Airworthiness Directives; Airbus Airplanes, 52414-52416 [2013-19459]
Download as PDF
<![CDATA[
52414
Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
Within 300 hours time-in-service:
(1) Inspect the rigging of the power-boosted
control system, referencing Figure 1 of
Eurocopter Alert Service Bulletin ASB MBB
BK117 C–2–67A–012, Revision 0, dated
September 20, 2010 (ASB). Ensure the piston
of the longitudinal actuator (right-hand side)
is held in the fully extended position and the
piston of the lateral actuator (left-hand side)
is held in the fully retracted position against
the mechanical stop. Also, ensure the gauge
block is clamped between the sliding sleeve
and the support tube.
(2) Insert the rigging wedges with the 25.4
degree (item 8 of Figure 1 of the ASB) and
19.5 degree (item 7 of Figure 1 of the ASB)
markings in the ‘‘A’’ side of the guide grooves
of the rigging device (item 3 of Figure 1 of
the ASB).
(3) If the gap between the rigging wedges
(items 7 and 8 of Figure 1 of the ASB) and
the inner sleeves (item 9 of Figure 1 of the
ASB) is closed, the rigging is correct.
(4) If there is a nonparallel gap between the
rigging wedges (items 7 and 8 of Figure 1 of
the ASB) and the inner sleeves (item 9 of
Figure 1 of the ASB), the rigging is not
correct. Perform a rigging procedure.
emcdonald on DSK67QTVN1PROD with RULES
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Jim Grigg,
Manager, Rotorcraft Directorate, 2601
Meacham Blvd., Fort Worth, TX 76137,
telephone (817) 222–5110, email Jim.Grigg@
faa.gov.
(2) For operations conducted under 14 CFR
part 119 operating certificate or under 14
CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a
principal inspector, the manager of the local
flight standards district office or certificate
holding district office before operating any
aircraft complying with this AD through an
AMOC.
(g) Additional Information
(1) For service information identified in
this AD, contact American Eurocopter
Corporation, 2701 N. Forum Drive, Grand
Prairie, TX 75052, telephone (972) 641–0000
or (800) 232–0323, fax (972) 641–3775, or at
https://www.eurocopter.com/techpub. You
may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region, 2601
Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2010–0248, dated November 26, 2010.
You may view the EASA AD at https://
www.regulations.gov in Docket No. FAA–
2013–0020.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6710 Main Rotor Control.
VerDate Mar<15>2010
16:22 Aug 22, 2013
Jkt 229001
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Eurocopter Alert Service Bulletin ASB
MBB BK117 C–2–67A–012, Revision 0, dated
September 20, 2010.
(ii) Reserved.
(3) For Eurocopter service information
identified in this AD, contact American
Eurocopter Corporation, 2701 N. Forum
Drive, Grand Prairie, TX 75052, telephone
(972) 641–0000 or (800) 232–0323, fax (972)
641–3775, or at https://www.eurocopter.com/
techpub.
(4) You may view this service information
that is incorporated by reference at https://
www.regulations.gov in Docket No. FAA–
2013–0020.
(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 Fort Worth, Texas, on August 2,
2013.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–19443 Filed 8–22–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1076; Directorate
Identifier 2011–NM–274–AD; Amendment
39–17556; AD 2013–16–18]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Airbus Model A320–214, –232 and –233
airplanes; and Model A321–211, –213,
and –231 airplanes. This AD was
prompted by a report of a missing
fastener between certain stringers of the
fuselage frame that connects the frame
to a tee. This AD requires an inspection
for a missing fastener, and a rototest
inspection and a modification or repair
of the fuselage frame at the affected area
SUMMARY:
PO 00000
Frm 00026
Fmt 4700
Sfmt 4700
if necessary. We are issuing this AD to
detect and correct cracking in the
fuselage that could result in reduced
structural integrity of the airplane.
DATES: This AD becomes effective
September 27, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 27, 2013.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC.
