Airworthiness Directives; Airbus Airplanes, 43158-43160 [2017-19042]
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43158
Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0560; Product
Identifier 2016–NM–172–AD; Amendment
39–19028; AD 2017–18–19]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A310–203, –204, –221,
–222, –304, –322, –324, and –325
airplanes. This AD was prompted by
reports of cracking in the drainage holes
on the lower skin panel in the center
wing box between frames (FR) 42 and
FR46. This AD requires repetitive
rotating probe inspections for cracking
of the trellis boom drainage holes, the
holes in the stringers bottom, and the
holes of the inner pump, and corrective
actions if necessary. We are issuing this
AD to address the unsafe condition on
these products.
DATES: This AD is effective October 19,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of October 19, 2017.
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.airwortheas@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–
0560.
SUMMARY:
rmajette on DSKBCKNHB2PROD with RULES
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–
0560; 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
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15:11 Sep 13, 2017
Jkt 241001
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street 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;
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 by adding an AD that would
apply to all Airbus Model A310–203,
–204, –221, –222, –304, –322, –324, and
–325 airplanes. The NPRM published in
the Federal Register on June 20, 2017
(82 FR 28030) (‘‘the NPRM’’). The
NPRM was prompted by reports of
cracking in the drainage holes on the
lower skin panel in the center wing box
between frames FR42 and FR46. The
NPRM proposed to require repetitive
rotating probe inspections for cracking
of the trellis boom drainage holes, the
holes in the stringers bottom, and the
holes of the inner pump, and corrective
actions if necessary. We are issuing this
AD to detect and correct cracking of
trellis boom drainage holes, the holes in
the stringers bottom, and the holes of
the inner pump, which could result in
reduced structural integrity of the
wings.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2016–0196, dated September
30, 2016 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A310–203, –204, –221, –222,
–304, –322, –324, and –325 airplanes.
The MCAI states:
´ ´
DGAC [Direction Generale de l’Aviation
Civile] France issued AD F–1992–106–132R7
to require certain inspections and
modifications which addressed JAR/FAR
[Joint Aviation Requirements/Federal
Aviation Regulations] 25–571 requirements,
related to damage-tolerance and fatigue
evaluation of structure. Following the
Extended Design Service Goal activities as
part of the Structure Task Group for the
Airbus A310 program, EASA published AD
2007–0053, which replaced DGAC France AD
F–1992–106–132R7.
PO 00000
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After EASA issued AD 2007–0053R1, the
thresholds and the intervals of Airbus
Service Bulletins (SB) A310–57–2050 and
A310–57–2064 were updated, prompting
EASA to issue AD 2009–0057 [which
corresponds to FAA AD 2011–10–06,
Amendment 39–16687 (76 FR 27227, May 11,
2011)] and [EASA] AD 2007–0053 was
revised (R2) accordingly. EASA AD 2009–
0057 also required the accomplishment of the
actions specified in Airbus SB A310–57–
2048 at Revision 01.
After EASA issued AD 2009–0057, in the
frame of the Widespread Fatigue Damage
campaign, new analysis has indicated the
need for additional work included in
Revision 03 of Airbus SB A310–57–2050.
For the reason described above, this new
[EASA] AD retains the requirements of EASA
AD 2009–0057, which is superseded, and
requires inspection and corrective actions as
specified in Airbus SB A310–57–2050
Revision 04.
Required actions include a repetitive
rotating probe inspection for cracking of
certain holes in the stringers bottom,
inner pumps, and the trellis boom; and
corrective actions, i.e., repair of holes
where cracks are discovered.
The compliance times vary depending
on airplane configuration. The earliest
initial inspection compliance time is
11,400 total flight cycles or 57,300 total
flight hours, whichever occurs first. The
latest initial compliance time is 38,700
total flight cycles or 77,500 total flight
hours, whichever occurs first. The
shortest repetitive interval is 6,200 flight
cycles or 31,200 flight hours, whichever
occurs first.
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–
0560.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the relevant data 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.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A310–57–2050, Revision 04, dated
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Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations
March 13, 2015. This service
information describes procedures for
repetitive rotating probe inspections for
cracking of the trellis boom drainage
holes, the holes in the stringers bottom,
and the holes of the inner pump, and
corrective actions. 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.
