Airworthiness Directives; Airbus Model A310 Series Airplanes, 62653-62656 [2011-26106]
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Federal Register / Vol. 76, No. 196 / Tuesday, October 11, 2011 / Proposed Rules
Credit for Actions Accomplished in
Accordance with Previous Service
Information
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
(j) Replacements done before the effective
date of this AD in accordance with the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737–78–
1074, dated April 7, 2005, are acceptable for
compliance with the requirements of
paragraph (h) of this AD.
Alternative Methods of Compliance
(AMOCs)
(k)(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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 manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) 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.
Related Information
(l) For more information about this AD,
contact Chris Parker, Aerospace Engineer,
Propulsion Branch, ANM–140S, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; phone: 425–917–6496; fax: 425–917–
6590; e-mail: chris.r.parker@faa.gov.
(m) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P. O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.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.
Issued in Renton, Washington, on
September 30, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–26104 Filed 10–7–11; 8:45 am]
srobinson on DSK4SPTVN1PROD with PROPOSALS
BILLING CODE 4910–13–P
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14 CFR Part 39
[Docket No. FAA–2011–1060; Directorate
Identifier 2011–NM–015–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for the
products listed above that would
supersede an existing AD. This
proposed AD results from mandatory
continuing airworthiness information
(MCAI) originated by an aviation
authority of another country to identify
and correct an unsafe condition on an
aviation product. The MCAI describes
the unsafe condition as:
SUMMARY:
Within the scope of the Fuel System Safety
Program (FSSP), analyses of the wire routing
showed that the route 2S of the fuel electrical
circuit in the Right Hand (RH) wing must be
modified in order to ensure better segregation
between fuel quantity indication wires and
the 115 Volts Alternating Current (VAC)
wires of route 2S.
This condition, if not corrected, could
result in short circuits leading to arcing, and
possible fuel tank explosion.
*
*
*
*
*
The proposed AD would require actions
that are intended to address the unsafe
condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by November 25,
2011.
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 SAS–
EAW (Airworthiness Office), 1 Rond
Point Maurice Bellonte, 31707 Blagnac
ADDRESSES:
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
62653
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; e-mail:
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.
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: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2125; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2011–1060; Directorate Identifier
2011–NM–015–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 January 3, 2008, we issued AD
2008–01–05, Amendment 39–15330 (73
FR 2795, January 16, 2008). That AD
required actions intended to address an
unsafe condition on the products listed
above.
Since we issued AD 2008–01–05,
Amendment 39–15330 (73 FR 2795,
January 16, 2008), we have determined
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62654
Federal Register / Vol. 76, No. 196 / Tuesday, October 11, 2011 / Proposed Rules
that the route 2S of the fuel electrical
circuit in the right hand wing must be
modified to ensure better segregation
between fuel quantity indication wires
and the 115 volts alternating current
wires of route 2S. The European
Aviation Safety Agency (EASA), which
is the Technical Agent for the Member
States of the European Community, has
issued EASA Airworthiness Directive
2011–0005, dated January 17, 2011
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
Within the scope of the Fuel System Safety
Program (FSSP), analyses of the wire routing
showed that the route 2S of the fuel electrical
circuit in the Right Hand (RH) wing must be
modified in order to ensure better segregation
between fuel quantity indication wires and
the 115 Volts Alternating Current (VAC)
wires of route 2S.
This condition, if not corrected, could
result in short circuits leading to arcing, and
possible fuel tank explosion.
To address this unsafe condition,
´ ´
[Direction Generale de l’Aviation Civile]
DGAC France issued AD 2002–578(B) [which
corresponds to FAA AD 2004–15–16,
Amendment 39–13750 (69 FR 45578, July 30,
2004)] to require improvements of the design
as specified in Airbus Service Bulletin (SB)
A310–28–2148 original issue or Revision 01.
EASA AD 2007–0230 [which corresponds to
FAA AD 2008–01–05 (73 FR 2795, January
16, 2008)], which superseded DGAC France
AD 2002–578(B), required those same
actions, plus additional work as defined in
Airbus SB A310–28–2148 Revision 02.
Since EASA AD 2007–0230 was issued, an
operator reported the possibility of chafing
with the new routing of the wire bundle 2S
in the RH wing pylon area to the generator
wire bundle of engine 2. The modification of
this zone was introduced by A310–28–2148
Revision 02 as additional work. Investigation
showed that, to avoid the risk of chafing, the
affected wiring harnesses must be installed at
a higher position to provide sufficient
clearance with the newly routed wire bundle
2S conduit.
