COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Schweizer (Hughes) 269 Series Helicopters AD/HU 269/85 Amdt 2 Tail Rotor Blade Abrasion Strip 6/91 DM Applicability: All models 269 series helicopters, certified in any category, equipped with 269A6035 series tail rotor blades manufactured before 15 September 1989. Requirement: Action in accordance with the technical requirement of FAA AD 89-20-03 R1, which requires the following: 1. Modify the affected tail rotor blades with the following serial numbers (S/N) in accordance with the procedures detailed in Schweizer SIN N-183.3 Part III. Blade S/N's Affected R0056 S521 S573 S638 R0086 S524 S576-S582 S640-S644 R1059 S534 S584 S646 R1066 S538 S586 S648-S650 R1560 S539 S588 S653 R1922 S544 S589-S594 S654 R3296 S546 S596 S657 R3314 S547 S598-S603 S660-S662 R3330 S549 S605 S664-S666 R3349 S550 S607 S668 S21 S553 S608 S670-S672 S431 S556-S563 R611-S620 S675-S677 S513 S565 S623-S626 S679-S682 S515 S566 S631-S633 S684-S688 S518 S568-S571 S637 S691-S694 2. Modify all tail rotor blades, whether manufactured by Schweizer or Hughes, except those listed in Requirement 1, in accordance with procedures detailed in Schweizer SIN N-183.3 Part III. 3. Visually check the abrasion strip of these blades for any evidence of cracking or chipping along the entire abrasion strip/airfoil bond line and the blade tip. (a) If, during the check required by Requirement 3, cracking or chipping is observed, inspect the bond line for bond separation using a 10 power or higher magnifying glass. If evidence of debonding along the abrasion strip/bond line or blade tip is detected, inspect the tail rotor blade using dye penetrant or equivalent inspection method and tap test prior to further flight in accordance with Schweizer SIN N-183.3 Part II. COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES (b) Remove from service, prior to further flight, any rotor blade found to contain bond separation. Note 1: Blades modified to Schweizer Installation Instructions No. CKP-C-40, Kit No. SCA-269-K-056, dated 31 August 1989, or Schweizer Service Information Notice No. N-183.3, 15 September 1989, Part III, comply with Requirements 1 and 2. Note 2: Tail rotor blades manufactured by Schweizer with a bond date on or after 15 September 1989, shown on the identification plate located on the inboard end of the blade, are exempt from the requirements of this AD. Compliance: 1. Unless already accomplished in accordance with AD/HU 269/85 Amdt 1; Prior to further flight after 10 April 1991. 2. Within 100 hours time in service after 10 April 1991. 3. At each daily inspection. Note: This Directive shall be entered on the Maintenance Release as maintenance required. The visual inspection required by Requirement 3 may be performed by the Pilot in command, in which case certification is to be made by entering AD/HU 269/85 against the daily inspection certification of the Maintenance Release. A copy of this Airworthiness Directive is to be kept in the aircraft. Background: The FAA has issued a new Airworthiness Directive, which amends an existing FAA AD that requires an inspection and modification of the abrasion strip of tail rotor blades with certain serial numbers; and supersedes an FAA AD for the same model helicopter that currently requires an inspection of Hughes-manufactured tail rotor blades with certain serial numbers This AD is prompted by reports of separation of the abrasion strips from tail rotor blade skins, which if not corrected, could result in the loss of abrasion strips, loss of tail rotor blades, and subsequent loss of control of the helicopter. Effective date required by the FAA extended by six weeks.