43159
Costs of Compliance
We estimate that this AD affects 8
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Inspection ........................................................
84 work-hours × $85 per hour = $7,140 ........
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
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.
rmajette on DSKBCKNHB2PROD with RULES
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.
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15:11 Sep 13, 2017
Jkt 241001
Parts cost
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
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 adding
the following new airworthiness
directive (AD):
■
2017–18–19 Airbus: Amendment 39–19028;
Docket No. FAA–2017–0560; Product
Identifier 2016–NM–172–AD.
(a) Effective Date
This AD is effective October 19, 2017.
(b) Affected ADs
This AD affects AD 2011–10–06,
Amendment 39–16687 (76 FR 27227, May 11,
2011) (‘‘AD 2011–10–06’’).
(c) Applicability
This AD applies to Airbus Model A310–
203, –204, –221, –222, –304, –322, –324, and
–325 airplanes, certificated in any category,
all serial numbers.
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$5,890
Cost per
product
$13,030
Cost on U.S.
operators
$104,240
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by reports of
cracking in the drainage holes on the lower
skin panel in the center wing box between
frames (FR) 42 and FR46. We are issuing this
AD to detect and correct cracking of trellis
boom drainage holes, the holes in the
stringers bottom, and the holes of the inner
pump, which could result in reduced
structural integrity of the wings.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Rotating Probe Inspections and
Corrective Actions
Except as provided by paragraph (h)(1) of
this AD, before exceeding the applicable
threshold or grace period, whichever occurs
later, as defined in paragraph 1.E.,
‘‘Compliance,’’ of Airbus Service Bulletin
A310–57–2050, Revision 04, dated March 13,
2015, accomplish the rotating probe
inspection for cracking of the trellis boom
drainage holes, the holes in the stringers
bottom, and the holes of the inner pump, as
applicable, and do all applicable corrective
actions, as specified in, and in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A310–57–2050,
Revision 04, dated March 13, 2015, except as
required by paragraph (h)(2) of this AD. Do
all applicable corrective actions before
further flight. Repeat the inspection
thereafter at intervals not to exceed those
defined in paragraph 1.E., ‘‘Compliance,’’ of
Airbus Service Bulletin A310–57–2050,
Revision 04, dated March 13, 2015.
(h) Exceptions to Service Information
(1) Where Airbus Service Bulletin A310–
57–2050, Revision 04, dated March 13, 2015,
specifies a grace period ‘‘after receipt of the
Service Bulletin without exceeding previous
Service Bulletin revision values,’’ this AD
requires compliance within the specified
grace period after the effective date of this
AD.
(2) Where Airbus Service Bulletin A310–
57–2050, Revision 04, dated March 13, 2015,
specifies to contact Airbus for appropriate
action, and specifies that action as ‘‘RC’’
(Required for Compliance): Before further
flight, accomplish corrective actions in
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43160
Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations
accordance with the procedures specified in
paragraph (l)(2) of this AD.
(i) No Terminating Action for Inspections
Accomplishing corrective actions on an
airplane as required by paragraph (g) or (h)(2)
of this AD does not constitute terminating
action for the repetitive actions required by
paragraph (g) of this AD.
(j) Terminating Action
Accomplishment of the initial inspection
required by paragraph (g) of this AD
constitutes terminating action for the actions
required by paragraph (h) of AD 2011–10–06.
(k) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (g) of this AD, if those
actions were performed before the effective
date of this AD using the service information
specified in Airbus Service Bulletin A310–
57–2050, Revision 03, dated December 19,
2014.
rmajette on DSKBCKNHB2PROD with RULES
(l) 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 (m)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: 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 DOAauthorized signature.
(3) Required for Compliance (RC): Except
as required by paragraph (h)(2) 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.
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15:11 Sep 13, 2017
Jkt 241001
(m) Related Information
DEPARTMENT OF TRANSPORTATION
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2016–0196, dated
September 30, 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–2017–0560.
(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 (n)(3) and (n)(4) of this AD.
(n) 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.
(i) Airbus Service Bulletin A310–57–2050,
Revision 04, dated March 13, 2015.
(ii) Reserved.
(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.
