Results
2014-03-04: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by a report of a translating door handle jamming during opening of an aft door. This AD requires replacing the handle shaft with a new single-piece machined handle shaft on the aft entry and service doors, and requires revising the maintenance program by incorporating a new airworthiness limitation task. We are issuing this AD to prevent a migrated pin from jamming a translating door handle, which could prevent opening of the door and impede an emergency evacuation.
70-16-07: 70-16-07 HUGHES: Amendment 39-1059. Applies to Model 369 Series helicopters, certificated in all categories, which incorporate P/N 369A1100 and P/N 369A1100-501 main rotor blade serial numbers listed in Hughes Service Information Notice No. HN-8, dated November 19, 1969, or later FAA approved revision and serial numbers listed in OH-6A Information Notice Numbers, 120, 120A, and 120B dated October 24, 1969; November 5, 1969; and December 19, 1969, respectively. Compliance required as indicated: To prevent failure of the main rotor blade P/N 369A1100 and P/N 369A1100-501 accomplish the following or an equivalent inspection procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region: Within 25 hours time in service after the effective date of this AD, unless already accomplished, determine the identification notation on the blade top and bottom doublers in accordance with the procedures in Part I a, b, and c of Hughes Service Information Notice No. HN-8, dated November 19, 1969, or later FAA approved revision. (a) For blades displaying "PR-12" ink stamps or blades lacking ink stamps below the part number on either of the doublers: (1) Inspect prior to further flight in accordance with Part I d of Hughes Service Information Notice No. HN-8, above. (2) If indications of cracks or doubler peeling or separation are found, remove the blade from service prior to further flight. (3) If indications of cracks or doubler peeling or separation are not found, repeat the inspection required under (1) above, at periods not to exceed 25 hours time in service from the last inspection until the blades are removed from service as specified in (4), below. (4) Remove from service prior to the accumulation of 100 hours time in service from the effective date of this AD. (b) Blades displaying ink stamp letters and numerals other than "PR-12" below the part number on both doublers may be returned to service with no further inspection, following refinishing and identification per Hughes Service Information Notice No. HN-8, dated November 19, 1969, or later FAA approved revision. This amendment becomes effective August 8, 1970.
91-09-12: 91-09-12 BOEING: Amendment 39-6976. Docket No. 90-NM-245-AD. \n\n\tApplicability: All Model 737-300, 737-400, and 737-500 series airplanes, certificated in any category. \n\n\tCompliance: Required within the next 36 months after the effective date of this AD, unless previously accomplished. \n\n\tTo preclude cross connection of the engine fire extinguishing wiring and plumbing during maintenance, accomplish the following: \n\n\tA.\tFor airplanes listed in Boeing Service Bulletin 737-26-1067, dated June 28, 1990: Modify the engine fire extinguishing system wiring and plumbing in accordance with the service bulletin. Accomplishment of this modification constitutes terminating action for the repetitive inspections and functional tests required by Airworthiness Directive 89-03-51, Amendment 39-6213, on Boeing Model 737-300, 737-400, and 737-500 airplanes following maintenance on the engine fire extinguishing wiring and plumbing. \n\n\tB.\tFor airplanes line position 1890 and subsequent on which PRR 34774 or an equivalent modification was incorporated during production: The repetitive inspections and functional tests required by Airworthiness Directive 89-03-51, Amendment 39-6213, are terminated. \n\n\tC.\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.\n \n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. \n\n\tThis amendment (39-6976, AD 91-09-12) becomes effective on May 28, 1991.
2014-04-11: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS350B, BA, B1, B2, B3, and D, and Model AS355E, F, F1, F2, and N helicopters with certain tail rotor (T/R) blades. This AD requires installing additional rivets to secure each T/R blade trailing edge tab (tab), and inspecting for evidence of debonding of the tab after the rivets are installed. This AD was prompted by reports of T/R blade tab debonding. The actions of this AD are intended to prevent loss of a T/R blade tab, which could result in excessive vibration and loss of control of the helicopter.
2014-05-02: We are superseding Airworthiness Directive (AD) 2002-10-11, which applied to certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2002-10-11 required repetitive inspections for cracking and corrosion of the aft pressure bulkhead, and corrective actions if necessary; and, for certain airplanes, enlargement of frame chord drain holes, and repetitive inspections of the frame chord drain path for debris, and corrective actions if necessary. This new AD specifies a drain path inspection for all airplanes. For certain airplanes, this new AD reduces the repetitive inspection interval; and adds repetitive inspections of the frame chord drain path for obstructions and debris, and corrective actions if necessary. This AD was prompted by three reports of severe corrosion in the area affected by AD 2002-10-11. We are issuing this AD to detect and correct corrosion or cracking of the aft pressure bulkhead, which could result in loss of the aft pressure bulkhead web and stiffeners, and consequent rapid decompression of the airplane.
