Airworthiness Directives; REIMS AVIATION S.A. Model F406 Airplanes, 3854-3856 [2011-1221]
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<![CDATA[
3854
Proposed Rules
Federal Register
Vol. 76, No. 14
Friday, January 21, 2011
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0058; Directorate
Identifier 2010–CE–071–AD]
RIN 2120–AA64
Airworthiness Directives; REIMS
AVIATION S.A. Model F406 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (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:
WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS
In early 2005, several reports had been
received regarding discovery of cracks in
rudder pulley brackets installed on Reims
F406 aeroplanes. This pulley bracket, Part
Number (P/N) 6015511–1, is installed on
aeroplanes with the optional ‘‘Camera Hole’’
modification.
This condition, if not detected and
corrected, could result in the loss of rudder
control on the airplane.
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 March 7, 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,
VerDate Mar<15>2010
12:47 Jan 20, 2011
Jkt 223001
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 20590,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Reims
´
Aviation Industries, Aerodrome de
Reims Prunay, 51360 Prunay, France;
telephone + 33 3 26 48 46 65; fax + 33
3 26 49 18 57; e-mail Jn.sirot@reimsaviation.fr. You may review copies of
the referenced service information at the
FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106.
For information on the availability of
this material at the FAA, call 816–329–
4148.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket 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:
Albert Mercado, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4119; fax: (816) 329–4090.
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–2011–0058; Directorate Identifier
2010–CE–071–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 because of those
comments.
PO 00000
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Fmt 4702
Sfmt 4702
We will post all comments we
receive, without change, to https://
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 12, 2007, we issued AD
2007–02–12, Amendment 39–14899 (72
FR 3047; January 24, 2007). That AD
required actions intended to address an
unsafe condition on the products listed
above.
Since we issued AD 2007–02–12,
REIMS AVIATION S.A. discovered that
airplane serial number (SN) F406–0091
had inadvertently not been included in
the service information and has revised
the service information to correct the
omission.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued AD No.: 2010–
0230, dated November 5, 2010 (referred
to after this as ‘‘the MCAI’’), to correct
an unsafe condition for the specified
products. The MCAI states:
In early 2005, several reports had been
received regarding discovery of cracks in
rudder pulley brackets installed on Reims
F406 aeroplanes. This pulley bracket, Part
Number (P/N) 6015511–1, is installed on
aeroplanes with the optional ‘‘Camera Hole’’
modification.
This condition, if not detected and
corrected, could result in the loss of rudder
control on the airplane.
To address this unsafe condition, DGAC
France issued Emergency (Urgent) AD UF–
2005–080, followed by the final AD F–2005–
080, requiring repetitive inspections of the
P/N 6015511–1 rudder pulley bracket and
replacement of the bracket with a modified
bracket, P/N 4061–2701–1, as terminating
action.
Recently, Reims discovered that aeroplane
s/n F406–0091 had inadvertently not been
included in the SB and this has been revised
to correct the omission.
For the reasons described above, this AD
retains the requirements of DGAC France AD
F–2005–080, which is superseded, and adds
aeroplane s/n F406–0091 to the Applicability
of the AD, by referencing Revision 2 of the
Reims Aviation Industries SB F406–58.
You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Reims Aviation S.A. has issued Reims
Aviation Industries Service Bulletin No.
F406–58, REV 1, dated October 27,
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2006; and Reims Aviation Industries
Service Bulletin No. F406–58, REV 2,
dated July 27, 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 the 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 this State of
Design Authority, they have notified us
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This Proposed 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
WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS
We estimate that this proposed AD
will affect 7 products of U.S. registry.
We also estimate that it would take
about 11 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Required
parts would cost about $750 per
product.
Based on these figures, we estimate
the cost of the proposed AD on U.S.
operators to be $11,795, or $1,685 per
product.
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.
12:47 Jan 20, 2011
Jkt 223001
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.
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.
Authority for This Rulemaking
VerDate Mar<15>2010
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–14899 (72 FR
3047; January 24, 2007), and adding the
following new AD:
Reims Aviation S.A.: Docket No. FAA–2011–
0058; Directorate Identifier 2010–CE–
071–AD.
PO 00000
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3855
Comments Due Date
(a) We must receive comments by March 7,
2011.
Affected ADs
(b) This AD supersedes AD 2007–02–12,
Amendment 39–14899.
Applicability
(c) This AD applies to Reims Aviation S.A.
Model F406 airplanes, serial numbers (SNs)
0002, 0003, 0004, 0006, 0008, 0009, 0010,
0012, 0013, 0017, 0024, 0025, 0039, 0042,
0044, 0045, 0066, 0070, 0073, 0074, 0075,
0077, 0080 through 0092, certificated in any
category.
