Airworthiness Directives; Airbus Airplanes, 30228-30230 [2012-12339]
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30228
Federal Register / Vol. 77, No. 99 / Tuesday, May 22, 2012 / Proposed Rules
Federal Aviation Administration
For information on the availability of
this material at the FAA, call 425–227–
1221.
14 CFR Part 39
Examining the AD Docket
[Docket No. FAA–2012–0488; Directorate
Identifier 2011–NM–106–AD]
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this 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,
Washington 98057–3356; telephone
(425) 227–2125; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
DEPARTMENT OF TRANSPORTATION
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 B4–600 and A300
B4–600R, Model A300, and Model A310
series airplanes. This proposed AD was
prompted by reports of fatigue cracking
in the crossbeams at the junction of the
actuator beam of the lower deck cargo
door. This proposed AD would require
repetitive inspections of the crossbeams
of certain fuselage frames, and repair if
necessary. We are proposing this AD to
detect and correct cracking of the
crossbeams at the junction of the
actuator beam of the lower deck cargo
door, which could result in failure to
withstand ultimate load conditions, and
consequent reduced structural integrity
of the airplane.
DATES: We must receive comments on
this proposed AD by July 6, 2012.
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—
EAW (Airworthiness Office), 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 review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington.
srobinson on DSK4SPTVN1PROD with PROPOSALS
SUMMARY:
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16:50 May 21, 2012
Jkt 226001
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–2012–0488; Directorate Identifier
2011–NM–106–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 aviation authority
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2011–0086,
dated May 12, 2011 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
Some operators have reported cracked
crossbeams at the junction with the lower
deck cargo door actuator beam. The
investigation results indicate that these
cracks initiated in the fastener hole,
propagated in a vertical direction and were
due to fatigue.
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This condition, if not corrected, could lead,
in case of cracks propagation in a crossbeam
(upper and lower web), to the floor grid being
unable to withstand ultimate load condition.
For the reasons described above, this
[EASA] AD requires repetitive [high
frequency eddy current] inspections [for
cracks] of certain crossbeams including those
previously repaired by the Structure Repair
Manual (SRM) or Repair Approval Sheet
(RAS).
The required actions include
repairing any cracking. As an option,
modifying the crossbeams terminates
the repetitive inspections. You may
obtain further information by examining
the MCAI in the AD docket.
Relevant Service Information
Airbus has issued the following
Service Bulletins:
• A300–53–0389, Revision 02, dated
April 27, 2011;
• A310–53–2133, Revision 02, dated
April 27, 2011; and
• A300–53–6166, Revision 01, dated
May 21, 2010.
Airbus has also issued the following
Mandatory Service Bulletins:
• A300–53–0390, dated January 15,
2010;
• A310–53–2134, dated January 15,
2010; and
• A300–53–6168, dated January 15,
2010.
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.
Differences Between This Proposed AD
and the MCAI or Service Information
Where the service information
identified in the ‘‘Relevant Service
Information’’ section specifies to contact
the manufacturer for instructions on
certain cracking conditions, this
proposed AD would require repairing
those conditions using a method
approved by the FAA or EASA (or its
delegated agent). In light of the type of
repair that would be required to address
the unsafe condition, and consistent
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Federal Register / Vol. 77, No. 99 / Tuesday, May 22, 2012 / Proposed Rules
with existing bilateral airworthiness
agreements, we have determined that,
for this proposed AD, a repair approved
by the FAA or the EASA (or its
delegated agent) would be acceptable for
compliance with this proposed AD.
Although the MCAI allows further
flight after cracks are found during
compliance with the required action,
this proposed AD would require repair
of any cracked/damaged frames before
further flight. This difference has been
coordinated with the EASA.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 152 products of U.S.
registry. We also estimate that it would
take about 1 work-hour per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of the
proposed AD on U.S. operators to be
$12,920, or $85 per product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
srobinson on DSK4SPTVN1PROD with PROPOSALS
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:
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16:50 May 21, 2012
Jkt 226001
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
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
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
The Boeing Company: Docket No. FAA–
2012–0488; Directorate Identifier 2011–
NM–106–AD.
