Airworthiness Directives; Airbus Airplanes, 34891-34894 [2017-15553]
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Federal Register / Vol. 82, No. 143 / Thursday, July 27, 2017 / Proposed Rules
phone: 562–627–5239; fax: 562–627–5210;
email: chandraduth.ramdoss@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740;
telephone: 562–797–1717; Internet: https://
www.myboeingfleet.com. You may view this
referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
Issued in Renton, Washington, on July 18,
2017.
Victor Wicklund,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–15554 Filed 7–26–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0708; Directorate
Identifier 2017–NM–035–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Examining the AD Docket
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) AD 2016–
20–11, for certain Airbus Model A300
B4–600, B4–600R, and F4–600R series
airplanes, and Model A300 C4–605R
Variant F airplanes (collectively called
Model A300–600 series airplanes); and
Airbus Model A310 series airplanes. AD
2016–20–11 requires repetitive
inspections of the external area of the aft
cargo door sill beam for cracking,
repetitive inspections for fatigue
cracking of the cargo door sill beam,
lock fitting, and torsion box plate, and
repair if necessary. Since we issued AD
2016–20–11, we have determined that
reinforcement of the aft cargo door sill
beam area is necessary to address the
unsafe condition, which constitutes
terminating action for the repetitive
inspections. This proposed AD would
retain the inspections for cracking, and
repair if necessary; and require
reinforcement of the aft cargo door sill
beam area. We are proposing this AD to
address the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by September 11,
2017.
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SUMMARY:
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You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Airbus SAS,
Airworthiness Office—EAW, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
ADDRESSES:
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0708; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–2125;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2017–0708; Directorate Identifier 2017–
NM–035–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
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34891
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On September 28, 2016, we issued AD
2016–20–11, Amendment 39–18677 (81
FR 85837, November 29, 2016) (‘‘AD
2016–20–11’’), for certain Airbus Model
A300–600 series airplanes; and Airbus
Model A310 series airplanes. AD 2016–
20–11 was prompted by reports of
fatigue cracks on the cargo door sill
beam, lock fitting, and torsion box plate.
AD 2016–20–11 requires repetitive
ultrasonic and detailed inspections of
the external area of the aft cargo door
sill beam for cracking, repetitive high
frequency eddy current (HFEC)
inspections for fatigue cracking of the
cargo door sill beam, lock fitting, and
torsion box plate, and repair if
necessary. We issued AD 2016–20–11 to
detect and correct fatigue cracking of the
cargo door sill beam, lock fitting, and
torsion box plate, which could result in
the loss of the door locking function and
subsequently, loss of the cargo door in
flight and rapid decompression.
Since we issued AD 2016–20–11,
Airbus has developed a reinforcement
modification of the aft cargo door sill
beam area, which constitutes
terminating action for the repetitive
inspections. We have determined the
reinforcement of the aft cargo door sill
beam area is necessary to address the
unsafe condition.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2017–0048,
dated March 15, 2017; corrected April
20, 2017 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A300–600 series airplanes; and
Airbus Model A310 series airplanes.
The MCAI states:
In the frame of the widespread fatigue
damage (WFD) compliance study and after an
in-service occurrence, the area of the aft
cargo door sill beam and adjacent structure
was identified as sensitive to the fatigue
loads.
This condition, if not detected and
corrected, could lead to failure of multiple
lock fittings, possibly resulting in loss of the
cargo door in flight and consequent explosive
decompression of the aeroplane.
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To address this potential unsafe condition,
Airbus issued Alert Operators Transmission
(AOT) A53W005–14 providing inspection
instructions and, consequently, EASA issued
Emergency AD 2014–0097–E [which
corresponded to FAA AD 2014–12–06] to
require repetitive ultrasonic inspections (US)
or detailed inspections (DET) of the aft cargo
door sill beam area [and corrective actions if
necessary].
