Results
2004-07-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes, and C-9 (military) airplanes, that currently requires repetitive ultrasonic or magnetic particle inspections to detect cracking of the engine pylon aft upper spar straps (caps); and if necessary, replacement of the strap with a new strap, or modification of the engine pylon rear spar straps, which constitutes terminating action for the repetitive inspections. This amendment requires new, improved repetitive ultrasonic inspections, and corrective actions if necessary. This amendment also requires, among other items, a terminating action for the repetitive inspection requirements. The actions specified by this AD are intended to detect and correct fatigue cracking, which could result in major damage to the adjacent structure of the pylon aft upper spar cap, and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
2011-13-02: We are adopting a new airworthiness directive (AD) for the products listed above. 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: During Landing Gear retraction/extension ground checks performed on the P2006T, a loose Seeger ring was found on the nose landing gear hydraulic actuator cap. The manufacturer has identified the root cause of this discrepancy in a design deficiency of the hydraulic actuator caps. This condition, if not corrected, could determine uncommanded and improper extension of the nose or main landing gear. We are issuing this AD to require actions to correct the unsafe condition on these products.
2021-13-08: The FAA is adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A. Arriel 2C and Arriel 2S1 model turboshaft engines. This AD was prompted by reports of error messages on the full authority digital engine control (FADEC) B digital engine control unit (DECU), caused by blistering of the varnish on the DECU circuit board. This AD requires the replacement of certain FADEC B DECUs. The FAA is issuing this AD to address the unsafe condition on these products.
98-04-24: This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company Models E55, E55A, 58, 58A, 58P, 58PA, 58TC, 58TCA airplanes, and 60, 65-B80, 65-B90, 90, F90, 100, 300, and B300 series airplanes. This action requires revising 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. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icingconditions by providing more clearly defined procedures and limitations associated with such conditions
98-04-22: This amendment adopts a new airworthiness directive (AD) that applies to SOCATA - Groupe AEROSPATIALE, Model TBM 700 airplanes. This action requires revising 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. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
98-04-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft Incorporated (Fairchild) Models SA226-TC, SA226-T, SA226-T(B), and SA226-AT airplanes. This action requires inspecting the center flap hinge and wing trailing edge ribs at the flap actuator attach brackets for cracks and if no cracks are found, installing a doubler on the rib, or replacing a cracked rib with a new rib assembly that is reinforced with a doubler. This action is the result of high local stress concentration, which led to fatigue cracking of the wing trailing edge ribs. The actions specified by this AD are intended to prevent asymmetrical flap deflection, which could force the airplane into an uncommanded roll with possible loss of control of the airplane.
93-01-16: 93-01-16 BEECH AIRCRAFT CORPORATION: Amendment 39-8470. Docket No. 92-CE-39-AD. Applicability: Model 1900C airplanes, serial numbers UC-1 through UC-174 and UD-1 through UD-6 (also referred to as Model C-12J), certificated in any category. Compliance: Required within the next 200 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent an airplane fire caused by fuel entering the electrically-heated stall warning vane housing, accomplish the following: (a) Inspect the pneumatic deice lines and the deice distributor valve for fuel leakage in accordance with Parts I and II of the ACCOMPLISHMENT INSTRUCTIONS section of Beech Service Bulletin (SB) No. 2430, dated March 1992. Prior to further flight, replace any fuel contaminated parts in accordance with Part II of the ACCOMPLISHMENT INSTRUCTIONS section of the referenced service information. (b) Modify the wet wing fuel barriers in accordance with Parts III and IV of the ACCOMPLISHMENT INSTRUCTIONS section of Beech SB No. 2430, dated March 1992. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and send it to the Manager, Wichita Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office. (e) The inspection and modification required by this AD shall be done in accordance with Beech Service Bulletin No. 2430, datedMarch 1992. 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 the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on March 8, 1993.
