81 FR 12413 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 46 (March 9, 2016)

Page Range		12413-12419
FR Document		2016-04577
We are superseding 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 required 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 for discrepancies if certain messages are found, and corrective actions if necessary. AD 2013-16-09 required 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, and replacement of the MLG door actuator if necessary. AD 2013-16-09 also provided optional terminating action for the repetitive inspections. This new AD reduces the interval of the MLG door opening sequence inspection, requires replacing or modifying certain MLG door actuators, and also requires a flushing procedure to be performed when installing a new MLG door actuator. This AD was prompted by a determination that the interval of the MLG door opening sequence inspection 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 airplane and injury to occupants.
Federal Register, Volume 81 Issue 46 (Wednesday, March 9, 2016)
[Federal Register Volume 81, Number 46 (Wednesday, March 9, 2016)]
[Rules and Regulations]
[Pages 12413-12419]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-04577]


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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; 
Amendment 39-18420; AD 2016-05-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding 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 required 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 for discrepancies if certain messages are 
found, and corrective actions if necessary. AD 2013-16-09 required 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, and replacement of the MLG door actuator if necessary. AD 
2013-16-09 also provided optional terminating action for the repetitive 
inspections. This new AD reduces the interval of the MLG door opening 
sequence inspection, requires replacing or modifying certain MLG door 
actuators, and also requires a flushing procedure to be performed when 
installing a new MLG door actuator. This AD was prompted by a 
determination that the interval of the MLG door opening sequence 
inspection 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

[[Page 12414]]

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: This AD becomes effective April 13, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 13, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of August 
23, 2013 (78 FR 48286, August 8, 2013).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of July 
12, 2011 (76 FR 37241, June 27, 2011).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of April 
27, 2007 (72 FR 13681, March 23, 2007).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0529; or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    For Airbus service information identified in this final rule, 
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 Elec tric service information 
identified in this final rule, 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. It is also 
available on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2014-0529.

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: 

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to supersede AD 2011-13-11, Amendment 39-16734 (76 
FR 37241, June 27, 2011) (``AD 2011-13-11''); and AD 2013-16-09, 
Amendment 39-17547 (78 FR 48286, August 8, 2013) (``AD 2013-16-09''). 
AD 2011-13-11 and AD 2013-16-09 applied to all Airbus Model A318, A319, 
A320, and A321 series airplanes. The SNPRM published in the Federal 
Register on September 22, 2015 (80 FR 57122). We preceded the SNPRM 
with a notice of proposed rulemaking (NPRM) that published in the 
Federal Register on August 13, 2014 (79 FR 47395; corrected August 27, 
2014 (79 FR 51117)) (``the NPRM''). The NPRM was prompted by a 
determination that the interval of the MLG door opening sequence 
inspection must be reduced. The NPRM proposed to continue to require an 
amendment of the AFM; repetitive checks of specific CFDS messages; an 
inspection of the opening sequence of the MLG door for discrepancies if 
certain messages are found, and corrective actions if necessary; 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, and replacement of the MLG door actuator if necessary; 
and optional terminating action for the repetitive inspections. The 
SNPRM proposed to require a flushing procedure to be performed when 
installing a new MLG door actuator. 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 and consequent MLG collapse during landing 
and 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 Union, has issued EASA 
Airworthiness Directive 2014-0221, dated September 30, 2014 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on all Airbus Model A318, 
A319, A320, and A321 series airplanes. The MCAI states:

    Some operators reported slow operation of the main landing gear 
(MLG) door opening/closing sequence, leading to the generation of 
[electronic centralized aircraft monitor] 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 may 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 (freefall) 
extension system.
    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.
    [An EASA AD] was issued [and later revised] to require 
repetitive inspections of the opening sequence of the MLG door in 
order to identify the affected actuators, and to introduce as an 
optional terminating action Airbus production Modification (mod) 
38274 and associated [Airbus] 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.
    [An EASA AD], which superseded EASA AD 2006-0112R1 [http://ad.easa.europa.eu/blob/easa_ad_2006_0112_R1_superseded.pdf/AD_2006-0112R1_1], was issued [and later revised] to require 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 EASA AD 2011-0069R1 [http://ad.easa.europa.eu/blob/easa_ad_2011_0069_R1_superseded.pdf/AD_2011-0069R1_1] 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

[[Page 12415]]

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 (pre-Airbus SB A320-32-1407--pre-GE 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] 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 Airbus 
production mod 153655).
    Since those ADs (EASA AD 2011-0069R1 and EASA AD 2013-0132-E) 
were issued, analyses performed by Airbus have revealed that the MLG 
door opening sequence inspection interval needed to be reduced, and 
that the (previously optional) terminating action needed to be made 
mandatory.
    Prompted by these findings, EASA issued AD 2013-0288 [http://ad.easa.europa.eu/blob/easa_ad_2013_0288_superseded.pdf/AD_2013-0288_1], retaining the requirements of EASA AD 2011-0069R1 and EASA 
AD 2013-0132-E, which were superseded, but with reduced inspection 
intervals, and to require replacement or modification, as 
applicable, of the affected MLG door actuators as terminating action 
to the monitoring and repetitive checks and inspections.
    Following introduction of post-mod 153655 MLG door actuators on 
in-service aeroplanes, it has been observed that, in case the 
removed pre-mod MLG door actuator has internal damage, contamination 
of the hydraulic system could have occurred.
    This condition, if not detected and corrected, could result in 
performance degradation (damping degradation) of the post-mod MLG 
door actuator. Testing performed with a new actuator tested in 
heavily contaminated hydraulic system did not show abnormal 
hydraulic restriction/blockage. It is thus not requested to perform 
this ``flushing procedure'' on aircraft already retrofitted with 
std-14 actuators.
    In addition, since EASA AD 2013-0288 was issued, the applicable 
AFM was revised and repetitive checks of specific CFDS messages are 
no longer considered to be required, due to the reduced intervals 
required by EASA AD 2013-0288.
    For the reasons described above, this [EASA] AD partially 
retains the requirements of EASA AD 2013-0288, which is superseded, 
introduces improved wording for clarification and requires, in 
addition to the revised operational (AFM) procedure, hydraulic 
flushing prior to any installation of a post-mod MLG door actuator.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0529-0003.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received on the SNPRM. The Air Line 
Pilots Association International submitted two comments which supported 
the SNPRM.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
this AD as proposed except for minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
SNPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletins A320-32-1390, Revision 03, 
dated July 3, 2014; and A320-32-1407, Revision 01, dated July 3, 2014. 
Airbus has also issued A318/A319/A320/A321 Temporary Revision (TR) 
TR437, L/G--GEAR NOT DOWNLOCKED, Issue 1.0, dated May 23, 2014, to the 
Airbus A318/A319/A320/A321 AFM.
    Airbus Service Bulletin A320-32-1390, Revision 03, dated July 3, 
2014, describes procedures for inspecting the operation of the MLG door 
opening sequence to determine if an actuator is defective, flushing 
contamination from the landing gear extension and retraction system 
(LGERS), and replacing the door actuator if necessary.
    Airbus Service Bulletin A320-32-1407, Revision 01, dated July 3, 
2014, describes procedures for flushing contamination from the LGERS 
and installing new MLG door actuators.
    Airbus A318/A319/A320/A321 TR TR437, L/G--GEAR NOT DOWNLOCKED, 
Issue 1.0, dated May 23, 2014, to the AFM updates the procedure used 
for incomplete landing gear extension during approach.
    General Electric has issued Service Bulletin 114122-32-105, 
Revision 2, dated June 24, 2014, which describes procedures for 
conversion of a MLG door actuator and removal of unwanted material from 
the hydraulic fluid route.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 953 airplanes of U.S. registry.
    The actions required by AD 2011-13-11, and retained in this 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 were required by AD 2011-13-11 is 
$595 per product, per inspection cycle.
    The actions required by AD 2013-16-09, and retained in this 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, per inspection cycle.
    We also estimate that it will take about 19 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost about $17,140 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $17,873,515, or $18,755 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 3 work-hours, for a cost of $255 per product. We have no way 
of determining the number of aircraft that might need these actions.

