[Federal Register Volume 83, Number 29 (Monday, February 12, 2018)]
[Rules and Regulations]
[Pages 5906-5912]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-02359]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0707; Product Identifier 2016-NM-014-AD; Amendment 
39-19185; AD 2018-03-12]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A318 series airplanes; Model A319 series airplanes; Model 
A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-
111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD 
was prompted by reports of fatigue damage in the structure for the door 
stop fittings on certain fuselage frames (FR). This AD requires 
repetitive rototest inspections for cracking of the fastener holes in 
certain door stop fittings, and repair if necessary. We are issuing 
this AD to address the unsafe condition on these products.

DATES: This AD is effective March 19, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 19, 
2018.

ADDRESSES: For 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. You may view this referenced service 
information at the FAA, Transport Standards Branch, 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-2017-0707.

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-2017-
0707; 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 Office (telephone: 
800-647-5527) is 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 20590.

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

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Airbus Model A318 
series airplanes; Model A319 series airplanes; Model A320-211, -212, -
214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -
211, -212, -213, -231, and -232 airplanes. The NPRM published in the 
Federal Register on July 25, 2017 (82 FR 34449) (``the NPRM''). The 
NPRM was prompted by reports of fatigue damage in the structure for the 
door stop fittings on certain fuselage frames. The NPRM proposed to 
require repetitive rototest inspections for cracking of the fastener 
holes in certain door stop fittings, and repair if necessary. We are 
issuing this AD to detect and correct cracking at the door stop fitting 
holes of fuselage FR66 and FR68. Such cracking could result in reduced 
structural integrity of the airplane due to the failure of structural 
components.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2016-0238, dated December 2, 2016; corrected January 4, 2017 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A318 series airplanes; Model A319 series airplanes; Model A320-211, -
212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -
131, -211, -212, -213, -231, and -232 airplanes. The MCAI states:

    During an A320 fatigue test campaign, it was determined that 
fatigue damage could appear at the door stop fitting holes of 
fuselage frame (FR) 66 and FR 68 on left hand (LH) and right hand 
(RH) sides.
    This condition, if not detected and corrected, could affect the 
structural integrity of the airframe.
    Two inspections, Airworthiness Limitations Item (ALI) tasks 
534129 and 534130, were introduced in the Airworthiness Limitations 
Section (ALS) Part 2 with the April 2012 revision and with some 
compliance time changes with Revision 3 of ALS Part 2 of October 
2014.
    Since these ALI tasks were implemented, a significant number of 
reports [were] received concerning non-critical damage and early 
crack findings. Prompted by these reports, Airbus published SB A320-
53-1288 and SB A320-53-1290, providing inspection instructions to 
improve damage management and modification instructions.
    Consequently, EASA issued AD 2016-0015, requiring repetitive 
rototest inspections of the affected door stop fitting holes and, 
depending on findings, repair of any cracked area(s).
    Since that [EASA] AD was issued, ALS Part 2 Revision 04 and 
later on Revision 05 were published, introducing updated thresholds 
and/or intervals for some tasks as specified in Airbus SB A320-53-
1288, introducing new configuration of aeroplane with RETRO WING 
having accomplished SB A320-57-1193 (mod 160080), and keeping the 
threshold or interval only in flight cycles (FC).
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2016-0015, which is superseded, but requires 
those actions within the updated thresholds and intervals. In 
addition, a corrected threshold for pre-mod 160021 A321 aeroplanes 
is introduced and the Applicability is reduced to exclude 
configurations that are not affected.
    This [EASA] AD is republished to clarify some requirements in 
Appendix 1 [in this EASA AD].

