Airworthiness Directive · Amendment 39-22189 · Flight controls
Bombardier, Inc., Airplanes
This AD applies to Bombardier, Inc., airplanes certificated in any category, identified in paragraphs (c)(1) through (3) of this AD.
(1) Model CL-600-1A11 (600) airplanes having serial numbers (S/Ns) 1004 through 1085 inclusive.
(2) Model CL-600-2A12 (601) airplanes having S/Ns 3001 through 3066 inclusive.
(3) Model CL-600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes having S/Ns 5001 through 5194 inclusive, 5301 through 5665 inclusive, 5701 through 5988 inclusive, 6050 through 6158 inclusive, and 6160 through 6162 inclusive.
The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-1A11 (600), CL-600-2A12 (601), and CL-600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. This AD was prompted by a report that some rudder power control unit (PCU) load limiters were found in service with the crimping missing from the end cap; therefore, the pilot command from the load limiter might not transmit correctly. This AD requires a one-time inspection of the rudder PCU load limiters for correct crimping of the end cap, and replacing any defective rudder PCU load limiter. For certain airplanes, this AD would also require repetitive testing of the rudder PCU load limiter for correct functioning, and applicable corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
At the applicable time specified in paragraph (g)(1) or (2) of this AD, inspect each rudder PCU load limiter having part number (P/N) 600-91302-43 or P/N 600-91302-53 for correct crimping of the end cap, in accordance with paragraph 2.B., Part A, of the Accomplishment Instructions of the applicable service information specified in figure 1 to paragraph (g) of this AD. If the crimping is missing from any end cap, before further flight, replace the defective rudder PCU load limiter, in accordance with paragraph 2.C., Part B, of the Accomplishment Instructions of the applicable service information specified in figure 1 to paragraph (g) of this AD.
(1) For Model CL-600-1A11 airplanes having S/Ns 1004 through 1085 inclusive; Model CL-600-2A12 airplanes having S/Ns 3001 through 3066 inclusive; and Model CL-600-2B16 airplanes having S/Ns 5001 through 5194 inclusive: Inspect within 800 flight hours after the effective date of this AD.
(2) For Model CL-600-2B16 airplanes having S/Ns 5301 through 5665 inclusive: Inspect within 2,200 flight hours after the effective date of this AD.
For Model CL-600-2B16 airplanes having S/Ns 5701 through 5988 inclusive, 6050 through 6158 inclusive, and 6160 through 6162 inclusive, do the actions specified in paragraphs (h)(1) and (2) of this AD.
(1) Within 1,000 flight hours after the effective date of this AD, test each rudder PCU load limiter for correct functioning, in accordance with paragraph 2.B., Part A, of the Accomplishment Instructions of the applicable service information specified in figure 1 to paragraph (g) of this AD. Repeat the test thereafter at intervals not to exceed 800 flight hours until the inspection required by paragraph (h)(2) of this AD has been accomplished. If any rudder PCU load limiter fails any test, before further flight, do the inspection specified in paragraph (h)(2) of this AD.
(2) Within 3,400 flight hours after the effective date of this AD, inspect each rudder PCU load limiter having P/N 600-1302-43 or P/N 600-1302-53 for correct crimping of the end cap, in accordance with paragraph 2.C., Part B, of the Accomplishment Instructions of the applicable service information specified in figure 1 to paragraph (g) of this AD. If the crimping is missing from any end cap, before further flight, replace the defective rudder PCU load limiter, in accordance with paragraph 2.D., Part C, of the Accomplishment Instructions of the applicable service information specified in figure 1 to paragraph (g) of this AD. Accomplishment of this inspection terminates the repetitive testing required by paragraph (h)(1) of this AD.
