[Federal Register Volume 76, Number 72 (Thursday, April 14, 2011)] [Proposed Rules] [Pages 20894-20898] From the Federal Register Online via the Government Publishing Office [www.gpo.gov] [FR Doc No: 2011-9091] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2011-0360; Directorate Identifier 2010-CE-061-AD] RIN 2120-AA64 Airworthiness Directives; Univair Aircraft Corporation Models (ERCO) 415-C, 415-CD, 415-D, E, G; (Forney) F-1 and F-1A; (Alon) A-2 and A2-A; and (Mooney) M10 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede an existing airworthiness directive (AD) that applies to Univair Aircraft Corporation Models (ERCO) 415-C, 415-CD, 415-D, E, G; (Forney) F-1 and F-1A; (Alon) A-2 and A2-A; and (Mooney) M10 Airplanes. The existing AD currently requires an inspection of the aileron balance assembly and ailerons for cracks and excessive looseness of associated parts with the required repair or replacement of defective parts as necessary. Since we issued that AD, we received a report of a Univair Aircraft Corporation Model ERCO 415-D Ercoupe that crashed after an in-flight breakup due to possible aileron flutter. This proposed AD would add airplanes to the Applicability section and require inspections of the ailerons, inspections of the aileron balance assembly and aileron rigging for looseness or wear with a required repair or replacement of parts as necessary, and a reporting of the inspection results. We are issuing this proposed AD to prevent failure of the aileron assembly and associated parts, which could result in loss of control. DATES: We must receive comments on this proposed AD by May 31, 2011. ADDRESSES: You may send comments 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 Univair Aircraft Corporation, 2500 Himalaya Road, Aurora, Colorado 80011; telephone: 303-375-8882, fax: 303 375-8888; Internet: http://univairparts.com. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 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: Roger Caldwell, Aerospace Engineer, FAA, Denver Aircraft Certification Office, 26805 East 68th Ave., Room 214, Denver, Colorado 80249-6361; telephone: (303) 342-1086; fax: (303) 342-1088; e-mail: [email protected]. 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-2011-0360; Directorate Identifier 2010-CE-061-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 We issued AD 52-02-02 (21 FR 9447, December 4, 1956) for Ercoupe Model 415 Series and Models E and G Airplanes. That AD requires an initial and repetitive inspection of the aileron balance assembly, including the aileron hinges, screws and control system, the ailerons for cracks in support structure and skin, and the repair or replacement of damaged parts. That AD resulted from several Ercoupe accidents. We issued that AD as a precautionary measure. Actions Since Existing AD Was Issued Since we issued AD 52-02-02, we received a report of a Univair Aircraft Corporation Model ERCO 415-D Ercoupe that crashed after an in- flight breakup. Witnesses of the accident noted that while the airplane was banking both ailerons were ``fluttering'' at a high frequency, and as the bank angle of the airplane increased to almost 90 degrees, the left wing of the airplane ``folded back'' and separated from the fuselage. We have received nine other documented cases of structural failures of the wing and associated components of the airframe. There are several Univair airplane models that have similar type design to that of above-referenced incidents, are not part of the compliance of AD 52-02-02, and should be subjected to the requirements of AD 52-02-02. Relevant Service Information We reviewed Ercoupe Service Memorandum Nos. 35, 56, and 57 (all not dated). The Ercoupe Service Memorandum No. 35 describes procedures for use in rigging or making adjustments to the rigging. The Ercoupe Service Memorandum No. 56 describes procedures for the inspection of control surfaces for cracks and excessive play and checking controls for excessive movement. The Ercoupe Service Memorandum No. 57 describes procedures for aileron balance weight inspection and removal. 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 add airplanes to the Applicability section of AD 52-02-02 and require inspections of the ailerons, add airplanes to the Applicability section, add repetitive inspections of the aileron bell crank and [[Page 20895]] the ailerons for looseness or wear with a repair or replacement of parts as necessary, and add the requirement to report the inspection results. Costs of Compliance We estimate that this proposed AD affects 2,600 airplanes of U.S. registry. We estimate the following costs to comply with the proposed AD: ---------------------------------------------------------------------------------------------------------------- Total cost per Total cost on Labor cost Parts cost airplane U.S. operators ---------------------------------------------------------------------------------------------------------------- Estimated Retained Costs ---------------------------------------------------------------------------------------------------------------- 4 work-hours x $85 per hour = $340.......... Not applicable................ $340 $884,000 ---------------------------------------------------------------------------------------------------------------- Estimated New Costs ---------------------------------------------------------------------------------------------------------------- .5 work-hour x $85 per hour = $42.50........ Not applicable................ 42.50 110,500 ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary replacements for the flight control system that would be required based on the results of the proposed inspection. We have no way of determining the number of airplanes that may need this replacement: On-Condition Costs ------------------------------------------------------------------------ Total cost per Labor cost Parts cost airplane ------------------------------------------------------------------------ 2 work-hours x $85 per hour = Aileron Hinge Part $195 $170. Number (P/N) 415- 24003 $25 2 work-hours x $85 per hour = Elevator Hinge P/N 415- 210 $170. 22007 $40. 2 work-hours x $85 per hour = Elevator Hinge P/N 415- 253 $170. 22008 $83. 2 work-hours x $85 per hour = Rudder Hinge P/N 415- 195 $170. 24003 $25. 2 work-hours x $85 per hour = Aileron Rod-End 190 $170. Bearing P/N GMM-3M- 670 $20. ------------------------------------------------------------------------ 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. 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 The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] The FAA amends Sec. 39.13 by removing airworthiness directive (AD) 52-02-02, (21 FR 9447, December 4, 1956), and adding the following new AD: Univair Aircraft Corporation: Docket No. FAA-2011-0360; Directorate Identifier 2010-CE-061-AD. Comments Due Date (a) The FAA must receive comments on this proposed AD action by May 31, 2011. Affected ADs (b) This AD supersedes AD 52-02-02 (21 FR 9447, December 4, 1956). Applicability (c) This AD applies to Univair Aircraft Corporation Models (ERCO) 415-C, 415-CD, 415-D, E, G; (Forney) F-1 and F-1A; (Alon) A-2 and A2-A; and (Mooney) M10 airplanes, all serial numbers, that are certificated in any category. Subject (d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 27, Flight Controls. Unsafe Condition (e) This AD was prompted by a Univair Aircraft Corporation Model ERCO 415-D Ercoupe that crashed after an in-flight breakup due to possible aileron flutter. We are issuing this AD to add airplanes to the Applicability section and require inspections of the ailerons, inspections of the aileron balance assembly and aileron rigging for looseness or wear with a required repair or replacement of parts as necessary, and a reporting of the inspection results. Compliance (f) Comply with this AD within the compliance times specified, unless already done. [[Page 20896]] ---------------------------------------------------------------------------------------------------------------- Actions Compliance Procedures ---------------------------------------------------------------------------------------------------------------- (1) For all airplanes: Inspect the (i) Within the next 25 hours time-in- Follow Ercoupe Service Memorandums ailerons for cracks in the support service (TIS) after the effective No. 56 and 57 (both not dated). structure and skin. date of this AD or within 3 months after the effective date of this AD, whichever occurs first. Repetitively thereafter inspect at intervals not to exceed 100 hours TIS or 12 months, whichever occurs first. (ii) We will allow ``unless already done'' credit for inspections done within the last 25 hours TIS before the effective date of this AD or within the last 3 months before the effective date of this AD, and you may use the results from that inspection for the reporting requirement in paragraph (f)(10) of this AD. (2) For airplanes with the aileron (i) Within the next 25 hours TIS Follow Ercoupe Service Memorandums balance assembly (ERCO Part Number after the effective date of this AD No. 56 and 57 (both not dated). (P/N) 415-16009) installed: Inspect or within 3 months after the the assembly for cracks in the effective date of this AD, support structure and skin. whichever occurs first. Repetitively thereafter inspect at intervals not to exceed 100 hours TIS or 12 months, whichever occurs first. (ii) We will allow ``unless already done'' credit for inspections done within the last 25 hours TIS before the effective date of this AD or within the last 3 months before the effective date of this AD, and you may use the results from that inspection for the reporting requirement in paragraph (f)(10) of this AD. (3) If any cracking is found during Before further flight after the Follow Ercoupe Service Memorandums the inspections required in inspection where the cracking was No. 56 and 57 (both not dated). paragraphs (f)(1) and/or (f)(2) of found. this AD, repair or replace cracked parts. (4) For airplanes with the aileron (i) Within the next 25 hours TIS Follow Ercoupe Service Memorandums balance assembly (ERCO P/N 415- after the effective date of this AD No. 56 and 57 (both not dated). 