FOR 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 include an AD that would
apply to the specified products. The
NPRM was published in the Federal
Register on October 16, 2012 (77 FR
63270). The NPRM proposed to correct
an unsafe condition for the specified
products. The European Aviation Safety
Agency (EASA), which is the aviation
authority for the Member States of the
European Community, has issued EASA
Airworthiness Directive 2011–0229,
dated December 6, 2011 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
During a quality check in production of an
A320 family aeroplane, it was discovered
that a fastener was missing at [frame] FR 24
between stringer (STRG) 25 and STRG 26 on
the right-hand (RH) side. The purpose of the
missing fastener, a 4 [millimeter] mm
diameter aluminum rivet, Part Number (P/N)
ASNA2050DXJ040, is to connect the FR 24 to
the FR 24 Tee. The hole where the fastener
was missing was not drilled.
Further investigations revealed that the
drilling was missing on the milling grid used
for frame assembly of a limited group of
aeroplanes.
This condition, if not corrected, could
impair the structural integrity of the affected
aeroplanes.
For the reasons described above, this
[EASA] AD requires a special detailed
inspection (SDI) [rototest inspection for
cracking] of the affected area, and the
accomplishment of the associated corrective
actions [modification and/or repair].
You may obtain further information by
examining the MCAI in the AD docket.
E:\FR\FM\23AUR1.SGM
23AUR1
Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received.
Request To Include Latest Revision of
Service Information
Airbus requested that we revise the
NPRM (77 FR 63270, October 16, 2012)
to reflect the latest revision of the
service information to add an inspection
for a missing fastener that is included in
that revised service information. Airbus
stated that the rototest inspection is
required only when it is confirmed that
the fastener is missing.
We agree with the commenter’s
request. Airbus has issued Airbus
Mandatory Service Bulletin A320–53–
1247, Revision 01, dated October 15,
2012. That service bulletin was revised
to include procedures for a general
visual inspection for a missing fastener.
For airplanes on which no fastener is
missing, the rototest inspection would
no longer be necessary. We have
changed paragraph (g) of this final rule
to provide instructions for
accomplishing the general visual
inspection, which if accomplished and
no fastener is missing, would eliminate
the need for the rototest inspection. We
have included the repair and
modification that were part of paragraph
(g) of the NPRM (77 FR 63270, October
16, 2012) as new paragraph (h) of this
final rule and changed subsequent
identifiers accordingly.
emcdonald on DSK67QTVN1PROD with RULES
Conclusion
We reviewed the available data,
including the comment received, 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 changes:
• Are consistent with the intent that
was proposed in the NPRM (77 FR
63270, October 16, 2012) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (77 FR 63270,
October 16, 2012).
Costs of Compliance
We estimate that this AD will affect
111 products of U.S. registry. We also
estimate that it will take about 6 workhours per product to comply with the
basic requirements of this AD. The
average labor rate is $85 per work-hour.
Required parts will cost about $85 per
product. Where the service information
lists required parts costs that are
covered under warranty, we have
assumed that there will be no charge for
these parts. As we do not control
VerDate Mar<15>2010
16:54 Aug 22, 2013
Jkt 229001
52415
warranty coverage for affected parties,
some parties may incur costs higher
than estimated here. Based on these
figures, we estimate the cost of this AD
to the U.S. operators to be $66,045, or
$595 per product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD. We have no way
of determining the number of products
that may need these actions.
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section.
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.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
PO 00000
Frm 00027
Fmt 4700
Sfmt 4700
List of Subjects in 14 CFR Part 39
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2013–16–18 Airbus: Amendment 39–17556.
