Document ID: FAA-2015-1275-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2016-01-14T05:00Z

[Federal Register Volume 81, Number 9 (Thursday, January 14, 2016)]
[Rules and Regulations]
[Pages 1870-1874]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-32519]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1275; Directorate Identifier 2014-NM-070-AD; 
Amendment 39-18354; AD 2015-26-06]
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 superseding Airworthiness Directive (AD) 2004-14-09 for 
certain Airbus Model A320-211, -212, and -231 airplanes. AD 2004-14-09 
required repetitive inspections for fatigue cracking of the lower 
surface panel on the wing center box, and repair if necessary; and 
modification of the lower surface panel on the wing center box, which 
constitutes terminating action for the repetitive inspections. This new 
AD retains the requirements of AD 2004-14-09, reduces the compliance 
times for the repetitive inspections, and requires an additional repair 
for certain airplanes. This AD was

[[Page 1871]]

prompted by a determination that, based on the average flight duration, 
the average weight of fuel at landing is higher than that defined for 
the analysis of the fatigue-related tasks; and that shot peening might 
have been improperly done on the chromic acid anodizing (CAA) 
protection, which would adversely affect fatigue crack protection. We 
are issuing this AD to detect and correct fatigue cracking of the lower 
surface panel on the wing center box, which could result in reduced 
structural integrity of the airplane.

DATES: This AD becomes effective February 18, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 18, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of August 
13, 2004 (69 FR 41398, July 9, 2004).
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
November 27, 1998 (63 FR 56542, October 22, 1998).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-1275; or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    For 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 account.airworth-eas@airbus.com; 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
1275.

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

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2004-14-09, Amendment 39-13718 (69 FR 41398, 
July 9, 2004). AD 2004-14-09 applied to certain Airbus Model A320-211, 
-212, and -231 airplanes. The NPRM published in the Federal Register on 
May 8, 2015 (80 FR 26492). The NPRM was prompted by a determination 
that, based on the average flight duration, the average weight of fuel 
at landing is higher than that defined for the analysis of the fatigue-
related tasks; and that shot peening might have been improperly done on 
the CAA protection, which would adversely affect fatigue crack 
protection. The NPRM proposed to continue to require repetitive 
inspections for fatigue cracking of the lower surface panel on the wing 
center box, and repair if necessary; and modification of the lower 
surface panel on the wing center box, which constitutes terminating 
action for the repetitive inspections. The NPRM also proposed to reduce 
the compliance times for the repetitive inspections, and would require 
a repair for certain airplanes. We are issuing this AD to detect and 
correct fatigue cracking of the lower surface panel on the wing center 
box, which could result in reduced structural integrity 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 2014-0065, dated March 14, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on certain Model A320-
211, -212, and -231 airplanes. The MCAI states:

    During center fuselage certification full scale test, damage was 
found in the center wing box (CWB) lower surface panel.
    This condition, if not detected and corrected, could affect the 
structural integrity of the CWB.
    To prevent such damage, Airbus developed mod 22418 which 
consists in shot-peening of the lower panel in the related area. Mod 
22418 has been embodied in production from aeroplane [manufacturer 
serial number] (MSN) 0359. For unmodified in-service aeroplanes, 
Airbus issued Service Bulletin (SB) A320-57-1082 to introduce 
repetitive High Frequency Eddy Current (HFEC) inspections on the 
external face of the center wing box lower panel between Frame (FR) 
41 and FR42 to detect damage.
    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France issued AD 2002-342 [http://ad.easa.europa.eu/blob/20023420tb_superseded.pdf/AD_F-2002-342_1] to require these 
inspections and, depending on findings, applicable corrective 
action(s). Airbus also issued SB A320-57-1043 as an optional 
terminating action for the repetitive inspections required by DGAC 
France AD 2002-342.
    Since that [DGAC] AD was issued, the results of a survey, 
carried out on the A320 fleet, highlighted some differences between 
the mission parameters, mainly on the weight of fuel at landing and 
on the average flight duration, which are higher than those defined 
for the analysis of the fatigue related tasks.
    These findings have led to an adjustment of the A320 reference 
fatigue mission. Consequently, the threshold and intervals of these 
repetitive inspections have been revised and a new threshold figure 
expressed in flight hours (FH) has been established.
    In addition, it has been identified that, on aeroplanes that 
have been modified in accordance with Airbus SB A320-57-1043 (Airbus 
mod 22418) at Revision 05 or an earlier Revision, the shot peening 
may have been improperly done on the Chromic Acid Anodizing (CAA) 
protection, which has no fatigue benefit effect. Therefore, the 
inspections per Airbus SB A320-57-1082 are required again on these 
aeroplanes.
    Consequently, new shot-peening procedures with proper CAA 
protection removal instructions have been developed and their 
embodiment through Airbus SB A320-57-1043 Revision 06 cancels the 
repetitive inspections per Airbus SB A320-57-1082, as required by 
DGAC France AD 2002-342.
    For the reasons described above, this new [EASA] AD retains the 
requirements of DGAC France AD 2002-342, which is superseded, but 
requires these actions to be accomplished within reduced thresholds 
and intervals. In addition, the optional terminating action 
provision (SB A320-57-1043) is amended by including reference to the 
SB at Revision 06.

