Airworthiness Directives; Airbus Airplanes, 7592-7596 [2014-02711]
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7592
Proposed Rules
Federal Register
Vol. 79, No. 27
Monday, February 10, 2014
DEPARTMENT OF AGRICULTURE
Animal and Plant Health Inspection
Service
9 CFR Part 3
[Docket No. APHIS–2012–0106]
Petition To Promulgate Standards for
Bears Under the Animal Welfare Act
Regulations
Animal and Plant Health
Inspection Service, USDA.
ACTION: Notice of petition; reopening of
comment period.
AGENCY:
We are reopening the
comment period for a petition
requesting that we amend the Animal
Welfare Act regulations to add specific
standards for the humane handling,
care, treatment, and transportation of all
species of bears held in captivity except
polar bears, for which there are already
standards. This action will allow
interested persons additional time to
prepare and submit comments.
DATES: The comment period for the
notice published November 26, 2013 (78
FR 70515) is reopened. We will consider
all comments that we receive on or
before March 12, 2014.
ADDRESSES: You may submit comments
by either of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov/#!document
Detail;D=APHIS-2012-0106-0001.
• Postal Mail/Commercial Delivery:
Send your comment to Docket No.
APHIS–2012–0106, Regulatory Analysis
and Development, PPD, APHIS, Station
3A–03.8, 4700 River Road Unit 118,
Riverdale, MD 20737–1238.
Supporting documents and any
comments we receive on this docket
may be viewed at https://www.
regulations.gov/#!docketDetail;D=
APHIS-2012-0106 or in our reading
room, located in Room 1141 of the
USDA South Building, 14th Street and
Independence Avenue SW.,
Washington, DC. Reading room hours
are 8 a.m. to 4:30 p.m., Monday through
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SUMMARY:
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Friday, except holidays. To be sure
someone is there to help you, please call
(202) 799–7039 before coming.
FOR FURTHER INFORMATION CONTACT: Dr.
Barbara Kohn, DVM, Senior Staff
Officer, USDA, APHIS, Animal Care,
4700 River Road Unit 84, Riverdale, MD
20737–1234; (301) 851–3751.
SUPPLEMENTARY INFORMATION:
DEPARTMENT OF TRANSPORTATION
Background
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
Airworthiness Directives; Airbus
Airplanes
On November 26, 2013, the Animal
and Plant Health Inspection Service
published in the Federal Register (78
FR 70515–70516, Docket No. APHIS–
2012–0106) a notice 1 requesting
comments on a petition from People for
the Ethical Treatment of Animals
requesting that we amend the Animal
Welfare Act regulations to add specific
standards for the humane handling,
care, treatment, and transportation of all
species of bears held in captivity except
polar bears, for which there are already
standards.
Comments on the notice were
required to be received on or before
January 27, 2014. We are reopening the
comment period on Docket No. APHIS–
2012–0106 for an additional 30 days.
This action will allow interested
persons additional time to prepare and
submit comments. We will also consider
all comments received between January
28, 2014 (the day after the close of the
original comment period) and the date
of this notice.
We encourage the submission of
scientific data, studies, or research to
support your comments and position,
including data or research that supports
any industry or professional standards
that pertain to the care of bears. We also
invite data on the costs and benefits
associated with any recommendations.
We will consider all comments and
recommendations we receive.
Authority: 7 U.S.C. 2131–2159; 7 CFR
2.22, 2.80, and 371.7.
Done in Washington, DC, this 3rd day of
February 2014.
Kevin Shea,
Administrator, Animal and Plant Health
Inspection Service.
[FR Doc. 2014–02756 Filed 2–7–14; 8:45 am]
BILLING CODE 3410–34–P
1 To view the notice, supporting documents, and
the comments we received, go to https://www.
regulations.gov/#!docketDetail;D=APHIS-20120106.
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0011; Directorate
Identifier 2013–NM–046–AD]
RIN 2120–AA64
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 98–13–23,
which applies to certain Airbus Model
A300 B4–600, B4–600R, and F4–600R
series airplanes, and Model A300 C4–
605R Variant F airplanes (collectively
called Model A300–600 series
airplanes). AD 98–13–23 requires
inspections to detect corrosion and
cracking of the lower horizontal
stabilizer cutout longeron, the corner
fitting, the skin strap, and the outer
skin; and repair, if necessary. Since we
issued AD 98–13–23, we have
determined that the risk of cracking is
higher than initially determined. This
proposed AD would reduce the
compliance times and repetitive
intervals, and changes the inspection
procedures. We are proposing this AD to
prevent cracking of the lower horizontal
stabilizer cutout longeron, the corner
fitting, the skin strap, and the outer
skin, which could result in reduced
structural integrity of the horizontalstabilizer cutout longeron.
