REVO - Luftfartstilsynet

(h) What ir I need to fly the airplane to another location to comply with this AD? The FAA can issue a special tlght permitundèr'sections 21.97 and 21.99 of the Federal Aviation Regulations (14 CFR 21.97 and 21.99) to operate your airplan~ t~a"location where you can accomplish the requirements ofthis AD. , (i) Areaiiy service bulletins incorporated into this AD by reference? Actions required by this AD must be (jone in accordance ReX'i Inc. Service Bulletin B-79 RI - Revised January 5, 2000. The Director of the Federal Register approved this incorporation 'by reference under 5 U.S.C. 552(a) and i CFR part 51. Y ou can get copies from REYO, lncorporated, P.O. Box 3,J.2,;One High Street, Sanford, Maine 04073. You can look at copies at FAA, Central Region, Offc~C?f the Regional Coun"sel, 90 i Locust, Room 506, Kansas City, Missouri; or at the Offce of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (j) When does this amendment become errective? This amendment becomes effective on June 20, 2000. FOR FURTHER INFORMATION CONTACT: Mr. Richard B. NolI, Aerospace Engineer, F AA, Boston Aircraft Certification Office, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone: (781) 238-7160; facsimile: (781) 238-7199. Issued in Kansas City, Missouri, on May 17,2000. Michael Gallagher, Manager, Small Airplane Directorate, Aircraft Certification Service. L I i. I ~ BLANK LUFTFARTSTILSYNET 1. TILSYNSAVDELING Postboks 8050 Dep., 0031Os1o Besøksadresse: Rådusgata 2, Oslo Telefon : 23 31 78 00 Telefax: 23 31 79 95 E-post: postmottak(Qcaa.dep.no MOTORDREVNE LUFFART0Y o LUFTDYKTIGHETSP ABUD (LDP) REVO - 2 Med hjemmel i lov av I L. juni 1993 nr. 101 om luftfart, kap. XV § 15-4 jf. kap. IV § 4-1 og Samferdselsdepartementets bemyndigelse av 25. mars 1994, fastsetter Luftfartstilsynet følgende forskrift om luftdyktighet. 2002-085 SPREKKONTROLL A V "WING SP AR DOUBLER AND ANGLES" Påbudet gjelder: Revo, Incorporated, alle Lake modeller som er listet i vedlagte kopi av F AA AD 2002- 21-05. Påbudet omfatter: Utfør tiltak som beskrevet i vedlagte kopi av FAA AD 2002-21-05. I. I. Anm.: Figure 1 to AD 2002-21-05 skal sendes F AA med kopi til Luftfartstilsynet. Tid for utførelse: Til de tider som beskrevet i vedlagte kopi av FAA AD 2002-21-05. Referanse: FAA AD 2002-21-05. Gyldighetsdato : 2002-11-18 MERK! For at angjeldende flymateriell skal være luftdyktig må påbudet være utført til rett tid og notat om utførelsen ført in i vedkommende journal med henvisning til denne LDPs numer. AIRWORTHINESS DIRECTIVE: I. Aircraft eertification Service Washington, De U.5. Department of Transportation Federal Aviation Administration We post ADs on the internet at "ww.airweb.faa.govlrgl" The following Airworthiness Directive issued by the Federal Avialion Adminislralion in accrdance with the provisions ol Tille 14 of the Code of Federel Regulalions (14 CFR) part 39, applies to an aircrfl model of which our records indicale you may be the regislered owner. Airwrtiness Direives afect avielion safety and are regulations which reuire immediate atlention. You are cautioned that no person may operale an aircraft to which an Airwortiness Direclve epplies, except in accrdance with the requirements ol the Airwrtiness Directive (reference 14 CFR part 39, subpart 39.3). 2002-21-05 Revo, Incorporated: Amendment 39-12911; Docket No. 2002-CE-40-AD. (a) What airplanes are affcted by this AD? This AD applies to the model and serial number airplanes in paragraph (a)(1) ofths AD and that incorporate any of the wing spar par numbers (or FAA-approved equivalent par numbers) specified in paragraph (a)(2) ofthis AD: (1) Affected Airplanes: This following model and serial number airplanes, certificated in any category, are affected by this AD: Model Lake LA-4 Lake LA-4A Lake LA-4P Lake LA-4200 Lake Model 250 Serial Nos. 246 though 421,423 through 429,445, and 446. 244 and 245. 121. 422,430 through 444, and all serial numbers after 446. 