Airworthiness Directives; Airbus Airplanes, 56865-56869 [2017-25763]
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Federal Register / Vol. 82, No. 230 / Friday, December 1, 2017 / Rules and Regulations
(3) The following service information was
approved for IBR on January 5, 2018.
(i) Airbus Service Bulletin A320–27–1206,
Revision 02, dated November 2, 2015.
(ii) Reserved.
(4) The following service information was
approved for IBR on March 26, 2014 (79 FR
9398, February 19, 2014).
(i) Airbus Service Bulletin A320–27–1206,
Revision 01, dated October 10, 2011.
(ii) Reserved.
(5) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(6) 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.
(7) 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.
(o) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0113, dated June 15, 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–2017–0476.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW.,
Renton, Washington 98057–3356; telephone
425–227–1405; fax 425–227–1149.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (p)(5) and (p)(6) of this AD.
jstallworth on DSKBBY8HB2PROD with RULES
Section, Transport Standards Branch, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the International Section, send it
to the attention of the person identified in
paragraph (o)(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
2014–08–01 are approved as AMOCs for the
corresponding provisions of paragraphs (g)
and (h) 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 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.
(3) Required for Compliance (RC): 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.
[Docket No. FAA–2017–0708; Product
Identifier 2017–NM–035–AD; Amendment
39–19113; AD 2017–24–09]
(p) 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.
VerDate Sep<11>2014
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Issued in Renton, Washington, on
November 16, 2017.
Chris Spangenberg,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2017–25557 Filed 11–30–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2016–20–
11, which applied to 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
required 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
SUMMARY:
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56865
beam, lock fitting, and torsion box plate,
and repair if necessary. This new AD
retains the inspections for cracking, and
repair if necessary; and requires
reinforcement of the aft cargo door sill
beam area. This AD was prompted by
the development of a reinforcement
modification of the aft cargo door sill
beam area, which constitutes
terminating action for the repetitive
inspections. We are issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective January 5,
2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 2, 2014 (79 FR 34403, June 17,
2014).
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of January 3, 2017 (81 FR
85837, November 29, 2016).
ADDRESSES: For service information
identified in this final rule, 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 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–
0708.
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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
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Federal Register / Vol. 82, No. 230 / Friday, December 1, 2017 / Rules and Regulations
telephone 425–227–2125; fax 425–227–
1149.
SUPPLEMENTARY INFORMATION:
jstallworth on DSKBBY8HB2PROD with RULES
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2016–20–11,
Amendment 39–18677 (81 FR 85837,
November 29, 2016) (‘‘AD 2016–20–
11’’). AD 2016–20–11 applied to certain
Airbus Model A300–600 series
airplanes; and Airbus Model A310
series airplanes. The NPRM published
in the Federal Register on July 27, 2017
(82 FR 34891). The NPRM was
prompted by a determination 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. The NPRM proposed to
continue to require 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. The NPRM also
proposed to require reinforcement of the
aft cargo door sill beam area. 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.
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.
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,
Amendment 39–17867, (79 FR 34403, June
17, 2014)] to require repetitive ultrasonic
inspections (US) or detailed inspections
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(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 [which
corresponded to FAA AD 2016–20–11],
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 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.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request To Make the Mandatory
Terminating Modification Optional
FedEx requested that the terminating
modification in paragraph (n) of the
proposed AD be made an optional
action. FedEx stated that they have
inspected their airplanes as required by
AD 2016–20–11 and have not found any
cracks during HFEC inspections. FedEx
noted that they have inspected airplanes
having accumulated anywhere from
12,000 total flight cycles to 40,000 total
flight cycles. FedEx suggested that the
modification would be necessary on less
than 1 percent of inspected airplanes
over the next 10 years. FedEx claimed
that the modification is an unproven
change that has not been subjected to
full scale fatigue testing. For these
reasons, FedEx argued that inspections
alone will maintain safe airworthiness
for the affected airplanes.
We disagree with the commenter’s
request. EASA, as the State of Design
Authority for Airbus products, has
determined an unsafe conditions exists
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after conducting a risk analysis taking
into consideration in-service data for the
worldwide fleet. We agree with EASA’s
risk assessment and their decision to
mitigate the risk by mandating the
modification in this AD. FedEx has not
provided sufficient data to support their
request to allow inspections in lieu of
the modification. We have not changed
this AD in this regard.
Request To Update the Costs for the
Modification
FedEx requested that we update the
labor costs for the modification in the
proposed AD. FedEx stated that their
labor costs for the modification will be
an additional $10,000 per airplane.
