[Federal Register Volume 78, Number 128 (Wednesday, July 3, 2013)]
[Proposed Rules]
[Pages 40069-40072]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-15959]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0539; Directorate Identifier 2012-NM-145-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of Proposed Rulemaking (NPRM).
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SUMMARY: We propose to supersede airworthiness directive (AD) 2000-12-
11, that applies to certain Model A300 B4-600 and Model A300 B4-600R
series airplanes. That AD currently requires repetitive inspections to
detect cracks in the bolt holes inboard and outboard of rib 9 on the
bottom booms of the front and rear wing spars, and repair if necessary.
Since we issued that AD, we have determined through a fleet survey and
an updated fatigue and damage tolerance analysis that the risk for
fatigue cracking on the front and rear spar bottom booms is higher than
was initially determined. This proposed AD would reduce the initial
inspection compliance time and repetitive inspection interval. We are
proposing this AD to detect and correct fatigue cracks in the bolt
holes of the wing spars, which could result in reduced structural
integrity of a wing spar.
DATES: We must receive comments on this proposed AD by August 19, 2013.
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, 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 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, WA 98057-3356; phone: (425) 227-2125;
fax: (425) 227-1149.
[[Page 40070]]
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-2013-0539;
Directorate Identifier 2012-NM-145-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
On June 9, 2000, we issued AD 2000-12-11, Amendment 39-11789 (65 FR
37853, June 19, 2000). That AD requires actions intended to address an
unsafe condition on the products listed above.
Since we issued AD 2000-12-11, the European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Community, has issued EASA Airworthiness Directive 2012-0138,
dated July 26, 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:
Full fatigue tests carried out by the manufacturer revealed
crack initiation from the bolts holes at inboard and outboard of rib
9, on the front and rear spar bottom booms. Similar cracks at the
same area were reported by A300-600 aeroplane operators.
This condition, if not detected and corrected, could affect the
structural integrity of the aeroplane.
To address this unsafe condition, [Direction
G[eacute]n[eacute]rale de l'Aviation Civile] DGAC France issued AD
94-208-169(B)R2 [which corresponds to FAA AD 95-07-05 Amendment 39-
9187 (60 FR 17990, April 10, 1995)] to require an ultrasonic
inspection of holes inboard and outboard of rib 9 on the front and
rear spar bottom booms on Left Hand and Right Hand wings.
Since that [DGAC] AD was issued, a fleet survey and updated
Fatigue and Damage Tolerance analysis have been performed in order
to substantiate the second A300-600 Extended Service Goal (ESG2)
exercise. The results of these analyses have shown that the risk for
these aeroplanes is higher than initially determined and that,
consequently, the inspection threshold and interval must be reduced
to allow timely detection of cracks and the accomplishment of an
applicable corrective action [and related investigative action].
For the reasons explained above, this new [EASA] AD retains the
requirements of DGAC France AD 94-208-169(B)R2, which is superseded,
and requires the accomplishment instructions within the new
thresholds and intervals specified in Revision 04 of Airbus
Mandatory Service Bulletin (SB) A300-57-6037 [dated February 24,
2011].
The related investigative action includes doing inspections for
cracking. The corrective actions include oversizing holes and
installing new fasteners, and for certain conditions, contacting the
FAA or EASA (or its delegated agent) for instructions. You may obtain
further information by examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A300-57-6037, Revision
04, dated February 24, 2011. 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 AD and the MCAI or Service Information
Airbus Mandatory Service Bulletin A300-57-6037, Revision 04, dated
February 24, 2011, specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions using a method approved by the
FAA or the EASA (or its delegated agent). In light of the type of
repair that would be required to address the unsafe condition, and
consistent 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.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 29 products of U.S. registry.
We estimate that it would take about 18 work-hours per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about $2,874
per product. Where the service information lists required parts costs
that are covered under warranty, we have assumed that there will be no
charge for these parts. As we do not control warranty coverage for
affected parties, some parties may incur costs higher than estimated
here. Based on these figures, we estimate the cost of the proposed AD
on U.S. operators to be $127,716, or $4,404 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);
[[Page 40071]]
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
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2000-12-11, Amendment 39-11789 (65 FR 37853, June 19, 2000), and adding
the following new AD:
Airbus: Docket No. FAA-2013-0539; Directorate Identifier 2012-NM-
145-AD.
(a) Comments Due Date
We must receive comments by August 19, 2013.
(b) Affected ADs
This AD supersedes AD 2000-12-11, Amendment 39-11789 (65 FR
37853, June 19, 2000).
