Results
95-19-01: This amendment adopts a new airworthiness directive (AD), applicable to Airbus Model A330 and A340 series airplanes equipped with certain BFGoodrich evacuation slides and slide/rafts. This action requires an inspection to detect the presence of certain discrepancies of the packboard associated with the evacuation slides and slide/rafts, and replacement or modification of the packboard unit, if necessary. It also requires the eventual modification of all affected packboard units. This amendment is prompted by reports indicating that these packboards have disengaged from the door mounting, due to cracking of the packboard and associated latch assembly that was incurred during hard landings. The actions specified in this AD are intended to prevent the packboard from disengaging from the door and restraining the door from fully opening, thereby preventing the evacuation slide from inflating and making both the slide and the door unusable during an emergency evacuation.
2006-12-20: The FAA is adopting a new airworthiness directive (AD) for all Raytheon Model BAe.125 series 800A (including variants C-29A and U- 125), 800B, 1000A, and 1000B airplanes and Model Hawker 800 (including variant U-125A) and 1000 airplanes; and for certain Raytheon Model HS.125 series 700A and 700B airplanes and Model Hawker 800XP airplanes. This AD requires measuring the resistance of the current limiters for the PE, PS1, and PS2 busses, and replacing a current limiter with a new part if necessary. This AD also requires reporting certain information to the airplane manufacturer. This AD allows a records review for determining if suspect current limiters were installed, which may exempt airplanes from the required measurement. This AD results from reports that certain current limiters have opened within two to four hours after installation. We are issuing this AD to prevent loss of all primary electrical power, which could result in the airplane operating only under emergency power.
2018-11-16: We are adopting a new airworthiness directive (AD) for certain Engine Alliance (EA) GP7270, GP7272, and GP7277 turbofan engines. This AD requires a one-time eddy current inspection (ECI) of the engine fan hub blade slot bottom and blade slot front edge for cracks, a visual inspection of the engine fan hub for damage, and removal of parts if damage or defects are found that are outside serviceable limits. This AD was prompted by an uncontained failure of the engine fan hub. We are issuing this AD to address the unsafe condition on these products.
2018-13-02: We are adopting a new airworthiness directive (AD) for all Pratt & Whitney Division (PW) PW4052, PW4056, PW4060, PW4062, PW4062A, PW4152, PW4156A, PW4158, PW4460, and PW4462 turbofan engine models, including engines identified with suffixes -1C, -1E, -3, -3A, or -3B. This AD was prompted by the discovery of multiple cracked 4th stage low-pressure turbine (LPT) air seals in the fleet. This AD requires removal from service of certain 4th stage LPT air seals. We are issuing this AD to address the unsafe condition on these products.
95-16-09: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Jetstream Model BAe ATP airplanes. This action requires modification of the electrical connections at the switches of the scavenge oil filter and pressure oil filter. This amendment is prompted by reports indicating that the electrical connections were miswired at the switches of the scavenge oil filter and pressure oil filter. The actions specified in this AD are intended to prevent the circulation of unfiltered oil through the engine without warning to the flightcrew, due to miswiring of electrical connections. Unfiltered oil containing contaminants could lead to a precautionary shutdown of the engine.
2018-09-04: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Models G-IV and GIV-X airplanes. This AD was prompted by the potential for fatigue cracks developing in the main landing gear actuator attachment fitting that had a certain repair incorporated. This AD requires incorporating new revisions into the Instructions for Continued Airworthiness of the Limitations section of the FAA-approved maintenance program (e.g., maintenance manual) that establish an inspection cycle for the repaired MLG side brace actuator fittings. We are issuing this AD to address the unsafe condition on these products.
2006-12-22: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 airplanes. This AD requires a detailed inspection for cracks and marks on the carbon blades of the ram air turbine (RAT), and replacement of the RAT with a new or serviceable RAT if necessary. This AD results from a report of three chord-wise cracks on the aft side of one carbon blade of a certain RAT. We are issuing this AD to detect and correct cracks and/or marks on the RAT carbon blades, which could result in reduced structural integrity of the carbon blade, and consequent loss of the RAT as a source of hydraulic and electrical power in an emergency.
67-21-02: 67-21-02 PILATUS: Amdt. No. 39-443, Part 39, Federal Register July 14, 1967. Applies to all Models PC-6 Airplanes, Serial Numbers to 620. Compliance required as indicated. To detect cracks of the elevator attachment bracket, Part No. 6300.11, accomplish the following: (a) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 50 hours' time in service, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, visually inspect the elevator attachment, P/N 6300.11, for cracks between the welded seams. (b) If cracks are detected during the inspection required by paragraph (a), before further flight either replace the defective part with a new or used uncracked part of the same part number or modify the part in accordance with Pilatus Service Bulletin No. 67 or later Swiss Federal Air Office-approved issue, or an FAA-approved equivalent. (c) The repetitiveinspections required by paragraph (a) of this AD may be discontinued after the elevator attachment bracket is modified in accordance with Pilatus Service Bulletin No. 67 or later Swiss Federal Air Office-approved issue, or an FAA-approved equivalent. This amendment effective August 13, 1967.
69-08-07: 69-08-07 LOCKHEED: Amdt. 39-752. Applies to Model L-188 Series airplanes. Compliance required within the next 400 hours' time in service after the effective date of this AD, unless previously accomplished. To detect cracks in the lower wing surfaces of Electra aircraft, accomplish the following: (1) Visually inspect the lower wing plank surfaces and areas around fasteners, including planks one through eight between W.S. 157 and W.S. 219 in accordance with the procedure outlined in Paragraphs A through E of FAA approved Lockheed Service Bulletin 88/SB- 669, or later FAA approved revisions. (2) If cracks exist, appropriate repair must be accomplished before further flight in accordance with Paragraph F of FAA approved Lockheed Service Bulletin 88/SB-669, or in a manner approved by the Chief, Aircraft Engineering Division, FAA Western Region. (3) Report all results of this inspection whether accomplished before or after the effective date of this AD, to the Chief,Aircraft Engineering Division, FAA Western Region. Reports must include crack locations and length, if any, aircraft serial number, and accumulated hours' time in service. The data received in the required reports will form the basis for any further AD action that may be required. (Reporting approved by the bureau of the Budged under BOB No. 04-R0174.) Airplanes with cracks may be flown in accordance with special flight permits issued pursuant to FAR 21.197 to a base where repair can be accomplished. This amendment becomes effective on April 17, 1969.
2006-12-21: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) airplanes. That AD currently requires revising the airplane flight manual (AFM) to provide the flightcrew with revised procedures for checking the flap system. The existing AD also requires revising the maintenance program to provide procedures for checking the flap system, and performing follow-on actions, if necessary. This new AD requires installing new flap actuators, a new or retrofitted air data computer, a new skew detection system, and new airspeed limitation placards; and revising the AFM to include revised maximum allowable speeds for flight with the flaps extended, and a new skew detection system/crosswind-related limitation for take-off flap selection. This AD results from a number of cases of flap system failure that resulted in a twisted outboard flap panel. We are issuing this AD to prevent an unannunciated failure of the flap system, which could result in a flap asymmetry and consequent reduced controllability of the airplane.