Results
68-08-07: 68-08-07 LOCKHEED: Amendment 39-585. Applies to Model 1329 Airplanes, Serial Numbers 5001 through 5092, 5094 through 5096. Compliance required as indicated. Recent calibration of several airplanes has revealed a difference in the airspeed and altimeter system static position error from the values presented in the AFM. These differences are in excess of tolerances which can be accepted as normal deviation from an Airplane Flight Manual calibration curve. To detect similar discrepancies, the following is required unless the system has previously been calibrated in accordance with the referenced manufacturer's instructions. Within the next 100 hours' time in service after the effective date of this AD, calibrate the pitot static system in accordance with the instructions given in Lockheed-Georgia Service Bulletin 329-250, Section 2a through 2p, or later FAA approved revision; or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. This amendment becomes effective April 19, 1968.
48-06-03: 48-06-03 NAVION: Applies to All models Equipped With Hartzell Propeller Blade Models 8428, 8428C, 8428R Having Serial Numbers Below 61000. Compliance required by April 15, 1948. Examine all Model 8428, 8428C, and 8428R blades having Serial Numbers below 61000 in bright daylight or strong artificial light on the front face in the area approximately 4 inches outboard of the blade clamp. Any fillers used in the blade will be discernible to the naked eye. If fillers are found in this area, the paint should be carefully removed and the fillers removed from the blade. Defects that can be eliminated by removing material to form a shallow saucer not over 1/8 inch at its deepest point, 3/8 inch in width overall, and 1 inch in length overall, should be repaired. Following removal of the defects, the area from which paint has been removed should be repainted and the propeller rebalanced before being returned to service. Blades having defects that cannot be repaired by the above methodor by methods described in the applicable portions of CAM 18, should be returned to the propeller manufacturer. The exact location and the extent of rework necessary to remove any defect should be recorded in the log book. Areas having maximum material removed may not have additional material removed for subsequent injuries.
2002-11-05 R1: The FAA is adopting a new airworthiness directive (AD) to revise AD 2002-11-05, which applies to certain Air Tractor, Inc. (Air Tractor) AT-400 series and Models AT-501, AT-802, and AT-802A airplanes. AD 2002-11-05 establishes a safe life for the wing lower spar cap. Since we issued AD 2002-11-05, we have received reports of cracks found prior to the established safe life on AT-400 series airplanes and on Model AT-802A airplanes. We are issuing separate AD actions for AT-400 series and Models AT-802 and AT-802A airplanes to address the unsafe condition of those airplanes. This AD retains the actions required in AD 2002-11-05 for Model AT-501 airplanes and removes AT-400 series and Models AT-802 and AT-802A airplanes from the applicability of AD 2002-11-05.
2003-13-11: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney (PW) PW4074, PW4074D, PW4077, PW4077D, PW4090, and PW4090-3 turbofan engines with high pressure compressor (HPC) rear cases, part numbers (P/Ns) 55H425-01, 55H385-01, and 56H396-01 installed. This AD requires initial and repetitive visual or fluorescent penetrant inspections (FPI) of the J flange on the HPC rear case, and removal from service of the rear case based on certain inspection results. This AD is prompted by reports of cracks propagating from bolt holes in the HPC rear case J flange, and reports of high-cycle HPC rear cases exhibiting cracks propagating into the shell wall. The actions specified in this AD are intended to prevent fracturing and rupturing of the HPC rear case, resulting in uncontained engine failure.
2001-24-11: This amendment adopts a new airworthiness directive (AD) that is applicable to all Raytheon Model Beech 400, 400A, and 400T series airplanes, Model Mitsubishi MU-300 airplanes, and Model Beech MU-300-10 airplanes. This action requires revising the Emergency Procedures Section of the Airplane Flight Manual to ensure the flightcrew is advised of in-flight procedures in the event of loss of airspeed indication. Such loss of airspeed indication and the resulting adverse effects on certain connecting systems could result in reduced controllability of the airplane.
