Airworthiness Directives; Cessna Aircraft Company (Cessna) Models 337, 337A (USAF 02B), 337B, 337C, 337D, 337E, T337E, 337F, T337F, 337G, T337G, M337B, F 337E, FT337E, F 337F, FT337F, F 337G, and FT337GP Airplanes, 25264-25273 [2011-10818]

Download as PDF 25264 Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules AOT specified in Table 1 of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. Parts Installation (k) As of the effective date of this AD, no person may install, on any airplane, a RAT turbine lower gear box assembly, as identified by part number in the applicable Hamilton Sundstrand service bulletin specified in Table 2 of this AD, unless it has been inspected and all applicable corrective actions have been done, in accordance with the requirements of this AD. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (l) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 227–2125; fax (425) 227–1149. 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. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: A Federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, and completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. Related Information (m) Refer to the applicable MCAI European Aviation Safety Agency (EASA) AD specified in Table 4 of this AD, the Airbus AOTs specified in Table 1 of this AD, and the Hamilton Sundstrand service bulletins specified in Table 2 of this AD, for related information. TABLE 4—EASA ADS For model— EASA AD— A300–600 and A310 series airplanes .......................................................................... A318, A319, A320, and A321 series airplanes ............................................................ A330 and A340 series airplanes .................................................................................. Issued in Renton, Washington, on April 26, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–10816 Filed 5–3–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0450; Directorate Identifier 2011–CE–010–AD] srobinson on DSKHWCL6B1PROD with PROPOSALS RIN 2120–AA64 Airworthiness Directives; Cessna Aircraft Company (Cessna) Models 337, 337A (USAF 02B), 337B, 337C, 337D, 337E, T337E, 337F, T337F, 337G, T337G, M337B, F 337E, FT337E, F 337F, FT337F, F 337G, and FT337GP Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: VerDate Mar<15>2010 17:53 May 03, 2011 Jkt 223001 2009–0258 2010–0120 2009–0260 Notice of proposed rulemaking (NPRM). ACTION: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD would require inspecting the wings for internal and external damage, repairing any damage, reinforcing the wings, installing operational limitation placards in the cockpit, and adding limitations to the airplane flight manual supplement. This proposed AD was prompted by a review of installed Flint Aero, Inc. wing tip auxiliary fuel tanks, Supplemental Type Certificate (STC) SA5090NM. We are issuing this proposed AD to detect and correct damage in the wings and to prevent overload failure of the wing due to the installation of the STC. Damage in the wing or overload failure of the wing could result in structural failure of the wing, which could result in loss of control. DATES: We must receive comments on this proposed AD by June 20, 2011. ADDRESSES: You may send comments by any of the following methods: SUMMARY: PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Dated— December 10, 2009. June 21, 2010. December 10, 2009 (corrected December 14, 2009). • Federal eRulemaking Portal: Go to https://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 proposed AD, contact Flint Aero, Inc., 1942 Joe Crosson Drive, El Cajon, CA 92020; phone: (619) 448–1551; fax: (619) 448–1571; Internet: https:// www.flintaero.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 https:// E:\FR\FM\04MYP1.SGM 04MYP1 25265 Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules 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: Dara Albouyeh, Aerospace Engineer, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Blvd., Lakewood, CA 90712; phone: (562) 627– 5222; fax: (562) 627–5210; e-mail: dara.albouyeh@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2011–0450; Directorate Identifier 2011– CE–010–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 https:// 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 In May 2010, we reviewed wing tip auxiliary fuel tank extension STCs to Cessna 336 and 337 series airplanes for compliance with airworthiness standards. Due to the STC similarities between Aviation Enterprises wing tip auxiliary fuel tank extensions and Flint Aero, Inc. wing tip auxiliary fuel tank extensions, both were reviewed for possible wing overload conditions. In June 2010, we determined the proper design loads for both Aviation Enterprises wing tip auxiliary fuel tank extension and Flint Aero, Inc. wing tip auxiliary fuel tank extension STCs exceeded the strength capabilities of the outer portions of the wing. On October 4, 2010, we issued AD 2010–21–18, Amendment 39–16478 (75 FR 64111, October 19, 2010), which applies to Cessna Models 336, 337, 337A (USAF 02B), 337B, M337B (USAF 02A), T337B, 337C, T337C, 337D, T337D, 337E, T337E, 337F, T337F, 337G, T337G, 337H, P337H, T337H, T337H–SP, F337E, FT337E, F337F, FT337F, F337G, FT337GP, F337H, and FT337HP airplanes that are now or have ever been modified by Aviation Enterprises wing tip auxiliary fuel tank extensions Supplemental Type Certificates (STC) SA02055AT, SA02056AT, SA02307AT, or SA02308AT. In January 2011, Flint Aero, Inc. confirmed the under-strength condition of the outer wing section. This condition, if not corrected, could result in structural failure of the wing, which could result in loss of control. Relevant Service Information We reviewed Flint Aero, Inc. Service Bulletin FA2, Rev 2, dated April 8, 2011, and Flint Aero, Inc. Drawing FA2, Rev A, dated April 8, 2011. The service information describes procedures for the reinforcement of the upper wing skin, the wing front spar cap, and the stringers. 