[Federal Register Volume 77, Number 99 (Tuesday, May 22, 2012)]
[Proposed Rules]
[Pages 30228-30230]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-12339]
[[Page 30228]]
=======================================================================
-----------------------------------------------------------------------
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 http://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 [email protected]; Internet http://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 http://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 http://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: [email protected].
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