[Federal Register Volume 79, Number 156 (Wednesday, August 13, 2014)]
[Proposed Rules]
[Pages 47395-47401]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-19157]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0529; Directorate Identifier 2013-NM-260-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2011-13-
11 and AD 2013-16-09, for all Airbus Model A318, A319, A320, and A321 
series airplanes. AD 2011-13-11 currently requires an amendment of the 
airplane flight manual (AFM), repetitive checks of specific centralized 
fault display system (CFDS) messages, an inspection of the opening 
sequence of the main landing gear (MLG) door actuator for discrepancies 
if certain messages are found, and corrective actions if necessary. AD 
2013-16-09

[[Page 47396]]

currently requires an inspection to determine airplane configuration 
and part numbers of the landing gear control interface unit and MLG 
door actuators; and, for affected airplanes, repetitive inspections of 
the opening sequence of the MLG door actuator, and replacement of the 
MLG door actuator if necessary; and provides optional terminating 
action for the repetitive inspections. Since we issued AD 2011-13-11 
and AD 2013-16-09, we have determined that the interval of the MLG door 
opening sequence inspection must be reduced. This proposed AD would 
reduce the interval of the MLG door opening sequence inspection. This 
proposed AD would also require replacing or modifying certain MLG door 
actuators. We are proposing this AD to detect and correct deterioration 
of the damping ring and associated retaining ring of the MLG door 
actuator, which can sufficiently increase the friction inside the 
actuator to restrict opening of the MLG door by gravity, during 
operation of the landing gear alternate (free-fall) extension system. 
This condition could prevent the full extension and/or down-locking of 
the MLG, possibly resulting in MLG collapse during landing and 
consequent damage to the airplane and injury to occupants.

DATES: We must receive comments on this proposed AD by September 29, 
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 Airbus service information identified in this proposed AD, 
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email [email protected] Internet 
http://www.airbus.com. For General Electric service information 
identified in this AD contact GE Aviation, Customer Support Center, 1 
Neumann Way, Cincinnati, OH 45215; phone: 513-552-3272; email: 
[email protected]; Internet: http://www.geaviation.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-
0529; 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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
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-2014-0529; 
Directorate Identifier 2013-NM-260-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 June 16, 2011, we issued AD 2011-13-11, Amendment 39-16734 (76 
FR 37241, June 27, 2011). AD 2011-13-11 required actions intended to 
address an unsafe condition on all Airbus Model A318, A319, A320, and 
A321 series airplanes. The unsafe condition is the deterioration of the 
damping ring and associated retaining ring of the MLG door actuator, 
which can sufficiently increase the friction inside the actuator to 
restrict opening of the MLG door by gravity, during operation of the 
landing gear alternate (free-fall) extension system. This condition 
could prevent the full extension and/or down-locking of the MLG, 
possibly resulting in MLG collapse during landing and consequent damage 
to the airplane and injury to occupants.
    On July 26, 2013, we issued AD 2013-16-09, Amendment 39-17547 (78 
FR 48286, August 8, 2013). AD 2013-16-09 required actions intended to 
detect and correct certain configuration of landing gear control 
interface unit and actuators, which could prevent the full extension or 
down-locking of the MLG, possibly resulting in MLG collapse during 
landing and consequent damage to the airplane and injury to occupants 
on all Airbus Model A318, A319, A320, and A321 series airplanes.
    Since we issued AD 2011-13-11, Amendment 39-16734 (76 FR 37241. 
June 27, 2011), and AD 2013-16-09, Amendment 39-17547 (78 FR 48286, 
August 8, 2013), we have determined that the interval of the MLG door 
opening sequence inspection must be reduced in order to detect and 
correct deterioration of the damping ring and associated retaining ring 
of the MLG door actuator, which can sufficiently increase the friction 
inside the actuator to restrict opening of the MLG door by gravity, 
during operation of the landing gear alternate (free-fall) extension 
system. This condition, if not detected and corrected, could prevent 
the full extension and/or down-locking of the MLG, possibly resulting 
in MLG collapse during landing and consequent damage to the airplane 
and injury to occupants.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2013-0288, dated December 6, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    Some operators reported slow operation of the main landing gear 
(MLG) door opening/closing sequence, leading to the generation of 
ECAM warnings during the landing gear retraction or extension 
sequence.
    Investigations showed that the damping ring and associated 
retaining ring of the MLG door actuator deteriorate. The resultant 
debris increases the friction inside the actuator which can be 
sufficiently high to restrict opening of the MLG door by gravity, 
during operation of the landing gear alternate (free-fall) extension 
system.

