-protection#0d34204c4340203c3c3b204c40424e205f485c58485e595e4d6b6c6c236a627b"><span class="__cf_email__" data-cfemail="3801157976751509090e157975777b156a7d696d7d6b6c6b785e5959165f574e">[email&#160;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) Special Flight Permits: Special flight permits, as described 
in Section 21.197 and Section 21.199 of the Federal Aviation 
Regulations (14 CFR 21.197 and 21.199), are not allowed.

(l) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
European Aviation Safety Agency Airworthiness Directive 2011-0088, 
dated May 13, 2011; and Airbus Mandatory Service Bulletin A340-52-
5017, excluding Appendices 1 and 2, dated February 17, 2011; for 
related information.

(m) Material Incorporated by Reference

    (1) You must use the following service information to do the 
actions required by this AD, unless the AD specifies otherwise. The 
Director of the Federal Register approved the incorporation by 
reference (IBR) of the following service information under 5 U.S.C. 
552(a) and 1 CFR part 51:
    (2) Airbus Mandatory Service Bulletin A340-52-5017, excluding 
Appendices 1 and 2, dated February 17, 2011.
    (3) For Airbus 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 <a href="/cdn-cgi/l/email-protection#2948405b5e465b5d4140474c5a5a07681a1a1904681a1d196948405b4b5c5a074a4644"><span class="__cf_email__" data-cfemail="d5b4bca7a2baa7a1bdbcbbb0a6a6fb94e6e6e5f894e6e1e595b4bca7b7a0a6fbb6bab8">[email&#160;protected]</span></a>; 
Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (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.
    (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 an NARA facility, call 202-741-6030, or go to <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.

    Issued in Renton, Washington, on March 23, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-7848 Filed 4-4-12; 8:45 am]
BILLING CODE 4910-13-P