Airworthiness Directives; Twin Commander Aircraft Corporation Models 690, 690A, and 690B Airplanes, 40385-40387 [06-6225]

Download as PDF 40385 Rules and Regulations Federal Register Vol. 71, No. 136 Monday, July 17, 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–2006–23785; Directorate Identifier 2006–CE–10–AD; Amendment 39– 14681; AD 2006–15–01] RIN 2120–AA64 Airworthiness Directives; Twin Commander Aircraft Corporation Models 690, 690A, and 690B Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for all Twin Commander Aircraft Corporation (Twin Commander) Models 690, 690A, and 690B airplanes. This AD requires you to inspect, visually and using fluorescent dye penetrant, the support structures for the inboard and center aileron hinge fittings on both wings for cracks and replace any cracked support structure. This AD requires you to reinforce the support structures for the inboard and center aileron hinge fittings on both wings. This AD results from reports that cracks were found in the support structures for the inboard and center aileron hinge fittings on both wings. We are issuing this AD to detect and correct cracks in the support structures for the inboard and center aileron hinge fittings on both wings, which could result in aileron failure. This failure could lead to reduced controllability or loss of control of the airplane. DATES: This AD becomes effective on August 21, 2006. As of August 21, 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 Twin Commander Aircraft LLC, 19010 59th Drive Northeast, Arlington, Washington 98223, telephone: (360) 435–9797; facsimile: (360) 435–1112. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 001 or on the Internet at http:// dms.dot.gov. The docket number is FAA–2006–23785; Directorate Identifier 2006–CE–10–AD. FOR FURTHER INFORMATION CONTACT: Vince Massey, Aerospace Engineer, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, WA 98057; telephone: (425) 917–6475; facsimile: (425) 917–6590. SUPPLEMENTARY INFORMATION: Discussion On March 10, 2006, we issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to all Twin Commander Models 690, 690A, and 690B, airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on March 16, 2006 (71 FR 13558). The NPRM proposed to require you to inspect, visually and using fluorescent dye penetrant, the support structures for the inboard and center aileron hinge fittings on both wings for cracks and replace any cracked support structure. The NPRM proposed to require you to reinforce the support structures for the inboard and center aileron hinge fittings on both wings. 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 275 airplanes in the U.S. registry. We estimate the following costs to do the inspection of the support structures of the inboard aileron hinge fittings on both wings: Labor cost Parts cost 10 work-hours × $80 an hour = $800 ............................................ Not applicable ............................ We estimate the following costs to do the inspection of the support structure $800 Parts cost 12 work-hours × $80 an hour = $960 ............................................ Total cost for each airplane Not applicable ............................ VerDate Aug<31>2005 15:22 Jul 14, 2006 Jkt 208001 Total cost on U.S. operators $800 × 275 = $220,000 of the center aileron hinge fittings on both wings: Labor cost rmajette on PROD1PC67 with RULES Total cost for each airplane PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 E:\FR\FM\17JYR1.SGM $960 17JYR1 Total cost on U.S. operators $960 × 275 = $264,000 40386 Federal Register / Vol. 71, No. 136 / Monday, July 17, 2006 / Rules and Regulations We estimate the following costs to do the reinforcement to the support structures on the inboard aileron hinge fittings on both wings: Labor cost Parts cost 25 work-hours × $80 an hour = $2,000 ............................... We estimate the following costs to do the reinforcement of the support Total cost for each airplane $1,526 $2,000 + $1,526 = $3,526 .......... Parts cost 50 work-hours × $80 an hour = $4,000 ............................... Total cost for each airplane $551 Total cost on U.S. operators $4,000 + $551 = $4,551 ............. fittings on both wings that may be required based on the results of the inspection. We have no way of Parts cost 62 work-hours × $80 an hour = $4,960 .................................................................................................. both wings that may be required based on the results of the inspection. We have no way of determining the number Labor cost 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 requirement.’’ 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. rmajette on PROD1PC67 with RULES 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. VerDate Aug<31>2005 15:22 Jul 14, 2006 Jkt 208001 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 amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: I PO 00000 $2,320 Parts cost For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this AD (and other information as included in the Regulatory Evaluation) and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include ‘‘Docket No. FAA–2006–23785; Directorate Identifier 2006–CE–10–AD’’ in your request. Frm 00002 Fmt 4700 Sfmt 4700 Total cost for each airplane $4,960 + $2,320 = $7,280 of airplanes that may need this replacement. 