Airworthiness Directives; Pacific Aerospace Corporation Ltd. 750XL Airplanes
The FAA proposes to supersede Airworthiness Directive (AD) 2005-26-53; Amendment 39-14451, which applies to all Pacific Aerospace Corporation Ltd. (PAC) 750XL airplanes. AD 2005-26-53 currently requires you to insert text into the Limitations Section of the Airplane Flight Manual (AFM) that reduces the maximum takeoff weight from 7,500 pounds to 7,125 pounds. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for New Zealand and the FAA's decision that the actions correct an unsafe condition. Consequently, this proposed AD would require you to remove rivets that have not been fully age hardened and replace them with bolts, washers, and nuts in specific locations where reduction in rivet strength affects overall structural capability. This proposed AD retains the actions of the previous AD until the rivets are replaced with the bolts, washers, and nuts. We are issuing this proposed AD so that wing ultimate load requirements are met. If wing ultimate load requirements are not met, wing failure could result with subsequent loss of control of the airplane.
Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
The FAA is superseding an existing airworthiness directive (AD) that applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. The existing AD currently requires revising the airworthiness limitations section of the Instructions for Continued Airworthiness of the aircraft maintenance manual (AMM) by incorporating procedures for repetitive functional tests of the pilot input lever of the pitch feel simulator (PFS) units. This AD requires new repetitive functional tests of the pilot input lever of the PFS unit, and corrective actions if necessary. After initiating the new tests, this AD also requires removal of the existing procedures for the repetitive functional tests from the AMM. This AD results from a report that the shear pin located in the input lever of two PFS units failed due to fatigue. We are issuing this AD to prevent undetected failure of the shear pin of both PFS units simultaneously, which could result in loss of pitch feel forces and consequent reduced control of the airplane.