Authority for This Rulemaking

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

[[Page 12416]]

Regulatory Findings

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

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=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 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive (AD) 2011-13-11, Amendment 39-16734 
(76 FR 37241, June 27, 2011) (``AD 2011-13-11''); and AD 2013-16-09, 
Amendment 39-17547 (78 FR 48286, August 8, 2013) (``AD 2013-16-09''); 
and
0
b. Adding the following new AD:

2016-05-02 Airbus: Amendment 39-18420. Docket No. FAA-2014-0529; 
Directorate Identifier 2013-NM-260-AD.

(a) Effective Date

    This AD becomes effective April 13, 2016.

(b) Affected ADs

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

(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 main landing gear (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 airplane and injury to 
occupants.

(f) Compliance

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

(g) Retained Repetitive Inspections/Replacement, With a Formatting 
Change

    This paragraph restates the requirements of paragraph (g) of AD 
2011-13-11, 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. 
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 39-14999 (72 FR 13681, March 23, 2007)), 
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 39-14999 (72 FR 13681, March 23, 2007)).
    (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, With No 
Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2011-13-11, 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), With 
Formatting Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2011-13-11, 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. Doing the actions required by 
paragraph (t) of this AD terminates the requirements of this 
paragraph.

           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 ABN-32 L/G GRAVITY
     EXTENSION.
------------------------------------------------------------------------


[[Page 12417]]

(j) Retained Repetitive Checks, With New Optional Actions and New 
Service Information

    This paragraph restates the requirements of paragraph (j) of AD 
2011-13-11, with new optional actions and new service information. 
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 Service Bulletin 
A320-32-1390, Revision 03, dated July 3, 2014, 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, With New Service Information and 
Revised Language for an Acronym

    This paragraph restates the requirements of paragraph (k) of AD 
2011-13-11, with new service information and revised langue for an 
acronym. 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 interface 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, Revision 03, dated July 3, 
2014). Do the inspection in accordance with paragraph 4.2.2 of 
Airbus AOT A320-32A1390, dated February 10, 2011; or the 
Accomplishment Instructions of Airbus Service Bulletin A320-32-1390, 
Revision 03, dated July 3, 2014. As of the effective date of this 
AD, use only Airbus Service Bulletin A320-32-1390, Revision 03, 
dated July 3, 2014, for the actions required by this paragraph.

(l) Retained Repetitive Inspections, With New Service Information, New 
Optional Actions, and Reduced Compliance Times

    This paragraph restates the requirements of paragraph (l) of AD 
2011-13-11, 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 
the Accomplishment Instructions of Airbus Service Bulletin A320-32-
1390, Revision 03, dated July 3, 2014). Do the inspection in 
accordance with the instructions of paragraph 4.2.2 of Airbus AOT 
A320-32A1390, dated February 10, 2011; or the Accomplishment 
Instructions of Airbus Service Bulletin A320-32-1390, Revision 03, 
dated July 3, 2014. As of the effective date of this AD, use only 
Airbus Service Bulletin A320-32-1390, Revision 03, dated July 3, 
2014, for the actions required by this paragraph. 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): 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, 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): Within 800 flight cycles after July 12, 
2011.

(m) Retained Replacement, With New Service Information

    This paragraph restates the requirements of paragraph (m) of AD 
2011-13-11, 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 
the Accomplishment Instructions of Airbus Service Bulletin A320-32-
1390, Revision 03, dated July 3, 2014) 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 03, dated July 3, 2014. As of the effective 
date of this AD, use only Airbus Service Bulletin A320-32-1390, 
Revision 03, dated July 3, 2014, to do the actions required by this 
paragraph.

(n) Retained Statement of No Terminating Action for Certain 
Requirements, With No Changes

    This paragraph restates the statement of paragraph (n) of AD 
2011-13-11, 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, With No 
Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2013-16-09, 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).

(p) Retained MLG Door Opening Sequence Repetitive Inspections, With No 
Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2013-16-09, 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 
figure 2 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.

       Figure 2 to Paragraph (p) of This AD--Affected Part Numbers
------------------------------------------------------------------------
                    Component name                          Part No.
------------------------------------------------------------------------
LGCIU (LH and RH)....................................    80-178-02-88012
                                                         80-178-03-88013
MLG door actuator....................................          114122006
                                                               114122007
                                                               114122009
                                                               114122010
                                                               114122011
                                                               114122012
------------------------------------------------------------------------


[[Page 12418]]

(q) Retained MLG Door Opening Sequence Corrective Action, With No 
Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2013-16-09, 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, With 
New Service Information

    This paragraph restates the requirements of paragraph (j) of AD 
2013-16-09, with new service information. 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; or Airbus Service 
Bulletin A320-32-1407, Revision 01, dated July 3, 2014. As of the 
effective date of this AD, use only Airbus Service Bulletin A320-32-
1407, Revision 01, dated July 3, 2014, for the actions required by 
this paragraph.

(s) Retained Repetitive Inspection Exception, With No Changes

    This paragraph restates the requirements of paragraph (k) of AD 
2013-16-09, 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 as 
described in Airbus Service Bulletin A320-32-1407), 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 Revision of the AFM

    Within 14 days after the effective date of this AD, revise the 
Emergency Procedure Section of the AFM to incorporate Airbus A318/
A319/A320/A321 Temporary Revision (TR) TR437, L/G--GEAR NOT 
DOWNLOCKED, Issue 1.0, dated May 23, 2014. When this TR has been 
included in general revisions of the AFM, the general revisions may 
be inserted in the AFM, provided the relevant information in the 
general revision is identical to that in this TR, and the copy of 
this TR may be removed from the AFM. Doing the action required by 
this paragraph terminates the actions required by paragraph (i) of 
this AD.

(u) 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 114122014, and flush the affected hydraulic system, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-32-1407, Revision 01, dated July 3, 2014; 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 2, dated June 24, 2014; except where General Electric 
Service Bulletin 114122-32-105, Revision 2, dated June 24, 2014, 
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).

(v) 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 figure 3 to 
paragraph (v) of this AD, except P/N 114122012, with a MLG door 
actuator having P/N 114122014, and flush the affected hydraulic 
system, in accordance with Accomplishment Instructions of Airbus 
Service Bulletin A320-32-1407, Revision 01, dated July 3, 2014; 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 2, dated June 24, 2014; except where General 
Electric Service Bulletin 114122-32-105, Revision 2, dated June 24, 
2014, 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 EASA; or 
Airbus's EASA DOA.

