[Federal Register Volume 82, Number 153 (Thursday, August 10, 2017)]
[Proposed Rules]
[Pages 37360-37366]
[FR Doc No: 2017-16051]

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Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.

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Federal Register / Vol. 82, No. 153 / Thursday, August 10, 2017 /
Proposed Rules

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0713; Directorate Identifier 2016-NM-199-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-12-
12, for all Airbus Model A330-200, A330-200 Freighter, A330-300, A340-
200, and A340-300 series airplanes; and AD 2013-16-26 for all Airbus
Model A330-200 Freighter, A330-200 and -300, and A340-200 and -300
series airplanes. AD 2012-12-12 requires repetitive inspections of the
outer skin rivets of the cargo doors; repair if necessary; and other
repetitive inspections. AD 2013-16-26 requires repetitive inspections
of certain cargo doors, and repair if necessary. Since we issued AD
2012-12-12 and AD 2013-16-26, we have determined that a new inspection
procedure is necessary to address the unsafe condition. This proposed
AD would continue to require repetitive inspections and repair if
necessary. This proposed AD would add a one-time inspection and
adjustment of certain hook gaps; reinforcement of the door frame
structure; related investigative and corrective actions if necessary;
and a modification, which would allow deferring reinforcement of the
cargo door structure. We are proposing this AD to address the unsafe
condition on these products.

DATES: We must receive comments on this proposed AD by September 25,
2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus
SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93
45 80; email<EMAIL_ADDRESS>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-2017-
0713; 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:<PHONE_NUMBER>) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone:<PHONE_NUMBER>;
fax:<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2017-0713;
Directorate Identifier 2016-NM-199-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 7, 2012, we issued AD 2012-12-12, Amendment 39-17092 (77 FR
37797, June 25, 2012) (``AD 2012-12-12''), for all Airbus Model A330-
200 series airplanes, Model A330-200 Freighter series airplanes, Model
A330-300 series airplanes, Model A340-200 series airplanes, and Model
A340-300 series airplanes. AD 2012-12-12 was prompted by reports of
sheared fasteners located on the outside skin of the forward cargo door
and cracks on the frame fork ends, as well as cracks of the aft cargo
door frame 64A. AD 2012-12-12 requires a detailed inspection of the
outer skin rivets at the frame fork ends of the forward and aft cargo
doors for sheared, loose, and missing rivets; repair of the outer skin
rivets if necessary; and other repetitive inspections. We issued AD
2012-12-12 to detect and correct sheared, loose, or missing fasteners
on the forward and aft cargo door frame, which could result in the loss
of structural integrity of the forward and aft cargo door.
    On August 9, 2013, we issued AD 2013-16-26, Amendment 39-17564 (78
FR 53640, August 30, 2013) (``2013-16-26''), for all Airbus Model A330-
200 Freighter series airplanes, Model A330-200 and -300 series
airplanes, and Model A340-200 and -300 series airplanes. AD 2013-16-26
was prompted by reports of cracked adjacent frame forks of a forward
cargo door. AD 2013-16-26 requires repetitive detailed inspections for
cracks and sheared, loose, or missing rivets of the forward cargo door
and, for certain airplanes, of the aft cargo door, and repair if
necessary. We issued AD 2013-16-26 to detect and correct cracked or
ruptured cargo door frames, which could result in

reduced structural integrity of the forward or aft cargo door.
    Since we issued AD 2012-12-12 and AD 2013-16-26, we have determined
that a new inspection procedure is necessary to address the unsafe
condition. In addition, the manufacturer has released some terminating
action modifications for the cargo door structure, and provided
procedures that allow postponing the structural reinforcement
modification, which terminate the repetitive inspections.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2016-0188, dated September 21, 2016; corrected September 22, 2016
(referred to after this as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''); to correct an unsafe condition for
certain Airbus Model A330-200 and -300 series airplanes; Model A330-200
Freighter series airplanes; and Model A340-200, -300, -500, and -600
series airplanes. The MCAI states:

    Several cases of cracked forward (FWD) and aft (AFT) cargo door
frames, as well as loose, lost, or sheared rivets, have been
reported by operators. Investigation showed that these findings are
due to the low margins with respect to fatigue requirements for the
AFT/FWD cargo door internal structure. Further analysis determined
that the cargo door hook adjustment is a contributing factor to this
issue. In case of a cracked or ruptured (FWD or AFT) cargo door
frame, the loads will be transferred to the remaining structural
elements. However, the secondary load path is able to sustain those
loads only for a limited number of flight cycles (FC).
    This condition, if not detected and corrected, could lead to
rupture of adjacent vertical frames and consequent reduced
structural integrity of the FWD or AFT cargo door, possibly
resulting in a cargo door failure, decompression of the aeroplane
and injury to occupants.
    To initially address this potential unsafe condition, Airbus
issued Service Bulletin (SB) A330-52-3043 and SB A340-52-4053 and,
consequently, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation
Civile] France issued AD 2001-124(B) and AD 2001-126(B), requiring a
special detailed inspection of A330 and A340 AFT cargo doors. Since
those [DGAC] ADs were issued, prompted by new occurrences, Airbus
issued Alert Operators Transmission (AOT) A330-52A3085, AOT A340-
52A4092, AOT A330-52A3084, AOT A340-52A4091, AOT A330-A52L003-12,
AOT 340-A52L004-12, AOT A330-A52L001-12 and AOT A340-A52L002-12,
providing instructions to inspect the affected areas of both FWD and
AFT cargo doors.
    Consequently, EASA issued AD 2011-0007 (later revised) [which
corresponds to FAA AD 2012-12-12], and AD 2012-0274 [which
corresponds to FAA AD 2013-16-26], to require repetitive detailed
visual inspections of AFT and FWD cargo doors at specific frames and
outer skin at all frame fork ends. Since these EASA ADs were issued,
Airbus published SB A330-52-3087, SB A330-52-3095, SB A340-52-4095,
SB A340-52-4101, SB A340-52-5020 and SB A340-52-5023, which took
over the instructions of the above mentioned AOTs, and introduced
revised thresholds and intervals. In addition, the inspection
program was expanded to A340-500/-600 aeroplanes. Taking into
account experience from inspections accomplished in accordance with
the applicable Airbus SBs at original issue (listed above), Airbus
issued Revision 01 of these SBs.
    Consequently, EASA issued AD 2015-0192, which superseded EASA AD
2011-0007R1 and EASA AD 2012-0274, to require for each FWD and AFT
cargo door, a one-time inspection/adjustment of the hook gaps ``U''
and ``V'', repetitive detailed inspections (DET) of all frame fork
areas, frame head areas and outer skin areas to detect cracks or
loose/sheared/missing fasteners, and, depending on findings,
accomplishment of applicable corrective action(s). In addition, EASA
AD 2015-0192 expanded the Applicability to Airbus A340-500/-600
aeroplanes.
    Since EASA AD 2015-0192 was issued, Airbus published Revision 02
of the inspection SBs, introducing high-frequency eddy-current
inspection method for the frame forks structure. Airbus also
determined that the interval for these repetitive inspections could
be increased. In addition, Airbus released some modifications (mod)
introducing reinforcements to the cargo door structure improving the
fatigue characteristics. These modifications and associated SBs
constitute terminating action for the required repetitive
inspections. Furthermore, Airbus also published other SBs,
introducing cold working after oversizing of the fastener holes as a
means for structural reinforcement. Accomplishment of these SBs
allows postponement of the required Point of Embodiment (Structural
Modification Point) for the structural reinforcement modification
SBs which terminate the repetitive inspection requirement.
    For the reasons described above, this [EASA] AD partially
retains the requirements of EASA AD 2015-0192, which is superseded,
and requires for each FWD and AFT cargo door initial and repetitive
special detailed inspections (SDI) of all frame fork areas and
detailed inspections (DET) of frame head areas and outer skin areas,
and a one-time inspection/adjustment of the hook gaps ``U'' and
``V'' and, depending on findings, the accomplishment of applicable
corrective action(s). Additionally, this [EASA] AD requires
reinforcement of the cargo door frame structure, while
accomplishment of a cold working modification allows to defer the
reinforcement of the cargo door structure.
    It should be noted that additional inspections exist for the
cargo doors, as specified in Airbus A330 ALS [Airworthiness
Limitation Section] Part 2 task 523211-02-01 and task 523211-02-02,
and in Airbus A340 ALS Part 2 Task 523211-02-01.
    This [EASA] AD is re-published to correct typographical errors
when referencing Airbus SB A340-52-4118.

    Related investigative actions include detailed inspections and high
frequency non-destructive test inspections. Corrective actions include
reaming holes, bushing holes, replacing affected parts, and repairing
cracks. Additional work includes a one-time inspection of the ``U'' and
``V'' hook gaps, and if necessary, an adjustment of the hook gaps.
    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-
0713.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
    The following service information describes procedures for
inspecting and repairing the frame fork area at beam 4 and frame head
area at beam 1 from frame 20B to frame 25 of the forward cargo door,
and adjusting the hook gaps ``U'' and ``V.'' This service information
is distinct since it applies to different airplane models.
     Service Bulletin A330-52-3087, Revision 02, including
Appendix 01, dated February 18, 2016.
     Service Bulletin A340-52-4095, Revision 02, including
Appendix 01, dated November 29, 2015.
     Service Bulletin A340-52-5020, Revision 02, including
Appendices 01 and 02, dated November 27, 2015.
    The following service information describes procedures for
modifying the frame fork area at beam 4 and frame head area at beam 1
from frame 20B to frame 25 of the forward cargo door frame. This
service information is distinct since it applies to different airplane
models and configurations.
     Service Bulletin A330-52-3105, dated February 24, 2016.
     Service Bulletin A330-52-3110, dated February 15, 2016.
     Service Bulletin A330-52-3111, dated February 15, 2016.
     Service Bulletin A340-52-4108, dated February 15, 2016.
     Service Bulletin A340-52-4113, dated February 15, 2016.
     Service Bulletin A340-52-4114, dated February 15, 2016.
    The following service information describes procedures for
modifying the fastener holes in the forward cargo door frame structure
by cold working and changing the fastener type and size. This service
information is distinct since it applies to different airplane models
and configurations.
     Service Bulletin A330-52-3116, dated April 20, 2016.
     Service Bulletin A330-52-3117, dated April 20, 2016.

