Document ID: FAA-2014-0132-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2014-02-24T05:00Z

[Federal Register Volume 79, Number 25 (Thursday, February 6, 2014)]
[Proposed Rules]
[Pages 7098-7103]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-02522]

 ========================================================================
 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. 25 / Thursday, February 6, 2014 / 
Proposed Rules  

[[Page 7098]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0012; Directorate Identifier 2012-NM-007-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) 2004-16-
01, that applies to certain Airbus Model A330-200 and -300, and Model 
A340-200 and -300, series airplanes. AD 2004-16-01 currently requires 
repetitive inspections for cracking of the chromed area of the left and 
right piston rods for the main landing gear (MLG) retraction actuators, 
and related investigative and corrective actions if necessary. Since we 
issued AD 2004-16-01, we have determined that the presence of water in 
the internal volume of the piston rod can consequently lead to 
propagation of longitudinal cracking in the body of the piston rod. We 
have also determined through sampling that certain retraction actuator 
piston rods of the MLG need to be replaced. This proposed AD would 
require repetitive draining of any fluid from the retraction actuator 
piston rod internal volume and sealing of the vent hole; repetitive 
ultrasonic inspections of the upper end of the piston rods, and 
corrective actions if necessary; a one-time ultrasonic inspection 
(longitudinal and circumferential) of the full-length of the piston 
rod, and corrective actions if necessary; and a terminating 
modification of the left-hand and right-hand MLG retraction actuators. 
We are proposing this AD to prevent cracking of the piston rods for the 
MLG retraction actuators, which could result in rupture of a piston 
rod, non-damped extension of the MLG, high loads on the fully extended 
MLG, and consequent reduced structural integrity of the MLG.

DATES: We must receive comments on this proposed AD by March 24, 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 airworthiness.A330-A340@airbus.com; 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-
0012; or in person at the Docket Management Facility 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-2014-0012; 
Directorate Identifier 2012-NM-007-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 July 23, 2004, we issued AD 2004-16-01, Amendment 39-13757 (69 
FR 46979, August 4, 2004). AD 2004-16-01 requires actions intended to 
address an unsafe condition on the products listed above.
    Since we issued AD 2004-16-01, the European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community, has issued EASA AD 2011-0178R1, dated March 6, 
2012, corrected March 7, 2012 (for Model A340-200 and -300 series 
airplanes); and EASA AD 2011-0179R1, dated March 6, 2012 (for Model 
A330-200 and -300 series airplanes) (both referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''); to 
correct an unsafe condition for the specified products. EASA AD 2011-
0178R1, dated March 6, 2012, corrected March 7, 2012, states:

    During an approach phase, the flight crew of an A330 aeroplane 
had to perform a free-fall extension of the left-hand (LH) MLG.
    Rupture of the LH MLG retraction actuator piston rod was found 
near the rod attachment point. The inspection revealed at the 
location of the rupture the presence of corrosion resulting from 
incorrect application of the anticorrosion protection, and 
circumferential cracks resulting from normal operational loading 
effects.
    Since the above rupture, new cases of crack propagation along 
the length of the piston rod occurred. These ruptures led to a non-
damped extension of the landing gear. Fully

[[Page 7099]]

