Airworthiness Directives; Airbus Airplanes, 64159-64162 [2013-25295]
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Federal Register / Vol. 78, No. 208 / Monday, October 28, 2013 / Rules and Regulations
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:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone (425) 227–1138; fax (425) 227–
1149. Information may be emailed to: 9ANM-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. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
wreier-aviles on DSK5TPTVN1PROD with RULES
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency (EASA)
Airworthiness Directive 2012–0021, dated
January 30, 2012, for related information.
You may examine the MCAI on the Internet
at https://www.regulations.gov by searching
for and locating it in Docket No. FAA–2013–
0832.
(2) Service information identified in this
AD that is not incorporated by reference may
be obtained 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 following service information
under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use the following service
information to do the actions required by this
AD, unless the AD specifies otherwise.
(i) A340 Airworthiness Limitations Section
(ALS), Part 4—Aging Systems Maintenance,
Revision 02, dated October 12, 2011. The
revision date is not identified on the title
page of this document.
(ii) Reserved.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(4) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
(5) You may also review copies of the
service information that is incorporated by
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12:59 Oct 25, 2013
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reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at an NARA facility, call 202–741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
September 17, 2013.
Ross Landes,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–23899 Filed 10–25–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0539; Directorate
Identifier 2012–NM–145–AD; Amendment
39–17616; AD 2013–20–10]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
airworthiness directive (AD) 2000–12–
11, for certain Model A300 B4–600 and
Model A300 B4–600R series airplanes.
AD 2000–12–11 required repetitive
inspections to detect cracks in the bolt
holes inboard and outboard of rib 9 on
the bottom booms of the front and rear
wing spars, and repair if necessary. This
new AD reduces the initial inspection
compliance time and repetitive
inspection interval. This AD was
prompted by a fleet survey and an
updated fatigue and damage tolerance
analysis indicating a high risk for
fatigue cracking on the front and rear
spar bottom booms. We are issuing this
AD to detect and correct fatigue cracks
in the bolt holes of the wing spars,
which could result in reduced structural
integrity of a wing spar.
DATES: This AD becomes effective
December 2, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 2, 2013.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2013-0539; or in
person at the U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
SUMMARY:
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64159
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC.
For service information identified in
this AD, contact Airbus SAS—EAW
(Airworthiness Office), 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 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.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: (425) 227–2125;
fax: (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. The
NPRM published in the Federal
Register on July 3, 2013 (78 FR 40069),
and proposed to supersede AD 2000–
12–11, Amendment 39–11789 (65 FR
37853, June 19, 2000). The NPRM
proposed to correct an unsafe condition
for the specified products.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2012–0138,
dated July 26, 2012 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for the specified products. The MCAI
states:
Full fatigue tests carried out by the
manufacturer revealed crack initiation from
the bolts holes at inboard and outboard of rib
9, on the front and rear spar bottom booms.
Similar cracks at the same area were reported
by A300–600 aeroplane operators.
This condition, if not detected and
corrected, could affect the structural integrity
of the aeroplane.
To address this unsafe condition,
´ ´
[Direction Generale de l’Aviation Civile]
DGAC France issued AD 94–208–169(B)R2
(https://ad.easa.europa.eu/blob/19942082tb_
superseded.pdf/AD_F-1994-208-169R2_2)
[which corresponds to FAA AD 95–07–05,
Amendment 39–9187 (60 FR 17990, April 10,
1995)] to require an ultrasonic inspection of
holes inboard and outboard of rib 9 on the
front and rear spar bottom booms on Left
Hand and Right Hand wings.
Since that [DGAC] AD was issued, a fleet
survey and updated Fatigue and Damage
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Tolerance analysis have been performed in
order to substantiate the second A300–600
Extended Service Goal (ESG2) exercise. The
results of these analyses have shown that the
risk for these aeroplanes is higher than
initially determined and that, consequently,
the inspection threshold and interval must be
reduced to allow timely detection of cracks
and the accomplishment of an applicable
corrective action [and related investigative
action].
