Results
97-21-16: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 97-21-16 that was sent previously to all known U.S. owners and operators of Dassault Model Mystere-Falcon series airplanes by individual notices. This AD requires a revision to the Limitations section of the FAA-approved Airplane Flight Manual (AFM) to include procedures to use certain values to correctly gauge the minimum allowable N1 speed of the operative engines during operation in icing conditions. This action is prompted by a report indicating that erroneous minimum anti-icing N1 thrust setting indications were displayed on the Engine Indication Electronic Display (EIED). The actions specified by this AD are intended to prevent flightcrew use of erroneous N1 thrust setting information displayed on the EIED, which could result in in-flight shutdown of engine(s).
98-19-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A321 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to prohibit automatic landings and Category III operations on runways with a magnetic orientation of 170 degrees through 190 degrees inclusive. This amendment also provides for optional terminating action for the AFM revision. 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 prevent the use of erroneous automatic roll-out guidance generated by the flight management and guidance computer, which could result in the airplane departing the runway upon landing.
98-01-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires replacement of certain electrical terminals with new electrical terminals. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent loose electrical connections from causing an increase in electrical resistance, which could result in overheating at the electrical terminals and consequent smoke/fire in the airplane passenger cabin.
97-14-13: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Gulfstream Model G-159 (G-I) airplanes, that currently requires repetitive inspections to detect chafe wear on the upper diagonal engine mount tube, and replacement or repair, if necessary. This amendment requires the installation of chafe guards at the engine mounts, which terminates the currently required inspections. It also requires that the chafe guards then be repetitively inspected for chafe wear. This amendment is prompted by the development of a modification that will provide better protection of the subject area against future chafe wear. The actions specified by this AD are intended to prevent excessive chafe wear in the area of the upper diagonal engine mount tubes and trusses; if not detected and corrected, such wear could result in failure of the engine mount assembly and possible separation of the engine from the airplane.
98-13-26: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, that requires repetitive detailed visual inspections to detect cracking in the trunnion fittings located in the nose landing gear (NLG) bay of the forward fuselage; and repair, if necessary. 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 detect and correct cracking in the trunnion fittings of the NLG, which could lead to collapse of the NLG during takeoff and landing, and possible injury to the flight crew and passengers.
98-06-02: This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model C-212 series airplanes, that requires a one-time inspection to detect discrepancies of the spherical bearing of the aileron control rod, and corrective action, if necessary; and installation of an improved retainer washer in the movable joint of the aileron control rod. 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 loss of the movable joint of the aileron control rod, caused by deterioration of the hinges, which could result in reduced controllability of the airplane.
97-09-09: This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company (formerly Beech Aircraft Corporation) Models 58P and 58PA airplanes. This action requires inspecting for cracks in the right-hand (RH) upper and lower longeron near the second RH cabin window, inspecting for missing rivets in the cabin structure (longeron) adjacent to and aft of the second RH cabin window, repairing any cracked structure or reinforcing the longeron if it is not cracked, and installing rivets, if missing. Reports of cracks in the upper and lower longeron and missing rivets that are supposed to secure the frame, splice, and longeron together prompted this action. The actions specified by this AD are intended to prevent structural cracking to the cabin caused by missing rivets, which if not corrected, could cause decompression injuries to passengers, structural failure of the fuselage, and loss of the airplane.
98-23-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires the installation of certain rivets on support arm 2 of the left and right flaps. 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 fatigue cracking of the support arms of the flaps, which could result in reduced structural integrity of the airplane.
99-09-12: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model 4101 series airplanes, that requires repetitive inspections to detect damage of the structure associated with the engine nacelle fairing attached to the wing flaps, and repair of any damage found; drilling a new drain hole in each engine nacelle fairing; and applying a sealant to the gap between the wing flap and engine nacelle fairing. This amendment also requires correction of discrepancies, and modification of the wing flap structure, which terminates the repetitive inspections. This amendment is prompted by reports of fatigue cracks found in the structure that attaches the engine nacelle fairing to the wing flaps. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in the partial or complete separation of the fairing from the wing flap, and consequent additional structural damage to the airframe and/or reduced controllability of the airplane.
98-06-14: This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model CN-235 series airplanes, that requires installation of a contactor and relocation of the existing fuse in the battery circuit. 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 failure of the battery circuit due to a burned fuse, and consequent inability to restart the engine using batteries during flight
98-11-30: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-145 series airplanes, that requires inspection of the main landing gear (MLG) bushing seats to detect cracks, and repair of the bushing hole or replacement of strut bushings with new bushings, if necessary. This amendment also requires replacement of the plain bearings of the MLG shock absorber with new bearings. 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 structural failure of the MLG due to fatigue cracking of the strut bushing seat.
97-24-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0070 and 0100 series airplanes, that requires a one-time operational test of a certain pitot heating system, repair or replacement of failed elements, and repair or replacement of the pitot heating system with a new improved system. This amendment also requires installation of new power supply wiring with increased gauge thickness, and a circuit breaker with an increased amperage rating. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent icing of the No. 1 pitot tube, which could result in failure of the No. 1 Air Data Computer, or output of erroneous airspeed data to all on-side subsidiary systems, including the Automatic Flight Control and Augmentation System.
97-18-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model BAe 125-800A series airplanes, and Model Hawker 800 and 800XP series airplanes, that requires modification of the rudder. This amendment is prompted by a report indicating that, due to the existing design of the rudder, overbias or overbalance of the rudder occurs during single engine handling. The actions specified by this AD are intended to prevent overbias or overbalance of the rudder, which could result in reduced controllability of the airplane.
