Airworthiness Directives; Mooney Airplane Company, Inc., (Mooney) Models M20M and M20R Airplanes, 9660-9662 [E7-3575]

Download as PDF 9660 Federal Register / Vol. 72, No. 42 / Monday, March 5, 2007 / Rules and Regulations (1) The associated interval for any new task is to be counted from the effective date of this AD. (2) The associated interval for any revised task is to be counted from the previous performance of the task. (3) For Model A340 airplanes that have exceeded the more restrictive limitations of Airbus A340 Certification Maintenance Requirements, Document 955.3019/92, Issue 14, Maintenance Significant Items (MSI) 21.28.00 and 21.43.00: Do the task within 2,500 flight hours after the previous accomplishment. Repeat the task thereafter at the applicable interval in the Airbus A340 Certification Maintenance Requirements, Document 955.3019/92, Issue 14. (4) For Model A340 airplanes that have accumulated more than 2,700 flight hours since the last maintenance done in accordance with Airbus A340 Certification Maintenance Requirements, Document 955.3019/92, Issue 14, MSI 28.24.00: Do the next task within 800 flight hours after the effective date of this AD. Repeat the task thereafter at the applicable interval in the Airbus A340 Certification Maintenance Requirements, Document 955.3019/92, Issue 14. Alternative Methods of Compliance (AMOCs) (g)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (h) The European Aviation Safety Agency airworthiness directives 2006–0224, dated July 27, 2006, and 2006–0225, dated July 21, 2006, also address the subject of this AD. erjones on PRODPC74 with RULES Material Incorporated by Reference (i) You must use Airbus A330 Certification Maintenance Requirements, Document 955.2074/93, Issue 19, dated March 22, 2006; or Airbus A340 Certification Maintenance Requirements, Document 955.3019/92, Issue 14, dated December 19, 2005; as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. VerDate Aug<31>2005 15:27 Mar 02, 2007 Jkt 211001 Issued in Renton, Washington, on February 22, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–3658 Filed 3–2–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26071; Directorate Identifier 2006–CE–51–AD; Amendment 39– 14965; AD 2007–05–04] RIN 2120–AA64 Airworthiness Directives; Mooney Airplane Company, Inc., (Mooney) Models M20M and M20R Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain Mooney Airplane Company, Inc., Models M20M and M20R airplanes. This AD requires you to remove the upper left and upper right engine mount attaching hardware, cut out and remove the upholstery and insulation between the fuselage tubular frame and the firewall, and replace the upper left and upper right engine mount attaching hardware with the new parts kit. This AD results from failure of the engine mount attaching hardware to maintain torque as a result of firewall insulation and upholstery being compressed between the fuselage tubular frame and the firewall at the upper left and upper right engine mount attach points. We are issuing this AD to prevent the upper right and upper left engine mounting hardware from losing torque, which could result in a reduction in engine mount load carrying capability and could lead to engine mount failure. DATES: This AD becomes effective on April 9, 2007. As of April 9, 2007, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. ADDRESSES: To get the service information identified in this AD, contact Mooney Airplane Company, Inc., 165 Al Mooney Road North, Kerrville, Texas 78028; telephone: (830) 896–6000, or go to: https:// www.mooney.com/images/pdfs/sb-pdf/ m20-292a.pdf. To view the AD docket, go to the Docket Management Facility; U.S. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001 or on the Internet at https:// dms.dot.gov. The docket number is FAA–2006–26071; Directorate Identifier 2006–CE–51–AD. FOR FURTHER INFORMATION CONTACT: Andrew McAnaul, Aerospace Engineer, ASW–150 (c/o MIDO–43), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: (210) 308– 3365; fax: (210) 308–3370. SUPPLEMENTARY INFORMATION: Discussion On November 7, 2006, we issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to certain Mooney Airplane Company, Inc. Models M20M and M20R airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on November 7, 2006 (71 FR 65062). The NPRM proposed to retorque the upper left and upper right engine mounting hardware as an interim action. The NPRM also proposed to