Results
2012-17-07: We are adopting a new airworthiness directive (AD) for certain Diamond Aircraft Industries GmbH Models DA 42, DA 42 NG, and DA 42 M-NG 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 excessive voids in the adhesive joint between the center wing spars and the [[Page 54801]] upper center wing skins. This condition could cause the wing to fail, which could result in loss of control of the airplane. We are issuing this AD to require actions to address the unsafe condition on these products.
98-09-24: This amendment adopts a new airworthiness directive (AD) that applies to certain Diamond Aircraft Industries (Diamond) Models H-36 "Dimona" ; and HK 36 R "Super Dimona" sailplanes. This AD requires: inspecting the elevator rib area for damage on certain Models H-36 " Dimona" and HK 36 R "Super Dimona" sailplanes, and either immediately or eventually replacing the elevator ribs depending on the results of the inspection; replacing the M6 screws that attach the wheel axle to steel support with M8 screws on certain Models HK 36 R "Super Dimona" sailplanes; and inspecting the shoulder harness fittings for improper bonding on certain Diamond Model H-36 "Dimona" sailplanes, and repairing any harness with an improper bond. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Austria. The actions specified by this AD are intended to prevent failure of either the shoulder harness fittings, elevator rib, or the wheel axle to steel support attachment, which could result in passenger injury caused by an inadequate restraint system; reduced sailplane controllability caused by structural damage to the elevator; and/or reduced sailplane controllability during takeoff, landing, and ground operations caused by the installation of incorrect wheel axle screws.
96-05-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires modification of a certain galley; repetitive inspections to detect damage and to determine the clearance of generator wires in the auxiliary power unit (APU); and repair or replacement of the damaged wires. This amendment is prompted by reports indicating that, during an unscheduled removal of a galley from the production line, the insulation of one of the generator wires of the APU was found damaged due to inadequate clearance with the adjacent structure. The actions specified by this AD are intended to prevent such damage, which could result in a short in the electrical wiring of the APU and, thus, pose a potential fire hazard.
2012-17-03: We are adopting a new airworthiness directive (AD) for certain Eurocopter France Model AS350 helicopters. This AD requires installing protection sleeves over certain forward (pitch) servo-control hydraulic hoses. This AD was prompted by an in-flight fire caused by the ignition of hydraulic fluid leaking from a damaged forward servo-control hydraulic hose. This AD's actions are intended to prevent the forward servo-control hydraulic hoses from becoming damaged and leaking hydraulic fluid that could ignite in flight, which could result in loss of main rotor (M/R) control, power loss, structural damage, propagation of fire, and subsequent loss of control of the helicopter.
58-23-03: 58-23-03 MOONEY: Applies to Model M-20 Aircraft Serial Numbers 1002 Through 1051. Compliance required as soon as practicable but not later than December 15, 1958. Several failures of the aileron counterbalance buttweld at the aileron spar have occurred. The affected airplanes do not have a 3/8 inch O.D. x 0.028 inch x 3 inch steel reinforcing brace installed. It must be determined whether this brace has been incorporated. If not, the following inspection and repair must be accomplished: 1. Remove the paint from the subject welded joint and inspect for cracks. 2. Reweld the joint if cracks are present. 3. Install the 3/8 inch O.D. x 0.028 inch x 3 inch 4130 steel tubular brace (trimmed to fit). (Mooney Aircraft, Inc. Service Letter 20-7 Revision B covers this same subject.)
