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 Department of Transportation Federal Aviation Administration 14 CFR Part 39
[Docket No. FAA-2012-18033; Directorate Identifier 2004-CE-16-AD]
RIN 2120-AA64
 AGENCY: Federal Aviation Administration (FAA), DOT.
 ACTION: Notice of proposed rulemaking (NPRM).
 SUMMARY: We propose to revise an existing airworthiness directive (AD) that applies to all Cessna Aircraft Company (Cessna) Models 190, 195 (L-126A,B,C), 195A, and 195B airplanes that are equipped with certain inboard aileron hinge brackets. The existing AD currently requires you to repetitively inspect the affected inboard aileron hinge brackets for cracks or corrosion and replace them if cracks or corrosion is found. Replacement with aluminum brackets would terminate the need for 
                        ( print page 1156)
                        the repetitive inspections. Since we issued AD 2004-21-08, the FAA, in recent months, has received reports of confusion between the casting number on the aileron hinge bracket and the part number (P/N) called out in the AD. This proposed AD would retain the actions of AD 2004-21-08 while requiring future compliance following a revised service bulletin that clarifies the casting numbers and part numbers to be inspected. We are proposing this AD to correct the unsafe condition on these products.
 DATES: We must receive comments on this proposed AD by February 22, 2013.
 ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: *Federal eRulemaking Portal:*
                         Go to 
                        *http://www.regulations.gov.*
                         Follow the instructions for submitting comments.
                    *Fax:*
                         202-493-2251.
                    *Mail:*
                         U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
                    *Hand Delivery:*
                         Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Cessna Aircraft Company, Customer service, P.O. Box 7706, Wichita, KS 67277; telephone: (316) 517-5800; fax: (316) 517-7271; email: 
                        *customercare@cessna.textron.com*; Internet: 
                        *http://www.cessnasupport.com.*
                         You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call (816) 329-4148. Examining the AD Docket You may examine the AD docket on the Internet at 
                    *http://www.regulations.gov*; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527) is in the 
                    **ADDRESSES**
                     section. Comments will be available in the AD docket shortly after receipt.
 FOR FURTHER INFORMATION CONTACT: Gary Park, Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Wichita, KS 67209; phone: (316) 946-4123; fax: (316) 946-4107; email: 
                        *gary.park@faa.gov.*


SUPPLEMENTARY INFORMATION:  Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the 
                    **ADDRESSES**
                     section. Include “Docket No. FAA-2012-18033; Directorate Identifier 2004-CE-16-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 because of those comments. We will post all comments we receive, without change, to 
                    *http://www.regulations.gov*, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On October 13, 2004, we issued AD 2004-21-08, amendment 39-13828 (69 FR 62396, October 26, 2004), for all Cessna Models 190, 195 (L-126A,B,C), 195A, and 195B airplanes that are equipped with certain inboard aileron hinge brackets. That AD requires you to repetitively inspect the affected inboard aileron hinge brackets for cracks or corrosion and replace them if cracks or corrosion is found. Replacement with aluminum brackets would terminate the need for the repetitive inspections. AD 2004-21-08 (69 FR 62396, October 26, 2004) resulted from several reports of cracks and corrosion found on the magnesium aileron hinge brackets. Magnesium is known to be susceptible to corrosion. We issued AD 2004-21-08 (69 FR 62396, October 26, 2004) to detect and correct corrosion damage to the inboard aileron hinge brackets. Such damage could result in the brackets cracking across the bearing boss and could lead to the aileron separating from the airplane with consequent reduced or loss of control. Actions Since Existing AD Was Issued Since we issued AD 2004-21-08 (69 FR 62396, October 26, 2004), the FAA, in recent months, has received reports of confusion between the casting number on the aileron hinge bracket and the P/N called out in the AD. Due to this misunderstanding, proper inspections and/or replacement of the aileron hinge bracket may not be occurring following the AD. In one report, a service center provided an airworthiness compliance record stating “aileron hinge brackets are of a different part # than those specified in the note.” However, during a later inspection of the bracket, a crack was found through the bearing boss. Relevant Service Information We reviewed Cessna Aircraft Company Single Engine Service Bulletin SEB04-1, dated April 26, 2004, and Single Engine Service Bulletin SEB04-01, Revision 1, dated October 3, 2012. The service information describes procedures for: —Inspecting P/N 0322709 and P/N 0322709-1 inboard aileron hinge brackets for cracks or corrosion; and —Replacing any bracket found cracked or corroded with a bracket that is FAA-approved and made from aluminum. Revision 1 of the service information adds casting numbers for the parts to be inspected and clarifies the inspection. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would retain all requirements of AD 2004-21-08 (69 FR 62396, October 26, 2004) while requiring future compliance following a revised service bulletin that clarifies the casting numbers and part numbers to be inspected. Change to Existing AD This proposed AD would retain all requirements of AD 2004-21-08 (69 FR 62396, October 26, 2004). Since AD 2004-21-08 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table: Revised Paragraph Identifiers
Requirement in AD 2004-21-08
Corresponding
                             requirement in this proposed ADparagraph (e)(1)
paragraph (h)paragraph (e)(2)
paragraph (i)paragraph (e)(3)
paragraph (j)
 Costs of Compliance We estimate that this proposed AD affects 643 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD:
                    ( print page 1157) Estimated Costs
Action
Labor cost
Parts cost
Cost per
                             product
Cost on U.S. operatorsInspection of the affected inboard aileron hinge brackets for cracks or corrosion
1 work-hour × $85 per hour = $85
Not Applicable
$85
1,180 airplanes × $85 = $54,655.
