Airworthiness directives › 2019-19-08
AD 2019-19-08 Airworthiness Directives; Bombardier, Inc., Airplanes
Applicability*9
This AD applies to Bombardier, Inc., airplanes, certificated in any category, as identified in paragraphs (c)(1) through (4) of this AD. (1) Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, serial numbers 7003 and subsequent. (2) Model CL-600-2C10 (Regional Jet Series 700, 701 & 702) airplanes, serial numbers 10002 through 10999 inclusive. (3) Model CL-600-2D15 (Regional Jet Series 705) and CL-600-2D24 (Regional Jet Series 900) airplanes, serial numbers 15001 through 15990 inclusive. (4) Model CL-600-2E25 (Regional Jet Series 1000) airplanes, serial numbers 19001 through 19990 inclusive.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
(1) For Model CL-600-2B19 airplanes operating under the LUMP: Within 90 days after the effective date of this AD, revise the existing maintenance or inspection program, as applicable, to incorporate the information specified in paragraphs (g)(1)(i) through (vi) of this AD. The initial compliance time for accomplishing the actions is within 90 days after the effective date of this AD; or within the applicable interval specified in Section 3—Systems and Powerplant Program, of the Bombardier Model CL-600-2B19 Series 100/200/440 Maintenance Planning Manual, Low Utilization Maintenance Program (MRLUMP-001), CSP A-054-009, Revision 37, dated July 10, 2018 (“MRLUMP-001, Revision 37”); or Section 3—Systems and Powerplant Program, of the Bombardier Model CL-600-2B19 Series 100/200/440 Maintenance Planning Manual, Low Utilization Maintenance Program (MRLUMP-002), CSP A-054-060, Revision 37, dated July 10, 2018 (“MRLUMP-002, Revision 37”), after the effective date of this AD; whichever occurs later. (i) Task 27-20-00-13, Operational Check of the Rudder Control System, of MRLUMP-001, Revision 37. (ii) Task 27-23-01-01, Detailed Inspection of the Rudder PCU Rod End Spherical Ball, of MRLUMP-001, Revision 37. (iii) Task 27-31-00-05, Operational Check of the Elevator Control System, of MRLUMP-001, Revision 37. (iv) Task 27-20-00-13, Operational Test of the Rudder Control System, of MRLUMP-002, Revision 37. (v) Task 27-23-01-01, Detailed Inspection of the Rudder PCU Rod End Spherical Ball, of MRLUMP-002, Revision 37. (vi) Task 27-31-00-05, Operational Test of the Elevator Control System, of MRLUMP-002, Revision 37. (2) For Model CL-600-2C10 airplanes having serial numbers 10004, 10040, 10043, 10052, 10100, 10164, 10183, 10187, 10204, 10206, 10217, 10247, 10289, 10332, and 10343 operating under the LUMP; and Model CL-600-2D15 and CL-600-2D24 airplanes having serial numbers 15158, 15278, and 15370 operating under the LUMP: Within 30 days after the effective date of this AD, revise the existing maintenance or inspection program, as applicable, to incorporate the information specified in paragraphs (g)(2)(i) through (iii) of this AD. The initial compliance time for accomplishing the actions is within 30 days after the effective date of this AD; or within the applicable interval specified in Section 3—Systems/Power Plant Tasks, of the Bombardier Model CL-600-2C10, CL-600-2D15, CL-600-2D24, Series 700/705/900 Maintenance Planning Manual, Low Utilization Maintenance Program (LUMP), CSP BC-116, Revision 15, dated May 25, 2017 (“LUMP, Revision 15”), after the effective date of this AD; whichever occurs later. (i) Task 27-20-00-106, Operational Test of the Rudder PCUs (Duplicate CMR 27-20-00-106), of LUMP, Revision 15. (ii) Task 273000-207, Operational Test of the Elevator Power-Control Units (PCUs), of LUMP, Revision 15. (iii) Task 273000-215, Detailed Inspection of the Elevator PCU Rod End Spherical Ball, of LUMP, Revision 15.
Unsafe condition
This AD was prompted by reports of power control unit (PCU) rod end fractures due to pitting corrosion. The FAA is issuing this AD to address this condition, which, if not detected and corrected, could lead to a disconnect between the PCU and the control surface, resulting in potential loss of the control surface function or inadequate flutter suppression.
Affected ADs
None.
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