Results
2014-06-08: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8 airplanes. This AD requires repetitive functional checks of the nose and main landing gear, and corrective actions if necessary. This AD also provides optional terminating action for the repetitive functional checks. This AD was prompted by a report that the emergency downlock indication system (EDIS) had given a false landing gear down-and-locked indication. We are issuing this AD to detect and correct a false down-and-locked landing gear indication, which, on landing, could result in possible collapse of the landing gear.
83-07-20: 83-07-20 SIAI-MARCHETTI: Amendment 39-4622. Applies to Model S205-22R airplanes with a muffler assembly P/N 870-8 or P/N 870-9 installed, certificated in any category. Compliance: Required as indicated unless already accomplished. To prevent failure of the exhaust system, accomplish the following: (a) Within the next 100 hours time-in-service after the effective date of this AD or when the muffler has accumulated 500 hours time-in-service, whichever occurs later, and at each 100-hour time-in-service interval thereafter, accomplish the following: (1) Perform a fiberscope inspection of the inside baffling of the muffler assembly for cracks by inserting an OLYMPUS ILK-2 type fiberscope (or equivalent) though the exhaust tube into the inside baffling of the muffler assembly in accordance with the "INSTRUCTION" section of SIAI-Marchetti Service Bulletin No. 205B56 dated November 20, 1981, or an FAA-approved equivalent. (i) If cracks are found, prior to further flight, replace the muffler. (ii) If no cracks are found, continue the repetitive inspections as indicated above. (b) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. (c) Operators who have not kept records of hours time-in-service of the mufflers must substitute airplane hours time-in-service in lieu thereof. (d) Airplane may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (e) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on April 14, 1983.
61-13-03: 61-13-03 SCHLEICHER: Amdt. 299 Part 507 Federal Register June 24, 1961. Applies to Model K7 Gliders With Serial Numbers Up To and Including 935 and Serial Number 984. Compliance required prior to next flight unless already accomplished. To preclude the buckling of fuselage steel tube members on each side at the rear of the fuselage, replacement of five tubes with tubes having greater wall thickness is required. Replace the existing steel tube diagonal members, counting forward from the tail post as follows, using Civil Aeronautics Manual 18 repair procedures or manufacturer's recommendation. (a) Right side only, third member: Replace with 12 MMS. (15/32"), outside diameter, 1MM. (.040") wall thickness tubes. (b) Right and left side, fourth and sixth members: Replace with 14 MMS. (9/16") outside diameter, 1 MM. (.040") wall thickness tubes. (Schleicher Drawing No. L-211.10-A4 dated March 15, 1961, covers this subject.) This directive effective June 24, 1961.
2014-05-16: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-200B, 747-300, 747-400, 747-400D, 747-400F series airplanes, and Model 767 series airplanes, powered by General Electric (GE) CF6-80C2 engines. This AD was prompted by reports of failure of the electro mechanical brake flexshaft (short flexshaft) of the thrust reverser actuation system (TRAS). This AD requires replacing the short flexshaft on each engine with a new short flexshaft, testing of the electro mechanical brake and center drive unit (CDU) cone brake to verify the holding torque, and performing related investigative and corrective actions if necessary. We are issuing this AD to prevent an uncommanded in-flight thrust reverser deployment and consequent loss of control of the airplane.
79-23-06: 79-23-06 BEECH: Amendment 39-3615. Applies to Model 76 (Serial Numbers ME-1 through ME-164, ME-166, ME-168 through ME-181, ME-184 through ME-193, ME-195 and ME-198) airplanes certificated in all categories. COMPLIANCE: Required as indicated unless already accomplished. To prevent possible restriction in aileron and rudder travel, within twenty-five (25) hours time-in-service after the effective date of this AD accomplish the following: A) On Serial Numbers ME-1 through ME-149, ME-151 through ME-164, ME-166, ME-168 through ME-181, ME-184 through ME-190, ME-192, and ME-193 visually inspect and, if necessary, replace the stop bolt nuts for the aileron bell cranks with self-locking nuts in accordance with procedures set forth in Beechcraft Service Instructions Number 1087. B) On Serial Numbers ME-1 through ME-164, ME-166, ME-168 through ME-181, ME-184 through ME-193, ME-195 and ME-198 visually inspect and, if necessary, replace the stop bolt nuts for the rudder bell crank with self-locking nuts in accordance with procedures set forth in Beechcraft Service Instructions Number 1087. C) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. D) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective November 23, 1979.