       Figure 3 to Paragraph (v) of This AD--Affected Part Numbers
------------------------------------------------------------------------
                    Component name                          Part No.
------------------------------------------------------------------------
MLG door actuator....................................          114122006
                                                               114122007
                                                               114122009
                                                               114122010
                                                               114122011
                                                               114122012
------------------------------------------------------------------------

(w) New Terminating Action

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

(x) 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 03, dated July 3, 2014; does 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, Revision 01, dated July 3, 2014.

(y) New Exception to AD Requirements

    (1) An airplane 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 as specified in Airbus 
Service Bulletin A320-32-1407, dated May 14, 2013; Airbus Service 
Bulletin A320-32-1407, Revision 01, dated July 3, 2014; 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; or General Electric Service Bulletin 114122-32-105, 
Revision 2, dated June 24, 2014); is not affected by the 
requirements of paragraphs (j) through (v) of this AD, provided that 
no MLG door actuator with a part number in figure 3 to paragraph (v) 
of this AD has been installed on that airplane since first flight, 
or since modification, as applicable.
    (2) An airplane in the configuration specified in paragraph 
(y)(1) of this AD, and with flight warning computers having P/N 
350E053021212 (H2F7) installed (Airbus Modification 153741 applied 
in production, or modified in service as specified in Airbus Service 
Bulletin A320-31-1414), is not affected by the requirement of 
paragraph (t) of this AD and, following modification, Airbus A318/
A319/A320/A321 TR TR437, L/G GEAR NOT DOWNLOCKED, Issue 1.0, dated 
May 23, 2014 (if inserted), may be removed from the AFM of that 
airplane.

(z) New Parts Installation Prohibitions

    (1) Except as specified in paragraph (z)(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 figure 3 to paragraph 
(v) of this AD.
    (2) For an airplane subject to the requirements of paragraphs 
(u) and (v) of this AD, as applicable, do not install a MLG door 
actuator having a part number listed in figure 3 to paragraph (v) of 
this AD after modification of the airplane.
    (3) Except as specified in paragraph (z)(4) of this AD, as of 
the effective date of this AD, do not install on any airplane a 
flight warning computer (FWC) having a part number listed in figure 
4 to paragraph (z) of this AD.
    (4) For an airplane subject to the requirements of paragraphs 
(u) and (v) of this AD, as applicable, do not install a FWC having a 
part number listed in figure 4 to paragraph (z) of this AD after 
modification of the airplane.

       Figure 4 to Paragraph (z) of This AD--Affected Part Numbers
------------------------------------------------------------------------
          Component name                          Part No.
------------------------------------------------------------------------
Flight warning computer..........  350E016187171 (C5)
                                   350E017238484 (H1D1)
                                   350E017248685 (H1D2)

[[Page 12419]]

 
                                   350E017251414 (H1E1)
                                   350E017271616 (H1E2)
                                   350E018291818 (H1E3CJ)
                                   350E018301919 (H1E3P)
                                   350E018312020 (H1E3Q)
                                   350E053020202 (H2E2)
                                   350E053020303 (H2E3)
                                   350E053020404 (H2E4)
                                   350E053020606 (H2F2)
                                   350E053020707 (H2F3)
                                   350E053021010 (H2F3P)
                                   350E053020808 (H2F4)
                                   350E053020909 (H2F5)
                                   350E053021111 (H2F6)
------------------------------------------------------------------------

(aa) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (g) of this AD, if those actions were performed before 
April 27, 2007 (the effective date of AD 2007-06-18), using Airbus 
Service Bulletin A320-32-1309, dated March 7, 2006. This service 
information is not incorporated by reference in this AD.
    (2) 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 Service 
Bulletin A320-32-1390, Revision 01, dated September 21, 2011; or 
Airbus Service Bulletin A320-32-1390, Revision 02, dated October 23, 
2013. This service information is not incorporated by reference in 
this AD.
    (3) This paragraph provides credit for actions required by 
paragraphs (u) and (v) 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; or General Electric 
Service Bulletin 114122-32-105, Revision 1, dated March 26, 2013. 
This service information is not incorporated by reference in this 
AD.

(bb) 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) Required for Compliance (RC): If any Airbus service 
information contains procedures or tests that are identified as RC, 
those procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.
    (3) Contacting the Manufacturer: As of the effective date of 
this AD, 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 EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (4) Previously Approved AMOCs: AMOCs approved previously for AD 
2011-13-11 and AD 2013-16-09 are approved as AMOCs for the 
corresponding provisions of this AD.

(cc) 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.

(dd) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0221, dated September 30, 
2014, 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) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (ee)(7), (ee)(8), and (ee)(9) of this AD.

(ee) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
April 13, 2016.
    (i) Airbus A318/A319/A320/A321 Temporary Revision TR437, L/G--
GEAR NOT DOWNLOCKED, Issue 1.0, dated May 23, 2014, to the Airbus 
A318/A319/A320/A321 Airplane Flight Manual.
    (ii) Airbus Service Bulletin A320-32-1390, Revision 03, dated 
July 3, 2014.
    (iii) Airbus Service Bulletin A320-32-1407, Revision 01, dated 
July 3, 2014.
    (iv) General Electric Service Bulletin 114122-32-105, Revision 
2, dated June 24, 2014.
    (4) The following service information was approved for IBR on 
August 23, 2013 (78 FR 48286, August 8, 2013).
    (i) Airbus Alert Operators Transmission A32N001-13, dated June 
24, 2013.
    (ii) Reserved.
    (5) The following service information was approved for IBR on 
July 12, 2011 (76 FR 37241, June 27, 2011).
    (i) Airbus All Operators Telex A320-32A1390, dated February 10, 
2011.
    (ii) Reserved.
    (6) The following service information was approved for IBR on 
April 27, 2007 (72 FR 13681, March 23, 2007).
    (i) Airbus Service Bulletin A320-32-1309, Revision 01, dated 
June 19, 2006.
    (ii) Reserved.
    (7) 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.
    (8) 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.
    (9) 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.
    (10) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on February 18, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-04577 Filed 3-8-16; 8:45 am]
 BILLING CODE 4910-13-P
Federal Register / Vol. 81, No. 46 / Wednesday, March 9, 2016 / Rules and Regulations 12413