     Service Bulletin A330-52-3118, dated April 20, 2016.
     Service Bulletin A340-52-4119, dated April 20, 2016.
     Service Bulletin A340-52-4120, dated April 20, 2016.
     Service Bulletin A340-52-4121, dated April 20, 2016.
    The following service information describes procedures for
inspecting the frame fork area at beam 4 and frame head area at beam 1
of the aft cargo door from frame 60 to frame 64A, adjusting the hook
gaps ``U'' and ``V,'' and doing corrective actions. This service
information is distinct since it applies to different airplane models
and configurations.
     Service Bulletin A330-52-3095, Revision 02, including
Appendices 01 and 02, dated February 19, 2016.
     Service Bulletin A340-52-4101, Revision 02, including
Appendices 01 and 02, dated November 27, 2015.
     Service Bulletin A340-52-5023, Revision 02, including
Appendices 01 and 02, dated November 27, 2015.
    The following service information describes procedures for
modifying the frame fork and head of the aft cargo door frame from
frame 59A to frame 65. This service information is distinct since it
applies to different airplane models and configurations.
     Service Bulletin A330-52-3106, dated February 24, 2016.
     Service Bulletin A330-52-3112, dated February 24, 2016.
     Service Bulletin A330-52-3113, dated February 15, 2016.
     Service Bulletin A330-52-3114, dated February 15, 2016.
     Service Bulletin A340-52-4109, dated February 25, 2016.
     Service Bulletin A340-52-4115, dated February 19, 2016.
    The following service information describes procedures for
modifying the fastener holes in the aft cargo door frame structure by
cold working and changing the fastener type and size. This service
information is distinct since it applies to different airplane models.
     Service Bulletin A330-52-3115, dated April 20, 2016.
     Service Bulletin A340-52-4118, dated April 20, 2016.
    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.

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 designs.

Costs of Compliance

    We estimate that this proposed AD affects 73 airplanes of U.S.
registry.
    We estimate that it would take up to 888 work-hours per product to
comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost up to
$126,420 per product. Based on these figures, we estimate the cost of
this proposed AD on U.S. operators to be up to $14,738,700, or up to
$201,900 per product.
    We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
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.

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, 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:
0
a. Removing Airworthiness Directive (AD) 2012-12-12, Amendment 39-17092
(77 FR 37797, June 25, 2012); and AD 2013-16-26, Amendment 39-17564 (78
FR 53640, August 30, 2013); and
0
b. Adding the following new AD:

Airbus: Docket No. FAA-2017-0713; Directorate Identifier 2016-NM-
199-AD.

(a) Comments Due Date

    We must receive comments by September 25, 2017.

(b) Affected ADs

    This AD replaces AD 2012-12-12, Amendment 39-17092 (77 FR 37797,
June 25, 2012) (``AD 2012-12-12''); and AD 2013-16-26, Amendment 39-
17564 (78 FR 53640, August 30, 2013) (``AD 2013-16-26'').

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) and (c)(2) of this AD, certified in any category, all
manufacturer serial numbers, except those on which Airbus
Modification 202702 and Modification 202790 have been embodied in
production; and the Airbus airplanes identified in paragraphs (c)(3)
through (c)(5) of this AD, certified in any category, all
manufacturer serial numbers.
    (1) Model A330-201, -202, -203, -223, -223F, -243, and -243F
airplanes.
    (2) Model A330-301, -302, -303, -321, -322, -323, -341, -342,
and -343 airplanes.
    (3) Model A340-211, -212, and -213 airplanes.
    (4) Model A340-311, -312, and -313 airplanes.

    (5) Model A340-541 and -642 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of cracked forward and aft cargo
door frames, and loose, missing, or sheared rivets. We are issuing
this AD to detect and correct cracked or ruptured cargo door frames,
which could result in reduced structural integrity of the forward or
aft cargo door.

(f) Compliance

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

(g) Affected Cargo Doors

    For the purpose of this AD, the affected cargo doors are pre-
modification 202702 (forward cargo door) and pre-modification 202790
(aft cargo door), and are listed by part number (P/N) in the
applicable service information identified in paragraph (h)(1) of
this AD. For post-modification doors, which are not affected by this
AD, the P/Ns are identified as F52370900XXX (forward cargo door) and
F52372315XXX (aft cargo door), where ``XXX'' can be a combination of
any three numerical digits.

