Airworthiness Directives; Airbus Airplanes, 32256-32258 [2016-11681]
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32256
Proposed Rules
Federal Register
Vol. 81, No. 99
Monday, May 23, 2016
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.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–6671; Directorate
Identifier 2015–NM–164–AD]
Examining the AD Docket
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 A300B4–203 and
A300B4–2C airplanes. This proposed
AD was prompted by cracks found on
pylon side panels (upper section) at rib
8. This proposed AD would require a
detailed inspection for crack indications
of the pylon side panels, a high
frequency eddy current (HFEC)
inspection to confirm any crack
indications, modification of the pylon
side panels, and repetitive inspections
and repair if necessary. We are
proposing this AD to detect and correct
cracking of the pylon side panels. Such
cracking could result in pylon structural
failure and in-flight loss of an engine.
DATES: We must receive comments on
this proposed AD by July 7, 2016.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, 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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
sradovich on DSK3TPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
16:06 May 20, 2016
Jkt 238001
For service information identified in
this NPRM, 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.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
6671; 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
(phone: 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 proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2016–6671; Directorate Identifier 2015–
NM–164–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 because of 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
PO 00000
Frm 00001
Fmt 4702
Sfmt 4702
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
Union, has issued EASA Airworthiness
Directive 2015–0201, dated October 7,
2015 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A300B4–203 and A300B4–2C
airplanes. 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 inflight loss of an engine.
Prompted by these findings, EASA issued
AD 2008–0181 [which corresponded 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 and, depending
on aeroplane configuration and/or findings,
the accomplishment of applicable corrective
action(s).
Since that [EASA] AD 2008–0181 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
were reduced to allow timely detection of
these cracks and the accomplishment of
applicable corrective action(s).
Consequently, EASA AD 2013–0136 was
published to supersede EASA AD 2008–0181
and to require the inspections to be
accomplished within reduced thresholds and
intervals. Afterwards, [EASA] AD 2013–0136
was mistakenly revised [EASA AD 2013–
0136R1 corresponds to FAA AD 2015–26–06,
Amendment 39–18354 (81 FR January
14,2016)] to reduce the Applicability,
because it was considered at the time that
aeroplanes on which Airbus mod 03599 was
embodied, were not concerned by the
requirements of EASA AD 2013–0136.
Since EASA AD 2013–0136R1 was issued,
a more thorough analysis determined that
post-mod 03599 aeroplanes could be affected
by this unsafe condition after all.
[During] further deeper review, a list of
nineteen A300 aeroplanes was identified as
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23MYP1
32257
Federal Register / Vol. 81, No. 99 / Monday, May 23, 2016 / Proposed Rules
missing in the [EASA] AD 2013–0136R1
applicability, (aeroplanes post-mod 03599).
For the reasons described above this AD
retains the requirements of EASA AD 2013–
0136R1 and mandates these requirements for
the 19 missing A300 aeroplanes MSNs.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
6671.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A300–54–0075, Revision 04, dated May
26, 2015. The service information
describes procedures for an inspection
for crack indications of the pylons, a
HFEC inspection to confirm cracking,
modification of the pylon side panels,
and repairs if cracks are found.
Airbus has also issued Service
Bulletin A300–54–0081, dated August
11, 1993. This service information
describes installation of a doubler on
the left pylon 1 and right pylon 2, on
pylon side panels (upper section) at Rib
8.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
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 these same
type designs.
Differences Between Proposed Rule and
Service Bulletin
Unlike the procedures described in
Airbus Service Bulletin A300–54–0075,
Revision 04, dated May 26, 2015, this
proposed AD would not permit further
flight if cracks are detected in the pylon
or pylon side panels. We have
determined that because of the safety
implications and consequences
associated with that cracking, any
cracked pylon or pylon side panel must
be repaired or modified before further
flight. This difference has been
coordinated with EASA.
Costs of Compliance
We estimate that this proposed AD
affects 4 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Cost per product
Inspection of the pylon side
panels.
30 work-hours × $85 per hour = $2,550 per inspection
cycle.