DATES: We must receive comments on
this proposed AD by March 27, 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
SUMMARY:
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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
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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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–
0011; 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 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–2014–0011; Directorate Identifier
2013–NM–046–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
On June 15, 1998, we issued AD 98–
13–23, Amendment 39–10614 (63 FR
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34576, June 25, 1998). That AD requires
actions intended to address an unsafe
condition on the products listed above.
Since we issued AD 98–13–23,
Amendment 39–10614 (63 FR 34576,
June 25, 1998), a fleet survey and
updated fatigue and damage tolerance
analyses showed that the risk of cracks
for these airplanes is higher than
initially determined. The European
Aviation Safety Agency (EASA), which
is the Technical Agent for the Member
States of the European Community, has
issued EASA Airworthiness Directive
2013–0048, dated March 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:
During a full scale fatigue test, a crack was
found at the lower corner of the assembly of
the horizontal stabilizer cut-out, between
Frame (FR)87 and FR89 and between Stringer
(STGR)24 and STGR27, Left Hand (LH) and
Right Hand (RH) sides.
This condition, if not detected and
corrected, could reduce the structural
integrity of the aeroplane.
DGAC France issued AD * * * to require
repetitive visual and High Frequency Eddy
Current (HFEC) rotating probe inspections of
the affected areas and subsequent corrective
action, in case of cracks.
Since that [DGAC France] AD was issued,
a fleet survey and updated Fatigue and
Damage Tolerance analyses have been
performed to substantiate the second A300–
600 Extended Service Goal (ESG2) exercise.
The results of these analyses have shown that
the risk of cracks for these aeroplanes is
higher than initially determined and that,
consequently, the thresholds and intervals
must be reduced to allow timely detection of
these cracks and accomplishment of an
applicable corrective action.
For the reasons described above, this
[EASA] AD retains the requirements of DGAC
France AD * * *, which is superseded, and
requires the accomplishment of these actions
within the new thresholds and intervals
defined in Revision 03 of Airbus Service
Bulletin (SB) A300–53–6042 [dated August
30, 2012].
The initial compliance times for
airplanes with an average flight time
greater than 1.5 hours, depending on the
inspection area, are between before
18,000 total flight cycles and 38,100
total flight hours, whichever occurs
first; and before 42,500 total flight
cycles or 89,000 total flight hours,
whichever occurs first. The repetitive
compliance times for airplanes with an
average flight time above 1.5 hours,
depending on the inspection area, are
between intervals not to exceed 3,900
flight cycles or 8,200 flight hours,
whichever occurs first; and intervals not
to exceed 6,000 flight cycles or 12,700
flight hours, whichever occurs first.
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The initial compliance times for
airplanes with an average flight time of
1.5 hours or less, depending on the
inspection area, are between before
19,900 total flight cycles and 29,800
total flight hours, whichever occurs
first; and before 47,100 total flight
cycles or 70,500 total flight hours,
whichever occurs first. The repetitive
compliance times for airplanes with an
average flight time of 1.5 hours or less,
depending on inspection area, are
between intervals not to exceed 4,300
flight cycles or 6,400 flight hours,
whichever occurs first, and intervals not
to exceed 6,600 flight cycles or 9,900
flight hours, whichever occurs first.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating it in Docket No. FAA–
2014–0011.
Explanation of Change to Applicability
We have revised the applicability of
this AD to identify model designations
as published in the most recent type
certificate data sheet for the affected
models.
Relevant Service Information
Airbus has issued Mandatory Service
Bulletin A300–53–6042, Revision 03,
dated August 30, 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.
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 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.
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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 the 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
new requirements of this proposed AD
would require 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 State
of Design Authority design organization
approval, as applicable’’ in this
proposed AD to refer to a DAH
authorized to approve newly required
repairs for this proposed AD.
Costs of Compliance
We estimate that this proposed AD
would affect about 5 products of U.S.
registry. We estimate the following costs
to comply with this proposed AD.
ESTIMATED COSTS
Action
Labor cost
Inspections [retained actions from AD 98–13–23,
Amendment 39–10614 (63 FR 34576, June 25,
1998].
Inspections [new proposed action] .........................
268 work-hour × $85 per
hour = $22,780 per inspection cycle.