    The optional terminating action described in Airbus Service 
Bulletin A320-57-1043, Revision 06, dated December 5, 2013, is 
accomplishing shot peening in the radius of the milling step between 
stiffeners 13 and 14 near the fuel pump aperture. You may examine the 
MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-1275-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (80 FR 26492, May 8, 2015) 
or on the determination of the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR

[[Page 1872]]

26492, May 8, 2015) for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 26492, May 8, 2015).

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-57-1043, Revision 06, dated 
December 5, 2013. This service information describes procedures for 
shot peening in the radius of the milling step between stiffeners 13 
and 14 near the fuel pump aperture.
    Airbus has also issued Service Bulletin A320-57-1082, Revision 04, 
dated December 5, 2013. This service information describes procedures 
for inspections for cracking of the lower surface panel on the wing 
center box.
    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 46 airplanes of U.S. registry.
    The actions that were required by AD 2004-14-09, Amendment 39-13718 
(69 FR 41398, July 9, 2004), and retained in this AD take about 25 
work-hours per product, at an average labor rate of $85 per work-hour. 
Based on these figures, the estimated cost of the actions that were 
required by AD 2004-14-09 is $2,125 per product.
    The new requirements of this AD will add no additional economic 
burden.
    We have received no definitive data that will enable us to provide 
cost estimates for the on-condition actions specified in this AD. We 
have no way of determining the number of aircraft that might need these 
actions.

Authority for This Rulemaking

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

Regulatory Findings

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

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-1275; or in person at the 
Docket Management Facility between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The AD docket contains this AD, the 
regulatory evaluation, any comments received, and other information. 
The street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), and adding 
the following new AD:

2015-26-06 Airbus: Amendment 39-18354. Docket No. FAA-2015-1275; 
Directorate Identifier 2014-NM-070-AD.

(a) Effective Date

    This AD becomes effective February 18, 2016.

(b) Affected ADs

    This AD replaces AD 2004-14-09, Amendment 39-13718 (69 FR 41398, 
July 9, 2004).

(c) Applicability

    This AD applies to Airbus Model A320-211, -212, and -231 
airplanes, certificated in any category, all manufacturer serial 
numbers, except those on which Airbus Modification 22418 has been 
embodied in production.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by a determination that, based on the 
average flight duration, the average weight of fuel at landing is 
higher than that defined for the analysis of the fatigue-related 
tasks; and that shot peening might have been improperly done on the 
chromic acid anodizing (CAA) protection, which would adversely 
affect fatigue crack protection. We are issuing this AD to detect 
and correct fatigue cracking of the lower surface panel on the wing 
center box (WCB), which could result in reduced structural integrity 
of the airplane.

(f) Compliance

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

(g) Retained Repetitive Inspections, With No Changes

    This paragraph restates the requirements of paragraph (a) of AD 
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no 
changes. Except as provided by paragraph (k) of this AD: Prior to 
the accumulation of 20,000 total flight cycles, or within 60 days 
after November 27, 1998 (the effective date of AD 98-22-05, 
Amendment 39-10851 (63 FR 56542, October 22, 1998)), whichever 
occurs later, perform a high frequency eddy current (HFEC) 
inspection to detect fatigue cracking of the lower surface panel on 
the WCB, in accordance with Airbus Service Bulletin A320-57-1082, 
Revision 01, dated December 10, 1997; or Revision 03, dated April 
30, 2002. Repeat the HFEC inspection thereafter at intervals not to 
exceed 7,500 flight cycles until the actions required by paragraph 
(i) of this AD are accomplished.

