Airworthiness Directives; Mitsubishi Heavy Industries MU-2B Series Airplanes, 36984-36986 [06-5653]

Download as PDF 36984 Federal Register / Vol. 71, No. 125 / Thursday, June 29, 2006 / Rules and Regulations PART 78—BRUCELLOSIS Accordingly, we are adopting as a final rule, without change, the interim rule that amended 9 CFR part 78 and that was published at 71 FR 2991–2993 on January 19, 2006. I Done in Washington, DC, this 23rd day of June 2006. Kevin Shea, Acting Administrator, Animal and Plant Health Inspection Service. [FR Doc. 06–5800 Filed 6–28–06; 8:45 am] BILLING CODE 3410–34–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23578; Directorate Identifier 2006–CE–01–AD; Amendment 39– 14668; AD 2006–13–15] RIN 2120–AA64 Airworthiness Directives; Mitsubishi Heavy Industries MU–2B Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for all Mitsubishi Heavy Industries MU–2B series airplanes. This AD requires you to do the following: Remove and visually inspect the wing attach barrel nuts, bolts, and retainers for cracks, corrosion, and fractures; replace any cracked, corroded, or fractured parts; inspect reusable wing attach barrel nuts and bolts for deformation and irregularities in the threads; check the minimum breakaway torque of reused wing attach barrel nuts; replace any deformed or irregular parts; and install new or reusable parts and torque to the correct value. This AD results from a recent safety evaluation that used a data-driven approach to evaluate 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 cracks, corrosion, fractures, and incorrect torque values in the wing attach barrel nuts, which could result in failure of the wing barrel nuts and/or associated wing attachment hardware. This failure could lead to in-flight separation of the outer wing from the center wing section and result in loss of controlled flight. DATES: This AD becomes effective on August 11, 2006. As of August 11, 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 Mitsubishi Heavy Industries America, Inc., 4951 Airport Parkway, Suite 800, Addison, Texas 95001; telephone: (972) 934– 5480; fax: (972) 934–5488, or Turbine Aircraft Services, Inc., 4550 Jimmy Doolittle Drive, Addison, Texas 75001; telephone: (972) 248–3108; facsimile: (972) 248–3321. 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–2006–23578; Directorate Identifier 2006–CE–01–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; facsimile: (210) 308–3370. SUPPLEMENTARY INFORMATION: Discussion On April 18, 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 Mitsubishi Heavy Industries MU–2B series airplanes. This proposal was published in the Federal Register as a supplemental notice of proposed rulemaking (NPRM) on April 24, 2006 (71 FR 20915). We issued the supplemental NPRM to incorporate revised manufacturer service information that adds airplanes to the applicability, revises the serial numbers of the affected airplanes, and updates the manufacturer’s contact information. The supplemental NPRM proposed to require you to do the following: • Remove and visually inspect the wing attach barrel nuts, bolts, and retainers for cracks, corrosion, and fractures; • Replace any cracked, corroded, or fractured wing attach barrel nuts, bolts, and retainers with new parts; • Inspect reusable wing attach barrel nuts and bolts for deformation and irregularities in the threads; • Check the minimum breakaway torque of reused wing attach barrel nuts; • Replace any deformed or irregular wing attach barrel nuts or bolts with new parts; and • Install new or reusable parts and torque to the correct value. Comments We provided the public the opportunity to participate in developing this AD. We received no comments on the proposal or on the determination of the cost to the public. 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 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 399 airplanes in the U.S. registry. We estimate the following costs to do the inspection: Parts cost Total cost for each airplane 12 work-hours × $80 an hour = $960 .................................................................. cprice-sewell on PROD1PC66 with RULES Labor cost Not applicable .... $960 We estimate the following costs to do any necessary replacements that will be VerDate Aug<31>2005 14:28 Jun 28, 2006 Jkt 208001 required based on the results of the inspection. We have no way of PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Total cost on U.S. operators $960 × 399 = $383,040 determining the number of airplanes that may need this replacement: E:\FR\FM\29JNR1.SGM 29JNR1 Federal Register / Vol. 71, No. 125 / Thursday, June 29, 2006 / Rules and Regulations Total cost for each airplane to replace all 8 wing attach barrel nuts Labor cost Parts cost No additional labor cost. Any necessary replacements will be done at the time of inspection. $60 for each barrel nut. There are 8 barrel nuts on each airplane. Possible total cost of: $60 × 8 = $480. 