Airworthiness Directives; Airbus Airplanes, 8513-8516 [2015-02697]
Download as PDF
<![CDATA[
Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations
(7) For Model A340–541 and –642
airplanes, repeat the inspections at intervals
not to exceed 100 flight cycles or 500 flight
hours, whichever occurs first.
mstockstill on DSK4VPTVN1PROD with RULES
(h) Corrective Action
If any cracking is found during any
inspection required by paragraph (g) of this
AD, before further flight, replace the cracked
MLG support rib 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. Replacement of
an MLG support rib does not terminate the
repetitive inspections required by paragraph
(g) of this AD.
(i) Credit for Previous Actions
This paragraph provides credit for the
corresponding actions required by paragraph
(g) of this AD, if those actions were
performed before the effective date of this AD
using the applicable service bulletin
identified in paragraphs (i)(1) through (i)(12)
of this AD.
(1) Airbus Service Bulletin A330–57A3096,
dated December 5, 2006, which was
incorporated by reference in AD 2007–03–04,
Amendment 39–14915 (72 FR 4416, January
31, 2007), on February 15, 2007.
(2) Airbus Service Bulletin A330–57A3096,
Revision 01, dated April 18, 2007, which is
not incorporated by reference in this AD.
(3) Airbus Service Bulletin A330–57–3096,
excluding appendix 01, Revision 02, dated
August 13, 2007, which was incorporated by
reference in AD 2007–22–10, Amendment
39–15246 (72 FR 61796, November 1, 2007;
corrected November 16, 2007 (72 FR 64532)),
on November 16, 2007.
(4) Airbus Service Bulletin A330–57–3096,
Revision 03, dated October 24, 2012, which
is not incorporated by reference in this AD.
(5) Airbus Service Bulletin A330–57–3096,
Revision 04, dated February 6, 2013, which
is not incorporated by reference in this AD.
(6) Airbus Service Bulletin A340–57A4104,
dated December 5, 2006, which was
incorporated by reference in AD 2007–03–04,
Amendment 39–14915 (72 FR 4416, January
31, 2007), on February 15, 2007.
(7) Airbus Service Bulletin A340–57–4104,
Revision 01, dated August 13, 2007, which is
not incorporated by reference in this AD.
(8) Airbus Service Bulletin A340–57–4104,
excluding appendix 01, Revision 02, dated
September 5, 2007, which was incorporated
by reference in AD 2007–22–10, Amendment
39–15246 (72 FR 61796, November 1, 2007;
corrected November 16, 2007 (72 FR 64532)),
on November 16, 2007.
(9) Airbus Service Bulletin A340–57–4104,
Revision 03, dated October 24, 2012, which
is not incorporated by reference in this AD.
(10) Airbus Service Bulletin A340–
57A5009, dated December 5, 2006, which
was incorporated by reference in AD 2007–
03–04, Amendment 39–14915 (72 FR 4416,
January 31, 2007), on February 15, 2007.
(11) Airbus Service Bulletin A340–57–
5009, excluding appendix 01, Revision 01,
dated August 13, 2007, which was
VerDate Sep<11>2014
17:46 Feb 17, 2015
Jkt 235001
incorporated by reference in AD 2007–22–10,
Amendment 39–15246 (72 FR 61796,
November 1, 2007; corrected November 16,
2007 (72 FR 64532)), on November 16, 2007.
(12) Airbus Service Bulletin A340–57–
5009, Revision 02, dated October 24, 2012,
which is not incorporated by reference in this
AD.
(j) 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:
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.
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0271, dated
November 14, 2013, for related information.
You may examine the MCAI in the AD
docket on the Internet at https://
www.regulations.gov/#!documentDetail;D=
FAA-2014-0620-0004.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (l)(3) and (l)(4) of this AD.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A330–57–3096,
Revision 05, dated October 17, 2013.
(ii) Airbus Service Bulletin A340–57–4104,
Revision 04, dated October 17, 2013.
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
8513
(iii) Airbus Service Bulletin A340–57–
5009, Revision 03, dated October 17, 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.
