Airworthiness Directives; Airbus Airplanes, 9801-9811 [2018-04645]
Download as PDF
<![CDATA[
Federal Register / Vol. 83, No. 46 / Thursday, March 8, 2018 / Rules and Regulations
BILLING CODE 4910–13–C
(h) Installation Prohibition
(i) Do not install an ECU if any of the fault
messages listed in paragraph (g)(2)(i) of this
AD are in the MDC OMS.
(ii) Do not install an ECU that has a P/N
listed in paragraph (c) of this AD unless it
was sealed as specified in paragraph (g)(1)(i)
of this AD.
(i) Terminating Action
Remove from the AFM, Figure 1, 2, or 3 to
paragraph (g) of this AD, after paragraph
(g)(1)(i) of this AD is accomplished.
(j) Credit for Previous Actions
You may take credit for the actions
required by paragraph (g)(1)(i) of this AD, if
you performed those actions before the
effective date of this AD using Honeywell SB
AS907–76–9021, Revision 0, dated May 13,
2016.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles ACO 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 (l) of this
AD.
(2) 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.
sradovich on DSK3GMQ082PROD with RULES
(l) Related Information
For more information about this AD,
contact Joseph Costa, Aerospace Engineer,
Los Angeles ACO Branch, FAA, 3960
Paramount Blvd., Lakewood, CA 90712–
4137; phone: 562–627–5246; fax: 562–627–
5210; email: joseph.costa@faa.gov.
(m) 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 the AD specifies otherwise.
(i) Honeywell Service Bulletin AS907–76–
9021, Revision 1, dated April 20, 2017.
(ii) Reserved.
(3) For Honeywell service information
identified in this AD, contact Honeywell
International Inc., 111 S. 34th Street,
Phoenix, AZ 85034–2802; phone: 800–601–
3099; internet: https://
myaerospace.honeywell.com/wps/portal/!ut/.
(4) You may view this service information
at FAA, Engine and Propeller Standards
Branch, 1200 District Avenue, Burlington,
MA 01803. For information on the
availability of this material at the FAA, call
781–238–7759.
(5) You may view this service information
that is incorporated by reference at the
VerDate Sep<11>2014
16:39 Mar 07, 2018
Jkt 244001
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Burlington, Massachusetts, on
February 23, 2018.
Karen M. Grant,
Acting Manager, Engine and Propeller
Standards Branch, Aircraft Certification
Service.
[FR Doc. 2018–04614 Filed 3–7–18; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; correction.
AGENCY:
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.
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: airworthiness.A330-A340@
airbus.com; internet https://
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
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
https://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 https://
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.
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.
SUPPLEMENTARY INFORMATION:
SUMMARY:
DATES:
9801
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.
E:\FR\FM\08MRR1.SGM
08MRR1
9802
Federal Register / Vol. 83, No. 46 / Thursday, March 8, 2018 / Rules and Regulations
sradovich on DSK3GMQ082PROD with RULES
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
VerDate Sep<11>2014
16:39 Mar 07, 2018
Jkt 244001
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.
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.
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Corrected]
2. The FAA amends § 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.
E:\FR\FM\08MRR1.SGM
08MRR1
Federal Register / Vol. 83, No. 46 / Thursday, March 8, 2018 / Rules and Regulations
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Affected Cargo Doors
sradovich on DSK3GMQ082PROD with RULES
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
VerDate Sep<11>2014
16:39 Mar 07, 2018
Jkt 244001
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
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
9803
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.
BILLING CODE 4910–13–P
E:\FR\FM\08MRR1.SGM
08MRR1
9804
Federal Register / Vol. 83, No. 46 / Thursday, March 8, 2018 / Rules and Regulations
Table 1 to paragraph (h)(1) of this AD- Forward Cargo Door Inspection Compliance
Time
Compliance Time
Airplane Condition
(on March 16,2018 (the effective date of
this AD))
Within 1,1 00 flight cycles after the last
inspection as specified in AOT
A330-52A3085
Inspected as specified in Airbus AOT
A330-52A3085 and as specified in AOT
A330-A52L003-12, and the last inspection
was accomplished as specified in AOT
A330-52A3085
Within 1,1 00 flight cycles after the last
inspection as specified in AOT
A330-A52L003-12
Inspected as specified in Airbus AOT
A340-52A4092 and as specified in AOT
A340-A52L004-12, and the last inspection
was accomplished as specified in AOT
A340-A52L004-12
Within 1,1 00 flight cycles after the last
inspection as specified in AOT
A340-52A4092
Inspected as specified in Airbus AOT
A340-52A4092 and as specified in AOT
A340-A52L004-12, and the last inspection
was accomplished as specified in AOT
A340-52A4092
Within 1,1 00 flight cycles after the last
inspection as specified in AOT
A340-A52L004-12
Inspected as specified in the original issue
of Airbus Service Bulletin (SB) A330-523087, or SB A340-52-4095, or SB A34052-5020, as applicable
There is no compliance time for the initial
inspection in paragraph (h)(1) ofthis AD
for these airplanes, provided these airplanes
comply with the actions specified
paragraph (s)(1) ofthis AD.
