Airworthiness Directives; Airbus Airplanes, 19009-19013 [2015-07799]
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Federal Register / Vol. 80, No. 68 / Thursday, April 9, 2015 / Rules and Regulations
and forest land to voluntarily make that
land available for access by the public
for wildlife-dependent recreation,
including hunting and fishing under
programs administered by State and
Tribal governments. VPA–HIP is not an
entitlement program and no grant will
be made unless the application is
acceptable to CCC. The program was
originally delegated to the
Administrator of FSA to administer on
behalf of CCC. The program is now
delegated to the Chief of NRCS, and
NRCS incorporated the necessary
administrative changes in the interim
rule. NRCS announced its Availability
of Program Funding on May 1, 2014, to
implement VPA–HIP in fiscal year 2014.
During its first round of grant proposals,
NRCS received requests for funding
from Indian Tribes which required
confirmation regarding whether Tribal
lands would be considered private lands
for the purposes of VPA–HIP. This final
rule clarifies that governmental and
Tribal lands are considered private
lands for the purposes of VPA–HIP
when such lands are part of a private
operation of a private individual or legal
entity.
Discussion of EWPP (7 CFR part 624):
NRCS purchases floodplain easements
to restore, protect, maintain, and
enhance the functions of the floodplain;
conserve natural values including fish
and wildlife habitat, water quality, flood
water retention, ground water recharge,
and open space; reduce long-term
Federal disaster assistance; and
safeguard lives and property from
floods, drought, and the products of
erosion. Section 382 of the Federal
Agriculture Improvement and Reform
Act of 1996 amended EWPP, 16 U.S.C.
2203, to authorize the purchase of
floodplain easements (FPE) as an
emergency measure on lands that
qualify for EWPP assistance. EWPP
FPEs are administered under 7 CFR part
624.
Prior to the 2014 Act, the EWPP–FPE
statute did not address modification or
termination of FPEs; therefore the
regulations at 7 CFR part 624 specified
that FPEs could not be modified or
terminated. Section 2206 of the 2014
Act provided such authority, and NRCS
is removing this prohibition from EWPP
regulations.
List of Subjects
7 CFR Part 610
Soil conservation, State Technical
Committees, Technical assistance, and
Water resources.
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7 CFR Part 622
Watershed projects, Watershed
protection, and Flood prevention.
19009
PART 1455—VOLUNTARY PUBLIC
ACCESS AND HABITAT INCENTIVE
PROGRAM
3. The authority citation for part 1455
continues to read as follows:
■
7 CFR Part 624
Disaster assistance, Floodplain
easement, Flooding, Imminent threat,
Natural disaster, and Watershed
impairment.
7 CFR Part 625
Authority: 15 U.S.C. 714b and 714c; 16
U.S.C. 3839.
4. Section 1455.2 is amended in
paragraph (b) by adding a definition for
‘‘legal entity’’ and revising the
definition of ‘‘privately-held land’’ to
read as follows:
■
Administrative practice and
procedure, Agriculture, and Soil
conservation.
§ 1455.2
7 CFR Part 652
*
NRCS, Soil conservation, and
Technical assistance.
7 CFR Part 662
Administrative practice and
procedure, Agriculture, and Soil
conservation.
7 CFR Part 1455
Definitions.
*
*
*
*
Legal entity means any entity created
under Federal or State law, excluding:
(a) a local, State or Federal government
or political subdivision or agency of
such government; and (b) a Tribal
government.
Privately-held land means farm,
ranch, or forest land that is owned or
operated by a person or legal entity.
*
*
*
*
*
Agriculture, Animals, Environmental
protection, Fishing, Forests and forest
products, Grant programs, Hunting,
Indians, Indians-land, Natural
resources, Recreation and recreation
areas, Rural areas, State and local
governments, and Wildlife.
Signed this 1st day of April, 2015 in
Washington, DC.
Jason A. Weller,
Vice President, Commodity Credit
Corporation, Chief, Natural Resources
Conservation Service.
7 CFR Part 1465
BILLING CODE 3410–16–P
Conservation contract, Conservation
plan, Conservation practices, and Soil
and water conservation.
DEPARTMENT OF TRANSPORTATION
[FR Doc. 2015–08008 Filed 4–8–15; 8:45 am]
Accordingly, the interim rule
amending 7 CFR parts 610, 622, 625,
652, 662, 1455, and 1465 which was
published at 79 FR 44635 on August 1,
2014, is adopted as a final rule with the
following changes:
Federal Aviation Administration
PART 624—EMERGENCY
WATERSHED PROTECTION
RIN 2120–AA64
1. The authority citation for part 624
continues to read as follows:
■
Authority: Sec. 216, Pub. L. 81–516, 33
U.S.C. 701b–1; Sec. 403, Pub. L. 95–334, as
amended, 16 U.S.C. 2203; 5 U.S.C. 301.
