Airworthiness Directives; Airbus Airplanes, 56526-56532 [2014-22467]
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56526
Federal Register / Vol. 79, No. 183 / Monday, September 22, 2014 / Proposed Rules
submissions at https://
www.regulations.gov as well as enter the
comment submissions into ADAMS.
The NRC does not routinely edit
comment submissions to remove
identifying or contact information.
If you are requesting or aggregating
comments from other persons for
submission to the NRC, then you should
inform those persons not to include
identifying or contact information that
they do not want to be publicly
disclosed in their comment submission.
Your request should state that the NRC
does not routinely edit comment
submissions to remove such information
before making the comment
submissions available to the public or
entering the comment submissions into
ADAMS.
II. The Petition
Anthony R. Pietrangelo, Vice
President, and Chief Nuclear Officer,
NEI, submitted a PRM dated June 12,
2014 (ADAMS Accession No.
ML14184B120), requesting that the NRC
revise its cyber security requirements.
Specifically, the petitioner requests that
the NRC revise 10 CFR 73.54(a) to
ensure the regulation is not overly
burdensome for NRC licensees, and
adequately protects the public health
and safety and common defense and
security. The petitioner requests that the
NRC promptly initiate rulemaking to
resolve this matter. The NRC has
determined that the petition meets the
threshold sufficiency requirements for a
petition for rulemaking under 10 CFR
2.802 ‘‘Petition for rulemaking,’’ and the
petition has been docketed as PRM–73–
18. The NRC is requesting public
comment on the petition for rulemaking.
asabaliauskas on DSK5VPTVN1PROD with RULES
III. The Petitioner
The petition states that NEI ‘‘is
responsible for establishing a unified
industry position on matters affecting
the nuclear energy industry, including
the regulatory aspects of generic
operational and technical issues.’’ The
petition further states that ‘‘NEI member
companies are specifically affected by
the NRC’s cyber security regulations.’’
The NEI claims it provides a ‘‘principal
interface between power reactor
licensees and the NRC on matters of
policy, including cyber security-related
policy.’’
IV. Discussion of the Petition
The petitioner states that power
reactor licensees are required to
establish and maintain a physical
protection program to protect against
the design basis threat of radiological
sabotage, and summarizes the physical
protection program and the attributes of
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the design basis threat of radiological
sabotage described in 10 CFR 73.1,
which include: (1) An external physical
assault, (2) an internal threat, (3) a land
vehicle bomb assault, (4) a waterborne
vehicle bomb assault, and (5) a cyber
attack. The petitioner asserts that to
prevent radiological sabotage, licensees
have well-established programs to
identify the set of personnel systems,
and equipment that must be protected
against the design basis threat in order
to prevent significant core damage and
spent fuel sabotage.
The petitioner noted that NRC’s cyber
security requirements, found in 10 CFR
73.54, provide the programmatic
requirements to defend against the
design basis threat of radiological
sabotage through a cyber attack, and that
Section 73.54(a)(1) requires licensees to
protect certain digital assets against
cyber attack even though those digital
assets, if compromised, would not
adversely impact the systems and
equipment necessary to prevent
significant core damage and spent fuel
sabotage. The petitioner asserts that the
current regulations require NRC
licensees to protect one set of systems
and equipment against the effects of
four of the attributes of the design basis
threat (physical assault; internal threat;
land vehicle bomb assault; waterborne
vehicle bomb assault), and a
substantially broader set of assets
against the fifth design basis threat
attribute, cyber attack. Further, the
petitioner contends that this regulatory
language is inconsistent with both the
agency’s intent in promulgating the
cyber security requirements and the
NRC’s programmatic requirements to
defend against other attributes of the
radiological sabotage design basis threat.
The petitioner argues that the
language in 10 CFR 73.54(a)(1)
unnecessarily diverts NRC licensee
attention and resources away from the
protection of assets that have a nexus to
radiological safety. The petitioner
asserts that this provision burdens NRC
reactor licensees without providing a
commensurate enhancement in the
protection of the public health and
safety, or plant security. Furthermore,
the petitioner claims that for digital
assets that do not reasonably require
protection against radiological sabotage,
the considerable time, resources, and
cost needed to protect them against
cyber attack is unjustified. In this
regard, the petitioner asserts that the
current cyber security regulations fail to
comply with the Commission’s
Principles of Good Regulation.
The petitioner states that the industry
has brought to the attention of the NRC
staff the significant problems created by
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the current scoping language in 10 CFR
73.54(a), and has determined that
revisions to NRC regulations are needed
to address this problem. The petitioner
further states that implementing the
revisions proposed herein will not
adversely affect NRC licensees’ ability to
ensure that public health, safety, and
security are being adequately protected.
NEI contends that the change
proposed in its petition is the single
most important near-term regulatory
improvement that can be made in the
area of cyber security. The petitioner
claims that it would provide a
substantial benefit to regulatory clarity
and stability by assuring that licensees
have protected those assets that, if
compromised by a cyber attack, would
be inimical to the health and safety of
the public.
The complete text of the petition is
available for review as described in
Section I.A. of this document.
Because the petitioner has satisfied
the docketing criteria in 10 CFR 2.802,
‘‘Petition for rulemaking,’’ the NRC has
docketed this petition as PRM–73–18.
The NRC is reviewing the issues raised
by the petitioner to determine whether
they should be considered in the NRC’s
rulemaking process.
Dated at Rockville, Maryland, this 15th day
of September, 2014.
For the Nuclear Regulatory Commission.
Annette L. Vietti-Cook,
Secretary of the Commission.
[FR Doc. 2014–22523 Filed 9–19–14; 8:45 am]
BILLING CODE 7590–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0648; Directorate
Identifier 2013–NM–136–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2010–06–
04, for certain Airbus Model A300 B2–
1C, B2–203, B2K–3C, B4–103, B4–203,
B4–2C airplanes; Model A310 series
airplanes; Model A300 B4–600 series
airplanes; and Model A300 B4–600R
series airplanes. AD 2010–06–04
currently requires repetitive inspections
to detect cracks of the pylon side panels
SUMMARY:
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(upper section) at rib 8; and corrective
actions if necessary. Since we issued AD
2010–06–04, fleet survey and updated
fatigue and damage tolerance analyses
were done. We have determined that
reduced compliance times are
necessary. This proposed AD would
continue to require repetitive
inspections for cracking of the pylons 1
and 2 side panels (upper section) at rib
8 with reduced compliance times, and
corrective actions if necessary. This
proposed AD would also require
repetitive post-repair and postmodification inspections and repair if
necessary. This proposed AD would
also remove certain airplanes having a
certain modification from the
applicability. We are proposing this AD
to detect and correct cracking of pylon
side panels (upper section) at rib 8,
which could lead to reduced structural
integrity of the pylon primary structure,
which could cause detachment of the
engine from the fuselage.
DATES: We must receive comments on
this proposed AD by November 6, 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.
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; 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
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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–2014–0648; Directorate Identifier
2013–NM–136–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 March 4, 2010, we issued AD
2010–06–04, Amendment 39–16228 (75
FR 11428, March 11, 2010); corrected
May 4, 2010 (75 FR 23572). AD 2010–
06–04 requires actions intended to
address an unsafe condition on Airbus
Model A300 B2–1C, B2–203, B2K–3C,
B4–103, B4–203, B4–2C airplanes;
Model A310 series airplanes; Model
A300 B4–600 series airplanes; and
Model A300 B4–600R series airplanes.
Since we issued AD 2010–06–04, fleet
survey and updated fatigue and damage
tolerance analyses were done. We have
determined that reduced compliance
times are necessary. The European
Aviation Safety Agency (EASA), which
is the Technical Agent for the Member
States of the European Community, has
issued EASA Airworthiness Directive
2013–0136R1, dated July 30, 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 pylon side panels
(upper section) at rib 8 on Airbus A300, A310
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56527
and A300–600 aeroplanes equipped with
General Electric engines. Investigation of
these findings indicated that this problem
was likely to also affect aeroplanes of this
type design with other engine installations.
This condition, if not detected and
corrected, could lead to reduced strength of
the pylon primary structure, possibly
resulting in pylon structural failure and inflight loss of an engine.
