Results
98-08-29: This amendment adopts a new airworthiness directive (AD) that applies to certain Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Model ASK 21 sailplanes. This AD requires removing certain pages from the sailplane flight manual and replacing these pages with new pages having different information regarding spin and stall recovery. This action is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent operators from using inaccurate stall and spin recovery information provided in the sailplane flight manual (SFM), which could result in the inability to recover from a spin or stall during flight.
2017-11-10: We are adopting a new airworthiness directive (AD) for all Lycoming TIO-540-AJ1A reciprocating engines. This AD requires initial and repetitive inspections of engine exhaust system weld joints and torque checking the exhaust pipe flange mounting nuts. This AD was prompted by several reports of engine exhaust leaks. We are [[Page 26983]] issuing this AD to correct the unsafe condition on these products.
2017-10-25: We are adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) model Spey 506-14A, Spey 555- 15, Spey 555-15H, Spey 555-15N, and Spey 555-15P turbofan engines. This AD requires reducing the maximum approved life limits for certain high- pressure compressor (HPC) stage 12 rotor disks. We are issuing this AD to correct the unsafe condition on these products.
98-08-24: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes, and C-9 (military) airplanes, that requires a one-time visual inspection to determine if all corners of the forward lower cargo doorjamb have been previously modified. This amendment also requires low frequency eddy current inspections to detect cracks of the fuselage skin and doubler at all corners of the forward lower cargo doorjamb, various follow-on repetitive inspections, and modification, if necessary. This amendment is prompted by fatigue cracks found in the fuselage skin and doubler at the corners of the forward lower cargo doorjamb. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane.
98-08-19: This amendment adopts a new airworthiness directive (AD) that applies to all Twin Commander Aircraft Corporation (Twin Commander) 500, 600, and 700 series airplanes. This AD requires installing access holes in both wing leading edges and repetitively inspecting the forward attach brackets and straps for cracks. Reports of cracks in the wing to fuselage attachment brackets and straps, wing station (WS) 24, and fuselage frames prompted this action. The actions specified by this AD are intended to detect cracks at the wing to fuselage attach points, which, if not detected and corrected, could cause structural failure and loss of control of the airplane.
80-12-06: 80-12-06 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-3788. Applies to Models N22B (Serial Nos. N22B-5 and up) and N24A (Serial Nos. N24-42 and up), certificated in all categories. Compliance required as indicated. To ensure fastener integrity and prevent possible loss of structural rigidity and strength of primary airframe structure, accomplish the following: (a) Within the next 100 hours time in service after the effective date of this AD, unless already accomplished, replace existing AGS-2050 rivets in the wing, rudder, aileron, flap and landing gear pod structures with improved structural rivets in accordance with the instructions contained in GAF Nomad Service Bulletin No. NMD-51-1 dated November 30, 1979, or an FAA- approved equivalent. (b) Aircraft may be flown in accordance with FAR 21.197 and FAR 21.199 to a location where the modification can be accomplished. (c) For purposes of complying with this AD, an FAA-approved equivalent must be approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region, Honolulu, Hawaii. NOTE: All persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request from the Government Aircraft Factories, 226 Lorimer Street, Port Melbourne, 3207 Vic., Australia. These documents may also be examined at the FAA, Engineering and Manufacturing District Office, 300 Ala Moana Blvd., Room 7321, Honolulu, Hawaii 96850, and Rules Docket, Room 916, FAA, 800 Independence Avenue, S.W., Washington, D.C. 20591. This amendment becomes effective June 16, 1980.
2017-08-08: We are adopting a new airworthiness directive (AD) for certain CFE Company (CFE) turbofan engines. This AD was prompted by a quality escape for high-pressure compressor (HPC) impellers made from forgings with nonconforming material grain size. This AD requires removal of the HPC impeller. We are issuing this AD to correct the unsafe condition on these products.
2005-20-16: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-100, -200, and -200C series airplanes. This AD requires a one-time detailed inspection for cracking of the lugs of the inboard attach fittings of the wing leading edge slat tracks at slat numbers 2 and 5; prior or concurrent actions for certain airplanes; repetitive high-frequency eddy current (HFEC) inspections for cracking of the lug surfaces of those inboard attach fittings if necessary; and replacement of the attach fittings with new, improved fittings. This AD results from reports of damage to the lugs of certain inboard attach fittings of the leading edge slat tracks. We are issuing this AD to prevent a lifted slat, which, if the airplane performs any non-normal maneuver during takeoff or landing at very high angles of attack, could lead to the loss of the slat and reduced control of the airplane.
98-08-15: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100, -200, and -300 series airplanes. This action requires repetitive detailed visual and/or borescope inspections to detect discrepancies of certain areas of the wing strut. This amendment also provides for an optional terminating action for the repetitive inspections. This amendment is prompted by reports that fatigue cracking was found in the vertical chords, midspar webs, and canted closure webs. The actions specified in this AD are intended to detect and correct fatigue cracking and stress corrosion of the wing strut, which could result in failure of the strut-to-wing interface, and consequent separation of the engine and strut from the airplane.
80-05-03: 80-05-03 MCDONNELL DOUGLAS: Amendment 39-3705. Applies to McDonnell Douglas Model DC-9-10, -20, -30, -40, -50 series, and C-9, C-9A, and VC-9 airplanes certificated in all categories, having the cabin aft pressure bulkhead fitted with a ventral door. \n\n\tCompliance required as indicated unless already accomplished. \n\n\tTo prevent elevator control cable binding resulting from interference with insulation blanket material, accomplish the following: \n\n\t(a)\tWithin the next 200 hours' time in service from the effective date of this AD, and thereafter at intervals not to exceed 200 hours' time in service since the last inspection, visually inspect the insulation blanket located in the aft entrance stairway area, left side, (looking forward), for security and to establish that there is no interference with the elevator control cable or pulley identified in Part 2 of McDonnell Douglas Service Bulletin 25-222, Revision 1, dated November 6, 1979. \n\n\t(b)\tIf evidence of insulation blanket sagging and/or interference with the elevator control cables or pulley is detected, rework the blanket as shown in Service Bulletin 25-222, Revision 1, dated November 6, 1979, prior to return to service. \n\n\t(c)\tThe repetitive inspection of paragraph (a) may be discontinued after accomplishment of the insulation blanket rework per paragraph (b) of this AD. \n\n\t(d)\tAlternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(e)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD. \n\n\tThis amendment becomes effective March 10, 1980.