Airworthiness Directives; EADS CASA (Type Certificate Previously Held by Construcciones Aeronauticas, S.A.) Model CN-235, CN-235-100, CN-235-200, and CN-235-300 Airplanes, and Model C-295 Airplanes, 68185-68189 [2010-27615]
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68185
Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations
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.
Send information to ATTN: Tim Dulin,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone (425)
227–2141; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards 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.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(n) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive 2009–
0141, dated July 2, 2009, and the service
information identified in Table 2 of this AD,
for related information.
TABLE 2—AIRBUS SERVICE INFORMATION
Document
Revision/issue
Airbus All Operators Telex A320–55A1038 ...............................................................................
Airbus All Operators Telex A320–55A1038 ...............................................................................
Airbus Technical Disposition TD/K4/S2/27086/2009 .................................................................
Revision 01 .................
Revision 02 .................
Issue E .......................
Material Incorporated by Reference
(o) You must use the service information
contained in Table 3 of this AD to do the
Date
June 10, 2009.
September 28, 2009.
September 17, 2009.
actions required by this AD, unless the AD
specifies otherwise.
TABLE 3—MATERIAL INCORPORATED BY REFERENCE
Document
Revision/issue
Date
Airbus All Operators Telex A320–55A1038* .............................................................................
Airbus All Operators Telex A320–55A1038* .............................................................................
Airbus Technical Disposition TD/K4/S2/27086/2009 .................................................................
Revision 01 .................
Revision 02 .................
Issue E .......................
June 10, 2009.
September 28, 2009.
September 17, 2009.
(* The first page of these documents contain the document number, revision level, and date; no other pages contain this information.)
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(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(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; e-mail:
account.airworth-eas@airbus.com; Internet
https://www.airbus.com.
(3) You may review copies of the 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.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_
locations.html.
Issued in Renton, Washington, on October
26, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–27614 Filed 11–4–10; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Prompted by [an] accident * * *the FAA
published SFAR 88 (Special Federal Aviation
Regulation 88) * * *.
*
14 CFR Part 39
[Docket No. FAA–2010–0640; Directorate
Identifier 2009–NM–142–AD; Amendment
39–16494; AD 2010–23–05]
RIN 2120–AA64
Airworthiness Directives; EADS CASA
(Type Certificate Previously Held by
Construcciones Aeronauticas, S.A.)
Model CN–235, CN–235–100, CN–235–
200, and CN–235–300 Airplanes, and
Model C–295 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
the products listed above. This 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:
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*
*
*
*
Fuel Airworthiness Limitations arising
from the required systems safety analysis are
items that have been shown to have failure
mode(s) associated with an ‘unsafe condition’
* * *. These are identified in Failure
Conditions for which an unacceptable
probability of ignition risk could exist if
specific tasks and/or practices are not
performed in accordance with the corrective
actions(s) developed by the TC [type
certificate] holder.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
December 10, 2010.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of December 10, 2010.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
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Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations
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:
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Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on June 29, 2010 (75 FR 37339),
and proposed to supersede AD 2008–
09–22, Amendment 39–15503 (73 FR
23939, May 1, 2008). That NPRM
proposed to correct an unsafe condition
for the specified products. The MCAI
states:
Prompted by [an] accident * * *, the FAA
published SFAR 88 (Special Federal Aviation
Regulation 88). Subsequently, the Joint
Aviation Authorities (JAA) recommended the
application of a similar regulation to the
National Aviation Authorities (NAA) of its
member countries. Under this regulation, all
holders of type certificates for passenger
transport aeroplanes with either a passenger
capacity of 30 or more, or a payload capacity
of 3 402 kg (7 500 lbs) or more, which have
received their certification since 01 January
1958, are required to conduct a design review
against explosion risks.
In August 2005, EASA published a policy
statement on the process for developing
instructions for maintenance and inspection
of Fuel Tank System ignition source
prevention (EASA D 2005/CPRO), that also
included the EASA expectations with regard
to compliance times of the corrective actions
on the unsafe and the not unsafe part of the
harmonised design review results.
Fuel Airworthiness Limitations arising
from the required systems safety analysis are
items that have been shown to have failure
mode(s) associated with an ‘unsafe condition’
as defined in the FAA memo 2003–112–15
‘SFAR 88—Mandatory Action Decision
Criteria’. These are identified in Failure
Conditions for which an unacceptable
probability of ignition risk could exist if
specific tasks and/or practices are not
performed in accordance with the corrective
action(s) developed by the TC [type
certificate] holder.
To address these potential unsafe
conditions, EASA issued AD 2007–0007,
mandating the Fuel System Airworthiness
Limitations, comprising maintenance and
inspection tasks and Critical Design
Configuration Control Limitations (CDCCL)
that were, at that moment, defined in issue
C of EADS–CASA document DT–0–C00–
05001. That document has now been revised
and updated to issue D.
For the reasons described above, this EASA
AD retains the requirements of AD 2007–
0007, which is superseded [and corresponds
to FAA AD 2008–09–22], and requires the
implementation of the revised Fuel
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16:35 Nov 04, 2010
Jkt 223001
Airworthiness Limitations contained in issue
D of EADS–CASA document DT–0–C00–
05001 and accomplishment of related
modifications.
