Airworthiness Directives; Airbus Airplanes, 65887-65891 [2014-24964]
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Federal Register / Vol. 79, No. 215 / Thursday, November 6, 2014 / Rules and Regulations
frequency eddy current inspection (Option
II), for cracking of the improved tee sections,
in accordance with the Accomplishment
Instructions of McDonnell Douglas DC–9
Alert Service Bulletin A53–231, Revision 2,
dated June 25, 1993, including Service
Sketch 3683D, Revision C, dated July 19,
1989.
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(i) Compliance Times
(1) For Option I and Option II inspections
specified in paragraph (h) of this AD: If the
time of installation of an improved tee
section having a part number listed in
paragraph (h) of this AD is known, do the
initial inspection required by paragraph (h)
of this AD within 50,000 flight cycles after
installation of the improved tee section, or
within 1,500 flight cycles after the effective
date of this AD, whichever occurs later.
(2) For Option I and Option II inspections
specified in paragraph (h) of this AD: If the
time of installation of an improved tee
section having a part number identified in
paragraph (h) of this AD is not known, do the
initial inspection required by paragraph (h)
of this AD before the accumulation of 75,000
total flight cycles, or within 1,500 flight
cycles after the effective date of this AD,
whichever occurs later.
(j) Repetitive Inspections
If no cracking is found during the
inspection required by paragraph (h) of this
AD: Do the actions specified in paragraph
(j)(1) or (j)(2) of this AD, as applicable, in
accordance with the Accomplishment
Instructions of McDonnell Douglas DC–9
Alert Service Bulletin A53–231, Revision 2,
dated June 25, 1993, including Service
Sketch 3683D, Revision C, dated July 19,
1989.
(1) For Option I: If Option I was used for
the inspection required by paragraph (h) of
this AD, do the actions at the applicable
intervals, as specified in paragraphs (j)(1)(i),
(j)(1)(ii), and (j)(1)(iii) of this AD.
(i) Repeat the LFEC inspection for cracking
of the side areas above the floor between
longerons L7 and L17 on the fuselage left and
right sides, at intervals not to exceed 2,000
flight cycles.
(ii) Repeat the general visual inspection for
cracking of the top and lower areas from
longeron L7 left side to L7 right side, and
lower fuselage longeron L17 to L20 on the
fuselage left and right sides, at intervals not
to exceed 1,500 flight cycles.
(iii) Repeat the general visual inspection
for cracking of the bottom areas from
longeron L20 left side to L20 right side, at
intervals not to exceed 3,500 flight cycles.
(2) For Option II: If Option II was used for
the inspection required by paragraph (h) of
this AD, repeat the high and low eddy
frequency eddy current inspections for
cracking around the entire periphery of the
fuselage from the forward side of the
bulkhead at intervals not to exceed 2,500
flight cycles.
(k) Corrective Action and Post-Replacement
Inspections
If any cracking is found during any
inspection required by paragraph (h) or (j) of
this AD: Before further pressurized flight,
replace each cracked tee section with an
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airworthy tee section having a part number
identified in paragraph (h) of this AD, or with
an original tee section having P/N 5910163–
89, 5910163–91, 5910163–92, 5910163–93,
5910163–94, or 5910163–95, in accordance
with the Accomplishment Instructions of
McDonnell Douglas DC–9 Alert Service
Bulletin A53–231, Revision 2, dated June 25,
1993, including Service Sketch 3683D,
Revision C, dated July 19, 1989.
(1) If the tee section is replaced with an
improved tee section listed in paragraph (h)
of this AD, prior to the accumulation of
50,000 flight cycles after installation, inspect
the tee section in accordance with paragraph
(h) of this AD and do all applicable corrective
actions and repetitive inspections in
accordance with and at the times specified in
paragraphs (j) and (k) of this AD.
(2) If the tee section is replaced with an
original tee section listed in paragraph (k) of
this AD, prior to the accumulation of 25,000
flight cycles after installation, inspect the tee
section in accordance with paragraph (h) of
this AD and do all applicable corrective
actions and repetitive inspections in
accordance with and at the times specified in
paragraphs (j) and (k) of this AD.
(l) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles Certification
Office (ACO), 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 of the ACO, send it to the
attention of the person identified in
paragraph (m) of this AD. Information may be
emailed to: 9-ANM-LAACO-AMOCREQUESTS@faa.gov.
(2) 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane and 14
CFR 25.571, Amendment 45, and the
approval must specifically refer to this AD.
(m) Related Information
For more information about this AD,
contact Eric Schrieber, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office, 3960
Paramount Boulevard, Lakewood, CA 90712–
4137; phone: 562–627–5348; fax: 562–627–
5210; email: eric.schrieber@faa.gov.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
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65887
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) McDonnell Douglas DC–9 Alert Service
Bulletin A53–231, Revision 2, dated June 25,
1993, including Service Sketch 3683D,
Revision C, dated July 19, 1989.
(ii) Reserved.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, 3855 Lakewood Boulevard, MC
D800–0019, Long Beach, CA 90846–0001;
telephone 206–544–5000, extension 2; fax
206–766–5683; Internet https://
www.myboeingfleet.com.
