Airworthiness Directives; Airbus Airplanes, 3533-3535 [2015-00943]
Download as PDF
Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules
Internet https://www.aerochain.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.
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Tom Rodriguez, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1137; 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
EASA; or ATR—GIE Avions de Transport
´
Regional’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
emcdonald on DSK67QTVN1PROD with PROPOSALS
25–1141, dated August 19, 2013; as
applicable.
(1) If, during the measurement required by
paragraph (i) of this AD, it is determined that
there is a gap equal to or greater than 6 mm
(0.236 inch): Before further flight, re-install
the LH and RH Type III Emergency Exit
Doors, in accordance with the
Accomplishment Instructions of ATR Service
Bulletin ATR42–25–0180, dated August 19,
2013; or ATR72–25–1141, dated August 19,
2013; as applicable.
(2) If, during the measurement required by
paragraph (i) of this AD, it is determined that
there is a gap less than 6 mm (0.236 inch):
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 ATR—GIE Avions
´
de Transport Regional’s EASA Design
Organization Approval (DOA).
[Docket No. FAA–2014–1047; Directorate
Identifier 2014–NM–157–AD]
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0280, dated
November 26, 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 Docket No.
FAA–2015–0077.
(2) For service information identified in
this AD, contact ATR—GIE Avions de
´
´
Transport Regional, 1, Allee Pierre Nadot,
31712 Blagnac Cedex, France; telephone +33
(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18;
email continued.airworthiness@atr.fr;
VerDate Sep<11>2014
19:56 Jan 22, 2015
Jkt 235001
Issued in Renton, Washington, on January
15, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–00956 Filed 1–22–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
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 A318, A319, A320, and
A321 series airplanes. This proposed
AD was prompted by a report that,
during the assembly process, several
gaps between the two parts of the girt
bar fittings for the aft passenger doors
were found to exceed tolerances. This
proposed AD would require an
inspection of the gap between the two
parts of the girt bar fittings on left-hand
(LH) and right-hand (RH) aft passenger
doors, and corrective actions if
necessary. We are proposing this AD to
detect and correct incorrect gaps
between the girt bar fittings. Detachment
of a girt bar could lead to the separation
of the slide or slide-raft from the
fuselage, making the emergency exit
inoperative, which could impede an
emergency evacuation.
DATES: We must receive comments on
this proposed AD by March 9, 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.
SUMMARY:
PO 00000
Frm 00036
Fmt 4702
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3533
• 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,
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
1047; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2014–1047; Directorate Identifier
2014–NM–157–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
E:\FR\FM\23JAP1.SGM
23JAP1
3534
Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules
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 2014–0178, dated July 25,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A318, A319, A320, and A321
series airplanes. The MCAI states:
During final assembly line process, several
AFT passenger door lower fitting gaps were
found excessive and out of tolerance between
two parts of the girt bar fittings. The gap
contributes to the correct locking of the girt
bar during the door lifting movement,
ensuring the retention of the girt bar when
the loads applied on the girt by the slide are
directed from the outside to the inside. If the
gap is too large, there is a risk that the girt
bar, when subjected to these loads, will
detach from one of the girt bar fittings.
This condition, if not detected and
corrected, could lead to the separation of the
slide/slide-raft from the fuselage, making the
emergency exit inoperative and,
consequently, significantly reducing the
safety margin for the occupants during an
evacuation.
For the reason described above, this
[EASA] AD requires a detailed inspection
(DET) to check the gap between the two parts
of the girt bar fittings, on AFT passenger
doors, left-hand (LH) and right-hand (RH)
sides, and, depending on findings,
accomplishment of the applicable corrective
actions [such as modifiying or replacing the
automatic latch].
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–2014–
1047.
emcdonald on DSK67QTVN1PROD with PROPOSALS
Related Service Information
Airbus has issued Service Bulletin
A320–53–1289, dated May 28, 2014.
The service information describes
procedures for a detailed inspection of
the gap in the girt bar fittings of the aft
passenger doors, LH and RH sides, and
corrective actions. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
VerDate Sep<11>2014
19:56 Jan 22, 2015
Jkt 235001
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 the
service information identified
previously 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 838 airplanes of U.S. registry.
