AD 2014-09-05

[Federal Register Volume 79, Number 82 (Tuesday, April 29, 2014)]
[Rules and Regulations]
[Pages 23909-23912]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2014-09412]



[[Page 23909]]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0255; Directorate Identifier 2014-NM-056-AD; 
Amendment 39-17840; AD 2014-09-05]
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 certain 
Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and 
-300 series airplanes. This AD requires repetitive inspections of 
certain sidestay upper cardan pins of the main landing gear (MLG), and 
associated nuts and retainer assemblies, and pin replacement if 
necessary. This AD also provides for an optional measurement of the 
cardan pin clearance dimensions (gap check) and corrective actions if 
necessary, which would terminate the repetitive inspections. This AD 
was prompted by a report of a sidestay upper cardan pin of the MLG 
migrating out of position. We are issuing this AD to detect and correct 
migration of the sidestay upper cardan pin, which could result in 
disconnection of the sidestay upper arm from the airplane structure, 
and could result in a landing gear collapse and consequent damage to 
the airplane and injury to occupants.

DATES: This AD becomes effective May 14, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 14, 
2014.
    We must receive comments on this AD by June 13, 2014.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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, 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 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#c2a3abb0b5adb0b6aaabaca7b1b1ec83f1f1f2ef83f1f6f282a3abb0a0b7b1eca1adaf"><span class="__cf_email__" data-cfemail="24454d56534b56504c4d4a4157570a65171714096517101464454d564651570a474b49">[email&#160;protected]</span></a>; Internet <a href="http://www.airbus.com">http://www.airbus.com</a>. You may view this referenced 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.

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> by searching for and locating Docket No. FAA-2014-
0255; 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, WA 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 2014-0066, (correction) dated March 20, 2014 
(referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), to correct an unsafe condition for 
certain Airbus Model A330-200 and -300 series airplanes, and Model 
A340-200 and -300 series airplanes. The MCAI states:

    An A330 aeroplane equipped with Basic (main landing gear) MLG 
was rolling out after landing when it experienced a nose wheel 
steering fault (unrelated to the safety subject addressed by this 
[EASA] AD), which resulted in the crew stopping the aeroplane on the 
taxiway after vacating the runway.
    The subsequent investigation revealed that the right-hand MLG 
sidestay upper cardan pin had migrated out of position. The sidestay 
upper cardan nut and retainer were found in the landing gear bay 
detached from the upper cardan pin. The nut and the retainer were 
still bolted together.
    This condition, if not detected and corrected, could lead to a 
complete migration of the sidestay upper cardan pin and a 
disconnection of the sidestay upper arm from the aeroplane 
structure, possibly resulting in MLG collapse with consequent damage 
to the aeroplane and injury to occupants.
    To address this potential condition, Airbus published Alert 
Operators Transmission (AOT) A32L003-14, providing inspection 
instructions.
    For the reasons described above, this [EASA] AD requires 
accomplishment of repetitive [detailed inspections for visible 
chrome] of the MLG upper cardan pin, nut and retainer [and pin 
replacement if necessary. This [EASA] AD also requires 
accomplishment of a gap check between wing rear spar fitting lugs 
and the bush flanges [and corrective actions if necessary. 
Corrective actions include repair or replacement of the cardan pin 
assembly].

    You may examine the MCAI on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2014-
0255.

Relevant Service Information

    Airbus has issued Airbus Alert Operators Transmission (AOT) 
A32L003-14, dated March 10, 2014, including Appendices 1, 2, and 3 (the 
issue date is not specified on the appendices). The actions described 
in this service information are intended to correct the unsafe 
condition identified in the MCAI.

Differences Between This AD and the MCAI

    Mandatory Continuing Airworthiness Information (MCAI) European 
Aviation Safety Agency Airworthiness Directive 2014-0066, (correction) 
dated March 20, 2014, specifies that accomplishment of the gap check 
and corrective actions constitute terminating action for the AD. We 
consider the replacement of the cardan pin assembly as specified in 
paragraph (g)(3) to be terminating action for the repetitive 
inspections required by this AD.

