Airworthiness Directives; Diamond Aircraft Industries Model DA 42 Airplanes, 32785-32787 [E7-11287]
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Federal Register / Vol. 72, No. 114 / Thursday, June 14, 2007 / Rules and Regulations
Issued in Renton, Washington, on June 1,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–11200 Filed 6–13–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Streamlined Issuance of AD
[Docket No. FAA–2007–27533 Directorate
Identifier 2007–CE–022–AD; Amendment
39–15102; AD 2007–12–24]
RIN 2120–AA64
Airworthiness Directives; Diamond
Aircraft Industries Model DA 42
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)
issued 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:
pwalker on PROD1PC71 with RULES
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.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective July
19, 2007.
On July 19, 2007, the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the
VerDate Aug<31>2005
17:11 Jun 13, 2007
Jkt 211001
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590.
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:
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. The 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 AD references the MCAI and
related service information that we
considered in forming the engineering
basis to correct the unsafe condition.
The AD contains text copied from the
MCAI and for this reason might not
follow our plain language principles.
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 April 13, 2007 (72 FR
18598). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states that:
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.
This airworthiness directive requires the
retroactive installation of this bracket for all
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
32785
airplanes, including the airplanes with steel
fittings.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow FAA policies.
Any such differences are highlighted in
a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect
70 products of U.S. registry. We also
estimate that it will take about 1.0 workhour per product to comply with basic
requirements of this AD. The average
labor rate is $80 per work-hour.
Required parts will 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 parts. 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 this AD to the 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
E:\FR\FM\14JNR1.SGM
14JNR1
32786
Federal Register / Vol. 72, No. 114 / Thursday, June 14, 2007 / Rules and Regulations
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
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD Docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://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 the
NPRM, 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.
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:
pwalker on PROD1PC71 with RULES
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.
VerDate Aug<31>2005
17:11 Jun 13, 2007
Jkt 211001
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
2007–12–24 Diamond Aircraft Industries:
Amendment 39–15102; Docket No.
FAA–2007–27533; Directorate Identifier
2007–CE–022–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective July 19, 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 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.
This airworthiness directive requires the
retroactive installation of this bracket for all
airplanes, including the airplanes with steel
fittings.
Actions and Compliance
(f) Unless already done, within the next 50
hours time-in-service after July 19, 2007 (the
effective date of this AD) or within the next
30 days after July 19, 2007 (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, which references
Diamond Aircraft Industries GmbH Work
Instruction WI–MSB–42–024, Revision 2,
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
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
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, which references
Diamond Aircraft Industries GmbH Work
Instruction WI–MSB–42–024, Revision 2,
dated September 19, 2006, for related
information.
Material Incorporated by Reference
(i) You must use Diamond Aircraft
Industries GmbH, Mandatory Service
Bulletin No. MSB–42–024/3, dated
September 19, 2006, which references
Diamond Aircraft Industries GmbH Work
Instruction WI–MSB–42–024, Revision 2,
dated September 19, 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 Diamond Aircraft Industries
GmbH, N.A. Otto-Strabe 5, A–2700 Wiener
Neustadt; Fax: **43–2622–26620; or e-mail:
support@diamond-air.at.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, Kansas City,
Missouri 64106; or at the National Archives
and Records Administration (NARA). For
information on the availability of this
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14JNR1
Federal Register / Vol. 72, No. 114 / Thursday, June 14, 2007 / Rules and Regulations
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on June 6,
2007.
James E. Jackson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–11287 Filed 6–13–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20863; Directorate
Identifier 2004–SW–36–AD; Amendment 39–
15100; AD 2007–12–22]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France Model AS350B, BA, B1, B2, B3,
D, and AS355E Helicopters
Federal Aviation
Administration, DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This amendment adopts a
new airworthiness directive (AD) for the
specified Eurocopter France (ECF)
model helicopters that requires
replacing the hydraulic fluid at a
specified time interval when operating
in cold weather. This amendment is
prompted by reports of ice forming due
to condensation in some parts of the
hydraulic system during cold weather
operation. The actions specified by this
AD are intended to prevent ice from
forming in the hydraulic system
resulting in an unintended movement of
the flight controls and subsequent loss
of control of the helicopter.