For the reasons explained above, this new
[EASA] AD retains the requirements of DGAC
France AD 94–208–169(B)R2, which is
superseded, and requires the
accomplishment instructions within the new
thresholds and intervals specified in
Revision 04 of Airbus Mandatory Service
Bulletin (SB) A300–57–6037 [dated February
24, 2011].
corrective actions include oversizing
holes and installing new fasteners, and
for certain conditions, contacting the
FAA or EASA (or its delegated agent) for
instructions. You may examine the
MCAI in the AD docket on the Internet
at https://www.regulations.gov/
#!documentDetail;D=FAA-2013-05390002.
The related investigative action includes
doing inspections for cracking. The
We reviewed the available data and
determined that air safety and the
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (78
FR 40069, July 3, 2013) or on the
determination of the cost to the public.
Conclusion
public interest require adopting this AD
as proposed—except for minor editorial
changes and re-formatting of the
estimates cost data. The estimated cost
data has not been changed. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (78 FR
40069, July 3, 2013) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (78 FR 40069,
July 3, 2013).
Costs of Compliance
We estimate that this AD affects 29
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per product
Inspection [new action] ..........
18 work-hours × $85 per hour
= $1,530 [per inspection
cycle].
$0
$1,530 [per inspection cycle]
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition workhours specified in this AD. The oncondition parts cost estimate is $2,874.
According to the manufacturer, some
of the costs 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 costs in our cost
estimate.
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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.
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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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2013-0539; 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
MCAI, the regulatory evaluation, any
comments received, and other
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Cost on U.S. operators
$44,370 [per inspection
cycle].
information. The street address for the
Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section.
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
removing airworthiness directive (AD)
2000–12–11, Amendment 39–11789 (65
FR 37853, June 19, 2000), and adding
the following new AD:
■
2013–20–10 Airbus: Amendment 39–17616.
Docket No. FAA–2013–0539; Directorate
Identifier 2012–NM–145–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective December 2, 2013.
(b) Affected ADs
This AD supersedes AD 2000–12–11,
Amendment 39–11789 (65 FR 37853, June
19, 2000).
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(c) Applicability
This AD applies to Airbus Model A300 B4–
601, B4–603, B4–620, B4–622, B4–605R, and
B4–622R airplanes; certificated in any
category; all manufacturer serial numbers,
except airplanes on which Airbus
Modification 10161 has been incorporated in
production.
(1) For normal range airplanes: Repeat the
inspection thereafter at intervals not to
exceed 3,900 flight cycles or 8,400 flight
hours, whichever occurs first.
(2) For short range airplanes: Repeat the
inspection thereafter at intervals not to
exceed 4,200 flight cycles or 6,300 flight
hours, whichever occurs first.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(i) Corrective Action for Cracking
(e) Reason
This AD was prompted by a fleet survey
and an updated fatigue and damage tolerance
analysis indicating a high risk for fatigue
cracking on the front and rear spar bottom
booms. We are issuing this AD to detect and
correct fatigue cracks in the bolt holes of the
wing spars, which could result in reduced
structural integrity of a wing spar.
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(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Repetitive Inspections
At the applicable time specified in
paragraph (g)(1) or (g)(2) of this AD: Perform
an ultrasonic inspection to detect fatigue
cracking of the bolt holes inboard and
outboard of rib 9 on the bottom booms of the
front and rear wing spars, in accordance with
the Accomplishment Instruction of Airbus
Mandatory Service Bulletin A300–57–6037,
Revision 04, dated February 24, 2011, except
as specified in paragraph (k) of this AD.
Repeat the inspection thereafter at intervals
not to exceed the applicable time specified in
paragraph (h) of this AD.
(1) For normal range airplanes, at the later
of the times in paragraphs (g)(1)(i) and
(g)(1)(ii) of this AD.
(i) Within 14,100 flight cycles or 30,400
flight hours since airplane first flight or
within 14,100 flight cycles or 30,400 flight
hours since airplane modification done as
specified in the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–6039 (which is not incorporated by
reference in this AD), whichever occurs first.
(ii) Within 1,600 flight cycles or 3,400
flight hours, whichever occurs first after the
effective date of this AD.
(2) For short range airplanes, at the later of
the times in paragraphs (g)(2)(i) and (g)(2)(ii)
of this AD.