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 require inspecting the wings for internal and external damage, repairing any damage, reinforcing the wings, installing operational limitation placards in the cockpit, and adding limitations to the Flint Aero, Inc. Airplane Flight Manual Supplement. Costs of Compliance We estimate that this AD affects 33 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Inspection of the wing for damage ................ 5 work-hours × $85 per hour = $425 per inspection cycle. 1 work-hour × $85 per hour = $85 .. Not applicable ..... Not applicable ..... $425 per inspection cycle. $85 ...................... $14,025 per inspection cycle. $2,805. .5 work-hour × $85 per hour = $42.50. Not applicable ..... $42.50 ................. $1,402.50. 25 work-hours × $85 per hour = $2,125. $1,070 ................. $3,195 ................. $105,435. Fabricating and installing placards in the cockpit. Modifying the Limitations section of the Flint Aero, Inc. Airplane Flight Manual Supplement. Reinforcing the upper wing skin, stringer, and wing front spar cap. srobinson on DSKHWCL6B1PROD with PROPOSALS 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: VerDate Mar<15>2010 17:53 May 03, 2011 Jkt 223001 ‘‘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. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 Regulatory Findings We 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. E:\FR\FM\04MYP1.SGM 04MYP1 25266 Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules For the reasons discussed above, I certify this 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 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): Cessna Aircraft Company: Docket No. FAA– 2011–0450; Directorate Identifier 2011– CE–010–AD. Comments Due Date (a) We must receive comments by June 20, 2011. Affected ADs (b) AD 2010–21–18, Amendment 39– 16478, is related to the subject of this AD. srobinson on DSKHWCL6B1PROD with PROPOSALS Applicability (c) This AD applies to Cessna Aircraft Company (Cessna) Models 337, 337A (USAF 02B), 337B, 337C, 337D, 337E, T337E, 337F, T337F, 337G, T337G, M337B, F 337E, FT337E, F 337F, FT337F, F 337G, and FT337GP airplanes, all serial numbers, that: (1) Are certificated in any category; and (2) Are or have ever been modified by Flint Aero, Inc. Supplemental Type Certificate (STC) SA5090NM. Subject (d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 57; Wings. Unsafe Condition (e) This AD was prompted by a review of installed Flint Aero, Inc. wing tip auxiliary fuel tanks, STC SA5090NM. We are issuing this AD to detect and correct damage in the wings and to prevent overload failure of the wing due to the installation of the STC. VerDate Mar<15>2010 17:53 May 03, 2011 Jkt 223001 Damage in the wing or overload failure of the wing could result in structural failure of the wing, which could result in loss of control. Compliance (f) Comply with this AD within the compliance times specified, unless already done. Required Actions (g) Within the next 50 hours time-inservice (TIS) after the effective date of this AD or within 30 days after the effective date of this AD, whichever occurs first, do a general and focused inspection of the left and right wing for internal and external damage at wing stations (WSTA) 150 and 177. Do the inspections following Appendix 1 of this AD. (h) After the inspection required in paragraph (g) of this AD if no damage was found and before the modification required in paragraph (k) of this AD is incorporated, anytime severe and/or extreme turbulence is encountered during flight, before the next flight do a focused inspection of the wing for damage following steps 1, 2, 3, 4, 7, and 10 in Appendix 1 of this AD. Also inspect for signs of distress in the upper front spar in the area around WSTA 150 and 177. The definition of severe and extreme turbulence can be found in table 7–1–9 of the FAA Aeronautical Information Manual (AIM). You may obtain a copy of the FAA AIM at https://www.faa.gov/air_traffic/publications/ atpubs/aim/. (i) For airplanes that have not had the modification specified in paragraphs (j) and (k) incorporated, within the next 50 hours time-in-service (TIS) after the effective date of this AD or within 30 days after the effective date of this AD, fabricate a placard (using at least 1⁄8-inch letters) with the following words and install the placard on the instrument panel within the pilot’s clear view: (1) ‘‘MAINTAIN AT LEAST 12 GAL OF FUEL IN EACH WING TIP FUEL TANK FOR AIRPLANE WEIGHTS BETWEEN 3,400 LBS AND 4,330 LBS.’’ (2) ‘‘MAINTAIN FULL FUEL IN EACH WING TIP FUEL TANK FOR AIRPLANE WEIGHTS AT OR ABOVE 4,330 LBS.’’ (j) If damage or signs of distress are found during the inspections required in paragraphs (g) and (h) of this AD, before further flight do the following: (1) Repair all damaged and distressed parts following FAA Advisory Circular (AC) 43.13–1B, Chapter 4, which can be found at https://rgl.faa.gov/; (2) Incorporate the modification reinforcement specified in Flint Aero, Inc. Service Bulletin FA2, Rev 2, dated April 8, 2011, following Flint Aero, Inc. Drawing FA2, Rev A, dated April 8, 2011; (3) Remove the placard specified in paragraph (i) of this AD; (4) Fabricate a new placard (using at least 1⁄8-inch letters) with the following words and install the placard on the instrument panel within the pilot’s clear view: ‘‘MAINTAIN AT LEAST 12 GAL OF FUEL IN EACH WING TIP FUEL TANK FOR AIRPLANE WEIGHTS AT OR ABOVE 4,330 LBS’’; and (5) Incorporate the information from Appendix 2 of this AD into the Limitations PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 section of the Flint Aero, Inc. Airplane Flight Manual Supplement. (k) If no damage or signs of distress are found during the inspections required in paragraphs (g) and (h) of this AD, within the next 100 hours TIS after the effective date of this AD or within 12 months after the effective date of this AD, whichever occurs first, do the following: (1) Incorporate the modification reinforcement specified in Flint Aero, Inc. Service Bulletin FA2, Rev 2, dated April 8, 2011, following Flint Aero, Inc. Drawing FA2, Rev A, dated April 8, 2011; (2) Remove the placard specified in paragraph (i) of this AD; (3) Fabricate a new placard (using at least 1⁄8-inch letters) with the following words and install the placard on the instrument panel within the pilot’s clear view: ‘‘MAINTAIN AT LEAST 12 GAL OF FUEL IN EACH WING TIP FUEL TANK FOR AIRPLANE WEIGHTS AT OR ABOVE 4,330 LBS’’; and (4) Incorporate the information from Appendix 2 of this AD into the Limitations section of the Flint Aero, Inc. Airplane Flight Manual Supplement. (l) You may incorporate the modification reinforcement specified in Flint Aero, Inc. Service Bulletin FA2, Rev 2, dated April 8, 2011, following Flint Aero, Inc. Drawing FA2, Rev A, dated April 8, 2011, at any time after the inspection required in paragraph (g) of this AD but no later than the compliance time specified in paragraph (k) of this AD as long as no cracks were found. As required in paragraph (j) of this AD, the modification reinforcement must be incorporated before further flight if damage or signs of distress are found. Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, Los Angeles 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. Related Information (n) For more information about this AD, contact Dara Albouyeh, Aerospace Engineer, FAA, Los Angeles ACO, 3960 Paramount Blvd., Lakewood, CA 90712; phone: (562) 627–5222; fax: (562) 627–5210; e-mail: dara.albouyeh@faa.gov. (o) For service information identified in this AD, contact Flint Aero, Inc., 1942 Joe Crosson Drive, El Cajon, CA 92020; phone: (619) 448–1551; fax: (619) 448–1571; Internet: https://www.flintaero.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. E:\FR\FM\04MYP1.SGM 04MYP1 Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules Appendix 1 to Docket No. FAA–2011–0450 General and Focused Inspection Procedures srobinson on DSKHWCL6B1PROD with PROPOSALS Perform a general and focused inspection of the wing for internal and external damage from wing station (WSTA) 23 to the wing tip. The general inspection must be performed in accordance with 14 CFR 43.15(c), using a checklist that includes at least the scope and detail of the items contained in Appendix D of 14 CFR part 43. The focused inspection must include the items listed below. Remove all wing access panels to conduct the inspections. Do these inspections following the manufacturer’s service information and any other appropriate guidance, such as FAA Advisory Circular (AC) 43.13–1B Acceptable Methods, Techniques, and Practices— Aircraft Inspection and Repair. AC 43.13–1B can be found at https://rgl.faa.gov/. Focused inspection items to look for: (1) Wrinkles in upper wing skins, from the outboard edge on the fuel tank access covers (WSTA 150 or 177) to the WSTA 222 (See View B, Figure 3). (2) Wrinkles in the upper wing skins from WSTA 55 to 66, adjacent to the booms (See View E, Figure 6). (3) Cracking of the upper wing skins. Pay particular attention to any wrinkles, the radius between stiffeners at WSTA 150 VerDate Mar<15>2010 17:53 May 03, 2011 Jkt 223001 (under fuel tank covers), and unreinforced access holes (See View B, Figure 3). (4) Working (smoking) rivets outboard of the wing tank access covers. (5) Fasteners with less than two diameters edge distance. (6) Fasteners with less than four diameters center to center spacing. (7) Looseness of attachments of the tip extension to the wing and wing tip to wing extension when pushing up and down on the tip. (8) Any signs of distress along both front and rear spars, particularly in the area around WSTA 177. (9) Inspect under any repairs to the upper skins, particularly in the area just outboard of the fuel tank access covers as these may be covering up existing damage. (10) Inter-rivet buckling of the stringers attached to the upper surface skin, outboard of the fuel tank access covers (See View F, Figure 7). (11) Inspect rib at WSTA 222 for damage. Trimming of the rib may have been done to allow installation of fuel lines (See View A, Figure 2). Repair in accordance with AC 43.13–1B, Chapter 4, paragraph 4–58(g) and Figure 4–14, or by using another FAAapproved method that restores equivalent strength of the wing rib. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 25267 Appendix 1 to Docket No. FAA–2011–0450 General and Focused Inspection Procedures (Continued) (12) Inspect and identify screws, installed in tapped (threaded) holes in metal substructure, used to attach wing tips, stall fences, fuel and electrical components, and access doors. For tapped holes, remove fastener and open up the diameter to provide a smooth bore hole, for the smallest oversize fastener, using close tolerance holes noted in AC 43.13–1B, paragraph 7–39 or other FAAapproved scheme. Maintain minimum 2 x fastener diameter edge distance and 4 x fastener diameter center to center spacing. Select and install new, equivalent strength or stronger, fasteners with nuts/collars in accordance with AC 43.13–1B, Chapter 7 and AC 43.13–2B, paragraph 108 or other FAAapproved repair. New fasteners must not have threads in bearing against the sides of the holes. (13) Inspect wing skins for unreinforced cutouts. (See View C, Figure 4). (14) Inspect the upper spar cap horizontal flanges for open holes (See View D, Figure 5). Appendix 1 to Docket No. FAA–2011–0450 (Continued) BILLING CODE 4910–13–P E:\FR\FM\04MYP1.SGM 04MYP1 Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules BILLING CODE 4910–13–C VerDate Mar<15>2010 17:53 May 03, 2011 Appendix 1 to Docket No. FAA–2011–0450 (Continued) Jkt 223001 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 E:\FR\FM\04MYP1.SGM 04MYP1 EP04MY11.005</GPH> srobinson on DSKHWCL6B1PROD with PROPOSALS 25268 Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules VerDate Mar<15>2010 17:53 May 03, 2011 Appendix 1 to Docket No. FAA–2011–0450 (Continued) Jkt 223001 PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 E:\FR\FM\04MYP1.SGM 04MYP1 EP04MY11.006</GPH> srobinson on DSKHWCL6B1PROD with PROPOSALS BILLING CODE 4910–13–C 25269 25270 Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules VerDate Mar<15>2010 17:53 May 03, 2011 Appendix 1 to Docket No. FAA–2011–0450 (Continued) Jkt 223001 PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 E:\FR\FM\04MYP1.SGM 04MYP1 EP04MY11.007</GPH> srobinson on DSKHWCL6B1PROD with PROPOSALS BILLING CODE 4910–13–C Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules VerDate Mar<15>2010 17:53 May 03, 2011 Appendix 1 to Docket No. FAA–2011–0450 (Continued) Jkt 223001 PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 E:\FR\FM\04MYP1.SGM 04MYP1 EP04MY11.008</GPH> srobinson on DSKHWCL6B1PROD with PROPOSALS BILLING CODE 4910–13–C 25271 25272 Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules VerDate Mar<15>2010 17:53 May 03, 2011 Appendix 1 to Docket No. FAA–2011–0450 (Continued) Jkt 223001 PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 E:\FR\FM\04MYP1.SGM 04MYP1 EP04MY11.009</GPH> srobinson on DSKHWCL6B1PROD with PROPOSALS BILLING CODE 4910–13–C Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules Issued in Kansas City, Missouri, on April 27, 2011. John Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–10818 Filed 5–3–11; 8:45 am] BILLING CODE 4910–13–P SECURITIES AND EXCHANGE COMMISSION srobinson on DSKHWCL6B1PROD with PROPOSALS 17 CFR Parts 229 and 240 [Release Nos. 33–9203; 34–64366; File No. S7–13–11] RIN 3235–AK95 Listing Standards for Compensation Committees Securities and Exchange Commission. AGENCY: VerDate Mar<15>2010 17:53 May 03, 2011 Proposed rule; extension of comment period. ACTION: Appendix 2 to Docket No. FAA–2011–0450 Airworthiness Limitations for the Flint Aero, Inc. Airplane Flight Manual Supplement ‘‘MAINTAIN AT LEAST 12 GAL OF FUEL IN EACH WING TIP FUEL TANK FOR AIRPLANE WEIGHTS AT OR ABOVE 4,330 LBS.’’ Jkt 223001 The Securities and Exchange Commission is extending the comment period for a release proposing a new rule and rule amendments to implement the provisions of Section 952 of the Dodd-Frank Wall Street Reform and Consumer Protection Act of 2010, which added Section 10C to the Securities Exchange Act of 1934 (the ‘‘Exchange Act’’). [Release No. 33–9199; 76 FR 18966 (April 6, 2011)]. The original comment period for Release 33–9199 is scheduled to end on April 29, 2011. The Commission is extending the time period in which to provide the Commission with comments on that release to May 19, 2011. This action will allow interested persons additional time to analyze the issues and prepare their comments. SUMMARY: Comments should be received on or before May 19, 2011. DATES: Comments may be submitted by any of the following methods: ADDRESSES: PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 Electronic Comments • Use the Commission’s Internet comment form (https://www.sec.gov/ rules/proposed.shtml); • Send an e-mail to rulecomments@sec.gov; or • Use the Federal Rulemaking ePortal (https://www.regulations.gov). Follow the instructions for submitting comments. Paper Comments • Send paper comments in triplicate to Elizabeth M. Murphy, Secretary, U.S. Securities and Exchange Commission, 100 F Street, NE., Washington, DC 20549–1090. All submissions should refer to File Number S7–13–11. This file number should be included on the subject line if e-mail is used. To help us process and review your comments more efficiently, please use only one method. The Commission will post all comments on the Commission’s Internet Web site (https://www.sec.gov/rules/ proposed.shtml). Comments are also available for Web site viewing and printing in the Commission’s Public Reference Room, 100 F Street, NE., Washington, DC 20549, on official business days between the hours of E:\FR\FM\04MYP1.SGM 04MYP1 EP04MY11.010</GPH> BILLING CODE 4910–13–C 25273

