Airworthiness Directives; Airbus Airplanes, 11355-11358 [2014-04495]
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Federal Register / Vol. 79, No. 40 / Friday, February 28, 2014 / Proposed Rules
Revision 1, dated October 25, 2007, including
Appendix 1, dated December 12, 2006, is
acceptable for compliance with the
replacement required by paragraph (l) of this
AD, provided the installation is
accomplished within the compliance time
specified in paragraph (l) of this AD; and,
except for airplanes that comply with
paragraph (m) of this AD, provided the
installation is accomplished within the
compliance time specified in paragraph (m)
of this AD.
(o) New Requirement: Concurrent
Modification
Prior to, or concurrently with, the
installation of the NLG unit required by
paragraph (l) of this AD or the optional
installation specified in paragraph (n) of this
AD, modify the nose landing gear (NLG)
bracket, in accordance with the
Accomplishment Instructions of Fokker
Services Bulletin SBF100–53–074, Revision
1, dated October 25, 2007.
(p) New Terminating Actions
Accomplishing the replacement specified
in paragraph (l) of this AD or the installation
specified in paragraph (n) of this AD
terminates the repetitive eddy current or dye
penetrant inspections required by paragraphs
(i) and (m)(1) of this AD.
(q) New Parts Installation Prohibition
(1) For airplanes equipped with MessierDowty nose landing gear (NLG) having part
number (P/N) 201071001 or 201071002, on
which a main fitting subassembly (MFSA)
having P/N 201071200, 201071228,
201071248, or 201071249 is installed: As of
October 3, 2000 (the effective date of AD
2000–17–03, Amendment 39–11876 (65 FR
52298, August 29, 2000), and until the
effective date of this AD: No person may
install an NLG having P/N 201071001 or
201071002 unless the installed MFSA has
been inspected, by means of an eddy current
or dye penetrant inspection, and corrected in
accordance with paragraph (i) of this AD.
(2) For all airplanes: As of the effective
date of this AD, no person may install an
NLG having P/N 201071001 or 201071002 on
any airplane.
emcdonald on DSK67QTVN1PROD with PROPOSALS
(r) Credit for Previous Actions
This paragraph provides credit for the
replacement required by paragraph (l) of this
AD, if those actions were performed before
the effective date of this AD using Fokker
Services B.V. Service Bulletin SBF 100–32–
119, dated January 31, 2000, provided part
number 201071003 or 201071004 nose gear
has been installed.
(s) 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
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to the International Branch, send it to ATTN:
Tom Rodriguez, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1137; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer, use these actions if they are
FAA-approved. Corrective actions are
considered FAA-approved if they were
approved by the State of Design Authority (or
its delegated agent, or the DAH with a State
of Design Authority’s design organization
approval). You are required to ensure the
product is airworthy before it is returned to
service.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(t) Related Information
(1) Refer to MCAI EASA Airworthiness
Directive 2012–0002R1, dated March 30,
2012, for related information. This MCAI
may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2014–0062.
(2) For service information identified in
this AD, contact Fokker Services B.V.,
Technical Services Dept., P.O. Box 1357,
2130 EL Hoofddorp, the Netherlands;
telephone +31 (0)88–6280–350; fax +31
(0)88–6280–111; email technicalservices@
fokker.com; Internet https://
www.myfokkerfleet.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.
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Issued in Renton, Washington, on February
14, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–04499 Filed 2–27–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0123; Directorate
Identifier 2013–NM–040–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt 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 proposed AD
was prompted by a report of inner skin
disbonding damage on a rudder. This
proposed AD would require repetitive
ultrasonic inspections for disbonding of
certain rudders; an elasticity of laminate
checker inspection; a woodpecker or tap
test inspection; venting the core, if
necessary; and repairing, if necessary.
We are proposing this AD to detect and
correct rudder disbonding, which could
affect the structural integrity of the
rudder.
