Airworthiness Directives; Diamond Aircraft Industries GmbH Model DA 42 Airplanes, 18598-18600 [E7-7050]

Download as PDF 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. PO 00000 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
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