(a) Comments Due Date
We must receive comments by July 6, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A300 B2–
1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103,
and B4–203; Model A300 B4–601, B4–603,
B4–620, and B4–622 airplanes; Model A300
B4–605R and B4–622R airplanes; and Model
A310–203, –204, –221, –222, –304, –322,
–324, and –325 airplanes; certificated in any
category; except those identified in paragraph
(c)(1), (c)(2), or (c)(3) of this AD, as
applicable.
(1) Airplanes on which Airbus Service
Bulletin A300–53–6166 (Airbus Modification
13434) has been embodied in service (for
Model A300 B4–600 and A300 B4–600R
series airplanes).
(2) Airplanes on which Airbus Service
Bulletin A300–53–0389 (Airbus Modification
13434) has been embodied in service (for
Model A300 series airplanes).
(3) Airplanes on which Airbus Service
Bulletin A310–53–2133 (Airbus Modification
13434) has been embodied in service (for
Model A310 series airplanes).
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30229
(d) Subject
Air Transport Association (ATA) of
America Code 53: Fuselage.
(e) Reason
This AD was prompted by reports of
fatigue cracking in the crossbeams at the
junction of the actuator beam of the lower
deck cargo door. We are issuing this AD to
detect and correct cracking of the crossbeams
at the junction of actuator beam of the lower
deck cargo door, which could result in failure
to withstand ultimate load conditions, and
consequent reduced structural integrity of the
airplane.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Repetitive High Frequency Eddy Current
Inspections
(1) For airplanes on which the crossbeams
at frames (FR) 22/23 and FR 61/62 have not
been repaired as specified in an Airbus
structural repair manual or repair approval
sheet as of the effective date of this AD:
Before the accumulation of 10,000 total flight
cycles since first flight of the airplane, or
within 600 flight cycles after the effective
date of this AD, whichever occurs later;
perform a high frequency eddy current
(HFEC) inspection for cracking of the
crossbeam fuselage frame stations FR 22/23
and FR 61/62, in accordance with the
Accomplishment Instructions of the
applicable service bulletin identified in
paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of
this AD. Repeat the inspection thereafter at
intervals not to exceed 600 flight cycles until
the modification specified in paragraph (i) of
this AD has been done.
(i) Airbus Mandatory Service Bulletin
A300–53–0390, dated January 15, 2010 (for
Model A300 series airplanes).
(ii) Airbus Mandatory Service Bulletin
A310–53–2134, dated January 15, 2010 (for
Model A310 series airplanes).
(iii) Airbus Mandatory Service Bulletin
A300–53–6168, dated January 15, 2010 (for
Model A300–600 series airplanes).
(2) For airplanes on which the crossbeams
at FR 22/23 and FR 61/62 have been repaired
as specified in an Airbus structural repair
manual or repair approval sheet as of the
effective date of this AD: Before the
accumulation of 10,000 total flight cycles
since first flight of the airplane, or within 600
flight cycles after the effective date of this
AD, whichever occurs later; repair in
accordance with a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA) (or
its delegated agent).
(h) Corrective Action
If any crack is found during any inspection
required by paragraph (g) of this AD: Before
further flight repair any crack using a method
approved by the Manager, International
Branch, ANM–116; or EASA (or its delegated
agent).
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Federal Register / Vol. 77, No. 99 / Tuesday, May 22, 2012 / Proposed Rules
(i) Optional Terminating Action
Modifying the crossbeam fuselage frame
stations FR 22/23 and FR 61/62, including
doing rotating probe inspections for cracks of
fastener holes in accordance with the
Accomplishment Instructions of the
applicable service bulletin identified in
paragraph (i)(1), (i)(2), or (i)(3) of this AD,
and repairing any crack using a method
approved by the Manager, International
Branch, ANM–116; or EASA (or its delegated
agent), terminates the repetitive inspections
required by paragraph (g)(1) of this AD.