SUMMARY:
We must receive comments on
this proposed AD by April 14, 2014.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Airbus SAS,
DATES:
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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.
emcdonald on DSK67QTVN1PROD with PROPOSALS
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0123; 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 proposed 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. Comments will
be available in the AD docket shortly
after receipt.
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:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2014–0123; Directorate Identifier
2013–NM–040–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2013–0039,
dated February 26, 2013 (referred to
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after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for the specified products. 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 by
searching for and locating Docket No.
FAA–2014–* * *.
Relevant Service Information
Airbus has issued Alert Operators
Transmission A55W002–12, dated
December 13, 2012. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
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Repair Approvals
In many FAA transport ADs, when
the service information specifies to
contact the manufacturer for further
instructions if certain discrepancies are
found, we typically include in the FAA
AD a requirement to accomplish the
action using a method approved by
either the FAA or the State of Design
Authority (or its delegated agent).
We have recently been notified that
certain laws in other countries do not
allow such delegation of authority, but
some countries do recognize design
approval organizations. In addition, we
have become aware that some U.S.
operators have used repair instructions
that were previously approved by a
State of Design Authority or a Design
Approval Holder (DAH) as a method of
compliance with this provision in FAA
ADs. Frequently, in these cases, the
previously approved repair instructions
come from the airplane structural repair
manual or DAH repair approval
statements that were not specifically
developed to address the unsafe
condition corrected by the AD. Using
repair instructions that were not
specifically approved for a particular
AD creates the potential for doing
repairs that were not developed to
address the unsafe condition identified
by the MCAI AD, the FAA AD, or the
applicable service information, which
could result in the unsafe condition not
being fully corrected.
To prevent the use of repairs that
were not specifically developed to
correct the unsafe condition, certain
requirements of this proposed AD
specify that the repair approval
specifically refer to the FAA AD. This
change is 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 use the phrase ‘‘its
delegated agent, or the DAH with the
State of Design Authority’s design
organization approval, as applicable’’ in
this proposed AD to refer to a DAH
authorized to approve certain required
repairs for this proposed AD.
Costs of Compliance
We estimate that this proposed 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 proposed
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
proposed AD on U.S. operators to be
$75,650, or $850 per product.
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We have received no definitive data
that would enable us to provide a cost
estimate for the on-condition actions
specified in this proposed AD.
Authority for This Rulemaking
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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 proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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 this proposed regulation:
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.
§ 39.13
[Amended]
2. Amend § 39.13 by adding the
following new AD:
■
Airbus: Docket No. FAA–2014–0123;
Directorate Identifier 2013–NM–040–AD.
(a) Comments Due Date
We must receive comments by April 14,
2014.
(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.
The Proposed Amendment
(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 the Accomplishment
Instructions of Airbus Alert Operator
Transmission (AOT) A55W002–12, dated
December 13, 2012. If the part number or
serial number cannot be determined, before
further flight, 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 EASA (or its
delegated agent, or by the Design Approval
Holder with EASA design organization
approval, as applicable). For an identification
method to be approved, the identification
method approval must specifically refer to
this AD.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
(h) Inspections
If a rudder assembly part number starting
with A55471500 is found during the
inspection required by paragraph (g) of this
List of Subjects in 14 CFR Part 39
emcdonald on DSK67QTVN1PROD with PROPOSALS
PART 39—AIRWORTHINESS
DIRECTIVES
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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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 Alert Operator
Transmission (AOT) A55W002–12, dated
December 13, 2012. If any damage is found,
before further flight, do the inspections to
confirm disbonding damage as specified in
paragraph (h)(1) and (h)(2) of this AD, in
accordance with Airbus Alert Operator
Transmission (AOT) A55W002–12, dated
December 13, 2012.
(1) 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.
(2) 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.
(i) Repair
(1) If any disbonding is confirmed during
any inspection required by paragraphs (h)(1)
and (h)(2) 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 its
delegated agent, or by the Design Approval
Holder with EASA design organization
approval, as applicable). 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 its
delegated agent, or the Design Approval
Holder with EASA’s design organization
approval, as applicable). For a repair method
to be approved, the repair approval must
specifically refer to this AD.