2. Amend § 624.10 by revising
paragraph (c) to read as follows:
■
§ 624.10
Floodplain easements.
*
*
*
*
*
(c) The Chief of NRCS may modify or
terminate an easement if, pursuant to 16
U.S.C. 2203(b), the Chief determines the
modification or termination is in the
public interest and will address a
compelling public need for which there
is no practicable alternative.
*
*
*
*
*
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14 CFR Part 39
[Docket No. FAA–2014–0123; Directorate
Identifier 2013–NM–040–AD; Amendment
39–18134; AD 2015–07–06]
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 A300 B4–601, B4–603,
B4–620, B4–622, B4–605R, B4–622R,
F4–605R, F4–622R, and C4–605R
Variant F airplanes; and Model A310–
203, –204, –221, –222, –304, –322, –324,
and –325 airplanes. This AD was
prompted by a report of inner skin
disbonding damage on a rudder. This
AD requires repetitive ultrasonic
inspections for disbonding of certain
rudders; an elasticity of laminate
SUMMARY:
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checker inspection; a woodpecker or tap
test inspection; venting the core, if
necessary; and repairing, if necessary.
We are issuing this AD to detect and
correct rudder disbonding, which could
affect the structural integrity of the
rudder.
DATES: This AD becomes effective May
14, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 14, 2015.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0123; 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—EAW, 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–
0123.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–2125;
fax 425–227–1149.
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 Airbus Model A300 B4–
601, B4–603, B4–620, B4–622, B4–605R,
B4–622R, F4–605R, F4–622R, and C4–
605R Variant F airplanes; and Model
A310–203, –204, –221, –222, –304,
–322, –324, and –325 airplanes. The
NPRM published in the Federal
Register on February 28, 2014 (79 FR
11355).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2013–0039, dated February 26,
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2013 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A300 B4–601, B4–603, B4–620,
B4–622, B4–605R, B4–622R, F4–605R,
F4–622R, and C4–605R Variant F
airplanes; and Model A310–203, –204,
–221, –222, –304, –322, –324, and –325
airplanes. The MCAI states:
One A310 operator found substantial inner
skin disbonding damage on a rudder that was
previously inspected in accordance with the
instructions of Airbus Service Bulletin (SB)
A310–55–2044. The results of the subsequent
investigation revealed that the most probable
cause of this damage was a blunt impact with
no visible damage from outside during the
rudder handling. Damage like this might
grow with pressure variation during groundair-ground cycles, and tests performed with
other rudders showed a rapid propagation of
damage during artificial pressure cycling.
This condition, if not detected and
corrected, could affect the structural integrity
of the rudder.
To address this potential unsafe condition,
Airbus issued Alert Operators Transmission
(AOT) A55W002–12 [dated December 13,
2012], pending Aircraft Maintenance Manual
(AMM) 27–21–21 PB401 revision to update
rudder handling procedures.
For the reasons described above, this
[EASA] AD requires ultrasonic test (UT)
inspections of the affected rudders to detect
signs of disbonding and, depending on
findings, accomplishment of applicable
corrective action(s).
Required actions also include an
elasticity of laminate checker inspection
to detect external and internal
disbonding, and a woodpecker or tap
test inspection to detect external
disbonding. You may examine the
MCAI in the AD docket on the Internet
at https://www.regulations.gov/
#!documentDetail;D=FAA-2014-01230002.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (79 FR 11355,
February 28, 2014) and the FAA’s
response to each comment.
Requests To Exclude Certain Airplanes
From AD Requirements
Airbus requested that we revise
paragraph (g) of the NPRM (79 FR
11355, February 28, 2014) to mirror the
language in Airbus Alert Operators
Transmission (AOT) A55W002–12,
dated December 13, 2012, which takes
into account whether or not the rudder
has been removed and/or installed since
the last inspection. Airbus stated that
the removal/installation process is
linked to the risk of the unseen damage
occurring to the rudder. Airbus
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suggested revised language for a
requirement to determine if the rudder
has been removed or installed since the
last inspection.
In addition, FedEx requested that we
revise paragraph (c) or (g) of the NPRM
(79 FR 11355, February 28, 2014) to
state that, if the installed rudder has
been inspected (and not removed) per
AD 2008–11–05, Amendment 39–15527
(73 FR 29423, May 21, 2008), since its
installation, no further inspection will
be required since the unsafe condition
would be alleviated.
