Airworthiness Directives; Mitsubishi Heavy Industries MU-2B Series Airplanes, 4072-4075 [E6-912]
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Federal Register / Vol. 71, No. 16 / Wednesday, January 25, 2006 / Proposed Rules
certification basis of the airplane, and the
approval must specifically refer to this AD.
Issued in Renton, Washington, on January
17, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–903 Filed 1–24–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23578; Directorate
Identifier 2006–CE–01–AD]
RIN 2120–AA64
Airworthiness Directives; Mitsubishi
Heavy Industries MU–2B Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
cprice-sewell on PROD1PC66 with PROPOSALS
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for all
Mitsubishi Heavy Industries (MHI) MU–
2B series airplanes. This proposed AD
would 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 parts; inspect reusable barrel
nuts and bolts for deformation and
irregularities in the threads; replace any
deformed or irregular parts; and install
new or reusable parts and torque to the
correct value. This proposed 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 to ensure
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 proposed
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: We must receive comments on
this proposed AD by February 27, 2006.
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15:04 Jan 24, 2006
Jkt 208001
Use one of the following
addresses to comment on this proposed
AD:
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: 1–202–493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Mitsubishi Heavy Industries,
Ltd., Nagoya Aerospace Systems Works,
10, OYE–CHO, Minato-Ku, Nagoya,
Japan, or Turbine Aircraft Services, Inc.,
4550 Jimmy Doolittle Drive, Addison,
Texas 75001; telephone: (972) 248–
3108; facsimile: (972) 248–3321, for the
service information identified in this
proposed AD.
You may examine the comments on
this proposed AD in the AD docket on
the Internet at https://dms.dot.gov.
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:
ADDRESSES:
Comments Invited
How do I comment on this proposed
AD? We invite you to send any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include the docket number,
‘‘FAA–2006–23578; Directorate
Identifier 2006–CE–01–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed
rulemaking. Using the search function
of the DOT docket web site, anyone can
find and read the comments received
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into any of our dockets, including the
name of the individual who sent the
comment (or signed the comment on
behalf of an association, business, labor
union, etc.). You may review the DOT’s
complete Privacy Act Statement in the
Federal Register published on April 11,
2000 (65 FR 19477–78) or you may visit
https://dms.dot.gov.
Examining the Dockets
Where can I go to view the docket
information? You may examine the
docket that contains the proposal, any
comments received and any final
disposition on the Internet at https://
dms.dot.gov, or in person at the DOT
Docket Offices between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket Office
(telephone 1–800–647–5227) is located
on the plaza level of the Department of
Transportation NASSIF Building at the
street address stated in ADDRESSES.
Comments will be available in the AD
docket shortly after the Docket
Management Facility receives them.
Discussion
What events have caused this
proposed AD? Recent accidents and the
service history of the Mitsubishi MU–2B
series airplanes prompted FAA to
conduct an MU–2B Safety Evaluation.
This evaluation used a data-driven
approach to evaluate the design,
operation, and maintenance of MU–2B
series airplanes in order to determine
their safety and define what steps, if
any, are necessary to ensure their safe
operation.
The safety evaluation provided an indepth review and analysis of MU–2B
incidents, accidents, safety data, pilot
training requirements, engine reliability,
and commercial operations. In
conducting this evaluation, the team
employed new analysis tools that
provided a much more detailed root
cause analysis of the MU–2B problems
than was previously possible.
Part of that evaluation was to identify
unsafe conditions that exist or could
develop on the affected type design
airplanes. One of these conditions is the
discovery of the right wing upper
forward and lower forward barrel nuts
found cracked during a scheduled
7,500-hour inspection on one of the
affected airplanes. The manufacturer
conducted additional investigations of
the barrel nuts on other affected
airplanes. The result of this
investigation revealed no other cracked
barrel nuts. However, it was discovered
that several airplanes had over-torqued
barrel nuts, which could result in
cracking.
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What is the potential impact if FAA
took no action? This condition, if not
detected and corrected, 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.
Relevant Service Information
Is there service information that
applies to this subject? We have
reviewed Mitsubishi Heavy Industries,
Ltd. MU–2 Service Bulletin referenced
as JCAB T.C.: No. 241, dated July 14,
2004, and MU–2 Service Bulletin
referenced as FAA T.C.: No. 103/57–
004, dated August 2, 2004.
What are the provisions of this service
information? These service bulletins
describe procedures for:
• Removing and inspecting the wing
attach barrel nuts and retainer for
cracks, corrosion, and fractures;
• Replacing any wing attach barrel
nuts and retainer with cracks, corrosion,
or fractures;
• Inspecting any bolts or barrel nuts
to be reused for deformation or
irregularities in the threads;
• Replacing any bolts or barrel nuts
with deformation or irregularities in the
threads; and
Type certificate
A10SW ...................
A2PC ......................
• Reinstalling the wing attach barrel
nuts and hardware to the correct torque
value.
Since Japan is the State of Design for
the affected airplanes on one of the two
type certificates, did the Japan Civil
Airworthiness Board (JCAB) take any
action? The MU–2B series airplane was
initially certificated in 1965 and again
in 1976 under two separate type
certificates that consist of basically the
same type design. Japan is the State of
Design for TC No. A2PC, and the United
States is the State of Design for TC No.
A10SW. The affected models are as
follows (where models are duplicated,
specific serial numbers are specified in
the individual TCs):
Affected models
MU–2B–25, MU–2B–26, MU–2B–26A, MU–2B–35, MU–2B–36, MU–2B–36A, MU–2B–40, and MU–2B–60.
MU–2B, MU–2B–10, MU–2B–15, MU–2B–20, MU–2B–25, MU–2B–26, MU–2B–30, MU–2B–35, and MU–2B–36.
The JCAB approved Mitsubishi Heavy
Industries, Ltd. MU–2 Service Bulletin
referenced as JCAB T.C.: No. 241, dated
July 14, 2004, and MU–2 Service
Bulletin referenced FAA T.C.: No. 103/
57–004, dated August 2, 2004, to ensure
the continued airworthiness of these
airplanes in Japan.
FAA’s Determination and Requirements
of the Proposed AD
Why have we determined AD action is
necessary and what would this
proposed AD require? We are proposing
this AD to address an unsafe condition
that we determined is likely to exist or
develop on other products of this same
type design. This proposed AD would
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 barrel nuts and
bolts for deformation and irregularities
in the threads; 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.
This proposed AD would require you
to use the service information described
previously to perform these actions.
Costs of Compliance
How many airplanes would this
proposed AD impact? We estimate that
this proposed AD affects 397 airplanes
in the U.S. registry.
What would be the cost impact of this
proposed AD on owners/operators of the
affected airplanes? We estimate the
following costs to do the proposed
inspection:
Labor cost
Parts cost
Total cost per
airplane
1 work hour × $65 per hour = $65 ...............................................................................
N/A ...........
$65
We estimate the following costs to do
any necessary replacements that would
be required based on the results of the
proposed inspection. We have no way of
cprice-sewell on PROD1PC66 with PROPOSALS
11 work hours × $65 per hour = $715 .............................
$60 for each barrel nut. There are 8 barrel nuts on
each airplane.
Possible total cost of: $60 × 8 = $480.
15:04 Jan 24, 2006
Jkt 208001
Authority for This Rulemaking
What authority does FAA have for
issuing this rulemaking action? 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.
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$65 × 397 = $25,805.
Total cost per airplane to
replace all 8 barrel nuts
Parts cost
Are there other actions that FAA is
issuing that would present a cost impact
on the MU–2B series airplane fleet? This
is one of several actions that FAA is
evaluating for unsafe conditions on the
MU–2B airplanes. To date, this is the
first proposed AD action to be taken.
Total cost on U.S.
operators
determining the number of airplanes
that may need this replacement:
Labor cost
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$715 + $480 = $1,195.
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
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Federal Register / Vol. 71, No. 16 / Wednesday, January 25, 2006 / Proposed Rules
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 rulemaking
action.
