Document ID: FAA-2019-0017-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus SAS Airplanes
Posted Date: 2019-02-25T05:00Z

[Federal Register Volume 84, Number 37 (Monday, February 25, 2019)]
[Proposed Rules]
[Pages 5960-5968]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-02929]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0017; Product Identifier 2018-NM-112-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2007-11-
11 and AD 2017-01-11, which apply to all Airbus SAS Model A318 and 
Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, 
and -233 airplanes; and Model A321 series airplanes. AD 2007-11-11 
requires an inspection to determine the serial number of both main 
landing gear (MLG) sliding tubes, repetitive inspections for cracking 
of the affected MLG sliding tubes and corrective actions if necessary, 
and eventual replacement of both MLG shock absorbers. AD 2017-01-11 
requires identification of the part number and serial number of the MLG 
sliding tubes; inspection of affected chromium plates and sliding tube 
axles for damage; and replacement of the sliding tube if necessary. 
Since we issued AD 2007-11-11 and AD 2017-01-11, it was determined that 
cracks were found in the MLG sliding tubes due to certain manufacturing 
defects that might not be identified using the current on-wing 
scheduled inspections. This proposed AD would retain certain 
requirements of AD 2007-11-11 and AD 2017-01-11. This proposed AD would 
also require repetitive inspections of affected MLG sliding tubes for 
cracking, replacement of cracked MLG sliding tubes, and eventual 
replacement of each affected MLG sliding tube. We are proposing this AD 
to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by April 11, 2019.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus 
SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine No: 2, 
31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email account.airworth-eas@airbus.com; internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. 
For information on the availability of this material at the FAA, call 
206-231-3195.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0017; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations (phone 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD 
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2019-0017; 
Product Identifier 2018-NM-112-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this proposed AD. We will consider 
all comments received by the closing date and may amend this proposed 
AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

[[Page 5961]]

Discussion

    We issued AD 2007-11-11, Amendment 39-15068 (72 FR 29241, May 25, 
2007) (``AD 2007-11-11''), for all Model A318 and Model A319 series 
airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; 
and Model A321 series airplanes. AD 2007-11-11 requires a one-time 
inspection to determine the serial number of both MLG sliding tubes, 
repetitive detailed inspections for cracking of the affected MLG 
sliding tubes and corrective actions if necessary, and eventual 
replacement of both MLG shock absorbers, which terminates the 
repetitive inspection requirements. AD 2007-11-11 resulted from a 
determination that inspections and mandatory replacement of the MLG 
shock absorbers are necessary. We issued AD 2007-11-11 to address 
cracking in an MLG sliding tube, which could result in failure of the 
sliding tube, loss of one axle, and consequent reduced controllability 
of the airplane.
    We also issued AD 2017-01-11, Amendment 39-18778 (82 FR 5362, 
January 18, 2017) (``AD 2017-01-11''), for all Model A318 and Model 
A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 
airplanes; and Model A321 series airplanes. AD 2017-01-11 requires 
identification of the part number and serial number of the MLG sliding 
tubes; inspection of affected chromium plates and sliding tube axles 
for damage; and replacement of the sliding tube if necessary. AD 2017-
01-11 resulted from a report of a rupture of an MLG sliding tube axle. 
We issued AD 2017-01-11 to address cracks in the axle and (partial) 
detachment of the axle and wheel from the sliding tube, which could 
result in failure of an MLG.

Actions Since AD 2007-11-11 and AD 2017-01-11 Were Issued

    Since AD 2007-11-11 and AD 2017-01-11 were issued, during MLG 
overhaul, cracks were found in the lower slave link bracket lug holes 
on two MLG sliding tubes. Subsequent investigations determined that 
these cracks may have developed due to burrs, which could have been 
present since manufacture, and it was determined that cracks in the 
affected sliding tubes may not be found during the existing on-wing 
scheduled inspections.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2018-0135, dated June 26, 2018 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for all Airbus SAS Model A318 and A319 series 
airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and 
-232 airplanes. The MCAI states:

    Cracks were reported on [main landing gear] MLG sliding tubes 
and the investigations determined metallic inclusion during 
production and abnormal grinding operation during overhaul as cause 
of these cracks. Prompted by these reports, respectively, [Direction 
Generale de l'Aviation Civile] DGAC France issued [French] AD F-
2005-115 (EASA approval 2005-6032) [which corresponds to FAA AD 
2007-11-11] and EASA issued AD 2014-0058 [which corresponds to FAA 
AD 2017-01-11], both requiring inspections and replacement of 
certain MLG sliding tubes.
    More recently, during overhaul, cracks were found in the lower 
slave link bracket lug holes on two MLG sliding tubes. Subsequent 
investigations determined that these cracks may have developed due 
to burrs, which could have been present since manufacture. Based on 
the fact that the sliding tube is certified as a safe life part, 
this is considered to be a non-compliance with the requirements of 
[Joint Aviation Requirements] JAR 25.571(c). Cracks in the affected 
sliding tubes may not be found during the existing on-wing scheduled 
inspections.
    This condition, if not detected and corrected, could lead to 
sliding tube failure, possibly resulting in MLG collapse, damage to 
the aeroplane and injury to occupants.
    Prompted by these findings, Safran Landing Systems, the MLG 
manufacturer (formerly Messier-Dowty, Messier-Bugatti-Dowty, and 
hereafter referred to as ``Safran'' in this AD), introduced 
additional quality steps to eliminate burrs in the manufacturing 
process. To address this potential unsafe condition on delivered MLG 
sliding tubes, Airbus issued SB [service bulletin] A320-32-1441, 
providing instructions for on-wing repetitive inspections, and 
Safran issued SB 200-32-321 and SB 201-32-68, as applicable to MLG 
configuration, providing instructions for inspection in shop.
    For the reason described above, this [EASA] AD partially retains 
the requirements of DGAC France AD F-2005-115 (EASA approval 2005-
6032) and EASA AD 2014-0058, which are superseded, requires 
repetitive inspections of the affected MLG sliding tubes [for 
cracking] and, depending on findings, accomplishment of applicable 
corrective action(s) [replacement of a cracked MLG sliding tube with 
a serviceable MLG sliding tube]. This [EASA] AD also defines 
criteria for installation on an aeroplane of an affected MLG sliding 
tube.

    You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0017.

Explanation of Change to Restated Text in Paragraph (g) of This 
Proposed AD

    Paragraph (g) of this proposed AD is a restatement of paragraph (i) 
of AD 2007-11-11. We have revised the restated text to remove the 
reference to Airbus A318/A319/A320/A321 Aircraft Maintenance Manual 
Chapter 32-11-13, page block 401. Instead, we have added Note 1 to 
paragraph (g) of this proposed AD to specify that guidance on the 
replacement specified in paragraph (g) of this proposed AD can be found 
in Airbus A318/A319/A320/A321 Aircraft Maintenance Manual Chapter 32-
11-13, page block 401.

Model A320-216 Airplanes

    The Airbus SAS Model A320-216 was U.S. type certificated on 
December 19, 2016. Before that date, any EASA ADs that affected Model 
A320-216 airplanes were included on the Required Airworthiness Actions 
List (RAAL). One or more Model A320-216 airplanes have subsequently 
been placed on the U.S. Register, and will now be included in FAA AD 
actions. For Model A320-216 airplanes, the requirements that correspond 
to AD 2007-11-11 and AD 2017-01-11 were mandated by the MCAI via the 
RAAL. Although that RAAL requirement is still in effect, for continuity 
and clarity we have identified Model A320-216 airplanes in paragraph 
(c) of this AD; the restated requirements of paragraphs (g) through (m) 
in this proposed AD would therefore apply to those airplanes.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
     Service Bulletin A320-32-1441, Revision 01, dated December 
14, 2017. The service information describes procedures for inspections 
of the MLG sliding tubes for cracking and corrective actions (which 
includes replacing the MLG sliding tubes).
     Service Bulletin A320-32A1273, Revision 02, including 
Appendix 01, dated May 26, 2005. The service information specifies the 
serial numbers of the MLG sliding tubes that must be replaced.
    Safran has issued the following service information. These 
documents are distinct since they apply to different airplane models.
     Service Bulletin 200-32-321, Revision 2, dated October 3, 
2017; and Service Bulletin 201-32-68, Revision 2, dated October 3, 
2017. These documents specify the part numbers and serial numbers of 
the affected MLG sliding tubes. These documents are distinct

