Results
47-32-01: 47-32-01 BELL: (Was Mandatory Note 1 of AD-1H-1.) Applies Only to Model 47B Serial Numbers 2 Through 13. Compliance required at next 100-hour inspection. Rework the stabilizer damper frame clamp with a 1/16-inch saw cut, as shown in Bell Service Bulletin No. 47C7, revised June 12, 1947, in order to permit a clamping action which will prevent the loosening of the subject part of the main rotor mast.
2012-26-14: We are adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan engines. This AD requires a one-time removal from service of the high-pressure (HP) compressor stages 1 to 6 rotor disc assembly before exceeding certain thresholds. This AD was prompted by a report of silver chloride-induced stress corrosion cracking of the HP compressor stages 1 to 6 rotor disc assembly, identified during overhaul. We are issuing this AD to prevent failure of the HP compressor stages 1 to 6 rotor disc assembly, which could result in uncontained failure of the engine and damage to the airplane.
73-15-03: 73-15-03 AVIONS MARCEL DASSAULT: Amendment 39-1688. Applies to Fan Jet Falcon airplanes, Serial Numbers 1 thru 111, which have aluminum alloy air conditioning pipes, P/N's MY20-721-28-1 and MY20-721-61-1, installed. Compliance is required as indicated. To prevent leakage of very hot air into the rear compartment, accomplish the following, unless already accomplished: (a) Within the next 100 hours' time in service after the effective date of this AD, comply with subparagraphs (1) and (2), and thereafter comply with subparagraph (1) at intervals not to exceed 200 hours' time in service from the last inspection. (1) Visually inspect the studs which retain the SEMCA coupling on pipe, P/N MY20-721-28-1, for scoring or bending, and inspect the holes receiving those studs for stretching or elongation, in accordance with Dassault Service Bulletin No. 430 (21-30) dated February 16, 1972, or an FAA-approved equivalent. (2) Inspect the weld beads and adjoining areas at the junction of the pipes, P/N's MY20-721-28-1 and MY20-721-61-1, for cracks using a magnifying glass of 5 power or greater and a dye penetrant, in accordance with Dassault Service Bulletin No. 430 (21-30) dated February 16, 1972, or an FAA-approved equivalent. (b) Within the next 100 hours' time in service after the effective date of this AD or before the accumulation of 600 hours' time in service on an aluminum alloy air conditioning pipe, P/N MY 20-721-28-1 or MY20-721-61-1, whichever occurs later (1) Replace the pipes, P/N's MY20-721-28-1 and MY20-721-61-1, with pipes of the same part number and thereafter continue to replace aluminum alloy pipes before the accumulation of 600 hours' time in service thereon and comply with paragraph (d); or (2) Replace the pipes, P/N's MY 20-721-28-1 and MY20-721-61-1, with stainless steel pipes, P/N's MY20-721-28-2 and MY20-721-61-2, in accordance with Dassault Service Bulletin No. 442 (21-31) dated February 16, 1972, oran FAA-approved equivalent. (c) If scoring or bending of the studs or stretching or elongation of the holes are found during an inspection specified in paragraph (a)(1) or cracks are found during an inspection specified in paragraph (a)(2) before further flight comply with subparagraph (1) or (2) of paragraph (b). (d) For aluminum alloy pipes installed as replacement in accordance with subparagraph (1) of paragraph (b) (1) Before the accumulation of 200 hours' time in service thereon, inspect in accordance with subparagraph (1) of paragraph (a); and (2) Thereafter, inspect in accordance with subparagraph (1) of paragraph (a) at intervals not to exceed 200 hours' time in service from the last inspection. (e) Operators who have not kept records of hours' time in service on pipes, P/N's MY20-721-28-1 and MY20-721-61-1, shall substitute airplane hours' time in service in lieu thereof. (f) The inspections required by paragraphs (a) and (d) and the replacements specified in subparagraph (1) of paragraph (b) may be discontinued when the aluminum alloy air conditioning pipes, P/N's MY20-721-28-1 and MY20-721-61-1, are replaced with stainless steel pipes, P/N's MY20-721-28-2 and MY20-721-61-2, in accordance with Dassault Service Bulletin No. 442 (21-31), dated February 16, 1972, or an FAA-approved equivalent. This amendment becomes effective August 15, 1973.
99-19-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Mitsubishi Model YS-11 and YS-11A 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.
2022-24-06: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-710A1-10, BR700-710A2-20, and BR700-710C4-11 model turbofan engines. This AD was prompted by reports of cracks on certain low-pressure compressor (LPC) rotor (fan) disks. This AD requires initial and repetitive visual inspections of certain LPC rotor fan disks and, depending on the results of the inspections, replacement of any LPC rotor fan disk with cracks detected. This AD also allows modification of the engine in accordance with RRD service information as a terminating action to these inspections, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
94-02-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires an inspection to detect chafing damage to certain wiring in the main avionics rack, repair or replacement of damaged wiring, and modification of the wiring installation. This amendment is prompted by a report of a chafed wire harness found on the main avionics rack on one airplane that resulted in arcing damage to the wire harness and adjacent structure. The actions specified in this AD are intended to prevent chafing of the main avionics rack wiring, which could result in arcing and a fire in the wire bundle; this could lead to damage to aircraft systems and loss of associated aircraft functions.
2012-27-02: We are adopting a new airworthiness directive (AD) for all Turbomeca S.A. Arriel 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K1, 1S, and 1S1 turboshaft engines. This AD requires performing a high gas generator speed (NG) rating vibration check. This AD was prompted by several reports of uncommanded in-flight shutdown on [[Page 2199]] Arriel 1 engines. We are issuing this AD to prevent an uncommanded in- flight shutdown of the engine, which could result in an emergency landing.
2012-26-51: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires revising the airplane flight manual (AFM) to advise the flight crew of emergency procedures for addressing Angle of Attack (AoA) sensor blockage. This AD also provides for optional terminating action for the AFM revision, which involves replacing AoA sensor conic plates with AoA sensor flat plates. This AD was prompted by a report that an airplane equipped with AoA sensors installed with conic plates recently experienced blockage of all sensors during climb, leading to autopilot disconnection and activation of the alpha protection (Alpha Prot) when Mach number was increased. We are issuing this AD to prevent reduced control of the airplane.
2012-26-01: We are adopting a new airworthiness directive (AD) for all Saab AB, Saab Aerosystems Model SAAB 2000 airplanes. This AD was prompted by reports of chafing on the bottom panel of the center cabin. This AD requires a general visual inspection to determine if certain fasteners are installed, and related investigative and corrective actions. We are issuing this AD to detect and correct any chafing on the bottom panel of the center cabin, which could affect the structural integrity of the affected wing-to-fuselage connection.
2022-10-02: The FAA is superseding Airworthiness Directive (AD) 2002-03- 01, which applied to certain Honeywell International, Inc. (Honeywell) T53 model turboshaft engines. AD 2002-03-01 required initial and repetitive special vibration tests of the engine and, if necessary, replacement with a serviceable reduction gearbox assembly, or a serviceable engine before further flight. This AD was prompted by reports of tachometer drive spur gear failure, resulting in potential engine overspeed, loss of power turbine speed (N2) instrument panel indication, and hard landings. This AD requires initial and repetitive special vibration tests of the engine and, depending on the results, replacement of either the reduction gearbox assembly or the engine. The FAA is issuing this AD to address the unsafe condition on these products.