(4) 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on August
31, 2017.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2017–19042 Filed 9–13–17; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–0451; Product
Identifier 2013–NM–253–AD; Amendment
39–19026; AD 2017–18–17]
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) 2004–23–
20, which applied to certain Airbus
Model A300, A300 B4–600, and A300
B4–600R series airplanes; and Model
A300 F4–605R and A300 C4–605R
Variant F airplanes. AD 2004–23–20
required, for certain airplanes, repetitive
inspections for cracking around certain
attachment holes, installation of new
fasteners for certain airplanes, and
follow-on corrective actions if
necessary. AD 2004–23–20 also required
modifying certain fuselage frames,
which terminated certain repetitive
inspections. This new AD reduces
certain compliance times, expands the
applicability, and requires an additional
repair on certain modified airplanes.
This AD was prompted by a report
indicating that the material used to
manufacture the upper frame feet was
changed and negatively affected the
fatigue life of the frame feet. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective October 19,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 19, 2017.
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–2016–
0451.
SUMMARY:
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]]>Agencies
[Federal Register Volume 82, Number 177 (Thursday, September 14, 2017)]
[Rules and Regulations]
[Pages 43158-43160]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-19042]
[[Page 43158]]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0560; Product Identifier 2016-NM-172-AD; Amendment
39-19028; AD 2017-18-19]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325
airplanes. This AD was prompted by reports of cracking in the drainage
holes on the lower skin panel in the center wing box between frames
(FR) 42 and FR46. This AD requires repetitive rotating probe
inspections for cracking of the trellis boom drainage holes, the holes
in the stringers bottom, and the holes of the inner pump, and
corrective actions if necessary. We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective October 19, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of October 19,
2017.
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-2017-0560.
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-
0560; 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 street 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; 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 by adding an AD that would apply to all Airbus Model A310-203,
-204, -221, -222, -304, -322, -324, and -325 airplanes. The NPRM
published in the Federal Register on June 20, 2017 (82 FR 28030) (``the
NPRM''). The NPRM was prompted by reports of cracking in the drainage
holes on the lower skin panel in the center wing box between frames
FR42 and FR46. The NPRM proposed to require repetitive rotating probe
inspections for cracking of the trellis boom drainage holes, the holes
in the stringers bottom, and the holes of the inner pump, and
corrective actions if necessary. We are issuing this AD to detect and
correct cracking of trellis boom drainage holes, the holes in the
stringers bottom, and the holes of the inner pump, which could result
in reduced structural integrity of the wings.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2016-0196, dated September 30, 2016 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes. The
MCAI states:
DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France issued AD F-1992-106-132R7 to require certain inspections and
modifications which addressed JAR/FAR [Joint Aviation Requirements/
Federal Aviation Regulations] 25-571 requirements, related to
damage-tolerance and fatigue evaluation of structure. Following the
Extended Design Service Goal activities as part of the Structure
Task Group for the Airbus A310 program, EASA published AD 2007-0053,
which replaced DGAC France AD F-1992-106-132R7.
After EASA issued AD 2007-0053R1, the thresholds and the
intervals of Airbus Service Bulletins (SB) A310-57-2050 and A310-57-
2064 were updated, prompting EASA to issue AD 2009-0057 [which
corresponds to FAA AD 2011-10-06, Amendment 39-16687 (76 FR 27227,
May 11, 2011)] and [EASA] AD 2007-0053 was revised (R2) accordingly.
EASA AD 2009-0057 also required the accomplishment of the actions
specified in Airbus SB A310-57-2048 at Revision 01.
After EASA issued AD 2009-0057, in the frame of the Widespread
Fatigue Damage campaign, new analysis has indicated the need for
additional work included in Revision 03 of Airbus SB A310-57-2050.
For the reason described above, this new [EASA] AD retains the
requirements of EASA AD 2009-0057, which is superseded, and requires
inspection and corrective actions as specified in Airbus SB A310-57-
2050 Revision 04.
Required actions include a repetitive rotating probe inspection for
cracking of certain holes in the stringers bottom, inner pumps, and the
trellis boom; and corrective actions, i.e., repair of holes where
cracks are discovered.