88 work-hour × $85 per
hour = $7,480 per inspection cycle.
We estimate the following costs to do
any necessary repairs that would be
Parts cost
Cost per product
Cost on U.S. operators
$0
$22,780 per inspection
cycle.
$45,560 per inspection
cycle (2 airplanes)
0
$7,480 per inspection
cycle.
$37,400 per inspection
cycle
required based on the results of the
proposed inspection. We have no way of
determining the number of aircraft that
might need these repairs:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per
product
Repair ..............................................
155 work-hours × $85 per hour = $13,175 ...............................................
$0
$13,175
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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.
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.
Regulatory Findings
The Proposed Amendment
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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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
removing airworthiness directive (AD)
98–13–23, Amendment 39–10614 (63
FR 34576, June 25, 1998), and adding
the following new AD:
■
Airbus: Docket No. FAA–2014–0011;
Directorate Identifier 2013–NM–046–AD.
(a) Comments Due Date
We must receive comments by March 27,
2014.
(b) Affected ADs
This AD supersedes AD 98–13–23,
Amendment 39–10614 (63 FR 34576, June
25, 1998).
(c) Applicability
This AD applies to Airbus Model A300 B4–
601, B4–603, B4–620, and B4–622 airplanes;
Model A300 B4–605R and B4–622R
airplanes; Model A300 F4–605R and F4–
622R airplanes; and Model A300 C4–605R
Variant F airplanes; certificated in any
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category; on which Airbus Modification 6146
has not been installed.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of
cracking found at the lower corner of the
horizontal stabilizer cutout longeron during a
full scale fatigue test, and a determination
that the risk of cracking is higher than
initially determined. We are issuing this AD
to prevent cracking of the lower horizontal
stabilizer cutout longeron, the corner fitting,
the skin strap, and the outer skin, which
could result in reduced structural integrity of
the horizontal-stabilizer cutout longeron.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Inspections and Corrective
Actions
This paragraph restates the requirements of
paragraphs (a), (b), (c), (d), and (e) of AD 98–
13–23, Amendment 39–10614 (63 FR 34576,
June 25, 1998), with revised service
information.
(1) Prior to the accumulation of 18,000
total landings, or within 2,000 landings after
July 30, 1998 (the effective date of AD 98–
13–23, Amendment 39–10614 (63 FR 34576,
June 25, 1998)), whichever occurs later:
Perform a visual and eddy current inspection
to detect cracks and/or corrosion of Areas 1
and 2 of the lower horizontal stabilizer
cutout longeron, in accordance with Airbus
Service Bulletin A300–53–6042, Revision 1,
dated February 20, 1995; or Airbus
Mandatory Service Bulletin A300–53–6042,
Revision 03, dated August 30, 2012. As of the
effective date of this AD, use only Airbus
Mandatory Service Bulletin A300–53–6042,
Revision 03, dated August 30, 2012, to do the
actions required by this paragraph.
(2) At the later of the times specified in
paragraphs (g)(2)(i) and (g)(2)(ii) of this AD:
Perform a visual and an eddy current
inspection to detect cracks and corrosion of
Area 3 of the lower horizontal stabilizer
cutout longeron, in accordance with Airbus
Service Bulletin A300–53–6042, Revision 1,
dated February 20, 1995; or Airbus
Mandatory Service Bulletin A300–53–6042,
Revision 03, dated August 30, 2012. As of the
effective date of this AD, use only Airbus
Mandatory Service Bulletin A300–53–6042,
Revision 03, dated August 30, 2012, to do the
actions required by this paragraph.
(i) Prior to the accumulation of 24,000 total
landings, but not before the accumulation of
18,000 total landings; or
(ii) Prior to the accumulation of 2,000
landings after July 30, 1998 (the effective date
of AD 98–13–23, Amendment 39–10614 (63
FR 34576, June 25, 1998)).
(3) If no cracking is detected during any
inspection required by paragraph (g)(1) or
(g)(2) of this AD: Before further flight, cold
work and ream the vacated fastener holes, in
accordance with Airbus Service Bulletin
A300–53–6042, Revision 1, dated February
20, 1995; or Airbus Mandatory Service
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Bulletin A300–53–6042, Revision 03, dated
August 30, 2012; and perform the
requirements of paragraph (g)(3)(i) or (g)(3)(ii)
of this AD, as applicable. As of the effective
date of this AD, use only Airbus Mandatory
Service Bulletin A300–53–6042, Revision 03,
dated August 30, 2012, to do the actions
required by this paragraph.