FedEx further noted that the
modification would extend their service
checks, resulting in additional out-ofservice time for their airplanes and
additional expenses.
We partially agree with the
commenter’s request. The number of
work-hours to complete the
modification depends on the airplane’s
configuration. In the NPRM, we used
the 40 work-hours estimate for the
configuration that requires less time to
modify. We have updated this final rule
to reflect work-hour costs of up to 68
hours (the estimated work-hours for the
other configuration) for the required
modification.
Regarding the additional costs related
to extended service checks, we do not
consider it appropriate to attribute the
costs associated with aircraft
‘‘downtime’’ to the AD. Normally,
compliance with the AD will not
necessitate any additional downtime
beyond that of a regularly scheduled
maintenance hold. Even if additional
downtime is necessary for some
airplanes in some cases, we do not have
sufficient information to evaluate the
number of airplanes that may be
affected or the amount of additional
downtime that may be required.
Therefore, we are unable to provide an
estimate for these variable costs. We
have made no further change to this
final rule regarding this issue.
Conclusion
We reviewed the available data,
including the comments received, and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
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Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A300–53–6181, Revision 01, dated July
2, 2015; and Service Bulletin A310–53–
2141, Revision 01, dated July 2, 2015.
This service information describes
procedures for reinforcing the aft cargo
door sill beam area. These documents
are distinct since they apply to different
airplane models.
Airbus has also issued Service
Bulletin A300–53–6179, dated
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.
December 12, 2014; and Service Bulletin
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
documents are distinct since they apply
to different airplane models.
Airbus has also issued Alert Operators
Transmission AOT A53W005–14,
Revision 01, dated April 29, 2014,
which describes procedures for doing an
ultrasonic inspection or detailed
Costs of Compliance
We estimate that this AD affects 75
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Inspection (retained action from AD
2016-20-11).
Modification (new action) .......................
12 work-hours × $85 per hour = $1,020
per inspection cycle.
Up to 68 work-hours × $85 per hour =
$5,780.
1 work hour × $85 per hour = $85 per
inspection cycle.
Reporting (retained action from AD
2016-20-11).
We have received no definitive data
that will enable us to provide cost
estimates for the on-condition actions
specified in this 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.
jstallworth on DSKBBY8HB2PROD with RULES
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.
VerDate Sep<11>2014
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Cost per product
N/A
$96,890
$0
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes to the Director of the System
Oversight Division.
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$76,500 per inspection cycle.
Up to $7,700,250.
$85 per inspection
cycle.
$6,375 per inspection cycle.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
Frm 00009
$1,020 per inspection cycle.
Up to $102,670 ......
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.
Regulatory Findings
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Cost on U.S.
operators
Parts cost
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§ 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:
■
2017–24–09 Airbus: Amendment 39–19113;
Docket No. FAA–2017–0708; Product
Identifier 2017–NM–035–AD.
(a) Effective Date
This AD is effective January 5, 2018.
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(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.
jstallworth on DSKBBY8HB2PROD with RULES
(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 Airbus 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.
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(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 Section, Transport Standards
Branch, 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
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Sfmt 4700
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
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 Section, Transport Standards
Branch, FAA; or 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 A300–53–6181, Revision 01,
dated July 2, 2015; or Airbus Service Bulletin
A310–53–2141, 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 the modified airplane only.
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jstallworth on DSKBBY8HB2PROD with RULES
(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.
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.
www.archives.gov/federal-register/cfr/ibrlocations.html.
(q) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the International Section, send it
to the attention of the person identified in
paragraph (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 Section, Transport
Standards Branch, FAA; or EASA; or
Airbus’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized 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 1 hour 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
(r) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
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 Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; telephone 425–
227–2125; 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 (s)(5) and (s)(6) of this AD.
[FR Doc. 2017–25763 Filed 11–30–17; 8:45 am]
VerDate Sep<11>2014
14:57 Nov 30, 2017
Jkt 244001
(s) 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 July 2, 2014 (79 FR
34403, June 17, 2014).
(i) Airbus Alert Operators Transmission
A53W005–14, dated April 22, 2014.
(ii) Reserved.
(4) The following service information was
approved for IBR on January 3, 2017, (81 FR
85837, November 29, 2016).
(i) Airbus Alert Operators Transmission
A53W005–14, Revision 01, dated April 29,
2014.
(ii) Airbus Service Bulletin A300–53–6179,
dated December 12, 2014.
(iii) Airbus Service Bulletin A300–53–
6181, Revision 01, dated July 2, 2015.
