Airworthiness Directives; Airbus Airplanes

[Federal Register Volume 83, Number 46 (Thursday, March 8, 2018)]
[Rules and Regulations]
[Pages 9801-9811]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-04645]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0713; Product Identifier 2016-NM-199-AD; Amendment 
39-19170; AD 2018-02-17]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; correction.

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SUMMARY: The FAA is correcting an airworthiness directive (AD) that 
published in the Federal Register. That AD applies to certain Airbus 
Model A330-200, -200 Freighter, and -300 series airplanes, and all 
Model A340-200, -300, -500, and -600 series airplanes. As published, 
six paragraph references located in three tables of that AD are 
incorrect. This document corrects the errors. In all other respects, 
the original document remains the same.

DATES: This correction is effective March 16, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 16, 
2018 (83 FR 5689, February 9, 2018).

ADDRESSES: For service information identified in this final rule, 
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 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-
0713.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov; 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 address for the 
Docket Office (phone: 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: Vladimir Ulyanov, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 1601 Lind 
Avenue SW, Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-
1149.

SUPPLEMENTARY INFORMATION: As published, Airworthiness Directive 2018-
02-17, Amendment 39-19170 (83 FR 5689, February 9, 2018) (``AD 2018-02-
17''), requires repetitive inspections of certain cargo doors, and 
repair if necessary, 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. 
That AD applies to certain Airbus Model A330-200, -200 Freighter, and -
300 series airplanes, and all Model A340-200, -300, -500, and -600 
series airplanes.

Need for the Correction

    As published, six paragraph references located in three tables of 
AD 2018-02-17 are incorrect.
    Table 1 to paragraph (h)(1) of AD 2018-02-17 refers to paragraphs 
(r)(1) and (r)(2) of that AD. Table 2 and table 3 to paragraph (l)(1) 
of AD 2018-02-17 refer to paragraphs (r)(3) and (r)(4) of that AD. In 
the notice of proposed rulemaking (NPRM) (82 FR 37360, August 10, 
2017), these references were correct. However, during the development 
of the final rule for AD 2018-02-17, paragraph (r) was redesignated as 
paragraph (s) but the references to paragraph (r) were not updated 
accordingly. Where the tables in AD 2018-02-17 refer to paragraphs 
(r)(1), (r)(2), (r)(3), and (r)(4), the correct references are 
paragraphs (s)(1), (s)(2), (s)(3), and (s)(4) of this AD.

[[Page 9802]]

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.
    <bullet> Service Bulletin A330-52-3087, Revision 02, including 
Appendix 01, dated February 18, 2016.
    <bullet> Service Bulletin A340-52-4095, Revision 02, including 
Appendix 01, dated November 29, 2015.
    <bullet> 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.
    <bullet> Service Bulletin A330-52-3105, dated February 24, 2016.
    <bullet> Service Bulletin A330-52-3110, dated February 15, 2016.
    <bullet> Service Bulletin A330-52-3111, dated February 15, 2016.
    <bullet> Service Bulletin A340-52-4108, dated February 15, 2016.
    <bullet> Service Bulletin A340-52-4113, dated February 15, 2016.
    <bullet> 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.
    <bullet> Service Bulletin A330-52-3116, dated April 20, 2016.
    <bullet> Service Bulletin A330-52-3117, dated April 20, 2016.
    <bullet> Service Bulletin A330-52-3118, dated April 20, 2016.
    <bullet> Service Bulletin A340-52-4119, dated April 20, 2016.
    <bullet> Service Bulletin A340-52-4120, dated April 20, 2016.
    <bullet> 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.
    <bullet> Service Bulletin A330-52-3095, Revision 02, including 
Appendices 01 and 02, dated February 19, 2016.
    <bullet> Service Bulletin A340-52-4101, Revision 02, including 
Appendices 01 and 02, dated November 27, 2015.
    <bullet> 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.
    <bullet> Service Bulletin A330-52-3106, dated February 24, 2016.
    <bullet> Service Bulletin A330-52-3112, dated February 24, 2016.
    <bullet> Service Bulletin A330-52-3113, dated February 15, 2016.
    <bullet> Service Bulletin A330-52-3114, dated February 15, 2016.
    <bullet> Service Bulletin A340-52-4109, dated February 25, 2016.
    <bullet> 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.
    <bullet> Service Bulletin A330-52-3115, dated April 20, 2016.
    <bullet> 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.

