Airworthiness Directives; Airbus Airplanes, 57340-57343 [2017-26037]
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Federal Register / Vol. 82, No. 232 / Tuesday, December 5, 2017 / Rules and Regulations
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–
0709.
(1) Applicability of the annual
limitation. When grants are no longer
available in a fiscal year, further
decisions to grant such relief must be
reserved until such time as a grant
becomes available under the annual
limitation in a subsequent fiscal year.
*
*
*
*
*
Examining the AD Docket
Dated: November 21, 2017.
Jefferson B. Sessions III,
Attorney General.
[FR Doc. 2017–26104 Filed 12–4–17; 8:45 am]
BILLING CODE 4410–30–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0709; Product
Identifier 2016–NM–200–AD; Amendment
39–19115; AD 2017–25–01]
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 certain
Airbus Model A318 series airplanes;
Model A319 series airplanes; and Model
A320–211, –212, –214, –216, –231,
–232, and –233 airplanes. This AD was
prompted by a report indicating that the
lower rib foot angle of the center wing
box did not match with the bottom skin
panel inner surface. This AD requires
repetitive inspections for cracking of the
external bottom skin in certain areas on
the left and right wings, and corrective
actions if necessary. We are issuing this
AD to address the unsafe condition on
these products.
DATES: This AD is effective January 9,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 9, 2018.
ADDRESSES: For service information
identified in this final rule, 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. You
may view this referenced service
information at the FAA, Transport
Standards Branch, 1601 Lind Avenue
SW., Renton, WA. For information on
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SUMMARY:
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You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0709; 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:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; 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 certain Airbus Model A318 and
A319 series airplanes; and Model A320–
211, –212, –214, –216, –231, –232, and
–233 airplanes. The NPRM published in
the Federal Register on July 25, 2017
(82 FR 34453) (‘‘the NPRM’’). The
NPRM was prompted by a report
indicating that the lower rib foot angle
of the center wing box did not match
with the bottom skin panel inner
surface. The NPRM proposed to require
repetitive inspections for cracking of the
external bottom skin in certain areas on
the left and right wings, and corrective
actions if necessary, and provided an
optional terminating modification for
the repetitive inspections. We are
issuing this AD to detect and correct
cracking of the external bottom skin in
the area of the rib 2 attachment of the
wings, 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 AD 2016–0222,
dated November 7, 2016 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
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MCAI’’), to correct an unsafe condition
for certain Airbus Model A318 and
A319 series airplanes; and Model A320–
211, –212, –214, –216, –231, –232, and
–233 airplanes. The MCAI states:
During installation in production of new
wing box ribs on post-mod 39729 aeroplanes,
it was discovered that the centre wing lower
rib foot angle was not matching with the
bottom skin panel inner surface.
This condition, if not detected and
corrected, could induce fatigue cracking of
the skin panel at the rib foot attachment, with
possible detrimental effect on wing structural
integrity.
This condition was initially addressed by
Airbus on the production line through
adaptation mod 152155, then through mod
152200. For affected aeroplanes in service,
Airbus issued Service Bulletin (SB) A320–
57–1205, providing instructions for repetitive
detailed inspections (DET) or special detailed
inspections (SDI), and SB A320–57–1207,
providing modification instructions.
For the reasons described above, this
[EASA] AD requires repetitive inspections
(DET or SDI) of the wing bottom skin lower
surface for crack detection and, depending on
findings, the accomplishment of applicable
corrective action(s). This [EASA] AD also
includes reference to an optional
modification (Airbus SB A320–57–1207),
providing terminating action for the
repetitive inspections required by this
[EASA] AD.
The corrective action for cracking is to
repair using a method approved by the
Manager, International Section,
Transport Standards Branch, FAA;
EASA; or Airbus’s EASA Design
Organization Approval. 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–
0709.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the NPRM and the FAA’s
response.