(i) Within 15,200 flight cycles or 22,800
flight hours since airplane first flight, or
since airplane modification done as specified
in the Accomplishment Instructions of
Airbus Service Bulletin A300–57–6039
(which is not incorporated by reference in
this AD), whichever occurs first.
(ii) Within 1,700 flight cycles or 2,500
flight hours, whichever occurs first after the
effective date of this AD.
(h) Repetitive Inspection Compliance Times
At the applicable time specified in
paragraph (h)(1) or (h)(2) of this AD, repeat
the inspection required by paragraph (g) of
this AD.
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If any crack is found during any inspection
required by paragraph (g) of this AD: Before
further flight, repair the cracking including
applicable related investigative and
corrective actions, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300–57–6037,
Revision 04, dated February 24, 2011, except
as specified in paragraph (k) of this AD. Do
related investigative and corrective actions
before further flight. Thereafter, repeat the
inspection required by paragraph (g) of this
AD at intervals not to exceed the applicable
time specified in paragraph (h) of this AD.
Corrective actions required by this paragraph
do not constitute terminating action for the
repetitive inspections required by paragraph
(h) of this AD.
(j) Definition of Short Range and Long Range
Airplanes
For purposes of this AD, short range
airplanes are those with an average flight
time lower than 1.5 flight hours, and normal
range airplanes are those with an average
flight time equal to or higher than 1.5 flight
hours.
(k) Exception to Service Information
Where the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A300–57–
6037, Revision 04, dated February 24, 2011,
specify contacting Airbus for an approved
repair: Before further flight, contact either the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA, or the
European Aviation Safety Agency (EASA) (or
its delegated agent), for instructions and do
those instructions.
(l) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (g) and (h) of this AD,
if those actions were performed before the
effective date of this AD using any of the
service bulletins specified in paragraphs
(l)(1) through (l)(4) of this AD.
(1) Airbus Mandatory Service Bulletin
A300–57–6037, dated August 1, 1994, which
was incorporated by reference in AD 2000–
12–11, Amendment 39–11789 (65 FR 37853,
June 19, 2000).
(2) Airbus Mandatory Service Bulletin
A300–57–6037, Revision 01, dated August
31, 1995, which was incorporated by
reference in AD 2000–12–11, Amendment
39–11789 (65 FR 37853, June 19, 2000).
(3) Airbus Mandatory Service Bulletin
A300–57–6037, Revision 02, dated January 9,
2001, which is not incorporated by reference
in this AD.
(4) Airbus Mandatory Service Bulletin
A300–57–6037, Revision 03, dated January
11, 2002, which is not incorporated by
reference in this AD.
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64161
(m) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: (425) 227–2125; fax: (425) 227–1149.
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. The AMOC approval letter
must specifically reference this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) AMOCs Approved Previously: AMOCs
approved previously in accordance with AD
2000–12–11, Amendment 39–11789 (65 FR
37853, June 19, 2000), are approved as
AMOCs for the corresponding provisions of
this AD.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information EASA
Airworthiness Directive 2012–0138, dated
July 26, 2012, for related information. You
may examine the MCAI in the AD docket on
the Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2013-0539-0002.
(2) Service information identified in this
AD that is not incorporated by reference may
be obtained at the addresses specified in
paragraphs (o)(4) and (o)(5) of this AD.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on December 2, 2013.
(i) Airbus Mandatory Service Bulletin
A300–57–6037, Revision 04, dated February
24, 2011.
(ii) Reserved.
(4) For service information identified in
this AD, contact Airbus SAS—EAW
(Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
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93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(5) 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.
(6) 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
September 18, 2013.
Ross Landes,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–25295 Filed 10–25–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0465; Directorate
Identifier 2012–NM–085–AD; Amendment
39–17617; AD 2013–20–11]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A318, A319, A320, and
A321 series airplanes. This AD was
prompted by a determination that
oxygen generators installed on a certain
batch of passenger emergency oxygen
container assemblies might become
detached by extreme pulling of the mask
tube at the end of the oxygen supply
causing a high temperature oxygen
generator and mask to fall down. This
AD requires modifying the passenger
emergency oxygen container assembly.
