80 FR 73099 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 226 (November 24, 2015)

We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a determination that, in specific flight conditions, the allowable load limits on the vertical tail plane could be reached and possibly exceeded. Exceeding allowable load could result in detachment of the vertical tail plane. This AD requires modification of the pin programming flight warning computer (FWC) to activate the stop rudder input warning (SRIW) logic; and an inspection to determine the part numbers of the FWC and the flight augmentation computer (FAC), and replacement of the FWC and FAC if necessary. We are issuing this AD to prevent detachment of the vertical tail plane and consequent loss of control of the airplane.

[Federal Register Volume 80, Number 226 (Tuesday, November 24, 2015)]
[Rules and Regulations]
[Pages 73099-73103]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-29702]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0251; Directorate Identifier 2014-NM-200-AD; 
Amendment 39-18330; AD 2015-23-13]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A318, A319, A320, and A321 series airplanes. This AD was 
prompted by a determination that, in specific flight conditions, the 
allowable load limits on the vertical tail plane could be reached and 
possibly exceeded. Exceeding allowable load could result in detachment 
of the vertical tail plane. This AD requires modification of the pin 
programming flight warning computer (FWC) to activate the stop rudder 
input warning (SRIW) logic; and an inspection to determine the part 
numbers of the FWC and the flight augmentation computer (FAC), and 
replacement of the FWC and FAC if necessary. We are issuing this AD to 
prevent detachment of the vertical tail plane and consequent loss of 
control of the airplane.

DATES: This AD becomes effective December 29, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 29, 
2015.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-0251; 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 AD, contact Airbus, 
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 
51; email [email protected]; Internet http://www.airbus.com. You may view this 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-
0251.

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 by adding an AD that would apply to all Airbus Model A318, 
A319, A320, and A321 series airplanes. The NPRM published in the 
Federal Register on March 5, 2015 (80 FR 11960). The NPRM was prompted 
by a determination that, in specific flight conditions, the allowable 
load limits on the vertical tail plane could be reached and possibly 
exceeded. Exceeding allowable load could result in detachment of the 
vertical tail plane. The NPRM proposed to require modification of the 
pin programming of the FWC to activate the SRIW logic; and an 
inspection to determine the part numbers of the FWC and the FAC, and 
replacement of the FWC and FAC if necessary. We are issuing this AD to 
prevent detachment of the vertical tail plane and consequent loss of 
control 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 2014-0217R1, dated February 26, 2015 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition. The MCAI states:

    During design reviews that were conducted following safety 
recommendations related to in-service incidents and one accident on 
another aircraft type, it has been determined that, in specific 
flight conditions, the allowable load limits on the vertical tail 
plane could be reached and possibly exceeded.
    This condition, if not corrected, could lead, in the worst case, 
to detachment of the

[[Page 73100]]

vertical tail plane in flight and consequent loss of the aeroplane.
    To prevent such a possibility, Airbus has developed 
modifications within the flight augmentation computer (FAC) to 
reduce the vertical tail plane stress and to activate a conditional 
aural warning within the flight warning computer (FWC) to further 
protect against pilot induced rudder doublets.
    Consequently, EASA issued AD 2014-0217 (ad.easa.europa.eu/blob/
easa_ad_2014_0217.pdf/AD_2014-0217_1) to require installation and 
activation of the stop rudder input warning (SRIW) logic. In 
addition, that [EASA] AD required, prior to or concurrent with 
modification of an aeroplane with the activation of the SRIW, 
upgrades of the FAC and FWC, to introduce the SRIW logic and SRIW 
aural capability, respectively. After modification, the [EASA] AD 
prohibited installation of certain Part Number (P/N) FWC and FAC.
    Since that [EASA] AD was issued, an additional previously-
published Airbus Service Bulletin (SB) was identified, and a new SB 
was published, for the concurrent requirement to replace the FAC 
with a unit having a P/N as listed in Table 3 of Appendix 1 of the 
AD.
    For the reasons described above, this [EASA] AD is revised to 
amend paragraph (2), adding references to additional Airbus SBs.