91-21-04: 91-21-04 BRITISH AEROSPACE: Amendment 39-8051. Docket No. 91-NM-26-AD. Applicability: Model BAC 1-11 200 and 400 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent degradation in the structural capabilities of the pressure cabin on affected airplanes, accomplish the following: A. For airplanes operating at a maximum cabin differential pressure of 7.5 pounds per square inch (psi), as specified in British Aerospace Alert Service Bulletin 53-A-PM5991, Issue 1, dated September 5, 1990: At or prior to the accumulation of 33,000 landings or within 4,000 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 8,000 landings, accomplish the following: 1. Perform a dye penetrant inspection to detect cracks in the left and right machined attachment angles, Part Number AB27-7761/2, in accordance with paragraph 2.1.3 of the service bulletin. 2. Perform a visual inspection to detect cracks in the top flange of the longitudinal boom of the left and right outboard auxiliary beam, in accordance with paragraph 2.1.4 of the service bulletin. B. For airplanes operating at a cabin pressure in excess of 7.5 psi up to a maximum of 8.2 psi, as specified in British Aerospace Alert Service Bulletin 53-A-PM5991, Issue 1, dated September 5, 1990: At or prior to the accumulation of 22,000 landings or within 3,000 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 5,000 landings, accomplish the following: 1. Perform a dye penetrant inspection to detect cracks in the left and right machined attachment angles, Part Number AB27-7761/2, in accordance with paragraph 2.2.3 of the service bulletin. 2. Perform a visual inspection to detect cracks in the top flange of the longitudinal boom of the left and right outboard auxiliary beam, in accordance with paragraph 2.2.4 of the service bulletin. C. If defects are found during the inspections required by this AD, prior to further flight, either replace the cracked structure with serviceable parts of the same part number; or repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. Following repair or replacement, repeat the inspections required by paragraphs A. and B. of this AD at the specified intervals. D. All machined attachment angles having Part Number AB27-7761/2 must be replaced with a new part of the same part number prior to the accumulation of 85,000 landings since new and thereafter at intervals not to exceed 85,000 landings. E. An 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. F. Special 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. G. The inspection, repair, and replacement requirements shall be done in accordance with British Aerospace Alert Service Bulletin 53-A-PM5991, Issue 1, dated September 5, 1990. 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C.This amendment (39-8051, AD 91-21-04) becomes effective on November 19, 1991.
2021-13-02: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-300ER series airplanes. This AD was prompted by a report that a production design change to certain insulation blankets inadvertently opened up leakage paths for halon and smoke to escape from the aft cargo compartment in the event of a fire. This AD requires installation of an insulation blanket assembly on top of existing insulation blankets in certain areas of the forward endwall in the aft cargo compartment. The FAA is issuing this AD to address the unsafe condition on these products.
2021-14-10: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400, 747-400D, and 747-400F series airplanes. This AD was prompted by reports of burned Boeing Material Specification (BMS) 8-39 urethane foam found in certain locations on the airplane; investigation revealed that the fire-retardant properties degrade with age. This AD requires inspecting the insulation blankets in certain areas of the forward cargo compartment for exposed BMS 8-39 urethane foam, not encapsulated by a protective fire resistant barrier, and for seal integrity, and replacing the BMS 8-39 urethane foam and seal if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
48-08-01: 48-08-01 BEECH: Applies to Model 35 Airplanes Having Serial Numbers Below D-1095 Except D-923, D-925, D-940, D-954, D975, D-983, D-1003, D-1006, D-1013, D-1025, D-1031, D-1038, D-1042, D-1048 Through D-1050, D-1052, D-1053, D-1056 Through D-1062, D-1064, D-1066 Through D-1068, D-1071, D-1072, D-1074, D-1075, D-1077 Through D-1081, D-1083, and D-1085 Through D-1093. Compliance required by November 1, 1948. To preclude possible engine malfunctioning as a result of starter gear chipping caused by improper engagement of the starter mechanism, accomplish the following: (1) Remove the starter assembly from the engine and replace the original starter pinion and clutch assembly with the new assembly, P/N DR1885537. Check the solenoid linkage adjustment to ascertain that the pinion and clutch assembly can move rearward to contact the starter adapter. If the linkage prevents full disengagement of the pinion, remove the toggle link pin and turn the plunger shaft outward untilfull retraction is obtained. Check to make sure that at least two threads are still engaged. Reinstall the starter assembly. (2) Install the new resistor coil, P/N DR 1885541, on the starter battery and ground power terminals. The coil must hang downward from the terminals. (3) Make all electrical connections as covered in Beech Starter Latching Relay Installation Instructions. (Continental Service Bulletin No. M47-19 dated August 31, 1947, and Beech Service Letter No. 10, Model 35, cover this same subject.)
