Airworthiness Directives; Airbus Airplanes, 58975-58978 [2013-23269]
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Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
Dassault Aviation: Docket No. FAA–2013–
0794; Directorate Identifier 2012–NM–
157–AD.
(a) Comments Due Date
We must receive comments by November
12, 2013.
(b) Affected ADs
Certain requirements of this AD terminate
the requirements of AD 2010–26–05,
Amendment 39–16544 (75 FR 79952,
December 21, 2010), for the airplanes
identified in paragraph (c) of this AD.
(c) Applicability
This AD applies to Dassault Aviation
Model FALCON 2000EX airplanes,
certificated in any category, all serial
numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 05, Time Limits/Maintenance
Checks.
(e) Reason
This AD was prompted by a revision to the
airplane airworthiness limitations to
introduce the corrosion prevention control
program, among other changes, to the
maintenance requirements and airworthiness
limitations. We are issuing this AD to prevent
reduced structural integrity of the airplane.
TKELLEY on DSK3SPTVN1PROD with PROPOSALS
(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) Revision of Maintenance or Inspection
Program
Within 30 days after the effective date of
this AD, revise the maintenance or inspection
program, as applicable, to incorporate the
information specified in Chapter 5–40,
Airworthiness Limitations, DGT 113877,
Revision 8, dated July 2012, of Chapter 5 of
the Dassault Falcon 2000EX, Falcon 2000EX
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16:14 Sep 24, 2013
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EASy, Falcon 2000DX, and Falcon 2000LX
Maintenance Manual, dated July 16, 2012.
The initial compliance time for
accomplishing the actions specified in
Chapter 5–40, Airworthiness Limitations,
DGT 113877, Revision 8, dated July 2012, of
Chapter 5 of the Dassault Falcon 2000EX,
Falcon 2000EX EASy, Falcon 2000DX, and
Falcon 2000LX Maintenance Manual, dated
July 16, 2012, is within the times specified
in that maintenance manual, or 30 days after
the effective date of this AD, whichever
occurs later, except as provided by
paragraphs (g)(1) through (g)(4) of this AD.
(1) The term ‘‘landings’’ in the ‘‘First
Inspection’’ column of any table in the
service information means total airplane
landings.
(2) The term ‘‘flight hours’’ in the ‘‘First
Inspection’’ column of any table in the
service information means total flight hours.
(3) The term ‘‘flight cycles’’ in the ‘‘First
Inspection’’ column of any table in the
service information means total flight cycles.
(4) For task number 52–20–00–610–801–01
52–205 the initial compliance time is within
24 months after the effective date of this AD.
(h) Terminating Action
Accomplishing paragraph (g) of this AD
terminates the requirements of paragraph (g)
of AD 2010–26–05, Amendment 39–16544
(75 FR 79952, December 21, 2010), for
Dassault Aviation Model FALCON 2000EX
Airplanes.
(i) No Alternative Actions and Intervals
After accomplishing the revision required
by paragraph (g) of this AD, no alternative
actions (e.g., inspections) or intervals may be
used unless the actions or intervals are
approved as an alternative method of
compliance (AMOC) in accordance with the
procedures specified in paragraph (j) of this
AD.
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) 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, Washington 98057–
3356; telephone 425–227–1137; fax 425–227–
1137. Information may be emailed to: 9ANM-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
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
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58975
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.
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency Airworthiness
Directive 2012–0157, dated August 23, 2012,
for related information. The MCAI can be
found in the AD docket on the Internet at
https://www.regulations.gov.
(2) For service information identified in
this AD, contact Dassault Falcon Jet, P.O. Box
2000, South Hackensack, NJ 07606;
telephone 201–440–6700; Internet https://
www.dassaultfalcon.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 13, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–23333 Filed 9–24–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0791; Directorate
Identifier 2012–NM–026–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 all
Airbus Model A318, A319, A320, and
A321 series airplanes. This proposed
AD was prompted by a report that an
investigation showed that when a
certain combination of a target/
proximity sensor serial number is
installed on a flap interconnecting strut,
a ‘‘target FAR’’ signal cannot be detected
when it reaches the mechanical end
stop of the interconnecting strut. This
proposed AD would require an
inspection to determine the part number
(P/N) of the interconnecting struts
installed on the wings, identifying the
P/N and the serial number (S/N) of the
associated target and proximity sensor if
applicable, and replacing or reidentifying the flap interconnecting
strut if applicable. We are proposing
SUMMARY:
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Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules
this AD to detect and correct a latent
failure of the flap down drive
disconnection due to an already-failed
interconnecting strut sensor, which
could result in asymmetric flap panel
movement and consequent loss of
control of the airplane.