(1) Airbus Service Bulletin A300–53–0389,
Revision 02, dated April 27, 2011 (for Model
A300 series airplanes).
(2) Airbus Service Bulletin A310–53–2133,
Revision 02, dated April 27, 2011 (for Model
A310 series airplanes).
(3) Airbus Service Bulletin A300–53–6166,
Revision 01, dated May 21, 2010 (for Model
A300–600 series airplanes).
srobinson on DSK4SPTVN1PROD with PROPOSALS
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, Washington 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 or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(k) Related Information
Refer to EASA Airworthiness Directive
2011–0086, dated May 12, 2011; and the
applicable service bulletin identified in
paragraphs (k)(1), (k)(2), (k)(3), (k)(4), (k)(5),
and (k)(6) of this AD for related information.
(1) Airbus Service Bulletin A300–53–0389,
Revision 02, dated April 27, 2011.
(2) Airbus Service Bulletin A310–53–2133,
Revision 02, dated April 27, 2011.
(3) Airbus Service Bulletin A300–53–6166,
Revision 01, dated May 21, 2010. (4) Airbus
Mandatory Service Bulletin A300–53–0390,
dated January 15, 2010.
(5) Airbus Mandatory Service Bulletin
A310–53–2134, dated January 15, 2010.
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16:50 May 21, 2012
Jkt 226001
(6) Airbus Mandatory Service Bulletin
A300–53–6168, dated January 15, 2010.
Issued in Renton, Washington, on May 10,
2012.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–12339 Filed 5–21–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0528; Directorate
Identifier 2011–SW–068–AD]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
Deutschland Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all
Eurocopter Deutschland GmbH Model
MBB–BK117 C–2 helicopters with
certain Generator Control Units (GCU)
installed. This proposed AD is
prompted by reports of internal short
circuits in certain GCUs. The proposed
actions are intended to replace any
affected GCUs to prevent a short circuit,
which could result in a loss of electrical
generating power, loss of systems
required for continued safe flight and
landing, and subsequent loss of control
of the helicopter.
DATES: We must receive comments on
this proposed AD by July 23, 2012.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays.
Examining the AD Docket: You may
examine the AD docket on the Internet
at https://www.regulations.gov or in
person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
SUMMARY:
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The AD docket contains this proposed
AD, the economic 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 service information identified in
this proposed AD, contact American
Eurocopter Corporation, 2701 N. Forum
Drive, Grand Prairie, TX 75052,
telephone (972) 641–0000 or (800) 232–
0323, fax (972) 641–3775, or at https://
www.eurocopter.com/techpub. You may
review a copy of the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
2601 Meacham Blvd., Room 663, Fort
Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT:
George Schwab, Aviation Safety
Engineer, FAA, Rotorcraft Directorate,
Safety Management Group, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5114; email
george.schwab@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to participate in this
rulemaking by submitting written
comments, data, or views. We also
invite comments relating to the
economic, environmental, energy, or
federalism impacts that might result
from adopting the proposals in this
document. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit only one time.
We will file in the docket all
comments that we receive, as well as a
report summarizing each substantive
public contact with FAA personnel
concerning this proposed rulemaking.
Before acting on this proposal, we will
consider all comments we receive on or
before the closing date for comments.
We will consider comments filed after
the comment period has closed if it is
possible to do so without incurring
expense or delay. We may change this
proposal in light of the comments we
receive.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued AD No.: 2011–
0149R1, dated September 30, 2011 (AD
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]]>Agencies
[Federal Register Volume 77, Number 99 (Tuesday, May 22, 2012)]
[Proposed Rules]
[Pages 30228-30230]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-12339]
[[Page 30228]]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0488; Directorate Identifier 2011-NM-106-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 B4-600 and A300 B4-600R, Model A300, and
Model A310 series airplanes. This proposed AD was prompted by reports
of fatigue cracking in the crossbeams at the junction of the actuator
beam of the lower deck cargo door. This proposed AD would require
repetitive inspections of the crossbeams of certain fuselage frames,
and repair if necessary. We are proposing this AD to detect and correct
cracking of the crossbeams at the junction of the actuator beam of the
lower deck cargo door, which could result in failure to withstand
ultimate load conditions, and consequent reduced structural integrity
of the airplane.
