[Federal Register Volume 79, Number 125 (Monday, June 30, 2014)]
[Proposed Rules]
[Pages 36666-36669]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-15254]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / 
Proposed Rules  

[[Page 36666]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0425; Directorate Identifier 2013-NM-180-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-06-
19, for certain Airbus Model A330-201, -202, -203, -223, -243, -301, -
302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and Model 
A340-200 and -300 series airplanes. AD 2012-06-19 currently requires 
repetitive inspections of the main fitting and sliding tube of the nose 
landing gear (NLG) for defects, damage, and cracks; and corrective 
actions if necessary. Since we issued AD 2012-06-19, we have determined 
that additional airplanes are affected by the identified unsafe 
condition. This proposed AD would add airplanes to the applicability. 
This proposed AD would require an inspection of the part number and 
serial number of the NLG main fitting and NLG sliding tube; for 
affected parts, a magnetic particle inspection (MPI) for cracks, and 
flap peening and replacement if necessary. This proposed AD would also 
require, for certain parts, additional inspections for damage and 
cracking. We are proposing this AD to detect and correct cracks, 
defects, or damage of the main fitting or sliding tube, which could 
result in consequent NLG collapse.

DATES: We must receive comments on this proposed AD by August 14, 2014.

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 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0425; 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, WA 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-2014-0425; 
Directorate Identifier 2013-NM-180-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

    On March 15, 2012, we issued AD 2012-06-19, Amendment 39-17000 (77 
FR 22188, April 13, 2012). AD 2012-06-19 requires actions intended to 
address an unsafe condition on certain Airbus Model A330-201, -202, -
203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -
343 airplanes; and Model A340-200 and -300 series airplanes.
    Since we issued AD 2012-06-19, Amendment 39-17000 (77 FR 22188, 
April 13, 2012), we have determined that additional airplanes are 
affected by the identified unsafe condition.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2013-0179, dated August 7, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -
341, -342, and -343 airplanes; and Model A340-200 and -300 series 
airplanes. The MCAI states:

    During the overhaul of two different Nose Landing Gear (NLG) 
units, cracks were found on the main fitting of one and the sliding 
tube of the other. Investigations concluded that the cracks 
initiated as a result of residual stress in the parts, following 
damage due to impact during towing incidents.
    A subsequent review of the reported incidents identified a 
specific group of NLG main fittings and sliding tubes that may have 
sustained impact damage as a result of towing incidents.
    This condition, if not detected and corrected could lead to NLG 
collapse.

[[Page 36667]]

    To address this potential unsafe condition, EASA issued AD 2010-
0034 [(http://ad.easa.europa.eu/blob/easa_ad_2010_0034_Corrected_superseded.pdf/AD_2010-0034_1) [which corresponds to 
FAA AD 2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012)] 
to require accomplishment of a one-time Magnetic Particles 
Inspection (MPI), followed by repetitive Detailed Visual Inspections 
(DVI) of the main fittings and sliding tubes of the affected NLG 
units identified by Part Number (P/N) and Serial Number (S/N) in the 
Applicability section of that AD and, depending on findings, 
accomplishment of applicable corrective actions.
    Since that [EASA] AD was issued, it has been found necessary to 
address the issue at the level of NLG detail parts and no longer at 
NLG assembly level, as some detail parts have been transferred from 
an aeroplane to another. Airbus revised the applicable Service 
Bulletins (SB), which now list the affected NLG main fittings and 
sliding tubes.
    For the reasons described above, this [EASA] AD retains 
[certain] requirements of EASA AD 2010-0034 which is superseded and 
requires [an inspection of the part number and serial number of the 
NLG main fitting and NLG sliding tube, and for affected parts,] a 
one-time MPI [for cracks], followed by repetitive DVI [for cracking, 
damage to paint, sealant, cadmium, and base metal] of the affected 
NLG main fittings and sliding tubes and, depending on inspection 
results, accomplishment of corrective actions [e.g., flap peening 
and replacing cracked parts]. This AD also extends the applicability 
to A330 freighters.

You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0425.

Relevant Service Information

    Airbus has issued Service Bulletin A330-32-3233, Revision 02, dated 
January 27, 2014; and Service Bulletin A340-32-4275, Revision 01, dated 
July 5, 2013. 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.

Costs of Compliance

    We estimate that this proposed AD affects 92 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:
    The actions that are required by AD 2012-06-19, Amendment 39-17000 
(77 FR 22188, April 13, 2012), and retained in this proposed AD take 
about 4 work-hours per product, at an average labor rate of $85 per 
work-hour. Required parts cost about $0 per product. Based on these 
figures, the estimated cost of the actions that are required by AD 
2012-06-19 is $31,280 per product.
    We also estimate that it would take about 10 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about $0 per 
product. Based on these figures, we estimate the cost of this proposed 
AD on U.S. operators to be $78,200, or $850 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 114 work-hours and require parts costing $435,000, for a 
cost of $444,690 per product. We have no way of determining the number 
of aircraft that might 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 proposed 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.

