Airworthiness Directives; Airbus Airplanes, 3155-3158 [2015-00716]
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Federal Register / Vol. 80, No. 14 / Thursday, January 22, 2015 / Rules and Regulations
3155
FIGURE 1 TO PARAGRAPH (g) OF THIS AD—AFM PROCEDURE
• At any time, with a speed above VLS, if the aircraft goes to a continuous nose down pitch rate that cannot be stopped with backward sidestick inputs, immediately:
Keep on one ADR.
Turn off two ADRs.
• If the Alpha Max strip (red) hides completely the Alpha Prot strip (black and amber) in a stabilized wings-level flight path (without
an increase in load factor):
Keep on one ADR.
Turn off two ADRs.
In case of dispatch with one ADR inoperative, switch only one ADR to OFF.
• CAUTION RISK OF ERRONEOUS DISPLAY OF THE VSW STRIP (RED AND BLACK)
Consider using the Flight Path Vector (FPV).
• If the Alpha Prot strip (black and amber) rapidly moves by more than 30 kt during flight maneuvers (with an increase in load factor), with AP ON and speed brakes retracted:
Keep on one ADR.
Turn off two ADRs.
In case of dispatch with one ADR inoperative, switch only one ADR to OFF.
CAUTION RISK OF ERRONEOUS DISPLAY OF THE VSW STRIP (RED AND BLACK)
Consider using the Flight Path Vector (FPV).
Issued in Renton, Washington, on January
7, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
(i) Other FAA Provisions
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
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. The AMOC
approval letter must specifically reference
this AD.
(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 Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
tkelley on DSK3SPTVN1PROD with RULES
(h) Special Flight Permits
Special flight permits, as described in
Section 21.197 and Section 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
[FR Doc. 2015–00714 Filed 1–21–15; 8:45 am]
(j) Related Information
For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
(k) Material Incorporated by Reference
None.
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Jkt 235001
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0927; Directorate
Identifier 2014–NM–230–AD; Amendment
39–18068; AD 2014–26–53]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Airbus Model A319–115, A319–133,
A320–214, A320–232, and A320–233
airplanes. This emergency AD was sent
previously to all known U.S. owners
and operators of these airplanes. This
AD requires repetitive detailed visual
inspections to detect discrepancies of
the wing lower skin surface and inboard
main landing gear (MLG) support rib
lower flange location fasteners and,
depending on findings, accomplishment
of applicable corrective action(s). This
AD was prompted by reports of failure
of certain fasteners located at the wing
lower skin surface and inboard MLG
support rib lower flange. We are issuing
this AD to detect and correct
SUMMARY:
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discrepancies of the fasteners at the
external surface of the lower wing skin
and inboard MLG support rib lower
flange, which could result in an airplane
not meeting its maximum loads
expected in service. This condition
could result in structural failure.
DATES: This AD is effective February 6,
2015 to all persons except those persons
to whom it was made immediately
effective by Emergency AD 2014–26–53,
issued on December 16, 2014, which
contained the requirements of this
amendment.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication identified in this
AD as of February 6, 2015.
We must receive comments on this
AD by March 9, 2015.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this 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.airwortheas@airbus.com; Internet https://
www.airbus.com.
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Federal Register / Vol. 80, No. 14 / Thursday, January 22, 2015 / Rules and Regulations
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–2014–
0927; or in person at the Docket
Operations Office 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 Operations Office (phone:
800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
On December 16, 2014, we issued
Emergency AD 2014–26–53, which
requires repetitive detailed visual
inspections to detect discrepancies of
the wing lower skin surface and inboard
MLG support rib lower flange location
fasteners and, depending on findings,
accomplishment of applicable corrective
action(s). Corrective actions include
fastener replacement or repair. This
emergency AD was sent previously to
all known U.S. owners and operators of
these airplanes.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued Airworthiness
Directive 2014–0270R1, dated December
15, 2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition on certain Airbus
Model A319–115, A319–133, A320–214,
A320–232, and A320–233 airplanes.
