Airworthiness Directive Schedule Aeroplanes Cessna 441 Series

Full document text

Issued 27 March 2014 Page 1 of 2 CAA of NZ Airworthiness Directive Schedule Aeroplanes Cessna 441 Series 27 March 2014 Notes: 1. This AD schedule is applicable to Cessna 441 aircraft manufactured under FAA Type Certificate No. A28CE. 2. The Federal Aviation Administration (FAA) is the National Airworthiness Authority (NAA) responsible for the issue of State of Design Airworthiness Directives (ADs) for these aircraft. State of Design ADs can be obtained directly from the FAA website at: Dynamic Regulatory System (faa.gov) 3. The date above indicates the amendment date of this schedule. 4. New or amended ADs are shown with an asterisk * Contents * DCA/CESS441/1A Airworthiness Directive Compliance .................................................................................. 2 DCA/CESS441/2B Fuel Boost Pump Wiring – Inspection and Modification .................................................... 2 Aeroplanes Cessna 441 Series Issued 27 March 2014 Page 2 of 2 CAA of NZ * DCA/CESS441/1A Airworthiness Directive Compliance Applicability: All model 441 series aircraft. Requirement: Compliance with the following FAA Airworthiness Directives (as applicable) is required: 79-08-07 Anti-icing propeller wiring 79-09-02 Aileron control surfaces drainage 79-19-12 Engine stoppage 79-19-13 Elevator trim tab 80-02-17 Flight manual performance data 83-12-03 Battery switch wiring 84-20-02 Nose Landing Gear 85-25-11 Nuts – Cessna P/N NAS1291-8 86-24-13 POH/AFM appendix – icing 92-16-07 Horizontal stabilizer front spar * 92-16-18 Passenger seat reinforcement 95-25-10 Replace outflow/safety valve * 96-12-22 Full Flow Engine Oil Adapter 97-25-04 AFM – Limitations – Power levers 98-04-28 AFM –Limitations – Icing * 2001-22-14 Fire Extinguishing System Bottle Cartridges * 2005-20-25 Avionics Bus Circuit Breaker Switches Note: Each part of this AD (each individual FAA AD) shall be certified in the aircraft log book separately. Compliance: Before issue of New Zealand Certificate of Airworthiness, or at the next ARA inspection after the effective date of this AD whichever is the sooner, unless previously accomplished, and thereafter at intervals not to exceed the times specified in the FAA ADs. Effective Date: DCA/CESS441/1 - 28 April 2005 DCA/CESS441/1A - 27 March 2014 DCA/CESS441/2B Fuel Boost Pump Wiring – Inspection and Modification Applicability: Model 441 S/N 0001 through 0362, and 698. Requirement: To detect and correct chafing and/or arcing of the boost pump wiring, which could result in arcing within the wing fuel tank, possible ignition of explosive vapor and loss of the aircraft, accomplish the following; 1. Inspect the P/N 5718106-1 wire harness and fuel boost pump lead wires for chafing or damage, per Cessna Conquest SB No CQB02-1Rev 2. If any wire harness or fuel boost pump lead wires are found chafed or damaged, replace the harnesses and repair or replace the lead wires, or replace the boost pump as detailed in the SB before further flight. 2. Install improved design fuel boost pump (P/N 1C12-17 or approved equivalent P/N), improved design wire harness (P/N 5718106-6 or approved equivalent P/N) and protective sleeving modification for boost pump lead wires per the SB. Installing both improved part numbers in each wing tank or protective sleeving modification terminates the repetitive inspection requirements of part 1 of this AD. (FAA AD 2003-09-09R1 refers) Compliance: 1. Inspect within the next 25 hours TIS or 60 days, whichever occurs first, unless already accomplished, and there after at intervals not to exceed 200 hours TIS. 2. Replace affected components within 400 hours TIS after 31 July 2003. Effective Date: DCA/CESS441/2A - 31 July 2003 DCA/CESS441/2B - 29 January 2004