DATES: We must receive comments on
this proposed AD by November 12,
2013.
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,
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–2013–0791; Directorate Identifier
2012–NM–026–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 2012–0012,
dated January 23, 2012 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
The flap interconnecting strut is a safety
device of the High Lift System which acts as
an alternative load path from one flap surface
to another in case of a flap drive system
disconnection. In such a failure case, the
installed proximity provide information to
the slat flap control computer (SFCC) and the
operation of the flap drive system is
inhibited.
A recent engineering investigation has
shown that, when a certain combination of
target/sensor serial number (s/n) is installed
on a flap interconnecting strut, a ‘‘target
FAR’’ signal cannot be detected when
reaching the mechanical end stop of the
interconnecting strut.
This condition, if not corrected, could
cause a flap down drive disconnection to
remain undetected, due to an already-failed
interconnecting strut sensor, potentially
resulting in asymmetric flap panel movement
and consequent loss of control of the
aeroplane.
For the reason described above, this
[EASA] AD requires the identification and
replacement [or re-identifying] of struts that
have a certain target/sensor s/n combination
installed.
You may obtain further information
by examining the MCAI in the AD
docket.
Relevant Service Information
Airbus has issued Service Bulletin
A320–27–1206, Revision 01, dated
October 10, 2011. 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 note 1 of the EASA
Airworthiness Directive 2012–0012,
dated January 23, 2012, allows flight for
50 flight cycles after the inspection of
the flap down drive if an
interconnecting strut cannot be
replaced, this proposed AD does not
include this exception.
Costs of Compliance
We estimate that this proposed AD
affects 755 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
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ESTIMATED COSTS
Action
Labor cost
Inspection and Reidentification.
VerDate Mar<15>2010
8 work-hours × $85 per hour = $680 per inspection cycle.
$0 ...............................
Cost per
product
Parts cost
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$680 per inspection
cycle.
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25SEP1
Cost on U.S.
operators
$513,400 per inspection cycle.
Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules
We estimate the following costs to do
any necessary replacements that would
be required based on the results of the
proposed inspection. We have no way of
58977
determining the number of aircraft that
might need these replacements:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Replacement .....................................
10 work-hours × $85 per hour = $850 .........................................................
Authority for This Rulemaking
List of Subjects in 14 CFR Part 39
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
TKELLEY on DSK3SPTVN1PROD with PROPOSALS
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.
VerDate Mar<15>2010
16:14 Sep 24, 2013
Jkt 229001
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 AD:
■
Airbus: Docket No. FAA–2013–0791;
Directorate Identifier 2012–NM–026–AD.
(a) Comments Due Date
We must receive comments by November
12, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus Model A318–
111, –112, –121, and –122 airplanes; Model
A319–111, –112, –113, –114, –115, –131,
–132, and –133 airplanes; Model A320–111,
–211, –212, –214, –231, –232, and –233
airplanes; and Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes;
certificated in any category; all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight controls.
(e) Reason
This AD was prompted by a report that an
investigation showed that when a certain
combination of a target/proximity sensor
serial number is installed on a flap
interconnecting strut, a ‘‘target FAR’’ signal
cannot be detected when reaching the
mechanical end stop of the interconnecting
strut. We are issuing this AD to detect and
correct a latent failure of the flap down drive
disconnection due to an already-failed
interconnecting strut sensor, which could
result in asymmetric flap panel movement
and consequent loss of control of the
airplane.
