Airworthiness Directives; Societe de Motorisations Aeronautiques (SMA) SR305-230 and SR305-230-1 Reciprocating Engines, 67245-67247 [E7-22812]
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Federal Register / Vol. 72, No. 228 / Wednesday, November 28, 2007 / Rules and Regulations
67245
TABLE 1.—SBS ALLOWING PREVIOUS CREDIT—Continued
(5) Engine—Accessory Gearbox Starter Pad Drain—Install the Open Starter Drain Adapter (23077526 or 23083403); RRC SB No. AE
3007C–72–223, dated January 19, 2006.
Alternative Methods of Compliance (AMOC)
(k) The Manager, Chicago Aircraft
Certification Office, has the authority to
approve AMOCs for this AD if requested
using the procedures found in 14 CFR 39.19.
(l) AMOCs currently approved for AD 99–
02–51 will remain in effect until the
terminating action date for this AD,
September 30, 2009. After that date, these
AMOCs will expire and will not be approved
as AMOCs for this AD.
Office, Small Airplane Directorate, FAA,
2300 E. Devon Ave., Des Plaines, IL 60018;
e-mail: kyri.zaroyiannis@faa.gov; telephone
(847) 294–7836; fax (847) 294–7834, for more
information about this AD.
Material Incorporated by Reference
(n) You must use the service information
specified in Table 2 to perform the actions
required by this AD. The Director of the
Federal Register approved the incorporation
by reference of the documents listed in Table
2 of this AD in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Contact RollsRoyce Corporation, P.O. Box 420,
Related Information
(m) Contact Kyri Zaroyiannis, Aerospace
Engineer, Chicago Aircraft Certification
Indianapolis, IN 46206; telephone (317) 230–
3774; fax (317) 230–8084; e-mail:
indy.pubs.services@rolls-royce.com, for a
copy of this service information. You may
review copies at the FAA, New England
Region, 12 New England Executive Park,
Burlington, MA; or 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/
cfr/ibr-locations.html.
TABLE 2.—INCORPORATION BY REFERENCE
Service Bulletin No.
Page
AE 3007A–72–274 ...............................................................................................
Total Pages—6
AE 3007A–72–321, AE 3007C–72–250 ..............................................................
Total Pages—13
AE 3007A–72–330 ...............................................................................................
Total Pages—6
AE 3007C–72–223 ..............................................................................................
Total Pages—7
ALL ............................
1
November 12, 2007.
ALL ............................
2
November 12, 2007.
ALL ............................
1
November 12, 2007.
ALL ............................
1
November 12, 2007.
Issued in Burlington, Massachusetts, on
November 14, 2007.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E7–22810 Filed 11–27–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26102; Directorate
Identifier 2006–NE–36–AD; Amendment 39–
15272; AD 2007–24–06]
RIN 2120–AA64
Airworthiness Directives; Societe de
Motorisations Aeronautiques (SMA)
SR305–230 and SR305–230–1
Reciprocating Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
ebenthall on PRODPC61 with RULES
AGENCY:
SUMMARY: We are superseding an
existing airworthiness directive (AD) for
the products listed above. This AD
results from mandatory continuing
VerDate Aug<31>2005
17:13 Nov 27, 2007
Jkt 214001
airworthiness information (MCAI)
provided by the European Aviation
Safety Agency (EASA) to identify and
correct an unsafe condition on SMA
SR305–230 and SR305–230–1
reciprocating engines. The MCAI states
the following:
Over a period of time, the alteration of one
electronic control unit (ECU) electronic
component can cause a rapid uncontrolled
power increase. Several occurrences have
already been reported during engine start or
during engine warm-up. This condition, if
not corrected, could result in the loss of
control of the aircraft if the pilot fails to react
appropriately by switching to the mechanical
backup mode.
We are issuing this AD to prevent a
rapid uncontrolled power increase and
possible loss of control of the airplane.
DATES: This AD becomes effective
December 13, 2007. The Director of the
Federal Register approved the
incorporation by reference of SMA
Service Bulletin (SB) No. SB–01–76–
005, dated December 15, 2006, as of
December 13, 2007.
We must receive comments on this
AD by December 28, 2007.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the instructions for sending your
comments electronically.