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

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 removing Airworthiness Directive (AD) 
2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012), and 
adding the following new AD:

Airbus: Docket No. FAA-2014-0425; Directorate Identifier 2013-NM-
180-AD.

(a) Comments Due Date

    We must receive comments by August 14, 2014.

(b) Affected ADs

    This AD supersedes AD 2012-06-19, Amendment 39-17000 (77 FR 
22188, April 13, 2012).

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
223F -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes; and Model A340-211, -212, -213, -311, -312, and 
-313 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 a cracked nose landing gear 
(NLG) main fitting and sliding tube during overhaul of the NLGs 
following damage due to impact during towing incidents. We are 
issuing this AD to detect and correct cracks, defects, or damage of 
the main fitting or sliding tube, which could result in consequent 
NLG collapse.

[[Page 36668]]

(f) Compliance

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

(g) Retained Detailed Inspection and Corrective Actions

    This paragraph restates the requirements of paragraph (g) of AD 
2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012) with 
revised service information. For Model A330-201, -202, -203, -223, -
243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 
airplanes; and Model A340-211, -212, -213, -311, -312, and -313 
airplanes; if fitted with the NLG identified in table 1 to paragraph 
(g) of this AD: Within 900 flight hours after April 30, 2012 (the 
effective date of AD 2012-06-19), do a detailed inspection of the 
NLG main fitting and sliding tube for any cracks, defects, and 
damage of the paint or surface protection, including paint removal 
and cracking of the surface treatment. Before further flight after 
doing the detailed inspection of the NLG, remove the labels, paint, 
surface protection coatings, and cadmium from the NLG main fitting; 
do a detailed inspection for any damage to the surface that will 
impair the magnetic particle inspection (MPI); and, if any defects 
are found, before further flight, remove any defects by polishing. 
Do all actions specified in paragraph (g) of this AD in accordance 
with the Accomplishment Instructions of the applicable service 
information specified in paragraph (g)(1) or (g)(2) of this AD.
    (1) For Model A330 airplanes: Airbus Mandatory Service Bulletin 
A330-32-3233, dated October 22, 2009; or Airbus Service Bulletin 
A330-32-3233, Revision 02, dated January 27, 2014.
    (2) For Model A340 airplanes: Airbus Mandatory Service Bulletin 
A340-32-4275, dated October 22, 2009; or Airbus Service Bulletin 
A340-32-4275, Revision 01, dated July 5, 2013.

 Table 1 to Paragraph (g) of This AD--Applicable NLG and Serial Numbers
------------------------------------------------------------------------
                  Part No.                            Serial No.
------------------------------------------------------------------------
D23285200..................................  B2
D23285101-7................................  B58
D23285101-10...............................  B75
D23581100-1................................  B124
D23581100-1................................  B159
D23581100-7................................  B386
D23581100-7................................  B398
D23581100-7................................  B400
D23581100-7................................  B403
------------------------------------------------------------------------

(h) Retained Magnetic Particle Inspection

    This paragraph restates the requirements of paragraph (h) of AD 
2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012), with 
revised service information. Before further flight after doing the 
actions required in paragraph (g) of this AD: Do an MPI for cracking 
of the NLG main fitting and sliding tube, in accordance with the 
Accomplishment Instructions of the applicable service information 
specified in paragraph (g)(1) or (g)(2) of this AD.
    (1) If no crack is detected during the MPI required by paragraph 
(h) of this AD: Before further flight, flap peen the inspected area 
where the paint and cadmium has been removed, and replace the 
protective coatings, in accordance with the Accomplishment 
Instructions of the applicable service information specified in 
paragraph (g)(1) or (g)(2) of this AD.
    (2) If any crack is detected during the MPI required by 
paragraph (h) of this AD: Before further flight, replace the damaged 
part with a new or serviceable part, in accordance with the 
Accomplishment Instructions of the applicable service information 
specified in paragraph (g)(1) or (g)(2) of this AD.

(i) New Requirement of This AD: Identification

    Within 1,000 flight hours after the effective date of this AD, 
identify the part number and serial number of the NLG main fitting 
and NLG sliding tube, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, 
dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, 
Revision 01, dated July 5, 2013; as applicable. A review of airplane 
maintenance records is acceptable in lieu of this identification if 
the part number and the serial number of the NLG main fitting and 
NLG sliding tube can be conclusively determined from that review.