Docket No. FAA–2012–1076; Directorate
Identifier 2011–NM–274–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective September 27, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A320–
214, –232, and –233 airplanes; and Model
A321–211, –213, and –231 airplanes;
certificated in any category; manufacturer
serial numbers 4338, 4371, 4374, 4375, 4377,
4381 through 4384 inclusive, 4386, 4387,
4388, 4390 through 4402 inclusive, 4404
through 4409 inclusive, 4411 through 4417
inclusive, 4419, 4420, 4421, 4423, 4424,
4426, 4429 through 4436 inclusive, 4438
through 4443 inclusive, 4445 through 4450
inclusive, 4453, 4454, 4456 through 4469
inclusive, 4471, 4472, 4474 through 4481
inclusive, 4483 through 4498 inclusive, 4500,
4504, 4505, 4506, and 4509.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report of a
missing fastener between certain stringers of
the fuselage frame that connects the frame to
a tee. We are issuing this AD to detect and
correct cracking in the fuselage that could
result in reduced structural integrity of the
airplane.
E:\FR\FM\23AUR1.SGM
23AUR1
52416
Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Inspections
Before the accumulation of 24,000 total
flight cycles since first flight of the airplane,
or within 30 days after the effective date of
this AD, whichever occurs later, do the
actions specified in paragraph (g)(1) or (g)(2)
of this AD.
(1) Do a general visual inspection for a
missing fastener between the two fasteners at
fuselage frame (FR) 24 between stringer 25
and stringer 26 right-hand side, in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–53–1247, Revision 01, dated
October 15, 2012.
(i) If the fastener is not missing, no further
action is required by paragraph (g) of this AD.
(ii) If the fastener is missing, before further
flight, do the actions required by paragraph
(g)(2) of this AD.
(2) Do a rototest inspection for cracking of
the two adjacent fastener holes at
fuselage FR 24 between stringer 25 and
stringer 26 right-hand side, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–53–1247,
dated July 15, 2011; or Airbus Mandatory
Service Bulletin A320–53–1247, Revision 01,
dated October 15, 2012.
emcdonald on DSK67QTVN1PROD with RULES
(h) Repair
(1) If, during the rototest inspection
specified by paragraph (g)(2) of this AD, any
crack is found, 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 its
delegated agent).
(2) If, during the rototest inspection
specified by paragraph (g)(2) of this AD, no
crack is found, before the accumulation of
24,000 total flight cycles since first flight of
the airplane, or within 30 days after the
effective date of this AD, whichever occurs
later: Modify fuselage FR 24 between stringer
25 and stringer 26 right-hand side, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1247, dated July 15, 2011; or Airbus
Mandatory Service Bulletin A320–53–1247,
Revision 01, dated October 15, 2012.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, 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;
VerDate Mar<15>2010
16:22 Aug 22, 2013
Jkt 229001
telephone (425) 227–1405; fax (425) 227–
1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(j) Related Information
Refer to mandatory continuing
airworthiness information (MCAI) EASA
Airworthiness Directive 2011–0229, dated
December 6, 2011, for related information.
The MCAI may be viewed on the Internet at
https://ad.easa.europa.eu/ad/2011–0229.
EASA ADs are at https://ad.easa.europa.eu/.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Airbus Mandatory Service Bulletin
A320–53–1247, Revision 01, dated October
15, 2012.
(ii) Airbus Service Bulletin A320–53–1247,
dated July 15, 2011.
(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.airwortheas@airbus.com; Internet https://
www.airbus.com.
(4) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
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 August
2, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–19459 Filed 8–22–13; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
Frm 00028
Fmt 4700
Sfmt 4700
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0092; Directorate
Identifier 2012–NM–067–AD; Amendment
39–17560; AD 2013–16–22]
RIN 2120–AA64
Airworthiness Directives; Embraer S.A.
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Embraer S.A. Model ERJ 170 and ERJ
190 airplanes. This AD was prompted
by reports of chafing between the
auxiliary power unit (APU) electronic
starter controller (ESC) power cables
and the airplane tail cone firewall. This
AD requires a detailed inspection for
damage to the insulation and inner
conductors of the APU ESC power
cables, installing a new grommet
support in the tail cone firewall, and
corrective actions if necessary. We are
issuing this AD to detect and correct
damage to the APU ESC power cable
harness, which if not corrected, could
result in reduced structural integrity of
the fuselage and empennage in the event
of fire penetration through the firewall.