The required actions are retaining the
limitations for fuel tank systems, adding
thermal insulation to the air condition
compression system, applying double
bonding connection on fuel tubes, and
modifying the separation between the
center wing electrical harness and fuel
tubes. The application of double
bonding connections on fuel tubes
includes doing general visual
inspections for damage of the inside of
the fuel tanks, and corrective actions if
necessary. The corrective actions
include contacting EADS CASA for
repair instructions and doing the repair.
You may obtain further information by
examining the MCAI in the AD docket.
You may obtain further information
by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Corrections to Table 1 of This AD
In the NPRM, the reference to Eaton
Component Maintenance Manual
(CMM) with Illustrated Parts List 28–
10–63, Revision 003, dated June 20,
2006, was incorrectly published as
Eaton CMM with Illustrated Parts List
28–0–63. This final rule refers to Eaton
CMM with Illustrated Parts List 28–10–
63.
We have changed Table 1 of this AD
to fix a typographical error, which is
specified in EADS CASA CMM with
Illustrated Parts List 28–21–12, Revision
003, dated June 15, 2007. The title page
of that document specifies ‘‘Revision
002.’’ The correct revision level is
‘‘Revision 003.’’
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
We determined that these changes will
not increase the economic burden on
any operator or increase the scope of the
AD.
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.
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Frm 00018
Fmt 4700
Sfmt 4700
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 required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect
about 8 products of U.S. registry.
The actions that are required by AD
2008–09–22 and retained in this AD
take about 1 work-hour per product, at
an average labor rate of $85 per workhour. Based on these figures, the
estimated cost of the currently required
actions is $85 per product.
We estimate that it will take about 90
work-hours per product to comply with
the new basic requirements of this AD.
The average labor rate is $85 per workhour. Based on these figures, we
estimate the cost of this AD to the U.S.
operators to be $61,200, or $7,650 per
product, depending on airplane
configuration.
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 AD will not
have federalism implications under
Executive Order 13132. This AD will
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 AD:
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Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations
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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Effective Date
(a) This airworthiness directive (AD)
becomes effective December 10, 2010.
Examining the AD Docket
Subject
(d) Air Transport Association (ATA) of
America Code 28: Fuel.
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 the NPRM, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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 39–15503 (73 FR
23939, May 1, 2008) and adding the
following new AD:
■
2010–23–05 EADS CASA (Type Certificate
Previously Held by Construcciones
Aeronauticas, S.A.): Amendment 39–
16494. Docket No. FAA–2010–0640;
Directorate Identifier 2009–NM–142–AD.
Affected ADs
(b) This AD supersedes AD 2008–09–22,
Amendment 39–15503.
Applicability
(c) This AD applies to EADS CASA (Type
Certificate previously held by Construcciones
Aeronauticas, S.A.) Model CN–235, CN–235–
100, CN–235–200, and CN–235–300
airplanes, and Model C–295 airplanes, all
serial numbers; certificated in any category.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Prompted by [an] accident * * *, the FAA
published SFAR 88 (Special Federal Aviation
Regulation 88). Subsequently, the Joint
Aviation Authorities (JAA) recommended the
application of a similar regulation to the
National Aviation Authorities (NAA) of its
member countries. Under this regulation, all
holders of type certificates for passenger
transport aeroplanes with either a passenger
capacity of 30 or more, or a payload capacity
of 3 402 kg (7 500 lbs) or more, which have
received their certification since 01 January
1958, are required to conduct a design review
against explosion risks.
In August 2005, EASA [European Aviation
Safety Agency] published a policy statement
on the process for developing instructions for
maintenance and inspection of Fuel Tank
System ignition source prevention (EASA D
2005/CPRO), that also included the EASA
expectations with regard to compliance times
of the corrective actions on the unsafe and
the not unsafe part of the harmonised design
review results.
Fuel Airworthiness Limitations arising
from the required systems safety analysis are
items that have been shown to have failure
mode(s) associated with an ‘unsafe condition’
as defined in the FAA memo 2003–112–15
‘SFAR 88—Mandatory Action Decision
Criteria’. These are identified in Failure
Conditions for which an unacceptable
probability of ignition risk could exist if
specific tasks and/or practices are not
performed in accordance with the corrective
action(s) developed by the TC [type
certificate] holder.
To address these potential unsafe
conditions, EASA issued AD 2007–0007,
mandating the Fuel System Airworthiness
Limitations, comprising maintenance and
inspection tasks and Critical Design
Configuration Control Limitations (CDCCL)
that were, at that moment, defined in issue
C of EADS–CASA document DT–0–C00–
05001. That document has now been revised
and updated to issue D.
For the reasons described above, this EASA
AD retains the requirements of AD 2007–
0007, which is superseded [and corresponds
to FAA AD 2008–09–22], and requires the
implementation of the revised Fuel
Airworthiness Limitations contained in issue
D of EADS–CASA document DT–0–C00–
05001 and accomplishment of related
modifications.
The required actions are retaining the
limitations for fuel tank systems, adding
thermal insulation to the air condition
compression system, applying double
bonding connection on fuel tubes, and
modifying the separation between the center
wing electrical harness and fuel tubes. The
application of double bonding connections
on fuel tubes includes doing general visual
inspections for damage of the inside of the
fuel tanks, and corrective actions if
necessary. The corrective actions include
contacting EADS CASA for repair
instructions and doing the repair. You may
obtain further information by examining the
MCAI in the AD docket.
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 2008–
09–22, With Revised Paragraph Formatting
(g) Do the following actions.