2006-10-03: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319-100 and A320-200 series airplanes, and Model A320-111 airplanes. This AD requires modifying the wiring to the fuel pump control of the center fuel tank. This AD results from reports that the low-pressure warning for the fuel pumps of the center fuel tank has come on in flight. We are issuing this AD to ensure that the fuel pumps do not run while dry, which could result in a potential ignition source inside the center fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
69-09-01: 69-09-01 EISEMANN: Amdt. 39-784. Applies to all type AM-4, AM-6, LA-4, and LA-6 Eisemann magnetos installed on, but not necessarily limited to: Continental A-50 Series Continental A-65 Series Continental A-75 Series Continental A-80 Series Continental C-75 Series Continental C-85 Series Continental C-115 Series Continental C-125 Series Continental E-165 Series Continental E-185 Series Franklin (Aircooled Motors) 2A4 Series Franklin (Aircooled Motors) 4AC Series Franklin (Aircooled Motors) 4A4 Series Franklin (Aircooled Motors) 6AC Series Franklin (Aircooled Motors) 6AL Series Franklin (Aircooled Motors) 6A8 Series Franklin (Aircooled Motors) 6A4 Series Franklin (Aircooled Motors) 6V4 Series Franklin (Aircooled Motors) 6AG4 Series Menasco C4, D4, D4-87 Compliance required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. To prevent the possibility of loss of engine power in flight caused by electrically shorted windings in the magneto coil, accomplish the following: (a) Inspect the coils P/N H27-958 used in Eisemann Type LA-4, LA-6, AM-4 and AM-6 magnetos for a yellow inspection stamp consisting of a letter and a numeral. (b) Remove from further service those coils inspected in (a) bearing the following stamps: A76, B76, C76, D76, F76, G76, H76, J76, K76, L76, M76, D86, E86, F86, G86, H86, J86, K86. (c) Install coils P/N H27-958 bearing yellow inspection stamp symbols other than those listed under (b) above or an equivalent approved by Chief, Engineering and Manufacturing Branch, FAA, Southern Region. (d) This airworthiness directive affects only coils with the green plastic covering and does not affect: (1) Taped coils. (2) Those covered in black plastic. (3) Those bearing inspection stamps of any type or color (other than those listed under (b) above). (4) Those bearing no inspection stamp. The compliance time may be adjusted up to a maximum of 10 hours to coincide with aircraft annual or 100-hour scheduled inspections. (American Industrial Sales Bulletin dated November 1, 1968, pertains to this same subject.) Effective May 1, 1969. Revised June 24, 1969.
2020-16-02: The FAA is adopting a new airworthiness directive (AD) for Pilatus Aircraft Ltd. Models PC-6, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/ B2-H4, PC-6/C-H2, PC-6/C1-H2, PC-6-H1, and PC-6-H2 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 rudder shaft assemblies with incorrect rivet configurations. The FAA is issuing this AD to address the unsafe condition on these products.
99-19-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Gulfstream American (Frakes Aviation) Model G-73 (Mallard) and G-73T series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
74-10-05 R1: 74-10-05 R1 PRATT & WHITNEY AIRCRAFT: Amendment 39-1834 as amended by Amendment 39-3972. Applies to all Pratt & Whitney Aircraft JT9D-7, JT9D-7A, and JT9D-20 turbofan engines. Compliance required as follows unless already accomplished. To preclude possible turbine blade or disc failures resulting from deflection of the second stage turbine nozzle guide vane inner support, perform a radioisotope inspection in accordance with paragraph 8 below per the following schedule: 1. Engines containing second stage vanes, P/N 708952. a. For vanes with less than 4000 hours total time in service or less than 4000 hours since the fuel nozzles and supports were last cleaned, as of June 7, 1974, inspect prior to the accumulation of 4000 hours total time, or 4000 hours since the fuel nozzles and supports were last cleaned, or 400 hours time in service after June 7, 1974, whichever occurs later. b. For vanes with 4000 or more hours total time in service and 4000 or more hours since the fuel nozzles and supports were last cleaned, as of June 7, 1974, inspect within the next 400 hours time in service. c. Repeat the above inspection every 700 hours time in service thereafter. 2. Engines containing second stage vanes, P/N 708952, that were reworked per Pratt & Whitney Service Bulletin 3946 and reidentified to P/N 728752 and operated in engines prior to rework. a. Inspect within the next 400 hours time in service after June 7, 1974. b. Repeat the above inspection every 700 hours time in service thereafter. 