Results
97-04-12: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Pratt & Whitney Canada (PWC) PT6 series turboprop engines. This action requires a one-time visual inspection of compressor bleed-off valves (BOVs) to determine if an affected supplier's code number is on the cover; and, if so, this AD requires the removal of the bleed valve cover assembly from the compressor bleed valve housing assembly and inspection of the cotter pin and the guide shaft pin. If the cotter pin or guide shaft pin is not acceptable, this AD requires modifying the compressor BOV or replacing it with a serviceable part. This amendment is prompted by reports of two malfunctions of compressor BOVs that resulted in inflight engine power reduction. The actions specified in this AD are intended to prevent engine power reduction due to malfunction of the compressor BOV, which could result in a forced landing and loss of the aircraft.
2005-02-03: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT8D-209, -217, -217A, -217C, and -219 series turbofan engines. That AD currently requires torque inspection of the 3rd stage and 4th stage low pressure turbine (LPT) blades for shroud notch wear and replacement of the blade if wear limits are exceeded. This AD continues to require those torque inspections at shorter inspection intervals of the refurbished 3rd stage and 4th stage LPT blades, but the same or longer inspection intervals of the new 3rd stage and 4th stage LPT blades, for shroud notch wear and replacement of the blade if wear limits are exceeded. This AD also requires replacing LPT-to-exhaust case bolts and nuts with bolts and nuts made of Tinidur material. This AD results from reports of 194 blade fractures since 1991, with 37 of those blade fractures resulting in LPT case separation, and three reports of uncontained 3rd stage and 4th stage LPT blade failures with cowl penetration. We are issuing this AD to prevent an uncontained blade failure that could result in damage to the airplane.
2023-12-22: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model 4101 airplanes. This AD was prompted by in-service cracking of the passenger door edge member, seal carrier, and inner skin, adjacent to the roller guide bracket. This AD requires a one-time inspection of the external visible surface of the inner skin, door edge member, and seal carrier adjacent to the roller bracket attachment brackets; and the inner skin, door edge member, and seal carrier at the roller bracket attachment bore, and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
82-23-07: 82-23-07 RATIER-FIGEAC FH.146: Amendment 39-4490. Applies to Ratier-Figeac propeller Model FH.146. Compliance required within the next 100 hours of operation after the effective date of this AD unless already accomplished. To preclude the possibility of propeller blade failure, accomplish the following: (a) In accordance with Ratier-Figeac Service Bulletin No. 61-142 dated June 1, 1982, or an equivalent method approved by the Manager, Aircraft Certification Division, Federal Aviation Administration, New England Region: 1. Measure electrical resistance at end of disconnected wires of slip ring assembly. 2. Measure electrical resistance of insulation between wires and each propeller blade. (b) Remove propellers with measurements outside the limits of Bulletin No. 61-142 from service prior to further flight. This airworthiness directive becomes effective November 15, 1982.
55-23-02: 55-23-02 LOCKHEED: Applies to Models 1049C, D, E, and G, Serial Numbers 4163 Through 4166, 4520 Through 4581, 4583 Through 4605, 4608 Through 4615, and 4620. Compliance required as indicated. 1. Inspect the outer wing main beam web between wing Stations 510 and 668 left and right for cracks as soon as practical and repeat at 125-hour intervals until reinforcement in accordance with paragraph 2 is accomplished. If cracks are found repair immediately in accordance with Lockheed Repair Manual, Report 8882, and continue 125-hour inspections until reinforcement per paragraph 2 is accomplished. Inspection for fuel stains alone as an indication of a crack is not sufficient because of the presence of fuel sealant on the forward side of the web. 2. To be accomplished as soon as possible, but not later than next scheduled progressive overhaul time, and in no case later than December 1, 1956, whichever occurs first: Reinforce the main beam web, left and right, between wing Stations510 and 668. This shall be accomplished by the addition of three extruded 75S-T6 stiffeners, (LS2186 or LS6097) or equivalent between each of the original stiffeners. The LS347-3 stiffeners added previously in accordance with AD 54-24-02 on some of these aircraft may be retained. In these cases, one new (LS2186 or LS6097 or equivalent) stiffener must be added between each of these and the original stiffeners in this area. (Lockheed Service Bulletin No. 1049/SB-2753 also covers this subject.)
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.
2005-02-04: The FAA is adopting a new airworthiness directive (AD) for the McDonnell Douglas airplanes listed above. This AD requires identifying the part number of the cargo compartment smoke detectors and, if necessary, revising the Limitations section of the airplane flight manual to include procedures for testing the smoke detection system after the last engine is started. This AD also provides for the optional replacement of the subject smoke detectors with modified smoke detectors, which would terminate the operational limitation. This AD is prompted by a report indicating that the cargo smoke detectors can "lock up" during electrical power transfer from the auxiliary power unit to the engines. We are issuing this AD to identify and provide corrective action for a potentially inoperative smoke detector in the cargo compartment and ensure that the flightcrew is alerted in the event of a cargo compartment fire.