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 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–2006–23578; Directorate Identifier 2006–CE–01–AD’’ in your request. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 36985 $480 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 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: 2006–13–15 Mitsubishi Heavy Industries, Ltd.: Amendment 39–14668; Docket No. FAA–2006–23578; Directorate Identifier 2006–CE–01–AD. Effective Date (a) This AD becomes effective on August 11, 2006. Affected ADs (b) None. Applicability (c) This AD affects the following airplane models and serial numbers that are certificated in any category: Serial Nos. MU–2B–10 ................................................................................................................ MU–2B–15 ................................................................................................................ MU–2B–20 ................................................................................................................ MU–2B–25 ................................................................................................................ MU–2B–26 ................................................................................................................ MU–2B–26A .............................................................................................................. MU–2B–30 ................................................................................................................ MU–2B–35 ................................................................................................................ MU–2B–36 ................................................................................................................ MU–2B–36A .............................................................................................................. MU–2B–40 ................................................................................................................ MU–2B–60 ................................................................................................................ cprice-sewell on PROD1PC66 with RULES Model 101 through 120 (Except 102, 114, 115, and 118). 114, 115, and 118. 102, and 121 through 238. 239 through 318 (Except 313), and 313SA. 319 through 347 (Except 321), and 349SA. 321SA, 348SA, and 350SA through 394SA (Except 365SA). 502 through 547. 548 through 654 (Except 652), and 652SA. 501, and 655 through 696 (Except 661). 661SA, and 697SA through 730SA (Except 700SA). 365SA. 700SA. Unsafe Condition (d) This AD results from a recent safety evaluation that used a data-driven approach to evaluate 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 to VerDate Aug<31>2005 14:28 Jun 28, 2006 Jkt 208001 identify 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 cracks, corrosion, fractures, and incorrect torque values in the wing attach barrel nuts, which could result in failure of the wing attach barrel nuts and/or associated wing PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 attachment hardware. This failure could lead to in-flight separation of the outer wing from the center wing section and result in loss of controlled flight. Compliance (e) To address this problem, you must do the following, unless already done: E:\FR\FM\29JNR1.SGM 29JNR1 36986 Federal Register / Vol. 71, No. 125 / Thursday, June 29, 2006 / Rules and Regulations Actions Compliance Procedures (1) Remove each wing attach barrel nut, bolt, and retainer and do a visual inspection for cracks, corrosion, and fractures. Within the next 200 hours time-in-service or 12 months after August 11, 2006 (the effective detailed date of this AD), whichever occurs first, unless already done. (2) If any signs of cracks, corrosion, or fractures are found on any wing attach barrel nut during the inspection required in paragraph (e)(1) of this AD, replace that wing attach barrel nut, bolt, and retainer with new parts and install to the correct torque value. (3) If no signs of cracks, corrosion, or fractures are found during the inspection required in paragraph (e)(1) of this AD, you may reuse the wing attach barrel nuts and bolts if they have been inspected and are free of deformation and irregularities in the threads and