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

[[Page 23910]]

develop on other products of these same type designs.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
migration of the sidestay upper cardan pin and disconnection of the 
sidestay upper arm from the airplane structure, could result in a 
landing gear collapse and consequent damage to the airplane and injury 
to occupants. Therefore, we determined that notice and opportunity for 
public comment before issuing this AD are impracticable and that good 
cause exists for making this amendment effective in fewer than 30 days.

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-2014-0255; Directorate 
Identifier 2014-NM-056-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 based on 
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.

Interim Action

    This AD is considered to be interim action. We are currently 
considering requiring a measurement of the cardan pin clearance 
dimensions (gap check) to determine that no gap exists between wing 
rear spar fitting lugs and the associated bush flanges of the left-hand 
and right-hand main landing gear (MLG), and applicable corrective 
actions, which will constitute terminating action for the repetitive 
inspections required by this AD action. However, the planned compliance 
time for the measurement would allow enough time to provide notice and 
opportunity for prior public comment on the merits of the measurement 
and applicable corrective actions.

Costs of Compliance

    We estimate that this AD affects 83 airplanes of U.S. registry.
    We also estimate that it will take about 1 work-hour 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 on U.S. operators to be $7,055, or $85 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 4 work-hours and require parts costing $7,530, for a cost of 
$7,870 per product. We have no way of determining the number of 
aircraft that might need these actions.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to 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 control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. 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.

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.

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 airworthiness 
directive (AD):

2014-09-05 Airbus: Amendment 39-17840. Docket No. FAA-2014-0255; 
Directorate Identifier 2014-NM-056-AD.

(a) Effective Date

    This AD becomes effective May 14, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category.
    (1) Airbus Model A330-201, A330-202, A330-203, A330-223, A330-
243, A330-301, A330-302, A330-303, A330-321, A330-322, A330-323, 
A330-341, A330-342, and A330-343 airplanes, all manufacturer serial 
numbers (MSNs), equipped with basic (201252 series) main landing 
gear (MLG), or growth (201490 series) MLG.
    (2) Airbus Model A340-211, A340-212, A340-213, A340-311, A340-
312, and A340-

[[Page 23911]]

313 airplanes, all MSNs, equipped with basic (201252 series) MLG or 
growth (201490 series) MLG.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of a sidestay upper cardan pin 
of the MLG migrating out of position. We are issuing this AD to 
detect and correct migration of the sidestay upper cardan pin, which 
could result in disconnection of the sidestay upper arm from the 
airplane structure, and which could result in a landing gear 
collapse and consequent damage to the airplane and injury to 
occupants.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Repetitive Detailed Inspections

    (1) For airplanes identified in paragraphs (g)(1)(i) and 
(g)(1)(ii) of this AD on which the affected MLG has exceeded 8 years 
since first overhaul, as of the effective date of this AD, except 
those MLG that have had a second overhaul: Within 30 days after the 
effective date of this AD, accomplish a detailed inspection for 
visible chrome of each affected MLG sidestay upper cardan pin, and 
associated nut and retainer assembly, in accordance with the 
instructions of Airbus Alert Operators Transmission (AOT) A32L003-
14, dated March 10, 2014, including Appendices 1, 2, and 3 (the 
issue date is not specified on the appendices).
    (i) Airplanes equipped with any MLG sidestay upper cardan pin 
subassembly part number (P/N) 201267202 (on 201252 series MLG).
    (ii) Airplanes equipped with any MLG sidestay upper cardan pin 
subassembly P/N 201483202 (on 201490 series MLG).
    (2) If, during any inspection required by paragraph (g)(1) of 
this AD, no pin chrome is visible inboard of the wing rear spar 
fitting lug, repeat the detailed inspection for visible chrome 
specified in paragraph (g)(1) of this AD, thereafter at intervals 
not to exceed 10 days.
    (3) If, during any inspection required by paragraphs (g)(1) or 
(g)(2) of this AD, pin chrome is visible inboard of the wing rear 
spar fitting lug, before further flight, replace the affected cardan 
pin assembly, in accordance with the instructions of Airbus AOT 
A32L003-14, dated March 10, 2014, including Appendices 1, 2, and 3 
(the issue date is not specified on the appendices). Replacement of 
the affected cardan pin assembly terminates the need for repetitive 
inspections required by paragraph (g)(2) of this AD.

