Airworthiness Directive · Amendment 39-16435 · Wings
G ROB-WERKE Model G120A Airplanes
This AD applies to Model G120A airplanes, all serial numbers, certificated in any category.
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
Unless already done, do the following actions:
(1) Before further flight after October 12, 2010 (the effective date of this AD), and repetitively thereafter before the first flight of each day, inspect the right hand (RH) and left hand (LH) flap ribs for cracks following GROB Aircraft AG Service Bulletin No.: ASB1121-113/1, Accomplishment Instructions, PART A, dated May 18, 2010.
(2) If no crack is found during any inspection required in paragraph (f)(1) of this AD, before further flight, you must comply with the following conditions until the Repair Instructions in GROB Aircraft AG Repair Instruction No. RI-1121-018, dated May 18, 2010, are done:
(i) Reduction of the airplane's maximum flap deflection to the “TAKE-OFF” position and reduction of the maximum flaps extended speed V FE to 114 knots indicated airspeed (KIAS);
(ii) Modification of the placard part number (P/N) 120A-7000.113E to show reduced flap deflection of “TAKE-OFF” position and maximum flaps extended speed V FE of 114 KIAS, and
(iii) Insertion into the limitations section of the airplane flight manual and/or pilots operating handbook an amendment showing that the Temporary Maximum Flap Position is TAKE-OFF and the Maximum Flap Extended Speed is 114 KIAS.
(3) If no crack is found during any inspection required in paragraph (f)(1) of this AD, within the next 12 months after the effective date of this AD, modify the LH and RH flap ribs following GROB Aircraft AG Repair Instruction No. RI-1121-018, dated May 18, 2010 and GROB Aircraft AG Service Bulletin No.: ASB1121-113/1, Accomplishment Instructions, PART B, dated May 18, 2010.
(4) If a crack is found during any inspection required in paragraph (f)(1) of this AD, before further flight, repair the applicable flap rib(s) following GROB Aircraft AG Repair Instruction No. RI-1121-017, dated April 1, 2010; GROB Aircraft AG Repair Instruction No. RI-1121-018, dated May 18, 2010; and GROB Aircraft AG Service Bulletin No.: ASB1121-113/1, Accomplishment Instructions, PART B, dated May 18, 2010.
(g) You may at any time complete GROB Aircraft AG Repair Instruction No. RI-1121-017, dated April 1, 2010, and GROB Aircraft AG Service Bulletin No. ASB1121-113/1, Accomplishment Instructions, PART B, dated May 18, 2010, to terminate the repetitive inspection required in paragraph (f)(1) of this AD, and to terminate the conditions required by paragraphs (f)(2) of this AD. This repair must be done before further flight if cracks are found as required in paragraph (f)(4) of this AD.
Note: This AD differs from the MCAI and/or service information as follows: The MCAI allows flight with known cracks for up to 100 hours time-in-service. FAA policy is to not allow further flight with known cracks in critical structure. We require that if any cracks are found, before further flight, the crack must be repaired following the applicable GROB service information.
