[Federal Register Volume 79, Number 71 (Monday, April 14, 2014)]
[Proposed Rules]
[Pages 20837-20839]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-08303]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0230; Directorate Identifier 2013-NM-242-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 adopt a new airworthiness directive (AD) for
certain Airbus Model A300-600 series airplanes. This proposed AD was
prompted by reports of cracking found in the pylon box, which was due
to the stresses resulting from the pressure applied by the engines'
thrust reverser cowl bumpers. This proposed AD would require repetitive
high frequency eddy current (HFEC) inspections for cracking, and
replacement of all fittings if necessary. Replacement of all fittings
would terminate the repetitive HFEC inspections. We are proposing this
AD to detect and correct cracks of the pylon rib 5, which could result
in reduced structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by May 29, 2014.
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, 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 [email protected]; Internet http://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 http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0230; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this 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
[[Page 20838]]
to an address listed under the ADDRESSES section. Include ``Docket No.
FAA-2014-0230; Directorate Identifier 2013-NM-242-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 Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2013-0286, dated December 4, 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:
Cracks were found on the lower side of rib 5 in the pylon box on
A300 aeroplanes powered with General Electric engines.
Investigations revealed that these cracks were due to the
stresses resulting from the pressure applied by the thrust reverser
cowl bumpers.
This condition, if not detected and corrected, could affect the
structural integrity of the aeroplane.
Airbus developed an inspection programme to detect the cracks
and associated actions to correct them.
For the reasons described above, this [EASA] AD requires
repetitive [HFEC] inspections of the pylon rib 5 on the left hand
side (LH) and right hand (RH) side and, when cracks are detected,
replacement of the affected structural part(s) [Replacement of all
fittings would terminate the repetitive HFEC inspections.]
You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No.
FAA-2014-0230.
Relevant Service Information
Airbus has issued the following service bulletins. The actions
described in this service information are intended to correct the
unsafe condition identified in the MCAI.
Airbus Service Bulletin A300-54-6031, dated May 30, 1996.
Airbus Mandatory Service Bulletin A300-54-6034, Revision
02, dated August 26, 2013.
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
While paragraph (2) of EASA AD 2013-0286, dated December 4, 2013,
gives a compliance time of within 250 flight hours to replace fittings,
this AD requires replacement of those fitting before further flight.
Costs of Compliance
We estimate that this proposed AD affects 129 airplanes of U.S.
registry.
We also estimate that it would take about 9 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 $0 per
product. Based on these figures, we estimate the cost of this proposed
AD on U.S. operators to be $98,685 or $765 per product.
In addition, we estimate that any necessary follow-on actions would
take about 32 work-hours and require parts costing $2,450, for a cost
of $5,170 per product. We have no way of determining the number of
aircraft that might need this action.
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 airworthiness
directive (AD):
Airbus: Docket No. FAA-2014-0230; Directorate Identifier 2013-NM-
242-AD.
(a) Comments Due Date
We must receive comments by May 29, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to 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, except those on which Airbus Modification 11110 has been
embodied in production, or that have been modified in service as
specified in Airbus Service Bulletin A300-54-6031, dated May 30,
1996.
[[Page 20839]]
(d) Subject
Air Transport Association (ATA) of America Code 54, Nacelles/
Pylons.
(e) Reason
This AD was prompted by reports of cracking found in the pylon
box, which was due to the stresses resulting from the pressure
applied by the thrust reverser cowl bumpers. We are issuing this AD
to detect and correct cracks of the pylon rib 5, which could result
in reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection and Replacement
(1) Before the accumulation of 15,000 total flight hours since
the airplane's first flight, or within 6,000 flight hours after the
effective date of this AD, whichever occurs later, do a high
frequency eddy current (HFEC) inspection for cracking on the lower
area of rib 5 on the left-hand and right-hand side pylons, in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A300-54-6034, Revision 02, dated August 26, 2013.
Repeat the inspection thereafter at intervals not to exceed 15,000
flight hours.
(2) If any crack is found during any inspection required by
paragraph (g)(1) of this AD, before further flight, replace all the
fittings with new standard fittings, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-54-6031,
dated May 30, 1996.
(h) Terminating Action
Replacement of all fittings as required by paragraph (g)(2) of
this AD, or modification of pylons in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-54-6031,
dated May 30, 1996, terminates the repetitive HFEC inspections
required by paragraph (g)(1) of this AD.
(i) Credit for Previous Actions
This paragraph provides credit for the inspections required by
paragraph (g)(1) of this AD, if those actions were performed before
the effective date of this AD using Airbus Service Bulletin A300-54-
6034, Revision 01, dated September 14, 1999, which is not
incorporated by reference in this AD.
(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, 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.
(k) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) European Aviation Safety Agency Airworthiness Directive 2013-
0286, dated December 4, 2013, for related information. This MCAI may
be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No.
FAA-2014-0230.
(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 [email protected];
Internet http://www.airbus.com. You may view this service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on April 1, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-08303 Filed 4-11-14; 8:45 am]
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