(4) You may view this service information
at 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 October
28, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–26330 Filed 11–5–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0192; Directorate
Identifier 2013–NM–221–AD; Amendment
39–17992; AD 2014–20–19]
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) 2013–10–
06, for all Airbus Model A330–200
Freighter, A330–200, A330–300, A340–
200, A340–300, A340–500, and A340–
600 series airplanes. AD 2013–10–06
required an inspection to identify the
installed windshields, and replacement
of any affected windshield. This new
AD requires expanding the inspection
area to 15 additional windshields’ serial
numbers. This AD was prompted by
several reports of a burning smell and/
or smoke in the cockpit during cruise
phase, leading in some cases, to
SUMMARY:
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diversion to alternate airports. We are
issuing this AD to prevent significantly
increased workload for the flightcrew,
which could, under some flight phases
and/or circumstances, constitute an
unsafe condition.
DATES: This AD becomes effective
December 11, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of December 11, 2014.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0192; or in
person at the Docket Management
Facility, U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC.
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. You
may view this 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:
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.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2013–10–06,
Amendment 39–17459 (78 FR 32347,
May 30, 2013). AD 2013–10–06 applied
to all Airbus Model A330–200 Freighter,
A330–200, A330–300, A340–200, A340–
300, A340–500, and A340–600 series
airplanes. The NPRM published in the
Federal Register on April 9, 2014 (79 FR
19548).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2013–0256,
dated October 21, 2013 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus Model A330–201, –202,
–203, –223, –223F, –243, –243F, –301,
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–302, –303, –321, –322, –323, –341,
–342, and –343 airplanes; and Model
A340–211, –212, –213, –311, –312,
–313, –541, and –642 airplanes. The
MCAI states:
Several operators reported cases of burning
smell and/or smoke in the cockpit during
cruise phase leading in some cases to
diversion. Findings showed that the cause of
these events is the burning of the SaintGobain Sully (SGS) windshield connector
terminal block.
This condition, if not corrected, could
significantly increase the flight crew
workload which would, under some flight
phases and/or circumstances constitute an
unsafe condition.
To address this unsafe condition, Airbus
published 3 different Service Bulletins (SB)
and EASA issued AD 2011–0242 [https://
ad.easa.europa.eu/blob/easa_ad_2011_0242_
Correction_superseded.pdf/AD_2011-0242_1]
(later corrected) which required the
identification of the installed windshields
and replacement of the affected part.
Since issuance of that [EASA] AD, a new
occurrence in service led Airbus to identify
a new batch of affected parts.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2011–0242 [https://ad.easa.europa.eu/
blob/easa_ad_2011_0242_Correction_
superseded.pdf/AD_2011-0242_1], which is
superseded, and requires identification and
replacement of the additionally identified
windshields.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-01920002.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (79
FR 19548, April 9, 2014) or on the
determination of the cost to the public.
‘‘Contacting the Manufacturer’’
Paragraph in This AD
Since late 2006, we have included a
standard paragraph titled ‘‘Airworthy
Product’’ in all MCAI ADs in which the
FAA develops an AD based on a foreign
authority’s AD.
We have become aware that some
operators have misunderstood or
misinterpreted the Airworthy Product
paragraph to allow the owner/operator
to use messages provided by the
manufacturer as approval of deviations
during the accomplishment of an ADmandated action. The Airworthy
Product paragraph does not approve
messages or other information provided
by the manufacturer for deviations to
the requirements of the AD-mandated
actions. The Airworthy Product
paragraph only addresses the
requirement to contact the manufacturer
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for corrective actions for the identified
unsafe condition and does not cover
deviations from other AD requirements.
However, deviations to AD-required
actions are addressed in 14 CFR 39.17,
and anyone may request the approval
for an alternative method of compliance
to the AD-required actions using the
procedures found in 14 CFR 39.19.
To address this misunderstanding and
misinterpretation of the Airworthy
Product paragraph, we have changed the
paragraph and retitled it ‘‘Contacting the
Manufacturer.’’ This paragraph now
clarifies that for any requirement in this
AD to obtain corrective actions from a
manufacturer, the actions must be
accomplished using a method approved
by the FAA, the EASA, or Airbus’s
EASA Design Organization Approval
(DOA).
The Contacting the Manufacturer
paragraph also clarifies that, if approved
by the DOA, the approval must include
the DOA-authorized signature. The DOA
signature indicates that the data and
information contained in the document
are EASA-approved, which is also FAAapproved. Messages and other
information provided by the
manufacturer that do not contain the
DOA-authorized signature approval are
not EASA-approved, unless EASA
directly approves the manufacturer’s
message or other information.
This clarification does not remove
flexibility previously afforded by the
Airworthy Product paragraph.
Consistent with long-standing FAA
policy, such flexibility was never
intended for required actions. This is
also consistent with the
recommendation of the Airworthiness
Directive Implementation Aviation
Rulemaking Committee to increase
flexibility in complying with ADs by
identifying those actions in
manufacturers’ service instructions that
are ‘‘Required for Compliance’’ with
ADs. We continue to work with
manufacturers to implement this
recommendation. But once we
determine that an action is required, any
deviation from the requirement must be
approved as an alternative method of
compliance.
We also have decided not to include
a generic reference to either the
‘‘delegated agent’’ or ‘‘design approval
holder (DAH) with State of Design
Authority design organization
approval,’’ but instead we have
provided the specific delegation
approval granted by the State of Design
Authority for the DAH throughout this
AD.
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Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR
19548, April 9, 2014) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (79 FR 19548,
April 9, 2014).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
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Costs of Compliance
We estimate that this AD affects 60
airplanes of U.S. registry.