extended, the landing gear assembly was submitted to high loads 
jeopardizing its structural integrity.
    This condition, if not detected and corrected, could lead to MLG 
failure during landing or roll-out and consequent damage to the 
aeroplane and injury to occupants.
    DGAC France issued AD F-2005-098 (EASA approval 2005-5887) [and 
AD F-2005-099 (EASA approval 2005-5888)] to address this unsafe 
condition [the FAA issued AD 2004-16-01, Amendment 39-13757 (69 FR 
46979, August 4, 2004)]. Since that [DGAC France] AD was issued, the 
results of extensive investigation determined that the presence of 
water in the internal volume of the piston rod can lead to the 
formation of ice which represents a potential source of high 
magnitude tensile hoop stresses in the material of the rod, leading 
to propagation of longitudinal crack in the body of the piston rod.
    Prompted by these findings, EASA issued AD 2006-0301, partially 
retaining the requirements of DGAC France AD F-2005-099, which was 
superseded, and to revise the inspection requirements as follows:
    a. Extend the repetitive inspections interval for the removal of 
fluid from the internal volume of the piston rod using flight cycles 
in lieu of flight hours as this better represents the mechanism for 
the accumulation of water within the piston rod.
    b. Remove the preliminary visual inspection from the ultrasonic 
longitudinal inspection of the upper end of the piston rod.
    c. Add a new one-time ultrasonic longitudinal and 
circumferential inspection of the full piston rod length to 
eliminate any parts that exhibit severe corrosion along the internal 
length of the piston rod.
    d. Require installation of new design hollow piston rod Part 
Number (P/N) 114256328 (Airbus mod. 52980--SB A340-32-4222 Revision 
01) without a vent hole, thus eliminating moisture ingress as the 
terminating action.
    EASA AD 2006-0301 was later revised:

--at revision 01, to correct a number of typographical errors and to 
add reference to Airbus SB A340-32-4212 Revision 04, and
--at revision 02 to extend the inspections threshold from 3 to 6 
years in service usage for retraction actuator piston rod P/N 
114256321 issue 06 which was re-identified to P/N 114256326 issue 01 
in accordance with the instructions of Airbus SB A340-32-4260.

    More recently, the sampling of piston rod P/N 114256326 issue 1 
and P/N 114256321 issue 06 have confirmed the need to replace all 
retraction actuator piston rods with a piston rod P/N114256328.
    For the reasons described above, this [EASA] AD at original 
issue retained the requirements of EASA AD 2006-0301R2 (http://ad.easa.europa.eu/blob/easa_ad_2006_0301_R2_superseded.pdf/AD_2006-0301R2_1), which is superseded, and required the replacement 
of all retraction actuator piston rods with a piston rod P/N 
114256328, which constitutes terminating action to the repetitive 
requirements of this AD.
    This [EASA] AD is revised to clarify that aeroplanes on which 
Airbus mod. 52980 has been embodied in production are not required 
to accomplish the reidentification of MLG retraction actuator P/N 
114256002-055 which is mentioned in the accomplishment instructions 
of Airbus SB A340-32-4222 Revision 03.
    This [EASA] AD has been republished to correct a typographical 
mistake of the applicable Airbus SB number in the Applicability (in 
the Note) and in the Reason sections of this [EASA] AD.

You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA-
2014-0012.

Relevant Service Information

    Airbus has issued the following service bulletins.
     Airbus Mandatory Service Bulletin A330-32-3173, Revision 
05, dated September 26, 2008.
     Airbus Mandatory Service Bulletin A330-32-3180, Revision 
03, dated January 28, 2011.
     Airbus Mandatory Service Bulletin A340-32-4212, Revision 
05, dated September 26, 2008.
     Airbus Mandatory Service Bulletin A340-32-4222, Revision 
03, dated January 28, 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 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 Proposed AD and the MCAI or Service 
Information

    EASA AD 2011-0178R1, dated March 6, 2012, corrected March 7, 2012 
(for Model A340-200 and -300 series airplanes); and AD 2011-0179R1, 
dated March 6, 2012 (for Model A330-200 and -300 series airplanes); 
require replacement of the retraction actuator within 10 flight cycles 
if the findings of the ultrasonic inspection of the retraction actuator 
piston rod end are between 75% and 90% FSH (full screen height) and 
between 5 and 7 in time base. However, paragraph (n) of this proposed 
AD would require replacement of the retraction actuator before further 
flight if the findings of the ultrasonic inspection of the retraction 
actuator piston rod end are higher than 75% and between 5 and 7 in time 
base.
    EASA AD 2011-0178R1, dated March 6, 2012, corrected March 7, 2012 
(for Model A340-200 and -300 series airplanes); and AD 2011-0179R1, 
dated March 6, 2012 (for Model A330-200 and -300 series airplanes); 
require replacement of the retraction actuator within 10 landings if 
the findings of the one-time ultrasonic circumferential inspection of 
the full-length chromed part of the piston rod give an indication 
between 75% and 90% FSH and between 7 and 9.5 in time base. However, 
paragraph (p)(2) of this proposed AD would require replacement of the 
retraction actuator before further flight if inspection findings are 
higher than 75% FSH and between 7 and 9.5 in time base.
    We have determined that, because of the safety implications and 
consequences associated with those findings, the actuator must be 
replaced before further flight. These differences have been coordinated 
with EASA.

