Airworthiness Directives; Airbus Airplanes, 60655-60658 [2012-24404]
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Federal Register / Vol. 77, No. 193 / Thursday, October 4, 2012 / Proposed Rules
causing damage to the fire protection system,
hydraulic system, electrical wiring, or other
equipment located in the forward and aft
cargo compartments. This damage could
adversely affect the continued safe flight of
the airplane.
TABLE 1 TO PARAGRAPH (h) OF THIS
AD—AFFECTED
CLD
YZLATCHES—Continued
D 255 7 2350 004
D 255 7 2350 006
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Retained Spacer Assembly Installation
This paragraph restates the requirements of
paragraph (f) of AD 2007–05–13, Amendment
39–14974 (72 FR 10348, March 8, 2007). For
Airbus Model A319, A320, and A321
airplanes identified in paragraphs (g)(1) and
(g)(2) of this AD: Within 36 months after
April 12, 2007 (the effective date of AD
2007–05–13), install spacer assemblies at the
attachment points of the YZ-latches of the
CLS in the forward and aft cargo
compartments, as applicable, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–25–1294,
Revision 2, dated September 5, 2006.
Accomplishing the actions in paragraph (i) of
this AD terminates the requirements of
paragraph (g) of this AD.
(1) Airplanes on which one of the
following has been incorporated in
production: Airbus Modification 20065,
20040, 24495, 24848, 24496, 21895, 21896,
25905, 25907, 22601, 22602, 27187, 28319,
28322, 28330, 28335, or 31797.
(2) Airplanes on which one of the
following has been incorporated in service:
Airbus Service Bulletin A320–25–1132,
A320–25–1133, A320–25–1145, A320–25–
1175, A320–25–1177, A320–25–1276, A320–
25–1278, A320–28–1134, or A320–28–1141.
emcdonald on DSK67QTVN1PROD with PROPOSALS
(h) New Modification
Except for Model A319, A320, and A321
airplanes on which both Airbus
Modifications 32244 and 32245, or both
Airbus Modifications 32316 and 32317, have
been incorporated in production, and on
which no YZ-latch replacements have been
made since first flight: Within 20 months
after the effective date of this AD, modify the
attachment points of fixed YZ-latches of the
CLS, having a part number (P/N) listed in
table 1 to paragraph (h) of this AD, in both
forward and aft lower deck cargo holds by
adding spacer assemblies having P/N
D2557232700000, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320–25–1294,
Revision 6, dated July 23, 2010.
Accomplishing the actions in paragraph (h)
of this AD terminates the requirements of
paragraph (g) of this AD.
TABLE 1 TO PARAGRAPH (h) OF THIS
AD—AFFECTED CLD YZ-LATCHES
D
D
D
D
D
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Part No.
255 7 2380 000
255 7 2380 002
255 7 2380 006
255 7 2380 008
255 7 2350 002
15:08 Oct 03, 2012
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(i) Parts Installation Limitation
As of the effective date of this AD, no
person may install, on the CLS of any
airplane, a YZ-latch having a part number
listed in table 1 to paragraph (h) of this AD,
unless it has been modified in accordance
with the requirements of paragraph (h) of this
AD.
(j) Credit for Previous Actions
(1) This paragraph provides credit for the
installation required by paragraph (g) of this
AD, if the installation was performed before
April 12, 2007 (the effective date of AD
2007–05–13, Amendment 39–14974 (72 FR
10348, March 8, 2007), using Airbus Service
Bulletin A320–25–1294, dated March 14,
2003; or Revision 1, dated March 27, 2006;
which are not incorporated by reference in
this AD.
(2) This paragraph provides credit for the
modification required by paragraph (h) of
this AD, if the modification was performed
before the effective date of this AD, using one
of the following service information and the
additional work is done, in accordance with
the applicable instructions referenced as
‘‘ADDITIONAL WORK’’ in the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320–25–1294,
Revision 6, dated July 23, 2010.
(i) Airbus Service Bulletin A320–25–1294,
dated March 14, 2003.
