Results
98-08-26: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires installing aluminum bonding bushings over certain screws in certain fuel tank underwing access panels. Several reports from the field revealing fuel tank access panels insufficiently electrically bonded to the airframe prompted this action. The actions specified by this AD are intended to prevent electrical arcing in the fuel tanks and detonation of the fuel-air mixture, which can be created by poor electrical bonding of fuel tank underwing access panels, and could result in a fire on the airplane.
98-08-27: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA - Groupe AEROSPATIALE (Socata) Model TBM 700 airplanes. This AD requires modifying the airplane's left-hand (LH) front side lower panel. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent interference between the side trim of the LH front side lower panel and the roll control compass on the LH wheel assembly, which could result in loss of directional control of the airplane.
56-09-02: 56-09-02 MARTIN: Applies to All Models 202, 202A, and 404 Aircraft. Compliance required by September 1, 1956. In order to eliminate shearing of rivets securing the rudder torque tube flange, P/N 2021U42196, to the rudder torque tube, P/N 2021D19331, caused by gust buffeting with gust locks not engaged and resulting in loss of adequate and/or positive rudder control, it is necessary to replace the 3/16-inch rivets with 1/4-inch 24ST heat treated rivets. (Martin Service Instruction Letters No. 202/202A-36 and No. 404-69 cover this same subject.)
2018-03-15: We are adopting a new airworthiness directive (AD) for Pacific Aerospace Limited Model 750XL airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as abrasion damage of components or wiring behind the instrument panel. We are issuing this AD to require actions to address the unsafe condition on these products.
98-08-23: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 and 767 series airplanes, that currently requires revising the FAA- approved Airplane Flight Manual (AFM) to prohibit the use of certain fuels; and either replacing the existing placard on the door of the fueling control panel with a new placard, or replacing all dribble flow fuel nozzles (DFFN's) with standard fuel nozzles, which terminates the requirements for a placard and AFM revision. This amendment continues these requirements and adds additional airplanes to the applicability. This amendment is prompted by a report of an engine flameout due to the use of JP-4 or Jet B fuel during certification testing on an engine with DFFN's installed. The actions specified in this AD are intended to prevent such engine flameouts and consequent engine shutdown.
98-08-18: This amendment supersedes Airworthiness Directive (AD) 79-01-04, which currently requires repetitively inspecting the elevator bungee spring for cracks or surface deformities on certain Piper Aircraft Corporation (known currently as The New Piper Aircraft, Inc.) Model PA-31-350 airplanes, and replacing any elevator bungee spring with cracks or surface deformities. This AD retains the repetitive inspection and replacement requirements from AD 79-01-04 on The New Piper Aircraft, Inc. (Piper) Model PA-31-350 airplanes until an elevator bungee spring of improved design is installed, and requires these repetitive inspection and replacement requirements on certain other Piper PA-31 and PA-31P series airplanes not affected by AD 79-01-04. This AD also requires replacing the elevator bungee link with a link of improved design on all affected airplanes except for the Piper Model PA-31P airplanes, and repetitively replacing the elevator bungee spring on all affected airplanes. ThisAD results from reports of cracked elevator bungee springs on airplanes incorporating the older design elevator bungee spring that are not affected by AD 79-01-04, and by reports of cracked elevator bungee springs on airplanes that have improved design elevator bungee springs installed. The actions specified by this AD are intended to prevent failure of the elevator bungee spring, which could result in a reduction in elevator control and consequent loss of control of the airplane.
2025-09-07: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-243, -243F, -841, and -941 airplanes. This AD was prompted by reports of loss of data synchronization between radio management panels (RMPs) and the audio management unit (AMU). This AD requires revising the existing airplane flight manual (AFM) by providing instructions to address dual loss of RMP data synchronization, and the existing minimum equipment list (MEL) by removing relief for an inoperative RMP 3. The FAA is issuing this AD to address the unsafe condition on these products.
98-08-20: This amendment adopts a new airworthiness directive (AD) that applies to certain AlliedSignal Aerospace Bendix/King Model KSA 470 autopilot servo actuators, part numbers 065-0076-10 through 065-0076-15, that are installed on aircraft. This AD requires replacing the autopilot servo actuator with a modified actuator. This is the result of two reports of the affected autopilot servo actuators containing loose roll pins within the servo housing. Loose roll pins could fall out, become lodged in the output shaft clutch mechanism, and prevent this mechanism from disengaging. The actions specified by this AD are intended to prevent such an occurrence, which could result in increased effort by the pilot to control the aircraft and possible loss of control of the affected flight control axis.
