Document ID: chunk:federal_register_of_legislation:F2006L01448:body:0:p3
Version: federal_register_of_legislation:F2006L01448
Segment Type: other
Provision Reference: 
Character Range: 5586–8717

shaft is not straight and the maximum gap between the shaft and the flat surface table exceeds .007 inch, or

           (vi) You find a crack, a surface or subsurface discontinuity, or pitting.

        (i) Assemble and inspect the gearbox, P/N 278-200, the shaft, P/ N 249-10, and the housing, P/N 249-3, by following Part 2, paragraph 2.6 of Brantly International Inc. Service Bulletin No. 105, Revision A, dated August 3, 2005 (SB).  Before assembling the pinion gear and the male coupling to the shaft, thoroughly inspect the bore for foreign objects or burrs.  Clean and deburr the bore.  If the assembly fails any inspection required by this paragraph, replace the gearbox, shaft, and housing with airworthy parts before further flight and before complying with the remainder of this AD.  When the SB uses the term "check", for purposes of this AD, it means "inspect."  Also, you are not required to contact the factory as stated in the SB.

      2. Align and bolt down the intermediate gearbox, P/N 278-100, its cover, P/N 252-3, and the bushing, P/N 252-4, the long horizontal shaft housing, P/N 14-13, and its retainer flange, P/N 15-17, without making any adjustment for the gearbox (upper), shaft (vertical), or housing.

   Note 1:  See the applicable maintenance manual for installation instructions.

      3. Install and inspect the gearbox, P/N 278-200, by following paragraphs 2.7 1 through 4, and Figure SB- 105-2 of the SB.  If the gearbox fails any portion of the installation procedures or any inspection tolerance required by this paragraph, the installation is not airworthy and the helicopter is grounded until the installation complies with the requirements of this paragraph.

      4. After an airworthy installation of the gearbox is complete, inspect the tail rotor rigging control and correct it, if necessary.

   Note 2:  See the applicable maintenance manual for tail rotor control rigging instructions.

                5. Report any discrepancies for the items listed below via the service difficulty reporting system, noting this AD number in the report.

                    * Flange Retainer part number (P/N) 15-17

                    * Shaft Housing, P/N 249-3

                    * Bushing, P/N 252-4

                    * Bevel Pinion, P/N 15-8

                    * Bolt, P/N 15-201

                    * Bolt 249-11

                    * Male Coupling, P/N 249-9

                    * Shaft, P/N 249-10

                    * Tail Rotor Gearbox Assembly, P/N 278-200

                    * Installation of Tail Rotor Gearbox Assembly

             Note 3:  FAA AD 2006-08-07 Amendment 39-14562 refers.
Compliance:     1. Within the next 10 hours time-in-service (TIS) and before further flight after any hard landing or any main or tail rotor sudden stoppage.  Compliance times for replacement of parts is as detailed in the applicable paragraph of Requirement 1of this AD.

                2. Before installing the gearbox (upper).

                3. Before further flight after the effective date of this AD.

                4. Before further flight