(ii) Airbus Service Bulletin A320–25–1294,
Revision 1, dated March 27, 2006.
(iii) Airbus Service Bulletin A320–25–
1294, Revision 2, dated September 5, 2006.
(iv) Airbus Mandatory Service Bulletin
A320–25–1294, Revision 3, dated January 22,
2007.
(v) Airbus Mandatory Service Bulletin
A320–25–1294, Revision 4, dated March 13,
2008.
(vi) Airbus Mandatory Service Bulletin
A320–25–1294, Revision 5, dated January 22,
2009.
(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:
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: 9ANM-116-AMOC-REQUESTS@faa.gov.
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60655
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) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(l) Related Information
(1) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive 2011–
0077, dated May 5, 2011; and the following
service information; for related information.
(i)Airbus Service Bulletin A320–25–1294,
Revision 06, dated July 23, 2010.
(ii) Airbus Service Bulletin A320–25–1294,
Revision 02, dated September 5, 2006.
(2) For service information identified in
this AD, contact Airbus SAS–EAW
(Airworthiness Office), 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.airwortheas@airbus.com; Internet https://
www.airbus.com. You may review copies of
the referenced service information at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on
September 26, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2012–24405 Filed 10–3–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1038; Directorate
Identifier 2011–NM–166–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD)
that applies to certain Airbus Model
A319 and A320 airplanes. The existing
AD currently requires repetitive detailed
inspections to detect cracks in the keel
beam side panels, and repair if
SUMMARY:
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Federal Register / Vol. 77, No. 193 / Thursday, October 4, 2012 / Proposed Rules
emcdonald on DSK67QTVN1PROD with PROPOSALS
necessary. Since we issued that AD, we
have received reports of access
difficulties. Additionally, we have
determined that the detailed inspection
is not sufficient to mitigate the unsafe
condition. This proposed AD would
require repetitive eddy current
inspections for cracking in the keel
beam side panels, and corrective actions
if necessary. We are proposing this AD
to detect and correct fatigue cracks on
the side panels of the keel beams, which
could result in reduced structural
integrity of the airplane.
DATES: We must receive comments on
this proposed AD by November 19,
2012.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Airbus,
Airworthiness Office—EAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office 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,
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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–2012–1038; Directorate Identifier
2011–NM–166–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On June 16, 2004, we issued AD
2004–13–06, Amendment 39–13688 (69
FR 38818, June 29, 2004). That AD
required actions intended to address an
unsafe condition on the products listed
above.
Since we issued AD 2004–13–06,
Amendment 39–13688 (69 FR 38818,
June 29, 2004), we have determined that
the detailed inspection required by AD
2004–13–06 is not sufficient to mitigate
the unsafe condition. The European
Aviation Safety Agency (EASA), which
is the Technical Agent for the Member
States of the European Community, has
issued EASA Airworthiness Directive
2011–0134, dated July 15, 2011 (referred
to after this as ‘‘the MCAI’’), to correct
an unsafe condition for the specified
products. The MCAI states:
During certification structural fatigue tests,
several cases of structural damage (cracks)
have been found on keel beam side panels.
Cracks were observed on both sides of the
keel beam around the rivets below the center
wing box between frame (FR) 40 and FR 42,
and in part of the area of the upper elliptical
cut out forward of FR 41.
This type of damage, if not detected and
repaired, would adversely affect the
structural integrity of the aeroplane.
To address this unsafe condition, DGAC
´ ´
[Direction Generale de l’Aviation Civile]
France issued AD 2003–146 [which
corresponds to FAA AD 2004–13–06,
Amendment 39–13688 (69 FR 38818, June
29, 2004)] to require repetitive detailed
inspections of those two areas and corrective
actions, depending on findings.
Prompted by reported access difficulties
and to allow extension of the interval
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Fmt 4702
Sfmt 4702
between two consecutive inspections, Airbus
validated an Eddy current Non-Destructive
Test (NDT) inspection to replace the detailed
inspection.