1 through 232. (2) Wing Spar Par Numbers Incorporated: The following specifies the par numbers ofthe wing spars that are installed on the affected airplanes: Wing spar parts Upper Spar Cap Angles Lower Spar Cap Angles Upper Spar Doublers Lower Spar Doublers Part N os. 2-1610-15 and 2-1610-16. 2-1610-75 and 2-1610-76. 2-1610-061 and 2-1610-81 and 2-1610-065. 2-1610-063 and 2-1610-083. (b) Who must comply with this AD? Anyone who wishes to operate any of the airplanes identified in paragraph (a) ofthis AD must comply with this AD. (c) What problem does this AD address? The actions specified by this AD are intended to prevent wing spar failure caused by cracks in the wing spar doublers or angles, which could result in the wing separating from the airplane with consequent loss of contro!. (d) What must I do to address this problem? To address ths problem, you must accomplish the following actions: 5 Actions ' .'. (1) Inspect the wing spar dpublers and spar cap.angles for cracks from the root end to the outboard of.the.. wing attachment fittings, aS follows: (i) From inside the wheel well, clean thé'ûppe(ard; lower wing spar doublers and adjQin.ng structue to the paint. Use a detergent or mineral-based solvent. (ii) Use a strong light source and a 3x magnifying glass to inspect the exposed areas of the upper and lower spar doublers and adjoining structue for cracks. Use a mirror to inspect the exposed edge of the spar cap angle behind the doubler. (2) Replace any doubler or angle found cracked durng the inspection required by paragraphs (d)(l), (d)(1)(i), and (d)(l)(ii) ofthis AD. Replace with new pars that incorporate the same par numbers or FAA- approved equivalent par numbers. (3) Report the results of the inspection to the F AA at the address specified in paragraph (f) ofthIs AD. Use the inspection report that is included as Figure 1 of this AD. The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and assigned OMB Control Number 2120-056. Compliance Upon accumulating 25 hours time-In- service (TIS) after incorporating Modification B-79 or FAA-approved equivalent (the modification required by AD 2000-10-22) or withIn the next 10 hours TIS after October 23,2002 (the effective date ofthis AD), whIchever occurs later, uness already accomplished after accumulating 25 hours TIS after incorporating the modification required by AD 2000-10-22. Prior to fuher £lght after the inspection. , , I I I " , Within 7 days after the the inspection required by this AD or 7 days after October 23,2002 (the effective date ofthIs AD), whIchever occurs later. 6 FIGURE L TO AD 2002-21-05 INSPECTION REPORT Report the following information to: Manager, Boston Aircraft Certification Offce Engine And Propeller Directorate Aircraft Certification Service Federal Aviation Administration 12 New England Executive Park Burlington, MA 01803-5299 Fax: (781) 238-7170 OperatorIRepair Station Aircraft Mode! Aircraft SIN Date of Inspection Aircraft Time-in Service (TIS): Total Since installation of AD 2000-10-22 Kit NOTE: Add additional pages for the following for each par inspected. Par No. Inspection Pass Fail Ifa crack is found, indicate the approximate location on the par and the length of the crack in inches: Par Time-In Service (TIS) (Hours): Estimated Actual Unkown 7 (e) Can I comply with this AD in any other way? You may use an alternative method of compliance or adjust the compliance time if: (1) Your alternative method ofcompliance provides an equivalent leve! of safety; and (2) The Manager, Boston Aircraft Certification Office (ACO), approves your alternative. Submit your request through an F AA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Boston ACO. Note: This AD applies to each airplane identified in paragraph (a) ofthis AD, regardless ofwhether it has been modified, altered, or repaired in the area subject to the requirements ofthis AD. For airplanes that have