Results
2023-04-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A310 series airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
81-17-03: 81-17-03 HILLER AIRCRAFT: Amendment 39-4187. Applies to Model UH-12 all series helicopters, certified in all categories, including Soloy Conversions STCs SH177WE and SH178WE, equipped with Main Transmission P/Ns 23500-3 and 23700-3, -5, -7 or -9. Compliance required as indicated, unless already accomplished. To prevent failure of the main transmission, accomplish the following: (a) Within 25 hours' additional time in service from the effective date of this AD, inspect the main transmission oil filter and chip detector according to paragraph 2 of Hiller Service Notice No. 23-2, dated 28 July 1981. (1) If magnetic chips or a quantity of gold colored flecks are present in the filter bowl, open transmission, inspect planetary system and replace worn parts per Hiller Overhaul Manual, before further flight. (2) If no chips are present on the magnetic chip detector, and only a trace of gold flecks is found in the filter bowl, clean filter and bowl, replace andmake detailed log book entry of the condition. If gold flecks are found after an additional 25 hours' time in service during an inspection per (a) above, replace with like serviceable part(s) per (a)(1), above, before further flight. (b) After completion of (a) (1) or (2) above, inspect, every 25 hours' time in service for turboshaft powered aircraft and 50 hours' time in service for reciprocating engine powered aircraft, according to (a) above. (c) Prior to 1200 hours' time in service or within the next 100 hours, after the effective date of this AD, remove P/N 23586-3 spacers from service and replace with serviceable parts. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate aircraft to a base for the accomplishment of inspections or modifications required by this AD. (e) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineeringand Manufacturing Branch, FAA Western Region. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made apart hereof pursuant to 5 U.S.C. 552(a(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Hiller Aviation, 2075 W. Scranton Avenue, Porterville, California 93257. These documents may also be examined at FAA Western Region Office, 15000 Aviation Boulevard, Hawthorne, California 90261 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at its Headquarters in Washington, D.C. and at FAA Western Region Office. This amendment becomes effective August 24, 1981.
96-26-07: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737 series airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to include procedures that will enable the flight crew to take appropriate action to maintain control of the airplane during an uncommanded yaw or roll condition, and to correct a jammed or restricted flight control condition. This amendment is prompted by an FAA determination that such procedures currently are not defined adequately in the AFM for these airplanes. The actions specified in this AD are intended to ensure that the flight crew is advised of the potential hazard associated with a jammed or restricted flight control condition and of the procedures necessary to address it.
84-07-01: 84-07-01 SHORT BROTHERS LTD: Amendment 39-4835. Applies to SD3-60 airplanes as listed in Short Brothers Service Bulletin SD360-55-02, dated November 1983, certificated in all categories. Compliance is required as indicated unless previously accomplished. To prevent vibration in the event of an elevator tab drive system failure, accomplish the following: A. Within 60 days after the effective date of this AD, modify the elevator and elevator tab mass balance weights in accordance with Short Brothers Ltd. Service Bulletin SD360- 55-02 dated November 1983. B. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. C. 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. This amendment becomes effective April 9, 1984.
2023-05-04: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by reports of ram air turbine (RAT) pump barrel assembly failures, which caused the RAT to fail to provide hydraulic power. The failures were determined to be caused by variations in the bronze metal used during manufacturing, which can result in varying fatigue properties. This AD requires an inspection or records review to determine the part number of the RAT pump and control module (PCM) and of the RAT assembly, and replacement of any RAT PCM or any RAT assembly having certain part numbers. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2014-07-08: We are adopting a new airworthiness directive (AD) for Centrair Model 101, 101A, 101AP, and 101P gliders. 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 structural damage to the fuselage. We are issuing this AD to require actions to address the unsafe condition on these products.