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$0
Cost per
product
$850
(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) Inspection To Determine the Part Number
of the Interconnecting Struts
Within 8,000 flight hours after the effective
date of this AD, inspect to determine the part
number of the interconnecting struts
installed on both the left-hand (LH) and
right-hand (RH) wings of the airplane, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
27–1206, Revision 01, dated October 10,
2011. A review of the airplane maintenance
records is acceptable for determining the part
number of the installed interconnecting
struts, in lieu of the inspection, if the part
number of the installed interconnecting
struts, and the part number and the serial
number of the associated target and
proximity sensor, can be conclusively
determined from that review.
(1) Airplanes on which Airbus
modification 27956 has been embodied in
production, on which no interconnecting
strut having a part number specified in figure
1 to paragraph (g) of this AD, and has been
replaced since the airplane’s first flight: No
further work is required by paragraph (g) of
this AD.
(2) If, during the inspection required by
paragraph (g) of this AD, any interconnecting
strut is installed with a part number specified
in figure 1 to paragraph (g) of this AD: Within
8,000 flight hours after the effective date of
this AD, determine the part number and the
serial number of the associated target and
proximity sensor.
FIGURE 1 TO PARAGRAPH (G) OF THIS
AD—Interconnecting Strut Part
Numbers
Interconnecting strut part numbers
D5757030500000
D5757030500100
D5757030500200
D5757030500600
D5757030500800
D5757030501000
D5757030501200
D5757032200000
(i) For airplanes having conditions
specified in paragraphs (g)(2)(i)(A),
(g)(2)(i)(B), (g)(2)(i)(C), and (g)(2)(i)(D) of this
AD: Before further flight, replace the
interconnecting strut with a serviceable unit,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
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Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules
27–1206, Revision 01, dated October 10,
2011. For the purpose of this AD, a
serviceable interconnecting strut is a unit
which has been determined to be in
compliance with the requirements of this AD.
(A) A target part number (P/N) ABS0121–
13 or P/N 8–536–01, and
(B) A target serial number lower than 1600,
or a target serial number that is unreadable,
and
(C) A proximity sensor having P/N
ABS0121–31 or P/N 8–372–04, and
(D) A proximity sensor having a serial
number between C59198 and C59435, or a
serial number (S/N) C500000 or higher.
(ii) For a target having S/N 1600 or higher
and target P/N ABS0121–13 or P/N 8–536–
01: Within 8,000 flight hours after the
effective date of this AD, re-identify the
interconnecting strut, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–27–1206, Revision 01,
dated October 10, 2011.
of Design Authority (or their delegated
agent). You are required to assure the product
is airworthy before it is returned to service.
(h) Parts Installation Prohibition
As of the effective date of this AD, no
person may install an interconnecting strut
with a part number specified in figure 1 to
paragraph (g) of this AD, on any airplane,
except for parts identified in paragraph
(g)(2)(ii) of this AD, provided that the actions
in paragraph (g)(2)(ii) are done.
Issued in Renton, Washington, on
September 13, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
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(i) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using Airbus Service
Bulletin A320–27–1206, dated January 28,
2011, and if additional work has been
accomplished using Airbus Service Bulletin
A320–27–1206, Revision 01, dated October
10, 2011.
(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, 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, Washington 98057–
3356; telephone (425) 227–1405; fax (425)
227–1149. Information may be emailed to: 9ANM-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 a manufacturer or other source,
use these actions if they are FAA-approved.
Corrective actions are considered FAAapproved if they are approved by the State
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16:14 Sep 24, 2013
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(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2012–0012, dated
January 23, 2012, for related information,
which can be found in the AD docket on the
Internet at https://www.regulations.gov.
(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.
[FR Doc. 2013–23269 Filed 9–24–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0828; Directorate
Identifier 2012–NM–036–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
airworthiness directive (AD) 2009–15–
17, which applied to certain Airbus
Model A330–200 and –300; and Model
A340–200 and –300 series airplanes. AD
2009–15–17 required an inspection for
damage to the protective treatments or
any corrosion of all main landing gear
(MLG) bogie beams, and application of
protective treatments if no damage or
corrosion was found. If any damage or
corrosion was found, corrective action
followed by the application of
protective treatments was required.