UPS, FedEx, and Airbus requested
that we revise the NPRM (79 FR 11355,
February 28, 2014) to eliminate
unnecessary AD tracking requirements.
UPS noted that the identified risk only
exists in cases where the rudder has
been changed since inspection under
AD 2008–11–05, Amendment 39–15527
(73 FR 29423, May 21, 2008). UPS
further stated that the NPRM does not
refer to AD 2008–11–05, even though
the repetitive ultrasonic inspections to
detect disbonding in the NPRM are
identical to the requirements of
paragraph (f)(2) of AD 2008–11–05.
Also, UPS stated that the airplane
maintenance manual (AMM) has been
updated as of June 1, 2013, to include
the same ultrasonic inspection specified
in both AD 2008–11–05 and the NPRM.
UPS suggested revised wording for the
NPRM.
We concur with the requests to limit
the airplanes subject to the requirements
of paragraph (g) of this AD. This AD
does relate to AD 2008–11–05 (73 FR
29423, dated May 21, 2008), in that the
ultrasonic inspections are required in
both ADs. This AD requires the
ultrasonic inspections for only certain
airplanes. Therefore, we have added a
new paragraph (h)(2) in this AD.
Paragraph (h)(2) of this AD specifies
that, for airplanes on which it can be
conclusively determined that the most
recent inspection specified in Airbus
Service Bulletin A310–55–2044 or
Airbus Service Bulletin A300–55–6043
was done on the airplane; or the rudder
was not removed for any reason since
doing the most recent inspection
specified in Airbus Service Bulletin
A310–55–2044 or Airbus Service
Bulletin A300–55–6043; no further
action is necessary, except as specified
in paragraphs (j) and (k) of this AD.
We have also re-designated
paragraphs (h), (h)(1), and (h)(2) of the
NPRM as paragraphs (h)(1), (h)(1)(i), and
(h)(1)(ii) of this AD, respectively.
Request To Remove Requirement To
Refer to This AD in Repair Approvals
UPS requested that we revise the
NPRM (79 FR 11355, February 28, 2014)
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to remove the requirement to include
the AD reference in repair approvals.
UPS noted its concerns that the NPRM
will increase requests for approval of
alternative methods of compliance
(AMOCs) and result in delays to other
services and actions addressed by the
FAA on a daily basis.
We concur with the commenter’s
request to remove from this AD the
requirement that repair approvals must
specifically refer to 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. The MCAI or referenced
service information in an FAA AD often
directs the owner/operator to contact
the manufacturer for corrective actions,
such as a repair. Briefly, the Airworthy
Product paragraph allowed owners/
operators to use corrective actions
provided by the manufacturer if those
actions were FAA-approved. In
addition, the paragraph stated that any
actions approved by the State of Design
Authority (or its delegated agent) are
considered to be FAA-approved.
In the NPRM (79 FR 11355, February
28, 2014), we proposed to prevent the
use of repairs that were not specifically
developed to correct the unsafe
condition, by requiring that the repair
approval provided by the State of
Design Authority or its delegated agent
specifically refer to this FAA AD. This
change was intended to clarify the
method of compliance and to provide
operators with better visibility of repairs
that are specifically developed and
approved to correct the unsafe
condition. In addition, we proposed to
change the phrase ‘‘its delegated agent’’
to include ‘‘the Design Approval Holder
(DAH) with a State of Design
Authority’s design organization
approval (DOA)’’ to refer to a DAH
authorized to approve required repairs
for the AD.
In its comments to the NPRM (79 FR
11355, February 28, 2014), UPS stated
the following: ‘‘The proposed wording,
being specific to repairs, eliminates the
interpretation that Airbus messages or
other approved EASA documents are
acceptable for approving minor
deviations (corrective actions) needed
during accomplishment of a[n AD]
mandated Airbus service bulletin.’’
This comment has made the FAA
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
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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
that 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, EASA,
or Airbus’s EASA 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 afforded previously 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 AD
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.
Other commenters to another NPRM
having Directorate Identifier 2012–NM–
101–AD (78 FR 78285, December 26,
2013) pointed out that in many cases the
foreign manufacturer’s service bulletin
and the foreign authority’s MCAI may
have been issued some time before the
FAA AD. Therefore, the DOA may have
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19011
provided U.S. operators with an
approved repair, developed with full
awareness of the unsafe condition,
before the FAA AD is issued. Under
these circumstances, to comply with the
FAA AD, the operator would be
required to go back to the
manufacturer’s DOA and obtain a new
approval document, adding time and
expense to the compliance process with
no safety benefit.