remove the upper left and upper right engine mount attaching hardware, cut out and remove the upholstery and insulation between the fuselage tubular frame and the firewall, and replace the upper left and upper right engine mount attaching hardware with the new parts kit. Comments We provided the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and FAA’s response to each comment: Comment Issue: Jack Buster of the Modification and Replacement Parts Association (MARPA) suggests that paragraph (g) of the proposed action be amended to include the Internet Uniform Resource Locator (URL) address for the relevant service information. We agree with the commenter’s (Jack Buster, MARPA) recommendation. We added the manufacturer’s Internet URL address in the information on how to obtain the relevant service information. Conclusion Since the NPRM was published, the manufacturer has revised the applicable service bulletin to clarify the fastener torque requirement. The change does not change the intent of the required action and does not create any additional burden on the owners/ operators. The AD will reference the appropriate service information: Mooney Airplane Company, Inc. Service E:\FR\FM\05MRR1.SGM 05MRR1 Federal Register / Vol. 72, No. 42 / Monday, March 5, 2007 / Rules and Regulations Bulletin M20–292A, dated December 22, 2006, but will give credit to anyone who has already done the action per the original service bulletin. We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial corrections. We have determined that these minor corrections: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Costs of Compliance We estimate that this AD affects 198 airplanes in the U.S. registry. We estimate the following costs to accomplish the required modifications: Total cost per airplane Total cost on U.S. operators Not Applicable ................................. $40 $7,920 $20 ................................................... 180 35,640 Labor cost Parts cost Retorquing of the upper left and upper right engine mounting hardware: .5 work-hours × $80 per hour = $40. Removing insulation and upholstery material at the engine mount upper right and upper left attaching points, and installing engine mount attaching hardware with the new parts kit: 2 work-hours X $80 per hour = $160. 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 AD. Regulatory Findings 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 summary of the costs to comply with this AD (and other information as included in the Regulatory Evaluation) and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include ‘‘Docket No. FAA–2006–26071; Directorate Identifier 2006–CE–51–AD’’ in your request. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment We have 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 that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 9661 Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] I 2. FAA amends § 39.13 by adding a new AD to read as follows: 2007–05–04 Mooney Airplane Company, Inc., (Mooney) Models M20M and M20R Airplanes: Amendment 39–14965; Docket No. FAA–2006–26071; Directorate Identifier 2006–CE–51–AD. Effective Date (a) This AD becomes effective on April 9, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Mooney Airplane Company, Inc., (Mooney) Model M20M airplanes, serial numbers 27–0317 through 27–0355 and Model M20R airplanes, serial numbers 29–0290 through 29–0448, that are certificated in any category. Unsafe Condition (d) This AD is the result of failure of the engine mount attaching hardware to maintain torque as a result of firewall insulation and upholstery being compressed between the fuselage tubular frame and the firewall at the upper left and upper right engine mount attach points. The actions specified in this AD are intended to prevent the upper right and upper left engine mounting hardware from losing torque. This failure could lead to a reduction in engine mount load carrying capability and could result in engine mount failure. Compliance (e) To address this problem, you must do the following, unless already done: Compliance Procedures (1) Locate and retorque the upper left and upper right engine mount attaching hardware. erjones on PRODPC74 with RULES Actions Within the next 25 hours time-in-service (TIS) after April 9, 2007 (the effective date of this AD). Follow Mooney Airplane Company, Inc. Service Bulletin M20–292A, dated December 22, 2006. VerDate