After that [EASA] AD was issued, further
analysis indicated that repetitive high
frequency eddy current (HFEC) inspections
needed to be introduced, and Airbus
published Service Bulletin (SB) A310–53–
2139 and SB A300–53–6179 to provide
instructions. Prompted by this determination,
EASA issued AD 2015–0150, retaining the
requirements of EASA Emergency AD 2014–
0097–E, which was superseded, and required
repetitive HFEC inspections of the concerned
areas. The first HFEC inspection terminated
the repetitive US/DET inspections. That
[EASA] AD also required the inspection
results to be reported.
Since that [EASA] AD was issued, Airbus
developed a reinforcement modification of
the aft cargo door sill beam area, and
published Airbus SB A310–53–2141 and SB
A300–53–6181, which were revised lately, to
make this available for in-service application.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2015–0150 [which corresponded to FAA
AD 2016–20–11], which is superseded, and
requires modification [reinforcement] of the
aft cargo door sill beam, which constitutes
terminating action for the repetitive
inspections.
This [EASA] AD is re-published to correct
the compliance time description in Table 4.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0708.
Related Service Information Under 1
CFR Part 51
Airbus has issued Airbus Service
Bulletin A300–53–6181, Revision 01,
dated July 2, 2015; and A310–53–2141,
Revision 01, dated July 2, 2015. This
service information describes
procedures for reinforcing the aft cargo
door sill beam. These service bulletins
are distinct since they apply to different
airplane models.
Airbus has issued Airbus Service
Bulletin A300–53–6179, dated
December 12, 2014; and A310–53–2139,
dated December 12, 2014. This service
information describes procedures for
repetitive HFEC inspections of the cargo
door sill beam, lock fitting, and torsion
box plate. These service bulletins are
distinct since they apply to different
airplane models.
Airbus has also issued AOT
A53W005–14, Revision 01, dated April
29, 2014, which describes procedures
for doing an ultrasonic inspection or
detailed inspection of the aft cargo door
sill beam external area for cracking.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Costs of Compliance
We estimate that this AD affects 75
airplanes of U.S. registry. We estimate
the following costs to comply with this
proposed AD:
ESTIMATED COSTS
Action
Inspection (retained actions
from AD 2016–20–11).
Modification (new proposed
action).
Reporting ................................
(retained action from AD
2016–20–11).
Labor cost
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Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this AD is 2120–0056. The
paperwork cost associated with this AD
has been detailed in the Costs of
Compliance section of this document
and includes time for reviewing
17:09 Jul 26, 2017
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Cost per product
Cost on U.S. operators
N/A
$1,020 per inspection cycle ...
$76,500 per inspection cycle.
$96,890
$100,290 ................................
$7,521,750.
0
12 work-hours × $85 per hour
= $1,020 per inspection
cycle.
40 work-hours × $85 per hour
= $3,400.
1 work-hour × $85 per hour =
$85 per inspection cycle.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
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Parts cost
$85 per inspection cycle ........
$6,375 per inspection cycle.
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this AD is mandatory. Comments
concerning the accuracy of this burden
and suggestions for reducing the burden
should be directed to the FAA at 800
Independence Ave. SW., Washington,
DC 20591, ATTN: Information
Collection Clearance Officer, AES–200.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
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We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
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substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
(4) Airbus Model A300 C4–605R Variant F
airplanes.
(5) Airbus Model A310–203, –204, –221,
–222, –304, –322, –324, and –325 airplanes.
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA).
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(i) Retained Reporting Requirement, With
No Changes
This paragraph restates the requirements of
paragraph (i) of AD 2016–20–11, with no
changes. Submit a report of the findings (both
positive and negative) of the inspection
required by paragraph (g) of this AD to
‘‘Airbus Service Bulletin Reporting Online
Application’’ on Airbus World (https://
w3.airbus.com/), at the applicable time
specified in paragraph (i)(1) or (i)(2) of this
AD. The report must include the inspection
results, including no findings.
(1) If the inspection was done on or after
January 3, 2017 (the effective date of AD
2016–20–11): Submit the report within 30
days after the inspection.
(2) If the inspection was done before
January 3, 2017 (the effective date of AD
2016–20–11): Submit the report within 30
days after January 3, 2017.