(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 its delegated
agent, or the Design Approval Holder with
EASA’s design organization approval, as
applicable). For a repair method to be
approved, the repair approval must
specifically refer to this AD.
(2) If liquid ingress is confirmed during
any inspection required by paragraphs (h)(1)
and (h)(2), before further flight, repair, using
a method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA (or its
delegated agent, or the Design Approval
Holder with EASA’s design organization
approval, as applicable). For a repair method
to be approved, the repair approval must
specifically refer to this AD.
(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
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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.
Issued in Renton, Washington, on February
14, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–04495 Filed 2–27–14; 8:45 am]
BILLING CODE 4910–13–P
(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, 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: 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, use these actions if they are
FAA approved. Corrective actions are
considered FAA-approved if they were
approved by the State of Design Authority (or
its delegated agent, or the Design Approval
Holder with a State of Design Authority’s
design organization approval, as applicable).
You are required to ensure the product is
airworthy before it is returned to service.
emcdonald on DSK67QTVN1PROD with PROPOSALS
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0039, dated
February 26, 2013; for related information,
which can be found in the AD docket on the
Internet at https://www.regulations.gov.
(2) 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.
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0124; Directorate
Identifier 2012–NM–197–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all
Airbus Model A300 series airplanes.
This proposed AD was prompted by an
analysis of the impacts of extended
service goal activities on Airbus Model
A300 series airplanes. This proposed
AD would require revising the
maintenance program. We are proposing
this AD to prevent failure of flight
critical systems.
DATES: We must receive comments on
this proposed AD by April 14, 2014.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0124; or in person at the Docket
Management Facility office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
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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. Comments will
be available in the AD docket shortly
after receipt.
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:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2014–0124; Directorate Identifier
2012–NM–197–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2012–0233,
dated November 7, 2012 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for the specified products. The MCAI
states:
The results of the Extended Service Goal
(ESG) exercise for A300 series aeroplanes
(75,000 flight hours (FH) or 48,000 flight
cycles (FC), whichever occurs first) identified
certain operational tests as Airworthiness
Limitation Items (ALI), necessary to ensure
the safety objectives for aeroplanes which
have accumulated or exceeded 60,000 FH.
These ALI are not fully new, since all nine
tasks derive from existing Maintenance
Planning Document (MPD) tasks.
Consequently, the intervals of those nine
tasks can no longer be escalated or retained
at an interval higher than that specified in
this [EASA] AD for each task.
Failure to comply with these tasks within
the established maximum intervals could be
detrimental to the safety of the affected
aeroplanes.
E:\FR\FM\28FEP1.SGM
28FEP1
]]>Agencies
[Federal Register Volume 79, Number 40 (Friday, February 28, 2014)]
[Proposed Rules]
[Pages 11355-11358]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-04495]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0123; Directorate Identifier 2013-NM-040-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt 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
proposed AD was prompted by a report of inner skin disbonding damage on
a rudder. This proposed AD would require repetitive ultrasonic
inspections for disbonding of certain rudders; an elasticity of
laminate checker inspection; a woodpecker or tap test inspection;
venting the core, if necessary; and repairing, if necessary. We are
proposing this AD to detect and correct rudder disbonding, which could
affect the structural integrity of the rudder.
DATES: We must receive comments on this proposed AD by April 14, 2014.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus SAS,
[[Page 11356]]
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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0123; 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 proposed 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. Comments will be available in the AD docket shortly after
receipt.
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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0123;
Directorate Identifier 2013-NM-040-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2013-0039, dated February 26, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:
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
by searching for and locating Docket No. FAA-2014-* * *.
Relevant Service Information
Airbus has issued Alert Operators Transmission A55W002-12, dated
December 13, 2012. The actions described in this service information
are intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Repair Approvals
In many FAA transport ADs, when the service information specifies
to contact the manufacturer for further instructions if certain
discrepancies are found, we typically include in the FAA AD a
requirement to accomplish the action using a method approved by either
the FAA or the State of Design Authority (or its delegated agent).
