Document ID: FAA-2017-0478-0006
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2017-11-28T05:00Z

[Federal Register Volume 82, Number 227 (Tuesday, November 28, 2017)]
[Rules and Regulations]
[Pages 56158-56163]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-23349]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0478; Product Identifier 2016-NM-174-AD; Amendment 
39-19087; AD 2017-22-07]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A319 series airplanes; Model A320-211, -212, -214, -231, -
232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes. This AD was prompted by a report of 
cracks on frame forks and outer skin on the forward and aft cargo 
compartment doors. This AD requires repetitive inspections of the frame 
forks, and corrective actions if necessary. This AD also includes 
optional modifications that constitute terminating action. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective January 2, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 2, 
2018.

ADDRESSES: For service information identified in this final rule, 
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; 
fax: +33 5 61 93 44 51; email: [email protected]; 
Internet: http://www.airbus.com. You may view this referenced service 
information at the FAA, Transport Standards Branch, 1601 Lind Avenue 
SW., Renton, WA. For information on the availability of this material 
at the FAA, call 425-227-1221. It is also available on the Internet at 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2017-0478.

[[Page 56159]]

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0478; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (telephone: 
800-647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

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

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Airbus Model A319 
series airplanes; Model A320-211, -212, -214, -231, -232, and -233 
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and 
-232 airplanes. The NPRM published in the Federal Register on May 22, 
2017 (82 FR 23160) (``the NPRM''). The NPRM was prompted by a report of 
cracks on frame forks and outer skin on the forward and aft cargo 
compartment doors. The NPRM proposed to require repetitive inspections 
of the frame forks, and corrective actions if necessary. The NPRM also 
included optional modifications that constitute terminating action. We 
are issuing this AD to detect and correct cracks on the frame forks and 
outer skin on the forward and aft cargo compartment doors, which could 
lead to reduced structural integrity and failure of the cargo 
compartment door, possible decompression of the airplane, and injury to 
occupants.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2016-0187, dated September 19, 2016 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus Model A319 series 
airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; 
and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes. The MCAI states:

    During full scale fatigue test, cracks have been found on frame 
forks and outer skin on forward and aft cargo doors.
    To improve the fatigue behaviour of the frame forks, Airbus 
introduced modification (mod) 22948 in production, and issued 
inspection Service Bulletin (SB) A320-52-1032 and modification SB 
A320-52-1042, both recommended.
    Since those actions were taken, further improved cargo 
compartment doors have been introduced in production through Airbus 
mod 26213, on aeroplanes having [manufacturer serial number] MSN 
0759 and up. This modification, which is not available for in-
service retrofit, also includes provisions that exclude installation 
of pre-mod 26213 aft and forward compartment cargo doors on an 
aeroplane.
    In the frame of the Widespread Fatigue Damage (WFD) study, it 
has been determined that repetitive inspections are necessary for 
aft and forward cargo compartment doors on aeroplanes that do not 
(or no longer) embody mod 22948 (or SB A320-52-1042), and those that 
do not embody mod 26213. Failure to detect cracks would reduce the 
cargo door structural integrity.
    This condition, if not detected and corrected, could lead to 
cargo door failure, possibly resulting in decompression of the 
aeroplane and injury to occupants.
    To address this unsafe condition, Airbus issued SB A320-52-1171 
to provide inspection instructions. This SB was later revised to 
correct the list of affected cargo doors. Airbus also issued SB 
A320-52-1170, introducing a door modification which constitutes 
terminating action for the repetitive special detailed inspection 
(SDI).
    For the reason described above, this [EASA] AD requires 
accomplishment of repetitive SDI by rototest of all frame forks in 
beam 4 area to detect cracks, and, depending on findings, 
accomplishment of applicable corrective action(s) [repair or 
replacement]. This AD also provides an optional [modification that 
constitutes] terminating action for the repetitive SDI required by 
this [EASA] AD.