98-03-16: This amendment adopts a new airworthiness directive (AD) that applies to The New Piper Aircraft Corporation (Piper) Model PA-38-112 airplanes. This action requires repetitively replacing the upper rudder hinge bracket. Reports of fatigue cracks occurring on the upper rudder hinge bracket, and the manufacture of a new upper rudder hinge bracket with a life limited improved design prompted this action. The actions specified by this AD are intended to prevent cracks in the upper rudder hinge bracket, which could result in separation of the rudder from the airplane and loss of control of the airplane.
2011-12-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: An inspection by the vendor revealed that a number of Rubber Bull Gears (RBG) in the Horizontal Stabilizer Trim Actuator (HSTA) of the CL-600-2C10, CL-600-2D15 and CL-600-2D24 aeroplanes were installed with a wheel material hardness out of specification. This non-conformity has a direct impact on the HSTA life limit. The teeth of these non-conformant RBGs could break and in extreme cases, could lead to uncontrolled HSTA movement without the ability to re-trim the aeroplane. If not corrected, this condition could result in a difficulty to control the pitch and subsequent loss of the aeroplane. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
98-04-09: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F28 Mark 0070 and Mark 0100 series airplanes, that requires a one-time visual inspection to detect cracking of the brake torque tube lever, and corrective action, if necessary. 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 failure of the brake torque tube lever, which could result in a disconnection between the brake pedal and brake system, and consequent reduced directional controllability of the airplane during landing.
90-25-08: 90-25-08 BOEING: Amendment 39-6816. Docket No. 90-NM-107-AD. \n\tApplicability: Model 747 and 767 series airplanes, equipped with Class "C" lower lobe cargo compartments that do not have complete cargo compartment floors, certificated in any category. \n\tCompliance: Required within 30 months after the effective date of this AD, unless previously accomplished; except that, for airplanes that are subject to the requirements of Federal Aviation Regulation (FAR) 121.314, the modifications required by this AD shall not be accomplished prior to the accomplishment of the modifications required by FAR 121.314. \n\tTo prevent a cargo compartment fire from migrating up behind the cargo liner, accomplish the following: \n\tA.\tInstall a fire stop near the bottom of the sloping sidewall cargo compartment liner, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office, FAA, Transport Airplane Directorate. Fire stop material must meet the requirements of FAR Part25, Appendix F, Part III. \n\tB.\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 (ACO), FAA, Transport Airplane Directorate. \n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \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\tThis amendment (39-6816, AD 90-25-08) becomes effective on January 2, 1991.
2004-06-04: This amendment adopts a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-76 A, B, and C helicopters with dual channel autopilot and dual inverters installed. This action requires a test to determine if the No. 1 inverter is wired to the DC essential bus, and if so, it requires modifying the wiring so that the No. 1 inverter is wired to the No. 2 DC primary bus and the No. 2 inverter is wired to the DC essential bus. If the wiring modification is required and is not performed before further flight, then revising the Rotorcraft Flight Manual (RFM) before further flight to limit the maximum instrument meteorological conditions (IMC) airspeed and installing a placard near the airspeed indicator is also required. The wiring modification is required within 30 days. This amendment is prompted by three incidents in which a No. 2 generator intermittent malfunction occurred and both autopilots disengaged. The actions specified in this AD are intendedto prevent both autopilots from disengaging following a No. 2 DC generator failure, and subsequent loss of control of the helicopter during IMC operations.
2021-14-03: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd. & Co KG (RRD) BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 model turbofan engines. This AD was prompted by reports of HPT stage 1 blades failing in service due to sulphidation and subsequent crack initiation. This AD requires removal and replacement of the HPT stage 1 blade and HPT stage 1 blade damper. The FAA is issuing this AD to address the unsafe condition on these products.
2021-15-04: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-300 series airplanes as modified by a certain supplemental type certificate (STC). This AD was prompted by a report that the electrical diagram for the C9066 circuit breaker connection (wiring) for the ''Main Deck Oxygen Alert Control'' is erroneous and might have resulted in incorrect installation. This AD requires inspecting the wiring connection common to the C9066 circuit breaker and, if necessary, making changes to the wiring connection and testing the main deck oxygen alert system. The FAA is issuing this AD to address the unsafe condition on these products.