(c) Applicability
This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, B4-
622, B4-605R and B4-622R airplanes; certificated in any category;
all manufacturer serial numbers, except airplanes on which Airbus
Modification 10161 has been incorporated in production.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by a fleet survey and an updated fatigue
and damage tolerance analysis indicating a high risk for fatigue
cracking on the front and rear spar bottom booms. We are issuing
this AD to detect and correct fatigue cracks in the bolt holes of
the wing spars, which could result in reduced structural integrity
of a wing spar.
(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 Inspections
At the applicable time specified in paragraph (g)(1) or (g)(2)
of this AD: Perform an ultrasonic inspection to detect fatigue
cracking of the bolt holes inboard and outboard of rib 9 on the
bottom booms of the front and rear wing spars, in accordance with
the Accomplishment Instruction of Airbus Mandatory Service Bulletin
A300-57-6037, Revision 04, dated February 24, 2011, except as
specified in paragraph (k) of this AD. Repeat the inspection
thereafter at intervals not to exceed the applicable time specified
in paragraph (h) of this AD.
(1) For normal range airplanes, at the later of the times in
paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
(i) Within 14,100 flight cycles or 30,400 flight hours since
airplane first flight or within 14,100 flight cycles or 30,400
flight hours since airplane modification done as specified in the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6039,
whichever occurs first.
(ii) Within 1,600 flight cycles or 3,400 flight hours, whichever
occurs first after the effective date of this AD.
(2) For short range airplanes, at the later of the times in
paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
(i) Within 15,200 flight cycles or 22,800 flight hours since
airplane first flight, or since airplane modification done as
specified in the Accomplishment Instructions of Airbus Service
Bulletin A300-57-6039, whichever occurs first.
(ii) Within 1,700 flight cycles or 2,500 flight hours, whichever
occurs first after the effective date of this AD.
(h) Repetitive Inspection Compliance Times
At the applicable time specified in paragraph (h)(1) or (h)(2)
of this AD, repeat the inspection required by paragraph (g) of this
AD.
(1) For normal range airplanes: Repeat the inspection thereafter
at intervals not to exceed 3,900 flight cycles or 8,400 flight
hours, whichever occurs first.
(2) For short range airplanes: Repeat the inspection thereafter
at intervals not to exceed 4,200 flight cycles or 6,300 flight
hours, whichever occurs first.
(i) Corrective Action for Cracking
If any crack is found during any inspection required by
paragraph (g) of this AD: Before further flight, repair the cracking
including applicable related investigative and corrective actions,
in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300-57-6037, Revision 04, dated February
24, 2011, except as specified in paragraph (k) of this AD. Do
related investigative and corrective actions before further flight.
Thereafter, repeat the inspection required by paragraph (g) of this
AD at intervals not to exceed the applicable time specified in
paragraph (h) of this AD. Corrective actions required by this
paragraph do not constitute terminating action for the repetitive
inspections required by paragraph (h) of this AD.
(j) Definition of Short Range and Long Range Airplanes
For purposes of this AD, short range airplanes are those with an
average flight time lower than 1.5 flight hours, and normal range
airplanes are those with an average flight time equal to or higher
than 1.5 flight hours.
(k) Exception to Service Information
Where the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A300-57-6037, Revision 04, dated February 24, 2011,
specify contacting Airbus for an approved repair: Before further
flight, contact either the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA, or the European Aviation Safety
Agency (EASA) (or its delegated agent), for instructions and do
those instructions.
(l) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using any of the service
bulletins specified in paragraphs (l)(1) through (l)(4) of this AD.
(1) Airbus Mandatory Service Bulletin A300-57-6037, dated August
1, 1994.
(2) Airbus Mandatory Service Bulletin A300-57-6037, Revision 01,
dated August 31, 1995.
(3) Airbus Mandatory Service Bulletin A300-57-6037, Revision 02,
dated January 9, 2001.
(4) Airbus Mandatory Service Bulletin A300-57-6037, Revision 03,
dated January 11, 2002.
(m) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: (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.
[[Page 40072]]
(3) AMOCs Approved Previously: AMOCs approved previously in
accordance with AD 2000-12-11, Amendment 39-11789 (65 FR 37853, June
19, 2000), are approved as AMOCs for the corresponding provisions of
this AD.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
European Aviation Safety Agency Airworthiness Directive 2012-0138,
dated July 26, 2012, and the service information specified in
paragraphs (m)(1)(i) through (m)(1)(iii) of this AD; for related
information.
(i) Airbus Mandatory Service Bulletin A300-57-6037, Revision 04,
dated February 24, 2011.
(ii) Airbus Service Bulletin A300-57-6037, dated August 1, 1994.
(iii) Airbus Service Bulletin A300-57-6037, Revision 01, dated
August 31, 1995.
(2) For service information identified in this 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, WA. For information on
the availability of this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on June 18, 2013.
John Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-15959 Filed 7-2-13; 8:45 am]
BILLING CODE 4910-13-P