PO 00000
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Fmt 4700
Sfmt 4700
Revision
Date
• Mail: Docket Management Facility,
U.S. Department of Transportation, 1200
New Jersey Avenue, SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590–0001.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: (202) 493–2251.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is the same as the Mail
address provided in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Christopher Spinney, Aerospace
Engineer, Engine Certification Office,
FAA, Engine and Propeller Directorate,
12 New England Executive Park,
Burlington, MA 01803; e-mail:
Christopher.spinney@faa.gov; telephone
(781) 238–7175; fax (781) 238–7199.
SUPPLEMENTARY INFORMATION:
E:\FR\FM\28NOR1.SGM
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67246
Federal Register / Vol. 72, No. 228 / Wednesday, November 28, 2007 / Rules and Regulations
Discussion
On October 31, 2006, we issued AD
2006–23–08, Amendment 39–14820 (71
FR 65041, November 7, 2006). That AD
required actions intended to address an
unsafe condition on the products listed
above. Since we issued AD 2006–23–08,
SMA developed a terminating action for
the unsafe condition. EASA, which is
the Technical Agent for the Member
States of the European Community,
issued AD 2007–0033, dated February
13, 2007. That AD supersedes EASA
EAD 2006–0312–E, which mandated a
temporary corrective action to the rapid
uncontrolled power increase. EASA AD
2007–0033 retains the requirements of
EASA AD 2006–0312–E, and also
requires replacing all affected ECUs
with a new part number ECU as
terminating action. EASA AD 2007–
0033 states:
Over a period of time, the alteration of one
electronic control unit (ECU) electronic
component can cause a rapid uncontrolled
power increase. Several occurrences have
already been reported during engine start or
during engine warm-up. This condition, if
not corrected, could result in the loss of
control of the aircraft if the pilot fails to react
appropriately by switching to the mechanical
backup mode.
You may obtain further information
by examining the MCAI in the AD
docket.
Relevant Service Information
SMA issued SB No. SB–01–76–005,
dated December 15, 2006. The actions
described in this service information are
intended to correct the unsafe condition
identified in EASA AD 2007–0033.
ebenthall on PRODPC61 with RULES
FAA’s Determination and Requirements
of This AD
This product has been approved by
the aviation authority of France, and is
approved for operation in the United
States. Pursuant to our bilateral
agreement with France, they have
notified us of the unsafe condition
described in the EASA AD and service
information referenced above. We are
issuing this AD because we evaluated
all the information provided by EASA
and SMA, and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design. This AD requires replacing
all affected ECUs with a new part
number ECU, as terminating action.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
VerDate Aug<31>2005
17:13 Nov 27, 2007
Jkt 214001
rule because of the short compliance
provided to correct the unsafe
condition. Therefore, we determined
that notice and opportunity for public
comment before issuing this AD are
impracticable and that good cause exists
for making this amendment effective in
fewer than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2006–26102;
Directorate Identifier 2006–NE–36–AD’’
at the beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
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
PO 00000
Frm 00020
Fmt 4700
Sfmt 4700
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this AD:
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.
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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–14820; (71 FR
65041, November 7, 2006) and adding
the following new AD:
2007–24–06 Societe de Motorisations
Aeronautiques (SMA): Amendment 39–
15272; Docket No. FAA–2006–26102;
Directorate Identifier 2006–NE–36–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective December 13, 2007.
Affected ADs
(b) This AD supersedes AD 2006–23–08,
Amendment 39–14820.
Applicability
(c) This AD applies to SMA SR305–230
and SR305–230–1 engines equipped with an
electronic control unit (ECU) having one of
the following part numbers (P/Ns):
SF01160009–0, SF01160011–0, SP01160013,
SP01160051–0, SP01160051–1, SP01160051–
2, SP01160051–3, SP01160051–4,
SP01160051–5, SP01160089–0, SP01160089–
1, SP01160089–2. These engines are installed
on, but not limited to, Cessna 182 series
airplanes with Supplemental Type Certificate
SA03302AT applied.