Agencies

[Federal Register Volume 76, Number 86 (Wednesday, May 4, 2011)]
[Proposed Rules]
[Pages 25264-25273]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-10818]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0450; Directorate Identifier 2011-CE-010-AD]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company (Cessna) Models 
337, 337A (USAF 02B), 337B, 337C, 337D, 337E, T337E, 337F, T337F, 337G, 
T337G, M337B, F 337E, FT337E, F 337F, FT337F, F 337G, and FT337GP 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed AD would require inspecting the 
wings for internal and external damage, repairing any damage, 
reinforcing the wings, installing operational limitation placards in 
the cockpit, and adding limitations to the airplane flight manual 
supplement. This proposed AD was prompted by a review of installed 
Flint Aero, Inc. wing tip auxiliary fuel tanks, Supplemental Type 
Certificate (STC) SA5090NM. We are issuing this proposed AD to detect 
and correct damage in the wings and to prevent overload failure of the 
wing due to the installation of the STC. Damage in the wing or overload 
failure of the wing could result in structural failure of the wing, 
which could result in loss of control.

DATES: We must receive comments on this proposed AD by June 20, 2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://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 proposed AD, contact 
Flint Aero, Inc., 1942 Joe Crosson Drive, El Cajon, CA 92020; phone: 
(619) 448-1551; fax: (619) 448-1571; Internet: https://www.flintaero.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 https://

[[Page 25265]]

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: Dara Albouyeh, Aerospace Engineer, 
FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Blvd., 
Lakewood, CA 90712; phone: (562) 627-5222; fax: (562) 627-5210; e-mail: 
dara.albouyeh@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2011-0450; 
Directorate Identifier 2011-CE-010-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 https://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

