Document ID: chunk:federal_register_of_legislation:F2010L01658:reg:65:p2
Version: federal_register_of_legislation:F2010L01658
Segment Type: reg
Provision Reference: reg 65 (pt 2/3)
Character Range: 8137–11208

type.  However, the principle guidance material is FAA Advisory Circular 23-13A "Fatigue, Fail-Safe, and Damage Tolerance Evaluation of Metallic Structure for Normal, Utility, Acrobatic, and Commuter Category Airplanes".

                    Note 2:

                CASA AD/BEECH 65/22 requires inspection of the wing fittings and attachment bolts.  These inspections have their own reduced intervals specified depending on the aircraft model.  These reduced intervals take precedence over those in the Beech SIRM.

                CASA AD/BEECH 65/57 requires inspection of the eight wing attach bolts and nuts per Inspection Index 10, Chart 201 of the Beech SIRM.

             Note 3:  The Retirement Schedule is based on certain assumptions regarding average cruise weight, and also assumes one flight per hour.  Should the average take-off weight, assessed over the life of the aircraft, be greater than the values shown in the Retirement Schedule, the registered operator must reassess the life limitation and submit the assessment to CASA for approval.  Any weight increase above the type certificated weight, will require a re-assessment of the life limitation.  Similarly, the Authority must be advised if the average time per flight stage (lift-off to touchdown) is shorter than the value shown.

             Note 4:  Some aircraft have been fitted with engines of a different type to the original, including IO-720 installation to US FAA STC SA444SW.  The engine installation itself may affect the wing life limitation, as for some models there may be a resultant MTOW increase and thus NOTE 3 may be applicable.

             Note 5:  For aircraft which, because of an unusual operational role, have had individual life assessments approved by the Authority prior to 1 December 1988, those assessments still stand.

             Note 6:  On the basis of the currently available fatigue substantiation for the aircraft, only one spar cap replacement is permitted.  Any proposal for a further extension in life incorporating a second spar change must be supported by a substantiation covering all the remaining primary structure including empennage, control surface hinge arms etc.  This substantiation must incorporate a safe life assessment, or a sufficiently rigorous revised inspection schedule to ensure that any fatigue cracking which could occur in service will be detected before the aircraft is endangered.  A third spar change will not be permitted.
Compliance:  As per requirement.
             This Amendment becomes effective on 23 June 2010.
Background:  This amendment is issued to allow continuation in service (of spar caps and wing attach fittings) beyond the fatigue lives specified in the retirement schedule, providing certain requirements are met.

             Spar caps and wing attach fittings that have reached the life specified in the retirement schedule may not operate until the operator has completed a review of the Beech SIRM to determine if it inspects these parts at all of the probable locations and considers