Regulatory Findings
Would this proposed AD impact
various entities? We have determined
that this proposed AD would not have
federalism implications under Executive
Order 13132. This proposed AD would
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 the proposed regulation:
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 regulatory evaluation
of the estimated costs to comply with
this proposed AD. See the ADDRESSES
section for a location to examine the
regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
proposes to amend 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Model
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Mitsubishi Heavy Industries, Ltd.: Docket
No. FAA–2006–23578; Directorate
Identifier 2006–CE–01–AD.
When Is the Last Date I Can Submit
Comments on This Proposed AD?
(a) The FAA must receive comments on
this AD action by February 27, 2006.
What Other ADs Are Affected by This
Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects the following
Mitsubishi Heavy Industries, Ltd. airplane
models and serial numbers that are
certificated in any category:
Serial numbers
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 ................................
101 through 347 (Except 313 and 321).
101 through 347 (Except 313 and 321).
101 through 347 (Except 313 and 321).
101 through 347 (Except 313 and 321), 313SA,
101 through 347 (Except 313 and 321), 313SA,
313SA, 321SA, and 348SA through 394SA.
501 through 696 (Except 652 and 661).
501 through 696 (Except 652 and 661), 652SA,
501 through 696 (Except 652 and 661), 652SA,
652SA, 661SA, and 697SA through 730SA.
What Is the Unsafe Condition Presented in
This AD?
(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 to ensure
321SA, and 348SA through 394SA.
321SA, and 348SA through 394SA.
661SA, and 697SA through 730SA.
661SA, and 697SA through 730SA.
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 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.
What Must I Do To Address This Problem?
(e) To address this problem, you must do
the following, unless already done:
Compliance
Procedures
(1) Remove each wing attach barrel nut, bolt,
and retainer and do a detailed visual inspection for cracks, corrosion, and fractures.
Within the next 200 hours time-in-service
(TIS) or 12 months after the effective 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.
cprice-sewell on PROD1PC66 with PROPOSALS
Actions
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. 103/57–004, dated August 2,
2004, 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. 103/57–004, dated August 2,
2004, as applicable, and the appropriate
maintenance manual.
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15:04 Jan 24, 2006
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Actions
Compliance
Procedures
(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 barrel nuts and bolts if they have been inspected and are free of deformation and
irregularities in the threads. Reinstall inspected parts to the correct torque value. If
the barrel nuts and bolts are not free of deformation and irregularities in the threads, 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. 103/57–004, dated August 2,
2004, as applicable, and the appropriate
maintenance manual.
May I Request an Alternative Method of
Compliance?
DEPARTMENT OF TRANSPORTATION
(f) The Manager, Fort Worth Airplane
Certification Office, FAA, has the authority to
approve alternative methods of compliance
for this AD, if requested using the procedures
found in 14 CFR 39.19.
(g) For information on any already
approved alternative methods of compliance
or for information pertaining to this AD,
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.
Federal Aviation Administration
Is There Other Information That Relates to
This Subject?
(h) Mitsubishi Heavy Industries, Ltd. MU–
2 Service Bulletins JCAB T.C.: No. 241, dated
July 14, 2004, and FAA T.C.: No. 103/57–004,
dated August 2, 2004, pertain to the subject
of this AD.
May I Get Copies of the Documents
Referenced in This AD?
(i) To get copies of the documents
referenced in this AD, contact Mitsubishi
Heavy Industries, Ltd., Nagoya Aerospace
Systems Works, 10, OYE–CHO, Minato-Ku,
Nagoya, Japan, 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, or on the
Internet at https://dms.dot.gov. The docket
number is Docket No. FAA–2006–23578;
Directorate Identifier 2006–CE–01–AD.
cprice-sewell on PROD1PC66 with PROPOSALS
Issued in Kansas City, Missouri, on January
19, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–912 Filed 1–24–06; 8:45 am]
BILLING CODE 4910–13–P
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Jkt 208001
14 CFR Part 39
[Docket No. FAA–2006–23674; Directorate
Identifier 2005–NM–234–AD]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB–120, –120ER,
–120FC, –120QC, and –120RT
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Empresa Brasileira de
Aeronautica S.A. (EMBRAER) Model
EMB–120, –120ER, –120FC, –120QC,
and –120RT airplanes. This proposed
AD would require a one-time inspection
of the interior of the internal elevator
torque tube of each elevator control
surface for oxidation and corrosion, and
corrective actions. This proposed AD
results from corrosion in torque tubes of
the elevators found during scheduled
maintenance. We are proposing this AD
to detect and correct corrosion in the
torque tubes of the elevators, which
could lead to an unbalanced elevator
and result in reduced controllability of
the airplane.