[[Page 5962]]

since they apply to different airplane models.
     Service Bulletin 200-32-286, Revision 3, dated October 3, 
2008; and Service Bulletin 201-32-43, Revision 3, dated October 3, 
2008. These documents specify the part numbers and serial numbers of 
the affected MLG shock absorbers. These documents are distinct since 
they apply to different airplane models.
    This proposed AD would also require Airbus Service Bulletin A320-
32-1416, including Appendix 01, dated March 10, 2014, which the 
Director of the Federal Register approved for incorporation by 
reference as of February 22, 2017 (82 FR 5362, January 18, 2017).
    The 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.

FAA's Determination

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all the relevant information and determined the unsafe 
condition described previously is likely to exist or develop on other 
products of the same type design.

Proposed Requirements of This NPRM

    This proposed AD would retain certain requirements of AD 2007-11-11 
and AD 2017-01-11. This proposed AD would also require repetitive 
inspections of affected MLG sliding tubes for cracking, replacing 
cracked MLG sliding tubes with serviceable MLG sliding tubes, and 
eventual replacement of each affected MLG sliding tube with a MLG 
sliding tube that is not affected, which is terminating action for the 
repetitive inspections.

Costs of Compliance

    We estimate that this proposed AD affects 1,186 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2007-11- 8 work-hours x $85  Up to $45,310.....  Up to $45,990.....  Up to $13,659,030
 11 (297 airplanes) \[*]\.         per hour = $680.                                            \[*]\.
Retained actions from AD 2017-01- 18 work-hours x     $0................  $1,530............  $1,814,580.
 11.                               $85 per hour =
                                   $1,530.
New proposed actions............  13 work-hours x     $0 [**]...........  $1,105............  $1,310,530.
                                   $85 per hour =
                                   $1,105.
----------------------------------------------------------------------------------------------------------------
* Operators should note that, although all U.S.-registered airplanes are subject to the requirements of AD 2007-
  11-11, there are only 297 possible affected MLG sliding tubes in the worldwide fleet. We have no way of
  knowing how many affected MLG sliding tubes, if any, are installed in U.S.-registered airplanes.
** We have received no definitive data for the parts costs for the replacements.

    We estimate the following costs to do any necessary on-condition 
action that would be required based on the results of any required 
actions. We have no way of determining the number of aircraft that 
might need this on-condition action:

                 Estimated Costs of On-Condition Action
------------------------------------------------------------------------
                                                             Cost per
               Labor cost                   Parts cost        product
------------------------------------------------------------------------
6 work-hours x $85 per hour = $510......        $0 \[*]\            $510
------------------------------------------------------------------------
* We have received no definitive data for the parts costs for the on-
  condition 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.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes and associated appliances to the 
Director of the System Oversight Division.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866,

[[Page 5963]]

    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    3. Will not affect intrastate aviation in Alaska, and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.   39.13 [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive (AD) 2007-11-11, Amendment 39-15068 
(72 FR 29241, May 25, 2007); and AD 2017-01-11, Amendment 39-18778 (82 
FR 5362, January 18, 2017); and
0
b. Adding the following new AD:

Airbus SAS: Docket No. FAA-2019-0017; Product Identifier 2018-NM-
112-AD.

(a) Comments Due Date

    We must receive comments by April 11, 2019.

(b) Affected ADs

    This AD replaces the following ADs.
    (1) AD 2007-11-11, Amendment 39-15068 (72 FR 29241, May 25, 
2007) (``AD 2007-11-11'').
    (2) AD 2017-01-11, Amendment 39-18778 (82 FR 5362, January 18, 
2017) (``AD 2017-01-11'').

(c) Applicability

    This AD applies to the Airbus SAS airplanes identified in 
paragraphs (c)(1) through (c)(4) of this AD, certificated in any 
category, 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, -216, -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 cracks were found 
in the main landing gear (MLG) sliding tubes due to certain 
manufacturing defects that might not be identified using the current 
on-wing scheduled inspections. We are issuing this AD to address 
cracking in an MLG sliding tube, which could lead to failure of an 
MLG sliding tube resulting in MLG collapse, damage to the airplane, 
and injury to passengers.