(iv) Airbus Service Bulletin A310–53–
2139, dated December 12, 2014.
(v) Airbus Service Bulletin A310–53–2141,
Revision 01, dated July 2, 2015.
(5) 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.
(6) 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.
(7) 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://
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
Issued in Renton, Washington, on
November 22, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
BILLING CODE 4910–13–P
DEPARTMENT OF LABOR
Employment and Training
Administration
20 CFR Part 641
[Docket No. ETA–2017–0005]
RIN 1205–AB79
Senior Community Service
Employment Program; Performance
Accountability
Employment and Training
Administration, Labor.
ACTION: Interim final rule; request for
comments.
AGENCY:
The Employment and
Training Administration (ETA) of the
Department of Labor (Department) is
issuing this Interim Final Rule (IFR)
revising performance accountability
measures for the Senior Community
Service Employment Program (SCSEP).
Revised measures are necessary because
the Older Americans Act
Reauthorization Act of 2016 (OAA)
amended the measures of performance
for the SCSEP program in large part to
align them with the performance
measures mandated for programs under
the Workforce Innovation and
Opportunity Act (WIOA). This IFR
revises the Performance Accountability
subpart of the SCSEP regulations to
reflect changes necessitated by the
passage of the 2016 OAA. In addition,
this rule makes minor, non-substantive
amendments to other subparts of the
SCSEP regulations to reflect the OAA
amendments that aligned the SCSEP
program statutory language with WIOA,
such as updating outdated terminology
and outdated references to the
Workforce Investment Act of 1998
(WIA), which WIOA superseded. This
IFR solicits public comment on this IFR,
which the Department will consider
when it issues a Final Rule.
DATES: Effective date: This IFR is
effective January 2, 2018.
Compliance date: Performance
information under the measures
implemented in this IFR are required to
be reported beginning July 1, 2018.
SUMMARY:
E:\FR\FM\01DER1.SGM
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]]>Agencies
[Federal Register Volume 82, Number 230 (Friday, December 1, 2017)]
[Rules and Regulations]
[Pages 56865-56869]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-25763]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0708; Product Identifier 2017-NM-035-AD; Amendment
39-19113; AD 2017-24-09]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2016-20-11,
which applied to 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 required 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.
This new AD retains the inspections for cracking, and repair if
necessary; and requires reinforcement of the aft cargo door sill beam
area. This AD was prompted by the development of a reinforcement
modification of the aft cargo door sill beam area, which constitutes
terminating action for the repetitive inspections. We are issuing this
AD to address the unsafe condition on these products.
DATES: This AD is effective January 5, 2018.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 2, 2014
(79 FR 34403, June 17, 2014).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of January
3, 2017 (81 FR 85837, November 29, 2016).
ADDRESSES: For service information identified in this final rule,
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 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-
0708.
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 AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 1601 Lind
Avenue SW., Renton, WA 98057-3356;
[[Page 56866]]
telephone 425-227-2125; fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2016-20-11, Amendment 39-18677 (81 FR 85837,
November 29, 2016) (``AD 2016-20-11''). AD 2016-20-11 applied to
certain Airbus Model A300-600 series airplanes; and Airbus Model A310
series airplanes. The NPRM published in the Federal Register on July
27, 2017 (82 FR 34891). The NPRM was prompted by a determination 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. The NPRM proposed to continue to require
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. The NPRM also proposed to require reinforcement of the
aft cargo door sill beam area. 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.
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.
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, Amendment 39-17867, (79 FR
34403, June 17, 2014)] 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 [which corresponded to FAA
AD 2016-20-11], 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 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.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Request To Make the Mandatory Terminating Modification Optional
FedEx requested that the terminating modification in paragraph (n)
of the proposed AD be made an optional action. FedEx stated that they
have inspected their airplanes as required by AD 2016-20-11 and have
not found any cracks during HFEC inspections. FedEx noted that they
have inspected airplanes having accumulated anywhere from 12,000 total
flight cycles to 40,000 total flight cycles. FedEx suggested that the
modification would be necessary on less than 1 percent of inspected
airplanes over the next 10 years. FedEx claimed that the modification
is an unproven change that has not been subjected to full scale fatigue
testing. For these reasons, FedEx argued that inspections alone will
maintain safe airworthiness for the affected airplanes.
