[Federal Register Volume 82, Number 66 (Friday, April 7, 2017)]
[Proposed Rules]
[Pages 16948-16952]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-06705]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
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 

  Federal Register / Vol. 82, No. 66 / Friday, April 7, 2017 / Proposed 
Rules  

[[Page 16948]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-0461; Directorate Identifier 2014-NM-159-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening 
of comment period.

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

SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) for all Airbus Model A319, A320, and A321 series airplanes. This 
action revises the notice of proposed rulemaking (NPRM) by reducing the 
compliance time for replacing the main landing gear (MLG) actuator 
fitting and removing an inspection requirement for certain airplanes. 
We are proposing this AD to address the unsafe condition on these 
products. Since these actions impose an additional burden over those 
proposed in the NPRM, we are reopening the comment period to allow the 
public the chance to comment on these proposed changes.

DATES: We must receive comments on this SNPRM by May 22, 2017.

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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this SNPRM, 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. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
0461; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (telephone: 800-647-5527) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-0461; 
Directorate Identifier 2014-NM-159-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We issued an NPRM to amend 14 CFR part 39 by adding an AD that 
would apply to all Airbus Model A319, A320, and A321 series airplanes. 
The NPRM published in the Federal Register on January 28, 2016 (81 FR 
4901) (``the NPRM''). The NPRM was prompted by a report that an MLG 
door could not be closed due to rupture of the actuator fitting. The 
NPRM proposed to require repetitive inspections for cracking of the MLG 
door actuator fitting and its components, and corrective actions if 
necessary. The NPRM also proposed to require eventual replacement of 
all affected MLG door actuator fittings with new monoblock fittings, 
which would terminate the repetitive inspections.

Actions Since the NPRM Was Issued

    Since the NPRM was issued, the European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Union, has issued EASA Airworthiness Directive 2016-0182, 
dated September 13, 2016 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for all Airbus Model A319, A320, and A321 series 
airplanes. The MCAI states:

    On one A320 aeroplane, it was reported that one of the main 
landing gear (MLG) doors could not be closed. Investigations 
revealed the rupture of the actuator fitting at the actuator 
attachment area on the door side. The MLG door is attached to the 
aeroplane by 2 (two) hinge fittings.
    This condition, if not corrected, could, under certain 
circumstances, lead to detachment of a MLG door from the aeroplane, 
possibly resulting in damage to the aeroplane, and/or injury to 
persons on the ground.
    Prompted by these findings, [Direction G[eacute]n[eacute]rale de 
l'Aviation Civile] France issued * * * [an AD] * * *, to require a 
MLG door actuator fitting inspection for cracks and to check the 
grain direction on a batch of aeroplanes. Subsequently, DGAC France 
issued * * * [an AD], retaining the requirements of DGAC France AD * 
* *, which was superseded, to require an inspection of the lower 
part of the MLG door actuator fitting.
    After that [DGAC] AD was issued, additional investigations 
revealed that damage could also appear on the nerve area

[[Page 16949]]

[of the forward monoblock fitting], in the upper part of the MLG 
door actuator fitting in the area of the hinge.
    Consequently, DGAC France issued F-2003-434, dated December 10, 
2003 [http://ad.easa.europa.eu/ad/F-2003-454] (EASA approval 2003-
1436), retaining the requirements of [a] DGAC France AD * * *, which 
was superseded, to require additional repetitive inspections. That 
[DGAC] AD also included an optional terminating action, by replacing 
the MLG door actuator fittings in accordance with the instructions 
of Airbus Service Bulletin (SB) A320-52-1073.
    After DGAC France AD F-2003-434 was issued, in the framework of 
the extended service goal campaign, it was decided to make 
replacement of the MLG door actuator fittings a required 
modification. Consequently, EASA issued AD 2014-0166 * * *, 
retaining the requirements of DGAC France AD F-2003-434, which was 
superseded, and requiring replacement of the MLG door actuator 
fittings with new monoblock fittings, which constitutes terminating 
action for the repetitive inspections.
    After EASA AD 2014-0166 [corresponding to the NPRM] was issued, 
errors were identified in the compliance time definitions. 
Replacement of the MLG door actuator fittings was required ``before 
exceeding 48,000 flight cycles (FC) or 96,000 flight hours (FH), 
whichever occurs later since aeroplane first flight'', which should 
have been ``whichever occurs first''. Furthermore, since the MLG 
door is an interchangeable part, the compliance time must be defined 
as FC/FH accumulated by the MLG door. Furthermore, it was discovered 
that one of the required inspection[s] is applicable only to a batch 
of MLG door fittings.
    For the reason described above, this AD retains the requirements 
of EASA AD 2014-0166, which is superseded, but requires 
accomplishment of the terminating action within more stringent 
compliance times, and reduce[s] the applicability of one of the 
required inspection[s].

