Document ID: chunk:federal_register_of_legislation:F2006B09465:body:0:p1
Version: federal_register_of_legislation:F2006B09465
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Character Range: 4–3224

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

    Embraer EMB-110 (Bandeirante) Series Aeroplanes

AD/EMB-110/24
    Amdt 1

    Applicability: All model EMB-110.

   Control Wheel Spindle 1/92

    Requirement: 1. Inspect Control Spindle as follows:

                 Remove control colume cover.

                 Measure diameter of forward thread of the spindle. If diameter is 3/4" no further action is necessary.
                 If diameter is 3/8" proceed with inspection:-

                 Remove spindle assembly and check vertical and conical wall thickness close to the aft ball bearing:

                   1. Measure the depth of the large hole - this dimension should be 42mm approx.

b.   Measure from the aft end to the aft bearing shoulder - this dimension should be 44 mm approx.

c.    Calculate difference in dimension under (a) and (b).

                  d.    Through the hole in the conical surface measure the wall thickness.

e.    Crack detect all parts at the junction of the aft spindle in the region of the hole in the conical surface using the fluorescent magnetic particle method.

                 Condition 1.

                  If dimension calculated at (c) is equal or greater than 2.6 mm and the dimension at (d) is equal or greater than 2 mm and there is no crack indication, the spindle may be reinstalled and the aircraft returned to service.

                 Condition 2.

                  If dimensions determined (c) and (d) are below 2.6 mm and/or 2 mm respectively and there is no crack indication:-

                  Install a new spindle P/N 110-500-10-01-10-04. If not available it is permitted to reinstall P/N 4A-500-10-01-10-03 and repeat inspection by fluorescent magnetic particle method at intervals not exceeding 250 hours time in service until P/N 110-500-10-01-10-04 is available.

                 Condition 3.

                  If a crack is detected the spindle is unserviceable and must be discarded.
 COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

               Install new spinddle P/N 110-500-10-01-10-04 if available or install a new spindle P/N 4A-500-10-01-10-03 and apply condition 1 or 2 as determined by inspection.

             2. Replace spindles affected by repeat inspections as specified in Condition 2 of Requirement 1, with a spindle P/N 4A-500-10-01-10-03 provided it complies with Condition 1 of Requirement 1, or; replace with spindles P/N 111A-500-10-01-10- 01 or P/N 110-500-10-01-10-04.

           Note 1: The terms aft end and forward end used in requirement 1 text have the following meaning:

             Aft End - The end of the spindle with the greater diameter.

             Forward End - The end of the spindle with the smaller threaded diameter.

           Note 2: Embraer Alert SB 110-27-0070 and Brazil CTA AD 83-02-01 R3 refers.

             Compliance: 1. Unless already accomplished; within 10 hours time in service after 12 January 1992, inspect in accordance with Requirement 1, until Requirement 2 is