(h) Forward Cargo Door Repetitive Inspections

    (1) Before exceeding 5,300 total flight cycles since first
installation of the forward cargo door on an airplane, or within the
applicable compliance time specified in table 1 to paragraph (h)(1)
of this AD, whichever occurs later, except as specified in paragraph
(q) of this AD: Do all applicable detailed and high frequency eddy
current (HFEC) inspections of all frame fork areas, frame head
areas, and outer skin areas of each affected forward cargo door, as
applicable; in accordance with the Accomplishment Instructions of
the applicable service information specified in paragraph (h)(1)(i),
(h)(1)(ii), or (h)(1)(iii) of this AD. Do all applicable related
investigative actions and corrective actions before further flight
in accordance with the Accomplishment Instructions of the applicable
service information specified in paragraph (h)(1)(i), (h)(1)(ii), or
(h)(1)(iii) of this AD, except as required by paragraph (p) of this
AD. Repeat the applicable inspections of the frame fork areas, frame
head areas, and outer skin areas of each affected forward cargo door
thereafter at intervals not to exceed 1,400 flight cycles.

  Table 1 to Paragraph (h)(1) of This AD--Forward Cargo Door Inspection
                             Compliance Time
------------------------------------------------------------------------
  Airplane condition (on the effective
            date of this AD)                     Compliance time
------------------------------------------------------------------------
Inspected only as specified in Airbus    Within 1,100 flight cycles
 Alert Operator Transmission (AOT) A330-  after the last inspection, but
 52A3085 or AOT A340-52A4092, as          without exceeding 10,600
 applicable.                              flight cycles since first
                                          installation of the forward
                                          cargo door on an airplane.
Inspected as specified in Airbus AOT     Within 1,100 flight cycles
 A330-52A3085 and as specified in AOT     after the last inspection as
 A330-A52L003-12, and the last            specified in AOT A330-52A3085.
 inspection was accomplished as
 specified in AOT A330-A52L003-12.
Inspected as specified in Airbus AOT     Within 1,100 flight cycles
 A330-52A3085 and as specified in AOT     after the last inspection as
 A330-A52L003-12, and the last            specified in AOT A330-A52L003-
 inspection was accomplished as           12.
 specified in AOT A330-52A3085.
Inspected as specified in Airbus AOT     Within 1,100 flight cycles
 A340-52A4092 and as specified in AOT     after the last inspection as
 A340-A52L004-12, and the last            specified in AOT A340-52A4092.
 inspection was accomplished as
 specified in AOT A340-A52L004-12.
Inspected as specified in Airbus AOT     Within 1,100 flight cycles
 A340-52A4092 and as specified in AOT     after the last inspection as
 A340-A52L004-12, and the last            specified in AOT A340-A52L004-
 inspection was accomplished as           12.
 specified in AOT A340-52A4092.
Inspected as specified in the original   There is no compliance time for
 issue of Airbus Service Bulletin (SB)    the initial inspection in
 A330-52-3087, or SB A340-52-4095, or     paragraph (h)(1) of this AD
 SB A340-52-5020, as applicable.          for these airplanes, provided
                                          these airplanes comply with
                                          the actions specified
                                          paragraph (r)(1) of this AD.
Inspected as specified in Revision 01    There is no compliance time for
 of Airbus SB A330-52-3087, or SB A340-   the initial inspection in
 52-4095, or SB A340-52-5020, as          paragraph (h)(1) of this AD
 applicable.                              for these airplanes, provided
                                          these airplanes comply with
                                          the actions specified in
                                          paragraph (r)(2) of this AD.
Inspected as specified in Revision 02    Within 1,400 flight cycles
 of Airbus SB A330-52-3087, or SB A340-   after the last inspection, but
 52-4095, or SB A340-52-5020, as          without exceeding 5,300 total
 applicable.                              flight cycles since first
                                          installation of the forward
                                          cargo door on an airplane.
Never inspected........................  Within 1,100 flight cycles
                                          after the effective date of
                                          this AD, but without exceeding
                                          6,400 flight cycles since
                                          first installation of the
                                          forward cargo door on an
                                          airplane.
------------------------------------------------------------------------

    (i) Airbus Service Bulletin A330-52-3087, Revision 02, dated
February 18, 2016 (``A330-52-3087, R2'').
    (ii) Airbus Service Bulletin A340-52-4095, Revision 02, dated
November 29, 2015 (``A340-52-4095, R2'').
    (iii) Airbus Service Bulletin A340-52-5020, Revision 02, dated
November 27, 2015 (``A340-52-5020, R2'').
    (2) Concurrently with the first inspection required by paragraph
(h)(1) of this AD: Do a one-time detailed inspection of the hook
gaps ``U'' and ``V'' of each affected forward cargo door for proper
adjustment, and, depending on findings, adjust the hook(s), in
accordance with the Accomplishment Instructions of the applicable
service information specified in paragraph (h)(2)(i), (h)(2)(ii), or
(h)(2)(iii) of this AD. Do all required hook gap adjustments before
further flight.
    (i) A330-52-3087, R2.
    (ii) A340-52-4095, R2.
    (iii) A340-52-5020, R2.