    In May 2010, we reviewed wing tip auxiliary fuel tank extension 
STCs to Cessna 336 and 337 series airplanes for compliance with 
airworthiness standards. Due to the STC similarities between Aviation 
Enterprises wing tip auxiliary fuel tank extensions and Flint Aero, 
Inc. wing tip auxiliary fuel tank extensions, both were reviewed for 
possible wing overload conditions.
    In June 2010, we determined the proper design loads for both 
Aviation Enterprises wing tip auxiliary fuel tank extension and Flint 
Aero, Inc. wing tip auxiliary fuel tank extension STCs exceeded the 
strength capabilities of the outer portions of the wing.
    On October 4, 2010, we issued AD 2010-21-18, Amendment 39-16478 (75 
FR 64111, October 19, 2010), which applies to Cessna Models 336, 337, 
337A (USAF 02B), 337B, M337B (USAF 02A), T337B, 337C, T337C, 337D, 
T337D, 337E, T337E, 337F, T337F, 337G, T337G, 337H, P337H, T337H, 
T337H-SP, F337E, FT337E, F337F, FT337F, F337G, FT337GP, F337H, and 
FT337HP airplanes that are now or have ever been modified by Aviation 
Enterprises wing tip auxiliary fuel tank extensions Supplemental Type 
Certificates (STC) SA02055AT, SA02056AT, SA02307AT, or SA02308AT.
    In January 2011, Flint Aero, Inc. confirmed the under-strength 
condition of the outer wing section.
    This condition, if not corrected, could result in structural 
failure of the wing, which could result in loss of control.

Relevant Service Information

    We reviewed Flint Aero, Inc. Service Bulletin FA2, Rev 2, dated 
April 8, 2011, and Flint Aero, Inc. Drawing FA2, Rev A, dated April 8, 
2011. The service information describes procedures for the 
reinforcement of the upper wing skin, the wing front spar cap, and the 
stringers.

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 require inspecting the wings for internal 
and external damage, repairing any damage, reinforcing the wings, 
installing operational limitation placards in the cockpit, and adding 
limitations to the Flint Aero, Inc. Airplane Flight Manual Supplement.

Costs of Compliance

    We estimate that this AD affects 33 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:


                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection of the wing for       5 work-hours x $85   Not applicable....  $425 per            $14,025 per
 damage.                          per hour = $425                          inspection cycle.   inspection cycle.
                                  per inspection
                                  cycle.
Fabricating and installing       1 work-hour x $85    Not applicable....  $85...............  $2,805.
 placards in the cockpit.         per hour = $85.
Modifying the Limitations        .5 work-hour x $85   Not applicable....  $42.50............  $1,402.50.
 section of the Flint Aero,       per hour = $42.50.
 Inc. Airplane Flight Manual
 Supplement.
Reinforcing the upper wing       25 work-hours x $85  $1,070............  $3,195............  $105,435.
 skin, stringer, and wing front   per hour = $2,125.
 spar cap.
----------------------------------------------------------------------------------------------------------------

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 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.

[[Page 25266]]

    For the reasons discussed above, I certify this 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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

Cessna Aircraft Company: Docket No. FAA-2011-0450; Directorate 
Identifier 2011-CE-010-AD.

Comments Due Date

    (a) We must receive comments by June 20, 2011.

Affected ADs

    (b) AD 2010-21-18, Amendment 39-16478, is related to the subject 
of this AD.

Applicability

    (c) This AD applies to Cessna Aircraft Company (Cessna) Models 
337, 337A (USAF 02B), 337B, 337C, 337D, 337E, T337E, 337F, T337F, 
337G, T337G, M337B, F 337E, FT337E, F 337F, FT337F, F 337G, and 
FT337GP airplanes, all serial numbers, that:
    (1) Are certificated in any category; and
    (2) Are or have ever been modified by Flint Aero, Inc. 
Supplemental Type Certificate (STC) SA5090NM.

Subject

    (d) Joint Aircraft System Component (JASC)/Air Transport 
Association (ATA) of America Code 57; Wings.

Unsafe Condition

    (e) This AD was prompted by a review of installed Flint Aero, 
Inc. wing tip auxiliary fuel tanks, STC SA5090NM. We are issuing 
this AD to detect and correct damage in the wings and to prevent 
overload failure of the wing due to the installation of the STC. 
Damage in the wing or overload failure of the wing could result in 
structural failure of the wing, which could result in loss of 
control.

Compliance

    (f) Comply with this AD within the compliance times specified, 
unless already done.