Prompted by these findings, EASA issued
AD 2008–0181 [https://www.regulations.gov/
#!documentDetail;D=FAA-2009-0789-0002]
[which corresponds to FAA AD 2010–06–04,
Amendment 39–16228 (75 FR 11428, March
11, 2010); corrected May 4, 2010 (75 FR
23572)] to require repetitive detailed visual
inspections [of the pylon side panels (upper
section) at rib 8] and, depending on
aeroplane configuration and/or findings, the
accomplishment of applicable corrective
action(s).
Since that [EASA] AD was issued, a fleet
survey and updated Fatigue and Damage
Tolerance analyses 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 consequently, the
threshold and interval must be reduced to
allow timely detection of these cracks and
the accomplishment of applicable correction
action(s).
EASA issued AD 2013–0136 [https://
ad.easa.europa.eu/ad/2013-0136R1] which
retained the requirements of EASA AD 2008–
0181, which was superseded, and required
the inspections to be accomplished within
reduced thresholds and intervals.
After publication of EASA AD 2013–0136,
it appeared that Airbus Mod 03599 had no
influence on the aeroplane configuration
affected by this AD. At the same time Airbus
Service Bulletin (SB) A300–54–6015
Revision 3 was not integrally taken into
account as this revision no longer identifies
configuration 3 aeroplanes.
For the reasons described above, EASA
2013–0136 is revised to exclude Airbus Mod
03599 from the applicability and to delete the
reference to the configuration 3 for A300–600
aeroplanes.
Corrective actions include doing a
repair. This proposed AD also provides
an optional modification (installing a
doubler), which would terminate the
repetitive inspections. Required actions
also include repetitive post-repair and
post-modification inspections and
repair if necessary.
Depending on airplane configuration:
Initial compliance times range from
4,800 flight cycles or 24,100 flight
hours, and 9,700 flight cycles or 19,400
flight hours. Initial post-modification
and post-repair inspection compliance
times range from 7,200 flight cycles or
36,400 flight hours, and 10,400 flight
cycles or 50,800 flight hours, depending
on inspection type. Repetitive intervals
range from 2,600 flight cycles or 13,000
flight hours, and 6,700 flight cycles or
18,700 flight hours. You may examine
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the MCAI in the AD docket on the
Internet at https://www.regulations.gov
by searching for and locating it in
Docket No. FAA–2014–0648.
Relevant Service Information
Airbus has issued the Service
Bulletins listed below. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
• Airbus Service Bulletin A300–54–
0075, Revision 03, dated March 27,
2013.
• Airbus Service Bulletin A300–54–
6015, Revision 03, dated April 11, 2013.
• Airbus Service Bulletin A310–54–
2018, Revision 03, dated April 11, 2013.
• Airbus Service Bulletin A300–54–
0081, dated August 11, 1993.
• Airbus Service Bulletin A300–54–
6021, Revision 02, dated May 21, 2008.
• Airbus Service Bulletin A310–54–
2024, dated August 11, 1993.
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.
proposed AD, this proposed AD would
require that you repair any cracking
before further flight.
Differences Between This Proposed AD
and the MCAI or Service Information
Although the MCAI or service
information allows further flight after
cracks are found during compliance
with the required actions of this
Costs of Compliance
Changes to This NPRM
Table 2, ‘‘Service Bulletins,’’ in AD
2010–06–04, Amendment 39–16228 (75
FR 11428, March 11, 2010), has been
converted to text in paragraph (g)(9) of
this AD.
Table 3, ‘‘Previous Service
Information,’’ in AD 2010–06–04,
Amendment 39–16228 (75 FR 11428,
March 11, 2010), has been converted to
text in paragraph (m)(1) of this AD.
We estimate that this proposed AD
affects 156 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Inspection [retained actions from AD 2010–06–
04, Amendment 39–16228 (75 FR 11428,
March 11, 2010); corrected May 4, 2010 (75
FR 23572)].
Inspection [new proposed actions] .....................
4 work-hours × $85 per
hour = $340.
$0
24 work-hours × $85
per hour = $2,040
per inspection cycle.
0
We estimate the following costs to do
any necessary repairs that would be
Parts cost
Cost per product
Cost on U.S. operators
$340 .............................
$53,040.
$2,040 per inspection
cycle.
$318,240 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
Labor cost
Parts cost
Repair ........................................................................
Optional Modification .................................................
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Action
58 work-hours × $85 per hour = $4,930 ...................
Up to 48 work-hours × $85 per hour = $4,080 .........
$3,910 ..............
Up to $1,026 .....
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
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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;
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Cost per product
$8,840.
Up to $5,106.
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:
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Federal Register / Vol. 79, No. 183 / Monday, September 22, 2014 / Proposed Rules
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. Amend § 39.13 by removing
Airworthiness Directive (AD) 2010–06–
04, Amendment 39–16228 (75 FR
11428, March 11, 2010); corrected May
4, 2010 (75 FR 23572), and adding the
following new AD:
■
Airbus: Docket No. FAA–2014–0648;
Directorate Identifier 2013–NM–136–AD.
(a) Comments Due Date
We must receive comments by November
6, 2014.
(b) Affected ADs
This AD replaces AD 2010–06–04,
Amendment 39–16228 (75 FR 11428, March
11, 2010); corrected May 4, 2010 (75 FR
23572).
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1), (c)(2), and (c)(3) of this
AD, certificated in any category.
(1) Airbus Model A300 B2–1C, B2–203,
B2K–3C, B4–103, B4–203, and B4–2C
airplanes, on which Airbus Modification
02434 has been embodied in production.
(2) Airbus Model A310–203, –204, –221,
–222, –304, –322, –324, and –325 airplanes,
except those on which Airbus Modification
10432 has been embodied in production.
(3) Airbus Model A300 B4–601, B4–603,
B4–605R, B4–620, B4–622, and B4–622R
airplanes, except those on which Airbus
Modification 10432 has been embodied in
production.
(d) Subject
Air Transport Association (ATA) of
America Code 54, Nacelles/Pylons.
(e) Reason
This AD was prompted by reports of cracks
found on pylon side panels at rib 8 and a
fleet survey and updated fatigue and damage
tolerance analyses. We are issuing this AD to
detect and correct cracking of pylon side
panels (upper section) at rib 8, which could
lead to reduced structural integrity of the
pylon primary structure, which could cause
detachment of the engine from the fuselage.
56529
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Actions and Compliance With
Revised Service Information
This paragraph restates the requirements of
paragraph (f) of AD 2010–06–04, Amendment
39–16228 (75 FR 11428, March 11, 2010);
corrected May 4, 2010 (75 FR 23572), with
revised service information. Accomplishing
the initial inspection required by paragraph
(h) of this AD terminates the requirements of
this paragraph.
(1) For Configuration 01 airplanes as
identified in the applicable service bulletin
identified in paragraph (g)(9) of this AD: At
the applicable time specified in table 1 to
paragraph (g) of this AD, except as required
by paragraphs (g)(2) and (g)(3) of this AD,
perform a detailed visual inspection of the
pylons 1 and 2 side panels (upper section) at
rib 8, in accordance with paragraph 3.B. of
the Accomplishment Instructions of the
applicable service bulletin identified in
paragraph (g)(9)(i) through (g)(9)(iii) of this
AD or paragraphs (k)(1), (k)(2), or (k)(3) of
this AD. Repeat the inspection at the time
specified in table 1 to paragraph (g) of this
AD.
TABLE 1—TO PARAGRAPH (G) OF THIS AD—COMPLIANCE TIMES FOR CONFIGURATION 1 AIRPLANES
For Model—
That have accumulated—
Inspect before the
accumulation of—
Or within—
And repeat the inspection
at intervals not to
exceed—
Whichever occurs later
≤17,500 total flight
A300 B4–103, B4–203,
and B4–2C airplanes.
A300 B4–103, B4–203,
and B4–2C airplanes.
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A300 B2–1C, B2–203, and
B2K–3C airplanes.
A300 B2–1C, B2–203, and
B2K–3C airplanes.
≤18,000 total flight cycles 1
A300 B4–601, B4–603,
B4–605R, B4–620, B4–
622, and B4–622R airplanes.
A300 B4–601, B4–603,
B4–605R, B4–620, B4–
622, and B4–622R airplanes.
A310–200 airplanes with
GE CF6–80A3 or Pratt &
Whitney engines.
A310–200 airplanes with
GE CF6–80A3 or Pratt &
Whitney engines.
A310–200 airplanes with
GE CF6–80C2 engines.
≤18,000 total flight cycles 1
A310–200 airplanes with
GE CF6–80C2 engines.