[[Page 47397]]

    This condition, if not corrected, could prevent the full 
extension and/or down locking of the MLG, possibly resulting in MLG 
collapse during landing or rollout and consequent damage to the 
aeroplane and injury to occupants.
    EASA AD 2006-0112R1 (http://ad.easa.europa.eu/blob/easa_ad_2006_0112_R1_superseded.pdf/AD_2006-0112R1_1) was issued to 
require repetitive inspections of the opening sequence of the MLG 
door in order to identify the defective actuators, and to introduce 
as an optional terminating action Airbus production Modification 
(MOD) 38274 and associated Service Bulletin (SB) A320-32-1338, which 
incorporate an improved retaining ring, located on the piston rod's 
extension end, and a new piston rod with machined shoulder to 
accommodate the thicker section of the modified retaining ring.
    After in-service introduction of the new MLG door actuator, Part 
Number (P/N) 114122012 (Post MOD 38274--SB A320-32-1338), several 
operators reported failures of internal parts of the MLG door 
actuator. Investigations confirmed that these failures could result 
in slow extension of the actuator rod, delaying the MLG door 
operation, or possibly stopping just before the end of the stroke, 
preventing the door to reach the fully open position.
    EASA AD 2011-0069R1 (http://ad.easa.europa.eu/blob/easa--ad--
2011--0069--R1--superseded.pdf/AD--2011-0069R1--1) (which 
corresponds to FAA AD 2011-13-11, Amendment 39-16734 (76 FR 37241, 
June 27, 2011)), which supersedes EASA AD 2006-0112R1 required an 
amendment of the applicable Airplane Flight Manual (AFM), repetitive 
checks of specific Centralized Fault Display System (CFDS) messages, 
repetitive inspections of the opening sequence of the MLG door 
actuator and, depending on findings, corrective action(s).
    Since that [EASA] AD was issued, Airbus introduced a reinforced 
MLG door actuator P/N 114122014 (MOD 153655). Airbus issued SB A320-
32-1407 containing instructions for in-service replacement of the 
affected MLG door actuators, or modification of the actuators to the 
new standard.
    In addition, following a recent occurrence with a gear extension 
problem, the result of additional analyses by Airbus revealed that 
the CFDS expected specific messages may not be generated and as a 
result, repetitive checks of messages are not effective for 
aeroplanes fitted with landing gear control interface unit (LGCIU) 
interlink communication ARINC 429 (applied in production through 
Airbus MOD 39303, or in service through Airbus SB A320-32-1409), in 
combination with LGCIUs 80-178-02-88012 or 80-178-03-88013 in both 
positions and at least one MLG door actuator pre MOD 153655 (SB 
A320-32-1407--SB 114122-32-105) installed.
    Prompted by these findings, EASA issued Emergency AD 2013-0132-E 
(http://ad.easa.europa.eu/blob/easa_ad_2013_0132_E_superseded.pdf/EAD_2013-0132-E_1) (which corresponds to FAA AD 
2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 2013)) to 
require identification of the affected aeroplanes to establish the 
configuration and, for those aeroplanes, repetitive inspections of 
the opening sequence of the MLG door actuator and, depending on 
findings, replacement of the MLG door actuator. That [EASA] AD also 
provided an optional terminating action by disconnection of the 
interlink for certain LGCIUs, or in-service modification of the 
aeroplane through Airbus SB A320-32-1407 (equivalent to production 
MOD 153655).
    Since those [EASA] ADs were issues, analyses performed by Airbus 
have revealed that the MLG door opening sequence inspection interval 
must be reduced, and that the (previously optional) terminating 
action must be made mandatory.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2011-0069R1 and [EASA] AD 2013-0132-E, which 
are superseded, but with reduced inspection intervals, and requires 
replacement or modification [including related investigative and 
corrective actions], as applicable, of the affected MLG door 
actuators as terminating action for the monitoring, repetitive 
checks and inspections.

    The related investigative actions include an inspection for damage 
(including nicks and burns) of the damping rings and an inspection for 
mechanical damage of the piston rod. Corrective actions include 
replacing or modifying parts. 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-2014-0529.