For the reasons described above, this
[EASA] AD, which supersedes DGAC France
AD 2003–146, requires repetitive Eddycurrent NDT inspections for cracks in the
affected areas of the keel beam side panel
below the center wing box and corrective
actions [repair], depending on findings.
You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued Mandatory Service
Bulletin A320–53–1060, Revision 02,
dated November 30, 2010. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This AD and the
MCAI or Service Information
Although the MCAI and Airbus
Mandatory Service Bulletin A320–53–
1060, Revision 02, dated November 30,
2010, allow further flight after cracks are
found during compliance with the
proposed actions, this proposed AD
would require repair before further
flight if cracks are detected in the keel
beam side panels. We have determined
that, because of the safety implications
and consequences associated with that
cracking, any cracking in the keel beam
side panels must be repaired before
further flight.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 351 products of U.S.
registry.
We estimate that it would take about
29 work-hours per product to comply
with the new basic requirements of this
proposed AD. The average labor rate is
$85 per work-hour. Based on these
figures, we estimate the cost of the
proposed AD on U.S. operators to be
$865,215, or $2,465 per product.
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Federal Register / Vol. 77, No. 193 / Thursday, October 4, 2012 / Proposed Rules
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD. We have
no way of determining the number of
products that may need these actions.
emcdonald on DSK67QTVN1PROD with PROPOSALS
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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
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,
VerDate Mar<15>2010
15:08 Oct 03, 2012
Jkt 229001
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
removing airworthiness directive (AD)
2004–13–06, Amendment 39–13688 (69
FR 38818, June 29, 2004), and adding
the following new AD:
Airbus: Docket No. FAA–2012–1038;
Directorate Identifier 2011–NM–166–AD.
(a) Comments Due Date
We must receive comments by November
19, 2012.
(b) Affected ADs
This AD supersedes AD 2004–13–06,
Amendment 39–13688 (69 FR 38818, June
29, 2004).
(c) Applicability
This AD applies to Airbus Model A319–
111, –112, –113, –114, –115, –131, –132, and
–133 airplanes; and Model A320–111, –211,
–212, –214, –231, –232, and –233 airplanes;
certificated in any category; all manufacturer
serial numbers, except those having
embodied Airbus modification 30355 in
production.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracks
on the side panels of the keel beams. We are
issuing this AD to detect and correct fatigue
cracks on the side panels of the keel beams,
which could result in reduced structural
integrity of the airplane.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Repetitive Eddy Current Inspection
At the applicable compliance time in
paragraph (k)(1) or (k)(2) of this AD: Do an
eddy current non-destructive test (NDT)
inspection to detect cracks in the keel beam
side panels at Area A and Area B, in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–53–1060, Revision 02, dated
November 30, 2010. Repeat the inspection
thereafter at intervals not to exceed 12,000
flight cycles or 26,700 flight hours,
whichever occurs first. Area A is part of the
area of the upper elliptical cut-out stringer
(STGR) 42 on the left-hand (LH) and righthand (RH) side forward of Frame (FR) 41, and
Area B is the area around the rivets on both
sides of the keel beam side panel below the
center wing box at STGR 42 on the LH and
RH side between FR 40 and FR 42.
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60657
(1) For airplanes that have been inspected
as specified in Airworthiness Limitations
Item (ALI) Task 533142–01–1, which was
specified in the Airbus A319/A320/A321 ALI
document up to Revision 05 inclusive; or as
specified in Airbus A319/A320/A321
Maintenance Review Board (MRB) Report up
to Revision 08 inclusive; or as specified in
the instructions of Airbus Service Bulletin
A320–53–1060, dated June 19, 2002, or
Revision 01, dated April 2, 2004: At the later
of the times specified in paragraphs (g)(1)(i)
and (g)(1)(ii) of this AD.
(i) Within 4,300 flight cycles or 9,600 flight
hours after the last inspection, whichever
occurs first.
(ii) Within 30 days after the effective date
of this AD.
(2) For airplanes other than those
identified in paragraph (g)(1) of this AD: At
the later of the times specified in paragraphs
(g)(2)(i) and (g)(2)(ii) of this AD.