2000-12-12: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300, A300-600, and A310 series airplanes, that currently requires inspections to detect cracks in the lower spar axis of the nacelle pylon between ribs 9 and 10, and repair, if necessary. The existing AD also provides for optional modification of the pylon, which terminates the inspections for Model A300 and A310 series airplanes and increases the threshold and repetitive interval of the inspections for Model A300-600 series airplanes. This amendment reduces the inspection threshold and requires repetitive inspections following accomplishment of the optional modification for Model A310 series airplanes. 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 fatigue cracking, which could result in reduced structural integrity of the lowerspar of the pylon.
2023-14-01: The FAA is superseding Airworthiness Directive (AD) 2023-06- 13, which applied to all Bombardier, Inc., Model BD-700-2A12 airplanes. AD 2023-06-13 required revising the existing airplane flight manual (AFM) with new limitations to mitigate identified hazards due to interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band) as identified by Notices to Air Missions (NOTAMs). Since the FAA issued AD 2023-06-13, the FAA determined that additional limitations are needed due to the continued deployment of new 5G C-Band stations whose signals are expected to cover most of the contiguous United States at transmission frequencies between 3.7-3.98 GHz. This AD requires revising the limitations section of the existing AFM to incorporate limitations prohibiting dispatch under certain master minimum equipment list (MMEL) items. The FAA is issuing this AD to address the unsafe condition on these products.
62-06-01: 62-06-01 BRANTLY: Amdt. 410 Part 507 Federal Register March 16, 1962. Applies to All Model B-2 Helicopters Equipped With Seat Back Adjustment Wire P/N B2-334-32. Compliance required within the next 10 hours' time in service after the effective date of this AD. To prevent the sudden movement of the seat backs to the full aft adjustment position, the following must be accomplished: Remove the seat back adjustment wire P/N B2-334-32 from the left and right seat backs. This directive effective March 23, 1962.
2000-12-21: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes. The AD requires installation of a modification of the thrust reverser control and indication system and wiring on each engine; and repetitive functional tests of that installation to detect discrepancies, and repair, if necessary. This amendment is prompted by the results of a safety review, which revealed that in-flight deployment of a thrust reverser could result in a significant reduction in airplane controllability. The actions specified by this AD are intended to ensure the integrity of the fail-safe features of the thrust reverser system by preventing possible failure modes, which could result in inadvertent deployment of a thrust reverser during flight, and consequent reduced controllability of the airplane.
98-20-38 R1: The FAA adopts a new airworthiness directive (AD) to revise AD 98-20-38, which applies to all Beech 200 series airplanes. AD 98-20-38 requires you to revise the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for and procedures for exiting from severe icing conditions. Part of the applicability of AD 98-20-38 includes the Raytheon Models B200 and B200C airplanes. AD 96-09-13 already requires AFM revisions on this subject for these airplane models. Consequently, FAA is revising AD 98-20-38 to remove the Models B200 and B200C from the applicability and add clarification that AD 96-09-13 affects these airplanes. We are issuing this AD to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations.
80-02-06: 80-02-06 AVIONS MARCEL DASSAULT - BREGUET AVIATION: Amendment 39- 3656. Applies to Fan Jet Falcon Series D, E and F airplanes, Serial numbers 1 through 404, certificated in all categories. Compliance is required as indicated, unless already accomplished. To reduce the possibility of flexible line failure in the engine fire extinguisher system, within the next 100 hours time in service after the effective date of this AD, unless already accomplished, in each engine fire extinguisher system, modify the rigid tubing and install a new flexible line in accordance with paragraph 2, "Accomplishment Instructions," of Avions Marcel Dassault, Service Bulletin No. 632, dated July 18, 1979, or an equivalent approved by the Chief, Aircraft Certification Staff, Federal Aviation Administration, Europe, Africa, and Middle East Region. This amendment becomes effective January 24, 1980.
2023-12-24: The FAA is adopting a new airworthiness directive (AD) for all GE Aviation Czech s.r.o. (GEAC) (type certificate previously held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.) Model M601E-11AS, M601E-11S, H75-100, H80-100, and H85-100 engines. This AD is prompted by reports of multiple failures of the needle bearing installed in propeller governors having part numbers (P/Ns) P-W11-1 or P-W11-2, caused by self-generated debris from the needle bearing, which led to oil contamination. This AD requires replacement of the affected propeller governors with a redesigned propeller governor and prohibits installation of the affected propeller governors, 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.
97-04-15: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Pacific Scientific Company, HTL/Kin-Tech Division, fire extinguisher bottle cartridges (squibs), which may be installed on various transport category airplanes. This action requires a one-time inspection of the electrical receptacle of these fire extinguisher bottle cartridges and their mating connectors to detect the presence of aluminum foil in the area of the pins of the cartridges and the connectors, and removal of any aluminum foil that is present. This amendment is prompted by a report of failure of a fire extinguisher bottle cartridge to discharge as a result of the presence of aluminum foil in the cartridge, which caused electrical shorting of the pins. The actions specified in this AD are intended to prevent such shorting, which could result in failure of the fire extinguisher bottle to discharge when commanded.
2000-12-11: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300-600 series airplanes, that currently requires repetitive ultrasonic inspections to detect cracks in the bolt holes inboard and outboard of rib 9 on the bottom booms of the front and rear wing spars, and repair, if necessary. This amendment requires revising the compliance thresholds for the inspection and requires that the inspections be repeated at reduced intervals. 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 fatigue cracks in the bolt holes of the wing spars, which could result in reduced structural integrity of a wing spar.