[Federal Register Volume 83, Number 61 (Thursday, March 29, 2018)]
[Rules and Regulations]
[Pages 13387-13395]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-05019]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0902; Product Identifier 2016-NM-188-AD; Amendment 
39-19224; AD 2018-06-04]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

[[Page 13388]]


ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2004-03-07, 
which applied to certain Airbus Model A320-111, -211, -212, and -231 
series airplanes. AD 2004-03-07 required repetitive inspections for 
fatigue cracking around the fasteners attaching the pressure panel to 
the flexible bracket at a certain frame (FR), adjacent to the 
longitudinal beams on the left and right sides of the airplane; and 
repair as necessary. This new AD retains certain requirements of AD 
2004-03-07, expands the applicability, and requires an inspection of 
the fastener holes on the pressure panel and modification or repair as 
applicable. This AD was prompted by fatigue tests which revealed 
cracking around the fasteners attaching the pressure panel to the 
flexible bracket, and by the discovery of additional cracks under the 
longitudinal beams at locations that are not included in the inspection 
area required by AD 2004-03-07. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective May 3, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of May 3, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of March 
15, 2004 (69 FR 5907, February 9, 2004).

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, 2200 South 216th St., Des 
Moines, WA. For information on the availability of this material at the 
FAA, call 206-231-3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0902.

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-
0902; 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 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, 2200 South 
216th St., Des Moines, WA 98198; telephone 206-231-3223; fax 206-231-
3398.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2004-03-07, Amendment 39-13451 (69 FR 5907, 
February 9, 2004) (``AD 2004-03-07''). AD 2004-03-07 applied to certain 
Airbus Model A320-111, -211, -212, and -231 series airplanes. The NPRM 
published in the Federal Register on October 6, 2017 (82 FR 46729). The 
NPRM was prompted by fatigue tests which revealed cracking around the 
fasteners attaching the pressure panel to the flexible bracket at FR 
36, adjacent to the longitudinal beams on the left and right sides of 
the airplane, and by the discovery of additional cracks under the 
longitudinal beams at locations that are not included in the inspection 
area required by AD 2004-03-07. The NPRM proposed to continue to 
require certain requirements of AD 2004-03-07. The NPRM also proposed 
to expand the applicability and require an inspection of the fastener 
holes on the pressure panel between FR 35 and FR 36 under the 
longitudinal beam and modification or repair as applicable. We are 
issuing this AD to detect and correct fatigue cracking around the 
fasteners attaching the pressure panel to the flexible bracket at the 
FR 36 adjacent to the longitudinal beams, which could result in reduced 
structural integrity of the airplane and possible rapid decompression 
of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0206, dated October 13, 2016; corrected 
October 14, 2016 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for certain Airbus Model A318 and Model A319 series 
airplanes, Model A320-211, -212, -214, -231, -232, and -233 airplanes, 
and Model A321-111, -112, -131,-211, -21-, 213, -231, and -232 
airplanes. The MCAI states:

    During fatigue tests, cracks were found around the fasteners 
connecting the pressure panel with the flexible bracket at fuselage 
frame (FR) 36, adjacent to the longitudinal beams on left-hand (LH) 
and right-hand (RH) sides.
    This condition, if not detected and corrected, could impair the 
structural integrity of the aeroplane.
    To address this unsafe condition, DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France issued [French] 
AD 2000-531-155(B) [which corresponds with FAA AD 2004-03-07] to 
require repetitive inspections of the longitudinal beams of the FR 
36 pressure panel and, depending on findings, the accomplishment of 
a repair.
    Since that [French] AD was issued, additional cracks have been 
found under the beams, but in locations not covered by the required 
inspections. Fatigue and damage tolerance analyses were performed, 
the results of which indicated that all the holes in the pressure 
panel above all the longitudinal beams have to be cold worked.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD 2000-531-155(B), which is superseded, 
extends the applicability to all A320 family aeroplanes and requires 
[a special detailed inspection of the fastener holes on the pressure 
panel between FR35 and FR36 under the longitudinal beam and] 
modification [or repair] of all the affected holes.
    This [EASA] AD is republished to correct the number of the 
superseded DGAC 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-
0902.

