Airworthiness Directives; Cessna Aircraft Company Models 172R, 172S, 182S, 182T, T182T, 206H, and T206H Airplanes, 45454-45457 [E6-12946]

Download as PDF 45454 Federal Register / Vol. 71, No. 153 / Wednesday, August 9, 2006 / Proposed Rules Actions Compliance Procedures (3) Do the installation of the external doubler at the upper rudder hinge. Upon accumulating 5,000 hours TIS or within the next 100 hours TIS after the effective date of this AD, whichever occurs later, unless already done. The installation of the external doubler at the upper rudder hinge required by paragraph (e)(2)(ii) or (e)(3) of this AD is the terminating action for the repetitive inspections required by this AD. As of the effective date of this AD ................... Follow Snow Engineering Co. Service Letter #247, dated August 14, 2005, revised May 17, 2006, and Snow Engineering Co. Process Specification Number 145, dated December 6, 1991. Cessna Aircraft Company (Cessna) Models 172R, 172S, 182S, 182T, T182T, 206H, and T206H airplanes. This proposed AD would require you to install Modification Kit MN172–25–10B or a steel lock rod/bar on both crew seat back cylinder lock assemblies. If a steel lock rod/bar has already been installed on the crew seat back cylinder lock assembly, no further action is required. If Modification Kit MK172–25–10A has previously been installed, this proposed AD would require you to do an installation inspection and correct any discrepancies found. This proposed AD results from reports of the crew seat back cylinder lock assembly failing at the aft end and other cylinder lock assemblies found cracked. We are proposing this AD to prevent the crew seat cylinder lock assembly from bending, cracking, or failing. This failure could cause uncontrolled movement of the seat back, resulting in possible backward collapse during flight. Backward collapse of either crew seat back could result in an abrupt pitch-up if the affected crew member continues to hold on to the control yoke during this failure and could cause difficulty in exiting the airplane from an aft passenger seat after landing. DATES: We must receive comments on this proposed AD by October 10, 2006. ADDRESSES: Use one of the following addresses to comment on this proposed AD: • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, KS 67277; telephone: (316) 517–5800; fax: (316) 942–9006. FOR FURTHER INFORMATION CONTACT: Gary Park, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946–4123; facsimile: (316) 946–4107. SUPPLEMENTARY INFORMATION: (4) Do not install any rudder without the external doubler at the upper rudder hinge required by paragraph (e)(3) of this AD. Alternative Methods of Compliance (AMOCs) (f) The Manager, Fort Worth Aircraft Certification Office, FAA, ATTN: Andrew McAnaul, Aerospace Engineer, ASW–150 (c/o MIDO–43), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: (210) 308–3365; facsimile: (210) 308–3370, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (g) To get copies of the service information referenced in this AD, contact Air Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 564–5616; facsimile: (940) 564–5612. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC, or on the Internet at http ://dms.dot.gov. The docket number is Docket No. FAA–2006–25260; Directorate Identifier 2006–CE–37–AD. Issued in Kansas City, Missouri, on August 3, 2006. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–12940 Filed 8–8–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25261; Directorate Identifier 2006–CE–38–AD] RIN 2120–AA64 Airworthiness Directives; Cessna Aircraft Company Models 172R, 172S, 182S, 182T, T182T, 206H, and T206H Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). jlentini on PROD1PC65 with PROPOSAL AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain VerDate Aug<31>2005 18:06 Aug 08, 2006 Jkt 208001 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 Not Applicable. Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number, ‘‘FAA–2006–25261; Directorate Identifier 2006–CE–38–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive concerning this proposed AD. Discussion We have received reports of the crew seat back cylinder lock bending at the aft end and failing. We have also received reports of cracks found in the cylinder lock assembly. This condition, if not corrected, could result in failure of the crew seat back cylinder lock assembly. This failure could cause uncontrolled movement of the seat back, resulting in possible backward collapse during flight. Backward collapse of either crew seat back could result in an abrupt pitch-up E:\FR\FM\09AUP1.SGM 09AUP1 Federal Register / Vol. 71, No. 153 / Wednesday, August 9, 2006 / Proposed Rules if the affected crew member continues to hold on to the control yoke during this failure and could cause difficulty in exiting the airplane from an aft passenger seat after landing. Relevant Service Information We have reviewed Cessna Single Engine Service Bulletin SB04–25–01, Revision 3, dated July 24, 2006. This service bulletin describes procedures for installing Modification Kit MK172–25–10B on both crew seat back cylinder lock assemblies to replace the cylinder lock with a new model cylinder lock. This service bulletin also described procedures for doing an installation inspection on airplanes that have Modification Kit MK172–25–10A installed following Cessna Single Engine Service Bulletin SB04–25–01, Revision 2, dated June 5, 2006. We have also reviewed Cessna Single Engine Service Bulletin SB04–25–02 Revision 1, dated October 17, 2005, and Revision 2, dated June 5, 2006. These service bulletins describe procedures for installing a steel lock rod/bar on the crew seat to replace the crew seat back cylinder lock assembly. FAA’s Determination and Requirements of the Proposed AD We are proposing this AD because we evaluated all information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. This proposed AD would require you to install a modification kit on both crew seat back cylinder lock assemblies, which replaces the cylinder lock with a new model cylinder lock, or install a steel lock rod/bar on both crew seat back cylinder lock assemblies. Costs of Compliance We estimate that this proposed AD would affect 4,039 airplanes in the U.S. registry. We provide below total fleet costs for both the proposed modification and the proposed steel lock rod/bar installation; however, only one of these proposed actions would be required. We estimate the following costs to do the proposed installation of the modification kit: Total cost per airplane for both seats Labor cost Parts cost for both seats 3.5 work-hours × $80 an hour = $280 for each modification kit. $590 for each modification kit. One modification kit required for each airplane. Total parts cost for both seats would be $590. 45455 Total cost on U.S. operators $870 × 4,039 = $3,513,930. $280 + $590 = $870. We estimate the following costs to do the proposed fabrication and installation of a steel lock rod/bar: Total cost per airplane for both seats Labor cost Parts cost for both seats 1.5 work-hours × $80 an hour = $120 for each crew seat. Total labor cost for both seats would be $240. Not applicable ......... We estimate the following costs to do the proposed installation inspection on $240 Total cost on U.S. operators $240 × 4,039 = $969,360 airplanes that have Modification Kit MK172–25–10A installed: Labor cost Parts cost for both seats 1 work-hour × $80 an hour = $80 for both crew seats ................................................ Not applicable ........................................... We have no method of determining the number of airplanes that may have the previously installed Modification Kit MK172–25–10A. jlentini on PROD1PC65 with PROPOSAL 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 VerDate Aug<31>2005 18:06 Aug 08, 2006 Jkt 208001 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 rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 Total cost per airplane for both seats $80 on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. E:\FR\FM\09AUP1.SGM 09AUP1 45456 Federal Register / Vol. 71, No. 153 / Wednesday, August 9, 2006 / Proposed Rules Examining the AD Docket You may examine the AD docket that contains the proposed AD, the regulatory evaluation, any comments received, and other information on the Internet at https://dms.dot.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. PART 39—AIRWORTHINESS DIRECTIVES Model 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 Cessna Aircraft Company: Docket No. FAA– 2006–25261; Directorate Identifier 2006– CE–38–AD. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Affected ADs (b) None. The Proposed Amendment Applicability (c) This AD affects the following airplane models and serial numbers that are certificated in any category: Model 172R .... 172S ..... 18280001 through 18280944. 18280945 through 18281701. T18208001 through T18208453. 20608001 through 20608250. T20608001 through T20608570. [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Comments Due Date (a) We must receive comments on this airworthiness directive (AD) action by October 10, 2006. Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: 182S ..... 182T ..... T182T ... 206H .... T206H .. Serial Nos. Serial Nos. 17280001 through 17281262. 172S8001 through 172S9994. Unsafe Condition (d) This AD results from reports of the crew seat back cylinder lock assembly failing at the aft end area and other cylinder lock assemblies found cracked. We are issuing this AD to prevent the crew seat cylinder lock assembly from bending, cracking, or failing. This failure could cause uncontrolled movement of the seat back, resulting in possible backward collapse during flight. Backward collapse of either crew seat back could result in an abrupt pitch-up if the affected crew member continues to hold on to the control yoke during this failure and could cause difficulty in exiting the airplane from an aft passenger seat after landing. Compliance (e) To address this problem, you must do the following, unless already done: (1) Airplanes that do not have Modification Kit MK172–25–10A installed: Action Compliance Procedures For each crew seat (pilot and copilot), install Modification Kit MK172–25–10B or fabricate and install a steel lock rod/bar. For airplanes that have over 1,000 hours time-in-service (TIS) on the effective date of this AD, do the action within the next 4 months after the effective date of this AD. For airplanes that have from 501 to 1,000 hours TIS on the effective date of this AD, do the action within the next 8 months after the effective date of this AD. For airplanes that have from 0 to 500 hours TIS on the effective date of this AD, do the action within the next 12 months after the effective date of this AD. Follow Cessna Single Engine Service Bulletin SB04–25–01, Revision 3, dated July 24, 2006, for installing Modification Kit MK172– 25–10B. Follow Cessna Single Engine Service Bulletin SB04–25–02 Revision 1, dated October 17, 2005, or Revision 2, dated June 5, 2006, for fabricating and installing a steel lock rod/bar. Action Compliance Procedures (i) For each crew seat (pilot and copilot), do an installation inspection. Within the next 30 days after the effective date of this AD. (ii) If you do not find any discrepancies during the inspection required in paragraph (e)(2)(i) of this AD, make a log book entry showing compliance with this AD and no further action is required. (iii) If you find discrepancies during the inspection required in paragraph (e)(2)(i) of this AD, make all necessary corrective actions. Before further flight after the inspection required in paragraph (e)(2)(i) of this AD. jlentini on PROD1PC65 with PROPOSAL (2) Airplanes that have Modification Kit MK172–25–10A installed: Note: Although not required by this AD, you may replace the steel lock rod/bar with Modification Kit MK172–25–10B. Alternative Methods of Compliance (AMOCs) (f) The Manager, Wichita Aircraft Certification Office, FAA, ATTN: Gary Park, VerDate Aug<31>2005 18:06 Aug 08, 2006 Jkt 208001 Before further flight after the inspection required in paragraph (e)(2)(i) of this AD. Aerospace Engineer, 1801 Airport Road, MidContinent Airport, Wichita, Kansas 67209; telephone: (316) 946–4123; facsimile: (316) 946–4107, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 Follow Cessna Single Engine SB04–25–01, Revision 3, 2006. Follow Cessna Single Engine SB04–25–01, Revision 3, 2006. Service Bulletin dated July 24, Service Bulletin dated July 24, Follow Cessna Single Engine Service Bulletin SB04–25–01, Revision 3, dated July 24, 2006. Related Information (g) To get copies of the service information referenced in this AD, contact Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, KS 67277; telephone: (316) 517– 5800; fax: (316) 942–9006. To view the AD docket, go to the Docket Management E:\FR\FM\09AUP1.SGM 09AUP1 Federal Register / Vol. 71, No. 153 / Wednesday, August 9, 2006 / Proposed Rules Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC, or on the Internet at https://dms.dot.gov. The docket number is Docket No. FAA–2006–25261; Directorate Identifier 2006–CE–38–AD. Issued in Kansas City, Missouri, on August 3, 2006. John Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–12946 Filed 8–8–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–19961; Directorate Identifier 2004–CE–48–AD] RIN 2120–AA64 Airworthiness Directives; Air Tractor, Inc. Models AT–501, AT–502, AT–502A, AT–502B, and AT–503A Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of the comment period. jlentini on PROD1PC65 with PROPOSAL AGENCY: SUMMARY: The FAA proposes to revise