(i) Prior to the accumulation of 24,200 total
flight cycles, or 48,400 total flight hours,
whichever occurs first.
(ii) Within 30 days after the effective date
of this AD.
(h) Corrective Action for Cracking
(1) If any crack is found in Area A during
any inspection required by paragraph (g) of
this AD: Before further flight, repair the
affected area, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320–53–1060,
Revision 02, dated November 30, 2010.
Accomplishing a repair terminates the
repetitive inspections of Area A required by
paragraph (g) of this AD for that side of the
keel beam.
(2) If any crack is found in Area B during
any inspection required by this AD: Before
further flight, repair the affected area in
accordance with a method approved by
either the Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA; or the European Aviation Safety
Agency (EASA) (or its delegated agent).
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, 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) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
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Federal Register / Vol. 77, No. 193 / Thursday, October 4, 2012 / Proposed Rules
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(j) Special Flight Permits
Special flight permits may be issued in
accordance with sections 21.197 and 21.199
of the Federal Aviation Regulations (14 CFR
21.197 and 21.199) to operate the airplane to
a location where the airplane can be repaired
(if the operator elects to do so), provided the
conditions in paragraph (n)(1), (n)(2), or
(n)(3) of this AD are met. Areas A and B are
defined in Airbus Mandatory Service
Bulletin A320–53–1060, Revision 02, dated
November 30, 2010.
(1) No multiple cracks in Area A.
(2) If there is a single crack in Area A, the
length must be less than 20.0 millimeters
(0.79 inch).
(3) No cracking in Area B.
–132 airplanes; Model A320–211, –212,
–214, –231, and –232 airplanes; and
Model A321–111 and –131 airplanes.
This proposed AD was prompted by a
report of two fatigue cracks on the lefthand and right-hand sides of the
continuity fittings at the front
windshield lower framing on a Model
A319 airplane. This proposed AD would
require a high frequency eddy current
(HFEC) inspection for any cracking on
the left-hand and right-hand sides of the
windshield central lower node
continuity fittings, and repair if
necessary. We are proposing this AD to
detect and correct cracking of the
windshield central lower node
continuity fittings, which could reduce
the structural integrity of the airplane.
DATES: We must receive comments on
this proposed AD by November 19,
2012.
[Docket No. FAA–2012–1039; Directorate
Identifier 2011–NM–275–AD]
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Airbus,
Airworthiness Office—EAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
RIN 2120–AA64
Examining the AD Docket
(k) Related Information
(1) Refer to MCAI EASA Airworthiness
Directive 2011–0134, dated July 15, 2011;
and Airbus Mandatory Service Bulletin
A320–53–1060, Revision 02, dated November
30, 2010; for related information.
(2) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com; Internet
https://www.airbus.com. You may review
copies of the referenced service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on
September 26, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2012–24404 Filed 10–3–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
emcdonald on DSK67QTVN1PROD with PROPOSALS
14 CFR Part 39
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 A319–112, –113, and
SUMMARY:
VerDate Mar<15>2010
15:08 Oct 03, 2012
Jkt 229001
ADDRESSES:
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office 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
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
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,
Washington 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–2012–1039; Directorate Identifier
2011–NM–275–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2011–0231,
dated December 9, 2011 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
One operator reported finding two fatigue
cracks on continuity fittings at left-hand (LH)
and right-hand (RH) sides at the front
windshield lower framing on an A319
aeroplane on which Airbus modification
(mod.) 22058 had been embodied in
production. Airbus mod. 22058 (which is
included in Airbus mod. 21999) was
introduced to improve the fatigue strength of
the windshield front framing by increasing
the thickness of framing flanges adjacent to
the concerned fittings.
Further analyses have demonstrated that
the damage tolerance and fatigue
requirements of JAR 25.571 (b) are not met
on aeroplanes in post-mod. 22058
configuration.
This condition, if not detected and
corrected, could reduce the structural
integrity of the affected aeroplanes.
