Airworthiness Directives; Raytheon Aircraft Company 65, 90, 99, and 100 Series Airplanes, 36185-36187 [06-5586]
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36185
Rules and Regulations
Federal Register
Vol. 71, No. 122
Monday, June 26, 2006
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–23319; Directorate
Identifier 2005–CE–52–AD; Amendment 39–
14663; AD 2006–13–10]
RIN 2120–AA64
Airworthiness Directives; Raytheon
Aircraft Company 65, 90, 99, and 100
Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) that
supersedes AD 92–07–05, which applies
to certain Raytheon Aircraft Company
(Raytheon) (formerly Beech) 65, 90, 99,
and 100 series airplanes. AD 92–07–05
currently requires you to inspect the
rudder trim tab for proper moisture
drainage provisions, and if the correct
drainage provisions do not exist, before
further flight, modify the rudder trim
tab. This AD results from receiving and
evaluating new service information that
requires the actions of AD 92–07–05 for
the added serial numbers LJ–1281
through LJ–1732 for the Model C90A
airplanes. This AD retains all the
actions of AD 92–07–05 and adds serial
numbers LJ–1281 through LJ–1732 for
the Model C90A airplanes in the
applicability section. We are issuing this
AD to prevent water accumulation in
the rudder trim tab, which could result
in a change in the mass properties and
possibly a lower flutter speed of the
airplane. A lower airplane flutter speed
could result in failure and loss of
control of the airplane.
DATES: This AD becomes effective on
August 7, 2006.
As of August 7, 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 Raytheon
Aircraft Company, P.O. Box 85, Wichita,
Kansas 67201–0085; telephone: (800)
429–5372 or (316) 676–3140.
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–2005–23319; Directorate Identifier
2005–CE–52–AD.
FOR FURTHER INFORMATION CONTACT:
Steven E. Potter, Aerospace Engineer,
Wichita Aircraft Certification Office,
FAA, 1801 Airport Road, Wichita,
Kansas 67209; telephone: (316) 946–
4124; facsimile: (316) 946–4107.
SUPPLEMENTARY INFORMATION:
Discussion
On January 31, 2006, we issued a
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an AD that would apply to
certain Raytheon 65, 90, 99, and 100
series airplanes. This proposal was
published in the Federal Register as a
notice of proposed rulemaking (NPRM)
on February 6, 2006 (71 FR 6025). The
NPRM proposed to supersede AD 92–
07–05, Amendment 39–8201 (57 FR
8721, March 12, 1992) and to add serial
numbers LJ–1281 through LJ–1732 for
the Model C90A airplanes in the
applicability section. This AD will
retain all the actions of AD 92–07–05 for
inspecting and modifying the rudder
trim tab for correct drainage provisions.
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 2,407
airplanes in the U.S. registry.
We estimate the following costs to do
the inspection:
Total cost per
airplane
Labor cost
Parts cost
1 work-hour × $80 = $80 ...............................................................
Not Applicable ...........................
We estimate the following costs to do
any necessary modification of the
rudder trim tab to provide the correct
drainage provisions that would be
required based on the results of this
inspection. We have no way of
$80
Total cost on U.S.
operators
2,407 × $80 = $192,560.
determining the number of airplanes
that may need this modification:
jlentini on PROD1PC65 with RULES
Labor cost
Parts cost
Total cost
per airplane
1 work-hour × $80 = $80 .........................................................................................................................................
$25
$105
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36186
Federal Register / Vol. 71, No. 122 / Monday, June 26, 2006 / Rules and Regulations
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–2005–23319;
Directorate Identifier 2005–CE–52–AD’’
in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
I
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
I 2. FAA amends § 39.13 by removing
Airworthiness Directive (AD) 92–07–05,
Amendment 39–8201 (57 FR 8721,
March 12, 1992), and by adding the
following new airworthiness directive:
2006–13–10 Raytheon Aircraft Company
(Formerly Beech): Amendment 39–
14663; Docket No. FAA–2005–23319;
Directorate Identifier 2005–CE–52–AD.