an earlier proposed airworthiness directive (AD) that applies to certain Air Tractor, Inc. (Air Tractor) Models AT– 502, AT–502A, AT–502B, and AT–503A airplanes, which proposes to supersede AD 2002–26–05. AD 2002–26–05 lowers the safe life for the wing lower spar caps for Models AT–502, AT–502A, AT– 502B, and AT–503A airplanes and those that incorporate or have incorporated Marburger Enterprises, Inc. (Marburger) winglets. AD 2002–26–05 also requires you to eddy-current inspect the wing lower spar caps immediately before modifying to correct any crack in a bolt hole before it extends to the modified center section of the wing and report the results of the inspection to the FAA if cracks are found. AD 2002–11–05 R1 currently requires similar action on Model AT–501 airplanes. Since issuing the earlier NPRM, we determined that Model AT–501 airplanes should be added to the Applicability section of this proposed AD and that this proposed AD should also supersede AD 2002–11– 05 R1. We have revised the alternative method of compliance (AMOC) to include inspection procedures for airplanes that have or have had Marburger winglets installed. We have also updated the safe life of the replacement and new production spar VerDate Aug<31>2005 20:41 Aug 08, 2006 Jkt 208001 cap based on additional data we have received from the manufacturer. Since these actions impose an additional burden over that proposed in the earlier NPRM, we are reopening the comment period to allow the public the chance to comment on these additional actions. DATES: We must receive any comments on this proposed AD by October 10, 2006. ADDRESSES: Use one of the following addresses to comments on this proposed AD: • DOT Docket Web site: Go to https:// dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Air Tractor, Incorporated, P.O. Box 485, Olney, Texas 76374; or Marburger Enterprises, Inc., 1227 Hillcourt, Williston, North Dakota 58801; telephone: (800) 893– 1420 or (701) 774–0230; facsimile: (701) 572–2602. FOR FURTHER INFORMATION CONTACT: Direct all questions to: • For the airplanes that do not incorporate and never have incorporated Marburger Enterprises, Inc. winglets: Rob Romero, Aerospace Engineer, FAA, Fort Worth Airplane Certification Office, 2601 Meacham Boulevard, Fort Worth, Texas 76193– 0150; telephone: (817) 222–5102; facsimile: (817) 222–5960; e-mail: robert.a.romero@faa.gov; and • For airplanes that incorporate or have incorporated Marburger Enterprises, Inc. winglets: John Cecil, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, 3960 Paramount Boulevard, Lakewood, California 90712; telephone: (562) 627– 5228; facsimile: (562) 627–5210. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include the docket PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 45457 number, ‘‘FAA–2004–19961; Directorate Identifier 2004–CE–48–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive concerning this proposed AD. Discussion Prior to issuing this supplemental notice of proposed rulemaking (NPRM), 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 Air Tractor Models AT–502, AT–502A, AT–502B, and AT–503A airplanes. That proposal was published in the Federal Register as an NPRM on February 9, 2005 (70 FR 6786). The NPRM proposed to supersede AD 2002–26–05 with a new AD that would retain the actions required in AD 2002–26–05, add additional airplanes to the applicability, and incorporate an AMOC to the actions retained from AD 2002–26–05. AD 2002–26–05, Amendment 39– 12991 (68 FR 18, January 2, 2003), currently applies to certain Air Tractor Models AT–502, AT–502A, AT–502B, and AT–503A airplanes. AD 2002–26– 05 supersedes AD 2002–11–03 and requires the following: • Maintaining the original requirements from AD 2002–11–03 for a lowered safe life, inspection, replacement/modification, and if cracks are found, reporting the results to the FAA; • Further lowering the safe life for the wing lower spar cap established in AD 2002–11–03 for Models AT–502, AT– 502B, and AT–503A airplanes; and • Expanding the applicability of Models AT–502A and AT–502B airplanes to account for future manufactured airplanes. With this supplemental NPRM we are also proposing to supersede AD 2002– 11–05 R1, Amendment 39–14564 (71 FR 19629, April 17, 2006), which currently applies to certain Air Tractor Model AT–501 airplanes. We issued AD 2002– 11–05 R1 to revise AD 2002–11–05 to remove AT–400 series and Models AT– 802 and AT–802A airplanes from the applicability because separate AD actions were issued for those airplanes. E:\FR\FM\09AUP1.SGM 09AUP1

