Airworthiness Directives; Airbus Airplanes, 7989-7992 [2015-02536]
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Federal Register / Vol. 80, No. 30 / Friday, February 13, 2015 / Proposed Rules
(2) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@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 January
30, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–02537 Filed 2–12–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0083; Directorate
Identifier 2014–NM–131–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Airbus Model A330–200, A330–200
Freighter, and A330–300 series
airplanes; and all A340–200 and A340–
300 series airplanes. This proposed AD
was prompted by reports that a bracket
that attaches the cockpit instrument
panel to the airplane structure, does not
sustain the fatigue loads of the design
service goal. This proposed AD would
require repetitive inspections of that
bracket for cracking and to determine if
both lugs are fully broken, an inspection
for cracking of an adjacent bracket, if
necessary, and corrective actions if
necessary. This AD would also provide
an optional modification, which would
terminate the repetitive inspections. We
are proposing this AD to detect and
correct cracking on a bracket of the
cockpit instrument panel, which,
combined with failure of the horizontal
beam, could lead to collapse of the
cockpit panel, and reduced
controllability of the airplane.
DATES: We must receive comments on
this proposed AD by March 30, 2015.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
SUMMARY:
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13:53 Feb 12, 2015
Jkt 235001
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: 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—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80; email
airworthiness.A330–A340@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–2015–
0083; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1138;
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–2015–0083; Directorate Identifier
2014–NM–131–AD’’ at the beginning of
your comments. We specifically invite
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7989
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2014–0127, dated May 15,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A330–200, A330–200 Freighter,
and A330–300 series airplanes; and all
A340–200, and A340–300 series
airplanes. The MCAI states:
During flight tests, high stress levels have
been measured on the bracket No 6 which
attaches the cockpit instrument panel to the
aeroplane structure, apparently introduced
through the nose landing gear due to bumps
on the runway. Airbus determined that the
bracket does not sustain the fatigue loads
during the Design Service Goal (DSG). This
condition, if not detected and corrected,
combined with failure of the horizontal
beam, could lead to collapse of the cockpit
panel, possibly resulting in reduced control
of the aeroplane.
To address this potential unsafe condition,
Airbus developed a program to inspect the
condition of the affected cockpit instrument
panel bracket No 6, and designed a stronger
(reinforced titanium undrilled) bracket. The
new bracket can be installed in-service
through Airbus Service Bulletin (SB) A330–
25–3548 or SB A340–25–4354, as applicable
to aeroplane type.
For the reasons described above, this
[EASA] AD requires repetitive inspections of
the cockpit instrument panel bracket No 6
and, depending on findings, the
accomplishment of applicable corrective
actions. This [EASA] AD also provides the
installation of the stronger bracket as
optional terminating action for the repetitive
actions required by this [EASA] AD.
The corrective actions include replacing
bracket No. 6 and bracket No. 7 with
serviceable parts, and repair, as
applicable.
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–2015–
0083.
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Federal Register / Vol. 80, No. 30 / Friday, February 13, 2015 / Proposed Rules
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information.
• Airbus Service Bulletin A330–25–
3538, Revision 02, dated April 24, 2014,
which provides procedures for
inspection of cockpit instrument panel
bracket 6.
• Airbus Service Bulletin A330–25–
3548, dated October 31, 2013, which
provides procedures for reinforcement
of cockpit instrument panel bracket 6.
• Airbus Service Bulletin A340–25–
4351, Revision 01, dated January 31,
2014, which provides procedures for
inspection of cockpit instrument panel
bracket 6.
• Airbus Service Bulletin A340–25–
4354, dated October 31, 2013, which
provides procedures for reinforcement
of cockpit instrument panel bracket 6.
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI. This service information is
reasonably available; see ADDRESSES for
ways to access this service information.
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.
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Explanation of ‘‘RC’’ Procedures and
Tests in Service Information
The FAA worked in conjunction with
industry, under the Airworthiness
Directives Implementation Aviation
Rulemaking Committee (AD ARC), to
enhance the AD system. One
enhancement was a new process for
annotating which procedures and tests
in the service information are required
for compliance with an AD.