We are issuing this AD to prevent a high
temperature oxygen generator and mask
from falling down and possibly
resulting in an ignition source in the
passenger compartment, injury to
wreier-aviles on DSK5TPTVN1PROD with RULES
SUMMARY:
passengers, and reduced availability of
supplemental oxygen.
DATES: This AD becomes effective
December 2, 2013.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of December 2, 2013.
ADDRESSES: You may examine the AD
on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2013-0465; or in
person at the U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC.
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. You may review
copies of the referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
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:
It has been determined that oxygen
generators, installed on a specific batch of
Type 1 (22 minute) passenger emergency
oxygen container assemblies, may become
detached by extreme pulling of the mask tube
at the end of oxygen supply. Investigations
revealed that such detachment can be caused
by the increase in temperature towards the
end of the generator operation, which may
weaken the plastic housing in the attachment
area of the bracket.
This condition, if not corrected, could
make the rivets slip through the plastic
housing, causing a ‘hot’ oxygen generator and
mask to fall down, possibly resulting in
injury to passengers.
For the reasons described above, this
[EASA] AD requires modification of the
affected oxygen container assemblies. This
[EASA] AD also prohibits the installation of
the affected (unmodified) containers on any
aeroplane as replacement parts.
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. The
NPRM published in the Federal
Register on July 3, 2013 (78 FR 40074).
The NPRM proposed to correct an
unsafe condition for the specified
products.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2012–0055,
dated April 3, 2012 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for the specified products. The MCAI
states:
We reviewed the available data and
determined that air safety and the
public interest require adopting this AD
as proposed–except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (78 FR
40074, July 3, 2013) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (78 FR 40074,
July 3, 2013).
The modification consists of adding a
reinforcement plate at the rear outside
of the container and adding two washers
to the rivets at the inside of the
container to prevent the generator from
detaching. You may examine the MCAI
in the AD docket on the Internet at
https://www.regulations.gov/
#!documentDetail;D=FAA-2013-04650002.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (78
FR 40074, July 3, 2013) or on the
determination of the cost to the public.
Conclusion
Costs of Compliance
We estimate that this AD affects 4
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Modification .....................................................
2 work-hours × $85 per hour = $170 .............
VerDate Mar<15>2010
12:59 Oct 25, 2013
Jkt 232001
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
Cost per
product
Parts cost
E:\FR\FM\28OCR1.SGM
$0
28OCR1
$170
Cost on U.S.
operators
$680
]]>Agencies
[Federal Register Volume 78, Number 208 (Monday, October 28, 2013)]
[Rules and Regulations]
[Pages 64159-64162]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-25295]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0539; Directorate Identifier 2012-NM-145-AD;
Amendment 39-17616; AD 2013-20-10]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding airworthiness directive (AD) 2000-12-11,
for certain Model A300 B4-600 and Model A300 B4-600R series airplanes.
AD 2000-12-11 required repetitive inspections to detect cracks in the
bolt holes inboard and outboard of rib 9 on the bottom booms of the
front and rear wing spars, and repair if necessary. This new AD reduces
the initial inspection compliance time and repetitive inspection
interval. This AD was prompted by a fleet survey and an updated fatigue
and damage tolerance analysis indicating a high risk for fatigue
cracking on the front and rear spar bottom booms. We are issuing this
AD to detect and correct fatigue cracks in the bolt holes of the wing
spars, which could result in reduced structural integrity of a wing
spar.
DATES: This AD becomes effective December 2, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 2,
2013.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2013-0539; or in person at the
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC.
For service information identified in this AD, contact Airbus SAS--
EAW (Airworthiness Office), 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 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.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: (425) 227-2125;
fax: (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
The NPRM published in the Federal Register on July 3, 2013 (78 FR
40069), and proposed to supersede AD 2000-12-11, Amendment 39-11789 (65
FR 37853, June 19, 2000). The NPRM proposed to correct an unsafe
condition for the specified products.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2012-0138, dated July 26, 2012 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:
Full fatigue tests carried out by the manufacturer revealed
crack initiation from the bolts holes at inboard and outboard of rib
9, on the front and rear spar bottom booms. Similar cracks at the
same area were reported by A300-600 aeroplane operators.
This condition, if not detected and corrected, could affect the
structural integrity of the aeroplane.