The MCAI states:
tkelley on DSK3SPTVN1PROD with RULES
During production of wings, a number of
taperlok fasteners were found failed after
installation. The fasteners in question are
located at the bottom skin of the Main
Landing Gear (MLG) reinforcing plate, wing
skin and Gear Support Rib 5 lower flange.
This condition, if not detected and
corrected could reduce the design margin of
the structure [and could result in structural
failure].
Based on the results of the preliminary
investigation, this affects only certain A319
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and A320 aeroplane Models delivered since
January 2014. A321 aeroplanes are not
affected, as the wing assembly is done using
parallel fasteners. A318 aeroplanes are not
affected, since none have been delivered
since January 2014.
Prompted by these findings, EASA issued
Emergency AD 2014–0270–E [dated
December 11, 2014] to require repetitive
inspections of the bottom skin taperlok
fasteners at the MLG Rib 5 footprint location
and, depending on findings, accomplishment
of applicable corrective action(s).
Since that AD was issued, operator
comments have indicated the need for
clarification, as well as correction.
For the reason described above, this
[EASA] AD is revised to add Notes for
information and to correct paragraphs (1) and
(2) of the AD.
This [EASA] AD is still considered to be
an interim action and further AD action may
follow.
Related Service Information
Airbus has issued Airbus Alert
Operators Transmission (AOT)
A57N006–14, Revision 00, dated
December 4, 2014. The service
information describes procedures for
inspections of the bottom skin fasteners
at the MLG rib 5 footprint location, and
replacement of affected fasteners. The
actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI. You can find this information at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2014–
0927.
FAA’s Determination and AD
Requirements
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are issuing this
AD because we evaluated all pertinent
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This AD and the
MCAI or Service Information
EASA Airworthiness Directive 2014–
0270–E, dated December 11, 2014,
specifies to do repetitive detailed visual
inspections of the outboard MLG
support rib lower flange fasteners and
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Fmt 4700
Sfmt 4700
nuts. However, these inspections are not
required by this AD. Since the specified
compliance time is four months, we are
considering further rulemaking to
require those inspections.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because discrepancies of the
fasteners at the external surface of the
lower wing skin and inboard MLG
support rib lower flange could result in
an airplane not meeting its maximum
loads expected in-service. This
condition could result in structural
failure. Therefore, we find that notice
and opportunity for prior public
comment are impracticable and that
good cause exists for making this
amendment effective in less than 30
days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety and
was not preceded by notice and an
opportunity for public comment.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include the docket number
FAA–2014–0927 and Directorate
Identifier 2014–NM–230–AD at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
Costs of Compliance
We estimate that this AD affects 80
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
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Federal Register / Vol. 80, No. 14 / Thursday, January 22, 2015 / Rules and Regulations
3157
ESTIMATED COSTS
Action
Labor cost
Parts cost
Inspection ......................
1 work-hour × $85 per hour = $85 [per inspection cycle].
$0
We estimate the following costs to do
any necessary replacements that would
Cost per product
$85 [per inspection
cycle].
be required based on the results of the
inspection. We have no way of
Cost on U.S. operators
$6,800 [per inspection
cycle].
determining the number of aircraft that
might need these replacements:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per product
Replacement ........................
3 work-hours × $85 per hour = $255 [per fastener replacement].
$400 [per fastener] ............
$655 [per fastener replacement].
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition repairs
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.
tkelley on DSK3SPTVN1PROD with RULES
Regulatory Findings
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
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
VerDate Sep<11>2014
16:25 Jan 21, 2015
Jkt 235001
(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):
■
2014–26–53 Airbus: Amendment 39–18068;
Docket No. FAA–2014–0927; Directorate
Identifier 2014–NM–230–AD.