86-14-07: 86-14-07 SIKORSKY AIRCRAFT: Amendment 39-5432. Applies to all Model S-76A helicopters certificated in any category and model S-76B helicopters, serial numbers 760262, 760269, 760299, 760303, and 760310 through 760319, certificated in any category. Compliance is required as indicated, unless already accomplished. To prevent operation with a failed pilot's yaw control rod assembly, P/N 76400-00034-041, accomplish the following: (a) Prior to further flight, inspect the push rod assembly in accordance with Section E, paragraph 1, of Sikorsky Alert Service Bulletin (ASB) No. 76-ASB-76-67-22A, dated July 7, 1986, or an FAA-approved equivalent. If no dent, crack, distortion, or bowing is detected in the rod, install a placard legible to the pilot and in full view of the pilot stating "single pilot operation prohibited." This placard is to remain until the inspection required by paragraph (b) below is accomplished. (b) Within the next 25 hours' time in service afterthe effective date of this AD, inspect the push rod assembly for condition of heat treat in accordance with Section E, paragraph 2, of Sikorsky ASB No. 76-ASB-76-67-22A, dated July 7, 1986, or an FAA-approved equivalent. (c) If as a result of the inspection of paragraph (a), a dent, crack, distortion, or bowing is detected or if as a result of the inspection of paragraph (b) above, the heat treat (hardness) is incorrect, replace the rod assembly with a new or serviceable component that complies with this AD prior to further flight. (d) Aircraft may be ferried in accordance with the provision of FAR Sections 21.197 and 21.199 to a base where the requirements of the AD can be accomplished. (e) Upon request, an alternate method of compliance which provides an equivalent level of safety with the requirements of this AD may be approved by the Manager, Boston Aircraft Certification Office, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, telephone (617) 273-7118. Sikorsky Aircraft ASB No. 76-ASB-76-67-22A identified and described in this document, is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Sikorsky Aircraft, Division of United Technologies, North Main Street, Stratford, Connecticut 06601. This document also may be examined at the Rules Docket, Office of the Regional Counsel, Federal Aviation Administration, Southwest Region, 4400 Blue Mound Road, Fort worth, Texas, 76106. This amendment becomes effective October 20, 1986, as to all persons except those to whom it was made immediately effective by individual priority letter AD No. 86-14-07 issued July 9, 1986, which contained this amendment.
99-11-06: This amendment adopts a new airworthiness directive (AD) that applies to all Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes. This AD requires inspecting both (left and right wing configurations) environmental control system bleed tubes for damage, leakage, and a correct gap between the tube and wing lower panel crossing area, inspecting the wiring and surrounding structures for damage, and correcting any discrepancies found. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent thermal expansion from causing leakage of an environmental control system bleed tube because of improper installation, which could result in deterioration of the electrical wiring and the surrounding structure.
2012-17-02: We are adopting a new airworthiness directive (AD) for all Eurocopter France (EC) Model SA-365N, SA-365N1, SA-366G1, AS-365N2, AS 365 N3, EC 155B, and EC155B1 helicopters. This AD was prompted by the discovery of a cracked main rotor mast nut. This condition, if not corrected, could lead to complete failure of the mast nut, resulting in failure of the rotor mast and loss of control of the helicopter. This AD will require replacing the main rotor mast nut with an airworthy main rotor mast nut to prevent this scenario.
2012-17-01: We are adopting a new airworthiness directive (AD) for Goodyear Aviation Tires, part number 299K63-1 (Brazilian made new tires only), installed on various transport category airplanes, including but not limited to Bombardier, Inc. Model CL-600-2B19 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 tire tread separations and tread-area bulges on the main landing gear tires due to low adhesion in the tread shoulder area. The unsafe condition is specific to Brazilian produced new tires, size H29x9.0-15, only; retread tires are not affected by this AD. This condition, if not detected and corrected, could cause the main landing gear tires to fail during takeoff or landing. The failure may cause damage to the airplane structure, flaps, engine, and wheel well and result in reduced controllability of the airplane. We are issuing this AD to require actions to address the unsafe condition on these products.
71-20-04: 71-20-04 CHAMPION: Amendment 39-1299. Applies to Model 7ECA (Serial Numbers 145, 151, 182, 190, 194, 199, 207, 211, 212, 226, 228, 229, 233, 242, 250, 253, 269, 270, 276, 281 thru 284, 287, 289, 292, 296, 298 thru 303, 306, 308, 316, 317, 321, 325, 328, 335, 344, 353, 354 thru 357, 365, 381, 387, 388, 403, 411, 416, 417, 421, 423, 439, 442, 447, 448, 450, 452, 463, 464, 470, 497, 501, 504, 515, 518, 531, 532, 543, 546, 552, 557, 560, 564, 569), Model 7GCAA (Serial Numbers 6, 8, 15, 44, 88, 91, 104, 106, 111, 112, 114, 125, 128, 141 thru 144, 150, 152, 154, 156 thru 167, 169, 172), Model 7GCBC (Serial Numbers 4, 7, 10, 14, 15, 16, 36, 45, 79, 83, 84, 86 thru 90, 92 thru 95), and Model 7KCAB (Serial Numbers 3, 16 thru 22, 24 thru 37, 39 thru 45, 47, 48, 50, 51, 53, 54, 55, 57, 58, 61, 62 and 64) airplanes. Compliance: Required as indicated, unless already accomplished. To prevent structural failure of the lower longerons, accomplish the following: A) Within the next50 hours' time in service after the effective date of this AD, visually inspect the lower fuselage longerons in accordance with Champion Service Letter No. 96, dated August 1, 1969, to determine its method of fabrication. B) If the lower fuselage longerons, inspected in accordance with Paragraph A, do not meet the radius criteria specified in Champion Service Letter No. 96, dated August 1, 1969, prior to return to service, install Champion Service Kit 233, or any equivalent modification approved by the Chief, Engineering & Manufacturing Branch, FAA, Central Region. NOTE: Champion Aircraft Corporation is now Bellanca Aircraft Corporation. This amendment becomes effective September 30, 1971.