2003-04-24: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model 717-200 airplanes. This action requires a one-time inspection for cracking of the support fitting assemblies and stop pads of the main spoiler actuators, and follow-on actions. This action is necessary to find and fix cracking of the support fitting assemblies of the main spoiler actuator, which could result in damage of adjacent structure such as the rear spar or upper skin panel, and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
2020-21-18: The FAA is superseding Airworthiness Directive (AD) 2019-14- 09, which applied to all Airbus SAS Model A330-200 Freighter series airplanes. AD 2019-14-09 required repetitive detailed inspections, including functional testing, of the oxygen crew and courier distribution system (OCCDS) and replacement of affected part(s) if necessary. This AD retains the requirements of AD 2019-14-09 and requires replacement of all affected parts with improved serviceable parts, which is terminating action for the repetitive inspections, as specified in a European Union Aviation Safety Agency (EASA) AD, which will be incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
66-29-03: 66-29-03 SIAI-MARCHETTI: Amdt. 39-313 Part 39 Federal Register November 23, 1966. Applies to Model S.205 Airplanes, Serial Numbers 101 through 222, 224, 228, 229, 231 through 233. Compliance required as indicated. To detect cracks on the rear spar web at areas adjacent to the aileron outboard hinge bracket bolts, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished within the last 90 hours' time in service, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, visually inspect the rear spar web for cracks in accordance with Siai Service Bulletin No. 205B4, dated September 14, 1966. If cracks are detected during this inspection, comply with (b) of this AD before further flight. (b) Modify the rear spar by incorporating a reinforcement as set forth in paragraph (b) of Siai Service Bulletin No. 205B4, dated September 14, 1966, or an FAA-approved equivalent. (c) The repetitive inspections required by (a) of this AD may be discontinued after the rear spar is reinforced in accordance with (b) of this AD. This directive effective November 23, 1966.
2003-04-20: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Raytheon Model DH.125, HS.125, BH.125, and BAe.125 (U-125 and C-29A) series airplanes; and Model Hawker 800, Hawker 800 (including variant U-125A), Hawker 800XP, and Hawker 1000 airplanes; that currently requires an inspection for cracking or corrosion of the cylinder head lugs of the main landing gear (MLG) actuator and follow-on/corrective actions. This amendment expands the applicability of the existing AD to add an airplane model and further clarify the applicability and, for certain airplanes, to clarify the compliance time of the inspection requirements. This action is necessary to prevent separation of the cylinder head lugs, which could prevent the MLG from extending and result in a partial gear-up landing. This action is intended to address the identified unsafe condition.
2018-03-13: We are adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CT7-5A2, CT7-5A3, CT7-7A, CT7-7A1, CT7- 9B, CT7-9B1, CT7-9B2, CT7-9C and CT7-9C3 model turboprop engines. This AD requires initial and repetitive visual inspection and fluorescent- penetrant inspection (FPI) of the main propeller shaft. This AD was prompted by the failure of a main propeller shaft. We are issuing this AD to address the unsafe condition on these products.