We have recently been notified that certain laws in other countries
do not allow such delegation of authority, but some countries do
recognize design approval organizations. In addition, we have become
aware that some U.S. operators have used repair instructions that were
previously approved by a State of Design Authority or a Design Approval
Holder (DAH) as a method of compliance with this provision in FAA ADs.
Frequently, in these cases, the previously approved repair instructions
come from the airplane structural repair manual or DAH repair approval
statements that were not specifically developed to address the unsafe
condition corrected by the AD. Using repair instructions that were not
specifically approved for a particular AD creates the potential for
doing repairs that were not developed to address the unsafe condition
identified by the MCAI AD, the FAA AD, or the applicable service
information, which could result in the unsafe condition not being fully
corrected.
To prevent the use of repairs that were not specifically developed
to correct the unsafe condition, certain requirements of this proposed
AD specify that the repair approval specifically refer to the FAA AD.
This change is 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 use the phrase ``its delegated agent, or the DAH with the
State of Design Authority's design organization approval, as
applicable'' in this proposed AD to refer to a DAH authorized to
approve certain required repairs for this proposed AD.
Costs of Compliance
We estimate that this proposed 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 proposed 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 proposed AD on U.S. operators to be $75,650, or $850 per product.
[[Page 11357]]
We have received no definitive data that would enable us to provide
a cost estimate for the on-condition actions specified in this proposed
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. Amend Sec. 39.13 by adding the following new AD:
Airbus: Docket No. FAA-2014-0123; Directorate Identifier 2013-NM-
040-AD.
(a) Comments Due Date
We must receive comments by April 14, 2014.
(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 the Accomplishment Instructions of Airbus Alert
Operator Transmission (AOT) A55W002-12, dated December 13, 2012. If
the part number or serial number cannot be determined, before
further flight, 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 EASA (or its delegated agent, or by the Design Approval Holder
with EASA design organization approval, as applicable). For an
identification method to be approved, the identification method
approval must specifically refer to this AD.
(h) Inspections
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
Alert Operator Transmission (AOT) A55W002-12, dated December 13,
2012. If any damage is found, before further flight, do the
inspections to confirm disbonding damage as specified in paragraph
(h)(1) and (h)(2) of this AD, in accordance with Airbus Alert
Operator Transmission (AOT) A55W002-12, dated December 13, 2012.
(1) 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.
(2) 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.
(i) Repair
(1) If any disbonding is confirmed during any inspection
required by paragraphs (h)(1) and (h)(2) 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 its delegated agent, or by the Design
Approval Holder with EASA design organization approval, as
applicable). 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 its delegated agent, or the
Design Approval Holder with EASA's design organization approval, as
applicable). For a repair method to be approved, the repair approval
must specifically refer to this AD.
(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 its delegated agent, or the
Design Approval Holder with EASA's design organization approval, as
applicable). For a repair method to be approved, the repair approval
must specifically refer to this AD.
(2) If liquid ingress is confirmed during any inspection
required by paragraphs (h)(1) and (h)(2), before further flight,
repair, using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA (or
its delegated agent, or the Design Approval Holder with EASA's
design organization approval, as applicable). For a repair method to
be approved, the repair approval must specifically refer to this AD.
(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
[[Page 11358]]
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, 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) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer, use these actions if they
are FAA approved. Corrective actions are considered FAA-approved if
they were approved by the State of Design Authority (or its
delegated agent, or the Design Approval Holder with a State of
Design Authority's design organization approval, as applicable). You
are required to ensure the product is airworthy before it is
returned to service.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2013-0039, dated February 26,
2013; for related information, which can be found in the AD docket
on the Internet at https://www.regulations.gov.
(2) 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.
Issued in Renton, Washington, on February 14, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-04495 Filed 2-27-14; 8:45 am]
BILLING CODE 4910-13-P
