Results
2022-11-02: The FAA is adopting a new airworthiness directive (AD) for all CFM International, S.A. (CFM) LEAP-1B21, LEAP-1B23, LEAP-1B25, LEAP- 1B27, LEAP-1B28, LEAP-1B28B1, LEAP-1B28B2, LEAP-1B28B2C, LEAP-1B28B3, LEAP-1B28BBJ1, and LEAP-1B28BBJ2 model turbofan engines. This AD was prompted by the detection of melt-related freckles in the billet, which may reduce the life of certain compressor rotor stages 6-10 spools, high pressure turbine (HPT) rotor mid seals, HPT rotor stage 2 disks, low pressure turbine (LPT) stage 2 disks, and LPT stage 3 disks. This AD requires revising the airworthiness limitations section (ALS) of the applicable CFM LEAP-1B Engine Shop Manual (ESM), and the operator's existing approved maintenance or inspection program, as applicable, to incorporate reduced life limits for these parts. The FAA is issuing this AD to address the unsafe condition on these products.
2004-15-03R1: The FAA is revising an existing airworthiness directive (AD) for General Electric Company (GE) CF34-3A1 and -3B1 series turbofan engines with certain serial numbers (SNs) of stage 5 low pressure turbine (LPT) disks, part number (P/N) 6078T92P01, and/or certain SNs of stage 6 LPT disks, P/N 6078T89P01. That AD currently requires initial and repetitive visual and eddy current inspections of those disks. That AD also allows as optional terminating action to the repetitive inspections, replacement of those SN disks. Also, that AD requires replacement of certain stage 5 and stage 6 LPT disks. This ad requires the same actions. This AD results from the discovery that an incorrect part number for stage 6 LPT disks was published in the existing AD and from the need to allow credit for actions completed per previous releases of Alert Service Bulletin CF34-AL S/B 72-A0173. We are issuing this AD to prevent LCF failure of stage 5 LPT disks and stage 6 LPT disks, which could lead to uncontained engine failure.
73-15-02: 73-15-02 PRATT & WHITNEY: Amdt. 39-1687 as amended by Amendment 39-1712. Applies to all JT3D-1, JT3D-1-MC6, JT3D-1-MC7, JT3D-3 and JT3D-3B model engines containing turbine nozzle case Part Numbers 399065, 496859, 570618, 626669, 669045, 669047, 694937, 694938, 390197, 694935 and 691326 incorporating vented 2nd stage outer airseals. Compliance required as follows: To preclude possible turbine blade or disc failures resulting from turbine case lug failures, inspect the turbine nozzle case for missing lugs by performing Ultrasonic, Isotope or Visual inspection at the time intervals specified below. First inspection, 1,000 hours time in service after the effective date of this AD unless already accomplished. (a) If there are no missing lugs, repeat the inspection every 1,000 hours time in service thereafter. (b) If one lug is found missing, repeat the inspection every 100 hours time in service. (c) If two or three lugs are found missing, remove the engine within the next 50 hours time in service. (d) If four or more lugs are missing, remove from service immediately. Turbine cases may be repaired in accordance with the procedures outlined in the Overhaul Manual, Section 72-51-2, or replaced. Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the compliance time. NOTE: Pratt & Whitney Service Bulletin 3993, or later FAA approved revisions pertain to this same subject. Amendment 39-1687 became effective August 18, 1973. This Amendment 39-1712 becomes effective September 14, 1973.
2004-15-02: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) models RB211 Trent 875-17, Trent 877-17, Trent 884-17, Trent 884B-17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan engines with low pressure (LP) compressor fan blades part number (P/N) FW18548, installed. This AD requires LP compressor fan blade replacement with new or previously reworked blades, or rework of the existing LP compressor fan blades. This AD results from a number of new production LP compressor fan blades found with surfaces formed outside of design intent. Findings included sharp edges, burrs, and damage present in the area at the top of the shear key slots. We are issuing this AD to prevent possible multiple uncontained LP compressor fan blade failure, due to cracking in the blade root caused by increased stresses in the shear key slots.
47-43-11: 47-43-11 LOCKHEED: (Was Mandatory Note 22 of AD-723-3.) Applies to All Model 18 Serial Numbers. Compliance required prior to next periodic inspection. Remove bolts connecting the elevator push-pull rod to the elevator horn and bellcrank and ascertain that the shank diameter falls within the limits of 0.248 to 0.250. Bolts outside these limits should be replaced with NAS 54-12 bolts. In view of the similarity of the Lockheed bolts with standard AN bolt, it is suggested that they be replaced with close tolerance bolts, NAS 54-12 and the push-pull rod. P/N 72149 placarded "Use NAS 54-12 bolt".