>18,000 total flight cycles 1
A310–300 SR 3 airplanes
with Pratt & Whitney
JT9D engines.
≤18,000 total flight cycles 1
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cycles 1
5,350 total flight cycles .....
2,500 flight cycles 2 ...........
4,300 flight cycles.
>17,500 total flight cycles 1
20,000 total flight cycles or
40,000 total flight hours,
whichever occurs first.
5,350 total flight cycles .....
250 flight cycles 2 ..............
4,300 flight cycles.
2,000 flight cycles 2 ...........
4,300 flight cycles.
250 flight cycles 2 ..............
4,300 flight cycles.
2,000 flight cycles 2 ...........
3,600 flight cycles.
>18,000 total flight cycles 1
20,000 total flight cycles or
40,000 total flight hours,
whichever occurs first.
4,200 total flight cycles .....
>18,000 total flight cycles 1
20,000 total flight cycles or
40,000 total flight hours,
whichever occurs first.
250 flight cycles 2 ..............
3,600 flight cycles.
≤18,000 total flight cycles 1
9,700 total flight cycles or
19,400 total flight hours,
whichever occurs first.
19,500 total flight cycles or
55,500 total flight hours,
whichever occurs first.
7,800 total flight cycles or
15,600 total flight hours,
whichever occurs first.
19,500 total flight cycles or
55,500 total flight hours,
whichever occurs first.
8,600 total flight cycles or
24,000 total flight hours,
whichever occurs first.
1,500 flight cycles 2 ...........
6,700 flight cycles or
13,400 flight hours,
whichever occurs first.
6,700 flight cycles or
13,400 flight hours,
whichever occurs first.
5,800 flight cycles or
11,600 flight hours,
whichever occurs first.
5,800 flight cycles or
11,600 flight hours,
whichever occurs first.
6,700 flight cycles or
18,700 flight hours,
whichever occurs first.
>18,000 total flight cycles 1
≤18,000 total flight cycles 1
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250 flight cycles 2 ..............
1,500 flight cycles 2 ...........
250 flight cycles 2 ..............
1,500 flight cycles 2 ...........
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TABLE 1—TO PARAGRAPH (G) OF THIS AD—COMPLIANCE TIMES FOR CONFIGURATION 1 AIRPLANES—Continued
A310–300 SR 3 airplanes
with Pratt & Whitney
JT9D engines.
A310–300 SR 3 airplanes
with GE engines.
>18,000 total flight cycles 1
A310–300 SR 3 airplanes
with GE engines.
>18,000 total flight cycles 1
A310–300 SR 3 airplanes
with Pratt & Whitney
4000 engines.
A310–300 SR 3 airplanes
with Pratt & Whitney
4000 engines.
A310–300 LR 4 airplanes
with Pratt & Whitney
JT9D engines.
A310–300 LR 4 airplanes
with Pratt & Whitney
JT9D engines.
A310–300 LR 4 airplanes
with GE engines.
≤18,000 total flight cycles 1
A310–300 LR 4 airplanes
with GE engines.
>18,000 total flight cycles 1
A310–300 LR 4 airplanes
with Pratt & Whitney
4000 engines.
A310–300 LR 4 airplanes
with Pratt & Whitney
4000 engines.
≤18,000 total flight cycles 1
≤18,000 total flight cycles 1
>18,000 total flight cycles 1
≤18,000 total flight cycles 1
>18,000 total flight cycles 1
≤18,000 total flight cycles 1
>18,000 total flight cycles 1
19,500 total flight cycles or
55,500 total flight hours,
whichever occurs first.
7,000 total flight cycles or
19,600 total flight hours,
whichever occurs first.
19,500 total flight cycles or
55,500 total flight hours,
whichever occurs first.
7,000 total flight cycles or
19,600 total flight hours,
whichever occurs first.
19,500 total flight cycles or
55,500 total flight hours,
whichever occurs first.
5,900 total flight cycles or
29,500 total flight hours,
whichever occurs first.
19,500 total flight cycles or
55,500 total flight hours,
whichever occurs first.
4,800 total flight cycles or
24,100 total flight hours,
whichever occurs first.
19,500 total flight cycles or
55,500 total flight hours,
whichever occurs first.
4,800 total flight cycles or
24,000 total flight hours,
whichever occurs first.
19,500 total flight cycles or
55,500 total flight hours,
whichever occurs first.
250 flight cycles 2 ..............
1,500 flight cycles 2 ...........
250 flight cycles 2 ..............
1,500 flight cycles 2 ...........
250 flight cycles 2 ..............
1,500 flight cycles 2 ...........
250 flight cycles 2 ..............
1,500 flight cycles 2 ...........
250 flight cycles 2 ..............
1,500 flight cycles 2 ...........
250 flight cycles 2 ..............
6,700 flight cycles or
18,700 flight hours,
whichever occurs first.
5,700 flight cycles or
15,900 flight hours,
whichever occurs first.
5,700 flight cycles or
15,900 flight hours,
whichever occurs first.
5,800 flight cycles or
16,200 flight hours,
whichever occurs first.
5,800 flight cycles or
16,200 flight hours,
whichever occurs first.
6,000 flight cycles or
30,300 flight hours,
whichever occurs first.
6,000 flight cycles or
30,300 flight hours,
whichever occurs first.
5,100 flight cycles or
25,500 flight hours,
whichever occurs first.
5,100 flight cycles or
25,500 flight hours,
whichever occurs first.
5,200 flight cycles or
26,300 flight hours,
whichever occurs first.
5,200 flight cycles or
26,300 flight hours,
whichever occurs first.
1 As
of April 15, 2010 (the effective date of AD 2010–06–04, Amendment 39–16228 (75 FR 11428, March 11, 2010)).
April 15, 2010 (the effective date of AD 2010–06–04, Amendment 39–16228 (75 FR 11428, March 11, 2010)).
3 ‘‘SR’’ applies to airplanes with average flights less than 4 flight hours.
4 ‘‘LR’’ refers to airplanes with average flights of 4 or more flight hours.
asabaliauskas on DSK5VPTVN1PROD with RULES
2 After
(2) For Model A300 and A300–600
airplanes that have accumulated more than
40,000 total flight hours as of April 15, 2010
(the effective date of AD 2010–06–04,
Amendment 39–16228 (75 FR 11428, March
11, 2010)): Within 250 flight cycles after
April 15, 2010, do the actions specified in
paragraph (g)(1) of this AD.
(3) For Model A310 airplanes that have
accumulated more than 55,500 total flight
hours as of April 15, 2010 (the effective date
of AD 2010–06–04, Amendment 39–16228
(75 FR 11428, March 11, 2010)): Within 250
flight cycles after April 15, 2010, do the
actions specified in paragraph (g)(1) of this
AD.
(4) For Configuration 01 airplanes, as
identified in the applicable service bulletin
identified in paragraph (g)(9) of this AD: If a
crack is found during any inspection
required by paragraph (g)(1) of this AD,
before further flight, install a doubler, in
accordance with paragraph 3.C. of the
Accomplishment Instructions of the
applicable service bulletin identified in
paragraph (g)(9) of this AD.
(5) For Configuration 02 airplanes, as
identified in the applicable service bulletin
identified in paragraph (g)(9) of this AD: At
the applicable time specified in paragraph
1.E.(2) of the applicable service bulletin
identified in paragraphs (g)(9)(i) through
(g)(9)(iii) of this AD, or within 250 flight
cycles after April 15, 2010 (the effective date
of AD 2010–06–04, Amendment 39–16228
VerDate Sep<11>2014
16:54 Sep 19, 2014
Jkt 232001
(75 FR 11428, March 11, 2010)), whichever
occurs later, perform a detailed visual
inspection of the pylons 1 and 2 side panels
(upper section) at rib 8, in accordance with
paragraph 3.B. of the Accomplishment
Instructions of the applicable service bulletin
identified in paragraph (g)(9) of this AD.
(6) For Configuration 03 airplanes, as
identified in the applicable service bulletin
identified in paragraph (g)(9) of this AD: At
the applicable time specified in paragraph
1.E.(2) of the applicable service bulletin
identified in paragraphs (g)(9)(i) through
(g)(9)(iii) of this AD, or within 250 flight
cycles after April 15, 2010 (the effective date
of AD 2010–06–04, Amendment 39–16228
(75 FR 11428, March 11, 2010)), whichever
occurs later, perform a detailed visual
inspection, and a high frequency eddy
current inspection as applicable, of the
pylons 1 and 2 side panels (upper section) at
rib 8, in accordance with paragraph 3.B. of
the Accomplishment Instructions of the
applicable service bulletin identified in
paragraph (g)(9) of this AD.