16009) installed: Inspect the four or within 3 months after the No. 6-32 screws that attach the effective date of this AD, balance weight support to the whichever occurs first. aileron for looseness and damage. Repetitively thereafter inspect at intervals not to exceed 100 hours TIS or 12 months, whichever occurs first. (ii) We will allow ``unless already done'' credit for inspections done within the last 25 hours TIS before the effective date of this AD or within the last 3 months before the effective date of this AD, and you may use the results from that inspection for the reporting requirement in paragraph (f)(10) of this AD. (5) If any looseness or damage is Before further flight after the Follow Ercoupe Service Memorandums found during the inspection of the inspection where the looseness or No. 56 and 57 (both not dated). screws required in paragraph (f)(4) damage was found. of this AD, replace the screws with AN 526-632 screws, making sure to not overstress during tightening. (6) For airplanes with the aileron (i) Within the next 25 hours TIS Follow Ercoupe Service Memorandums balance assembly (ERCO P/N 415- after the effective date of this AD No. 56 and 57 (both not dated). 16009) installed: Inspect the or within 3 months after the aileron hinges and aileron control effective date of this AD, system for excessive looseness or whichever occurs first. wear in hinge pins or bearings. If, Repetitively thereafter inspect at with one aileron blocked in the intervals not to exceed 100 hours neutral position, the total play of TIS or 12 months, whichever occurs the other aileron, measured at the first. trailing edge, exceeds \7/16\ inch, (ii) We will allow ``unless already inspect all the joints and bearings done'' credit for inspections done and tighten or replace those which within the last 25 hours TIS after are loose. the effective date of this AD or within the last 3 months before the effective date of this AD, and you may use the results from that inspection for the reporting requirement in paragraph (f)(10) of this AD. [[Page 20897]] (7) For airplanes that have never Within the next 25 hours TIS after Follow Ercoupe Service Memorandums had the aileron balance assembly the effective date of this AD or No. 56 and 57 (both not dated). (ERCO P/N 415-16009) installed or within 3 months after the effective from which it has been removed date of this AD, whichever occurs following Ercoupe Service first. Memorandum No. 57: Inspect the aileron hinges and aileron control system for excessive looseness or wear in hinge pins or bearings. If, with one aileron blocked in the neutral position the total play of the other aileron, measured at the trailing edge, exceeds \5/16\ inch, inspect all the joints and bearings and tighten those which are loose. (8) For all airplanes: Determine Within the next 25 hours TIS after Follow FAA Advisory Circular (AC) 23- that the air speed instrument is the effective date of this AD or 8B, Appendix 9, Airspeed correctly calibrated and distinctly within 3 months after the effective Calibrations, dated August 14, marked in accordance with the date of this AD, whichever occurs 2003, or any other FAA-approved operating limitations. first. airspeed calibration method. AC 23- 8B can be found at http://rgl.faa.gov/. (9) For all airplanes: Remove load Within the next 25 hours TIS after Follow Ercoupe Service Memorandum from nose wheel and adjust rigging. the effective date of this AD or No. 35 (not dated). within 3 months after the effective date of this AD, whichever occurs first. Repetitively thereafter inspect at intervals not to exceed 100 hours TIS or 12 months, whichever occurs first. (10) For all airplanes: Report the Within 3 days after the initial Use the reporting form found in results from the inspections and/or inspections and/or actions required figure 1 and send the report to the actions required in paragraphs in paragraphs (f)(1), (f)(2), following offices: (f)(1), (f)(2), (f)(4), (f)(6), (f)(4), (f)(6), (f)(7), (f)(8), and (i) Roger A. Caldwell, Aerospace (f)(7), (f)(8), and (f)(9) of this (f)(9) of this AD or within 3 days Engineer, FAA, ANM-100D, Denver AD. after the next repetitive Aircraft Certification Office inspection and/or action required (ACO), 26805 East 68th Avenue, Room in paragraphs (f)(1), (f)(2), 214, Denver, Colorado 80249-6361; (f)(4), (f)(6), and (f)(9), and whichever occurs first. (ii) Univair