    Note 1 to paragraph (g) of this AD:  MLG sidestay upper cardan 
pin subassembly P/N 201267202 (found in Airbus Illustrated Parts 
Catalogue (IPC) as item 32-11-18-01) includes the cardan pin P/N 
201267600. MLG sidestay upper cardan pin subassembly P/N 201483202 
(found in Airbus IPC as item 32-11-18-01) includes the cardan pin P/
N 201483600.

(h) Optional Terminating Action--Gap Check

    Measuring the cardan pin clearance dimensions (gap check) and 
doing the applicable corrective action specified in paragraph (h)(1) 
or (h)(2) of this AD terminates the repetitive inspections required 
by paragraphs (g)(1) and (g)(2) of this AD for that sidestay upper 
cardan pin, nut, and retainer only. The measurement must be done in 
accordance with the instructions of Airbus AOT A32L003-14, dated 
March 10, 2014, including Appendices 1, 2, and 3 (the issue date is 
not specified on the appendices).
    (1) If the total clearance dimension (gap check result) is equal 
to or greater than 1.5 mm, replace the cardan pin assembly, in 
accordance with Airbus AOT A32L003-14, dated March 10, 2014, 
including Appendices 1, 2, and 3 (the issue date is not specified on 
the appendices).
    (2) If the total clearance dimension (gap check) is less than 
1.5 mm but greater than 0.6 mm, do the actions specified in 
paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
    (i) Send the information (Appendix 2 proforma, photographs, and 
the movement traceability sheet) specified in paragraph 4.2.3, 
``Findings'' of Airbus AOT A32L003-14, dated March 10, 2014, 
including Appendices 1, 2, and 3, to Airbus at the address specified 
in Appendix 2 of Airbus AOT A32L003-14, dated March 10, 2014.
    (ii) Repair using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or European Aviation Safety Agency (EASA) (or its delegated agent, 
or the Design Approval Holder with EASA's design organization 
approval, as applicable).

(i) 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, 
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information 
may be emailed to: <a href="/cdn-cgi/l/email-protection#1c25315d5251312d2d2a315d51535f314e594d49594f484f5c7a7d7d327b736a"><span class="__cf_email__" data-cfemail="dce5f19d9291f1ededeaf19d91939ff18e998d89998f888f9cbabdbdf2bbb3aa">[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, use these actions if they 
are FAA-approved. Corrective actions are considered FAA-approved if 
they were approved by the State of Design Authority (or its 
delegated agent, or the DAH with a State of Design Authority's 
design organization approval, as applicable). You are required to 
ensure 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.

(j) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
European Aviation Safety Agency Airworthiness Directive 2014-0066, 
(correction) dated March 20, 2014, for related information. You may 
examine the MCAI on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by 
searching for and locating Docket No. FAA-2014-0255.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register 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 this AD specifies otherwise.
    (i) Airbus Alert Operators Transmission (AOT) A32L003-14, dated 
March 10, 2014, including Appendices 1, 2, and 3 (the issue date is 
not specified on the appendices).
    (ii) Reserved.
    (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 <a href="/cdn-cgi/l/email-protection#ff9e968d88908d8b9796919a8c8cd1becccccfd2becccbcfbf9e968d9d8a8cd19c9092"><span class="__cf_email__" data-cfemail="f1909883869e838599989f948282dfb0c2c2c1dcb0c2c5c1b1909883938482df929e9c">[email&#160;protected]</span></a>; 
Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (4) You may view this 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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.


[[Page 23912]]


    Issued in Renton, Washington, on April 16, 2014.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-09412 Filed 4-28-14; 8:45 am]
BILLING CODE 4910-13-P