The actions required by AD 2013–10–
06, Amendment 39–17459 (78 FR
32347, May 30, 2013), and retained in
this AD take about 2 work-hours per
product, at an average labor rate of $85
per work-hour. Required parts cost
about $0 per product. Based on these
figures, the estimated cost of the actions
that were required by AD 2013–10–06 is
$170 per product.
We also estimate that it would take
about 2 work-hours per product to
comply with the basic requirements of
this AD. The average labor rate is $85
per work-hour. Required parts would
cost about $0 per product. Based on
these figures, we estimate the cost of
this AD on U.S. operators to be $10,200,
or $170 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 10 work-hours and require parts
costing $0, for a cost of $850 per
product. We have no way of
determining the number of aircraft that
might need this action.
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,
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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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0192; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
AD, the regulatory evaluation, any
comments received, and other
information. The street address for the
Docket 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:
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65889
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)
2013–10–06, Amendment 39–17459 (78
FR 32347, May 30, 2013), and adding
the following new AD:
■
2014–20–19 Airbus: Amendment 39–17992.
Docket No. FAA–2014–0192; Directorate
Identifier 2013–NM–221–AD.
(a) Effective Date
This AD becomes effective December 11,
2014.
(b) Affected ADs
This AD supersedes AD 2013–10–06,
Amendment 39–17459 (78 FR 32347, May 30,
2013).
(c) Applicability
This AD applies to all airplanes identified
in paragraphs (c)(1) and (c)(2) of this AD,
certificated in any category, all manufacturer
serial numbers.
(1) Airbus Model A330–201, –202, –203,
–223, –223F, –243, –243F, –301, –302, –303,
–321, –322, –323, –341, –342, and –343
airplanes.
(2) Airbus Model A340–211, –212, –213,
–311, –312, –313, –541, and –642 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 56, Windows.
(e) Reason
This AD was prompted by several reports
of a burning smell and/or smoke in the
cockpit during cruise phase, leading in some
cases, to diversion to alternate airports. We
are issuing this AD to prevent significantly
increased workload for the flightcrew, which
could, under some flight phases and/or
circumstances, constitute an unsafe
condition.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Inspection With Revised Service
Information
This paragraph restates the requirements of
paragraph (g) of AD 2013–10–06,
Amendment 39–17459 (78 FR 32347, May 30,
2013), with revised service information.
Within 1,200 flight hours after July 5, 2013
(the effective date of AD 2013–10–06),
inspect to identify the manufacturer, the part
number, and the serial number of the lefthand (LH) and right-hand (RH) windshields
installed on the airplane, in accordance with
the Accomplishment Instructions of the
applicable Airbus service information
specified in paragraph (g)(1), (g)(2), or (g)(3)
of this AD. A review of airplane delivery or
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maintenance records is acceptable in lieu of
this inspection if the manufacturer, part
number, and serial number of the installed
windshields can be conclusively determined
from that review.
(1) For Model A330–201, –202, –203, –223,
–223F, –243, –243F, –301, –302, –303, –321,
–322, –323, –341, –342, and –343 airplanes:
Airbus Service Bulletin A330–56–3009,
Revision 02, including Appendix 01, dated
February 8, 2012; or Airbus Service Bulletin
A330–56–3009, Revision 03, including
Appendixes 01 and 02, dated August 1, 2013.
As of the effective date of this AD, use only
Airbus Service Bulletin A330–56–3009,
Revision 03, including Appendixes 01 and
02, dated August 1, 2013, to do the actions
required by paragraph (g) of this AD.
(2) For Model A340–211, –212, –213, –311,
–312, and –313 airplanes: Airbus Service
Bulletin A340–56–4008, Revision 01,
including Appendix 01, dated February 8,
2012; or Airbus Service Bulletin A340–56–
4008, Revision 02, including Appendixes 01
and 02, dated August 1, 2013. As of the
effective date of this AD, use only Airbus
Service Bulletin A340–56–4008, Revision 02,
including Appendixes 01 and 02, dated
August 1, 2013, to do the actions required by
paragraph (g) of this AD.
(3) For Model A340–541 and –642
airplanes: Airbus Service Bulletin A340–56–
5002, Revision 01, including Appendix 01,
dated February 8, 2012; or Airbus Service
Bulletin A340–56–5002, Revision 02,
including Appendixes 01 and 02, dated
August 1, 2013. As of the effective date of
this AD, use only Airbus Service Bulletin
A340–56–5002, Revision 02, including
Appendixes 01 and 02, dated August 1, 2013,
to do the actions required by paragraph (g)
of this AD.
(h) Retained Replacement With Revised
Service Information
This paragraph restates the requirements of
paragraph (h) of AD 2013–10–06,
Amendment 39–17459 (78 FR 32347, May 30,
2013), with revised service information. If it
is found, during the inspection required by
paragraph (g) of this AD, that any installed
LH or RH windshield was manufactured by
Saint-Gobain Sully (SGS) and the part
number and serial number are specified in
the applicable Airbus service information
specified in paragraph (g)(1), (g)(2), or (g)(3)
of this AD: Within 9 months or 1,200 flight
hours after July 5, 2013 (the effective date of
AD 2013–10–06), whichever occurs first,
replace all affected LH and RH windshields,
in accordance with the Accomplishment
Instructions of the applicable Airbus service
information specified in paragraph (h)(1),
(h)(2), or (h)(3) of this AD.