Issued in Renton, Washington, on February
2, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–02672 Filed 2–17–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0484; Directorate
Identifier 2013–NM–245–AD; Amendment
39–18101; AD 2015–03–05]
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) 2012–09–
07 for certain Airbus Model A319–111,
–112, and –132 airplanes; Model A320–
111, –211, –212, –214, and –232
airplanes; and Model A321–111, –211,
–212, and –231 airplanes. AD 2012–09–
07 required an electrical bonding test
between the gravity fill re-fuel adaptor
and the top skin panels on the wings;
and, if necessary, an inspection for
corrosion of the component interface
and adjacent area; and repairing the
gravity fuel adaptor if necessary. This
new AD adds airplanes to the
applicability and requires inspecting
those airplanes to determine if a repair
was done, and doing the electrical
bonding test and corrective action if
necessary. This AD was prompted by a
determination that more airplanes are
SUMMARY:
E:\FR\FM\18FER1.SGM
18FER1
8514
Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations
mstockstill on DSK4VPTVN1PROD with RULES
subject to the identified unsafe
condition. We are issuing this AD to
detect and correct corrosion and
improper bonding, which, in
combination with a lightning strike in
this area, could create a source of
ignition in a fuel tank, resulting in a fire
or explosion and consequent loss of the
airplane.
DATES: This AD becomes effective
March 25, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 25, 2015.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/#!docketDetail;D=
FAA-2014-0484; 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, 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 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. It is also available on the Internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2014–0484.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012–09–07,
Amendment 39–17042 (77 FR 28238,
May 14, 2012). AD 2012–09–07 applied
to certain Airbus Model A319–111,
–112, and –132 airplanes; Model A320–
111, –211, –212, –214, and –232
airplanes; and Model A321–111, –211,
–212, and –231 airplanes. The NPRM
published in the Federal Register on
July 30, 2014 (79 FR 44144).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
VerDate Sep<11>2014
17:46 Feb 17, 2015
Jkt 235001
Directive 2013–0277R1, dated December
4, 2013 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A318–111, –112, –121, and –122
airplanes; Model A319–111, –112, –113,
–114, –115, –131, –132, and –133
airplanes; Model A320–111, –211, –212,
–214, –231, –232, and –233 airplanes;
and Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
The MCAI states:
Cases of corrosion findings were reported
on the overwing refueling aperture (used to
fill the fuel tank by gravity) on the wing top
skin. The reported corrosion was on the
mating surface of the aperture flange,
underneath the refuel adaptor. Corrosion
findings have been repaired on a case by case
basis in accordance with approved data.
For certain aeroplanes, the repair provided
by Airbus contained instructions to apply
primer coating on the mating surface. Since
doing those repairs, it has been found that
this primer coating may prevent proper
electrical bonding provision between the
overwing refueling cap adaptor and the wing
skin.
This condition, if not detected and
corrected, could, in combination with a
lightning strike in this area, create a source
of ignition in a fuel tank, possibly resulting
in a fire or explosion and consequent loss of
the aeroplane.
To address this potential unsafe condition,
EASA issued AD 2011–0034 [https://
ad.easa.europa.eu/blob/easa_ad_2011_
0034.pdf/AD_2011-0034] to require a onetime electrical bonding check between the
gravity fill re-fuel adaptor and the top skin
panels on the affected aeroplanes (identified
by MSN [manufacturer serial number] in the
applicability section of that [EASA] AD) and,
in case of findings, the accomplishment of
applicable corrective actions.
Since that [EASA] AD was issued, EASA
has been made aware that some operators
may inadvertently have applied an Airbus
repair, approved for only one aeroplane
MSN, to other aeroplanes, without requesting
a revision of the repair to add aeroplanes, or
to notify Airbus of such action(s).
Consequently, the condition addressed by
EASA AD 2011–0034 could affect more
aeroplanes than initially determined.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2011–0034, which is superseded, and
expands the Applicability to all A320 family
aeroplane Models, all MSN.
This [EASA] AD has been revised to amend
and clarify paragraph (3), and to correct an
error in the Type/Model designations on page
1, where the A318 was inadvertently omitted.
For the newly added airplanes, required
actions include inspecting for the
presence of a corrosion repair on an
overwing refueling aperture, and doing
the electrical bonding test and
applicable corrective actions if a repair
has been installed. You may examine
the MCAI in the AD docket on the
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
Internet at https://www.regulations.gov/#
!documentDetail;D=FAA-2014-04840002.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the NPRM (79 FR 44144,
July 30, 2014) and the FAA’s response
to the comment.
Request To Include Revised Service
Information
United Airlines (UAL) asked that we
include a statement in the NPRM (79 FR
44144, July 30, 2014), which allows
performing the required actions in
accordance with the instructions of
Airbus Service Bulletin A320–57–1152,
Revision 01, dated December 19, 2013.
