Airworthiness Directives; Mitsubishi Heavy Industries MU-2B Series Airplanes, 47699-47702 [E6-13441]

Download as PDF Federal Register / Vol. 71, No. 160 / Friday, August 18, 2006 / Rules and Regulations 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 adjustment of the flight idle fuel flow setting. The above issue, if uncorrected, could result 47699 in degraded performance and poor handling qualities with consequent loss of control of the airplane in certain situations. Compliance (e) To address this problem, you must do the following: TABLE 2.—ACTIONS/COMPLIANCE/PROCEDURES Actions Compliance Procedures Do flight checks of the rigging of the engine and propeller systems and make any necessary corrections. 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 do these actions. Make an entry into the aircraft logbook showing compliance with this portion of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). Check within 100 hours time-in-service (TIS) after September 22, 2006 (the effective date of this AD), and repetitively thereafter at intervals not to exceed 100 hours TIS. If any corrections are necessary, make the corrections before further flight. For airplanes listed in TCDS A2PC: Follow MHI MV–2 Service Bulletin No. 234, dated October 7, 1998. For airplanes listed in TCDS A10SW: Follow MHI MV–2 Service Bulletin No. 097/73– 001, dated July 24, 1998. Alternative Methods of Compliance (AMOCs) (f) The Manager, Fort Worth ACO, FAA, ATTN: Rao Edupuganti, Aerospace Engineer, ASW–150, 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. Issued in Kansas City, Missouri, on August 11, 2006. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–13554 Filed 8–17–06; 8:45 am] BILLING CODE 4910–13–P Related Information DEPARTMENT OF TRANSPORTATION (g) Japan Civil Aviation Bureau Airworthiness Directive No. TCD 4890–98, dated November 4, 1998; and MHI MV–2 Service Bulletins No. 234, dated October 7, 1998; and No. 097/73–001, dated July 24, 1998, also address the subject of this AD. Federal Aviation Administration rwilkins on PROD1PC63 with RULES Material Incorporated by Reference (h) You must do the actions required by this AD following the instructions in Mitsubishi Heavy Industries MV–2 Service Bulletin No. 234, dated October 7, 1998; and Mitsubishi Heavy Industries MV–2 Service Bulletin No. 097/73–001, dated July 24, 1998. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of these service bulletins, contact Mitsubishi Heavy Industries America, Inc., 4951 Airport Parkway, Suite 800, Addison, Texas 75001; telephone: (972) 934–5480; facsimile: (972) 934–5488. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html or call (202) 741–6030. 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– 2006–23884; Directorate Identifier 2006–CE– 13–AD. VerDate Aug<31>2005 18:30 Aug 17, 2006 Jkt 208001 14 CFR Part 39 [Docket No. FAA–2006–23883; Directorate Identifier 2006–CE–12–AD; Amendment 39– 14722; AD 2006–17–01] RIN 2120–AA64 Airworthiness Directives; Mitsubishi Heavy Industries MU–2B Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: The FAA adopts a new airworthiness directive (AD) for all Mitsubishi Heavy Industries (MHI) MU– 2B series airplanes. This AD requires you to incorporate power assurance charts into the Limitations Section of the Airplane Flight Manual (AFM), inspect the engine torque indication system, and recalibrate the torque pressure transducers as required. 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 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 that exist or could develop on the affected type design airplanes. We are issuing this AD to detect and correct torque transducers that are out of calibration. The above issue, if uncorrected, could result in degraded performance and poor handling qualities with consequent loss of control of the airplane in certain situations. DATES: This AD becomes effective on September 22, 2006. As of September 22, 2006, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. To get the service information identified in 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– 0001 or on the Internet at https:// dms.dot.gov. The docket number is FAA–2006–23883; Directorate Identifier 2006–CE–12–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: ADDRESSES: Discussion On April 21, 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 all E:\FR\FM\18AUR1.SGM 18AUR1 47700 Federal Register / Vol. 71, No. 160 / Friday, August 18, 2006 / Rules and Regulations Mitsubishi Heavy Industries (MHI) MU– 2B series airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on April 28, 2006 (71 FR 25120). The NPRM proposed to detect and correct torque transducers that are out of calibration. The above issue, if uncorrected, could result in degraded performance and poor handling qualities with consequent loss of control of the airplane in certain situations. 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 No. 1: Revise the Manufacturer Contact Information Ralph Sorrells, Deputy General Manager of Mitsubishi Heavy Industries America, Inc., requests that we revise MU–2B–25 ................. MU–2B–26 ................. MU–2B–35 ................. the manufacturer contact information from Mitsubishi Heavy Industries in Nagoya, Japan, to Mitsubishi Heavy Industries America, Inc. in Addison Texas. We agree with the commenter and will incorporate the change into this final rule AD action. Comment Issue No. 2: Correct the Date of the Japanese AD Ralph Sorrells, Deputy General Manager of Mitsubishi Heavy Industries America, Inc., requests that we correct the date of Japanese AD No. TCD 4889– 98 from October 7, 1998, to November 5, 1998. We agree with the commenter and will incorporate the change into this final rule AD action. Comment Issue No. 3: Remove LongBody Models From Table 1, Paragraph (c)(1) The airplanes described in Table 1, paragraph (c)(1) are short-body airplanes. Models MU–2B–30, MU–2B– 35, and MU–2B–36 are long-body airplanes. Ralph Sorrells, Deputy General Manager of Mitsubishi Heavy Industries America, Inc., requests that we remove reference of the long-body airplanes from Table 1, paragraph (c)(1). We agree with the commenter and will incorporate the change into this final rule AD action. Comment Issue No. 4: Add the Following Rows to TABLE 3.