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2004-22-20: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model MD-11 and MD-11F airplanes. This AD requires replacement of low base terminal boards, related investigative action, and corrective actions if necessary. This AD is prompted by arcing between a power feeder cable and terminal board support bracket. We are issuing this AD to prevent arcing damage to the power feeder cables, terminal boards, and adjacent structure, which could result in smoke and/or fire in the cabin.
2004-22-08: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, that requires repetitive inspections of the check valves and air supply ducts of the rear bulkhead for damage, and related corrective actions. This amendment also would require eventual rework or replacement of the air supply ducts, which would terminate the repetitive inspections for the air supply ducts only. This action is necessary to prevent disconnection of an air supply duct, which, if combined with failure of a bulkhead check valve, could result in rapid depressurization of the airplane. This action is intended to address the identified unsafe condition.
2004-21-08: The FAA adopts a new airworthiness directive (AD) for all Cessna Aircraft Company (Cessna) Models 190, 195 (L-126A,B,C), 195A, and 195B airplanes that are equipped with certain inboard aileron hinge brackets. This AD requires you to repetitively inspect the affected inboard aileron hinge brackets for cracks or corrosion and replace them if found cracked or corroded. Replacement with aluminum brackets would terminate the need for the repetitive inspections. This AD results from several reports of cracks and corrosion found on the magnesium aileron hinge brackets. Magnesium is known to be susceptible to corrosion. We are issuing this AD to detect and correct corrosion damage to the inboard aileron hinge brackets. Such damage could result in the brackets cracking across the bearing boss and could lead to the aileron separating from the airplane with consequent reduced or loss of control of the airplane.
2004-21-05: The FAA is superseding Airworthiness Directive (AD) 96-20-07, which applies to certain B-Series Combustion Heaters Models B1500, B2030, B3040, and B4050 that are installed on airplanes. AD 96-20-07 currently requires you to repetitively test (pressure decay) the combustion tube and overhaul any heater that does not pass any test. AD 96-20-07 also requires you to repetitively test the operation of the combustion air pressure switch and replace any combustion pressure switch that does not pass one of the tests. As a terminating action for the repetitive test requirements of AD 96-20-07, you could install a new ceramic-coated combustion tube and an improved design combustion air pressure switch. This AD is the result of reports that the new ceramic-coated combustion tubes are subject to the same distress as the non-ceramic coated combustion tubes. Consequently, this AD retains the repetitive testing requirements of AD 96-20-07, removes the terminating action for the combustion tube, and adds Models B2500, B3500, and B4500 to the applicability section. We are issuing this AD to prevent combustion by-products (carbon-monoxide exhaust) and fuel leakage from the combustion heaters caused by failure of the combustion heater system. This failure could result in fire or explosion in the airplane and possible carbon monoxide poisoning of the crew and passengers in the cabin.
2004-20-12: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 B2 and B4 series airplanes; Model A300 B4-600, A300 B4-600R, A300 F4-600R series airplanes, and A300 C4- 605R Variant F airplanes (collectively called A300-600); and Model A310 series airplanes. This amendment requires a detailed inspection of certain pulleys and control cables in the rear fuselage for corrosion and damage; and corrective action, if necessary. This action is necessary to detect and correct frayed or corroded control cables for the elevator and rudder, which could result in a ruptured control cable, and possible reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2004-20-09: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD requires repetitive inspections for cracks, sealant damage, and corrosion of the main fittings of the main landing gear (MLG), and corrective actions if necessary. This AD is prompted by a report of a cracked main fitting of the MLG. We are issuing this AD to detect and correct fatigue cracking of the main fitting of the MLG and consequent failure of the main fitting, which could result in the collapse of the MLG.
2004-20-04: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney Canada (PWC) PT6B-36A and PT6B-36B turboshaft engines with compressor rear hubs, part number (P/N) 3018111 installed. This AD requires reviewing, and correcting if necessary the critical part record for compressor rear hubs, P/N 3018111. This AD also requires removing compressor rear hubs from service that exceed the published part life limit, before further flight. This AD results from the discovery of a compressor rear hub, P/N 3018111, that exceeded the published life limit. This occurred because the operator used an incorrect life limit calculation contained in a PWC Service Bulletin. We are issuing this AD to prevent uncontained failure of the compressor rear hub and damage to the airplane.
2004-19-06: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767-200, -300, and -300F series airplanes, that requires inspections to detect cracking or corrosion of the fail-safe straps between the side fitting of the rear spar bulkhead at body station 955 and the skin; and follow-on/corrective actions. This action is necessary to detect and correct fatigue cracking or corrosion of the fail-safe straps, which could result in cracking of adjacent structure and consequent reduced structural integrity of the fuselage. This action is intended to address the identified unsafe condition.
2004-19-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102 airplanes, that requires modification of the electrical power circuit. This action is necessary to prevent component failure in the radar indicator, resulting in an overcurrent condition and consequent overheating or burning of an internal component or the ribbon cable. This could lead to smoke in the cockpit, resulting in incapacitation of the flight crew and loss of control of the airplane. This action is intended to address the identified unsafe condition.
2004-17-01: The FAA supersedes Airworthiness Directive (AD) AD 2002-22-17, which applies to all Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes; and AD 2003-21-04, which applies to certain Cessna Models 208 and 208B airplanes. This AD requires you to repetitively inspect the flap bellcranks for cracks and eventually replace these bellcranks. The installation of a newly designed bellcrank to increase the life limits is terminating action for the repetitive inspections. This AD is the result of these developments: Since FAA issued AD 2002- 22-17 and AD 2003-21-04, Cessna designed a new flap bell crank with a life limit of 40,000 landings instead of 7,000 landings. Also, FAA has done more analysis and examination of cracks and missing/incomplete welds in all of the bell cranks. This failure could lead to damage to the flap system and surrounding structure and result in reduced or loss of control of the airplane. DATES: This AD becomes effective on September 26, 2004.As of December 31, 2002 (67 FR 68508, November 12, 2002), the Director of the Federal Register approved the incorporation by reference of Cessna Service Bulletin No. CAB02-1, dated February 11, 2002. As of October 21, 2003 (68 FR 59707, October 17, 2003), the Director of the Federal Register approved the incorporation by reference of the following: Cessna Caravan Service Bulletin No.: CAB03-11, Revision 1, dated September 24, 2003; Cessna Caravan Service Bulletin No.: CAB02-12, revision 1, dated January 27, 2003; and Cessna Caravan Service Kit No.: SK208-148A, dated January 27, 2003 (Original issue: October 21, 2002).