(e) Reason
This AD was prompted by reports of
fatigue cracks on the cargo door sill beam,
lock fitting, and torsion box plate. We are
issuing this AD to prevent fatigue cracking of
the cargo door sill beam, lock fitting, and
torsion box plate, which could result in the
loss of the door locking function and
subsequently, loss of the cargo door in flight
and rapid decompression.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(b) Affected ADs
This AD replaces AD 2016–20–11,
Amendment 39–18677 (81 FR 85837,
November 29, 2016) (‘‘AD 2016–20–11’’).
(g) Retained Inspection, With No Changes
This paragraph restates the requirements of
paragraph (g) of AD 2016–20–11, with no
changes. Within the compliance time
identified in paragraph (g)(1), (g)(2), or (g)(3)
of this AD, as applicable: Do an ultrasonic
inspection or detailed inspection of the aft
cargo door sill beam external area for
cracking, in accordance with Airbus Alert
Operators Transmission (AOT) A53W005–14,
dated April 22, 2014; or Airbus AOT
A53W005–14, Revision 01, dated April 29,
2014. Repeat the inspection thereafter at
intervals not to exceed 275 flight cycles. As
of January 3, 2017 (the effective date of AD
2016–20–11), use only AOT A53W005–14,
Revision 01, dated April 29, 2014, to comply
with the requirements of this paragraph.
(1) For airplanes that have accumulated
30,000 flight cycles or more since the
airplane’s first flight as of July 2, 2014 (the
effective date of AD 2014–12–06,
Amendment 39–17867, (79 FR 34403, June
17, 2014) (‘‘AD 2014–12–06’’)): Within 50
flight cycles after July 2, 2014.
(2) For airplanes that have accumulated
18,000 flight cycles or more, but fewer than
30,000 flight cycles since the airplane’s first
flight as of July 2, 2014 (the effective date of
AD 2014–12–06): Within 275 flight cycles
after July 2, 2014.
(3) For airplanes that have accumulated
fewer than 18,000 flight cycles since the
airplane’s first flight as of July 2, 2014 (the
effective date of AD 2014–12–06): Before
exceeding 18,275 flight cycles since the
airplane’s first flight.
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1) through (c)(5) of this AD,
certificated in any category, all manufacturer
serial numbers on which Airbus Modification
05438 has been embodied in production,
except those on which Airbus Modification
12046 has been embodied in production.
(1) Airbus Model A300 B4–601, B4–603,
B4–620, and B4–622 airplanes.
(2) Airbus Model A300 B4–605R and B4–
622R airplanes.
(3) Airbus Model A300 F4–605R and F4–
622R airplanes.
(h) Retained Optional Terminating Action,
With No Changes
This paragraph restates the provisions of
paragraph (h) of AD 2016–20–11, with no
changes. Accomplishment of a high
frequency eddy current (HFEC) inspection for
cracking, in accordance with Airbus AOT
A53W005–14, dated April 22, 2014; or AOT
A53W005–14, Revision 01, dated April 29,
2014; terminates the repetitive inspections
required by paragraph (g) of this AD for that
airplane. If any cracking is found during the
HFEC inspection, before further flight, repair
using a method approved by the Manager,
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2016–20–11, Amendment 39–18677 (81
FR 85837, November 29, 2016), and
adding the following new AD:
■
Airbus: Docket No. FAA–2017–0708;
Directorate Identifier 2017–NM–035–AD.
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(a) Comments Due Date
We must receive comments by September
11, 2017.
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(j) Retained Definition of Airplane Groups,
With No Changes
This paragraph restates the definitions
specified in paragraph (j) of AD 2016–20–11,
with no changes. Paragraphs (k)(1), (k)(2),
and (k)(3) of this AD refer to airplane groups,
as identified in paragraphs (j)(1), (j)(2), and
(j)(3) of this AD.
(1) Airplanes on which an HFEC
inspection was accomplished as specified in
Airbus AOT A53W005–14.
(2) Airplanes on which no HFEC
inspection was accomplished as specified in
Airbus AOT A53W005–14, that have
accumulated more than 18,000 total flight
cycles as of January 3, 2017 (the effective
date of AD 2016–20–11).