Relevant Service Information

    Airbus has issued Service Bulletin A320-32-1390, Revision 02, dated 
October 23, 2013; and General Electric has issued Service Bulletin 
114122-32-105, Revision 1, dated March 26, 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.

Differences Between This Proposed AD and the MCAI or Service 
Information

    Paragraph (17) of the MCAI incorrectly refers to paragraph (11) of 
the MCAI as requiring inspections; however, paragraph (11) of the MCAI 
specifies replacement actions. Paragraphs (j), (l), and (p) of this 
proposed AD refer to the inspections specified in paragraph (17) of the 
MCAI.

``Contacting the Manufacturer'' Paragraph in This Proposed AD

    Since late 2006, we have included a standard paragraph titled 
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD 
based on a foreign authority's AD.
    The MCAI or referenced service information in an FAA AD often 
directs the owner/operator to contact the manufacturer for corrective 
actions, such as a repair. Briefly, the Airworthy Product paragraph 
allowed owners/operators to use corrective actions provided by the 
manufacturer if those actions were FAA-approved. In addition, the 
paragraph stated that any actions approved by the State of Design 
Authority (or its delegated agent) are considered to be FAA-approved.
    In an NPRM having Directorate Identifier 2012-NM-101-AD (78 FR 
78285, December 26, 2013), we proposed to prevent the use of repairs 
that were not specifically developed to correct the unsafe condition, 
by requiring that the repair approval provided by the State of Design 
Authority or its delegated agent specifically refer to the FAA AD. This 
change was intended to clarify the method of compliance and to provide 
operators with better visibility of repairs that are specifically 
developed and approved to correct the unsafe condition. In addition, we 
proposed to change the phrase ``its delegated agent'' to include a 
design approval holder (DAH) with State of Design Authority design 
organization approval (DOA), as applicable, to refer to a DAH 
authorized to approve required repairs for the proposed AD.
    One commenter to the NPRM having Directorate Identifier 2012-NM-
101-AD (78 FR 78285, December 26, 2013) stated the following: ``The 
proposed wording, being specific to repairs, eliminates the 
interpretation that Airbus messages are acceptable for approving minor 
deviations (corrective actions) needed during accomplishment of an AD 
mandated Airbus service bulletin.''
    This comment has made the FAA aware that some operators have 
misunderstood or misinterpreted the Airworthy Product paragraph to 
allow the owner/operator to use messages provided by the manufacturer 
as approval of deviations during the accomplishment of an AD-mandated 
action. The Airworthy Product

[[Page 47398]]

paragraph does not approve messages or other information provided by 
the manufacturer for deviations to the requirements of the AD-mandated 
actions. The Airworthy Product paragraph only addresses the requirement 
to contact the manufacturer for corrective actions for the identified 
unsafe condition and does not cover deviations from other AD 
requirements. However, deviations to AD-required actions are addressed 
in 14 CFR 39.17, and anyone may request the approval for an alternative 
method of compliance to the AD-required actions using the procedures 
found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the 
Airworthy Product paragraph, we have changed the paragraph and retitled 
it ``Contacting the Manufacturer.'' This paragraph now clarifies that 
for any requirement in this proposed AD to obtain corrective actions 
from a manufacturer, the actions must be accomplished using a method 
approved by the FAA, EASA, or Airbus's EASA DOA.
    The Contacting the Manufacturer paragraph also clarifies that, if 
approved by the DOA, the approval must include the DOA-authorized 
signature. The DOA signature indicates that the data and information 
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer 
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or 
other information.
    This clarification does not remove flexibility previously afforded 
by the Airworthy Product paragraph. Consistent with long-standing FAA 
policy, such flexibility was never intended for required actions. This 
is also consistent with the recommendation of the Airworthiness 
Directive Implementation Aviation Rulemaking Committee to increase 
flexibility in complying with ADs by identifying those actions in 
manufacturers' service instructions that are ``Required for 
Compliance'' with ADs. We continue to work with manufacturers to 
implement this recommendation. But once we determine that an action is 
required, any deviation from the requirement must be approved as an 
alternative method of compliance.

Revisions to Notes in AD 2011-13-11, Amendment 39-16734 (76 FR 37241, 
June 27, 2011)

    We have removed Note 1 of AD 2011-13-11, Amendment 39-16734 (76 FR 
37241, June 27, 2011), and included that information in paragraph 
(g)(3) of this proposed AD.
    We have removed Note 2 of AD 2011-13-11, Amendment 39-16734 (76 FR 
37241, June 27, 2011), and included that information in paragraph (i) 
of this proposed AD.
    We have removed Note 3 of AD 2011-13-11, Amendment 39-16734 (76 FR 
37241, June 27, 2011), from this proposed AD. The note explained 
differences with the previous MCAI.