been modified, altered, or repaired so that the perfonnance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) ofthis AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, ifyou have not eliminated the unsafe condition, specific actions you propose to address it. (f) Where can I get information about any already-approved alternative methods of compliance? Contact Mr. Richard B. Noll, Aerospace Engineer, F AA, Boston Aircraf Certification Office, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone: (781) 238-7160; facsimile: (781) 238-7170. (g) What if I need to lly the airplane to another location to comply with this AD? The F AA can issue a special flght pennit under sections 21.197 and 21.199 ofthe Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate your airplane to a location where you can accomplish the requirements ofthis AD. (h) When does this amendment be come effective? This amendment becomes effective on October 23, 2002. Issued in Kansas City, Missouri, on October 8, 2002. Michael Gallagher, Manager, Small Airplane Directorate, Aircraft Certification Service. (FR Doc. 02-26371 Filed 10-16-02; 8:45 am) BILLING CODE 491O-13-P 8 BLANK LUFARTSTILYNET L. TILYNSAVDELING Postboks 8050 Dep., 0031Osl0 Besøksadresse: Rådusgata 2, Oslo Telefon : 23 31 78 00 Telefax: 23 3 i 79 95 E-post: postmottkêcaa.dep.no MOTORDREVNE LUFFART0Y o LUFTDYKTIGHETSPABU D REVO - 3 Med hjemmel i lov av L 1. juni 1993 nr. 101 om luftfart, kap. XV § 15-4 jf. kap. IV § 4-1 og Samferdselsdepartementets bemyndigelse av 25. mars i 994, fastsetter Luftfartstilsynet følgende forskrift om luftdyktighet. ! 2005-037 SPREKKONTROLL I SKIFTE A V "HORIZONTAL STABILIZER ATT ACHMENT FITTING" Påbudet gjelder: Revo, Incorporated, alle Lake modeller som er listet i vedlagte kopi av F AA AD 2005-12-02. Påbudet omfatter: Utfør tiltak som beskrevet i vedlagte kopi av FAA AD 2005-12-02. Anm.: Dersomfeil oppdages skal utflt skjema i samsvar med Figure 1 i AD 2005-12-02 sendes F AA på angitte adresse, med kopi til Luftfartstilsynet. Tid for utførelse: Til de tider og intervaller som er beskrevet i vedlagte kopi av FAA AD 2005-12-02. Referanse: FAA AD 2005-12-02. Gyldighetsdato: 2005-07-08. MERK! For at angjeldende flymateriell skal være luftdyktig må påbudet være utført til rett tid og notat om utførelsen ført inn i vedkommende journal med henvisning til denne LDPs nummer. AIRWORTHINESS DIRECTIVE Aircraft Certification Service Washington, DC U.5. Department of Transportation Federal Aviation Administration We post ADs on the internet at "wwfaa.gov" The following Airworthiness Directive issued by the Federal Aviation Administration In accordance with the provisions of nle 14 of the Code of Federal Regulations (14 CFR) part 39, appiies 10 an alrcraft mod ei of which our records indicate you may be the registered owner. Airworthiness Directives affecl aviatlon safety and are reguiations which require immediate atlention. Vou are cautioned that no person may operate an aircraft to which an Airwortiness Directive appiies, e.cept in accordance with the requirements of the Airworthiness Directive (reference 14 CFR part 39, subpart 39.3). 2005-12-02 Revo, Incorporated (Type Certificate 1A13 formerly held by Colonial Aircraft Company, Lake Aircraft Corporation, Consolidated Aeronautics, Inc., and Global Amphibians LLC): Amendment 39-14118; Docket No. FAA-2005-21092; Directorate Identifier 2005-CE-20-AD. When Does This AD Become Effective? (a) This AD becomes effective on luly 8, 2005. Aire Any Other Ans Affected By This Action? (b) Yes. This AD supersedes AD 98-10-12; Amendment 39-10524. What Airplaimes Are Afected by Tros AD? (c) This AD affects Models Colonial C-2, Lake LA-4, Lake LA-4A, Lake LA-4P, and Lake LA- 4-200, all serial numbers, that are certificated in any category. What is the Unsafe Condition Presented in Tids AD? (d) This AD is the result of several rep arts of fatigue cracks found in the horizontal