Since we issued AD 2009–15–17, we
received reports of thin paint coats and
paint degradation on enhanced MLG
bogie beams. This proposed AD would
add repetitive detailed inspections of
the MLG bogie beams. This proposed
AD would also require modification of
the MLG bogie beams, which would
SUMMARY:
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terminate the repetitive inspections for
any modified bogie beam. This
proposed AD would also provide
optional methods of compliance for
inspections for corrosion, damage of the
protective treatment, repair, and
modification, of the MLG bogie beam.
This proposed AD would also revise the
applicability. We are proposing this AD
to detect and correct damage or
corrosion of the MLG bogie beams,
which could cause a runway excursion
event, bogie beam detachment from the
airplane, or MLG collapse, which could
result in damage to the airplane and
injury to the occupants.
DATES: We must receive comments on
this proposed AD by November 12,
2013.
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 Airbus 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. For Messier-Dowty
service information identified in this
AD, contact Messier-Dowty: Messier
Services Americas, Customer Support
Center, 45360 Severn Way, Sterling, VA
20166–8910; telephone 703–450–8233;
fax 703–404–1621; Internet https://
techpubs.services/messier-dowty.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.
ADDRESSES:
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
E:\FR\FM\25SEP1.SGM
25SEP1
]]>Agencies
[Federal Register Volume 78, Number 186 (Wednesday, September 25, 2013)]
[Proposed Rules]
[Pages 58975-58978]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-23269]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0791; Directorate Identifier 2012-NM-026-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 all
Airbus Model A318, A319, A320, and A321 series airplanes. This proposed
AD was prompted by a report that an investigation showed that when a
certain combination of a target/proximity sensor serial number is
installed on a flap interconnecting strut, a ``target FAR'' signal
cannot be detected when it reaches the mechanical end stop of the
interconnecting strut. This proposed AD would require an inspection to
determine the part number (P/N) of the interconnecting struts installed
on the wings, identifying the P/N and the serial number (S/N) of the
associated target and proximity sensor if applicable, and replacing or
re-identifying the flap interconnecting strut if applicable. We are
proposing
[[Page 58976]]
this AD to detect and correct a latent failure of the flap down drive
disconnection due to an already-failed interconnecting strut sensor,
which could result in asymmetric flap panel movement and consequent
loss of control of the airplane.
DATES: We must receive comments on this proposed AD by November 12,
2013.
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, 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-2013-0791;
Directorate Identifier 2012-NM-026-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 2012-0012, dated January 23, 2012 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
The flap interconnecting strut is a safety device of the High
Lift System which acts as an alternative load path from one flap
surface to another in case of a flap drive system disconnection. In
such a failure case, the installed proximity provide information to
the slat flap control computer (SFCC) and the operation of the flap
drive system is inhibited.
A recent engineering investigation has shown that, when a
certain combination of target/sensor serial number (s/n) is
installed on a flap interconnecting strut, a ``target FAR'' signal
cannot be detected when reaching the mechanical end stop of the
interconnecting strut.
This condition, if not corrected, could cause a flap down drive
disconnection to remain undetected, due to an already-failed
interconnecting strut sensor, potentially resulting in asymmetric
flap panel movement and consequent loss of control of the aeroplane.
For the reason described above, this [EASA] AD requires the
identification and replacement [or re-identifying] of struts that
have a certain target/sensor s/n combination installed.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Airbus has issued Service Bulletin A320-27-1206, Revision 01, dated
October 10, 2011. 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 note 1 of the EASA Airworthiness Directive 2012-0012,
dated January 23, 2012, allows flight for 50 flight cycles after the
inspection of the flap down drive if an interconnecting strut cannot be
replaced, this proposed AD does not include this exception.
Costs of Compliance
We estimate that this proposed AD affects 755 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection and Re- 8 work-hours x $85 per $0............... $680 per $513,400 per
identification. hour = $680 per inspection cycle. inspection
inspection cycle. cycle.
----------------------------------------------------------------------------------------------------------------
[[Page 58977]]
We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed inspection.
We have no way of determining the number of aircraft that might need
these replacements:
On-condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
---------------------------------------------------------------------------------------------------------------
Replacement.................................. 10 work-hours x $85 per hour = $850.. $0 $850
----------------------------------------------------------------------------------------------------------------
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
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 AD:
Airbus: Docket No. FAA-2013-0791; Directorate Identifier 2012-NM-
026-AD.