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 Remove Reporting Requirement

    United Airlines (UAL) requested that we omit paragraph (k)(2)(ii) 
of the proposed AD, which would require operators to report any 
findings of cracking that exceeded the limits specified in Airbus 
Service Bulletin A320-53-1264, Revision 01, excluding Appendix 01, 
dated July 4, 2016, from the proposed AD. UAL stated that paragraph 
(k)(2)(ii) of the proposed AD is confusing and unjustified because 
there is no explanation for why it is required when it was not included 
in EASA AD 2016-0206. UAL stated the requirement to report findings in 
paragraph (k)(2)(ii) is redundant with the actions of paragraph 
(k)(2)(i) of the proposed AD. UAL noted that for the

[[Page 13389]]

crack repair specified in paragraph (k)(2)(i) of the proposed AD, the 
findings would be reported. UAL suggested the paragraph (k)(2)(ii) of 
the proposed AD required using an unconventional means to report 
findings that might require additional procedures and training specific 
to the proposed AD. UAL also stated that restricting reporting to a 
website may cause issues if the sender does not have access and that 
Airbus Service Bulletin A320-53-1264, Revision 01, excluding Appendix 
01, dated July 4, 2016, lists alternative options for reporting, like 
email, fax, or mail.
    We agree to remove the reporting requirement specified in paragraph 
(k)(2)(ii) of the proposed AD from this AD. Neither Airbus Service 
Bulletin A320-53-1264, Revision 01, excluding Appendix 01, dated July 
4, 2016, nor the MCAI specifically includes reporting to a website as 
specified in paragraph (k)(2)(ii) of the proposed AD. We note that 
Airbus Service Bulletin A320-53-1264, Revision 01, excluding Appendix 
01, dated July 4, 2016, does include reporting within the required for 
compliance (RC) procedure for the repair, which indicates that 
reporting would be required regardless of whether reporting was called 
out in the MCAI. We also verified with EASA that reporting should be 
done as defined in the service information. However, we have determined 
that a specific reporting requirement is not necessary. As stated by 
the commenter, operators will report findings to obtain the repair, 
which is specified in paragraph (k)(2)(i) of the proposed AD. We have 
removed paragraphs (k)(2)(i) and (k)(2)(ii) from this AD and revised 
paragraph (k)(2) of this AD to include the information that was in 
paragraph (k)(2)(i) of the proposed AD. We have also added paragraph 
(n) to this AD to specify that reporting is not required for this AD 
and redesignated the subsequent paragraphs accordingly.

Request To Refer to Latest Service Information

    Two commenters requested that we refer to the latest service 
information. UAL requested that we update paragraph (k) of the proposed 
AD to use Airbus Service Bulletin A320-53-1264, Revision 02, dated 
March 14, 2017, which corrects an error with the fastener lengths for 
part number (P/N) EN6115K3. We infer that UAL intended to refer to 
Airbus Service Bulletin A320-53-1240, Revision 02, dated March 14, 
2017, because there is no Revision 02 for Airbus Service Bulletin A320-
53-1264, and because P/N EN6115K3 is referenced in Airbus Service 
Bulletin A320-53-1240, Revision 02, dated March 14, 2017. Airbus 
requested that we refer to Airbus Service Bulletin A320-53-1240, 
Revision 02, dated March 14, 2017, in the proposed AD.
    We agree to refer to the latest service information in this AD. In 
addition to Airbus Service Bulletin A320-53-1240, Revision 02, dated 
March 14, 2017, we have also reviewed Airbus Service Bulletin A320-53-
1263, Revision 02, excluding Appendix 01 and including Appendix 02, 
dated December 6, 2017, which updates kit information and figures among 
other minor changes. We have revised paragraph (k)(1) of this AD 
accordingly. We have also provided credit for Airbus Service Bulletin 
A320-53-1240, Revision 01, dated April 4, 2016; and Airbus Service 
Bulletin A320-53-1263, Revision 01, dated February 29, 2016; in 
paragraphs (o)(3)(ii) and (o)(3)(iv) of this AD, respectively.