(j) New Requirement of This AD: MPI

    If, during the identification required by paragraph (i) of this 
AD, it is determined any NLG main fitting or NLG sliding tube is 
installed and the fitting or tube has a part number and serial 
number listed in Airbus Service Bulletin A330-32-3233, Revision 02, 
dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, 
Revision 01, dated July 5, 2013; as applicable: Within 1,000 flight 
hours after the effective date of this AD, do an MPI for cracks of 
the affected parts, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, 
dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, 
Revision 01, dated July 5, 2013; as applicable. Accomplishing the 
MPI required by this paragraph terminates the inspections required 
by paragraphs (g) and (h) of this AD.
    (1) If any crack is detected during the MPI required by 
paragraph (j) of this AD, before further flight, replace any cracked 
part (NLG main fitting and NLG sliding tube) with a serviceable one, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-32-3233, Revision 02, dated January 27, 2014; or 
Airbus Service Bulletin A340-32-4275, Revision 01, dated July 5, 
2013; as applicable.
    (2) If no crack is detected during the MPI required by paragraph 
(j) of this AD, before further flight, do a flap peening to 
introduce compressive residual stress and corrosion protection, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-32-3233, Revision 02, dated January 27, 2014; or 
Airbus Service Bulletin A340-32-4275, Revision 01, dated July 5, 
2013; as applicable.

(k) New Requirement of This AD: Detailed Inspection

    Within 900 flight hours after doing the flap peening required by 
paragraph (j)(2) of this AD, do a detailed inspection for damage to 
paint, damage to the sealant around the labels, damage to the 
cadmium or base metal, and for cracking of the affected parts; in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-32-3233, Revision 02, dated January 27, 2014; or 
Airbus Service Bulletin A340-32-4275, Revision 01, dated July 5, 
2013; as applicable. Repeat the inspection thereafter at intervals 
not to exceed 900 flight hours.
    (1) If damage to the paint, damage to the sealant around the 
labels, or damage to the cadmium or base metal, is detected during 
any detailed inspection required by paragraph (k) of this AD, before 
further flight, do an MPI for cracking of the affected parts, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-32-3233, Revision 02, dated January 27, 2014; or 
Airbus Service Bulletin A340-32-4275, Revision 01, dated July 5, 
2013; as applicable.
    (2) If any cracking is detected during any inspection required 
by paragraph (k) or (k)(1) of this AD, before further flight, 
replace any cracked part with a serviceable part, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A330-32-
3233, Revision 02, dated January 27, 2014; or Airbus Service 
Bulletin A340-32-4275, Revision 01, dated July 5, 2013; as 
applicable.

(l) Terminating Action

    Replacement of a part as required by paragraph (j)(1) or (k)(2) 
of this AD is terminating action for the repetitive detailed 
inspections required by paragraph (k) of this AD for that part, 
provided that the part number and serial number of the replacement 
part is not listed in Airbus Service Bulletin A330-32-3233, Revision 
02, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, 
Revision 01, dated July 5, 2013; as applicable.

(m) Parts Installation Limitation

    As of the effective date of this AD, installation of an NLG main 
fitting or NLG sliding tube having a part number and serial number 
listed in Airbus Service Bulletin A330-32-3233, Revision 02, dated 
January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 
01, dated July 5, 2013; as applicable; is allowed, provided that the 
NLG main fitting and NLG sliding tube has not accumulated more than 
900 flight hours since the most recent inspection accomplished in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-32-3233, Revision 02, dated January 27, 2014; or 
Airbus Service Bulletin A340-32-4275, Revision 01, dated July 5, 
2013; as applicable.

(n) Credit for Previous Actions

    This paragraph provides credit for inspections required by 
paragraphs (j) and (k) of this AD and the flap peening required by 
paragraph (j)(2) of this AD, if those actions were performed before 
the effective date of

[[Page 36669]]

this AD using the service information specified in paragraph (n)(1), 
(n)(2), or (n)(3) of this AD.
    (1) Airbus Service Bulletin A330-32-3233, dated October 22, 
2009.
    (2) Airbus Service Bulletin A330-32-3233, Revision 01, dated 
July 5, 2013.
    (3) Airbus Service Bulletin A340-32-4275, dated October 22, 
2009.

(o) 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: [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, 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 by the Design Approval Holder 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.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency Airworthiness Directive 2013-
0179, dated August 7, 2013, for related information. This MCAI may 
be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2014-0425.
    (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 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.

    Issued in Renton, Washington, on June 19, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-15254 Filed 6-27-14; 8:45 am]
BILLING CODE 4910-13-P