    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-2016-
0461.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:
     Airbus Service Bulletin A320-52-1073, Revision 04, dated 
August 10, 1999.
     Airbus Service Bulletin A320-52-1073, Revision 05, dated 
September 28, 2006.
     Airbus Service Bulletin A320-52A1086, Revision 01, dated 
September 10, 1999.
     Airbus Service Bulletin A320-52-1096, Revision 02, dated 
July 12, 2006.
    This service information describes procedures for inspections for 
cracking of the MLG door actuator fitting and its components, and 
corrective actions if necessary. This service information also 
describes procedures for replacement of all affected MLG door actuator 
fittings with new monoblock fittings. These documents are distinct 
since they apply to different airplane models. 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.

Comments

    We gave the public the opportunity to participate in developing 
this proposed AD. We considered the comments received.

Support for the NPRM

    A commenter, Kevin Grandberry, stated that he supports the 
inspections of the MLG door actuator fittings specified in the NPRM.

Request To Reduce the Compliance Time for Replacing the MLG Actuator 
Fitting

    Airbus asked that we reduce the compliance time for the replacement 
specified in paragraph (j)(1) of the proposed AD (in the NPRM) from 
``whichever occurs later since the first flight of the airplane'' to 
``whichever occurs first since the first flight of the airplane.'' 
Airbus stated that EASA updated EASA AD 2014-0166, dated July 16, 2014 
(referenced in the NPRM), to correct the error noted in the compliance 
time (among other changes).
    We agree with the commenter's request in light of the superseded 
EASA AD, which corrects the compliance time. We have changed the 
compliance time specified in paragraph (j)(1) of this proposed AD 
accordingly.

Request To Change Applicability

    United Airlines (UA) asked that we limit the applicability of the 
NPRM to the manufacturer serial numbers (MSNs) included in Airbus 
Service Bulletin A320-52-1073, Revision 05, dated September 28, 2006. 
UA did not provide a reason for the request.
    We do not agree with the commenter's request. The effectivity of 
Airbus Service Bulletin A320-52-1073, Revision 05, dated September 28, 
2006, is based on airplanes delivered with the affected parts. However, 
the parts are rotable and could be installed on MSNs other than those 
identified in Airbus Service Bulletin A320-52-1073, Revision 05, dated 
September 28, 2006. Therefore, this AD applies to all airplanes 
identified in paragraph (c) of this AD. We have not changed this 
proposed AD in this regard.

Request for Credit for Previous Accomplishment of the Optional 
Terminating Action

    UA asked that we give credit for modifying the airplane (as 
specified in the optional terminating action in paragraph (k) of the 
proposed AD (in the NPRM)) using Airbus Service Bulletin A320-52-1073, 
Revision 04, dated August 10, 1999; or any prior revision. UA stated 
that accomplishing any revisions (including future revisions) would 
terminate the repetitive inspections required by paragraphs (g) and (h) 
of the proposed AD.
    We partially agree with the request. We agree to include Airbus 
Service Bulletin A320-52-1073, Revision 04, dated August 10, 1999, in 
this proposed AD; however, we do not agree to allow the use of any 
prior version because changes to the installation procedures were added 
to Airbus Service Bulletin A320-52-1073, Revision 04, dated August 10, 
1999, to prevent damage to the carbon fiber of the MLG door. We have 
added Airbus Service Bulletin A320-52-1073, Revision 04, dated August 
10, 1999, as a method of compliance for the optional terminating action 
in paragraph (k) of this proposed AD.

Request To Extend the Compliance Time for the Inspections

    Delta Air Lines (DAL) asked that we extend the compliance time 
specified in paragraphs (g) and (j)(2) of the proposed AD (in the 
NPRM). DAL stated that the FAA waited years to take any action on the 
subject unsafe condition and, in light of that fact, the ``calendar 
date'' for the compliance time in paragraph (g) of the proposed AD (in 
the NPRM) should be extended from 30 to 180 days. DAL also stated that 
using a calendar date for a crack growth concern is not based on 
industry-accepted analysis. DAL noted that mandating the inspections 
with this short interval has a significant impact on operators with 
multiple aircraft that are affected by the proposed AD. DAL added that 
an immediate safety concern is not evident in the speed with which the 
FAA moved to enact the regulatory action, or in the details provided in 
the NPRM. In addition, DAL asked that the compliance time in paragraph 
(j)(2) of the proposed AD (in the NPRM) be extended from 30 days to 24 
months. DAL stated that operators would have difficulty complying with 
the 30-day compliance time for replacing the MLG door actuator fitting 
due to the extensive time necessary to modify each door. DAL added that 
the replacement should be done in a hangar environment where skilled 
composite facilities and