(i) Forward Cargo Door Modification

    (1) Except as specified in paragraph (i)(2) of this AD, before
exceeding 18,500 total flight cycles since first installation of the
forward cargo door on an airplane, or within 12 months after the
effective date of this AD, whichever occurs later: Do reinforcement
modifications on the frame structure of each affected forward cargo
door, in accordance with the Accomplishment Instructions of the
applicable service information specified in paragraphs (i)(1)(i)
through (i)(1)(vi) of this AD, except as required by paragraph (p)
of this AD.
    (i) Airbus Service Bulletin A330-52-3105, dated February 24,
2016 (for certain Model A330-202, -223, and -243 airplanes; and
Model A330-301, -321, -322, -341, and -342 airplanes).
    (ii) Airbus Service Bulletin A330-52-3110, dated February 15,
2016 (for certain Model A330-202, -203, -223, and -243 airplanes;
and Model A330-303, -323, and -343 airplanes).
    (iii) Airbus Service Bulletin A330-52-3111, dated February 15,
2016 (for certain Model A330-202, -203, -223, -223F, -243, and -243F
airplanes; and Model A330-302, -303, -323, -342, and -343
airplanes).
    (iv) Airbus Service Bulletin A340-52-4108, dated February 15,
2016 (for certain

Model A340-211, -212, and -213 airplanes; and Model A340-311, -312,
and -313 airplanes).
    (v) Airbus Service Bulletin A340-52-4113, dated February 15,
2016 (for certain Model A340-312 and -313 airplanes).
    (vi) Airbus Service Bulletin A340-52-4114, dated February 15,
2016 (for certain Model A340-313 airplanes).
    (2) Accomplishment of the reinforcement modifications required
by paragraph (i)(1) of this AD may be deferred, provided that,
before exceeding 18,500 total flight cycles since first installation
of the forward cargo door on an airplane, or within 12 months after
the effective date of this AD, whichever occurs later, but not
earlier than 14,500 total flight cycles for Model A330 airplanes, or
12,500 total flight cycles for Model A340 airplanes, cold working is
accomplished on the frame structure of each affected forward cargo
door, in accordance with the Accomplishment Instructions of the
applicable service information specified in paragraphs (i)(2)(i)
through (i)(2)(vi) of this AD, except as required by paragraph (p)
of this AD. Modification of an airplane by accomplishment of the
cold working specified in this paragraph does not constitute
terminating action for the repetitive inspections required by
paragraph (h)(1) of this AD.
    (i) Airbus Service Bulletin A330-52-3116, dated April 20, 2016
(for certain Model A330-202, -223, and -243 airplanes; and Model
A330-301, -321, -322, -341, and -342 airplanes).
    (ii) Airbus Service Bulletin A330-52-3117, dated April 20, 2016
(for certain Model A330-202, -203, -223, and -243 airplanes; and
Model A330-303, -323, and -343 airplanes).
    (iii) Airbus Service Bulletin A330-52-3118, dated April 20, 2016
(for certain Model A330-202, -203, -223, -223F, -243, and -243F
airplanes; and Model A330-302, -303, -323, -342, and -343
airplanes).
    (iv) Airbus Service Bulletin A340-52-4119, dated April 20, 2016
(for certain Model A340-211, -212, and -213 airplanes; and Model
A340-311, -312, and -313 airplanes).
    (v) Airbus Service Bulletin A340-52-4120, dated April 20, 2016
(for certain Model A340-312 and -313 airplanes).
    (vi) Airbus Service Bulletin A340-52-4121, dated April 20, 2016
(for certain Model A340-313 airplanes).
    (3) Within 18,500 flight cycles after cold working is
accomplished on the frame structure of each affected forward cargo
door as specified in paragraph (i)(2) of this AD: Do the
reinforcement modifications on the frame structure of each affected
forward cargo door, using a method 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).

(j) Forward Cargo Door Terminating Action

    Modification of an airplane by reinforcement of the cargo door
frame structure required by paragraph (i)(1) or (i)(3) of this AD
constitutes terminating action for the repetitive inspections
required by paragraph (h)(1) of this AD for that airplane.

(k) Definitions of Pre-Modified and Post-Modified Airplanes

    (1) For the purpose of this AD, pre-modified Model A330-200
series airplanes, Model A330-200 Freighter series airplanes, Model
A330-300 series airplanes, Model A340-200 series airplanes, and
Model A340-300 series airplanes are defined as those not having
Airbus Modification 44852, or Modification 44854 applied in
production, or being in pre-Airbus Service Bulletin A330-52-3044 or
pre-Airbus Service Bulletin A340-52-4054 configuration, as
applicable.
    (2) For the purpose of this AD, post-modification Model A330-200
series airplanes, Model A330-200 Freighter series airplanes, Model
A330-300 series airplanes, Model A340-200 series airplanes, and
Model A340-300 series airplanes are defined as those having Airbus
Modification 44852 or Modification 44854 applied in production, or
modified in service as specified in Airbus Service Bulletin A330-52-
3044 or Airbus Service Bulletin A340-52-4054, as applicable.