Reason
(d) European Aviation Safety Agency
(EASA) AD 2007–0033, dated February 13,
2007, states:
E:\FR\FM\28NOR1.SGM
28NOR1
Federal Register / Vol. 72, No. 228 / Wednesday, November 28, 2007 / Rules and Regulations
Over a period of time, the alteration of one
electronic control unit (ECU) electronic
component can cause a rapid uncontrolled
power increase. Several occurrences have
already been reported during engine start or
during engine warm-up. This condition, if
not corrected, could result in the loss of
control of the aircraft if the pilot fails to react
appropriately by switching to the mechanical
backup mode.
We are issuing this AD to prevent a rapid
uncontrolled power increase and possible
loss of control of the airplane.
Actions and Compliance
(e) Unless already done, do the following
actions:
(1) Before further flight, check if the ECU
has a P/N listed in the Applicability section
of this AD and a serial number (SN) of 131
or below, except SNs 70, 71, 83, and 88. If
it does, then do not operate the engine.
(2) Remove and replace the ECU with an
ECU P/N SP01160089–3, using SMA Service
Bulletin (SB) No. SB–01–76–005, dated
December 15, 2006.
(3) No later than 30 days after the effective
date of this AD, replace all remaining
affected P/N ECUs with an ECU P/N
SP01160089–3, using SMA SB No. SB–01–
76–005, dated December 15, 2006.
(4) After the effective date of this AD, do
not install a spare ECU having a P/N listed
in the Applicability section of this AD as a
replacement part on any SMA SR305–230 or
SR305–230–1 engine.
FAA AD Differences
(f) This AD differs from the Mandatory
Continuing Airworthiness Information
(MCAI) and/or service information as
follows:
(1) EASA AD No. 2007–0033 requires
compliance with the AD by March 31, 2007.
(2) This AD, written later, requires
compliance within 30 days after the effective
date of the AD.
Other FAA AD Provisions
(g) Alternative Methods of Compliance:
The Manager, Engine Certification Office,
FAA, has the authority to approve alternative
methods of compliance for this AD, if
requested using the procedures found in 14
CFR 39.19.
ebenthall on PRODPC61 with RULES
Related Information
(h) Refer to EASA AD 2007–0033, dated
February 13, 2007, for related information.
(i) Contact Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: Christopher.spinney@faa.gov;
telephone (781) 238–7175; fax (781) 238–
7199 for more information about this AD.
Material Incorporated by Reference
(j) You must use Societe de Motorisations
Aeronautiques Service Bulletin No. SB–01–
76–005, dated December 15, 2006, 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.
VerDate Aug<31>2005
15:16 Nov 27, 2007
Jkt 214001
(2) For service information identified in
this AD, contact Societe de Motorisations
Aeronautiques, 10–12 Rue Didier Daurat, F–
18021 Bourges, France—Telephone +33 (0) 2
4867 5600; Fax: +33 (0) 2 4850 0141; e-mail:
customer_services@smasr.com.
(3) You may review service information
copies at the FAA, New England Region, 12
New England Executive Park, Burlington,
MA 01803; or 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/
cfr/ibr-locations.html.
Issued in Burlington, MA, on November
15, 2007.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E7–22812 Filed 11–27–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28987; Directorate
Identifier 2007–NM–127–AD; Amendment
39–15269; AD 2007–24–03]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB–135ER,
–135KE, –135KL, and –135LR
Airplanes and Model EMB–145,
–145ER, –145MR, –145LR, –145XR,
–145MP, and –145EP Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
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:
It has been found the development of
cracks in the forward fuselage right hand
(RH) side skin during full-scale fatigue tests.
Those cracks may quickly reach their critical
length, reducing the aircraft structural
integrity, with possible rapid decompression
of the aircraft.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
January 2, 2008.
PO 00000
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Fmt 4700
Sfmt 4700
67247
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 2, 2008.
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.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–2125;
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 August 16, 2007 (72 FR
45963). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
It has been found the development of
cracks in the forward fuselage right hand
(RH) side skin during full-scale fatigue tests.
Those cracks may quickly reach their critical
length, reducing the aircraft structural
integrity, with possible rapid decompression
of the aircraft.
The corrective action includes rework
of the aircraft structure on the forward
fuselage LH (left-hand) and RH sides.