stabilzer attachment fitting (part number (P/N) 2-2200-21) of Model LA-4-200 airplanes and one report of a Model LA-4-200 airplane accident with a fatality attributed to a fatigue crack in the horizontal stabilzer attachment fitting. We are issuing this AD to detect, correct, and prevent future cracks in the horizontal stabilzer attachment fitting (P/N 2-2200-21), which could result in failure of the horizontal stabilizer attachment fitting. This failure could result in loss of control of the airplane. Wbat Mest I Do To Addiress This Piroblem? (e) To address this problem, you must do the following: 5 Actions (1) For airplanes with 825 hours time-in-service (TIS) or more on any horizontal stabilzer attachment fitting as of July 8, 2005 (the effective date ofthis AD): (i) Replace the horizontal stabilzer attachment fitig (part number (P/N) 2-2200-21). (ii) If necessary, trim the horizontal stabilzer rear beam doublèr flange to provide positive clearance to the fitting. (2) For airplanes with less than 825 hours ris on any horizontal stabilizer attachment fitting as of July 8,2005 (the effective date ofths AD): (i) Remove the horizontal stabilzer attachment fittig (P/N 2-2200-21) from the airplane and inspect for cracks (using dye penetrant), fretting, or corrosion. To take "already done' , credit for this, you must have removed the fitting from the airplane when the inspection was done. (ii) Replace any horizontal stabilzer attachment fittingif you find any cracks, fretting, or corrosion. (3) For all airplanes: Repetitively replace the horizontal stabilzer attachment fittings upon accumulating 850 hours TIS on the fittings. (4) For all airplanes: Measure the gap between the horizontal skin and the horizontal stabilzer attachment fitting (P/N 2-2200-21). If gap is less than 116-inch, trim the skin to provide at Ieast 1 16-inch gap. Compliance Within the next 25 hours TIS after luly 8, 2005 (the effective date of this AD) Repetitively replace any horizontal stabilzer attachment fitting (P/N 2-2200-21) thereafter following paragraph (e) (3) of this AD. Inspect withn the next 25 hours TIS after luly 8, 2005 (the effective date of this AD), unless already done. If cracks, fretting, or corrosion is found, replace befare further flght after the inspection. Every 850 hours TIS Before further flght after any replacement of the fittig required by paragraphs (e) (1), (e) (2), and (e) (3) of this AD. 6 Procedures Follow Revo, Inc. Service Bulletin B-78, dated April 3, 1998, paragraphs 2 and 3 of the INSPECTION and REP AIR section and the APPENDIX. Follow Revo, Inc. Service Bulletin B-78, dated April 3, 1998, INSPECTION and REP AIR section and the APPENDIX. I- I i I Follow Revo, Inc. Service Bulletin B-78, dated April 3, 1998, paragraphs 2 and 3 of the INSPECTION and REPAIR section and the APPENDIX. Follow Revo, Inc. Service Bulletin B-78, dated April 3, 1998. (5) For all airplanes: Repetitively inspect (visual) the horizontal stabilzer attachedment fitting using the following procedures. (i) Mave the elevator as required to see the fittig, ensuring that the aft face of the fitting is visible. (ii) Clean the fitting. Pay special attention to the radius edges of the fittingjust outboard of the fitting ear. (iii) Visually inspect the fitting for cracks using a flashlight (a small magnifying glass or bores cape is recommended). Pay special attention again to the radius edges just outboard of the fitting ear. Also, inspect as far forward on the edge that is possible because same cracks progress along the forward face of the fitting that is mostly hidden by the horizontal stabilizer rear beam. (iv) Reference the sketch on page 1 of the Service Bulletin B-78 to see where the crack is likely to begin. .