Airworthiness Directives; Diamond Aircraft Industries GmbH Model DA 42 Airplanes, 18598-18600 [E7-7050]
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<![CDATA[
18598
Federal Register / Vol. 72, No. 71 / Friday, April 13, 2007 / Proposed Rules
(Passenger Information and
Entertainment Services Domain).
The proposed architecture of the 787
is different from that of existing
production (and retrofitted) airplanes. It
allows new kinds of passenger
connectivity to previously isolated data
networks connected to systems that
perform functions required for the safe
operation of the airplane. Because of
this new passenger connectivity, the
proposed data network design and
integration may result in security
vulnerabilities from intentional or
unintentional corruption of data and
systems critical to the safety and
maintenance of the airplane. The
existing regulations and guidance
material did not anticipate this type of
system architecture or electronic access
to aircraft systems that provide flight
critical functions. Furthermore, 14 CFR
regulations and current system safety
assessment policy and techniques do
not address potential security
vulnerabilities that could be caused by
unauthorized access to aircraft data
buses and servers. Therefore, a special
condition is proposed to ensure that
security, integrity, and availability of
the aircraft systems and data networks
are not compromised by certain wired
or wireless electronic connections
between airplane data buses and
networks.
Applicability
As discussed above, these proposed
special conditions are applicable to the
787. Should Boeing apply at a later date
for a change to the type certificate to
include another model incorporating the
same novel or unusual design features,
these proposed special conditions
would apply to that model as well
under the provisions of § 21.101.
Conclusion
This action affects only certain novel
or unusual design features of the 787. It
is not a rule of general applicability, and
it affects only the applicant that applied
to the FAA for approval of these features
on the airplane.
List of Subjects in 14 CFR Part 25
cprice-sewell on PRODPC61 with PROPOSALS
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
The authority citation for these
Special Conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Proposed Special Conditions
Accordingly, the Administrator of the
Federal Aviation Administration (FAA)
proposes the following special
conditions as part of the type
VerDate Aug<31>2005
14:53 Apr 12, 2007
Jkt 211001
certification basis for the Boeing Model
787–8 airplane.
The design shall prevent all inadvertent or
malicious changes to, and all adverse impacts
upon, all systems, networks, hardware,
software, and data in the Aircraft Control
Domain and in the Airline Information
Domain from all points within the Passenger
Information and Entertainment Domain.
Issued in Renton, Washington, on April 5,
2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E7–7065 Filed 4–12–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27533; Directorate
Identifier 2007–CE–022–AD]
RIN 2120–AA64
Airworthiness Directives; Diamond
Aircraft Industries GmbH Model DA 42
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. 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:
Shortly after an engine change, the
aluminium fitting attached to the engine
gearbox holding lines and fittings of the
propeller control system was found to be
cracked. This led to a pressure loss in the
propeller control system following a control
system malfunction and led to an in-flight
engine shutdown.
The broken fitting is part of the engine
installation and was initially a steel part. It
was later modified by the engine
manufacturer to an aluminium design.
Investigation determined that the area is
critical for cracks due to combination of
mass, material and installation torque values.
Diamond Aircraft Industries incorporated
¨
with Design Change MAM 42–184 an
additional bracket into production airplanes
to improve the installations and prevent
vibration cracks.
The proposed AD would require
actions that are intended to address the
unsafe condition described in the MCAI.
PO 00000
Frm 00002
Fmt 4702
Sfmt 4702
We must receive comments on
this proposed AD by May 14, 2007.
ADDRESSES: You may send comments by
any of the following methods:
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Fax: (202) 493–2251.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
DATES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.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–
5227) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Sarjapur Nagarajan, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4145; fax: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. This streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
follow all FAA AD issuance processes to
meet legal, economic, Administrative
Procedure Act, and Federal Register
requirements. We also continue to meet
our technical decision-making
responsibilities to identify and correct
unsafe conditions on U.S.-certificated
products.