Subject
(d) Air Transport Association of America
(ATA) Code 27: Flight Controls.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
In early 2005, several reports had been
received regarding discovery of cracks in
rudder pulley brackets installed on Reims
F406 aeroplanes. This pulley bracket, Part
Number (P/N) 6015511–1, is installed on
aeroplanes with the optional ‘‘Camera Hole’’
modification.
This condition, if not detected and
corrected, could result in the loss of rudder
control on the airplane.
To address this unsafe condition, DGAC
France issued Emergency (Urgent) AD UF–
2005–080, followed by the final AD F–2005–
080, requiring repetitive inspections of the
P/N 6015511–1 rudder pulley bracket and
replacement of the bracket with a modified
bracket, P/N 4061–2701–1, as terminating
action.
Recently, Reims discovered that aeroplane
s/n F406–0091 had inadvertently not been
included in the SB and this has been revised
to correct the omission.
For the reasons described above, this AD
retains the requirements of DGAC France AD
F–2005–080, which is superseded, and adds
aeroplane s/n F406–0091 to the Applicability
of the AD, by referencing Revision 2 of the
Reims Aviation Industries SB F406–58.
Actions and Compliance
(f) Unless already done, do the following
actions:
(1) For all affected SNs except F406–0091:
(i) Within the next 10 hours time-in-service
(TIS) after February 13, 2007 (the effective
date retained from AD 2007–02–12), perform
the initial inspection as specified in Reims
Aviation Industries Service Bulletin No.
F406–58, REV 1, dated October 27, 2006; or
Reims Aviation Industries Service Bulletin
No. F406–58, REV 2, dated July 27, 2010.
(ii) If no cracking is found following the
initial inspection required in paragraph
(f)(1)(i) of this AD, repetitively thereafter
inspect every 50 hours TIS or 1 month,
whichever occurs first, until the installation
of the modified pulley bracket specified in
paragraphs (f)(1)(iii) or (f)(1)(iv) of this AD is
done.
(iii) If any cracking is found during the
inspection required in paragraph (f)(1)(i) of
this AD, before further flight, install the
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WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS
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Federal Register / Vol. 76, No. 14 / Friday, January 21, 2011 / Proposed Rules
modified pulley bracket as specified in Reims
Aviation Industries Service Bulletin No.
F406–58, REV 1, dated October 27, 2006; or
Reims Aviation Industries Service Bulletin
No. F406–58, REV 2, dated July 27, 2010.
This installation terminates the repetitive
inspections required in paragraph (f)(1)(ii) of
this AD.
(iv) Within the next 100 hours TIS or 2
months after February 13, 2007 (the effective
date retained from AD 2007–02–12),
whichever occurs first, install the modified
pulley bracket as specified in Reims Aviation
Industries Service Bulletin No. F406–58, REV
1, dated October 27, 2006; or Reims Aviation
Industries Service Bulletin No. F406–58, REV
2, dated July 27, 2010. This installation
terminates the repetitive inspections required
in paragraph (f)(1)(ii) of this AD.
(v) The modified pulley bracket specified
in Reims Aviation Industries Service Bulletin
No. F406–58, REV 1, dated October 27, 2006;
or Reims Aviation Industries Service Bulletin
No. F406–58, REV 2, dated July 27, 2010,
may be installed at any time after the
inspection required in paragraph (f)(1)(i) of
this AD, as long as no cracking is found, but
no later than the compliance time specified
in paragraph (f)(1)(iv) of this AD. If cracking
is found, it must be replaced before further
flight as required in paragraph (f)(1)(iii) of
this AD.
(2) For serial number F406–0091:
(i) Within the next 10 hours TIS after the
effective of this AD, perform the initial
inspection as specified in Reims Aviation
Industries Service Bulletin No. F406–58, REV
2, dated July 27, 2010.
(ii) If no cracking is found following the
initial inspection required in paragraph
(f)(2)(i) of this AD, repetitively thereafter
inspect every 50 hours TIS or 1 month,
whichever occurs first, until the installation
of the modified pulley bracket specified in
paragraphs (f)(2)(iii) and (f)(2)(iv) of this AD
is done.
(iii) If any cracking is found during the
inspection required in paragraph (f)(2)(i) of
this AD, before further flight, install the
modified pulley bracket as specified in Reims
Aviation Industries Service Bulletin No.
F406–58, REV 2, dated July 27, 2010. This
installation terminates the repetitive
inspections required in paragraph (f)(2)(ii) of
this AD.