2014-03-01: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB139 and AW139 helicopters with a certain wire strike protection system (WSPS) top cable cutter assembly installed. This AD requires reworking or replacing the top cable cutter assembly to increase clearance between the WSPS and the main rotor (M/R) blades and requires that the reworked or replaced part be marked at the end of the part number to reflect the field modification. This AD was prompted by a report of in-flight contact between the top cable-cutter assembly and two M/R blades. The actions of this AD are intended to prevent damage to the M/R blades and subsequent loss of helicopter control.
91-15-22: 91-15-22 MCDONNELL DOUGLAS: Amendment 39-7087. Docket No. 91-NM-18-AD. \n\n\tApplicability: McDonnell Douglas Model DC-10-40 series airplanes, as listed in McDonnell Douglas Service Bulletin 71-154, dated January 18, 1991, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent fuel line and engine fuel shutoff cable damage and possible fire caused by an uncontained engine failure, accomplish the following: \n\n\tA.\tWithin one year after the effective date of this AD, replace the fuel line shield on the left side of the number 2 engine bellmouth panel, and install an additional plate, as applicable, in accordance with the accomplishment instructions of McDonnell Douglas DC-10 Service Bulletin 71-154, dated January 18, 1991. \n\n\tB.\tAn 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, Los Angeles Aircraft Certification Office (AC0), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may concur or comment and then send it to the Manager, Los Angeles ACO. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tD.\tThe replacement and installation requirements shall be done in accordance with McDonnell Douglas DC-10 Service Bulletin 71-154, dated January 18, 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 McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: DC-10 Technical Publications, Technical Administrative Support C1-L5B. Copies may be inspected at the FAA, Transport Airplane Directorate, Renton, Washington; or at the LosAngeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\tThis amendment (39-7087, AD 91-15-22) becomes effective on September 9, 1991.
2014-03-03: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 310, 320, 340, 401, 402, 411, 414, and 421 airplanes. This AD was prompted by an investigation of recent and historical icing-related accidents and incidents for the products listed above. This AD requires either having the supplemental airplane flight manual/airplane flight manual supplement (SAFM/AFMS) inside the airplane and accessible to the pilot during the airplane's operation or installing a placard that prohibits flight into known icing conditions and installing a placard that increases published airspeed on approach at least 17 mph (15 knots) in case of an inadvertent encounter with icing. We are issuing this AD to correct the unsafe condition on these products.
2014-03-05: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD-700-1A10 airplanes. This AD was prompted by a report that the manufacturer has determined that some completion centers used the heater/brake monitoring unit (HBMU) logic circuit to control the line voltage of the drain mast heaters. Since the drain mast heaters are connected in parallel with the number 2 pitot static (PS) probe heater circuit, a number 2 PS probe heater failure may not be detected by the fault monitoring capabilities of the HBMU. This AD requires modification of the air data probes and sensors. We are issuing this AD to detect and correct an unannunciated failure of two PS probe heaters, which could affect controllability of the airplane in icing conditions.
2014-02-06: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB412 helicopters. This AD requires visually inspecting the main rotor swashplate outer ring (outer ring) for a crack and replacing that outer ring if a crack exists. This AD is prompted by two cases of cracks caused by fatigue on certain outer rings. These actions are intended to prevent the failure of the outer ring, which would lead to loss of main rotor blade pitch control and subsequently loss of helicopter control.
2018-07-16: We are adopting a new airworthiness directive (AD) for all Austro Engine GmbH model E4 and E4P diesel piston engines. This AD requires replacement of the waste gate controller and the control rod circlip. This AD was prompted by reports of broken or disconnected turbocharger waste gate control rods on some engines. We are issuing this AD to address the unsafe condition on these products.
2014-04-01: We are adopting a new airworthiness directive (AD) for all Slingsby Aviation Ltd. Model T67M260 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 cracked horizontal stabilizer attachment brackets. We are issuing this AD to require actions to address the unsafe condition on these products.
2014-03-21: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 727-200 and 727-200F series airplanes. This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This AD requires a one-time inspection for cracking of the pressure floor of both main wheel wells, and related investigative and corrective actions if necessary; and modifying the pressure floor of both main wheel wells. We are issuing this AD to prevent fatigue cracking in the pressure floor of the main wheel wells, which could lead to rapid loss of cabin pressurization.