Request To Include Additional Airplane Models in the Applicability

    Airbus requested that Model A320-215 and Model A320-216 airplanes 
be in included in the applicability of the proposed AD. The commenter 
noted that these airplane models are included in the MCAI.
    We do not agree with the commenter's request. We have not certified 
Model A320-215 airplanes for operation in the U.S., and therefore, we 
did not include that model in the applicability of this AD. We did not 
include Model A320-216 airplanes in the applicability of this AD 
because the MCAI was already added to the required airworthiness action 
list (RAAL) for Model A320-216 airplanes. We have not changed this AD 
in this regard.

Request To Revise Service Bulletin Descriptions in the Related Service 
Information Under 1 CFR Part 51 Paragraph in the Preamble of the NPRM

    Airbus stated that the proposed AD identifies the means of 
inspection, i.e., rototest inspection, using three different wordings 
in the descriptions of the service bulletins specified in the Related 
Service Information under 1 CFR part 51 paragraph in the preamble of 
the NPRM. Airbus also stated that Service Bulletin A320-53-1240, 
Revision 02, dated March 14, 2017, no longer contains a rototest 
inspection requirement. In addition, Airbus noted that Service Bulletin 
A320-53-1240, Revision 02, dated March 14, 2017, does not contain 
repair instructions. We infer the commenter is requesting that we 
revise the service bulletin descriptions in the Related Service 
Information under 1 CFR part 51 paragraph in the preamble of the NPRM.
    We acknowledge the description of the rototest inspection is 
different for each service bulletin specified in the Related Service 
Information under 1 CFR part 51 paragraph in the preamble of the NPRM. 
In the NPRM, we matched the description of the inspection as given in 
each service bulletin specified in the Related Service Information 
under 1 CFR part 51 paragraph. We have revised the description of 
Airbus Service Bulletin A320-53-1240, Revision 02, dated March 14, 
2017, to remove the reference to an inspection and repair.

Request To Clarify What Prompted the Proposed AD

    Airbus requested that we revise paragraph (e) of the proposed AD to 
clarify that the proposed AD was prompted by a report of cracking in an 
additional area. Airbus stated that paragraph (e) of the proposed AD 
describes only the fatigue test results that prompted AD 2004-03-07.
    We agree to revise paragraph (e) of this AD for clarity. This AD 
was prompted by the original report of cracking and the additional 
report. We have revised paragraph (e) of this AD to include the 
additional cracking that prompted the issuance of this AD.

Request To Revise Repair Language in Paragraph (k)(2)(i) of the 
Proposed AD

    Airbus requested that we revise the language in paragraph (k)(2)(i) 
of the proposed AD, which specifies to repair any cracking in 
accordance with Airbus Service Bulletin A320-53-1264, Revision 01, 
excluding Appendix 01, dated July 4, 2016. Airbus stated that this 
service information does not provide direct repair instructions and 
instead specifies to contact Airbus.
    We agree to clarify the language in paragraph (k)(2) of this AD 
(which corresponds with paragraph (k)(2)(i) of the proposed AD). 
Paragraph (k)(2) of this AD also specifies that where Airbus Service 
Bulletin A320-53-1264, Revision 01, excluding Appendix 01, dated July 
4, 2016, specifies to contact Airbus for appropriate action, and 
specifies that action as ``RC'' (Required for Compliance), operators 
must request approval of repair instructions using a method approved in 
accordance with the procedures specified in paragraph (p)(2) of this 
AD, and accomplish the repair accordingly within the compliance time 
specified in those instructions. We have not changed this AD in this 
regard.