Effective Date
(a) This AD becomes effective on August 7,
2006.
Affected ADs
(b) This AD supersedes AD 92–07–05;
Amendment 39–8201.
Applicability
(c) This AD affects the following airplane
models and serial numbers that are
certificated in any category:
(1) Group 1 (maintains the actions from AD
92–07–05):
Model
Serial Nos.
(i) 65–90, 65–A90, B90, C90, and C90A .................................................
(ii) E90 ......................................................................................................
(iii) 99, 99A, A99, A99A, B99, and C99 ...................................................
(iv) 100 and A100 .....................................................................................
(v) B100 ....................................................................................................
(vi) 65–A90–1 (U–21A, JU–21A, RU–21D, RU–21H, RU–21A, U–21G)
(vii) 65–A90–2 (RU–21B) .........................................................................
(viii) 65–A90–3 (RU–21C) ........................................................................
(ix) 65–A90–4 (RU–21EA, U–21H, RU–21H) ..........................................
(x) H90 (T–44A) ........................................................................................
(xi) 99A (FACH) ........................................................................................
(xii) A100 (U–21F) ....................................................................................
(2) Group 2: Model C90A, serial numbers
LJ–1281 through LJ–1732.
Unsafe Condition
(d) This AD results from receiving and
evaluating new service information that
requires the actions of AD 92–07–05 for the
LJ–1 through LJ–1280.
LW–1 through LW–347.
U–1 through U–136 and U–146 through U–239.
B1 through B–94, B–100 through B–204, and B–206 through B247.
BE–1 through BE–137.
LM–1 through LM–141.
LS–1, LS–2, and LS–3.
LT–1 and LT–2.
LU–1 through LU–16.
LL–1 through LL–61.
U–137 through U–145.
B95 through B–99.
added serial numbers LJ–1281 through LJ–
1732 for the Model C90A airplanes. The
actions specified in this AD are intended to
prevent water accumulation in the rudder
trim tab, which could result in a change in
the mass properties and possibly a lower
flutter speed of the airplane. A lower airplane
flutter speed could result in failure and loss
of control of the airplane.
Compliance
(e) To address this problem, you must do
the following:
jlentini on PROD1PC65 with RULES
Actions
Compliance
Procedures
(1) For Group 1 Airplanes: Inspect the rudder
trim tab for proper moisture drainage provisions.
(2) For Group 1 Airplanes: If the correct drainage provisions do not exist, modify the rudder trim tab.
(3) For Group 2 Airplanes: Inspect the rudder
trim tab for proper moisture drainage provisions.
Within 150 hours time-in-service (TIS) after
April 30, 1992 (the effective date of AD 92–
07–05), unless already done.
Before further flight after the inspection required by paragraph (e)(1) of this AD.
Follow Beech Service Bulletin No. 2365, Revision 1, dated December 1991.
Within 150 hours TIS after August 7, 2006
(the effective date of this AD), unless already done.
Follow Raytheon Aircraft Company Service
Bulletin No. SB 55–2365, Revision 2,
Issued: January 1991, Revised: October
2005.
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Follow Beech Service Bulletin No. 2365, Revision 1, dated December 1991.
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Federal Register / Vol. 71, No. 122 / Monday, June 26, 2006 / Rules and Regulations
36187
Actions
Compliance
Procedures
(4) For Group 2 Airplanes: If the correct drainage provisions do not exist, modify the rudder trim tab.
Before further flight after the inspection required by paragraph (e)(3) of this AD.
Follow Raytheon Aircraft Company Service
Bulletin No. SB 55–2365, Revision 2,
Issued: January 1991, Revised: October
2005.
Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
(f) The Manager, Wichita Aircraft
Certification Office (ACO), FAA, ATTN:
Steven E. Potter, Aerospace Engineer,
Wichita ACO, FAA, 1801 Airport Road,
Wichita, Kansas 67209; telephone: (316) 946–
4124; facsimile: (316) 946–4107, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19.
