Results
2014-21-06: We are adopting a new airworthiness directive (AD) for certain Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company; Beech Aircraft Corporation) Model 400, 400A, 400T, and MU-300 airplanes. This AD was prompted by a report of a failure of the Acme nut threads in a pitch trim actuator (PTA). This AD requires an inspection to determine if PTAs having a certain serial number and part number are installed, and replacement if they are installed. This AD also requires repetitive replacements of PTAs with new PTAs or certain overhauled PTAs. We are issuing this AD to prevent failure of the Acme nut threads in the PTA, which could lead to loss of control of pitch trim and reduced controllability of the airplane.
2000-13-05: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc. (RR) RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan engines. This action requires initial and repetitive ultrasonic inspections for cracks in fan blade dovetail roots, and if necessary, replacement with serviceable parts. This amendment is prompted by reports of fan blade failures due to dovetail root cracks in factory engine. The actions specified in this AD are intended to prevent possible multiple fan blade failures, which could result in an uncontained engine failure and damage to the airplane.
2014-21-02: We are adopting a new airworthiness directive (AD) for Pacific Aerospace Limited Model FU24-954 and FU24A-954 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 cracking of the control column at the wiring access hole, which could lead to loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
97-04-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires a visual inspection to determine if rudder disconnection has occurred, and replacement of the disconnect unit with a new disconnect unit, if necessary. This amendment is prompted by reports that, due to the existing design, the disconnect unit of the rudder disconnect system inadvertently opened on some airplanes. The actions specified by this AD are intended to prevent the disconnect unit from opening inadvertently, which could lead to inadequate rudder control, if the engine fails during take-off or go-around and if the airplane is at low speed.
2005-02-05: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce (RR) plc RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 series turbofan engines. That AD currently requires initial and repetitive ultrasonic inspections of installed LPC fan blade roots on-wing and during overhaul using a surface wave ultrasonic probe, and relubrication, according to accumulated life cycles. That AD also adds the application of Metco 58 blade root coating as an optional terminating action. This AD requires the same actions, but changes the reference to Mandatory Service Bulletin (MSB) No. RB.211-72-C879 from Revision 3 to Revision 4. This AD results from RR issuing MSB No. RB.211-72-C879, Revision 4, which contains revised Accomplishment Instructions and consumable materials list. We are issuing this AD to detect cracks in low pressure compressor (LPC) fan blade roots, which if not detected, could lead to uncontained multiple fan blade failure, and damage to the airplane.
80-14-10: 80-14-10 BRITTEN-NORMAN (BEMBRIDGE) LTD.: Amendment 39-3828. Applies to Model BN-2A Mark III Series Trislander airplanes, certificated in all categories. Compliance is required as indicated unless already accomplished. To detect corrosion and to prevent loss of the rudder mass balance arm brackets which could cause hazardous rudder flutter, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD or prior to 2 years since new, whichever occurs later, visually inspect for corrosion the support brackets of the mass balance arms at the top, and on each side, of the rudder in accordance with paragraph "ACTION," of Britten-Norman Service Bulletin BN-2/SB.116, dated June 5, 1978 (hereinafter referred to as the service bulletin), or an FAA-approved equivalent. (b) If corrosion is found as a result of the inspection required by paragraph (a) of this AD, before further flight, except that the aircraft may be flown in accordance with FAR 21.197 and FAR 21.199 to a base where the work can be performed, accomplish either of the following: (1) Perform the permanent repair as specified in "Rectification - Part 1" of the service bulletin or an FAA-approved equivalent, and thereafter reinspect for corrosion in accordance with paragraph (a) of this AD, at intervals not to exceed 3 years from the date of the repair; or (2) Perform the temporary repair as specified in "Rectification - Part 2" of the service bulletin or an FAA-approved equivalent, and thereafter continue to perform the inspection required by paragraph (a) of this AD, at intervals not to exceed 2 months from the date of the repair, for a maximum of 1 year at which time the permanent repair and inspection required by paragraph (b)(1) of this AD must be accomplished. (c) If no external corrosion is found as a result of the inspection required by paragraph (a) of this AD, the mass balance arm support brackets may continue in servicefor a period not to exceed 6 months from the date of the initial inspection, provided that the visual inspection required by paragraph (a) of this AD is repeated at intervals not to exceed 2 months or 200 hours time in service from the last inspection, whichever occurs first, after which the permanent or temporary repairs and inspections of paragraph (b)(1) or (b)(2) must be accomplished. (d) Prior to the installation of rudders held in stock as spares, accomplish the inspection and repair as necessary in accordance with paragraphs (a) and (b)(1) of this AD. (e) For purposes of this AD, an FAA-approved equivalent must be approved by the Chief, Aircraft Certification Staff, Federal Aviation Administration, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium, Telephone: 513.38.30. This amendment becomes effective July 14, 1980.
