Document ID: chunk:federal_register_of_legislation:F2006B02125:body:0:p1
Version: federal_register_of_legislation:F2006B02125
Segment Type: other
Provision Reference: 
Character Range: 4–4499

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
    SCHEDULE OF AIRWORTHINESS DIRECTIVES

    Twin Commander (Gulfstream/Rockwell/ Aerocommander 500, 600 and 700) Series Aeroplanes

    AD/AC/66
    Amdt 8

    Wing Fatigue Life Limitation 13/89

    Applicability: As specified in the Requirement.

               Requirement: Retire wing main spar lower cap assembly from service (or modify in accordance with a scheme approved by the Authority) in accordance with the schedule below:

      AIRCRAFT MODELS AFFECTED
      (The straps referred to are wing spar lower cap fatigue life improvement reinforcements)

      SPAR CAP RETIREMENT LIFE
      (Hours' Time in Service)

                                                                                         MTOW of 6750 lb.    MTOW of 7400 lb.
 500B                                                                                        30400         -
 500B used in low level survey type operations                                               19900         -
 500U with external strap (Pre S/N 1731)                                                     23200               17700
 500U with external strap (Pre S/N 1731) and used in low level survey type operations        15900               12100
 560F                                                                                        24100
 560F used in low level survey type operations                                               16300
                                                                                         MTOW of 8000 lb.    MTOW of 8500 lb.
 680F                                                                                        17100         -
 680FL with external strap (Pre S/N 1731)                                                    17100               11200
 680FL with internal strap (S/N 1731 and on)                                                 3900                30000
 680FL (P) with external strap (Pre S/N 1731)                                          -                         25200
 680T                                                                                                         27100
 680V, 680W (Pre S/N 1731) with external strap                                                                23500
 685                                                                                                          20700
 690, 690A                                                                                                    12900
 690B                                                                                                         11500
 690C, 695 - canted aerodynamic wing tips                                                                     11300
 690C, 695 - plain tips for total operational life                                                            24800
 695A                                                                                                       To be Advised.

               Note 1: If Models 680F(P) or 680FL(P) aircraft are flown predominantly at low or zero cabin differential pressure, then the retirement life of Models 680F or 680FL respectively, shall apply.
 COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

           Note 2: Should models other than the 500B, 500U and 560F be used in low level survey type operations, the Authority must be advised as a reduction in life will be necessary. For all aircraft engaged in low level operations appropriate log book entries must be made listing times actually engaged in such operations. The Authority must also be advised of any aircraft operating consistently at a flight duration of less than 45 minutes when averaged over the life of the aircraft.

           Note 3: The wing spar lower cap assembly subject to retirement consists of the spar cap "T" section element together with the nesting angles, outer wing spar cap splice angles and, as fitted, either internal or external reinforcement straps. The outer wing spar caps need not be retired.

           Note 4: On the basis of currently available fatigue substantiating data only one spar cap assembly replacement is permitted without further evaluation. This will normally allow only a single life extension from spar cap replacement or reinforcement/modification.

           Note 5: