Airworthiness Directives; Mitsubishi Heavy Industries, Ltd. MU-2B Series Airplanes, 41116-41118 [E6-11419]

Download as PDF 41116 Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Seattle Aircraft Certification Office, 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 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Material Incorporated by Reference (j) You must use Boeing Service Bulletin 737–28A1192, Revision 2, dated April 27, 2006, 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 this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, Nassif Building, Washington, DC; on the Internet at https://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on July 7, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–11418 Filed 7–19–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23645; Directorate Identifier 2006–CE–04–AD; Amendment 39– 14687; AD 2006–15–07] RIN 2120–AA64 Airworthiness Directives; Mitsubishi Heavy Industries, Ltd. MU–2B Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. wwhite on PROD1PC76 with RULES AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for certain Mitsubishi Heavy Industries, Ltd. (MHI) MU–2B series airplanes. This AD requires you to incorporate text from the service information into the Limitations VerDate Aug<31>2005 16:42 Jul 19, 2006 Jkt 208001 Section of the FAA-approved Airplane Flight Manual (AFM). This AD results from a recent safety evaluation that used a data-driven approach to analyze the design, operation, and maintenance of the MU–2B series airplanes in order to determine their safety and define what steps, if any, are necessary for their safe operation. Part of that evaluation was the identification of unsafe conditions that exist or could develop on the affected type design airplanes. Field reports indicate an unsafe condition of improper rigging and/or adjustment of the propeller feathering linkage. Service centers found the unsafe condition during inspections. We are issuing this AD to detect and correct improper rigging of the propeller feathering linkage. The above issue, if uncorrected, could result in degraded performance and poor handling qualities with consequent loss of control of the airplane. This AD becomes effective on August 24, 2006. ADDRESSES: For service information related to this AD, contact Mitsubishi Heavy Industries America, Inc., 4951 Airport Parkway, Suite 800, Addison, Texas 75001; telephone: (972) 934– 5480; facsimile: ( 972) 934–5488. 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– 001 or on the Internet at https:// dms.dot.gov. The docket number is FAA–2006–23645; Directorate Identifier 2006–CE–04–AD. FOR FURTHER INFORMATION CONTACT: Rao Edupuganti, Aerospace Engineer, ASW– 150, Fort Worth Aircraft Certification Office, 2601 Meacham Blvd., Fort Worth, Texas 76193; telephone: (817) 222–5284; facsimile: (817) 222–5960. SUPPLEMENTARY INFORMATION: DATES: Discussion On March 16, 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 MHI MU–2B series airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on March 22, 2006 (71 FR 14425). The NPRM proposed to require you to incorporate text from the service information into the Limitations Section of the FAA-approved AFM. Comments We provided the public the opportunity to participate in developing this AD. The following presents the PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 comment received on the proposal and FAA’s response to that comment: Comment Issue: Issuance of an AD Requiring a Procedure That Has Been in the AFM for Almost 10 Years Ralph Sorrells, Mitsubishi Heavy Industries America (MHIA), Inc. contends that while MHIA does not object to the issuance of an AD to ensure that the feathering valve linkage inspection revision is included in the AFMs, MHIA does not understand why this condition would now merit an AD requiring the MU–2B operators to follow a procedure that has been in their AFMs for almost 10 years. This condition has not been the subject of a service difficulty report. Field reports have indicated that some MU–2B aircraft being inspected by service centers require re-rigging and/or adjustment of the propeller feathering linkage. Typically, misadjustment of the feathering linkage could result in the inability of the linkage to pull the feather valve to function as designed. The inability to feather the propeller could result in asymmetric drag and control difficulties that are outside the operational envelope of the aircraft. For type certificate data sheet (TCDS) A2PC, Service Bulletin No. 229, dated February 20, 1996, was issued by MHI, Ltd. and mandated by issuance of the Japan Civil Aviation Bureau (JCAB) AD No. TCD 4379–96, dated February 20, 1996, to ensure the continued airworthiness of the airplanes in Japan. For TCDS A10SW, Service Bulletin No. 090/76–003, dated January 22, 1997, was issued by MHI, Ltd. and the compliance was mandatory. At that time, issuance of an AD by FAA was not warranted, based on the information and lack of risk assessment tools. Recent accidents and the service history of the MU–2B series airplanes prompted FAA to conduct an MU–2B Safety Evaluation. Part of that evaluation was the identification of unsafe conditions that exist or could develop on the affected type design airplanes. Part of this evaluation was evaluating the JCAB ADs for which there were no FAA ADs. In conducting this evaluation, the team employed new analysis tools that provided a much more detailed root cause analysis of the MU–2B problems than was previously possible. The results of this evaluation warranted the issuance of this AD. Conclusion 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 E:\FR\FM\20JYR1.SGM 20JYR1 Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations 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. The Agency is committed to updating the aviation community of expected costs associated with the MU–2B series airplane safety evaluation conducted in 2005. As a result of that commitment, the accumulating expected costs of all ADs related to the MU–2B series airplane safety evaluation may be found in the Final Report section at the following Web site: https://www.faa.gov/ aircraft/air_cert/design_approvals/ small_airplanes/cos/ mu2_foia_reading_library/. Costs of Compliance We estimate that this AD affects 397 airplanes in the U.S. registry. We estimate the following costs to do the AFM insertion: Total cost per airplane Labor cost Parts cost 1 work-hour × $80 = $80 ................................................................................................................ Not applicable .... 