Results
2019-12-11: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports indicating there is a possibility of excessive error in the signal generated by the angle of attack (AOA) transducer. This AD requires replacing certain AOA transducers. The FAA is issuing this AD to address the unsafe condition on these products.
2006-12-10: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-400 series airplanes. This AD requires inspecting the support bracket of the crew oxygen cylinder installation to determine the manufacturing date marked on the support, and performing corrective action if necessary. This AD results from a report indicating that certain oxygen cylinder supports may not have been properly heat-treated. We are issuing this AD to prevent failure of the oxygen cylinder support under the most critical flight load conditions, which could cause the oxygen cylinder to come loose and leak oxygen. Leakage of oxygen could result in oxygen being unavailable for the flightcrew or could result in a fire hazard in the vicinity of the leakage.
95-25-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Learjet Model 23, 24, 25, 35, and 36 airplanes. This action requires repetitive inspections to detect deterioration of both flapper valves of the tip tank in each wing of the airplane, and various follow-on actions. This AD action also requires replacing the flapper valves with new flapper valves, and repetitively performing certain other follow-on actions. This amendment is prompted by reports of imbalance of the fuel loads in the wings of the airplane due to failed or cracked flapper valves. The actions specified in this AD are intended to prevent significant reduction in the lateral control of the airplane due to imbalance of the fuel loads in the wings of the airplane.
2019-12-09: The FAA is adopting a new airworthiness directive (AD) for certain part-numbered Rockwell Collins, Inc. (Rockwell Collins) FDSA- 6500 flight display system applications installed on airplanes. This AD imposes operating limitations on the traffic collision avoidance system (TCAS) by revising the Limitations section of the airplane flight manual (AFM) or AFM supplement (AFMS) and installing a placard on each aircraft primary flight display. This AD was prompted by a conflict between the TCAS display indications and aural alerts that may occur during a resolution advisory (RA) scenario. The FAA is issuing this AD to require actions that address the unsafe condition on these products.
2019-12-16: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by a report that the capability of the diagonal struts fitted at a certain frame is below the expected design specifications. This AD requires replacing the original diagonal struts at a certain frame with new, improved parts, as specified in an European Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
74-24-02 R1: 74-24-02 SWEARINGEN: Amendment 39-2012 as amended by Amendment 39-2529. Applies to Models SA226-T, SA226-AT, and SA226-TC airplane. Compliance required as indicated. To detect cracks and provide for repair and reinforcement of the horizontal stabilizer rear spar at the outboard elevator hinge bracket attachment accomplish the following inspection and modifications: (a) After September 2, 1974, conduct the following inspection for the Model SA226-TC before the next flight unless already accomplished and for the Models SA226-T and SA226-AT within the next 10 hours time in service unless already accomplished. Inspect horizontal stabilizer rear spar in the vicinity of the left and right outboard elevator hinge bracket attachment for spanwise cracking above and below the hinge bracket in the bend radii of the spar flanges in accordance with paragraphs II.A.1. through 4. of Swearingen Service Bulletins A27-40-3067, revised October 9, 1974, for the Model SA226-T and A27-40-2064-4067, revised October 9, 1974, for the Models SA226-TC and SA226-AT or later FAA approved revisions. (b) If cracks are found, before further flight, repair horizontal stabilizer rear spar in accordance with: (1) Paragraph II.B. of Swearingen Service Bulletin A27-40-3067, revised October 9, 1974 or later FAA approved revision for the Model SA226-T, or (2) Paragraph II.B. of Swearingen Service Bulletin A27-40-2064-4067 revised October 9, 1974 or later FAA approved revision for the Models SA226-TC and SA226-AT. (c) If no cracks are found, accomplish the following: (1) Continue the inspections specified in (a) for the Model SA226-T at intervals not to exceed 200 hours time in service after the effective date of this AD. These periodic inspections may be discontinued after installation of the spar reinforcement specified in paragraph II.C. of Swearingen Service Bulletin A27-40-3067 revised October 9, 1974 or later FAA approved revision. (2) Within 50 hours timein service after the effective date of this AD, unless already accomplished for the Models SA226-TC and SA226-AT, install the spar reinforcement specified in paragraph II.C. of Swearingen Service Bulletin A27-40-2064-4067 revised October 9, 1974, or later FAA approved revisions. (3) After the rework specified in (c)(2), continue the inspections specified in (a) for the Models SA226-TC and SA226-AT at intervals not to exceed 500 hours' time in service from the date of rework or from the effective date of this AD if the rework was accomplished before the effective date. (d) Alternate methods of spar repair and reinforcement must be approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, FAA. Amendment 39-2012 superseded Amendment 39-1950, AD 74-18-14, and became effective November 18, 1974. This amendment 39-2529 becomes effective March 8, 1976.