    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-2017-
0707.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Request To Add a Grace Period for Certain Repetitive Inspections

    United Airlines (UAL) requested that we revise paragraph (h) of the 
proposed AD to allow a 60-day grace period after

[[Page 5907]]

the effective date of this AD to give operators time to update their 
maintenance programs. UAL noted that for airplanes on which inspections 
were previously accomplished as specified in airworthiness limitation 
item (ALI) task 534129 or 534130, paragraph (h) of the proposed AD 
requires future inspections be done in accordance with Airbus Service 
Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 
03, dated October 3, 2016. UAL noted that operators who are not yet 
incorporating Airbus Service Bulletin A320-53-1288, Revision 01, 
including Appendixes 01, 02, and 03, dated October 3, 2016, may have to 
schedule special inspection visits instead of doing the inspections 
during scheduled maintenance.
    We agree with the commenter's request to add a grace period to 
paragraph (h) of this AD to allow operators to plan for the new 
inspection interval. However, since the commenter did not provide 
adequate justification to support a 60-day grace period, we have 
determined that a 30-day grace period is appropriate. Additionally, 
under the provisions of paragraph (q)(1) of this 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 revised 
paragraph (h) of this AD to include a 30-day grace period.

Request To Allow Deviations From the Service Information for Certain 
Modified Airplanes

    UAL requested that either the service information or the proposed 
AD be revised to provide alternate instructions for airplanes with 
modified hardware. UAL noted that ``paragraph (i)'' of the proposed AD 
requires repetitive inspections on airplanes modified by cold working 
fastener holes, which includes installing oversize hardware. UAL 
pointed out that the inspections must be done in accordance with Airbus 
Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 
02, and 03, dated October 3, 2016, which requires using nominal size 
hardware that no longer exists on modified airplanes.
    We infer that the commenter meant to refer to paragraph (j) of the 
proposed AD, which discusses post-modification inspections, rather than 
paragraph (i) of the proposed AD, which discusses an optional 
modification. We agree with the commenter's request. We acknowledge 
that Airbus Service Bulletin A320-53-1288, Revision 01, including 
Appendixes 01, 02, and 03, dated October 3, 2016, does not specifically 
address oversize hardware; however, EASA has stated that ``the same 
inspection principle applies for post SB [Service Bulletin] 53-1290 
configuration.'' Therefore, we have retained Airbus Service Bulletin 
A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated 
October 3, 2016, in paragraph (j) of this AD. We have also revised 
paragraph (j) of this AD to include an option for operators to obtain 
inspection instructions using a method approved by the Manager, 
International Section, Transport Standards Branch, FAA; or EASA; or 
Airbus's EASA Design Organization Approval (DOA).