Aug<31>2005 15:27 Mar 02, 2007 Jkt 211001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\05MRR1.SGM 05MRR1 9662 Federal Register / Vol. 72, No. 42 / Monday, March 5, 2007 / Rules and Regulations Actions Compliance Procedures (2) Replace the old engine mount attaching hardware by doing the following:. (i) Remove and discard the upper left and upper right engine mount attaching hardware; (ii) Cut out and remove the upholstery and insulation material to allow full metal-tometal contact of the fuselage tubular frame to the firewall; and (iii) Install the new upper left and upper right engine mount attaching hardware part kits (3) If you do the actions of paragraph (e)(2) of this AD before the compliance time specified for the action in paragraph (e)(1) of this AD, it terminates the requirement for the action in paragraph (e)(1) of this AD. Within the next 100 hours time-in-service (TIS) after April 9, 2007 (the effective date of this AD). Follow Mooney Airplane Company, Inc. Service Bulletin M20–292A, dated December 22, 2006. As of April 9, 2007 (the effective date of this AD). Follow Mooney Airplane Company, Inc. Service Bulletin M20–292A, dated December 22, 2006. (f) Compliance will be acceptable if the above actions are accomplished by following the procedures described in Mooney Airplane Company, Inc. Service Bulletin M20–292, dated September 22, 2006. You may take ‘‘unless already done’’ credit, and no further action per this AD is necessary. Alternative Methods of Compliance (AMOCs) (g) The Manager, Fort Worth Airplane Certification Office, FAA, ATTN: Andrew McAnaul, Aerospace Engineer, ASW–150 (c/o MIDO–43), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: (210) 308–3365; fax: (210) 308–3370, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information erjones on PRODPC74 with RULES Material Incorporated by Reference (i) You must use Mooney Airplane Company, Inc. Service Bulletin M20–292A, dated December 22, 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 the Mooney Airplane Company, Inc., 165 Al Mooney Road North, Kerrville, TX 78028, telephone: 830–896– 6000, or go to: https://www.mooney.com/ images/pdfs/sb-pdf/m20-292a.pdf. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ibr_ locations.html. 15:27 Mar 02, 2007 Jkt 211001 BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23871; Directorate Identifier 2006–NE–01–AD; Amendment 39– 14975; AD 2007–05–14] RIN 2120–AA64 Airworthiness Directives; General Electric Company (GE) CF6–80C2 Turbofan Engines (h) None. VerDate Aug<31>2005 Issued in Kansas City, Missouri, on February 21, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–3575 Filed 3–2–07; 8:45 am] Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE CF6–80C2 series turbofan engines. This AD requires replacing certain installed part number (P/N) and serial number (SN) cast titanium weld-repaired forward engine mount platforms and cast titanium forward mount yokes, with a forged titanium or a non-welded cast titanium part. This AD results from the discovery of cracks, in a weldrepaired area on a forward engine mount platform and a forward engine mount yoke, found during a fluorescent penetrant inspection (FPI). These parts were weld-repaired during manufacture. We are issuing this AD to prevent cracks in the forward engine mount platform and forward engine mount yoke that could result in possible separation of the engine from the airplane. PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 This AD becomes effective April 9, 2007. ADDRESSES: You can get the service information identified in this AD from General Electric Company via Lockheed Martin Technology Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513) 672–8400, fax (513) 672–8422. You may examine the AD docket on the Internet at https://dms.dot.gov or in Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC. FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7176; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to GE CF6–80C2 series turbofan engines. We published the proposed AD in the Federal Register on December 13, 2006 (71 FR 74873). That action proposed to require replacing certain installed part number (P/N) and serial number (SN) cast titanium weldrepaired forward engine mount platforms and cast titanium forward mount yokes, with a forged titanium or a non-welded cast titanium part. DATES: Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. E:\FR\FM\05MRR1.SGM 05MRR1