Costs of Compliance

    We estimate that this proposed AD affects 24 Model A330-200 and -
300 series airplanes of U.S. registry. There are no Model A340-200 and 
-300 series airplanes of U.S. registry.
    We estimate that it would take about 67 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 
$56,000 per product (2 actuators). Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $1,480,680, or 
$61,695 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 38 work-hours and require parts costing $56,000 (2 
actuators), for a cost of $59,230 per product. We have no way of 
determining the number of aircraft that might need these actions.
    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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

[[Page 7100]]

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 proposed AD 
is 2120-0056. The paperwork cost associated with this proposed 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. Therefore, all reporting 
associated with this proposed AD is 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.

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) 
2004-16-01, Amendment 39-13757 (69 FR 46979, August 4, 2004), and 
adding the following new AD:

Airbus: Docket No. FAA-2014-0012; Directorate Identifier 2012-NM-
007-AD.

(a) Comments Due Date

    We must receive comments by March 24, 2014.

(b) Affected ADs

    This AD supersedes AD 2004-16-01, Amendment 39-13757 (69 FR 
46979, August 4, 2004).

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 
airplanes; and Model A340-211, -212, and -213, -311, -312, and -313 
airplanes; certificated in any category; all manufacturer serial 
numbers, except for those airplanes that have had Airbus 
Modification 52980 incorporated in production on both main landing 
gear (MLG) units, or airplanes that have had Airbus Modification 
54500 incorporated in production.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of the piston rods for the MLG 
retraction actuators rupturing during flight. We are issuing this AD 
to prevent cracking of the piston rods for the MLG retraction 
actuators, which could result in rupture of a piston rod, non-damped 
extension of the MLG, high loads on the fully extended MLG, and 
consequent reduced structural integrity of the MLG.

(f) Compliance

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

(g) Repetitive Detailed Inspections

    At the applicable time specified in paragraph (g)(1) or (g)(2) 
of this AD: Do a detailed inspection for cracking of the visible 
chromed area of the MLG retraction actuator piston rods in the fully 
extended position, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-32-3173, 
Revision 05, dated September 26, 2008 (for Model A330 series 
airplanes); or Airbus Mandatory Service Bulletin A340-32-4212, 
Revision 05, dated September 26, 2008 (for Model A340-200 and -300 
series airplanes). Repeat the inspection thereafter at intervals not 
to exceed 8 days until the actions required by paragraphs (j) and 
(o) of this AD are accomplished.
    (1) For MLG retraction actuator piston rods that have not had a 
detailed inspection accomplished as of the effective date of this 
AD, as described in any applicable service information specified in 
paragraph (h)(1) or (h)(2) of this AD: At the applicable time 
specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD.
    (i) For MLG retraction actuator piston rods having part number 
(P/N) 114256309, or P/N 114256321 issue 03: Do the inspection within 
60 days after the effective date of this AD, or before the MLG 
retraction actuator has been in service 36 months, whichever occurs 
later.
    (ii) For MLG retraction actuator piston rods having P/N 
114256326 issue 01, or P/N 114256321 issue 06: Do the inspection 
within 60 days after the effective date of this AD, or before the 
MLG retraction actuator has been in service 72 months, whichever 
occurs later.
    (2) For MLG retraction actuator piston rods having P/N 
114256309, P/N 114256321 issue 03, P/N 114256326 issue 01, or P/N 
114256321 issue 06, that have had a detailed inspection accomplished 
as of the effective date of this AD, as described in the applicable 
service information specified in paragraph (h)(1) or (h)(2) of this 
AD: Inspect within 8 days after the effective date of this AD.