(i) For airplanes on which no cracking is
found in Area 1 or 2: Repeat the inspections
required by paragraph (g)(1) of this AD
thereafter at intervals not to exceed 6,000
flight cycles.
(ii) For airplanes on which no cracking is
found in Area 3: Perform the various followon actions in accordance with Airbus Service
Bulletin A300–53–6042, Revision 1, dated
February 20, 1995; or Airbus Mandatory
Service Bulletin A300–53–6042, Revision 03,
dated August 30, 2012. (The follow-on
actions include installing a new corner
fitting, installing a new longeron, and
performing a cold working procedure.) After
accomplishment of these follow-on actions,
no further action is required by this AD. After
the effective date of this AD, use only Airbus
Mandatory Service Bulletin A300–53–6042,
Revision 03, dated August 30, 2012, to do the
actions required by this paragraph.
(4) If any cracking is detected during any
inspection required by paragraph (g)(1) or
(g)(2) of this AD, perform the requirements of
paragraph (g)(4)(i) or (g)(4)(ii) of this AD, as
applicable.
(i) If any cracking is found in Area 1 or 3
that is within the limits specified in Airbus
Service Bulletin A300–53–6042, Revision 1,
dated February 20, 1995; or Airbus
Mandatory Service Bulletin A300–53–6042,
Revision 03, dated August 30, 2012: Before
further flight, repair in accordance with
Airbus Service Bulletin A300–53–6042,
Revision 1, dated February 20, 1995; or
Airbus Mandatory Service Bulletin A300–53–
6042, Revision 03, dated August 30, 2012. As
of the effective date of this AD, use only
Airbus Mandatory Service Bulletin A300–53–
6042, Revision 03, dated August 30, 2012, to
do the actions required by this paragraph.
(ii) If any cracking is found in Area 2, or
if any cracking is found in any area and that
cracking is beyond the limits described in
Airbus Service Bulletin A300–53–6042,
Revision 1, dated February 20, 1995; or
Airbus Mandatory Service Bulletin A300–53–
6042, Revision 03, dated August 30, 2012:
Before further flight, repair using 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,
or by the Design Approval Holder (DAH)
with EASA design organization approval).
(5) If any corrosion is detected during any
inspection required by paragraph (g) of this
AD, prior to further flight, repair the
corrosion, in accordance with Airbus Service
Bulletin A300–53–6042, Revision 1, dated
February 20, 1995; or Airbus Mandatory
Service Bulletin A300–53–6042, Revision 03,
dated August 30, 2012. As of the effective
date of this AD, use only Airbus Mandatory
Service Bulletin A300–53–6042, Revision 03,
dated August 30, 2012, to do the actions
required by this paragraph.
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(h) New Inspections
At the applicable times specified in
paragraph 1.E., ‘‘Compliance,’’ of Airbus
Mandatory Service Bulletin A300–53–6042,
Revision 03, dated August 30, 2012, except
as provided by paragraph (j)(1) and (j)(2) of
this AD: Do the actions specified in
paragraphs (h)(1), (h)(2), and (h)(3) of this
AD, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A300–53–6042, Revision 03, dated
August 30, 2012. Repeat the inspections,
thereafter, at the applicable intervals
specified in paragraph 1.E., ‘‘Compliance,’’ of
Airbus Mandatory Service Bulletin A300–53–
6042, Revision 03, dated August 30, 2012.
Doing the initial inspections required by
paragraph (h) of this AD and applicable
corrective actions required by paragraph (i) of
this AD terminates the requirements of
paragraph (g) of this AD.
(1) Do a general visual inspection for
cracking and corrosion of the lower
horizontal stabilizer cut-out longeron, the
corner fitting, the skin strap, and the skin
between frame (FR)87 and FR89 and between
stringers (STGR)24 and STGR27, left- and
right-hand sides.
(2) Do a high frequency eddy current
(HFEC) inspection for cracking of the flanges
of the lower corner fittings and the edges of
the outer skin and the edges of the longeron,
the skin strap, and the skin at the run-out of
the corner fitting above the last eight
fasteners.
(3) Do a rotating probe inspection for
cracking of the fastener holes. If no cracking
is found during the rotating probe inspection,
before further flight, do a cold expansion of
the fastener holes, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300–53–6042,
Revision 03, dated August 30, 2012.
(i) New Corrective Actions
(1) If any corrosion is found during any
inspection required by paragraph (h) of this
AD, before further flight, repair, in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A300–53–6042, Revision 03, dated
August 30, 2012.