UAL stated that the revised service
information specifies the same method
of inspection as specified in Airbus
Service Bulletin A320–57–1152, dated
June 14, 2010. UAL further stated that
Revision 01 of this service bulletin also
provides operators with updated repair
instructions that were not available in
the original issue of this service
bulletin.
We agree with the commenter’s
request. Since issuance of the NPRM (79
FR 44144, July 30, 2014), Airbus has
issued Service Bulletin A320–57–1152,
Revision 01, dated December 19, 2013.
This revision states that no additional
work is necessary on airplanes changed
in accordance with Airbus Service
Bulletin A320–57–1152, dated June 14,
2010, which was specified as the
appropriate source of service
information in the NPRM (79 FR 44144,
July 30, 2014).
We have changed paragraph (g) of this
AD to specify Airbus Service Bulletin
A320–57–1152, Revision 01, dated
December 19, 2013. We have also added
a new paragraph (h) to this AD to give
credit for actions done before the
effective date of this AD using Airbus
Service Bulletin A320–57–1152, dated
June 14, 2010, and redesignated
subsequent paragraphs accordingly.
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
44144, July 30, 2014) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
E:\FR\FM\18FER1.SGM
18FER1
Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations
proposed in the NPRM (79 FR 44144,
July 30, 2014).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–57–1152, Revision 01, dated
December 19, 2013. The service
information describes procedures for
inspecting certain airplanes to
determine if a repair was done, and
doing an electrical bonding test and
corrective action if necessary. This
service information is reasonably
available; see ADDRESSES for ways to
access this service information.
mstockstill on DSK4VPTVN1PROD with RULES
Costs of Compliance
We estimate that this AD affects 851
airplanes of U.S. registry.
The actions required by AD 2012–09–
07, Amendment 39–17042 (77 FR
28238, May 14, 2012), and retained in
this AD take about 2 work-hours per
product, at an average labor rate of $85
per work-hour. Based on these figures,
the estimated cost of the actions that
were required by AD 2012–09–07 is
$170 per product.
We also estimate that it takes 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 cost about $0 per
product. Based on these figures, we
estimate the cost of this AD on U.S.
operators to be $144,670, or $170 per
product.
In addition, we estimate that any
necessary follow-on actions will take
about 11 work-hours, for a cost of $935
per product. We have no way of
determining the number of aircraft that
might need these actions.
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
VerDate Sep<11>2014
17:46 Feb 17, 2015
Jkt 235001
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-2014-0484; 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
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)
2012–09–07, Amendment 39–17042 (77
FR 28238, May 14, 2012), and adding
the following new AD:
■
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
8515
2015–03–05 Airbus: Amendment 39–18101.
Docket No. FAA–2014–0484; Directorate
Identifier 2013–NM–245–AD.
(a) Effective Date
This AD becomes effective March 25, 2015.
(b) Affected ADs
This AD replaces AD 2012–09–07,
Amendment 39–17042 (77 FR 28238, May 14,
2012).
(c) Applicability
(1) This AD applies to Airbus Model A318–
111, –112, –121, and –122 airplanes; Model
A319–111, –112, –113, –114, –115, –131,
–132, and –133 airplanes; Model A320–111,
–211, –212, –214, –231, –232, and –233
airplanes; and Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes;
certificated in any category; all manufacturer
serial numbers, except airplanes identified in
paragraph (c)(2) of this AD.