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–2006–23645; Directorate Identifier 2006–CE–04–AD’’ in your request. List of Subjects in 14 CFR Part 39 41117 $80 Total cost on U.S. operators $31,760 the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: 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 the following new AD: 2006–15–07 Mitsubishi Heavy Industries, LTD.: Amendment 39–14687; Docket No. FAA–2006–23645; Directorate Identifier 2006–CE–04–AD. Effective Date (a) This AD becomes effective on August 24, 2006. Affected ADs (b) None. Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, I Applicability (c) This AD affects the following airplane models and serial numbers that are certificated in any category: Models Serial Nos. (1) A2PC .............................. (2) A2PC .............................. MU–2B, MU–2B–10, MU–2B–15, MU–2B–20, MU–2B– 25, and MU–2B–26. MU–2B–30, MU–2B–35, and MU–2B–36 ....................... (3) A10SW ........................... (4) A10SW ........................... wwhite on PROD1PC76 with RULES Type certificate MU–2B–25, MU–2B–26, MU–2B–26A, and MU–2B–40 MU–2B–35, MU–2B–36, MU–2B–36A, and MU–2B–60 008 through 312, 314 through 320, and 322 through 347. 501 through 651, 653 through 660, and 662 through 696. 313SA, 321SA, and 348SA through 459SA. 652SA, 661SA, and 697SA through 1569SA. Unsafe Condition (d) This AD results from a recent safety evaluation that used a data-driven approach to analyze the design, operation, and maintenance of the MU–2B series airplanes in order to determine their safety and define what steps, if any, are necessary for their safe VerDate Aug<31>2005 16:42 Jul 19, 2006 Jkt 208001 operation. Part of that evaluation was the identification of unsafe conditions that exist or could develop on the affected type design airplanes. The actions specified in this AD are intended to detect and correct improper rigging of the propeller feathering linkage. The above issue if uncorrected could result PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 in degraded performance and poor handling qualities with consequent loss of control of the airplane. Compliance (e) To address this problem, you must do the following: E:\FR\FM\20JYR1.SGM 20JYR1 41118 Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations Actions Compliance Procedures Incorporate the following information into the Limitations Section of the FAA-approved Airplane Flight Manual (AFM): (1) For airplanes listed in Type Certificate No. A2PC insert pages 3 and 4 from Mitsubishi Heavy Industries, Ltd. (MHI) MU–2 Service Bulletin No. 229, dated February 20, 1996. (2) For airplanes listed in Type Certificate No. A10SW insert page 3 of 3 from MHI MU–2 Service Bulletin No. 090/76–003, dated January 22, 1997. (3) For all of the above airplanes the logbook entry required after each pilot check on page 3 of MHI MU–2 Service Bulletin No. 090/76– 003, dated January 22, 1997, and page 4 of MHI MU–2 Service Bulletin No. 229, dated February 20, 1996, is not required. Within 100 hours time-in-service after August 24, 2006 (the effective date of this AD). The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may insert the information into the AFM as specified in paragraph (e) of this AD. Make an entry into the aircraft records showing compliance with this portion of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). Note: The language in the service information states the procedure is an ‘‘inspection,’’ but the procedure is a ‘‘pilot check.’’ (f) The Manager, Fort Worth Aircraft Certification Office (ACO), FAA, ATTN: Rao Edupuganti, Aerospace Engineer, ASW–150, Fort Worth ACO, 2601 Meacham Blvd., Fort Worth, Texas 76193; telephone: (817) 222– 5284; facsimile: (817) 222–5960, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (g) Japan Civil Aviation Bureau Airworthiness Directive No. TCD 4379–96, dated February 20, 1996, addresses the subject of this AD. (h) For service information related to this AD, contact Mitsubishi Heavy Industries America, Inc., 4951 Airport Parkway, Suite 800, Addison, Texas 75001; telephone: (972) 934–5480; facsimile: (972) 934–5488. 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 20590–001 or on the Internet at https:// dms.dot.gov. The docket number is FAA– 2006–23645; Directorate Identifier 2006–CE– 04–AD. Issued in Kansas City, Missouri, on July 11, 2006. Steven W. Thompson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–11419 Filed 7–19–06; 8:45 am] wwhite on PROD1PC76 with RULES VerDate Aug<31>2005 16:42 Jul 19, 2006 Jkt 208001 Federal Aviation Administration 14 CFR Part 39 Alternative Methods of Compliance (AMOCs) BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION [Docket No. FAA–2006–23675; Directorate Identifier 2001–NM–320–AD; Amendment 39–14686; AD 2006–15–06] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B2–203 and A300 B4–203 Airplanes; Model A300 B4–600, B4– 600R, and F4–600R Series Airplanes, and Model C4–605R Variant F Airplanes (Collectively Called A300– 600 Series Airplanes); and Model A310–200 and –300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300 series airplanes and all Model A300–600 and A310 series airplanes. That AD currently requires repetitive inspections of the pitch trim system to detect continuity defects in the autotrim function, and follow-on corrective actions if necessary. For certain airplanes, this new AD requires replacing the flight augmentation computers (FACs) with new improved FACs. This AD also revises the applicability of the existing AD. This AD results from the development of a final action intended to address the unsafe condition. We are issuing this AD to prevent a sudden change in pitch due to an out-of-trim condition combined with an autopilot disconnect, which could result in reduced controllability of the airplane. DATES: This AD becomes effective August 24, 2006. PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of August 24, 2006. On December 20, 2000 (65 FR 68876, November 15, 2000), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD. ADDRESSES: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2797; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at https://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2000–23–07, amendment 39–11977 (65 FR 68876, November 15, 2000). The existing AD applies to E:\FR\FM\20JYR1.SGM 20JYR1

