Document ID: chunk:federal_register_of_legislation:F2006B10758:body:0:p2
Version: federal_register_of_legislation:F2006B10758
Segment Type: other
Provision Reference: 
Character Range: 2737–5699

any airspeed after attaining translational lift.

                   1. For blades that do not have TE logged, before further flight, log the TE in the aircraft logbook or equivalent record as follows:

                      1. Log the TE, if known.
 COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

ii.        For non-cargo hook operations, if the number of TE is unknown, log 6 TE for each hour time in service.

iii.      For cargo hook (external load) operations, or for any combination of non- cargo hook operations and cargo hook (external load) operations, if the number of TE is unknown, log 20 TE for each hour time in service.

               b.    Make an entry into the component record or equivalent record to reflect new life limits for blade part numbers as follows:

                  1. For part number 369A1100-507, Models 369A, 369H, 369HE, 369HM, 369HS, and OH-6A, enter 1,750 hours time in service or 10,600 TE, whichever occurs first.

ii.        For part number 369D21100-517, Models 369D and 369E, enter 2,500 hours time in service or 15,000 TE, whichever occurs first.

iii.      For part number 369D21102-517, Model 369F, 369FF, and 500N, enter 2,500 hours time in service or 15,000 TE, whichever occurs first.

             4.    After compliance with Requirement 3 of this Directive, during each operation thereafter, maintain a count of TE performed and additional hours time in service accumulated, and, at the end of each day's operations, add those counts to the accumulated number of TE and hours time in service on the aircraft logbook or equivalent record.

             5.    The blades are no longer retired based upon only hours time in service. This Directive revises the Airworthiness Limitations Section of the maintenance manual by establishing a new retirement life for certain blade part numbers based on hours time in service or a number of TE, whichever occurs first.

           Note: FAA AD 98-15-26 Amdt 39-10675 refers.

 Compliance: For Requirement 1. Unless already accomplished, before further flight after
           4 February 1998 for affected main rotor blades that have accumulated 600 or more hours time in service; thereafter at intervals not to exceed 25 hours time in service.

           For Requirement 2: Before further flight after 4 February 1998. For Requirements 3, 4, and 5: As specified in each Requirement.
           The compliance of the previous issue of this Directive remains unchanged for Requirements 1 and 2.

           This Amendment becomes effective on 8 October 1998.

           Background:  This Directive was prompted by an accident in which a main rotor blade failed on a Model 369D helicopter due to cracks. The blade that failed had accumulated over 2,300 hours time in service. Subsequent investigation revealed cracks in two other blades on the same helicopter. The cracks