Change to AD 2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 
2013)

    We have moved the information specified in paragraph (l) of AD 
2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 2013), into 
paragraphs (j) and (l) of this proposed AD.

Costs of Compliance

    We estimate that this proposed AD affects 851 airplanes of U.S. 
registry.
    The actions that are required by AD 2011-13-11, Amendment 39-16734 
(76 FR 37241, June 27, 2011), and retained in this proposed AD take 
about 7 work-hours per product, per inspection cycle, at an average 
labor rate of $85 per work-hour. Based on these figures, the estimated 
cost of the actions that are required by AD 2011-13-11 is $595 per 
product.
    The actions that are required by AD 2013-16-09, Amendment 39-17547 
(78 FR 48286, August 8, 2013), and retained in this proposed AD take 
about 3 work-hours per product, per inspection cycle, at an average 
labor rate of $85 per work-hour. Based on these figures, the estimated 
cost of the actions that were required by AD 2013-16-09 is $255 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 
$17,140 for two actuators. Based on these figures, we estimate the cost 
of this proposed AD on U.S. operators to be $15,309,490, or $17,990 per 
product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

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:
0
a. Removing Airworthiness Directive (AD) 2011-13-11, Amendment 39-16734 
(76 FR 37241, June 27, 2011); and AD 2013-16-09, Amendment 39-17547 (78 
FR 48286, August 8, 2013); and
0
b. Adding the following new AD:

Airbus: Docket No. FAA-2014-0529; Directorate Identifier 2013-NM-
260-AD.

(a) Comments Due Date

    We must receive comments by September 29, 2014.

[[Page 47399]]

(b) Affected ADs

    This AD replaces AD 2011-13-11, Amendment 39-16734 (76 FR 37241, 
June 27, 2011); and AD 2013-16-09, Amendment 39-17547 (78 FR 48286, 
August 8, 2013).

(c) Applicability

    This AD applies to the Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1), (c)(2), (c)(3), and 
(c)(4) of this AD, all manufacturer serial numbers.
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
    (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by a determination that the inspection 
interval of the MLG door opening sequence must be reduced. We are 
issuing this AD to detect and correct deterioration of the damping 
ring and associated retaining ring of the MLG door actuator, which 
can sufficiently increase the friction inside the actuator to 
restrict opening of the MLG door by gravity, during operation of the 
landing gear alternate (free-fall) extension system. This condition 
could prevent the full extension and/or down-locking of the MLG, 
possibly resulting in MLG collapse during landing and consequent 
damage to the aeroplane and injury to occupants.

(f) Compliance

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

(g) Retained Repetitive Inspections/Replacement

    This paragraph restates the requirements of paragraph (g) of AD 
2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011), with a 
formatting change. At the time specified in paragraph (g)(1) or 
(g)(2) of this AD, as applicable: Do a general visual inspection of 
the operation of the MLG door opening sequence to determine if a 
defective actuator is installed by doing all the applicable actions, 
including replacing the door actuator, as applicable, specified in 
the Accomplishment Instructions of Airbus Service Bulletin A320-32-
1309, Revision 01, dated June 19, 2006. Do all applicable 
replacements before further flight. Repeat the inspection thereafter 
at intervals not to exceed 900 flight cycles. Accomplishing the 
actions before April 27, 2007 (the effective date of AD 2007-06-18, 
Amendment 39-14999 (72 FR 13681, March 23, 2007)), in accordance 
with Airbus Service Bulletin A320-32-1309, dated March 7, 2006, is 
acceptable for compliance with the corresponding requirements in 
this paragraph. Doing the inspection required by paragraph (l) of 
this AD terminates the requirements of this paragraph.
    (1) For airplanes on which a record of the total number of 
flight cycles on the MLG door actuator is available: Before the 
accumulation of 3,000 total flight cycles on the MLG door actuator, 
or within 800 flight cycles after April 27, 2007 (the effective date 
of AD 2007-06-18, Amendment 39-16734 (76 FR 37241, June 27, 2011)), 
whichever is later.
    (2) For airplanes on which a record of the total number of 
flight cycles on the MLG door actuator is not available: Within 800 
flight cycles after April 27, 2007 (the effective date of AD 2007-
06-18, Amendment 39-16734 (76 FR 37241, June 27, 2011)).
    (3) For the purposes of this AD, a general visual inspection is: 
``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
enhance visual access to all exposed surfaces in the inspection 
area. This level of inspection is made under normally available 
lighting conditions such as daylight, hangar lighting, flashlight, 
or droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''