Agencies

[Federal Register Volume 71, Number 139 (Thursday, July 20, 2006)]
[Rules and Regulations]
[Pages 41116-41118]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-11419]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23645; Directorate Identifier 2006-CE-04-AD; 
Amendment 39-14687; AD 2006-15-07]
RIN 2120-AA64


Airworthiness Directives; Mitsubishi Heavy Industries, Ltd. MU-2B 
Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Mitsubishi Heavy Industries, Ltd. (MHI) MU-2B series airplanes. This AD 
requires you to incorporate text from the service information into the 
Limitations Section of the FAA-approved Airplane Flight Manual (AFM). 
This AD results from a recent safety evaluation that used a data-driven 
approach to analyze the design, operation, and maintenance of the MU-2B 
series airplanes in order to determine their safety and define what 
steps, if any, are necessary for their safe operation. Part of that 
evaluation was the identification of unsafe conditions that exist or 
could develop on the affected type design airplanes. Field reports 
indicate an unsafe condition of improper rigging and/or adjustment of 
the propeller feathering linkage. Service centers found the unsafe 
condition during inspections. We are issuing this AD to detect and 
correct improper rigging of the propeller feathering linkage. The above 
issue, if uncorrected, could result in degraded performance and poor 
handling qualities with consequent loss of control of the airplane.

DATES: This AD becomes effective on August 24, 2006.