meet the minimum breakaway torque requirement. Reinstall inspected parts to the correct torque value. If the wing attach barrel nuts and bolts are not free of deformation and irregularities in the threads or do not meet the minimum breakaway torque requirement, install new parts to the correct torque value. Before further flight after the inspection required in paragraph (e)(1) of this AD, unless already done. Follow Mitsubishi Heavy Industries, Ltd. MU–2 Service Bulletins referenced as JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57–004A, dated March 10, 2006, as applicable. Follow Mitsubishi Heavy Industries, Ltd. MU–2 Service Bulletins referenced as JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57–004A, dated March 10, 2006, as applicable, and the appropriate maintenance manual. Follow Mitsubishi Heavy Industries, Ltd. MU–2 Service Bulletins referenced as JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57–004A, dated March 10, 2006, as applicable, and the appropriate maintenance manual. Alternative Methods of Compliance (AMOCs) (f) 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; facsimile: (210) 308–3370, has the authority to approve alternative methods of compliance for this AD, if requested using the procedures found in 14 CFR 39.19. cprice-sewell on PROD1PC66 with RULES Related Information (g) Mitsubishi Heavy Industries, Ltd. MU– 2 Service Bulletins JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57– 004A, dated March 10, 2006, pertain to the subject of this AD. Material Incorporated by Reference (h) You must do the actions required by this AD following Mitsubishi Heavy Industries, Ltd. MU–2 Service Bulletins referenced as JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57–004A, pages 1 and 4 dated March 10, 2006, pages 2, 3, 5, 6, and 7 dated August 2, 2004. 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 95001; telephone: (972) 934–5480; fax: (972) 934– 5488, or Turbine Aircraft Services, Inc., 4550 Jimmy Doolittle Drive, Addison, Texas 75001; telephone: (972) 248–3108; facsimile: (972) 248–3321. 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 VerDate Aug<31>2005 14:28 Jun 28, 2006 Jkt 208001 Before further flight after the inspection required in paragraph (e)(1) of this AD, unless already done. 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– 2006–23578; Directorate Identifier 2006–CE– 01–AD. Issued in Kansas City, Missouri, on June 19, 2006. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–5653 Filed 6–28–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HEALTH AND HUMAN SERVICES Food and Drug Administration 21 CFR Parts 1 and 11 [Docket No. 2005D–0356] Guidance for Industry: Questions and Answers Regarding the Final Rule on Establishment and Maintenance of Records (Edition 3); Availability AGENCY: Food and Drug Administration, HHS. Notice of availability of guidance. ACTION: SUMMARY: The Food and Drug Administration (FDA) is announcing the availability of a guidance entitled ‘‘Questions and Answers Regarding Establishment and Maintenance of Records (Edition 3).’’ The guidance responds to various questions raised about section 306 of the Public Health PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Security and Bioterrorism Preparedness and Response Act of 2002 (the Bioterrorism Act) and the agency’s implementing regulation, which requires the establishment and maintenance of records by persons who manufacture, process, pack, transport, distribute, receive, hold, or import food in the United States. Such records are to allow for the identification of the immediate previous sources and the immediate subsequent recipients of food. Persons covered by the regulation who employ 500 or more full-time equivalent employees (FTEs) had to be in compliance by December 9, 2005, and those who employ 11-499 FTEs had to be in compliance by June 9, 2006. Persons who employ 10 or fewer FTEs have until December 11, 2006 to be in compliance. ‘‘Person’’ includes an individual, partnership, corporation, and association. DATES: Submit written or electronic comments on the agency guidance at any time. ADDRESSES: You may submit comments, identified by Docket No. 2005D–0356, by any of the following methods: Electronic Submissions Submit electronic comments in the following ways: • Federal eRulemaking Portal: https:// www.regulations.gov. Follow the instructions for submitting comments. • Agency Web site: https:// www.fda.gov/dockets/ecomments. Follow the instructions for submitting comments on the agency Web site. Written Submissions Submit written submissions in the following ways: E:\FR\FM\29JNR1.SGM 29JNR1

