Document ID: chunk:federal_register_of_legislation:F2006B10747:reg:4008
Version: federal_register_of_legislation:F2006B10747
Segment Type: reg
Provision Reference: reg 4008
Character Range: 6333–8826

4008  4062  4779  4780   4782  5956  5957  7037  AE57   AE96.

                 Tail rotor blade P/N 369A1100-501, -503 Serial numbers: AC10 AM10 Y249 Y268.
2.    Affected main rotor blades

                 Visually inspect leading edge abrasion strip attachment integrity. Any blisters, bubbling or lifting of the strip is cause for removal before further flight.

3.    Affected tail rotor blades

                   (a)     Dye-penetrant inspect and tap test per Part 1 of MDHC SI Nos DN-130.2, EN- 19.2, FN-17.1 or HN-197.2 as applicable.

                   (b)     Visually inspect each tail rotor blade abrasion strip for any evidence of bond failure along the abrasion strip/airfoil bond line.

               Note: If evidence of separation along the abrasion strip/airfoil bond line is suspected; using a 10X magnifying glass, closely check along abrasion strip/airfoil bond line and at blade tip for any separation between epoxy adhesive and abrasion strip.

               Any blade with void or bond separation beyond prescribed limits must be removed from service before further flight.

 Compliance: 1. Within next 5 hours time in service after 14 December 1990.

             2.    Within next 5 hours time in service after 14 December 1990 and thereafter at intervals not exceeding 50 hours time in service. Also prior to the first flight of each day the helicopter is to be operated.

                3.    (a) Within next 5 hours time in service after 14 December 1990 and thereafter at intervals not exceeding 50 hours time in service.

                (b) Within next 5 hours time in service after 14 December 1990 and thereafter prior to the first flight of each day the helicopter is to be operated.

           Note: This Directive shall be entered on the Maintenance Release as maintenance required. The visual inspection required by Para 2 and 3 may be performed by the pilot in command in which case certification is to be made by entering AD/HU 369/82 against the daily inspection certification of the Maintenance Release. A copy of this Airworthiness Directive is to be kept in the aircraft.

           Background:  An investigation in New Zealand has revealed that certain main and tail rotor blades repaired in that country had not been repaired in accordance with proper procedures (eg time expired adhesives etc).

           The New Zealand CAA believe this to be a potentially serious safety of flight issue and that some of these blades are in Australia.