ADDRESSES: For service information related to this AD, contact 
Mitsubishi Heavy Industries America, Inc., 4951 Airport Parkway, Suite 
800, Addison, Texas 75001; telephone: (972) 934-5480; facsimile: ( 972) 
934-5488.
    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 20590-001 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2006-23645; Directorate 
Identifier 2006-CE-04-AD.

FOR FURTHER INFORMATION CONTACT: Rao Edupuganti, Aerospace Engineer, 
ASW-150, Fort Worth Aircraft Certification Office, 2601 Meacham Blvd., 
Fort Worth, Texas 76193; telephone: (817) 222-5284; facsimile: (817) 
222-5960.

SUPPLEMENTARY INFORMATION:

Discussion

    On March 16, 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 MHI MU-2B series airplanes. This proposal was 
published in the Federal Register as a notice of proposed rulemaking 
(NPRM) on March 22, 2006 (71 FR 14425). The NPRM proposed to require 
you to incorporate text from the service information into the 
Limitations Section of the FAA-approved AFM.

Comments

    We provided the public the opportunity to participate in developing 
this AD. The following presents the comment received on the proposal 
and FAA's response to that comment:

Comment Issue: Issuance of an AD Requiring a Procedure That Has Been in 
the AFM for Almost 10 Years

    Ralph Sorrells, Mitsubishi Heavy Industries America (MHIA), Inc. 
contends that while MHIA does not object to the issuance of an AD to 
ensure that the feathering valve linkage inspection revision is 
included in the AFMs, MHIA does not understand why this condition would 
now merit an AD requiring the MU-2B operators to follow a procedure 
that has been in their AFMs for almost 10 years. This condition has not 
been the subject of a service difficulty report.
    Field reports have indicated that some MU-2B aircraft being 
inspected by service centers require re-rigging and/or adjustment of 
the propeller feathering linkage. Typically, misadjustment of the 
feathering linkage could result in the inability of the linkage to pull 
the feather valve to function as designed. The inability to feather the 
propeller could result in asymmetric drag and control difficulties that 
are outside the operational envelope of the aircraft.
    For type certificate data sheet (TCDS) A2PC, Service Bulletin No. 
229, dated February 20, 1996, was issued by MHI, Ltd. and mandated by 
issuance of the Japan Civil Aviation Bureau (JCAB) AD No. TCD 4379-96, 
dated February 20, 1996, to ensure the continued airworthiness of the 
airplanes in Japan.
    For TCDS A10SW, Service Bulletin No. 090/76-003, dated January 22, 
1997, was issued by MHI, Ltd. and the compliance was mandatory. At that 
time, issuance of an AD by FAA was not warranted, based on the 
information and lack of risk assessment tools.
    Recent accidents and the service history of the MU-2B series 
airplanes prompted FAA to conduct an MU-2B Safety Evaluation. Part of 
that evaluation was the identification of unsafe conditions that exist 
or could develop on the affected type design airplanes. Part of this 
evaluation was evaluating the JCAB ADs for which there were no FAA ADs. 
In conducting this evaluation, the team employed new analysis tools 
that provided a much more detailed root cause analysis of the MU-2B 
problems than was previously possible. The results of this evaluation 
warranted the issuance of this AD.

Conclusion

    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

[[Page 41117]]

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.
    The Agency is committed to updating the aviation community of 
expected costs associated with the MU-2B series airplane safety 
evaluation conducted in 2005. As a result of that commitment, the 
accumulating expected costs of all ADs related to the MU-2B series 
airplane safety evaluation may be found in the Final Report section at 
the following Web site: https://www.faa.gov/aircraft/air_cert/design_
approvals/small_airplanes/cos/mu2_foia_reading_library/. 

Costs of Compliance

    We estimate that this AD affects 397 airplanes in the U.S. 
registry.
    We estimate the following costs to do the AFM insertion:

----------------------------------------------------------------------------------------------------------------
                                                                                         Total cost   Total cost
                  Labor cost                                  Parts cost                    per        on U.S.
                                                                                          airplane    operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $80 = $80.......................  Not applicable........................          $80      $31,760
----------------------------------------------------------------------------------------------------------------

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-2006-23645; Directorate Identifier 2006-CE-04-AD'' in your 
request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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 the following new AD:

2006-15-07 Mitsubishi Heavy Industries, LTD.: Amendment 39-14687; 
Docket No. FAA-2006-23645; Directorate Identifier 2006-CE-04-AD.