To address this unsafe condition, [Direction
G[eacute]n[eacute]rale de l'Aviation Civile] DGAC France issued AD
94-208-169(B)R2 (https://ad.easa.europa.eu/blob/19942082tb_superseded.pdf/AD_F-1994-208-169R2_2) [which corresponds to FAA AD
95-07-05, Amendment 39-9187 (60 FR 17990, April 10, 1995)] to
require an ultrasonic inspection of holes inboard and outboard of
rib 9 on the front and rear spar bottom booms on Left Hand and Right
Hand wings.
Since that [DGAC] AD was issued, a fleet survey and updated
Fatigue and Damage
[[Page 64160]]
Tolerance analysis have been performed in order to substantiate the
second A300-600 Extended Service Goal (ESG2) exercise. The results
of these analyses have shown that the risk for these aeroplanes is
higher than initially determined and that, consequently, the
inspection threshold and interval must be reduced to allow timely
detection of cracks and the accomplishment of an applicable
corrective action [and related investigative action].
For the reasons explained above, this new [EASA] AD retains the
requirements of DGAC France AD 94-208-169(B)R2, which is superseded,
and requires the accomplishment instructions within the new
thresholds and intervals specified in Revision 04 of Airbus
Mandatory Service Bulletin (SB) A300-57-6037 [dated February 24,
2011].
The related investigative action includes doing inspections for
cracking. The corrective actions include oversizing holes and
installing new fasteners, and for certain conditions, contacting the
FAA or EASA (or its delegated agent) for instructions. You may examine
the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2013-0539-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (78 FR 40069, July 3,
2013) or on the determination of the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting this AD as proposed--except for
minor editorial changes and re-formatting of the estimates cost data.
The estimated cost data has not been changed. We have determined that
these minor changes:
Are consistent with the intent that was proposed in the
NPRM (78 FR 40069, July 3, 2013) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 40069, July 3, 2013).
Costs of Compliance
We estimate that this AD affects 29 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 [new action]......... 18 work-hours x $85 $0 $1,530 [per $44,370 [per
per hour = $1,530 inspection cycle]. inspection cycle].
[per inspection
cycle].
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition work-hours specified in this AD.
The on-condition parts cost estimate is $2,874.
According to the manufacturer, some of the costs 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 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.
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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2013-0539; 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
MCAI, the regulatory evaluation, any comments received, and other
information. The street address for the Docket Operations office
(telephone (800) 647-5527) is in the ADDRESSES section.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2000-12-11, Amendment 39-11789 (65 FR 37853, June 19, 2000), and adding
the following new AD:
2013-20-10 Airbus: Amendment 39-17616. Docket No. FAA-2013-0539;
Directorate Identifier 2012-NM-145-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective December 2,
2013.
(b) Affected ADs
This AD supersedes AD 2000-12-11, Amendment 39-11789 (65 FR
37853, June 19, 2000).
[[Page 64161]]
(c) Applicability
This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, B4-
622, B4-605R, and B4-622R airplanes; certificated in any category;
all manufacturer serial numbers, except airplanes on which Airbus
Modification 10161 has been incorporated in production.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by a fleet survey and an updated fatigue
and damage tolerance analysis indicating a high risk for fatigue
cracking on the front and rear spar bottom booms. We are issuing
this AD to detect and correct fatigue cracks in the bolt holes of
the wing spars, which could result in reduced structural integrity
of a wing spar.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Repetitive Inspections
At the applicable time specified in paragraph (g)(1) or (g)(2)
of this AD: Perform an ultrasonic inspection to detect fatigue
cracking of the bolt holes inboard and outboard of rib 9 on the
bottom booms of the front and rear wing spars, in accordance with
the Accomplishment Instruction of Airbus Mandatory Service Bulletin
A300-57-6037, Revision 04, dated February 24, 2011, except as
specified in paragraph (k) of this AD. Repeat the inspection
thereafter at intervals not to exceed the applicable time specified
in paragraph (h) of this AD.
(1) For normal range airplanes, at the later of the times in
paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
(i) Within 14,100 flight cycles or 30,400 flight hours since
airplane first flight or within 14,100 flight cycles or 30,400
flight hours since airplane modification done as specified in the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6039
(which is not incorporated by reference in this AD), whichever
occurs first.