DATES: Effective July 19, 2007.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of July 19,
2007.
You may get the service
information identified in this AD from
American Eurocopter Corporation, 2701
Forum Drive, Grand Prairie, Texas
75053–4005, telephone (972) 641–3460,
fax (972) 641–3527.
Examining the Docket: You may
examine the docket that contains this
AD, any comments, and other
information on the Internet at https://
dms.dot.gov, or at the Docket
Management System (DMS), U.S.
Department of Transportation, 400
Seventh Street SW., Room PL–401, on
the plaza level of the Nassif Building,
Washington, DC.
pwalker on PROD1PC71 with RULES
ADDRESSES:
VerDate Aug<31>2005
17:11 Jun 13, 2007
Jkt 211001
Ed
Cuevas, Aviation Safety Engineer, FAA,
Rotorcraft Directorate, Safety
Management Group, Fort Worth, Texas
76193–0111, telephone (817) 222–5355,
fax (817) 222–5961.
SUPPLEMENTARY INFORMATION: A
proposal to amend 14 CFR part 39 to
include an AD for the specified model
helicopters was published in the
Federal Register on April 7, 2005 (70 FR
17621). That action proposed replacing
the hydraulic fluid at a specified time
interval when operating in cold
weather.
The Direction Generale de l’Aviation
Civile (DGAC), the airworthiness
authority for France, notified the FAA
that an unsafe condition may exist on
the specified ECF Model AS350 and
AS355 helicopters. The DGAC advises
of the formation of ice in some parts of
the hydraulic system during flights in
cold weather and when the hydraulic
fluid is highly contaminated by water.
ECF has issued Alert Service Bulletin
Nos. 05.00.43 and 05.00.45, both dated
April 8, 2004, which specify provisions
for replacing hydraulic fluid in cold
weather. The DGAC classified these
service bulletins as mandatory and
issued AD Nos. F–2004–055 and F–
2004–056, both dated April 28, 2004, to
ensure the continued airworthiness of
these helicopters in France.
These helicopter models are
manufactured in France and are type
certificated for operation in the United
States under the provisions of 14 CFR
21.29 and the applicable bilateral
agreement. Pursuant to the applicable
bilateral agreement, the DGAC has kept
us informed of the situation described
above. We have examined the findings
of the DGAC, reviewed all available
information, and determined that AD
action is necessary for products of these
type designs that are certificated for
operation in the United States.
Interested persons have been afforded
an opportunity to participate in the
making of this amendment. Due
consideration has been given to the one
comment received.
The one commenter states that the
ASB is adequate until Eurocopter sorts
out the moisture problem, and changing
the fluid every 100 hours or 30 days is
wasteful and not necessary, and such
action will not get all the moisture out
of the system. Therefore, an AD should
not be issued.
The FAA does not agree. The ASB is
not adequate until Eurocopter sorts out
the moisture problem. Generally, part 91
operators are not required to follow an
ASB; however, they are required to
follow an AD. An AD is issued to
FOR FURTHER INFORMATION CONTACT:
PO 00000
Frm 00015
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32787
address an unsafe condition. This AD
requires replacing the hydraulic fluid at
the specified intervals to prevent ice
from forming in the hydraulic system
resulting in an unintended movement of
the flight controls and subsequent loss
of control of the helicopter. The ASB
was written in association with the
airworthiness authority in France
(DGAC) to address the problem of
moisture in the hydraulic fluid resulting
in feedback in the system during
operations in cold temperatures in
Canada. Moisture that is absorbed into
the hydraulic fluid is not a function of
the type of fluid. Moisture is absorbed
into the hydraulic fluid due to heating
and cooling of the fluid in the reservoir
because the reservoir is vented to
atmospheric pressure (humidity). It is
not a closed system. Moisture may occur
with either MIL–H–83282 or MIL–H–
5606 fluid. Normally, there is not
enough moisture in the system to cause
any problems but occasionally there is
enough to cause some feedback in the
cyclic control (due to ice crystals
forming in cold weather). MIL–H–83282
hydraulic fluid is the preferred fluid
and MIL–H–5606 is an alternate. In
many climates, the operator cannot use
the MIL–H–5606 fluid because it has a
lower flash point than the MIL–H–
83282 fluid. Therefore, MIL–H–5606
fluid can only be used in colder
environments. As a result, the option for
the alternate fluid is limited to colder
environments.