(a) Effective Date
This AD is effective February 6, 2015 to all
persons except those persons to whom it was
made immediately effective by Emergency
AD 2014–26–53, issued on December 16,
2014, which contained the requirements of
this amendment.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A319–
115, A319–133, A320–214, A320–232, and
A320–233 airplanes, certificated in any
category, manufacturer serial numbers (MSN)
5817, 5826, 5837, 5848, 5855, 5864, 5875,
5886, 5896, and 5910, and MSNs 5918 and
subsequent.
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Fmt 4700
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(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of failure
of certain fasteners located at the wing lower
skin surface and inboard main landing gear
(MLG) support rib lower flange. We are
issuing this AD to detect and correct
discrepancies of the fasteners at the external
surface of the lower wing skin and inboard
MLG support rib lower flange, which could
result in an airplane not meeting its
maximum loads expected in-service. This
condition could result in structural failure.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections
Within 8 days after the effective date of
this AD, or within 8 days since the date of
issuance of the original certificate of
airworthiness or the original export
certificate of airworthiness, or before further
flight for any airplane that is not in
operation, whichever occurs later: Do the
inspections required by paragraphs (g)(1) and
(g)(2) of this AD, in accordance with Airbus
Alert Operators Transmission (AOT)
A57N006–14, Revision 00, dated December 4,
2014. Repeat the inspections thereafter at
intervals not to exceed 8 days.
(1) Do a detailed visual inspection of the
external surface of the left-hand and righthand wing lower skin surface to detect
missing or broken or migrated fasteners.
(2) Do a detailed visual inspection of the
inboard MLG support rib lower flange to
detect missing or broken nuts or fastener
tails.
(h) Corrective Actions for the Inspections
Required by Paragraph (g)(1) of This AD
(1) If, during any inspection required by
paragraph (g)(1) of this AD, only one
discrepancy (any missing or broken or
migrated fastener) is found on the left- or
right-side: Before further flight, do corrective
actions in accordance with a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA. Replacement of fasteners
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3158
Federal Register / Vol. 80, No. 14 / Thursday, January 22, 2015 / Rules and Regulations
on an airplane does not constitute
terminating action for any inspection
required by paragraph (g) of this AD.
(2) If, during any inspection required by
paragraph (g)(1) of this AD, more than one
discrepancy (any missing or broken or
migrated fastener) is found on the left- or
right-side: Before further flight, replace all
affected fasteners on the affected side(s), in
accordance with Airbus AOT A57N006–14,
Revision 00, dated December 4, 2014. One
fastener per side may be missing or broken
or migrated provided the applicable actions
required by paragraph (h)(1) of this AD are
done. Replacement of fasteners on an
airplane does not constitute terminating
action for any inspection required by
paragraph (g) of this AD.
(i) Corrective Actions for the Inspections
Required by Paragraph (g)(2) of This AD
(1) If, during any inspection required by
paragraph (g)(2) of this AD, only one
discrepancy (any missing or broken nut or
fastener tail) is found on the left- or rightside: Before further flight, do corrective
actions in accordance with a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA. Replacement of fasteners
on an airplane does not constitute
terminating action for any inspection
required by paragraph (g) of this AD.
(2) If, during any inspection required by
paragraph (g)(2) of this AD, more than one
discrepancy (any missing or broken nut or
fastener tail) is found on the left- or rightside: Before further flight, replace all affected
fasteners on the affected side(s), in
accordance with Airbus AOT A57N006–14,
Revision 00, dated December 4, 2014. One
fastener per side may be missing or broken
or migrated provided the applicable actions
required by paragraph (i)(1) of this AD are
done. Replacement of fasteners on an
airplane does not constitute terminating
action for any inspection required by
paragraph (g) of this AD.
tkelley on DSK3SPTVN1PROD with RULES
(j) Special Flight Permits
Special flight permits, as described in
Section 21.197 and Section 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(k) Other FAA Provisions
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the Manager, International Branch, send it
to ATTN: Sanjay Ralhan, Aerospace
Engineer, International Branch, ANM–116,
Transport Airplane Directorate, FAA, 1601
Lind Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
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. The AMOC
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16:25 Jan 21, 2015
Jkt 235001
approval letter must specifically reference
this AD.