Agencies

[Federal Register Volume 71, Number 153 (Wednesday, August 9, 2006)]
[Proposed Rules]
[Pages 45454-45457]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-12946]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25261; Directorate Identifier 2006-CE-38-AD]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company Models 172R, 
172S, 182S, 182T, T182T, 206H, and T206H Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Cessna Aircraft Company (Cessna) Models 172R, 172S, 182S, 182T, 
T182T, 206H, and T206H airplanes. This proposed AD would require you to 
install Modification Kit MN172-25-10B or a steel lock rod/bar on both 
crew seat back cylinder lock assemblies. If a steel lock rod/bar has 
already been installed on the crew seat back cylinder lock assembly, no 
further action is required. If Modification Kit MK172-25-10A has 
previously been installed, this proposed AD would require you to do an 
installation inspection and correct any discrepancies found. This 
proposed AD results from reports of the crew seat back cylinder lock 
assembly failing at the aft end and other cylinder lock assemblies 
found cracked. We are proposing this AD to prevent the crew seat 
cylinder lock assembly from bending, cracking, or failing. This failure 
could cause uncontrolled movement of the seat back, resulting in 
possible backward collapse during flight. Backward collapse of either 
crew seat back could result in an abrupt pitch-up if the affected crew 
member continues to hold on to the control yoke during this failure and 
could cause difficulty in exiting the airplane from an aft passenger 
seat after landing.

DATES: We must receive comments on this proposed AD by October 10, 
2006.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, KS 
67277; telephone: (316) 517-5800; fax: (316) 942-9006.

FOR FURTHER INFORMATION CONTACT: Gary Park, Aerospace Engineer, FAA, 
Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent 
Airport, Wichita, Kansas 67209; telephone: (316) 946-4123; facsimile: 
(316) 946-4107.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number, ``FAA-
2006-25261; Directorate Identifier 2006-CE-38-AD'' at the beginning of 
your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
AD. We will consider all comments received by the closing date and may 
amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact we 
receive concerning this proposed AD.

Discussion

    We have received reports of the crew seat back cylinder lock 
bending at the aft end and failing. We have also received reports of 
cracks found in the cylinder lock assembly.
    This condition, if not corrected, could result in failure of the 
crew seat back cylinder lock assembly. This failure could cause 
uncontrolled movement of the seat back, resulting in possible backward 
collapse during flight. Backward collapse of either crew seat back 
could result in an abrupt pitch-up

[[Page 45455]]

if the affected crew member continues to hold on to the control yoke 
during this failure and could cause difficulty in exiting the airplane 
from an aft passenger seat after landing.

Relevant Service Information

    We have reviewed Cessna Single Engine Service Bulletin SB04-25-01, 
Revision 3, dated July 24, 2006.
    This service bulletin describes procedures for installing 
Modification Kit MK172-25-10B on both crew seat back cylinder lock 
assemblies to replace the cylinder lock with a new model cylinder lock. 
This service bulletin also described procedures for doing an 
installation inspection on airplanes that have Modification Kit MK172-
25-10A installed following Cessna Single Engine Service Bulletin SB04-
25-01, Revision 2, dated June 5, 2006.
    We have also reviewed Cessna Single Engine Service Bulletin SB04-
25-02 Revision 1, dated October 17, 2005, and Revision 2, dated June 5, 
2006.
    These service bulletins describe procedures for installing a steel 
lock rod/bar on the crew seat to replace the crew seat back cylinder 
lock assembly.

