
[Federal Register Volume 80, Number 89 (Friday, May 8, 2015)]
[Proposed Rules]
[Pages 26492-26496]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-10949]


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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]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2004-14-
09, for certain Airbus Model A320-211, -212, and -231 airplanes. AD 
2004-14-09 currently requires 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. Since we issued AD 2004-14-09, we have determined 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. This proposed AD would reduce the 
compliance times for the repetitive inspections, and would require a 
repair for certain airplanes. We are proposing 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: We must receive comments on this proposed AD by June 22, 2015.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed 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. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-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 proposed 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. 
Comments will be available in the AD docket shortly after receipt.

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

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-1275; 
Directorate Identifier 2014-NM-070-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On June 29, 2004, we issued AD 2004-14-09, Amendment 39-13718 (69 
FR 41398, July 9, 2004). AD 2004-14-09 requires actions intended to 
address an unsafe condition on the products listed above. AD 2004-14-09 
superseded AD 98-22-05, Amendment 39-10851 (63 FR 56542, October 22, 
1998).
    Since we issued AD 2004-14-09, Amendment 39-13718 (69 FR 41398, 
July 9, 2004), we have determined 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 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,

[[Page 26493]]

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 by searching for and locating Docket No. FAA-2015-
1275.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-57-1043, Revision 06, dated 
December 5, 2013. This service bulletin 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 bulletin describes procedures for 
inspections for cracking of the lower surface panel on the wing center 
box.
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI. 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 of this NPRM.

FAA's Determination and Requirements of This Proposed AD

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

Costs of Compliance

    We estimate that this proposed AD affects 46 airplanes of U.S. 
registry.
    The actions that are required by AD 2004-14-09, Amendment 39-13718 
(69 FR 41398, July 9, 2004), and retained in this proposed 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 proposed AD would add no additional 
economic burden.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator,

[[Page 26494]]

the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

Airbus: Docket No. FAA-2014-1275; Directorate Identifier 2014-NM-
070-AD.

(a) Comments Due Date

    We must receive comments by June 22, 2015.

(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 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 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 
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 No Changes

    This paragraph restates the requirements of paragraph (d) of AD 
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no 
changes. 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).

(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

[[Page 26495]]

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 No Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no 
changes. 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). 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 described in Airbus Service 
Bulletin A320-57-1043 have not been accomplished, and on which a 
repair has been accomplished, as described in Airbus Service 
Bulletin A320-57-1082, dated October 31, 1996; Revision 01, dated 
December 10, 1997; Revision 02, dated July 26, 1999; or Revision 03, 
dated April 30, 2002: 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 European Aviation Safety Agency (EASA); or Airbus's EASA design 
organization approval (DOA).

(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 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 described 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 Airbus Service Bulletin A320-57-1082, dated October 31, 
1996; Revision 01, dated December 10, 1997; Revision 02, dated July 
26, 1999; or Revision 03, dated April 30, 2002.
    (2) For airplanes on which the actions specified in Airbus 
Service Bulletin A320-57-1043, dated February 16, 1993; Revision 01, 
dated June 14, 1996; Revision 02, dated May 14, 1997; Revision 03, 
dated October 24, 1997; Revision 04, dated March 15, 1999; or 
Revision 05, dated April 30, 2002; 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-2014-1275.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.


[[Page 26496]]


    Issued in Renton, Washington, on April 29, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-10949 Filed 5-7-15; 8:45 am]
 BILLING CODE 4910-13-P