Airbus published Revision 03 of SB A310–
28–2148 to describe these changes, but a new
interference has been found and requires
updating SB A310–28–2148 to Revision 04
[or 05].
For the reasons described above, this new
[EASA] AD retains the requirements of EASA
AD 2007–0230, which is superseded, and
requires the additional work as specified in
Revision 04 [or 05] of Airbus SB A310–28–
2148.
Required actions include modifying the
wire routings and installing a modified
bracket. You may obtain further
information by examining the MCAI in
the AD docket.
Relevant Service Information
Airbus has issued Mandatory Service
Bulletin A310–28–2148, Revision 05,
dated August 3, 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
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have proposed
different actions in this AD from those
in the MCAI in order to follow FAA
policies. Any such differences are
highlighted in a NOTE within the
proposed AD.
Costs of Compliance
We estimate that this proposed AD
would affect 61 airplanes of U.S.
registry. The following table provides
the estimated costs for U.S. operators to
comply with this proposed AD.
TABLE—ESTIMATED COSTS
Work
hours
Action
srobinson on DSK4SPTVN1PROD with PROPOSALS
Modification (required by AD 2004–15–16, Amendment 39-13750
(69 FR 45578, July 30, 2004)) .......................................................
Modification (required by AD 2008–01–05, Amendment 39-15330
(73 FR 2795, January 16, 2008)) ..................................................
Modification (new proposed action) ...................................................
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
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Average
labor rate
per hour
Parts
$4,459
$7,434
68
$505,512
22
62
85
85
1,870
2,210
3,740
7,480
68
61
254,320
456,280
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
Fmt 4702
Fleet cost
$85
Regulatory Findings
Frm 00011
Number
of U.S.registered
airplanes
35
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.
PO 00000
Cost per
airplane
Sfmt 4702
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); and
3. 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.
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Federal Register / Vol. 76, No. 196 / Tuesday, October 11, 2011 / Proposed Rules
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
Restatement of Requirements of AD 2004–
15–16 Amendment 39–13750 (69 FR 45578,
July 30, 2004), With New Service
Information
List of Subjects in 14 CFR Part 39
Modification
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
removing Amendment 39–15330 (73 FR
2795, January 16, 2008) and adding the
following new AD:
Airbus: Docket No. FAA–2011–1060;
Directorate Identifier 2011–NM–015–AD.
Comments Due Date
(a) We must receive comments by
November 25, 2011.
Affected ADs
(b) This AD supersedes AD 2008–01–05,
Amendment 39–15330 (73 FR 2795, January
16, 2008).
Applicability
(c) This AD applies to Airbus Model A310–
203, –204, –221, –222, –304, –322, –324, and
–325 airplanes; certificated in any category;
all serial numbers.
Subject
(d) Air Transport Association (ATA) of
America Code 28: Fuel.
srobinson on DSK4SPTVN1PROD with PROPOSALS
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Within the scope of the Fuel System Safety
Program (FSSP), analyses of the wire routing
showed that the route 2S of the fuel electrical
circuit in the Right Hand (RH) wing must be
modified in order to ensure better segregation
between fuel quantity indication wires and
the 115 Volts Alternating Current (VAC)
wires of route 2S.
This condition, if not corrected, could
result in short circuits leading to arcing, and
possible fuel tank explosion.
*
*
*
*
*
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
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(g) For all airplanes except airplanes on
which Airbus Service Bulletin A310–28–
2148, Revision 02, dated March 9, 2007, has
been done (Airbus Modifications 12427 and
12435): Within 4,000 flight hours after
September 3, 2004 (the effective date of AD
2004–15–16 (69 FR 45578, July 30, 2004)),
modify the routing of wires in the RH wing
by installing cable sleeves, per the
Accomplishment Instructions of Airbus
Service Bulletin A310–28–2148, Revision 01,
dated October 29, 2002; Revision 02, dated
March 9, 2007; or Revision 05, dated August
3, 2010. As of February 20, 2008 (the
effective date of AD 2008–01–05,
Amendment 39–15330 (73 FR 2795, January
16, 2008)), Revision 02 must be used. As of
the effective date of this AD, Revision 05
must be used.