176 work-hours × $80 an hour = $14,080 ..................................................................................... Authority for This Rulemaking $4,551 × 275 = $1,251,525 determining the numb er of airplanes that may need this replacement: Labor cost We estimate the following costs to do any replacements of support structure for the center aileron hinge fittings on $3,526 × 275 = $969,650 structure of the center aileron hinge fittings on both wings: Labor cost We estimate the following costs to do any replacements of the support structures for the inboard aileron hinge Total cost on U.S. operators $3,330 Total cost for each airplane $14,080 + $3,330 = $17,410 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] 2. FAA amends § 3913 by adding the following new AD: I 2006–15–01 Twin Commander Aircraft Corporation: Amendment 39–14681; Docket No. FAA–2006–23785; Directorate Identifier 2006–CE–10–AD. Effective Date (a) This AD becomes effective on August 21, 2006. Affected ADs (b) None. Applicability (c) This AD affects Models 690, 690A, and 690B airplanes, all serial numbers, that are certificated in any category. Unsafe Condition (d) This AD results from reports of cracks found in the support structures for the inboard and center aileron hinge fittings on both wings. The actions specified in this AD are intended to detect and correct cracks in the support structures for the inboard and center aileron hinge fittings on both wings, which could result in aileron failure. This failure could lead to reduced controllability or loss of control of the airplane. E:\FR\FM\17JYR1.SGM 17JYR1 Federal Register / Vol. 71, No. 136 / Monday, July 17, 2006 / Rules and Regulations 40387 Compliance (e) To address this problem, you must do the following: Actions Compliance Procedures (1) Inspect, visually and using fluorescent dye penetrant, the support structures for the inboard and center aileron hinge fittings on both wings for cracks. (2) If you do not find cracks during the inspection required in paragraph (e)(1) of this AD, reinforce the support structures for the inboard and center aileron hinge fittings on both wings that are crack free. (3) If you find cracks during the inspection required in paragraph (e)(1) of this AD, replace and reinforce the cracked support structure. Within the next 150 hours time-in-service or 12 months after August 21, 2006 (the effective date of this AD), whichever occurs first. Before further flight after the inspection required in paragraph (e)(1) of this AD. After doing the reinforcement, no further action is required. Follow Twin Commander Aircraft LLC Alert Service Bulletin 236A and Alert Service Bulletin 238, both dated December 21, 2004, as applicable. Follow Twin Commander Aircraft LLC Alert Service Bulletin 236A and Alert Service Bulletin 238, both dated December 21, 2004, as applicable. Before further flight after the inspection required in paragraph (e)(1) of this AD. After doing the replacement and reinforcement, no further action is required. Follow Twin Commander Aircraft LLC Alert Service Bulletin 236A and Alert Service Bulletin 238, both dated December 21, 2004, as applicable. Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION (f) The Manager, Seattle Aircraft Certification Office (ACO), FAA, ATTN: Vince Massey, Aerospace Engineer, Seattle, ACO, 1601 Lind Avenue SW., Renton, WA 98057; telephone: (425) 917–6475; facsimile: (425) 917–6590, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24522; Directorate Identifier 2006–NM–002–AD; Amendment 39–14680; AD 2006–14–09] RIN 2120–AA64 Material Incorporated by Reference rmajette on PROD1PC67 with RULES (g) You must do the actions required by this AD following Twin Commander Aircraft LLC Alert Service Bulletin 236A and Twin Commander Aircraft LLC Alert Service Bulletin 238, both dated December 21, 2004. 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 Twin Commander Aircraft LLC, 19010 59th Drive NE., Arlington, WA 98223, telephone: (360) 435–9797; facsimile: (360) 435–1112. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html or call (202) 741–6030. To view the AD docket, go to the Docket Management Facility; US Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590–001 or on the Internet at http:// dms.dot.gov. The docket number is FAA– 2006–23785; Directorate Identifier 2006–CE– 10–AD. Issued in Kansas City, Missouri, on July 7, 2006. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–6225 Filed 7–14–06; 8:45 am] BILLING CODE 4910–13–M VerDate Aug<31>2005 15:22 Jul 14, 2006 Jkt 208001 Airworthiness Directives; Airbus Model A330–200 and –300, and A340–200 and –300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330–200 and –300, and A340–200 and –300 series airplanes. This AD requires modifying certain rotary actuator assemblies for the leading edge slat. This AD results from a leak found at the seal of the torque limiter output shaft of the Type A rotary actuator of leading edge slat No. 1. We are issuing this AD to prevent a decrease in the torque limiter function, which could result in degradation and damage to the attachment bolts of the leading edge slat, loss of the slat, and consequent reduced control of the airplane. This AD becomes effective August 21, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of August 21, 2006. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, DATES: PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 SW., Nassif Building, Room PL–401, Washington, DC. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for the service information identified in this AD. Tim Backman, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2797; fax (425) 227–1149. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Airbus Model A330– 200 and –300, and A340–200 and –300 series airplanes. That NPRM was published in the Federal Register on April 21, 2006 (71 FR 20599). That NPRM proposed to require modifying certain rotary actuator assemblies for the leading edge slat. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the single comment received. E:\FR\FM\17JYR1.SGM 17JYR1