(h) Service Information To Determine Airplane Configuration for 
Paragraph (g) of This AD

    (1) For Model A330 airplanes:
    (i) Airbus Mandatory Service Bulletin A330-32-3173, Revision 01, 
dated June 16, 2004;
    (ii) Airbus Mandatory Service Bulletin A330-32-3173, Revision 
02, dated May 11, 2005;
    (iii) Airbus Mandatory Service Bulletin A330-32-3173, Revision 
03, dated March 13, 2006;
    (iv) Airbus Mandatory Service Bulletin A330-32-3173, Revision 
04, dated June 12, 2006; or
    (v) Airbus Mandatory Service Bulletin A330-32-3173, Revision 05, 
dated September 26, 2008.
    (2) For Model A340-200 and -300 series airplanes:
    (i) Airbus Mandatory Service Bulletin A340-32-4212, Revision 01, 
dated June 16, 2004;
    (ii) Airbus Mandatory Service Bulletin A340-32-4212, Revision 
02, dated May 11, 2005;

[[Page 7101]]

    (iii) Airbus Mandatory Service Bulletin A340-32-4212, Revision 
03, dated March 13, 2006;
    (iv) Airbus Mandatory Service Bulletin A340-32-4212, Revision 
04, dated June 12, 2006; or
    (v) Airbus Mandatory Service Bulletin A340-32-4212, Revision 05, 
dated September 26, 2008.

(i) Corrective Action for Cracking

    If any cracking is found during any inspection required by 
paragraph (g) of this AD: Before further flight, replace the MLG 
retraction actuator with a new or serviceable part, in accordance 
with the Accomplishment Instructions of Airbus Mandatory Service 
Bulletin A330-32-3173, Revision 05, dated September 26, 2008 (for 
Model A330 series airplanes); or Airbus Mandatory Service Bulletin 
A340-32-4212, Revision 05, dated September 26, 2008 (for Model A340-
200 and -300 series airplanes).

(j) Repetitive Fluid Draining and Vent Hole Sealing

    At the applicable time specified in paragraph (j)(1) or (j)(2) 
of this AD: Drain any fluid from the retraction actuator piston rod 
internal volume and seal the vent hole, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A330-32-3173, Revision 05, dated September 26, 2008 (for Model A330 
series airplanes); or Airbus Mandatory Service Bulletin A340-32-
4212, Revision 05, dated September 26, 2008 (for Model A340-200 and 
-300 series airplanes). Repeat the draining and sealing thereafter 
at intervals not to exceed 1,000 flight cycles or 24 months, 
whichever occurs first.
    (1) For MLG retraction actuator piston rods that have not been 
inspected and have not had the fluid drained as of the effective 
date of this AD, as described in the applicable service information 
specified in paragraph (k)(1) or (k)(2) of this AD: At the 
applicable time specified in paragraph (j)(1)(i) or (j)(1)(ii) of 
this AD.
    (i) For MLG retraction actuator piston rods having P/N 
114256309, or P/N 114256321 issue 03: Do the draining and sealing 
within 60 days after the effective date of this AD or before the MLG 
retraction actuator has been in service 36 months, whichever occurs 
later.
    (ii) For MLG retraction actuator piston rods having P/N 
114256326 issue 01, or P/N 114256321 issue 06: Do the draining and 
sealing within 60 days after the effective date of this AD or before 
the MLG retraction actuator has been in service 72 months, whichever 
occurs later.
    (2) For MLG retraction actuator piston rods having P/N 
114256309, P/N 114256321 issue 03, P/N 114256326 issue 01, or P/N 
114256321 issue 06, that have been inspected and the fluid drained 
as of the effective date of this AD, as described in the applicable 
service information specified in paragraph (k)(1) or (k)(2) of this 
AD: Do the draining and sealing at the later of the times specified 
in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD.
    (i) Within 1,000 flight cycles or 24 months, whichever occurs 
first, from the last inspection and fluid drainage accomplished in 
accordance with the actions required in paragraph (j) of this AD.
    (ii) Within 60 days after the effective date of this AD.

