Airworthiness Directives; Raytheon Aircraft Company 65, 90, 99, and 100 Series Airplanes, 36185-36187 [06-5586]

Download as PDF 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 http:// 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 VerDate Aug<31>2005 15:58 Jun 23, 2006 Jkt 208001 PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 E:\FR\FM\26JNR1.SGM 26JNR1 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. VerDate Aug<31>2005 15:58 Jun 23, 2006 Jkt 208001 PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Follow Beech Service Bulletin No. 2365, Revision 1, dated December 1991. E:\FR\FM\26JNR1.SGM 26JNR1 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: http:// 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 http:// 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] jlentini on PROD1PC65 with RULES BILLING CODE 4910–13–P VerDate Aug<31>2005 15:58 Jun 23, 2006 Jkt 208001 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 http://dms.dot.gov and follow the instructions for sending your comments electronically; • Government-wide rulemaking Web site: Go to http://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 Fmt 4700 Sfmt 4700 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 http://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 E:\FR\FM\26JNR1.SGM 26JNR1

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 http://
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: 
http://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 http://
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