(h) Retained Repair, With No Changes

    This paragraph restates the requirements of paragraph (b) of AD 
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no 
changes. Except as provided by paragraph (j) of this AD, if any 
cracking is detected during any inspection required by paragraph (g) 
of this AD: Prior to further flight, repair in accordance with 
Airbus

[[Page 1873]]

Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997; 
or Revision 03, dated April 30, 2002. Accomplishment of the repair 
constitutes terminating action for the repetitive inspections 
required by paragraph (g) of this AD for the repaired area only.

(i) Retained Inspection/Modification/Repair, With New Terminating 
Action

    This paragraph restates the requirements of paragraph (c) of AD 
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with new 
terminating action provided. Prior to the accumulation of 25,000 
total flight cycles, or within 60 days after November 27, 1998 (the 
effective date of AD 98-22-05, Amendment 39-10851 (63 FR 56542, 
October 22, 1998)), whichever occurs later: Perform an HFEC 
inspection to detect fatigue cracking of the lower surface panel on 
the WCB, in accordance with Airbus Service Bulletin A320-57-1082, 
Revision 01, dated December 10, 1997; or Revision 03, dated April 
30, 2002. Accomplishment of the initial inspection required by 
paragraph (p) of this AD constitutes terminating action for the 
inspection requirements of this paragraph.
    (1) If no cracking is detected: Prior to further flight, modify 
the lower surface panel on the WCB, in accordance with Airbus 
Service Bulletin A320-57-1043, Revision 02, dated May 14, 1997; or 
Revision 05, dated April 30, 2002. Accomplishment of the 
modification constitutes terminating action for the requirements of 
paragraph (g) of this AD.
    (2) Except as provided by paragraph (j) of this AD: If any 
cracking is detected, prior to further flight, repair in accordance 
with Airbus Service Bulletin A320-57-1082, Revision 01, dated 
December 10, 1997, or Revision 03, dated April 30, 2002; and modify 
any uncracked area, in accordance with Airbus Service Bulletin A320-
57-1043, Revision 02, dated May 14, 1997, or Revision 05, dated 
April 30, 2002. Accomplishment of the repair of cracked area(s) and 
modification of uncracked area(s) constitutes terminating action for 
the requirements of paragraph (g) of this AD.

(j) Retained Service Bulletin Exception, With Revised Repair 
Instructions

    This paragraph restates the requirements of paragraph (d) of AD 
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with 
revised repair instructions. If any cracking is detected during any 
inspection required by paragraph (h) or (i)(2) of this AD, and the 
applicable service bulletin specifies to contact Airbus for an 
appropriate action: Prior to further flight, repair using a method 
approved by the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate; or the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated 
agent); or the European Aviation Safety Agency (EASA); or Airbus's 
EASA Design Organization Approval (DOA). After the effective date of 
this AD only repair using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the EASA; or Airbus's EASA DOA.

(k) Retained Provision for Certain Inspection Exception, With No 
Changes

    This paragraph restates the provision of paragraph (e) of AD 
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no 
changes. The actions required by paragraph (g) of this AD are not 
required to be accomplished if the requirements of paragraph (i) of 
this AD are accomplished at the time specified in paragraph (g) of 
this AD.

(l) Retained Initial Inspection, With Terminating Action

    This paragraph restates the requirements of paragraph (f) of AD 
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with 
terminating action provided. For airplanes on which neither the 
inspection required by paragraph (g) of this AD nor the modification 
required by paragraph (i)(1) of this AD has been done before August 
13, 2004 (the effective date of AD 2004-14-09): Perform an HFEC 
inspection to detect fatigue cracking of the lower surface panel on 
the WCB, in accordance with Airbus Service Bulletin A320-57-1082, 
Revision 01, dated December 10, 1997; or Revision 03, dated April 
30, 2002; at the later of the times specified in paragraphs (l)(1) 
and (l)(2) of this AD. Accomplishment of the inspection required by 
this paragraph terminates the requirements of paragraph (g) of this 
AD. Accomplishment of the initial inspection required by paragraph 
(p) of this AD terminates the inspection requirements of this 
paragraph.
    (1) Prior to the accumulation of 13,200 total flight cycles or 
39,700 total flight hours, whichever is first.
    (2) Prior to the accumulation of 20,000 total flight cycles, or 
within 3,500 flight cycles after August 13, 2004 (the effective date 
of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004)), 
whichever is later.