Agencies

[Federal Register Volume 71, Number 136 (Monday, July 17, 2006)]
[Rules and Regulations]
[Pages 40385-40387]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-6225]



========================================================================
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. 136 / Monday, July 17, 2006 / Rules 
and Regulations

[[Page 40385]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23785; Directorate Identifier 2006-CE-10-AD; 
Amendment 39-14681; AD 2006-15-01]
RIN 2120-AA64


Airworthiness Directives; Twin Commander Aircraft Corporation 
Models 690, 690A, and 690B Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Twin Commander Aircraft Corporation (Twin Commander) Models 690, 690A, 
and 690B airplanes. This AD requires you to inspect, visually and using 
fluorescent dye penetrant, the support structures for the inboard and 
center aileron hinge fittings on both wings for cracks and replace any 
cracked support structure. This AD requires you to reinforce the 
support structures for the inboard and center aileron hinge fittings on 
both wings. This AD results from reports that cracks were found in the 
support structures for the inboard and center aileron hinge fittings on 
both wings. We are issuing this AD to detect and correct cracks in the 
support structures for the inboard and center aileron hinge fittings on 
both wings, which could result in aileron failure. This failure could 
lead to reduced controllability or loss of control of the airplane.

DATES: This AD becomes effective on August 21, 2006.
    As of August 21, 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 Twin 
Commander Aircraft LLC, 19010 59th Drive Northeast, Arlington, 
Washington 98223, telephone: (360) 435-9797; facsimile: (360) 435-1112.
    To view the AD docket, go to the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC 20590-001 or on the Internet at http://
dms.dot.gov. The docket number is FAA-2006-23785; Directorate 
Identifier 2006-CE-10-AD.

FOR FURTHER INFORMATION CONTACT: Vince Massey, Aerospace Engineer, FAA, 
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
WA 98057; telephone: (425) 917-6475; facsimile: (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    On March 10, 2006, we issued a proposal to amend part 39 of the 
Federal Aviation Regulations (14 CFR part 39) to include an AD that 
would apply to all Twin Commander Models 690, 690A, and 690B, 
airplanes. This proposal was published in the Federal Register as a 
notice of proposed rulemaking (NPRM) on March 16, 2006 (71 FR 13558). 
The NPRM proposed to require you to inspect, visually and using 
fluorescent dye penetrant, the support structures for the inboard and 
center aileron hinge fittings on both wings for cracks and replace any 
cracked support structure. The NPRM proposed to require you to 
reinforce the support structures for the inboard and center aileron 
hinge fittings on both wings.

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 275 airplanes in the U.S. 
registry.
    We estimate the following costs to do the inspection of the support 
structures of the inboard aileron hinge fittings on both wings:

----------------------------------------------------------------------------------------------------------------
                                                            Total cost for
             Labor cost                    Parts cost        each airplane      Total cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
10 work-hours x $80 an hour = $800.  Not applicable.......            $800  $800 x 275 = $220,000
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do the inspection of the support 
structure of the center aileron hinge fittings on both wings:

----------------------------------------------------------------------------------------------------------------
                                                            Total cost for
             Labor cost                    Parts cost        each airplane      Total cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
12 work-hours x $80 an hour = $960.  Not applicable.......            $960  $960 x 275 = $264,000
----------------------------------------------------------------------------------------------------------------


[[Page 40386]]

    We estimate the following costs to do the reinforcement to the 
support structures on the inboard aileron hinge fittings on both wings:

--------------------------------------------------------------------------------------------------------------------------------------------------------
              Labor cost                Parts cost             Total cost for each airplane                       Total cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
25 work-hours x $80 an hour = $2,000.       $1,526  $2,000 + $1,526 = $3,526.........................  $3,526 x 275 = $969,650
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do the reinforcement of the 
support structure of the center aileron hinge fittings on both wings:

--------------------------------------------------------------------------------------------------------------------------------------------------------
              Labor cost                Parts cost             Total cost for each airplane                       Total cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
50 work-hours x $80 an hour = $4,000.         $551  $4,000 + $551 = $4,551...........................  $4,551 x 275 = $1,251,525
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any replacements of the 
support structures for the inboard aileron hinge fittings on both wings 
that may be required based on the results of the inspection. We have no 
way of determining the numb er of airplanes that may need this 
replacement:

----------------------------------------------------------------------------------------------------------------
                  Labor cost                     Parts cost              Total cost for each airplane
----------------------------------------------------------------------------------------------------------------
62 work-hours x $80 an hour = $4,960..........       $2,320  $4,960 + $2,320 = $7,280
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any replacements of support 
structure for the center aileron hinge fittings on both wings that may 
be required based on the results of the inspection. We have no way of 
determining the number of airplanes that may need this replacement.