(2) If any cracking is found during any
inspection required by paragraph (h) of this
AD, before further flight, repair in accordance
with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A300–53–
6042, Revision 03, dated August 30, 2012,
except where Airbus Mandatory Service
Bulletin A300–53–6042, Revision 03, dated
August 30, 2012, specifies to contact Airbus,
before further flight, repair using 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,
or the Design Approval Holder (DAH) with
EASA design organization approval). For a
repair method to be approved, the repair
approval must specifically refer to this AD.
(j) Exception
(1) Where Airbus Mandatory Service
Bulletin A300–53–6042, Revision 03, dated
August 30, 2012, specifies a grace period of
1950 flight cycles or 4100 flight hours, this
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10FEP1
7596
Federal Register / Vol. 79, No. 27 / Monday, February 10, 2014 / Proposed Rules
AD specifies the grace period after the
effective date of this AD.
(2) Where Airbus Mandatory Service
Bulletin A300–53–6042, Revision 03, dated
August 30, 2012, specifies a compliance time
‘‘after receipt of this service bulletin,’’ this
AD requires compliance within the specified
compliance time after the effective date of
this AD.
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.
(k) Credit for Previous Actions
This paragraph provides credit for the
corresponding actions required by paragraph
(g) of this AD, if those actions were
performed before the effective date of this AD
using Airbus Service Bulletin A300–53–6042,
Revision 01, dated February 20, 1995; or
Airbus Service Bulletin A300–53–6042,
Revision 02, dated April 28, 1998; which are
not incorporated by reference in this AD.
Issued in Renton, Washington, on January
27, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
emcdonald on DSK67QTVN1PROD with PROPOSALS
(l) 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;
telephone 425–227–2125; 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. AMOCs
approved for AD 98–13–23, Amendment 39–
10614 (63 FR 34576, June 25, 1998), are
approved as AMOCs for the corresponding
requirements of 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) European
Aviation Safety Agency (EASA)
Airworthiness Directive 2013–0048, dated
March 4, 2013, 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 it in Docket No.
FAA–2014–0011.
(2) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, 1 Rond Point Maurice
VerDate Mar<15>2010
17:14 Feb 07, 2014
Jkt 232001
[FR Doc. 2014–02711 Filed 2–7–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0004; Directorate
Identifier 2013–NM–143–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 A320–111, –211, –212,
and –231 airplanes. This proposed AD
was prompted by reports of broken
struts of the center wing box (CWB).
This proposed AD would require a
detailed inspection of the CWB struts
for cracking, and repair if necessary. We
are proposing this AD to detect and
correct cracked or broken struts, which
could result in strut failure and
consequent reduced structural integrity
of the airplane.
DATES: We must receive comments on
this proposed AD by March 27, 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:
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
For service information identified in
this proposed AD, contact Airbus,
Airworthiness Office—EAS, 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–
0004; 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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–227–1405; 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–2014–0004; Directorate Identifier
2013–NM–143–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
E:\FR\FM\10FEP1.SGM
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]]>Agencies
[Federal Register Volume 79, Number 27 (Monday, February 10, 2014)]
[Proposed Rules]
[Pages 7592-7596]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-02711]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0011; Directorate Identifier 2013-NM-046-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 98-13-23,
which applies to certain Airbus Model A300 B4-600, B4-600R, and F4-600R
series airplanes, and Model A300 C4-605R Variant F airplanes
(collectively called Model A300-600 series airplanes). AD 98-13-23
requires inspections to detect corrosion and cracking of the lower
horizontal stabilizer cutout longeron, the corner fitting, the skin
strap, and the outer skin; and repair, if necessary. Since we issued AD
98-13-23, we have determined that the risk of cracking is higher than
initially determined. This proposed AD would reduce the compliance
times and repetitive intervals, and changes the inspection procedures.
We are proposing this AD to prevent cracking of the lower horizontal
stabilizer cutout longeron, the corner fitting, the skin strap, and the
outer skin, which could result in reduced structural integrity of the
horizontal-stabilizer cutout longeron.
DATES: We must receive comments on this proposed AD by March 27, 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
[[Page 7593]]
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 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-
0011; 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
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-2014-0011;
Directorate Identifier 2013-NM-046-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
On June 15, 1998, we issued AD 98-13-23, Amendment 39-10614 (63 FR
34576, June 25, 1998). That AD requires actions intended to address an
unsafe condition on the products listed above.