Based on these comments, we
removed the requirement from this AD
that the DAH-provided repair
specifically refer to this AD. Before
adopting such a requirement in the
future, the FAA will coordinate with
affected DAHs and verify they are
prepared to implement means to ensure
that their repair approvals consider the
unsafe condition addressed in an AD.
Any such requirements will be adopted
through the normal AD rulemaking
process, including notice-and-comment
procedures, when appropriate.
We have also decided not to include
a generic reference to either the
‘‘delegated agent’’ or the ‘‘DAH with
State of Design Authority design
organization approval,’’ but instead we
will provide the specific delegation
approval granted by the State of Design
Authority for the DAH.
Compliance Time Clarification
In paragraph (g) of this AD, for
airplanes on which the part number or
serial number cannot be determined, we
have revised the compliance time of
‘‘before further flight’’ to ‘‘within 3
months after the effective date of this
AD.’’ This clarification corresponds to
the compliance time in the MCAI. We
have determined that extending the
compliance time will provide an
acceptable level of safety.
Conclusion
We reviewed the relevant data,
considered the comments 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 minor changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR
11355, February 28, 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 11355,
February 28, 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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Related Service Information Under 1
CFR Part 51
Airbus has issued AOT A55W002–12,
dated December 13, 2012, including
Inspection Flowchart. The service
information describes, among other
actions, procedures for an ultrasonic
inspection along the Z-profile of the
rudder side panel. This service
information is reasonably available; see
ADDRESSES for ways to access this
service information.
Costs of Compliance
We estimate that this AD affects 89
airplanes of U.S. registry. We also
estimate that it would take about 10
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 $75,650, or $850 per
product.
We have received no definitive data
that would enable us to provide a cost
estimate for the on-condition actions
specified in this AD.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
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;
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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-2014-0123; 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 adding
the following new airworthiness
directive (AD):
■
2015–07–06 Airbus: Amendment 39–18134.
Docket No. FAA–2014–0123; Directorate
Identifier 2013–NM–040–AD.
(a) Effective Date
This AD becomes effective May 14, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1) and (c)(2) of this AD,
except airplanes on which modification
08827 has been embodied in production.
(1) Airbus Model A300 B4–601, B4–603,
B4–620, B4–622, B4–605R, B4–622R, F4–
605R, F4–622R, and C4–605R Variant F
airplanes, certificated in any category, all
manufacturer serial numbers.
(2) Airbus Model A310–203, –204, –221,
–222, –304, –322, –324, and –325 airplanes,
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certificated in any category, all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 55; Stabilizers.
(e) Reason
This AD was prompted by a report of inner
skin disbonding damage on a rudder. We are
issuing this AD to detect and correct rudder
disbonding, which could affect the structural
integrity of the rudder.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Identification of Part Number
Within 3 months after the effective date of
this AD, identify the rudder assembly part
number (P/N) and serial number (S/N), in
accordance with Airbus Alert Operators
Transmission (AOT) A55W002–12, dated
December 13, 2012, including Inspection
Flowchart. If the part number or serial
number cannot be determined, within 3
months after the effective date of this AD,
identify the part number and serial number,
in accordance with a method approved by
either 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).
(h) Inspections
(1) Except as provided by paragraph (h)(2)
of this AD, if a rudder assembly part number
starting with A55471500 is found during the
inspection required by paragraph (g) of this
AD, before further flight, do an ultrasonic
(UT) inspection for damage (e.g., disbonding
and liquid ingress) of the rudder side panel
along the Z-profile and in the booster area,
in accordance with Airbus AOT A55W002–
12, dated December 13, 2012, including
Inspection Flowchart. If any damage is
found, before further flight, do the
inspections to confirm disbonding damage,
as specified in paragraphs (h)(1)(i) and
(h)(1)(ii) of this AD, in accordance with
Airbus AOT A55W002–12, dated December
13, 2012.
(i) Do an elasticity of laminate checker
inspection to detect external and internal
disbonding of the rudder side panel along the
Z-profile and in the booster area.
(ii) Do a woodpecker or tap test inspection
to detect external disbonding of the rudder
side panel along the Z-profile and in the
booster area.
(2) For airplanes on which it can be
conclusively determined that the most recent
inspection specified in Airbus Service
Bulletin A310–55–2044 or Airbus Service
Bulletin A300–55–6043 was done on the
airplane; or the rudder was not removed for
any reason since doing the most recent
inspection specified in Airbus Service
Bulletin A310–55–2044 or Airbus Service
Bulletin A300–55–6043: No further action is
required by this AD, except as specified in
paragraphs (j) and (k) of this AD.