Inspected as specified in Revision 01 of
Airbus SB A330-52-3087, or SB A340-524095, or SB A340-52-5020, as applicable
There is no compliance time for the initial
inspection in paragraph (h)(1) of this AD
for these airplanes, provided these airplanes
comply with the actions specified in
paragraph (s)(2) ofthis AD.
VerDate Sep<11>2014
16:39 Mar 07, 2018
Jkt 244001
PO 00000
Frm 00012
Fmt 4700
Sfmt 4725
E:\FR\FM\08MRR1.SGM
08MRR1
ER08MR18.003</GPH>
Within 1,1 00 flight cycles after the last
inspection, but without exceeding 10,600
flight cycles since first installation of the
forward cargo door on an airplane
Inspected as specified in Airbus AOT
A330-52A3085 and as specified in AOT
A330-A52L003-12, and the last inspection
was accomplished as specified in AOT
A330-A52L003-12
sradovich on DSK3GMQ082PROD with RULES
Inspected only as specified in Airbus Alert
Operator Transmission (AOT)
A330-52A3085 or AOT A340-52A4092, as
applicable
Federal Register / Vol. 83, No. 46 / Thursday, March 8, 2018 / Rules and Regulations
sradovich on DSK3GMQ082PROD with RULES
(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).
VerDate Sep<11>2014
16:39 Mar 07, 2018
Jkt 244001
(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
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
–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 PostModified Airplanes of Aft Cargo Door
(1) For the purpose of this AD, premodified 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, postmodification Model A330–200 series
airplanes, Model A330–200 Freighter series
airplanes, Model A330–300 series airplanes,
Model A340–200 series airplanes, and Model
E:\FR\FM\08MRR1.SGM
08MRR1
ER08MR18.004</GPH>
BILLING CODE 4910–13–C
9805
9806
Federal Register / Vol. 83, No. 46 / Thursday, March 8, 2018 / Rules and Regulations
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
sradovich on DSK3GMQ082PROD with RULES
(1) Before exceeding 4,000 total flight
cycles for pre-modified airplanes, or 12,000
total flight cycles for post-modified airplanes,
VerDate Sep<11>2014
16:39 Mar 07, 2018
Jkt 244001
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
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
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.
BILLING CODE 4910–13–P
E:\FR\FM\08MRR1.SGM
08MRR1
Federal Register / Vol. 83, No. 46 / Thursday, March 8, 2018 / Rules and Regulations
9807
Table 2 to paragraph (1)(1) of this AD -Aft Cargo Door Inspection Compliance Times
for Pre-Modified Airplanes
Compliance Time
Airplane Condition
(on March 16,2018 (the effective date of
this AD))
Within 550 flight cycles after the last
inspection as specified in AOT A33052A3084
Inspected as specified in Airbus AOT
A330-52A3084 and as specified in AOT
A330-A52L001-12, and the last inspection
was accomplished as specified in AOT
A330-52A3084
Within 550 flight cycles after the last
inspection as specified in AOT
A330-A52L001-12
Inspected as specified in Airbus AOT
A340-52A4091 and as specified in AOT
A340-A52L002-12, and the last inspection
was accomplished as specified in AOT
A340-A52L002-12
Within 550 flight cycles after the last
inspection as specified in AOT A34052A4091
Inspected as specified in Airbus AOT
A340-52A4091 and as specified in AOT
A340-A52L002-12, and the last inspection
was accomplished as specified in AOT
A340-52A4091
Within 550 flight cycles after the last
inspection as specified in AOT
A340-A52L002-12
Inspected as specified in the original issue
of Airbus SB A330-52-3095, or SB
A340-52-4101, as applicable
There is no compliance time for the initial
inspection in paragraph (1)(1) of this AD
for these airplanes, provided these
airplanes comply with the actions specified
in paragraph ( s)(3) of this AD.
Inspected as specified in Revision 01 of
Airbus SB A330-52-3095, or SB
A340-52-4101, as applicable
There is no compliance time for the initial
inspection in paragraph (1)(1) of this AD
for these airplanes, provided these
airplanes comply with the actions specified
in paragraph ( s)(4) of this AD.