(3) Airplanes on which no HFEC
inspection was accomplished as specified in
Airbus AOT A53W005–14, that have
accumulated 18,000 total flight cycles or
fewer as of January 3, 2017 (the effective date
of AD 2016–20–11).
(k) Retained Repetitive HFEC Inspections,
With No Changes
This paragraph restates the requirements of
paragraph (k) of AD 2016–20–11, with no
changes. At the applicable time specified in
paragraph (k)(1), (k)(2), or (k)(3) of this AD:
Do an HFEC inspection for fatigue cracking
of the cargo door sill beam, lock fitting, and
torsion box plate, in accordance with Airbus
Service Bulletin A300–53–6179, dated
December 12, 2014; or Airbus Service
Bulletin A310–53–2139, dated December 12,
2014; as applicable. Repeat the HFEC
inspection thereafter at intervals not to
exceed 4,600 flight cycles.
(1) For airplanes identified in paragraph
(j)(1) of this AD: Inspect within 4,600 flight
cycles after the most recent HFEC inspection
specified in Airbus AOT A53W005–14.
(2) For airplanes identified in paragraph
(j)(2) of this AD: Inspect within 2,000 flight
cycles after January 3, 2017 (the effective date
of AD 2016–20–11).
(3) For airplanes identified in paragraph
(j)(3) of this AD: Inspect before exceeding
13,000 total flight cycles since the airplane’s
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first flight, or within 2,000 flight cycles after
January 3, 2017 (the effective date of AD
2016–20–11), whichever occurs later.
(l) Retained Corrective Action, With No
Changes
This paragraph restates the requirements of
paragraph (l) of AD 2016–20–11, with no
changes. If any crack is found during any
inspection required by paragraph (g) or (k) of
this AD: Before further flight, repair using a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the EASA; or
Airbus’s EASA DOA.
(m) Retained Terminating Action for
Repetitive Inspections in Paragraph (g) of
This AD, With No Changes
This paragraph restates the terminating
action of paragraph (m)(1) of AD 2016–20–11,
with no changes. For any airplane identified
in paragraphs (j)(2) and (j)(3) of this AD,
accomplishment of the initial inspection
required by paragraph (k) of this AD
terminates the repetitive inspections required
by paragraph (g) of this AD.
(n) New Cargo Door Reinforcement
At the latest of the applicable times
specified in paragraphs (n)(1), (n)(2), and
(n)(3) of this AD: Reinforce the aft cargo door
sill beam area, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A310–53–2141, Revision 01,
dated July 2, 2015; or Airbus Service Bulletin
A300–53–6181, Revision 01, dated July 2,
2015; as applicable.
(1) Before exceeding 19,600 flight cycles
since first flight of the airplane.
(2) Within 2,300 flight cycles after the last
HFEC or detailed inspection required by this
AD that was accomplished before the
effective date of this AD.
(3) Within 12 months after the effective
date of this AD.
(o) New Terminating Action
Modification of an airplane as required by
paragraph (n) of this AD constitutes
terminating action for the repetitive
inspections required by paragraphs (g) and
(k) of this AD for that airplane.
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(p) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (n) of this AD, if those
actions were performed before the effective
date of this AD using Airbus Service Bulletin
A300–53–6181, dated June 26, 2015; or
Airbus Service Bulletin A310–53–2141,
dated June 26, 2015; as applicable.
(q) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to the
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17:09 Jul 26, 2017
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attention of the person identified in
paragraph (r)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov.
(i) 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.
(ii) AMOCs approved previously for AD
2016–20–11 are approved as AMOCs for the
corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(4) Required for Compliance (RC): Except
as required by paragraph (l) of this AD: If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(r) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2017–0048, dated
March 15, 2017; corrected April 20, 2017, 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–2017–0708.
(2) For more information about this AD,
contact Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
PO 00000
Frm 00011
Fmt 4702
Sfmt 4702
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–2125; fax 425–227–1149.