 The new requirements of this proposed AD add no additional economic burden. We estimate the following costs to do any necessary replacements that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need these replacements: On-Condition Costs
Action
Labor cost
Parts cost
Cost per
                             productReplacement of left-hand (LH) brackets
3 work-hours × $85 per hour = $255
$1,999
$2,254Replacement of right-hand (RH) brackets
3 work-hours × $85 per hour = $255
1,592
1,847Replacement of LH and RH brackets
6 work-hours × $85 per hour = $510
4,101
4,611
 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), (3) Will not affect intrastate aviation in Alaska, and (4) 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. List of Subjects in 14 CFR Part 39 Air transportation
Aircraft
Aviation safety
Incorporation by reference
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. § 39.13
 2.The FAA amends § 39.13 by removing airworthiness directive (AD) 2004-21-08, Amendment 39-13828 ( 69 FR 62396, October 26, 2004), and adding the following new AD: **Cessna Aircraft Company:**
                         Docket No. FAA-2012-18033; Directorate Identifier 2004-CE-16-AD. (a) Comments Due Date The FAA must receive comments on this AD action by February 22, 2013. (b) Affected ADs This AD revises AD 2004-21-08, Amendment 39-13828. (c) Applicability This AD affects Models 190, 195 (L-126A,B,C), 195A, and 195B airplanes, all serial numbers, that are: (1) Certificated in any category; and (2) Equipped with at least one part number (P/N) 0322709 or P/N 0322709-1 inboard aileron hinge bracket. (d) Subject Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 2710, Aileron Control System. (e) Unsafe Condition This AD was prompted by reports of confusion between the casting number on the aileron hinge bracket and the part number called out in the AD. We are issuing this AD to correct the unsafe condition on these products. (f) Compliance Comply with this AD at the times specified following the procedures in Cessna Aircraft Company Single Engine Service Bulletin SEB04-01, Revision 1, dated October 3, 2012, unless already done. (g) Credit for Actions Accomplished in Accordance With Previous Service Information This paragraph provides credit for the actions required by paragraphs (h), (i), and (j) of this AD, if the actions were performed before the effective date of this AD using Cessna Aircraft Company Single Engine Service Bulletin SEB04-1, dated April 26, 2004. All actions performed after the effective date of this AD will be required following Cessna Aircraft Company Single Engine Service Bulletin SEB04-01, Revision 1, dated October 3, 2012.
                        ( print page 1158) (h) Inspect Each P/N 0322709 and P/N 0322709-1 Inboard Aileron Hinge Bracket or Any Other Bracket Made From Magnesium for Cracks or Corrosion Within the next 100 hours time-in-service (TIS) after November 30, 2004 (the effective date retained from AD 2004-21-08, Amendment 39-13828 (69 FR 62396, October 26, 2004)), and repetitively thereafter at intervals not to exceed 100 hours TIS until each bracket is replaced with aluminum, inspect each P/N 0322709 and P/N 0322709-1 inboard aileron hinge bracket or any other bracket made from magnesium for cracks or corrosion. (i) Replace Any Cracked or Corroded Inboard Aileron Hinge Bracket Before further flight after any inspection where any cracked or corroded bracket is found, replace any cracked or corroded inboard aileron hinge. (1) If replacement is with an FAA-approved bracket made from magnesium, do the 100-hour TIS interval repetitive inspections as required in paragraph (h) of this AD. (2) If replacement is with an FAA-approved bracket that is made from aluminum, then no further inspections are necessary. These can be Cessna parts or non-Cessna parts. (j) Terminating Action for the Repetitive Inspections (1) As terminating action for the repetitive inspections, you may replace all inboard aileron hinge brackets with FAA-approved brackets that are made from aluminum (as specified in paragraph (i)(2) of this AD) regardless if any corrosion or crack is found. (2) You may do this replacement at any time, but you must replace any corroded or cracked bracket before further flight after the applicable inspection where any corrosion or crack is found. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Wichita Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) All AMOCs approved for AD 2004-21-08 (69 FR 62396, October 26, 2004) are approved for this AD. (l) Related Information (1) For more information about this AD, contact Gary Park, Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Wichita, KS 67209; phone: (316) 946-4123; fax: (316) 946-4107; email: 
                        *gary.park@faa.gov.* (2) For service information identified in this AD, contact Cessna Aircraft Company, Customer Service, P.O. Box 7706, Wichita, KS 67277; telephone: (316) 517-5800; fax: (316) 517-7271; email: 
                        *customercare@cessna.textron.com*; Internet: 
                        *http://www.cessnasupport.com.*
                         You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call (816) 329-4148. Issued in Kansas City, Missouri, on December 31, 2012. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service.


[FR Doc. 2013-00069 Filed 1-7-13; 8:45 am] BILLING CODE 4910-13-P