(7) For Configuration 02 and 03 airplanes,
as identified in the applicable service
bulletin identified in paragraph (g)(9) of this
AD: If a crack is found during any inspection
required by paragraph (g)(1), (g)(5), or (g)(6)
of this AD, before further flight, repair in
accordance with paragraph 3.C. of the
Accomplishment Instructions of the
applicable service bulletin identified in
paragraph (g)(9) of this AD.
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Frm 00007
Fmt 4702
Sfmt 4702
(8) For all airplanes, except those in
Configuration 01, as identified in the
applicable service bulletin identified in
paragraph (g)(9) of this AD: Repeat the
inspection specified in paragraph (g)(1),
(g)(5), or (g)(6) of this AD, as applicable, at
the intervals specified in paragraph 1.E.(2) of
the applicable service bulletin identified in
paragraph (g)(9)(i) through (g)(9)(iii) of this
AD.
(9) For the actions specified in paragraph
(g) of this AD, use the applicable service
bulletin identified in paragraphs (g)(9)(i)
through (g)(9)(iii) of this AD, or paragraph
(k)(1), (k)(2), or (k)(3) of this AD.
(i) Airbus Mandatory Service Bulletin
A300–54–0075, excluding Appendices 1, 2,
and 3, Revision 02, dated June 26, 2008 (For
Model A300 B2–1C, B2–203, B2K–3C, B4–
103, B4–203, and B4–2C airplanes).
(ii) Airbus Mandatory Service Bulletin
A300–54–6015, excluding Appendices 1, 2,
and 3, Revision 02, dated June 26, 2008 (For
Model A300 B4–601, B4–603, B4–605R, B4–
620, B4–622, and B4–622R airplanes).
(iii) Airbus Mandatory Service Bulletin
A310–54–2018, excluding Appendices 1, 2,
and 3, Revision 02, dated June 26, 2008 (for
Model A310 series airplanes).
(h) New Repetitive Inspections and Repair
Except as required by paragraphs (l)(1) and
(l)(2) of this AD, at the applicable times
specified in paragraph 1.E., ‘‘Compliance,’’ of
the applicable service bulletin identified in
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paragraph (k) of this AD: Do a detailed
inspection for cracking of the pylons 1 and
2 side panels (upper section) at rib 8, in
accordance with the Accomplishment
Instructions of the applicable service bulletin
identified in paragraph (k) of this AD.
Accomplishing the inspection required by
this paragraph terminates the requirements of
paragraph (g)(1) through (g)(9) of this AD.
(1) If any cracking is found, before further
flight, do a high frequency eddy current
(HFEC) inspection to confirm the crack, in
accordance with the Accomplishment
Instructions of the applicable service bulletin
identified in paragraph (k) of this AD.
(i) If any crack indication is confirmed
during the HFEC inspection specified in
paragraph (h)(1) of this AD, and the crack is
less than 20 mm, before further flight, repair,
in accordance with the Accomplishment
Instructions of the applicable service bulletin
identified in paragraph (k) of this AD.
(ii) If any crack indication is confirmed
during the HFEC inspection specified in
paragraph (h)(1) of this AD and the crack is
greater than or equal to 20 mm, 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
Airbus’s EASA Design Organization
Approval (DOA).
(2) If no cracking is found, or if crack
indication is not confirmed during the HFEC
inspection required by paragraph (h)(1) of
this AD, at the applicable interval specified
in paragraph 1.E., ‘‘Compliance,’’ of the
applicable service bulletin identified in
paragraph (k) of this AD, repeat the
inspection specified in paragraph (h) of this
AD, in accordance with the Accomplishment
Instructions of the applicable service bulletin
identified in paragraph (k) of this AD until
the modification specified in paragraph (i) is
done.
asabaliauskas on DSK5VPTVN1PROD with RULES
(i) Optional Modification
Modifying by installing a doubler on the
left hand (LH) pylon 1 and right hand (RH)
pylon 2, on pylon side panels (upper
section), at rib 8, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–54–0081, dated
August 11, 1993; A310–54–2024, dated
August 11, 1993; or A300–54–6021, Revision
02, dated May 21, 2008; as applicable,
terminates the repetitive inspections
specified in paragraph (h)(2) of this AD.
(j) Post-Modification and Post-Repair
Repetitive Inspections and Corrective
Actions
For airplanes on which the modification
has been done as specified in paragraph (i)
of this AD, and airplanes on which the repair
has been done as specified in paragraph (h)
of this AD: At the applicable compliance
time specified in paragraph 1.E.,
Compliance,’’ of the applicable service
bulletin identified in paragraph (k) of this
AD, do the post-modification and post-repair
detailed inspections for cracking, as
applicable, of the LH and RH side panels of
pylons 1 and 2, in accordance with the
applicable service bulletins identified in
paragraph (k) of this AD. Repeat the
VerDate Sep<11>2014
16:54 Sep 19, 2014
Jkt 232001
inspections thereafter at the times specified
in paragraph 1.E., ‘‘Compliance’’ of the
applicable service bulletin specified in
paragraph (k) of this AD. If any cracking is
found, before further flight, repair using a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA; or
Airbus’s EASA Design Organization
Approval (DOA). This repair is not a
terminating action for the repetitive
inspections required by this paragraph.
(k) New Service Information
Use the applicable service bulletin
identified in paragraphs (k)(1) through (k)(3)
of this AD to accomplish the inspections
required by paragraphs (h) and (j) of this AD.
(1) Airbus Mandatory Service Bulletin
A300–54–0075, Revision 03, dated March 27,
2013 (for Model A300 B2–1C, B2–203, B2K–
3C, B4–103, B4–203, and B4–2C airplanes).
(2) Airbus Mandatory Service Bulletin
A310–54–2018, Revision 03, dated April 11,
2013 (for Model A310–203, –204, –221, –222,
–304, –322, –324, and –325 airplanes).
(3) Airbus Mandatory Service Bulletin
A300–54–6015, Revision 03, dated April 11,
2013 (for Model A300 B4–601, B4–603, B4–
605R, B4–620, B4–622, and B4–622R
airplanes).
(l) Exceptions
(1) Where the compliance time column in
the tables in paragraph 1.E., ‘‘Compliance,’’
of the applicable service bulletin identified
in paragraph (k) of this AD specifies a
‘‘threshold’’ in FC or FH, and does not
specify from repair or service bulletin
embodiment, those compliance times are
total flight cycles and total flight hours.
(2) Where the tables in paragraph 1.E.,
‘‘Compliance,’’ of the applicable service
bulletin specified in paragraph (k) of this AD
specifies ‘‘grace period after the receipt of the
service bulletin,’’ this AD requires
compliance within the corresponding
compliance time after the effective date of
this AD.
(m) Credit for Previous Actions
(1) This paragraph restates the credit
provided by paragraph (f)(9) of AD 2010–06–
04, Amendment 39–16228 (75 FR 11428,
March 11, 2010) with no changes. This
paragraph provides credit for initial
inspections required by paragraph (g) of this
AD, if those actions were performed prior to
April 15, 2010 (the effective date of AD
2010–06–04) using the applicable service
bulletins specified in paragraphs (m)(1)(i)
through (m)(1)(vi) of this AD, which are not
incorporated by reference in this AD.
(i) Airbus Service Bulletin A300–54–0075,
dated August 11, 1993.
(ii) Airbus Service Bulletin A300–54–0075,
Revision 01, dated November 9, 2007.
(iii) Airbus Service Bulletin A300–54–
6015, dated August 11, 1993.
(iv) Airbus Service Bulletin A300–54–
6015, Revision 01, dated November 9, 2007.
(v) Airbus Service Bulletin A310–54–2018,
dated August 11, 1993.
(vi) Airbus Service Bulletin A310–54–
2018, Revision 01, dated November 16, 2007.
(2) This paragraph provides credit for
initial inspections required by paragraph (h)
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
56531
of this AD, if those actions were performed
before the effective date of this AD using the
applicable service bulletins specified in
paragraphs (m)(2)(i) through (m)(2)(vi) of this
AD.
(i) Airbus Service Bulletin A300–54–0075,
dated August 11, 1993, which is not
incorporated by reference in this AD.
