AD 2000-16-04 Airworthiness Directives; Bell Helicopter Textron Canada (BHTC) Model 430 Helicopters

Models named: 430. Read the applicability below — it usually turns on serial or part numbers too.

Model 430 helicopters, 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 (d) 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 prevent tip path plane separation, increased vibrations, damage to the main rotor system, and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight: (1) Inspect all four main rotor adapter assemblies for flapping contact between the adapter liners and the upper stop assembly plugs. Refer to Figures 1, 2, and 3 of the Accomplishment Instructions of Bell Helicopter Textron Canada (BHTC) Alert Service Bulletin (ASB) No. 430-97-2, dated July 11, 1997. Flapping contact is indicated by the scrubbing (or smudging) of the adapter liner surface, characteristic of relative motion between the surfaces of the adapter lines and upper stop assembly plugs. (2) Inspect all four main rotor adapter assemblies for lead-lag contact between the adapter pads and the yoke assembly. Refer to Figures 1 and 2 of the Accomplishment Instructions of BHTC ASB No. 430-97-2, dated July 11, 1997. Lead-lag contact is indicated by a permanent indentation or split in the surface of the adapter pads. (3) If the inspections in paragraphs (a)(1) or (a)(2) of this AD reveal that there has been contact, inspect and replace the main rotor yoke and stop assemblies in accordance with Part I, No. 3 of the Accomplishment Instructions of BHTC ASB No. 430-97-2, dated July 11, 1997, except return of any damaged upper stops to the manufacturer is not required. (4) For helicopters with skid landing gear or retractable landing gear, remove the existing never-exceed-velocity (VNE) placard from the overhead console and install VNE placard, P/N 430-075-208-107, or P/N 430-075-208-109, as applicable, in accordance with Part II, of the Accomplishment Instructions of BHTC ASB No. 430-97-2, dated July 11, 1997. (5) Install on each airspeed indicator a red arc between 120 knots and 150 knots to indicate that airspeeds above 120 knots indicated airspeed are prohibited. Install a slippage mark on each airspeed indicator glass and instrument case. (6) Insert the temporary revisions, BHT-430-FM-1 and BHT-430-FMS-1, as appropriate, both dated July 7, 1997, into the rotorcraft flight manual. (b) Within 100 hours time-in-service, (1) Remove the fluidlastic damper blade set, P/N 430-310-100-101 or 430-310-107-101 in accordance with the Accomplishment Instructions of ASB 430-97-4, dated December 19, 1997, Part 1, steps 1 through 5, and install damper blade set, P/N 430-310-104-105, in accordance with the Accomplishment Instructions, Part I, of BHTC ASB 430-98-8, dated December 31, 1998. (2) Return pilot and copilot airspeed indicators to their original configuration by removing the markings specified by paragraph (a)(5) of this AD. (3) Remove the temporary revisions, BHT 430-FM-1 or BHT-430-FMS-1, as appropriate, both dated July 7, 1997. Insert the temporary revisions, BHT-430-FM-1, or BHT-430-FMS-1, as appropriate, both dated December 11, 1998, into the rotorcraft flight manual. (c) If paragraph (b)(1) was previously accomplished by installation of fluidlastic damper blade set, P/N 430-310-104-103, remove fluidlastic damper blade set, P/N 430-310-104-103, and install fluidlastic damper blade set, P/N 430-310-104-105, in accordance with the Accomplishment Instructions of BHTC ASB 430-98-8, dated December 31, 1998. (d) 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, Regulations Group, FAA, Rotorcraft Directorate, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Regulations Group. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Regulations Group. (e) Special flight permits may be issued 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. (f) The main rotor adapter assembly inspections and replacement and the placard modifications shall be done in accordance with Part I, No. 3, and Part II of the Accomplishment Instructions and references to Figures 1, 2, and 3 in Bell Helicopter Textron Canada Alert Service Bulletin No. 430-97-2, dated July 11, 1997. The incorporation by reference of that document was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51, as of October 24, 1997 (62 FR 52653, October 9, 1997). The removal of certain fluidlastic damper blade sets shall be done in accordance with the Accomplishment Instructions of Bell Helicopter Textron Canada Alert Service Bulletin 430-97-4, dated December 19, 1997, Part 1, steps 1 through 5. The removal and installation of certain damper blade sets shall be done in accordance with the Accomplishment Instructions of Bell Helicopter Textron Canada Alert Service Bulletin No. 430-98-8, dated December 31, 1998. The incorporation by reference of those documents was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Bell Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec JON1LO, telephone (800) 463-3036, fax (514) 433-0272. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on September 19, 2000. Note 3: The subject of this AD is addressed in Transport Canada (Canada) AD No. CF-97-23R1, dated March 30, 1999. Issued in Fort Worth, Texas, on August 2, 2000. Henry A. Armstrong, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 00-20403 Filed 8-14-00; 8:45 am] BILLING CODE 4910-13-U