    One of the optional modifications includes related investigative 
and corrective actions. The related investigative action is a high 
frequency eddy current (HFEC) rotating probe inspection for cracks, and 
the corrective action is a repair. You may examine the MCAI in the AD 
docket on the Internet at http://www.regulations.gov by searching for 
and locating Docket No. FAA-2017-0478.

Comments

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

Requests To Refer to Updated Service Information

    Delta Air Lines and United Airlines requested that we revise the 
NPRM to refer to Airbus Service Bulletin A320-52-1171, Revision 02, 
dated April 10, 2017. United Airlines mentioned that Airbus has made 
number of updates and clarifications in Airbus Service Bulletin A320-
52-1171, Revision 02, dated April 10, 2017. Additionally, United 
Airlines pointed out that EASA AD 2016-0187, dated September 19, 2016, 
quoted in the ``Discussion'' section of the NPRM, allows for use of 
later approved revisions.
    We agree with the commenters for the reasons provided. We have 
revised this AD to refer to Airbus Service Bulletin A320-52-1171, 
Revision 02, dated April 10, 2017. We have also redesignated paragraph 
(m) (of the proposed AD) as paragraph (m)(1) of this AD and added 
paragraph (m)(2) to provide credit for actions done before the 
effective date of this AD, if those actions were done using Airbus 
Service Bulletin A320-52-1171, Revision 01, dated September 5, 2016.

Request To Clarify That Certain Service Information Cancels the 
Requirements of Certain Other Service Information

    United Airlines requested that we clarify that Airbus Service 
Bulletin A320-52-1171, Revision 02, dated April 10, 2017, cancels the 
requirements of Airbus Service Bulletin A320-52-1032. The commenter 
indicated that a statement regarding this subject would clarify the 
required actions for operators. The commenter also pointed out that a 
statement is listed in Airbus Service Bulletin A320-52-1171, Revision 
02, dated April 10, 2017, that specifies the cancellation of the 
requirements of Airbus Service Bulletin A320-52-1032.
    We agree to clarify. Airbus Service Bulletin A320-52-1171, Revision 
02, dated April 10, 2017, does include a statement indicating that the 
actions specified in Airbus Service Bulletin A320-52-1171, Revision 02, 
dated April 10, 2017, cancel the actions specified in Airbus Service 
Bulletin A320-52-1032. However, the actions specified in Airbus Service 
Bulletin A320-52-1032 are not required by any AD, and therefore, we do 
not specifically address Airbus Service Bulletin A320-52-1032 in this 
AD (except for the compliance time reference in paragraph (h)(4) of 
this AD). We have not changed this AD in this regard.

[[Page 56160]]

Request To Update the NPRM To Include Modifications 22948 and 26213

    Delta Air Lines requested that we revise paragraphs (c) and (g) of 
the proposed AD to refer to Modifications 22948 and 26213. 
Specifically, Delta Air Lines requested that we include information 
that elaborates on the specific airplanes affected by the NPRM. Delta 
Air Lines pointed out that EASA AD 2016-0187, dated September 19, 2016, 
quoted in the ``Discussion'' section of the NPRM, and Airbus Service 
Bulletin A320-52-1042, Revision 2, dated January 14, 1997, already 
refer to the modifications. Delta Air Lines also mentioned that it has 
40 forward and aft cargo compartment doors affected by the NPRM, which 
are pre-Modifications 22948 and 26213 and under manufacturer serial 
number 0758.
    We disagree to refer to Modifications 22948 and 26213 in paragraphs 
(c) and (g) of this AD; however, we agree that clarification is 
necessary. The applicability of this AD refers to the affected models 
having manufacturer serial numbers through 0758 inclusive; all 
airplanes having these serial numbers are affected by the identified 
unsafe condition. Airbus introduced modification 22948 in production, 
and issued Airbus Service Bulletin A320-52-1032 for recommended 
inspections and Airbus Service Bulletin A320-52-1042 for recommended 
modification 22948. Since that service information was issued, Airbus 
has introduced further improved forward and aft cargo compartment doors 
(modification 26213) in production on airplanes having manufacturer 
serial number 0759 and above; however, this modification is unavailable 
for in-service retrofit. Modification 26213 includes provisions that 
prohibit installation of earlier configurations of forward or aft cargo 
compartment doors (pre-modification 26213). Airplanes having 
manufacturer serial numbers 0759 and subsequent have modification 26213 
installed in production. We have not changed this AD in this regard.