$2,550 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
Cost on U.S. operators
$10,200 per inspection
cycle.
determining the number of airplanes
that might need this repair.
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per product
Crack Repair ........................
56 work-hours × $85 per hour = $4,760 per repair ......
$3,910 per repair ...............
$8,670 per repair.
sradovich on DSK3TPTVN1PROD with PROPOSALS
Authority for This Rulemaking
Regulatory Findings
List of Subjects in 14 CFR Part 39
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.
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.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
VerDate Sep<11>2014
16:06 May 20, 2016
Jkt 238001
PO 00000
Frm 00002
Fmt 4702
Sfmt 4702
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2016–6671;
Directorate Identifier 2015–NM–164–AD.
E:\FR\FM\23MYP1.SGM
23MYP1
32258
Federal Register / Vol. 81, No. 99 / Monday, May 23, 2016 / Proposed Rules
(a) Comments Due Date
We must receive comments by July 7, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A300B4–
203 and A300B4–2C airplanes, certificated in
any category, manufacturer serial numbers
210, 212, 218, 220, 227, 234, 235, 236, 239,
247, 255, 256, 259, 261, 274, 277, 292, 299,
and 302.
(d) Subject
Air Transport Association (ATA) of
America Code 54, Nacelles/Pylons.
(e) Reason
This AD was prompted by cracks found on
pylon side panels (upper section) at rib 8. We
are proposing this AD to detect and correct
cracking of the pylon side panels. Such
cracking could result in pylon structural
failure and in-flight loss of an engine.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Detailed Inspection of Pylons and
Corrections
At the applicable time specified in Airbus
Service Bulletin A300–54–0075, Revision 04,
dated May 26, 2015: Do a detailed inspection
for crack indications of the pylons 1 and 2
side panels (upper section) at rib 8, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
54–0075, Revision 04, dated May 26, 2015.
sradovich on DSK3TPTVN1PROD with PROPOSALS
(h) Crack Confirmation
If any crack indication is found during the
inspection required by paragraph (g) of this
AD: Before further flight, do a high frequency
eddy current (HFEC) inspection to confirm
the crack, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–54–0075, Revision 04,
dated May 26, 2015.
(i) Follow-On Actions for No Crack/
Indication
If the inspection required by paragraph (g)
of this AD reveals no crack indication, or if
the HFEC inspection specified by paragraph
(h) of this AD confirms no crack: Do the
actions specified in either paragraph (i)(1) or
(i)(2) of this AD.
(1) Repeat the inspection required by
paragraph (g) of this AD at the applicable
time specified in Airbus Service Bulletin
A300–54–0075, Revision 04, dated May 26,
2015.
(2) At the applicable time specified in
Airbus Service Bulletin A300–54–0081,
dated August 11, 1993: Modify the pylons, in
accordance with Airbus Service Bulletin
300–54–0081, dated August 11, 1993.
Thereafter, repeat the HFEC inspection
specified in paragraph (h) of this AD at the
applicable interval specified in Airbus
Service Bulletin A300–54–0075, Revision 04,
dated May 26, 2015, and repair any crack
before further flight using a method approved
by the Manager, International Branch, ANM–
VerDate Sep<11>2014
16:06 May 20, 2016
Jkt 238001
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA).
(j) Follow-On Actions for Crack Findings
If any crack is confirmed during the
inspection required by paragraph (h) of this
AD, repair before further flight using a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA; or
Airbus’s EASA DOA.
(k) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (g), (h), (i), and (j) of
this AD, if those actions were performed
before the effective date of this AD using the
service information specified in paragraphs
(k)(1) through (k)(4) of this AD.
(1) Airbus Service Bulletin A300–54–0075,
dated August 11, 1993, which was
incorporated by referenced in AD 2010–06–
04, Amendment 39–16228 (75 FR 11428,
March 11, 2010); corrected May 4, 2010 (75
FR 23572).
(2) Airbus Service Bulletin A300–54–0075,
Revision 01, dated November 9, 2007, which
is not incorporated by reference in this AD.