(l) Aft Cargo Door Repetitive Inspections

    (1) Before exceeding 4,000 total flight cycles for pre-modified
airplanes, or 12,000 total flight cycles for post-modified
airplanes, since first installation of the aft cargo door on an
airplane, as applicable, or within the compliance time specified in
table 2 to paragraph (l)(1) of this AD or table 3 to paragraph
(l)(1) of this AD, as applicable, whichever occurs later, except as
specified in paragraph (q) of this AD: Do all applicable inspections
of all frame fork areas, frame head areas, and outer skin area of
each affected aft cargo door, in accordance with the Accomplishment
Instructions of the applicable service information specified in
paragraph (l)(1)(i), (l)(1)(ii), or (l)(1)(iii) of this AD. Do all
applicable related investigative actions and corrective actions
before further flight in accordance with the Accomplishment
Instructions of the applicable service information specified in
paragraph (l)(1)(i), (l)(1)(ii), or (l)(1)(iii) of this AD, except
as required by paragraph (p) of this AD. Repeat the applicable
inspections thereafter at intervals not to exceed 1,400 flight
cycles.

    Table 2 to Paragraph (l)(1) of This AD--Aft Cargo Door Inspection
               Compliance Times for Pre-Modified Airplanes
------------------------------------------------------------------------
  Airplane condition (on the effective
            date of this AD)                     Compliance time
------------------------------------------------------------------------
Inspected only as specified in Airbus    Within 550 flight cycles after
 AOT A330-52A3084, or AOT A340-52A4091,   the last inspection, but
 as applicable.                           without exceeding 15,800
                                          flight cycles since first
                                          installation of the aft cargo
                                          door on an airplane.
Inspected as specified in Airbus AOT     Within 550 flight cycles after
 A330-52A3084 and as specified in AOT     the last inspection as
 A330-A52L001-12, and the last            specified in AOT A330-52A3084.
 inspection was accomplished as
 specified in AOT A330-A52L001-12.
Inspected as specified in Airbus AOT     Within 550 flight cycles after
 A330-52A3084 and as specified in AOT     the last inspection as
 A330-A52L001-12, and the last            specified in AOT A330-A52L001-
 inspection was accomplished as           12.
 specified in AOT A330-52A3084.
Inspected as specified in Airbus AOT     Within 550 flight cycles after
 A340-52A4091 and as specified in AOT     the last inspection as
 A340-A52L002-12, and the last            specified in AOT A340-52A4091.
 inspection was accomplished as
 specified in AOT A340-A52L002-12.
Inspected as specified in Airbus AOT     Within 550 flight cycles after
 A340-52A4091 and as specified in AOT     the last inspection as
 A340-A52L002-12, and the last            specified in AOT A340-A52L002-
 inspection was accomplished as           12.
 specified in AOT A340-52A4091.
Inspected as specified in the original   There is no compliance time for
 issue of Airbus SB A330-52-3095, or SB   the initial inspection in
 A340-52-4101, as applicable.             paragraph (l)(1) of this AD
                                          for these airplanes, provided
                                          these airplanes comply with
                                          the actions specified in
                                          paragraph (r)(3) of this AD.
Inspected as specified in Revision 01    There is no compliance time for
 of Airbus SB A330-52-3095, or SB A340-   the initial inspection in
 52-4101, as applicable.                  paragraph (l)(1) of this AD
                                          for these airplanes, provided
                                          these airplanes comply with
                                          the actions specified in
                                          paragraph (r)(4) of this AD.
Inspected as specified in Revision 02    Within 1,400 flight cycles
 of Airbus SB A330-52-3095, or SB A340-   after the last inspection as
 52-4101, as applicable.                  specified in Revision 02 of
                                          Airbus SB A330-52-3095, or SB
                                          A340-52-4101, as applicable
                                          but without exceeding 4,000
                                          flight cycles since first
                                          installation of the aft cargo
                                          door on an airplane, as
                                          applicable.

Never inspected........................  Within 550 flight cycles after
                                          the effective date of this AD,
                                          but without exceeding 4,550
                                          flight cycles since first
                                          installation of the aft cargo
                                          door on an airplane.
------------------------------------------------------------------------

    Table 3 to Paragraph (l)(1) of This AD--Aft Cargo Door Inspection
Compliance Times for Post-Modified Airplanes and Model A340-500 and -600
                                Airplanes
------------------------------------------------------------------------
  Airplane condition (on the effective
            date of this AD)                     Compliance time
------------------------------------------------------------------------
Never inspected........................  Within 550 flight cycles after
                                          the effective date of this AD,
                                          but without exceeding 12,550
                                          flight cycles since first
                                          installation of the aft cargo
                                          door on an airplane.
Inspected as specified in the original   There is no compliance time for
 issue of Airbus SB A330-52-3095 or SB    paragraph (l)(1) of this AD
 A340-52-4101, or SB A340-5023, as        for these airplanes, provided
 applicable.                              these airplanes comply with
                                          the actions specified in
                                          paragraph (r)(3) of this AD.
Inspected as specified in Revision 01    There is no compliance time for
 of Airbus SB A330-52-3095, or SB A340-   paragraph (l)(1) of this AD
 52-4101, or SB A340-5023, as             for these airplanes, provided
 applicable.                              these airplanes comply with
                                          the actions specified in
                                          paragraph (r)(4) of this AD.
Inspected as specified in Revision 02    Within 1,400 flight cycles
 of Airbus SB A330-52-3095, or SB A340-   after the last inspection as
 52-4101, or SB A340-5023, as             specified in Revision 02 of
 applicable.                              Airbus SB A330-52-3095, or SB
                                          A340-52-4101, or SB A340-5023,
                                          as applicable, but without
                                          exceeding 12,000 flight cycles
                                          since first installation of
                                          the aft cargo door on an
                                          airplane.
------------------------------------------------------------------------