    In addition, this AD requires, prior to or concurrent with 
modification of an airplane with the activation of the SRIW, upgrades 
of the FAC and FWC to introduce the SRIW logic and SRIW aural 
capability, respectively. After modification, this AD prohibits 
installation of FWCs and FACs having certain part numbers. You may 
examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-0251-0003.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (80 
FR 11960, March 5, 2015) and the FAA's response to each comment.

Request To Refer to Revised Service Information

    Airbus requested that we refer to revised service information.
    We agree with the Airbus request to refer to revised service 
information. No additional work is required by the revised service 
information. We have revised paragraph (g) of this AD to refer to 
Airbus Service Bulletin A320-22-1480, Revision 02, dated March 30, 
2015. We have added new paragraph (m)(1) of this AD to provide credit 
for the actions required by paragraph (g) of this AD, if those actions 
were performed before the effective date of this AD using Airbus 
Service Bulletin A320-22-1480, dated July 9, 2014; or Airbus Service 
Bulletin A320-22-1480, Revision 01, dated February 6, 2015.
    We have revised paragraph (i) of this AD to refer in part to the 
following service information.
     Airbus Service Bulletin A320-22-1427, Revision 05, 
including Appendix 01, dated November 24, 2014 (FAC 622 hard B).
     Airbus Service Bulletin A320-22-1447, Revision 03, dated 
April 21, 2015 (FAC CAA02 hard C).
     Airbus Service Bulletin A320-22-1454, dated February 12, 
2014 (FAC CAA02).
     Airbus Service Bulletin A320-22-1461, Revision 07, 
including Appendix 01, dated March 23, 2015 (FAC B623 hard B).
     Airbus Service Bulletin A320-22-1502, dated November 14, 
2014 (FAC CAA02).
    We have redesignated paragraph (m) of the proposed AD (80 FR 11960, 
March 5, 2015) as new paragraph (m)(2) of this AD to provide credit for 
the actions required by paragraph (i) of this AD, if those actions were 
performed before the effective date of this AD using the following 
additional service information.
     Airbus Service Bulletin A320-22-1427, Revision 04, dated 
February 11, 2014.
     Airbus Service Bulletin A320-22-1447, Revision 01, dated 
September 18, 2014.
     Airbus Service Bulletin A320-22-1447, Revision 02, dated 
December 2, 2014.
     Airbus Service Bulletin A320-22-1461, Revision 04, dated 
September 15, 2014.
     Airbus Service Bulletin A320-22-1461, Revision 05, dated 
November 13, 2014.
     Airbus Service Bulletin A320-22-1461, Revision 06, dated 
January 21, 2015.

Request To Clarify Approved Parts

    United Airlines (UAL) requested that we split paragraph (h)(3)(iv) 
of the proposed AD (80 FR 11960, March 5, 2015) into two paragraphs to 
clarify the approved parts. UAL stated that paragraphs (h)(3)(i), 
(h)(3)(ii), and (h)(3)(iii) of the proposed AD clearly denote three of 
the four possible standards of FAC, but paragraph (h)(3)(iv) of the 
proposed AD leads one to believe that a FAC CAA02 hard C is required 
regardless of the airplane configuration.
    We agree with UAL's request to clarify the FWCs and FACs having the 
part numbers that are compatible with SRIW activation required by 
paragraph (g) of this AD. We have revised paragraph (h)(3)(iv) of the 
AD to state that for all airplanes configured with an FAC standard 
CAA01, an FAC having soft P/N G2856AAA02 installed on hard P/N 
C13206AA00 (CAA02 hard C) are compatible with SRIW activation required 
by paragraph (g) of this AD. We have added new paragraph (h)(3)(v) of 
this AD to state that for all airplane configurations, an FWC having P/
N 350E053021212 (H2-F7) are compatible with SRIW activation required by 
paragraph (g) of this AD.