(1) Within 6 months after June 5, 2008 (the
effective date of AD 2008–09–22), do the
revisions specified in (g)(1)(i) or (g)(1)(ii) of
this AD.
(i) Revise the Airworthiness Limitations
section of the Instructions for Continued
Airworthiness to include the CDCCL data
using a method approved in accordance with
the procedures specified in paragraph (i)(1)
of this AD.
(ii) Revise the Airworthiness Limitations
section of the Instructions for Continued
Airworthiness by incorporating the
information in EADS CASA CN–235/C–295
Technical Document DT–0–C00–05001, Issue
C, dated October 2006. Where this EADS
CASA technical document refers to an EADS
CASA component maintenance manual
(CMM), use the applicable CMM specified in
Table 1 of this AD.
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TABLE 1—APPLICABLE CMMS
CDCCL
number
CDCCL description
CMM
8 ....................
Fuel pumps ................................
8 ....................
Centrifugal fuel boost pump ......
9 ....................
Low level sensor ........................
10 ..................
3/4″ shutoff motorized valve ......
Parker Hannifin CMM with Illustrated Parts List 28–
22–12 (replaces CM 1C12–34).
Parker Hannifin CMM with Illustrated Parts List CM
1C7–20, –21 (replaces CMM RR54170).
EADS CASA CMM with Illustrated Parts List 28–21–
12.
Eaton CMM with Illustrated Parts List 28–20–81 .........
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Revision
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Date
5
January 10, 2008.
B
November 20, 2006.
003
June 15, 2007.
2
June 20, 2006.
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TABLE 1—APPLICABLE CMMS—Continued
CDCCL
number
CDCCL description
11 ..................
12 ..................
13 ..................
CMM
motorized spherical plug
pressure relief valve.
Signal conditioner ......................
Fuel control unit .........................
Eaton CMM with Illustrated Parts List 28–10–63 .........
3
June 20, 2006.
Gull CMM with Illustrated Parts List 28–40–61 ............
Zodiac Intertechnique CMM with Illustrated Parts List
28–41–05.
3
3
June 28, 2007.
September 25, 2006.
2″
Note 1: Table 1 of this AD does not include
CMMs 28–22–15, CE 400150–E01, and C
17MQ0020–005SE, which are listed in EADS
CASA CN–235/C–295 Technical Document
DT–0–C00–05001, Issue C, dated October
2006. These CMM document numbers no
longer apply. In addition, CMM document
number 28–21–81 in EADS CASA CN–235/
C–295 Technical Document DT–0–C00–
05001, Issue C, dated October 2006, should
be CMM document number 28–20–81.
(2) After accomplishing the actions
specified in paragraph (g)(1) of this AD, no
alternative CDCCLs may be used unless the
CDCCLs are approved as an alternative
method of compliance (AMOC) in
accordance with the procedures specified in
paragraph (i)(1) of this AD.
New Requirements of This AD
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(h) Do the following actions.
(1) Within 3 months after the effective date
of this AD, revise the Airworthiness
Limitations section of the Instructions for
Continued Airworthiness by incorporating
the information in EADS CASA CN–235/C–
295 Technical Document DT–0–C00–05001,
Issue D, dated October 2008. Where this
EADS CASA technical document refers to an
EADS CASA CMM, use the applicable CMM
specified in Table 1 of this AD. Doing this
revision terminates the requirements
specified in paragraph (g) of this AD.
Note 2: Notwithstanding any other
maintenance or operational requirements,
components that have been identified as
airworthy or installed on the affected
airplanes before the revision of the fuel
airworthiness limitations, as required by
paragraphs (g) and (h) of this AD, do not need
to be reworked in accordance with the
CDCCLs. However, once the fuel
airworthiness limitations have been revised,
future maintenance actions on these
components must be done in accordance
with the CDCCLs.
(2) After accomplishing the actions
specified in paragraph (h)(1) of this AD, no
alternative CDCCLs may be used unless the
CDCCLs are approved as an AMOC in
accordance with the procedures specified in
paragraph (i)(1) of this AD.
Revision
(3) Within 6 months after the effective date
of this AD, accomplish the modifications
specified in paragraphs (h)(3)(i), (h)(3)(ii),
and (h)(3)(iii) of this AD, as applicable.
(i) For Model CN–235, CN–235–200, and
CN–235–300 airplanes having serial numbers
identified in EADS CASA Service Bulletin
SB–235–21–18, dated August 2, 2007: Add
thermal insulation to the air condition
compression system, in accordance with the
Accomplishment Instructions of EADS CASA
Service Bulletin SB–235–21–18, dated
August 2, 2007.
(ii) For Model CN–235, CN–235–200, and
CN–235–300 airplanes having serial numbers
identified in EADS CASA Service Bulletin
SB–235–28–18, dated August 2, 2007: Apply
double bonding connections on fuel tubes
and do general visual inspections for damage
inside of the tank, in accordance with the
Accomplishment Instructions of EADS CASA
Service Bulletin SB–235–28–18, dated
August 2, 2007. If any damage is found inside
the tank, before further flight, contact EADS
CASA for repair instructions and do the
repair.
(iii) For Model CN–235, CN–235–200, and
CN–235–300 airplanes having serial numbers
identified in EADS CASA Service Bulletin
SB–235–24–20, dated August 2, 2007: Modify
the separation between the center wing
electrical harnesses and fuel tubes, in
accordance with the Accomplishment
Instructions of EADS CASA Service Bulletin
SB–235–24–20, dated August 2, 2007.