(h) Retained Provision Regarding Reporting/Parts Return

    This paragraph restates the requirements of paragraph (h) of AD 
2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011), with no 
changes. Although the Accomplishment Instructions of Airbus Service 
Bulletin A320-32-1309, Revision 01, dated June 19, 2006, specify 
submitting certain information to the manufacturer and sending 
defective actuators back to the component manufacturer for 
investigation, this AD does not include those requirements.

(i) Retained Revision of the Airplane Flight Manual (AFM)

    This paragraph restates the requirements of paragraph (i) of AD 
2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011), with 
formatting changes. Within 14 days after July 12, 2011 (the 
effective date of AD 2011-13-11), revise the Emergency Procedure 
Section of the AFM to incorporate the information in figure 1 to 
paragraph (i) of this AD. This may be done by inserting a copy of 
this AD into the AFM. When a statement identical to that in figure 1 
to paragraph (i) of this AD has been included in the Emergency 
Procedure Section of the general revisions of the AFM, the general 
revisions may be inserted into the AFM, and the copy of this AD may 
be removed from the AFM.

           Figure 1 to Paragraph (i) of This AD--AFM Revision
------------------------------------------------------------------------
 
-------------------------------------------------------------------------
 If ECAM triggers the ``L/G GEAR NOT DOWNLOCKED'' warning apply
 the following procedure:
    Recycle landing gear.
 If unsuccessful after 2 min:
    Extend landing gear by gravity. Refer to AGN-32 L/G GRAVITY
     EXTENSION.
------------------------------------------------------------------------

(j) Retained Repetitive Checks

    This paragraph restates the requirements of paragraph (j) of AD 
2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011), with 
new optional actions. Within 14 days after July 12, 2011 (the 
effective date of AD 2011-13-11), or before the accumulation of 800 
total flight cycles, whichever occurs later, check the post flight 
report (PFR) for centralized fault display system (CFDS) messages 
triggered within the last 8 days, in accordance with paragraph 4.2.1 
of Airbus All Operators Telex (AOT) A320-32A1390, dated February 10, 
2011. Repeat the check thereafter at intervals not to exceed 8 days 
or 5 flight cycles, whichever occurs later. If done in accordance 
with a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA, the use of an alternative 
method to check the PFR for CFDS messages (e.g., AIRMAN) is 
acceptable in lieu of this check if the messages can be conclusively 
determined from that method. Repetitive inspections of the door 
opening sequence of the left-hand (LH) and right-hand (RH) doors of 
the MLG, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A320-32-1390, Revision 02, dated 
October 23, 2013, are an acceptable method of compliance for the 
actions required by this paragraph. Repetitive inspections of the 
door opening sequence of the LH and RH doors of the MLG of an 
airplane, as required by paragraph (p) of this AD, is an acceptable 
method to comply with the requirements of this paragraph.

(k) Retained On-Condition Inspection

    This paragraph restates the requirements of paragraph (k) of AD 
2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011), with 
new service information. If, during any check required by paragraph 
(j) of this AD, a pair of specific CFDS messages specified in 
paragraph 4.2.1 of Airbus AOT A320-32A1390, dated February 10, 2011, 
has been triggered by both landing gear control and indication units 
(LGCIU) for the same flight, before further flight, inspect the door 
opening sequence of the affected doors of the MLG for discrepancies 
(i.e., if any condition specified in steps (a) through (d) of 
paragraph 4.2.2 of Airbus AOT A320-32A1390, dated February 10, 2011, 
is not met; or if any door actuator fails any inspection check 
specified in Airbus Service Bulletin A320-32-1390,

[[Page 47400]]

Revision 02, dated October 23, 2013). Do the inspection in 
accordance with paragraph 4.2.2 of Airbus AOT A320-32A1390, dated 
February 10, 2011; or Airbus Service Bulletin A320-32-1390, Revision 
02, dated October 23, 2013. As of the effective date of this AD, use 
only Airbus Service Bulletin A320-32-1390, Revision 02, dated 
October 23, 2013, for the actions required by this paragraph.