Since we issued AD 98-13-23, Amendment 39-10614 (63 FR 34576, June
25, 1998), a fleet survey and updated fatigue and damage tolerance
analyses showed that the risk of cracks for these airplanes is higher
than initially determined. The European Aviation Safety Agency (EASA),
which is the Technical Agent for the Member States of the European
Community, has issued EASA Airworthiness Directive 2013-0048, dated
March 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:
During a full scale fatigue test, a crack was found at the lower
corner of the assembly of the horizontal stabilizer cut-out, between
Frame (FR)87 and FR89 and between Stringer (STGR)24 and STGR27, Left
Hand (LH) and Right Hand (RH) sides.
This condition, if not detected and corrected, could reduce the
structural integrity of the aeroplane.
DGAC France issued AD * * * to require repetitive visual and
High Frequency Eddy Current (HFEC) rotating probe inspections of the
affected areas and subsequent corrective action, in case of cracks.
Since that [DGAC France] AD was issued, a fleet survey and
updated Fatigue and Damage Tolerance analyses have been performed to
substantiate the second A300-600 Extended Service Goal (ESG2)
exercise. The results of these analyses have shown that the risk of
cracks for these aeroplanes is higher than initially determined and
that, consequently, the thresholds and intervals must be reduced to
allow timely detection of these cracks and accomplishment of an
applicable corrective action.
For the reasons described above, this [EASA] AD retains the
requirements of DGAC France AD * * *, which is superseded, and
requires the accomplishment of these actions within the new
thresholds and intervals defined in Revision 03 of Airbus Service
Bulletin (SB) A300-53-6042 [dated August 30, 2012].
The initial compliance times for airplanes with an average flight time
greater than 1.5 hours, depending on the inspection area, are between
before 18,000 total flight cycles and 38,100 total flight hours,
whichever occurs first; and before 42,500 total flight cycles or 89,000
total flight hours, whichever occurs first. The repetitive compliance
times for airplanes with an average flight time above 1.5 hours,
depending on the inspection area, are between intervals not to exceed
3,900 flight cycles or 8,200 flight hours, whichever occurs first; and
intervals not to exceed 6,000 flight cycles or 12,700 flight hours,
whichever occurs first.
The initial compliance times for airplanes with an average flight
time of 1.5 hours or less, depending on the inspection area, are
between before 19,900 total flight cycles and 29,800 total flight
hours, whichever occurs first; and before 47,100 total flight cycles or
70,500 total flight hours, whichever occurs first. The repetitive
compliance times for airplanes with an average flight time of 1.5 hours
or less, depending on inspection area, are between intervals not to
exceed 4,300 flight cycles or 6,400 flight hours, whichever occurs
first, and intervals not to exceed 6,600 flight cycles or 9,900 flight
hours, whichever occurs first.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating it in Docket No.
FAA-2014-0011.
Explanation of Change to Applicability
We have revised the applicability of this AD to identify model
designations as published in the most recent type certificate data
sheet for the affected models.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A300-53-6042, Revision
03, dated August 30, 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.
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 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.
[[Page 7594]]
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 the 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 new requirements of this
proposed AD would require 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 State of Design Authority design organization approval, as
applicable'' in this proposed AD to refer to a DAH authorized to
approve newly required repairs for this proposed AD.
Costs of Compliance
We estimate that this proposed AD would affect about 5 products of
U.S. registry. We estimate the following costs to comply with this
proposed AD.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts Cost on U.S.
Action Labor cost cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspections [retained actions from 268 work-hour x $85 $0 $22,780 per $45,560 per
AD 98-13-23, Amendment 39-10614 per hour = $22,780 inspection cycle. inspection cycle (2
(63 FR 34576, June 25, 1998]. per inspection cycle. airplanes)
Inspections [new proposed action]. 88 work-hour x $85 0 $7,480 per $37,400 per
per hour = $7,480 inspection cycle. inspection cycle
per inspection cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
would be required based on the results of the proposed inspection. We
have no way of determining the number of aircraft that might need these
repairs:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Repair.................................... 155 work-hours x $85 per hour = $0 $13,175
$13,175.
----------------------------------------------------------------------------------------------------------------
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. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
98-13-23, Amendment 39-10614 (63 FR 34576, June 25, 1998), and adding
the following new AD:
Airbus: Docket No. FAA-2014-0011; Directorate Identifier 2013-NM-
046-AD.
(a) Comments Due Date
We must receive comments by March 27, 2014.
(b) Affected ADs
This AD supersedes AD 98-13-23, Amendment 39-10614 (63 FR 34576,
June 25, 1998).