2003-13-09: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 series airplanes. This action requires repetitive inspections for cracking of the upper skin of the outboard and center sections of the horizontal stabilizer and the rear spar structure, hinge fittings, terminal fittings, and splice plates; and repair if necessary. This action is necessary to find and fix such cracking, which could lead to reduced structural capability of the outboard and center sections of the horizontal stabilizer, and result in loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
91-10-07: 91-10-07 MCDONNELL DOUGLAS: Amendment 39-6991. Docket No. 91-NM-02-AD. \n\n\tApplicability: All McDonnell Douglas Model DC-10 series airplanes, manufacturer's fuselage numbers 1 through 379, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent inadvertent opening of a cargo door in flight, a condition which could result in loss of pressurization and reduced controllability of the aircraft, accomplish the following: \n\n\tA.\tWithin 16 months after performing the torque test required by AD 90-19-12, Amendment 39-6735, perform magnetic particle inspections on the H-11 cargo door latch spool fitting attach bolts or replace the H-11 cargo door latch spool fitting attach bolts with new bolts and associated hardware, in accordance with the Accomplishment Instructions for Phase 2 of McDonnell Douglas DC-10 Alert Service Bulletin A52-212, Revision 1, dated September 14, 1990 (hereafter referred to as the "Service Bulletin").1.\tIf a bolt does not pass the magnetic particle inspection, prior to further flight, replace it with a new bolt and seal in accordance with Figure 1 of the Service Bulletin. \n\n\t\t2.\tIf a bolt passes the magnetic particle inspection, prior to further flight, reinstall the bolt and seal in accordance with the Service Bulletin. \n\n\tB.\tWithin 16 months after accomplishment of the inspections required by paragraph A. of this AD, and at intervals not to exceed sixteen months, replace the H-11 cargo door latch spool fitting attach bolts with new bolts and associated hardware or perform either a magnetic particle or ultrasonic inspection on the H-11 cargo door latch spool fitting attach bolts in accordance with the Accomplishment Instructions for Phase 2 of the Service Bulletin. \n\n\t\t1.\tIf a bolt does not pass the magnetic particle/ultrasonic inspection, prior to further flight, replace it with a new bolt and seal in accordance with Figure 1 of the Service Bulletin. \n\n\t\t2.\tIf a bolt passes the magnetic particle/ultrasonic inspection, prior to further flight, reinstall the bolt and seal in accordance with the Service Bulletin. \n\n\tC.\tThe inspections required by paragraphs A. and B. of this AD are not required for Inconel bolts, part numbers RA21026-7, 77711-7, and 3D0031-7. \n\n\tD.\tWithin five years after the effective date of this AD, replace all H-11 cargo door latch spool fitting attach bolts with Inconel bolts, part numbers RA21026-7, 77711-7, and 3D0031-7 (grip lengths as applicable per location as specified in Figure 1 sheets 3 and 4 of the Service Bulletin) in accordance with the Accomplishment Instructions for Phase 3 of the Service Bulletin. Installation of Inconel bolts constitutes terminating action for the requirements of paragraphs A. and B. of this AD. \n\n\tE.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes unpressurized to a base for the accomplishment of the requirements of this AD. \n\n\tF.\tAn 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, Los Angeles Aircraft Certification Office (ACO), FAA Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, P.O. Box 1771, Long Beach, California 90846-0001, Attention: Business Unit Manager, Technical Publications, C1-HDR (54-60). These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. \n\n\tThis amendment (39-6991, AD 91-10-07) becomes effective on June 11, 1991.
2014-03-14: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 and -300 series airplanes, and Model A340-200, - 300, -500, and -600 series airplanes. This AD was prompted by results from fuel system reviews conducted by the airplane manufacturer. This AD requires removing bulb-type maintenance lights; installing a drain mast on certain airplanes; and installing muffs on connecting bleed elements on certain airplanes. We are issuing this AD to prevent ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2014-03-07: We are superseding Airworthiness Directive (AD) 2009-26-16 for certain The Boeing Company Model MD-11 and MD-11F airplanes. AD 2009- 26-16 required inspecting to determine if wires touch the upper surface of the center upper auxiliary fuel tank, and marking the location, as necessary; inspecting all wire bundles above the center upper auxiliary fuel tank for splices and damage; inspecting for damage to the fuel vapor barrier seal and upper surface of the center upper auxiliary fuel tank; and performing corrective actions, as necessary. AD 2009-26-16 also required installing nonmetallic barrier/shield sleeving, new clamps, new attaching hardware, and a new extruded channel. This new AD requires inspections of additional center upper auxiliary fuel tank locations and corrective actions as necessary. This AD was prompted by reports that identified additional locations where inspections and corrective actions of the center upper auxiliary fuel tank are needed. We are issuing thisAD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2014-03-09: We are adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR42 and Model ATR72 airplanes. This AD was prompted by reports of defective sealing between the nacelle lower fairing and the underwing box. This AD requires a one-time general visual inspection for damaged (worn, torn, or abraded) or missing seals between the nacelle lower fairing and the underwing box of both the left-hand and right-hand engine nacelles, and replacement of the seal and/or shims if necessary. We are issuing this AD to prevent the decrease of the fire extinguishing agent efficiency, which could delay fire extinction and allow fire propagation out of the nacelle fire protected area, resulting in damage to the airplane.