[[Page 13390]]

Request To Include Wording From the MCAI in Paragraph (m)(1)(iii) of 
the Proposed AD

    Airbus requested that we revise paragraph (m)(1)(iii) of the 
proposed AD. Airbus stated the wording is similar to paragraph (9) of 
the MCAI except that the important wording ``in accordance with Airbus 
approved instructions that identify the repair as technically 
equivalent to the accomplishment of Airbus SB A320-53-1240 or SB A320-
53-1263'' is omitted.
    We disagree with the commenter's request. The intent of paragraph 
(m)(1)(iii) of this AD is to obtain corrective actions from the 
manufacturer that are approved by the FAA, EASA, or Airbus's EASA 
Design Organization Approval (DOA). These approved instructions will 
provide an equivalent level of safety. We have not changed this AD in 
this regard.

Conclusion

    We reviewed the available data, including 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 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 Service Bulletin A320-53-1029, Revision 01, 
including Appendix 01, dated April 29, 2002. The service information 
describes procedures for repairing cracking.
    Airbus has also issued Service Bulletin A320-53-1240, Revision 01, 
dated April 4, 2016; and A320-53-1240, Revision 02, dated March 14, 
2017, which describe procedures for modifying the pressure panel above 
the left and right longitudinal beams, by cold working the attachment 
holes under the longitudinal beam at FR 36 for airplanes on which no 
cracking was found. Service Bulletin A320-53-1240, Revision 01, dated 
April 4, 2016 also includes related investigative action (e.g., high 
frequency eddy current (rototest) inspection of all the removed 
fastener holes) and corrective actions (e.g., repair). These documents 
are distinct since they are different revision levels.
    Airbus has also issued Service Bulletin A320-53-1263, Revision 01, 
dated February 29, 2016; and A320-53-1263, Revision 02, excluding 
Appendix 01 and including Appendix 02, dated December 6, 2017, which 
describe procedures for modifying the pressure panel above the left and 
right longitudinal beams, including related investigative actions 
(e.g., eddy current rotating probe inspection of the fastener holes) 
and corrective actions (e.g., repair), by adding a doubler and a 
filler, and cold expansion of the holes under the longitudinal beam at 
FR 36 for airplanes on which cracking was found. These documents are 
distinct because they are different revision levels.
    Airbus has also issued Service Bulletin A320-53-1264, Revision 01, 
excluding Appendix 01, dated July 4, 2016. The service information 
describes procedures for a special detailed inspection (rotating probe) 
for cracking of the fastener holes on the pressure panel between FR 35 
and FR 36 under the longitudinal beam and repair of any crack.
    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 737 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
----------------------------------------------------------------------------------------------------------------
Inspection [Retained from AD     Up to 2 work-hours x                 $0  Up to $170 per      Up to $125,290 per
 2004-03-07].                     $85 per hour = $170                      inspection cycle.   inspection cycle.
                                  per inspection cycle.
Inspection [new proposed         13 work-hours x $85 per              $0  $1,105............  $814,385.
 requirement].                    hour = $1,105.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary modifications 
that will be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need these 
modifications:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
               Action                         Labor cost                Parts cost           Cost per product
----------------------------------------------------------------------------------------------------------------
Modification.......................  Up to 213 work-hours x $85   Up to $8,510..........  Up to $26,615.
                                      per hour = $18,105.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that will enable us to provide 
a cost estimate for the on-condition repairs specified in this AD.

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.

[[Page 13391]]

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 removing Airworthiness Directive 
(Airworthiness Directive (AD) 2004-03-07, Amendment 39-13451 (69 FR 
5907, February 9, 2004), and adding the following new AD:

2018-06-04 Airbus: Amendment 39-19224; Docket No. FAA-2017-0902; 
Product Identifier 2016-NM-188-AD.

(a) Effective Date

    This AD is effective May 3, 2018.

(b) Affected ADs

    This AD replaces AD 2004-03-07, Amendment 39-13451 (69 FR 5907, 
February 9, 2004) (``AD 2004-03-07'').