2012-16-14: We are adopting a new airworthiness directive (AD) for all Honeywell International Inc. TFE731-20R, -20AR, -20BR, -40, -40AR, - 40R, -50R, and -60 turbofan engines. This AD was prompted by a report of a quality escape of about 8,000 2nd stage low-pressure turbine (LPT2) rotor blades, manufactured by Honeywell Chihuahua Manufacturing Operation since 2009. This AD requires removing and inspecting certain LPT2 rotor blades. We are issuing this AD to correct an unsafe condition caused by these blades installed on these engines.
99-10-11: This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney JT8D-200 series turbofan engines, that currently requires periodic inspection of fan blades for locked rotors and foreign object damage (FOD), unlocking of shrouds if necessary, lubrication of fan blade shrouds, and dimensional restoration of the fan blade leading edge. In addition, that AD requires installation of improved design fan blades as terminating action for the inspections. This AD will reduce the lubrication interval, and require removal of rotors that experience repeat lockups within 225 cycles in service. This supersedure is prompted by reports of twenty-five fan blade failures to date. The actions specified by the AD are intended to prevent fan blade failure, which can result in damage to the aircraft.
2012-15-08: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-76A helicopters to require modifying the electric rotor brake (ERB) and inserting changes into the ``Normal Procedures'' and ``Emergency Procedures'' sections of the Rotorcraft Flight Manual (RFM). This AD was prompted by a fire in the main gearbox area as a result of a hot electric rotor brake (ERB). The actions are intended to prevent overheating of the ERB, ignition of the ERB hydraulic fluid, a fire in the main gearbox area, and subsequent loss of control of the helicopter.
99-06-17: This action confirms the effective date of Airworthiness Directive (AD) 99-06-17, which applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. AD 99-06-17 requires installing a support bracket and a cut-out relay for the second generator control unit. AD 99-06-17 also requires making all the wiring additions and adjustments necessary for the above-referenced installations. This AD was the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified in this AD are intended to prevent damage to electrical components because incorrectly connected cables or broken or damaged wires cause excessive voltages to the second generator, which could result in loss of electrical power during any phase of flight.
76-05-09: 76-05-09 AER PEGASO (AEROMERE & AVIONAUTICA RIO): Amendment 39-2544. Applies to M100S gliders, certificated in all categories. Compliance is required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. To prevent separation of lower rudder hinge pin from the rudder hinge bracket and the consequent loss of rudder control, accomplish the following: Replace the lower rudder hinge pin with a new pin made of SAE 1024 steel and inspect the new pin's weld for cracks, using the dye penetrant method, in accordance with the steps (1) through (9) of the Description section of Ingg. A. & P. Morrelli (Aer Pegaso) Technical Bulletin No. 11/M100S, dated March 16, 1971, or an FAA- approved equivalent. This amendment becomes effective March 25, 1976.
2025-09-01: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited (BTCL) Model 505 helicopters. This AD was prompted by reports of possible chafing in certain locations between the basic and supplemental helicopter wiring and the structure. This AD requires repetitively inspecting the wire harnesses at certain locations for damage, and if any wire damage is found, repairing the damaged wire/bundles, 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.