Request To Include Technical
Adaptations
Delta Airlines asked for another
‘‘Contacting the Manufacturer’’
subparagraph acknowledging Technical
Adaptations from Airbus to be added
under paragraph (j) of the proposed AD,
‘‘Other FAA AD Provisions.’’ Delta
observed that the FAA provision for
contacting the manufacturer in
paragraph (j) of the proposed AD would
provide allowances for corrective
actions without alternative methods of
compliance (AMOCs). Delta noted that
operators often receive Technical
Adaptations that include an EASA
Design Organization Approval (DOA)
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Federal Register / Vol. 82, No. 232 / Tuesday, December 5, 2017 / Rules and Regulations
authorized signature for typographical,
omitted instruction, and technical
errors, and that they should be included
in the proposed AD.
We disagree with the commenter. The
‘‘Contacting the Manufacturer’’
paragraph in ADs only addresses the
requirement to contact the manufacturer
for corrective actions for the identified
unsafe condition and does not cover
deviations from other AD requirements.
This paragraph states, in part, that for
any requirement in an AD to obtain
corrective actions from a manufacturer,
the actions must be accomplished using
a method approved by the FAA; or the
EASA; or Airbus’s EASA DOA. We do
not agree to extend this allowance to
other AD requirements. All deviations
from the service information sections
that are marked ‘‘RC’’ (Required for
Compliance) require AMOC approval
unless otherwise stated in the AD. We
have not changed this AD in this regard.
Conclusion
We reviewed the relevant data,
considered the comment 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.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–57–1205, dated May 26, 2016.
This service information describes
procedures for inspecting the external
bottom skin for cracking in the area of
the rib 2 attachment between stringer 8
57341
and stringer 11 on both wings, and
repairing any cracks.
Airbus has also issued Service
Bulletin A320–57–1207, including
Appendix 01 and Appendix 02, dated
May 26, 2016. This service information
describes procedures for inspecting the
lower rib feet (rib 2) and the bottom skin
upper surface on both wings for
cracking, modifying the wings by
installing shims between the lower rib
foot (rib 2) and the bottom skin upper
surface, and repairing any cracks.
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 10
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS
Action
Labor cost
Inspection ...............
5 work-hours × $85 per hour = $425 per inspection cycle.
Cost per
product
Parts cost
$0
$425 per inspection
cycle.
Cost on U.S.
operators
$4,250 per inspection
cycle.
ESTIMATED COSTS FOR OPTIONAL ACTIONS
Action
Labor cost
Modification ......................................
32 work-hours × $85 per hour = $2,720 ...................................................
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We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
According to the manufacturer, some
of the costs of the optional modification
of this AD may be covered under
warranty, thereby reducing the cost
impact on affected individuals. We do
not control warranty coverage for
affected individuals. As a result, we
have included all available costs in our
cost estimate.
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
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Parts cost
Cost per
product
$5,750
$8,470
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.
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.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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List of Subjects in 14 CFR Part 39
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Federal Register / Vol. 82, No. 232 / Tuesday, December 5, 2017 / Rules and Regulations
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):
■
2017–25–01 Airbus: Amendment 39–19115;
Docket No. FAA–2017–0709; Product
Identifier 2016–NM–200–AD.
(a) Effective Date
This AD is effective January 9, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1), (c)(2), and
(c)(3) of this AD, certificated in any category,
all manufacturer serial numbers on which
Airbus Modification 39729 was embodied in
production, except those airplanes on which
Airbus Modification 152155 or Modification
152200 was embodied in production.
(1) Airbus Model A318–111, –112, –121,
and –122 airplanes.
(2) Airbus Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes.
(3) Airbus Model A320–211, –212, –214,
–216, –231, –232, and –233 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by a report
indicating that the lower rib foot angle of the
center wing box did not match with the
bottom skin panel inner surface.
Misalignment of the lower rib foot angle of
the center wing box with the bottom skin
panel inner surface could induce fatigue
cracking of the skin panel at the rib foot
attachment. We are issuing this AD to detect
and correct cracking of the external bottom
skin in the area of the rib 2 attachment of the
wings, 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) Repetitive Inspections
Before exceeding the applicable
compliance time specified in table 1 to
paragraph (g) of this AD, or within 3 months
after the effective date of this AD, whichever
occurs later: Do a detailed inspection or a
special detailed inspection for cracking of the
external bottom skin in the area of the rib 2
attachment between stringer 8 and stringer 11
of the left and right wings, and do all
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–57–1205,
dated May 26, 2016. Do all applicable
corrective actions before further flight.