(3) Airbus Service Bulletin A300–54–0075,
Revision 02, dated June 26, 2008, which is
not incorporated by reference in this AD.
(4) Airbus Service Bulletin A300–54–0075,
Revision 03, dated March 27, 2013, which is
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, 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.
(2) Contacting the Manufacturer: 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
the EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0201, dated
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
October 7, 2015, 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 Docket No. FAA–
2016–6671.
(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 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 May 11,
2016.
Suzanne Masterson,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–11681 Filed 5–20–16; 8:45 am]
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Proposed rule; extension of
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23MYP1
Agencies
[Federal Register Volume 81, Number 99 (Monday, May 23, 2016)]
[Proposed Rules]
[Pages 32256-32258]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-11681]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
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.
========================================================================
Federal Register / Vol. 81, No. 99 / Monday, May 23, 2016 / Proposed
Rules
[[Page 32256]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-6671; Directorate Identifier 2015-NM-164-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Airbus Model A300B4-203 and A300B4-2C airplanes. This proposed
AD was prompted by cracks found on pylon side panels (upper section) at
rib 8. This proposed AD would require a detailed inspection for crack
indications of the pylon side panels, a high frequency eddy current
(HFEC) inspection to confirm any crack indications, modification of the
pylon side panels, and repetitive inspections and repair if necessary.
We are proposing this AD to detect and correct cracking of the pylon
side panels. Such cracking could result in pylon structural failure and
in-flight loss of an engine.
DATES: We must receive comments on this proposed AD by July 7, 2016.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, 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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, 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-2016-
6671; 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 (phone: 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 proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2016-6671;
Directorate Identifier 2015-NM-164-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 because of 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 Union, has issued EASA
Airworthiness Directive 2015-0201, dated October 7, 2015 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A300B4-203 and A300B4-2C airplanes. 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 [which
corresponded 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 and, depending on aeroplane
configuration and/or findings, the accomplishment of applicable
corrective action(s).
Since that [EASA] AD 2008-0181 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 were reduced to allow
timely detection of these cracks and the accomplishment of
applicable corrective action(s).
Consequently, EASA AD 2013-0136 was published to supersede EASA
AD 2008-0181 and to require the inspections to be accomplished
within reduced thresholds and intervals. Afterwards, [EASA] AD 2013-
0136 was mistakenly revised [EASA AD 2013-0136R1 corresponds to FAA
AD 2015-26-06, Amendment 39-18354 (81 FR January 14,2016)] to reduce
the Applicability, because it was considered at the time that
aeroplanes on which Airbus mod 03599 was embodied, were not
concerned by the requirements of EASA AD 2013-0136.
Since EASA AD 2013-0136R1 was issued, a more thorough analysis
determined that post-mod 03599 aeroplanes could be affected by this
unsafe condition after all.
[During] further deeper review, a list of nineteen A300
aeroplanes was identified as
[[Page 32257]]
missing in the [EASA] AD 2013-0136R1 applicability, (aeroplanes
post-mod 03599).
For the reasons described above this AD retains the requirements
of EASA AD 2013-0136R1 and mandates these requirements for the 19
missing A300 aeroplanes MSNs.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6671.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A300-54-0075, Revision 04, dated
May 26, 2015. The service information describes procedures for an
inspection for crack indications of the pylons, a HFEC inspection to
confirm cracking, modification of the pylon side panels, and repairs if
cracks are found.
Airbus has also issued Service Bulletin A300-54-0081, dated August
11, 1993. This service information describes installation of a doubler
on the left pylon 1 and right pylon 2, on pylon side panels (upper
section) at Rib 8.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
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 these
same type designs.
Differences Between Proposed Rule and Service Bulletin
Unlike the procedures described in Airbus Service Bulletin A300-54-
0075, Revision 04, dated May 26, 2015, this proposed AD would not
permit further flight if cracks are detected in the pylon or pylon side
panels. We have determined that because of the safety implications and
consequences associated with that cracking, any cracked pylon or pylon
side panel must be repaired or modified before further flight. This
difference has been coordinated with EASA.
Costs of Compliance
We estimate that this proposed AD affects 4 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Cost per product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspection of the pylon side panels 30 work-hours x $85 per $2,550 per inspection $10,200 per inspection
hour = $2,550 per cycle. 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 airplanes that might need this
repair.
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Crack Repair....................... 56 work-hours x $85 per $3,910 per repair..... $8,670 per repair.
hour = $4,760 per repair.
----------------------------------------------------------------------------------------------------------------
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 adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2016-6671; Directorate Identifier 2015-NM-
164-AD.
[[Page 32258]]
(a) Comments Due Date
We must receive comments by July 7, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A300B4-203 and A300B4-2C
airplanes, certificated in any category, manufacturer serial numbers
210, 212, 218, 220, 227, 234, 235, 236, 239, 247, 255, 256, 259,
261, 274, 277, 292, 299, and 302.
(d) Subject
Air Transport Association (ATA) of America Code 54, Nacelles/
Pylons.
(e) Reason
This AD was prompted by cracks found on pylon side panels (upper
section) at rib 8. We are proposing this AD to detect and correct
cracking of the pylon side panels. Such cracking could result in
pylon structural failure and in-flight loss of an engine.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Detailed Inspection of Pylons and Corrections
At the applicable time specified in Airbus Service Bulletin
A300-54-0075, Revision 04, dated May 26, 2015: Do a detailed
inspection for crack indications of the pylons 1 and 2 side panels
(upper section) at rib 8, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-54-0075, Revision 04,
dated May 26, 2015.
(h) Crack Confirmation
If any crack indication is found during the inspection required
by paragraph (g) of this AD: Before further flight, do a high
frequency eddy current (HFEC) inspection to confirm the crack, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-54-0075, Revision 04, dated May 26, 2015.
(i) Follow-On Actions for No Crack/Indication
If the inspection required by paragraph (g) of this AD reveals
no crack indication, or if the HFEC inspection specified by
paragraph (h) of this AD confirms no crack: Do the actions specified
in either paragraph (i)(1) or (i)(2) of this AD.
(1) Repeat the inspection required by paragraph (g) of this AD
at the applicable time specified in Airbus Service Bulletin A300-54-
0075, Revision 04, dated May 26, 2015.
(2) At the applicable time specified in Airbus Service Bulletin
A300-54-0081, dated August 11, 1993: Modify the pylons, in
accordance with Airbus Service Bulletin 300-54-0081, dated August
11, 1993. Thereafter, repeat the HFEC inspection specified in
paragraph (h) of this AD at the applicable interval specified in
Airbus Service Bulletin A300-54-0075, Revision 04, dated May 26,
2015, and repair any crack before further flight 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).
(j) Follow-On Actions for Crack Findings
If any crack is confirmed during the inspection required by
paragraph (h) of this AD, repair before further flight using a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
(k) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g), (h), (i), and (j) of this AD, if those actions were
performed before the effective date of this AD using the service
information specified in paragraphs (k)(1) through (k)(4) of this
AD.
(1) Airbus Service Bulletin A300-54-0075, dated August 11, 1993,
which was incorporated by referenced in AD 2010-06-04, Amendment 39-
16228 (75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR
23572).
(2) Airbus Service Bulletin A300-54-0075, Revision 01, dated
November 9, 2007, which is not incorporated by reference in this AD.
(3) Airbus Service Bulletin A300-54-0075, Revision 02, dated
June 26, 2008, which is not incorporated by reference in this AD.
(4) Airbus Service Bulletin A300-54-0075, Revision 03, dated
March 27, 2013, which is 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, 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.
(2) Contacting the Manufacturer: 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 the EASA;
or Airbus's EASA DOA. If approved by the DOA, the approval must
include the DOA-authorized signature.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2015-0201, dated October 7,
2015, 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 Docket No. FAA-2016-6671.
(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 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 May 11, 2016.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-11681 Filed 5-20-16; 8:45 am]
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