(3) For Airbus Model A310 series (EASA); or Airbus’s EASA Design www.archives.gov/federal-register/cfr/ibr-
airplanes: Airbus Service Bulletin A310–53– Organization Approval (DOA). If approved by locations.html.
2136, dated February 14, 2014. the DOA, the approval must include the
Issued in Renton, Washington, on February
DOA-authorized signature.
(j) Corrective Actions 23, 2016.
(3) Reporting Requirements: A federal
If, during any inspection required by agency may not conduct or sponsor, and a Dionne Palermo,
paragraph (h) of this AD, any cracking is person is not required to respond to, nor Acting Manager, Transport Airplane
found, before further flight, replace the shall a person be subject to a penalty for Directorate, Aircraft Certification Service.
affected THS support strut(s) with failure to comply with a collection of [FR Doc. 2016–04545 Filed 3–8–16; 8:45 am]
serviceable struts and install clamps on each information subject to the requirements of BILLING CODE 4910–13–P
strut end, in accordance with the the Paperwork Reduction Act unless that
Accomplishment Instructions of the collection of information displays a current
applicable service bulletin identified in valid OMB Control Number. The OMB
paragraphs (g)(1) through (g)(3) of this AD. Control Number for this information
DEPARTMENT OF TRANSPORTATION
(k) Clarification collection is 2120–0056. Public reporting for
this collection of information is estimated to
Federal Aviation Administration
Installation of reinforcing clamps as be approximately 5 minutes per response,
required by paragraph (i) of this AD, and the including the time for reviewing instructions, 14 CFR Part 39
replacement of support struts and/or the completing and reviewing the collection of
installation of clamps as required by [Docket No. FAA–2014–0529; Directorate
information. All responses to this collection
paragraph (j) of this AD, do not constitute Identifier 2013–NM–260–AD; Amendment
of information are mandatory. Comments
terminating action for the repetitive 39–18420; AD 2016–05–02]
concerning the accuracy of this burden and
inspections required by paragraph (h) of this suggestions for reducing the burden should
AD. RIN 2120–AA64
be directed to the FAA at 800 Independence
(l) Reporting Ave. SW., Washington, DC 20591, Attn: Airworthiness Directives; Airbus
At the applicable time specified in Information Collection Clearance Officer, Airplanes
paragraphs (l)(1) and (l)(2) of this AD: After AES–200.
accomplishment of any inspection required (n) Related Information
AGENCY: Federal Aviation
by paragraph (g) of this AD, report all Administration (FAA), Department of
Refer to Mandatory Continuing Transportation (DOT).
inspection results to Airbus, including no
Airworthiness Information (MCAI) EASA
findings, in accordance with the ACTION: Final rule.
Airworthiness Directive 2014–0164, dated
Accomplishment Instructions of the
July 11, 2014, for related information. This
applicable service bulletins specified in SUMMARY: We are superseding
MCAI may be found in the AD docket on the
paragraphs (g)(1) through (g)(3) of this AD. Airworthiness Directive (AD) 2011–13–
(1) If the inspection was done on or after Internet at http://www.regulations.gov/
#!documentDetail;D=FAA-2015-0243-0002. 11 and AD 2013–16–09 for all Airbus
the effective date of this AD: Submit the
report within 30 days after the inspection. Model A318, A319, A320, and A321
(o) Material Incorporated by Reference
(2) If the inspection was done before the series airplanes. AD 2011–13–11
(1) The Director of the Federal Register required an amendment of the airplane
effective date of this AD: Submit the report
approved the incorporation by reference
within 30 days after the effective date of this flight manual (AFM), repetitive checks
(IBR) of the service information listed in this
AD. of specific centralized fault display
paragraph under 5 U.S.C. 552(a) and 1 CFR
(m) Other FAA AD Provisions part 51. system (CFDS) messages, an inspection
(2) You must use this service information of the opening sequence of the main
The following provisions also apply to this
AD: as applicable to do the actions required by landing gear (MLG) door for
(1) Alternative Methods of Compliance this AD, unless this AD specifies otherwise. discrepancies if certain messages are
(AMOCs): The Manager, International (i) Airbus Service Bulletin A300–53–0394, found, and corrective actions if
Branch, ANM–116, Transport Airplane dated February 14, 2014. necessary. AD 2013–16–09 required an
Directorate, FAA, has the authority to (ii) Airbus Service Bulletin A300–53–0395, inspection to determine airplane
approve AMOCs for this AD, if requested dated February 14, 2014.
configuration and part numbers of the
using the procedures found in 14 CFR 39.19. (iii) Airbus Service Bulletin A300–53–
6172, dated February 14, 2014. landing gear control interface unit and
In accordance with 14 CFR 39.19, send your MLG door actuators; and, for affected
request to your principal inspector or local (iv) Airbus Service Bulletin A300–53–
Flight Standards District Office, as 6174, dated February 14, 2014. airplanes, repetitive inspections of the
appropriate. If sending information directly (v) Airbus Service Bulletin A310–53–2136, opening sequence of the MLG door, and
to the International Branch, send it to ATTN: dated February 14, 2014. replacement of the MLG door actuator if
Dan Rodina, Aerospace Engineer, (vi) Airbus Service Bulletin A310–53– necessary. AD 2013–16–09 also
International Branch, ANM–116, Transport 2137, dated February 14, 2014. provided optional terminating action for
Airplane Directorate, FAA, 1601 Lind (3) For service information identified in the repetitive inspections. This new AD
Avenue SW., Renton, WA 98057–3356; this AD, contact Airbus SAS, Airworthiness
reduces the interval of the MLG door
telephone 425–227–2125; fax 425–227–1149. Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; opening sequence inspection, requires
Information may be emailed to: 9-ANM-116-
AMOC-REQUESTS@faa.gov. Before using telephone +33 5 61 93 36 96; fax +33 5 61 replacing or modifying certain MLG
any approved AMOC, notify your appropriate 93 44 51; email account.airworth-eas@ door actuators, and also requires a
principal inspector, or lacking a principal airbus.com; Internet http://www.airbus.com. flushing procedure to be performed
inspector, the manager of the local flight (4) You may view this service information when installing a new MLG door
standards district office/certificate holding at the FAA, Transport Airplane Directorate, actuator. This AD was prompted by a
district office. The AMOC approval letter 1601 Lind Avenue SW., Renton, WA. For determination that the interval of the
must specifically reference this AD. information on the availability of this MLG door opening sequence inspection
Lhorne on DSK5TPTVN1PROD with RULES

(2) Contacting the Manufacturer: For any material at the FAA, call 425–227–1221.
must be reduced. We are issuing this AD
requirement in this AD to obtain corrective (5) You may view this service information
actions from a manufacturer, the action must that is incorporated by reference at the to detect and correct deterioration of the
be accomplished using a method approved National Archives and Records damping ring and associated retaining
by the Manager, International Branch, ANM– Administration (NARA). For information on ring of the MLG door actuator, which
116, Transport Airplane Directorate, FAA; or the availability of this material at NARA, call can sufficiently increase the friction
the European Aviation Safety Agency 202–741–6030, or go to: http:// inside the actuator to restrict opening of

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Federal Register / Vol. 81, No. 46 / Wednesday, March 9, 2016 / Rules and Regulations 12415