2025-09-03: The FAA is superseding Airworthiness Directive (AD) 2021-24- 09, which applied to certain Bell Textron Canada Limited Model 430 helicopters. AD 2021-24-09 required a visual inspection of the main rotor (M/R) pitch link clevis (clevis), rod end, and a certain part- numbered universal bearing, performing a purge grease, and performing a magnetic particle inspection of each M/R clevis, and depending on the inspection results, removing or replacing certain parts and performing additional actions. AD 2021-24-09 also required recurring inspections of each M/R clevis and each universal bearing. Since the FAA issued AD 2021-24-09, the manufacturer has reduced the life limits of the affected parts and introduced new M/R pitch link assemblies by re- identifying the M/R pitch link assemblies that were required to be inspected by AD 2021-24-09. This AD requires similar actions as AD 2021-24-09 but reduces the life limits and requires replacing the M/R pitch link assemblies with re-identified part numbered assemblies. These actions are 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.
2012-16-05: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -200 freighter series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD requires modification of the control circuit for the fuel pumps for the center fuel tanks for certain airplanes, and center and rear fuel tanks for certain other airplanes. We are issuing this AD to prevent 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.
99-09-18: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 and Mark 0100 series airplanes, that currently requires a one-time inspection for heat damage of the fuselage skin and stubwing structure; either repetitive tests of certain seals or repair of heat damage, as necessary; and eventual replacement of corrujoint seals with new, improved seals. This amendment adds a requirement for repetitive inspections for heat damage of the subject area, and provides for a new optional terminating action for the repetitive inspections. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent leakage of hot air from the corrujoint seals of certain valves in the stubwings, and subsequent heat damage of the fuselage skin and stubwing structure, which could result in reduced structural integrity of theairplane. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of June 8, 1999. The incorporation by reference of certain other publications as listed in the regulations, was approved previously by the Director of the Federal Register as of May 14, 1998 (63 FR 17318, April 9, 1998).
75-24-11: 75-24-11 BEECH: Amendment 39-2437. Applies to all civilly certificated Models A45 (Military T-34A, B-45) and D45 (Military T-34B) airplanes. Compliance: Required as indicated, unless already accomplished. To prevent failure of the P/N 45-524504 and 45-524505 rudder-aileron bungee interconnect cable assembly and the P/N 45-524697 or P/N 45-524028 bellcrank assembly, accomplish the following: A) On Model A45 (Military T-34A, B-45) airplanes not incorporating P/N MS- 20219-2 pulleys (1.75 inch O.D.) per Beech Kit 45-325 and Beech P/N 105740B-ZF-0105 bronze bushings per Beech Drawing 45-000060, Rev. C, or later revision, within 50 hours' time in service after the effective date of this AD, or within 100 hours' time in service after the last inspection per AD 62-27-01, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, accomplish Paragraphs 1(a) and 1(b). B) On Models A45 (Military T-34A, B-45) and D45 (Military T-34B) airplanes incorporating P/N MS-20219-2 pulleys (1.75 inch O.D.) per Beech Kit 45-325 and Beech P/N 105740B-ZF-0105 bronze bushings per Beech Drawing 45-000060, Rev. C, or later revision, within 50 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 300 hours' time in service from the last inspection, accomplish Paragraphs 1(a) and 1(b). 1. (a) Disconnect the turn buckles P/N 45-524504 and 45-524505 rudder-aileron bungee interconnect cable assemblies, visually inspect the cables and replace frayed, internally broken or excessively worn cables. (b) Disconnect the two AN 161-8RS forks that attach to the P/N 45- 524697 or P/N 45-524028 bellcrank assembly and visually inspect the 3/16-inch diameter holes in the bellcrank for elongation or cracks. If elongation exceeds 0.02 inches or if cracks are found, replace the bellcrank. If no elongation or cracks are found, lubricate the holes in the bellcrank prior to reinstallation of theAN 161-8RS forks. 2. The airplane may be flown in accordance with FAR 21.197 to a location where parts replacement can be accomplished. 3. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Beechcraft Service Bulletin No. 32 on Model A45 (Military T-34A, B-45) airplanes covers the cable inspection. This AD supersedes AD 62-27-01. This amendment becomes effective November 28, 1975.
2012-16-10: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by chafing on high pressure fuel lines due to improper installation of an expandable pin on the lower cowl assembly. This AD requires installing spring clips and repositioning the lanyard attachment points at the forward end and the forward firefloor of the lower cowl. We are issuing this AD to prevent chafing of the high pressure fuel lines, which if not corrected, could cause fuel leakage in a fire zone.