Agencies

[Federal Register Volume 72, Number 42 (Monday, March 5, 2007)]
[Rules and Regulations]
[Pages 9660-9662]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-3575]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26071; Directorate Identifier 2006-CE-51-AD; 
Amendment 39-14965; AD 2007-05-04]
RIN 2120-AA64


Airworthiness Directives; Mooney Airplane Company, Inc., (Mooney) 
Models M20M and M20R Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain 
Mooney Airplane Company, Inc., Models M20M and M20R airplanes. This AD 
requires you to remove the upper left and upper right engine mount 
attaching hardware, cut out and remove the upholstery and insulation 
between the fuselage tubular frame and the firewall, and replace the 
upper left and upper right engine mount attaching hardware with the new 
parts kit. This AD results from failure of the engine mount attaching 
hardware to maintain torque as a result of firewall insulation and 
upholstery being compressed between the fuselage tubular frame and the 
firewall at the upper left and upper right engine mount attach points. 
We are issuing this AD to prevent the upper right and upper left engine 
mounting hardware from losing torque, which could result in a reduction 
in engine mount load carrying capability and could lead to engine mount 
failure.

DATES: This AD becomes effective on April 9, 2007.
    As of April 9, 2007, the Director of the Federal Register approved 
the incorporation by reference of certain publications listed in the 
regulation.

ADDRESSES: To get the service information identified in this AD, 
contact Mooney Airplane Company, Inc., 165 Al Mooney Road North, 
Kerrville, Texas 78028; telephone: (830) 896-6000, or go to: https://
www.mooney.com/images/pdfs/sb-pdf/m20-292a.pdf.
    To view the AD docket, go to the Docket Management Facility; U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC 20590-0001 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2006-26071; Directorate 
Identifier 2006-CE-51-AD.

FOR FURTHER INFORMATION CONTACT: Andrew McAnaul, Aerospace Engineer, 
ASW-150 (c/o MIDO-43), 10100 Reunion Place, Suite 650, San Antonio, 
Texas 78216; telephone: (210) 308-3365; fax: (210) 308-3370.

SUPPLEMENTARY INFORMATION:

Discussion

    On November 7, 2006, we issued a proposal to amend part 39 of the 
Federal Aviation Regulations (14 CFR part 39) to include an AD that 
would apply to certain Mooney Airplane Company, Inc. Models M20M and 
M20R airplanes. This proposal was published in the Federal Register as 
a notice of proposed rulemaking (NPRM) on November 7, 2006 (71 FR 
65062). The NPRM proposed to retorque the upper left and upper right 
engine mounting hardware as an interim action. The NPRM also proposed 
to remove the upper left and upper right engine mount attaching 
hardware, cut out and remove the upholstery and insulation between the 
fuselage tubular frame and the firewall, and replace the upper left and 
upper right engine mount attaching hardware with the new parts kit.

Comments

    We provided the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
and FAA's response to each comment:
    Comment Issue: Jack Buster of the Modification and Replacement 
Parts Association (MARPA) suggests that paragraph (g) of the proposed 
action be amended to include the Internet Uniform Resource Locator 
(URL) address for the relevant service information.
    We agree with the commenter's (Jack Buster, MARPA) recommendation. 
We added the manufacturer's Internet URL address in the information on 
how to obtain the relevant service information.

Conclusion

    Since the NPRM was published, the manufacturer has revised the 
applicable service bulletin to clarify the fastener torque requirement. 
The change does not change the intent of the required action and does 
not create any additional burden on the owners/operators. The AD will 
reference the appropriate service information: Mooney Airplane Company, 
Inc. Service

[[Page 9661]]

Bulletin M20-292A, dated December 22, 2006, but will give credit to 
anyone who has already done the action per the original service 
bulletin.
    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed 
except for minor editorial corrections. We have determined that these 
minor corrections:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Costs of Compliance

    We estimate that this AD affects 198 airplanes in the U.S. 
registry.
    We estimate the following costs to accomplish the required 
modifications:

----------------------------------------------------------------------------------------------------------------
                                                                                  Total cost per   Total cost on
                  Labor cost                               Parts cost                airplane     U.S. operators
----------------------------------------------------------------------------------------------------------------
Retorquing of the upper left and upper right    Not Applicable..................             $40          $7,920
 engine mounting hardware: .5 work-hours x $80
 per hour = $40.
Removing insulation and upholstery material at  $20.............................             180          35,640
 the engine mount upper right and upper left
 attaching points, and installing engine mount
 attaching hardware with the new parts kit: 2
 work-hours X $80 per hour = $160.
----------------------------------------------------------------------------------------------------------------

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 AD.

Regulatory Findings

    We have 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 that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD (and 
other information as included in the Regulatory Evaluation) and placed 
it in the AD Docket. You may get a copy of this summary by sending a 
request to us at the address listed under ADDRESSES. Include ``Docket 
No. FAA-2006-26071; Directorate Identifier 2006-CE-51-AD'' in your 
request.