(2) Airplanes that have been delivered from
production with Airbus Modification 38209
(Removal of the Outer Wing Refueling
Aperture) incorporated, and without Airbus
Modification 38206 (Re-introduction of the
Outer Wing Refueling Aperture)
incorporated, are not affected by the
requirements of this AD.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by a determination
that more airplanes are subject to the
identified unsafe condition. We are issuing
this AD to detect and correct corrosion and
improper bonding, which, in combination
with a lightning strike in this area, could
create a source of ignition in a fuel tank,
resulting in a fire or explosion and
consequent loss of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Electrical Bonding Test, and
General Visual Inspection if Necessary, With
Changes
This paragraph restates the requirements of
paragraph (g) of AD 2012–09–07,
Amendment 39–17042 (77 FR 28238, May 14,
2012), with revised repair approval language
and revised service information. For Model
A319–111, –112, and –132 airplanes; Model
A320–111, –211, –212, –214 and –232
airplanes; and Model A321–111, –211, –212,
and –231 airplanes; certificated in any
category; having manufacturer serial numbers
0039, 0078, 0109, 0118, 0120, 0153, 0174,
0187, 0203, 0215, 0218, 0226, 0227, 0228,
0236, 0237, 0269, 0270, 0278, 0285, 0286,
0287, 0288, 0294, 0301, 0337, 0377, 0462,
0463, 0464, 0465, 0520, 0523, 0528, 0876,
0888, 0921, 0935, 0974, 1014, 1102, 1130,
1160, 1162, 1177, 1215, 1250, 1287, 1336,
1388, 1404, 1444, 1449, 1476, 1505, 1524,
1564, 1605, 1616, 1622, 1640, 1645, 1658,
1677, 1691, 1729, and 1905: Within 24
months after June 18, 2012 (the effective date
of AD 2012–09–07), do an electrical bonding
E:\FR\FM\18FER1.SGM
18FER1
8516
Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations
test to check for bonding between the re-fuel
adaptor of the gravity fill and the top skin
panels on the left-hand and right-hand wings,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
57–1152, Revision 01, dated December 19,
2013.
(1) If the resistance value is 10 milliohms
or less at the left-hand and right-hand wing,
no further action is required by this
paragraph.
(2) If the resistance value is greater than 10
milliohms at the left-hand or right-hand
wing, before further flight, do a general visual
inspection for corrosion of the component
interface and adjacent area, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–57–1152,
Revision 01, dated December 19, 2013. If any
corrosion is found during the inspection,
before further flight, repair the gravity fill
fuel adaptor, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–57–1152, Revision 01,
dated December 19, 2013; except where
Airbus Service Bulletin A320–57–1152,
Revision 01, dated December 19, 2013,
specifies to contact Airbus, before further
flight, repair 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 DOAauthorized signature.
mstockstill on DSK4VPTVN1PROD with RULES
(h) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using Airbus Service
Bulletin A320–57–1152, dated June 14, 2010,
which was incorporated by reference in AD
2012–09–07, Amendment 39–17042 (77 FR
28238, May 14, 2012).
(i) New Requirement of This AD:
Maintenance Check/Electrical Bonding Test
and Corrective Action if Necessary
For airplanes other than those identified in
paragraph (g) of this AD: Within 24 months
after the effective date of this AD, determine
whether a corrosion repair has been done on
an overwing refueling aperture, whereby a
primer coating has been applied on the
mating surface of the aperture flange. A
review of the airplane maintenance records is
acceptable to make this determination,
provided that whether a primer coat was
applied can be conclusively determined from
that review.
(1) If it is determined that a primer coating
was applied on the mating surface of the
aperture flange; or if a determination cannot
be made, or the outcome is inconclusive:
Within 24 months after the effective date of
this AD do the electrical bonding test
specified in paragraph (g) of this AD, and
before further flight, do all applicable actions
specified in paragraph (g)(2) of this AD.
(2) If it is determined that a corrosion
repair has not been done, and a primer
coating has not been applied on the mating
surface of the aperture flange since first entry
into service, no further action is required by
this paragraph.
VerDate Sep<11>2014
17:46 Feb 17, 2015
Jkt 235001
(j) Corrosion Repair Provision
As of the effective date of this AD, any
corrosion repair done on an overwing
refueling aperture on any airplane must
comply with the repair requirements of
paragraph (g)(2) of this AD.
(k) 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:
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.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov.
(i) 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.
(ii) AMOCs approved previously for AD
2012–09–07, Amendment 39–17042 (77 FR
28238, May 14, 2012), are approved as
AMOCs for the corresponding provisions of
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
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0277R1, dated
December 4, 2013, for related information.
This MCAI may be found in the AD docket
on the Internet at
https://www.regulations.gov/#!document
Detail;D=FAA-2014-0484-0002.
(2) Service information identified in this
AD that is not incorporated by reference in
this AD is available at the addresses specified
in paragraphs (m)(4) and (m)(5) of this AD.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320–57–1152,
Revision 01, dated December 19, 2013.
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
(ii) Reserved.