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(i) Repair
(1) If any disbonding is confirmed during
any inspection required by paragraphs
(h)(1)(i) and (h)(1)(ii) of this AD, before
further flight, repair as specified in
paragraphs (i)(1)(i) and (i)(1)(ii) of this AD, as
applicable.
(i) If disbonding is less than or equal to 50
millimeters (mm) in width and less than or
equal to 150 mm in length, before further
flight, vent the core, using a method
approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA; or
Airbus’s EASA DOA. Within 100 flight cycles
after the UT inspection specified in
paragraph (h) of this AD is done, repair using
a method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA; or
Airbus’s EASA DOA.
(ii) If disbonding is greater than 50 mm in
width or greater than 150 mm in length,
before further flight, repair using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA; or Airbus’s EASA
DOA.
(2) If liquid ingress is confirmed during
any inspection required by paragraphs
(h)(1)(i) and (h)(1)(ii) of this AD, before
further flight, repair using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA; or Airbus’s EASA
DOA.
(j) Inspection after Re-Installation
If any rudder has been inspected as
specified in Airbus Service Bulletin A300–
55–6043, Revision 01, dated December 3,
2007; or A310–55–2044, Revision 01, dated
December 3, 2007; as applicable; and has
been removed and re-installed on any
airplane after this inspection, that rudder
must be re-inspected as required by
paragraph (g) of this AD; and all applicable
actions required by paragraphs (h) and (i) of
this AD must be done.
Rmajette on DSK2VPTVN1PROD with RULES
(k) Parts Installation Limitation
As of the effective date of this AD, no
person may install, on any airplane, a rudder
assembly having a part number starting with
A55471500, unless it has been inspected as
required by paragraph (h) of this AD, and all
applicable actions required by paragraph (i)
of this AD have been done.
(l) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
VerDate Sep<11>2014
15:10 Apr 08, 2015
Jkt 235001
19013
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–2125; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
Issued in Renton, Washington, on March
27, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
(m) Related Information
Airworthiness Directives; Lockheed
Martin Corporation/Lockheed Martin
Aeronautics Company Airplanes
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0039, dated
February 26, 2013, for related information.
This MCAI may be found in the AD docket
on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-0123-0002.
(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.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Alert Operators Transmission
(AOT) A55W002–12, dated December 13,
2012, including Inspection Flowchart. The
inspection flowchart attached to this AOT is
referred to in the AOT as ‘‘Appendix 1’’;
however, the flowchart page does not
identify itself as an appendix. While the
inspection flowchart page does specify the
AOT document number, it does not specify
a revision level or an issue date.
(ii) Reserved.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, 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.
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
[FR Doc. 2015–07799 Filed 4–8–15; 08:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0627; Directorate
Identifier 2013–NM–217–AD; Amendment
39–18126; AD 2015–06–08]
RIN 2120–AA64
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2011–09–
03 for all Lockheed Martin Corporation/
Lockheed Martin Aeronautics Company
Model 382, 382B, 382E, 382F, and 382G
airplanes. AD 2011–09–03 required
repetitive eddy current inspections to
detect cracks in the center wing upper
and lower rainbow fittings, and
corrective actions if necessary; and
repetitive replacement of rainbow
fittings, which would extend the
repetitive interval for the next
inspection. This new AD requires
reduced intervals for inspections of the
upper rainbow fittings. This AD was
prompted by analysis of in-service
cracking, which has shown that a
reduction in the inspection intervals is
necessary for the upper rainbow fittings.
We are issuing this AD to detect and
correct fatigue cracking of the upper and
lower rainbow fittings on the center
wings, which could grow large and lead
to the failure of the fitting and a
catastrophic failure of the center wing.
DATES: This AD is effective May 14,
2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 14, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of May 26, 2011 (76 FR
22311, April 21, 2011).
ADDRESSES: For service information
identified in this AD, contact Lockheed
Martin Corporation/Lockheed Martin
Aeronautics Company, Airworthiness
SUMMARY:
E:\FR\FM\09APR1.SGM
09APR1
]]>Agencies
[Federal Register Volume 80, Number 68 (Thursday, April 9, 2015)]
[Rules and Regulations]
[Pages 19009-19013]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-07799]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0123; Directorate Identifier 2013-NM-040-AD;
Amendment 39-18134; AD 2015-07-06]
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 A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-
605R, F4-622R, and C4-605R Variant F airplanes; and Model A310-203, -
204, -221, -222, -304, -322, -324, and -325 airplanes. This AD was
prompted by a report of inner skin disbonding damage on a rudder. This
AD requires repetitive ultrasonic inspections for disbonding of certain
rudders; an elasticity of laminate
[[Page 19010]]
checker inspection; a woodpecker or tap test inspection; venting the
core, if necessary; and repairing, if necessary. We are issuing this AD
to detect and correct rudder disbonding, which could affect the
structural integrity of the rudder.