[[Page 16950]]

technicians are available, which occurs every 24 months.
    We do not agree with the commenter's requests. The compliance times 
in paragraphs (g) and (j)(2) of this proposed AD are based on EASA's 
assessment of the overall risk to the fleet, including the severity of 
the failure and the likelihood of the failure to occur. We are unaware 
of any information or data that substantiates the compliance time 
change the commenter has requested, and nothing was provided by the 
commenter to support the request. We also do not agree that FAA 
requirements related to crack growth are based on calendar time. The 
calendar time of 30 days, as retained in this proposed AD, is a grace 
period to provide additional time for airplanes that have exceeded 
their limit of validity of engineering data. All other compliance time 
requirements are based on flight cycles and flight hours.
    We also note that since this is a SNPRM, operators will have 
additional time to plan for AD compliance. However, under the 
provisions of paragraph (n)(1) of this proposed AD, we will consider 
requests for approval of an extension of the compliance time if 
sufficient data are submitted to substantiate that the new compliance 
time would provide an acceptable level of safety. We have not changed 
this proposed AD in this regard.

Request To Include MLG Serial Numbers

    DAL asked that we change paragraph (h) of the proposed AD (in the 
NPRM) to include the affected serial numbers of the left- and right-
hand doors of the MLG. DAL stated that paragraph (g) of the proposed AD 
(in the NPRM) provides the door serial numbers to assist with 
identifying the affected doors, and similar information should be 
provided in paragraph (h) of the proposed AD (in the NPRM).
    We agree with the commenter's request. Paragraph (4) of EASA AD 
2016-0182, dated September 13, 2016, which corresponds to paragraph (h) 
of this proposed AD, identifies the affected serial numbers. It was not 
our intent to deviate from the MCAI. We have added the serial numbers 
to paragraph (h) of this proposed AD.

Request To Clarify Modification Titles

    UA asked that we clarify the language in paragraph (l) of the 
proposed AD (in the NPRM) to add ``or Airbus Modification'' before each 
modification number specified.
    We agree and have clarified paragraph (l) of this proposed AD 
accordingly.

FAA's Determination and Requirements of This SNPRM

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.
    Certain changes described above expand the scope of the NPRM. As a 
result, we have determined that it is necessary to reopen the comment 
period to provide additional opportunity for the public to comment on 
this SNPRM.

Costs of Compliance

    We estimate that this proposed AD affects 71 airplanes of U.S. 
registry.
    We also estimate that it would take about 38 work-hours per product 
to comply with the inspection requirements of this proposed AD. The 
average labor rate is $85 per work-hour. Based on these figures, we 
estimate the cost for the inspection specified in this proposed AD on 
U.S. operators to be $229,330, or $3,230 per product.
    We estimate that it would take about 98 work-hours per product to 
comply with the MLG actuator replacement requirements of this proposed 
AD. Required parts would cost about $6,258 per product. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost for the actuator replacement specified in this proposed AD on 
U.S. operators to be $1,035,748, or $14,588 per product.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2016-0461; Directorate Identifier 2014-NM-
159-AD.

(a) Comments Due Date

    We must receive comments by May 22, 2017.

(b) Affected ADs

    None.

(c) Applicability

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

[[Page 16951]]

    (3) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

    This AD was prompted by a report that a main landing gear (MLG) 
door could not be closed due to rupture of the actuator fitting. 
Later reports indicated that the forward monoblock fitting of the 
MLG door actuator (referred to as the nerve area) could be damaged 
after rupture of the actuator fitting. We are issuing this AD to 
prevent rupture of the door actuator fittings, which could result in 
detachment of an MLG door and subsequent exterior damage and 
consequent reduced structural integrity of the airplane.

(f) Compliance

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

(g) Repetitive Inspections of MLG Door Actuator Fittings

    For airplanes equipped with MLG door actuator fittings having 
part number (P/N) D52880224000 or P/N D52880224001 that were 
installed before the first flight of the airplane on MLG doors 
identified in paragraphs (g)(1) and (g)(2) of this AD: Within 500 
flight hours since the most recent high frequency eddy current 
(HFEC) inspection done as specified in Airbus Service Bulletin A320-
52A1086, Revision 01, dated September 10, 1999, or within 30 days 
after the effective date of this AD, whichever occurs later, perform 
an HFEC inspection for cracking of the MLG door fittings, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52A1086, Revision 01, dated September 10, 1999. Repeat 
the inspection thereafter at intervals not to exceed 500 flight 
hours, except as provided by paragraphs (i), (j), and (k) of this 
AD.
    (1) Left-hand MLG doors with serial numbers (S/Ns) 1206 through 
1237 inclusive, 1239 through 1247 inclusive, and 1249 through 1251 
inclusive.
    (2) Right-hand MLG doors with S/Ns 1208 through 1239 inclusive, 
1241 through 1249 inclusive, and 1251.