DATES: We must receive comments on this proposed AD by July 6, 2012.
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--EAW (Airworthiness Office), 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 review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, Washington. 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; 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, Washington 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-2012-0488;
Directorate Identifier 2011-NM-106-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 aviation
authority for the Member States of the European Community, has issued
EASA Airworthiness Directive 2011-0086, dated May 12, 2011 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
Some operators have reported cracked crossbeams at the junction
with the lower deck cargo door actuator beam. The investigation
results indicate that these cracks initiated in the fastener hole,
propagated in a vertical direction and were due to fatigue.
This condition, if not corrected, could lead, in case of cracks
propagation in a crossbeam (upper and lower web), to the floor grid
being unable to withstand ultimate load condition.
For the reasons described above, this [EASA] AD requires
repetitive [high frequency eddy current] inspections [for cracks] of
certain crossbeams including those previously repaired by the
Structure Repair Manual (SRM) or Repair Approval Sheet (RAS).
The required actions include repairing any cracking. As an option,
modifying the crossbeams terminates the repetitive inspections. You may
obtain further information by examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued the following Service Bulletins:
A300-53-0389, Revision 02, dated April 27, 2011;
A310-53-2133, Revision 02, dated April 27, 2011; and
A300-53-6166, Revision 01, dated May 21, 2010.
Airbus has also issued the following Mandatory Service Bulletins:
A300-53-0390, dated January 15, 2010;
A310-53-2134, dated January 15, 2010; and
A300-53-6168, dated January 15, 2010.
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.
Differences Between This Proposed AD and the MCAI or Service
Information
Where the service information identified in the ``Relevant Service
Information'' section specifies to contact the manufacturer for
instructions on certain cracking conditions, this proposed AD would
require repairing those conditions using a method approved by the FAA
or EASA (or its delegated agent). In light of the type of repair that
would be required to address the unsafe condition, and consistent
[[Page 30229]]
with existing bilateral airworthiness agreements, we have determined
that, for this proposed AD, a repair approved by the FAA or the EASA
(or its delegated agent) would be acceptable for compliance with this
proposed AD.
Although the MCAI allows further flight after cracks are found
during compliance with the required action, this proposed AD would
require repair of any cracked/damaged frames before further flight.
This difference has been coordinated with the EASA.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 152 products of U.S. registry. We also estimate that
it would take about 1 work-hour per product to comply with the basic
requirements of this proposed AD. The average labor rate is $85 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $12,920, or $85 per product.
We have received no definitive data that would enable us to provide
cost estimates 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
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
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]
2. The FAA amends Sec. 39.13 by adding the following new AD:
The Boeing Company: Docket No. FAA-2012-0488; Directorate Identifier
2011-NM-106-AD.
(a) Comments Due Date
We must receive comments by July 6, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-
203, B4-2C, B4-103, and B4-203; Model A300 B4-601, B4-603, B4-620,
and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; and
Model A310-203, -204, -221, -222, -304, -322, -324, and -325
airplanes; certificated in any category; except those identified in
paragraph (c)(1), (c)(2), or (c)(3) of this AD, as applicable.
(1) Airplanes on which Airbus Service Bulletin A300-53-6166
(Airbus Modification 13434) has been embodied in service (for Model
A300 B4-600 and A300 B4-600R series airplanes).
(2) Airplanes on which Airbus Service Bulletin A300-53-0389
(Airbus Modification 13434) has been embodied in service (for Model
A300 series airplanes).
(3) Airplanes on which Airbus Service Bulletin A310-53-2133
(Airbus Modification 13434) has been embodied in service (for Model
A310 series airplanes).
(d) Subject
Air Transport Association (ATA) of America Code 53: Fuselage.