Repeat the inspection thereafter at the
applicable intervals, based on the method
used for the most recent inspection, as
specified in table 2 to paragraph (g) of this
AD.
TABLE 1 TO PARAGRAPH (g) OF THIS AD—INITIAL INSPECTION TIMES
Airplane model and configuration
Compliance time—whichever occurs first
since first flight of the airplane
Model A318 series airplanes; Model A319 series airplanes; and Model A320–211, –212, –214,
–216, –231, –232, and –233 airplanes; pre-Airbus Modification 155374; not used as VIP or
Elite.
Model A318 series airplanes; Model A319 series airplanes; and Model A320–211, –212, –214,
–216, –231, –232, and –233 airplanes; post-Airbus Modification 155374; not used as VIP or
Elite.
Model A319 series airplanes; post-Airbus Modifications 28162, 28238, and 28342; used as VIP
or CJ.
Model A318 series airplanes; post-Airbus Modification 39195; used as VIP or Elite ....................
Before the accumulation of 14,500 total flight
cycles or 29,000 total flight hours.
Before the accumulation of 13,600 total flight
cycles or 27,300 total flight hours.
Before the accumulation of 7,400 total flight cycles or 32,000 total flight hours.
Before the accumulation of 14,500 total flight
cycles or 43,500 total flight hours.
TABLE 2 TO PARAGRAPH (g) OF THIS AD—REPETITIVE INSPECTION INTERVALS
Airplane model and configuration
Detailed inspection—
whichever occurs first
Special detailed inspection—
whichever occurs first
Model A318 series airplanes; Model A319 series airplanes; and Model
A320–211, –212, –214, –216, –231, –232, and –233 airplanes; not
used as VIP or Elite.
Model A319 series airplanes; post-Airbus Modifications 28162, 28238
and 28342; used as VIP or CJ.
Model A318 series airplanes; post-Airbus Modification 39195; used as
VIP or Elite.
4,000 flight cycles or 8,000 flight
hours.
5,000 flight cycles or 10,000 flight
hours.
2,000 flight cycles or 8,600 flight
hours.
4,000 flight cycles or 12,000 flight
hours.
2,500 flight cycles or 11,000 flight
hours.
5,000 flight cycles or 15,000 flight
hours.
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Note 1 to paragraph (g) of this AD: Airbus
Modification 155374 defines the minimum
airplane configuration for operation on
Commonwealth of Independent States
runway profiles.
(h) Terminating Action Limitation
Repair of an airplane, as required by
paragraph (g) of this AD, does not constitute
terminating action for the repetitive
inspections required by paragraph (g) of this
AD unless otherwise specified in the
instructions obtained using the procedures
specified in paragraph (j)(2) of this AD.
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Jkt 244001
(i) Optional Terminating Action
Modification of the wings including a
detailed inspection of the lower rib feet (rib
2) and bottom skin upper surface of the
wings for cracking and all applicable
corrective actions, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–57–1207, including
Appendix 01 and Appendix 02, dated May
26, 2016, constitutes terminating action for
the repetitive inspections required by
paragraph (g) of this AD for that airplane. If,
during modification of an airplane as
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specified in this paragraph, accomplishment
of any modification instruction is not
possible due to configuration difficulties,
accomplish the modification using the
procedures specified in paragraph (j)(1) of
this AD.
(j) 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
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Federal Register / Vol. 82, No. 232 / Tuesday, December 5, 2017 / Rules and Regulations
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the manager of the International
Branch, send it to the attention of the person
identified in paragraph (k)(2) of this AD.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: 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): 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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(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0222, dated November 7, 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–2017–0709.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW.,
Renton, WA 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 (l)(3) and (l)(4) of this AD.
(l) 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 A320–57–1205,
dated May 26, 2016.
(ii) Airbus Service Bulletin A320–57–1207,
including Appendix 01 and Appendix 02,
dated May 26, 2016.
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(3) 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.