FAA AD Difference
Note 3: This AD differs from the MCAI
and/or service information as follows:
(1) The European Aviation Safety Agency
(EASA) AD 2009–0146, dated July 3, 2009,
inadvertently refers to the incorrect service
bulletins. For applying double bonding
connections on fuel tubes and doing general
visual inspections for damage inside the
tank, we refer to EADS CASA Service
Bulletin SB–235–28–18, dated August 2,
2007. For modifying the separation between
the center wing electrical harnesses and fuel
tubes, we refer to EADS CASA Service
Bulletin SB–235–24–20, dated August 2,
2007.
(2) The EASA AD 2009–0146, dated July 3,
2009; and EADS CASA Service Bulletin SB–
Date
235–28–18, dated August 2, 2007; do not
specify corrective actions if any damage is
found inside the tank. If any damage is found
inside the tank, this AD requires contacting
EADS CASA for repair instructions and
doing the repair.
Other FAA AD Provisions
(i) 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.
Send information to Attn: 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. Before using any approved AMOC
on any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards 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.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(j) Refer to MCAI EASA Airworthiness
Directive 2009–0146, dated July 3, 2009, the
CMMs identified in Table 1 of this AD, and
the service information identified in Table 2
of this AD, for related information.
TABLE 2—SERVICE INFORMATION
Document
EADS
EADS
EADS
EADS
CASA
CASA
CASA
CASA
VerDate Mar<15>2010
Issue
Service Bulletin SB–235–21–18 .....................................................................
Service Bulletin SB–235–24–20 .....................................................................
Service Bulletin SB–235–28–18 .....................................................................
CN–235/C–295 Technical Document DT-0-C00-05001 .................................
16:35 Nov 04, 2010
Jkt 223001
PO 00000
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Original
Original
Original
Issue C
.................................
.................................
.................................
.................................
E:\FR\FM\05NOR1.SGM
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Date
August 2, 2007.
August 2, 2007.
August 2, 2007.
October 2006.
68189
Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations
TABLE 2—SERVICE INFORMATION—Continued
Document
Issue
EADS CASA CN–235/C–295 Technical Document, DT–0–C00–05001 .............................
Issue D .................................
Material Incorporated by Reference
(k) You must use the service information
contained in Table 3 of this AD to do the
actions required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact EADS–CASA, Military
Transport Aircraft Division (MTAD),
Integrated Customer Services (ICS),
´
Technical Services, Avenida de Aragon 404,
28022 Madrid, Spain; telephone +34 91 585
55 84; fax +34 91 585 55 05; e-mail
MTA.TechnicalService@casa.eads.net;
Internet https://www.eads.net.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the
Date
October 2008.
availability of this material at the FAA, call
425–227–1221.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
TABLE 3—MATERIAL INCORPORATED BY REFERENCE
Revision/issue
Date
EADS CASA CMM with Illustrated Parts List 28–21–12 .....................................................
EADS CASA CN–235/C–295 Technical Document DT–0–C00–05001 ..............................
EADS CASA CN–235/C–295 Technical Document DT–0–C00–05001 ..............................
EADS CASA Service Bulletin SB–235–21–18 .....................................................................
EADS CASA Service Bulletin SB–235–24–20 .....................................................................
EADS CASA Service Bulletin SB–235–28–18 .....................................................................
Eaton CMM with Illustrated Parts List 28–10–63 .................................................................
Eaton CMM with Illustrated Parts List 28–20–81 .................................................................
Gull CMM with Illustrated Parts List 28–40–61 ....................................................................
Parker Hannifin CMM with Illustrated Parts List 28–22–12 .................................................
Parker Hannifin CMM with Illustrated Parts List CM 1C7–20, –21 .....................................
Zodiac Intertechnique CMM with Illustrated Parts List 28–41–05 .......................................
mstockstill on DSKH9S0YB1PROD with RULES
Document
Revision 003 .........................
Issue C .................................
Issue D .................................
Original .................................
Original .................................
Original .................................
Revision 3 .............................
Revision 2 .............................
Revision 3 .............................
Revision 5 .............................
Revision B ............................
Revision 3 .............................
June 15, 2007.
October 2006.
October 2008.
August 2, 2007.
August 2, 2007.
August 2, 2007.
June 20, 2006.
June 20, 2006.
June 28, 2007.
January 10, 2008.
November 20, 2006.
September 25, 2006.
(The title page of EADS CASA CMM with
Illustrated Parts List 28–21–12 contains an
incorrect revision level; the correct revision
level is 003. The issue date of EADS CASA
CN–235/C–295 Technical Document DT–0–
C00–05001, Issue C; and EADS CASA CN–
235/C–295 Technical Document DT–0–C00–
05001, Issue D; can only be found on the title
page and in the Revisions Record. Certain
pages of EADS CASA Service Bulletin SB–
235–28–18 have missing or incomplete
document numbers and dates; the correct
document number and dates for those pages
can be found on the first page of that
document. The date shown on the List of
Effective Pages for Eaton CMM with
Illustrated Parts List 28–10–63, and Eaton
CMM with Illustrated Parts List 28–20–81, is
incorrect; the correct date for that page of
those documents is June 20, 2006. The
revision level shown on page 7 of Parker
Hannifin CMM with Illustrated Parts List CM
1C7–20, –21 (replaces CMM RR54170), is
incorrect; the correct revision level for that
page is B. The revision level of EADS CASA
CN–235/C–295 Technical Document DT–0–
C00–05001, Issue C; EADS CASA CN–235/C–
295 Technical Document DT–0–C00–05001,
Issue D; and Eaton CMM with Illustrated
Parts List 28–20–81; is located only in the
Record of Revisions for those documents.)