Request To Include Instructions for Rotable Parts

    Delta Air Lines requested that we include instructions for rotable 
parts in paragraph (g) of the proposed AD. The commenter mentioned that 
forward or aft cargo compartment doors could be migrated from 
manufacturer serial number 0759 and above to airplanes that are 
affected, and asked if those airplanes are still affected. The 
commenter also requested that Airbus provide a list of manufacturer 
serial numbers that are affected by the proposed AD.
    We partially agree with the commenter. Airplanes originally 
delivered with the affected doors are subject to the requirements of 
this AD. Paragraph (h) of this AD only requires actions on affected 
doors. It is not physically possible to install the affected doors on 
serial numbers 0759 and above; therefore, parts rotability does not 
need to be addressed in this AD.
    In addition, paragraph (n) of this AD provides a parts installation 
limitation for the forward or aft cargo compartment doors for the 
airplanes identified in paragraph (c) of this AD. We have no practical 
method to provide a manufacturer serial number list of affected 
airplanes on which a non-affected door might have been installed or to 
predict an airplane configuration in the worldwide fleet. Therefore, we 
have not changed this AD in this regard.

Request To Clarify Optional Terminating Actions

    United Airlines requested that we clarify the optional terminating 
actions specified in paragraph (j) of the proposed AD. The commenter 
requested we include a statement that specifies modification of all 
affected doors of an airplane in accordance with the requirements of 
paragraphs (j)(1), (j)(2), or (j)(3) of this AD constitutes terminating 
action. The commenter pointed out that EASA AD 2016-0187, dated 
September 19, 2016, quoted in the ``Discussion'' section of the NPRM, 
allows for modification of an airplane as specified in Airbus Service 
Bulletin A320-52-1042, Revision 2, dated January 14, 1997; or Airbus 
Service Bulletin A320-52-1170, dated September 5, 2016; and either is 
considered terminating action for the repetitive inspections.
    We agree that clarification is necessary. We have revised paragraph 
(j) of this AD to include introductory text with the statement: 
``Modification of all affected doors of an airplane in accordance with 
the requirements of paragraph (j)(1), (j)(2), or (j)(3) of this AD 
constitutes terminating action . . . .''

Request To Include Compliance Times for Optional Terminating Actions

    Mr. Petit requested that we add compliance times for the optional 
terminating actions specified in the proposed AD. Mr. Petit indicated 
that 14 CFR 26.21 might require a mandatory terminating action before 
56,300 flight cycles. Mr. Petit also recommended that the optional 
terminating action not be embodied before 21,700 flight cycles.
    We disagree with the commenter's request to include compliance 
times for the optional terminating action specified in this AD. 14 CFR 
26.21 mandates the limit of validity (LOV) and does not specify 
compliance times for the optional terminating action specified in this 
AD. This AD mandates repetitive inspections of the frame forks as 
specified in the service information provided by the design approval 
holder (DAH) to meet the LOV. In addition, we do not include compliance 
times for optional actions in ADs because doing so would make the 
actions mandatory. We intend for the terminating actions in this AD to 
be optional, which aligns with the MCAI.
    Regarding the commenter's recommendation to prohibit accomplishing 
the optional terminating action before 21,700 flight cycles, the 
commenter provided no substantiation for this prohibition. We have 
received no data indicating that the optional terminating action should 
not be accomplished before 21,700 flight cycles. Therefore, we have not 
changed this AD in this regard.