Required Actions

    (g) Within the next 50 hours time-in-service (TIS) after the 
effective date of this AD or within 30 days after the effective date 
of this AD, whichever occurs first, do a general and focused 
inspection of the left and right wing for internal and external 
damage at wing stations (WSTA) 150 and 177. Do the inspections 
following Appendix 1 of this AD.
    (h) After the inspection required in paragraph (g) of this AD if 
no damage was found and before the modification required in 
paragraph (k) of this AD is incorporated, anytime severe and/or 
extreme turbulence is encountered during flight, before the next 
flight do a focused inspection of the wing for damage following 
steps 1, 2, 3, 4, 7, and 10 in Appendix 1 of this AD. Also inspect 
for signs of distress in the upper front spar in the area around 
WSTA 150 and 177. The definition of severe and extreme turbulence 
can be found in table 7-1-9 of the FAA Aeronautical Information 
Manual (AIM). You may obtain a copy of the FAA AIM at https://www.faa.gov/air_traffic/publications/atpubs/aim/.
    (i) For airplanes that have not had the modification specified 
in paragraphs (j) and (k) incorporated, within the next 50 hours 
time-in-service (TIS) after the effective date of this AD or within 
30 days after the effective date of this AD, fabricate a placard 
(using at least \1/8\-inch letters) with the following words and 
install the placard on the instrument panel within the pilot's clear 
view:
    (1) ``MAINTAIN AT LEAST 12 GAL OF FUEL IN EACH WING TIP FUEL 
TANK FOR AIRPLANE WEIGHTS BETWEEN 3,400 LBS AND 4,330 LBS.''
    (2) ``MAINTAIN FULL FUEL IN EACH WING TIP FUEL TANK FOR AIRPLANE 
WEIGHTS AT OR ABOVE 4,330 LBS.''
    (j) If damage or signs of distress are found during the 
inspections required in paragraphs (g) and (h) of this AD, before 
further flight do the following:
    (1) Repair all damaged and distressed parts following FAA 
Advisory Circular (AC) 43.13-1B, Chapter 4, which can be found at 
https://rgl.faa.gov/;
    (2) Incorporate the modification reinforcement specified in 
Flint Aero, Inc. Service Bulletin FA2, Rev 2, dated April 8, 2011, 
following Flint Aero, Inc. Drawing FA2, Rev A, dated April 8, 2011;
    (3) Remove the placard specified in paragraph (i) of this AD;
    (4) Fabricate a new placard (using at least \1/8\-inch letters) 
with the following words and install the placard on the instrument 
panel within the pilot's clear view: ``MAINTAIN AT LEAST 12 GAL OF 
FUEL IN EACH WING TIP FUEL TANK FOR AIRPLANE WEIGHTS AT OR ABOVE 
4,330 LBS''; and
    (5) Incorporate the information from Appendix 2 of this AD into 
the Limitations section of the Flint Aero, Inc. Airplane Flight 
Manual Supplement.
    (k) If no damage or signs of distress are found during the 
inspections required in paragraphs (g) and (h) of this AD, within 
the next 100 hours TIS after the effective date of this AD or within 
12 months after the effective date of this AD, whichever occurs 
first, do the following:
    (1) Incorporate the modification reinforcement specified in 
Flint Aero, Inc. Service Bulletin FA2, Rev 2, dated April 8, 2011, 
following Flint Aero, Inc. Drawing FA2, Rev A, dated April 8, 2011;
    (2) Remove the placard specified in paragraph (i) of this AD;
    (3) Fabricate a new placard (using at least \1/8\-inch letters) 
with the following words and install the placard on the instrument 
panel within the pilot's clear view: ``MAINTAIN AT LEAST 12 GAL OF 
FUEL IN EACH WING TIP FUEL TANK FOR AIRPLANE WEIGHTS AT OR ABOVE 
4,330 LBS''; and
    (4) Incorporate the information from Appendix 2 of this AD into 
the Limitations section of the Flint Aero, Inc. Airplane Flight 
Manual Supplement.
    (l) You may incorporate the modification reinforcement specified 
in Flint Aero, Inc. Service Bulletin FA2, Rev 2, dated April 8, 
2011, following Flint Aero, Inc. Drawing FA2, Rev A, dated April 8, 
2011, at any time after the inspection required in paragraph (g) of 
this AD but no later than the compliance time specified in paragraph 
(k) of this AD as long as no cracks were found. As required in 
paragraph (j) of this AD, the modification reinforcement must be 
incorporated before further flight if damage or signs of distress 
are found.

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, Los Angeles 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.