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, 
except for airplanes on which Airbus Modification 151574 was 
embodied in production.
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
    (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by fatigue tests which revealed cracking 
around the fasteners attaching the pressure panel to the flexible 
bracket at frame (FR) 36, adjacent to the longitudinal beams on the 
left and right sides of the airplane, and by the discovery of 
additional cracks under the longitudinal beams at locations that are 
not included in the inspection area required by AD 2004-03-07. We 
are issuing this AD to detect and correct fatigue cracking around 
the fasteners attaching the pressure panel to the flexible bracket 
at the FR 36 adjacent to the longitudinal beams, which could result 
in reduced structural integrity of the airplane and possible rapid 
decompression of the airplane.

(f) Compliance

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

(g) Retained Inspection and Follow-on Actions, With No Changes

    This paragraph restates the requirements of paragraphs (a) and 
(b) of AD 2004-03-07, with no changes.
    (1) For Model A320-211, -212, and -231 series airplanes having 
serial numbers 0002 through 0107 inclusive, except those airplanes 
on which Airbus Modification 21202/K1432 has been incorporated in 
production, or on which Airbus Service Bulletin A320-53-1029, 
Revision 01, including Appendix 01, dated April 29, 2002, has been 
incorporated in service: Prior to the accumulation of 30,000 total 
flight cycles, do a rotating probe inspection on airplanes with a 
center fuel tank, or a detailed inspection on airplanes without a 
center fuel tank, to detect cracking around the fasteners that 
attach the pressure panel to the flexible bracket at FR 36, adjacent 
to the longitudinal beams on the left and right sides of the 
airplane, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1030, Revision 01, excluding 
Appendix 01, dated May 21, 2002.
    (2) If no crack is detected by the inspection required by 
paragraph (g)(1) of this AD, repeat the applicable inspection 
thereafter at intervals not to exceed 6,000 flight cycles for 
airplanes without a center fuel tank, and at intervals not to exceed 
18,000 flight cycles for airplanes with a center fuel tank.

(h) Retained Corrective Actions, With Specific Delegation Approval 
Language

    This paragraph restates the requirements of paragraphs (c) and 
(d) of AD 2004-03-07, with specific delegation approval language.
    (1) If any crack is detected during any inspection required by 
paragraph (g)(1) of this AD, before further flight, repair the 
affected structure by accomplishing all applicable actions in 
accordance with paragraphs 3.B. through 3.E. of the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1030, Revision 01, 
excluding Appendix 01, dated May 21, 2002. Repeat the applicable 
inspection thereafter at intervals not to exceed 6,000 flight cycles 
for airplanes without a center fuel tank, and at intervals not to 
exceed 18,000 flight cycles for airplanes with a center fuel tank. 
For any area where cracking is repaired, the repair constitutes 
terminating action for the repetitive inspection of that area.
    Note 1 to paragraph (h)(1) of this AD: Airbus Service Bulletin 
A320-53-1030 references Airbus Service Bulletin A320-53-1029, 
Revision 01, including Appendix 01, dated April 29, 2002, as an 
additional source of service information for certain repairs.
    (2) If Airbus Service Bulletin A320-53-1030, Revision 01, 
excluding Appendix 01, dated May 21, 2002, specifies to contact the 
manufacturer for appropriate action: Before further flight, repair 
using a method approved in accordance with the procedures specified 
in paragraph (p)(2) of this AD.

(i) Retained Optional Terminating Action, With Revised Compliance 
Language

    This paragraph restates the requirements of paragraph (e) of AD 
2004-03-07, with revised compliance language, to provide optional 
terminating action for paragraphs (g) and (h) of this AD. For Model 
A320-211, -212, and -231 series airplanes having serial numbers 0002 
through 0107 inclusive, except those airplanes on which Airbus 
Modification 21202/K1432 has been incorporated in production, or 
Airbus Service Bulletin A320-53-1029, Revision 01, including 
Appendix 01, dated April 29, 2002, has been incorporated in service: 
Modification, before the effective date of this AD, of the structure 
around the fasteners that attach the pressure panel to the flexible 
bracket at FR 36, adjacent to the longitudinal beams on the left and 
right sides of the airplane, by accomplishing all applicable actions 
in accordance with paragraphs 3.A. through 3.E. of the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1029, 
Revision 01, including Appendix 01, dated April 29, 2002, 
constitutes terminating action for the actions required by 
paragraphs (g) and (h) of this AD.