Correction of Publication

    This document corrects several errors and correctly adds the AD as 
an amendment to 14 CFR 39.13. Although no other part of the preamble or 
regulatory information has been corrected, we are publishing the entire 
rule in the Federal Register.
    The effective date of this AD remains March 16, 2018.
    Since this action only corrects paragraph references, it has no 
adverse economic impact and imposes no additional burden on any person. 
Therefore, we have determined that notice and public procedures are 
unnecessary.

List of Subjects in 14 CFR Part 39

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

Adoption of the Correction

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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   [Corrected]

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

2018-02-17 Airbus: Amendment 39-19170; Docket No. FAA-2017-0713; 
Product Identifier 2016-NM-199-AD.

(a) Effective Date

    This AD is effective March 16, 2018.

(b) Affected ADs

    This AD replaces 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).

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD, certificated 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, certificated 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.

[[Page 9803]]

(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) or 
(l)(1) of this AD. For post-modification doors, which are not 
affected by this AD, the part numbers 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.

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    (i) Airbus Service Bulletin A330-52-3087, Revision 02, including 
Appendix 01, dated February 18, 2016 (``SB A330-52-3087, R02'').
    (ii) Airbus Service Bulletin A340-52-4095, Revision 02, 
including Appendix 01, dated November 29, 2015 (``SB A340-52-4095, 
R02'').
    (iii) Airbus Service Bulletin A340-52-5020, Revision 02, 
including Appendices 01 and 02, dated November 27, 2015 (``SB A340-
52-5020, R02'').
    (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 the required hook gap adjustments 
before further flight.
    (i) SB A330-52-3087, R02.
    (ii) SB A340-52-4095, R02.
    (iii) SB A340-52-5020, R02.

(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 March 
16, 2018 (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 
March 16, 2018 (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 Section, Transport Standards Branch, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(j) Forward Cargo Door Terminating Action

    Modification of an airplane by reinforcement of the forward 
cargo door frame structure required by paragraph (i)(1) or (i)(3) of 
this AD constitutes terminating action for the inspections required 
by paragraph (h)(1) and (h)(2) of this AD for that airplane.

(k) Definitions of Pre-Modified and Post-Modified Airplanes of Aft 
Cargo Door

    (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

[[Page 9806]]

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.
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BILLING CODE 4910-13-C
    (i) Airbus Service Bulletin A330-52-3095, Revision 02, including 
Appendices 01 and 02, dated February 19, 2016 (``SB A330-52-3095, 
R02'').
    (ii) Airbus Service Bulletin A340-52-4101, Revision 02, 
including Appendices 01 and 02, dated November 27, 2015 (``SB A340-
52-4101, R02'').
    (iii) Airbus Service Bulletin A340-52-5023, Revision 02, 
including Appendices 01 and 02, dated November 27, 2015 (``SB A340-
52-5023, R02'').
    (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 the required hook gap adjustments 
before further flight.
    (i) SB A330-52-3095, R02.
    (ii) SB A340-52-4101, R02.
    (iii) SB A340-52-5023, R02.

(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 March 16, 2018 (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 March 16, 
2018 (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.

[[Page 9810]]

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 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.

(n) Terminating Action Aft Cargo Doors for Pre-Modified Airplanes

    Modification of an airplane by reinforcement of the aft cargo 
door frame structure required by paragraph (m)(1) or (m)(3) of this 
AD constitutes terminating action for the inspections required by 
paragraph (l)(1) and (l)(2) 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 aft 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 
Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA 
DOA, constitutes terminating action for the inspections required by 
paragraph (l)(1) and (l)(2) of this AD for that airplane. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(p) Exceptions 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 (t)(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) Exception To Reporting in the Service Information

    Although the Airbus service bulletins specified in paragraphs 
(r)(1) through (r)(6) of this AD specify to submit certain 
information to the manufacturer, and specify that action as ``RC'' 
(Required for Compliance), this AD does not include that 
requirement.
    (1) SB A330-52-3087, R02.
    (2) SB A330-52-3095, R02.
    (3) SB A340-52-4095, R02.
    (4) SB A340-52-4101, R02.
    (5) SB A340-52-5020, R02.
    (6) SB A340-52-5023, R02.