(ii) Within 1,600 flight cycles or 3,400 flight hours, whichever
occurs first after the effective date of this AD.
(2) For short range airplanes, at the later of the times in
paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
(i) Within 15,200 flight cycles or 22,800 flight hours since
airplane first flight, or since airplane modification done as
specified in the Accomplishment Instructions of Airbus Service
Bulletin A300-57-6039 (which is not incorporated by reference in
this AD), whichever occurs first.
(ii) Within 1,700 flight cycles or 2,500 flight hours, whichever
occurs first after the effective date of this AD.
(h) Repetitive Inspection Compliance Times
At the applicable time specified in paragraph (h)(1) or (h)(2)
of this AD, repeat the inspection required by paragraph (g) of this
AD.
(1) For normal range airplanes: Repeat the inspection thereafter
at intervals not to exceed 3,900 flight cycles or 8,400 flight
hours, whichever occurs first.
(2) For short range airplanes: Repeat the inspection thereafter
at intervals not to exceed 4,200 flight cycles or 6,300 flight
hours, whichever occurs first.
(i) Corrective Action for Cracking
If any crack is found during any inspection required by
paragraph (g) of this AD: Before further flight, repair the cracking
including applicable related investigative and corrective actions,
in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300-57-6037, Revision 04, dated February
24, 2011, except as specified in paragraph (k) of this AD. Do
related investigative and corrective actions before further flight.
Thereafter, repeat the inspection required by paragraph (g) of this
AD at intervals not to exceed the applicable time specified in
paragraph (h) of this AD. Corrective actions required by this
paragraph do not constitute terminating action for the repetitive
inspections required by paragraph (h) of this AD.
(j) Definition of Short Range and Long Range Airplanes
For purposes of this AD, short range airplanes are those with an
average flight time lower than 1.5 flight hours, and normal range
airplanes are those with an average flight time equal to or higher
than 1.5 flight hours.
(k) Exception to Service Information
Where the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A300-57-6037, Revision 04, dated February 24, 2011,
specify contacting Airbus for an approved repair: Before further
flight, contact either the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA, or the European Aviation Safety
Agency (EASA) (or its delegated agent), for instructions and do
those instructions.
(l) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using any of the service
bulletins specified in paragraphs (l)(1) through (l)(4) of this AD.
(1) Airbus Mandatory Service Bulletin A300-57-6037, dated August
1, 1994, which was incorporated by reference in AD 2000-12-11,
Amendment 39-11789 (65 FR 37853, June 19, 2000).
(2) Airbus Mandatory Service Bulletin A300-57-6037, Revision 01,
dated August 31, 1995, which was incorporated by reference in AD
2000-12-11, Amendment 39-11789 (65 FR 37853, June 19, 2000).
(3) Airbus Mandatory Service Bulletin A300-57-6037, Revision 02,
dated January 9, 2001, which is not incorporated by reference in
this AD.
(4) Airbus Mandatory Service Bulletin A300-57-6037, Revision 03,
dated January 11, 2002, which is not incorporated by reference in
this AD.
(m) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: (425) 227-2125; fax: (425) 227-1149. 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. The
AMOC approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) AMOCs Approved Previously: AMOCs approved previously in
accordance with AD 2000-12-11, Amendment 39-11789 (65 FR 37853, June
19, 2000), are approved as AMOCs for the corresponding provisions of
this AD.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information EASA
Airworthiness Directive 2012-0138, dated July 26, 2012, for related
information. You may examine the MCAI in the AD docket on the
Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2013-
0539-0002.
(2) Service information identified in this AD that is not
incorporated by reference may be obtained at the addresses specified
in paragraphs (o)(4) and (o)(5) of this AD.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
December 2, 2013.
(i) Airbus Mandatory Service Bulletin A300-57-6037, Revision 04,
dated February 24, 2011.
(ii) Reserved.
(4) For service information identified in this AD, contact
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61
[[Page 64162]]
93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com.
(5) 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.
(6) 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 September 18, 2013.
Ross Landes,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-25295 Filed 10-25-13; 8:45 am]
BILLING CODE 4910-13-P