Actions Accomplished Previously
(h) Modification of the routing of wires
accomplished before September 3, 2004, per
Airbus Service Bulletin A310–28–2148,
dated January 23, 2002, is acceptable for
compliance with the corresponding
requirements of paragraph (g) of this AD.
62655
Service Bulletin A310–28–2148, Revision 05,
dated August 3, 2010.
(k) For airplanes on which the actions
specified in Airbus Service Bulletin A310–
28–2148, Revision 02, dated March 9, 2007,
have been accomplished, and have
production modification 07633 or on which
Airbus Service Bulletin A310–36–2015 has
been done: Within 1,000 flight hours after the
effective date of this AD, install a modified
bracket, in accordance with paragraph 3.B.(7)
‘‘Additional Work 2’’ of the Accomplishment
Instructions of Airbus Service Bulletin A310–
28–2148, Revision 05, dated August 3, 2010.
(l) For airplanes on which the actions
specified in Airbus Service Bulletin A310–
28–2148, Revision 03, dated June 2, 2009,
have been accomplished; and have
modification 07633 done in production or on
which the actions specified in Airbus Service
Bulletin A310–36–2015 have been done; no
further action is required by this AD.
Credit for Actions Accomplished in
Accordance With Previous Service
Information
(m) Modifications done in accordance with
Airbus Service Bulletin A310–28–2148,
Revision 04, dated April 14, 2010, before the
effective date of this AD are acceptable for
compliance with the corresponding
modification required by paragraph (g), (i),
(j), and (k) of this AD.
Restatement of Requirements of AD 2008–
01–05, Amendment 39–15330 (73 FR 2795,
January 16, 2008), With New Service
Information
FAA AD Differences
Modification (Additional Work)
(i) For airplanes on which the actions
specified in Airbus Service Bulletin A310–
28–2148, dated January 23, 2002; or Airbus
Service Bulletin A310–28–2148, Revision 01,
dated October 29, 2002; have been done
before February 20, 2008, except for airplanes
on which Airbus Service Bulletin A310–28–
2148, Revision 02, dated March 9, 2007, has
been done (Airbus Modifications 12427 and
12435): Within 6,000 flight hours or 30
months after February 20, 2008, whichever
occurs first, perform further modification by
installing additional protection sleeves in the
outer wing area near the cadensicon sensor
and segregating wire route 2S in the RH
pylon area, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A310–28–2148, Revision 02,
dated March 9, 2007; or Revision 05, dated
August 3, 2010. As of the effective date of
this AD, Revision 05 must be used.
Other FAA AD Provisions
(n) 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:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 227–2125; fax (425)
227–1149. Information may be e-mailed 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. AMOCs approved previously in
accordance with AD 2008–01–05,
Amendment 39–15330 (73 FR 2795, January
16, 2008), are approved as AMOCs for the
corresponding provisions of 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
New Requirements of This AD
Additional Modification/Installation for
Certain Airplanes
(j) For airplanes on which the actions
specified in Airbus Service Bulletin A310–
28–2148, Revision 02, dated March 9, 2007,
have been accomplished, and do not have
production modification 07633 and on which
Airbus Service Bulletin A310–36–2015 has
not been done: Within 6,000 flight hours or
30 months after the effective date of this AD,
whichever occurs first, modify the wire
routings, in accordance with the
Accomplishment Instructions of Airbus
PO 00000
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Note 1: This AD differs from the MCAI
and/or service information as follows: No
differences.
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Federal Register / Vol. 76, No. 196 / Tuesday, October 11, 2011 / Proposed Rules
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.
Related Information
(o) Refer to MCAI European Aviation
Safety Agency (EASA) Airworthiness
Directive 2011–0005, dated January 17, 2011;
and Airbus Service Bulletin A310–28–2148,
Revision 05, dated August 3, 2010; for related
information.
Issued in Renton, Washington, on
September 28, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–26106 Filed 10–7–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–1062; Directorate
Identifier 2011–NM–038–AD]
RIN 2120–AA64
Airworthiness Directives; Saab AB,
Saab Aerosystems Model 340A (SAAB/
SF340A) and SAAB 340B Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for the
products listed above that would
supersede an existing AD. This
proposed AD results from mandatory
continuing airworthiness information
(MCAI) originated by an aviation
authority of another country to identify
and correct an unsafe condition on an
aviation product. The MCAI describes
the unsafe condition as:
srobinson on DSK4SPTVN1PROD with PROPOSALS
SUMMARY:
In 2003, a number of reports had been
received concerning broken wires and
corroded connectors in the SAAB 340 main
landing gear (MLG) emergency release
system. The investigation results showed that
these were due to improper repairs and
installations, not conforming to the approved
type design.