(g) AMOCs approved for AD 92–07–05 are
not approved for this AD.
Federal Aviation Administration
Material Incorporated by Reference
AGENCY:
(h) You must do the actions required by
this AD following the instructions in
Beechcraft Mandatory Service Bulletin No.
2365, Revision 1, dated December 1991, and
Raytheon Aircraft Company Service Bulletin
No. SB 55–2365, Revision 2, Issued: January
1991, Revised: October 2005. The Director of
the Federal Register approved the
incorporation by reference of these service
bulletins in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. To get a copy of this
service information, contact Raytheon
Aircraft Company, P.O. Box 85, Wichita,
Kansas 67201–0085; telephone: (800) 429–
5372 or (316) 676–3140. 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/6federal_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–
2005–23319; Directorate Identifier 2005–CE–
52–AD.
Issued in Kansas City, Missouri, on June
13, 2006.
James E. Jackson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–5586 Filed 6–23–06; 8:45 am]
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14 CFR Part 39
[Docket No. FAA–2006–25098; Directorate
Identifier 2006–SW–12–AD; Amendment 39–
14667; AD 2006–13–14]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada Model 222,
222B, 222U, 230, and 430 Helicopters
Federal Aviation
Administration, DOT.
ACTION: Final rule; request for
comments.
Examining the Docket
SUMMARY: This amendment adopts a
new airworthiness directive (AD) for the
specified Bell Helicopter Textron
Canada (BHTC) model helicopters. This
action requires initial and repetitive
inspections of each tail rotor
counterweight bellcrank (bellcrank)
with a specified part number and serial
number. If external damage, a crack,
roughness, or looseness between the
bearing set and bellcrank is found or if
bearing set axial play exceeds 0.015
inch, this action requires replacing the
bellcrank with an airworthy bellcrank
with two prefix letters in the serial
number. This amendment is prompted
by reports of failure and subsequent loss
of a weighted portion of the bellcrank
and reports of certain replacement
bellcranks having design flaws. The
actions specified in this AD are
intended to prevent bellcrank failure,
loss of a weighted portion of the
bellcrank, and subsequent loss of
control of the helicopter.
DATES: Effective July 11, 2006.
Comments for inclusion in the Rules
Docket must be received on or before
August 25, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
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
Frm 00003
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Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590;
• Fax: (202) 493–2251; or
• 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.
You may get the service information
identified in this AD from Bell
Helicopter Textron Canada, 12,800 Rue
de l’Avenir, Mirabel, Quebec J7J1R4,
telephone (450) 437–2862 or (800) 363–
8023, fax (450) 433–0272.
You may examine the docket that
contains the AD, any comments, and
other information on the Internet at
https://dms.dot.gov, or in person at the
Docket Management System (DMS)
Docket Offices between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket Office
(telephone (800) 647–5227) is located on
the plaza level of the Department of
Transportation Nassif Building at the
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the DMS
receives them.
FOR FURTHER INFORMATION CONTACT:
Sharon Miles, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations
and Guidance Group, Fort Worth, Texas
76193–0111, telephone (817) 222–5122,
fax (817) 222–5961.
SUPPLEMENTARY INFORMATION: This
amendment adopts a new AD for the
specified BHTC model helicopters. This
action requires initial and repetitive
inspections of certain bellcranks for
external damage, a crack, looseness, or
bearing set roughness by rotating each
bellcrank while applying a load to the
bearing set in both axial and radial
directions. If external damage, a crack,
roughness, or looseness between the
bearing set and bellcrank is found or if
the bearing axial play exceeds 0.015
inch, this action requires replacing the
part with an airworthy bellcrank with
two prefix letters in the serial number.