—AFM INSERTION PAGES: Ralph Sorrells, Deputy General Manager of Mitsubishi Heavy Industries America, Inc., request that we add the following rows to TABLE 3.—AFM INSERTION PAGES: AFM, Section 6, Revision 9, dated January 14, 1999 .................................................................................... AFM, Section 6, Revision 9, dated January 14, 1999 .................................................................................... AFM, Section 6, Revision 10, dated January 14, 1999 .................................................................................. We agree with the commenter and will incorporate the change into this final rule AD action. 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 the changes above and minor editorial corrections. We have determined that these changes and 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 397 airplanes in the U.S. registry. We estimate the following costs to accomplish the inspection: Total cost per airplane Labor cost Parts cost 5 work-hours × $80 = $400 ....................................................................... Not applicable .................................. The FAA 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/. rwilkins on PROD1PC63 with RULES 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, VerDate Aug<31>2005 18:30 Aug 17, 2006 Jkt 208001 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. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 6–19 6–19 6–19 $400 Total cost on U.S. operators $158,800 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 E:\FR\FM\18AUR1.SGM 18AUR1 47701 Federal Register / Vol. 71, No. 160 / Friday, August 18, 2006 / Rules and Regulations 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–2006–23883; Directorate Identifier 2006–CE–12–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 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 2006–17–01 Mitsubishi Heavy Industries: Amendment 39–14722; Docket No. FAA–2006–23883; Directorate Identifier 2006–CE–12–AD. Effective Date (a) This AD becomes effective on September 22, 2006. PART 39—AIRWORTHINESS DIRECTIVES Affected ADs 1. The authority citation for part 39 continues to read as follows: Applicability (b) None. I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] (c) This AD affects the following airplane models and serial numbers that are certificated in any category: 2. FAA amends § 39.13 by adding a new AD to read as follows: I TABLE 1.—APPLICABILITY Type certificate Models Serial Nos. (1) 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 ........................... 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. (2) A2PC ..................... (3) A10SW .................. (4) A10SW .................. Unsafe Condition (d) This AD is the result of 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 501 through 651, 653 through 660, and 662 through 696. 313SA, 321SA, and 348SA through 459SA. 652SA, 661SA, and 697SA through 1569SA. 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 torque transducers that are out of calibration. The above issue, if uncorrected, could result in degraded performance and poor handling qualities and lead to loss of control of the airplane in certain situations. Compliance (e) To address this problem, you must do the following: TABLE 2.—ACTIONS/COMPLIANCE/PROCEDURES Actions Compliance Procedures (1) Incorporate the following pages from the Airplane Flight Manual (AFM) charts listed in TABLE 3.—AFM INSERTION PAGES, paragraph (f) of this AD, into the Limitations Section of the FAA-approved AFM. Within 100 hours time-in-service (TIS) after September 22, 2006 (the effective date of this AD). (2) Inspect the engine torque indication system and recalibrate the torque pressure transducers as required. This inspection requires the use of the power assurance charts referenced in paragraph (e)(1) of this AD and in TABLE 3, paragraph (f) of this AD. Within 100 hours TIS after September 22, 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 do the flight manual changes requirement 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). (i) For airplanes listed in Type Certificate No. A2PC follow Mitsubishi Heavy Industries, Ltd. (MHI) MV–2 Service Bulletin No. 233A, dated January 14, 1999. (ii) For airplanes listed Type Certificate No. A10SW follow MHI Service Bulletin No. MV–2 095/77–002, dated July 15, 1998. (f) Use the following power assurance charts when doing the ground check portion of the inspection required in paragraph (e)(2) of this AD. TABLE 3.—AFM INSERTION PAGES rwilkins on PROD1PC63 with RULES Model of airplane affected (i) MU–2B ................... (ii) MU–2B–15 ............ (iii) MU–2B–20 ........... (iv) MU–2B–25 ........... VerDate Aug<31>2005 Page number from AFM Date and version of AFM AFM, AFM, AFM, AFM, AFM, 18:30 Aug 17, 2006 Section Section Section Section Section 6, 6, 6, 6, 6, Jkt 208001 Revision 9, dated January 14, 1999 ............................................................................. Revision 9, dated January 14, 1999 ............................................................................. Revision 9, dated January 14, 1999 ............................................................................. Reissued March 25, 1986; and .................................................................................... Revision 9, dated January 14, 1999 ............................................................................. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\18AUR1.SGM 18AUR1 6–34. 6–19. 6–20. 6–18 and 6–19 6–19. 47702 Federal Register / Vol. 71, No. 160 / Friday, August 18, 2006 / Rules and Regulations TABLE 3.—AFM INSERTION PAGES—Continued Model of airplane affected (v) MU–2B–26 ............ (vi) MU–2B–26A ......... (vii) MU–2B–35 .......... (viii) MU–2B–36A ....... (ix) MU–2B–40 ........... (x) MU–2B–60 ............ (xi) MU–2B–10 ........... (xii) MU–2B–30 .......... (xiii) MU–2B–36 ......... AFM, AFM, AFM, AFM, AFM, AFM, AFM, AFM, AFM, AFM, AFM, Section Section Section Section Section Section Section Section Section Section Section 6, 6, 6, 6, 6, 6, 6, 6, 6, 6, 6, Reissued March 25, 1986; and .................................................................................... Revision 9, dated January 14, 1999 ............................................................................. Reissued March 25, 1986 ............................................................................................. Reissued March 25, 1986; and .................................................................................... Revision 9, dated January 14, 1999 ............................................................................. Reissued February 28, 1986 ........................................................................................ Reissued March 25, 1986 ............................................................................................. Reissued September 24, 1985 ..................................................................................... Revision 9, dated January 14, 1999 ............................................................................. Revision 10, dated January 14, 1999 ........................................................................... Revision 9, dated January 14, 1999 ............................................................................. Note: AFM, Section 6, Reissued March 25, 1986 (FAA-approved) TCDS A10SW. AFM, Section 6, Revision 9 and Revision 10, dated January 14, 1999 (JCAB-approved). Alternative Methods of Compliance (AMOCs) (g) The Manager, Fort Worth Aircraft Certification Office, 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 (h) Japan Civil Aviation Bureau Airworthiness Directive No. TCD 4889–98, dated November 5, 1998, also addresses the subject of this AD. rwilkins on PROD1PC63 with RULES Material Incorporated by Reference (i) You must do the actions required by this AD following the instructions in Mitsubishi Heavy Industries, Ltd. MV–2 Service Bulletins No. 233A, dated January 14, 1999; and No. 095/77–002, dated July 15, 1998. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Mitsubishi Heavy Industries America, Inc., 4951 Airport Parkway, Suite 800, Addison, Texas 75001; telephone: (972) 934–5480; facsimile: (972) 934–5488. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html or call (202) 741–6030. 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– 2006–23883; Directorate Identifier 2006–CE– 12–AD. VerDate Aug<31>2005 Page number from AFM Date and version of AFM 18:30 Aug 17, 2006 Jkt 208001 Issued in Kansas City, Missouri, on August 9, 2006. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–13441 Filed 8–17–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24253; Directorate Identifier 2006–CE–23–AD; Amendment 39– 14723; AD 2006–17–02] RIN 2120–AA64 Airworthiness Directives; GROB– WERKE GMBH & CO KG Model G102 ASTIR CS Sailplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: The FAA supersedes Airworthiness Directive (AD) 84–09–05, which applies to certain GROB–WERKE GMBH & CO KG (previously identified as BURKHART–GROB FLUGZEUGBAU INDUSTRIESTRABE) Model G102 ASTIR CS sailplanes. AD 84–09–05 requires you to install a modified spherical locking bolt and nut in the forward horizontal stabilizer connection to the vertical stabilizer and install new locking pins in the aft connecting plate for the horizontal stabilizer. Since we issued AD 84–09–05, fatigue cracks were found in the modified spherical locking bolt. Consequently, this AD requires you to replace the modified spherical locking bolt, the retaining pins (collar bolts), and associated hardware; add a life limit on the spherical locking bolt and the retaining pins; and repetitively inspect the front and rear horizontal stabilizer attachment. This AD results from mandatory continuing airworthiness information (MCAI) PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 6–17 and 6–19. 6–17 and 6–18 and 6–19. 6–20 and 6–17 and 6–19 and 6–19. 6–19. 6–20. 6–18 6–18. 6–19 6–21. 6–18. 6–20. issued by the airworthiness authority for Germany. We are issuing this AD to prevent cracks in the spherical locking bolt, which could result in failure of the horizontal stabilizer connection. This failure could lead to loss of control. DATES: This AD becomes effective on September 22, 2006. As of September 22, 2006, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. ADDRESSES: For service information identified in this AD, contact GROB Luft-und Raumfahrt, Lettenbachstrasse 9, D–86874 Tussenhausen-Mattsies, Federal Republic of Germany; telephone: 011 49 8268 998139; fax: 011 49 8268 998200; e-mail: productsupport@grob-aerospace.de. 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–2006–24253; Directorate Identifier 2006–CE–23–AD. FOR FURTHER INFORMATION CONTACT: Gregory A. Davison, Aerospace Engineer, ACE–112, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4130; facsimile: (816) 329– 4090. SUPPLEMENTARY INFORMATION: Discussion On May 30, 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 GROB–WERKE GMBH & CO KG (previously identified as BURKHART– GROB FLUGZEUGBAU INDUSTRIESTRABE) Model G102 ASTIR CS sailplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) E:\FR\FM\18AUR1.SGM 18AUR1