(iv) Within the next 100 hours TIS or 2
months after the effective of this AD,
whichever occurs first, install the modified
pulley bracket as specified in Reims Aviation
Industries Service Bulletin No. F406–58, REV
2, dated July 27, 2010. This installation
terminates the repetitive inspections required
in paragraph (f)(2)(ii) of this AD.
(v) The modified pulley bracket specified
in Reims Aviation Industries Service Bulletin
No. F406–58, REV 2, dated July 27, 2010,
may be installed at any time after the
inspection required in paragraph (f)(2)(i) of
this AD as long as no cracking is found, but
no later than the compliance time specified
in paragraph (f)(2)(iv) of this AD. If cracking
is found, it must be replaced before further
flight as required in paragraph (f)(2)(iii) of
this AD.
VerDate Mar<15>2010
12:47 Jan 20, 2011
Jkt 223001
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
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: Albert Mercado, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4119; fax: (816) 329–
4090. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(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, a federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave., SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
Related Information
(h) Refer to MCAI European Aviation
Safety Agency (EASA) AD 2010–0230, dated
November 5, 2010; Reims Aviation Industries
Service Bulletin No. F406–58, REV 1, dated
October 27, 2006; and Reims Aviation
Industries Service Bulletin No. F406–58, REV
2, dated July 27, 2010, for related
information. For service information related
to this AD, contact Reims Aviation
´
Industries, Aerodrome de Reims Prunay,
51360 Prunay, France; telephone + 33 3 26
48 46 65; fax + 33 3 26 49 18 57; e-mail
Jn.sirot@reims-aviation.fr. You may review
copies of the referenced service information
at the FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call 816–329–4148.
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
Issued in Kansas City, Missouri, on January
14, 2011.
John Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–1221 Filed 1–20–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0028; Directorate
Identifier 2009–NM–228–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Model 737–100, –200, –200C, –300,
–400, and –500 series airplanes. This
proposed AD would result in all
airplanes having new relays with a
ground fault interrupter (GFI) feature.
This proposed AD would require,
depending on airplane configuration,
doing certain wiring changes, replacing
the fuel pump power control relays for
the main, center and auxiliary tanks, as
applicable, with new relays having a
GFI feature, performing certain bonding
resistance measurements, and
modifying relay module assemblies. The
proposed AD also would require
revising the maintenance program to
incorporate Airworthiness Limitations
(AWLs) 28–AWL–23 (for Model 737–
100, 737–200, and 737–200C series
airplanes), and 28–AWL–22 (for Model
737–300, 737–400, and 737–500 series
airplanes). This proposed AD results
from fuel system reviews conducted by
the manufacturer. We are proposing this
AD to prevent damage to the fuel pumps
caused by electrical arcing that could
introduce an ignition source in the fuel
tank, which, in combination with
flammable fuel vapors, could result in a
fuel tank explosion and consequent loss
of the airplane.
DATES: We must receive comments on
this proposed AD by March 7, 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.
SUMMARY:
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]]>Agencies
[Federal Register Volume 76, Number 14 (Friday, January 21, 2011)]
[Proposed Rules]
[Pages 3854-3856]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-1221]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 76, No. 14 / Friday, January 21, 2011 /
Proposed Rules
[[Page 3854]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0058; Directorate Identifier 2010-CE-071-AD]
RIN 2120-AA64
Airworthiness Directives; REIMS AVIATION S.A. Model F406
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (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:
In early 2005, several reports had been received regarding
discovery of cracks in rudder pulley brackets installed on Reims
F406 aeroplanes. This pulley bracket, Part Number (P/N) 6015511-1,
is installed on aeroplanes with the optional ``Camera Hole''
modification.
This condition, if not detected and corrected, could result in
the loss of rudder control on the airplane.
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 March 7, 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 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Reims Aviation Industries, A[eacute]rodrome de Reims Prunay, 51360
Prunay, France; telephone + 33 3 26 48 46 65; fax + 33 3 26 49 18 57;
e-mail Jn.sirot@reims-aviation.fr. You may review copies of the
referenced service information at the FAA, Small Airplane Directorate,
901 Locust, Kansas City, Missouri 64106. For information on the
availability of this material at the FAA, call 816-329-4148.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket 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: Albert Mercado, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090.
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-2011-0058;
Directorate Identifier 2010-CE-071-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 because of those comments.
We will post all comments we receive, without change, to https://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 12, 2007, we issued AD 2007-02-12, Amendment 39-14899
(72 FR 3047; January 24, 2007). That AD required actions intended to
address an unsafe condition on the products listed above.