Request To Remove a Reference to a Non-Terminating Action

    UAL requested that we remove the statement ``repair of an airplane 
as required by this paragraph does not constitute terminating action 
for the repetitive inspections required by paragraph (g) or (j) of this 
AD for that repair, unless specified otherwise'' from paragraph (k) of 
the proposed AD. UAL suggested that statement be replaced with one 
instructing operators to accomplish inspections as specified in the 
repair instructions.
    UAL noted that paragraph (k) of the proposed AD states that a crack 
repair must be done using a method approved by the Manager, 
International Section, Transport Standards Branch, FAA; or EASA; or 
Airbus's EASA DOA and says that such a repair does not constitute 
terminating action for the repetitive inspections done in accordance 
with Airbus Service Bulletin A320-53-1288, Revision 01, including 
Appendixes 01, 02, and 03, dated October 3, 2016, unless specified 
otherwise.
    UAL pointed out that Airbus Service Bulletin A320-53-1288, Revision 
01, including Appendixes 01, 02, and 03, dated October 3, 2016, 
contains language to allow operators to accomplish crack repairs in 
accordance with structural repair manual (SRM) 53-41-12, and then 
perform inspections of the repaired area in accordance with SRM 53-41-
12. UAL noted that the SRM repair instructions do not state that they 
terminate the inspections in Airbus Service Bulletin A320-53-1288, 
Revision 01, including Appendixes 01, 02, and 03, dated October 3, 
2016. UAL further noted that Airbus Service Bulletin A320-53-1288, 
Revision 01, including Appendixes 01, 02, and 03, dated October 3, 
2016, only applies to unrepaired areas with nominal size holes (the 
repaired areas would have oversized holes).
    We disagree with the commenter's request. We acknowledge that 
Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 
01, 02, and 03, dated October 3, 2016, allows repairs to be done using 
an SRM. However, this AD does not include that allowance since SRMs 
published before the effective date of this AD might not address the 
unsafe condition identified in this AD. Therefore, paragraph (k) of 
this AD requires repairs to be done using a method approved by the 
Manager, International Section, Transport Standards Branch, FAA; or 
EASA; or Airbus's EASA DOA.
    Additionally, the statement that the commenter requested us to 
remove from paragraph (k) of this proposed AD aligns with the MCAI. The 
statement is meant to clarify that doing a repair does not necessarily 
terminate the repetitive inspections; the repetitive inspections would 
only be terminated if the repair approved by the Manager, International 
Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA 
specifically states that the inspections are terminated. If the 
approved repair does not state that the inspections are terminated, 
operators must continue to inspect using Airbus Service Bulletin A320-
53-1288, Revision 01, including Appendixes 01, 02, and 03, dated 
October 3, 2016, or using a method approved by the Manager, 
International Section, Transport Standards Branch, FAA; or EASA; or 
Airbus's EASA DOA. Therefore, we have not changed the requirements in 
paragraph (k) of this AD nor have we removed the statement identified 
by the commenter. However, we have revised paragraph (g) of this AD to 
include an option for operators to obtain inspection instructions using 
a method approved by the Manager, International Section, Transport 
Standards Branch, FAA; or EASA; or Airbus's EASA DOA.

Request To Remove Requirement To Obtain Certain Inspection Instructions

    UAL requested that we remove paragraph (l)(2) of the proposed AD 
because it has no real purpose. UAL noted that paragraph (l)(2) of the 
proposed AD requires operators to obtain inspection instructions and 
corrective actions for all repaired fastener holes by contacting the 
Manager, International Section, Transport Standards Branch, FAA; or 
EASA; or Airbus's EASA DOA. UAL claimed that if a repair was 
accomplished using the instructions in an SRM or repair design approval 
sheet (RDAS), the repair approval contains, at a minimum, the initial 
compliance threshold. UAL added that it is standard

[[Page 5908]]

practice for operators to contact Airbus prior to the inspection 
threshold if the compliance method and intervals are not yet defined.
    We disagree with the commenter's request. Airbus intends to provide 
specific instructions for airplanes inspected in accordance with ALI 
task 534129 or task 534130 and repaired in accordance with an SRM or 
RDAS published before the effective date of this AD. Since repair 
instructions published before the effective date of this AD might not 
address the unsafe condition identified in this AD, the SRM or RDAS 
instructions might need to be re-evaluated or revised to address the 
unsafe condition. In addition, we do not rely on an operator's standard 
practices, and instead require operators to obtain inspections and 
corrective actions to address the unsafe condition. We have not revised 
this AD regarding this issue.

Request To Clarify Actions for Airplanes With Certain Repairs

    UAL requested that we delete paragraph (n) of the proposed AD. UAL 
noted that paragraph (n) of the proposed AD requires operators to 
determine if a repair was done using an RDAS that is unrelated to ALI 
task 534129 or task 534130. UAL suggested that the repair instructions 
would have to state that the damage was found as a result of the 
applicable ALI, but noted that the ALI task is an inspection that may 
not be referenced in a documented repair. UAL questioned the relevance 
of whether or not a repair was related to ALI task 534129 or task 
534130, noting that the same considerations are given to repair 
instructions, regardless of how damage was found. UAL stated that 
operators would know to seek an alternative method of compliance (AMOC) 
if they cannot inspect a previously repaired area in accordance with 
Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 
01, 02, and 03, dated October 3, 2016.
    We disagree with the commenter's request. The intent of paragraph 
(n) of the proposed AD is to require operators to re-evaluate existing 
repairs performed using an Airbus RDAS unrelated to ALI task 534129 or 
task 534130 because those repairs may not address the findings from the 
specific inspection types required by the ALI tasks. Therefore, the 
corresponding repairs might not address the unsafe condition and 
operators might need new instructions. We have not changed this AD in 
this regard.