DATES: This AD becomes effective May 14, 2015.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 14,
2015.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0123; 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--EAW, 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-2014-0123.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125;
fax 425-227-1149.
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 Airbus Model A300
B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and
C4-605R Variant F airplanes; and Model A310-203, -204, -221, -222, -
304, -322, -324, and -325 airplanes. The NPRM published in the Federal
Register on February 28, 2014 (79 FR 11355).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2013-0039, dated February 26, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-
622R, and C4-605R Variant F airplanes; and Model A310-203, -204, -221,
-222, -304, -322, -324, and -325 airplanes. The MCAI states:
One A310 operator found substantial inner skin disbonding damage
on a rudder that was previously inspected in accordance with the
instructions of Airbus Service Bulletin (SB) A310-55-2044. The
results of the subsequent investigation revealed that the most
probable cause of this damage was a blunt impact with no visible
damage from outside during the rudder handling. Damage like this
might grow with pressure variation during ground-air-ground cycles,
and tests performed with other rudders showed a rapid propagation of
damage during artificial pressure cycling.
This condition, if not detected and corrected, could affect the
structural integrity of the rudder.
To address this potential unsafe condition, Airbus issued Alert
Operators Transmission (AOT) A55W002-12 [dated December 13, 2012],
pending Aircraft Maintenance Manual (AMM) 27-21-21 PB401 revision to
update rudder handling procedures.
For the reasons described above, this [EASA] AD requires
ultrasonic test (UT) inspections of the affected rudders to detect
signs of disbonding and, depending on findings, accomplishment of
applicable corrective action(s).
Required actions also include an elasticity of laminate checker
inspection to detect external and internal disbonding, and a woodpecker
or tap test inspection to detect external disbonding. You may examine
the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0123-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (79
FR 11355, February 28, 2014) and the FAA's response to each comment.
Requests To Exclude Certain Airplanes From AD Requirements
Airbus requested that we revise paragraph (g) of the NPRM (79 FR
11355, February 28, 2014) to mirror the language in Airbus Alert
Operators Transmission (AOT) A55W002-12, dated December 13, 2012, which
takes into account whether or not the rudder has been removed and/or
installed since the last inspection. Airbus stated that the removal/
installation process is linked to the risk of the unseen damage
occurring to the rudder. Airbus suggested revised language for a
requirement to determine if the rudder has been removed or installed
since the last inspection.
In addition, FedEx requested that we revise paragraph (c) or (g) of
the NPRM (79 FR 11355, February 28, 2014) to state that, if the
installed rudder has been inspected (and not removed) per AD 2008-11-
05, Amendment 39-15527 (73 FR 29423, May 21, 2008), since its
installation, no further inspection will be required since the unsafe
condition would be alleviated.
UPS, FedEx, and Airbus requested that we revise the NPRM (79 FR
11355, February 28, 2014) to eliminate unnecessary AD tracking
requirements. UPS noted that the identified risk only exists in cases
where the rudder has been changed since inspection under AD 2008-11-05,
Amendment 39-15527 (73 FR 29423, May 21, 2008). UPS further stated that
the NPRM does not refer to AD 2008-11-05, even though the repetitive
ultrasonic inspections to detect disbonding in the NPRM are identical
to the requirements of paragraph (f)(2) of AD 2008-11-05. Also, UPS
stated that the airplane maintenance manual (AMM) has been updated as
of June 1, 2013, to include the same ultrasonic inspection specified in
both AD 2008-11-05 and the NPRM. UPS suggested revised wording for the
NPRM.
We concur with the requests to limit the airplanes subject to the
requirements of paragraph (g) of this AD. This AD does relate to AD
2008-11-05 (73 FR 29423, dated May 21, 2008), in that the ultrasonic
inspections are required in both ADs. This AD requires the ultrasonic
inspections for only certain airplanes. Therefore, we have added a new
paragraph (h)(2) in this AD. Paragraph (h)(2) of this AD specifies
that, for airplanes on which it can be conclusively determined that the
most recent inspection specified in Airbus Service Bulletin A310-55-
2044 or Airbus Service Bulletin A300-55-6043 was done on the airplane;
or the rudder was not removed for any reason since doing the most
recent inspection specified in Airbus Service Bulletin A310-55-2044 or
Airbus Service Bulletin A300-55-6043; no further action is necessary,
except as specified in paragraphs (j) and (k) of this AD.
We have also re-designated paragraphs (h), (h)(1), and (h)(2) of
the NPRM as paragraphs (h)(1), (h)(1)(i), and (h)(1)(ii) of this AD,
respectively.