Differentiating these procedures and
tests from other tasks in the service
information is expected to improve an
owner’s/operator’s understanding of
crucial AD requirements and help
provide consistent judgment in AD
compliance. The actions specified in
Airbus Service Bulletin A330–25–3538,
Revision 02, dated April 24, 2014; and
Airbus Service Bulletin A340–25–4351,
Revision 01, dated January 31, 2014;
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13:53 Feb 12, 2015
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include procedures and tests that are
identified as RC (required for
compliance) because these procedures
have a direct effect on detecting,
preventing, resolving, or eliminating an
identified unsafe condition.
As specified in a NOTE under the
Accomplishment Instructions of the
specified service information,
procedures and tests identified as RC
must be done to comply with the
proposed AD. However, procedures and
tests that are not identified as RC are
recommended. Those procedures and
tests that are not identified as RC may
be deviated from using accepted
methods in accordance with the
operator’s maintenance or inspection
program without obtaining approval of
an alternative method of compliance
(AMOC), provided the procedures and
tests identified as RC can be done and
the airplane can be put back in a
serviceable condition. Any substitutions
or changes to procedures or tests
identified as RC will require approval of
an AMOC.
Costs of Compliance
We estimate that this proposed AD
affects 76 airplanes of U.S. registry.
We also estimate that it would take
about 8 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of
this proposed AD on U.S. operators to
be $51,680, or $680 per product.
We have received no definitive data
that would enable us to provide cost
estimates for the follow-on repairs
specified in this AD.
In addition, we estimate that any
necessary follow-on replacements
would take about 23 work-hours and
require parts costing $0, for a cost of
$1,955 per product. We have no way of
determining the number of aircraft that
might need these actions.
We estimate that the optional
modification would take about 9 work
hours and require parts costing $1,770,
for a cost of $2,535.
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
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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
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–2015–0083;
Directorate Identifier 2014–NM–131–AD.
(a) Comments Due Date
We must receive comments by March 30,
2015.
(b) Affected ADs
None.
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Federal Register / Vol. 80, No. 30 / Friday, February 13, 2015 / Proposed Rules
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) and (c)(2) of
this AD, certificated in any category.
(1) Model A330–201, –202, –203, –223,
–243, –223F, –243F, –301, –302, –303, –321,
–322, –323, –341, –342, and –313 airplanes,
all manufacturer serial numbers except those
on which Airbus Modification 203287 has
been embodied in production.
(2) Model A340–211, –212, –213, –311,
–312, and –313 airplanes, all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 25, Equipment/Furnishings.
(e) Reason
This AD was prompted by reports that a
bracket that attaches the cockpit instrument
panel to the airplane structure, does not
sustain the fatigue loads of the design service
goal. We are issuing this AD to detect and
correct cracking on a bracket of the cockpit
instrument panel, which, combined with
failure of the horizontal beam, could lead to
collapse of the cockpit panel, and reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
(g) Inspection of Bracket No. 6 of the Cockpit
Instrument Panel
At the latest of the times specified in
paragraphs (g)(1), (g)(2), and (g)(3) of this AD:
Do a detailed inspection of bracket No. 6 of
the cockpit instrument panel for cracking and
to determine if both bracket lugs are fully
broken, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–25–3538, Revision 02,
dated April 24, 2014; or Airbus Service
Bulletin A340–25–4351, Revision 01, dated
January 31, 2014; as applicable. Repeat the
inspection thereafter at intervals not to
exceed 2,600 flight cycles.
(1) Prior to accumulating 17,200 total flight
cycles since the airplane’s first flight.
(2) Prior to bracket No. 6 of the cockpit
instrument panel accumulating 17,200 total
flight cycles since installation on an airplane.
(3) Within 500 flight cycles after the
effective date of this AD.
(h) Inspection and Corrective Actions
(1) If, during any inspection required by
paragraph (g) of this AD, any cracking of
bracket No. 6 of the cockpit instrument panel
is found, but both bracket lugs are not fully
broken: Within 2,600 flight cycles after that
inspection, replace bracket No. 6 of the
cockpit instrument panel with a serviceable
part, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–25–3538, Revision 02,
dated April 24, 2014; or Airbus Service
Bulletin A340–25–4351, Revision 01, dated
January 31, 2014; as applicable. Replacement
of bracket No. 6 of the cockpit instrument
panel does not constitute terminating action
for the repetitive inspections required by
paragraph (g) of this AD.