You may view this service information at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
For information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on July 14,
2017.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–15553 Filed 7–26–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF COMMERCE
Bureau of Economic Analysis
15 CFR Part 801
[Docket No.: 170322304–7304–01]
RIN 0691–AA86
Direct Investment Surveys: BE–12,
Benchmark Survey of Foreign Direct
Investment in the United States
Bureau of Economic Analysis,
Commerce.
ACTION: Notice of proposed rulemaking.
AGENCY:
This proposed rule would
amend regulations of the Department of
Commerce’s Bureau of Economic
Analysis (BEA) to set forth the reporting
requirements for the 2017 BE–12,
Benchmark Survey of Foreign Direct
Investment in the United States. The
BE–12 survey is conducted every five
years; the prior survey covered 2012.
The benchmark survey covers the
universe of foreign direct investment in
the United States and is BEA’s most
detailed survey of such investment. For
the 2017 benchmark survey, BEA
proposes changes in data items
collected, the design of the survey
forms, and the reporting requirements
for the survey to satisfy changing data
needs, improve data quality and the
effectiveness and efficiency of data
collection.
DATES: Comments on this proposed rule
will receive consideration if submitted
in writing on or before 5 p.m. September
25, 2017.
ADDRESSES: You may submit comments,
identified by RIN 0691–AA86, and
referencing the agency name (Bureau of
Economic Analysis), by any of the
following methods:
SUMMARY:
E:\FR\FM\27JYP1.SGM
27JYP1
Agencies
[Federal Register Volume 82, Number 143 (Thursday, July 27, 2017)]
[Proposed Rules]
[Pages 34891-34894]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-15553]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0708; Directorate Identifier 2017-NM-035-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) AD 2016-
20-11, for certain Airbus Model A300 B4-600, B4-600R, and F4-600R
series airplanes, and Model A300 C4-605R Variant F airplanes
(collectively called Model A300-600 series airplanes); and Airbus Model
A310 series airplanes. AD 2016-20-11 requires repetitive inspections of
the external area of the aft cargo door sill beam for cracking,
repetitive inspections for fatigue cracking of the cargo door sill
beam, lock fitting, and torsion box plate, and repair if necessary.
Since we issued AD 2016-20-11, we have determined that reinforcement of
the aft cargo door sill beam area is necessary to address the unsafe
condition, which constitutes terminating action for the repetitive
inspections. This proposed AD would retain the inspections for
cracking, and repair if necessary; and require reinforcement of the aft
cargo door sill beam area. We are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on this proposed AD by September 11,
2017.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Airbus
SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44
51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0708; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2017-0708;
Directorate Identifier 2017-NM-035-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On September 28, 2016, we issued AD 2016-20-11, Amendment 39-18677
(81 FR 85837, November 29, 2016) (``AD 2016-20-11''), for certain
Airbus Model A300-600 series airplanes; and Airbus Model A310 series
airplanes. AD 2016-20-11 was prompted by reports of fatigue cracks on
the cargo door sill beam, lock fitting, and torsion box plate. AD 2016-
20-11 requires repetitive ultrasonic and detailed inspections of the
external area of the aft cargo door sill beam for cracking, repetitive
high frequency eddy current (HFEC) inspections for fatigue cracking of
the cargo door sill beam, lock fitting, and torsion box plate, and
repair if necessary. We issued AD 2016-20-11 to detect and correct
fatigue cracking of the cargo door sill beam, lock fitting, and torsion
box plate, which could result in the loss of the door locking function
and subsequently, loss of the cargo door in flight and rapid
decompression.
Since we issued AD 2016-20-11, Airbus has developed a reinforcement
modification of the aft cargo door sill beam area, which constitutes
terminating action for the repetitive inspections. We have determined
the reinforcement of the aft cargo door sill beam area is necessary to
address the unsafe condition.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2017-0048, dated March 15, 2017; corrected April 20, 2017 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A300-600 series airplanes; and Airbus Model A310 series airplanes. The
MCAI states:
In the frame of the widespread fatigue damage (WFD) compliance
study and after an in-service occurrence, the area of the aft cargo
door sill beam and adjacent structure was identified as sensitive to
the fatigue loads.
