Document ID: chunk:federal_register_of_legislation:F2006B10644:body:0:p1
Version: federal_register_of_legislation:F2006B10644
Segment Type: other
Provision Reference: 
Character Range: 4–3548

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