(j) New Requirement of This AD: Inspection

    For all airplanes, except for airplanes identified in paragraph 
(l) of this AD: At the applicable time specified in table 1 to 
paragraph (j) of this AD, do a special detailed inspection for 
cracking of the fastener holes

[[Page 13392]]

on the pressure panel between FR 35 and FR 36 under the longitudinal 
beam, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-53-1264, Revision 01, excluding Appendix 01, 
dated July 4, 2016.
[GRAPHIC] [TIFF OMITTED] TR29MR18.007

[GRAPHIC] [TIFF OMITTED] TR29MR18.008


[[Page 13393]]


[GRAPHIC] [TIFF OMITTED] TR29MR18.009

[GRAPHIC] [TIFF OMITTED] TR29MR18.010

(k) On-Condition Actions

    (1) If, during any inspection required by paragraph (j) of this 
AD, no cracking is found, or cracking is found that is within the 
limits specified in Airbus Service Bulletin A320-53-1264, Revision 
01, excluding Appendix 01, dated July 4, 2016: Before further 
flight, modify the pressure panel above the left and right 
longitudinal beams, including doing all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1240, 
Revision 02, dated March 14, 2017; or Service Bulletin A320-53-1263, 
Revision 02, excluding

[[Page 13394]]

Appendix 01 and including Appendix 02, dated December 6, 2017, as 
applicable. Do all related investigative and corrective actions 
before further flight. Where Airbus Service Bulletin A320-53-1240, 
Revision 02, dated March 14, 2017; or Service Bulletin A320-53-1263, 
Revision 02, excluding Appendix 01 and including Appendix 02, dated 
December 6, 2017; specify to contact Airbus for appropriate action: 
Before further flight, accomplish the repair using a method approved 
in accordance with the procedures specified in paragraph (p)(2) of 
this AD.
    (2) If, during any inspection required by paragraph (j) of this 
AD, any cracking is found that exceeds the limits specified in 
Airbus Service Bulletin A320-53-1264, Revision 01, excluding 
Appendix 01, dated July 4, 2016: Before further flight, repair any 
cracking in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1264, Revision 01, excluding 
Appendix 01, dated July 4, 2016. Where Airbus Service Bulletin A320-
53-1264, Revision 01, excluding Appendix 01, dated July 4, 2016, 
specifies to contact Airbus for appropriate action, and specifies 
that action as ``RC'' (Required for Compliance), before further 
flight, request approval of repair instructions using a method 
approved in accordance with the procedures specified in paragraph 
(p)(2) of this AD, and accomplish the repair accordingly within the 
compliance time specified in those instructions. If no compliance 
time is defined in the repair instructions, accomplish the repair 
before further flight.

(l) Actions for Certain Airplanes

    For Model A319 and Model A320 series airplanes on which the 
actions specified in Airbus Service Bulletin A320-57-1193 have been 
embodied and the airplane has accumulated 33,000 flight cycles or 
66,000 flight hours or more since the airplane's first flight on the 
effective date of this AD: Within 30 days after the effective date 
of this AD, contact the Manager, International Section, Transport 
Standards Branch FAA; or the European Aviation Safety Agency (EASA); 
or Airbus's EASA Design Organization Approval (DOA) for approved 
repair instructions and within the compliance time specified in 
those instructions, accomplish the repair accordingly. If approved 
by the DOA, the approval must include the DOA-authorized signature. 
If no compliance time is defined in the repair instructions, 
accomplish the repair before the next flight.