Since we issued AD 2007-02-12, REIMS AVIATION S.A. discovered that
airplane serial number (SN) F406-0091 had inadvertently not been
included in the service information and has revised the service
information to correct the omission.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued AD
No.: 2010-0230, dated November 5, 2010 (referred to after this as ``the
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:
In early 2005, several reports had been received regarding
discovery of cracks in rudder pulley brackets installed on Reims
F406 aeroplanes. This pulley bracket, Part Number (P/N) 6015511-1,
is installed on aeroplanes with the optional ``Camera Hole''
modification.
This condition, if not detected and corrected, could result in
the loss of rudder control on the airplane.
To address this unsafe condition, DGAC France issued Emergency
(Urgent) AD UF-2005-080, followed by the final AD F-2005-080,
requiring repetitive inspections of the P/N 6015511-1 rudder pulley
bracket and replacement of the bracket with a modified bracket, P/N
4061-2701-1, as terminating action.
Recently, Reims discovered that aeroplane s/n F406-0091 had
inadvertently not been included in the SB and this has been revised
to correct the omission.
For the reasons described above, this AD retains the
requirements of DGAC France AD F-2005-080, which is superseded, and
adds aeroplane s/n F406-0091 to the Applicability of the AD, by
referencing Revision 2 of the Reims Aviation Industries SB F406-58.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Reims Aviation S.A. has issued Reims Aviation Industries Service
Bulletin No. F406-58, REV 1, dated October 27,
[[Page 3855]]
2006; and Reims Aviation Industries Service Bulletin No. F406-58, REV
2, dated July 27, 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 the 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 this State of Design Authority, they
have notified us of the unsafe condition described in the MCAI and
service information referenced above. We are proposing this AD because
we evaluated all information and determined the unsafe condition exists
and is likely to exist or develop on other products of the same type
design.
Differences Between This Proposed 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 will affect 7 products of U.S.
registry. We also estimate that it would take about 11 work-hours per
product to comply with the basic requirements of this proposed AD. The
average labor rate is $85 per work-hour. Required parts would cost
about $750 per product.
Based on these figures, we estimate the cost of the proposed AD on
U.S. operators to be $11,795, or $1,685 per product.
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.
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 39-14899 (72 FR
3047; January 24, 2007), and adding the following new AD:
Reims Aviation S.A.: Docket No. FAA-2011-0058; Directorate
Identifier 2010-CE-071-AD.
Comments Due Date
(a) We must receive comments by March 7, 2011.
Affected ADs
(b) This AD supersedes AD 2007-02-12, Amendment 39-14899.
Applicability
(c) This AD applies to Reims Aviation S.A. Model F406 airplanes,
serial numbers (SNs) 0002, 0003, 0004, 0006, 0008, 0009, 0010, 0012,
0013, 0017, 0024, 0025, 0039, 0042, 0044, 0045, 0066, 0070, 0073,
0074, 0075, 0077, 0080 through 0092, certificated in any category.
Subject
(d) Air Transport Association of America (ATA) Code 27: Flight
Controls.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
In early 2005, several reports had been received regarding
discovery of cracks in rudder pulley brackets installed on Reims
F406 aeroplanes. This pulley bracket, Part Number (P/N) 6015511-1,
is installed on aeroplanes with the optional ``Camera Hole''
modification.
This condition, if not detected and corrected, could result in
the loss of rudder control on the airplane.
To address this unsafe condition, DGAC France issued Emergency
(Urgent) AD UF-2005-080, followed by the final AD F-2005-080,
requiring repetitive inspections of the P/N 6015511-1 rudder pulley
bracket and replacement of the bracket with a modified bracket, P/N
4061-2701-1, as terminating action.
Recently, Reims discovered that aeroplane s/n F406-0091 had
inadvertently not been included in the SB and this has been revised
to correct the omission.
For the reasons described above, this AD retains the
requirements of DGAC France AD F-2005-080, which is superseded, and
adds aeroplane s/n F406-0091 to the Applicability of the AD, by
referencing Revision 2 of the Reims Aviation Industries SB F406-58.
Actions and Compliance
(f) Unless already done, do the following actions:
(1) For all affected SNs except F406-0091:
(i) Within the next 10 hours time-in-service (TIS) after
February 13, 2007 (the effective date retained from AD 2007-02-12),
perform the initial inspection as specified in Reims Aviation
Industries Service Bulletin No. F406-58, REV 1, dated October 27,
2006; or Reims Aviation Industries Service Bulletin No. F406-58, REV
2, dated July 27, 2010.
(ii) If no cracking is found following the initial inspection
required in paragraph (f)(1)(i) of this AD, repetitively thereafter
inspect every 50 hours TIS or 1 month, whichever occurs first, until
the installation of the modified pulley bracket specified in
paragraphs (f)(1)(iii) or (f)(1)(iv) of this AD is done.