Request for Additional Details and Clarification Regarding SRIW Changes

    The National Transportation Safety Board (NTSB) stated that there 
are differences between the Airbus Model A300/A310 series airplane SRIW 
system and the Airbus Model A320 series airplane SRIW system. The NTSB 
explained that the Model A300/A310 series airplane SRIW contains a red 
warning light on the glareshield, which lights when the SRIW is 
activated; however, the NPRM (80 FR 11960, March 5, 2015) did not 
mention the warning light as part of the Model A320 series airplane 
SRIW. The NTSB also stated that details associated with the 
modifications of the FAC and FWC are not stated in the NPRM (80 FR 
11960, March 5, 2015). The NTSB stated that without details regarding 
the changes associated with the Model A320 series airplane SRIW it 
cannot fully assess the FAA response for the Model A320 series 
airplanes to NTSB safety recommendations A-04-56 (http://www.ntsb.gov/safety/safety-recs/recletters/A04_56_62.pdf) and A-04-57 (http://www.ntsb.gov/safety/safety-recs/recletters/A04_56_62.pdf). The NTSB 
also wanted the FAA to clarify whether the Model A320 series airplane 
SRIW has more comprehensive protections compared with the Model A300 
series airplane SRIW.
    We agree with the NTSB that there are differences between the 
Airbus Model A300/A310 series airplane and Model A318/A319/A320/A321 
series airplane SRIW systems, such as, the latter does not include a 
light on the glareshield in front of each pilot; instead it includes a 
red master caution warning in addition to the aural synthetic voice 
warning to prevent pilots from making any further reversals. In 
addition, the Model Airbus A318/A319/A320/A321 series airplane SRIW 
modification includes a rudder travel limiter unit (RTLU) modification 
in the FAC that minimizes the available deflections for all the 
possible combinations of altitude and speed. This will ensure that 
after one full rudder pedal reversal, the vertical tail

[[Page 73101]]

plane (VTP) loads remain within the safe limits. After reviewing the 
design, analyses, and simulator demonstrations, the FAA has concluded 
that these warnings will prevent the flightcrew from continuing the 
inappropriate rudder inputs prior to exceeding the ultimate design 
loads that could result in failure of the vertical tail plane. We have 
determined that details associated with our disposition to NTSB safety 
recommendations A-04-56 and A-04-57 are outside the context of this AD. 
We will provide those details directly to the NTSB in our response to 
the safety recommendations. We have not changed this final rule in this 
regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 11960, March 5, 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 11960, March 5, 2015).
    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 A320-22-1480, Revision 02, dated 
March 30, 2015. This service information describes procedures for 
modifying the pin programming to activate the SRIW logic.
    Airbus has also issued the following service information. The 
service information describes procedures for replacing FWCs and FACs.
     Airbus Service Bulletin A320-22-1375, dated January 15, 
2014.
     Airbus Service Bulletin A320-22-1427, Revision 05, dated 
November 24, 2014.
     Airbus Service Bulletin A320-22-1447, Revision 03, dated 
April 21, 2015.
     Airbus Service Bulletin A320-22-1454, dated February 12, 
2014.
     Airbus Service Bulletin A320-22-1461, Revision 07, dated 
March 23, 2015.
     Airbus Service Bulletin A320-22-1502, dated November 14, 
2014.
     Airbus Service Bulletin A320-31-1414, Revision 03, dated 
September 15, 2014.
    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 
AD.

Costs of Compliance

    We estimate that this AD affects 953 airplanes of U.S. registry.
    We also estimate that it will take about 3 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $243,015, or $255 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 6 work-hours (3 work-hours for an FWC and 3 work-hours for 
an FAC), for a cost of up to $510 per product. We have received no 
definitive data that will enable us to provide part 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-2015-0251; 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 adding the following new airworthiness 
directive (AD):

2015-23-13 Airbus: Amendment 39-18330. Docket No. FAA-2015-0251; 
Directorate Identifier 2014-NM-200-AD.

