Airworthiness Directive · Amendment 39-18557 · Fuselage
GROB Aircraft AG Airplanes
This AD applies to Grob Aircraft AG Models G115EG airplanes, serial numbers up to and including 82323/E, certificated in any category.
We are adopting a new airworthiness directive (AD) for GROB Aircraft AG Model G115EG airplanes. 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 cracks in the bonded joint of the rear horizontal stabilizer frame. We are issuing this AD to require actions to address the unsafe condition on these products.
Unless already done, do the actions in paragraphs (f)(1) through (6) of this AD.
(1) Within the next 50 hours time-in-service (TIS) after July 20, 2016 (the effective date of this AD), and repetitively thereafter at intervals not to exceed 50 hours, inspect the rear horizontal stabilizer frame following the Accomplishment Instructions in section 1.8, Part A, of GROB Aircraft AG Service Bulletin (SB) No. MSB1078-200, dated February 25, 2016.
(2) If any crack within the green area as defined in Figure 2 of the Accomplishment Instructions in section 1.8, Part A, of GROB Aircraft AG Service Bulletin (SB) No. MSB1078-200, dated February 25, 2016, is found during any inspection required in paragraph (f)(1) of this AD, before further flight, install a temporary placard stating “NO AEROBATICS, NO SPINS AND NO SIDE SLIPS ALLOWED” in full view of the pilot(s) and place a copy of this AD in the airplane flight manual (AFM); and after each day of flight operations, do a crack propagation inspection following the Accomplishment Instructions in Section 1.8, Part B, of GROB Aircraft AG SB No. MSB1078-200, dated February 25, 2016.
(3) If any crack within the red area as defined in Figure 2 of the Accomplishment Instructions in section 1.8, Part A, of GROB Aircraft AG Service Bulletin (SB) No. MSB1078-200, dated February 25, 2016, is found during any inspection required by this AD, before further flight, repair the affected area following the Accomplishment Instructions in Section 1.8, Part C, of GROB Aircraft AG SB No. MSB1078-200, dated February 25, 2016.
(4) Within the next 19 months after July 20, 2016 (the effective date of this AD), unless already done as required by paragraph (f)(3) of this AD, modify the airplane following the Accomplishment Instructions in Section 1.8, Part C, of GROB Aircraft AG SB No. MSB1078-200, dated February 25, 2016.
(5) After modification of the airplane as required by paragraph (f)(3) or (4) of this AD, remove the placard installed as required in paragraph (f)(2) of this AD and remove the copy of this AD from the applicable AFM.
(6) Modification of an airplane as required in paragraph (f)(3) or (4) of this AD, as applicable, constitutes terminating action for the repetitive inspections required in paragraph (f)(1) and (2) of this AD.
