Results
75-24-03: 75-24-03 LEARJET MODEL 24A: Amendment 39-2423. Applies only to airplanes modified per STC ST7RM when used in cargo operation. Compliance required within the next 150 hours time in service after the effective date of this AD, unless already accomplished. To provide an adequate emergency exit for flight crew members, install Alpine Aircraft Charters, Inc., STC SA14RM or equivalent approved by Chief, Engineering and Manufacturing Branch, Rocky Mountain Region, or provide access to the existing emergency exit on the right side of the fuselage in a manner approved by Chief, Engineering and Manufacturing Branch, Rocky Mountain Region. This amendment becomes effective on December 18, 1975.
2013-19-10: We are adopting a new airworthiness directive (AD) for PILATUS AIRCRAFT LTD. Model PC-12/47E 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 common grounding of both the pilot primary flight display (PFD) and the Electronic Standby Instrument System (ESIS). If the common ground fails both navigations systems could fail simultaneously, which could result in loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
2013-16-21: We are superseding an airworthiness directive (AD) for Agusta Model A109E helicopters that required reducing the tail rotor (T/R) blade life limit, modifying a T/R hub and grip assembly, re-identifying two T/R assemblies, clarifying the never-exceed speed (Vne) limitation, and reducing the inspection interval. Since we issued that AD, the manufacturer has redesigned a T/R grip bushing (bushing) that reduces the loads, which caused the T/R cracking, on the T/R blades. This action requires installing the new bushing and re-identifying the T/R hub-and-grip and hub-and-blade assemblies and requires a recurring inspection of each bushing. These actions are intended to prevent fatigue failure of a T/R blade and subsequent loss of control of the helicopter.
73-26-08: 73-26-08 BEECH: Amendment 39-1764. Applies to Models 95-55, 95-A55, 95-B55 (Serial Numbers TC-1 through TC-1573 except TC-350); 95-C55, D55, D55A, E55 and E55A (Serial Numbers TE-1 through TE-919 and TC-350), airplanes equipped with the EDO-AIRE Mitchell AK-292 Autopilot. \n\n\tCompliance: Required within 25 hours' time in service after the effective date of this AD, unless previously accomplished in accordance with data described herein or any alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. \n\n\tTo determine if the roll and pitch servo clamps have slipped and to assure sufficient torque on the clamp bolts accomplish the following: \n\n\tA)\tInspect the roll pitch bridle cables and clamps by: \n\n\t\t(1)\tRunning the aileron and pitch controls through their full travel to assure that there is no binding or restrictions between the bridle cables and clamps and aircraft components. Clamps should be positioned so there is no binding or restriction between the bridle cable and capstan flange. \n\n\t\t(2)\tDetermine that the bridle cables tensions are the same as the tension of the control cable they are attached to. \n\n\tB)\tTorque the bolts on the cable clamps to 55 + or - 5 in. lbs. with a minimum gap of .005 between halves of clamp after torquing. \n\n\tNOTE: Figure 1, attached hereto, depicts a typical installation of the bridle cables and clamps. \n\n\tThis amendment becomes effective December 26, 1973.
92-10-09: 92-10-09 BRITISH AEROSPACE: Amendment 39-8243. Docket No. 91-NM-260-AD. Applicability: British Aerospace Model BAe 125-800A series airplanes, having NA numbers as listed in British Aerospace Service Bulletin SB 27-155, dated August 16, 1991, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced controllability of the airplane, accomplish the following: (a) Within 3 months after the effective date of this AD, inspect the rudder pedal torque tubes (four per airplane) for defects or cracks, using BAe High Frequency Eddy Current Inspection Technique No. 27-20-101, in accordance with British Aerospace Service Bulletin SB 27-155, dated August 16, 1991. (b) If any defects or cracks are detected that exceed the limit specified in British Aerospace Service Bulletin SB 27-155, dated August 16, 1991, prior to further flight, replace them with serviceable components in accordance with the service bulletin. (c) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The inspections and repairs shall be done in accordance with British Aerospace Service Bulletin SB 27-155, dated August 16, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (f) This amendment becomes effective on June 29, 1992.
2013-18-09: We are adopting a new airworthiness directive (AD) for certain Honeywell ASCa Inc. emergency locator transmitters (ELTs) installed on various transport category airplanes. This AD requires various one-time general visual inspections of the ELT transmitter units (TUs), and corrective actions if necessary. This AD was prompted by a fire on a parked and unoccupied airplane; preliminary information indicated combustion in the area of the ELT TU. We are issuing this AD to detect and correct discrepancies of the battery wiring installation inside the TU, which could result in an electrical short and possible ignition source.
2013-18-01: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155B, EC155B1, SA-365N, SA- 365N1, AS-365N2, AS 365 N3, and SA-366G1 helicopters. This AD requires inspecting the collective pitch lever for correct locking and unlocking conditions. This AD was prompted by two separate reports of inadvertent collective pitch lever locking and unlocking. The actions of this AD are intended to detect an incorrectly adjusted collective pitch lever, which could result in loss of control of the helicopter.
2000-12-15: This amendment adopts a new airworthiness directive (AD), applicable to all Dassault Model Falcon 2000, Mystere-Falcon 900, Falcon 900EX, Fan Jet Falcon, Mystere-Falcon 50, Mystere-Falcon 20, Mystere-Falcon 200, and Falcon 10 series airplanes, that requires repetitive tests and inspections to detect discrepancies of the overwing emergency exit; and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the overwing emergency exits to open, and consequent injury to passengers or crew members during an emergency evacuation.
2013-18-04: We are adopting a new airworthiness directive (AD) for all PIAGGIO AERO INDUSTRIES S.p.A Model P-180 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 cracks at the joint between the hinge pin sub-assembly and the lock pin of the main landing gear lever hinge fitting. We are issuing this AD to require actions to address the unsafe condition on these products.
2021-18-06: The FAA is superseding Airworthiness Directive (AD) 2021-11- 03, which applied to certain Airbus Helicopters Model EC 155B, EC155B1, SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters. AD 2021-11-03 required inspecting the main gearbox (MGB) fixed cowling front fitting (MGB front fitting), and depending on findings, corrective action. This AD retains the requirements of AD 2021-11-03, and includes service information that was omitted for Airbus Helicopter Model EC 155B and EC155B1 helicopters, as specified in a European Aviation Safety Agency (now 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.