Effective Date

    (a) This AD becomes effective on August 24, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD affects the following airplane models and serial 
numbers that are certificated in any category:

------------------------------------------------------------------------
      Type certificate               Models              Serial Nos.
------------------------------------------------------------------------
(1) A2PC....................  MU-2B, MU-2B-10, MU-  008 through 312, 314
                               2B-15, MU-2B-20, MU-  through 320, and
                               2B-25, and MU-2B-26.  322 through 347.
(2) A2PC....................  MU-2B-30, MU-2B-35,   501 through 651, 653
                               and MU-2B-36.         through 660, and
                                                     662 through 696.
(3) A10SW...................  MU-2B-25, MU-2B-26,   313SA, 321SA, and
                               MU-2B-26A, and MU-    348SA through
                               2B-40.                459SA.
(4) A10SW...................  MU-2B-35, MU-2B-36,   652SA, 661SA, and
                               MU-2B-36A, and MU-    697SA through
                               2B-60.                1569SA.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from a recent safety evaluation that used a 
data-driven approach to analyze the design, operation, and 
maintenance of the MU-2B series airplanes in order to determine 
their safety and define what steps, if any, are necessary for their 
safe operation. Part of that evaluation was the identification of 
unsafe conditions that exist or could develop on the affected type 
design airplanes. The actions specified in this AD are intended to 
detect and correct improper rigging of the propeller feathering 
linkage. The above issue if uncorrected could result in degraded 
performance and poor handling qualities with consequent loss of 
control of the airplane.

Compliance

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

[[Page 41118]]



------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
Incorporate the following     Within 100 hours      The owner/operator
 information into the          time-in-service       holding at least a
 Limitations Section of the    after August 24,      private pilot
 FAA-approved Airplane         2006 (the effective   certificate as
 Flight Manual (AFM):          date of this AD).     authorized by
(1) For airplanes listed in                          section 43.7 of the
 Type Certificate No. A2PC                           Federal Aviation
 insert pages 3 and 4 from                           Regulations (14 CFR
 Mitsubishi Heavy                                    43.7) may insert
 Industries, Ltd. (MHI) MU-2                         the information
 Service Bulletin No. 229,                           into the AFM as
 dated February 20, 1996.                            specified in
(2) For airplanes listed in                          paragraph (e) of
 Type Certificate No. A10SW                          this AD. Make an
 insert page 3 of 3 from MHI                         entry into the
 MU-2 Service Bulletin No.                           aircraft records
 090/76-003, dated January                           showing compliance
 22, 1997.                                           with this portion
(3) For all of the above                             of the AD in
 airplanes the logbook entry                         accordance with
 required after each pilot                           section 43.9 of the
 check on page 3 of MHI MU-2                         Federal Aviation
 Service Bulletin No. 090/76-                        Regulations (14 CFR
 003, dated January 22,                              43.9).
 1997, and page 4 of MHI MU-
 2 Service Bulletin No. 229,
 dated February 20, 1996, is
 not required.
------------------------------------------------------------------------


    Note: The language in the service information states the 
procedure is an ``inspection,'' but the procedure is a ``pilot 
check.''

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Fort Worth Aircraft Certification Office (ACO), 
FAA, ATTN: Rao Edupuganti, Aerospace Engineer, ASW-150, Fort Worth 
ACO, 2601 Meacham Blvd., Fort Worth, Texas 76193; telephone: (817) 
222-5284; facsimile: (817) 222-5960, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19.

Related Information

    (g) Japan Civil Aviation Bureau Airworthiness Directive No. TCD 
4379-96, dated February 20, 1996, addresses the subject of this AD.
    (h) For service information related to this AD, contact 
Mitsubishi Heavy Industries America, Inc., 4951 Airport Parkway, 
Suite 800, Addison, Texas 75001; telephone: (972) 934-5480; 
facsimile: (972) 934-5488. 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 20590-001 
or on the Internet at https://dms.dot.gov. The docket number is FAA-
2006-23645; Directorate Identifier 2006-CE-04-AD.

    Issued in Kansas City, Missouri, on July 11, 2006.
Steven W. Thompson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-11419 Filed 7-19-06; 8:45 am]
BILLING CODE 4910-13-P
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