This proposed AD references the
MCAI and related service information
that we considered in forming the
engineering basis to correct the unsafe
condition. The proposed AD contains
text copied from the MCAI and for this
reason might not follow our plain
language principles.
E:\FR\FM\13APP1.SGM
13APP1
Federal Register / Vol. 72, No. 71 / Friday, April 13, 2007 / Proposed Rules
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–2007–27533; Directorate Identifier
2007–CE–022–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://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued AD No: 2006–
0277, dated September 06, 2006
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
Shortly after an engine change, the
aluminium fitting attached to the engine
gearbox holding lines and fittings of the
propeller control system was found to be
cracked. This led to a pressure loss in the
propeller control system following a control
system malfunction and led to a in-flight
engine shutdown.
The broken fitting is part of the engine
installation and was initially a steel part. It
was later modified by the engine
manufacturer to an aluminium design.
Investigation determined that the area is
critical for cracks due to combination of
mass, material and installation torque values.
Diamond Aircraft Industries incorporated
¨
with Design Change MAM 42–184 an
additional bracket into production airplanes
to improve the installations and prevent
vibration cracks.
The MCAI requires:
This airworthiness directive requires the
retroactive installation of this bracket for all
airplanes, including the airplanes with steel
fittings.
You may obtain further information by
examining the MCAI in the AD docket.
cprice-sewell on PRODPC61 with PROPOSALS
Relevant Service Information
Diamond Aircraft Industries GmbH
has issued Mandatory Service Bulletin
No. MSB–42–024/3, dated September
19, 2006. The actions described in this
service information are intended to
correct the unsafe condition identified
in the MCAI.
VerDate Aug<31>2005
14:53 Apr 12, 2007
Jkt 211001
18599
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.
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.
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.
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.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 70 products of U.S. registry.
We also estimate that it would take
about 1 work-hour per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $80 per work-hour. Required
parts would cost about $208 per
product. Where the service information
lists required parts costs that are
covered under warranty, we have
assumed that there will be no charge for
these costs. As we do not control
warranty coverage for affected parties,
some parties may incur costs higher
than estimated here.
Based on these figures, we estimate
the cost of the proposed AD on U.S.
operators to be $20,160, or $288 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.
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Frm 00003
Fmt 4702
Sfmt 4702
Regulatory Findings
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Diamond Aircraft Industries GmbH: Docket
No. FAA–2007–27533; Directorate
Identifier 2007–CE–022–AD.
E:\FR\FM\13APP1.SGM
13APP1
18600
Federal Register / Vol. 72, No. 71 / Friday, April 13, 2007 / Proposed Rules
Comments Due Date
(a) We must receive comments by May 14,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to DA 42 airplanes,
serial numbers 42.004 through 42.129,
42.177, and 42.AC001, certificated in any
category.
Subject
(d) Air Transport Association of America
(ATA) Code 72: Engine.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Shortly after an engine change, the
aluminium fitting attached to the engine
gearbox holding lines and fittings of the
propeller control system was found to be
cracked. This led to a pressure loss in the
propeller control system following a control
system malfunction and led to a in-flight
engine shutdown.
The broken fitting is part of the engine
installation and was initially a steel part. It
was later modified by the engine
manufacturer to an aluminium design.
Investigation determined that the area is
critical for cracks due to combination of
mass, material and installation torque values.
Diamond Aircraft Industries incorporated
¨
with Design Change MAM 42–184 an
additional bracket into production airplanes
to improve the installations and prevent
vibration cracks.
Actions and Compliance
(f) Unless already done, within 50 hours
time-in-service or 30 days after the effective
date of this AD, whichever occurs first,
install the additional steel bracket following
Diamond Aircraft Industries GmbH
Mandatory Service Bulletin NO. MSB–42–
024/3, dated September 19, 2006.