2019-12-17: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC-8-102, -103, and -106 airplanes; Model DHC-8-200 series airplanes; and Model DHC-8-300 series airplanes. This AD was prompted by the reported loss of an elevator spring tab balance weight prior to takeoff. This AD requires inspecting the two balance weights and the two hinge arms on each elevator spring tab, and corrective actions if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
87-25-07: 87-25-07 BRITISH AEROSPACE: Amendment 39-5789. Applies to all Model H.S. 748 airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent severe stress and damage to the engine support structure, accomplish the following: A. Within the next 6 months after the effective date of this AD, or prior to accumulating 6,000 landings, whichever is later, and thereafter at intervals not to exceed 2,000 landings, perform a visual inspection of the engine subframe/wing attachment assemblies in accordance with paragraph 2A of British Aerospace Service Bulletin 54-29, dated October 1986. Any assembly found to exhibit excessive movement or wear must be repaired, prior to further flight, in a manner approved by the FAA. B. No later than the next scheduled engine removal after the effective date of this AD or prior to accumulating 6,000 landings, whichever is later, and thereafter at intervals not to exceed 6,000 landings, perform a visual inspection of the engine subframe/wing attachment assemblies while trying to induce movement in accordance with paragraph 2C of British Aerospace Service Bulletin 54-29, dated October 1986. Any components found to be unserviceable must be repaired, prior to further flight, in a manner approved by the FAA. C. Prior to the next scheduled engine removal after the effective date of this AD, or prior to accumulating 12,000 landings, whichever is later, and thereafter at intervals not to exceed 12,000 landings, perform an inspection with the taper bolt and taper split-bush removed from the engine subframe/wing attachment assemblies in accordance with paragraph 2D of British Aerospace Service Bulletin 54-29, dated October 1986. Any components found to be unserviceable must be repaired, prior to further flight, in a manner approved by the FAA. D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, maybe used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this proposal who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, Librarian for Service Bulletins, P.O. Box 17414 Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective January 19, 1988.
98-15-08: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146 and Model Avro 146-RJ series airplanes, that requires repetitive detailed visual inspections of the top wing skins for stress corrosion cracks, damage, or missing surface protective finish of the metallic surfaces; and repair, if necessary. This amendment is prompted by reports of stress corrosion cracks found on the top wing skin during routine inspection on three airplanes. The actions specified by this AD are intended to detect and correct such cracking, which could result in reduced structural integrity of the wing.
2007-01-01: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes. This AD requires determining the part number of the lift spoiler actuators/jacks (referred to after this as "lift spoiler jacks''). For affected lift spoiler jacks, this AD requires determining the date of manufacture of the lift spoiler jacks, repetitively inspecting the eye-end assembly of the lift spoiler jacks to detect discrepancies of the assembly or associated parts, and performing corrective actions if necessary. This AD results from a report that a lift spoiler deployed in flight due to corrosion at the thread where the eye-end assembly was screwed into the piston of the lift spoiler jack. We are issuing this AD to prevent detachment of the eye-end assembly of a lift spoiler jack, which could result in uncommanded deployment of a lift spoiler in flight, and consequent reduced controllability of the airplane.
64-24-03: 64-24-03 GENERAL DYNAMICS: Amdt. 824 Part 507 Federal Register October 23, 1964. Applies to Model 30 Series Aircraft Which Have Been Altered in accordance with Either American Airlines Fleet Campaign Directive No. 194K or General Dynamics/Convair (990) Service Bulletin No. 27-66 Dated December 6, 1963. Compliance required within 300 hours' time in service following the effective date of this AD unless already accomplished. American Airlines Fleet Campaign Directive No. 194K and General Dynamics/Convair (990) Service Bulletin No. 27-66 describe emergency electric stabilizer trim system circuit change which interlock the "up relay" and "down relay" coils. Under certain circumstances the emergency electrical stabilizer trim systems which incorporate these circuit changes could permit a runaway stabilizer condition to exist. To correct this condition, modify the aircraft emergency electric stabilizer trim system circuits in accordance with either paragraph (a) or (b). The circuit changes described in General Dynamics/Convair Service Bulletin No. 27-66, which interlock the coils of the "up relay" and "down relay", may be used when the changes described in paragraph (b) are accomplished. (a) Restore the emergency electric stabilizer trim system circuits to the original Convair type certification design; or (b) Replace the single pole, double throw, emergency electric stabilizer control "nose up"-"nose down" switch (S-246), with a double pole, double throw, momentary on, center position off, momentary on switch. Connect the added poles of the switch so that the power control relay (K-276) is energized with the "up relay" (K-124) and with the "down relay" (K-123) but is not energized when the switch is in the "off" position. This modification shall be accomplished in accordance with General Dynamics/Convair (990) Service Bulletin No. 27-66A dated April 22, 1964, or by an equivalent approved by the Aircraft Engineering Division, FAA Western Region.This directive effective October 23, 1964.