Request To Remove Requirement To Refer to This AD in Repair Approvals
UPS requested that we revise the NPRM (79 FR 11355, February 28,
2014)
[[Page 19011]]
to remove the requirement to include the AD reference in repair
approvals. UPS noted its concerns that the NPRM will increase requests
for approval of alternative methods of compliance (AMOCs) and result in
delays to other services and actions addressed by the FAA on a daily
basis.
We concur with the commenter's request to remove from this AD the
requirement that repair approvals must specifically refer to 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. The MCAI or referenced service
information in an FAA AD often directs the owner/operator to contact
the manufacturer for corrective actions, such as a repair. Briefly, the
Airworthy Product paragraph allowed owners/operators to use corrective
actions provided by the manufacturer if those actions were FAA-
approved. In addition, the paragraph stated that any actions approved
by the State of Design Authority (or its delegated agent) are
considered to be FAA-approved.
In the NPRM (79 FR 11355, February 28, 2014), we proposed to
prevent the use of repairs that were not specifically developed to
correct the unsafe condition, by requiring that the repair approval
provided by the State of Design Authority or its delegated agent
specifically refer to this FAA AD. This change was intended to clarify
the method of compliance and to provide operators with better
visibility of repairs that are specifically developed and approved to
correct the unsafe condition. In addition, we proposed to change the
phrase ``its delegated agent'' to include ``the Design Approval Holder
(DAH) with a State of Design Authority's design organization approval
(DOA)'' to refer to a DAH authorized to approve required repairs for
the AD.
In its comments to the NPRM (79 FR 11355, February 28, 2014), UPS
stated the following: ``The proposed wording, being specific to
repairs, eliminates the interpretation that Airbus messages or other
approved EASA documents are acceptable for approving minor deviations
(corrective actions) needed during accomplishment of a[n AD] mandated
Airbus service bulletin.''
This comment has made the FAA 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 that 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, EASA, or Airbus's EASA 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 afforded previously
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 AD 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.
Other commenters to another NPRM having Directorate Identifier
2012-NM-101-AD (78 FR 78285, December 26, 2013) pointed out that in
many cases the foreign manufacturer's service bulletin and the foreign
authority's MCAI may have been issued some time before the FAA AD.
Therefore, the DOA may have provided U.S. operators with an approved
repair, developed with full awareness of the unsafe condition, before
the FAA AD is issued. Under these circumstances, to comply with the FAA
AD, the operator would be required to go back to the manufacturer's DOA
and obtain a new approval document, adding time and expense to the
compliance process with no safety benefit.
Based on these comments, we removed the requirement from this AD
that the DAH-provided repair specifically refer to this AD. Before
adopting such a requirement in the future, the FAA will coordinate with
affected DAHs and verify they are prepared to implement means to ensure
that their repair approvals consider the unsafe condition addressed in
an AD. Any such requirements will be adopted through the normal AD
rulemaking process, including notice-and-comment procedures, when
appropriate.
We have also decided not to include a generic reference to either
the ``delegated agent'' or the ``DAH with State of Design Authority
design organization approval,'' but instead we will provide the
specific delegation approval granted by the State of Design Authority
for the DAH.
Compliance Time Clarification
In paragraph (g) of this AD, for airplanes on which the part number
or serial number cannot be determined, we have revised the compliance
time of ``before further flight'' to ``within 3 months after the
effective date of this AD.'' This clarification corresponds to the
compliance time in the MCAI. We have determined that extending the
compliance time will provide an acceptable level of safety.
Conclusion
We reviewed the relevant data, considered the comments 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 minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 11355, February 28, 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 11355, February 28, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
[[Page 19012]]
Related Service Information Under 1 CFR Part 51
Airbus has issued AOT A55W002-12, dated December 13, 2012,
including Inspection Flowchart. The service information describes,
among other actions, procedures for an ultrasonic inspection along the
Z-profile of the rudder side panel. This service information is
reasonably available; see ADDRESSES for ways to access this service
information.
Costs of Compliance
We estimate that this AD affects 89 airplanes of U.S. registry. We
also estimate that it would take about 10 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 $75,650, or $850 per product.
We have received no definitive data that would enable us to provide
a cost estimate for the on-condition actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
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-2014-0123; 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 adding the following new airworthiness
directive (AD):
2015-07-06 Airbus: Amendment 39-18134. Docket No. FAA-2014-0123;
Directorate Identifier 2013-NM-040-AD.
(a) Effective Date
This AD becomes effective May 14, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes identified in paragraphs (c)(1)
and (c)(2) of this AD, except airplanes on which modification 08827
has been embodied in production.
