CAA-AD-065/2003

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(1) CAA-AD-065/2003 1/4 PŘÕKAZ K ZACHOV¡NÕ LETOV… ZPŮSOBILOSTI ⁄ŘAD PRO CIVILNÕ LETECTVÕ ČESK¡ REPUBLIKA Sekce technick· letiötě Ruzyně, 160 08 Praha 6 tel: 233320922, fax: 220562270 ČÌslo: CAA -AD-065/2003 Nahrazuje CAA-AD-T-115/2001 Datum vyd·nÌ: 18. července 2003 Schweizer Aircraft Corp. 269A, 269A-1, 269B, 269C, TH-55A VRTULNÕK - SILOV› UZEL PŘÕHRADOV… KONSTRUKCE DRAKU ñ KONTROLA/V›MĚNA T˝k· se: vrtulnÌků 269A, 269A-1, 269B, 269C, TH-55A vyroben˝ firmou Schweizer Aircraft Corp., certifikovan˝ch ve kterÈkoliv kategorii, vybaven˝ch uzlem vzpěry ocasnÌho nosnÌku jak je blÌûe specifikov·no v č·sti ÑApplicabilityì FAA AD 2003-13-15 (přÌloha tohoto PZZ). Důvod vyd·nÌ: předejÌt poruöe oka třmenu zadnÌ vzpěry silovÈho uzlu přÌhradovÈ konstrukce draku, coû můûe vÈst k otočenÌ ocasnÌho nosnÌku do roviny ot·čenÌ listů hlavnÌho rotoru a n·slednÈ ztr·tě řiditelnosti vrtulnÌku. Datum ˙činnosti: ihned po obdrûenÌ. ProvÈst v termÌnech: Jak je pops·no v FAA AD 2003-13-15 od data ˙činnosti tohoto PZZ. Postup provedenÌ pracÌ: Dle FAA AD 2003-13-15. Pozn·mky: - ProvedenÌ tohoto PZZ musÌ b˝t zaps·no do letadlovÈ knihy. - PřÌpadnÈ dotazy t˝kajÌcÌ se tohoto PZZ adresujte na ⁄CL sekce technick· ñ Ing. B. Fiala. - Pokud to vyûaduje povaha tohoto PZZ, musÌ b˝t zapracov·n do přÌsluönÈ č·sti dokumentace pro obsluhu, ˙drûbu a opravy letadla. - Tento PZZ byl vypracov·n na z·kladě FAA AD 2003-13-15, kter˝ nahrazuje FAA E AD 2001-25-52. Ing. Pavel MATOUäEK ředitel CAA-AD-065/2003 2/4 2003-13-15 Schweizer Aircraft Corporation: Amendment 39-13217. Docket No. 2002-SW-25-AD. Supersedes AD 2001-25-52, Amendment 39-12726, Docket No. 2001-SW-58-AD. Applicability: Model 269A, 269A-1, 269B, 269C, and TH-55A helicopters, certificated in any category, with a tailboom support strut (strut) assembly, part number (P/N) 269A2015 or 269A2015-5; or with a center frame aft cluster fitting, P/N 269A2234 or 269A2235, and an aft cluster fitting listed in the following table: Helicopter model number Helicopter serial number With aft cluster fitting, P/N Model 269C 0570 through 1165 269A2234-3 Model 269C 0500 through 1165 269A2235-3 Model 269A, A-1, B, or C, or TH- 55A All 269A2234-3 or 269A2235-3 Exception: For the Model 269A, A-1, B, or C or TH-55A helicopters with Hughes-manufactured cluster fittings, P/N 269A2234-3 or P/N 269A2235-3, installed, if there is written documentation in the aircraft or manufacturer's records that shows the cluster fitting was originally sold by Hughes after June 1, 1988, the requirements of this AD are not applicable. Note 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (h) of this 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 if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent failure of a tailboom support strut or lug on a cluster fitting, which could cause rotation of a tailboom into the main rotor blades, and subsequent loss of control of the helicopter, accomplish the following: (a) Within 10 hours time-in-service (TIS), and thereafter at intervals not to exceed 50 hours TIS, for helicopters with cluster fittings, P/N 269A2234 or P/N 269A2235: (1) Using paint remover, remove paint from the lugs on each cluster fitting. Wash with water and dry. The tailboom support strut must be removed prior to the paint stripping. (2) Dye-penetrant inspect the lugs on each cluster fitting. See the following Figure 1: BILLING CODE 4910-13-P CAA-AD-065/2003 3/4 Figure 1 BILLING CODE 4910-13-C (3) If a crack is found, before further flight, replace the cracked cluster fitting with an airworthy cluster fitting. (b) Cluster fittings, P/N 269A2234 and P/N 269A2235, that have NOT been modified with Kit P/N SA-269K- 106-1, are NOT eligible replacement parts. (c) Within 150 hours TIS or 6 months, whichever occurs first, replace each cluster fitting, P/N 269A2234 and P/N 269A2235, with an airworthy cluster fitting or modify each cluster fitting, P/N 269A2234 and P/N 269A2235, with Kit, P/N SA-269K-106-1. Installing the kit is terminating action for the 50-hour TIS repetitive dye-penetrant inspection for these cluster fittings. Broken or cracked cluster fittings are not eligible for the kit modification. (d) For helicopters with strut assemblies, P/N 269A2015 or 269A2015-5, accomplish the following: (1) At intervals not to exceed 50 hours TIS: (i) Remove the strut assemblies, P/N 269A2015 or P/N 269A2015-5. (ii) Visually inspect the strut aluminum end fittings for deformation or damage and dye-penetrant inspect the strut aluminum end fittings for a crack in accordance with Step II of Schweizer Service Information Notice No. N- 109.2, dated September 1, 1976 (SIN N-109.2). (iii) If deformation, damage, or a crack is found, before further flight, modify the strut assemblies by replacing the aluminum end fittings with stainless steel end fittings, P/N 269A2017-3 and -5, and attach bolts in accordance with Step III of SIN N-109.2; or replace each strut assembly P/N 269A2015 with P/N 269A2015-9, and replace CAA-AD-065/2003 4/4 each strut assembly P/N 269A2015-5 with P/N 269A2015-11. (2) Within 500 hours TIS or one year, whichever occurs first, modify or replace the strut assemblies in accordance with paragraph (d)(1)(iii) of this AD. (e) For the Model 269C helicopters, within 100 hours TIS, serialize each strut assembly, P/N 269A2015-5 and