VerDate Sep<11>2014
16:39 Mar 07, 2018
Jkt 244001
PO 00000
Frm 00015
Fmt 4700
Sfmt 4725
E:\FR\FM\08MRR1.SGM
08MRR1
ER08MR18.005</GPH>
Within 550 flight cycles after the last
inspection, but without exceeding 15,800
flight cycles since first installation of the
aft cargo door on an airplane
Inspected as specified in Airbus AOT
A330-52A3084 and as specified in AOT
A330-A52L001-12, and the last inspection
was accomplished as specified in AOT
A330-A52L001-12
sradovich on DSK3GMQ082PROD with RULES
Inspected only as specified in Airbus AOT
A330-52A3084, or AOT A340-52A4091,
as applicable
9808
Federal Register / Vol. 83, No. 46 / Thursday, March 8, 2018 / Rules and Regulations
Compliance Time
Airplane Condition
(on March 16,2018 (the effective date of
this AD))
Within 550 flight cycles after March 16,
2018 (the effective date ofthis AD), but
without exceeding 4,550 flight cycles since
first installation of the aft cargo door on an
airplane
VerDate Sep<11>2014
16:39 Mar 07, 2018
Jkt 244001
PO 00000
Frm 00016
Fmt 4700
Sfmt 4725
E:\FR\FM\08MRR1.SGM
08MRR1
ER08MR18.006</GPH>
Within 1,400 flight cycles after the last
inspection as 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
sradovich on DSK3GMQ082PROD with RULES
Inspected as specified in Revision 02 of
Airbus SB A330-52-3095, or SB
A340-52-4101, as applicable
sradovich on DSK3GMQ082PROD with RULES
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.
VerDate Sep<11>2014
16:39 Mar 07, 2018
Jkt 244001
(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).
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
9809
(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.
E:\FR\FM\08MRR1.SGM
08MRR1
ER08MR18.007</GPH>
Federal Register / Vol. 83, No. 46 / Thursday, March 8, 2018 / Rules and Regulations
9810
Federal Register / Vol. 83, No. 46 / Thursday, March 8, 2018 / Rules and Regulations
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 DOAauthorized 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.
sradovich on DSK3GMQ082PROD with RULES
(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
VerDate Sep<11>2014
16:39 Mar 07, 2018
Jkt 244001
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
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
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: 9-ANM-116AMOC–REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: As of
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
E:\FR\FM\08MRR1.SGM
08MRR1
Federal Register / Vol. 83, No. 46 / Thursday, March 8, 2018 / Rules and Regulations
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.
sradovich on DSK3GMQ082PROD with RULES
(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 https://
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.
VerDate Sep<11>2014
16:39 Mar 07, 2018
Jkt 244001
(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:
airworthiness.A330-A340@airbus.com;
internet: https://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: https://
www.archives.gov/federal-register/cfr/ibrlocations.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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–1166; Product
Identifier 2017–CE–042–AD; Amendment
39–19217; AD 2018–05–08]
RIN 2120–AA64
Airworthiness Directives; GA 8 Airvan
(Pty) Ltd Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2013–19–
12 for GA 8 Airvan (Pty) Ltd Models
SUMMARY:
PO 00000
Frm 00019
Fmt 4700
Sfmt 4700
9811
GA8 and GA8–TC320 airplanes. This
AD results from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and address
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as the fuel system integral
sump tank not meeting FAA regulations.
We are issuing this AD to require
actions to address the unsafe condition
on these products.
DATES: This AD is effective April 12,
2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 12, 2018.
ADDRESSES: You may examine the AD
docket on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
1166; or in person at Docket Operations,
U.S. Department of Transportation, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
For service information identified in
this AD, contact GA 8 Airvan (Pty) Ltd,
c/o GippsAero Pty Ltd, Attn: Technical
Services, P.O. Box 881, Morwell
Victoria 3840, Australia; telephone: +61
03 5172 1200; fax: +61 03 5172 1201;
email: aircraft.techpubs@
mahindraaerospace.com. You may view
this referenced service information at
the FAA, Policy and Innovation
Division, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA,
call (816) 329–4148. It is also available
on the internet at https://
www.regulations.gov by searching for
Docket No. FAA–2017–1166.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Standards Branch,
901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; fax: (816) 329–4090; email:
doug.rudolph@faa.gov.
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 GA 8 Airvan (Pty) Ltd Models
GA8 and GA8–TC320 airplanes. That
NPRM was published in the Federal
Register on December 19, 2017 (82 FR
60128), and proposed to supersede AD
2013–19–12, Amendment 39–17594 (78
FR 58872, September 25, 2013) (‘‘AD
2013–19–12’’).
Since we issued AD 2013–19–12, the
related service information has been
amended to incorporate a modification
E:\FR\FM\08MRR1.SGM
08MRR1
]]>Agencies
[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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
https://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 https://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 https://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.
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.
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.
BILLING CODE 4910-13-P
[[Page 9804]]
[GRAPHIC] [TIFF OMITTED] TR08MR18.003
[[Page 9805]]
[GRAPHIC] [TIFF OMITTED] TR08MR18.004
BILLING CODE 4910-13-C
(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.
BILLING CODE 4910-13-P
[[Page 9807]]
[GRAPHIC] [TIFF OMITTED] TR08MR18.005
[[Page 9808]]
[GRAPHIC] [TIFF OMITTED] TR08MR18.006
[[Page 9809]]
[GRAPHIC] [TIFF OMITTED] TR08MR18.007
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 https://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: https://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: https://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