(k) Service Information To Determine Configuration for Paragraph (j) of 
This AD

    (1) For Model A330 airplanes:
    (i) Airbus Mandatory Service Bulletin A330-32-3173, Revision 02, 
dated May 11, 2005;
    (ii) Airbus Mandatory Service Bulletin A330-32-3173, Revision 
03, dated March 13, 2006;
    (iii) Airbus Mandatory Service Bulletin A330-32-3173, Revision 
04, dated June 12, 2006; or
    (iv) Airbus Mandatory Service Bulletin A330-32-3173, Revision 
05, dated September 26, 2008.
    (2) For Model A340-200 and -300 series airplanes:
    (i) Airbus Mandatory Service Bulletin A340-32-4212, Revision 02, 
dated May 11, 2005;
    (ii) Airbus Mandatory Service Bulletin A340-32-4212, Revision 
03, dated March 13, 2006;
    (iii) Airbus Mandatory Service Bulletin A340-32-4212, Revision 
04, dated June 12, 2006; or
    (iv) Airbus Mandatory Service Bulletin A340-32-4212, Revision 
05, dated September 26, 2008.

(l) Ultrasonic Inspection

    At the applicable time specified in paragraph (l)(1) or (l)(2) 
of this AD: Do an ultrasonic longitudinal inspection for cracking of 
the retraction actuator piston rod end, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A330-32-3173, Revision 05, dated September 26, 2008 (for Model A330 
series airplanes); or Airbus Mandatory Service Bulletin A340-32-
4212, Revision 05, dated September 26, 2008 (for Model A340-200 and 
-300 series airplanes).
    (1) For MLG retraction actuator piston rods that have not had a 
non-destructive test (NDT) inspection as of the effective date of 
this AD, as described in the applicable service information 
specified in paragraph (m)(1) or (m)(2) of this AD: At the 
applicable time specified in paragraph (l)(1)(i) or (l)(1)(ii) of 
this AD.
    (i) For MLG retraction actuator piston rods having P/N 
114256309, or P/N 114256321 issue 03: Do the inspection within 60 
days after the effective date of this AD, or before the MLG 
retraction actuator has been in service 36 months, whichever occurs 
later.
    (ii) For MLG retraction actuator piston rods having P/N 
114256326 issue 01, or P/N 114256321 issue 06: Do the inspection 
within 60 days after the effective date of this AD, or before the 
MLG retraction actuator has been in service 72 months, whichever 
occurs later.
    (2) For MLG retraction actuator piston rods having P/N 
114256309, P/N 114256321 issue 03, P/N 114256326 issue 01, or P/N 
114256321 issue 06, that have had an NDT inspection as of the 
effective date of this AD, as described in the applicable service 
information specified in paragraph (m)(1) or (m)(2) of this AD: Do 
the inspection at the later of the times specified in paragraphs 
(l)(2)(i) and (l)(2)(ii) of this AD.
    (i) Within 1,400 flight hours, 250 flight cycles, or 4 months, 
whichever occurs first after the date of the last ultrasonic 
longitudinal inspection performed as described in the applicable 
service information specified in paragraph (m)(1) or (m)(2) of this 
AD.
    (ii) Within 60 days after the effective date of this AD.