The compliance times vary depending on airplane configuration. The
earliest initial inspection compliance time is 11,400 total flight
cycles or 57,300 total flight hours, whichever occurs first. The latest
initial compliance time is 38,700 total flight cycles or 77,500 total
flight hours, whichever occurs first. The shortest repetitive interval
is 6,200 flight cycles or 31,200 flight hours, whichever occurs first.
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-
0560.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the relevant data 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.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A310-57-2050, Revision 04, dated
[[Page 43159]]
March 13, 2015. This service information describes procedures for
repetitive rotating probe inspections for cracking of the trellis boom
drainage holes, the holes in the stringers bottom, and the holes of the
inner pump, and corrective actions. 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 8 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspection............................ 84 work-hours x $85 per $5,890 $13,030 $104,240
hour = $7,140.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
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 adding the following new airworthiness
directive (AD):
2017-18-19 Airbus: Amendment 39-19028; Docket No. FAA-2017-0560;
Product Identifier 2016-NM-172-AD.
(a) Effective Date
This AD is effective October 19, 2017.
(b) Affected ADs
This AD affects AD 2011-10-06, Amendment 39-16687 (76 FR 27227,
May 11, 2011) (``AD 2011-10-06'').
(c) Applicability
This AD applies to Airbus Model A310-203, -204, -221, -222, -
304, -322, -324, and -325 airplanes, certificated in any category,
all serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by reports of cracking in the drainage
holes on the lower skin panel in the center wing box between frames
(FR) 42 and FR46. We are issuing this AD to detect and correct
cracking of trellis boom drainage holes, the holes in the stringers
bottom, and the holes of the inner pump, which could result in
reduced structural integrity of the wings.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Rotating Probe Inspections and Corrective Actions
Except as provided by paragraph (h)(1) of this AD, before
exceeding the applicable threshold or grace period, whichever occurs
later, as defined in paragraph 1.E., ``Compliance,'' of Airbus
Service Bulletin A310-57-2050, Revision 04, dated March 13, 2015,
accomplish the rotating probe inspection for cracking of the trellis
boom drainage holes, the holes in the stringers bottom, and the
holes of the inner pump, as applicable, and do all applicable
corrective actions, as specified in, and in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A310-57-2050,
Revision 04, dated March 13, 2015, except as required by paragraph
(h)(2) of this AD. Do all applicable corrective actions before
further flight. Repeat the inspection thereafter at intervals not to
exceed those defined in paragraph 1.E., ``Compliance,'' of Airbus
Service Bulletin A310-57-2050, Revision 04, dated March 13, 2015.
(h) Exceptions to Service Information
(1) Where Airbus Service Bulletin A310-57-2050, Revision 04,
dated March 13, 2015, specifies a grace period ``after receipt of
the Service Bulletin without exceeding previous Service Bulletin
revision values,'' this AD requires compliance within the specified
grace period after the effective date of this AD.
(2) Where Airbus Service Bulletin A310-57-2050, Revision 04,
dated March 13, 2015, specifies to contact Airbus for appropriate
action, and specifies that action as ``RC'' (Required for
Compliance): Before further flight, accomplish corrective actions in
[[Page 43160]]
accordance with the procedures specified in paragraph (l)(2) of this
AD.
(i) No Terminating Action for Inspections
Accomplishing corrective actions on an airplane as required by
paragraph (g) or (h)(2) of this AD does not constitute terminating
action for the repetitive actions required by paragraph (g) of this
AD.
(j) Terminating Action
Accomplishment of the initial inspection required by paragraph
(g) of this AD constitutes terminating action for the actions
required by paragraph (h) of AD 2011-10-06.
(k) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(g) of this AD, if those actions were performed before the effective
date of this AD using the service information specified in Airbus
Service Bulletin A310-57-2050, Revision 03, dated December 19, 2014.
(l) 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 (m)(2) of this AD. Information
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office.
(2) Contacting the Manufacturer: 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): Except as required by
paragraph (h)(2) 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.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2016-0196, dated September 30,
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-2017-0560.
(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 (n)(3) and (n)(4) of this AD.
(n) 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.
(i) Airbus Service Bulletin A310-57-2050, Revision 04, dated
March 13, 2015.
(ii) Reserved.
(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.
(4) 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.
(5) 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 August 31, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2017-19042 Filed 9-13-17; 8:45 am]
BILLING CODE 4910-13-P