(l) Retained Repetitive Inspections

    This paragraph restates the requirements of paragraph (l) of AD 
2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011), with 
new service information, new optional actions, and reduced 
compliance times. At the applicable time specified in paragraph 
(l)(1) or (l)(2) of this AD: Inspect the door opening sequence of 
the LH and RH doors of the MLG for discrepancies (i.e., if any 
condition specified in steps (a) through (d) of paragraph 4.2.2 of 
Airbus AOT A320-32A1390, dated February 10, 2011, is not met; or if 
any door actuator fails any inspection check specified in Airbus 
Service Bulletin A320-32-1390, Revision 02, dated October 23, 2013). 
Do the inspection in accordance with the instructions of paragraph 
4.2.2 of Airbus AOT A320-32A1390, dated February 10, 2011; or Airbus 
Service Bulletin A320-32-1390, Revision 02, dated October 23, 2013. 
As of the effective date of this AD, use only Airbus Service 
Bulletin A320-32-1390, Revision 02, dated October 23, 2013. Repeat 
the inspection within 8 days or 5 flight cycles after the effective 
date of this AD, whichever occurs later, without exceeding 425 
flight cycles since the most recent inspection; and thereafter 
repeat the inspection at intervals not to exceed 8 days or 5 flight 
cycles, whichever occurs later. In addition, whenever any airplane 
is not operated for a period longer than 8 days, do the inspection 
before further flight. Doing this inspection terminates the 
requirements of paragraph (g) of this AD. Repetitive inspections of 
the door opening sequence of the LH and RH doors of the MLG of an 
airplane, as required by paragraph (p) of this AD, is an acceptable 
method to comply with the requirements of this paragraph.
    (1) For airplanes on which an inspection required by paragraph 
(g) of this AD has been done as of July 12, 2011 (the effective date 
of AD 2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011)): 
Within 800 flight cycles after doing the most recent inspection 
required by paragraph (g) of this AD, or within 100 flight cycles 
after July 12, 2011 (the effective date of AD 2011-13-11, Amendment 
39-16734 (76 FR 37241, June 27, 2011)), whichever occurs later.
    (2) For airplanes on which an inspection required by paragraph 
(g) of this AD has not been done as of July 12, 2011 (the effective 
date of AD 2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 
2011)): Within 800 flight cycles after July 12, 2011.

(m) Retained Replacement

    This paragraph restates the requirements of paragraph (m) of AD 
2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011), with 
new service information. If any discrepancy (i.e., if any condition 
specified in steps (a) through (d) of paragraph 4.2.2 of Airbus AOT 
A320-32A1390, dated February 10, 2011, is not met; or if any door 
actuator fails any inspection check specified in Airbus Service 
Bulletin A320-32-1390, Revision 02, dated October 23, 2013) is found 
during any inspection required by paragraph (k) or (l) of this AD, 
before further flight, replace the affected MLG door actuator with a 
new MLG door actuator, in accordance with the instructions of Airbus 
AOT A320-32A1390, dated February 10, 2011; or Airbus Service 
Bulletin A320-32-1390, Revision 02, dated October 23, 2013. As of 
the effective date of this AD, use only Airbus Service Bulletin 
A320-32-1390, Revision 02, dated October 23, 2013, to do the actions 
required by this paragraph.

(n) Retained: No Terminating Action for Certain Requirements

    This paragraph restates the statement of paragraph (n) of AD 
2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011), with no 
changes. Replacement of the MLG door actuator as required by 
paragraph (m) of this AD is not a terminating action for the 
repetitive actions required by paragraphs (j) and (l) of this AD.

(o) Retained Configuration and Part Number Determination

    This paragraph restates the requirements of paragraph (g) of AD 
2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 2013), with 
no changes. At the later of the compliance times specified in 
paragraphs (o)(1) and (o)(2) of this AD: Do an inspection to 
determine the configuration (modification status) of the airplane 
and identify the part number of the LH and RH LGCIU and MLG door 
actuators. A review of the airplane delivery or maintenance records 
is acceptable for compliance with the requirements of this paragraph 
provided the airplane configuration and installed components can be 
conclusively determined from that review.
    (1) Prior to the accumulation of 800 total flight cycles since 
first flight of the airplane.
    (2) Within 14 days after August 23, 2013 (the effective date of 
AD 2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 2013)).