An ECF ASB is written in association
with an AD issued by a foreign authority
(European Aviation Safety Agency
(EASA) or DGAC). The foreign ASB is
in place when the AD is published to
require that operators comply with the
manufacturer’s ASB. The FAA AD
follows the requirements placed on
other parts of the world by the foreign
authority (state of design) if the FAA
agrees with those requirements.
After careful review of the available
data, including the comments noted
above, the FAA has determined that air
safety and the public interest require the
adoption of the rule as proposed except
for a change in paragraph (b) of the AD
to add additional contact information
and to revise the total cost impact; we
have used a labor rate of $80 instead of
$65. The FAA has determined that these
changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
We estimate that this AD will affect
556 helicopters of U.S. registry, and the
required actions will take about:
• 2 work hours to replace the
hydraulic fluid per helicopter at an
average labor rate of $80 per work hour;
and
E:\FR\FM\14JNR1.SGM
14JNR1
]]>Agencies
[Federal Register Volume 72, Number 114 (Thursday, June 14, 2007)]
[Rules and Regulations]
[Pages 32785-32787]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-11287]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27533 Directorate Identifier 2007-CE-022-AD;
Amendment 39-15102; AD 2007-12-24]
RIN 2120-AA64
Airworthiness Directives; Diamond Aircraft Industries Model DA 42
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) issued 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.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective July 19, 2007.
On July 19, 2007, the Director of the Federal Register approved the
incorporation by reference of certain publications listed in this AD.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Document Management Facility, U.S.
Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC
20590.
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. The 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 AD references the MCAI and related service information that we
considered in forming the engineering basis to correct the unsafe
condition. The AD contains text copied from the MCAI and for this
reason might not follow our plain language principles.
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 April 13, 2007 (72
FR 18598). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states that:
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.
This airworthiness directive requires the retroactive
installation of this bracket for all airplanes, including the
airplanes with steel fittings.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect 70 products of U.S. registry.
We also estimate that it will take about 1.0 work-hour per product to
comply with basic requirements of this AD. The average labor rate is
$80 per work-hour. Required parts will 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 parts. 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 this AD to the 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
[[Page 32786]]
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 DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD Docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
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 the NPRM, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2007-12-24 Diamond Aircraft Industries: Amendment 39-15102; Docket
No. FAA-2007-27533; Directorate Identifier 2007-CE-022-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective July 19,
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 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.
This airworthiness directive requires the retroactive
installation of this bracket for all airplanes, including the
airplanes with steel fittings.
Actions and Compliance
(f) Unless already done, within the next 50 hours time-in-
service after July 19, 2007 (the effective date of this AD) or
within the next 30 days after July 19, 2007 (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, which
references Diamond Aircraft Industries GmbH Work Instruction WI-MSB-
42-024, Revision 2, 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, which references Diamond Aircraft Industries GmbH Work
Instruction WI-MSB-42-024, Revision 2, dated September 19, 2006, for
related information.
Material Incorporated by Reference
(i) You must use Diamond Aircraft Industries GmbH, Mandatory
Service Bulletin No. MSB-42-024/3, dated September 19, 2006, which
references Diamond Aircraft Industries GmbH Work Instruction WI-MSB-
42-024, Revision 2, dated September 19, 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
Diamond Aircraft Industries GmbH, N.A. Otto-Strabe 5, A-2700 Wiener
Neustadt; Fax: **43-2622-26620; or e-mail: support@diamond-air.at.
(3) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri
64106; or at the National Archives and Records Administration
(NARA). For information on the availability of this
[[Page 32787]]
material at NARA, call 202-741-6030, or go to: https://
www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on June 6, 2007.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-11287 Filed 6-13-07; 8:45 am]
BILLING CODE 4910-13-P