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(2) If, during any inspection required by
paragraph (g) of this AD, any cracking of
bracket No. 6 of the cockpit instrument panel
is found and both bracket lugs are fully
broken: Before further flight, do a detailed
inspection of bracket No. 7 of the cockpit
instrument panel for cracking, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A330–25–3538,
Revision 02, dated April 24, 2014; or Airbus
Service Bulletin A340–25–4351, Revision 01,
dated January 31, 2014; as applicable.
(i) If, during the inspection required by
paragraph (h)(2) of this AD, no cracking is
found in bracket No. 7 of the cockpit
instrument panel: Before further flight,
replace bracket No. 6 and bracket No. 7 of the
cockpit instrument panel with serviceable
parts, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–25–3538, Revision 02,
dated April 24, 2014; or Airbus Service
Bulletin A340–25–4351, Revision 01, dated
January 31, 2014; as applicable. Replacement
of bracket No. 6 of the cockpit instrument
panel does not constitute terminating action
for the repetitive inspections required by
paragraph (g) of this AD.
(ii) If, during the inspection required by
paragraph (h)(2) of this AD, any cracking is
found in bracket No. 7 of the cockpit
instrument panel: Although Airbus Service
Bulletin A330–25–3538, Revision 02, dated
April 24, 2014; and Airbus Service Bulletin
A340–25–4351, Revision 01, dated January
31, 2014; specify to contact Airbus for repair
instructions, and specify that action as ‘‘RC’’
(Required for Compliance), repair the
cracking before further flight using a repair
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).
(i) Optional Terminating Modification for
Paragraph (g) of This AD
Modifying an airplane by replacing bracket
No. 6 of the cockpit instrument panel with
a new, reinforced bracket, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A330–25–3548, dated
October 31, 2013; or Airbus Service Bulletin
A340–25–4354, dated October 31, 2013; as
applicable; terminates the repetitive
inspections required by paragraph (g) of this
AD.
(j) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (g) and (h) of this AD,
if those actions were performed before the
effective date of this AD using the service
information identified in paragraph (j)(1),
(j)(2), or (j)(3) of this AD, which are not
incorporated by reference in this AD.
(1) Airbus Service Bulletin A330–25–3538,
dated September 10, 2013.
(2) Airbus Service Bulletin A330–25–3538,
Revision 01, dated April 24, 2014.
(3) Airbus Service Bulletin A340–25–4351,
dated September 10, 2014.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
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7991
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1138; 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.
(3) Required for Compliance (RC): Except
as required by paragraph (h)(2)(ii) of this AD,
if Airbus Service Bulletin A330–25–3538,
Revision 02, dated April 24, 2014; or Airbus
Service Bulletin A340–25–4351, Revision 01,
dated January 31, 2014; contain procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures and tests that
are not identified as RC are recommended.
Those procedures and tests that are not
identified as RC may be deviated from, using
accepted methods in accordance with the
operators maintenance or inspection program
without obtaining approval of an AMOC,
provided the procedures and tests identified
as RC can be done and the airplane can be
put back in a serviceable condition. Any
substitutions or changes to procedures or
tests identified as RC require approval of an
AMOC.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0127, dated
May 15, 2014, 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–
2015–0083.
(2) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@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.
E:\FR\FM\13FEP1.SGM
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7992
Federal Register / Vol. 80, No. 30 / Friday, February 13, 2015 / Proposed Rules
Issued in Renton, Washington, on January
30, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–02536 Filed 2–12–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0084; Directorate
Identifier 2014–NM–181–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Airbus Model A300 B4–2C, B4–103, and
B4–203 airplanes; Airbus Model A300
B4–600 series airplanes; and Airbus
Model A300 B4–600R series airplanes.
This proposed AD was prompted by
reports indicating that, on airplanes that
received a certain repair following crack
findings, cracks can re-initiate. This
proposed AD would require repetitive
inspections for cracking of the frame
(FR) 40 forward fittings for airplanes
previously repaired. We are proposing
this AD to detect and correct cracking
on the FR 40 forward fittings, which
could result in rupture of the forward
fittings and reduction of in-flight
structural strength.
DATES: We must receive comments on
this proposed AD by March 30, 2015.