(p) Retained MLG Door Opening Sequence Repetitive Inspections

    This paragraph restates the requirements of paragraph (h) of AD 
2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 2013), with 
no changes. If, during the determination and identification required 
by paragraph (o) of this AD, the configuration of the airplane is 
determined to be post-Airbus modification 39303 or post-Airbus 
Service Bulletin A320-32-1409 (Interlink Communication ARINC 429 
installed), and both an LGCIU and a MLG door actuator are installed 
with a part number listed in table 1 to paragraph (p) of this AD: 
Except as provided by paragraph (s) of this AD, at the later of the 
compliance times specified in paragraphs (o)(1) and (o)(2) of this 
AD, and thereafter at intervals not to exceed 8 days or 5 flight 
cycles, whichever occurs later, do an inspection of the door opening 
sequence of the LH and RH MLG doors, in accordance with the 
instructions of Airbus Alert Operators Transmission (AOT) A32N001-
13, dated June 24, 2013.

                   Table 1 to Paragraph (p) of This AD
------------------------------------------------------------------------
                    Component name                        Part number
------------------------------------------------------------------------
LGCIU (LH and RH)....................................    80-178-02-88012
LGCIU (LH and RH)....................................    80-178-03-88013
MLG door actuator....................................          114122006
MLG door actuator....................................          114122007
MLG door actuator....................................          114122009
MLG door actuator....................................          114122010
MLG door actuator....................................          114122011
MLG door actuator....................................          114122012
------------------------------------------------------------------------

(q) Retained MLG Door Opening Sequence Corrective Action

    This paragraph restates the requirements of paragraph (i) of AD 
2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 2013), with 
no changes. If a slow door operation or restricted extension is 
found during any inspection required by paragraph (p) of this AD: 
Before further flight, replace the affected MLG door actuator with a 
new or serviceable actuator, in accordance with the instructions of 
Airbus AOT A32N001-13, dated June 24, 2013.

(r) Retained Terminating Action Limitation for Certain Actions

    This paragraph restates the requirements of paragraph (j) of AD 
2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 2013), with 
no changes. Replacement of a MLG door actuator, as required by 
paragraph (q) of this AD, does not constitute terminating action for 
the repetitive inspections required by paragraph (p) of this AD, 
unless MLG door actuators having P/N 114122014 are installed on both 
LH and RH sides, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A320-32-1407, dated May 14, 2013.

(s) Retained Repetitive Inspection Exception

    This paragraph restates the requirements of paragraph (k) of AD 
2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 2013), with 
no changes. Airplanes on which the LGCIU interlink is disconnected 
(Airbus modification 155522 applied in production, or modified in-
service in accordance with the instructions of Airbus AOT A32N001-
13, dated June 24, 2013), or on which MLG door actuators having P/N 
114122014 are installed on both LH and RH sides (Airbus modification 
153655 applied in production, or modified in-service in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-32-1407, dated May 14, 2013), are not required to do the 
actions required by paragraph (p) of this AD, provided that the 
airplane is not modified to a configuration as defined in paragraph 
(p) of this AD.

(t) New Replacement of MLG Door Actuator having P/N 114122012

    Within 12 months after the effective date of this AD: Replace 
each MLG door actuator having P/N 114122012 with a MLG door actuator 
having P/N 14122014, in accordance with the Accomplishment 
Instructions of

[[Page 47401]]

Airbus Service Bulletin A320-32-1407, dated May, 14 2013; or modify 
each actuator, including doing all applicable related investigative 
and corrective actions; in accordance with the Accomplishment 
Instructions of General Electric Service Bulletin 114122-32-105, 
Revision 1, dated March 26, 2013; except where General Electric 
Service Bulletin114122-32-105, Revision 1, dated March 26, 2013, 
specifies to contact the manufacturer, before further flight, repair 
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or the European Aviation 
Safety Agency (EASA); or Airbus's EASA Design Organization Approval 
(DOA). If approved by the DOA, the approval must include the DOA-
authorized signature.