This condition, if not corrected, could
inhibit the functioning of the separation bolt,
preventing proper release of the MLG during
an emergency situation, possibly resulting in
damage to aeroplane during landing and
injury to the occupants.
*
*
*
*
*
The proposed AD would require
actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by November 25,
2011.
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17:42 Oct 07, 2011
Jkt 223001
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 Saab AB,
Saab Aerosystems, SE–581 88,
¨
Linkoping, Sweden; telephone +46 13
18 5591; fax +46 13 18 4874; e-mail
saab2000.techsupport@saabgroup.com;
Internet https://www.saabgroup.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.
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
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:
Shahram Daneshmandi, Aerospace
Engineer, International Branch, ANM–
116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1112; 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–2011–1062; Directorate Identifier
2011–NM–038–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
PO 00000
Frm 00013
Fmt 4702
Sfmt 4702
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 May 28, 2004, we issued AD
2004–12–03, Amendment 39–13662 (69
FR 35235, June 24, 2004). That AD
required actions intended to address an
unsafe condition on the products listed
above.
Since we issued AD 2004–12–03,
Amendment 39–13662 (69 FR 35235,
June 24, 2004), we have received reports
that the previous modification does not
fully meet the expected results;
therefore, an improved separation bolt
harness having part number (P/N)
7292520–691 has been designed to
replace the current separation bolt
harness having P/N 7292520–678. The
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2011–0003,
dated January 17, 2011 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
In 2003, a number of reports had been
received concerning broken wires and
corroded connectors in the SAAB 340 main
landing gear (MLG) emergency release
system. The investigation results showed that
these were due to improper repairs and
installations, not conforming to the approved
type design.
This condition, if not corrected, could
inhibit the functioning of the separation bolt,
preventing proper release of the MLG during
an emergency situation, possibly resulting in
damage to aeroplane during landing and
injury to the occupants.
To address that unsafe condition, Swedish
AD (SAD) 1–186 was issued to require an
inspection and, depending on findings,
corrective action, in accordance with SAAB
Service Bulletin (SB) 340–32–127.
Subsequently, Saab introduced a
modification to ensure correct functioning of
the MLG emergency release system.
Accomplishment of that modification (SAAB
SB 340–32–128) was made mandatory by
SAD 1–189 [which corresponds to FAA AD
2004–12–03 (69 FR 35235, June 24, 2004)].
Since that [SAD] AD was issued, service
experience has shown that this modification
does not fully meet the expected results.
Prompted by these findings, SAAB has
developed an improved separation bolt
harness with a new routing.
For the reasons described above, this AD
requires replacement of the current
E:\FR\FM\11OCP1.SGM
11OCP1
]]>Agencies
[Federal Register Volume 76, Number 196 (Tuesday, October 11, 2011)]
[Proposed Rules]
[Pages 62653-62656]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-26106]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-1060; Directorate Identifier 2011-NM-015-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above that would supersede an existing AD. This
proposed AD results from mandatory continuing airworthiness information
(MCAI) originated by an aviation authority of another country to
identify and correct an unsafe condition on an aviation product. The
MCAI describes the unsafe condition as:
Within the scope of the Fuel System Safety Program (FSSP),
analyses of the wire routing showed that the route 2S of the fuel
electrical circuit in the Right Hand (RH) wing must be modified in
order to ensure better segregation between fuel quantity indication
wires and the 115 Volts Alternating Current (VAC) wires of route 2S.
This condition, if not corrected, could result in short circuits
leading to arcing, and possible fuel tank explosion.
* * * * *
The proposed AD would require actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by November 25,
2011.
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 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; e-mail: 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.
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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-1060;
Directorate Identifier 2011-NM-015-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 January 3, 2008, we issued AD 2008-01-05, Amendment 39-15330 (73
FR 2795, January 16, 2008). That AD required actions intended to
address an unsafe condition on the products listed above.