VerDate Mar<15>2010
16:35 Nov 04, 2010
Jkt 223001
Issued in Renton, Washington, on October
20, 2010.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2010–27615 Filed 11–4–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 121
[Docket No. FAA–2009–0022; Amendment
No.: 121–350]
RIN 2120–AJ30
Crewmember Requirements When
Passengers are Onboard
assigned to the flight to substitute for a
flight attendant when that flight
attendant does not remain within the
immediate vicinity of the door through
which passengers are boarding. This
rule will also allow a reduction of flight
attendants remaining on board the
airplane during passenger deplaning, as
long as certain conditions are met. The
FAA has determined that these
revisions to current regulations can be
made as a result of recent safety
enhancements to airplane equipment
and procedures. These changes have
mitigated the risks to passengers during
ground operations that previously
required all flight attendants to be on
board the airplane during passenger
boarding and deplaning.
AGENCY:
These amendments become
effective January 4, 2011.
Currently, during passenger
boarding and deplaning, all flight
attendants are required to be on board
the airplane. This final rule will allow
one required flight attendant to deplane
during passenger boarding, to conduct
safety-related duties, as long as certain
conditions are met. In addition, this rule
will allow a pilot or flight engineer not
For
technical questions concerning this final
rule contact Nancy Lauck Claussen, Air
Transportation Division AFS–200,
Federal Aviation Administration, 800
Independence Avenue, SW.,
Washington, DC 20591; telephone (202)
267–8166; facsimile (202) 267–5229,
e-mail Nancy.L.Claussen@faa.gov. For
legal questions concerning this final
rule contact Paul G. Greer, Regulations
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY:
PO 00000
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FOR FURTHER INFORMATION CONTACT:
E:\FR\FM\05NOR1.SGM
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]]>Agencies
[Federal Register Volume 75, Number 214 (Friday, November 5, 2010)]
[Rules and Regulations]
[Pages 68185-68189]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-27615]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0640; Directorate Identifier 2009-NM-142-AD;
Amendment 39-16494; AD 2010-23-05]
RIN 2120-AA64
Airworthiness Directives; EADS CASA (Type Certificate Previously
Held by Construcciones Aeronauticas, S.A.) Model CN-235, CN-235-100,
CN-235-200, and CN-235-300 Airplanes, and Model C-295 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. This 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:
Prompted by [an] accident * * *the FAA published SFAR 88
(Special Federal Aviation Regulation 88) * * *.
* * * * *
Fuel Airworthiness Limitations arising from the required systems
safety analysis are items that have been shown to have failure
mode(s) associated with an `unsafe condition' * * *. These are
identified in Failure Conditions for which an unacceptable
probability of ignition risk could exist if specific tasks and/or
practices are not performed in accordance with the corrective
actions(s) developed by the TC [type certificate] holder.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective December 10, 2010.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of December 10,
2010.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
[[Page 68186]]
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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on June 29, 2010 (75 FR
37339), and proposed to supersede AD 2008-09-22, Amendment 39-15503 (73
FR 23939, May 1, 2008). That NPRM proposed to correct an unsafe
condition for the specified products. The MCAI states:
Prompted by [an] accident * * *, the FAA published SFAR 88
(Special Federal Aviation Regulation 88). Subsequently, the Joint
Aviation Authorities (JAA) recommended the application of a similar
regulation to the National Aviation Authorities (NAA) of its member
countries. Under this regulation, all holders of type certificates
for passenger transport aeroplanes with either a passenger capacity
of 30 or more, or a payload capacity of 3 402 kg (7 500 lbs) or
more, which have received their certification since 01 January 1958,
are required to conduct a design review against explosion risks.
In August 2005, EASA published a policy statement on the process
for developing instructions for maintenance and inspection of Fuel
Tank System ignition source prevention (EASA D 2005/CPRO), that also
included the EASA expectations with regard to compliance times of
the corrective actions on the unsafe and the not unsafe part of the
harmonised design review results.
Fuel Airworthiness Limitations arising from the required systems
safety analysis are items that have been shown to have failure
mode(s) associated with an `unsafe condition' as defined in the FAA
memo 2003-112-15 `SFAR 88--Mandatory Action Decision Criteria'.
These are identified in Failure Conditions for which an unacceptable
probability of ignition risk could exist if specific tasks and/or
practices are not performed in accordance with the corrective
action(s) developed by the TC [type certificate] holder.
To address these potential unsafe conditions, EASA issued AD
2007-0007, mandating the Fuel System Airworthiness Limitations,
comprising maintenance and inspection tasks and Critical Design
Configuration Control Limitations (CDCCL) that were, at that moment,
defined in issue C of EADS-CASA document DT-0-C00-05001. That
document has now been revised and updated to issue D.