(s) 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 March 16, 2018 (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 SB A330-52-3087, R02; SB A340-52-4095, R02; or SB A340-52-5020, 
R02, as applicable.
    (2) This paragraph provides credit for the initial inspection 
required by paragraph (h) of this AD, if that inspection was 
performed before March 16, 2018 (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 SB A330-52-3087, R02; SB A340-52-
4095, R02; or SB A340-52-5020, R02, as applicable.
    (3) This paragraph provides credit for the initial inspection 
required by paragraph (l) of this AD, if that inspection was 
performed before March 16, 2018 (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 SB A330-52-3095, 
R02; SB A340-52-4101, R02; or SB A340-52-5023, R02, as applicable.
    (4) This paragraph provides credit for the initial inspection 
required by paragraph (l) of this AD, if that inspection was 
performed before March 16, 2018 (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 SB A330-52-3095, R02; SB A340-52-
4101, R02; or SB A340-52-5023, R02, as applicable.
    (5) Where Airbus Service Bulletins A330-52-3095, Revision 01, 
dated July 28, 2014; A340-52-4101, Revision 01, dated July 28, 2014; 
A340-52-5020, Revision 01, dated July 9, 2014; and A340-52-5023, 
Revision 01, dated July 28, 2014; refer to using fasteners having P/
N ASNA2657, this AD also allows the use of alternative HST11 series 
fasteners.

(t) 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 manager of the certification office, send it to the 
attention of the person identified in paragraph (u)(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: As of March 16, 2018 (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 
Section, Transport Standards Branch, 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 
paragraphs (p) and (r) 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

[[Page 9811]]

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.

(u) 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 Section, Transport 
Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; 
telephone 425-227-1138; 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 (v)(4) and (v)(5) of this AD.

(v) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
March 16, 2018 (83 FR 5689, February 9, 2018).
    (i) Airbus Service Bulletin A330-52-3087, Revision 02, including 
Appendix 01, dated February 18, 2016.
    (ii) Airbus Service Bulletin A330-52-3095, Revision 02, 
including Appendices 01 and 02, dated February 19, 2016.
    (iii) Airbus Service Bulletin A330-52-3105, dated February 24, 
2016.
    (iv) Airbus Service Bulletin A330-52-3106, dated February 24, 
2016.
    (v) Airbus Service Bulletin A330-52-3110, dated February 15, 
2016.
    (vi) Airbus Service Bulletin A330-52-3111, dated February 15, 
2016.
    (vii) Airbus Service Bulletin A330-52-3112, dated February 24, 
2016.
    (viii) Airbus Service Bulletin A330-52-3113, dated February 15, 
2016.
    (ix) Airbus Service Bulletin A330-52-3114, dated February 15, 
2016.
    (x) Airbus Service Bulletin A330-52-3115, dated April 20, 2016.
    (xi) Airbus Service Bulletin A330-52-3116, dated April 20, 2016.
    (xii) Airbus Service Bulletin A330-52-3117, dated April 20, 
2016.
    (xiii) Airbus Service Bulletin A330-52-3118, dated April 20, 
2016.
    (xiv) Airbus Service Bulletin A340-52-4095, Revision 02, 
including Appendix 01, dated November 29, 2015.
    (xv) Airbus Service Bulletin A340-52-4101, Revision 02, 
including Appendices 01 and 02, dated November 27, 2015.
    (xvi) Airbus Service Bulletin A340-52-4108, dated February 15, 
2016.
    (xvii) Airbus Service Bulletin A340-52-4109, dated February 25, 
2016.
    (xviii) Airbus Service Bulletin A340-52-4113, dated February 15, 
2016.
    (xix) Airbus Service Bulletin A340-52-4114, dated February 15, 
2016.
    (xx) Airbus Service Bulletin A340-52-4115, dated February 19, 
2016.
    (xxi) Airbus Service Bulletin A340-52-4118, dated April 20, 
2016.
    (xxii) Airbus Service Bulletin A340-52-4119, dated April 20, 
2016.
    (xxiii) Airbus Service Bulletin A340-52-4120, dated April 20, 
2016.
    (xxiv) Airbus Service Bulletin A340-52-4121, dated April 20, 
2016.
    (xxv) Airbus Service Bulletin A340-52-5020, Revision 02, 
including Appendices 01 and 02, dated November 27, 2015.
    (xxvi) Airbus Service Bulletin A340-52-5023, Revision 02, 
including Appendices 01 and 02, dated November 27, 2015.
    (4) 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 protected]; 
internet: http://www.airbus.com.
    (5) 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.
    (6) 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 March 1, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-04645 Filed 3-7-18; 8:45 am]
 BILLING CODE 4910-13-P

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