Request To Verify the Latest Service Information is Referenced

    UAL requested that, prior to the release of this final rule, we 
verify that we are referencing the latest revisions of Airbus Service 
Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 
03, dated October 3, 2016; and Airbus Service Bulletin A320-53-1290, 
Revision 01, dated October 3, 2016.
    We agree with the commenter's request. We have verified that no 
later revisions of the service information have been issued, and no 
change is needed to this AD.

Explanation of Change to the Final Rule

    In the proposed AD, Table 1 to paragraphs (g) and (j) of this AD 
and Table 2 to paragraphs (g) and (j) of this AD included a compliance 
time that stated ``. . . or before November 30, 2017. . . .'' Since 
this final rule will become effective after November 30, 2017, we have 
changed this statement to read ``. . . or within 30 days after the 
effective date of this AD. . . .'' We have determined that this revised 
compliance time addresses the unsafe condition.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
     Airbus Service Bulletin A320-53-1288, Revision 01, 
including Appendixes 01, 02, and 03, dated October 3, 2016. This 
service information describes procedures for rototest inspections for 
cracking of the fastener holes in the airframe structure for the door 
stop fittings installation in FR66 and FR68.
     Airbus Service Bulletin A320-53-1290, Revision 01, dated 
October 3, 2016. This service information describes procedures for cold 
working the fastener holes in the airframe structure for the door stop 
fittings installation in FR66 and FR68.
    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 1,084 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
           Action                  Labor cost         Parts cost       Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspections................  23 work-hours x $85                $0  $1,955 per inspection  $2,119,220 per
                              per hour = $1,955                      cycle.                 inspection cycle.
                              per inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the required inspection. We 
have no way of determining the number of aircraft that might need this 
repair.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair.....................................  27 work-hours x $85 per hour =                 $610          $2,905
                                              $2,295.
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[[Page 5909]]

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 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 to 
the Director of the System Oversight Division.

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.

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 adding the following new airworthiness 
directive (AD):

2018-03-12 Airbus: Amendment 39-19185; Docket No. FAA-2017-0707; 
Product Identifier 2016-NM-014-AD.

(a) Effective Date

    This AD is effective March 19, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A318-111, -112, -121, and -122 
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -
133 airplanes; Model A320-211, -212, -214, 231, -232, and -233 
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes; certificated in any category; all manufacturer 
serial numbers, except airplanes specified in paragraphs (c)(1), 
(c)(2), and (c)(3) of this AD.
    (1) Airplanes on which Airbus modification (Mod) 157039 has been 
embodied in production.
    (2) Model A319 series airplanes on which Mod 28238, Mod 28162, 
and Mod 28342 have been embodied in production.
    (3) Model A318 series airplanes on which Mod 39195 has been 
embodied in production or Airbus Service Bulletin A320-00-1219 has 
been embodied in service.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by reports of fatigue damage in the 
structure for the door stop fittings on certain fuselage frames 
(FR). We are issuing this AD to detect and correct cracking at the 
door stop fitting holes of fuselage FR66 and FR68. Such cracking 
could result in reduced structural integrity of the airplane due to 
the failure of structural components.