Since we issued AD 2008-01-05, Amendment 39-15330 (73 FR 2795,
January 16, 2008), we have determined
[[Page 62654]]
that the route 2S of the fuel electrical circuit in the right hand wing
must be modified to ensure better segregation between fuel quantity
indication wires and the 115 volts alternating current wires of route
2S. The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2011-0005, dated January 17, 2011 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
Within the scope of the Fuel System Safety Program (FSSP),
analyses of the wire routing showed that the route 2S of the fuel
electrical circuit in the Right Hand (RH) wing must be modified in
order to ensure better segregation between fuel quantity indication
wires and the 115 Volts Alternating Current (VAC) wires of route 2S.
This condition, if not corrected, could result in short circuits
leading to arcing, and possible fuel tank explosion.
To address this unsafe condition, [Direction
G[eacute]n[eacute]rale de l'Aviation Civile] DGAC France issued AD
2002-578(B) [which corresponds to FAA AD 2004-15-16, Amendment 39-
13750 (69 FR 45578, July 30, 2004)] to require improvements of the
design as specified in Airbus Service Bulletin (SB) A310-28-2148
original issue or Revision 01. EASA AD 2007-0230 [which corresponds
to FAA AD 2008-01-05 (73 FR 2795, January 16, 2008)], which
superseded DGAC France AD 2002-578(B), required those same actions,
plus additional work as defined in Airbus SB A310-28-2148 Revision
02.
Since EASA AD 2007-0230 was issued, an operator reported the
possibility of chafing with the new routing of the wire bundle 2S in
the RH wing pylon area to the generator wire bundle of engine 2. The
modification of this zone was introduced by A310-28-2148 Revision 02
as additional work. Investigation showed that, to avoid the risk of
chafing, the affected wiring harnesses must be installed at a higher
position to provide sufficient clearance with the newly routed wire
bundle 2S conduit.
Airbus published Revision 03 of SB A310-28-2148 to describe
these changes, but a new interference has been found and requires
updating SB A310-28-2148 to Revision 04 [or 05].
For the reasons described above, this new [EASA] AD retains the
requirements of EASA AD 2007-0230, which is superseded, and requires
the additional work as specified in Revision 04 [or 05] of Airbus SB
A310-28-2148.
Required actions include modifying the wire routings and installing a
modified bracket. You may obtain further information by examining the
MCAI in the AD docket.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A310-28-2148, Revision
05, dated August 3, 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
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the proposed AD.
Costs of Compliance
We estimate that this proposed AD would affect 61 airplanes of U.S.
registry. The following table provides the estimated costs for U.S.
operators to comply with this proposed AD.
Table--Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Work Average Cost per U.S.-
Action hours labor rate Parts airplane registered Fleet cost
per hour airplanes
----------------------------------------------------------------------------------------------------------------
Modification (required by AD 2004-15-16, 35 $85 $4,459 $7,434 68 $505,512
Amendment 39[dash]13750 (69 FR 45578, July
30, 2004))................................
Modification (required by AD 2008-01-05, 22 85 1,870 3,740 68 254,320
Amendment 39[dash]15330 (73 FR 2795,
January 16, 2008))........................
Modification (new proposed action)......... 62 85 2,210 7,480 61 456,280
----------------------------------------------------------------------------------------------------------------
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); and
3. 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.
[[Page 62655]]
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 Amendment 39-15330 (73 FR
2795, January 16, 2008) and adding the following new AD:
Airbus: Docket No. FAA-2011-1060; Directorate Identifier 2011-NM-
015-AD.
Comments Due Date
(a) We must receive comments by November 25, 2011.
Affected ADs
(b) This AD supersedes AD 2008-01-05, Amendment 39-15330 (73 FR
2795, January 16, 2008).
Applicability
(c) This AD applies to Airbus Model A310-203, -204, -221, -222,
-304, -322, -324, and -325 airplanes; certificated in any category;
all serial numbers.
Subject
(d) Air Transport Association (ATA) of America Code 28: Fuel.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Within the scope of the Fuel System Safety Program (FSSP),
analyses of the wire routing showed that the route 2S of the fuel
electrical circuit in the Right Hand (RH) wing must be modified in
order to ensure better segregation between fuel quantity indication
wires and the 115 Volts Alternating Current (VAC) wires of route 2S.
This condition, if not corrected, could result in short circuits
leading to arcing, and possible fuel tank explosion.