2014-03-17: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD requires repetitive inspections for fractured or incorrectly oriented fasteners on the inboard flap hinge-box forward fittings on both wings, and fastener replacement if necessary. This AD was prompted by two reports of fractured fastener heads found on the inboard flap hinge-box forward fitting. We are issuing this AD to detect and correct incorrectly oriented or fractured fasteners, which could result in detachment of the flap hinge-box and the flap surface, and consequent reduced controllability of the airplane.
2014-01-05: We are adopting a new airworthiness directive (AD) for certain the Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report of cracks in stringer splices at body station STA 360 and STA 908, between stringer (S) S-10L and S-10R; cracks in butt straps between S-5L and S-3L, and S-3R and S-5R; vertical chem-mill fuselage skin cracks at certain butt joints; and an instance of cracking that occurred in all those three structural elements on one airplane. This AD requires repetitive inspections for any cracking of stringer splices and butt straps, and related corrective and investigative actions if necessary. We are issuing this AD to detect and correct cracking in the three structural elements, which could result in the airplane not being able to sustain limit load requirements and possibly result in uncontrolled decompression.
2025-05-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A300 B4-600, B4-600R, and F4-600R series airplanes; and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a 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.
2014-02-09: We are adopting a new airworthiness directive (AD) for Eurocopter Model EC225LP and AS332L1 helicopters with emergency floatation gear. The AD requires, before the next overwater flight, inspecting the strap installation on the hinged rods of the emergency flotation gear on both rear cradles for correct installation. If a strap is installed under the hinged rod median plate rather than over it, reinstalling the strap is required. The AD is prompted by incorrect routing of the straps on the hinged rods of the emergency flotation gear rear cradles. The actions are intended to detect incorrect strap installation and prevent failure of the rods or straps upon deployment of the emergency flotation gear, incorrect float position, and subsequent capsizing of the helicopter.
2025-05-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus Canada Limited Partnership (ACLP) Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a design review of aircraft structural and stress reports that resulted in a revision of operational loads for some aircraft flight phases. This AD requires using a certain version of the aircraft structural repair manual (ASRP) and a review and disposition of repairs based on previous versions, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2013-24-04: We are superseding Airworthiness Directive (AD) 2003-19-11 for certain Learjet Inc. Model 60 airplanes. AD 2003-19-11 required determining if a certain fuel crossflow tube is installed; and follow- on/corrective actions, as applicable. This new AD requires retaining all actions in AD 2003-19-11, and it also requires determining if a certain fuel crossflow tube is installed, performing repetitive measurements of the fuel crossflow tube and surrounding valves and cables, and doing corrective actions if necessary. In addition, this new AD expands the applicability of AD 2003-19-11. This AD was prompted by a report that airplanes produced since 2003 might also be subject to the unsafe condition; and that the minimum allowable clearance is not established in the airplane maintenance information. We are issuing this AD to prevent chafing and consequent failure of the fuel crossflow tube due to inadequate clearance between the tube and the flight control cables, which could result inloss of fuel from one fuel tank during normal operating conditions or loss of fuel from both main fuel tanks during fuel cross-feeding operations.
67-28-04: 67-28-04 GENERAL ELECTRIC ENGINES: Amdt. 39-489 Part 39 Federal Register October 5, 1967. Applies to Type CJ805-3, 3A, 3B, 23, 23B and 23C Turbojet Engines. Compliance required as indicated. To prevent failure of the eighth stage compressor disc P/N 106R682P1 and 108R619P1 accomplish the following: (a) Remove from service eighth stage compressor discs with 12,000 or more cycles on the effective date of this AD within the next 50 cycles. (b) Remove from service eighth stage compressor discs with 11,000 or more cycles on the effective date of this AD within the next 250 cycles. (c) Remove from service eighth stage compressor discs with less than 11,000 cycles but more than 9500 cycles on the effective date of this AD within the next 600 cycles. (d) Remove from service eighth stage compressor discs with less than 9500 cycles on the effective date of this AD within the next 1250 cycles or at 8000 cycles, whichever occurs later. (e) Remove from serviceeighth stage compressor discs installed into engines on or after the effective date of this AD at or before 8000 cycles. (f) For the purpose of this AD, the number of cycles equals the number of flights that involve an engine operating sequence consisting of engine starting, take off operation, landing, and engine shutdown. The number of cycles may be determined by actual count or, subject to acceptance by the assigned FAA Maintenance Inspector, may be calculated by dividing each eighth stage compressor disc's time in service by the operator's fleet average time per flight (involving an engine operating sequence consisting of engine starting, take off operation, landing and engine shutdown). (General Electric Alert Service Bulletins A72-254 and A72-261 cover the same subject.) This amendment effective October 5, 1967.