(m) Service Information To Determine Configuration for Paragraph (l) of 
This AD

    (1) For Model A330 airplanes:
    (i) Airbus Mandatory Service Bulletin A330-32-3173, dated 
December 17, 2003;
    (ii) Airbus Mandatory Service Bulletin A330-32-3173, Revision 
01, dated June 16, 2004;
    (iii) Airbus Mandatory Service Bulletin A330-32-3173, Revision 
02, dated May 11, 2005;
    (iv) Airbus Mandatory Service Bulletin A330-32-3173, Revision 
03, dated March 13, 2006;
    (v) Airbus Mandatory Service Bulletin A330-32-3173, Revision 04, 
dated June 12, 2006; or
    (vi) Airbus Mandatory Service Bulletin A330-32-3173, Revision 
05, dated September 26, 2008.
    (2) For Model A340-200 and -300 series airplanes:
    (i) Airbus Mandatory Service Bulletin A340-32-4212, dated 
December 17, 2003;
    (ii) Airbus Mandatory Service Bulletin A340-32-4212, Revision 
01, dated June 16, 2004;
    (iii) Airbus Mandatory Service Bulletin A340-32-4212, Revision 
02, dated May 11, 2005;
    (iv) Airbus Mandatory Service Bulletin A340-32-4212, Revision 
03, dated March 13, 2006;
    (v) Airbus Mandatory Service Bulletin A340-32-4212, Revision 04, 
dated June 12, 2006; or
    (vi) Airbus Mandatory Service Bulletin A340-32-4212, Revision 
05, dated September 26, 2008.

(n) Corrective Action for Ultrasonic Inspection; Repetitive Interval

    (1) If the finding of the inspection required by paragraph (l) 
of this AD gives an indication of 75% or higher of full screen 
height (FSH) and between 5 and 7 in time base: Before further 
flight, replace the MLG retraction actuator with a new or 
serviceable part, in accordance with the Accomplishment Instructions 
of Airbus Mandatory Service Bulletin A330-32-3173, Revision 05, 
dated September 26, 2008 (for Model A330 series airplanes); or 
Airbus Mandatory Service Bulletin A340-32-4212, Revision 05, dated 
September 26, 2008 (for Model A340-200 and -300 series airplanes).
    (2) If the finding of the inspection required by paragraph (l) 
of this AD gives an indication of less than 75% FSH and between 5 
and 7 in time base: Repeat the inspection required by paragraph (l) 
of this AD thereafter at intervals not to exceed 1,400 flight hours, 
250 flight cycles, or 4 months, whichever occurs first.

[[Page 7102]]

(o) One-Time Ultrasonic Inspections of the Full-Length of the Piston 
Rod

    At the applicable time specified in paragraph (o)(1) or (o)(2) 
of this AD: Do a full-length ultrasonic longitudinal and a full-
length circumferential inspection of the chromium-plated area of the 
piston rod for cracking, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-32-3173, 
Revision 05, dated September 26, 2008 (for Model A330 series 
airplanes); or Airbus Mandatory Service Bulletin A340-32-4212, 
Revision 05, dated September 26, 2008 (for Model A340-200 and -300 
series airplanes).
    (1) For MLG retraction actuator piston rods having P/N 
114256309, or P/N 114256321 issue 03: Inspect at the later of the 
times specified in paragraphs (o)(1)(i) and (o)(1)(ii) of this AD.
    (i) Within 1,750 flight hours, 315 flight cycles, or 5 months 
after the effective date of this AD, whichever occurs first.
    (ii) Before the MLG retraction actuator has been in service 36 
months.
    (2) For MLG retraction actuator piston rods having P/N 114256326 
issue 01, or P/N 114256321 issue 06: Inspect at the later of the 
times specified in paragraphs (o)(2)(i) and (o)(2)(ii) of this AD.
    (i) Within 1,750 flight hours, 315 flight cycles, or 5 months 
after the effective date of this AD, whichever occurs first.
    (ii) Before the MLG retraction actuator has been in service 72 
months.