Required actions include an HFEC
inspection for any cracking on the lefthand and right-hand sides of the
windshield central lower node
continuity fittings, and repair if
E:\FR\FM\04OCP1.SGM
04OCP1
]]>Agencies
[Federal Register Volume 77, Number 193 (Thursday, October 4, 2012)]
[Proposed Rules]
[Pages 60655-60658]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-24404]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1038; Directorate Identifier 2011-NM-166-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to certain Airbus Model A319 and A320 airplanes. The
existing AD currently requires repetitive detailed inspections to
detect cracks in the keel beam side panels, and repair if
[[Page 60656]]
necessary. Since we issued that AD, we have received reports of access
difficulties. Additionally, we have determined that the detailed
inspection is not sufficient to mitigate the unsafe condition. This
proposed AD would require repetitive eddy current inspections for
cracking in the keel beam side panels, and corrective actions if
necessary. We are proposing this AD to detect and correct fatigue
cracks on the side panels of the keel beams, which could result in
reduced structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by November 19,
2012.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44
51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
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-2012-1038;
Directorate Identifier 2011-NM-166-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On June 16, 2004, we issued AD 2004-13-06, Amendment 39-13688 (69
FR 38818, June 29, 2004). That AD required actions intended to address
an unsafe condition on the products listed above.
Since we issued AD 2004-13-06, Amendment 39-13688 (69 FR 38818,
June 29, 2004), we have determined that the detailed inspection
required by AD 2004-13-06 is not sufficient to mitigate the unsafe
condition. The European Aviation Safety Agency (EASA), which is the
Technical Agent for the Member States of the European Community, has
issued EASA Airworthiness Directive 2011-0134, dated July 15, 2011
(referred to after this as ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI states:
During certification structural fatigue tests, several cases of
structural damage (cracks) have been found on keel beam side panels.
Cracks were observed on both sides of the keel beam around the
rivets below the center wing box between frame (FR) 40 and FR 42,
and in part of the area of the upper elliptical cut out forward of
FR 41.
This type of damage, if not detected and repaired, would
adversely affect the structural integrity of the aeroplane.
To address this unsafe condition, DGAC [Direction
G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 2003-
146 [which corresponds to FAA AD 2004-13-06, Amendment 39-13688 (69
FR 38818, June 29, 2004)] to require repetitive detailed inspections
of those two areas and corrective actions, depending on findings.
Prompted by reported access difficulties and to allow extension
of the interval between two consecutive inspections, Airbus
validated an Eddy current Non-Destructive Test (NDT) inspection to
replace the detailed inspection.
For the reasons described above, this [EASA] AD, which
supersedes DGAC France AD 2003-146, requires repetitive Eddy-current
NDT inspections for cracks in the affected areas of the keel beam
side panel below the center wing box and corrective actions
[repair], depending on findings.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A320-53-1060, Revision
02, dated November 30, 2010. The actions described in this service
information are intended to correct the unsafe condition identified in
the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This AD and the MCAI or Service Information
Although the MCAI and Airbus Mandatory Service Bulletin A320-53-
1060, Revision 02, dated November 30, 2010, allow further flight after
cracks are found during compliance with the proposed actions, this
proposed AD would require repair before further flight if cracks are
detected in the keel beam side panels. We have determined that, because
of the safety implications and consequences associated with that
cracking, any cracking in the keel beam side panels must be repaired
before further flight.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 351 products of U.S. registry.
We estimate that it would take about 29 work-hours per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of the proposed AD on U.S. operators to be $865,215, or $2,465
per product.
[[Page 60657]]
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD. We have no way of determining the number of products that may 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing airworthiness directive
(AD) 2004-13-06, Amendment 39-13688 (69 FR 38818, June 29, 2004), and
adding the following new AD:
Airbus: Docket No. FAA-2012-1038; Directorate Identifier 2011-NM-
166-AD.
(a) Comments Due Date
We must receive comments by November 19, 2012.
(b) Affected ADs
This AD supersedes AD 2004-13-06, Amendment 39-13688 (69 FR
38818, June 29, 2004).