DATES: We must receive comments on
this proposed AD by February 24, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
PO 00000
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Seventh Street, SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Empresa Brasileira de
Aeronautica S.A. (EMBRAER), P.O. Box
343—CEP 12.225, Sao Jose dos
Campos—SP, Brazil, for service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–1175;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2006–23674; Directorate
Identifier 2005–NM–234–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
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]]>Agencies
[Federal Register Volume 71, Number 16 (Wednesday, January 25, 2006)]
[Proposed Rules]
[Pages 4072-4075]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-912]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23578; Directorate Identifier 2006-CE-01-AD]
RIN 2120-AA64
Airworthiness Directives; Mitsubishi Heavy Industries MU-2B
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Mitsubishi Heavy Industries (MHI) MU-2B series airplanes. This
proposed AD would 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
parts; inspect reusable barrel nuts and bolts for deformation and
irregularities in the threads; replace any deformed or irregular parts;
and install new or reusable parts and torque to the correct value. This
proposed 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 to ensure 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 proposed 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: We must receive comments on this proposed AD by February 27,
2006.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD:
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: 1-202-493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Mitsubishi Heavy Industries, Ltd., Nagoya Aerospace Systems
Works, 10, OYE-CHO, Minato-Ku, Nagoya, Japan, or Turbine Aircraft
Services, Inc., 4550 Jimmy Doolittle Drive, Addison, Texas 75001;
telephone: (972) 248-3108; facsimile: (972) 248-3321, for the service
information identified in this proposed AD.
You may examine the comments on this proposed AD in the AD docket
on the Internet at https://dms.dot.gov.
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:
Comments Invited
How do I comment on this proposed AD? We invite you to send any
written relevant data, views, or arguments regarding this proposal.
Send your comments to an address listed under ADDRESSES. Include the
docket number, ``FAA-2006-23578; Directorate Identifier 2006-CE-01-AD''
at the beginning of your comments. We specifically invite comments on
the overall regulatory, economic, environmental, and energy aspects of
the proposed AD. We will consider all comments received by the closing
date and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed rulemaking. Using the search
function of the DOT docket web site, anyone can find and read the
comments received into any of our dockets, including the name of the
individual who sent the comment (or signed the comment on behalf of an
association, business, labor union, etc.). You may review the DOT's
complete Privacy Act Statement in the Federal Register published on
April 11, 2000 (65 FR 19477-78) or you may visit https://dms.dot.gov.
Examining the Dockets
Where can I go to view the docket information? You may examine the
docket that contains the proposal, any comments received and any final
disposition on the Internet at https://dms.dot.gov, or in person at the
DOT Docket Offices between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Office (telephone 1-800-647-5227)
is located on the plaza level of the Department of Transportation
NASSIF Building at the street address stated in ADDRESSES. Comments
will be available in the AD docket shortly after the Docket Management
Facility receives them.
Discussion
What events have caused this proposed AD? Recent accidents and the
service history of the Mitsubishi MU-2B series airplanes prompted FAA
to conduct an MU-2B Safety Evaluation. This evaluation used a data-
driven approach to evaluate the design, operation, and maintenance of
MU-2B series airplanes in order to determine their safety and define
what steps, if any, are necessary to ensure their safe operation.
The safety evaluation provided an in-depth review and analysis of
MU-2B incidents, accidents, safety data, pilot training requirements,
engine reliability, and commercial operations. In conducting this
evaluation, the team employed new analysis tools that provided a much
more detailed root cause analysis of the MU-2B problems than was
previously possible.
