Airworthiness Directive · Amendment 39-15481 · Wings
Alpha Aviation Design Limited (Type Certificate No. A48EU Previously Held by APEX Aircraft and AVIONS PIERRE ROBIN) Model R2160 Airplanes
Superseded. A later AD replaced this one: AD 2015-25-07. Comply with the one in force.
This AD applies to Model R2160 airplanes, serial numbers 001 through 378, 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 an 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) Disassemble the wings from the fuselage and inspect the wing structure and assembly components using instruction No. 1 in Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. If any defects are found, repair following Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. Use the following compliance times for the inspection:
(i) For airplanes with less than 4,000 hours time-in-service (TIS): When the airplane reaches a total of 3,500 hours TIS or within the next 100 hours TIS after May 27, 2008 (the effective date of this AD), whichever occurs later, and thereafter at intervals not to exceed 750 hours TIS.
(ii) For airplanes with 4,000 hours TIS or more that have not complied with the special instruction in paragraph E of Avions Pierre Robin Service Bulletin No. 123, revision 2, dated November 14, 1995: Within the next 100 hours TIS after May 27, 2008 (the effective date of this AD) and thereafter at intervals not to exceed 750 hours TIS.
(iii) For airplanes with 4,000 hours TIS or more that have complied with the special instruction in paragraph E of Avions Pierre Robin Service Bulletin No. 123, revision 2, dated November 14, 1995: Within the next 750 hours TIS after May 27, 2008 (the effective date of this AD) and thereafter at intervals not to exceed 750 hours TIS.
(2) When the airplane reaches a total of 3,500 hours TIS with original wing-to-fuselage bolts installed or 3,500 hours TIS of an airplane since new bolts have been installed or within the next 100 hours TIS after May 27, 2008 (the effective date of this AD), whichever occurs later, do a non-destructive inspection of the wing-to-fuselage retaining bolts and replace any bolts that do not pass this inspection following instruction No. 2 in Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. Thereafter, repetitively inspect wing-to-fuselage retaining bolts and replace any bolts that do not pass this inspection every 750 hours TIS following instruction No. 2 in Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999.
Note 1: The requirement for a 3,500-hour inspection is a time since new or time since installation (that is, the TIS of new bolts).
(3) Within the next 50 hours TIS after re-assembling the wing and thereafter at intervals not to exceed 100 hours TIS, inspect the wing-to-fuselage retaining bolts for correct torque settings following instruction No. 3 in Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. The required torque value is 22 ft-lb with nut part number 95.24.39.010. Tighten to 16 ft-lb (pre-loading) and then torque from 16 to 22 ft-lb.
Note 2: This AD differs from the MCAI and/or service information as follows: No differences.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