2007-01-06: This amendment supersedes an existing airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (BHTC) model helicopters. The existing AD currently requires certain inspections and checks of the tail rotor blade (blade) for a deformation, a crack, and a bent or deformed tail rotor weight (weight). Also, that AD requires, before further flight, replacing each blade with an airworthy blade if a deformation, a crack, or a bent or deformed weight is found. This action contains the same actions as the existing AD and also adds to the applicability certain serial-numbered blades inadvertently omitted from the current AD. This action also requires replacing each affected blade, which is a terminating action. This amendment is prompted by three reports of skin cracks originating near the blade trailing edge balance weight. The actions specified by this AD are intended to prevent blade failure and subsequent loss of control of the helicopter.
2006-25-12: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce Corporation (RRC) 501-D series turboprop engines. That AD requires removal from service of certain turbine rotor components at reduced life limits. This AD requires the same actions but adds two new life limits. This AD results from RRC reevaluating and revising component life limits for 501-D22 series turboprop engines. We are issuing this AD to prevent uncontained turbine rotor failure resulting in an in-flight engine shutdown and possible damage to the airplane.
81-04-10: 81-04-10 KAWASAKI HEAVY INDUSTRIES, LTD.: Amendment 39-4045. Applies to Models KV107-II and KV107-IIA helicopters, certificated in all categories, with pilot or copilot cyclic stick boots, P/N 107S2226-9, installed. Compliance required as indicated, unless already accomplished. To prevent possible restriction of cyclic stick travel, which could result in an unsafe flight condition, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD, loosen the velcro tape and camloc fasteners securing the pilot and copilot cyclic stick boots, P/N 107S2226-9, and remove the boots. (b) Remove the two rivets which attach the forward spring, P/N 107S2226-12, to the forward end of the boot base and discard the forward spring. (c) Install washers and new rivets to plug the resulting two empty holes in the boot base. (d) Reinstall the pilot and copilot stick boots. (e) In accordance with FAR Sections 21.197 and 21.199, the helicopter may be flown to a base where the modification can be accomplished. This amendment becomes effective February 26, 1981.
2019-12-08: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports that certain aft fuselage fittings are susceptible to cracking because they were not manufactured correctly. This AD requires replacement of those fittings with correctly manufactured parts, an eddy current inspection of certain fastener holes for cracking, and corrective actions if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2006-26-09: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-200, -300, -400, and -500 series airplanes. This AD requires a one-time inspection of the frames between station 360 and station 907 to determine if a subject support bracket for the air conditioning outlet extrusion is installed, and related repetitive investigative actions and repair if necessary. This AD also provides an optional preventive modification that ends the repetitive investigative actions. This AD also requires a one-time post-modification/repair inspection for cracking of each repaired/modified frame. This AD results from numerous reports indicating that frame cracks have been found at the attachment holes for support brackets for the air conditioning outlet extrusion. We are issuing this AD to detect and correct such cracking, which, if the cracking were to continue to grow, could result in a severed frame. A severed frame, combined with existing multi-site damage at the stringer 10 lap splice, could result in rapid decompression of the airplane.
2006-26-11: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model ERJ 170 and ERJ 190 airplanes. This AD requires repetitive inspections to detect damaged smoke seals in the aft avionics compartment, repair/replacement if any damage is found, and reinforcement if no damage is found. This AD also requires eventual replacement of all smoke seals in the aft avionics compartment with new, improved seals having new part numbers, which terminates the repetitive inspections. This AD results from a report of damaged smoke seals in the aft avionics compartment of the affected airplanes. We are issuing this AD to prevent smoke from penetrating into the passenger cabin during a fire in the avionics compartment.
2006-25-13: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation (RRC) AE 2100D3 turboprop engines. This AD requires removing certain part number (P/N) compressor cone shaft assemblies at a new reduced cyclic life limit of 5,000 engine cycles. This AD results from low-cycle-fatigue testing and analysis of certain P/N compressor cone shaft assemblies, by RRC. We are issuing this AD to prevent uncontained failure of the compressor cone shaft assembly, leading to engine shutdown and damage to the airplane.
2001-02-10: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Models 60, A60, and B60 airplanes. This AD requires you to inspect for the existence of any lower forward wing bolts with the Mercury Aerospace trademark, and replace any such bolt with an FAA-approved bolt without this trademark. This AD is the result of a report that wing bolts supplied by Mercury Aerospace may not meet the required Rockwell hardness specifications. The actions specified by this AD are intended to detect and correct wing bolts that do not meet strength requirements. Continued airplane operation with such bolts could result in fatigue failure of the bolts with consequent separation of the wing from the airplane.