This amendment is prompted by reports
of failure and subsequent loss of a
weighted portion of the ballcrank due to
gas porosity in the casting or external
damage. Also, this amendment is
prompted by reports that certain
replacement bellcranks have an oversize
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]]>Agencies
[Federal Register Volume 71, Number 122 (Monday, June 26, 2006)]
[Rules and Regulations]
[Pages 36185-36187]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5586]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 71, No. 122 / Monday, June 26, 2006 / Rules
and Regulations
[[Page 36185]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-23319; Directorate Identifier 2005-CE-52-AD;
Amendment 39-14663; AD 2006-13-10]
RIN 2120-AA64
Airworthiness Directives; Raytheon Aircraft Company 65, 90, 99,
and 100 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) that
supersedes AD 92-07-05, which applies to certain Raytheon Aircraft
Company (Raytheon) (formerly Beech) 65, 90, 99, and 100 series
airplanes. AD 92-07-05 currently requires you to inspect the rudder
trim tab for proper moisture drainage provisions, and if the correct
drainage provisions do not exist, before further flight, modify the
rudder trim tab. This AD results from receiving and evaluating new
service information that requires the actions of AD 92-07-05 for the
added serial numbers LJ-1281 through LJ-1732 for the Model C90A
airplanes. This AD retains all the actions of AD 92-07-05 and adds
serial numbers LJ-1281 through LJ-1732 for the Model C90A airplanes in
the applicability section. We are issuing this AD to prevent water
accumulation in the rudder trim tab, which could result in a change in
the mass properties and possibly a lower flutter speed of the airplane.
A lower airplane flutter speed could result in failure and loss of
control of the airplane.
DATES: This AD becomes effective on August 7, 2006.
As of August 7, 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
Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085;
telephone: (800) 429-5372 or (316) 676-3140.
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-2005-23319; Directorate
Identifier 2005-CE-52-AD.
FOR FURTHER INFORMATION CONTACT: Steven E. Potter, Aerospace Engineer,
Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Wichita,
Kansas 67209; telephone: (316) 946-4124; facsimile: (316) 946-4107.
SUPPLEMENTARY INFORMATION:
Discussion
On January 31, 2006, we issued a proposal to amend part 39 of the
Federal Aviation Regulations (14 CFR part 39) to include an AD that
would apply to certain Raytheon 65, 90, 99, and 100 series airplanes.
This proposal was published in the Federal Register as a notice of
proposed rulemaking (NPRM) on February 6, 2006 (71 FR 6025). The NPRM
proposed to supersede AD 92-07-05, Amendment 39-8201 (57 FR 8721, March
12, 1992) and to add serial numbers LJ-1281 through LJ-1732 for the
Model C90A airplanes in the applicability section. This AD will retain
all the actions of AD 92-07-05 for inspecting and modifying the rudder
trim tab for correct drainage provisions.
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 2,407 airplanes in the U.S.
registry.
We estimate the following costs to do the inspection:
----------------------------------------------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $80 = $80............ Not Applicable....... $80 2,407 x $80 = $192,560.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary modification of
the rudder trim tab to provide the correct drainage provisions that
would be required based on the results of this inspection. We have no
way of determining the number of airplanes that may need this
modification:
------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane
------------------------------------------------------------------------
1 work-hour x $80 = $80............... $25 $105
------------------------------------------------------------------------
[[Page 36186]]
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-2005-23319; Directorate Identifier 2005-CE-52-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 removing Airworthiness Directive (AD) 92-
07-05, Amendment 39-8201 (57 FR 8721, March 12, 1992), and by adding
the following new airworthiness directive:
2006-13-10 Raytheon Aircraft Company (Formerly Beech): Amendment 39-
14663; Docket No. FAA-2005-23319; Directorate Identifier 2005-CE-52-
AD.
Effective Date
(a) This AD becomes effective on August 7, 2006.
Affected ADs
(b) This AD supersedes AD 92-07-05; Amendment 39-8201.
Applicability
(c) This AD affects the following airplane models and serial
numbers that are certificated in any category:
(1) Group 1 (maintains the actions from AD 92-07-05):
------------------------------------------------------------------------
Model Serial Nos.
------------------------------------------------------------------------
(i) 65-90, 65-A90, B90, C90, and C90A.. LJ-1 through LJ-1280.