* * * * *
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2004-15-16 Amendment 39-13750 (69 FR
45578, July 30, 2004), With New Service Information
Modification
(g) For all airplanes except airplanes on which Airbus Service
Bulletin A310-28-2148, Revision 02, dated March 9, 2007, has been
done (Airbus Modifications 12427 and 12435): Within 4,000 flight
hours after September 3, 2004 (the effective date of AD 2004-15-16
(69 FR 45578, July 30, 2004)), modify the routing of wires in the RH
wing by installing cable sleeves, per the Accomplishment
Instructions of Airbus Service Bulletin A310-28-2148, Revision 01,
dated October 29, 2002; Revision 02, dated March 9, 2007; or
Revision 05, dated August 3, 2010. As of February 20, 2008 (the
effective date of AD 2008-01-05, Amendment 39-15330 (73 FR 2795,
January 16, 2008)), Revision 02 must be used. As of the effective
date of this AD, Revision 05 must be used.
Actions Accomplished Previously
(h) Modification of the routing of wires accomplished before
September 3, 2004, per Airbus Service Bulletin A310-28-2148, dated
January 23, 2002, is acceptable for compliance with the
corresponding requirements of paragraph (g) of this AD.
Restatement of Requirements of AD 2008-01-05, Amendment 39-15330 (73 FR
2795, January 16, 2008), With New Service Information
Modification (Additional Work)
(i) For airplanes on which the actions specified in Airbus
Service Bulletin A310-28-2148, dated January 23, 2002; or Airbus
Service Bulletin A310-28-2148, Revision 01, dated October 29, 2002;
have been done before February 20, 2008, except for airplanes on
which Airbus Service Bulletin A310-28-2148, Revision 02, dated March
9, 2007, has been done (Airbus Modifications 12427 and 12435):
Within 6,000 flight hours or 30 months after February 20, 2008,
whichever occurs first, perform further modification by installing
additional protection sleeves in the outer wing area near the
cadensicon sensor and segregating wire route 2S in the RH pylon
area, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A310-28-2148, Revision 02, dated March 9, 2007; or
Revision 05, dated August 3, 2010. As of the effective date of this
AD, Revision 05 must be used.
New Requirements of This AD
Additional Modification/Installation for Certain Airplanes
(j) For airplanes on which the actions specified in Airbus
Service Bulletin A310-28-2148, Revision 02, dated March 9, 2007,
have been accomplished, and do not have production modification
07633 and on which Airbus Service Bulletin A310-36-2015 has not been
done: Within 6,000 flight hours or 30 months after the effective
date of this AD, whichever occurs first, modify the wire routings,
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A310-28-2148, Revision 05, dated August 3, 2010.
(k) For airplanes on which the actions specified in Airbus
Service Bulletin A310-28-2148, Revision 02, dated March 9, 2007,
have been accomplished, and have production modification 07633 or on
which Airbus Service Bulletin A310-36-2015 has been done: Within
1,000 flight hours after the effective date of this AD, install a
modified bracket, in accordance with paragraph 3.B.(7) ``Additional
Work 2'' of the Accomplishment Instructions of Airbus Service
Bulletin A310-28-2148, Revision 05, dated August 3, 2010.
(l) For airplanes on which the actions specified in Airbus
Service Bulletin A310-28-2148, Revision 03, dated June 2, 2009, have
been accomplished; and have modification 07633 done in production or
on which the actions specified in Airbus Service Bulletin A310-36-
2015 have been done; no further action is required by this AD.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(m) Modifications done in accordance with Airbus Service
Bulletin A310-28-2148, Revision 04, dated April 14, 2010, before the
effective date of this AD are acceptable for compliance with the
corresponding modification required by paragraph (g), (i), (j), and
(k) of this AD.
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service
information as follows: No differences.
Other FAA AD Provisions
(n) 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: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425) 227-2125; fax (425) 227-1149.
Information may be e-mailed 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. AMOCs approved previously in accordance with AD 2008-01-05,
Amendment 39-15330 (73 FR 2795, January 16, 2008), are approved as
AMOCs for the corresponding provisions of 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
[[Page 62656]]
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.
Related Information
(o) Refer to MCAI European Aviation Safety Agency (EASA)
Airworthiness Directive 2011-0005, dated January 17, 2011; and
Airbus Service Bulletin A310-28-2148, Revision 05, dated August 3,
2010; for related information.
Issued in Renton, Washington, on September 28, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-26106 Filed 10-7-11; 8:45 am]
BILLING CODE 4910-13-P