(p) Corrective Action for One-time Ultrasonic Inspections of the Full-
Length of the Piston Rod

    (1) If the finding of the full-length ultrasonic longitudinal 
inspection required by paragraph (o) of this AD gives an indication 
of 75% or higher FSH and between 5 and 7 in time base: Before 
further flight, replace the MLG retraction actuator with a new or 
serviceable part, in accordance with the Accomplishment Instructions 
of Airbus Mandatory Service Bulletin A330-32-3173, Revision 05, 
dated September 26, 2008 (for Model A330 series airplanes); or 
Airbus Mandatory Service Bulletin A340-32-4212, Revision 05, dated 
September 26, 2008 (for Model A340-200 and -300 series airplanes).
    (2) If the finding of the full-length ultrasonic circumferential 
inspection required by paragraph (o) of this AD gives an indication 
of 75% or higher FSH and between 7 and 9.5 in time base: Before 
further flight, replace the MLG retraction actuator with a new or 
serviceable part, in accordance with the Accomplishment Instructions 
of Airbus Mandatory Service Bulletin A330-32-3173, Revision 05, 
dated September 26, 2008 (for Model A330 series airplanes); or 
Airbus Mandatory Service Bulletin A340-32-4212, Revision 05, dated 
September 26, 2008 (for Model A340-200 and -300 series airplanes).

(q) Reporting Requirement

    Report the results (regardless of findings) of the detailed 
inspection, the fluid drain/seal of the retraction actuator piston 
rod, the one-time ultrasonic longitudinal inspection of the upper 
end of the piston rod, and the one-time full-length ultrasonic 
circumferential inspection required by this AD, and the findings of 
the actions required by this AD that cause an actuator to be 
replaced, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A330-32-3173, Revision 05, dated 
September 26, 2008 (for Model A330 series airplanes); or Airbus 
Mandatory Service Bulletin A340-32-4212, Revision 05, dated 
September 26, 2008 (for Model A340-200 and -300 series airplanes). 
Submit the report to Airbus Customer Services Directorate, 
Attention: SEDCC1 Technical Data and Documentation Services fax: 
(+33) 5 61 93 28 06; email: sb.reporting@airbus.com, or via your 
resident customer support office. Submit the report at the 
applicable time specified in paragraph (q)(1) or (q)(2) of this AD.
    (1) If the actions requiring reporting, as specified in 
paragraph (q) of this AD, are done on or after the effective date of 
this AD: Submit the report within 90 days after those actions have 
been done.
    (2) If the actions requiring reporting, as specified in 
paragraph (q) of this AD, were done before the effective date of 
this AD: Submit the report within 90 days after the effective date 
of this AD.

(r) Terminating Actions for Repetitive Detailed Inspections

    Accomplishment of the initial drainage of the fluid from the 
piston, as required by paragraph (j) of this AD, the full-length 
ultrasonic longitudinal inspection, and the full-length 
circumferential inspection, as required by paragraph (o) of this AD, 
constitutes terminating action for the repetitive detailed 
inspections required by paragraph (g) of this AD, provided no crack 
is found during the inspections.

(s) Terminating Modification

    Within 48 months after the effective date of this AD: Modify the 
left-hand and right-hand MLG retraction actuators, in accordance 
with the Accomplishment Instructions of Airbus Mandatory Service 
Bulletin A330-32-3180, Revision 03, dated January 28, 2011 (for 
Model A330 series airplanes); or Airbus Mandatory Service Bulletin 
A340-32-4222, Revision 03, dated January 28, 2011 (for Model A340-
200 and -300 series airplanes). Accomplishment of the modification 
required by this paragraph terminates the repetitive requirements of 
this AD for the MLG retraction actuator that is modified.

(t) Exception to Re-Identification of the MLG Retraction Actuator

    The re-identification of the MLG retraction actuator having P/N 
114256002-055, which is described in Airbus Mandatory Service 
Bulletin A330-32-3180, Revision 03, dated January 28, 2011 (for 
Model A330 series airplanes); or Airbus Mandatory Service Bulletin 
A340-32-4222, Revision 03, dated January 28, 2011 (for Model A340-
200 and -300 series airplanes); is not required on airplanes that 
have Airbus modification 52980 embodied in production.

(u) Optional Parts Installation

    Installation of retraction actuator piston rod having P/N 
114256323, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A330-32-3174, Revision 02, dated September 
16, 2005 (for Model A330 series airplanes); or Airbus Service 
Bulletin A340-32-4213, Revision 01, dated September 16, 2005 (for 
Model A340-200 and -300 series airplanes); constitutes an acceptable 
method of compliance with the requirements of paragraphs (g), (j), 
(l), and (o) of this AD for that installed MLG retraction actuator.