(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 Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(l) Related Information
For further information about this AD,
contact: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Airbus Alert Operators Transmission
A57N006–14, Revision 00, dated December 4,
2014.
(ii) Reserved.
(3) For service information referenced 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.
You may view this referenced service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
WA.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(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 January
7, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–00716 Filed 1–21–15; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0580; Directorate
Identifier 2014–NM–081–AD; Amendment
39–18062; AD 2015–01–01]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2011–09–
11, for certain The Boeing Company
Model 777–200 and –300 series
airplanes. AD 2011–09–11 required
repetitive inspections for hydraulic
fluid contamination of the interior of the
strut disconnect assembly; repetitive
inspections for discrepancies of the
interior of the strut disconnect
assembly, if necessary; repetitive
inspections of the exterior of the strut
disconnect assembly for cracks, if
necessary; corrective action if necessary;
and an optional terminating action for
the inspections. This new AD adds, for
certain airplanes, an inspection of the
side and top cover plates to determine
if all cover plate attach fasteners have
been installed, and installing any
missing fasteners including doing an
inspection for damage, and repair if
necessary. This AD was prompted by
reports of side and top cover plates
installed with missing fastener bolts,
which results in an unsealed opening on
the system disconnect assembly. We are
issuing this AD to detect and correct
hydraulic fluid contamination, which
can cause cracking of titanium parts in
the system disconnect assembly; and
also to detect and correct missing
fasteners, which results in unsealed
openings on the system disconnect
assembly. Both unsafe conditions can
compromise the engine firewall and
result in fire hazards for both the engine
compartment and the strut.
DATES: This AD is effective February 26,
2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of February 26, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of June 6, 2011 (76 FR 24354,
May 2, 2011).
ADDRESSES: For service information
identified in this AD, contact Boeing
SUMMARY:
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Agencies
[Federal Register Volume 80, Number 14 (Thursday, January 22, 2015)]
[Rules and Regulations]
[Pages 3155-3158]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-00716]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0927; Directorate Identifier 2014-NM-230-AD;
Amendment 39-18068; AD 2014-26-53]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Airbus Model A319-115, A319-133, A320-214, A320-232, and A320-233
airplanes. This emergency AD was sent previously to all known U.S.
owners and operators of these airplanes. This AD requires repetitive
detailed visual inspections to detect discrepancies of the wing lower
skin surface and inboard main landing gear (MLG) support rib lower
flange location fasteners and, depending on findings, accomplishment of
applicable corrective action(s). This AD was prompted by reports of
failure of certain fasteners located at the wing lower skin surface and
inboard MLG support rib lower flange. We are issuing this AD to detect
and correct discrepancies of the fasteners at the external surface of
the lower wing skin and inboard MLG support rib lower flange, which
could result in an airplane not meeting its maximum loads expected in
service. This condition could result in structural failure.
DATES: This AD is effective February 6, 2015 to all persons except
those persons to whom it was made immediately effective by Emergency AD
2014-26-53, issued on December 16, 2014, which contained the
requirements of this amendment.
The Director of the Federal Register approved the incorporation by
reference of a certain publication identified in this AD as of February
6, 2015.
We must receive comments on this AD by March 9, 2015.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this 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.
