FR Doc 06-5653

[Federal Register: June 29, 2006 (Volume 71, Number 125)]
[Rules and Regulations]
[Page 36984-36986]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29jn06-3]

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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.

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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 http://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: http://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

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Model Serial Nos.
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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: http://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 http://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]

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