Airworthiness Directive · Amendment 39-17891 · Fuselage
EADS CASA (Type Certificate Previously Held by Construcciones Aeronauticas, S.A.) Airplanes
This AD applies to EADS CASA (Type Certificate previously held by Construcciones Aeronauticas, S.A.) Model CN-235-300 airplanes, certificated in any category, manufacturer serial numbers (MSN) C-143 through C-208, inclusive.
We are adopting a new airworthiness directive (AD) for certain EADS CASA (Type Certificate Previously Held by Construcciones Aeronauticas, S.A.) Model CN-235-300 airplanes. This AD was prompted by reports of reduced thickness of the center fuselage lower skin panel. This AD requires a detailed inspection to determine the presence of panel thickness reduction; and repetitive nondestructive testing (NDT) inspections and repair if necessary. We are issuing this AD to detect and correct reduced thickness of lower panel joints, which could result in reduced fatigue and damage tolerant characteristics of the lower panel joint to the adjacent side panels and failure of the center fuselage lower skin panel, resulting in loss of control of the airplane.
For airplanes having MSNs C-143 through C-195 inclusive, C-201, and C-202: At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, do a detailed inspection to determine the presence of panel thickness reduction of the lower panel joint with the side panels at stringer (STR) 24 left-hand and STR24 right-hand, in accordance with Airbus Military All Operator Letter (AOL) 235-024, Revision 01, dated March 1, 2013.
(1) For airplane versions CG01, CL04, ED01, GC01, MM01, and SM01: Inspect at the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
(i) Before the accumulation of 1,900 total flight cycles.
(ii) Within 10 flight cycles or 30 days after the effective date of this AD, whichever occurs first.
(2) For any airplane version not identified in paragraph (g)(1) of this AD: Inspect at the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
(i) Before the accumulation of 3,800 total flight cycles.
(ii) Within 10 flight cycles or 30 days after the effective date of this AD, whichever occurs first.
(1) For airplanes having MSNs C-196 through C-200 inclusive and C-203 through C-208 inclusive, and for airplanes with a reduced panel thickness identified during the inspection required by paragraph (g) of this AD: At the applicable time specified in paragraph (g)(1)(i) of this AD (for airplanes identified in paragraph (g)(1) of this AD), or paragraph (g)(2)(i) of this AD (for airplanes identified in paragraph (g)(2) of this AD), or within 50 flight cycles after the effective date of this AD, whichever occurs later, do an NDT inspection for cracking, in accordance with Airbus Military AOL 235-024, Revision 01, dated March 1, 2013. Repeat the inspection thereafter at the applicable time specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD.
(i) For airplane versions CG01, CL04, ED01, GC01, MM01, and SM01: Inspect at intervals not to exceed 1,000 flight cycles.
(ii) For airplane versions other than those identified in paragraph (h)(1)(i) of this AD: Inspect at intervals not to exceed 2,000 flight cycles.
(2) If any cracking is detected during the inspection required by paragraph (h)(1) of this AD, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j)(2) of this AD.
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.