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: 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,
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
13:53 Feb 12, 2015
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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–2015–
0084; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, 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–2015–0084; Directorate Identifier
2014–NM–181–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2014–0199, dated September
05, 2014 (referred to after this as the
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Fmt 4702
Sfmt 4702
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A300 B4–2C, B4–103, and B4–
203 airplanes; Airbus Model A300 B4–
600 series airplanes; and Airbus Model
A300 B4–600R series airplanes. The
MCAI states:
During routine inspection on an A300–600
aeroplane, a crack was found in the righthand frame (FR) 40 forward fitting between
stringer (STRG) 32 and STRG 33. The subject
aeroplane had previously been modified, as
a crack prevention measure, in accordance
with Airbus SB A300–57–6053 (mod 10453).
To ensure the structural integrity of FR 40,
pending completion of the full root cause
analysis using a refined Finite Element
Model (FEM), EASA issued AD 2009–0094
[dated April 21, 2009, https://
ad.easa.europa.eu/ad/2009–0094], to require,
a one-time Detailed Visual Inspection (DVI)
of A300 and A300–600 aeroplanes on which
Airbus SB A300–53–0297 or SB A300–57–
6053, as applicable, was embodied as a crack
prevention measure.
Thereafter, cracks were found during
maintenance check in the FR 40 forward
fitting on two aeroplanes, one A300 with
Airbus SB A300–53–0297 embodied and one
A300–600 with Airbus SB A300–57–6053
embodied. EASA AD 2009–0094 had been
accomplished on both aeroplanes.
Consequently, EASA issued AD 2011–0163
[dated August 30, 2011, https://
ad.easa.europa.eu/ad/2011-0163],
superseding EASA AD 2009–0094, to require,
for aeroplanes modified preventively,
repetitive DVI of the FR 40 forward fitting
(without nut removal), accomplishment of a
one-time Eddy Current (EC) inspection or
liquid penetrant inspection of this area (with
nut removal) and, depending on findings, the
accomplishment of associated corrective
actions.
A detailed FEM study was recently
completed which demonstrated that, on
aeroplanes repaired following crack findings
in accordance with the instructions of Airbus
SB A300–53–0297 or SB A300–57–6053 at
any revision, as applicable, cracks can reinitiate.
For the reasons described above, this
[EASA] AD requires repetitive inspections of
the FR 40 forward fitting for aeroplanes
repaired in accordance with the instructions
of Airbus SB A300–53–0297 or SB A300–57–
6053 following crack findings.
The corrective actions include a
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).
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–2015–
0084.
E:\FR\FM\13FEP1.SGM
13FEP1
]]>Agencies
[Federal Register Volume 80, Number 30 (Friday, February 13, 2015)]
[Proposed Rules]
[Pages 7989-7992]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-02536]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0083; Directorate Identifier 2014-NM-131-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 A330-200, A330-200 Freighter, and A330-300 series
airplanes; and all A340-200 and A340-300 series airplanes. This
proposed AD was prompted by reports that a bracket that attaches the
cockpit instrument panel to the airplane structure, does not sustain
the fatigue loads of the design service goal. This proposed AD would
require repetitive inspections of that bracket for cracking and to
determine if both lugs are fully broken, an inspection for cracking of
an adjacent bracket, if necessary, and corrective actions if necessary.
This AD would also provide an optional modification, which would
terminate the repetitive inspections. We are proposing this AD to
detect and correct cracking on a bracket of the cockpit instrument
panel, which, combined with failure of the horizontal beam, could lead
to collapse of the cockpit panel, and reduced controllability of the
airplane.
DATES: We must receive comments on this proposed AD by March 30, 2015.
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: 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--EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 45 80; email airworthiness.A330-A340@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-2015-
0083; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138;
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-2015-0083;
Directorate Identifier 2014-NM-131-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0127, dated May 15, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A330-200, A330-200 Freighter, and A330-300 series airplanes; and all
A340-200, and A340-300 series airplanes. The MCAI states:
During flight tests, high stress levels have been measured on
the bracket No 6 which attaches the cockpit instrument panel to the
aeroplane structure, apparently introduced through the nose landing
gear due to bumps on the runway. Airbus determined that the bracket
does not sustain the fatigue loads during the Design Service Goal
(DSG). This condition, if not detected and corrected, combined with
failure of the horizontal beam, could lead to collapse of the
cockpit panel, possibly resulting in reduced control of the
aeroplane.
To address this potential unsafe condition, Airbus developed a
program to inspect the condition of the affected cockpit instrument
panel bracket No 6, and designed a stronger (reinforced titanium
undrilled) bracket. The new bracket can be installed in-service
through Airbus Service Bulletin (SB) A330-25-3548 or SB A340-25-
4354, as applicable to aeroplane type.