(ii) E90............................... LW-1 through LW-347.
(iii) 99, 99A, A99, A99A, B99, and C99. U-1 through U-136 and U-146
through U-239.
(iv) 100 and A100...................... B1 through B-94, B-100 through
B-204, and B-206 through B247.
(v) B100............................... BE-1 through BE-137.
(vi) 65-A90-1 (U-21A, JU-21A, RU-21D, LM-1 through LM-141.
RU-21H, RU-21A, U-21G).
(vii) 65-A90-2 (RU-21B)................ LS-1, LS-2, and LS-3.
(viii) 65-A90-3 (RU-21C)............... LT-1 and LT-2.
(ix) 65-A90-4 (RU-21EA, U-21H, RU-21H). LU-1 through LU-16.
(x) H90 (T-44A)........................ LL-1 through LL-61.
(xi) 99A (FACH)........................ U-137 through U-145.
(xii) A100 (U-21F)..................... B95 through B-99.
------------------------------------------------------------------------
(2) Group 2: Model C90A, serial numbers LJ-1281 through LJ-1732.
Unsafe Condition
(d) This AD results from receiving and evaluating new service
information that requires the actions of AD 92-07-05 for the added
serial numbers LJ-1281 through LJ-1732 for the Model C90A airplanes.
The actions specified in this AD are intended to prevent water
accumulation in the rudder trim tab, which could result in a change
in the mass properties and possibly a lower flutter speed of the
airplane. A lower airplane flutter speed could result in failure and
loss of control of the airplane.
Compliance
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) For Group 1 Airplanes: Within 150 hours Follow Beech Service
Inspect the rudder trim tab time-in-service Bulletin No. 2365,
for proper moisture (TIS) after April Revision 1, dated
drainage provisions. 30, 1992 (the December 1991.
effective date of
AD 92-07-05),
unless already done.
(2) For Group 1 Airplanes: Before further Follow Beech Service
If the correct drainage flight after the Bulletin No. 2365,
provisions do not exist, inspection required Revision 1, dated
modify the rudder trim tab. by paragraph (e)(1) December 1991.
of this AD.
(3) For Group 2 Airplanes: Within 150 hours TIS Follow Raytheon
Inspect the rudder trim tab after August 7, Aircraft Company
for proper moisture 2006 (the effective Service Bulletin
drainage provisions. date of this AD), No. SB 55-2365,
unless already done. Revision 2, Issued:
January 1991,
Revised: October
2005.
[[Page 36187]]
(4) For Group 2 Airplanes: Before further Follow Raytheon
If the correct drainage flight after the Aircraft Company
provisions do not exist, inspection required Service Bulletin
modify the rudder trim tab. by paragraph (e)(3) No. SB 55-2365,
of this AD. Revision 2, Issued:
January 1991,
Revised: October
2005.
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Wichita Aircraft Certification Office (ACO),
FAA, ATTN: Steven E. Potter, Aerospace Engineer, Wichita ACO, FAA,
1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946-4124;
facsimile: (316) 946-4107, has the authority to approve AMOCs for
this AD, if requested using the procedures found in 14 CFR 39.19.
(g) AMOCs approved for AD 92-07-05 are not approved for this AD.
Material Incorporated by Reference
(h) You must do the actions required by this AD following the
instructions in Beechcraft Mandatory Service Bulletin No. 2365,
Revision 1, dated December 1991, and Raytheon Aircraft Company
Service Bulletin No. SB 55-2365, Revision 2, Issued: January 1991,
Revised: October 2005. The Director of the Federal Register approved
the incorporation by reference of these service bulletins in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of
this service information, contact Raytheon Aircraft Company, P.O.
Box 85, Wichita, Kansas 67201-0085; telephone: (800) 429-5372 or
(316) 676-3140. 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/6 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-2005-23319; Directorate
Identifier 2005-CE-52-AD.
Issued in Kansas City, Missouri, on June 13, 2006.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-5586 Filed 6-23-06; 8:45 am]
BILLING CODE 4910-13-P