98-11-04 R1: This amendment corrects information in an existing airworthiness directive (AD), applicable to all Boeing Model 737-100 and -200 series airplanes, that currently requires that the FAA-approved maintenance inspection program be revised to include inspections that will give no less than the required damage tolerance rating for each Structural Significant Item, and repair of cracked structure. The actions specified in that AD are intended to ensure the continued structural integrity of the entire Boeing Model 737-100 and -200 fleet. This amendment corrects the requirements of the current AD by allowing operators not to change their programs if they determine that the existing inspections are effective for the new or affected SSI. This amendment is prompted by a review of the requirements of the existing AD.
99-06-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires repetitive flow checks of the hydraulic pump drain system to ensure that the system is not clogged, and correction of any discrepancy. This amendment also requires replacement of the existing magnetic seals of the accessory gearbox assembly with new, improved seals. Replacement of certain seals terminates the requirement for repetitive flow checks. This amendment also requires replacement of the engine drain modules with drain manifolds. 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 contamination of the engine accessory gearbox oil with hydraulic fluid, which could result in an in-flight engine shutdown.
98-12-23: This amendment adopts a new airworthiness directive (AD) that applies to certain British Aerospace (BAe) Model H.P. 137 Jetstream Mk. 1, Jetstream Model 3101, Jetstream Model 3201, and Jetstream 200 series airplanes. This AD requires replacing the windshield wiper arm attachment bolts and windshield wiper arm on all of the affected airplanes; and measuring the material thickness of the upper and lower toggle attachment brackets on the nose landing gear of the affected airplanes, and replacing the toggle attachment bracket lugs. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent the windshield wiper arm from corroding, detaching from the airplane during flight, and penetrating the fuselage, which could result in possible injury to the pilot and passengers; and to prevent collapse of the nose landing gear caused by design deficiency, which could result in loss of control of the airplane during landing operations.
98-03-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires removal and replacement of the center screw of the crew seat belt buckle. 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 failure of the center screw of the crew seat belt buckle, which could result in injury to the flightcrew during an emergency landing.
98-19-13: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-19-13, which was sent previously to all known U.S. owners and operators of BHTC Model 407 helicopters by individual letters. This AD requires, on or before the accumulation of 50 hours total time-in-service (TIS) on the engine-to-transmission driveshaft (driveshaft), replacing the driveshaft with an airworthy driveshaft. This amendment is prompted by analysis and test data which revealed that the life limit of the driveshaft is less than that which is stated in the applicable maintenance manual. The actions specified by this AD are intended to prevent failure of the driveshaft, loss of engine drive to the rotor system, damage to critical structural components, and subsequent loss of control of the helicopter.
98-20-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes, that requires repetitive inspections to detect corrosion on the fuselage skin panels that surround the emergency exits immediately aft of the wing; and follow-on corrective actions, if necessary. 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 detect and correct corrosion on the fuselage skin panels that surround the emergency exits immediately aft of the wing, which could result in reduced structural integrity of the fuselage pressure vessel.
97-07-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires the replacement of weight limitation placards in the aft main baggage bay and in the aft right stowage compartment with new placards indicating lower maximum weight limits. It also requires a revision of the Airplane Flight Manual to delete references to the current higher weight limits for these areas. This amendment is prompted by a report indicating that existing weight limitations could result in failure of the front bulkhead of the aft main baggage bay and doors of the aft right stowage compartment during emergency dynamic landing conditions. The actions specified by this AD are intended to prevent such failure, which consequently could result in injury to passengers and flight crew, and hinder evacuation of the airplane through the exit adjacent to this bulkhead.
99-13-03: This amendment adopts a new airworthiness directive (AD) that is applicable to BHTC Model 206L-4 helicopters. This action requires a reduction in the retirement lives of certain collective idler links and collective levers, and re-identifying certain collective idler links and collective levers. This amendment is prompted by the discovery of two types of collective idler links and collective levers--manufactured from different materials--that are identified with the same part numbers but should have substantially different retirement lives. The actions specified in this AD are intended to prevent use of a collective idler link (link) or collective lever (lever) beyond its retirement life, which could lead to failure of the link or lever and subsequent loss of control of the helicopter.
98-20-30: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A320 series airplanes equipped with a bulk cargo door, that requires repetitive inspections to detect fatigue cracking of the upper frame flanges; and repair, if necessary. This amendment also requires modification of the upper frame flanges of the bulk cargo door, which constitutes terminating action for the repetitive inspections. 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 fatigue cracking of the upper frame flanges, which could result in reduced structural integrity of the airplane.
97-23-15: This amendment adopts a new airworthiness directive (AD), applicable to all Fairchild Model F-27 series airplanes, that requires revising the Airplane Flight Manual (AFM) to prohibit positioning power levers below the flight idle stop during flight, and to provide a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the propeller ground beta range was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
98-06-34: This amendment adopts a new airworthiness directive (AD), applicable to all Aerospatiale Model ATR-42 and ATR-72 series airplanes, that requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits positioning the power levers below the flight idle stop during flight, and to provide a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the ground propeller beta range was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
97-13-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Gulfstream American (Frakes Aviation) Model G-73 (Mallard) series airplanes, that requires revising the Airplane Flight Manual (AFM) to prohibit positioning the power levers below the flight idle stop, and to provide a statement of consequences of positioning the power levers below the flight idle stop. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the propeller beta was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.