Results
2015-20-10: We are adopting a new airworthiness directive (AD) for all Gulfstream Aerospace Corporation Model GVI airplanes. This AD was prompted by reports of corrosion on in-service air non-return valves. This AD requires a revision to the Emergency Procedures section of the airplane flight manual (AFM). This AD also requires a revision to the maintenance or inspection program, as applicable, to incorporate airworthiness limitations for the high pressure (HP) Stage 5 air non- return valves. We are issuing this AD to ensure the flightcrew is provided with [[Page 61089]] procedures to mitigate the risks associated with failure of the HP Stage 5 air non-return valve. Failure of the HP Stage 5 air non-return valve in the open position could result in engine instability and uncommanded in-flight shutdown.
2002-10-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires replacing certain flight warning computers (FWCs) with improved FWCs. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent erroneous display of decision height information to the flightcrew during final approach, which could result in an increased risk of collision with terrain.
2015-20-08: We are adopting a new airworthiness directive (AD) for all Model FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G airplanes; Model MYSTERE-FALCON 200 airplanes; and Model MYSTERE-FALCON 20-C5, 20-D5, 20-E5, and 20-F5 airplanes. This AD was prompted by reports of defective fire extinguisher tubes. It was determined the defects were caused by corrosion. This AD requires repetitive general visual inspections of the fire extinguisher tubes for cracking and corrosion, and replacement of any cracked tube with a serviceable tube, if necessary. We are issuing this AD to detect and correct cracking and corrosion in the fire extinguisher tubes, which could impact the capability to extinguish an engine fire, and possibly result in damage to the airplane and injury to the passengers.
99-01-06: This action confirms the effective date of Airworthiness Directive (AD) 99-01-06, which applies to certain British Aerospace Jetstream Model 3101 airplanes. AD 99-01-06 requires installing a standard bonding socket that is fitted flush with the upper surface of each wing at the fueling points (Station 297). This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified in this AD are intended to correct a potentially insufficient ground contact between the refueler hose nozzle and the aircraft, which, if not corrected before the fuel cap is removed, could result in sparks with a consequent fire and/or explosion in the fuel tank.
2002-08-19: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2C10 (Regional Jet Series 700 and 701) series airplanes, that currently requires revising the Airplane Flight Manual to address uncommanded transfer of fuel between the wing fuel tanks and the center fuel tank; revising the Minimum Equipment List; limiting airplane operation; and increasing normal mission fuel requirements by 3,000 pounds. This amendment retains the requirements of the existing AD, and adds requirements for modification of the fuel distribution system for the center tank; and an inspection of that system for discrepancies, and corrective actions if necessary. This amendment is prompted by reports of uncommanded fuel transfer between wing fuel tanks and the center fuel tank, and reports of misaligned or damaged fuel tubes due to vibration. The actions specified in this AD are intended to ensure that the flight crew has the procedures necessary to address uncommanded fuel transfer; and to detect and correct discrepancies in the fuel distribution system, which could cause the center tank to overfill and fuel to leak from the center tank vent system or to become inaccessible, and could result in engine fuel starvation.
52-24-01: 52-24-01\tNAVION: Applies to All Models, Serial Numbers NAV-4-2 and Above. \n\nCompliance required as soon as possible but not later than November 1, 1952. \n\nIn order to eliminate the possibility of the aileron control chain jamming, each end of the fiber channel chain guard should be reworked as shown in Figure 1. The chain and guard are on the control column. \n\n(Ryan Navion Field Service Bulletin No. 18 dated September 3, 1952, covers this same subject.) \n\n\nAD 52-24-01
98-26-14: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 and 200) series airplanes. This action requires a one-time visual inspection to detect chafing or cracking of all electrical wiring conduits located in the center fuel tank, and inadequate clearance between the tube assemblies and adjacent structures; and corrective actions, if necessary. This action also requires a modification to reinforce the right wing crossflow shutoff valve conduit. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct chafing or cracking of the electrical conduits in the center fuel tank and inadequate clearance between tube assemblies and adjacent structures, which could result in electrical arcing and consequent fire or explosion in the center fuel tank.
2015-18-51: We are publishing a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires inspecting certain tail rotor (T/R) blades, replacing the set of T/R blades if there is damage, deactivating the rotor de-icing system, revising the rotorcraft flight manual (RFM), and installing a placard. This AD is prompted by a report of a T/R de-icing system power supply box stuck in a ``closed'' position providing an uncontrolled and un-annunciated power supply to the system. These actions are intended to detect and prevent structural damage to the T/R blades caused by overheating, and subsequent loss of control of the helicopter.
71-17-07: 71-17-07 AEROSTAR: Amdt. 39-1269. Applies to Models 600 and 601 airplanes, Serial Numbers 60-001 through 60-0056 and 61-0001 through 61-0070 with Aerostar Kit No. 600-23-1 installed in accordance with AD 70-23-04. \n\n\tCompliance required as indicated unless already accomplished. To prevent failure of the inboard wing flap attachment ribs accomplish the following before further flight using flaps and within the next 10 hours time in service after the effective date of this AD. \n\n\ta.\tInspect for cracks in the cutout radius of the inboard wing fairing ribs (P/N A200094) in the area shown on the attached drawing. Cracked parts should be replaced with new parts using procedures shown in Aerostar Service Bulletin 600-23 or by an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, FAA, Fort Worth, Texas. \n\n\n\n\nAD 71-17-07 \n\n\n\tb.\tInspect for missing or incorrectly located rivets attaching the inboard flap tracks to the wing fairingribs as shown on the attached drawing No. A200094. The installation should be corrected where necessary to conform to this drawing or by an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, FAA, Fort Worth, Texas. \n\n\tThis amendment becomes effective to all known owners of Aerostar Models 600 and 601 airplanes upon receipt of individual copies mailed August 13, 1971, and to all other persons on August 23, 1971.
65-18-01: 65-18-01 MAULE: Amdt. 39-115 Part 39 Federal Register August 19, 1965. Applies to Models Be Dee M-4, Serial Numbers 3 through 14; M-4, Serial Numbers 15 through 86; and M- 4-210, Serial Numbers 1001 through 1028 Airplanes. Compliance required within the next 50 hours' time in service after the effective date of this AD unless already accomplished. To prevent further failures of the attachment of the fuselage fabric to the windshield channel, install a metal reinforcement strip in accordance with Maule Service Letter No. 8, dated July 26, 1965, or later FAA-approved revision, or an FAA-approved equivalent. This directive effective August 17, 1965.