Note 1: If the above action was
accomplished following the procedures
described in Diamond Aircraft Industries
GmbH Mandatory Service Bulletin No. MSB–
42–024/2, dated August 31, 2006, you may
take ‘‘unless already done’’ credit, and no
further action per this AD is necessary.
FAA AD Differences
cprice-sewell on PRODPC61 with PROPOSALS
Note 2: 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 Staff,
FAA, ATTN: Sarjapur Nagarajan, Aerospace
Engineer, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4145; fax: (816)
329–4090, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
VerDate Aug<31>2005
14:53 Apr 12, 2007
Jkt 211001
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 FAAapproved 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
(h) Refer to MCAI European Aviation
Safety Agency (EASA) AD No: 2006–0277,
dated September 06, 2006; and Diamond
Aircraft Industries GmbH, Mandatory Service
Bulletin No. MSB–42–024/3, dated
September 19, 2006, for related information.
Issued in Kansas City, Missouri, on April
6, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E7–7050 Filed 4–12–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27708; Directorate
Identifier 2007–CE–027–AD]
RIN 2120–AA64
Airworthiness Directives; Diamond
Aircraft Industries GmbH Model DA 42
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. 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:
From airplanes that have installed the
Auxiliary Fuel Tank Optional Design Change
(O–M) No. 42–056, three in-service failures of
the auxiliary fuel tank venting system have
been reported. These failures have led to the
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
inability to supply the complete auxiliary
fuel quantity to the main tanks and the
collapse of the auxiliary tank. It is suspected
that the vent lines were obstructed either by
ice accretion under certain climatic
conditions or by blockage of the vent valves
because of fuel contaminants.
Undetected malfunctions of the venting
system and damaged auxiliary fuel tanks may
lead to a lower usable fuel quantity,
subsequent fuel starvation and/or fuel
spillage into the nacelle.
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 May 14, 2007.
ADDRESSES: You may send comments by
any of the following methods:
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Fax: (202) 493–2251.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.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–
5227) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Sarjapur Nagarajan, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4145; fax: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. This streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
follow all FAA AD issuance processes to
E:\FR\FM\13APP1.SGM
13APP1
]]>Agencies
[Federal Register Volume 72, Number 71 (Friday, April 13, 2007)]
[Proposed Rules]
[Pages 18598-18600]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-7050]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27533; Directorate Identifier 2007-CE-022-AD]
RIN 2120-AA64
Airworthiness Directives; Diamond Aircraft Industries GmbH Model
DA 42 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. 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:
Shortly after an engine change, the aluminium fitting attached
to the engine gearbox holding lines and fittings of the propeller
control system was found to be cracked. This led to a pressure loss
in the propeller control system following a control system
malfunction and led to an in-flight engine shutdown.
The broken fitting is part of the engine installation and was
initially a steel part. It was later modified by the engine
manufacturer to an aluminium design.
Investigation determined that the area is critical for cracks
due to combination of mass, material and installation torque values.
Diamond Aircraft Industries incorporated with Design Change
M[Auml]M 42-184 an additional bracket into production airplanes to
improve the installations and prevent vibration cracks.
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 May 14, 2007.
ADDRESSES: You may send comments by any of the following methods:
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Fax: (202) 493-2251.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
dms.dot.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) 647-5227) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sarjapur Nagarajan, Aerospace
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone: (816) 329-4145; fax: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new process for streamlining the issuance
of ADs related to MCAI. This streamlined process will allow us to adopt
MCAI safety requirements in a more efficient manner and will reduce
safety risks to the public. This process continues to follow all FAA AD
issuance processes to meet legal, economic, Administrative Procedure
Act, and Federal Register requirements. We also continue to meet our
technical decision-making responsibilities to identify and correct
unsafe conditions on U.S.-certificated products.
This proposed AD references the MCAI and related service
information that we considered in forming the engineering basis to
correct the unsafe condition. The proposed AD contains text copied from
the MCAI and for this reason might not follow our plain language
principles.
