[Federal Register Volume 81, Number 46 (Wednesday, March 9, 2016)]
[Rules and Regulations]
[Pages 12413-12419]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-04577]
-----------------------------------------------------------------------
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