(ii) Airbus Service Bulletin A300–54–0075,
Revision 01, dated November 9, 2007, which
is not incorporated by reference in this AD.
(iii) Airbus Service Bulletin A300–54–
0075, Revision 02, dated June 26, 2008,
which is incorporated by reference in this
AD.
(iv) Airbus Service Bulletin A300–54–
6015, dated August 11, 1993, which is not
incorporated by reference in this AD.
(v) Airbus Service Bulletin A300–54–6015,
Revision 01, dated November 9, 2007, which
is not incorporated by reference in this AD.
(vi) Airbus Service Bulletin A300–54–
6015, Revision 02, dated June 26, 2008,
which is incorporated by reference in this
AD.
(vii) Airbus Service Bulletin A310–54–
2018, dated August 11, 1993, which is not
incorporated by reference in this AD.
(viii) Airbus Service Bulletin A310–54–
2018, Revision 01, dated November 16, 2007,
which is not incorporated by reference in this
AD.
(ix) Airbus Service Bulletin A310–54–
2018, Revision 02, dated June 26, 2008,
which is incorporated by reference in this
AD.
(3) This paragraph provides credit for
initial inspections required by paragraph (i)
of this AD, if those actions were performed
before the effective date of this AD using the
applicable service bulletins specified in
paragraphs (m)(3)(i) and (m)(3)(ii) of this AD.
(i) Airbus Service Bulletin A300–54–6021,
dated August 11, 1993.
(ii) Airbus Service Bulletin A300–54–6021,
Revision 01, dated November 16, 2007.
(n) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, 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: 9ANM-116-AMOC-REQUESTS@faa.gov.
(i) 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.
(ii) AMOCs approved previously for AD
2010–06–04, Amendment 39–16228 (75 FR
E:\FR\FM\22SEP1.SGM
22SEP1
56532
Federal Register / Vol. 79, No. 183 / Monday, September 22, 2014 / Proposed Rules
11428, March 11, 2010); corrected May 4,
2010 (75 FR 23572); are approved as AMOCs
for the corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(o) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0136R1, dated
July 30, 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–2014–0648.
(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
September 12, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–22467 Filed 9–19–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HEALTH AND
HUMAN SERVICES
Food and Drug Administration
21 CFR Part 890
[Docket No. FDA–2000–N–0158]
Reclassification of Iontophoresis
Devices Intended for Any Other
Purposes
AGENCY:
Food and Drug Administration,
Proposed order.
The Food and Drug
Administration (FDA) is proposing to
reclassify iontophoresis devices
intended for any other purposes, a
preamendments class III device, into
class II (special controls), and to amend
the device identification. FDA is
proposing this reclassification on its
own initiative based on new
information. This action implements
certain statutory requirements.
asabaliauskas on DSK5VPTVN1PROD with RULES
SUMMARY:
VerDate Sep<11>2014
16:54 Sep 19, 2014
Jkt 232001
Electronic Submissions
Submit electronic comments in the
following way:
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
Written Submissions
Submit written submissions in the
following ways:
• Mail/Hand delivery/Courier (for
paper submissions): Division of Dockets
Management (HFA–305), Food and Drug
Administration, 5630 Fishers Lane, Rm.
1061, Rockville, MD 20852.
Instructions: All submissions received
must include the Docket No. (FDA–
2000–N–0158) for this rulemaking. All
comments received may be posted
without change to https://
www.regulations.gov, including any
personal information provided. For
additional information on submitting
comments, see the ‘‘Comments’’ heading
of the SUPPLEMENTARY INFORMATION
section of this document.
Docket: For access to the docket to
read background documents or
comments received, go to https://
www.regulations.gov and insert the
docket number, found in brackets in the
heading of this document, into the
‘‘Search’’ box and follow the prompts
and/or go to the Division of Dockets
Management, 5630 Fishers Lane, Rm.
1061, Rockville, MD 20852.
FOR FURTHER INFORMATION CONTACT:
Michael Ryan, Center for Devices and
Radiological Health, Food and Drug
Administration,10903 New Hampshire
Ave., Bldg. 66, Rm. 1615, Silver Spring,
MD 20993–0002, 301–796–6283.
SUPPLEMENTARY INFORMATION:
I. Background—Regulatory Authorities
HHS.
ACTION:
Submit either electronic or
written comments by December 22,
2014. See section XII for the proposed
effective date of a final order based on
this proposed order.
ADDRESSES: You may submit comments
by any of the following methods:
DATES:
The Federal Food, Drug, and Cosmetic
Act (the FD&C Act), as amended by the
Medical Device Amendments of 1976
(the 1976 amendments) (Pub. L. 94–
295), the Safe Medical Devices Act of
1990 (Pub. L. 101–629), the Food and
Drug Administration Modernization Act
of 1997 (Pub. L. 105–115), the Medical
Device User Fee and Modernization Act
of 2002 (Pub. L. 107–250), the Medical
Devices Technical Corrections Act (Pub.
L. 108–214), the Food and Drug
Administration Amendments Act of
2007 (Pub. L. 110–85), and the Food and
Drug Administration Safety and
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
Innovation Act (FDASIA) (Pub. L. 112–
144), among other amendments,
established a comprehensive system for
the regulation of medical devices
intended for human use. Section 513 of
the FD&C Act (21 U.S.C. 360c)
established three categories (classes) of
devices, reflecting the regulatory
controls needed to provide reasonable
assurance of their safety and
effectiveness. The three categories of
devices are class I (general controls),
class II (special controls), and class III
(premarket approval).
Section 513(a)(1) of the FD&C Act
defines class II devices as those devices
for which the general controls by
themselves are insufficient to provide
reasonable assurance of safety and
effectiveness, but for which there is
sufficient information to establish
special controls to provide such
assurance.
Under section 513 of the FD&C Act,
devices that were in commercial
distribution before the enactment of the
1976 amendments, May 28, 1976
(generally referred to as preamendments
devices), are classified after FDA has: (1)
Received a recommendation from a
device classification panel (an FDA
advisory committee); (2) published the
panel’s recommendation for comment,
along with a proposed regulation
classifying the device; and (3) published
a final regulation classifying the device.
FDA has classified most
preamendments devices under these
procedures.
Devices that were not in commercial
distribution prior to May 28, 1976
(generally referred to as
postamendments devices) are
automatically classified by section
513(f) of the FD&C Act into class III
without any FDA rulemaking process.
Those devices remain in class III and
require premarket approval unless, and
until, the device is reclassified into class
I or II or FDA issues an administrative
order finding the device to be
substantially equivalent, in accordance
with section 513(i) of the FD&C Act, to
a predicate device that does not require
premarket approval. The Agency
determines whether new devices are
substantially equivalent to predicate
devices by means of premarket
notification procedures in section 510(k)
of the FD&C Act (21 U.S.C. 360(k)) and
part 807 (21 CFR part 807).
On July 9, 2012, FDASIA was enacted.
Section 608(a) of FDASIA amended
section 513(e) of the FD&C Act,
changing the process for reclassifying a
device from rulemaking to an
administrative order. Section 513(e) of
the FD&C Act governs reclassification of
classified preamendments devices. This
E:\FR\FM\22SEP1.SGM
22SEP1
]]>Agencies
[Federal Register Volume 79, Number 183 (Monday, September 22, 2014)]
[Proposed Rules]
[Pages 56526-56532]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-22467]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0648; Directorate Identifier 2013-NM-136-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) 2010-06-
04, for certain Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-
203, B4-2C airplanes; Model A310 series airplanes; Model A300 B4-600
series airplanes; and Model A300 B4-600R series airplanes. AD 2010-06-
04 currently requires repetitive inspections to detect cracks of the
pylon side panels
[[Page 56527]]
(upper section) at rib 8; and corrective actions if necessary. Since we
issued AD 2010-06-04, fleet survey and updated fatigue and damage
tolerance analyses were done. We have determined that reduced
compliance times are necessary. This proposed AD would continue to
require repetitive inspections for cracking of the pylons 1 and 2 side
panels (upper section) at rib 8 with reduced compliance times, and
corrective actions if necessary. This proposed AD would also require
repetitive post-repair and post-modification inspections and repair if
necessary. This proposed AD would also remove certain airplanes having
a certain modification from the applicability. We are proposing this AD
to detect and correct cracking of pylon side panels (upper section) at
rib 8, which could lead to reduced structural integrity of the pylon
primary structure, which could cause detachment of the engine from the
fuselage.