2011-22-05 R1: We are revising Airworthiness Directive (AD) 2011-22-05 for Eurocopter France (Eurocopter) Model AS350B, B1, B2, B3, BA, C, D, D1, AS355E, F, F1, F2, N, and NP helicopters with certain tail rotor (T/R) pitch control rods (control rods) installed. AD 2011-22-05 required checking the control rod for play before the first flight of each day. This new AD requires checking the control rod for play within 30 hours time-in-service (TIS) and, if no bearing play is detected, thereafter at intervals not to exceed 30 hours TIS. The actions in this AD are intended to prevent failure of a T/R control rod, loss of T/R control, and subsequent loss of control of the helicopter.
2014-05-11: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332L, AS332L1, AS332L2, EC225LP, and SA330J helicopters with a certain tail rotor control turnbuckle (turnbuckle) installed. This AD requires inspecting the turnbuckles for corrosion or a crack, and depending on the results, either replacing the turnbuckle or treating the turnbuckle for corrosion. This AD was prompted by a report that a turnbuckle had failed because of corrosion. The actions of this AD are intended to detect corrosion or a crack on a turnbuckle and prevent the failure of a turnbuckle, loss of control of the tail rotor and subsequent loss of control of the helicopter.
63-17-04: 63-17-04 LOCKHEED: Amdt. 600 Part 507 Federal Register August 13, 1963. Applies to All Model 1329 Aircraft. Serial Numbers 5001 and Up. Compliance required as indicated. As a result of cracks in the rib flanges of the horizontal stabilizer box section, accomplish the following: (a) Prior to further flight post the following placards in full view of the pilot: (1) "Airspeed Limit V MO Equals 300 Knots Eas. M Mo Remains Mach 0.82." (2) "Do Not Extend Speed Brake During Flight at Speeds Above 250 Knots EAS or at Altitudes Above 30,000 Feet Except in an Emergency." (b) Within the next 20 hours' time in service, after the effective date of this AD, inspect the horizontal stabilizer in accordance with the provisions specified in Lockheed Bulletin No. 329-142. (c) When a new stabilizer P/N JE 205-502 is installed in accordance with Lockheed Jetstar Service Bulletin No. 329-148 dated January 31, 1964, or an equivalent modification approved by the Chief, Engineering Branch, FAA Southern Region is incorporated, compliance with this AD is no longer required. This directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated July 25, 1963. Revised September 7, 1963. Revised March 7, 1964.
2014-05-04: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model MBB-BK 117 C-2 helicopters with a jettisonable sliding door (door) installed. This AD requires inspecting the lock release assembly and the middle and upper lever locking bolts of each door, replacing any damaged parts with airworthy parts, and ensuring the door is correctly installed. This AD was prompted by the uncommanded detaching of a door from an MBB-BK 117 C-2 fuselage. The actions of this AD are intended to prevent the in- flight loss of the door, which could damage the helicopter and injure persons on the ground.
70-15-13: 70-15-13 ROLLS-ROYCE, LIMITED: Amdt. 39-1045. Applies to all series Rolls Royce Dart Models 506, 510, 511, 514, 525, 526, 528, 529, and 532 engines having Dart Modification 827 or 1224 fuel washed burners installed. These engines are installed on, but not necessarily limited to, the following type aircraft: Hawker Siddeley, Argosy AW.650; Fairchild Hiller F-27, F-27A, F-27B, F-27F, F-27G, F-27J, FH-227, FH-227B, FH-227C, FH-227D, FH-227E; Fokker F.27, all marks; British Aircraft Corporation Viscount 744, 745D, and 810; and Grumman G-159. To prevent cracking of the fuel washed burners, within the next 300 hours' time in service after the effective date of this AD, unless already accomplished, replace Dart Modification 827 and 1224 fuel washed burners with burners incorporating Rolls Royce Dart Modification 1155, 1226, or 1536, in accordance with Rolls Royce Dart Aero Engine Alert Service Bulletin Number Da 73-A.54, Revision 3, dated February 16, 1970, or late ARB-approvedissue or an FAA-approved equivalent. This amendment becomes effective August 20, 1970.