48-13-02: 48-13-02 BELL: Applies to Model 47 Series Equipped With Franklin 6V4-178-B3 and B32 Engines. Compliance required at next preflight inspection. Inspect fuel pump rocker pins to determine type. If pin has retaining rings which snap on each end, replace with new type pin having a head on one end and a staked washer on the other. Until new type pin is installed, daily inspection to determine the condition of the snap ring locks is required. A red paint dab for identification should be placed on all fuel pumps incorporating rocker pin change. Replacement pins are available through Aircooled Motors, Inc. (Franklin Service Bulletin No. 64 covers this same subject.)
2004-07-02: This amendment adopts a new airworthiness directive (AD) that is applicable to all Airbus Model A318, A319, A320, and A321 series airplanes. This action requires a one-time general visual inspection to determine the part number and serial number of both main landing gear (MLG) sliding tubes, and related investigative and corrective actions if necessary. This action is necessary to detect and correct cracking in a MLG sliding tube, which could result in failure of the sliding tube, loss of one axle, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2011-11-01: We are adopting a new airworthiness directive (AD) for the products listed above. 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: As a result of fatigue-testing programme on Jetstream aeroplanes, cracks have been found on the main landing gear (MLG) fittings that embody modifications JM5218 or JM8003. This condition, if not detected and corrected, could lead to a MLG collapse on the ground or during landing, possibly resulting in a fuel tank rupture, consequent damage to the aeroplane or injury to the occupants. We are issuing this AD to require actions to correct the unsafe condition on these products.
2005-12-04: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200, -200PF, and -200CB series airplanes. This AD requires repetitive inspections of the shim installation between the vertical flange and bulkhead. This AD is prompted by reports of cracks, loose and broken bolts, and shim migration in the joint between the aft torque bulkhead and the strut-to-diagonal brace fitting. We are issuing this AD to detect and correct such cracks, loose and broken bolts, and shim migration, which could result in damage to the strut and consequent separation of the strut and engine from the airplane.
2021-13-19: The FAA is superseding Airworthiness Directive (AD) 2014-11-02 for Airbus Helicopters Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters. AD 2014-11-02 required repetitively inspecting frame number (No.) 9 for a crack. This AD was prompted by Airbus Helicopters developing a modification that provides an optional terminating action for the repetitive inspections required by AD 2014-11-02. This AD retains the requirements of AD 2014-11-02, provides an optional terminating action for the repetitive inspections, and reduces the applicability by excluding certain post-modified helicopters. The FAA is issuing this AD to address the unsafe condition on these products.
76-11-04: 76-11-04 DORNIER GmbH: Amendment 39-2631. Applies to Model Do 28D-1 airplanes certificated in all categories, serial numbers 4001 through 4039. Compliance is required as indicated, unless already accomplished. To prevent smoke and fire resulting from the chafing of teleflex engine control cables against electrical cables, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, visually inspect the electrical cable insulation under each engine for chafing damage at those points where the throttle and mixture control teleflex cables cross the electrical cables. Actuate the teleflex dables during the inspection. If a chafed electrical cable is found, repair the cable in accordance with paragraph (c) of this AD before further flight. (b) Within the next 100 hours time in service after the effective date of this AD, unless earlier compliance is required pursuant to paragraph (a) of this AD, comply with paragraph (c) of this AD. (c) Wrap helical Rapidon wear protection material, or FAA-approved equivalent material, around the electrical cables and teleflex cables under each engine in accordance with Dornier Service Bulletin 1031-1901, dated March 25, 1971, or an FAA approved equivalent. This amendment becomes effective June 15, 1976.
97-15-15: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 97-15-15, which was sent previously to all known U.S. owners and operators of Eurocopter France Model SA-365N, SA-365N1, and SA-366G1 helicopters by individual letters. This AD requires an inspection of the main gearbox magnetic plug (magnetic plug) and the main gearbox oil filter (oil filter) for ferrous chips; vibration measurements, if necessary; and replacement of the main gearbox if a specified quantity of ferrous chips are discovered, or if abnormal vibrations are identified at a certain frequency. This amendment is prompted by two recent reports of cracks found in planetary gear shafts (gear shafts) in main gearboxes that have not been modified in accordance with MOD 077244. The actions specified by this AD are intended to detect cracks in the gear shaft which could lead to failure of the gear shaft, failure of the transmission, and subsequent loss of control of the helicopter.