----------------------------------------------------------------------------------------------------------------
                 Labor cost                   Parts cost               Total cost for each airplane
----------------------------------------------------------------------------------------------------------------
176 work-hours x $80 an hour = $14,080.....       $3,330  $14,080 + $3,330 = $17,410
----------------------------------------------------------------------------------------------------------------

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 
requirement.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this AD.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD (and 
other information as included in the Regulatory Evaluation) and placed 
it in the AD Docket. You may get a copy of this summary by sending a 
request to us at the address listed under ADDRESSES. Include ``Docket 
No. FAA-2006-23785; Directorate Identifier 2006-CE-10-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.  3913 by adding the following new AD:

2006-15-01 Twin Commander Aircraft Corporation: Amendment 39-14681; 
Docket No. FAA-2006-23785; Directorate Identifier 2006-CE-10-AD.

Effective Date

    (a) This AD becomes effective on August 21, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD affects Models 690, 690A, and 690B airplanes, all 
serial numbers, that are certificated in any category.

Unsafe Condition

    (d) This AD results from reports of cracks found in the support 
structures for the inboard and center aileron hinge fittings on both 
wings. The actions specified in this AD are intended to detect and 
correct cracks in the support structures for the inboard and center 
aileron hinge fittings on both wings, which could result in aileron 
failure. This failure could lead to reduced controllability or loss 
of control of the airplane.

[[Page 40387]]

Compliance

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

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Inspect, visually and     Within the next 150   Follow Twin
 using fluorescent dye         hours time-in-        Commander Aircraft
 penetrant, the support        service or 12         LLC Alert Service
 structures for the inboard    months after August   Bulletin 236A and
 and center aileron hinge      21, 2006 (the         Alert Service
 fittings on both wings for    effective date of     Bulletin 238, both
 cracks.                       this AD), whichever   dated December 21,
                               occurs first.         2004, as
                                                     applicable.
(2) If you do not find        Before further        Follow Twin
 cracks during the             flight after the      Commander Aircraft
 inspection required in        inspection required   LLC Alert Service
 paragraph (e)(1) of this      in paragraph (e)(1)   Bulletin 236A and
 AD, reinforce the support     of this AD. After     Alert Service
 structures for the inboard    doing the             Bulletin 238, both
 and center aileron hinge      reinforcement, no     dated December 21,
 fittings on both wings that   further action is     2004, as
 are crack free.               required.             applicable.
(3) If you find cracks        Before further        Follow Twin
 during the inspection         flight after the      Commander Aircraft
 required in paragraph         inspection required   LLC Alert Service
 (e)(1) of this AD, replace    in paragraph (e)(1)   Bulletin 236A and
 and reinforce the cracked     of this AD. After     Alert Service
 support structure.            doing the             Bulletin 238, both
                               replacement and       dated December 21,
                               reinforcement, no     2004, as
                               further action is     applicable.
                               required.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, ATTN: Vince Massey, Aerospace Engineer, Seattle, ACO, 1601 Lind 
Avenue SW., Renton, WA 98057; telephone: (425) 917-6475; facsimile: 
(425) 917-6590, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19.

Material Incorporated by Reference

    (g) You must do the actions required by this AD following Twin 
Commander Aircraft LLC Alert Service Bulletin 236A and Twin 
Commander Aircraft LLC Alert Service Bulletin 238, both dated 
December 21, 2004. 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 Twin Commander Aircraft LLC, 19010 59th 
Drive NE., Arlington, WA 98223, telephone: (360) 435-9797; 
facsimile: (360) 435-1112. To review copies of this service 
information, go to the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, go to: http://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html or call (202) 741-6030. To 
view the AD docket, go to the Docket Management Facility; US 
Department of Transportation, 400 Seventh Street, SW., Nassif 
Building, Room PL-401, Washington, DC 20590-001 or on the Internet 
at http://dms.dot.gov. The docket number is FAA-2006-23785; 
Directorate Identifier 2006-CE-10-AD.

    Issued in Kansas City, Missouri, on July 7, 2006.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 06-6225 Filed 7-14-06; 8:45 am]
BILLING CODE 4910-13-M