(1) For Model A330–201, –202, –203, –223,
–223F, –243, –243F, –301, –302, –303, –321,
–322, –323, –341, –342, and –343 airplanes:
Airbus Service Bulletin A330–56–3009,
Revision 02, including Appendix 01, dated
February 8, 2012; or Airbus Service Bulletin
A330–56–3009, Revision 03, including
Appendixes 01 and 02, dated August 1, 2013.
As of the effective date of this AD, use only
Airbus Service Bulletin A330–56–3009,
Revision 03, including Appendixes 01 and
02, dated August 1, 2013, to do the actions
required by paragraph (h) of this AD.
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(2) For Model A340–211, –212, –213, –311,
–312, and –313 airplanes: Airbus Service
Bulletin A340–56–4008, Revision 01,
including Appendix 01, dated February 8,
2012; or Airbus Service Bulletin A340–56–
4008, Revision 02, including Appendixes 01
and 02, dated August 1, 2013. As of the
effective date of this AD, use only Airbus
Service Bulletin A340–56–4008, Revision 02,
including Appendixes 01 and 02, dated
August 1, 2013, to do the actions required by
paragraph (h) of this AD.
(3) For Model A340–541 and –642
airplanes: Airbus Service Bulletin A340–56–
5002, Revision 01, including Appendix 01,
dated February 8, 2012; or Airbus Service
Bulletin A340–56–5002, Revision 02,
including Appendixes 01 and 02, dated
August 1, 2013. As of the effective date of
this AD, use only Airbus Service Bulletin
A340–56–5002, Revision 02, including
Appendixes 01 and 02, dated August 1, 2013,
to do the actions required by paragraph (h)
of this AD.
(i) New Requirement of This AD: Inspection
Within 6 months after the effective date of
this AD, inspect to identify the manufacturer,
the part number, and the serial number of the
LH and RH windshields installed on the
airplane, in accordance with the
Accomplishment Instructions of the
applicable Airbus service information
specified in paragraph (i)(1), (i)(2), or (i)(3) of
this AD. A review of airplane delivery or
maintenance records is acceptable in lieu of
this inspection if the manufacturer, part
number, and serial number of the installed
windshields can be conclusively determined
from that review.
(1) For Model A330–201, –202, –203, –223,
–223F, –243, –243F, –301, –302, –303, –321,
–322, –323, –341, –342, and –343 airplanes:
Airbus Service Bulletin A330–56–3009,
Revision 03, including Appendixes 01 and
02, dated August 1, 2013.
(2) For Model A340–211, –212, –213, –311,
–312, and –313 airplanes: Airbus Service
Bulletin A340–56–4008, Revision 02,
including Appendixes 01 and 02, dated
August 1, 2013.
(3) For Model A340–541 and –642
airplanes: Airbus Service Bulletin A340–56–
5002, Revision 02, including Appendixes 01
and 02, dated August 1, 2013.
(j) New Requirement of This AD:
Replacement
If it is found, during the inspection
required by paragraph (i) of this AD, that any
installed LH or RH windshield was
manufactured by Saint-Gobain Sully (SGS)
and the part number and serial number are
specified in Appendix 02 of the applicable
Airbus service information specified in
paragraph (j)(1), (j)(2), or (j)(3) of this AD, or
if the manufacturer or part number or serial
number is not identifiable: Within 6 months
after the effective date of this AD, replace the
affected LH and/or RH windshield with a
serviceable part, in accordance with the
Accomplishment Instructions of the
applicable Airbus service information
specified in paragraph (j)(1), (j)(2), or (j)(3) of
this AD.
(1) For Model A330–201, –202, –203, –223,
–223F, –243, –243F, –301, –302, –303, –321,
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
–322, –323, –341, –342, and –343 airplanes:
Airbus Service Bulletin A330–56–3009,
Revision 03, including Appendixes 01 and
02, dated August 1, 2013.
(2) For Model A340–211, –212, –213, –311,
–312, and –313 airplanes: Airbus Service
Bulletin A340–56–4008, Revision 02,
including Appendixes 01 and 02, dated
August 1, 2013.
(3) For Model A340–541 and –642
airplanes: Airbus Service Bulletin A340–56–
5002, Revision 02, including Appendixes 01
and 02, dated August 1, 2013.
(k) Definition of Serviceable Windshield
For the purposes of this AD, a serviceable
windshield is a windshield not identified in
Appendix 01 of the applicable Airbus service
information as specified in paragraphs (j)(1),
(j)(2), or (j)(3) of this AD; or it is specified in
Appendix 01 but has a suffix ‘‘U’’ added to
the serial number on the identification plate.
(l) Parts Installation Limitations
As of the effective date of this AD, no
person may install, on any airplane, an
affected windshield from SGS having a part
number and serial number identified in
Appendix 01 of the applicable Airbus service
information as specified in paragraph (l)(1),
(l)(2), or (l)(3) of this AD, unless a suffix ‘‘U’’
has been added on the serial number
identification plate.
(1) For Model A330–201, –202, –203, –223,
–223F, –243, –243F, –301, –302, –303, –321,
–322, –323, –341, –342, and –343 airplanes:
Airbus Service Bulletin A330–56–3009,
Revision 03, including Appendixes 01 and
02, dated August 1, 2013.
(2) For Model A340–211, –212, –213, –311,
–312, and –313 airplanes: Airbus Service
Bulletin A340–56–4008, Revision 02,
including Appendix 01 and 02, dated August
1, 2013.