Agencies

[Federal Register Volume 71, Number 160 (Friday, August 18, 2006)]
[Rules and Regulations]
[Pages 47699-47702]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-13441]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23883; Directorate Identifier 2006-CE-12-AD; 
Amendment 39-14722; AD 2006-17-01]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA adopts a new airworthiness directive (AD) for all 
Mitsubishi Heavy Industries (MHI) MU-2B series airplanes. This AD 
requires you to incorporate power assurance charts into the Limitations 
Section of the Airplane Flight Manual (AFM), inspect the engine torque 
indication system, and recalibrate the torque pressure transducers as 
required. 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. We are 
issuing this AD to detect and correct torque transducers that are out 
of calibration. The above issue, if uncorrected, could result in 
degraded performance and poor handling qualities with consequent loss 
of control of the airplane in certain situations.

DATES: This AD becomes effective on September 22, 2006.
    As of September 22, 2006, 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 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 20590-0001 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2006-23883; Directorate 
Identifier 2006-CE-12-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 April 21, 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 all

[[Page 47700]]

Mitsubishi Heavy Industries (MHI) MU-2B series airplanes. This proposal 
was published in the Federal Register as a notice of proposed 
rulemaking (NPRM) on April 28, 2006 (71 FR 25120). The NPRM proposed to 
detect and correct torque transducers that are out of calibration. The 
above issue, if uncorrected, could result in degraded performance and 
poor handling qualities with consequent loss of control of the airplane 
in certain situations.

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 No. 1: Revise the Manufacturer Contact Information

    Ralph Sorrells, Deputy General Manager of Mitsubishi Heavy 
Industries America, Inc., requests that we revise the manufacturer 
contact information from Mitsubishi Heavy Industries in Nagoya, Japan, 
to Mitsubishi Heavy Industries America, Inc. in Addison Texas.
    We agree with the commenter and will incorporate the change into 
this final rule AD action.