(h) Repetitive Inspections of MLG Hinge and Nerve Areas

    For airplanes equipped with MLG door actuator fittings having P/
N D52880224000, P/N D52880224001, P/N D52880235000, or P/N 
D52880235001 that were installed before the first flight of the 
airplane on MLG doors identified in paragraphs (h)(1) and (h)(2) of 
this AD: Within 400 flight cycles after the effective date of this 
AD, or before the accumulation of 9,000 total flight cycles since 
first flight of the airplane, whichever occurs later, perform an 
HFEC inspection of both hinge and nerve areas of the MLG doors for 
cracking, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-52-1096, Revision 02, dated July 12, 
2006. Repeat the inspection thereafter at intervals not to exceed 
800 flight cycles, except as provided by paragraphs (i)(1), (j), and 
(k) of this AD.
    (1) Left-hand MLG doors with S/Ns 1206 through 1510 inclusive, 
1548, 1564, and 2000 through 2065 inclusive.
    (2) Right-hand MLG doors with S/Ns 1208 through 1519 inclusive, 
1551, and 2000 through 2065 inclusive.

(i) Inspections/Corrective Actions

    (1) If any crack is found during any inspection required by 
paragraph (g) or (h) of this AD: Before further flight, replace the 
affected MLG door actuator fittings with new monoblock fittings, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52-1073, Revision 05, dated September 28, 2006. 
Accomplishing this replacement terminates the repetitive inspections 
required by paragraphs (g) and (h) of this AD.
    (2) If, during any HFEC inspection required by paragraph (g) of 
this AD, no crack is found: Before further flight, perform a low 
frequency eddy current (LFEC) inspection to determine the grain 
direction of the raw material of each MLG actuator fitting, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52A1086, Revision 01, dated September 10, 1999.
    (i) If the grain direction of the raw material is correct, the 
repetitive inspections required by paragraph (g) of this AD may be 
terminated.
    (ii) If the grain direction of the raw material is incorrect, 
repeat the HFEC inspection required by paragraph (g) of this AD at 
the time specified in paragraph (g) of this AD. Replacement of the 
MLG door actuator fittings with new monoblock fittings as specified 
in paragraph (i)(1) of this AD terminates the repetitive inspections 
required by paragraphs (g) and (i) of this AD.

(j) MLG Door Actuator Fitting Replacement

    For airplanes equipped with any MLG door actuator fitting having 
P/N D52880102000, P/N D52880102001, P/N D52880220000, P/N 
D52880220001, P/N D52880224000, P/N D52880224001, P/N D52880235000, 
or P/N D52880235001: At the later of the times specified in 
paragraphs (j)(1) and (j)(2) of this AD, replace the MLG door 
actuator fittings with new monoblock fittings, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-52-
1073, Revision 05, dated September 28, 2006. Accomplishing this 
replacement terminates the repetitive inspections required by 
paragraphs (g) and (h) of this AD.
    (1) Before the accumulation of 48,000 total flight cycles or 
96,000 total flight hours on the MLG door, whichever occurs first.
    (2) Within 30 days after the effective date of this AD.

(k) Optional Terminating Action

    Replacement of the MLG door actuator fittings with new monoblock 
fittings, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-52-1073, Revision 04, dated August 10, 
1999; or Airbus Service Bulletin A320-52-1073, Revision 05, dated 
September 28, 2006; terminates the repetitive inspections required 
by paragraphs (g) and (h) of this AD.

(l) Airplanes Excluded From Certain AD Requirements

    (1) For airplanes on which Airbus Modification 24903, or Airbus 
Modification 25372, or Airbus Modification 36979 has been embodied 
in production, no action is required by this AD, provided that no 
MLG door actuator fitting having any part number identified in 
paragraph (j) of this AD has been reinstalled on the airplane since 
first flight.
    (2) Modification of an airplane by installing a version (P/N) of 
the MLG door actuator fitting approved after the effective date of 
this AD is acceptable for compliance with the requirements in 
paragraph (j) of this AD, provided the conditions specified in 
paragraphs (l)(2)(i) and (l)(2)(ii) are met.
    (i) The MLG door actuator fitting (P/N) must be 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).
    (ii) The modification must be accomplished in accordance with 
instructions approved by the Manager, International Branch, EASA, or 
Airbus's EASA DOA.

(m) Parts Installation Limitation

    As of the effective date of this AD, no person may install an 
MLG door actuator fitting having any part number identified in 
paragraph (j) of this AD on any airplane.

(n) 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.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; 
or Airbus's EASA Design Organization Approval (DOA). If approved by 
the DOA, the approval must include the DOA-authorized signature.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA

[[Page 16952]]

Airworthiness Directive 2016-0182, dated September 13, 2016, 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-2016-0461.
    (2) For 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. You may view this service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on March 29, 2017.

Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-06705 Filed 4-6-17; 8:45 am]
 BILLING CODE 4910-13-P