Agencies

[Federal Register Volume 71, Number 125 (Thursday, June 29, 2006)]
[Rules and Regulations]
[Pages 36984-36986]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5653]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23578; Directorate Identifier 2006-CE-01-AD; 
Amendment 39-14668; AD 2006-13-15]
RIN 2120-AA64


Airworthiness Directives; Mitsubishi Heavy Industries 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 all 
Mitsubishi Heavy Industries MU-2B series airplanes. This AD requires 
you to do the following: Remove and visually inspect the wing attach 
barrel nuts, bolts, and retainers for cracks, corrosion, and fractures; 
replace any cracked, corroded, or fractured parts; inspect reusable 
wing attach barrel nuts and bolts for deformation and irregularities in 
the threads; check the minimum breakaway torque of reused wing attach 
barrel nuts; replace any deformed or irregular parts; and install new 
or reusable parts and torque to the correct value. This AD results from 
a recent safety evaluation that used a data-driven approach to evaluate 
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 cracks, corrosion, fractures, and incorrect torque values in 
the wing attach barrel nuts, which could result in failure of the wing 
barrel nuts and/or associated wing attachment hardware. This failure 
could lead to in-flight separation of the outer wing from the center 
wing section and result in loss of controlled flight.

DATES: This AD becomes effective on August 11, 2006.
    As of August 11, 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 
Mitsubishi Heavy Industries America, Inc., 4951 Airport Parkway, Suite 
800, Addison, Texas 95001; telephone: (972) 934-5480; fax: (972) 934-
5488, or Turbine Aircraft Services, Inc., 4550 Jimmy Doolittle Drive, 
Addison, Texas 75001; telephone: (972) 248-3108; facsimile: (972) 248-
3321.
    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-2006-23578; Directorate 
Identifier 2006-CE-01-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; facsimile: (210) 308-3370.

SUPPLEMENTARY INFORMATION:

Discussion

    On April 18, 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 Mitsubishi Heavy Industries MU-2B series airplanes. 
This proposal was published in the Federal Register as a supplemental 
notice of proposed rulemaking (NPRM) on April 24, 2006 (71 FR 20915). 
We issued the supplemental NPRM to incorporate revised manufacturer 
service information that adds airplanes to the applicability, revises 
the serial numbers of the affected airplanes, and updates the 
manufacturer's contact information. The supplemental NPRM proposed to 
require you to do the following:
     Remove and visually inspect the wing attach barrel nuts, 
bolts, and retainers for cracks, corrosion, and fractures;
     Replace any cracked, corroded, or fractured wing attach 
barrel nuts, bolts, and retainers with new parts;
     Inspect reusable wing attach barrel nuts and bolts for 
deformation and irregularities in the threads;
     Check the minimum breakaway torque of reused wing attach 
barrel nuts;
     Replace any deformed or irregular wing attach barrel nuts 
or bolts with new parts; and
     Install new or reusable parts and torque to the correct 
value.

Comments

    We provided the public the opportunity to participate in developing 
this AD. We received no comments on the proposal or on the 
determination of the cost to the public.

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 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 399 airplanes in the U.S. 
registry.
    We estimate the following costs to do the inspection:

----------------------------------------------------------------------------------------------------------------
                                                             Total cost for
           Labor cost                    Parts cost          each airplane       Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
12 work-hours x $80 an hour =     Not applicable..........            $960   $960 x 399 = $383,040
 $960.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that will be required based on the results of the inspection. We have 
no way of determining the number of airplanes that may need this 
replacement:

[[Page 36985]]



------------------------------------------------------------------------
                                                        Total cost for
                                                       each airplane to
          Labor cost                 Parts cost       replace all 8 wing
                                                      attach barrel nuts
------------------------------------------------------------------------
No additional labor cost. Any  $60 for each barrel                 $480
 necessary replacements will    nut. There are 8
 be done at the time of         barrel nuts on each
 inspection.                    airplane. Possible
                                total cost of: $60 x
                                8 = $480.
------------------------------------------------------------------------

    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 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-2006-23578; Directorate Identifier 2006-CE-01-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 the following new AD:

2006-13-15 Mitsubishi Heavy Industries, Ltd.: Amendment 39-14668; 
Docket No. FAA-2006-23578; Directorate Identifier 2006-CE-01-AD.

Effective Date

    (a) This AD becomes effective on August 11, 2006.

Affected ADs

    (b) None.