For the reasons described above, this EASA AD retains the
requirements of AD 2007-0007, which is superseded [and corresponds
to FAA AD 2008-09-22], and requires the implementation of the
revised Fuel Airworthiness Limitations contained in issue D of EADS-
CASA document DT-0-C00-05001 and accomplishment of related
modifications.
The required actions are retaining the limitations for fuel tank
systems, adding thermal insulation to the air condition compression
system, applying double bonding connection on fuel tubes, and modifying
the separation between the center wing electrical harness and fuel
tubes. The application of double bonding connections on fuel tubes
includes doing general visual inspections for damage of the inside of
the fuel tanks, and corrective actions if necessary. The corrective
actions include contacting EADS CASA for repair instructions and doing
the repair. You may obtain further information by examining the MCAI in
the AD docket.
You may obtain further information by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Corrections to Table 1 of This AD
In the NPRM, the reference to Eaton Component Maintenance Manual
(CMM) with Illustrated Parts List 28-10-63, Revision 003, dated June
20, 2006, was incorrectly published as Eaton CMM with Illustrated Parts
List 28-0-63. This final rule refers to Eaton CMM with Illustrated
Parts List 28-10-63.
We have changed Table 1 of this AD to fix a typographical error,
which is specified in EADS CASA CMM with Illustrated Parts List 28-21-
12, Revision 003, dated June 15, 2007. The title page of that document
specifies ``Revision 002.'' The correct revision level is ``Revision
003.''
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
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 required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect about 8 products of U.S.
registry.
The actions that are required by AD 2008-09-22 and retained in this
AD take about 1 work-hour per product, at an average labor rate of $85
per work-hour. Based on these figures, the estimated cost of the
currently required actions is $85 per product.
We estimate that it will take about 90 work-hours per product to
comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this AD to the U.S. operators to be $61,200, or $7,650 per product,
depending on airplane configuration.
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 AD will not have federalism implications
under Executive Order 13132. This AD will 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 AD:
[[Page 68187]]
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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
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 the NPRM, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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 removing Amendment 39-15503 (73 FR
23939, May 1, 2008) and adding the following new AD:
2010-23-05 EADS CASA (Type Certificate Previously Held by
Construcciones Aeronauticas, S.A.): Amendment 39-16494. Docket No.
FAA-2010-0640; Directorate Identifier 2009-NM-142-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective December
10, 2010.
Affected ADs
(b) This AD supersedes AD 2008-09-22, Amendment 39-15503.
Applicability
(c) This AD applies to EADS CASA (Type Certificate previously
held by Construcciones Aeronauticas, S.A.) Model CN-235, CN-235-100,
CN-235-200, and CN-235-300 airplanes, and Model C-295 airplanes, all
serial numbers; certificated in any category.
Subject
(d) Air Transport Association (ATA) of America Code 28: Fuel.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Prompted by [an] accident * * *, the FAA published SFAR 88
(Special Federal Aviation Regulation 88). Subsequently, the Joint
Aviation Authorities (JAA) recommended the application of a similar
regulation to the National Aviation Authorities (NAA) of its member
countries. Under this regulation, all holders of type certificates
for passenger transport aeroplanes with either a passenger capacity
of 30 or more, or a payload capacity of 3 402 kg (7 500 lbs) or
more, which have received their certification since 01 January 1958,
are required to conduct a design review against explosion risks.
In August 2005, EASA [European Aviation Safety Agency] published
a policy statement on the process for developing instructions for
maintenance and inspection of Fuel Tank System ignition source
prevention (EASA D 2005/CPRO), that also included the EASA
expectations with regard to compliance times of the corrective
actions on the unsafe and the not unsafe part of the harmonised
design review results.
Fuel Airworthiness Limitations arising from the required systems
safety analysis are items that have been shown to have failure
mode(s) associated with an `unsafe condition' as defined in the FAA
memo 2003-112-15 `SFAR 88--Mandatory Action Decision Criteria'.
These are identified in Failure Conditions for which an unacceptable
probability of ignition risk could exist if specific tasks and/or
practices are not performed in accordance with the corrective
action(s) developed by the TC [type certificate] holder.
To address these potential unsafe conditions, EASA issued AD
2007-0007, mandating the Fuel System Airworthiness Limitations,
comprising maintenance and inspection tasks and Critical Design
Configuration Control Limitations (CDCCL) that were, at that moment,
defined in issue C of EADS-CASA document DT-0-C00-05001. That
document has now been revised and updated to issue D.
For the reasons described above, this EASA AD retains the
requirements of AD 2007-0007, which is superseded [and corresponds
to FAA AD 2008-09-22], and requires the implementation of the
revised Fuel Airworthiness Limitations contained in issue D of EADS-
CASA document DT-0-C00-05001 and accomplishment of related
modifications.
The required actions are retaining the limitations for fuel tank
systems, adding thermal insulation to the air condition compression
system, applying double bonding connection on fuel tubes, and
modifying the separation between the center wing electrical harness
and fuel tubes. The application of double bonding connections on
fuel tubes includes doing general visual inspections for damage of
the inside of the fuel tanks, and corrective actions if necessary.
The corrective actions include contacting EADS CASA for repair
instructions and doing the repair. You may obtain further
information by examining the MCAI in the AD docket.
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 2008-09-22, With Revised Paragraph
Formatting
(g) Do the following actions.
(1) Within 6 months after June 5, 2008 (the effective date of AD
2008-09-22), do the revisions specified in (g)(1)(i) or (g)(1)(ii)
of this AD.