[[Page 18599]]
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-2007-
27533; Directorate Identifier 2007-CE-022-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://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued AD
No: 2006-0277, dated September 06, 2006 (referred to after this as
``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:
Shortly after an engine change, the aluminium fitting attached
to the engine gearbox holding lines and fittings of the propeller
control system was found to be cracked. This led to a pressure loss
in the propeller control system following a control system
malfunction and led to a in-flight engine shutdown.
The broken fitting is part of the engine installation and was
initially a steel part. It was later modified by the engine
manufacturer to an aluminium design.
Investigation determined that the area is critical for cracks
due to combination of mass, material and installation torque values.
Diamond Aircraft Industries incorporated with Design Change
M[Auml]M 42-184 an additional bracket into production airplanes to
improve the installations and prevent vibration cracks.
The MCAI requires:
This airworthiness directive requires the retroactive
installation of this bracket for all airplanes, including the
airplanes with steel fittings.
You may obtain further information by examining the MCAI in the
AD docket.
Relevant Service Information
Diamond Aircraft Industries GmbH has issued Mandatory Service
Bulletin No. MSB-42-024/3, dated September 19, 2006. 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
Based on the service information, we estimate that this proposed AD
would affect about 70 products of U.S. registry. We also estimate that
it would take about 1 work-hour per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Required parts would cost about $208 per product. Where the
service information lists required parts costs that are covered under
warranty, we have assumed that there will be no charge for these costs.
As we do not control warranty coverage for affected parties, some
parties may incur costs higher than estimated here.
Based on these figures, we estimate the cost of the proposed AD on
U.S. operators to be $20,160, or $288 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, 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 adding the following new AD:
Diamond Aircraft Industries GmbH: Docket No. FAA-2007-27533;
Directorate Identifier 2007-CE-022-AD.
[[Page 18600]]
Comments Due Date
(a) We must receive comments by May 14, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to DA 42 airplanes, serial numbers 42.004
through 42.129, 42.177, and 42.AC001, certificated in any category.
Subject
(d) Air Transport Association of America (ATA) Code 72: Engine.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Shortly after an engine change, the aluminium fitting attached
to the engine gearbox holding lines and fittings of the propeller
control system was found to be cracked. This led to a pressure loss
in the propeller control system following a control system
malfunction and led to a in-flight engine shutdown.
The broken fitting is part of the engine installation and was
initially a steel part. It was later modified by the engine
manufacturer to an aluminium design.
Investigation determined that the area is critical for cracks
due to combination of mass, material and installation torque values.
Diamond Aircraft Industries incorporated with Design Change
M[Auml]M 42-184 an additional bracket into production airplanes to
improve the installations and prevent vibration cracks.
Actions and Compliance
(f) Unless already done, within 50 hours time-in-service or 30
days after the effective date of this AD, whichever occurs first,
install the additional steel bracket following Diamond Aircraft
Industries GmbH Mandatory Service Bulletin NO. MSB-42-024/3, dated
September 19, 2006.
Note 1: If the above action was accomplished following the
procedures described in Diamond Aircraft Industries GmbH Mandatory
Service Bulletin No. MSB-42-024/2, dated August 31, 2006, you may
take ``unless already done'' credit, and no further action per this
AD is necessary.
FAA AD Differences
Note 2: 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 Staff, FAA, ATTN: Sarjapur Nagarajan, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4145; fax: (816) 329-4090, has
the authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. 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, 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
(h) Refer to MCAI European Aviation Safety Agency (EASA) AD No:
2006-0277, dated September 06, 2006; and Diamond Aircraft Industries
GmbH, Mandatory Service Bulletin No. MSB-42-024/3, dated September
19, 2006, for related information.
Issued in Kansas City, Missouri, on April 6, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E7-7050 Filed 4-12-07; 8:45 am]
BILLING CODE 4910-13-P