(f) Compliance

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

(g) Retained Replacement of AD 2007-11-11, With Updated References to 
Service Information and Specific Delegation Approval Language

    This paragraph restates the requirements of paragraph (i) of AD 
2007-11-11, with updated references to service information and 
specific delegation approval language. Within 41 months after June 
29, 2007 (the effective date of AD 2007-11-11), replace all MLG 
shock absorbers equipped with sliding tubes having serial numbers 
listed in Airbus All Operators Telex (AOT) A320-32A1273, Revision 
01, dated May 6, 2004; or the Accomplishment Instructions of Airbus 
Service Bulletin A320-32A1273, Revision 02, including Appendix 01, 
dated May 26, 2005; with new or serviceable MLG shock absorbers 
equipped with sliding tubes having serial numbers not listed in 
Airbus AOT A320-32A1273, Revision 01, dated May 6, 2004; or the 
Accomplishment Instructions of Airbus Service Bulletin A320-32A1273, 
Revision 02, including Appendix 01, dated May 26, 2005; using a 
method approved by the Manager, International Section, Transport 
Standards Branch, FAA; or the European Aviation Safety Agency 
(EASA); or Airbus SAS's EASA Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature. As of June 29, 2007, only Airbus Service Bulletin A320-
32A1273, Revision 02, including Appendix 01, dated May 26, 2005, may 
be used to determine the affected sliding tubes.

    Note 1 to paragraph (g) of this AD:  Guidance on the replacement 
specified in paragraph (g) of this AD can be found in Airbus A318/
A319/A320/A321 Aircraft Maintenance Manual Chapter 32-11-13, page 
block 401.

(h) Retained MLG Sliding Tube Part Number and Serial Number 
Identification of AD 2017-01-11, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2017-01-11, with no changes. Within three months after February 22, 
2017 (the effective date of AD 2017-01-11): Do an inspection to 
identify the part number and serial number of the MLG sliding tubes 
installed on the airplane. A review of airplane maintenance records 
is acceptable in lieu of this inspection if the part number and 
serial number of the MLG sliding tubes can be conclusively 
determined from that review.

(i) Retained Identification of Airplanes of AD 2017-01-11, With No 
Changes

    This paragraph restates the identification specified in 
paragraph (h) of AD 2017-01-11, with no changes. An airplane with a 
manufacturer serial number (MSN) not listed in figure 1 to paragraph 
(i) of this AD is not affected by the requirements of paragraph (j) 
of this AD, provided it can be determined that no MLG sliding tube 
having a part number and serial number listed in table 1 to 
paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD 
has been installed on that airplane since first flight of the 
airplane.

[[Page 5964]]

[GRAPHIC] [TIFF OMITTED] TP25FE19.000

[[Page 5965]]

[GRAPHIC] [TIFF OMITTED] TP25FE19.001

[[Page 5966]]

[GRAPHIC] [TIFF OMITTED] TP25FE19.002

(j) Retained Inspections of AD 2017-01-11, With No Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2017-01-11, with no changes. For each MLG sliding tube identified as 
required by paragraph (h) of this AD, having a part number and 
serial number listed in table 1 to paragraphs (i), (j), (l)(1), 
(l)(2), (m)(1), and (m)(2) of this AD: Within 3 months after 
February 22, 2017 (the effective date of AD 2017-01-11) inspect 
affected MLG axles and brake flanges by doing a detailed visual 
inspection of the chromium plates for damage, and a Barkhausen noise 
inspection of the sliding tube axles for damage, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-32-
1416, including Appendix 01, dated March 10, 2014. For Model A318 
series airplanes, use the procedures specified for Model A319 series 
airplanes in Airbus Service Bulletin A320-32-1416, including 
Appendix 01, dated March 10, 2014.

(k) Retained Corrective Action of AD 2017-01-11, With No Changes

    This paragraph restates the requirements of paragraph (j) of AD 
2017-01-11, with no changes. If, during any inspection required by 
paragraph (j) of this AD, any damage is detected: Before further 
flight, replace the MLG sliding tube with a serviceable tube, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-32-1416, including Appendix 01, dated March 10, 2014. 
For Model A318 series airplanes, use the procedures specified for 
Model A319 series airplanes in Airbus Service Bulletin A320-32-1416, 
including Appendix 01, dated March 10, 2014.