(a) Effective Date

    This AD becomes effective December 29, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A318-111, -112, -121, and -122 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 
airplanes.
    (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes.

[[Page 73102]]

(d) Subject

    Air Transport Association (ATA) of America Code 22, Auto Flight; 
31, Instruments.

(e) Reason

    This AD was prompted by a determination that, in specific flight 
conditions, the allowable load limits on the vertical tail plane 
could be reached and possibly exceeded. Exceeding allowable load 
could result in detachment of the vertical tail plane. We are 
issuing this AD to prevent detachment of the vertical tail plane and 
consequent loss of control of the airplane.

(f) Compliance

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

(g) Pin Programming Modification

    Within 48 months after the effective date of this AD, modify the 
pin programming to activate the stop rudder input warning (SRIW) 
logic, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-22-1480, Revision 02, dated March 30, 2015.

(h) Inspection To Determine Part Numbers (P/Ns), Flight Warning 
Computer (FWC) and Flight Augmentation Computer (FAC) Replacement

    Prior to or concurrently with the actions required by paragraph 
(g) of this AD: Inspect the part numbers of the FWC and the FAC 
installed on the airplane. If any FWC or FAC having a part number 
identified in paragraph (h)(1) or (h)(2) of this AD, as applicable, 
is installed on an airplane, prior to or concurrently with the 
actions required by paragraph (g) of this AD, replace all affected 
FWCs and FACs with a unit having a part number identified in 
paragraph (h)(3) of this AD, in accordance with the Accomplishment 
Instructions of the applicable Airbus service information specified 
in paragraph (i) of this AD.
    (1) Paragraphs (h)(1)(i) through (h)(1)(xvii) of this AD 
identify FWCs having part numbers that are non-compatible with the 
SRIW activation required by paragraph (g) of this AD.
    (i) 350E017238484 (H1D1).
    (ii) 350E053020303 (H2E3).
    (iii) 350E016187171 (C5).
    (iv) 350E053020404 (H2E4).
    (v) 350E017248685 (H1D2).
    (vi) 350E053020606 (H2F2).
    (vii) 350E017251414 (H1E1).
    (viii) 350E053020707 (H2F3).
    (ix) 350E017271616 (H1E2).
    (x) 350E053021010 (H2F3P).
    (xi) 350E018291818 (H1E3CJ).
    (xii) 350E053020808 (H2F4).
    (xiii) 350E018301919 (H1E3P).
    (xiv) 350E053020909 (H2-F5).
    (xv) 350E018312020 (H1E3Q).
    (xvi) 350E053021111 (H2-F6).
    (xvii) 350E053020202 (H2E2).
    (2) Paragraphs (h)(2)(i) through (h)(2)(xxxiv) of this AD 
identify FACs having part numbers that are non-compatible with the 
SRIW activation required by paragraph (g) of this AD.
    (i) B397AAM0202.
    (ii) B397BAM0101.
    (iii) B397BAM0512.
    (iv) B397AAM0301.
    (v) B397BAM0202.
    (vi) B397BAM0513.
    (vii) B397AAM0302.
    (viii) B397BAM0203.
    (ix) B397BAM0514.
    (x) B397AAM0303.
    (xi) B397BAM0305.
    (xii) B397BAM0515.
    (xiii) B397AAM0404.
    (xiv) B397BAM0406.
    (xv) B397BAM0616.
    (xvi) B397AAM0405.
    (xvii) B397BAM0407.
    (xviii) B397BAM0617.
    (xix) B397AAM0506.
    (xx) B397BAM0507.
    (xxi) B397BAM0618.
    (xxii) B397AAM0507.
    (xxiii) B397BAM0508.
    (xxiv) B397BAM0619.
    (xxv) B397AAM0508.
    (xxvi) B397BAM0509.
    (xxvii) B397BAM0620.
    (xxviii) B397AAM0509.
    (xxix) B397BAM0510.
    (xxx) B397CAM0101.
    (xxxi) B397AAM0510.
    (xxxii) B397BAM0511.
    (xxxiii) B397CAM0102.
    (xxxiv) Soft P/N G2856AAA01 installed on hard P/N C13206AA00.
    (3) Paragraphs (h)(3)(i) through (h)(3)(v) of this AD identify 
the FWCs and FACs having the part numbers that are compatible with 
SRIW activation required by paragraph (g) of this AD.
    (i) For airplane configurations with no sharklet, an FAC having 
P/N B397BAM0621 (621 hard B).
    (ii) For airplanes configured with sharklet A320 and A319, an 
FAC having P/N B397BAM0622 (622 hard B).
    (iii) For airplanes configured with sharklet A321, an FAC having 
P/N B397BAM0623 (623 hard B).
    (iv) For all airplanes configured with an FAC standard CAA01, an 
FAC having soft P/N G2856AAA02 installed on hard P/N C13206AA00 
(CAA02 hard C).
    (v) For all airplane configurations, an FWC having P/N 
350E053021212 (H2-F7).