3. For engines containing new production second stage vanes 719552, 728752, 731552, 735882, 740292, 747082, 746492, and 747172, not reworked in accordance with Service Bulletin 3946 and operated prior to the incorporation of Pratt & Whitney Service Bulletin 4146. a. For vanes with less than 5000 hours total time in service or less than 4000 hours since the fuel nozzles and supports were last cleaned, as of June 7, 1974, inspect prior to the accumulation of 5000 hours total time, or 4000 hours since the fuel nozzles and supports were last cleaned, or 400 hours time in service after June 7, 1974, whichever occurs later. b. For vanes with 5000 or more hours total time in service and 4000 or more hours since the fuel nozzles and supports were last cleaned, as of June 7, 1974, inspect within the next 400 hours time in service. c. Repeat the above inspection every 2500 hours time in service thereafter. 4. For engines containing second stage vanes, 719552, 728752, 731552, 740292, and 747172, that have incorporated Pratt & Whitney Service Bulletin 4146 before operation. a. For vanes with less than 5000 hours total time in service or less than 5000 hours since the fuel nozzles and supports were cleaned, as of June 7, 1974, inspect prior to the accumulation of 5000 hours total time or 5000 hours since the fuel nozzles and supports were cleaned, or 400 hours time in service after June 7, 1974, whichever occurs later. b. For vanes with more than 5000 hours total time in service and 5000 or more hours since the fuel nozzles and supports were cleaned, as of June 7, 1974, inspect within the next 400 hours time in service. c. Repeat the above inspection every 2500 hours time in service thereafter. 5. If any radioisotope inspection mentioned above indicates a deflection which exceeds .070 inch, remove the affected engine from service prior to further flight. 6. For engines containing a complete set of second stage vanes 735882, 746492, 747082, 772572, or 785992 that have incorporated Pratt & Whitney Service Bulletin 4146 before operation. a. For vanes with less than 5000 hours total time in service or less than 5000 hours since the fuel nozzles and supports were cleaned, as of May 10, 1974, inspect prior to the accumulation of 5000 hours total time or 5000 hours since the fuel nozzles and supports were cleaned, or 400 hours time in service after May 10, 1974, whichever occurs later. b. For vanes with more than 5000 hours total time in service and 5000 or more hours since the fuel nozzles and supports were cleaned, as of May 10, 1974, inspect within the next 400 hours time in service. c. Repeat the above inspection every 2500 hours time in service thereafter. 7. If the radioisotope inspection in accordance with paragraph 6 above indicates vane deflection which exceeds 0.130 inches, remove the affected engine from service prior to further flight. Engines with vane deflection greater than 0.070 inches and up to 0.130 inches must be reinspected every 1250 hours time in service thereafter. Engines with vane deflection of 0.070 inches and less must be reinspected every 2500 hours time in service thereafter. 8. The inspections required above are radioisotope inspections conducted as follows: a. For JT9D-7 and JT9D-7A engines, inspect in accordance with radioisotope inspection procedures specified in the Boeing Maintenance Manual, Section 72-00-00, Paragraph E(7), Pages 680N and 680P, revision dated March 1974, for those engines, or later Federal Aviation Administration approved revision. b. For JT9D-20 engines, inspect in accordance with radioisotope inspection procedures specified in the McDonnell-Douglas Maintenance Manual, Section 72-00-00, Paragraph 2.G., Pages 631 and 633, revision dated May 1973, for this engine, or later Federal Aviation Administration approved revision. 9. Upon submittal of substantiating data through a Federal Aviation Administration Inspector, the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England Region, may adjust the compliance time. 10. For cases where vanes are mixed, if ten or more vanes of any one of the above part numbered categories are installed in an engine, the most restrictive category will apply. The manufacturer's specifications and procedures identified and described in this directive areincorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to The Boeing Company, Post Office Box 3707, Seattle, Washington 98124 and McDonnell- Douglas Corporation, Douglas Aircraft Company, 3855 Lakewood Boulevard, Long Beach, California 90801. These documents may also be examined at the Office of the Regional Counsel, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803 and at Federal Aviation Administration Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the Federal Aviation Administration at its headquarters in Washington, D.C., and at the New England Regional Office in Burlington, Massachusetts. Note: Pratt & Whitney Alert Service Bulletin 4304 pertains to this subject. Amendment 39-1834 became effective June 7, 1974. This amendment 39-3972 becomes effective November 17, 1980.