Airworthiness Directive · Amendment 39-18312 · Fuselage
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
This AD applies to Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 188A and 188C airplanes, certificated in any category, serial numbers 1001 and subsequent.
We are adopting a new airworthiness directive (AD) for certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 188 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the circumferential fuselage splice at fuselage-station (FS) 695 is subject to widespread fatigue damage (WFD). This AD requires an inspection for corrosion and previous repairs, severed stringers, cracking, and loose or distressed fasteners of the forward and aft ends of the stringer splices of certain stringers, inspection for cracking and modification of certain fastener holes common to the stringer and splice member at the forward and aft ends of the splice, and related investigative and corrective actions if necessary. We are issuing this AD to prevent loss of residual strength of the circumferential fuselage splice at FS 695, which could lead to rapid decompression of the cabin and potential loss of the airplane.
Before the accumulation of 38,200 total flight hours or within 30 days after the effective date of this AD, whichever occurs later: Do a general visual inspection for corrosion and previous repairs, severed stringers, cracking, and loose or distressed fasteners of the forward and aft ends of the stringer splices of stringers 1-7 and 66-72; remove the four rivets common to the stringer and splice member at the forward and aft ends of the splice and do a bolt hole eddy current inspection or an equivalent inspection procedure for cracking in each of the fastener holes; modify the fastener holes; and do all applicable related investigative and corrective actions and other specified actions; in accordance with the Accomplishment Instructions of Lockheed Martin Electra Service Bulletin 88/SB-722, dated April 30, 2014, except as specified in paragraph (h) of this AD. Do all applicable related investigative and corrective actions and other specified actions before further flight. If any repairs exceed the repair limits specified in Lockheed Martin Electra Service Bulletin 88/SB-722, dated April 30, 2014, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD.
(1) If, during any inspection required by paragraph (g) of this AD, any corrosion or previous repair is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD.
(2) If, during any inspection required by paragraph (g) of this AD, any loose or distressed fastener is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD.
Although Lockheed Martin Electra Service Bulletin 88/SB-722, dated April 30, 2014, specifies to submit certain information to the manufacturer, this AD does not include that requirement.