(v) Parts Installation Limitation

    As of the effective date of this AD, no person may install a 
piston rod having P/N 114256309, or 114256321, or 114256326 issue 01 
for the MLG retraction actuator on any airplane, unless the part 
meets the applicable requirements of this AD at the specified times 
and intervals.

(w) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraphs (g), (j), (l), and (o) of this AD, if those actions were 
performed before the effective date of this AD using the service 
information specified in paragraphs (w)(1)(i) through (w)(1)(ix) of 
this AD.
    (i) Airbus Mandatory Service Bulletin A330-32-3173, dated 
December 17, 2003; (for Model A330 series airplanes).
    (ii) Airbus Mandatory Service Bulletin A330-32-3173, Revision 
01, dated June 16, 2004 (for Model A330 series airplanes).
    (iii) Airbus Mandatory Service Bulletin A330-32-3173, Revision 
02, dated May 11, 2005 (for Model A330 series airplanes).
    (iv) Airbus Mandatory Service Bulletin A330-32-3173, Revision 
03, dated March 13, 2006 (for Model A330 series airplanes).
    (v) Airbus Mandatory Service Bulletin A330-32-3173, Revision 04, 
dated June 12, 2006 (for Model A330 series airplanes).
    (vi) Airbus Mandatory Service Bulletin A340-32-4212, dated 
December 17, 2003 (for Model A340-200 and -300 series airplanes).
    (vii) Airbus Mandatory Service Bulletin A340-32-4212, Revision 
01, dated June 16, 2004 (for Model A340-200 and -300 series 
airplanes).
    (viii) Airbus Mandatory Service Bulletin A340-32-4212, Revision 
02, dated May 11, 2005; Revision 03, dated March 13, 2006 (for Model 
A340-200 and -300 series airplanes).
    (ix) Airbus Mandatory Service Bulletin A340-32-4212, Revision 
04, dated June 12, 2006 (for Model A340-200 and -300 series 
airplanes).
    (2) This paragraph provides credit for the actions required by 
paragraph (s) of this AD, if the modification was done before the 
effective date of this AD using the service bulletins specified in 
paragraphs (u)(2)(i) through (u)(2)(iv) of this AD.
    (i) Airbus Service Bulletin A330-32-3180, Revision 01, dated 
August 15, 2005 for Model A330 series airplanes).
    (ii) Airbus Mandatory Service Bulletin A330-32-3180, Revision 
02, dated April 4, 2007 (for Model A330 series airplanes).
    (iii) Airbus Service Bulletin A340-32-4222, Revision 01, dated 
August 15, 2005 (for Model A340-200 and -300 series airplanes).
    (iv) Airbus Mandatory Service Bulletin A340-32-4222, Revision 
02, dated April 4, 2007 (for Model A340-200 and -300 series 
airplanes).

[[Page 7103]]

    (3) This paragraph provides credit for the actions required by 
paragraph (s) of this AD, if the modification was done before the 
effective date of this AD using Airbus Service Bulletin A340-32-
4222, dated September 20, 2004; and re-identified using Airbus 
Service Bulletin A340-32-4222, Revision 01, dated August 15, 2005, 
or Airbus Mandatory Service Bulletin A340-32-4222, Revision 02, 
dated April 4, 2007.

(x) 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: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
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, or the DAH with a State of Design 
Authority's design organization approval). For a repair method to be 
approved, the repair approval must specifically refer to this AD. 
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.

(y) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency Airworthiness Directive 2011-
0178R1, dated March 6, 2012 (corrected March 7, 2012); and 2011-
0179R1, dated March 6, 2012; for related information. These MCAIs 
may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2014-0012.
    (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 airworthiness.A330-A340@airbus.com; 
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 January 29, 2014.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-02522 Filed 2-5-14; 8:45 am]
BILLING CODE 4910-13-P