Results
97-08-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires a functional flow test and leak test to verify if the pressure reducing valve in the cargo fire extinguishing system is in a serviceable condition, and replacement of any faulty valve with a new valve prior to extended range twin-engine operations of the airplane. This amendment is prompted by a report that, during a scheduled maintenance check, an inoperative pressure reducing valve was found in the cargo fire extinguishing system. The actions specified by this AD are intended to ensure that a faulty pressure reducing valve is not installed, which could result in reduced fire protection of the cargo compartment of the airplane.
98-18-17: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9-80 series airplanes and Model MD-90-30 and MD-88 airplanes, that requires a one-time inspection of the harness assembly of the tailcone emergency evacuation slide to determine the diameter of the swaged balls; reidentification of the harness assembly; and reinstallation or replacement of the assembly with a new assembly, if necessary. This amendment is prompted by a failed deployment of the tailcone emergency evacuation slide during a system test conducted by the manufacturer. The actions specified by this AD are intended to prevent failure of the tailcone emergency evacuation slide to deploy automatically due to incorrect diameter of the swaged balls on the wire rope of the harness assembly.
59-05-02: 59-05-02 de HAVILLAND: Applies to All Model 104 "Dove" Aircraft With Modification PP.173 Embodied. Compliance required as soon as possible but not later than March 30, 1959. (1) A case has been reported where faulty readings were obtained from the dipstick used in an oil tank P/N 4LT.475A/1, in which Modification PP.173 was embodied. This would result in low oil content which, on prolonged flights, might give rise to oil starvation with consequent engine seizure. (2) Within the period stated above, dipsticks must be removed from oil tanks with Modification PP.173 embodied and reworked as follows: (a) Measure along the dipstick a distance of 4.15 inches from the base and file a notch or deep score mark at this point. (This position also falls 0.65-inch above existing one-half mark.) (b) Obliterate the existing one- quarter and one-half marks. (c) Add a stamped arrow pointing to the notch or score mark followed by this marking "6 US gallons minimum accurate reading". (3) The above rework must be accomplished on spar oil tanks prior to fitment to aircraft. The British Air Registration Board considers this mandatory. The FAA concurs with this action and considers compliance therewith mandatory. (de Havilland TNS CT (104) No. 158 Issue 2 covers the same subject.)
2021-21-08: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AB139 and AW139 helicopters. This AD was prompted by a report of damage (burns) on the tail rotor blades (TRBs). This AD requires an inspection of each TRB for the general condition and any evidence of burns and replacement if necessary, 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.
69-11-03: 69-11-03\tBOEING: Amdt. 39-766 applies to Model 707-300B and 707-300C series airplanes listed as follows. AA Serial No. 20170, PA Serial Nos. 20030, 20031, 20033, and 20034, LU Serial No. 20123, OA Serial No. 20035, TP Serial No. 19969, LY Serial No. 20097, PK Serial No. 19866, NW, RD, PK and EJ airplane serial numbers on which rudder power control units purchased as spares from Bertea have been installed. \n\tCompliance required as indicated unless already accomplished. \n\tTo prevent cracking of the control rod end of the rudder power control unit, accomplish the following: \n\tPrior to next flight, remove any rudder power unit, Boeing Part Number 10-60815, having Bertea Serial Number 760 through 818 and replace with a power unit of the same part number but of a different serial number than noted above. Power units Numbers 760 through 818 may be returned to service when the rod end, Bertea Part Number 60043-9 (Schafer Part Number YTD 112A), has been replaced in accordance with FAA approved instructions from the manufacturer (Bertea). The airplane may not be ferried under the provisions of FAR 21.197(b) and (c). Airplanes may be ferried after issuance of individual special flight permits under the provisions of FAR 21.197(a)(1) and FAR 21.199 after a pre-takeoff determination that the rudder operates normally in the "Boost On" mode. Pursuant to FAR 21.199(a)(6), the limitations in the special flight permit will prohibit flights over congested areas or which may otherwise endanger persons or property on the ground. \n\tThis amendment becomes effective upon publication in the FEDERAL REGISTER for all persons except those to whom it was made effective immediately by telegram dated April 14, 1969.
2004-09-29: The FAA is adopting a new airworthiness directive (AD) for Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Turbine Engine Company, and AiResearch Manufacturing Company of Arizona) (Honeywell) TPE331-10 and -11 series turboprop engines with certain part numbers (P/Ns) and serial numbers (SNs) of first stage turbine disks. This AD requires initial and repetitive fluorescent penetrant inspections (FPIs) and eddy current inspections (ECIs) of the affected first stage turbine disks. This AD results from a report of a first stage turbine disk found cracked at the disk bore. The crack originated from a localized; melt related, low-alloy area of the disk. We are issuing this AD to prevent cracked first stage turbine disks from causing uncontained disk separation, resulting in engine damage and shutdown and damage to the airplane.
98-18-08: This amendment adopts a new airworthiness directive (AD) that applies to certain Bombardier Inc. (formerly deHavilland Inc) Model DHC-3 (Otter) airplanes that have been modified in accordance with A.M. Luton Supplemental Type Certificate (STC) No. SA3777NM. This AD requires modifying the airplane s electrical system. The actions specified by this AD are intended to prevent electrical system failure caused by inadequate electrical system design, which could result in the loss of the engine instruments or a possible electrical fire in the airplane s cockpit.
2021-21-10: The FAA is adopting a new airworthiness directive (AD) for certain Pacific Aerospace Limited Model 750XL airplanes. This AD was prompted by 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 identifies the unsafe condition as chafing damage in the port wing skin caused by the fuel system finger filters. This AD requires inspecting the wing internal skin for chafing and taking any necessary corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
53-18-01: 53-18-01 CESSNA: Applies to All Model T-50 Aircraft. Compliance required by November 1, 1953. As a result of reported failures of the outer bearing in the Goodrich Model 751A/M, G-3- 49A, 7.50-10 main gear assembly, each resulting in loss of a wheel, the following should be accomplished if the outer bearing has not been replaced since the airplane was converted from military to civil operation. If the outer bearing has been replaced subsequent to that time, compliance only with item 1 is required. 1. Not later than the date specified above, replace the 1 7/16-inch washer located between the axle nut and the inner bearing cone with a washer 1 7/8 inch outside diameter, 0.953 + 0.005 inch inside diameter and 0.093 + 0.005 inch thick manufactured from SAE 1010 or equivalent. This precautionary measure will not prevent bearing failure but may prevent the wheel from coming off the axle during landing in the event of a bearing failure. 2. At the time of item 1 and at every 100 hours of operation thereafter until the bearing is replaced, check wheel side movement, inspect bearing and replace bearing as necessary. Replacement should be accomplished with Timken Cone No. 07100 and Cup No. 07196 or an equivalent bearing. (B.F. Goodrich Co. Service Bulletin No. 36, revised April 20, 1953, covers this same subject and supplies information for the fabrication of the new washer and for ordering proper replacement bearings.)
2004-09-35: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires removing the two direct current (DC) over- voltage/feeder-fault test switches from the Test 2 Panel of the generator control unit, and follow-on actions. This action is necessary to prevent loss of the DC generators, which could result in the loss of normal electrical power to the airplane and increased pilot workload. This action is intended to address the identified unsafe condition.