(i) Service Information for Actions Required by Paragraph (h) of This 
AD

    Do the actions required by paragraph (h) of this AD in 
accordance with the Accomplishment Instructions of the applicable 
Airbus service information specified in paragraphs (i)(1) through 
(i)(7) of this AD.
    (1) Airbus Service Bulletin A320-22-1375, dated January 15, 2014 
(FAC 621 hard B).
    (2) Airbus Service Bulletin A320-22-1427, Revision 05, including 
Appendix 01, dated November 24, 2014 (FAC 622 hard B).
    (3) Airbus Service Bulletin A320-22-1447, Revision 03, dated 
April 21, 2015 (FAC CAA02 hard C).
    (4) Airbus Service Bulletin A320-22-1454, dated February 12, 
2014 (FAC CAA02).
    (5) Airbus Service Bulletin A320-22-1461, Revision 07, including 
Appendix 01, dated March 23, 2015 (FAC 623 hard B).
    (6) Airbus Service Bulletin A320-22-1502, dated November 14, 
2014 (FAC CAA02).
    (7) Airbus Service Bulletin A320-31-1414, Revision 03, dated 
September 15, 2014 (FWC H-F7).

(j) Exclusion From Actions Required by Paragraphs (g) and (h) of This 
AD

    An airplane on which Airbus Modification 154473 has been 
embodied in production is excluded from the requirements of 
paragraphs (g) and (h) of this AD, provided that within 30 days 
after the effective date of this AD, an inspection of the part 
numbers of the FWC and the FAC installed on the airplane is done to 
determine that no FWC having a part number listed in paragraph 
(h)(1) of this AD, and no FAC having a part number listed in 
paragraph (h)(2) of this AD, has been installed on that airplane 
since date of manufacture. A review of airplane maintenance records 
is acceptable in lieu of this inspection if the part numbers of the 
FWC and FAC can be conclusively determined from that review. If any 
FWC or FAC having a part number identified in paragraph (h)(1) or 
(h)(2) of this AD, as applicable, is installed on a post-Airbus 
Modification 154473 airplane: Within 30 days after the effective 
date of this AD, do the replacement required by paragraph (h) of 
this AD.

(k) Parts Installation Prohibitions

    After modification of an airplane as required by paragraphs (g), 
(h), and (j) of this AD: Do not install on that airplane any FWC 
having a part number listed in paragraph (h)(1) of this AD or any 
FAC having a part number listed in paragraph (h)(2) of this AD.