(u) New Replacement of Certain Other MLG Door Actuators

    Within 24 months after the effective date of this AD: Replace 
each MLG door actuator having a part number listed in table 1 to 
paragraph (p) of this AD, except P/N 114122012, with a MLG door 
actuator having P/N 14122014, in accordance with Accomplishment 
Instructions of Airbus Service Bulletin A320-32-1407, dated May 14, 
2013; or modify each actuator, including doing all applicable 
related investigative and corrective actions; in accordance with the 
Accomplishment Instructions of General Electric Service Bulletin 
114122-32-105, Revision 1, dated March 26, 2013; except where 
General Electric Service Bulletin 114122-32-105, Revision 1, dated 
March 26, 2013, specifies to contact the manufacturer, before 
further flight, repair using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the European Aviation Safety Agency (EASA); or Airbus's EASA DOA. 
If approved by the DOA, the approval must include the DOA-authorized 
signature.

(v) New Terminating Action

    Modification of an airplane as required by paragraphs (t) and 
(u) of this AD, as applicable, constitutes terminating action for 
all repetitive actions (PFR monitoring checks and inspections) 
required by this AD for that airplane.

(w) New Conditional Terminating Action

    Replacement of a MLG door actuator as required by paragraphs (m) 
and (q) of this AD; or corrective actions as specified in Airbus AOT 
A320-32A1390, dated February 10, 2011; or replacement of a MLG door 
actuator as specified in Airbus Service Bulletin A320-32-1390, 
Revision 1, dated September 21, 2011; do not constitute terminating 
action for the repetitive inspections required by paragraphs (j), 
(l), and (p) of this AD, unless MLG door actuators having P/N 
114122014 are installed on both LH and RH sides, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-32-
1407, dated May 14, 2013.

(x) New Exception to AD Requirements

    An airplane on which MLG door actuators having P/N 114122014 are 
installed on both LH and RH sides (Airbus MOD 153655 applied in 
production, or modified in service as specified in Airbus Service 
Bulletin A320-32-1407, dated May, 14 2013; General Electric Service 
Bulletin 114122-32-105, dated January 17, 2013; or General Electric 
Service Bulletin 114122-32-105, Revision 1, dated March 26, 2013; is 
not affected by the requirements of paragraphs (j) through (u) of 
this AD, provided that no MLG door actuator with a part number in 
table 1 to paragraph (p) of this AD has been installed on that 
airplane since first flight, or since modification, as applicable.

(y) New Parts Installation Prohibitions

    (1) Except as specified in paragraph (y)(2) of this AD, as of 
the effective date of this AD, do not install on any airplane a MLG 
door actuator, having a part number listed in table 1 to paragraph 
(p) of this AD.
    (2) For an airplane subject to the requirements of paragraphs 
(t) and (u) of this AD, as applicable, do not install a MLG door 
actuator having a part number listed in table 1 to paragraph (p) of 
this AD after modification of the airplane.

(z) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraphs (k), (l), and (m) of this AD, if those actions were 
performed before the effective date of this AD using Airbus 
Mandatory Service Bulletin A320-32-1390, Revision 01, dated 
September 21, 2011, which is not incorporated by reference in this 
AD.
    (2) This paragraph provides credit for actions required by 
paragraphs (t) and (u) of this AD, if those actions were performed 
before the effective date of this AD using General Electric Service 
Bulletin 114122-32-105, dated January 17, 2013, which is not 
incorporated by reference in this AD.

(aa) 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: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; 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) Contacting the Manufacturer: Except as specified in 
paragraph (j) of this AD for the use of an alternative method to 
check the PFR for CFDS messages, for any requirement in this AD to 
obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (3) Previously Approved AMOCs: AMOCs approved previously for the 
ADs identified in paragraphs (aa)(3)(i) and (aa)(3)(ii) of this AD, 
are approved as AMOCs for the corresponding provisions of this AD.
    (i) AD 2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 
2011).
    (ii) AD 2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 
2013).

(bb) Special Flight Permits

    Special flight permits may be issued in accordance with sections 
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199) to operate the airplane to a location where the airplane 
can be modified (if the operator elects to do so), provided the MLG 
remains extended and locked, and that no MLG recycle is done.

(cc) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0288, dated December 6, 
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-2014-0529.
    (2) For Airbus service information identified in this AD, 
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email [email protected]; 
Internet http://www.airbus.com.
    (3) For General Electric service information identified in this 
AD, contact GE Aviation, Customer Support Center, 1 Neumann Way, 
Cincinnati, OH 45215; phone: 513-552-3272; email: 
[email protected]; Internet: http://www.geaviation.com.
    (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.

    Issued in Renton, Washington, on August 1, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-19157 Filed 8-12-14; 8:45 am]
BILLING CODE 4910-13-P