97-01-11: 97-01-11 AIRBUS INDUSTRIE: Amendment 39-9882. Docket 92-NM-225-AD. Supersedes AD 96-20-02, amendment 39-9768. Applicability: Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 series airplanes, on which Modification 2626 has not been installed; certificated in any category. Compliance: Required as indicated, unless accomplished previously. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (f) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent fatigue cracking, which could result in reduced structural integrity of the airplane, accomplish the following: (a) For Model A300 B2-1C, B2K-3C, B2-203, B4-2C, and B4-103 series airplanes: Perform a detailed visual inspection to detect cracking of the fuselage, frame 47 at hole "I", in accordance with Airbus All Operator Telex (AOT) 53-02, dated November 2, 1992, at the times specified in paragraphs (a)(1) or (a)(2), as applicable. (1) For Model A300 B2-1C, B2K-3C, and B2-203 series airplanes: Perform the inspection prior to the accumulation of 15,000 total landings, or within 50 landings after November 4, 1996 (the effective date of AD 96-20-02, amendment 39-9768), whichever occurs later. (2) For Model A300 B4-2C and B4-103 series airplanes: Perform the inspection prior tothe accumulation of 18,700 total landings, or within 50 landings after November 4, 1996, whichever occurs later. (b) For Model A300 B4-203 series airplanes: Prior to the accumulation of 14,100 total landings, or within 50 landings after the effective date of this AD, whichever occurs later, perform a detailed visual inspection to detect cracking of the fuselage, frame 47 at hole "I", in accordance with Airbus All Operator Telex (AOT) 53-02, dated November 2, 1992. (c) If no crack is detected during the inspection required by paragraph (a) or (b) of this AD, repeat the detailed visual inspection at intervals not to exceed 200 landings. (d) If a crack is detected during any inspection required by paragraph (a), (b), or (c) of this AD, prior to further flight, repair in accordance with either paragraph (d)(1), (d)(2), or (d)(3) of this AD: (1) Repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate; or (2) Repair in accordance with crack repair procedures specified in Airbus A300 Service Bulletin 53-265, Revision 2, dated March 10, 1992; or (3) Repair in accordance with crack repair procedures specified in Airbus Service Bulletin A300-53-299, dated December 14, 1993. (e) Conducting a repetitive Rototest inspection of hole "I" in accordance with Airbus A300 Service Bulletin 53-265, Revision 2, dated March 10, 1992, or Airbus Service Bulletin A300-53-299, dated December 14, 1993, constitutes terminating action for the detailed visual inspections required by this AD. If any crack is found during a Rototest inspection, prior to further flight, repair it in accordance with that service bulletin. (f) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (g) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (h) The visual inspection shall be done in accordance with Airbus All Operator Telex (AOT) 53-02, dated November 2, 1992. This incorporation by reference was approved previously by the Director of the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51, as of November 4, 1996 (61 FR 50988, September 30, 1996). Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (i) This amendment becomes effective on February 10, 1997.
2011-25-05: We are adopting a new airworthiness directive (AD) for The Boeing Company Model 767 airplanes. This AD requires installing new panel assemblies in the main equipment center or on the forward cargo compartment sidewall and removing certain relays from some panels in the main equipment center. This AD also requires revising the maintenance program to incorporate Airworthiness Limitations (AWLs) No. 28-AWL-27 and No. 28-AWL-28. This AD also includes an alternative location for the installation of the new panel assemblies for airplanes that have the optional water system drain plumbing and changing the interconnecting wiring between the P141 panel and the P36 and P37 panels. For airplanes with a deactivated center fuel tank, this AD also requires an alternative functional test for the left and right override/jettison pumps. We are issuing this AD to prevent possible sources of ignition in a fuel tank caused by electrical fault or uncommanded dry operation of the main tank boost pumps and center auxiliary tank override and jettison pumps. This AD was prompted by fuel system reviews conducted by the manufacturer. An ignition source in the fuel tank could result in a fire or an explosion and consequent loss of the airplane.
2003-04-18: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 airplanes, that requires measuring the length of the wear indicator on the brake stack of the main landing gear (MLG) brake assembly to determine the degree of wear, and follow-on actions. This action also requires eventual replacement of the existing MLG brake assembly with a new, improved or modified assembly, which constitutes terminating action for any repetitive actions being performed per this AD. The actions specified by this AD are intended to prevent failure of the MLG brakes and consequent loss of braking capability, which could result in the airplane overrunning the runway during take-off or landing. This action is intended to address the identified unsafe condition.
2018-03-21: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-202, -203, -223, and -243 airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by a design review of the airplane configuration incorporating certain fire extinguisher bottles and an optional galley cooling rack installation, which revealed that the air cooling rack is installed too close to the supply hose of a high rate fire extinguishing bottle. We are issuing this AD to address the unsafe condition on these products.
76-03-04: 76-03-04 RAVEN INDUSTRIES, INC.: Amendment 39-2508. Applies to Raven Model RX-6 hot air balloons certificated in all categories. Compliance required before further flight. To prevent cracking and breaking of the polyethylene gondola liner, accomplish the following: Install a placard on the instrument panel in clear view of the pilot, stating, "Operation limited to ground surface temperatures of 40 degrees F and above". The hot air balloon may be operated only when ground surface temperature is at or above 40 degrees F until modifications to reinforce the gondola liner, to be made available by Raven Industries, Inc., are installed. This amendment becomes effective February 13, 1976.