(l) Later Approved Parts

    Installation of a version (part number) of the FWC or FAC 
approved after the effective date of this AD is an approved method 
of compliance with the requirements of paragraph (h) or (j) of this 
AD, provided the requirements specified in paragraphs (l)(1) and 
(l)(2) of this AD are met.
    (1) The version (part number) must be approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the European Aviation Safety Agency (EASA); or Airbus's EASA 
Design Organization Approval (DOA).
    (2) The installation must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.

(m) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-22-
1480, dated July 9, 2014; or Airbus Service Bulletin A320-22-1480, 
Revision 01, dated February 6, 2015. This service information is not 
incorporated by reference in this AD.
    (2) This paragraph provides credit for actions required by 
paragraph (i) of this AD, if those actions were performed before the 
effective date of this AD using the applicable Airbus service 
information identified in paragraphs (m)(2)(i) through (m)(2)(xviii) 
of

[[Page 73103]]

this AD. This service information is not incorporated by reference 
in this AD.
    (i) Airbus Service Bulletin A320-22-1427, dated January 25, 
2013.
    (ii) Airbus Service Bulletin A320-22-1427, Revision 01, dated 
July 30, 2013.
    (iii) Airbus Service Bulletin A320-22-1427, Revision 02, dated 
October 14, 2013.
    (iv) Airbus Service Bulletin A320-22-1427, Revision 03, dated 
November 8, 2013.
    (v) Airbus Service Bulletin A320-22-1427, Revision 04, dated 
February 11, 2014.
    (vi) Airbus Service Bulletin A320-22-1447, dated October 18, 
2013.
    (vii) Airbus Service Bulletin A320-22-1447, Revision 01, dated 
September 18, 2014.
    (viii) Airbus Service Bulletin A320-22-1447, Revision 02, dated 
December 2, 2014.
    (ix) Airbus Service Bulletin A320-22-1461, dated October 31, 
2013.
    (x) Airbus Service Bulletin A320-22-1461, Revision 01, dated 
February 25, 2014.
    (xi) Airbus Service Bulletin A320-22-1461, Revision 02, dated 
April 30, 2014.
    (xii) Airbus Service Bulletin A320-22-1461, Revision 03, dated 
July 17, 2014.
    (xiii) Airbus Service Bulletin A320-22-1461, Revision 04, dated 
September 15, 2014.
    (xiv) Airbus Service Bulletin A320-22-1461, Revision 05, dated 
November 13, 2014.
    (xv) Airbus Service Bulletin A320-22-1461, Revision 06, dated 
January 21, 2015.
    (xvi) Airbus Service Bulletin A320-31-1414, dated December 19, 
2012.
    (xvii) Airbus Service Bulletin A320-31-1414, Revision 01, dated 
March 21, 2013.
    (xviii) Airbus Service Bulletin A320-31-1414, Revision 02, dated 
July 30, 2013.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. Information may be 
emailed to: [email protected]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.
    (3) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0217R1, dated February 26, 
2015, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-0251-0003.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (p)(3) and (p(4) of this AD.

(p) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A320-22-1375, dated January 15, 
2014.
    (ii) Airbus Service Bulletin A320-22-1427, Revision 05, 
including Appendix 01, dated November 24, 2014.
    (iii) Airbus Service Bulletin A320-22-1447, Revision 03, dated 
April 21, 2015.
    (iv) Airbus Service Bulletin A320-22-1454, dated February 12, 
2014.
    (v) Airbus Service Bulletin A320-22-1461, Revision 07, including 
Appendix 01, dated March 23, 2015.
    (vi) Airbus Service Bulletin A320-22-1480, Revision 02, dated 
March 30, 2015.
    (vii) Airbus Service Bulletin A320-22-1502, dated November 14, 
2014.
    (viii) Airbus Service Bulletin A320-31-1414, Revision 03, dated 
September 15, 2014.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email [email protected]; Internet http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on November 9, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-29702 Filed 11-23-15; 8:45 am]
BILLING CODE 4910-13-P