DATES: We must receive comments on this proposed AD by November 6,
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.
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; 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-2014-0648;
Directorate Identifier 2013-NM-136-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 March 4, 2010, we issued AD 2010-06-04, Amendment 39-16228 (75
FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572). AD
2010-06-04 requires actions intended to address an unsafe condition on
Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, B4-2C
airplanes; Model A310 series airplanes; Model A300 B4-600 series
airplanes; and Model A300 B4-600R series airplanes.
Since we issued AD 2010-06-04, fleet survey and updated fatigue and
damage tolerance analyses were done. We have determined that reduced
compliance times are necessary. 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-
0136R1, dated July 30, 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 pylon side panels (upper section) at rib 8
on Airbus A300, A310 and A300-600 aeroplanes equipped with General
Electric engines. Investigation of these findings indicated that
this problem was likely to also affect aeroplanes of this type
design with other engine installations.
This condition, if not detected and corrected, could lead to
reduced strength of the pylon primary structure, possibly resulting
in pylon structural failure and in-flight loss of an engine.
Prompted by these findings, EASA issued AD 2008-0181 [https://www.regulations.gov/#!documentDetail;D=FAA-2009-0789-0002] [which
corresponds to FAA AD 2010-06-04, Amendment 39-16228 (75 FR 11428,
March 11, 2010); corrected May 4, 2010 (75 FR 23572)] to require
repetitive detailed visual inspections [of the pylon side panels
(upper section) at rib 8] and, depending on aeroplane configuration
and/or findings, the accomplishment of applicable corrective
action(s).
Since that [EASA] AD was issued, a fleet survey and updated
Fatigue and Damage Tolerance analyses 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
consequently, the threshold and interval must be reduced to allow
timely detection of these cracks and the accomplishment of
applicable correction action(s).
EASA issued AD 2013-0136 [https://ad.easa.europa.eu/ad/2013-0136R1] which retained the requirements of EASA AD 2008-0181, which
was superseded, and required the inspections to be accomplished
within reduced thresholds and intervals.
After publication of EASA AD 2013-0136, it appeared that Airbus
Mod 03599 had no influence on the aeroplane configuration affected
by this AD. At the same time Airbus Service Bulletin (SB) A300-54-
6015 Revision 3 was not integrally taken into account as this
revision no longer identifies configuration 3 aeroplanes.
For the reasons described above, EASA 2013-0136 is revised to
exclude Airbus Mod 03599 from the applicability and to delete the
reference to the configuration 3 for A300-600 aeroplanes.
Corrective actions include doing a repair. This proposed AD also
provides an optional modification (installing a doubler), which would
terminate the repetitive inspections. Required actions also include
repetitive post-repair and post-modification inspections and repair if
necessary.
Depending on airplane configuration: Initial compliance times range
from 4,800 flight cycles or 24,100 flight hours, and 9,700 flight
cycles or 19,400 flight hours. Initial post-modification and post-
repair inspection compliance times range from 7,200 flight cycles or
36,400 flight hours, and 10,400 flight cycles or 50,800 flight hours,
depending on inspection type. Repetitive intervals range from 2,600
flight cycles or 13,000 flight hours, and 6,700 flight cycles or 18,700
flight hours. You may examine
[[Page 56528]]
the MCAI in the AD docket on the Internet at https://www.regulations.gov
by searching for and locating it in Docket No. FAA-2014-0648.
Relevant Service Information
Airbus has issued the Service Bulletins listed below. The actions
described in this service information are intended to correct the
unsafe condition identified in the MCAI.
Airbus Service Bulletin A300-54-0075, Revision 03, dated
March 27, 2013.
Airbus Service Bulletin A300-54-6015, Revision 03, dated
April 11, 2013.
Airbus Service Bulletin A310-54-2018, Revision 03, dated
April 11, 2013.
Airbus Service Bulletin A300-54-0081, dated August 11,
1993.
Airbus Service Bulletin A300-54-6021, Revision 02, dated
May 21, 2008.
Airbus Service Bulletin A310-54-2024, dated August 11,
1993.
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
Although the MCAI or service information allows further flight
after cracks are found during compliance with the required actions of
this proposed AD, this proposed AD would require that you repair any
cracking before further flight.
Changes to This NPRM
Table 2, ``Service Bulletins,'' in AD 2010-06-04, Amendment 39-
16228 (75 FR 11428, March 11, 2010), has been converted to text in
paragraph (g)(9) of this AD.
Table 3, ``Previous Service Information,'' in AD 2010-06-04,
Amendment 39-16228 (75 FR 11428, March 11, 2010), has been converted to
text in paragraph (m)(1) of this AD.
Costs of Compliance
We estimate that this proposed AD affects 156 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspection [retained actions 4 work-hours x $0 $340........... $53,040.
from AD 2010-06-04, $85 per hour =
Amendment 39-16228 (75 FR $340.
11428, March 11, 2010);
corrected May 4, 2010 (75 FR
23572)].
Inspection [new proposed 24 work-hours x 0 $2,040 per $318,240 per inspection cycle.
actions]. $85 per hour = inspection
$2,040 per cycle.
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
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Repair............................ 58 work-hours x $85 $3,910.................... $8,840.
per hour = $4,930.
Optional Modification............. Up to 48 work-hours x Up to $1,026.............. Up to $5,106.
$85 per hour =
$4,080.
----------------------------------------------------------------------------------------------------------------
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:
[[Page 56529]]
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 removing Airworthiness Directive (AD) 2010-06-
04, Amendment 39-16228 (75 FR 11428, March 11, 2010); corrected May 4,
2010 (75 FR 23572), and adding the following new AD:
Airbus: Docket No. FAA-2014-0648; Directorate Identifier 2013-NM-
136-AD.
(a) Comments Due Date
We must receive comments by November 6, 2014.
(b) Affected ADs
This AD replaces AD 2010-06-04, Amendment 39-16228 (75 FR 11428,
March 11, 2010); corrected May 4, 2010 (75 FR 23572).
(c) Applicability
This AD applies to the airplanes identified in paragraphs
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category.
(1) Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and
B4-2C airplanes, on which Airbus Modification 02434 has been
embodied in production.
(2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324,
and -325 airplanes, except those on which Airbus Modification 10432
has been embodied in production.
(3) Airbus Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622,
and B4-622R airplanes, except those on which Airbus Modification
10432 has been embodied in production.
(d) Subject
Air Transport Association (ATA) of America Code 54, Nacelles/
Pylons.
(e) Reason
This AD was prompted by reports of cracks found on pylon side
panels at rib 8 and a fleet survey and updated fatigue and damage
tolerance analyses. We are issuing this AD to detect and correct
cracking of pylon side panels (upper section) at rib 8, which could
lead to reduced structural integrity of the pylon primary structure,
which could cause detachment of the engine from the fuselage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Actions and Compliance With Revised Service Information
This paragraph restates the requirements of paragraph (f) of AD
2010-06-04, Amendment 39-16228 (75 FR 11428, March 11, 2010);
corrected May 4, 2010 (75 FR 23572), with revised service
information. Accomplishing the initial inspection required by
paragraph (h) of this AD terminates the requirements of this
paragraph.
(1) For Configuration 01 airplanes as identified in the
applicable service bulletin identified in paragraph (g)(9) of this
AD: At the applicable time specified in table 1 to paragraph (g) of
this AD, except as required by paragraphs (g)(2) and (g)(3) of this
AD, perform a detailed visual inspection of the pylons 1 and 2 side
panels (upper section) at rib 8, in accordance with paragraph 3.B.
of the Accomplishment Instructions of the applicable service
bulletin identified in paragraph (g)(9)(i) through (g)(9)(iii) of
this AD or paragraphs (k)(1), (k)(2), or (k)(3) of this AD. Repeat
the inspection at the time specified in table 1 to paragraph (g) of
this AD.
Table 1--to Paragraph (g) of This AD--Compliance Times for Configuration 1 Airplanes
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
For Model-- That have Inspect before the Or within-- And repeat the
accumulated-- accumulation of-- inspection at
intervals not to
exceed--
----------------------------------------
Whichever occurs later
----------------------------------------------------------------------------------------------------------------
A300 B2-1C, B2-203, and B2K-3C <=17,500 total 5,350 total flight 2,500 flight 4,300 flight
airplanes. flight cycles \1\. cycles. cycles \2\. cycles.
A300 B2-1C, B2-203, and B2K-3C >17,500 total 20,000 total 250 flight cycles 4,300 flight
airplanes. flight cycles \1\. flight cycles or \2\. cycles.