(e) Reason
This AD was prompted by reports of fatigue cracking in the
crossbeams at the junction of the actuator beam of the lower deck
cargo door. We are issuing this AD to detect and correct cracking of
the crossbeams at the junction of actuator beam of the lower deck
cargo door, which could result in failure to withstand ultimate load
conditions, and consequent reduced structural integrity of the
airplane.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Repetitive High Frequency Eddy Current Inspections
(1) For airplanes on which the crossbeams at frames (FR) 22/23
and FR 61/62 have not been repaired as specified in an Airbus
structural repair manual or repair approval sheet as of the
effective date of this AD: Before the accumulation of 10,000 total
flight cycles since first flight of the airplane, or within 600
flight cycles after the effective date of this AD, whichever occurs
later; perform a high frequency eddy current (HFEC) inspection for
cracking of the crossbeam fuselage frame stations FR 22/23 and FR
61/62, in accordance with the Accomplishment Instructions of the
applicable service bulletin identified in paragraph (g)(1)(i),
(g)(1)(ii), or (g)(1)(iii) of this AD. Repeat the inspection
thereafter at intervals not to exceed 600 flight cycles until the
modification specified in paragraph (i) of this AD has been done.
(i) Airbus Mandatory Service Bulletin A300-53-0390, dated
January 15, 2010 (for Model A300 series airplanes).
(ii) Airbus Mandatory Service Bulletin A310-53-2134, dated
January 15, 2010 (for Model A310 series airplanes).
(iii) Airbus Mandatory Service Bulletin A300-53-6168, dated
January 15, 2010 (for Model A300-600 series airplanes).
(2) For airplanes on which the crossbeams at FR 22/23 and FR 61/
62 have been repaired as specified in an Airbus structural repair
manual or repair approval sheet as of the effective date of this AD:
Before the accumulation of 10,000 total flight cycles since first
flight of the airplane, or within 600 flight cycles after the
effective date of this AD, whichever occurs later; repair in
accordance with a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA) (or its delegated agent).
(h) Corrective Action
If any crack is found during any inspection required by
paragraph (g) of this AD: Before further flight repair any crack
using a method approved by the Manager, International Branch, ANM-
116; or EASA (or its delegated agent).
[[Page 30230]]
(i) Optional Terminating Action
Modifying the crossbeam fuselage frame stations FR 22/23 and FR
61/62, including doing rotating probe inspections for cracks of
fastener holes in accordance with the Accomplishment Instructions of
the applicable service bulletin identified in paragraph (i)(1),
(i)(2), or (i)(3) of this AD, and repairing any crack using a method
approved by the Manager, International Branch, ANM-116; or EASA (or
its delegated agent), terminates the repetitive inspections required
by paragraph (g)(1) of this AD.
(1) Airbus Service Bulletin A300-53-0389, Revision 02, dated
April 27, 2011 (for Model A300 series airplanes).
(2) Airbus Service Bulletin A310-53-2133, Revision 02, dated
April 27, 2011 (for Model A310 series airplanes).
(3) Airbus Service Bulletin A300-53-6166, Revision 01, dated May
21, 2010 (for Model A300-600 series airplanes).
(j) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington
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 or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(k) Related Information
Refer to EASA Airworthiness Directive 2011-0086, dated May 12,
2011; and the applicable service bulletin identified in paragraphs
(k)(1), (k)(2), (k)(3), (k)(4), (k)(5), and (k)(6) of this AD for
related information.
(1) Airbus Service Bulletin A300-53-0389, Revision 02, dated
April 27, 2011.
(2) Airbus Service Bulletin A310-53-2133, Revision 02, dated
April 27, 2011.
(3) Airbus Service Bulletin A300-53-6166, Revision 01, dated May
21, 2010. (4) Airbus Mandatory Service Bulletin A300-53-0390, dated
January 15, 2010.
(5) Airbus Mandatory Service Bulletin A310-53-2134, dated
January 15, 2010.
(6) Airbus Mandatory Service Bulletin A300-53-6168, dated
January 15, 2010.
Issued in Renton, Washington, on May 10, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-12339 Filed 5-21-12; 8:45 am]
BILLING CODE 4910-13-P