(v) Replace the fitting prior to further flght if cracks are found during any of these inspections. (6) For all airplanes: Report to F AA the results of the initial inspection required by paragraph (e) (2) of this AD even if no damage is found, and report the results of the repetitive inspections required by paragraph (e) (2) of this AD only if cracks are found. The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions of Paperwork Reduction Act of 1980 (44 D.S.C. 3501 and those following sections) and assigned OMB Contral Number 2120-0056. (7) For all airplanes: Do not install used serviceable fittings, unless you know the number of accumulated hours TIS and have inspected following the requirements of paragraph (e) (2) of this AD. Repetitively inspect at whichever of the following that occurs first (first repetitive starts after the initial inspection or replacement) : · 50 hours TIS; or · the next annual inspection Replace the fitting prior to further £light after any inspection where cracks are found. Within 10 days after the inspection required by paragraph (e) (2) or (e) (5) of this AD or within 10 days after luly 8, 2005 (the effective date of this AD), whichever occurs later. As of luly 8, 2005 (the effective date of this AD). 7 Follow the procedures presented in the Actions column of this paragraph, including the sketch on page 1 of the Service Bulletin B- 78. Send the form (Figur e 1 of this AD) to F AA, Atlanta ACO, 1895 Phoenix Boulevard, suite 450, Atlanta. Georgia 30349; telephone: (770) 703- 6078; facsimile: (770) 703-6097. Not Applicable. AD **-**-** INSPECTION REPORT 1. Inspection Perormed By: 2. Telephone: 3. Aircraft Model: 4. Aircraft Serial Number: 5. Date of AD Inspection: 6. Total hours time-in-service (1IS) on the fitting: 7. Cracksfound? 8. Length ofCrack(s): D Yes aNa Left jUting: a Lel fitting a Rightfilting Right fitting 9. Fretting found? 10. Corrosion found? a res aNo a Yes aNo a Lef fitting a Right fitting a Left jUting a Right jUting Send to: Federal AviatIon Admstration Atlanta Aircraft Certification Offce 1895 PhoenIx Boulevard, Suite 450 Atianta, Georgia 30349 Telephone: (770) 703-6078 Facsimle: (770) 703.6097 i I- i Figue 1. May I Request aJ Ahernative Method of Compiiance? (f) You may request a different method of compliance or a different complianee time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and wil send your request to the Manager, Atlanta Aircraft Certification Offce (ACO) , F AA. For information on any already approved alternative methods of compliance, contact Cindy Lorenzen, Aerospace Engineer, FAA, Atlanta ACO, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; telephone: (770) 703- 6078; facsimile: (770) 703-6097. May I Obtai aSpecia! Flight Permit for the Initial Inspection or Replacemeiit Requiirement of Tids AD? (g) Yes. Special flght permits are allowed for this AD with these limitations: (1) Vne reduced to 121 m.p.h. (105 knots); and (2) N o flght into known turbulence. 8 Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by this AD following the instructions in Revo, Inc. Service Bulletin B-78, dated April 3, 1998. The Director of the Federal Register approved the incorporation by reference ofthis service bulletin in accordance with 5 US.C. 552(a) and 1 CFR part 51. To get a copy ofthis service information, contact Revo, Incorporated, 1396 Grandview Boulevard, Kissimmee, FL 34744. To review copies ofthis service information, go to the National Archives and Records Administration (NARA). For information on the availabilty ofthis material at NARA, go to: http://ww.archives.gov /federaLregister!code_or-federaLregulationslibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facilty; US. Department of Transportation, 400 Seventh Street, S.W., Nassif Building, Room PL-401, Washington, DC 20590- 001 or on the Internet at http://dms.dot.gov. The docket number is FAA-200s-21092; Directorate Identifier 200s-CE-20-AD. Issued in Kansas City, Missouri, on lune 2, 2005. Kim Smith, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. (FR Doc. 05-11361 Filed 6-9-05; 8:45 am) BILLING CODE 491O-13-P I 9