(m) Retained Repetitive Inspections, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no 
changes. If no cracking is detected during the inspection required 
by paragraph (g) or (l) of this AD: Repeat the inspection required 
by paragraph (l) of this AD at the applicable time specified in 
paragraph (m)(1) or (m)(2) of this AD. Accomplishment of the 
modification required by paragraph (i)(1) of this AD terminates the 
requirements of this paragraph.
    (1) For airplanes on which the inspections required by paragraph 
(g) of this AD have been initiated before August 13, 2004 (the 
effective date of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, 
July 9, 2004)): Do the next inspection within 5,700 flight cycles 
after accomplishment of the last inspection, or within 1,800 flight 
cycles after August 13, 2004, whichever is later. Repeat the 
inspection thereafter at intervals not to exceed 5,700 flight 
cycles.
    (2) For airplanes on which no inspection required by paragraph 
(g) of this AD has been done before August 13, 2004 (the effective 
date of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 
2004)): Do the next inspection within 5,700 flight cycles after 
accomplishment of the inspection required by paragraph (l) of this 
AD. Repeat the inspection thereafter at intervals not to exceed 
5,700 flight cycles.

(n) Retained Repair/Modification, With Revised Repair Instructions

    This paragraph restates the requirements of paragraph (h) of AD 
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with 
revised repair instructions. If any cracking is detected during any 
inspection required by paragraph (l) or (m) of this AD, prior to 
further flight, repair in accordance with Airbus Service Bulletin 
A320-57-1082, Revision 01, dated December 10, 1997, or Revision 03, 
dated April 30, 2002; and modify any uncracked area, in accordance 
with Airbus Service Bulletin A320-57-1043, Revision 02, dated May 
14, 1997, or Revision 05, dated April 30, 2002. Where Airbus Service 
Bulletin A320-57-1082 specifies to contact Airbus for an appropriate 
repair action: Prior to further flight, repair using a method 
approved by the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate; or the DGAC (or its delegated 
agent)); or EASA; or Airbus's EASA DOA. After the effective date of 
this AD only repair using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA; or Airbus's EASA DOA. Accomplishment of the repair of 
cracked area(s) and modification of uncracked area(s) constitutes 
terminating action for the requirements of paragraphs (g) through 
(n) of this AD.

(o) New Requirement of This AD: Repair of Certain Airplanes

    For airplanes on which the actions specified in Airbus Service 
Bulletin A320-57-1043 have not been accomplished, and on which a 
repair has been accomplished, as specified in the service 
information identified in paragraph (o)(1), (o)(2), (o)(3), or 
(o)(4) of this AD: Within 30 days after the effective date of this 
AD, repair using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; the EASA; or 
Airbus's EASA DOA.
    (1) Airbus Service Bulletin A320-57-1082, dated October 31, 
1996.
    (2) Airbus Service Bulletin A320-57-1082, Revision 01, dated 
December 10, 1997.
    (3) Airbus Service Bulletin A320-57-1082, Revision 02, dated 
July 26, 1999.
    (4) Airbus Service Bulletin A320-57-1082, Revision 03, dated 
April 30, 2002.

(p) New Requirement of This AD: Repetitive WCB Inspections

    At the applicable time specified in paragraphs (p)(1) and (p)(2) 
of this AD: Do an HFEC inspection for cracking of the lower surface 
panel on the WCB, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A320-57-1082, Revision 04, dated December 
5, 2013. Repeat the inspection of the lower surface panel on the WCB 
thereafter at intervals not to exceed 7,200 flight cycles or 14,400 
flight hours, whichever occurs first. Accomplishment of