40,000 total
flight hours,
whichever occurs
first.
A300 B4-103, B4-203, and B4-2C <=18,000 total 5,350 total flight 2,000 flight 4,300 flight
airplanes. flight cycles \1\. cycles. cycles \2\. cycles.
A300 B4-103, B4-203, and B4-2C >18,000 total 20,000 total 250 flight cycles 4,300 flight
airplanes. flight cycles \1\. flight cycles or \2\. cycles.
40,000 total
flight hours,
whichever occurs
first.
A300 B4-601, B4-603, B4-605R, B4- <=18,000 total 4,200 total flight 2,000 flight 3,600 flight
620, B4-622, and B4-622R flight cycles \1\. cycles. cycles \2\. cycles.
airplanes.
A300 B4-601, B4-603, B4-605R, B4- >18,000 total 20,000 total 250 flight cycles 3,600 flight
620, B4-622, and B4-622R flight cycles \1\. flight cycles or \2\. cycles.
airplanes. 40,000 total
flight hours,
whichever occurs
first.
A310-200 airplanes with GE CF6- <=18,000 total 9,700 total flight 1,500 flight 6,700 flight
80A3 or Pratt & Whitney engines. flight cycles \1\. cycles or 19,400 cycles \2\. cycles or 13,400
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-200 airplanes with GE CF6- >18,000 total 19,500 total 250 flight cycles 6,700 flight
80A3 or Pratt & Whitney engines. flight cycles \1\. flight cycles or \2\. cycles or 13,400
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-200 airplanes with GE CF6- <=18,000 total 7,800 total flight 1,500 flight 5,800 flight
80C2 engines. flight cycles \1\. cycles or 15,600 cycles \2\. cycles or 11,600
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-200 airplanes with GE CF6- >18,000 total 19,500 total 250 flight cycles 5,800 flight
80C2 engines. flight cycles \1\. flight cycles or \2\. cycles or 11,600
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-300 SR \3\ airplanes with <=18,000 total 8,600 total flight 1,500 flight 6,700 flight
Pratt & Whitney JT9D engines. flight cycles \1\. cycles or 24,000 cycles \2\. cycles or 18,700
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
[[Page 56530]]
A310-300 SR \3\ airplanes with >18,000 total 19,500 total 250 flight cycles 6,700 flight
Pratt & Whitney JT9D engines. flight cycles \1\. flight cycles or \2\. cycles or 18,700
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-300 SR \3\ airplanes with <=18,000 total 7,000 total flight 1,500 flight 5,700 flight
GE engines. flight cycles \1\. cycles or 19,600 cycles \2\. cycles or 15,900
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-300 SR \3\ airplanes with >18,000 total 19,500 total 250 flight cycles 5,700 flight
GE engines. flight cycles \1\. flight cycles or \2\. cycles or 15,900
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-300 SR \3\ airplanes with <=18,000 total 7,000 total flight 1,500 flight 5,800 flight
Pratt & Whitney 4000 engines. flight cycles \1\. cycles or 19,600 cycles \2\. cycles or 16,200
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-300 SR \3\ airplanes with >18,000 total 19,500 total 250 flight cycles 5,800 flight
Pratt & Whitney 4000 engines. flight cycles \1\. flight cycles or \2\. cycles or 16,200
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-300 LR \4\ airplanes with <=18,000 total 5,900 total flight 1,500 flight 6,000 flight
Pratt & Whitney JT9D engines. flight cycles \1\. cycles or 29,500 cycles \2\. cycles or 30,300
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-300 LR \4\ airplanes with >18,000 total 19,500 total 250 flight cycles 6,000 flight
Pratt & Whitney JT9D engines. flight cycles \1\. flight cycles or \2\. cycles or 30,300
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-300 LR \4\ airplanes with <=18,000 total 4,800 total flight 1,500 flight 5,100 flight
GE engines. flight cycles \1\. cycles or 24,100 cycles \2\. cycles or 25,500
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-300 LR \4\ airplanes with >18,000 total 19,500 total 250 flight cycles 5,100 flight
GE engines. flight cycles \1\. flight cycles or \2\. cycles or 25,500
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-300 LR \4\ airplanes with <=18,000 total 4,800 total flight 1,500 flight 5,200 flight
Pratt & Whitney 4000 engines. flight cycles \1\. cycles or 24,000 cycles \2\. cycles or 26,300
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-300 LR \4\ airplanes with >18,000 total 19,500 total 250 flight cycles 5,200 flight
Pratt & Whitney 4000 engines. flight cycles \1\. flight cycles or \2\. cycles or 26,300
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
----------------------------------------------------------------------------------------------------------------
\1\ As of April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-16228 (75 FR 11428, March 11,
2010)).
\2\ After April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-16228 (75 FR 11428, March 11,
2010)).
\3\ ``SR'' applies to airplanes with average flights less than 4 flight hours.
\4\ ``LR'' refers to airplanes with average flights of 4 or more flight hours.
(2) For Model A300 and A300-600 airplanes that have accumulated
more than 40,000 total flight hours as of April 15, 2010 (the
effective date of AD 2010-06-04, Amendment 39-16228 (75 FR 11428,
March 11, 2010)): Within 250 flight cycles after April 15, 2010, do
the actions specified in paragraph (g)(1) of this AD.
(3) For Model A310 airplanes that have accumulated more than
55,500 total flight hours as of April 15, 2010 (the effective date
of AD 2010-06-04, Amendment 39-16228 (75 FR 11428, March 11, 2010)):
Within 250 flight cycles after April 15, 2010, do the actions
specified in paragraph (g)(1) of this AD.
(4) For Configuration 01 airplanes, as identified in the
applicable service bulletin identified in paragraph (g)(9) of this
AD: If a crack is found during any inspection required by paragraph
(g)(1) of this AD, before further flight, install a doubler, in
accordance with paragraph 3.C. of the Accomplishment Instructions of
the applicable service bulletin identified in paragraph (g)(9) of
this AD.
(5) For Configuration 02 airplanes, as identified in the
applicable service bulletin identified in paragraph (g)(9) of this
AD: At the applicable time specified in paragraph 1.E.(2) of the
applicable service bulletin identified in paragraphs (g)(9)(i)
through (g)(9)(iii) of this AD, or within 250 flight cycles after
April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-
16228 (75 FR 11428, March 11, 2010)), whichever occurs later,
perform a detailed visual inspection of the pylons 1 and 2 side
panels (upper section) at rib 8, in accordance with paragraph 3.B.
of the Accomplishment Instructions of the applicable service
bulletin identified in paragraph (g)(9) of this AD.
(6) For Configuration 03 airplanes, as identified in the
applicable service bulletin identified in paragraph (g)(9) of this
AD: At the applicable time specified in paragraph 1.E.(2) of the
applicable service bulletin identified in paragraphs (g)(9)(i)
through (g)(9)(iii) of this AD, or within 250 flight cycles after
April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-
16228 (75 FR 11428, March 11, 2010)), whichever occurs later,
perform a detailed visual inspection, and a high frequency eddy
current inspection as applicable, of the pylons 1 and 2 side panels
(upper section) at rib 8, in accordance with paragraph 3.B. of the
Accomplishment Instructions of the applicable service bulletin
identified in paragraph (g)(9) of this AD.
(7) For Configuration 02 and 03 airplanes, as identified in the
applicable service bulletin identified in paragraph (g)(9) of this
AD: If a crack is found during any inspection required by paragraph
(g)(1), (g)(5), or (g)(6) of this AD, before further flight, repair
in accordance with paragraph 3.C. of the Accomplishment Instructions
of the applicable service bulletin identified in paragraph (g)(9) of
this AD.
(8) For all airplanes, except those in Configuration 01, as
identified in the applicable service bulletin identified in
paragraph (g)(9) of this AD: Repeat the inspection specified in
paragraph (g)(1), (g)(5), or (g)(6) of this AD, as applicable, at
the intervals specified in paragraph 1.E.(2) of the applicable
service bulletin identified in paragraph (g)(9)(i) through
(g)(9)(iii) of this AD.
(9) For the actions specified in paragraph (g) of this AD, use
the applicable service bulletin identified in paragraphs (g)(9)(i)
through (g)(9)(iii) of this AD, or paragraph (k)(1), (k)(2), or
(k)(3) of this AD.