80-20-06: 80-20-06 CESSNA: Amendment 39-3937. Applies to Model 421C airplanes (Serial Number 421C0401 and on) having King KFC-200 Flight Control System installed under Supplemental Type Certificate SA1246CE. COMPLIANCE: Required as indicated unless already accomplished. To prevent the airplane from exceeding 60 degrees bank angle in the event of a roll axis hard-over malfunction, accomplish the following: A) Within the next 25 hours time-in-service after the effective date of this AD, reset the KFC-200 roll axis slip clutch from 60 plus or minus 6 inch-pounds to 38 plus or minus 4 inch-pounds in accordance with the instructions contained in King Radio Service Sales Installation Bulletin No. 167 dated August 4, 1980. B) Airplanes may be flown in accordance with FAR 21.197 to a location where the maintenance required by this AD may be performed provided the autopilot is inoperative. C) Any equivalent method of compliance must be approved by the Chief, Aircraft Certification Program, Federal Aviation Administration, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209. This amendment becomes effective October 14, 1980.
2023-14-02: The FAA is adopting a new airworthiness directive (AD) for all Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500-1A11 airplanes. This AD was prompted by a determination that radio altimeters cannot be relied upon to perform their intended function if they experience interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band), and a recent determination that this interference may affect other airplane systems using radio altimeter data, including the ground spoiler deployment system. This AD requires revising the limitations section of the existing AFM to incorporate limitations prohibiting the use of a certain master minimum equipment list (MMEL) item. The FAA is issuing this AD to address the unsafe condition on these products.
79-19-04: 79-19-04 SHORT BROTHERS LIMITED: Amendment 39-3552. Applies to Model SD3-30 airplanes, S/Nos. SH 3004, 3005, 3006, 3007, and 3008, certificated in all categories. Compliance is required prior to the accumulation of 10,000 flights or prior to the accumulation of 25 flights after the effective date of this AD, whichever occurs later, unless already accomplished; and thereafter at intervals not to exceed 10,000 flights. To prevent fatigue failure of the flap control rods, replace flap control rods, Part Nos. SD3-45-1853 and SD3-45-1855, located immediately aft of wing center section rear spar and part of inner flap mechanism, with new rods of identical part numbers in accordance with Section 2, "Accomplishment Instructions" of Short Brothers Ltd. Service Bulletin SD3-27-14, dated April 28, 1978, or an equivalent approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Region, Federal Aviation Administration, c/o American Embassy, Brussels,Belgium. For purposes of complying with this AD, a flight is defined as one takeoff and one landing. This amendment becomes effective October 4, 1979.
2000-12-08: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) Models CF6-80C2A1/A2/A3/A5/A5F/A8/D1F turbofan engines. This AD requires initial and repetitive visual inspections of left hand and right hand aft engine mount link assemblies for separations, cracks and spherical bearing race migration. Cracked or separated parts must be replaced prior to further flight. If spherical bearing race migration is discovered, an additional borescope inspection for cracks is also required. If no cracks are discovered by the additional borescope inspection, assemblies have a 75- cycle grace period for remaining in service before replacement. Finally, installation of improved aft engine mount link assemblies constitutes terminating action to the inspections of this AD. This amendment is prompted by a report of a fractured left hand aft engine mount link discovered during a scheduled removal of an engine of similar design. The actions specified by the AD are intended to prevent aft engine mount link failure, which can result in adverse redistribution of the aft engine mount loads and possible aft engine mount system failure.