(f) Compliance

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

(g) Repetitive Rototest Inspections

    Within the applicable compliance times specified in table 1 to 
paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and 
(j) of this AD: Do a rototest inspection of all holes below each 
door stop fitting at fuselage FR66 and FR68, both left-hand (LH) and 
right-hand (RH) sides, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1288, Revision 01, 
including Appendixes 01, 02, and 03, dated October 3, 2016; or using 
a method approved by the Manager, International Section, Transport 
Standards Branch, FAA; or the European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA). Repeat 
the inspections thereafter at the applicable compliance times 
specified in table 1 to paragraphs (g) and (j) of this AD and table 
2 to paragraphs (g) and (j) of this AD, until the modification 
specified in paragraph (i) of this AD is done. Where the 
``Threshold'' column of table 1 to paragraphs (g) and (j) of this AD 
and table 2 to paragraphs (g) and (j) of this AD, specifies 
compliance times in ``FC'' (flight cycles), those compliance times 
are total flight cycles since the first flight of the airplane.
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(h) Airworthiness Limitations Item (ALI) Inspections Accomplished 
Before the Effective Date of This AD

    Inspections accomplished as specified in ALI task 534129 or task 
534130 before the effective date of this AD are acceptable for 
compliance with the initial inspection required by paragraph (g) of 
this AD. As of 30 days after the effective date of this AD, 
repetitive inspections must be continued as required by paragraph 
(g) of this AD.

(i) Optional Modification

    For airplanes on which no cracks were detected during any 
rototest inspection required by paragraph (g) of this AD: Modifying 
the affected area by cold working the fastener holes before further 
flight after no cracks were detected, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1290, 
Revision 01, dated October 3, 2016, terminates the repetitive 
inspections required by paragraph (g) of this AD for the modified 
area only.

(j) Post-Modification Repetitive Inspections

    For airplanes on which the modification specified in paragraph 
(i) of this AD has been done: At the compliance time specified in 
paragraphs (j)(1), (j)(2), or (j)(3) of this AD, as applicable, 
accomplish a rototest inspection of all holes at the door stop 
fitting locations at fuselage FR66 and FR68, both LH and RH sides, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 
03, dated October 3, 2016; or using a method approved by the 
Manager, International Section, Transport Standards Branch, FAA; or 
the European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). Repeat the inspection thereafter at 
intervals not to exceed the applicable compliance times specified in 
table 1 to paragraphs (g) and (j) of this AD and table 2 to 
paragraphs (g) and (j) of this AD.
    (1) For airplanes with less than 1,800 flight cycles accumulated 
since first flight of the airplane at the time of accomplishing the 
modification specified in paragraph (i) of this AD: At the 
applicable initial compliance time specified in table 1 to 
paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and 
(j) of this AD.
    (2) For airplanes with 1,800 flight cycles or more and less than 
13,800 flight cycles accumulated since first flight of the airplane 
at the time of accomplishing the modification specified in paragraph 
(i) of this AD: Before the accumulation of 48,000 flight cycles 
since first flight of the airplane.
    (3) For airplanes with 13,800 flight cycles or more accumulated 
since first flight of the airplane at the time of accomplishing the 
modification specified in paragraph (i) of this AD: Before the 
accumulation of 60,000 flight cycles since first flight of the 
airplane.

(k) Repair

    If, during any inspection required by paragraph (g) or (j) of 
this AD, any crack is detected, before further flight, repair using 
a method approved by the Manager, International Section, Transport 
Standards Branch, FAA; or EASA; or Airbus's EASA DOA. Repair of an 
airplane as required by this paragraph does not constitute 
terminating action for the repetitive inspections required by 
paragraph (g) or (j) of this AD for that airplane, unless specified 
otherwise in instructions obtained using a method approved by the 
Manager, International Section, Transport Standards Branch, FAA; or 
EASA; or Airbus's EASA DOA.