FAA's Determination and Requirements of the Proposed AD

    We are proposing this AD because we evaluated all information and 
determined the unsafe condition described previously is likely to exist 
or develop on other products of the same type design. This proposed AD 
would require you to install a modification kit on both crew seat back 
cylinder lock assemblies, which replaces the cylinder lock with a new 
model cylinder lock, or install a steel lock rod/bar on both crew seat 
back cylinder lock assemblies.

Costs of Compliance

    We estimate that this proposed AD would affect 4,039 airplanes in 
the U.S. registry. We provide below total fleet costs for both the 
proposed modification and the proposed steel lock rod/bar installation; 
however, only one of these proposed actions would be required.
    We estimate the following costs to do the proposed installation of 
the modification kit:

--------------------------------------------------------------------------------------------------------------------------------------------------------
           Labor cost                 Parts cost for both seats       Total cost per airplane for both seats         Total cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.5 work-hours x $80 an hour =    $590 for each modification kit.    $280 + $590 = $870.                      $870 x 4,039 = $3,513,930.
 $280 for each modification kit.   One modification kit required
                                   for each airplane. Total parts
                                   cost for both seats would be
                                   $590.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do the proposed fabrication and 
installation of a steel lock rod/bar:

----------------------------------------------------------------------------------------------------------------
                                                            Total cost per
           Labor cost            Parts cost for both seats   airplane for       Total cost on U.S. operators
                                                              both seats
----------------------------------------------------------------------------------------------------------------
1.5 work-hours x $80 an hour =   Not applicable...........            $240  $240 x 4,039 = $969,360
 $120 for each crew seat. Total
 labor cost for both seats
 would be $240.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do the proposed installation 
inspection on airplanes that have Modification Kit MK172-25-10A 
installed:

------------------------------------------------------------------------
                                                          Total cost per
             Labor cost              Parts cost for both   airplane for
                                            seats           both seats
------------------------------------------------------------------------
1 work-hour x $80 an hour = $80 for  Not applicable.....             $80
 both crew seats.
------------------------------------------------------------------------

    We have no method of determining the number of airplanes that may 
have the previously installed Modification Kit MK172-25-10A.

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 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

[[Page 45456]]

Examining the AD Docket

    You may examine the AD docket that contains the proposed AD, the 
regulatory evaluation, any comments received, and other information on 
the Internet at https://dms.dot.gov; or in person at the Docket 
Management Facility between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Office (telephone (800) 647-5227) 
is located at the street address stated in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Cessna Aircraft Company: Docket No. FAA-2006-25261; Directorate 
Identifier 2006-CE-38-AD.

Comments Due Date

    (a) We must receive comments on this airworthiness directive 
(AD) action by October 10, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD affects the following airplane models and serial 
numbers that are certificated in any category:

------------------------------------------------------------------------
            Model                             Serial Nos.
------------------------------------------------------------------------
172R........................  17280001 through 17281262.
172S........................  172S8001 through 172S9994.
182S........................  18280001 through 18280944.
182T........................  18280945 through 18281701.
T182T.......................  T18208001 through T18208453.
206H........................  20608001 through 20608250.
T206H.......................  T20608001 through T20608570.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from reports of the crew seat back cylinder 
lock assembly failing at the aft end area and other cylinder lock 
assemblies found cracked. We are issuing this AD to prevent the crew 
seat cylinder lock assembly from bending, cracking, or failing. This 
failure could cause uncontrolled movement of the seat back, 
resulting in possible backward collapse during flight. Backward 
collapse of either crew seat back could result in an abrupt pitch-up 
if the affected crew member continues to hold on to the control yoke 
during this failure and could cause difficulty in exiting the 
airplane from an aft passenger seat after landing.