    (i) Airbus Service Bulletin A330-52-3095, Revision 02, dated
February 19, 2016 (``A330-52-3095, R2'').
    (ii) Airbus Service Bulletin A340-52-4101, Revision 02, dated
November 27, 2015 (``A340-52-4101, R2'').
    (iii) Airbus Service Bulletin A340-52-5023, Revision 02, dated
November 27, 2015 (``A340-52-5023, R2'').
    (2) Concurrently with the first inspection required by paragraph
(l)(1) of this AD: Do a one-time detailed inspection of the hook
gaps ``U'' and ``V'' of each affected aft cargo door for proper
adjustment and, depending on findings, adjust the hook(s) in
accordance with the Accomplishment Instructions of the applicable
service information specified in paragraph (l)(2)(i), (l)(2)(ii), or
(l)(2)(iii) of this AD. Do all required hook gap adjustments before
further flight.
    (i) A330-52-3095, R2.
    (ii) A340-52-4101, R2.
    (iii) A340-52-5023, R2.

(m) Modification for Pre-Modified Airplanes

    (1) For pre-modified airplanes, except as specified in paragraph
(m)(2) of this AD: Before exceeding 18,500 total flight cycles since
first installation of the aft cargo door on an airplane, or within
12 months after the effective date of this AD, whichever occurs
later, do reinforcement modifications, in accordance with the
Accomplishment Instructions of the applicable service information
specified in paragraphs (m)(1)(i) through (m)(1)(vi) of this AD,
except as required by paragraph (p) of this AD.
    (i) Airbus Service Bulletin A330-52-3106, dated February 24,
2016 (for certain Model A330-301, -321, -322, -341, and -342
airplanes).
    (ii) Airbus Service Bulletin A330-52-3112, dated February 24,
2016 (for certain Model A330-202 and -223 airplanes; and Model A330-
301, -322, -341, and -342 airplanes).
    (iii) Airbus Service Bulletin A330-52-3113, dated February 15,
2016 (for certain Model A330-223 and -243 airplanes; and Model A330-
322 and -342 airplanes).
    (iv) Airbus Service Bulletin A330-52-3114, dated February 15,
2016 (for certain Model A330-202, -203, -223, -223F, -243, and -243F
airplanes; and Model A330-302, -303, -323, -342, and -343
airplanes).
    (v) Airbus Service Bulletin A340-52-4109, dated February 25,
2016 (for certain Model A340-211, -212, and -213 airplanes; and
Model A340-311, -312, and -313 airplanes).
    (vi) Airbus Service Bulletin A340-52-4115, dated February 19,
2016 (for certain Model A340-212, -213, and -313 airplanes).
    (2) Accomplishment of the reinforcement modifications required
by paragraph (m)(1) of this AD may be deferred provided that before
exceeding 18,500 total flight cycles since first installation of the
aft cargo door on an airplane, or within 12 months after the
effective date of this AD, whichever occurs later, but not earlier
than 14,500 total flight cycles, cold working is accomplished on the
frame structure of each affected aft cargo door, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A330-52-
3115, dated April 20, 2016; or Airbus Service Bulletin A340-52-4118,
dated April 20, 2016; as applicable. Modification of an airplane by
accomplishment of the cold working specified in this paragraph does
not constitute terminating action for the repetitive inspections
required by paragraph (l)(1) of this AD.
    (3) For an airplane on which the cold working on the cargo door
frame structure is accomplished, as specified in paragraph (m)(2) of
this AD: Within 18,500 flight cycles after the application of cold
working, do reinforcement modifications, in accordance with the
Accomplishment Instructions of the service information specified in
paragraphs (m)(1)(i) through (m)(1)(vi) of this AD, as applicable,
or using a method approved by the Manager, International Branch,
ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's
EASA DOA.

(n) Aft Cargo Door Terminating Action

    Modification of an airplane by reinforcement of the cargo door
frame structure required by paragraph (m)(1) or (m)(3) of this AD
constitutes terminating action for the repetitive inspections
required by paragraph (l)(1) of this AD for that airplane.

(o) Optional Terminating Action Modification for Post-Modified
Airplanes

    For post-modified airplanes, modification of an airplane by
reinforcement of the cargo door frame structure, in accordance with
the Accomplishment Instructions of the applicable service
information specified in paragraphs (m)(1)(i) through (m)(1)(vi) of
this AD, or using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Airbus's EASA DOA, constitutes terminating action for the repetitive
inspections required by paragraph (l)(1) of this AD.