Clarification of Exception

    Paragraph (i)(2) of the proposed AD, which refers to Airbus Service 
Bulletin A320-52-1170, dated September 5, 2016, includes an exception 
as specified in paragraph (k) of the proposed AD. However, paragraph 
(k) of the proposed AD does not mention Airbus Service Bulletin A320-
52-1170, dated September 5, 2016. We have added Airbus Service Bulletin 
A320-52-1170, dated September 5, 2016, to the exception specified in 
paragraph (k) of this AD.

Conclusion

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

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.

[[Page 56161]]

     Airbus Service Bulletin A320-52-1171, Revision 02, dated 
April 10, 2017, describes procedures for repetitive special detailed 
inspections of all frame forks in the beam 4 area of any affected door, 
and corrective actions.
     Airbus Service Bulletin A320-52-1042, Revision 2, dated 
January 14, 1997, describes procedures for modification of all affected 
forward and aft cargo compartment doors of an airplane.
     Airbus Service Bulletin A320-52-1170, dated September 5, 
2016, describes modification of all affected forward and aft cargo 
compartment doors of an airplane, including related investigative and 
corrective actions.
    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 88 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Special detailed inspection........  25 work-hours x $85 per                  $0          $2,125        $187,000
                                      hour = $2,125.
----------------------------------------------------------------------------------------------------------------

                                                Optional Actions
----------------------------------------------------------------------------------------------------------------
                 Action                          Labor cost               Parts cost          Cost per product
----------------------------------------------------------------------------------------------------------------
Modification............................  24 work-hours x $85 per   Up to $240...........  Up to $2,280.
                                           hour = $2,040.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition repairs and replacements specified 
in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2017-22-07 Airbus: Amendment 39-19087; Docket No. FAA-2017-0478; 
Product Identifier 2016-NM-174-AD.

(a) Effective Date

    This AD is effective January 2, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A319-111, -112, -113, -114, -
115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -
231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, 
-212, -213, -231, and -232 airplanes, certificated in any category, 
manufacturer serial numbers through 0758 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

    This AD was prompted by a report of cracks on the frame forks 
and outer skin on the forward and aft cargo compartment doors. We 
are issuing this AD to detect and correct cracks on the frame forks 
and outer skin on the forward and aft cargo compartment doors, which 
could lead to reduced structural integrity and failure of the cargo 
compartment door, possible decompression of the airplane, and injury 
to occupants.

(f) Compliance

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

(g) Definition of Affected Door

    For the purpose of this AD, an ``affected door'' is a forward or 
aft cargo compartment

[[Page 56162]]

door, having any part number listed in table 1 to paragraph (g) of 
this AD, except a cargo compartment door on which Airbus Service 
Bulletin A320-52-1042 or Airbus Service Bulletin A320-52-1170 is 
embodied.
[GRAPHIC] [TIFF OMITTED] TR28NO17.017

(h) Repetitive Special Detailed Inspection of Frame Forks

    At the latest of the compliance times listed in paragraphs 
(h)(1) through (h)(4) of this AD: Do a special detailed inspection 
of all frame forks in the beam 4 area of any affected door as 
defined in paragraph (g) of this AD, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-52-1171, 
Revision 02, dated April 10, 2017, except as specified in paragraphs 
(k) and (l) of this AD. Repeat the inspection thereafter at 
intervals not to exceed 3,000 flight cycles. A review of the 
airplane delivery or maintenance records is acceptable to identify 
any affected door installed on the airplane, provided that the cargo 
compartment door part number can be conclusively determined from 
that review.
    (1) Before exceeding 37,500 flight cycles since first 
installation of the door on an airplane.
    (2) Within 900 flight cycles after the effective date of this 
AD, without exceeding 41,950 flight cycles since first installation 
of the door on an airplane.
    (3) Within 50 flight cycles after the effective date of this AD, 
for a door having reached or exceeded 41,900 flight cycles since 
first installation on an airplane.
    (4) Within 3,000 flight cycles since the last inspection of the 
door as specified in Airbus Service Bulletin A320-52-1032.