(a) Comments Due Date
We must receive comments by November 12, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus Model A318-111, -112, -121, and -
122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232,
and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes; certificated in any category; all
manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
controls.
(e) Reason
This AD was prompted by a report that an investigation showed
that when a certain combination of a target/proximity sensor serial
number is installed on a flap interconnecting strut, a ``target
FAR'' signal cannot be detected when reaching the mechanical end
stop of the interconnecting strut. We are issuing this AD to detect
and correct a latent failure of the flap down drive disconnection
due to an already-failed interconnecting strut sensor, which could
result in asymmetric flap panel movement and consequent loss of
control 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) Inspection To Determine the Part Number of the Interconnecting
Struts
Within 8,000 flight hours after the effective date of this AD,
inspect to determine the part number of the interconnecting struts
installed on both the left-hand (LH) and right-hand (RH) wings of
the airplane, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-27-1206, Revision 01, dated October 10,
2011. A review of the airplane maintenance records is acceptable for
determining the part number of the installed interconnecting struts,
in lieu of the inspection, if the part number of the installed
interconnecting struts, and the part number and the serial number of
the associated target and proximity sensor, can be conclusively
determined from that review.
(1) Airplanes on which Airbus modification 27956 has been
embodied in production, on which no interconnecting strut having a
part number specified in figure 1 to paragraph (g) of this AD, and
has been replaced since the airplane's first flight: No further work
is required by paragraph (g) of this AD.
(2) If, during the inspection required by paragraph (g) of this
AD, any interconnecting strut is installed with a part number
specified in figure 1 to paragraph (g) of this AD: Within 8,000
flight hours after the effective date of this AD, determine the part
number and the serial number of the associated target and proximity
sensor.
Figure 1 to Paragraph (g) of This AD--Interconnecting Strut Part Numbers
------------------------------------------------------------------------
Interconnecting strut part numbers
-------------------------------------------------------------------------
D5757030500000
D5757030500100
D5757030500200
D5757030500600
D5757030500800
D5757030501000
D5757030501200
D5757032200000
------------------------------------------------------------------------
(i) For airplanes having conditions specified in paragraphs
(g)(2)(i)(A), (g)(2)(i)(B), (g)(2)(i)(C), and (g)(2)(i)(D) of this
AD: Before further flight, replace the interconnecting strut with a
serviceable unit, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A320-
[[Page 58978]]
27-1206, Revision 01, dated October 10, 2011. For the purpose of
this AD, a serviceable interconnecting strut is a unit which has
been determined to be in compliance with the requirements of this
AD.
(A) A target part number (P/N) ABS0121-13 or P/N 8-536-01, and
(B) A target serial number lower than 1600, or a target serial
number that is unreadable, and
(C) A proximity sensor having P/N ABS0121-31 or P/N 8-372-04,
and
(D) A proximity sensor having a serial number between C59198 and
C59435, or a serial number (S/N) C500000 or higher.
(ii) For a target having S/N 1600 or higher and target P/N
ABS0121-13 or P/N 8-536-01: Within 8,000 flight hours after the
effective date of this AD, re-identify the interconnecting strut, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-27-1206, Revision 01, dated October 10, 2011.
(h) Parts Installation Prohibition
As of the effective date of this AD, no person may install an
interconnecting strut with a part number specified in figure 1 to
paragraph (g) of this AD, on any airplane, except for parts
identified in paragraph (g)(2)(ii) of this AD, provided that the
actions in paragraph (g)(2)(ii) are done.
(i) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Airbus Service Bulletin A320-27-
1206, dated January 28, 2011, and if additional work has been
accomplished using Airbus Service Bulletin A320-27-1206, Revision
01, dated October 10, 2011.
(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, 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, Washington 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 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.
(k) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2012-0012, dated January 23,
2012, for related information, which can be found in the AD docket
on the Internet at https://www.regulations.gov.
(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 13, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-23269 Filed 9-24-13; 8:45 am]
BILLING CODE 4910-13-P