We also estimate that it would take
about 3 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 $213,690, or $255 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 4 work-hours and require parts
costing $435, for a cost of $775 per
PO 00000
Frm 00037
Fmt 4702
Sfmt 4702
product. We have no way of
determining the number of aircraft that
might need these actions.
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:
E:\FR\FM\23JAP1.SGM
23JAP1
Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / 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. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2014–1047;
Directorate Identifier 2014–NM–157–AD.
(a) Comments Due Date
We must receive comments by March 9,
2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus airplanes
identified in paragraphs (c)(1) through (c)(4)
of this AD, certificated in any category,
except those on which Airbus Modification
154966 has been embodied during
production.
(1) Model A318–111, –112, –121, and –122
airplanes.
(2) Model A319–111, –112, –113, –114,
–115, –131, –132, and –133 airplanes.
(3) Model A320–211, –212, –214, –231,
–232, and –233 airplanes.
(4) Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report that,
during the assembly process, several gaps
between the two parts of the girt bar fittings
for the aft passenger doors were found to
exceed tolerances. We are issuing this AD to
detect and correct incorrect gaps between the
girt bar fittings. Detachment of a girt bar
could lead to the separation of the slide or
slide-raft from the fuselage, making the
emergency exit inoperative, which could
impede an emergency evacuation.
emcdonald on DSK67QTVN1PROD with PROPOSALS
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection and Corrective Action
Except as provided by paragraph (h) of this
AD, within 36 months after the effective date
of this AD, do a detailed inspection of the
gap in the girt bar fittings of the aft passenger
doors, LH and RH sides, and do all
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–53–1289,
dated May 28, 2014. Do all applicable
corrective actions before further flight.
(h) Exception
For any airplane that has been modified to
a configuration where one or both LH and RH
aft passenger doors are permanently
VerDate Sep<11>2014
19:56 Jan 22, 2015
Jkt 235001
inoperative or deactivated: If any aft
passenger door is reactivated, after
reactivation but before further flight, do the
detailed inspection of the reactivated aft
passenger door(s) and all applicable
corrective actions, as required by paragraph
(g) of this AD.
(i) 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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; 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) Required for Compliance (RC): If the
service information contains 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
operator’s 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.
(3) 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 European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(j) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency (EASA)
Airworthiness Directive 2014–0178, dated
July 25, 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–
2014–1047.
(2) For service information identified in
this AD, contact Airbus, Airworthiness
PO 00000
Frm 00038
Fmt 4702
Sfmt 4702
3535
Office–EIAS, 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 January
14, 2015.
John P. Piccola,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–00943 Filed 1–22–15; 8:45 am]
BILLING CODE 4910–13–P
CONSUMER PRODUCT SAFETY
COMMISSION
16 CFR Part 1422
[Docket No. CPSC–2009–0087]
Recreational Off-Highway Vehicles
(ROVs); Notice of Extension of
Comment Period
U.S. Consumer Product Safety
Commission.
ACTION: Extension of comment period.
AGENCY:
The Consumer Product Safety
Commission (Commission or CPSC)
published a notice of proposed
rulemaking (NPR) in the Federal
Register on November 19, 2014,
concerning recreational off-highway
vehicles (ROVs). The NPR invited the
public to submit written comments by
February 2, 2015. In response to two
requests for an extension, the
Commission is extending the comment
period.
DATES: Submit comments by April 8,
2015.
ADDRESSES: You may submit comments,
identified by Docket No. CPSC–2009–
0087, by any of the following methods:
SUMMARY:
Electronic Submissions
Submit electronic comments in the
following way:
Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
The Commission does not accept
comments submitted by electronic mail
(email), except through: https://
www.regulations.gov. The Commission
encourages you to submit electronic
comments by using the Federal
eRulemaking Portal, as described above.