(3) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(4) You may view this service information
at the FAA, Transport 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 February
4, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–02697 Filed 2–17–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0522; Directorate
Identifier 2014–NM–087–AD; Amendment
39–18100; AD 2015–03–04]
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 747–100,
747–100B, 747–100B SUD, 747–200B,
747–200C, 747–200F, 747–300, 747–
400, 747–400D, 747–400F, 747SR, and
747SP series airplanes. This AD was
prompted by reports of fuselage skin
cracks at the lower forward corner of the
main entry door (MED) 1 cutout. This
AD requires repetitive inspections of the
fuselage skin of the MED 1 cutout for
cracking, and repair if necessary; and
also provides an optional terminating
modification, including post-repair or
post-modification fuselage skin
inspections for cracking, and corrective
actions if necessary. We are issuing this
AD to detect and correct skin cracking,
which can become large and could
adversely affect the structural integrity
of the airplane.
DATES: This AD is effective March 25,
2015.
SUMMARY:
E:\FR\FM\18FER1.SGM
18FER1
]]>Agencies
[Federal Register Volume 80, Number 32 (Wednesday, February 18, 2015)]
[Rules and Regulations]
[Pages 8513-8516]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-02697]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0484; Directorate Identifier 2013-NM-245-AD;
Amendment 39-18101; AD 2015-03-05]
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) 2012-09-07 for
certain Airbus Model A319-111, -112, and -132 airplanes; Model A320-
111, -211, -212, -214, and -232 airplanes; and Model A321-111, -211, -
212, and -231 airplanes. AD 2012-09-07 required an electrical bonding
test between the gravity fill re-fuel adaptor and the top skin panels
on the wings; and, if necessary, an inspection for corrosion of the
component interface and adjacent area; and repairing the gravity fuel
adaptor if necessary. This new AD adds airplanes to the applicability
and requires inspecting those airplanes to determine if a repair was
done, and doing the electrical bonding test and corrective action if
necessary. This AD was prompted by a determination that more airplanes
are
[[Page 8514]]
subject to the identified unsafe condition. We are issuing this AD to
detect and correct corrosion and improper bonding, which, in
combination with a lightning strike in this area, could create a source
of ignition in a fuel tank, resulting in a fire or explosion and
consequent loss of the airplane.
DATES: This AD becomes effective March 25, 2015.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 25,
2015.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0484; 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,
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44
51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0484.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012-09-07, Amendment 39-17042 (77 FR 28238,
May 14, 2012). AD 2012-09-07 applied to certain Airbus Model A319-111,
-112, and -132 airplanes; Model A320-111, -211, -212, -214, and -232
airplanes; and Model A321-111, -211, -212, and -231 airplanes. The NPRM
published in the Federal Register on July 30, 2014 (79 FR 44144).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2013-0277R1, dated December 4, 2013 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A318-111, -112, -121, and -122 airplanes; Model A319-111, -112, -113, -
114, -115, -131, -132, and -133 airplanes; Model A320-111, -211, -212,
-214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -
211, -212, -213, -231, and -232 airplanes. The MCAI states:
Cases of corrosion findings were reported on the overwing
refueling aperture (used to fill the fuel tank by gravity) on the
wing top skin. The reported corrosion was on the mating surface of
the aperture flange, underneath the refuel adaptor. Corrosion
findings have been repaired on a case by case basis in accordance
with approved data.
For certain aeroplanes, the repair provided by Airbus contained
instructions to apply primer coating on the mating surface. Since
doing those repairs, it has been found that this primer coating may
prevent proper electrical bonding provision between the overwing
refueling cap adaptor and the wing skin.
This condition, if not detected and corrected, could, in
combination with a lightning strike in this area, create a source of
ignition in a fuel tank, possibly resulting in a fire or explosion
and consequent loss of the aeroplane.
To address this potential unsafe condition, EASA issued AD 2011-
0034 [https://ad.easa.europa.eu/blob/easa_ad_2011_0034.pdf/AD_2011-0034] to require a one-time electrical bonding check between the
gravity fill re-fuel adaptor and the top skin panels on the affected
aeroplanes (identified by MSN [manufacturer serial number] in the
applicability section of that [EASA] AD) and, in case of findings,
the accomplishment of applicable corrective actions.
Since that [EASA] AD was issued, EASA has been made aware that
some operators may inadvertently have applied an Airbus repair,
approved for only one aeroplane MSN, to other aeroplanes, without
requesting a revision of the repair to add aeroplanes, or to notify
Airbus of such action(s). Consequently, the condition addressed by
EASA AD 2011-0034 could affect more aeroplanes than initially
determined.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2011-0034, which is superseded, and expands
the Applicability to all A320 family aeroplane Models, all MSN.