(i) Corrective Actions

    If any crack is found during any inspection required by 
paragraph (h) of this AD, before further flight, do all applicable 
corrective actions in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-52-1171, Revision 02, 
dated April 10, 2017, except as specified in paragraphs (k) and (l) 
of this AD. Accomplishment of applicable corrective actions does not 
constitute terminating action for the repetitive inspections.

(j) Optional Terminating Action

    Modification of all affected doors of an airplane in accordance 
with the requirements of paragraph (j)(1), (j)(2), or (j)(3) of this 
AD, constitutes terminating action for the repetitive inspections 
specified in paragraph (h) of this AD for that airplane.
    (1) Modification of all affected doors of an airplane in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52-1042, Revision 2, dated January 14, 1997, 
constitutes terminating action for the repetitive inspections 
specified in paragraph (h) of this AD for that airplane, provided 
that, after modification, no affected door is re-installed on that 
airplane.
    (2) Modification of all affected doors of an airplane including 
accomplishment of all applicable related investigative and 
corrective actions in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-52-1170, dated 
September 5, 2016, except as specified in paragraph (k) of this AD, 
constitutes terminating action for the repetitive inspections 
specified in paragraph (h) of this AD for that airplane, provided 
that, after modification, no affected door is re-installed on that 
airplane.
    (3) Modification of all affected doors on an airplane, in case 
of finding damaged frame forks, as specified in an Airbus Repair 
Design Approval Sheet (RDAS), and done in accordance with a method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or the European Aviation Safety Agency (EASA); or 
Airbus's EASA Design Organization Approval (DOA); constitutes 
terminating action for the repetitive inspection specified in 
paragraph (h) of this AD for that airplane, provided that, after 
modification, no affected door is re-installed on that airplane.

(k) Exception to Service Information

    Where Airbus Service Bulletin A320-52-1170, dated September 5, 
2016; or Airbus Service Bulletin A320-52-1171, Revision 02, dated 
April 10, 2017; specifies to contact Airbus for appropriate action, 
and specifies that action as ``RC'' (Required for Compliance): 
Before further flight, accomplish corrective actions in accordance 
with the procedures specified in paragraph (o)(2) of this AD.

[[Page 56163]]

(l) No Reporting Requirement

    Although Airbus Service Bulletin A320-52-1171, Revision 02, 
dated April 10, 2017, specifies to submit certain information to the 
manufacturer, and specifies that action as ``RC,'' this AD does not 
include that requirement.

(m) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraphs (h) and (i) of this AD, if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A320-52-1171, dated October 29, 2015, provided that it can be 
conclusively determined that any part number D52371000018 was also 
inspected as specified in paragraph (h) of this AD.
    (2) This paragraph provides credit for the actions required by 
paragraphs (h) and (i) of this AD, if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A320-52-1171, Revision 01, dated September 5, 2016.

(n) Parts Installation Limitation

    As of the effective date of this AD, no person may install, on 
any airplane, an affected door specified in paragraph (g) of this 
AD, unless it has been inspected in accordance with the requirements 
of paragraph (h) of this AD and all applicable corrective actions 
have been done in accordance with paragraph (i) of this AD.

(o) Other FAA AD Provisions

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

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0187, dated September 19, 2016, for related 
information. This MCAI may be found in the AD docket on the Internet 
at http://www.regulations.gov by searching for and locating Docket 
No. FAA-2017-0478.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 
425-227-1405; fax: 425-227-1149.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (q)(3) and (q)(4) of this AD.

(q) 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 A320-52-1042, Revision 2, dated 
January 14, 1997 (pages 5, 9, and 19 through 22 of this document are 
identified as Revision 1, dated November 22, 1993).
    (ii) Airbus Service Bulletin A320-52-1170, dated September 5, 
2016, including Appendices 01 and 02, dated September 5, 2016.
    (iii) Airbus Service Bulletin A320-52-1171, Revision 02, dated 
April 10, 2017.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 
5 61 93 44 51; email: [email protected]; Internet: 
http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on October 17, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-23349 Filed 11-27-17; 8:45 am]
BILLING CODE 4910-13-P