Comment Issue No. 2: Correct the Date of the Japanese AD

    Ralph Sorrells, Deputy General Manager of Mitsubishi Heavy 
Industries America, Inc., requests that we correct the date of Japanese 
AD No. TCD 4889-98 from October 7, 1998, to November 5, 1998.
    We agree with the commenter and will incorporate the change into 
this final rule AD action.

Comment Issue No. 3: Remove Long-Body Models From Table 1, Paragraph 
(c)(1)

    The airplanes described in Table 1, paragraph (c)(1) are short-body 
airplanes. Models MU-2B-30, MU-2B-35, and MU-2B-36 are long-body 
airplanes.
    Ralph Sorrells, Deputy General Manager of Mitsubishi Heavy 
Industries America, Inc., requests that we remove reference of the 
long-body airplanes from Table 1, paragraph (c)(1).
    We agree with the commenter and will incorporate the change into 
this final rule AD action.

Comment Issue No. 4: Add the Following Rows to TABLE 3.--AFM INSERTION 
PAGES:

    Ralph Sorrells, Deputy General Manager of Mitsubishi Heavy 
Industries America, Inc., request that we add the following rows to 
TABLE 3.--AFM INSERTION PAGES:

------------------------------------------------------------------------
 
------------------------------------------------------------------------
MU-2B-25........................  AFM, Section 6, Revision          6-19
                                   9, dated January 14,
                                   1999.
MU-2B-26........................  AFM, Section 6, Revision          6-19
                                   9, dated January 14,
                                   1999.
MU-2B-35........................  AFM, Section 6, Revision          6-19
                                   10, dated January 14,
                                   1999.
------------------------------------------------------------------------

    We agree with the commenter and will incorporate the change into 
this final rule AD action.

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 the changes above and minor editorial corrections. We have 
determined that these changes and 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 397 airplanes in the U.S. 
registry.
    We estimate the following costs to accomplish the inspection:

----------------------------------------------------------------------------------------------------------------
                                                                                                   Total cost on
                  Labor cost                               Parts cost             Total cost per       U.S.
                                                                                     airplane        operators
----------------------------------------------------------------------------------------------------------------
5 work-hours x $80 = $400.....................  Not applicable..................            $400        $158,800
----------------------------------------------------------------------------------------------------------------

    The FAA 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/.

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

[[Page 47701]]

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-
23883; Directorate Identifier 2006-CE-12-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:

2006-17-01 Mitsubishi Heavy Industries: Amendment 39-14722; Docket 
No. FAA-2006-23883; Directorate Identifier 2006-CE-12-AD.

Effective Date

    (a) This AD becomes effective on September 22, 2006.

Affected ADs

    (b) None.

Applicability

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

                         Table 1.--Applicability
------------------------------------------------------------------------
      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-2B-  348SA through
                              40.                    459SA.
(4) A10SW..................  MU-2B-35, MU-2B-36,    652SA, 661SA, and
                              MU-2B-36A, and MU-2B-  697SA through
                              60.                    1569SA.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD is the result of 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 torque transducers that are out of calibration. 
The above issue, if uncorrected, could result in degraded 
performance and poor handling qualities and lead to loss of control 
of the airplane in certain situations.

Compliance

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

                 Table 2.--Actions/Compliance/Procedures
------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Incorporate the           Within 100 hours      The owner/operator
 following pages from the      time-in-service       holding at least a
 Airplane Flight Manual        (TIS) after           private pilot
 (AFM) charts listed in        September 22, 2006    certificate as
 TABLE 3.--AFM INSERTION       (the effective date   authorized by
 PAGES, paragraph (f) of       of this AD).          section 43.7 of the
 this AD, into the                                   Federal Aviation
 Limitations Section of the                          Regulations (14 CFR
 FAA-approved AFM.                                   43.7) may do the
                                                     flight manual
                                                     changes requirement
                                                     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).
(2) Inspect the engine        Within 100 hours TIS  (i) For airplanes
 torque indication system      after September 22,   listed in Type
 and recalibrate the torque    2006 (the effective   Certificate No.
 pressure transducers as       date of this AD).     A2PC follow
 required. This inspection                           Mitsubishi Heavy
 requires the use of the                             Industries, Ltd.
 power assurance charts                              (MHI) MV-2 Service
 referenced in paragraph                             Bulletin No. 233A,
 (e)(1) of this AD and in                            dated January 14,
 TABLE 3, paragraph (f) of                           1999.
 this AD.                                           (ii) For airplanes
                                                     listed Type
                                                     Certificate No.
                                                     A10SW follow MHI
                                                     Service Bulletin
                                                     No. MV-2 095/77-
                                                     002, dated July 15,
                                                     1998.
------------------------------------------------------------------------