Compliance

    (e) To address this problem, you must do the following, unless 
already done:
    (1) Airplanes that do not have Modification Kit MK172-25-10A 
installed:

----------------------------------------------------------------------------------------------------------------
               Action                              Compliance                            Procedures
----------------------------------------------------------------------------------------------------------------
For each crew seat (pilot and         For airplanes that have over 1,000    Follow Cessna Single Engine Service
 copilot), install Modification Kit    hours time-in-service (TIS) on the    Bulletin SB04-25-01, Revision 3,
 MK172-25-10B or fabricate and         effective date of this AD, do the     dated July 24, 2006, for installing
 install a steel lock rod/bar.         action within the next 4 months       Modification Kit MK172-25-10B.
                                       after the effective date of this AD.  Follow Cessna Single Engine Service
                                      For airplanes that have from 501 to    Bulletin SB04-25-02 Revision 1,
                                       1,000 hours TIS on the effective      dated October 17, 2005, or Revision
                                       date of this AD, do the action        2, dated June 5, 2006, for
                                       within the next 8 months after the    fabricating and installing a steel
                                       effective date of this AD.            lock rod/bar.
                                      For airplanes that have from 0 to
                                       500 hours TIS on the effective date
                                       of this AD, do the action within
                                       the next 12 months after the
                                       effective date of this AD.
----------------------------------------------------------------------------------------------------------------

    (2) Airplanes that have Modification Kit MK172-25-10A installed:

----------------------------------------------------------------------------------------------------------------
               Action                              Compliance                            Procedures
----------------------------------------------------------------------------------------------------------------
(i) For each crew seat (pilot and     Within the next 30 days after the     Follow Cessna Single Engine Service
 copilot), do an installation          effective date of this AD.            Bulletin SB04-25-01, Revision 3,
 inspection.                                                                 dated July 24, 2006.
(ii) If you do not find any           Before further flight after the       Follow Cessna Single Engine Service
 discrepancies during the inspection   inspection required in paragraph      Bulletin SB04-25-01, Revision 3,
 required in paragraph (e)(2)(i) of    (e)(2)(i) of this AD.                 dated July 24, 2006.
 this AD, make a log book entry
 showing compliance with this AD and
 no further action is required.
(iii) If you find discrepancies       Before further flight after the       Follow Cessna Single Engine Service
 during the inspection required in     inspection required in paragraph      Bulletin SB04-25-01, Revision 3,
 paragraph (e)(2)(i) of this AD,       (e)(2)(i) of this AD.                 dated July 24, 2006.
 make all necessary corrective
 actions.
----------------------------------------------------------------------------------------------------------------


    Note: Although not required by this AD, you may replace the 
steel lock rod/bar with Modification Kit MK172-25-10B.

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Wichita Aircraft Certification Office, FAA, 
ATTN: Gary Park, Aerospace Engineer, 1801 Airport Road, Mid-
Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4123; 
facsimile: (316) 946-4107, has the authority to approve AMOCs for 
this AD, if requested using the procedures found in 14 CFR 39.19.

Related Information

    (g) To get copies of the service information referenced in this 
AD, contact Cessna Aircraft Company, Product Support, P.O. Box 7706, 
Wichita, KS 67277; telephone: (316) 517-5800; fax: (316) 942-9006. 
To view the AD docket, go to the Docket Management

[[Page 45457]]

Facility; U.S. Department of Transportation, 400 Seventh Street, 
SW., Nassif Building, Room PL-401, Washington, DC, or on the 
Internet at https://dms.dot.gov. The docket number is Docket No. FAA-
2006-25261; Directorate Identifier 2006-CE-38-AD.

    Issued in Kansas City, Missouri, on August 3, 2006.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-12946 Filed 8-8-06; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.