Document ID: chunk:federal_register_of_legislation:F2008L02506:body:0:p2
Version: federal_register_of_legislation:F2008L02506
Segment Type: other
Provision Reference: 
Character Range: 2723–5691

numbers (MSN) 027,102, 106 and 214, and modified per SB ATR42-27-0080 - Unless accomplished previously, undo changes introduced by SB ATR42-27-0080 and restrict the maximum permissible flaps extension in normal operations to 30° and install new speed limits placards as instructed in the accomplishment instructions of SB ATR42-27-0099 original issue or later EASA approved revision and after embodiment, send the accomplishment report back to ATR.

                4. For ATR 42 MSN 097, if not previously modified per SB ATR42-27-0008 at any revision - Modify the aircraft per the instructions of SB ATR42-27-0099 original issue or later EASA approved revision.

                5. For ATR 42 MSN 403 - Modify the aircraft per the instructions of SB ATR42-27-0099 original issue or later EASA approved revision.

                6. For all other ATR 42 not addressed by Requirements 2, 3, 4 & 5 of this AD - Check that the red colour mechanical stop is installed on flaps control and that the following statement is written on the speed limits placard concerning the VFE limitations:

                 "EMER: (45°). 130 kt".

                 If any discrepancy is found, contact ATR to obtain the procedure in order to restore the aircraft to the approved configuration and implement the procedure accordingly.

                7.  Do not install ATR Mod. 01314 or implement SB ATR42-27-0080 on any aeroplane.

             Note 3:  EASA AD 2008-0124 dated 4 July 2008 refers. The EASA AD supersedes Direction Générale de l'Aviation Civile (DGAC) France AD F-1986-130-003.

             Note 4:  DGAC AD F-1986-130-003 is listed in Table 1 of AD/ATR 42/1, "State of Design Airworthiness Directives". AD/ATR 42/1 requires the operator to determine the applicability of each of the ADs listed in Table 1. As AD F-1986-130-003 has been superseded by EASA AD 2008-0124, F-1986-130-003 should be considered as no longer being applicable.
Compliance:  For Requirement 1 - Within 7 days after the effective date of this AD.

             For Requirements 2, 3, 4, 5 and 6 - Within 6 months after the effective date of this AD.

             For Requirement 7 - After the effective date of this AD.
             This Airworthiness Directive becomes effective on 16 July 2008.

Background:  DGAC AD F-1986-130-003 was issued following an incident during a training flight when a temporary loss of the aircraft pitch control occurred due to a suspected tailplane stall that would have been caused by the conjunction of ice accretion on tail surface, flaps extension at 45° and airplane by the approach speed.

             Revision 1 of AD F-1986-130-003, in April 1997, prohibited the use of flaps at the 45° configuration, except for emergency situations, and mandated the installation of a mechanical stop along with new markings through ATR modification (Mod) 01192 (ATR Service Bulletin (SB) ATR 42-27-0008).  However the DGAC AD let the possibility for some