You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
EMBRAER has issued Service Bulletin
145–53–0067, Revision 02, dated
August 28, 2007. We referred to
EMBRAER Service Bulletin 145–53–
0067, Revision 01, dated February 27,
2007, as the appropriate source of
service information for doing the actions
specified in the NPRM. The procedures
in Revision 02 of the service bulletin are
essentially the same as those procedures
in Revision 01. Revision 02 revises the
illustrations and makes editorial
changes. We have revised paragraph
(f)(1) and Table 1 of this AD to also refer
to Revision 02 of the service bulletin.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received.
Request To Extend Grace Period
American Eagle Airlines requests that
we extend the grace period specified in
E:\FR\FM\28NOR1.SGM
28NOR1
]]>Agencies
[Federal Register Volume 72, Number 228 (Wednesday, November 28, 2007)]
[Rules and Regulations]
[Pages 67245-67247]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-22812]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26102; Directorate Identifier 2006-NE-36-AD;
Amendment 39-15272; AD 2007-24-06]
RIN 2120-AA64
Airworthiness Directives; Societe de Motorisations Aeronautiques
(SMA) SR305-230 and SR305-230-1 Reciprocating Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. This AD results from mandatory
continuing airworthiness information (MCAI) provided by the European
Aviation Safety Agency (EASA) to identify and correct an unsafe
condition on SMA SR305-230 and SR305-230-1 reciprocating engines. The
MCAI states the following:
Over a period of time, the alteration of one electronic control
unit (ECU) electronic component can cause a rapid uncontrolled power
increase. Several occurrences have already been reported during
engine start or during engine warm-up. This condition, if not
corrected, could result in the loss of control of the aircraft if
the pilot fails to react appropriately by switching to the
mechanical backup mode.
We are issuing this AD to prevent a rapid uncontrolled power
increase and possible loss of control of the airplane.
DATES: This AD becomes effective December 13, 2007. The Director of the
Federal Register approved the incorporation by reference of SMA Service
Bulletin (SB) No. SB-01-76-005, dated December 15, 2006, as of December
13, 2007.
We must receive comments on this AD by December 28, 2007.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 1200 New Jersey Avenue, SE., West Building Ground
Floor, Room W12-140, Washington, DC 20590-0001.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is the same as
the Mail address provided in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803; e-
mail: Christopher.spinney@faa.gov; telephone (781) 238-7175; fax (781)
238-7199.
SUPPLEMENTARY INFORMATION:
[[Page 67246]]
Discussion
On October 31, 2006, we issued AD 2006-23-08, Amendment 39-14820
(71 FR 65041, November 7, 2006). That AD required actions intended to
address an unsafe condition on the products listed above. Since we
issued AD 2006-23-08, SMA developed a terminating action for the unsafe
condition. EASA, which is the Technical Agent for the Member States of
the European Community, issued AD 2007-0033, dated February 13, 2007.
That AD supersedes EASA EAD 2006-0312-E, which mandated a temporary
corrective action to the rapid uncontrolled power increase. EASA AD
2007-0033 retains the requirements of EASA AD 2006-0312-E, and also
requires replacing all affected ECUs with a new part number ECU as
terminating action. EASA AD 2007-0033 states:
Over a period of time, the alteration of one electronic control
unit (ECU) electronic component can cause a rapid uncontrolled power
increase. Several occurrences have already been reported during
engine start or during engine warm-up. This condition, if not
corrected, could result in the loss of control of the aircraft if
the pilot fails to react appropriately by switching to the
mechanical backup mode.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
SMA issued SB No. SB-01-76-005, dated December 15, 2006. The
actions described in this service information are intended to correct
the unsafe condition identified in EASA AD 2007-0033.
FAA's Determination and Requirements of This AD
This product has been approved by the aviation authority of France,
and is approved for operation in the United States. Pursuant to our
bilateral agreement with France, they have notified us of the unsafe
condition described in the EASA AD and service information referenced
above. We are issuing this AD because we evaluated all the information
provided by EASA and SMA, and determined the unsafe condition exists
and is likely to exist or develop on other products of the same type
design. This AD requires replacing all affected ECUs with a new part
number ECU, as terminating action.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because of
the short compliance provided to correct the unsafe condition.