This [EASA] AD has been revised to amend and clarify paragraph
(3), and to correct an error in the Type/Model designations on page
1, where the A318 was inadvertently omitted.
For the newly added airplanes, required actions include inspecting for
the presence of a corrosion repair on an overwing refueling aperture,
and doing the electrical bonding test and applicable corrective actions
if a repair has been installed. You may examine the MCAI in the AD
docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0484-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the NPRM (79 FR
44144, July 30, 2014) and the FAA's response to the comment.
Request To Include Revised Service Information
United Airlines (UAL) asked that we include a statement in the NPRM
(79 FR 44144, July 30, 2014), which allows performing the required
actions in accordance with the instructions of Airbus Service Bulletin
A320-57-1152, Revision 01, dated December 19, 2013. UAL stated that the
revised service information specifies the same method of inspection as
specified in Airbus Service Bulletin A320-57-1152, dated June 14, 2010.
UAL further stated that Revision 01 of this service bulletin also
provides operators with updated repair instructions that were not
available in the original issue of this service bulletin.
We agree with the commenter's request. Since issuance of the NPRM
(79 FR 44144, July 30, 2014), Airbus has issued Service Bulletin A320-
57-1152, Revision 01, dated December 19, 2013. This revision states
that no additional work is necessary on airplanes changed in accordance
with Airbus Service Bulletin A320-57-1152, dated June 14, 2010, which
was specified as the appropriate source of service information in the
NPRM (79 FR 44144, July 30, 2014).
We have changed paragraph (g) of this AD to specify Airbus Service
Bulletin A320-57-1152, Revision 01, dated December 19, 2013. We have
also added a new paragraph (h) to this AD to give credit for actions
done before the effective date of this AD using Airbus Service Bulletin
A320-57-1152, dated June 14, 2010, and redesignated subsequent
paragraphs accordingly.
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 44144, July 30, 2014) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already
[[Page 8515]]
proposed in the NPRM (79 FR 44144, July 30, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-57-1152, Revision 01, dated
December 19, 2013. The service information describes procedures for
inspecting certain airplanes to determine if a repair was done, and
doing an electrical bonding test and corrective action if necessary.
This service information is reasonably available; see ADDRESSES for
ways to access this service information.
Costs of Compliance
We estimate that this AD affects 851 airplanes of U.S. registry.
The actions required by AD 2012-09-07, Amendment 39-17042 (77 FR
28238, May 14, 2012), and retained in this AD take about 2 work-hours
per product, at an average labor rate of $85 per work-hour. Based on
these figures, the estimated cost of the actions that were required by
AD 2012-09-07 is $170 per product.
We also estimate that it takes 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 cost about $0 per product. Based
on these figures, we estimate the cost of this AD on U.S. operators to
be $144,670, or $170 per product.
In addition, we estimate that any necessary follow-on actions will
take about 11 work-hours, for a cost of $935 per product. We have no
way of determining the number of aircraft that might need these
actions.
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-2014-0484; 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)
2012-09-07, Amendment 39-17042 (77 FR 28238, May 14, 2012), and adding
the following new AD:
2015-03-05 Airbus: Amendment 39-18101. Docket No. FAA-2014-0484;
Directorate Identifier 2013-NM-245-AD.
(a) Effective Date
This AD becomes effective March 25, 2015.
(b) Affected ADs
This AD replaces AD 2012-09-07, Amendment 39-17042 (77 FR 28238,
May 14, 2012).
(c) Applicability
(1) This AD applies to Airbus Model A318-111, -112, -121, and -
122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232,
and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes; certificated in any category; all
manufacturer serial numbers, except airplanes identified in
paragraph (c)(2) of this AD.
(2) Airplanes that have been delivered from production with
Airbus Modification 38209 (Removal of the Outer Wing Refueling
Aperture) incorporated, and without Airbus Modification 38206 (Re-
introduction of the Outer Wing Refueling Aperture) incorporated, are
not affected by the requirements of this AD.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by a determination that more airplanes are
subject to the identified unsafe condition. We are issuing this AD
to detect and correct corrosion and improper bonding, which, in
combination with a lightning strike in this area, could create a
source of ignition in a fuel tank, resulting in a fire or explosion
and consequent loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Electrical Bonding Test, and General Visual Inspection if
Necessary, With Changes
This paragraph restates the requirements of paragraph (g) of AD
2012-09-07, Amendment 39-17042 (77 FR 28238, May 14, 2012), with
revised repair approval language and revised service information.