[[Page 3156]]
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-2014-
0927; or in person at the Docket Operations Office 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 Operations Office
(phone: 800-647-5527) is in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
On December 16, 2014, we issued Emergency AD 2014-26-53, which
requires repetitive detailed visual inspections to detect discrepancies
of the wing lower skin surface and inboard MLG support rib lower flange
location fasteners and, depending on findings, accomplishment of
applicable corrective action(s). Corrective actions include fastener
replacement or repair. This emergency AD was sent previously to all
known U.S. owners and operators of these airplanes.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued
Airworthiness Directive 2014-0270R1, dated December 15, 2014 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition on certain Airbus Model
A319-115, A319-133, A320-214, A320-232, and A320-233 airplanes. The
MCAI states:
During production of wings, a number of taperlok fasteners were
found failed after installation. The fasteners in question are
located at the bottom skin of the Main Landing Gear (MLG)
reinforcing plate, wing skin and Gear Support Rib 5 lower flange.
This condition, if not detected and corrected could reduce the
design margin of the structure [and could result in structural
failure].
Based on the results of the preliminary investigation, this
affects only certain A319 and A320 aeroplane Models delivered since
January 2014. A321 aeroplanes are not affected, as the wing assembly
is done using parallel fasteners. A318 aeroplanes are not affected,
since none have been delivered since January 2014.
Prompted by these findings, EASA issued Emergency AD 2014-0270-E
[dated December 11, 2014] to require repetitive inspections of the
bottom skin taperlok fasteners at the MLG Rib 5 footprint location
and, depending on findings, accomplishment of applicable corrective
action(s).
Since that AD was issued, operator comments have indicated the
need for clarification, as well as correction.
For the reason described above, this [EASA] AD is revised to add
Notes for information and to correct paragraphs (1) and (2) of the
AD.
This [EASA] AD is still considered to be an interim action and
further AD action may follow.
Related Service Information
Airbus has issued Airbus Alert Operators Transmission (AOT)
A57N006-14, Revision 00, dated December 4, 2014. The service
information describes procedures for inspections of the bottom skin
fasteners at the MLG rib 5 footprint location, and replacement of
affected fasteners. The actions described in this service information
are intended to correct the unsafe condition identified in the MCAI.
You can find this information at https://www.regulations.gov by
searching for and locating Docket No. FAA-2014-0927.
FAA's Determination and AD Requirements
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are issuing this AD because we
evaluated all pertinent information and determined the unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This AD and the MCAI or Service Information
EASA Airworthiness Directive 2014-0270-E, dated December 11, 2014,
specifies to do repetitive detailed visual inspections of the outboard
MLG support rib lower flange fasteners and nuts. However, these
inspections are not required by this AD. Since the specified compliance
time is four months, we are considering further rulemaking to require
those inspections.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because
discrepancies of the fasteners at the external surface of the lower
wing skin and inboard MLG support rib lower flange could result in an
airplane not meeting its maximum loads expected in-service. This
condition could result in structural failure. Therefore, we find that
notice and opportunity for prior public comment are impracticable and
that good cause exists for making this amendment effective in less than
30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, we invite you to send any written data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include the docket number FAA-2014-0927 and
Directorate Identifier 2014-NM-230-AD at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this AD. We will
consider all comments received by the closing date and may amend this
AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Costs of Compliance
We estimate that this AD affects 80 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
[[Page 3157]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection..................... 1 work-hour x $85 per $0 $85 [per $6,800 [per
hour = $85 [per inspection cycle]. inspection
inspection cycle]. cycle].
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that would be required based on the results of the inspection. We have
no way of determining the number of aircraft that might need these
replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement........................ 3 work-hours x $85 per hour $400 [per fastener]... $655 [per fastener
= $255 [per fastener replacement].
replacement].
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition repairs 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.
Regulatory Findings
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 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):
2014-26-53 Airbus: Amendment 39-18068; Docket No. FAA-2014-0927;
Directorate Identifier 2014-NM-230-AD.