    (f) Use the following power assurance charts when doing the 
ground check portion of the inspection required in paragraph (e)(2) 
of this AD.

                      Table 3.--AFM Insertion Pages
------------------------------------------------------------------------
                              Date and version of
 Model of airplane affected           AFM           Page number from AFM
------------------------------------------------------------------------
(i) MU-2B..................  AFM, Section 6,        6-34.
                              Revision 9, dated
                              January 14, 1999.
(ii) MU-2B-15..............  AFM, Section 6,        6-19.
                              Revision 9, dated
                              January 14, 1999.
(iii) MU-2B-20.............  AFM, Section 6,        6-20.
                              Revision 9, dated
                              January 14, 1999.
(iv) MU-2B-25..............  AFM, Section 6,        6-18 and 6-19
                              Reissued March 25,    6-19.
                              1986; and.
                             AFM, Section 6,
                              Revision 9, dated
                              January 14, 1999.

[[Page 47702]]

 
(v) MU-2B-26...............  AFM, Section 6,        6-17 and 6-18 6-19.
                              Reissued March 25,
                              1986; and.
                             AFM, Section 6,
                              Revision 9, dated
                              January 14, 1999.
(vi) MU-2B-26A.............  AFM, Section 6,        6-17 and 6-18.
                              Reissued March 25,
                              1986.
(vii) MU-2B-35.............  AFM, Section 6,        6-18 and 6-19
                              Reissued March 25,    6-19.
                              1986; and.
                             AFM, Section 6,
                              Revision 9, dated
                              January 14, 1999.
(viii) MU-2B-36A...........  AFM, Section 6,        6-20 and 6-21.
                              Reissued February
                              28, 1986.
(ix) MU-2B-40..............  AFM, Section 6,        6-17 and 6-18.
                              Reissued March 25,
                              1986.
(x) MU-2B-60...............  AFM, Section 6,        6-19 and 6-20.
                              Reissued September
                              24, 1985.
(xi) MU-2B-10..............  AFM, Section 6,        6-19.
                              Revision 9, dated
                              January 14, 1999.
(xii) MU-2B-30.............  AFM, Section 6,        6-19.
                              Revision 10, dated
                              January 14, 1999.
(xiii) MU-2B-36............  AFM, Section 6,        6-20.
                              Revision 9, dated
                              January 14, 1999.
------------------------------------------------------------------------


    Note: AFM, Section 6, Reissued March 25, 1986 (FAA-approved) 
TCDS A10SW. AFM, Section 6, Revision 9 and Revision 10, dated 
January 14, 1999 (JCAB-approved).

Alternative Methods of Compliance (AMOCs)

    (g) The Manager, Fort Worth Aircraft Certification Office, 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

    (h) Japan Civil Aviation Bureau Airworthiness Directive No. TCD 
4889-98, dated November 5, 1998, also addresses the subject of this 
AD.

Material Incorporated by Reference

    (i) You must do the actions required by this AD following the 
instructions in Mitsubishi Heavy Industries, Ltd. MV-2 Service 
Bulletins No. 233A, dated January 14, 1999; and No. 095/77-002, 
dated July 15, 1998. The Director of the Federal Register approved 
the incorporation by reference of this service bulletin in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of 
this service information, contact Mitsubishi Heavy Industries 
America, Inc., 4951 Airport Parkway, Suite 800, Addison, Texas 
75001; telephone: (972) 934-5480; facsimile: (972) 934-5488. To 
review copies of this service information, go to the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, go to: https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html or call (202) 741-6030. 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-2006-23883; Directorate 
Identifier 2006-CE-12-AD.

    Issued in Kansas City, Missouri, on August 9, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-13441 Filed 8-17-06; 8:45 am]
BILLING CODE 4910-13-P
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