not be generated and as a result, repetitive for clarification and requires, in addition to door actuator and removal of unwanted
checks of messages are not effective for the revised operational (AFM) procedure, material from the hydraulic fluid route.
aeroplanes fitted with landing gear control hydraulic flushing prior to any installation of
interface unit (LGCIU) interlink a post-mod MLG door actuator.
This service information is reasonably
communication ARINC 429 (applied in available because the interested parties
production through Airbus mod 39303, or in You may examine the MCAI in the have access to it through their normal
service through Airbus SB A320–32–1409), AD docket on the Internet at http:// course of business or by the means
in combination with LGCIUs 80–178–02– www.regulations.gov/ identified in the ADDRESSES section.
88012 or 80–178–03–88013 in both positions #!documentDetail;D=FAA-2014-0529-
and at least one MLG door actuator pre-mod 0003. Costs of Compliance
153655 (pre-Airbus SB A320–32–1407—pre-
GE SB 114122–32–105) installed. Comments We estimate that this AD affects 953
Prompted by these findings, EASA issued airplanes of U.S. registry.
We gave the public the opportunity to
Emergency AD 2013–0132–E [http:// participate in developing this AD. We The actions required by AD 2011–13–
ad.easa.europa.eu/blob/ 11, and retained in this AD, take about
easa_ad_2013_0132_E_superseded.pdf/
considered the comments received on
the SNPRM. The Air Line Pilots 7 work-hours per product, per
EAD_2013-0132-E_1] [which corresponds to inspection cycle, at an average labor rate
FAA AD 2013–16–09] to require Association International submitted two
comments which supported the of $85 per work-hour. Based on these
identification of the affected aeroplanes to
establish the configuration and, for those SNPRM. figures, the estimated cost of the actions
aeroplanes, repetitive inspections of the that were required by AD 2011–13–11 is
opening sequence of the MLG door actuator Conclusion $595 per product, per inspection cycle.
and, depending on findings, replacement of We reviewed the available data, The actions required by AD 2013–16–
the MLG door actuator. That [EASA] AD also including the comments received, and 09, and retained in this AD, take about
provided an optional terminating action by determined that air safety and the 3 work-hours per product, per
disconnection of the interlink for certain
public interest require adopting this AD inspection cycle, at an average labor rate
LGCIUs, or in-service modification of the
aeroplane through Airbus SB A320–32–1407 as proposed except for minor editorial of $85 per work-hour. Based on these
(equivalent to Airbus production mod changes. We have determined that these figures, the estimated cost of the actions
153655). minor changes: that were required by AD 2013–16–09 is
Since those ADs (EASA AD 2011–0069R1 • Are consistent with the intent that $255 per product, per inspection cycle.
and EASA AD 2013–0132–E) were issued, was proposed in the SNPRM for We also estimate that it will take
analyses performed by Airbus have revealed correcting the unsafe condition; and about 19 work-hours per product to
that the MLG door opening sequence • Do not add any additional burden comply with the basic requirements of
inspection interval needed to be reduced, upon the public than was already
and that the (previously optional)
this AD. The average labor rate is $85
proposed in the SNPRM. per work-hour. Required parts will cost
terminating action needed to be made
mandatory. Related Service Information Under 1 about $17,140 per product. Based on
Prompted by these findings, EASA issued CFR Part 51 these figures, we estimate the cost of
AD 2013–0288 [http://ad.easa.europa.eu/ this AD on U.S. operators to be
blob/easa_ad_2013_0288_superseded.pdf/ Airbus has issued Service Bulletins $17,873,515, or $18,755 per product.
AD_2013-0288_1], retaining the requirements A320–32–1390, Revision 03, dated July
3, 2014; and A320–32–1407, Revision In addition, we estimate that any
of EASA AD 2011–0069R1 and EASA AD
2013–0132–E, which were superseded, but 01, dated July 3, 2014. Airbus has also necessary follow-on actions will take
with reduced inspection intervals, and to issued A318/A319/A320/A321 about 3 work-hours, for a cost of $255
require replacement or modification, as Temporary Revision (TR) TR437, L/G— per product. We have no way of
applicable, of the affected MLG door GEAR NOT DOWNLOCKED, Issue 1.0, determining the number of aircraft that
actuators as terminating action to the
dated May 23, 2014, to the Airbus A318/ might need these actions.
monitoring and repetitive checks and
inspections. A319/A320/A321 AFM. Authority for This Rulemaking
Following introduction of post-mod Airbus Service Bulletin A320–32–
1390, Revision 03, dated July 3, 2014, Title 49 of the United States Code
153655 MLG door actuators on in-service
describes procedures for inspecting the specifies the FAA’s authority to issue
aeroplanes, it has been observed that, in case
the removed pre-mod MLG door actuator has operation of the MLG door opening rules on aviation safety. Subtitle I,
internal damage, contamination of the sequence to determine if an actuator is section 106, describes the authority of
hydraulic system could have occurred. defective, flushing contamination from the FAA Administrator. ‘‘Subtitle VII:
This condition, if not detected and the landing gear extension and Aviation Programs,’’ describes in more
corrected, could result in performance retraction system (LGERS), and detail the scope of the Agency’s
degradation (damping degradation) of the authority.
post-mod MLG door actuator. Testing
replacing the door actuator if necessary.
Airbus Service Bulletin A320–32– We are issuing this rulemaking under
performed with a new actuator tested in
heavily contaminated hydraulic system did 1407, Revision 01, dated July 3, 2014, the authority described in ‘‘Subtitle VII,
not show abnormal hydraulic restriction/ describes procedures for flushing Part A, Subpart III, Section 44701:
blockage. It is thus not requested to perform contamination from the LGERS and General requirements.’’ Under that
this ‘‘flushing procedure’’ on aircraft already installing new MLG door actuators. section, Congress charges the FAA with
retrofitted with std-14 actuators. Airbus A318/A319/A320/A321 TR promoting safe flight of civil aircraft in
In addition, since EASA AD 2013–0288 TR437, L/G—GEAR NOT air commerce by prescribing regulations
was issued, the applicable AFM was revised DOWNLOCKED, Issue 1.0, dated May for practices, methods, and procedures
and repetitive checks of specific CFDS 23, 2014, to the AFM updates the the Administrator finds necessary for
Lhorne on DSK5TPTVN1PROD with RULES

messages are no longer considered to be
procedure used for incomplete landing safety in air commerce. This regulation
required, due to the reduced intervals
required by EASA AD 2013–0288. gear extension during approach. is within the scope of that authority
For the reasons described above, this General Electric has issued Service because it addresses an unsafe condition
[EASA] AD partially retains the requirements Bulletin 114122–32–105, Revision 2, that is likely to exist or develop on
of EASA AD 2013–0288, which is dated June 24, 2014, which describes products identified in this rulemaking
superseded, introduces improved wording procedures for conversion of a MLG action.