(i) Airbus Mandatory Service Bulletin A300-54-0075, excluding
Appendices 1, 2, and 3, Revision 02, dated June 26, 2008 (For Model
A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and B4-2C airplanes).
(ii) Airbus Mandatory Service Bulletin A300-54-6015, excluding
Appendices 1, 2, and 3, Revision 02, dated June 26, 2008 (For Model
A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R
airplanes).
(iii) Airbus Mandatory Service Bulletin A310-54-2018, excluding
Appendices 1, 2, and 3, Revision 02, dated June 26, 2008 (for Model
A310 series airplanes).
(h) New Repetitive Inspections and Repair
Except as required by paragraphs (l)(1) and (l)(2) of this AD,
at the applicable times specified in paragraph 1.E., ``Compliance,''
of the applicable service bulletin identified in
[[Page 56531]]
paragraph (k) of this AD: Do a detailed inspection for cracking of
the pylons 1 and 2 side panels (upper section) at rib 8, in
accordance with the Accomplishment Instructions of the applicable
service bulletin identified in paragraph (k) of this AD.
Accomplishing the inspection required by this paragraph terminates
the requirements of paragraph (g)(1) through (g)(9) of this AD.
(1) If any cracking is found, before further flight, do a high
frequency eddy current (HFEC) inspection to confirm the crack, in
accordance with the Accomplishment Instructions of the applicable
service bulletin identified in paragraph (k) of this AD.
(i) If any crack indication is confirmed during the HFEC
inspection specified in paragraph (h)(1) of this AD, and the crack
is less than 20 mm, before further flight, repair, in accordance
with the Accomplishment Instructions of the applicable service
bulletin identified in paragraph (k) of this AD.
(ii) If any crack indication is confirmed during the HFEC
inspection specified in paragraph (h)(1) of this AD and the crack is
greater than or equal to 20 mm, 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 Airbus's EASA Design Organization Approval (DOA).
(2) If no cracking is found, or if crack indication is not
confirmed during the HFEC inspection required by paragraph (h)(1) of
this AD, at the applicable interval specified in paragraph 1.E.,
``Compliance,'' of the applicable service bulletin identified in
paragraph (k) of this AD, repeat the inspection specified in
paragraph (h) of this AD, in accordance with the Accomplishment
Instructions of the applicable service bulletin identified in
paragraph (k) of this AD until the modification specified in
paragraph (i) is done.
(i) Optional Modification
Modifying by installing a doubler on the left hand (LH) pylon 1
and right hand (RH) pylon 2, on pylon side panels (upper section),
at rib 8, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-54-0081, dated August 11, 1993; A310-
54-2024, dated August 11, 1993; or A300-54-6021, Revision 02, dated
May 21, 2008; as applicable, terminates the repetitive inspections
specified in paragraph (h)(2) of this AD.
(j) Post-Modification and Post-Repair Repetitive Inspections and
Corrective Actions
For airplanes on which the modification has been done as
specified in paragraph (i) of this AD, and airplanes on which the
repair has been done as specified in paragraph (h) of this AD: At
the applicable compliance time specified in paragraph 1.E.,
Compliance,'' of the applicable service bulletin identified in
paragraph (k) of this AD, do the post-modification and post-repair
detailed inspections for cracking, as applicable, of the LH and RH
side panels of pylons 1 and 2, in accordance with the applicable
service bulletins identified in paragraph (k) of this AD. Repeat the
inspections thereafter at the times specified in paragraph 1.E.,
``Compliance'' of the applicable service bulletin specified in
paragraph (k) of this AD. If any cracking is found, before further
flight, repair using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Airbus's EASA Design Organization Approval (DOA). This repair is not
a terminating action for the repetitive inspections required by this
paragraph.
(k) New Service Information
Use the applicable service bulletin identified in paragraphs
(k)(1) through (k)(3) of this AD to accomplish the inspections
required by paragraphs (h) and (j) of this AD.
(1) Airbus Mandatory Service Bulletin A300-54-0075, Revision 03,
dated March 27, 2013 (for Model A300 B2-1C, B2-203, B2K-3C, B4-103,
B4-203, and B4-2C airplanes).
(2) Airbus Mandatory Service Bulletin A310-54-2018, Revision 03,
dated April 11, 2013 (for Model A310-203, -204, -221, -222, -304, -
322, -324, and -325 airplanes).
(3) Airbus Mandatory Service Bulletin A300-54-6015, Revision 03,
dated April 11, 2013 (for Model A300 B4-601, B4-603, B4-605R, B4-
620, B4-622, and B4-622R airplanes).
(l) Exceptions
(1) Where the compliance time column in the tables in paragraph
1.E., ``Compliance,'' of the applicable service bulletin identified
in paragraph (k) of this AD specifies a ``threshold'' in FC or FH,
and does not specify from repair or service bulletin embodiment,
those compliance times are total flight cycles and total flight
hours.
(2) Where the tables in paragraph 1.E., ``Compliance,'' of the
applicable service bulletin specified in paragraph (k) of this AD
specifies ``grace period after the receipt of the service
bulletin,'' this AD requires compliance within the corresponding
compliance time after the effective date of this AD.
(m) Credit for Previous Actions
(1) This paragraph restates the credit provided by paragraph
(f)(9) of AD 2010-06-04, Amendment 39-16228 (75 FR 11428, March 11,
2010) with no changes. This paragraph provides credit for initial
inspections required by paragraph (g) of this AD, if those actions
were performed prior to April 15, 2010 (the effective date of AD
2010-06-04) using the applicable service bulletins specified in
paragraphs (m)(1)(i) through (m)(1)(vi) of this AD, which are not
incorporated by reference in this AD.
(i) Airbus Service Bulletin A300-54-0075, dated August 11, 1993.
(ii) Airbus Service Bulletin A300-54-0075, Revision 01, dated
November 9, 2007.
(iii) Airbus Service Bulletin A300-54-6015, dated August 11,
1993.
(iv) Airbus Service Bulletin A300-54-6015, Revision 01, dated
November 9, 2007.
(v) Airbus Service Bulletin A310-54-2018, dated August 11, 1993.
(vi) Airbus Service Bulletin A310-54-2018, Revision 01, dated
November 16, 2007.
(2) This paragraph provides credit for initial inspections
required by paragraph (h) of this AD, if those actions were
performed before the effective date of this AD using the applicable
service bulletins specified in paragraphs (m)(2)(i) through
(m)(2)(vi) of this AD.
(i) Airbus Service Bulletin A300-54-0075, dated August 11, 1993,
which is not incorporated by reference in this AD.
(ii) Airbus Service Bulletin A300-54-0075, Revision 01, dated
November 9, 2007, which is not incorporated by reference in this AD.
(iii) Airbus Service Bulletin A300-54-0075, Revision 02, dated
June 26, 2008, which is incorporated by reference in this AD.
(iv) Airbus Service Bulletin A300-54-6015, dated August 11,
1993, which is not incorporated by reference in this AD.
(v) Airbus Service Bulletin A300-54-6015, Revision 01, dated
November 9, 2007, which is not incorporated by reference in this AD.
(vi) Airbus Service Bulletin A300-54-6015, Revision 02, dated
June 26, 2008, which is incorporated by reference in this AD.
(vii) Airbus Service Bulletin A310-54-2018, dated August 11,
1993, which is not incorporated by reference in this AD.
(viii) Airbus Service Bulletin A310-54-2018, Revision 01, dated
November 16, 2007, which is not incorporated by reference in this
AD.
(ix) Airbus Service Bulletin A310-54-2018, Revision 02, dated
June 26, 2008, which is incorporated by reference in this AD.
(3) This paragraph provides credit for initial inspections
required by paragraph (i) of this AD, if those actions were
performed before the effective date of this AD using the applicable
service bulletins specified in paragraphs (m)(3)(i) and (m)(3)(ii)
of this AD.
(i) Airbus Service Bulletin A300-54-6021, dated August 11, 1993.
(ii) Airbus Service Bulletin A300-54-6021, Revision 01, dated
November 16, 2007.
(n) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, 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.
(i) 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.
(ii) AMOCs approved previously for AD 2010-06-04, Amendment 39-
16228 (75 FR
[[Page 56532]]
11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572); are
approved as AMOCs for the corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or EASA; or Airbus's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(o) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2013-0136R1, dated July 30,
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-2014-0648.
(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 September 12, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-22467 Filed 9-19-14; 8:45 am]
BILLING CODE 4910-13-P