2022-11-09: The FAA is adopting a new airworthiness directive (AD) for all Viking Air Limited (Viking) (type certificate previously held by Bombardier Inc. and de Havilland, Inc.) Model DHC-6-1, DHC-6-100, DHC- 6-200, DHC-6-300, and DHC-6-400 airplanes. 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 identifies the unsafe condition as cracks and corrosion damage to the aileron internal structure. This AD requires visually inspecting the entire aileron internal structure, correcting any damage found, and reporting the inspection results to Viking. The FAA is issuing this AD to address the unsafe condition on these products.
2013-05-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes. This AD was prompted by reports of stiff operation of the elevator pitch control system and jammed elevator controls. This AD requires replacing pressure seal assemblies; doing repetitive inspections for dirt, loose particles, or blockage of the flanged tube and drain hole for the pressure seals, and corrective action if necessary; replacing the aft air-intake duct assembly with a new or modified assembly and installing a dripshield; and installing gutters on the horizontal stabilizer center section and modifying the side brace fittings. We are issuing this AD to prevent moisture from collecting and freezing on the elevator control system components, which could limit the ability of the flightcrew to make elevator control inputs and result in reduced controllability of the airplane.
2004-16-02: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3 series airplanes, that requires installing a new warning annunciator light on the central warning panel and revising the Normal Procedures Section of the Aircraft Flight Manual to provide the flightcrew with procedures related to the new light. This action is necessary to prevent an engine shut-down in icing conditions, which could result in loss of control of the airplane and consequent injury to flightcrew and passengers. This action is intended to address the identified unsafe condition.
72-01-03: 72-01-03 BELLANCA: Amdt. 39-1373. Applies to Models 17-30A (Serial Numbers 30394, 30395, 30396, 30397, 30398, 30399, 30400, 30401, 30402, 30403 and 30405); 17-31A (Serial Number 32-53); and 17-31ATC (Serial Numbers 31022, 31023, 31024 and 31025) Airplanes. Compliance: Required as indicated, unless already accomplished. To prevent loss of engine power due to fuel starvation, accomplish the following: Prior to next flight replace hose Aeroquip P/N 359-8D-0153, located between the firewall and engine driven fuel pump, with hose Bellanca P/N 198003-10, or an equivalent method of compliance approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Bellanca Service Letter No. 68 dated December 3, 1971, pertains to this subject. This amendment becomes effective January 5, 1972, to all persons except those to whom it was made effective by telegram dated December 17, 1971.
69-14-03: 69-14-03 BRITISH AIRCRAFT CORPORATION: Amdt. 39-794. Applies to Model BAC 1-11 200 and 400 Series Airplanes. Compliance required within the next 1,500 hours' time in service after the effective date of this AD, unless already accomplished. To prevent the failure of the windshield heating circuit, install 20K ohm resistors and 1 mfd capacitors into both phases of the heating circuit for pilot's and copilot's main windshield in accordance with British Aircraft Corporation Modification Bulletin No. 30-PM 3092, Revision 8, dated July 22, 1968 or later ARB-approved revision or an FAA approved equivalent. This amendment becomes effective August 10, 1969.
2022-11-10: The FAA is adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (Piper) Model PA-46-600TP airplanes. This AD was prompted by testing that showed that the wing splice assembly could fail before the assembly reaches its established life limit. This AD requires revising the Airworthiness Limitations section (ALS) of the existing maintenance manual (MM) or instructions for continued airworthiness (ICA) to reduce the life limit of the wing splice assembly. The FAA is issuing this AD to address the unsafe condition on these products.
46-44-03: 46-44-03 CESSNA: (Was Mandatory Note 3 of AD-768-4.) Applies Only to 120 and 140 Aircraft Serial Numbers 8001 to 9619, Inclusive. Compliance required prior to January 1, 1947. Rework attachment of windshield upper edge by the installation of a retaining channel deeper than the original and extending the entire width of the fuselage. The channel consists of two pieces; one an 0.040-inch 24ST alclad strip, 1 7/8 inches x 42 inches, outside of the windshield and with the rear edge inserted between the fuselage top skin and the front flange of the spar "U" channel; the other an 0.032-inch 24ST alclad strip, 1 13/16 inches x 44 inches, inside of the windshield and overlapping the above-mentioned spar flange. These strips are secured to the top skin and spar flange by a single row of 44 AN 456AD4 rivets. A piece of felt, 2 3/4 inches x 44 inches x 1/16-inch thick, SAE F-55 or equivalent, should be folded over the edge of the windshield and cemented thereto to provide a seal and a tight fit in the channel. This modification is necessary to insure that the windshield will not pull out at the top and alter the airflow, thereby seriously affecting the operational characteristics of the airplane. (Cessna Service Letter No. 14-120 and 140 covers this same subject.)