(l) Retained Definition of Serviceable MLG Sliding Tube of AD 2017-01-
11, With No Changes

    This paragraph restates the definition specified in paragraph 
(k) of AD 2017-01-11, with no changes. For the purpose of paragraph 
(k) of this AD, a serviceable sliding tube is defined as a sliding 
tube that meets the criterion in either paragraph (l)(1) or (l)(2) 
of this AD.
    (1) A sliding tube having a part number and serial number not 
listed in table 1 to paragraphs (i), (j), (l)(1), (l)(2), (m)(1), 
and (m)(2) of this AD.
    (2) A sliding tube having a part number and serial number listed 
in table 1 to paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and 
(m)(2) of this AD that has passed the inspections required by 
paragraph (j) of this AD.

(m) Retained Parts Installation Prohibition of AD 2017-01-11, With No 
Changes

    This paragraph restates the requirements of paragraph (l) of AD 
2017-01-11, with no changes.
    (1) For airplanes that have an MLG sliding tube installed that 
has a part number and serial number listed in table 1 to paragraphs 
(i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD: After an 
airplane is returned to service following accomplishment of the 
actions required by paragraphs (h), (i), and (j) of this AD, no 
person may install on any airplane an MLG sliding tube having a part 
number and serial number listed in table 1 to paragraphs (i), (j), 
(l)(1), (l)(2), (m)(1), and (m)(2) of this AD, unless that sliding 
tube has passed the inspection required by paragraph (j) of this AD.
    (2) For airplanes that, as of February 22, 2017 (the effective 
date of AD 2017-01-11), do not have an MLG sliding tube installed 
that has a part number and serial number listed in table 1 to 
paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD: 
No person may install, on any airplane, an MLG sliding tube having a 
part number and serial number listed in table 1 to paragraphs (i), 
(j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD unless that 
sliding tube has passed the inspection required by paragraph (j) of 
this AD.

(n) New Definitions

    For the purpose of paragraphs (o), (p), (q), (r), and (s) of 
this AD the following definitions apply.
    (1) Affected MLG shock absorber: An MLG shock absorber having a 
part number and serial number as identified in Safran Service 
Bulletin 200-32-286, Revision 3, dated October 3, 2008, for Model 
A318, A319, and A320 series airplanes; and Safran Service Bulletin 
201-32-43, Revision 3, dated October 3, 2008, for Model A321 series 
airplanes.
    (2) Affected MLG sliding tube: An MLG sliding tube having a part 
number and serial number as identified in Appendix B of Safran 
Service Bulletin 200-32-321, Revision 2, dated October 3, 2017, for 
Model A318, A319, and A320 series airplanes; or Safran Service 
Bulletin 201-32-68, Revision 2, dated October 3, 2017, for Model 
A321 series airplanes, except those parts that passed an inspection 
as specified in Safran Service

[[Page 5967]]

Bulletin 200-32-321; or Safran Service Bulletin 201-32-68, as 
applicable, and those parts that, after that inspection, have been 
repaired, using instructions approved by the Manager, International 
Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's 
EASA DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
    (3) Serviceable MLG sliding tube: A MLG sliding tube that is not 
affected, or an affected MLG sliding tube, that has not exceeded 
10,000 flight cycle since first installation on an airplane, or an 
affected MLG sliding tube that, within the last 5,000 flight cycles 
before installation on an airplane, passed an inspection specified 
in Airbus Service Bulletin A320-32-1441.

(o) New Requirement of This AD: Repetitive Inspections

    At the compliance time specified in figure 2 to paragraph (o) of 
this AD, and thereafter at intervals not to exceed 5,000 flight 
cycles: Do a detailed inspection of each affected MLG sliding tube, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-32-1441, Revision 01, dated December 14, 2017.
[GRAPHIC] [TIFF OMITTED] TP25FE19.003

    Note 2 to paragraph (o) of this AD: If no reliable data 
regarding the number of flight cycles accumulated by the MLG sliding 
tube are available, operators may refer to the guidance specified in 
Chapter 5.2, ``Traceability'', of Section 1, of Part 1 of the Airbus 
A318/A319/A320/A321 Airworthiness Limitations Section.