(c) Applicability
This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, and
B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model
A300 F4-605R and F4-622R airplanes; and Model A300 C4-605R Variant F
airplanes; certificated in any
[[Page 7595]]
category; on which Airbus Modification 6146 has not been installed.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracking found at the lower
corner of the horizontal stabilizer cutout longeron during a full
scale fatigue test, and a determination that the risk of cracking is
higher than initially determined. We are issuing this AD to prevent
cracking of the lower horizontal stabilizer cutout longeron, the
corner fitting, the skin strap, and the outer skin, which could
result in reduced structural integrity of the horizontal-stabilizer
cutout longeron.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspections and Corrective Actions
This paragraph restates the requirements of paragraphs (a), (b),
(c), (d), and (e) of AD 98-13-23, Amendment 39-10614 (63 FR 34576,
June 25, 1998), with revised service information.
(1) Prior to the accumulation of 18,000 total landings, or
within 2,000 landings after July 30, 1998 (the effective date of AD
98-13-23, Amendment 39-10614 (63 FR 34576, June 25, 1998)),
whichever occurs later: Perform a visual and eddy current inspection
to detect cracks and/or corrosion of Areas 1 and 2 of the lower
horizontal stabilizer cutout longeron, in accordance with Airbus
Service Bulletin A300-53-6042, Revision 1, dated February 20, 1995;
or Airbus Mandatory Service Bulletin A300-53-6042, Revision 03,
dated August 30, 2012. As of the effective date of this AD, use only
Airbus Mandatory Service Bulletin A300-53-6042, Revision 03, dated
August 30, 2012, to do the actions required by this paragraph.
(2) At the later of the times specified in paragraphs (g)(2)(i)
and (g)(2)(ii) of this AD: Perform a visual and an eddy current
inspection to detect cracks and corrosion of Area 3 of the lower
horizontal stabilizer cutout longeron, in accordance with Airbus
Service Bulletin A300-53-6042, Revision 1, dated February 20, 1995;
or Airbus Mandatory Service Bulletin A300-53-6042, Revision 03,
dated August 30, 2012. As of the effective date of this AD, use only
Airbus Mandatory Service Bulletin A300-53-6042, Revision 03, dated
August 30, 2012, to do the actions required by this paragraph.
(i) Prior to the accumulation of 24,000 total landings, but not
before the accumulation of 18,000 total landings; or
(ii) Prior to the accumulation of 2,000 landings after July 30,
1998 (the effective date of AD 98-13-23, Amendment 39-10614 (63 FR
34576, June 25, 1998)).
(3) If no cracking is detected during any inspection required by
paragraph (g)(1) or (g)(2) of this AD: Before further flight, cold
work and ream the vacated fastener holes, in accordance with Airbus
Service Bulletin A300-53-6042, Revision 1, dated February 20, 1995;
or Airbus Mandatory Service Bulletin A300-53-6042, Revision 03,
dated August 30, 2012; and perform the requirements of paragraph
(g)(3)(i) or (g)(3)(ii) of this AD, as applicable. As of the
effective date of this AD, use only Airbus Mandatory Service
Bulletin A300-53-6042, Revision 03, dated August 30, 2012, to do the
actions required by this paragraph.
(i) For airplanes on which no cracking is found in Area 1 or 2:
Repeat the inspections required by paragraph (g)(1) of this AD
thereafter at intervals not to exceed 6,000 flight cycles.
(ii) For airplanes on which no cracking is found in Area 3:
Perform the various follow-on actions in accordance with Airbus
Service Bulletin A300-53-6042, Revision 1, dated February 20, 1995;
or Airbus Mandatory Service Bulletin A300-53-6042, Revision 03,
dated August 30, 2012. (The follow-on actions include installing a
new corner fitting, installing a new longeron, and performing a cold
working procedure.) After accomplishment of these follow-on actions,
no further action is required by this AD. After the effective date
of this AD, use only Airbus Mandatory Service Bulletin A300-53-6042,
Revision 03, dated August 30, 2012, to do the actions required by
this paragraph.
(4) If any cracking is detected during any inspection required
by paragraph (g)(1) or (g)(2) of this AD, perform the requirements
of paragraph (g)(4)(i) or (g)(4)(ii) of this AD, as applicable.
(i) If any cracking is found in Area 1 or 3 that is within the
limits specified in Airbus Service Bulletin A300-53-6042, Revision
1, dated February 20, 1995; or Airbus Mandatory Service Bulletin
A300-53-6042, Revision 03, dated August 30, 2012: Before further
flight, repair in accordance with Airbus Service Bulletin A300-53-
6042, Revision 1, dated February 20, 1995; or Airbus Mandatory
Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012.