DATES: This AD becomes effective
September 27, 2013.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 27, 2013.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Cindy Ashforth, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone (425) 227–2768;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
SUMMARY:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on February 22, 2013 (78 FR
E:\FR\FM\23AUR1.SGM
23AUR1
]]>Agencies
[Federal Register Volume 78, Number 164 (Friday, August 23, 2013)]
[Rules and Regulations]
[Pages 52414-52416]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-19459]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1076; Directorate Identifier 2011-NM-274-AD;
Amendment 39-17556; AD 2013-16-18]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Airbus Model A320-214, -232 and -233 airplanes; and Model A321-211, -
213, and -231 airplanes. This AD was prompted by a report of a missing
fastener between certain stringers of the fuselage frame that connects
the frame to a tee. This AD requires an inspection for a missing
fastener, and a rototest inspection and a modification or repair of the
fuselage frame at the affected area if necessary. We are issuing this
AD to detect and correct cracking in the fuselage that could result in
reduced structural integrity of the airplane.
DATES: This AD becomes effective September 27, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September
27, 2013.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.
FOR 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 include an AD that would apply to the specified products.
The NPRM was published in the Federal Register on October 16, 2012 (77
FR 63270). The NPRM proposed to correct an unsafe condition for the
specified products. The European Aviation Safety Agency (EASA), which
is the aviation authority for the Member States of the European
Community, has issued EASA Airworthiness Directive 2011-0229, dated
December 6, 2011 (referred to after this as ``the MCAI''), to correct
an unsafe condition for the specified products. The MCAI states:
During a quality check in production of an A320 family
aeroplane, it was discovered that a fastener was missing at [frame]
FR 24 between stringer (STRG) 25 and STRG 26 on the right-hand (RH)
side. The purpose of the missing fastener, a 4 [millimeter] mm
diameter aluminum rivet, Part Number (P/N) ASNA2050DXJ040, is to
connect the FR 24 to the FR 24 Tee. The hole where the fastener was
missing was not drilled.
Further investigations revealed that the drilling was missing on
the milling grid used for frame assembly of a limited group of
aeroplanes.
This condition, if not corrected, could impair the structural
integrity of the affected aeroplanes.
For the reasons described above, this [EASA] AD requires a
special detailed inspection (SDI) [rototest inspection for cracking]
of the affected area, and the accomplishment of the associated
corrective actions [modification and/or repair].
You may obtain further information by examining the MCAI in the AD
docket.
[[Page 52415]]
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received.
Request To Include Latest Revision of Service Information
Airbus requested that we revise the NPRM (77 FR 63270, October 16,
2012) to reflect the latest revision of the service information to add
an inspection for a missing fastener that is included in that revised
service information. Airbus stated that the rototest inspection is
required only when it is confirmed that the fastener is missing.
We agree with the commenter's request. Airbus has issued Airbus
Mandatory Service Bulletin A320-53-1247, Revision 01, dated October 15,
2012. That service bulletin was revised to include procedures for a
general visual inspection for a missing fastener. For airplanes on
which no fastener is missing, the rototest inspection would no longer
be necessary. We have changed paragraph (g) of this final rule to
provide instructions for accomplishing the general visual inspection,
which if accomplished and no fastener is missing, would eliminate the
need for the rototest inspection. We have included the repair and
modification that were part of paragraph (g) of the NPRM (77 FR 63270,
October 16, 2012) as new paragraph (h) of this final rule and changed
subsequent identifiers accordingly.
Conclusion
We reviewed the available data, including the comment received, 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 changes:
Are consistent with the intent that was proposed in the
NPRM (77 FR 63270, October 16, 2012) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 63270, October 16, 2012).
Costs of Compliance
We estimate that this AD will affect 111 products of U.S. registry.