(3) For Model A340–541 and –642
airplanes: Airbus Service Bulletin A340–56–
5002, Revision 02, including Appendixes 01
and 02, dated August 1, 2013.
(m) 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 the applicable
Airbus service information specified in
paragraphs (m)(1) through (m)(4) of this AD,
provided that the actions were accomplished
on the airplane, and no replacement
windshield has been installed with a part
number and serial number identified in
Appendix 02 of the applicable Airbus service
information as specified in paragraphs (j)(1)
through (j)(3) of this AD.
(1) Airbus Service Bulletin A330–56–3009,
dated May 4, 2010 (for Model A330–201,
–202, –203, –223, –223F, –243, –243F, –301,
–302, –303, –321, –322, –323, –341, –342,
and –343 airplanes), which is not
incorporated by reference in this AD.
(2) Airbus Service Bulletin A330–56–3009,
Revision 01, dated January 27, 2011 (for
Model A330–201, –202, –203, –223, –223F,
–243, –243F, –301, –302, –303, –321, –322,
–323, –341, –342, and –343 airplanes), which
is not incorporated by reference in this AD.
(3) Airbus Service Bulletin A340–56–4008,
dated May 4, 2010 (for Model A340–211,
E:\FR\FM\06NOR1.SGM
06NOR1
Federal Register / Vol. 79, No. 215 / Thursday, November 6, 2014 / Rules and Regulations
–212, –213, –311, –312, and –313 airplanes),
which is not incorporated by reference in this
AD.
(4) Airbus Service Bulletin A340–56–5002,
dated May 4, 2010 (for Model A340–541 and
–642 airplanes), which is not incorporated by
reference in this AD.
(n) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, FAA, Transport Airplane
Directorate, 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: 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) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
rmajette on DSK2TPTVN1PROD with RULES
(o) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0256, dated
October 21, 2013, for related information.
You may examine the MCAI in the AD
docket on the Internet at https://www.
regulations.gov/#!documentDetail;D=FAA2014-0192-0002.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (p)(3) and (p)(4) of this AD.
VerDate Sep<11>2014
15:26 Nov 05, 2014
Jkt 235001
(iii) Airbus Service Bulletin A340–56–
5002, Revision 02, including Appendixes 01
and 02, dated August 1, 2013.
(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 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.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 4, 1996 (61 FR 39860,
July 31, 1996).
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, 3855
Lakewood Boulevard, MC D800–0019,
Long Beach, CA 90846–0001; telephone
206–544–5000, extension 2; fax 206–
766–5683; Internet https://
www.myboeingfleet.com. You may view
this 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.
Issued in Renton, Washington, on
September 24, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
Examining the AD Docket
[FR Doc. 2014–24964 Filed 11–5–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0232; Directorate
Identifier 2013–NM–100–AD; Amendment
39–18010; AD 2014–22–05]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model DC–9–10,
DC–9–20, DC–9–30, DC–9–40, and DC–
9–50 series airplanes. This AD was
prompted by an evaluation by the
design approval holder (DAH)
indicating that the bulkhead dome tees,
which connect the bulkhead web to the
fuselage, are subject to widespread
fatigue damage (WFD). This AD requires
repetitive inspections of the improved
ventral aft pressure bulkhead tees, and
replacement if necessary. We are issuing
this AD to detect and correct fatigue
cracking of the bulkhead dome tees,
which could result in reduced structural
integrity and rapid decompression of
the airplane.
DATES: This AD is effective December
11, 2014.
SUMMARY:
(p) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A330–56–3009,
Revision 03, including Appendixes 01 and
02, dated August 1, 2013.
(ii) Airbus Service Bulletin A340–56–4008,
Revision 02, including Appendix 01 and 02,
dated August 1, 2013.
65891
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Frm 00019
Fmt 4700
Sfmt 4700
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0232; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Eric
Schrieber, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office,
3960 Paramount Boulevard, Lakewood,
CA 90712–4137; phone: 562–627–5348;
fax: 562–627–5210; email:
eric.schrieber@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model DC–9–10, DC–9–20, DC–9–30,
DC–9–40, and DC–9–50 series airplanes.
The NPRM published in the Federal
Register on April 17, 2014 (79 FR
21655). The NPRM was prompted by an
evaluation by the DAH indicating that
the bulkhead dome tees, which connect
the bulkhead web to the fuselage, are
subject to WFD. The NPRM proposed to
require repetitive inspections of the
improved ventral aft pressure bulkhead
tees, and replacement if necessary. We
are issuing this AD to detect and correct
E:\FR\FM\06NOR1.SGM
06NOR1
]]>Agencies
[Federal Register Volume 79, Number 215 (Thursday, November 6, 2014)]
[Rules and Regulations]
[Pages 65887-65891]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-24964]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0192; Directorate Identifier 2013-NM-221-AD;
Amendment 39-17992; AD 2014-20-19]
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) 2013-10-06,
for all Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200,
A340-300, A340-500, and A340-600 series airplanes. AD 2013-10-06
required an inspection to identify the installed windshields, and
replacement of any affected windshield. This new AD requires expanding
the inspection area to 15 additional windshields' serial numbers. This
AD was prompted by several reports of a burning smell and/or smoke in
the cockpit during cruise phase, leading in some cases, to
[[Page 65888]]
diversion to alternate airports. We are issuing this AD to prevent
significantly increased workload for the flightcrew, which could, under
some flight phases and/or circumstances, constitute an unsafe
condition.
DATES: This AD becomes effective December 11, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of December 11,
2014.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0192; or in person at the
Docket Management Facility, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC.