This condition, if not detected and corrected, could lead to
failure of multiple lock fittings, possibly resulting in loss of the
cargo door in flight and consequent explosive decompression of the
aeroplane.
[[Page 34892]]
To address this potential unsafe condition, Airbus issued Alert
Operators Transmission (AOT) A53W005-14 providing inspection
instructions and, consequently, EASA issued Emergency AD 2014-0097-E
[which corresponded to FAA AD 2014-12-06] to require repetitive
ultrasonic inspections (US) or detailed inspections (DET) of the aft
cargo door sill beam area [and corrective actions if necessary].
After that [EASA] AD was issued, further analysis indicated that
repetitive high frequency eddy current (HFEC) inspections needed to
be introduced, and Airbus published Service Bulletin (SB) A310-53-
2139 and SB A300-53-6179 to provide instructions. Prompted by this
determination, EASA issued AD 2015-0150, retaining the requirements
of EASA Emergency AD 2014-0097-E, which was superseded, and required
repetitive HFEC inspections of the concerned areas. The first HFEC
inspection terminated the repetitive US/DET inspections. That [EASA]
AD also required the inspection results to be reported.
Since that [EASA] AD was issued, Airbus developed a
reinforcement modification of the aft cargo door sill beam area, and
published Airbus SB A310-53-2141 and SB A300-53-6181, which were
revised lately, to make this available for in-service application.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2015-0150 [which corresponded to FAA AD
2016-20-11], which is superseded, and requires modification
[reinforcement] of the aft cargo door sill beam, which constitutes
terminating action for the repetitive inspections.
This [EASA] AD is re-published to correct the compliance time
description in Table 4.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0708.
Related Service Information Under 1 CFR Part 51
Airbus has issued Airbus Service Bulletin A300-53-6181, Revision
01, dated July 2, 2015; and A310-53-2141, Revision 01, dated July 2,
2015. This service information describes procedures for reinforcing the
aft cargo door sill beam. These service bulletins are distinct since
they apply to different airplane models.
Airbus has issued Airbus Service Bulletin A300-53-6179, dated
December 12, 2014; and A310-53-2139, dated December 12, 2014. This
service information describes procedures for repetitive HFEC
inspections of the cargo door sill beam, lock fitting, and torsion box
plate. These service bulletins are distinct since they apply to
different airplane models.
Airbus has also issued AOT A53W005-14, Revision 01, dated April 29,
2014, which describes procedures for doing an ultrasonic inspection or
detailed inspection of the aft cargo door sill beam external area for
cracking.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Costs of Compliance
We estimate that this AD affects 75 airplanes of U.S. registry. We
estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection (retained actions from 12 work-hours x $85 N/A $1,020 per $76,500 per
AD 2016-20-11). per hour = $1,020 inspection cycle. inspection cycle.
per inspection
cycle.
Modification (new proposed 40 work-hours x $85 $96,890 $100,290........... $7,521,750.
action). per hour = $3,400.
Reporting........................ 1 work-hour x $85 0 $85 per inspection $6,375 per
(retained action from AD 2016-20- per hour = $85 per cycle. inspection cycle.
11). inspection cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a
[[Page 34893]]
substantial direct effect on the States, on the relationship between
the national Government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2016-20-11, Amendment 39-18677 (81 FR 85837, November 29, 2016), and
adding the following new AD:
Airbus: Docket No. FAA-2017-0708; Directorate Identifier 2017-NM-
035-AD.
(a) Comments Due Date
We must receive comments by September 11, 2017.
(b) Affected ADs
This AD replaces AD 2016-20-11, Amendment 39-18677 (81 FR 85837,
November 29, 2016) (``AD 2016-20-11'').
(c) Applicability
This AD applies to the airplanes identified in paragraphs (c)(1)
through (c)(5) of this AD, certificated in any category, all
manufacturer serial numbers on which Airbus Modification 05438 has
been embodied in production, except those on which Airbus
Modification 12046 has been embodied in production.
(1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622
airplanes.
(2) Airbus Model A300 B4-605R and B4-622R airplanes.
(3) Airbus Model A300 F4-605R and F4-622R airplanes.