(p) New Requirement of This AD: Corrective Actions

    (1) If, during any inspection required by paragraph (o) of this 
AD, any crack is detected on an MLG sliding tube: Before further 
flight, replace that MLG sliding tube with a serviceable MLG sliding 
tube, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-32-1441, Revision 01, dated December 14, 2017.
    (2) Replacement of an MLG on an airplane with an MLG having a 
serviceable MLG sliding tube installed is an acceptable method to 
comply with the requirements of paragraph (p)(1) of this AD for that 
airplane.

(q) New Requirement of This AD: Part Replacement

    (1) Within 10 years after the effective date of this AD: Replace 
each affected MLG sliding tube with an MLG sliding tube that is not 
affected. Installation of an MLG sliding tube that is not affected 
on an airplane constitutes terminating action for the repetitive 
inspections required by paragraph (o) of this AD for that airplane.
    (2) Replacement of an MLG on an airplane with an MLG that does 
not have an affected MLG sliding tube installed is an acceptable 
method to comply with the requirement of paragraph (q)(1) of this AD 
for that airplane.

(r) New Requirement of This AD: Parts Installation Limitation

    (1) As of the effective date of this AD no person may install on 
any airplane an affected MLG shock absorber.
    (2) Do not install an affected MLG sliding tube on any airplane 
as specified in paragraph (r)(2)(i) or (r)(2)(ii) of this AD, as 
applicable.
    (i) For an airplane with an affected MLG sliding tube installed 
as of the effective date of this AD: After replacement of each 
affected MLG sliding tube as required by paragraph (q) of this AD.
    (ii) For an airplane that does not have an affected MLG sliding 
tube installed as of the effective date of this AD: As of the 
effective date of this AD.

(s) Identification of Airplanes Not Affected by Certain Requirements of 
This AD

    An airplane on which Airbus Modification 161202 or Modification 
161346 has been installed in production is not affected by the 
requirements of paragraphs (g), (h), (j), (o), and (q), of this AD, 
provided it has been verified that no affected MLG sliding tube is 
installed on that airplane.

(t) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before 
June 29, 2007, using Airbus AOT A320-32A1273, Revision 01, dated May 
6, 2004.
    (2) This paragraph provides credit for the initial inspection 
and applicable corrective actions required by paragraphs (o) and (p) 
of this AD if those actions were performed before the effective date 
of this AD, using the Accomplishment Instructions in Airbus Service 
Bulletin A320-32-1441, dated December 28, 2016.

(u) Service Information Exceptions

    The service information specified in paragraph (g) of this AD 
has instructions to send any cracked part to Messier-Dowty. This AD 
does not include such a requirement, in accordance with the 
procedures specified in paragraph (w)(2) of this AD.

(v) No Reporting Requirement

    Although Airbus Service Bulletin A320-32-1441, Revision 01, 
dated December 14, 2017, specifies to submit certain information to 
the manufacturer, and specifies that action as ``RC,'' (required for 
compliance) this AD does not include that requirement.

(w) Other FAA AD Provisions

    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, 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 Section, send it to the attention of 
the person identified in paragraph (x)(2) of this AD. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
    (i) 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.
    (ii) AMOCs approved previously for AD 2007-11-11 are approved as 
AMOCs for the corresponding provisions of paragraph (g) of this AD.
    (iii) AMOCs approved previously for AD 2017-01-11 are approved 
as AMOCs for the corresponding provisions of paragraphs (h), (i), 
(j), (k), (l), and (m) of this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, 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 Section, Transport Standards 
Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the 
DOA, the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraphs (u) and (v) of this

[[Page 5968]]

AD: If any 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.

(x) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2018-0135, dated June 26, 2018, 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-2019-0017.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3223.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine 
No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email account.airworth-eas@airbus.com; internet 
http://www.airbus.com. You may view this service information at the 
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, 
WA. For information on the availability of this material at the FAA, 
call 206-231-3195.

    Issued in Des Moines, Washington, on February 1, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-02929 Filed 2-22-19; 8:45 am]
 BILLING CODE 4910-13-P