AD 99-13-12 Airworthiness Directives; Bell Helicopter Textron Canada Model 206L, 206L-1, 206L-3, and 206L-4 Helicopters

Models named: 206L, 206L-1, 206L-3, 206L-4. Read the applicability below — it usually turns on serial or part numbers too.

Model 206L helicopters, serial numbers (S/N) 45004 through 45153, and 46601 through 46617; Model 206L-1 helicopters, S/N 45154 through 45790; Model 206L-3 helicopters, S/N 51001 through 51613; and Model 206L-4 helicopters, S/N 52001 and higher, with tailboom, part number (P/N) 206-033-004-all dash numbers, installed, certificated in any category. 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 (f) 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.

Required as indicated, unless accomplished previously. To detect a crack in the tailboom skin and to prevent separation of the tailboom from the helicopter and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, and thereafter, at intervals not to exceed 10 hours time-in-service (TIS) until accomplishing the one- time fluorescent-penetrant inspection (FPI) required by paragraph (c)(2) of this AD, [[Page 33749]] visually inspect for any crack in the shaded areas shown in Figure 1. Use a 10-power or higher magnifying glass. If any crack is found, replace the tailboom with an airworthy tailboom. (b) At intervals not to exceed 5 hours TIS, visually conduct a preflight check of the shaded areas shown in Figure 1 for any crack. If any crack is found, replace the tailboom with an airworthy tailboom. The visual check may be performed by an owner/operator (pilot) holding at least a private pilot certificate, and must be entered into the aircraft records showing compliance with paragraph (b) of this AD in accordance with sections 43.11 and 91.417 (a)(2)(v) of the Federal Aviation Regulations (14 CFR sections 43.11 and 91.417 (a)(2)(v)). (c) Within 50 hours TIS: (1) Remove all 4 horizontal stabilizer supports, P/N 206-023- 100-all dash numbers, from the tailboom and the horizontal stabilizer. (2) Perform a one-time FPI of the edges of the tailboom skins for any crack around the left and right horizontal stabilizer openings (Figure 1). Remove paint and primer to inspect the edges and exterior skin surface in the skin area at least \3/4\ inch around the edges of the horizontal stabilizer openings. (3) If a crack is found, replace the tailboom with an airworthy tailboom. BILLING CODE 4910-13-P [[Page 33750]] [GRAPHIC] [TIFF OMITTED] TR24JN99.102 BILLING CODE 4910-13-C [[Page 33751]] (d) At intervals not to exceed 100 hours TIS after completion of the FPI, accomplish the following: (1) Remove all 4 horizontal stabilizer supports, P/N 206-023- 100-all dash numbers, from the tailboom and the horizontal stabilizer. (2) Visually inspect the entire edge of the horizontal stabilizer opening on both sides of the tailboom for any crack using a 10-power or higher magnifying glass. (3) If any crack is found, replace the tailboom with an airworthy tailboom. (e) Insert a copy of this AD into the Rotorcraft Flight Manual. (f) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Rotorcraft Certification Office, FAA, Rotorcraft Directorate. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Certification Office. (g) Special flight permits may be issued for a one-time flight, not to exceed 5 hours TIS and a maximum of one landing, in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the helicopter to a location where the requirements of this AD can be accomplished. The visual preflight check required by paragraph (b) must be accomplished prior to making a one-time flight. (h) This amendment becomes effective on July 9, 1999. Note 3: The subject of this AD is addressed in Transport Canada (Canada) AD No. CF-98-42R1, dated February 16, 1999. Issued in Fort Worth, Texas, on June 16, 1999. Henry A. Armstrong, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 99-15925 Filed 6-23-99; 8:45 am] BILLING CODE 4910-13-P