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(j) Retained Repetitive Checks, With New service information, new optional actions, 32–1390, Revision 03, dated July 3, 2014, to
Optional Actions and New Service and reduced compliance times. At the do the actions required by this paragraph.
Information applicable time specified in paragraph (l)(1)
or (l)(2) of this AD: Inspect the door opening (n) Retained Statement of No Terminating
This paragraph restates the requirements of Action for Certain Requirements, With No
paragraph (j) of AD 2011–13–11, with new sequence of the LH and RH doors of the MLG
for discrepancies (i.e., if any condition Changes
optional actions and new service
information. Within 14 days after July 12, specified in steps (a) through (d) of paragraph This paragraph restates the statement of
2011 (the effective date of AD 2011–13–11), 4.2.2 of Airbus AOT A320–32A1390, dated paragraph (n) of AD 2011–13–11, with no
or before the accumulation of 800 total flight February 10, 2011, is not met; or if any door changes. Replacement of the MLG door
cycles, whichever occurs later, check the post actuator fails any inspection check specified actuator as required by paragraph (m) of this
flight report (PFR) for centralized fault in the Accomplishment Instructions of AD is not a terminating action for the
display system (CFDS) messages triggered Airbus Service Bulletin A320–32–1390, repetitive actions required by paragraphs (j)
within the last 8 days, in accordance with Revision 03, dated July 3, 2014). Do the
and (l) of this AD.
paragraph 4.2.1 of Airbus All Operators Telex inspection in accordance with the
(AOT) A320–32A1390, dated February 10, instructions of paragraph 4.2.2 of Airbus (o) Retained Configuration and Part Number
2011. Repeat the check thereafter at intervals AOT A320–32A1390, dated February 10, Determination, With No Changes
not to exceed 8 days or 5 flight cycles, 2011; or the Accomplishment Instructions of
This paragraph restates the requirements of
whichever occurs later. If done in accordance Airbus Service Bulletin A320–32–1390,
paragraph (g) of AD 2013–16–09, with no
with a method approved by the Manager, Revision 03, dated July 3, 2014. As of the
effective date of this AD, use only Airbus changes. At the later of the compliance times
International Branch, ANM–116, Transport specified in paragraphs (o)(1) and (o)(2) of
Airplane Directorate, FAA, the use of an Service Bulletin A320–32–1390, Revision 03,
dated July 3, 2014, for the actions required this AD: Do an inspection to determine the
alternative method to check the PFR for
by this paragraph. Repeat the inspection configuration (modification status) of the
CFDS messages (e.g., AIRMAN) is acceptable
in lieu of this check if the messages can be within 8 days or 5 flight cycles after the airplane and identify the part number of the
conclusively determined from that method. effective date of this AD, whichever occurs LH and RH LGCIU and MLG door actuators.
Repetitive inspections of the door opening later, without exceeding 425 flight cycles A review of the airplane delivery or
sequence of the left-hand (LH) and right-hand since the most recent inspection; and maintenance records is acceptable for
(RH) doors of the MLG, in accordance with thereafter repeat the inspection at intervals compliance with the requirements of this
the Accomplishment Instructions of Airbus not to exceed 8 days or 5 flight cycles, paragraph provided the airplane
Service Bulletin A320–32–1390, Revision 03, whichever occurs later. In addition, configuration and installed components can
dated July 3, 2014, are an acceptable method whenever any airplane is not operated for a be conclusively determined from that review.
of compliance for the actions required by this period longer than 8 days, do the inspection (1) Prior to the accumulation of 800 total
paragraph. Repetitive inspections of the door before further flight. Doing this inspection flight cycles since first flight of the airplane.
opening sequence of the LH and RH doors of terminates the requirements of paragraph (g) (2) Within 14 days after August 23, 2013
the MLG of an airplane, as required by of this AD. Repetitive inspections of the door (the effective date of AD 2013–16–09).
paragraph (p) of this AD, is an acceptable opening sequence of the LH and RH doors of
method to comply with the requirements of the MLG of an airplane, as required by (p) Retained MLG Door Opening Sequence
this paragraph. paragraph (p) of this AD, is an acceptable Repetitive Inspections, With No Changes
method to comply with the requirements of This paragraph restates the requirements of
(k) Retained On-Condition Inspection, With this paragraph.
New Service Information and Revised paragraph (h) of AD 2013–16–09, with no
(1) For airplanes on which an inspection
Language for an Acronym changes. If, during the determination and
required by paragraph (g) of this AD has been
This paragraph restates the requirements of done as of July 12, 2011 (the effective date identification required by paragraph (o) of
paragraph (k) of AD 2011–13–11, with new of AD 2011–13–11): Within 800 flight cycles this AD, the configuration of the airplane is
service information and revised langue for an after doing the most recent inspection determined to be post-Airbus Modification
acronym. If, during any check required by required by paragraph (g) of this AD, or 39303 or post-Airbus Service Bulletin A320–
paragraph (j) of this AD, a pair of specific within 100 flight cycles after July 12, 2011, 32–1409 (Interlink Communication ARINC
CFDS messages specified in paragraph 4.2.1 whichever occurs later. 429 installed), and both an LGCIU and a MLG
of Airbus AOT A320–32A1390, dated (2) For airplanes on which an inspection door actuator are installed with a part
February 10, 2011, has been triggered by both required by paragraph (g) of this AD has not number listed in figure 2 to paragraph (p) of
landing gear control and interface units been done as of July 12, 2011 (the effective this AD: Except as provided by paragraph (s)
(LGCIU) for the same flight, before further date of AD 2011–13–11): Within 800 flight of this AD, at the later of the compliance
flight, inspect the door opening sequence of cycles after July 12, 2011. times specified in paragraphs (o)(1) and (o)(2)
the affected doors of the MLG for of this AD, and thereafter at intervals not to
(m) Retained Replacement, With New
discrepancies (i.e., if any condition specified exceed 8 days or 5 flight cycles, whichever
Service Information
in steps (a) through (d) of paragraph 4.2.2 of occurs later, do an inspection of the door
Airbus AOT A320–32A1390, dated February This paragraph restates the requirements of opening sequence of the LH and RH MLG
10, 2011, is not met; or if any door actuator paragraph (m) of AD 2011–13–11, with new doors, in accordance with the instructions of
fails any inspection check specified in Airbus service information. If any discrepancy (i.e., Airbus Alert Operators Transmission (AOT)
Service Bulletin A320–32–1390, Revision 03, if any condition specified in steps (a) through
A32N001–13, dated June 24, 2013.
dated July 3, 2014). Do the inspection in (d) of paragraph 4.2.2 of Airbus AOT A320–
accordance with paragraph 4.2.2 of Airbus 32A1390, dated February 10, 2011, is not
AOT A320–32A1390, dated February 10, met; or if any door actuator fails any FIGURE 2 TO PARAGRAPH (p) OF THIS
2011; or the Accomplishment Instructions of inspection check specified in the AD—AFFECTED PART NUMBERS
Airbus Service Bulletin A320–32–1390, Accomplishment Instructions of Airbus
Revision 03, dated July 3, 2014. As of the Service Bulletin A320–32–1390, Revision 03, Component name Part No.
effective date of this AD, use only Airbus dated July 3, 2014) is found during any
Service Bulletin A320–32–1390, Revision 03, inspection required by paragraph (k) or (l) of LGCIU (LH and RH) ....... 80–178–02–88012
dated July 3, 2014, for the actions required this AD, before further flight, replace the 80–178–03–88013
Lhorne on DSK5TPTVN1PROD with RULES

by this paragraph. affected MLG door actuator with a new MLG MLG door actuator ......... 114122006
door actuator, in accordance with the 114122007
(l) Retained Repetitive Inspections, With instructions of Airbus AOT A320–32A1390, 114122009
New Service Information, New Optional dated February 10, 2011; or Airbus Service
Actions, and Reduced Compliance Times 114122010
Bulletin A320–32–1390, Revision 03, dated 114122011
This paragraph restates the requirements of July 3, 2014. As of the effective date of this 114122012
paragraph (l) of AD 2011–13–11, with new AD, use only Airbus Service Bulletin A320–

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12418 Federal Register / Vol. 81, No. 46 / Wednesday, March 9, 2016 / Rules and Regulations