For Model A319-111, -112, and -132 airplanes; Model A320-111, -211,
-212, -214 and -232 airplanes; and Model A321-111, -211, -212, and -
231 airplanes; certificated in any category; having manufacturer
serial numbers 0039, 0078, 0109, 0118, 0120, 0153, 0174, 0187, 0203,
0215, 0218, 0226, 0227, 0228, 0236, 0237, 0269, 0270, 0278, 0285,
0286, 0287, 0288, 0294, 0301, 0337, 0377, 0462, 0463, 0464, 0465,
0520, 0523, 0528, 0876, 0888, 0921, 0935, 0974, 1014, 1102, 1130,
1160, 1162, 1177, 1215, 1250, 1287, 1336, 1388, 1404, 1444, 1449,
1476, 1505, 1524, 1564, 1605, 1616, 1622, 1640, 1645, 1658, 1677,
1691, 1729, and 1905: Within 24 months after June 18, 2012 (the
effective date of AD 2012-09-07), do an electrical bonding
[[Page 8516]]
test to check for bonding between the re-fuel adaptor of the gravity
fill and the top skin panels on the left-hand and right-hand wings,
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-57-1152, Revision 01, dated December 19, 2013.
(1) If the resistance value is 10 milliohms or less at the left-
hand and right-hand wing, no further action is required by this
paragraph.
(2) If the resistance value is greater than 10 milliohms at the
left-hand or right-hand wing, before further flight, do a general
visual inspection for corrosion of the component interface and
adjacent area, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-57-1152, Revision 01, dated December
19, 2013. If any corrosion is found during the inspection, before
further flight, repair the gravity fill fuel adaptor, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-57-1152, Revision 01, dated December 19, 2013; except where
Airbus Service Bulletin A320-57-1152, Revision 01, dated December
19, 2013, specifies to contact Airbus, before further flight, repair
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.
(h) Credit for Previous Actions
This paragraph provides credit for the actions specified in
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Airbus Service Bulletin A320-57-
1152, dated June 14, 2010, which was incorporated by reference in AD
2012-09-07, Amendment 39-17042 (77 FR 28238, May 14, 2012).
(i) New Requirement of This AD: Maintenance Check/Electrical Bonding
Test and Corrective Action if Necessary
For airplanes other than those identified in paragraph (g) of
this AD: Within 24 months after the effective date of this AD,
determine whether a corrosion repair has been done on an overwing
refueling aperture, whereby a primer coating has been applied on the
mating surface of the aperture flange. A review of the airplane
maintenance records is acceptable to make this determination,
provided that whether a primer coat was applied can be conclusively
determined from that review.
(1) If it is determined that a primer coating was applied on the
mating surface of the aperture flange; or if a determination cannot
be made, or the outcome is inconclusive: Within 24 months after the
effective date of this AD do the electrical bonding test specified
in paragraph (g) of this AD, and before further flight, do all
applicable actions specified in paragraph (g)(2) of this AD.
(2) If it is determined that a corrosion repair has not been
done, and a primer coating has not been applied on the mating
surface of the aperture flange since first entry into service, no
further action is required by this paragraph.
(j) Corrosion Repair Provision
As of the effective date of this AD, any corrosion repair done
on an overwing refueling aperture on any airplane must comply with
the repair requirements of paragraph (g)(2) of this AD.
(k) 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: 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. Information may be
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
(i) 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.
(ii) AMOCs approved previously for AD 2012-09-07, Amendment 39-
17042 (77 FR 28238, May 14, 2012), are approved as AMOCs for the
corresponding provisions of 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 EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
(l) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2013-0277R1, dated December 4,
2013, for related information. This MCAI may be found in the AD
docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0484-0002.
(2) Service information identified in this AD that is not
incorporated by reference in this AD is available at the addresses
specified in paragraphs (m)(4) and (m)(5) of this AD.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320-57-1152, Revision 01, dated
December 19, 2013.
(ii) Reserved.
(3) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com.
(4) You may view this service information at the FAA, Transport
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 February 4, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-02697 Filed 2-17-15; 8:45 am]
BILLING CODE 4910-13-P