Applicability

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

----------------------------------------------------------------------------------------------------------------
              Model                                                 Serial Nos.
----------------------------------------------------------------------------------------------------------------
MU-2B-10.........................  101 through 120 (Except 102, 114, 115, and 118).
MU-2B-15.........................  114, 115, and 118.
MU-2B-20.........................  102, and 121 through 238.
MU-2B-25.........................  239 through 318 (Except 313), and 313SA.
MU-2B-26.........................  319 through 347 (Except 321), and 349SA.
MU-2B-26A........................  321SA, 348SA, and 350SA through 394SA (Except 365SA).
MU-2B-30.........................  502 through 547.
MU-2B-35.........................  548 through 654 (Except 652), and 652SA.
MU-2B-36.........................  501, and 655 through 696 (Except 661).
MU-2B-36A........................  661SA, and 697SA through 730SA (Except 700SA).
MU-2B-40.........................  365SA.
MU-2B-60.........................  700SA.
----------------------------------------------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from a recent safety evaluation that used a 
data-driven approach to evaluate 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 to identify 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 cracks, corrosion, fractures, and incorrect torque 
values in the wing attach barrel nuts, which could result in failure 
of the wing attach barrel nuts and/or associated wing attachment 
hardware. This failure could lead to in-flight separation of the 
outer wing from the center wing section and result in loss of 
controlled flight.

Compliance

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

[[Page 36986]]



------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Remove each wing attach   Within the next 200   Follow Mitsubishi
 barrel nut, bolt, and         hours time-in-        Heavy Industries,
 retainer and do a visual      service or 12         Ltd. MU-2 Service
 inspection for cracks,        months after August   Bulletins
 corrosion, and fractures.     11, 2006 (the         referenced as JCAB
                               effective detailed    T.C.: No. 241,
                               date of this AD),     dated July 14,
                               whichever occurs      2004, and FAA T.C.:
                               first, unless         No. 103/57-004A,
                               already done.         dated March 10,
                                                     2006, as
                                                     applicable.
(2) If any signs of cracks,   Before further        Follow Mitsubishi
 corrosion, or fractures are   flight after the      Heavy Industries,
 found on any wing attach      inspection required   Ltd. MU-2 Service
 barrel nut during the         in paragraph (e)(1)   Bulletins
 inspection required in        of this AD, unless    referenced as JCAB
 paragraph (e)(1) of this      already done.         T.C.: No. 241,
 AD, replace that wing                               dated July 14,
 attach barrel nut, bolt,                            2004, and FAA T.C.:
 and retainer with new parts                         No. 103/57-004A,
 and install to the correct                          dated March 10,
 torque value.                                       2006, as
                                                     applicable, and the
                                                     appropriate
                                                     maintenance manual.
(3) If no signs of cracks,    Before further        Follow Mitsubishi
 corrosion, or fractures are   flight after the      Heavy Industries,
 found during the inspection   inspection required   Ltd. MU-2 Service
 required in paragraph         in paragraph (e)(1)   Bulletins
 (e)(1) of this AD, you may    of this AD, unless    referenced as JCAB
 reuse the wing attach         already done.         T.C.: No. 241,
 barrel nuts and bolts if                            dated July 14,
 they have been inspected                            2004, and FAA T.C.:
 and are free of deformation                         No. 103/57-004A,
 and irregularities in the                           dated March 10,
 threads and meet the                                2006, as
 minimum breakaway torque                            applicable, and the
 requirement. Reinstall                              appropriate
 inspected parts to the                              maintenance manual.
 correct torque value. If
 the wing attach barrel nuts
 and bolts are not free of
 deformation and
 irregularities in the
 threads or do not meet the
 minimum breakaway torque
 requirement, install new
 parts to the correct torque
 value.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (f) 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; facsimile: (210) 308-3370, has the authority to 
approve alternative methods of compliance for this AD, if requested 
using the procedures found in 14 CFR 39.19.

Related Information

    (g) Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletins 
JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57-
004A, dated March 10, 2006, pertain to the subject of this AD.

Material Incorporated by Reference

    (h) You must do the actions required by this AD following 
Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletins referenced 
as JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/
57-004A, pages 1 and 4 dated March 10, 2006, pages 2, 3, 5, 6, and 7 
dated August 2, 2004. 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 
95001; telephone: (972) 934-5480; fax: (972) 934-5488, or Turbine 
Aircraft Services, Inc., 4550 Jimmy Doolittle Drive, Addison, Texas 
75001; telephone: (972) 248-3108; facsimile: (972) 248-3321. 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 20590-001 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2006-23578; Directorate 
Identifier 2006-CE-01-AD.

    Issued in Kansas City, Missouri, on June 19, 2006.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-5653 Filed 6-28-06; 8:45 am]
BILLING CODE 4910-13-P
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