Aircraft Corporation, 2500 Himalaya Road, Aurora, Colorado 80011. ---------------------------------------------------------------------------------------------------------------- Docket No. FAA-2011-0360 Inspection Report ------------------------------------------------------------------------ ------------------------------------------------------------------------ Airplane model and year of manufacture ------------------------------------------------------------------------ Airplane serial number ------------------------------------------------------------------------ Airplane registration ------------------------------------------------------------------------ Airplane tachometer hours at time of inspection ------------------------------------------------------------------------ Airspeed calibrated and marked per YES, but no YES, and paragraph (f)(8) of this AD? calibration calibration was adjustment adjusted. required. ------------------------------------------------------------------------ ------------------------------------------------------------------------ For Ercoupe Service Memorandum No. 56 ------------------------------------------------------------------------ Did aileron system play exceed \7/ NO YES, and was adjusted. 16\ of an inch? ------------------------------------------------------------------------ Was rudder looseness greater than NO YES, and was adjusted. \1/4\ of an inch at the trailing edge? ------------------------------------------------------------------------ Was there elevator motion greater NO YES, and was adjusted. than \3/8\ of an inch? ------------------------------------------------------------------------ Were any other discrepancies noticed during this inspection, to include cracks or loose hinges? ------------------------------------------------------------------------ For Ercoupe Service Memorandum No. 57 ------------------------------------------------------------------------ Does the airplane have aileron NO YES balance weights? ------------------------------------------------------------------------ If balance weights are installed, NO YES Not applicable. were the attachments secure? ------------------------------------------------------------------------ Did you remove the balance weights NO YES Not applicable. if allowed? ------------------------------------------------------------------------ If you did not remove balance NO YES Not applicable. weights, did you perform Ercoupe Service Memorandum No. 20 (Ailerons-Reinforcement of) ------------------------------------------------------------------------ If balance weights were removed, NO YES Not applicable. was the aileron free play \5/16\ of an inch or less? ------------------------------------------------------------------------ [[Page 20898]] Were any other discrepancies noticed during this inspection? ------------------------------------------------------------------------ For Ercoupe Service Memorandum No. 35 ------------------------------------------------------------------------ Did you perform steps 1, 2, and 7 NO YES of the Ercoupe Service Memorandum No. 35? ------------------------------------------------------------------------ Were any other discrepancies noticed during this inspection? ------------------------------------------------------------------------ Send report to: Roger A. Caldwell, Aerospace Engineer, FAA, ANM-100D, Denver ACO, 26805 East 68th Avenue, Room 214, Denver, Colorado 80249-6361; fax: (303) 342-1088; E-mail: [email protected]; and Univair Aircraft Corporation, 2500 Himalaya Road, Aurora, Colorado 80011 Figure 1 ------------------------------------------------------------------------ Paperwork Reduction Act Burden Statement (g) 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, 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. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, Denver 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 Principal Maintenance Inspector or Principal Avionics Inspector, as appropriate, or lacking a principal inspector, your local Flight Standards District Office. (3) AMOCs approved for AD 52-02-02 are approved as AMOCs for this AD. Related Information (i) For more information about this AD, contact Roger Caldwell, Aerospace Engineer, FAA, Denver ACO, 26805 East 68th Ave., Room 214, Denver, Colorado 80249-6361; telephone: (303) 342-1086; fax: (303) 342-1088; e-mail: [email protected]. (j) For service information identified in this AD, contact Univair Aircraft Corporation, 2500 Himalaya Road, Aurora, Colorado 80011; telephone: (303) 375-8882, facsimile: (303) 375-8888; Internet: http://univairparts.com. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust St., 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 April 7, 2011. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011-9091 Filed 4-13-11; 8:45 am] BILLING CODE 4910-13-P