(i) Revise the Airworthiness Limitations section of the
Instructions for Continued Airworthiness to include the CDCCL data
using a method approved in accordance with the procedures specified
in paragraph (i)(1) of this AD.
(ii) Revise the Airworthiness Limitations section of the
Instructions for Continued Airworthiness by incorporating the
information in EADS CASA CN-235/C-295 Technical Document DT-0-C00-
05001, Issue C, dated October 2006. Where this EADS CASA technical
document refers to an EADS CASA component maintenance manual (CMM),
use the applicable CMM specified in Table 1 of this AD.
Table 1--Applicable CMMs
----------------------------------------------------------------------------------------------------------------
CDCCL
CDCCL number description CMM Revision Date
----------------------------------------------------------------------------------------------------------------
8............................ Fuel pumps...... Parker Hannifin CMM 5 January 10, 2008.
with Illustrated
Parts List 28-22-12
(replaces CM 1C12-
34).
8............................ Centrifugal fuel Parker Hannifin CMM B November 20, 2006.
boost pump. with Illustrated
Parts List CM 1C7-
20, -21 (replaces
CMM RR54170).
9............................ Low level sensor EADS CASA CMM with 003 June 15, 2007.
Illustrated Parts
List 28-21-12.
10........................... 3/4'' shutoff Eaton CMM with 2 June 20, 2006.
motorized valve. Illustrated Parts
List 28-20-81.
[[Page 68188]]
11........................... 2'' motorized Eaton CMM with 3 June 20, 2006.
spherical plug Illustrated Parts
pressure relief List 28-10-63.
valve.
12........................... Signal Gull CMM with 3 June 28, 2007.
conditioner. Illustrated Parts
List 28-40-61.
13........................... Fuel control Zodiac Intertechnique 3 September 25, 2006.
unit. CMM with Illustrated
Parts List 28-41-05.
----------------------------------------------------------------------------------------------------------------
Note 1: Table 1 of this AD does not include CMMs 28-22-15, CE
400150-E01, and C 17MQ0020-005SE, which are listed in EADS CASA CN-
235/C-295 Technical Document DT-0-C00-05001, Issue C, dated October
2006. These CMM document numbers no longer apply. In addition, CMM
document number 28-21-81 in EADS CASA CN-235/C-295 Technical
Document DT-0-C00-05001, Issue C, dated October 2006, should be CMM
document number 28-20-81.
(2) After accomplishing the actions specified in paragraph
(g)(1) of this AD, no alternative CDCCLs may be used unless the
CDCCLs are approved as an alternative method of compliance (AMOC) in
accordance with the procedures specified in paragraph (i)(1) of this
AD.
New Requirements of This AD
(h) Do the following actions.
(1) Within 3 months after the effective date of this AD, revise
the Airworthiness Limitations section of the Instructions for
Continued Airworthiness by incorporating the information in EADS
CASA CN-235/C-295 Technical Document DT-0-C00-05001, Issue D, dated
October 2008. Where this EADS CASA technical document refers to an
EADS CASA CMM, use the applicable CMM specified in Table 1 of this
AD. Doing this revision terminates the requirements specified in
paragraph (g) of this AD.
Note 2: Notwithstanding any other maintenance or operational
requirements, components that have been identified as airworthy or
installed on the affected airplanes before the revision of the fuel
airworthiness limitations, as required by paragraphs (g) and (h) of
this AD, do not need to be reworked in accordance with the CDCCLs.
However, once the fuel airworthiness limitations have been revised,
future maintenance actions on these components must be done in
accordance with the CDCCLs.
(2) After accomplishing the actions specified in paragraph
(h)(1) of this AD, no alternative CDCCLs may be used unless the
CDCCLs are approved as an AMOC in accordance with the procedures
specified in paragraph (i)(1) of this AD.
(3) Within 6 months after the effective date of this AD,
accomplish the modifications specified in paragraphs (h)(3)(i),
(h)(3)(ii), and (h)(3)(iii) of this AD, as applicable.
(i) For Model CN-235, CN-235-200, and CN-235-300 airplanes
having serial numbers identified in EADS CASA Service Bulletin SB-
235-21-18, dated August 2, 2007: Add thermal insulation to the air
condition compression system, in accordance with the Accomplishment
Instructions of EADS CASA Service Bulletin SB-235-21-18, dated
August 2, 2007.
(ii) For Model CN-235, CN-235-200, and CN-235-300 airplanes
having serial numbers identified in EADS CASA Service Bulletin SB-
235-28-18, dated August 2, 2007: Apply double bonding connections on
fuel tubes and do general visual inspections for damage inside of
the tank, in accordance with the Accomplishment Instructions of EADS
CASA Service Bulletin SB-235-28-18, dated August 2, 2007. If any
damage is found inside the tank, before further flight, contact EADS
CASA for repair instructions and do the repair.
(iii) For Model CN-235, CN-235-200, and CN-235-300 airplanes
having serial numbers identified in EADS CASA Service Bulletin SB-
235-24-20, dated August 2, 2007: Modify the separation between the
center wing electrical harnesses and fuel tubes, in accordance with
the Accomplishment Instructions of EADS CASA Service Bulletin SB-
235-24-20, dated August 2, 2007.