(1) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R,
B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes,
certificated in any category, all manufacturer serial numbers.
(2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324,
and -325 airplanes, certificated in any category, all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 55; Stabilizers.
(e) Reason
This AD was prompted by a report of inner skin disbonding damage
on a rudder. We are issuing this AD to detect and correct rudder
disbonding, which could affect the structural integrity of the
rudder.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Identification of Part Number
Within 3 months after the effective date of this AD, identify
the rudder assembly part number (P/N) and serial number (S/N), in
accordance with Airbus Alert Operators Transmission (AOT) A55W002-
12, dated December 13, 2012, including Inspection Flowchart. If the
part number or serial number cannot be determined, within 3 months
after the effective date of this AD, identify the part number and
serial number, in accordance with a method approved by either 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).
(h) Inspections
(1) Except as provided by paragraph (h)(2) of this AD, if a
rudder assembly part number starting with A55471500 is found during
the inspection required by paragraph (g) of this AD, before further
flight, do an ultrasonic (UT) inspection for damage (e.g.,
disbonding and liquid ingress) of the rudder side panel along the Z-
profile and in the booster area, in accordance with Airbus AOT
A55W002-12, dated December 13, 2012, including Inspection Flowchart.
If any damage is found, before further flight, do the inspections to
confirm disbonding damage, as specified in paragraphs (h)(1)(i) and
(h)(1)(ii) of this AD, in accordance with Airbus AOT A55W002-12,
dated December 13, 2012.
(i) Do an elasticity of laminate checker inspection to detect
external and internal disbonding of the rudder side panel along the
Z-profile and in the booster area.
(ii) Do a woodpecker or tap test inspection to detect external
disbonding of the rudder side panel along the Z-profile and in the
booster area.
(2) For airplanes on which it can be conclusively determined
that the most recent inspection specified in Airbus Service Bulletin
A310-55-2044 or Airbus Service Bulletin A300-55-6043 was done on the
airplane; or the rudder was not removed for any reason since doing
the most recent inspection specified in Airbus Service Bulletin
A310-55-2044 or Airbus Service Bulletin A300-55-6043: No further
action is required by this AD, except as specified in paragraphs (j)
and (k) of this AD.
[[Page 19013]]
(i) Repair
(1) If any disbonding is confirmed during any inspection
required by paragraphs (h)(1)(i) and (h)(1)(ii) of this AD, before
further flight, repair as specified in paragraphs (i)(1)(i) and
(i)(1)(ii) of this AD, as applicable.
(i) If disbonding is less than or equal to 50 millimeters (mm)
in width and less than or equal to 150 mm in length, before further
flight, vent the core, using a method approved by either the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or EASA; or Airbus's EASA DOA. Within 100 flight
cycles after the UT inspection specified in paragraph (h) of this AD
is done, repair using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or EASA; or Airbus's EASA DOA.
(ii) If disbonding is greater than 50 mm in width or greater
than 150 mm in length, before further flight, repair using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
(2) If liquid ingress is confirmed during any inspection
required by paragraphs (h)(1)(i) and (h)(1)(ii) of this AD, before
further flight, repair using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or EASA; or Airbus's EASA DOA.
(j) Inspection after Re-Installation
If any rudder has been inspected as specified in Airbus Service
Bulletin A300-55-6043, Revision 01, dated December 3, 2007; or A310-
55-2044, Revision 01, dated December 3, 2007; as applicable; and has
been removed and re-installed on any airplane after this inspection,
that rudder must be re-inspected as required by paragraph (g) of
this AD; and all applicable actions required by paragraphs (h) and
(i) of this AD must be done.
(k) Parts Installation Limitation
As of the effective date of this AD, no person may install, on
any airplane, a rudder assembly having a part number starting with
A55471500, unless it has been inspected as required by paragraph (h)
of this AD, and all applicable actions required by paragraph (i) of
this AD have been done.
(l) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. Information may be
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Airbus's EASA DOA. If approved by the DOA, the approval must include
the DOA-authorized signature.
(m) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA Airworthiness Directive 2013-0039, dated February 26, 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-
0123-0002.
(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.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Alert Operators Transmission (AOT) A55W002-12, dated
December 13, 2012, including Inspection Flowchart. The inspection
flowchart attached to this AOT is referred to in the AOT as
``Appendix 1''; however, the flowchart page does not identify itself
as an appendix. While the inspection flowchart page does specify the
AOT document number, it does not specify a revision level or an
issue date.
(ii) Reserved.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, 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 March 27, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-07799 Filed 4-8-15; 08:45 am]
BILLING CODE 4910-13-P