As of the effective date of this AD, use only Airbus Mandatory
Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012,
to do the actions required by this paragraph.
(ii) If any cracking is found in Area 2, or if any cracking is
found in any area and that cracking is beyond the limits described
in Airbus Service Bulletin A300-53-6042, Revision 1, dated February
20, 1995; or Airbus Mandatory Service Bulletin A300-53-6042,
Revision 03, dated August 30, 2012: Before further flight, repair
using 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, or by the Design
Approval Holder (DAH) with EASA design organization approval).
(5) If any corrosion is detected during any inspection required
by paragraph (g) of this AD, prior to further flight, repair the
corrosion, in accordance with Airbus Service Bulletin A300-53-6042,
Revision 1, dated February 20, 1995; or Airbus Mandatory Service
Bulletin A300-53-6042, Revision 03, dated August 30, 2012. As of the
effective date of this AD, use only Airbus Mandatory Service
Bulletin A300-53-6042, Revision 03, dated August 30, 2012, to do the
actions required by this paragraph.
(h) New Inspections
At the applicable times specified in paragraph 1.E.,
``Compliance,'' of Airbus Mandatory Service Bulletin A300-53-6042,
Revision 03, dated August 30, 2012, except as provided by paragraph
(j)(1) and (j)(2) of this AD: Do the actions specified in paragraphs
(h)(1), (h)(2), and (h)(3) of this AD, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A300-53-6042, Revision 03, dated August 30, 2012. Repeat the
inspections, thereafter, at the applicable intervals specified in
paragraph 1.E., ``Compliance,'' of Airbus Mandatory Service Bulletin
A300-53-6042, Revision 03, dated August 30, 2012. Doing the initial
inspections required by paragraph (h) of this AD and applicable
corrective actions required by paragraph (i) of this AD terminates
the requirements of paragraph (g) of this AD.
(1) Do a general visual inspection for cracking and corrosion of
the lower horizontal stabilizer cut-out longeron, the corner
fitting, the skin strap, and the skin between frame (FR)87 and FR89
and between stringers (STGR)24 and STGR27, left- and right-hand
sides.
(2) Do a high frequency eddy current (HFEC) inspection for
cracking of the flanges of the lower corner fittings and the edges
of the outer skin and the edges of the longeron, the skin strap, and
the skin at the run-out of the corner fitting above the last eight
fasteners.
(3) Do a rotating probe inspection for cracking of the fastener
holes. If no cracking is found during the rotating probe inspection,
before further flight, do a cold expansion of the fastener holes, in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012.
(i) New Corrective Actions
(1) If any corrosion is found during any inspection required by
paragraph (h) of this AD, before further flight, repair, in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012.
(2) If any cracking is found during any inspection required by
paragraph (h) of this AD, before further flight, repair in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012,
except where Airbus Mandatory Service Bulletin A300-53-6042,
Revision 03, dated August 30, 2012, specifies to contact Airbus,
before further flight, repair using 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, or the Design Approval Holder (DAH) with EASA
design organization approval). For a repair method to be approved,
the repair approval must specifically refer to this AD.
(j) Exception
(1) Where Airbus Mandatory Service Bulletin A300-53-6042,
Revision 03, dated August 30, 2012, specifies a grace period of 1950
flight cycles or 4100 flight hours, this
[[Page 7596]]
AD specifies the grace period after the effective date of this AD.
(2) Where Airbus Mandatory Service Bulletin A300-53-6042,
Revision 03, dated August 30, 2012, specifies a compliance time
``after receipt of this service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(k) Credit for Previous Actions
This paragraph provides credit for the corresponding actions
required by paragraph (g) of this AD, if those actions were
performed before the effective date of this AD using Airbus Service
Bulletin A300-53-6042, Revision 01, dated February 20, 1995; or
Airbus Service Bulletin A300-53-6042, Revision 02, dated April 28,
1998; which are not incorporated by reference in this AD.
(l) 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; 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. AMOCs
approved for AD 98-13-23, Amendment 39-10614 (63 FR 34576, June 25,
1998), are approved as AMOCs for the corresponding requirements of
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) European Aviation Safety Agency (EASA) Airworthiness
Directive 2013-0048, dated March 4, 2013, 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 it in Docket No.
FAA-2014-0011.
(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 January 27, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-02711 Filed 2-7-14; 8:45 am]
BILLING CODE 4910-13-P