(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
November 22, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2017–26037 Filed 12–4–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0340; Product
Identifier 2017–NM–002–AD; Amendment
39–19114; AD 2017–24–10]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
PO 00000
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Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC
110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; Internet
https://www.myboeingfleet.com. 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.
It is also available on the Internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2017–
0340.
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–
0340; 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 final rule, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Muoi Vuong, Aerospace Engineer,
Airframe Section, FAA, Los Angeles
ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5205; fax: 562–627–
5210; email: Muoi.Vuong@faa.gov.
SUPPLEMENTARY INFORMATION:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 757–200,
–200PF, and –300 series airplanes. This
AD was prompted by reports of cracking
found at a certain fuselage frame inner
chord. This AD requires repetitive
inspections for any cracking of a certain
fuselage frame inner chord;
identification of the material of a certain
fuselage frame inner chord for certain
airplanes; and applicable corrective
actions. We are issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective January 9,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 9, 2018.
ADDRESSES: For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
SUMMARY:
57343
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 757–200, –200PF, and –300
series airplanes. The NPRM published
in the Federal Register on May 19, 2017
(82 FR 22915). The NPRM was
prompted by reports of cracking found
at a certain fuselage frame inner chord.
The NPRM proposed to require
repetitive inspections for any cracking
of a certain fuselage frame inner chord,
identification of the material of a certain
fuselage frame inner chord for certain
airplanes, and applicable corrective
actions. We are issuing this AD to detect
and correct such cracks, which could
result in the cargo door opening during
flight, and result in rapid
decompression of the airplane and the
inability to sustain loads required for
continued safe flight and landing.
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]]>Agencies
[Federal Register Volume 82, Number 232 (Tuesday, December 5, 2017)]
[Rules and Regulations]
[Pages 57340-57343]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-26037]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0709; Product Identifier 2016-NM-200-AD; Amendment
39-19115; AD 2017-25-01]
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 certain
Airbus Model A318 series airplanes; Model A319 series airplanes; and
Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes. This
AD was prompted by a report indicating that the lower rib foot angle of
the center wing box did not match with the bottom skin panel inner
surface. This AD requires repetitive inspections for cracking of the
external bottom skin in certain areas on the left and right wings, and
corrective actions if necessary. We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective January 9, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 9,
2018.
ADDRESSES: For service information identified in this final rule,
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. 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-
0709.
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-
0709; 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: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 1601 Lind
Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 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 certain Airbus Model A318
and A319 series airplanes; and Model A320-211, -212, -214, -216, -231,
-232, and -233 airplanes. The NPRM published in the Federal Register on
July 25, 2017 (82 FR 34453) (``the NPRM''). The NPRM was prompted by a
report indicating that the lower rib foot angle of the center wing box
did not match with the bottom skin panel inner surface. The NPRM
proposed to require repetitive inspections for cracking of the external
bottom skin in certain areas on the left and right wings, and
corrective actions if necessary, and provided an optional terminating
modification for the repetitive inspections. We are issuing this AD to
detect and correct cracking of the external bottom skin in the area of
the rib 2 attachment of the wings, 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 AD
2016-0222, dated November 7, 2016 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for certain Airbus Model A318 and A319
series airplanes; and Model A320-211, -212, -214, -216, -231, -232, and
-233 airplanes. The MCAI states:
During installation in production of new wing box ribs on post-
mod 39729 aeroplanes, it was discovered that the centre wing lower
rib foot angle was not matching with the bottom skin panel inner
surface.
This condition, if not detected and corrected, could induce
fatigue cracking of the skin panel at the rib foot attachment, with
possible detrimental effect on wing structural integrity.
This condition was initially addressed by Airbus on the
production line through adaptation mod 152155, then through mod
152200. For affected aeroplanes in service, Airbus issued Service
Bulletin (SB) A320-57-1205, providing instructions for repetitive
detailed inspections (DET) or special detailed inspections (SDI),
and SB A320-57-1207, providing modification instructions.
For the reasons described above, this [EASA] AD requires
repetitive inspections (DET or SDI) of the wing bottom skin lower
surface for crack detection and, depending on findings, the
accomplishment of applicable corrective action(s). This [EASA] AD
also includes reference to an optional modification (Airbus SB A320-
57-1207), providing terminating action for the repetitive
inspections required by this [EASA] AD.