83-13-09 R1: 83-13-09 R1 McDONNELL DOUGLAS: Amendment 39-4679 as amended by Amendment 39-4744. Applies to certain McDonnell Douglas DC-10-15 and DC-10-30 airplanes, and all KC-10A airplanes, certified in all categories, which are listed in McDonnell Douglas DC-10 Service Bulletin 23-46, dated May 12, 1983, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, Compliance required within 30 days from the effective date of this AD unless already accomplished. \n\n\tTo prevent loss of communication transmission capability from airplane to ground, accomplish the following: \n\n\tA.\tModify the service and flight interphone audio system wiring in accordance with the Accomplishment Instructions in McDonnell Douglas DC-10 Service Bulletin No. 23-46, dated May 12, 1983, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tAlternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\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 modifications required by this AD. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tAmendment 39-4679 became effective July 18, 1983. \n\n\tThis Amendment 39-4744 becomes effective October 27, 1983.
2003-04-12: This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (Bell) model helicopters that requires modifying the auxiliary fin assemblies and revising the Limitations section of the Rotorcraft Flight Manual (RFM) to reduce the never-exceed speed (Vne) for a tail rotor pedal stop failure. This amendment is prompted by several incidents of main rotor blades contacting the top of the fin that have resulted in an upper tuning weight (weight) becoming loose. The actions specified by this AD are intended to prevent a main rotor blade from striking an auxiliary fin, loss of a tuning weight, impact with a tail or main rotor blade, and subsequent loss of control of the helicopter.
2003-04-22: This amendment adopts a new airworthiness directive (AD), that is applicable to Hartzell Propeller Inc. model HD-E6C-3B/E13890K propellers with certain serial numbers of model D-1199-2 propeller control units (PCU's) installed. This amendment requires initial and repetitive inspections for below-limit propeller flight idle blade angles, and, as a terminating action, removal of the affected PCU's from service and performance of a complete Major Periodic Inspection (overhaul) when the applicable time-since-new or time-since-overhaul limit is reached, or when any flight idle blade angle is below limits. This amendment is prompted by a review by Hartzell Propeller Inc. of the model D-1199-2 PCU overhaul procedures, that revealed several dimensional checks and a nondestructive evaluation were not performed on certain serial number PCU's during a Major Periodic Inspection (overhaul). The overhaul procedures are required to comply with the Airworthiness Limitation PCU Major PeriodicInspection (overhaul) directive. The actions specified by this AD are intended to prevent below-limit flight idle propeller blade angles that, if not corrected, could result in degraded aircraft performance and control.
98-06-11: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-100 series airplanes, that requires a one-time visual inspection to determine the presence of block seals on the upper portions of the cabin/baggage compartment bulkheads, and installation of a new or serviceable block seal for any missing block seal. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent smoke contamination of the passenger and crew cabins, in the event of fire or smoke in the baggage compartment, due to a direct smoke path between the baggage compartment and the cabins.
55-17-01: 55-17-01 LOCKHEED: Applies to All Models 49, 149, 649, 749, and 1049 Airplanes. Compliance required by December 1, 1955, unless already accomplished. A recent failure of wing flap torque tube assembly, P/N 326605-3, on a Model 1049C is attributed to a defective bolt, P/N AN 23-19. Initial overtorque of the bolt is suspected as the cause of failure of the bolt. It is therefore necessary that all Constellation and Super Constellation airplanes be inspected to ascertain proper installation of bolts, including bolt torque, on all wing flap torque tubes. Proper torque value for the AN 23-19 bolts is 10 to 20 inch-pounds. Nut torque must be checked with a torque wrench and all overtorqued bolts replaced. If necessary, the next size longer bolt (P/N AN23-20) may be used to facilitate installation within proper torque tolerances. Washers may be used as required, but not to exceed two under the head or two under the nut, to prevent the nut from bottoming on the shank.
98-07-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200 and -300 series airplanes, that requires a one-time inspection for worn or broken wire bundles in the ceiling above the main passenger door and repair, if necessary; and relocation of the wire bundles to prevent chafing. This amendment is prompted by a report indicating that the opening of the main passenger door caused the door liner and a ceiling panel to chafe and ultimately break wires installed in this area. The actions specified by this AD are intended to prevent these wires from becoming worn or breaking, which could lead to the failure of several systems, such as the fuel shutoff valves, and may contribute to the inability of the flight crew to stop the flow of fuel to the engines in the event of an engine fire.
2018-03-12: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318 series airplanes; Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321- 111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by reports of fatigue damage in the structure for the door stop fittings on certain fuselage frames (FR). This AD requires repetitive rototest inspections for cracking of the fastener holes in certain door stop fittings, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.