Document ID: chunk:federal_register_of_legislation:F2006B03854:body:0:p2
Version: federal_register_of_legislation:F2006B03854
Segment Type: other
Provision Reference: 
Character Range: 2981–6253

b.        The internal stub spar incorporated through STC SA1649CE and STC SA1650CE may be retained.

c.         The external angles incorporated through STC SA1649CE may also be retained by properly trimming the leading edges section to permit installation of the stabiliser reinforcement referenced in Requirement paragraph 5.a. of this Directive.

d.        For the Beech Models S35, V35, V35A, and V35B aircraft, the tail-safe external angles that were installed in accordance with STC SA1649CE may be retained and used instead of the stabiliser reinforcement specified in Requirement paragraph 5.a. of this Directive.

              5.         Accomplish the following in accordance with the instructions to RAC Kit No. 35-4016-3, 35-4016-5, 35-4016-7, or 35-4016-9, as applicable, and as specified in Beech SB No. 2188:

                  1. Install stabiliser reinforcements;

b.        Set the elevator nose-down trim; and.

c.         Replace the ruddervator tab control cables with larger diameter cables.

              6.         Verify the accuracy of the aircraft basic weight and balance information and correct any discrepancies, in accordance with the following procedures:

                  1. Weight and Balance Accuracy Method No.1:

                    1. Review existing weight and balance documentation to assure completeness and accuracy of the documentation from the most recent approved weighing or from factory delivery to date of compliance with this Directive.

                    ii.        Compare the actual configuration of the aircraft to the configuration described in the weight and balance documentation.

                    iii.      If equipment additions or deletions are not reflected in the documentation or if modifications affecting the location of the centre of gravity (eg. paint or structural repairs) are not documented, determine the accuracy of the aircraft weight and balance data in accordance with Method No.2.

b.        Weight and Balance Information Accuracy Method No.2:

                    1. Determine the basic empty weight and centre of gravity (CG) of the empty aircraft using the Weighing Instructions in the Weight and Balance section of the aircraft flight manual/pilot's operating handbook (AFM/POH).

                    ii.        Record the results in the aircraft records, and use these new values as the basis for computing the weight and CG information as specified in the Weight and Balance section of the AFM/POH.

            Note: FAA AD 94-20-04 R2 Amdt 39-13147 refers.

              Compliance: 1. Within 100 hours time in service after 5 January 1995; thereafter before further flight after the ruddervators are repaired or repainted (even if stripes are added or paint is touched up).

              2.         Unless already accomplished, inspect and set the controls, tension, and rigging within 100 hours time in service after 2 October 2003. Accomplish any repairs and replacements before further flight after the inspection.

              3.         Within 100 hours time in service after 2 October 2003; thereafter at intervals not to exceed 100 hours time in service.

              4.         Within 100 hours time in service after 5 January 1995, unless already accomplished.