The corrective action for cracking is to repair using a method
approved by the Manager, International Section, Transport Standards
Branch, FAA; EASA; or Airbus's EASA Design Organization Approval. 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-
0709.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the NPRM and
the FAA's response.
Request To Include Technical Adaptations
Delta Airlines asked for another ``Contacting the Manufacturer''
subparagraph acknowledging Technical Adaptations from Airbus to be
added under paragraph (j) of the proposed AD, ``Other FAA AD
Provisions.'' Delta observed that the FAA provision for contacting the
manufacturer in paragraph (j) of the proposed AD would provide
allowances for corrective actions without alternative methods of
compliance (AMOCs). Delta noted that operators often receive Technical
Adaptations that include an EASA Design Organization Approval (DOA)
[[Page 57341]]
authorized signature for typographical, omitted instruction, and
technical errors, and that they should be included in the proposed AD.
We disagree with the commenter. The ``Contacting the Manufacturer''
paragraph in ADs only addresses the requirement to contact the
manufacturer for corrective actions for the identified unsafe condition
and does not cover deviations from other AD requirements. This
paragraph states, in part, that for any requirement in an AD to obtain
corrective actions from a manufacturer, the actions must be
accomplished using a method approved by the FAA; or the EASA; or
Airbus's EASA DOA. We do not agree to extend this allowance to other AD
requirements. All deviations from the service information sections that
are marked ``RC'' (Required for Compliance) require AMOC approval
unless otherwise stated in the AD. We have not changed this AD in this
regard.
Conclusion
We reviewed the relevant data, considered the comment 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.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-57-1205, dated May 26,
2016. This service information describes procedures for inspecting the
external bottom skin for cracking in the area of the rib 2 attachment
between stringer 8 and stringer 11 on both wings, and repairing any
cracks.
Airbus has also issued Service Bulletin A320-57-1207, including
Appendix 01 and Appendix 02, dated May 26, 2016. This service
information describes procedures for inspecting the lower rib feet (rib
2) and the bottom skin upper surface on both wings for cracking,
modifying the wings by installing shims between the lower rib foot (rib
2) and the bottom skin upper surface, and repairing any cracks.
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 10 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.................... 5 work-hours x $85 $0 $425 per inspection $4,250 per
per hour = $425 per cycle. inspection cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Modification............................... 32 work-hours x $85 per hour = $5,750 $8,470
$2,720.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD.
According to the manufacturer, some of the costs of the optional
modification of this AD may be covered under warranty, thereby reducing
the cost impact on affected individuals. We do not control warranty
coverage for affected individuals. As a result, we have included all
available costs in our cost estimate.
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.
[[Page 57342]]
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):
2017-25-01 Airbus: Amendment 39-19115; Docket No. FAA-2017-0709;
Product Identifier 2016-NM-200-AD.
(a) Effective Date
This AD is effective January 9, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category,
all manufacturer serial numbers on which Airbus Modification 39729
was embodied in production, except those airplanes on which Airbus
Modification 152155 or Modification 152200 was embodied in
production.
(1) Airbus Model A318-111, -112, -121, and -122 airplanes.
(2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
(3) Airbus Model A320-211, -212, -214, -216, -231, -232, and -
233 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by a report indicating that the lower rib
foot angle of the center wing box did not match with the bottom skin
panel inner surface. Misalignment of the lower rib foot angle of the
center wing box with the bottom skin panel inner surface could
induce fatigue cracking of the skin panel at the rib foot
attachment. We are issuing this AD to detect and correct cracking of
the external bottom skin in the area of the rib 2 attachment of the
wings, 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) Repetitive Inspections
Before exceeding the applicable compliance time specified in
table 1 to paragraph (g) of this AD, or within 3 months after the
effective date of this AD, whichever occurs later: Do a detailed
inspection or a special detailed inspection for cracking of the
external bottom skin in the area of the rib 2 attachment between
stringer 8 and stringer 11 of the left and right wings, and do all
applicable corrective actions, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-57-1205, dated May 26,
2016. Do all applicable corrective actions before further flight.
Repeat the inspection thereafter at the applicable intervals, based
on the method used for the most recent inspection, as specified in
table 2 to paragraph (g) of this AD.
Table 1 to Paragraph (g) of This AD--Initial Inspection Times
------------------------------------------------------------------------
Compliance time--
whichever occurs first
Airplane model and configuration since first flight of the
airplane
------------------------------------------------------------------------
Model A318 series airplanes; Model A319 Before the accumulation
series airplanes; and Model A320-211, -212, - of 14,500 total flight
214, -216, -231, -232, and -233 airplanes; cycles or 29,000 total
pre-Airbus Modification 155374; not used as flight hours.
VIP or Elite.
Model A318 series airplanes; Model A319 Before the accumulation
series airplanes; and Model A320-211, -212, - of 13,600 total flight
214, -216, -231, -232, and -233 airplanes; cycles or 27,300 total
post-Airbus Modification 155374; not used as flight hours.
VIP or Elite.
Model A319 series airplanes; post-Airbus Before the accumulation
Modifications 28162, 28238, and 28342; used of 7,400 total flight
as VIP or CJ. cycles or 32,000 total
flight hours.
Model A318 series airplanes; post-Airbus Before the accumulation
Modification 39195; used as VIP or Elite. of 14,500 total flight
cycles or 43,500 total
flight hours.
------------------------------------------------------------------------
Table 2 to Paragraph (g) of This AD--Repetitive Inspection Intervals
------------------------------------------------------------------------
Detailed Special detailed
inspection-- inspection--
Airplane model and configuration whichever occurs whichever occurs
first first
------------------------------------------------------------------------
Model A318 series airplanes; 4,000 flight 5,000 flight
Model A319 series airplanes; cycles or 8,000 cycles or 10,000
and Model A320-211, -212, -214, flight hours. flight hours.
-216, -231, -232, and -233
airplanes; not used as VIP or
Elite.
Model A319 series airplanes; 2,000 flight 2,500 flight
post-Airbus Modifications cycles or 8,600 cycles or 11,000
28162, 28238 and 28342; used as flight hours. flight hours.
VIP or CJ.
Model A318 series airplanes; 4,000 flight 5,000 flight
post-Airbus Modification 39195; cycles or 12,000 cycles or 15,000
used as VIP or Elite. flight hours. flight hours.
------------------------------------------------------------------------
Note 1 to paragraph (g) of this AD: Airbus Modification 155374
defines the minimum airplane configuration for operation on
Commonwealth of Independent States runway profiles.
(h) Terminating Action Limitation
Repair of an airplane, as required by paragraph (g) of this AD,
does not constitute terminating action for the repetitive
inspections required by paragraph (g) of this AD unless otherwise
specified in the instructions obtained using the procedures
specified in paragraph (j)(2) of this AD.
(i) Optional Terminating Action
Modification of the wings including a detailed inspection of the
lower rib feet (rib 2) and bottom skin upper surface of the wings
for cracking and all applicable corrective actions, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-57-1207, including Appendix 01 and Appendix 02, dated May 26,
2016, constitutes terminating action for the repetitive inspections
required by paragraph (g) of this AD for that airplane. If, during
modification of an airplane as specified in this paragraph,
accomplishment of any modification instruction is not possible due
to configuration difficulties, accomplish the modification using the
procedures specified in paragraph (j)(1) of this AD.
(j) 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
[[Page 57343]]
AD, if requested using the procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your request to your principal
inspector or local Flight Standards District Office, as appropriate.
If sending information directly to the manager of the International
Branch, send it to the attention of the person identified in
paragraph (k)(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): 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.
(k) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2016-0222, dated November 7, 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-2017-0709.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 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 (l)(3) and (l)(4) of this AD.
(l) 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 A320-57-1205, dated May 26, 2016.
(ii) Airbus Service Bulletin A320-57-1207, including Appendix 01
and Appendix 02, dated May 26, 2016.
(3) 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.
(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 November 22, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-26037 Filed 12-4-17; 8:45 am]
BILLING CODE 4910-13-P