Written Submissions
Submit written submissions in the
following way:
Mail/Hand delivery/Courier,
preferably in five copies, to: Office of the
E:\FR\FM\23JAP1.SGM
23JAP1
Agencies
[Federal Register Volume 80, Number 15 (Friday, January 23, 2015)]
[Proposed Rules]
[Pages 3533-3535]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-00943]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-1047; Directorate Identifier 2014-NM-157-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 A318, A319, A320, and A321 series airplanes. This
proposed AD was prompted by a report that, during the assembly process,
several gaps between the two parts of the girt bar fittings for the aft
passenger doors were found to exceed tolerances. This proposed AD would
require an inspection of the gap between the two parts of the girt bar
fittings on left-hand (LH) and right-hand (RH) aft passenger doors, and
corrective actions if necessary. We are proposing this AD to detect and
correct incorrect gaps between the girt bar fittings. Detachment of a
girt bar could lead to the separation of the slide or slide-raft from
the fuselage, making the emergency exit inoperative, which could impede
an emergency evacuation.
DATES: We must receive comments on this proposed AD by March 9, 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, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
1047; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-1047;
Directorate Identifier 2014-NM-157-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
[[Page 3534]]
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 2014-0178, dated July 25, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A318, A319, A320, and A321 series airplanes. The MCAI states:
During final assembly line process, several AFT passenger door
lower fitting gaps were found excessive and out of tolerance between
two parts of the girt bar fittings. The gap contributes to the
correct locking of the girt bar during the door lifting movement,
ensuring the retention of the girt bar when the loads applied on the
girt by the slide are directed from the outside to the inside. If
the gap is too large, there is a risk that the girt bar, when
subjected to these loads, will detach from one of the girt bar
fittings.
This condition, if not detected and corrected, could lead to the
separation of the slide/slide-raft from the fuselage, making the
emergency exit inoperative and, consequently, significantly reducing
the safety margin for the occupants during an evacuation.
For the reason described above, this [EASA] AD requires a
detailed inspection (DET) to check the gap between the two parts of
the girt bar fittings, on AFT passenger doors, left-hand (LH) and
right-hand (RH) sides, and, depending on findings, accomplishment of
the applicable corrective actions [such as modifiying or replacing
the automatic latch].
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-2014-
1047.
Related Service Information
Airbus has issued Service Bulletin A320-53-1289, dated May 28,
2014. The service information describes procedures for a detailed
inspection of the gap in the girt bar fittings of the aft passenger
doors, LH and RH sides, and corrective actions. The actions described
in this service information are intended to correct the unsafe
condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of 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 the service information identified previously
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 838 airplanes of U.S.
registry.
We also estimate that it would take about 3 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 $213,690, or $255
per product.
In addition, we estimate that any necessary follow-on actions would
take about 4 work-hours and require parts costing $435, for a cost of
$775 per product. We have no way of determining the number of aircraft
that might need these actions.
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 3535]]
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-2014-1047; Directorate Identifier 2014-NM-
157-AD.
(a) Comments Due Date
We must receive comments by March 9, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus airplanes identified in paragraphs
(c)(1) through (c)(4) of this AD, certificated in any category,
except those on which Airbus Modification 154966 has been embodied
during production.
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report that, during the assembly
process, several gaps between the two parts of the girt bar fittings
for the aft passenger doors were found to exceed tolerances. We are
issuing this AD to detect and correct incorrect gaps between the
girt bar fittings. Detachment of a girt bar could lead to the
separation of the slide or slide-raft from the fuselage, making the
emergency exit inoperative, which could impede an emergency
evacuation.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection and Corrective Action
Except as provided by paragraph (h) of this AD, within 36 months
after the effective date of this AD, do a detailed inspection of the
gap in the girt bar fittings of the aft passenger doors, LH and RH
sides, and do all applicable corrective actions, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-53-
1289, dated May 28, 2014. Do all applicable corrective actions
before further flight.
(h) Exception
For any airplane that has been modified to a configuration where
one or both LH and RH aft passenger doors are permanently
inoperative or deactivated: If any aft passenger door is
reactivated, after reactivation but before further flight, do the
detailed inspection of the reactivated aft passenger door(s) and all
applicable corrective actions, as required by paragraph (g) of this
AD.
(i) 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: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; 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) Required for Compliance (RC): If the service information
contains 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
operator's 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.
(3) 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
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(j) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) European Aviation Safety Agency (EASA) Airworthiness
Directive 2014-0178, dated July 25, 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-
2014-1047.
(2) For service information identified in this AD, contact
Airbus, Airworthiness Office-EIAS, 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 January 14, 2015.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-00943 Filed 1-22-15; 8:45 am]
BILLING CODE 4910-13-P