(p) Exception to Service Information

    Where the service information specified in paragraphs (h)(1),
(i)(1), (i)(2), (l)(1), and (m) of this AD specifies to contact
Airbus for instructions or repair, before further flight, accomplish
corrective actions in accordance with the procedures specified in
paragraph (s)(2) of this AD.

(q) Exception to Initial Inspection Compliance Time

    For the purposes of table 1 to paragraph (h)(1) of this AD,
table 2 to paragraph (l)(1) of this AD, and table 3 to paragraph
(l)(1) of this AD: As soon as a cargo door is inspected using any
applicable service information specified in this AD, the previous
inspections accomplished in accordance with any alert operator
transmission can be disregarded for the determination of the
compliance time for the initial inspection required by this AD.

(r) Credit for Previous Actions

    (1) This paragraph provides credit for the initial inspection
required by paragraph (h) of this AD, if that inspection was
performed before the effective date of this AD using Airbus Service
Bulletin A330-52-3087, dated August 29, 2013; Airbus Service
Bulletin A340-52-4095, dated August 29, 2013; or Airbus Service
Bulletin A340-52-5020, dated August 29, 2013; as applicable;
provided that the actions identified as ``additional work'' in the
Accomplishment Instructions of Airbus Service Bulletin A330-52-3087,
Revision 01, dated July 9, 2014; Airbus Service Bulletin A340-52-
4095, Revision 01, dated July 28, 2014; or Airbus Service Bulletin
A340-52-5020, Revision 01, dated July 9, 2014; as applicable; are
accomplished within 1,100 flight cycles after that inspection; and
provided the next inspection of all frame fork areas, frame head
areas, and outer skin area of each affected forward cargo door is
accomplished within 1,100 flight cycles after that inspection, in
accordance with the Accomplishment Instructions of A330-52-3087, R2;
A330-52-3095, R2; or A340-52-5020, R2, as applicable.
    (2) This paragraph provides credit for the initial inspection
required by paragraph (h) of this AD, if that inspection was
performed before the effective date of this AD using Airbus Service
Bulletin A330-52-3087, Revision 01, dated July 9, 2014; Airbus
Service Bulletin A340-52-4095, Revision 01, dated July 28, 2014; or
Airbus Service Bulletin A340-52-5020, Revision 01, dated July 9,
2014; as applicable; provided that the next inspection of all frame
fork areas, frame head areas, and outer skin area of each affected
forward cargo door, is accomplished within 1,100 flight cycles after
that inspection in accordance with the Accomplishment Instructions
of A330-52-3087, R2; A330-52-3095, R2; or A340-52-5020, R2, as
applicable.
    (3) This paragraph provides credit for the initial inspection
required by paragraph (l) of this AD, if that inspection was
performed before the effective date of this AD using Airbus Service
Bulletin A330-52-3095, dated August 29, 2013; Airbus Service
Bulletin A340-52-4101, dated August 29, 2013; or Airbus Service
Bulletin A340-52-5023, dated August 29, 2013; provided that the
actions identified as ``additional work'' in the Accomplishment
Instructions of Airbus Service Bulletin A330-52-3095, Revision 01,
dated July 28, 2014; Airbus Service Bulletin A340-52-4101, Revision
01, dated July 28, 2014; or Airbus Service Bulletin A340-52-5023,
Revision 01, dated July 28, 2014; as applicable; are accomplished
within 550 flight cycles after that inspection, and provided the
next inspection of all frame fork areas, frame head areas, and outer
skin area of each affected aft cargo door is accomplished within 550
flight cycles after that inspection in accordance with the
Accomplishment Instructions of A330-52-3095, R2; A340-52-4101, R2;
or A340-52-5023, R2, as applicable.
    (4) This paragraph provides credit for the initial inspection
required by paragraph (l) of this AD, if that inspection was
performed before the effective date of this AD using Airbus Service
Bulletin A330-52-3095, Revision 01, dated July 28, 2014; Airbus
Service Bulletin A340-52-4101, Revision 01, dated July 28, 2014; or
Airbus Service Bulletin A340-52-5023, Revision 01, dated July 28,
2014; as applicable; provided that the next inspection of all frame
fork areas, frame head areas, and outer skin area of each affected
aft cargo door is accomplished within 550 flight cycles after that
inspection in accordance with the Accomplishment Instructions of
A330-52-3095, R2; A340-52-4101, R2; or A340-52-5023, R2, as
applicable.

(s) 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 manager of the International Branch, send it to the
attention of the person identified in paragraph (t)(2) of this AD.
Information may be emailed to<EMAIL_ADDRESS>
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.
    (3) Required for Compliance (RC): Except as required by
paragraph (p) 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.

(t) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2016-0188, dated September 21, 2016; corrected
September 22, 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-2017-0713.
    (2) For more information about this AD, contact, Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>.
    (3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96;
fax: +33 5 61 93 45 80; email<EMAIL_ADDRESS>
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<PHONE_NUMBER>.

    Issued in Renton, Washington, on July 19, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-16051 Filed 8-9-17; 8:45 am]
 BILLING CODE 4910-13-P