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. You may view this 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: 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.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2013-10-06, Amendment 39-17459 (78 FR 32347,
May 30, 2013). AD 2013-10-06 applied to all Airbus Model A330-200
Freighter, A330-200, A330-300, A340-200, A340-300, A340-500, and A340-
600 series airplanes. The NPRM published in the Federal Register on
April 9, 2014 (79 FR 19548).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2013-0256, dated October 21, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A330-201, -202, -203, -223, -223F, -243, -243F, -301, -302, -303, -321,
-322, -323, -341, -342, and -343 airplanes; and Model A340-211, -212, -
213, -311, -312, -313, -541, and -642 airplanes. The MCAI states:
Several operators reported cases of burning smell and/or smoke
in the cockpit during cruise phase leading in some cases to
diversion. Findings showed that the cause of these events is the
burning of the Saint-Gobain Sully (SGS) windshield connector
terminal block.
This condition, if not corrected, could significantly increase
the flight crew workload which would, under some flight phases and/
or circumstances constitute an unsafe condition.
To address this unsafe condition, Airbus published 3 different
Service Bulletins (SB) and EASA issued AD 2011-0242 [https://ad.easa.europa.eu/blob/easa_ad_2011_0242_Correction_superseded.pdf/AD_2011-0242_1] (later corrected) which required the identification
of the installed windshields and replacement of the affected part.
Since issuance of that [EASA] AD, a new occurrence in service
led Airbus to identify a new batch of affected parts.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2011-0242 [https://ad.easa.europa.eu/blob/easa_ad_2011_0242_Correction_superseded.pdf/AD_2011-0242_1], which
is superseded, and requires identification and replacement of the
additionally identified windshields.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0192-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (79 FR 19548, April 9,
2014) or on the determination of the cost to the public.
``Contacting the Manufacturer'' Paragraph in This AD
Since late 2006, we have included a standard paragraph titled
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD
based on a foreign authority's AD.
We have become aware that some operators have misunderstood or
misinterpreted the Airworthy Product paragraph to allow the owner/
operator to use messages provided by the manufacturer as approval of
deviations during the accomplishment of an AD-mandated action. The
Airworthy Product paragraph does not approve messages or other
information provided by the manufacturer for deviations to the
requirements of the AD-mandated actions. The Airworthy Product
paragraph only addresses the requirement to contact the manufacturer
for corrective actions for the identified unsafe condition and does not
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request
the approval for an alternative method of compliance to the AD-required
actions using the procedures found in 14 CFR 39.19.
To address this misunderstanding and misinterpretation of the
Airworthy Product paragraph, we have changed the paragraph and retitled
it ``Contacting the Manufacturer.'' This paragraph now clarifies that
for any requirement in this AD to obtain corrective actions from a
manufacturer, the actions must be accomplished using a method approved
by the FAA, the EASA, or Airbus's EASA Design Organization Approval
(DOA).
The Contacting the Manufacturer paragraph also clarifies that, if
approved by the DOA, the approval must include the DOA-authorized
signature. The DOA signature indicates that the data and information
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or
other information.
This clarification does not remove flexibility previously afforded
by the Airworthy Product paragraph. Consistent with long-standing FAA
policy, such flexibility was never intended for required actions. This
is also consistent with the recommendation of the Airworthiness
Directive Implementation Aviation Rulemaking Committee to increase
flexibility in complying with ADs by identifying those actions in
manufacturers' service instructions that are ``Required for
Compliance'' with ADs. We continue to work with manufacturers to
implement this recommendation. But once we determine that an action is
required, any deviation from the requirement must be approved as an
alternative method of compliance.
We also have decided not to include a generic reference to either
the ``delegated agent'' or ``design approval holder (DAH) with State of
Design Authority design organization approval,'' but instead we have
provided the specific delegation approval granted by the State of
Design Authority for the DAH throughout this AD.
[[Page 65889]]
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting this AD with the changes described
previously and minor editorial changes. We have determined that these
minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 19548, April 9, 2014) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 19548, April 9, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 60 airplanes of U.S. registry.
The actions required by AD 2013-10-06, Amendment 39-17459 (78 FR
32347, May 30, 2013), and retained in this AD take about 2 work-hours
per product, at an average labor rate of $85 per work-hour. Required
parts cost about $0 per product. Based on these figures, the estimated
cost of the actions that were required by AD 2013-10-06 is $170 per
product.
We also estimate that it would take about 2 work-hours per product
to comply with the basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts would cost about $0 per
product. Based on these figures, we estimate the cost of this AD on
U.S. operators to be $10,200, or $170 per product.
In addition, we estimate that any necessary follow-on actions would
take about 10 work-hours and require parts costing $0, for a cost of
$850 per product. We have no way of determining the number of aircraft
that might need this action.
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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0192; or in person at the
Docket Management Facility between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD docket contains this AD, the
regulatory evaluation, any comments received, and other information.
The street address for the Docket 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)
2013-10-06, Amendment 39-17459 (78 FR 32347, May 30, 2013), and adding
the following new AD:
2014-20-19 Airbus: Amendment 39-17992. Docket No. FAA-2014-0192;
Directorate Identifier 2013-NM-221-AD.
(a) Effective Date
This AD becomes effective December 11, 2014.
(b) Affected ADs
This AD supersedes AD 2013-10-06, Amendment 39-17459 (78 FR
32347, May 30, 2013).