FAA AD Difference
Note 3: This AD differs from the MCAI and/or service information
as follows:
(1) The European Aviation Safety Agency (EASA) AD 2009-0146,
dated July 3, 2009, inadvertently refers to the incorrect service
bulletins. For applying double bonding connections on fuel tubes and
doing general visual inspections for damage inside the tank, we
refer to EADS CASA Service Bulletin SB-235-28-18, dated August 2,
2007. For modifying the separation between the center wing
electrical harnesses and fuel tubes, we refer to EADS CASA Service
Bulletin SB-235-24-20, dated August 2, 2007.
(2) The EASA AD 2009-0146, dated July 3, 2009; and EADS CASA
Service Bulletin SB-235-28-18, dated August 2, 2007; do not specify
corrective actions if any damage is found inside the tank. If any
damage is found inside the tank, this AD requires contacting EADS
CASA for repair instructions and doing the repair.
Other FAA AD Provisions
(i) 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. Send information to Attn: 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. Before using any
approved AMOC on any airplane to which the AMOC applies, notify your
principal maintenance inspector (PMI) or principal avionics
inspector (PAI), as appropriate, or lacking a principal inspector,
your local Flight Standards 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.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(j) Refer to MCAI EASA Airworthiness Directive 2009-0146, dated
July 3, 2009, the CMMs identified in Table 1 of this AD, and the
service information identified in Table 2 of this AD, for related
information.
Table 2--Service Information
----------------------------------------------------------------------------------------------------------------
Document Issue Date
----------------------------------------------------------------------------------------------------------------
EADS CASA Service Bulletin SB-235-21-18.... Original................... August 2, 2007.
EADS CASA Service Bulletin SB-235-24-20.... Original................... August 2, 2007.
EADS CASA Service Bulletin SB-235-28-18.... Original................... August 2, 2007.
EADS CASA CN-235/C-295 Technical Document Issue C.................... October 2006.
DT[dash]0[dash]C00[dash]05001.
[[Page 68189]]
EADS CASA CN-235/C-295 Technical Document, Issue D.................... October 2008.
DT-0-C00-05001.
----------------------------------------------------------------------------------------------------------------
Material Incorporated by Reference
(k) You must use the service information contained in Table 3 of
this AD to do the actions required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact EADS-
CASA, Military Transport Aircraft Division (MTAD), Integrated
Customer Services (ICS), Technical Services, Avenida de
Arag[oacute]n 404, 28022 Madrid, Spain; telephone +34 91 585 55 84;
fax +34 91 585 55 05; e-mail MTA.TechnicalService@casa.eads.net;
Internet https://www.eads.net.
(3) You may review copies of the 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.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Table 3--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision/issue Date
----------------------------------------------------------------------------------------------------------------
EADS CASA CMM with Illustrated Parts List Revision 003............... June 15, 2007.
28-21-12.
EADS CASA CN-235/C-295 Technical Document Issue C.................... October 2006.
DT-0-C00-05001.
EADS CASA CN-235/C-295 Technical Document Issue D.................... October 2008.
DT-0-C00-05001.
EADS CASA Service Bulletin SB-235-21-18.... Original................... August 2, 2007.
EADS CASA Service Bulletin SB-235-24-20.... Original................... August 2, 2007.
EADS CASA Service Bulletin SB-235-28-18.... Original................... August 2, 2007.
Eaton CMM with Illustrated Parts List 28-10- Revision 3................. June 20, 2006.
63.
Eaton CMM with Illustrated Parts List 28-20- Revision 2................. June 20, 2006.
81.
Gull CMM with Illustrated Parts List 28-40- Revision 3................. June 28, 2007.
61.
Parker Hannifin CMM with Illustrated Parts Revision 5................. January 10, 2008.
List 28-22-12.
Parker Hannifin CMM with Illustrated Parts Revision B................. November 20, 2006.
List CM 1C7-20, -21.
Zodiac Intertechnique CMM with Illustrated Revision 3................. September 25, 2006.
Parts List 28-41-05.
----------------------------------------------------------------------------------------------------------------
(The title page of EADS CASA CMM with Illustrated Parts List 28-
21-12 contains an incorrect revision level; the correct revision
level is 003. The issue date of EADS CASA CN-235/C-295 Technical
Document DT-0-C00-05001, Issue C; and EADS CASA CN-235/C-295
Technical Document DT-0-C00-05001, Issue D; can only be found on the
title page and in the Revisions Record. Certain pages of EADS CASA
Service Bulletin SB-235-28-18 have missing or incomplete document
numbers and dates; the correct document number and dates for those
pages can be found on the first page of that document. The date
shown on the List of Effective Pages for Eaton CMM with Illustrated
Parts List 28-10-63, and Eaton CMM with Illustrated Parts List 28-
20-81, is incorrect; the correct date for that page of those
documents is June 20, 2006. The revision level shown on page 7 of
Parker Hannifin CMM with Illustrated Parts List CM 1C7-20, -21
(replaces CMM RR54170), is incorrect; the correct revision level for
that page is B. The revision level of EADS CASA CN-235/C-295
Technical Document DT-0-C00-05001, Issue C; EADS CASA CN-235/C-295
Technical Document DT-0-C00-05001, Issue D; and Eaton CMM with
Illustrated Parts List 28-20-81; is located only in the Record of
Revisions for those documents.)
Issued in Renton, Washington, on October 20, 2010.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-27615 Filed 11-4-10; 8:45 am]
BILLING CODE 4910-13-P