(c) Applicability
This AD applies to Airbus Model A319-111, -112, -113, -114, -
115, -131, -132, and -133 airplanes; and Model A320-111, -211, -212,
-214, -231, -232, and -233 airplanes; certificated in any category;
all manufacturer serial numbers, except those having embodied Airbus
modification 30355 in production.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracks on the side panels of
the keel beams. We are issuing this AD to detect and correct fatigue
cracks on the side panels of the keel beams, which could result in
reduced structural integrity of the airplane.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Repetitive Eddy Current Inspection
At the applicable compliance time in paragraph (k)(1) or (k)(2)
of this AD: Do an eddy current non-destructive test (NDT) inspection
to detect cracks in the keel beam side panels at Area A and Area B,
in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320-53-1060, Revision 02, dated November
30, 2010. Repeat the inspection thereafter at intervals not to
exceed 12,000 flight cycles or 26,700 flight hours, whichever occurs
first. Area A is part of the area of the upper elliptical cut-out
stringer (STGR) 42 on the left-hand (LH) and right-hand (RH) side
forward of Frame (FR) 41, and Area B is the area around the rivets
on both sides of the keel beam side panel below the center wing box
at STGR 42 on the LH and RH side between FR 40 and FR 42.
(1) For airplanes that have been inspected as specified in
Airworthiness Limitations Item (ALI) Task 533142-01-1, which was
specified in the Airbus A319/A320/A321 ALI document up to Revision
05 inclusive; or as specified in Airbus A319/A320/A321 Maintenance
Review Board (MRB) Report up to Revision 08 inclusive; or as
specified in the instructions of Airbus Service Bulletin A320-53-
1060, dated June 19, 2002, or Revision 01, dated April 2, 2004: At
the later of the times specified in paragraphs (g)(1)(i) and
(g)(1)(ii) of this AD.
(i) Within 4,300 flight cycles or 9,600 flight hours after the
last inspection, whichever occurs first.
(ii) Within 30 days after the effective date of this AD.
(2) For airplanes other than those identified in paragraph
(g)(1) of this AD: At the later of the times specified in paragraphs
(g)(2)(i) and (g)(2)(ii) of this AD.
(i) Prior to the accumulation of 24,200 total flight cycles, or
48,400 total flight hours, whichever occurs first.
(ii) Within 30 days after the effective date of this AD.
(h) Corrective Action for Cracking
(1) If any crack is found in Area A during any inspection
required by paragraph (g) of this AD: Before further flight, repair
the affected area, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A320-53-1060,
Revision 02, dated November 30, 2010. Accomplishing a repair
terminates the repetitive inspections of Area A required by
paragraph (g) of this AD for that side of the keel beam.
(2) If any crack is found in Area B during any inspection
required by this AD: Before further flight, repair the affected area
in accordance with a method approved by either the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the European Aviation Safety Agency (EASA) (or its delegated
agent).
(i) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, 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) Airworthy Product: For any requirement in this AD to obtain
corrective actions from
[[Page 60658]]
a manufacturer or other source, use these actions if they are FAA-
approved. Corrective actions are considered FAA-approved if they are
approved by the State of Design Authority (or their delegated
agent). You are required to assure the product is airworthy before
it is returned to service.
(j) Special Flight Permits
Special flight permits may be issued in accordance with sections
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199) to operate the airplane to a location where the airplane
can be repaired (if the operator elects to do so), provided the
conditions in paragraph (n)(1), (n)(2), or (n)(3) of this AD are
met. Areas A and B are defined in Airbus Mandatory Service Bulletin
A320-53-1060, Revision 02, dated November 30, 2010.
(1) No multiple cracks in Area A.
(2) If there is a single crack in Area A, the length must be
less than 20.0 millimeters (0.79 inch).
(3) No cracking in Area B.
(k) Related Information
(1) Refer to MCAI EASA Airworthiness Directive 2011-0134, dated
July 15, 2011; and Airbus Mandatory Service Bulletin A320-53-1060,
Revision 02, dated November 30, 2010; for related information.
(2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on September 26, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-24404 Filed 10-3-12; 8:45 am]
BILLING CODE 4910-13-P