(m) Terminating Action for Repetitive Inspections

    (1) Modification of an airplane as specified in paragraph 
(m)(1)(i), (m)(1)(ii), or (m)(1)(iii) of this AD constitutes 
terminating action for the repetitive inspection required by 
paragraph (g)(2) of this AD for that airplane only.
    (i) Modification of an airplane as required by paragraph (k)(1) 
of this AD.
    (ii) Modification of an airplane prior to the effective date of 
this AD, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1240, Revision 01, dated April 4, 
2016; or Airbus Service Bulletin A320-53-1263, Revision 01, dated 
February 29, 2016; as applicable.
    (iii) Modification of an airplane using instructions obtained in 
accordance with the procedures specified in paragraph (p)(2) of this 
AD.
    (2) Repair of an airplane as required by paragraph (k)(2) of 
this AD constitutes terminating action for the repetitive 
inspections required by paragraph (g)(2) of this AD for that 
airplane, unless specified otherwise in the repair instructions 
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.

(n) No Reporting Requirement

    Although Airbus Service Bulletin A320-53-1264, Revision 01, 
excluding Appendix 01, dated July 4, 2016, specifies to submit 
certain information to the manufacturer, and specifies that action 
as ``RC'' (Required for Compliance), this AD does not include that 
requirement.

(o) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraphs (g) and (h)(1) of this AD, if those actions were 
performed before March 15, 2004 (the effective date of AD 2004-03-
07) using Airbus Service Bulletin A320-53-1030, dated January 5, 
2000; or Airbus Service Bulletin A320-53-1029, dated January 5, 
2000.
    (2) This paragraph provides credit for actions required by 
paragraph (j) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-53-
1264, dated March 19, 2015.
    (3) This paragraph provides credit for actions required by 
paragraph (k)(1) of this AD, if those actions were performed before 
the effective date of this AD using the applicable service 
information specified in paragraphs (o)(3)(i) through (o)(3)(iv) of 
this AD, for that airplane only.
    (i) Airbus Service Bulletin A320-53-1240, dated March 19, 2015.
    (ii) Airbus Service Bulletin A320-53-1240, Revision 01, dated 
April 4, 2016.
    (iii) Airbus Service Bulletin A320-53-1263, dated March 19, 
2015.
    (iv) Airbus Service Bulletin A320-53-1263, Revision 01, dated 
February 29, 2016.
    (4) This paragraph provides credit for actions required by 
paragraph (m)(1)(ii) of this AD if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A320-53-1240, dated March 19, 2015; or Service Bulletin A320-53-
1263, dated March 19, 2015.

(p) 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 Branch, send it to the attention of 
the person identified in paragraph (q)(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: 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 the European Aviation Safety Agency (EASA); or 
Airbus's EASA Design Organization Approval (DOA). If approved by the 
DOA, the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraphs (k)(2) and (n) of this 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.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0206, dated October 13, 2016; corrected October 
14, 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-2017-0902.
    (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 
206-231-3223; fax 206-231-3398.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (r)(5) and (r)(6) of this AD.

(r) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
May 3, 2018.
    (i) Airbus Service Bulletin A320-53-1029, Revision 01, including 
Appendix 01, dated April 29, 2002.
    (ii) Airbus Service Bulletin A320-53-1240, Revision 01, dated 
April 4, 2016.
    (iii) Airbus Service Bulletin A320-53-1240, Revision 02, dated 
March 14, 2017.

[[Page 13395]]

    (iv) Airbus Service Bulletin A320-53-1263, Revision 01, dated 
February 29, 2016.
    (v) Airbus Service Bulletin A320-53-1263, Revision 02, excluding 
Appendix 01 and including Appendix 02, dated December 6, 2017.
    (vi) Airbus Service Bulletin A320-53-1264, Revision 01, 
excluding Appendix 01, dated July 4, 2016.
    (4) The following service information was approved for IBR on 
March 15, 2004 (69 FR 5907, February 9, 2004).
    (i) Airbus Service Bulletin A320-53-1030, Revision 01, excluding 
Appendix 01, dated May 21, 2002.
    (ii) Reserved.
    (5) 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.
    (6) 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.
    (7) 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 March 2, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-05019 Filed 3-28-18; 8:45 am]
 BILLING CODE 4910-13-P