Therefore, we determined that notice and opportunity for public comment
before issuing this AD are impracticable and that good cause exists for
making this amendment effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2006-26102; Directorate
Identifier 2006-NE-36-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD because of
those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
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:
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.
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]
2. The FAA amends Sec. 39.13 by removing Amendment 39-14820; (71
FR 65041, November 7, 2006) and adding the following new AD:
2007-24-06 Societe de Motorisations Aeronautiques (SMA): Amendment
39-15272; Docket No. FAA-2006-26102; Directorate Identifier 2006-NE-
36-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective December
13, 2007.
Affected ADs
(b) This AD supersedes AD 2006-23-08, Amendment 39-14820.
Applicability
(c) This AD applies to SMA SR305-230 and SR305-230-1 engines
equipped with an electronic control unit (ECU) having one of the
following part numbers (P/Ns): SF01160009-0, SF01160011-0,
SP01160013, SP01160051-0, SP01160051-1, SP01160051-2, SP01160051-3,
SP01160051-4, SP01160051-5, SP01160089-0, SP01160089-1, SP01160089-
2. These engines are installed on, but not limited to, Cessna 182
series airplanes with Supplemental Type Certificate SA03302AT
applied.
Reason
(d) European Aviation Safety Agency (EASA) AD 2007-0033, dated
February 13, 2007, states:
[[Page 67247]]
Over a period of time, the alteration of one electronic control
unit (ECU) electronic component can cause a rapid uncontrolled power
increase. Several occurrences have already been reported during
engine start or during engine warm-up. This condition, if not
corrected, could result in the loss of control of the aircraft if
the pilot fails to react appropriately by switching to the
mechanical backup mode.
We are issuing this AD to prevent a rapid uncontrolled power
increase and possible loss of control of the airplane.
Actions and Compliance
(e) Unless already done, do the following actions:
(1) Before further flight, check if the ECU has a P/N listed in
the Applicability section of this AD and a serial number (SN) of 131
or below, except SNs 70, 71, 83, and 88. If it does, then do not
operate the engine.
(2) Remove and replace the ECU with an ECU P/N SP01160089-3,
using SMA Service Bulletin (SB) No. SB-01-76-005, dated December 15,
2006.
(3) No later than 30 days after the effective date of this AD,
replace all remaining affected P/N ECUs with an ECU P/N SP01160089-
3, using SMA SB No. SB-01-76-005, dated December 15, 2006.
(4) After the effective date of this AD, do not install a spare
ECU having a P/N listed in the Applicability section of this AD as a
replacement part on any SMA SR305-230 or SR305-230-1 engine.
FAA AD Differences
(f) This AD differs from the Mandatory Continuing Airworthiness
Information (MCAI) and/or service information as follows:
(1) EASA AD No. 2007-0033 requires compliance with the AD by
March 31, 2007.
(2) This AD, written later, requires compliance within 30 days
after the effective date of the AD.
Other FAA AD Provisions
(g) Alternative Methods of Compliance: The Manager, Engine
Certification Office, FAA, has the authority to approve alternative
methods of compliance for this AD, if requested using the procedures
found in 14 CFR 39.19.
Related Information
(h) Refer to EASA AD 2007-0033, dated February 13, 2007, for
related information.
(i) Contact Christopher Spinney, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
Christopher.spinney@faa.gov; telephone (781) 238-7175; fax (781)
238-7199 for more information about this AD.
Material Incorporated by Reference
(j) You must use Societe de Motorisations Aeronautiques Service
Bulletin No. SB-01-76-005, dated December 15, 2006, 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
Societe de Motorisations Aeronautiques, 10-12 Rue Didier Daurat, F-
18021 Bourges, France--Telephone +33 (0) 2 4867 5600; Fax: +33 (0) 2
4850 0141; e-mail: customer_services@smasr.com.
(3) You may review service information copies at the FAA, New
England Region, 12 New England Executive Park, Burlington, MA 01803;
or 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/cfr/
ibr-locations.html.
Issued in Burlington, MA, on November 15, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E7-22812 Filed 11-27-07; 8:45 am]
BILLING CODE 4910-13-P