(l) Post-Repair Actions for Certain Airplanes

    For an airplane that has been inspected as specified in ALI task 
534129 or task 534130 and repaired before the effective date of this 
AD as specified in the applicable structural repair manual (SRM) or 
as specified in an Airbus repair design approval sheet (RDAS): 
Comply with the requirements of paragraphs (l)(1) and (l)(2) of this 
AD.
    (1) For all fastener holes where no damage or cracks were 
detected (i.e., those not repaired), accomplish the actions required 
by paragraph (g) of this AD, unless the terminating action specified 
in paragraph (m) of this AD has been done.
    (2) For all repaired fastener holes: Within 30 days after the 
effective date of this AD, or within a compliance time approved by 
the Manager, International Section, Transport Standards Branch, FAA; 
or EASA; or Airbus's EASA DOA, whichever occurs later, contact the 
Manager, International Section, Transport Standards Branch, FAA; or 
EASA; or Airbus's EASA DOA; for inspection instructions and 
applicable corrective actions, and do the inspections and applicable 
corrective actions accordingly.

(m) Terminating Action for Certain Airplanes

    For airplanes that have been inspected, as specified in ALI task 
534129 or task 534130, and repaired before the effective date of 
this AD, as specified in the applicable SRM, or as specified in an 
Airbus RDAS: Modification of the four fastener holes at door stop 
locations where no damage or crack was detected (i.e., door stop 
locations not repaired) by cold working holes before further flight 
after no cracks were detected, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1290, Revision 01, 
dated October 3, 2016, constitutes terminating action for the 
repetitive inspections of those four fastener holes at those door 
stop locations as required by paragraphs (g) or (l)(1) of this AD 
for that airplane.

(n) Actions for Airplanes With Certain Repairs

    For an airplane that has been repaired before the effective date 
of this AD in the areas described in this AD using an Airbus RDAS 
unrelated to ALI task 534129 or task 534130: Before exceeding the 
compliance times specified in paragraph (g) of this AD, contact the 
Manager, International Section, Transport Standards Branch, FAA; or 
EASA; or Airbus's EASA DOA; for corrective action instructions and 
accomplish those instructions accordingly. Accomplishment of 
corrective action(s) on an airplane, as required by this paragraph, 
does not constitute terminating action for the repetitive 
inspections as required by paragraphs (g) or (j) of this AD for that 
airplane, as applicable, unless specified otherwise in the 
instructions.

[[Page 5912]]

(o) Terminating Action for ALI Tasks

    (1) Accomplishment of inspections on an airplane, as required by 
paragraphs (g), (j), or (l) of this AD, as applicable, constitutes 
terminating action for the inspection requirements of ALI task 
534129 or task 534130, as applicable, for that airplane.
    (2) Modification of the four fastener holes at a door stop 
location of an airplane as specified in paragraphs (i) or (m) of 
this AD, as applicable, and subsequent initial inspection required 
by paragraph (j) of this AD, constitutes terminating action for the 
inspection requirements of ALI task 534129 or task 534130, as 
applicable, for those holes for that airplane. Subsequent repetitive 
inspections are required by paragraph (j) of this AD.

(p) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraphs (g) and (j) of this AD, if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A320-53-1288, including Appendixes 01 and 02, dated October 10, 
2014.
    (2) This paragraph provides credit for actions required by 
paragraphs (i) and (m) of this AD, if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A320-53-1290, dated October 10, 2014.

(q) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (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 (r)(2) of this AD. 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 
Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA 
DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
    (3) Required for Compliance (RC): 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.

(r) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0238, dated December 2, 2016; corrected January 
4, 2017, 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-2017-0707.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone: 
425-227-1405; fax: 425-227-1149.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (s)(3) and (s)(4) of this AD.

(s) 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.
    (i) Airbus Service Bulletin A320-53-1288, Revision 01, including 
Appendixes 01, 02, and 03, dated October 3, 2016.
    (ii) Airbus Service Bulletin A320-53-1290, Revision 01, dated 
October 3, 2016.
    (3) 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.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.
    (5) 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 January 29, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-02359 Filed 2-9-18; 8:45 am]
 BILLING CODE 4910-13-P