(q) Retained MLG Door Opening Sequence the affected hydraulic system, in accordance by paragraphs (j), (l), and (p) of this AD,
Corrective Action, With No Changes with the Accomplishment Instructions of unless MLG door actuators having P/N
This paragraph restates the requirements of Airbus Service Bulletin A320–32–1407, 114122014 are installed on both LH and RH
paragraph (i) of AD 2013–16–09, with no Revision 01, dated July 3, 2014; or modify sides, in accordance with the
changes. If a slow door operation or restricted each actuator, including doing all applicable Accomplishment Instructions of Airbus
extension is found during any inspection related investigative and corrective actions, Service Bulletin A320–32–1407, Revision 01,
required by paragraph (p) of this AD: Before in accordance with the Accomplishment dated July 3, 2014.
further flight, replace the affected MLG door Instructions of General Electric Service (y) New Exception to AD Requirements
actuator with a new or serviceable actuator, Bulletin 114122–32–105, Revision 2, dated
June 24, 2014; except where General Electric (1) An airplane on which MLG door
in accordance with the instructions of Airbus
Service Bulletin 114122–32–105, Revision 2, actuators having P/N 114122014 are installed
AOT A32N001–13, dated June 24, 2013. on both LH and RH sides (Airbus
dated June 24, 2014, specifies to contact the
(r) Retained Terminating Action Limitation manufacturer, before further flight, repair Modification 153655 applied in production,
for Certain Actions, With New Service using a method approved by the Manager, or modified in service as specified in Airbus
Information International Branch, ANM–116, Transport Service Bulletin A320–32–1407, dated May
Airplane Directorate, FAA; or the European 14, 2013; Airbus Service Bulletin A320–32–
This paragraph restates the requirements of
Aviation Safety Agency (EASA); or Airbus’s 1407, Revision 01, dated July 3, 2014;
paragraph (j) of AD 2013–16–09, with new General Electric Service Bulletin 114122–32–
service information. Replacement of a MLG EASA Design Organization Approval (DOA).
105, dated January 17, 2013; or General
door actuator, as required by paragraph (q) of (v) New Replacement of Certain Other MLG Electric Service Bulletin 114122–32–105,
this AD, does not constitute terminating Door Actuators Revision 1, dated March 26, 2013; or General
action for the repetitive inspections required Electric Service Bulletin 114122–32–105,
by paragraph (p) of this AD, unless MLG door Within 24 months after the effective date
of this AD: Replace each MLG door actuator Revision 2, dated June 24, 2014); is not
actuators having P/N 114122014 are installed affected by the requirements of paragraphs (j)
on both LH and RH sides, in accordance with having a part number listed in figure 3 to
through (v) of this AD, provided that no MLG
the Accomplishment Instructions of Airbus paragraph (v) of this AD, except P/N
door actuator with a part number in figure 3
Service Bulletin A320–32–1407, dated May 114122012, with a MLG door actuator having
to paragraph (v) of this AD has been installed
14, 2013; or Airbus Service Bulletin A320– P/N 114122014, and flush the affected
on that airplane since first flight, or since
32–1407, Revision 01, dated July 3, 2014. As hydraulic system, in accordance with modification, as applicable.
of the effective date of this AD, use only Accomplishment Instructions of Airbus (2) An airplane in the configuration
Airbus Service Bulletin A320–32–1407, Service Bulletin A320–32–1407, Revision 01, specified in paragraph (y)(1) of this AD, and
Revision 01, dated July 3, 2014, for the dated July 3, 2014; or modify each actuator, with flight warning computers having P/N
actions required by this paragraph. including doing all applicable related 350E053021212 (H2F7) installed (Airbus
investigative and corrective actions, in Modification 153741 applied in production,
(s) Retained Repetitive Inspection Exception, accordance with the Accomplishment or modified in service as specified in Airbus
With No Changes Instructions of General Electric Service Service Bulletin A320–31–1414), is not
This paragraph restates the requirements of Bulletin 114122–32–105, Revision 2, dated affected by the requirement of paragraph (t)
paragraph (k) of AD 2013–16–09, with no June 24, 2014; except where General Electric of this AD and, following modification,
changes. Airplanes on which the LGCIU Service Bulletin 114122–32–105, Revision 2, Airbus A318/A319/A320/A321 TR TR437, L/
interlink is disconnected (Airbus dated June 24, 2014, specifies to contact the G GEAR NOT DOWNLOCKED, Issue 1.0,
Modification 155522 applied in production, manufacturer, before further flight, repair dated May 23, 2014 (if inserted), may be
or modified in-service in accordance with the using a method approved by the Manager, removed from the AFM of that airplane.
instructions of Airbus AOT A32N001–13, International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the EASA; or (z) New Parts Installation Prohibitions
dated June 24, 2013), or on which MLG door
actuators having P/N 114122014 are installed Airbus’s EASA DOA. (1) Except as specified in paragraph (z)(2)
on both LH and RH sides (Airbus of this AD, as of the effective date of this AD,
Modification 153655 applied in production, FIGURE 3 TO PARAGRAPH (v) OF THIS do not install on any airplane a MLG door
or modified in-service as described in Airbus actuator having a part number listed in figure
AD—AFFECTED PART NUMBERS 3 to paragraph (v) of this AD.
Service Bulletin A320–32–1407), are not
required to do the actions required by (2) For an airplane subject to the
Component name Part No. requirements of paragraphs (u) and (v) of this
paragraph (p) of this AD, provided that the
airplane is not modified to a configuration as AD, as applicable, do not install a MLG door
MLG door actuator ......... 114122006 actuator having a part number listed in figure
defined in paragraph (p) of this AD. 114122007 3 to paragraph (v) of this AD after
(t) New Revision of the AFM 114122009 modification of the airplane.
114122010 (3) Except as specified in paragraph (z)(4)
Within 14 days after the effective date of
114122011 of this AD, as of the effective date of this AD,
this AD, revise the Emergency Procedure
114122012 do not install on any airplane a flight
Section of the AFM to incorporate Airbus
A318/A319/A320/A321 Temporary Revision warning computer (FWC) having a part
(TR) TR437, L/G—GEAR NOT (w) New Terminating Action number listed in figure 4 to paragraph (z) of
DOWNLOCKED, Issue 1.0, dated May 23, Modification of an airplane as required by this AD.
2014. When this TR has been included in paragraphs (u) and (v) of this AD, as (4) For an airplane subject to the
general revisions of the AFM, the general applicable, constitutes terminating action for requirements of paragraphs (u) and (v) of this
revisions may be inserted in the AFM, all repetitive actions (PFR monitoring checks AD, as applicable, do not install a FWC
and inspections) required by this AD for that having a part number listed in figure 4 to
provided the relevant information in the
airplane. paragraph (z) of this AD after modification of
general revision is identical to that in this
the airplane.
TR, and the copy of this TR may be removed
(x) New Conditional Terminating Action
from the AFM. Doing the action required by
this paragraph terminates the actions Replacement of a MLG door actuator as FIGURE 4 TO PARAGRAPH (z) OF THIS
required by paragraph (i) of this AD. required by paragraphs (m) and (q) of this AD—AFFECTED PART NUMBERS
Lhorne on DSK5TPTVN1PROD with RULES

AD; or corrective actions as specified in
(u) New Replacement of MLG Door Actuator Airbus AOT A320–32A1390, dated February Component
Having P/N 114122012 10, 2011; or replacement of a MLG door Part No.
name
Within 12 months after the effective date actuator as specified in Airbus Service
of this AD: Replace each MLG door actuator Bulletin A320–32–1390, Revision 03, dated Flight warning 350E016187171 (C5)
having P/N 114122012 with a MLG door July 3, 2014; does not constitute terminating computer. 350E017238484 (H1D1)
actuator having P/N 114122014, and flush action for the repetitive inspections required 350E017248685 (H1D2)

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Federal Register / Vol. 81, No. 46 / Wednesday, March 9, 2016 / Rules and Regulations 12419