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 Federal Aviation Administration amends part 39 of the Federal 
Aviation Regulations (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. FAA amends Sec.  39.13 by adding a new AD to read as follows:

2007-05-04 Mooney Airplane Company, Inc., (Mooney) Models M20M and 
M20R Airplanes: Amendment 39-14965; Docket No. FAA-2006-26071; 
Directorate Identifier 2006-CE-51-AD.

Effective Date

    (a) This AD becomes effective on April 9, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Mooney Airplane Company, Inc., (Mooney) 
Model M20M airplanes, serial numbers 27-0317 through 27-0355 and 
Model M20R airplanes, serial numbers 29-0290 through 29-0448, that 
are certificated in any category.

Unsafe Condition

    (d) This AD is the result of failure of the engine mount 
attaching hardware to maintain torque as a result of firewall 
insulation and upholstery being compressed between the fuselage 
tubular frame and the firewall at the upper left and upper right 
engine mount attach points. The actions specified in this AD are 
intended to prevent the upper right and upper left engine mounting 
hardware from losing torque. This failure could lead to a reduction 
in engine mount load carrying capability and could result in engine 
mount failure.

Compliance

    (e) To address this problem, you must do the following, unless 
already done:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Locate and retorque the   Within the next 25    Follow Mooney
 upper left and upper right    hours time-in-        Airplane Company,
 engine mount attaching        service (TIS) after   Inc. Service
 hardware.                     April 9, 2007 (the    Bulletin M20-292A,
                               effective date of     dated December 22,
                               this AD).             2006.

[[Page 9662]]

 
(2) Replace the old engine    Within the next 100   Follow Mooney
 mount attaching hardware by   hours time-in-        Airplane Company,
 doing the following:.         service (TIS) after   Inc. Service
(i) Remove and discard the     April 9, 2007 (the    Bulletin M20-292A,
 upper left and upper right    effective date of     dated December 22,
 engine mount attaching        this AD).             2006.
 hardware;.
(ii) Cut out and remove the
 upholstery and insulation
 material to allow full
 metal-to-metal contact of
 the fuselage tubular frame
 to the firewall; and.
(iii) Install the new upper
 left and upper right engine
 mount attaching hardware
 part kits.
(3) If you do the actions of  As of April 9, 2007   Follow Mooney
 paragraph (e)(2) of this AD   (the effective date   Airplane Company,
 before the compliance time    of this AD).          Inc. Service
 specified for the action in                         Bulletin M20-292A,
 paragraph (e)(1) of this                            dated December 22,
 AD, it terminates the                               2006.
 requirement for the action
 in paragraph (e)(1) of this
 AD.
------------------------------------------------------------------------

    (f) Compliance will be acceptable if the above actions are 
accomplished by following the procedures described in Mooney 
Airplane Company, Inc. Service Bulletin M20-292, dated September 22, 
2006. You may take ``unless already done'' credit, and no further 
action per this AD is necessary.

Alternative Methods of Compliance (AMOCs)

    (g) The Manager, Fort Worth Airplane Certification Office, FAA, 
ATTN: Andrew McAnaul, Aerospace Engineer, ASW-150 (c/o MIDO-43), 
10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: 
(210) 308-3365; fax: (210) 308-3370, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19.

Related Information

    (h) None.

Material Incorporated by Reference

    (i) You must use Mooney Airplane Company, Inc. Service Bulletin 
M20-292A, dated December 22, 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 the 
Mooney Airplane Company, Inc., 165 Al Mooney Road North, Kerrville, 
TX 78028, telephone: 830-896-6000, or go to: https://www.mooney.com/
images/pdfs/sb-pdf/m20-292a.pdf.
    (3) You may review copies at the FAA, Central Region, Office of 
the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at 
the National Archives and Records Administration (NARA). For 
information on the availability of this material at NARA, call 202-
741-6030, or go to: https://www.archives.gov/federal_register/code_
of_federal_regulations/ibr_locations.html.

    Issued in Kansas City, Missouri, on February 21, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E7-3575 Filed 3-2-07; 8:45 am]
BILLING CODE 4910-13-P
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