Part of that evaluation was to identify unsafe conditions that
exist or could develop on the affected type design airplanes. One of
these conditions is the discovery of the right wing upper forward and
lower forward barrel nuts found cracked during a scheduled 7,500-hour
inspection on one of the affected airplanes. The manufacturer conducted
additional investigations of the barrel nuts on other affected
airplanes. The result of this investigation revealed no other cracked
barrel nuts. However, it was discovered that several airplanes had
over-torqued barrel nuts, which could result in cracking.
[[Page 4073]]
What is the potential impact if FAA took no action? This condition,
if not detected and corrected, 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.
Relevant Service Information
Is there service information that applies to this subject? We have
reviewed Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletin
referenced as JCAB T.C.: No. 241, dated July 14, 2004, and MU-2 Service
Bulletin referenced as FAA T.C.: No. 103/57-004, dated August 2, 2004.
What are the provisions of this service information? These service
bulletins describe procedures for:
Removing and inspecting the wing attach barrel nuts and
retainer for cracks, corrosion, and fractures;
Replacing any wing attach barrel nuts and retainer with
cracks, corrosion, or fractures;
Inspecting any bolts or barrel nuts to be reused for
deformation or irregularities in the threads;
Replacing any bolts or barrel nuts with deformation or
irregularities in the threads; and
Reinstalling the wing attach barrel nuts and hardware to
the correct torque value.
Since Japan is the State of Design for the affected airplanes on
one of the two type certificates, did the Japan Civil Airworthiness
Board (JCAB) take any action? The MU-2B series airplane was initially
certificated in 1965 and again in 1976 under two separate type
certificates that consist of basically the same type design. Japan is
the State of Design for TC No. A2PC, and the United States is the State
of Design for TC No. A10SW. The affected models are as follows (where
models are duplicated, specific serial numbers are specified in the
individual TCs):
------------------------------------------------------------------------
Type certificate Affected models
------------------------------------------------------------------------
A10SW................................ MU-2B-25, MU-2B-26, MU-2B-26A, MU-
2B-35, MU-2B-36, MU-2B-36A, MU-
2B-40, and MU-2B-60.
A2PC................................. MU-2B, MU-2B-10, MU-2B-15, MU-2B-
20, MU-2B-25, MU-2B-26, MU-2B-
30, MU-2B-35, and MU-2B-36.
------------------------------------------------------------------------
The JCAB approved Mitsubishi Heavy Industries, Ltd. MU-2 Service
Bulletin referenced as JCAB T.C.: No. 241, dated July 14, 2004, and MU-
2 Service Bulletin referenced FAA T.C.: No. 103/57-004, dated August 2,
2004, to ensure the continued airworthiness of these airplanes in
Japan.
FAA's Determination and Requirements of the Proposed AD
Why have we determined AD action is necessary and what would this
proposed AD require? We are proposing this AD to address an unsafe
condition that we determined is likely to exist or develop on other
products of this same type design. This proposed AD would 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 barrel nuts and bolts for deformation and
irregularities in the threads; 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.
This proposed AD would require you to use the service information
described previously to perform these actions.
Costs of Compliance
How many airplanes would this proposed AD impact? We estimate that
this proposed AD affects 397 airplanes in the U.S. registry.
What would be the cost impact of this proposed AD on owners/
operators of the affected airplanes? We estimate the following costs to
do the proposed inspection:
----------------------------------------------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work hour x $65 per hour = $65.. N/A................ $65 $65 x 397 = $25,805.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed inspection.
We have no way of determining the number of airplanes that may need
this replacement:
----------------------------------------------------------------------------------------------------------------
Total cost per airplane to replace all 8
Labor cost Parts cost barrel nuts
----------------------------------------------------------------------------------------------------------------
11 work hours x $65 per hour = $715.. $60 for each barrel nut. $715 + $480 = $1,195.
There are 8 barrel nuts on
each airplane.
Possible total cost of: $60 x
8 = $480..
----------------------------------------------------------------------------------------------------------------
Are there other actions that FAA is issuing that would present a
cost impact on the MU-2B series airplane fleet? This is one of several
actions that FAA is evaluating for unsafe conditions on the MU-2B
airplanes. To date, this is the first proposed AD action to be taken.