72-07-02: 72-07-02 CESSNA: Amdt. 39-1415. Applies to the following airplanes: MODELS SERIAL NUMBERS AFFECTED 172 28000 thru 29999 172 36000 thru 36999 172 46001 thru 46754 172A 46755 thru 47746 172B 17247747 thru 17248734 172C 17248735 thru 17249544 172D 17249545 thru 17250572 172E 17250573 thru 17251822 172F 17251823 thru 17253392 172G 17253393 thru 17254892 172H 17254893 thru 17256512 172I 17256513 thru 17257161 172K 17257162 thru 17258855 Compliance: Required as indicated, unless already accomplished. To reduce the possibility of engine power interruption at altitudes above 5000 feet caused by vapor formation in the fuel lines, accomplish the following: (A) Effective now, the airplane must be operated on a single fuel tank immediately upon reaching cruise altitudes above 5000 feet. (B) On or before April 1, 1972, install at the fuel selector valve applicable Cessna placards P/N's 0509021-1, 0509021-2 or 0509021-3 as provided with Cessna Service Letter SE72-7, dated March 17, 1972, or any FAA-approved equivalent placard which reads as follows: SWITCH TO SINGLE TANK OPERATION IMMEDIATELY UPON REACHING CRUISE ALTITUDES ABOVE 5000 FEET. (C) Compliance with the provisions of Paragraphs A and B is no longer required when the fuel system has been modified by the installation of applicable Cessna Kit No. SK172-31B or SK172-32 referenced by Cessna Service Letter SE72-7, dated March 17, 1972, or by the accomplishment of any equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective March 25, 1972.
2022-10-08: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320-214, -251N, and -271N airplanes. This AD was prompted by reports that damaged seat rail covers were detected in the forward and aft seat fixation area of some airplanes during initial delivery. This AD requires a one-time detailed inspection of the affected passenger seats and corrective actions if necessary, as specified in a European Union Aviation Safety Agency (EASA). The FAA is issuing this AD to address the unsafe condition on these products.
52-02-03: 52-02-03 MARTIN: Applies to All Models 202 and 202A Aircraft. Compliance required not later than May 1, 1952. Relocate such oxygen bottles as necessary from lower center section to location in upper right forward baggage compartment in order to eliminate the high pressure line now in the bottom of the fuselage.
2022-10-01: The FAA is adopting a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC-12/47E airplanes. This AD was prompted by 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 identifies the unsafe condition as a batch of incorrectly sized fuel transfer ejector nozzles that were installed on Model PC-12/47E airplanes during production. This AD requires removing the affected fuel transfer ejectors from service and prohibits installation of the affected fuel transfer ejectors. The FAA is issuing this AD to address the unsafe condition on these products.
2013-04-14: We are adopting a new airworthiness directive (AD) for all Airbus 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); and Model A310 series airplanes. This AD was prompted by a report of an uncommanded slide back of the co-pilot seat to the end stop position. This AD requires a one-time inspection for a part number, a tensile test of the affected seats, and corrective actions if necessary. We are issuing this AD to detect and prevent unwanted movement of a pilot or co-pilot seat in the horizontal direction, which could lead to inadvertent input on the flight control commands and possibly result in loss of controllability of the airplane.
72-19-03: 72-19-03 NORTH AMERICAN ROCKWELL: Amdt. 39-1519. Applies to all Models NA-265, NA-265-20, and NA-265-30 airplanes, plus NA-265-40, serial numbers 282-1 thru 282- 98; NA-265-50, serial number 287-1; and NA-265-60, serial numbers 306-1 thru 306-37. Within the next 25 hours' time in service after receipt of this telegram, but not later than 1 October 1972, whichever occurs first, unless already accomplished, comply with the inspection and parts replacement provisions of North American Rockwell Sabreliner Service Bulletin 72-14 dated 25 August 1972, or later FAA approved revision, or equivalent FAA approved inspection and replacement. This amendment is effective September 15, 1972 and was effective upon receipt for all recipients of the telegram dated 25 August 1972 which contained this amendment.
