AD 2018-17-02

For airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD: Within 60 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate the life limit AWL tasks identified in table 1 to paragraph (g) of this AD, as specified in the applicable service information identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. The initial compliance time is within 500 flight cycles of the effective date of this AD, or at the applicable time (in terms of landings) specified in the applicable AWL task identified in table 1 to paragraph (g) of this AD, whichever occurs later.

(1) For Model CL-600-1A11 (600) airplanes, Section 5-10-10, “Time Limits (Structural),” of Section 5-10-00, “Airworthiness Limitations,” of Bombardier Challenger 600 Time Limits/Maintenance Checks, Publication No. PSP 605, Revision 39, dated January 8, 2018.

(2) For Model CL-600-2A12 (601) airplanes, the applicable task specified in paragraph (g)(2)(i), (g)(2)(ii), or (g)(2)(iii) of this AD, as identified in Section 5-10-00, “Airworthiness Limitations,” of Bombardier Challenger 601 Time Limits/Maintenance Checks, Publication No. PSP 601-5, Revision 46, dated January 8, 2018.

(i) Section 5-10-10, “Time Limits (Structural)—Pre SB 601−0280.”

(ii) Section 5-10-11, “Time Limits (Structural)—Post SB 601−0280.”

(iii) Section 5-10-12, “Time Limits (Structural)—Post SB 601−0360.”

(3) For Model CL-600-2B16 (601-3A and 601-3R Variants) airplanes, the applicable task specified in paragraph (g)(3)(i), (g)(3)(ii), or (g)(3)(iii) of this AD, as identified in Section 5-10-00, “Airworthiness Limitations,” of Bombardier Challenger 601 Time Limits/Maintenance Checks, Publication No. PSP 601A-5, Revision 42, dated January 8, 2018.

(i) Section 5-10-10, “Time Limits (Structural).”

(ii) Section 5-10-11, “Time Limits (Structural).”

(iii) Section 5-10-12, “Time Limits (Structural).”

For airplanes identified in paragraph (c)(4) of this AD: Within 60 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate new life limit AWL Task 27-42-01-108, “Discard of the Horizontal-Stabilizer Trim-Actuator (HSTA) Trunnion Support; Part No. 601R92386-1/-3,” and Task 27-42-01-112, “Discard of the Horizontal-Stabilizer Trim-Actuator (HSTA) Upper and Lower Attachment Pins; Upper Pin Part No. 600-92384-5/-7 or 601R92310-1/-3 and Lower Pin Part No. 600-92383-5/-7 or 601R92309-1/-3,” as specified in the applicable time limits maintenance checks (TLMC) manuals identified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD. The initial compliance time is within 500 flight cycles after the effective date of this AD, or at the applicable time specified in the applicable AWL task, whichever occurs later.

(1) For airplanes having serial numbers 5301 through 5665 inclusive: Section 5-10-10, “Life Limits (Structures),” of Bombardier Challenger 604 CL-604 Time Limits/Maintenance Checks, Part 2 Airworthiness Limitations, Revision 30, dated December 4, 2017.

(2) For airplanes having serial numbers 5701 through 5990 inclusive: Section 5-10-10, “Life Limits (Structures),” of Bombardier Challenger 605 CL-605 Time Limits/Maintenance Checks, Part 2 Airworthiness Limitations, Revision 18, dated December 4, 2017.

(3) For airplanes having serial numbers 6050 and subsequent: Section 5-10-10, “Life Limits (Structures),” of Bombardier Challenger 650 CL-650 Time Limits/Maintenance Checks, Part 2 Airworthiness Limitations, Revision 5, dated December 4, 2017.

For airplanes identified in table 2 to paragraph (i) of this AD: Within 48 months after the effective date of this AD, or prior to performing a maintenance task required by paragraph (g) or (h) of this AD, as applicable, whichever occurs first, do a general visual inspection for damage (including linear scratches, pits, spalling, dents, or surface texture variations), and add serial numbers to the HSTA trunnions, lower attachment pin, and upper attachment pin, as applicable, in accordance with the Accomplishment Instructions of the applicable service information specified in table 2 to paragraph (i) of this AD. If any damage to the HSTA trunnions or attachment pins is found, repair the damage in accordance with the applicable service information specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD; or using a method approved by the Manager, New York ACO Branch, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. If the damaged HSTA trunnion or attachment pin cannot be repaired in accordance with the applicable service information specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD: Before further flight, replace the damaged HSTA trunnion or attachment pin with a serviceable serialized HSTA trunnion or attachment pin, in accordance with the applicable service information specified in table 2 to paragraph (i) of this AD.

(1) Bombardier Repair Engineering Order (REO) 600-27-42-002, “General Repair—HSTA Upper and Lower Pins,” dated December 15, 2016.

(2) Bombardier Repair Engineering Order (REO) 604-27-42-011, “General Repair—HSTA Trunnion P/N 601R92386-1/-3,” dated December 15, 2016.

(3) Bombardier Repair Engineering Order (REO) 604-27-42-012, “General Repair—HSTA Upper and Lower Pins,” dated December 15, 2016.

After the maintenance or inspection program has been revised as required by paragraph (g) or (h) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (m)(1) of this AD.