FIGURE 4 TO PARAGRAPH (z) OF THIS inspector, the manager of the local flight NOT DOWNLOCKED, Issue 1.0, dated May
standards district office/certificate holding 23, 2014, to the Airbus A318/A319/A320/
AD—AFFECTED PART NUMBERS— district office. The AMOC approval letter A321 Airplane Flight Manual.
Continued must specifically reference this AD. (ii) Airbus Service Bulletin A320–32–1390,
(2) Required for Compliance (RC): If any Revision 03, dated July 3, 2014.
Component Airbus service information contains
Part No. (iii) Airbus Service Bulletin A320–32–
name procedures or tests that are identified as RC,
those procedures and tests must be done to 1407, Revision 01, dated July 3, 2014.
350E017251414 (H1E1) comply with this AD; any procedures or tests (iv) General Electric Service Bulletin
350E017271616 (H1E2) that are not identified as RC are 114122–32–105, Revision 2, dated June 24,
350E018291818 (H1E3CJ) recommended. Those procedures and tests 2014.
350E018301919 (H1E3P) that are not identified as RC may be deviated (4) The following service information was
350E018312020 (H1E3Q) from using accepted methods in accordance approved for IBR on August 23, 2013 (78 FR
350E053020202 (H2E2) with the operator’s maintenance or 48286, August 8, 2013).
350E053020303 (H2E3) inspection program without obtaining
350E053020404 (H2E4) (i) Airbus Alert Operators Transmission
approval of an AMOC, provided the
350E053020606 (H2F2) A32N001–13, dated June 24, 2013.
procedures and tests identified as RC can be
350E053020707 (H2F3) done and the airplane can be put back in an (ii) Reserved.
350E053021010 (H2F3P) airworthy condition. Any substitutions or (5) The following service information was
350E053020808 (H2F4) changes to procedures or tests identified as approved for IBR on July 12, 2011 (76 FR
350E053020909 (H2F5) RC require approval of an AMOC. 37241, June 27, 2011).
350E053021111 (H2F6) (3) Contacting the Manufacturer: As of the (i) Airbus All Operators Telex A320–
effective date of this AD, except as specified 32A1390, dated February 10, 2011.
(aa) Credit for Previous Actions in paragraph (j) of this AD for the use of an (ii) Reserved.
(1) This paragraph provides credit for alternative method to check the PFR for (6) The following service information was
actions required by paragraph (g) of this AD, CFDS messages, for any requirement in this approved for IBR on April 27, 2007 (72 FR
if those actions were performed before April AD to obtain corrective actions from a
13681, March 23, 2007).
27, 2007 (the effective date of AD 2007–06– manufacturer, the action must be
accomplished using a method approved by (i) Airbus Service Bulletin A320–32–1309,
18), using Airbus Service Bulletin A320–32– Revision 01, dated June 19, 2006.
1309, dated March 7, 2006. This service the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or (ii) Reserved.
information is not incorporated by reference
in this AD. EASA; or Airbus’s EASA DOA. If approved (7) For Airbus service information
(2) This paragraph provides credit for by the DOA, the approval must include the identified in this AD, contact Airbus,
actions required by paragraphs (k), (l), and DOA-authorized signature. Airworthiness Office—EIAS, 1 Rond Point
(m) of this AD, if those actions were (4) Previously Approved AMOCs: AMOCs Maurice Bellonte, 31707 Blagnac Cedex,
performed before the effective date of this AD approved previously for AD 2011–13–11 and France; telephone +33 5 61 93 36 96; fax +33
using Airbus Service Bulletin A320–32–1390, AD 2013–16–09 are approved as AMOCs for 5 61 93 44 51; email account.airworth-
Revision 01, dated September 21, 2011; or the corresponding provisions of this AD.
eas@airbus.com; Internet http://
Airbus Service Bulletin A320–32–1390, (cc) Special Flight Permits www.airbus.com.
Revision 02, dated October 23, 2013. This (8) For General Electric service information
Special flight permits may be issued in
service information is not incorporated by identified in this AD contact GE Aviation,
accordance with sections 21.197 and 21.199
reference in this AD.
of the Federal Aviation Regulations (14 CFR Customer Support Center, 1 Neumann Way,
(3) This paragraph provides credit for
21.197 and 21.199) to operate the airplane to Cincinnati, OH 45215; phone: 513–552–3272;
actions required by paragraphs (u) and (v) of
a location where the airplane can be email: cs.techpubs@ge.com; Internet: http://
this AD, if those actions were performed
modified (if the operator elects to do so), www.geaviation.com.
before the effective date of this AD using
provided the MLG remains extended and (9) You may view this service information
General Electric Service Bulletin 114122–32– locked, and that no MLG recycle is done.
105, dated January 17, 2013; or General at the FAA, Transport Airplane Directorate,
Electric Service Bulletin 114122–32–105, (dd) Related Information 1601 Lind Avenue SW., Renton, WA. For
Revision 1, dated March 26, 2013. This (1) Refer to Mandatory Continuing information on the availability of this
service information is not incorporated by Airworthiness Information (MCAI) EASA material at the FAA, call 425–227–1221.
reference in this AD. Airworthiness Directive 2014–0221, dated (10) You may view this service information
(bb) Other FAA AD Provisions September 30, 2014, for related information. that is incorporated by reference at the
This MCAI may be found in the AD docket National Archives and Records
The following provisions also apply to this on the Internet at http://www.regulations.gov
AD: Administration (NARA). For information on
by searching for and locating Docket No. the availability of this material at NARA, call
(1) Alternative Methods of Compliance FAA–2014–0529.
(AMOCs): The Manager, International 202–741–6030, or go to: http://
(2) Service information identified in this
Branch, ANM–116, Transport Airplane AD that is not incorporated by reference is www.archives.gov/federal-register/cfr/ibr-
Directorate, FAA, has the authority to available at the addresses specified in locations.html.
approve AMOCs for this AD, if requested paragraphs (ee)(7), (ee)(8), and (ee)(9) of this
using the procedures found in 14 CFR 39.19. Issued in Renton, Washington, on February
AD. 18, 2016.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local (ee) Material Incorporated by Reference Dionne Palermo,
Flight Standards District Office, as (1) The Director of the Federal Register Acting Manager, Transport Airplane
appropriate. If sending information directly approved the incorporation by reference Directorate, Aircraft Certification Service.
to the International Branch, send it to ATTN: (IBR) of the service information listed in this
[FR Doc. 2016–04577 Filed 3–8–16; 8:45 am]
Sanjay Ralhan, Aerospace Engineer, paragraph under 5 U.S.C. 552(a) and 1 CFR
International Branch, ANM–116, Transport part 51. BILLING CODE 4910–13–P
Lhorne on DSK5TPTVN1PROD with RULES

Airplane Directorate, FAA, 1601 Lind (2) You must use this service information
Avenue SW., Renton, WA 98057–3356; as applicable to do the actions required by
telephone 425–227–1405; fax 425–227–1149. this AD, unless this AD specifies otherwise.
Information may be emailed to: 9-ANM-116- (3) The following service information was
AMOC-REQUESTS@faa.gov. Before using approved for IBR on April 13, 2016.
any approved AMOC, notify your appropriate (i) Airbus A318/A319/A320/A321
principal inspector, or lacking a principal Temporary Revision TR437, L/G—GEAR

VerDate Sep<11>2014 14:06 Mar 08, 2016 Jkt 238001 PO 00000 Frm 00015 Fmt 4700 Sfmt 9990 E:\FR\FM\09MRR1.SGM 09MRR1
Document Created: 2016-03-09 00:12:54
Document Modified: 2016-03-09 00:12:54
Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final rule.
Dates		This AD becomes effective April 13, 2016.
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.
FR Citation		81 FR 12413
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
81 FR 12413 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 81, Issue 46 (March 9, 2016)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