For the reasons described above, this [EASA] AD requires
repetitive inspections of the cockpit instrument panel bracket No 6
and, depending on findings, the accomplishment of applicable
corrective actions. This [EASA] AD also provides the installation of
the stronger bracket as optional terminating action for the
repetitive actions required by this [EASA] AD.
The corrective actions include replacing bracket No. 6 and bracket No.
7 with serviceable parts, and repair, as applicable.
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-2015-
0083.
[[Page 7990]]
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information.
Airbus Service Bulletin A330-25-3538, Revision 02, dated
April 24, 2014, which provides procedures for inspection of cockpit
instrument panel bracket 6.
Airbus Service Bulletin A330-25-3548, dated October 31,
2013, which provides procedures for reinforcement of cockpit instrument
panel bracket 6.
Airbus Service Bulletin A340-25-4351, Revision 01, dated
January 31, 2014, which provides procedures for inspection of cockpit
instrument panel bracket 6.
Airbus Service Bulletin A340-25-4354, dated October 31,
2013, which provides procedures for reinforcement of cockpit instrument
panel bracket 6.
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI. This service
information is reasonably available; see ADDRESSES for ways to access
this service information.
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.
Explanation of ``RC'' Procedures and Tests in Service Information
The FAA worked in conjunction with industry, under the
Airworthiness Directives Implementation Aviation Rulemaking Committee
(AD ARC), to enhance the AD system. One enhancement was a new process
for annotating which procedures and tests in the service information
are required for compliance with an AD. Differentiating these
procedures and tests from other tasks in the service information is
expected to improve an owner's/operator's understanding of crucial AD
requirements and help provide consistent judgment in AD compliance. The
actions specified in Airbus Service Bulletin A330-25-3538, Revision 02,
dated April 24, 2014; and Airbus Service Bulletin A340-25-4351,
Revision 01, dated January 31, 2014; include procedures and tests that
are identified as RC (required for compliance) because these procedures
have a direct effect on detecting, preventing, resolving, or
eliminating an identified unsafe condition.
As specified in a NOTE under the Accomplishment Instructions of the
specified service information, procedures and tests identified as RC
must be done to comply with the proposed AD. However, procedures and
tests that are not identified as RC are recommended. Those procedures
and tests that are not identified as RC may be deviated from using
accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an alternative method
of compliance (AMOC), provided the procedures and tests identified as
RC can be done and the airplane can be put back in a serviceable
condition. Any substitutions or changes to procedures or tests
identified as RC will require approval of an AMOC.
Costs of Compliance
We estimate that this proposed AD affects 76 airplanes of U.S.
registry.
We also estimate that it would take about 8 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $51,680, or $680
per product.
We have received no definitive data that would enable us to provide
cost estimates for the follow-on repairs specified in this AD.
In addition, we estimate that any necessary follow-on replacements
would take about 23 work-hours and require parts costing $0, for a cost
of $1,955 per product. We have no way of determining the number of
aircraft that might need these actions.
We estimate that the optional modification would take about 9 work
hours and require parts costing $1,770, for a cost of $2,535.
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-2015-0083; Directorate Identifier 2014-NM-
131-AD.
(a) Comments Due Date
We must receive comments by March 30, 2015.
(b) Affected ADs
None.
[[Page 7991]]
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) and (c)(2) of this AD, certificated in any category.
(1) Model A330-201, -202, -203, -223, -243, -223F, -243F, -301,
-302, -303, -321, -322, -323, -341, -342, and -313 airplanes, all
manufacturer serial numbers except those on which Airbus
Modification 203287 has been embodied in production.
(2) Model A340-211, -212, -213, -311, -312, and -313 airplanes,
all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 25, Equipment/
Furnishings.
(e) Reason
This AD was prompted by reports that a bracket that attaches the
cockpit instrument panel to the airplane structure, does not sustain
the fatigue loads of the design service goal. We are issuing this AD
to detect and correct cracking on a bracket of the cockpit
instrument panel, which, combined with failure of the horizontal
beam, could lead to collapse of the cockpit panel, and reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection of Bracket No. 6 of the Cockpit Instrument Panel
At the latest of the times specified in paragraphs (g)(1),
(g)(2), and (g)(3) of this AD: Do a detailed inspection of bracket
No. 6 of the cockpit instrument panel for cracking and to determine
if both bracket lugs are fully broken, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-25-3538,
Revision 02, dated April 24, 2014; or Airbus Service Bulletin A340-
25-4351, Revision 01, dated January 31, 2014; as applicable. Repeat
the inspection thereafter at intervals not to exceed 2,600 flight
cycles.