(4) Airbus Model A300 C4-605R Variant F airplanes.
(5) Airbus Model A310-203, -204, -221, -222, -304, -322, -324,
and -325 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of fatigue cracks on the cargo
door sill beam, lock fitting, and torsion box plate. We are issuing
this AD to prevent fatigue cracking of the cargo door sill beam,
lock fitting, and torsion box plate, which could result in the loss
of the door locking function and subsequently, loss of the cargo
door in flight and rapid decompression.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection, With No Changes
This paragraph restates the requirements of paragraph (g) of AD
2016-20-11, with no changes. Within the compliance time identified
in paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable: Do
an ultrasonic inspection or detailed inspection of the aft cargo
door sill beam external area for cracking, in accordance with Airbus
Alert Operators Transmission (AOT) A53W005-14, dated April 22, 2014;
or Airbus AOT A53W005-14, Revision 01, dated April 29, 2014. Repeat
the inspection thereafter at intervals not to exceed 275 flight
cycles. As of January 3, 2017 (the effective date of AD 2016-20-11),
use only AOT A53W005-14, Revision 01, dated April 29, 2014, to
comply with the requirements of this paragraph.
(1) For airplanes that have accumulated 30,000 flight cycles or
more since the airplane's first flight as of July 2, 2014 (the
effective date of AD 2014-12-06, Amendment 39-17867, (79 FR 34403,
June 17, 2014) (``AD 2014-12-06'')): Within 50 flight cycles after
July 2, 2014.
(2) For airplanes that have accumulated 18,000 flight cycles or
more, but fewer than 30,000 flight cycles since the airplane's first
flight as of July 2, 2014 (the effective date of AD 2014-12-06):
Within 275 flight cycles after July 2, 2014.
(3) For airplanes that have accumulated fewer than 18,000 flight
cycles since the airplane's first flight as of July 2, 2014 (the
effective date of AD 2014-12-06): Before exceeding 18,275 flight
cycles since the airplane's first flight.
(h) Retained Optional Terminating Action, With No Changes
This paragraph restates the provisions of paragraph (h) of AD
2016-20-11, with no changes. Accomplishment of a high frequency eddy
current (HFEC) inspection for cracking, in accordance with Airbus
AOT A53W005-14, dated April 22, 2014; or AOT A53W005-14, Revision
01, dated April 29, 2014; terminates the repetitive inspections
required by paragraph (g) of this AD for that airplane. If any
cracking is found during the HFEC inspection, before further flight,
repair using a method approved by the Manager, International Branch,
ANM-116, Transport Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA); or Airbus's EASA Design Organization
Approval (DOA).
(i) Retained Reporting Requirement, With No Changes
This paragraph restates the requirements of paragraph (i) of AD
2016-20-11, with no changes. Submit a report of the findings (both
positive and negative) of the inspection required by paragraph (g)
of this AD to ``Airbus Service Bulletin Reporting Online
Application'' on Airbus World (https://w3.airbus.com/), at the
applicable time specified in paragraph (i)(1) or (i)(2) of this AD.
The report must include the inspection results, including no
findings.
(1) If the inspection was done on or after January 3, 2017 (the
effective date of AD 2016-20-11): Submit the report within 30 days
after the inspection.
(2) If the inspection was done before January 3, 2017 (the
effective date of AD 2016-20-11): Submit the report within 30 days
after January 3, 2017.
(j) Retained Definition of Airplane Groups, With No Changes
This paragraph restates the definitions specified in paragraph
(j) of AD 2016-20-11, with no changes. Paragraphs (k)(1), (k)(2),
and (k)(3) of this AD refer to airplane groups, as identified in
paragraphs (j)(1), (j)(2), and (j)(3) of this AD.
(1) Airplanes on which an HFEC inspection was accomplished as
specified in Airbus AOT A53W005-14.
(2) Airplanes on which no HFEC inspection was accomplished as
specified in Airbus AOT A53W005-14, that have accumulated more than
18,000 total flight cycles as of January 3, 2017 (the effective date
of AD 2016-20-11).