75-04-12: 75-04-12 BELLANCA: Amendment 39-2093. Applies to Model 8GCBC Airplanes, Serial Numbers 1-74 through 119-74, 120-75 through 153-75 certificated in all categories. Compliance required within the next 10 hours time in service after the effective date of this airworthiness directive, unless already accomplished. To prevent possible resonant vibratory conditions with McCauley Model 1A200/HFA fixed pitch propellers installed on Lycoming 0-360-C2A, or -C2E type engines, accomplish the following in accordance with Bellanca Service Letter Number 115 and Bellanca Service Kit Number 245. (a) Remove existing markings on the tachometer instrument glass and affix Mylar decal, Bellanca P/N 1-10443. The decal is properly affixed when: a green arc extends from 500 to 1700 RPM; a yellow arc from 1700 to 2100 RPM; a green arc from 2100 RPM to 2700 RPM; and a red radial is positioned at 2700 RPM. (b) Install Bellanca P/N 1-10437, placard "AVOID 1700-2100 DURING DESCENT", on thetachometer instrument glass below the hour meter. (c) Accomplish Revision Number 1 to existing FAA Approved Airplane Flight Manual (AFM) in accordance with AFM revisions page. This amendment becomes effective February 21, 1975.
2012-16-06: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-600 series airplanes and Model A310-203, -204, - 221, and -222 airplanes. This AD was prompted by a report of a capacitive density condensator (cadensicon) coil overheating during testing. This AD requires an inspection to determine if a certain fuel quantity indication computer (FQIC) is installed, replacement of identified FQICs, and modification of the associated wiring. We are issuing this AD to detect and correct potential overheating of the cadensicon coil, which could create an ignition source inside a fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
67-18-03: 67-18-03 LOCKHEED: Amendment 39-423 as amended by Amendment 39-1601. Applies to Model 382 and 382B series airplanes, serial numbers 3946 and 4101 through 4196. Compliance as indicated. (a) For airplanes with 2350 or more hours' total time in service on the effective date of this AD comply with paragraph (c) within the next 50 hours' time in service, and thereafter at intervals not to exceed 800 hours' time in service from the last inspection. (b) For airplanes with less than 2350 hours' total time in service on the effective date of the AD comply with Paragraph (c) before the accumulation of 2400 hours' total time in service, and thereafter at intervals not to exceed 800 hours' time in service from the last inspection. (c) Inspect all eight affected engine mount truss assemblies in accordance with the tooling and inspection instructions given in Lockheed-Georgia Service Bulletin 82-153 dated December 1, 1966, Section 1f and 2a through 2e, respectively, or later FAA approved revision, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. (1) Cracked parts shall be replaced with new parts having the same part number, or with the applicable updated part specified in Section 2g of Lockheed-Georgia Service Bulletin 82-153 dated December 1, 1966, or later FAA approved revision. Replacement truss assemblies shall be installed according to the replacement instructions given in Section 2h through 2aa in the above Service Bulletin, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. (2) Replacement of cracked trusses shall be accomplished before further flight, except that one flight may be made for the purpose of obtaining the necessary replacements in accordance with the provisions of FAR 21.197. (d) When a particular truss assembly is replaced with the applicable updated part specified in Section 2g of Lockheed-Georgia Service Bulletin 82-153dated December 1, 1966, or later FAA approved revision, the repetitive inspection of that truss as required by this AD may be discontinued. Lockheed-Georgia Service Bulletin 82-153, dated December 1, 1966, covers this same subject. Amendment 39-423 became effective June 25, 1967. This Amendment 39-1601 becomes effective March 12, 1973.
2018-05-06: We are superseding Airworthiness Directive (AD) 2016-09-12, which applied to certain The Boeing \n\n((Page 9689)) \n\nCompany Model 787-8 and 787-9 airplanes. AD 2016-09-12 required repetitive inspections of the bilge barriers located in the forward and aft cargo compartments for disengaged decompression panels, and reinstalling any disengaged panels. This AD retains the actions required by AD 2016-09-12 and requires replacing the existing decompression panels with new panels and straps, which terminates the repetitive inspections. This AD also removes airplanes from the applicability. This AD was prompted by a terminating modification developed to address the unsafe condition. We are issuing this AD to address the unsafe condition on these products.