(c) Applicability
This AD applies to all airplanes identified in paragraphs (c)(1)
and (c)(2) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F,
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
(2) Airbus Model A340-211, -212, -213, -311, -312, -313, -541,
and -642 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 56, Windows.
(e) Reason
This AD was prompted by several reports of a burning smell and/
or smoke in the cockpit during cruise phase, leading in some cases,
to diversion to alternate airports. We are issuing this AD to
prevent significantly increased workload for the flightcrew, which
could, under some flight phases and/or circumstances, constitute an
unsafe condition.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection With Revised Service Information
This paragraph restates the requirements of paragraph (g) of AD
2013-10-06, Amendment 39-17459 (78 FR 32347, May 30, 2013), with
revised service information. Within 1,200 flight hours after July 5,
2013 (the effective date of AD 2013-10-06), inspect to identify the
manufacturer, the part number, and the serial number of the left-
hand (LH) and right-hand (RH) windshields installed on the airplane,
in accordance with the Accomplishment Instructions of the applicable
Airbus service information specified in paragraph (g)(1), (g)(2), or
(g)(3) of this AD. A review of airplane delivery or
[[Page 65890]]
maintenance records is acceptable in lieu of this inspection if the
manufacturer, part number, and serial number of the installed
windshields can be conclusively determined from that review.
(1) For Model A330-201, -202, -203, -223, -223F, -243, -243F, -
301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes:
Airbus Service Bulletin A330-56-3009, Revision 02, including
Appendix 01, dated February 8, 2012; or Airbus Service Bulletin
A330-56-3009, Revision 03, including Appendixes 01 and 02, dated
August 1, 2013. As of the effective date of this AD, use only Airbus
Service Bulletin A330-56-3009, Revision 03, including Appendixes 01
and 02, dated August 1, 2013, to do the actions required by
paragraph (g) of this AD.
(2) For Model A340-211, -212, -213, -311, -312, and -313
airplanes: Airbus Service Bulletin A340-56-4008, Revision 01,
including Appendix 01, dated February 8, 2012; or Airbus Service
Bulletin A340-56-4008, Revision 02, including Appendixes 01 and 02,
dated August 1, 2013. As of the effective date of this AD, use only
Airbus Service Bulletin A340-56-4008, Revision 02, including
Appendixes 01 and 02, dated August 1, 2013, to do the actions
required by paragraph (g) of this AD.
(3) For Model A340-541 and -642 airplanes: Airbus Service
Bulletin A340-56-5002, Revision 01, including Appendix 01, dated
February 8, 2012; or Airbus Service Bulletin A340-56-5002, Revision
02, including Appendixes 01 and 02, dated August 1, 2013. As of the
effective date of this AD, use only Airbus Service Bulletin A340-56-
5002, Revision 02, including Appendixes 01 and 02, dated August 1,
2013, to do the actions required by paragraph (g) of this AD.
(h) Retained Replacement With Revised Service Information
This paragraph restates the requirements of paragraph (h) of AD
2013-10-06, Amendment 39-17459 (78 FR 32347, May 30, 2013), with
revised service information. If it is found, during the inspection
required by paragraph (g) of this AD, that any installed LH or RH
windshield was manufactured by Saint-Gobain Sully (SGS) and the part
number and serial number are specified in the applicable Airbus
service information specified in paragraph (g)(1), (g)(2), or (g)(3)
of this AD: Within 9 months or 1,200 flight hours after July 5, 2013
(the effective date of AD 2013-10-06), whichever occurs first,
replace all affected LH and RH windshields, in accordance with the
Accomplishment Instructions of the applicable Airbus service
information specified in paragraph (h)(1), (h)(2), or (h)(3) of this
AD.
(1) For Model A330-201, -202, -203, -223, -223F, -243, -243F, -
301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes:
Airbus Service Bulletin A330-56-3009, Revision 02, including
Appendix 01, dated February 8, 2012; or Airbus Service Bulletin
A330-56-3009, Revision 03, including Appendixes 01 and 02, dated
August 1, 2013. As of the effective date of this AD, use only Airbus
Service Bulletin A330-56-3009, Revision 03, including Appendixes 01
and 02, dated August 1, 2013, to do the actions required by
paragraph (h) of this AD.
(2) For Model A340-211, -212, -213, -311, -312, and -313
airplanes: Airbus Service Bulletin A340-56-4008, Revision 01,
including Appendix 01, dated February 8, 2012; or Airbus Service
Bulletin A340-56-4008, Revision 02, including Appendixes 01 and 02,
dated August 1, 2013. As of the effective date of this AD, use only
Airbus Service Bulletin A340-56-4008, Revision 02, including
Appendixes 01 and 02, dated August 1, 2013, to do the actions
required by paragraph (h) of this AD.
(3) For Model A340-541 and -642 airplanes: Airbus Service
Bulletin A340-56-5002, Revision 01, including Appendix 01, dated
February 8, 2012; or Airbus Service Bulletin A340-56-5002, Revision
02, including Appendixes 01 and 02, dated August 1, 2013. As of the
effective date of this AD, use only Airbus Service Bulletin A340-56-
5002, Revision 02, including Appendixes 01 and 02, dated August 1,
2013, to do the actions required by paragraph (h) of this AD.
