Document ID: chunk:federal_register_of_legislation:F2006B09238:reg:734388:p1
Version: federal_register_of_legislation:F2006B09238
Segment Type: reg
Provision Reference: reg 734388 (pt 1/2)
Character Range: 3027–6320

734388                    734388-27-A1 Revision 1   27-A1

                (d)     Upon reassembly, install the through bolt and torque to between 20 and 25 in- lb.

             2.    Unless already accomplished per Part I, Requirement 1.(c); replace all splined couplings on torque tubes located per Part I, Requirement 1.(b)(ii) above, in accordance with the accomplishment instructions in the appropriate Sundstrand service bulletin (Table 2). Re-identify the torque tubes as indicated in the service bulletins. Marking the service bulletin number on the rod with indelible ink will satisfy this requirement.

           Part II.  For aircraft serial numbers 3 through 293:

              1. Accomplish the following visual inspection of the flap primary-drive torque tube system and the flap secondary-drive flex shaft system:

                (a)     Extend flaps fully.

                (b)     Visually inspect the flap primary-drive torque tubes over their entire length for fracture, rubbing and wear.

                (c)     Torque tubes must be replaced before further flight if wear exceeds 0.25mm (0.010 inch) in depth or is present over more than 180 degrees around the circumference of the shafts.

(d)     Visually inspect the flap secondary-drive flex drive for permanent deformation (kinks), or evidence of excessive heat (blueing of outer braided sheath, melting of outer plastic sheath, loss of blue anodic film on the casing ferrules).

(e)     Damaged flex shafts must be replaced with serviceable flex shafts before further flight.

                 2.    Accomplish the following:

(a)     Perform an operational check of the torque sensor as per maintenance program task 2750/11. Refer to DASH 8 Maintenance Program Supplementary Information, PSM 1-8-7/1-83-7, Volume 2, Procedures-27.

(b)     Any torque sensor found malfunctioning or jammed must be replaced with a serviceable unit before further flight.

               Note: The inspections required by Part II, Requirements 1 and 2 above may be terminated on aircraft that have complied with Part III of this Directive and which have incorporated both of the Boeing Canada/de Havilland modifications listed below:

                      (i)       Modification No. 8/1473, Service Bulletin No. 8-54-16, 'Nacelles - Flap Torque Tube - Introduction of Torque Tube Guard'.

                      (ii)    Modification No. 8/0803, Service Bulletin No. 8-27-47, 'Flight Controls - Flap Power Drive Unit - Replacement of Flow Regulator Valve'.

               Part III. For aircraft serial numbers 3 through 293:

               Modify the wing flap system torque sensor in accordance with Boeing Canada/de Havilland Service Bulletin No. 8-27-61.

               Note: Transport Canada AD CF-89-09R4 refers.

    Compliance: Part I:

                   1. For aircraft serial numbers 3 through 177; within 300 hours time in service after 15 October 1992.

                  For aircraft serial numbers 178 through 231, 233, 235, 237 and 243; unless already accomplished, within 300 hours time in service after 13 October 1994.

               2.    Within 900 hours time in service after 15 October 1992. Part II:
                   1. Within 300 hours time in service after 19 April 1990 (the compliance date of the