(1) Prior to accumulating 17,200 total flight cycles since the
airplane's first flight.
(2) Prior to bracket No. 6 of the cockpit instrument panel
accumulating 17,200 total flight cycles since installation on an
airplane.
(3) Within 500 flight cycles after the effective date of this
AD.
(h) Inspection and Corrective Actions
(1) If, during any inspection required by paragraph (g) of this
AD, any cracking of bracket No. 6 of the cockpit instrument panel is
found, but both bracket lugs are not fully broken: Within 2,600
flight cycles after that inspection, replace bracket No. 6 of the
cockpit instrument panel with a serviceable part, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A330-25-
3538, Revision 02, dated April 24, 2014; or Airbus Service Bulletin
A340-25-4351, Revision 01, dated January 31, 2014; as applicable.
Replacement of bracket No. 6 of the cockpit instrument panel does
not constitute terminating action for the repetitive inspections
required by paragraph (g) of this AD.
(2) If, during any inspection required by paragraph (g) of this
AD, any cracking of bracket No. 6 of the cockpit instrument panel is
found and both bracket lugs are fully broken: Before further flight,
do a detailed inspection of bracket No. 7 of the cockpit instrument
panel for cracking, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-25-3538, Revision 02,
dated April 24, 2014; or Airbus Service Bulletin A340-25-4351,
Revision 01, dated January 31, 2014; as applicable.
(i) If, during the inspection required by paragraph (h)(2) of
this AD, no cracking is found in bracket No. 7 of the cockpit
instrument panel: Before further flight, replace bracket No. 6 and
bracket No. 7 of the cockpit instrument panel with serviceable
parts, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A330-25-3538, Revision 02, dated April 24, 2014; or
Airbus Service Bulletin A340-25-4351, Revision 01, dated January 31,
2014; as applicable. Replacement of bracket No. 6 of the cockpit
instrument panel does not constitute terminating action for the
repetitive inspections required by paragraph (g) of this AD.
(ii) If, during the inspection required by paragraph (h)(2) of
this AD, any cracking is found in bracket No. 7 of the cockpit
instrument panel: Although Airbus Service Bulletin A330-25-3538,
Revision 02, dated April 24, 2014; and Airbus Service Bulletin A340-
25-4351, Revision 01, dated January 31, 2014; specify to contact
Airbus for repair instructions, and specify that action as ``RC''
(Required for Compliance), repair the cracking before further flight
using a repair 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).
(i) Optional Terminating Modification for Paragraph (g) of This AD
Modifying an airplane by replacing bracket No. 6 of the cockpit
instrument panel with a new, reinforced bracket, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A330-25-
3548, dated October 31, 2013; or Airbus Service Bulletin A340-25-
4354, dated October 31, 2013; as applicable; terminates the
repetitive inspections required by paragraph (g) of this AD.
(j) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using the service information
identified in paragraph (j)(1), (j)(2), or (j)(3) of this AD, which
are not incorporated by reference in this AD.
(1) Airbus Service Bulletin A330-25-3538, dated September 10,
2013.
(2) Airbus Service Bulletin A330-25-3538, Revision 01, dated
April 24, 2014.
(3) Airbus Service Bulletin A340-25-4351, dated September 10,
2014.
(k) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-1138; 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.
(3) Required for Compliance (RC): Except as required by
paragraph (h)(2)(ii) of this AD, if Airbus Service Bulletin A330-25-
3538, Revision 02, dated April 24, 2014; or Airbus Service Bulletin
A340-25-4351, Revision 01, dated January 31, 2014; contain
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures and tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified as RC may be deviated from, using
accepted methods in accordance with the operators maintenance or
inspection program without obtaining approval of an AMOC, provided
the procedures and tests identified as RC can be done and the
airplane can be put back in a serviceable condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.
(l) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0127, dated May 15, 2014,
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-2015-0083.
(2) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email airworthiness.A330-A340@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.
[[Page 7992]]
Issued in Renton, Washington, on January 30, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-02536 Filed 2-12-15; 8:45 am]
BILLING CODE 4910-13-P