Authority for This Rulemaking
What authority does FAA have for issuing this rulemaking action?
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
[[Page 4074]]
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 rulemaking action.
Regulatory Findings
Would this proposed AD impact various entities? We have determined
that this proposed AD would not have federalism implications under
Executive Order 13132. This proposed AD would 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 the proposed
regulation:
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 regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 14
CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Mitsubishi Heavy Industries, Ltd.: Docket No. FAA-2006-23578;
Directorate Identifier 2006-CE-01-AD.
When Is the Last Date I Can Submit Comments on This Proposed AD?
(a) The FAA must receive comments on this AD action by February
27, 2006.
What Other ADs Are Affected by This Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects the following Mitsubishi Heavy Industries,
Ltd. airplane models and serial numbers that are certificated in any
category:
------------------------------------------------------------------------
Model Serial numbers
------------------------------------------------------------------------
MU-2B-10..................................... 101 through 347 (Except
313 and 321).
MU-2B-15..................................... 101 through 347 (Except
313 and 321).
MU-2B-20..................................... 101 through 347 (Except
313 and 321).
MU-2B-25..................................... 101 through 347 (Except
313 and 321), 313SA,
321SA, and 348SA through
394SA.
MU-2B-26..................................... 101 through 347 (Except
313 and 321), 313SA,
321SA, and 348SA through
394SA.
MU-2B-26A.................................... 313SA, 321SA, and 348SA
through 394SA.
MU-2B-30..................................... 501 through 696 (Except
652 and 661).
MU-2B-35..................................... 501 through 696 (Except
652 and 661), 652SA,
661SA, and 697SA through
730SA.
MU-2B-36..................................... 501 through 696 (Except
652 and 661), 652SA,
661SA, and 697SA through
730SA.
MU-2B-36A.................................... 652SA, 661SA, and 697SA
through 730SA.
------------------------------------------------------------------------
What Is the Unsafe Condition Presented in This AD?
(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 to ensure
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 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.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following, unless
already done:
------------------------------------------------------------------------
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 detailed service (TIS) or 12 Ltd. MU-2 Service
visual inspection for months after the Bulletins
cracks, corrosion, and effective date of referenced as JCAB
fractures. this AD, whichever T.C.: No. 241,
occurs first, dated July 14,
unless already done. 2004, and FAA T.C.:
No. 103/57-004,
dated August 2,
2004, 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. 103/57-004,
and install to the correct dated August 2,
torque value. 2004, as
applicable, and the
appropriate
maintenance manual.
[[Page 4075]]
(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 barrel nuts and already done. T.C.: No. 241,
bolts if they have been dated July 14,
inspected and are free of 2004, and FAA T.C.:
deformation and No. 103/57-004,
irregularities in the dated August 2,
threads. Reinstall 2004, as
inspected parts to the applicable, and the
correct torque value. If appropriate
the barrel nuts and bolts maintenance manual.
are not free of deformation
and irregularities in the
threads, install new parts
to the correct torque value.
------------------------------------------------------------------------
May I Request an Alternative Method of Compliance?
(f) The Manager, Fort Worth Airplane Certification Office, FAA,
has the authority to approve alternative methods of compliance for
this AD, if requested using the procedures found in 14 CFR 39.19.
(g) For information on any already approved alternative methods
of compliance or for information pertaining to this AD, 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.
Is There Other Information That Relates to This Subject?
(h) Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletins
JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57-
004, dated August 2, 2004, pertain to the subject of this AD.
May I Get Copies of the Documents Referenced in This AD?
(i) To get copies of the documents referenced in this AD,
contact Mitsubishi Heavy Industries, Ltd., Nagoya Aerospace Systems
Works, 10, OYE-CHO, Minato-Ku, Nagoya, Japan, 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, or on the Internet at https://dms.dot.gov. The
docket number is Docket No. FAA-2006-23578; Directorate Identifier
2006-CE-01-AD.
Issued in Kansas City, Missouri, on January 19, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-912 Filed 1-24-06; 8:45 am]
BILLING CODE 4910-13-P