2019-12-03: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model CL-600-2C10 (Regional Jet Series 700, 701 & 702), CL-600-2D15 (Regional Jet Series 705), and CL-600-2D24 (Regional Jet Series 900) airplanes. This AD was prompted by a determination that new and more restrictive airworthiness limitations are necessary for operational checks of the landing gear alternate extension system (AES). This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new and more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
97-16-06: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300-600 series airplanes, that requires an inspection to detect cracks of certain attachment holes; and installation of a new fastener and follow-on inspections or repair, if necessary. This amendment is prompted by reports of fatigue cracking found on the forward fitting of frame 47 at the level of the last fastener of the external angle fitting. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the airframe.
88-24-01: 88-24-01 BOEING: Amendment 39-6057. Applies to all Model 727 series airplanes, listed in Boeing Service Bulletin 727-32-306, Revision 1, dated February 25, 1988, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent failure of the main landing gear support link shaft, which could result in damage to the wing and/or hydraulic system, accomplish the following: \n\n\tA.\tWithin the next 1,000 hours time-in-service since the last inspection in accordance with AD 68-17-01, and thereafter at intervals not to exceed 1,000 hours time-in-service until the requirements of paragraph B., below, are accomplished, perform an ultrasonic inspection for cracks of the P/N 65- 19657-4, -5, -8, or -13 main landing gear (MLG) support link in accordance with paragraph II, Accomplishment Instructions, Part I - Inspection Data, B. Ultrasonic Inspection Data of Boeing Service Bulletin 32-90, Revision 1, dated May 29, 1968, or Boeing Service Bulletin 32-189, dated May 25, 1971. If any cracks are detected, prior to further flight, perform visual and magnetic particle inspections of the MLG support link shaft as described in paragraph B., below, and replace or modify the MLG support link and bushing accordingly. \n\n\tB.\tExcept for airplanes identified in paragraph C., below, within the next 6,000 hours time- in-service or 2 years after the effective date of this AD, whichever occurs sooner, perform a visual inspection of the MLG support link shaft for corrosion, and a magnetic particle inspection for cracks. If any corrosion, and/or cracks are detected in the MLG support link shaft, prior to further flight, repair or replace in accordance with Section 32-01-02 of the Boeing 727 Landing Gear Overhaul Manual. In addition, replace or modify the MLG support link, P/N 65-19657-4, -5, -8, -11, -13, -15, -16, or -18, and associated bushing, as necessary, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 727-32-306, Revision 1, dated February 25, 1988. \n\n\tC.\tIn lieu of the requirements of paragraph B., above, for airplanes line numbers 1793 and subsequent, and airplanes that have been modified in accordance with Boeing Service Bulletin 727-32- 306, dated March 26, 1982, and which have had the MLG support links lubricated at intervals not to exceed 500 hours time-in-service: Within the next 6,000 hours time-in-service or 2 years after the effective date of this AD, whichever occurs sooner, or 5 years since the modification, whichever occurs later, perform a visual inspection for corrosion and a magnetic particle inspection for cracks of the MLG support link shaft. If any corrosion and/or cracks are detected in the MLG support link shaft, prior to further flight, repair or replace in accordance with Section 32-01-02 of the Boeing Model 727 Landing Gear Overhaul Manual. In addition, replace or modify the MLG support link and associated bushing, as necessary, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 727-32-306, Revision 1, dated February 25, 1988. \n\n\tD.\tAn alternate means 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, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tE.\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 Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment supersedes AD 68-17-01, Amendment 39-635, as amended by Amendment 39-1228. \n\tThis amendment, 39-6057, becomes effective December 16, 1988.
85-24-01: 85-24-01 MCDONNELL DOUGLAS: Amendment 39-5169. Applies to McDonnell Douglas Model DC-8-70 series airplanes, equipped with an auxiliary power unit in accordance with STC SA1387NM. \n\n\tCompliance is required as indicated. \n\n\tTo preclude potential APU exhaust door failures and resulting wiring and structural damage, accomplish the following, unless already accomplished: \n\n\tA.\tWithin six (6) months after the effective date of this AD, complete the modifications defined in McDonnell Douglas DC-8-70 Service Bulletin 49-2, dated May 16, 1985, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. The modifications involve removal of the APU; modification of the APU module and control boxes; revision of the APU control system sensing and firex control wiring; replacement of three generator phase circuit breakers; and the APU control and fuel supply circuit breakers; inspection of the wire routing; and reinstallation ofthe APU. \n\n\tB.\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\tC.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis amendment becomes effective December 19, 1985.
2006-25-14: We are adopting a new airworthiness directive (AD) for the products listed above. 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 the possible failure of the attachment of the propeller blades. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2019-12-14: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 C-2 helicopters. This AD requires establishing or reducing the life limit of various parts. This AD was prompted by recalculations. The actions of this AD are intended to address an unsafe condition on these products.