We also estimate that it will take about 6 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Required parts will cost about $85 per product.
Where the service information lists required parts costs that are
covered under warranty, we have assumed that there will be no charge
for these parts. As we do not control warranty coverage for affected
parties, some parties may incur costs higher than estimated here. Based
on these figures, we estimate the cost of this AD to the U.S. operators
to be $66,045, or $595 per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD. We
have no way of determining the number of products that may 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (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 adding the following new AD:
2013-16-18 Airbus: Amendment 39-17556. Docket No. FAA-2012-1076;
Directorate Identifier 2011-NM-274-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective September
27, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A320-214, -232, and -233
airplanes; and Model A321-211, -213, and -231 airplanes;
certificated in any category; manufacturer serial numbers 4338,
4371, 4374, 4375, 4377, 4381 through 4384 inclusive, 4386, 4387,
4388, 4390 through 4402 inclusive, 4404 through 4409 inclusive, 4411
through 4417 inclusive, 4419, 4420, 4421, 4423, 4424, 4426, 4429
through 4436 inclusive, 4438 through 4443 inclusive, 4445 through
4450 inclusive, 4453, 4454, 4456 through 4469 inclusive, 4471, 4472,
4474 through 4481 inclusive, 4483 through 4498 inclusive, 4500,
4504, 4505, 4506, and 4509.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report of a missing fastener between
certain stringers of the fuselage frame that connects the frame to a
tee. We are issuing this AD to detect and correct cracking in the
fuselage that could result in reduced structural integrity of the
airplane.
[[Page 52416]]
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Inspections
Before the accumulation of 24,000 total flight cycles since
first flight of the airplane, or within 30 days after the effective
date of this AD, whichever occurs later, do the actions specified in
paragraph (g)(1) or (g)(2) of this AD.
(1) Do a general visual inspection for a missing fastener
between the two fasteners at fuselage frame (FR) 24 between stringer
25 and stringer 26 right-hand side, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A320-53-1247, Revision 01, dated October 15, 2012.
(i) If the fastener is not missing, no further action is
required by paragraph (g) of this AD.
(ii) If the fastener is missing, before further flight, do the
actions required by paragraph (g)(2) of this AD.
(2) Do a rototest inspection for cracking of the two adjacent
fastener holes at
fuselage FR 24 between stringer 25 and stringer 26 right-hand
side, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-53-1247, dated July 15, 2011; or Airbus
Mandatory Service Bulletin A320-53-1247, Revision 01, dated October
15, 2012.
(h) Repair
(1) If, during the rototest inspection specified by paragraph
(g)(2) of this AD, any crack is found, 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 its delegated agent).
(2) If, during the rototest inspection specified by paragraph
(g)(2) of this AD, no crack is found, before the accumulation of
24,000 total flight cycles since first flight of the airplane, or
within 30 days after the effective date of this AD, whichever occurs
later: Modify fuselage FR 24 between stringer 25 and stringer 26
right-hand side, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A320-53-1247, dated July 15, 2011; or
Airbus Mandatory Service Bulletin A320-53-1247, Revision 01, dated
October 15, 2012.
(i) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, 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. Before using any approved AMOC, notify your
appropriate principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office/
certificate holding district office. The AMOC approval letter must
specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(j) Related Information
Refer to mandatory continuing airworthiness information (MCAI)
EASA Airworthiness Directive 2011-0229, dated December 6, 2011, for
related information. The MCAI may be viewed on the Internet at
https://ad.easa.europa.eu/ad/2011-0229. EASA ADs are at https://ad.easa.europa.eu/.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Airbus Mandatory Service Bulletin A320-53-1247, Revision 01,
dated October 15, 2012.
(ii) Airbus Service Bulletin A320-53-1247, dated July 15, 2011.
(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 review copies of the 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 August 2, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-19459 Filed 8-22-13; 8:45 am]
BILLING CODE 4910-13-P