(a) Effective Date
This AD is effective February 6, 2015 to all persons except
those persons to whom it was made immediately effective by Emergency
AD 2014-26-53, issued on December 16, 2014, which contained the
requirements of this amendment.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A319-115, A319-133, A320-214,
A320-232, and A320-233 airplanes, certificated in any category,
manufacturer serial numbers (MSN) 5817, 5826, 5837, 5848, 5855,
5864, 5875, 5886, 5896, and 5910, and MSNs 5918 and subsequent.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of failure of certain fasteners
located at the wing lower skin surface and inboard main landing gear
(MLG) support rib lower flange. We are issuing this AD to detect and
correct discrepancies of the fasteners at the external surface of
the lower wing skin and inboard MLG support rib lower flange, which
could result in an airplane not meeting its maximum loads expected
in-service. This condition could result in structural failure.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections
Within 8 days after the effective date of this AD, or within 8
days since the date of issuance of the original certificate of
airworthiness or the original export certificate of airworthiness,
or before further flight for any airplane that is not in operation,
whichever occurs later: Do the inspections required by paragraphs
(g)(1) and (g)(2) of this AD, in accordance with Airbus Alert
Operators Transmission (AOT) A57N006-14, Revision 00, dated December
4, 2014. Repeat the inspections thereafter at intervals not to
exceed 8 days.
(1) Do a detailed visual inspection of the external surface of
the left-hand and right-hand wing lower skin surface to detect
missing or broken or migrated fasteners.
(2) Do a detailed visual inspection of the inboard MLG support
rib lower flange to detect missing or broken nuts or fastener tails.
(h) Corrective Actions for the Inspections Required by Paragraph (g)(1)
of This AD
(1) If, during any inspection required by paragraph (g)(1) of
this AD, only one discrepancy (any missing or broken or migrated
fastener) is found on the left- or right-side: Before further
flight, do corrective actions in accordance with a method approved
by the Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA. Replacement of fasteners
[[Page 3158]]
on an airplane does not constitute terminating action for any
inspection required by paragraph (g) of this AD.
(2) If, during any inspection required by paragraph (g)(1) of
this AD, more than one discrepancy (any missing or broken or
migrated fastener) is found on the left- or right-side: Before
further flight, replace all affected fasteners on the affected
side(s), in accordance with Airbus AOT A57N006-14, Revision 00,
dated December 4, 2014. One fastener per side may be missing or
broken or migrated provided the applicable actions required by
paragraph (h)(1) of this AD are done. Replacement of fasteners on an
airplane does not constitute terminating action for any inspection
required by paragraph (g) of this AD.
(i) Corrective Actions for the Inspections Required by Paragraph (g)(2)
of This AD
(1) If, during any inspection required by paragraph (g)(2) of
this AD, only one discrepancy (any missing or broken nut or fastener
tail) is found on the left- or right-side: Before further flight, do
corrective actions in accordance with a method approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA. Replacement of fasteners on an airplane does not
constitute terminating action for any inspection required by
paragraph (g) of this AD.
(2) If, during any inspection required by paragraph (g)(2) of
this AD, more than one discrepancy (any missing or broken nut or
fastener tail) is found on the left- or right-side: Before further
flight, replace all affected fasteners on the affected side(s), in
accordance with Airbus AOT A57N006-14, Revision 00, dated December
4, 2014. One fastener per side may be missing or broken or migrated
provided the applicable actions required by paragraph (i)(1) of this
AD are done. Replacement of fasteners on an airplane does not
constitute terminating action for any inspection required by
paragraph (g) of this AD.
(j) Special Flight Permits
Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(k) Other FAA Provisions
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the Manager, International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. 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. The AMOC approval letter must specifically reference this
AD.
(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
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Airbus's EASA Design Organization Approval (DOA). If approved by the
DOA, the approval must include the DOA-authorized signature.
(l) Related Information
For further information about this AD, contact: Sanjay Ralhan,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Airbus Alert Operators Transmission A57N006-14, Revision 00,
dated December 4, 2014.
(ii) Reserved.
(3) For service information referenced 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. You may view this referenced service information at
the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA.
(4) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(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 January 7, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-00716 Filed 1-21-15; 8:45 am]
BILLING CODE 4910-13-P