We disagree with the commenter's request. EASA, as the State of
Design Authority for Airbus products, has determined an unsafe
conditions exists after conducting a risk analysis taking into
consideration in-service data for the worldwide fleet. We agree with
EASA's risk assessment and their decision to mitigate the risk by
mandating the modification in this AD. FedEx has not provided
sufficient data to support their request to allow inspections in lieu
of the modification. We have not changed this AD in this regard.
Request To Update the Costs for the Modification
FedEx requested that we update the labor costs for the modification
in the proposed AD. FedEx stated that their labor costs for the
modification will be an additional $10,000 per airplane. FedEx further
noted that the modification would extend their service checks,
resulting in additional out-of-service time for their airplanes and
additional expenses.
We partially agree with the commenter's request. The number of
work-hours to complete the modification depends on the airplane's
configuration. In the NPRM, we used the 40 work-hours estimate for the
configuration that requires less time to modify. We have updated this
final rule to reflect work-hour costs of up to 68 hours (the estimated
work-hours for the other configuration) for the required modification.
Regarding the additional costs related to extended service checks,
we do not consider it appropriate to attribute the costs associated
with aircraft ``downtime'' to the AD. Normally, compliance with the AD
will not necessitate any additional downtime beyond that of a regularly
scheduled maintenance hold. Even if additional downtime is necessary
for some airplanes in some cases, we do not have sufficient information
to evaluate the number of airplanes that may be affected or the amount
of additional downtime that may be required. Therefore, we are unable
to provide an estimate for these variable costs. We have made no
further change to this final rule regarding this issue.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
this AD as proposed except for minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
[[Page 56867]]
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A300-53-6181, Revision 01, dated
July 2, 2015; and Service Bulletin A310-53-2141, Revision 01, dated
July 2, 2015. This service information describes procedures for
reinforcing the aft cargo door sill beam area. These documents are
distinct since they apply to different airplane models.
Airbus has also issued Service Bulletin A300-53-6179, dated
December 12, 2014; and Service Bulletin 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 documents are distinct since they apply to different
airplane models.
Airbus has also issued Alert Operators Transmission 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.
Costs of Compliance
We estimate that this AD affects 75 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection (retained action 12 work-hours x $85 per N/A $1,020 per $76,500 per
from AD 2016[dash]20[dash]11). hour = $1,020 per inspection cycle. inspection cycle.
inspection cycle.
Modification (new action)...... Up to 68 work-hours x $96,890 Up to $102,670.... Up to $7,700,250.
$85 per hour = $5,780.
Reporting (retained action from 1 work hour x $85 per $0 $85 per inspection $6,375 per
AD 2016[dash]20[dash]11). hour = $85 per cycle. inspection cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that will enable us to provide
cost estimates for the on-condition actions specified in this 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.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes to
the Director of the System Oversight Division.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2016-20-11, Amendment 39-18677 (81 FR 85837, November 29, 2016), and
adding the following new AD:
2017-24-09 Airbus: Amendment 39-19113; Docket No. FAA-2017-0708;
Product Identifier 2017-NM-035-AD.
(a) Effective Date
This AD is effective January 5, 2018.
[[Page 56868]]
(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 Airbus 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
Section, Transport Standards Branch, 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 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 Section, Transport Standards Branch, FAA; or 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 A300-53-6181, Revision 01, dated July 2,
2015; or Airbus Service Bulletin A310-53-2141, 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 the modified
airplane only.
[[Page 56869]]
(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 Section, Transport Standards Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Section, send it to the attention of
the person identified in paragraph (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 Section, Transport Standards
Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA,
the approval must include the DOA-authorized signature.
(3) 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 1
hour 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 AD 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 Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone
425-227-2125; 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 (s)(5) and (s)(6) of this AD.
(s) 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
July 2, 2014 (79 FR 34403, June 17, 2014).
(i) Airbus Alert Operators Transmission A53W005-14, dated April
22, 2014.
(ii) Reserved.
(4) The following service information was approved for IBR on
January 3, 2017, (81 FR 85837, November 29, 2016).
(i) Airbus Alert Operators Transmission A53W005-14, Revision 01,
dated April 29, 2014.
(ii) Airbus Service Bulletin A300-53-6179, dated December 12,
2014.
(iii) Airbus Service Bulletin A300-53-6181, Revision 01, dated
July 2, 2015.
(iv) Airbus Service Bulletin A310-53-2139, dated December 12,
2014.
(v) Airbus Service Bulletin A310-53-2141, Revision 01, dated
July 2, 2015.
(5) 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.
(6) 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.
(7) 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 November 22, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-25763 Filed 11-30-17; 8:45 am]
BILLING CODE 4910-13-P