(3) Airplanes on which no HFEC inspection was accomplished as
specified in Airbus AOT A53W005-14, that have accumulated 18,000
total flight cycles or fewer as of January 3, 2017 (the effective
date of AD 2016-20-11).
(k) Retained Repetitive HFEC Inspections, With No Changes
This paragraph restates the requirements of paragraph (k) of AD
2016-20-11, with no changes. At the applicable time specified in
paragraph (k)(1), (k)(2), or (k)(3) of this AD: Do an HFEC
inspection for fatigue cracking of the cargo door sill beam, lock
fitting, and torsion box plate, in accordance with Airbus Service
Bulletin A300-53-6179, dated December 12, 2014; or Airbus Service
Bulletin A310-53-2139, dated December 12, 2014; as applicable.
Repeat the HFEC inspection thereafter at intervals not to exceed
4,600 flight cycles.
(1) For airplanes identified in paragraph (j)(1) of this AD:
Inspect within 4,600 flight cycles after the most recent HFEC
inspection specified in Airbus AOT A53W005-14.
(2) For airplanes identified in paragraph (j)(2) of this AD:
Inspect within 2,000 flight cycles after January 3, 2017 (the
effective date of AD 2016-20-11).
(3) For airplanes identified in paragraph (j)(3) of this AD:
Inspect before exceeding 13,000 total flight cycles since the
airplane's
[[Page 34894]]
first flight, or within 2,000 flight cycles after January 3, 2017
(the effective date of AD 2016-20-11), whichever occurs later.
(l) Retained Corrective Action, With No Changes
This paragraph restates the requirements of paragraph (l) of AD
2016-20-11, with no changes. If any crack is found during any
inspection required by paragraph (g) or (k) of this AD: Before
further flight, repair using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the EASA; or Airbus's EASA DOA.
(m) Retained Terminating Action for Repetitive Inspections in Paragraph
(g) of This AD, With No Changes
This paragraph restates the terminating action of paragraph
(m)(1) of AD 2016-20-11, with no changes. For any airplane
identified in paragraphs (j)(2) and (j)(3) of this AD,
accomplishment of the initial inspection required by paragraph (k)
of this AD terminates the repetitive inspections required by
paragraph (g) of this AD.
(n) New Cargo Door Reinforcement
At the latest of the applicable times specified in paragraphs
(n)(1), (n)(2), and (n)(3) of this AD: Reinforce the aft cargo door
sill beam area, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A310-53-2141, Revision 01, dated July 2,
2015; or Airbus Service Bulletin A300-53-6181, Revision 01, dated
July 2, 2015; as applicable.
(1) Before exceeding 19,600 flight cycles since first flight of
the airplane.
(2) Within 2,300 flight cycles after the last HFEC or detailed
inspection required by this AD that was accomplished before the
effective date of this AD.
(3) Within 12 months after the effective date of this AD.
(o) New Terminating Action
Modification of an airplane as required by paragraph (n) of this
AD constitutes terminating action for the repetitive inspections
required by paragraphs (g) and (k) of this AD for that airplane.
(p) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(n) of this AD, if those actions were performed before the effective
date of this AD using Airbus Service Bulletin A300-53-6181, dated
June 26, 2015; or Airbus Service Bulletin A310-53-2141, dated June
26, 2015; as applicable.
(q) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to the attention of
the person identified in paragraph (r)(2) of this AD. Information
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
(i) 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.
(ii) AMOCs approved previously for AD 2016-20-11 are approved as
AMOCs for the corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
(3) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(4) Required for Compliance (RC): Except as required by
paragraph (l) of this AD: If any service information contains
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures or tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified as RC may be deviated from using
accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC, provided
the procedures and tests identified as RC can be done and the
airplane can be put back in an airworthy condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.
(r) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2017-0048, dated March 15, 2017;
corrected April 20, 2017, 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-2017-0708.
(2) For more information about this AD, contact Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. You may view this
service information at the FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com;
Internet https://www.airbus.com. For information on the availability
of this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on July 14, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-15553 Filed 7-26-17; 8:45 am]
BILLING CODE 4910-13-P