Related Information

    (n) For more information about this AD, contact Dara Albouyeh, 
Aerospace Engineer, FAA, Los Angeles ACO, 3960 Paramount Blvd., 
Lakewood, CA 90712; phone: (562) 627-5222; fax: (562) 627-5210; e-
mail: dara.albouyeh@faa.gov.
    (o) For service information identified in this AD, contact Flint 
Aero, Inc., 1942 Joe Crosson Drive, El Cajon, CA 92020; phone: (619) 
448-1551; fax: (619) 448-1571; Internet: https://www.flintaero.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.

[[Page 25267]]

Appendix 1 to Docket No. FAA-2011-0450

General and Focused Inspection Procedures

    Perform a general and focused inspection of the wing for 
internal and external damage from wing station (WSTA) 23 to the wing 
tip. The general inspection must be performed in accordance with 14 
CFR 43.15(c), using a checklist that includes at least the scope and 
detail of the items contained in Appendix D of 14 CFR part 43. The 
focused inspection must include the items listed below. Remove all 
wing access panels to conduct the inspections. Do these inspections 
following the manufacturer's service information and any other 
appropriate guidance, such as FAA Advisory Circular (AC) 43.13-1B 
Acceptable Methods, Techniques, and Practices--Aircraft Inspection 
and Repair. AC 43.13-1B can be found at https://rgl.faa.gov/.
    Focused inspection items to look for:
    (1) Wrinkles in upper wing skins, from the outboard edge on the 
fuel tank access covers (WSTA 150 or 177) to the WSTA 222 (See View 
B, Figure 3).
    (2) Wrinkles in the upper wing skins from WSTA 55 to 66, 
adjacent to the booms (See View E, Figure 6).
    (3) Cracking of the upper wing skins. Pay particular attention 
to any wrinkles, the radius between stiffeners at WSTA 150 (under 
fuel tank covers), and unreinforced access holes (See View B, Figure 
3).
    (4) Working (smoking) rivets outboard of the wing tank access 
covers.
    (5) Fasteners with less than two diameters edge distance.
    (6) Fasteners with less than four diameters center to center 
spacing.
    (7) Looseness of attachments of the tip extension to the wing 
and wing tip to wing extension when pushing up and down on the tip.
    (8) Any signs of distress along both front and rear spars, 
particularly in the area around WSTA 177.
    (9) Inspect under any repairs to the upper skins, particularly 
in the area just outboard of the fuel tank access covers as these 
may be covering up existing damage.
    (10) Inter-rivet buckling of the stringers attached to the upper 
surface skin, outboard of the fuel tank access covers (See View F, 
Figure 7).
    (11) Inspect rib at WSTA 222 for damage. Trimming of the rib may 
have been done to allow installation of fuel lines (See View A, 
Figure 2). Repair in accordance with AC 43.13-1B, Chapter 4, 
paragraph 4-58(g) and Figure 4-14, or by using another FAA-approved 
method that restores equivalent strength of the wing rib.

Appendix 1 to Docket No. FAA-2011-0450

General and Focused Inspection Procedures (Continued)

    (12) Inspect and identify screws, installed in tapped (threaded) 
holes in metal substructure, used to attach wing tips, stall fences, 
fuel and electrical components, and access doors. For tapped holes, 
remove fastener and open up the diameter to provide a smooth bore 
hole, for the smallest oversize fastener, using close tolerance 
holes noted in AC 43.13-1B, paragraph 7-39 or other FAA-approved 
scheme. Maintain minimum 2 x fastener diameter edge distance and 4 x 
fastener diameter center to center spacing. Select and install new, 
equivalent strength or stronger, fasteners with nuts/collars in 
accordance with AC 43.13-1B, Chapter 7 and AC 43.13-2B, paragraph 
108 or other FAA-approved repair. New fasteners must not have 
threads in bearing against the sides of the holes.
    (13) Inspect wing skins for unreinforced cutouts. (See View C, 
Figure 4).
    (14) Inspect the upper spar cap horizontal flanges for open 
holes (See View D, Figure 5).

Appendix 1 to Docket No. FAA-2011-0450 (Continued)

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Appendix 1 to Docket No. FAA-2011-0450 (Continued)

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Appendix 1 to Docket No. FAA-2011-0450 (Continued)

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Appendix 2 to Docket No. FAA-2011-0450

    Airworthiness Limitations for the Flint Aero, Inc. Airplane 
Flight Manual Supplement
    ``MAINTAIN AT LEAST 12 GAL OF FUEL IN EACH WING TIP FUEL TANK 
FOR AIRPLANE WEIGHTS AT OR ABOVE 4,330 LBS.''

    Issued in Kansas City, Missouri, on April 27, 2011.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-10818 Filed 5-3-11; 8:45 am]
BILLING CODE 4910-13-P
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