Results
2010-04-05: The FAA is superseding an existing airworthiness directive (AD) for McCauley Propeller Systems 1A103/TCM series propellers. That AD requires, for certain serial numbers (S/Ns) of McCauley Propeller Systems 1A103/TCM series propellers, initial and repetitive visual and dye penetrant inspections for cracks in the propeller hub, replacement of propellers with cracks that do not meet acceptable limits, and rework of propellers with cracks that meet acceptable limits. This AD requires, for all McCauley Propeller Systems 1A103/TCM series propellers, the same actions but at reduced compliance times. This AD also requires inspections of the bolt holes, reaming holes if necessary, and inspections of steel reinforcement plates and gaskets. This AD results from 16 reports received of propeller hubs found cracked since AD 2003-12-05 was issued. We are issuing this AD to prevent propeller separation due to hub fatigue cracking, which can result in loss of control of the airplane.
95-07-01: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 95-07-01 that was sent previously to all known U.S. owners and operators of Textron Lycoming O-360, LO-360, HO-360, HIO-360, TIO-360, LIO-360, AEIO-360, O-540, IO-540, TIO-540, LTIO-540, IVO-540, AEIO-540, TIO-541, and IO-720 series reciprocating engines by individual letters. This AD requires removal prior to further flight of suspect unapproved connecting rod bolts and replacement with serviceable connecting rod bolts. This amendment is prompted by reports of connecting rod bolt failures. The actions specified by this AD are intended to prevent engine failure due to connecting rod bolt failure, which could result in damage to or loss of the aircraft.
50-39-01: 50-39-01 CESSNA: Applies to All Models 190 and 195 Aircraft, Up to and Including Serial Number 7586. Inspection required not later than November 25, 1950, on aircraft having 300 hours or more service and at each 100 hours operation on all aircraft. Service experience has indicated that close inspection of rudder cables is necessary in order to detect premature cable fraying at the forward pulley. Due to the difficulty of inspection and since some failures may have occurred in core strands, the following methods are recommended: Detach the rudder cable from the rudder bellcrank in the aft fuselage or at the rudder horn at the pedal and pull the cable through the inspection openings immediately aft of the rudder pedal or through the tunnel at the aircraft centerline in the cabin. The cable should then be carefully inspected, by flexing, at a point 9 to 10 inches aft of the swaged fitting at the forward end of the cable for broken strands. Replace all cables showing signsof breakage. The above inspection may be discontinued when at least the next larger size pulleys are installed. (Cessna Service Kit, SK 9050-1 provides the larger pulley and inspection opening for those aircraft prior to Serial No. 7587.)
2021-02-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200, -200 Freighter, -300, -800, and -900 series airplanes; Model A340-200 and -300 series airplanes; and Model A340-541 and A340-642 airplanes. This AD was prompted by a report that an erroneous torque value for the attachment nuts to install a pitot probe was included in the affected Aircraft Maintenance Manual (AMM) task. This AD requires re-torqueing the attachment nuts of each affected part. In addition, this AD prohibits the use of the affected AMM task, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
66-13-02: 66-13-02\tBOEING: Amdt. 39-236 Part 39 Federal Register May 13, 1966. Applies to Models 707 and 720 Series Airplanes Listed in Boeing Service Bulletin 1789, Revision 1. \n\n\tCompliance required as indicated, unless already accomplished.\n \n\t(a)\tWithin the next 125 hours' time in service after the effective date of this AD, incorporate the following operating limitation in either the Airplane Flight Manual or on a placard installed adjacent to the cabin dome light switch: \n\n\t"THE DOME LIGHT SWITCH MUST BE IN EITHER THE BLUE, LOW OR BRIGHT POSITION DURING \t\t\tTAKEOFF AND LANDING". \n\n\t(b)\tWithin the next 1,200 hours' time in service after the effective date of this AD, install a new relay in the emergency exit light circuit or rewire the circuit to use existing contacts on the essential a.c. power failure relay, so that the emergency exit lights will function automatically when power is lost on the essential a.c. bus in accordance with Boeing Service Bulletin 1789, Revision 1, or later FAA-approved revision or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region.\n \n\t(c)\tThe operating limitation imposed under (a) may be removed when the modification required in (b) has been accomplished.\n\n\tThis directive effective May 13, 1966.
2004-01-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Hamburger Flugzeugbau G.m.b.H. Model HFB 320 HANSA airplanes, that requires replacement of the elevator trim control cable assemblies with new assemblies. This action is necessary to prevent loss of elevator trim and possible loss of rudder and/or elevator function due to stress-corrosion cracking of certain cable terminals. This action is intended to address the identified unsafe condition.
95-04-08: This amendment adopts a new airworthiness directive (AD), applicable to Boeing Model 747-300 and -400 series airplanes equipped with certain stretched upper deck evacuation slides manufactured by BFGoodrich series airplanes. This amendment requires modification of the slide's main restraint strap, regulator assembly, and turbo fan flapper retaining roll pins. This amendment is prompted by reports of loss of air pressure and non-inflation of the inflatable tubes of the slide due to problems associated with the restraint strap, regulator assembly, and turbo fan flapper retaining roll pins. The actions specified by this AD are intended to prevent loss of air pressure or non-inflation of the inflatable tubes of the slide, which could impede the successful evacuation of passengers from the airplane during an emergency.
2004-01-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Falcon 2000 and 900EX, and Dassault Model Mystere-Falcon 900 series airplanes. This AD requires measuring the paint thickness on the upper and lower surfaces of the left and right sides of the horizontal stabilizer, performing corrective actions if necessary, and installing maintenance caution placards on the upper surface of the left and right sides of the horizontal stabilizer. This action is necessary to prevent structural damage to the horizontal stabilizer after a direct lightning strike, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
58-10-07: 58-10-07 VICKERS: Applies to All Viscount 700 Series Aircraft. Compliance required as indicated. Cases have been reported of a variation in the clearances between the aileron lock arms and their associated locking levers on different aircraft when the control locks are disengaged. Vickers-Armstrong has issued the following corrective measures which the British Air registration Board considers mandatory: 1. As soon as possible, but not later than August 1, 1958, all aircraft should be inspected to determine that a nominal clearance of 0.15 inch is provided at the inboard and outboard aileron control lock assemblies. 2. If the clearances are less than 0.10 inch, the locking levers can be filed to a maximum of 0.10 inch to obtain the required clearance of not less than 0.15 inch. 3. If the clearances are between 0.10 and 0.15 inch, the filing of the locking levers to obtain the required clearance of not less than 0.15 inch, can be deferred until the next major check or next removal of the ailerons, whichever occurs sooner. The FAA concurs with this action and considers compliance therewith mandatory. (Vickers-Armstrong PTL No. 173 and Modification No. D.2491 cover this subject.)
2010-04-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: There have been several in-service cases reported of impact damage to the blowout (decompression) panel protective cage assemblies installed in the aft baggage cargo compartment. When damaged, these cages could prevent proper operation of the blowout panels, with potential degradation of smoke detection and fire extinguishing capabilities in the event of a fire. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.