Airworthiness Directive · Amendment 39-19402 · Flight controls
Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A. (CASA)) Airplanes
Superseded. A later AD replaced this one: AD 2020-03-18. Comply with the one in force.
This AD applies to Airbus Defense and Space S.A. Model C-212-CB, C-212-CC, C-212-CD, C-212-CE, and C-212-DF airplanes; manufacturer serial numbers 009, 034, 039, 089, 092, 119, 125, 133, 138, 149, 150, 154, 159, 161, 162, 164, 165, 167 through 169 inclusive, 171, 172, 174, 175, 178, 180, 181, 190, 192, 193, 195, 209 through 212 inclusive, 214 through 216 inclusive, 219 through 222 inclusive, 224 through 227 inclusive, 229, 235, 236, 238, 240, 242, 247 through 257 inclusive, 261 through 263 inclusive, 265, 272 through 282 inclusive, 286, 287, 289 through 292 inclusive, 294, 308, 311, 320, 322 through 324 inclusive, 328, 332, 336, 343, 347 through 349 inclusive, 356, 359, 363, 371, 379, 393, 397, 398, 405, 410, 411, 413, 465, 470, 472, 474, 475, 478, and 480 through 482 inclusive; certificated in any category; except airplanes modified in accordance with the Accomplishment Instructions of EADS-CASA Service Bulletin SB-212-27-0057, dated May 21, 2014.
We are adopting a new airworthiness directive (AD) for certain Airbus Defense and Space S.A. Model C-212-CB, C-212-CC, C-212-CD, C- 212-CE, and C-212-DF airplanes. This AD was prompted by reports of failures of the rudder pedal control system support. This AD requires repetitive detailed visual inspections of the rudder pedal control system support box and shaft and applicable corrective actions. We are issuing this AD to address the unsafe condition on these products.
(1) For the purposes of this AD, an affected part is defined as a rudder pedal support box having Part Number (P/N) 212-46195.1 and shaft P/N 212-46120-20.
(2) For the purposes of this AD, a discrepancy or defect of the rudder pedal support box P/N 212-46195.1 is defined as any crack or deformation on any welded area.
(3) For the purposes of this AD, a discrepancy or defect of the shaft P/N 212-46120-20 is defined as any crack or deformation.
Within 3 months or during the next scheduled A-check maintenance, whichever occurs first after the effective date of this AD, and thereafter, at intervals not to exceed 150 flight hours, do a detailed visual inspection of each affected part in accordance with the instructions of Airbus Alert Operators Transmission AOT-C212-27-0002, dated February 28, 2018.
If any discrepancy or defect is detected during any inspection required by paragraph (h) of this AD: Before further flight, obtain corrective actions approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus Defense and Space S.A.'s EASA Design Organization Approval (DOA); and accomplish the corrective actions within the compliance time specified therein. If approved by the DOA, the approval must include the DOA-authorized signature. Accomplishment of a repair, as required by this paragraph, does not constitute terminating action for the repetitive inspections required by paragraph (h) of this AD.
As of the effective date of this AD, an affected part may be installed on any airplane provided that it is a new part or that, before installation, the visual inspection required by paragraph (h) of this AD has been accomplished on that part and the part passed the inspection (no discrepancy or defect detected), as required by paragraph (h) of this AD.
Accomplishing the actions required by this AD terminates all of the requirements of AD 2017-19-08.
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.