[[Page 1874]]

the initial inspection required by this paragraph terminates the 
inspections required by paragraphs (g), (i), and (l) of this AD.
    (1) For airplanes on which the actions specified in Airbus 
Service Bulletin A320-57-1043 have not been done: At the later of 
the times specified in paragraphs (p)(1)(i) and (p)(1)(ii) of this 
AD.
    (i) Before the accumulation of 20,700 flight cycles or 41,400 
flight hours, whichever occurs first since first flight of the 
airplane.
    (ii) Within 7,200 flight cycles or 14,400 flight hours, 
whichever occurs first after doing the most recent inspection as 
specified in the service information specified in paragraph (o)(1), 
(o)(2), (o)(3), or (o)(4) of this AD.
    (2) For airplanes on which the actions specified in Airbus 
Service Bulletin A320-57-1043 have been done: At the latest of the 
times specified in paragraphs (p)(2)(i), (p)(2)(ii), and (p)(2)(iii) 
of this AD.
    (i) Within 7,200 flight cycles or 14,400 flight hours, whichever 
occurs first since doing the actions specified in Airbus Service 
Bulletin A320-57-1043.
    (ii) Within 3,750 flight cycles or 7,500 flight hours, whichever 
occurs first after July 31, 2012 (as described in Airbus Service 
Bulletin A320-57-1082, Revision 04, dated December 5, 2013).
    (iii) Within 850 flight cycles or 1,700 flight hours, whichever 
occurs first after the effective date of this AD.

(q) New Requirement of This AD: Repair of WCB

    If any crack is found during any inspection required by 
paragraph (p) of this AD: Before further flight, repair using a 
method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; the EASA; or Airbus's EASA DOA.

(r) New Optional Terminating Action

    Modification of an airplane, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-57-1043, 
Revision 06, dated December 5, 2013, constitutes terminating action 
for the actions required by paragraph (p) of this AD.

(s) Credit for Previous Actions

    This paragraph provides credit for applicable actions required 
by paragraphs (g) through (n) of this AD, if those actions were 
performed before the effective date of this AD using the applicable 
Airbus Service Information provided in paragraphs (s)(1) through 
(s)(8) of this AD.
    (1) Airbus Service Bulletin A320-57-1043, dated February 16, 
1993, which is not incorporated by reference in this AD.
    (2) Airbus Service Bulletin A320-57-1043, Revision 01, dated 
June 14, 1996, which is not incorporated by reference in this AD.
    (3) Airbus Service Bulletin A320-57-1043, Revision 02, dated May 
14, 1997, which was incorporated by reference on November 27, 1998 
(63 FR 56542, October 22, 1998).
    (4) Airbus Service Bulletin A320-57-1043, Revision 03, dated 
October 24, 1997, which is not incorporated by reference in this AD.
    (5) Airbus Service Bulletin A320-57-1043, Revision 04, dated May 
15, 1999, which is not incorporated by reference in this AD.
    (6) Airbus Service Bulletin A320-57-1082, Revision 01, dated 
December 10, 1997, which was incorporated by reference on November 
27, 1998 (63 FR 56542, October 22, 1998).
    (7) Airbus Service Bulletin A320-57-1082, Revision 02, dated 
July 26, 1999, which is not incorporated by reference in this AD.
    (8) Airbus Service Bulletin A320-57-1082, Revision 03, dated 
April 30, 2002, which was incorporated by reference on August 13, 
2004 (69 FR 41398, July 9, 2004).

(t) 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: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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 Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(u) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0065, dated March 14, 2014, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2015-1275.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (v)(6) and (v)(7) of this AD.

(v) 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 
February 18, 2016.
    (i) Airbus Service Bulletin A320-57-1043, Revision 06, dated 
December 5, 2013.
    (ii) Airbus Service Bulletin A320-57-1082, Revision 04, dated 
December 5, 2013. (4) The following service information was approved 
for IBR on August 13, 2004 (69 FR 41398, July 9, 2004).
    (i) Airbus Service Bulletin A320-57-1043, Revision 05, dated 
April 30, 2002.
    (ii) Airbus Service Bulletin A320-57-1082, Revision 03, dated 
April 30, 2002.
    (5) The following service information was approved for IBR on 
November 27, 1998 (63 FR 56542, October 22, 1998).
    (i) Airbus Service Bulletin A320-57-1043, Revision 02, dated May 
14, 1997. Pages 1 through 6, 8, 13, and 14 of this service bulletin 
are marked Revision 02, dated May 14, 1997; pages 7, 9 through 12, 
and 15 of this service bulletin are from the original issue, dated 
February 16, 1993.
    (ii) Airbus Service Bulletin A320-57-1082, Revision 01, dated 
December 10, 1997.
    (6) 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 account.airworth-eas@airbus.com; Internet http://www.airbus.com.
    (7) 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.
    (8) 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 December 18, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-32519 Filed 1-13-16; 8:45 am]
 BILLING CODE 4910-13-P