(iii) If any cracking is found during the inspection required in
paragraph (f)(1)(i) of this AD, before further flight, install the
[[Page 3856]]
modified pulley bracket as specified in Reims Aviation Industries
Service Bulletin No. F406-58, REV 1, dated October 27, 2006; or
Reims Aviation Industries Service Bulletin No. F406-58, REV 2, dated
July 27, 2010. This installation terminates the repetitive
inspections required in paragraph (f)(1)(ii) of this AD.
(iv) Within the next 100 hours TIS or 2 months after February
13, 2007 (the effective date retained from AD 2007-02-12), whichever
occurs first, install the modified pulley bracket as specified in
Reims Aviation Industries Service Bulletin No. F406-58, REV 1, dated
October 27, 2006; or Reims Aviation Industries Service Bulletin No.
F406-58, REV 2, dated July 27, 2010. This installation terminates
the repetitive inspections required in paragraph (f)(1)(ii) of this
AD.
(v) The modified pulley bracket specified in Reims Aviation
Industries Service Bulletin No. F406-58, REV 1, dated October 27,
2006; or Reims Aviation Industries Service Bulletin No. F406-58, REV
2, dated July 27, 2010, may be installed at any time after the
inspection required in paragraph (f)(1)(i) of this AD, as long as no
cracking is found, but no later than the compliance time specified
in paragraph (f)(1)(iv) of this AD. If cracking is found, it must be
replaced before further flight as required in paragraph (f)(1)(iii)
of this AD.
(2) For serial number F406-0091:
(i) Within the next 10 hours TIS after the effective of this AD,
perform the initial inspection as specified in Reims Aviation
Industries Service Bulletin No. F406-58, REV 2, dated July 27, 2010.
(ii) If no cracking is found following the initial inspection
required in paragraph (f)(2)(i) of this AD, repetitively thereafter
inspect every 50 hours TIS or 1 month, whichever occurs first, until
the installation of the modified pulley bracket specified in
paragraphs (f)(2)(iii) and (f)(2)(iv) of this AD is done.
(iii) If any cracking is found during the inspection required in
paragraph (f)(2)(i) of this AD, before further flight, install the
modified pulley bracket as specified in Reims Aviation Industries
Service Bulletin No. F406-58, REV 2, dated July 27, 2010. This
installation terminates the repetitive inspections required in
paragraph (f)(2)(ii) of this AD.
(iv) Within the next 100 hours TIS or 2 months after the
effective of this AD, whichever occurs first, install the modified
pulley bracket as specified in Reims Aviation Industries Service
Bulletin No. F406-58, REV 2, dated July 27, 2010. This installation
terminates the repetitive inspections required in paragraph
(f)(2)(ii) of this AD.
(v) The modified pulley bracket specified in Reims Aviation
Industries Service Bulletin No. F406-58, REV 2, dated July 27, 2010,
may be installed at any time after the inspection required in
paragraph (f)(2)(i) of this AD as long as no cracking is found, but
no later than the compliance time specified in paragraph (f)(2)(iv)
of this AD. If cracking is found, it must be replaced before further
flight as required in paragraph (f)(2)(iii) of this AD.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Office, 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: Albert Mercado, Aerospace Engineer, FAA, Small
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4119; fax: (816) 329-4090. Before using
any approved AMOC on any airplane to which the AMOC applies, notify
your appropriate principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking a PI, your local FSDO.
(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, a federal agency may not conduct or sponsor, and a person
is not required to respond to, nor shall a person be subject to a
penalty for failure to comply with a collection of information
subject to the requirements of the Paperwork Reduction Act unless
that collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
Related Information
(h) Refer to MCAI European Aviation Safety Agency (EASA) AD
2010-0230, dated November 5, 2010; Reims Aviation Industries Service
Bulletin No. F406-58, REV 1, dated October 27, 2006; and Reims
Aviation Industries Service Bulletin No. F406-58, REV 2, dated July
27, 2010, for related information. For service information related
to this AD, contact Reims Aviation Industries, A[eacute]rodrome de
Reims Prunay, 51360 Prunay, France; telephone + 33 3 26 48 46 65;
fax + 33 3 26 49 18 57; e-mail Jn.sirot@reims-aviation.fr. You may
review copies of the referenced service information at the FAA,
Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106.
For information on the availability of this material at the FAA,
call 816-329-4148.
Issued in Kansas City, Missouri, on January 14, 2011.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-1221 Filed 1-20-11; 8:45 am]
BILLING CODE 4910-13-P