2004-16-08: This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc. Model MD900 helicopters. This action requires installing a fan input force limiting control rod assembly fail-safe device (fail-safe device). This AD also requires, after installing a fail-safe device, before the first flight of each day, checking the fail-safe device for bent clips, taut lanyards, and piston rod movement. If any of these conditions are found, this AD requires replacing the control rod assembly with an airworthy control rod assembly before further flight. This amendment is prompted by an accident report of fatigue failure of the piston rod in the spring capsule on a control rod assembly. The actions specified in this AD are intended to provide a temporary backup support system in the event of a piston rod failure and to prevent subsequent loss of control of the helicopter.
47-10-21: 47-10-21 LOCKHEED: (Was Mandatory Note 23 of AD-763-3.) Applies to Model 49 Serials Up to and Including 2088. Compliance required prior to July 1, 1947. Install steel torque links, LAC P/N 293882, on each main landing gear. (LAC Service Instruction 49/SI-100A covers this same subject.)
2013-04-06: We are adopting a new airworthiness directive (AD) for the Eurocopter France (Eurocopter) Model AS332C, AS332L, and AS332L1 helicopters. This AD requires modifying the main landing gear control panel (control panel) 33G, connector 100G, and wiring. It also requires tests to ensure that these modifications function correctly. This AD was prompted by reports of electro-valve power supply disruptions while a helicopter is on the ground, causing the landing gear to retract and the helicopter nose to drop. This results in damage to the forward section of the helicopter's bottom structure. The actions of this AD are intended to prevent an uncommanded landing gear retraction that would cause the helicopter nose to drop and hit the ground while the rotor blades are spinning.
2022-09-12: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report indicating that on the A350 final assembly line (FAL), certain load sensing drive struts (LSDS) and drive struts (DS) were found not adjusted (the nut was not torqued) and not locked. Investigation revealed that the LSDS and DS had been changed as re-work action due to pre-installation damage, but production operations (adjustment and locking) were not done afterwards. This AD requires, for certain airplanes, inspection of the LSDS for correct adjustment and locking, and replacement if necessary, and, for certain other airplanes, replacement of each affected DS with a serviceable part, 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.
87-16-05: 87-16-05 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-5687. Applies to Lockheed Model L-188A and L-188C airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To ensure the continuing structural integrity of these airplanes, accomplish the following: A. Within one year after the effective date of this AD, incorporate a revision into the FAA-approved maintenance inspection program which provides no less than the requirements specified for the structurally significant details listed in Section III C. of Lockheed Report No. LR29428, dated January 16, 1984, and Revision A, dated May 14, 1986, or later revision approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. B. Cracks found in the structurally significant details as a result of the supplemental inspections required by paragraph A., above, must be repaired before further flight in accordance with an FAA-approved method.C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a base to accomplish the requirements of this AD. D. Alternate 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. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Order Administration Dept. 65-33, U-33, B-1. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This Amendment becomes effective August 31, 1987.
59-12-07: 59-12-07 WRIGHT: Applies to R-1300-1A Engines Installed in North American T-28A Aircraft. Compliance required by July 1, 1959, or within the next 10 hours of operation, whichever occurs first. There is a possibility that a small number of R-1300-1A engines were released by the military for civil sale and use with crankshafts that had undergone a chrome plating salvage repair operation during the last military overhaul. This operation was found to render the crankshaft unsafe and accordingly was discontinued. Engines with these salvaged crankshafts have a note to this effect in the records and log sheets kept for the engine. No other identification of such engine was provided. A re-examination of the military records of these engines must be made and if any indication is found that the crankshaft has been salvaged by chrome plating it is mandatory that the engine be removed from service consistent with the above stipulated compliance provisions and prior to reuse of the engine in civil aircraft the affected crankshaft must be replaced.
2022-09-09: The FAA is adopting a new airworthiness directive (AD) for all CFM International, S.A. (CFM) LEAP-1A23, LEAP-1A24, LEAP-1A24E1, LEAP- 1A26, LEAP-1A26CJ, LEAP-1A26E1, LEAP-1A29, LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, and LEAP-1A35A model turbofan engines. This AD was prompted by the detection of melt-related freckles in the billet, which may reduce the life of certain compressor rotor stages 6-10 spools, high pressure turbine (HPT) rotor interstage seals, HPT rotor stage 2 disks, low pressure turbine (LPT) stage 1 disks, LPT stage 2 disks, LPT stage 3 disks, and LPT stage 4 disks. This AD requires revising the airworthiness limitations section (ALS) of the applicable CFM LEAP-1A Engine Shop Manual (ESM) and the operator's existing approved continuous airworthiness maintenance program (CAMP) to incorporate reduced life limits for these parts. This AD also requires the removal of certain LPT stage 4 disks identified by serial number (S/N) prior to their new life limits. The FAA is issuing this AD to address the unsafe condition on these products.