(i) New Requirement of This AD: Inspection
Within 6 months after the effective date of this AD, inspect to
identify the manufacturer, the part number, and the serial number of
the LH and RH windshields installed on the airplane, in accordance
with the Accomplishment Instructions of the applicable Airbus
service information specified in paragraph (i)(1), (i)(2), or (i)(3)
of this AD. A review of airplane delivery or maintenance records is
acceptable in lieu of this inspection if the manufacturer, part
number, and serial number of the installed windshields can be
conclusively determined from that review.
(1) For Model A330-201, -202, -203, -223, -223F, -243, -243F, -
301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes:
Airbus Service Bulletin A330-56-3009, Revision 03, including
Appendixes 01 and 02, dated August 1, 2013.
(2) For Model A340-211, -212, -213, -311, -312, and -313
airplanes: Airbus Service Bulletin A340-56-4008, Revision 02,
including Appendixes 01 and 02, dated August 1, 2013.
(3) For Model A340-541 and -642 airplanes: Airbus Service
Bulletin A340-56-5002, Revision 02, including Appendixes 01 and 02,
dated August 1, 2013.
(j) New Requirement of This AD: Replacement
If it is found, during the inspection required by paragraph (i)
of this AD, that any installed LH or RH windshield was manufactured
by Saint-Gobain Sully (SGS) and the part number and serial number
are specified in Appendix 02 of the applicable Airbus service
information specified in paragraph (j)(1), (j)(2), or (j)(3) of this
AD, or if the manufacturer or part number or serial number is not
identifiable: Within 6 months after the effective date of this AD,
replace the affected LH and/or RH windshield with a serviceable
part, in accordance with the Accomplishment Instructions of the
applicable Airbus service information specified in paragraph (j)(1),
(j)(2), or (j)(3) of this AD.
(1) For Model A330-201, -202, -203, -223, -223F, -243, -243F, -
301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes:
Airbus Service Bulletin A330-56-3009, Revision 03, including
Appendixes 01 and 02, dated August 1, 2013.
(2) For Model A340-211, -212, -213, -311, -312, and -313
airplanes: Airbus Service Bulletin A340-56-4008, Revision 02,
including Appendixes 01 and 02, dated August 1, 2013.
(3) For Model A340-541 and -642 airplanes: Airbus Service
Bulletin A340-56-5002, Revision 02, including Appendixes 01 and 02,
dated August 1, 2013.
(k) Definition of Serviceable Windshield
For the purposes of this AD, a serviceable windshield is a
windshield not identified in Appendix 01 of the applicable Airbus
service information as specified in paragraphs (j)(1), (j)(2), or
(j)(3) of this AD; or it is specified in Appendix 01 but has a
suffix ``U'' added to the serial number on the identification plate.
(l) Parts Installation Limitations
As of the effective date of this AD, no person may install, on
any airplane, an affected windshield from SGS having a part number
and serial number identified in Appendix 01 of the applicable Airbus
service information as specified in paragraph (l)(1), (l)(2), or
(l)(3) of this AD, unless a suffix ``U'' has been added on the
serial number identification plate.
(1) For Model A330-201, -202, -203, -223, -223F, -243, -243F, -
301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes:
Airbus Service Bulletin A330-56-3009, Revision 03, including
Appendixes 01 and 02, dated August 1, 2013.
(2) For Model A340-211, -212, -213, -311, -312, and -313
airplanes: Airbus Service Bulletin A340-56-4008, Revision 02,
including Appendix 01 and 02, dated August 1, 2013.
(3) For Model A340-541 and -642 airplanes: Airbus Service
Bulletin A340-56-5002, Revision 02, including Appendixes 01 and 02,
dated August 1, 2013.
(m) 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 the applicable Airbus
service information specified in paragraphs (m)(1) through (m)(4) of
this AD, provided that the actions were accomplished on the
airplane, and no replacement windshield has been installed with a
part number and serial number identified in Appendix 02 of the
applicable Airbus service information as specified in paragraphs
(j)(1) through (j)(3) of this AD.
(1) Airbus Service Bulletin A330-56-3009, dated May 4, 2010 (for
Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes), which is not
incorporated by reference in this AD.
(2) Airbus Service Bulletin A330-56-3009, Revision 01, dated
January 27, 2011 (for Model A330-201, -202, -203, -223, -223F, -243,
-243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343
airplanes), which is not incorporated by reference in this AD.
(3) Airbus Service Bulletin A340-56-4008, dated May 4, 2010 (for
Model A340-211,
[[Page 65891]]
-212, -213, -311, -312, and -313 airplanes), which is not
incorporated by reference in this AD.
(4) Airbus Service Bulletin A340-56-5002, dated May 4, 2010 (for
Model A340-541 and -642 airplanes), which is not incorporated by
reference in this AD.
(n) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
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: 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) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the European Aviation Safety Agency
(EASA); or Airbus's EASA Design Organization Approval (DOA). If
approved by the DOA, the approval must include the DOA-authorized
signature.
(o) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2013-0256, dated October 21,
2013, for related information. You may examine the MCAI in the AD
docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0192-0002.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (p)(3) and (p)(4) of this AD.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A330-56-3009, Revision 03, including
Appendixes 01 and 02, dated August 1, 2013.
(ii) Airbus Service Bulletin A340-56-4008, Revision 02,
including Appendix 01 and 02, dated August 1, 2013.
(iii) Airbus Service Bulletin A340-56-5002, Revision 02,
including Appendixes 01 and 02, dated August 1, 2013.
(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 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 September 24, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-24964 Filed 11-5-14; 8:45 am]
BILLING CODE 4910-13-P