81-18-03: 81-18-03 GENERAL ELECTRIC: Amendment 39-4195. Applies to all fuel controls on General Electric CT58 turboshaft engines. Accomplish in accordance with General Electric Alert Service Bulletin CT58 (A73-71) CEB-261, Revision 1, dated January 9, 1981. 1. Compliance required prior to the first flight of each day or until paragraph 2 is accomplished. a. Check lead lag servo housing attachment screws to make sure there are no signs of looseness and that none are missing or broken. b. Check lock wire to make sure it is not loose. c. Check lead lag servo housing to make sure it is secure. d. If a screw is missing or broken, remove the fuel control and replace it with a serviceable fuel control prior to further flight. NOTE: Signs of lock wire, screw, or lead lag servo housing looseness may be an indication of screw breakage. 2. Compliance required within the next 100 hours time in service after the effective date of this AD. a. For fuel control,S/N 28090 and above, replace screws P/Ns 69691A64, 69691A65, and 69691A69 with P/Ns NAS1352N3H10 AND NAS1352N3H24. b. For fuel control S/N 28089 and below, remove lead lag servo housing screws, perform a counter bore check and replace with the appropriate set of NAS1352N3H screws. NOTE: 1. For fuel controls, A/N 28089 and below, that have previously complied with the original General Electric Service Bulletin, CT58 (A73-71) CEB-261, dated December 24, 1979, compliance with Part 2b of this AD. 2. Replace screws one at a time. Later FAA approved revisions or equivalent means may be approved by the Chief, Engineering and Manufacturing Branch, New England Region. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, New England Region, may adjust the replacement interval specified in this AD to permit compliance at an established inspection period of the operator if the requestcontains substantiating data to justify the increase for that operator. The manufacturer's specifications and procedures identified and described in pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to General Electric Company, 1000 Western Avenue, Lynn, Massachusetts 01910. These documents may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. This amendment becomes effective September 17, 1981.
82-05-04: 82-05-04 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4331. Applies to Model SA360C and SA365C series helicopters certificated in all categories (Airworthiness Docket No. 82-ASW-4). Compliance is required within 30 days after the effective date of this AD. To prevent possible excessive deformation of the pilot's and copilot's seat long slides and resulting tilt of the seats, accomplish the following modification unless already accomplished. (a) Add doublers to the 4 long slides as prescribed in Aerospatiale Dauphin Service Bulletin No. 25.08, dated March 23, 1981, or as prescribed in an equivalent modification approved by Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office. (b) Aircraft may be flown in accordance with FAR 21.197 and 21.199 to a base where the slide doublers may be installed. This amendment becomes effective March 12, 1982.
2004-24-11: The FAA is adopting a new airworthiness directive (AD) for certain Schempp-Hirth (SCHEMPP-HIRTH) Flugzeugbau GmbH Model Duo-Discus gliders. This AD requires you to do a one-time inspection of the bonding of the spar cap and spar web and repair any defective bonding of the spar cap and spar web. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to detect and correct failure of the bonding of the spar cap and spar web, which, if not detected and corrected, could result in an in-flight wing failure.
2014-07-05: We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the butt-joints on the forward fuselage above the passenger door are subject to widespread fatigue damage (WFD). This AD requires inspecting the forward fuselage butt-joints for cracking, repairing any crack, and eventually doing a terminating repair. We are issuing this AD to prevent fatigue cracking of such butt-joints, which could result in reduced structural integrity of the airplane and in- flight decompression of the airplane.
82-16-09: 82-16-09 ENSTROM HELICOPTER CORPORATION: Amendment 39-4429. Applies to all Model F-28A, F-28C, F-28C, F-28F, 280, 280C, and 280F helicopters certificated in all categories. Compliance required as indicated unless already accomplished. To detect wear damage and to prevent possible failure of the main rotor blade grips, accomplish the following: Within the next 100 hours' time in service from the effective date of this AD and thereafter at intervals not to exceed 200 hours' time in service from the last inspection: (a) Remove the main rotor blades per instructions in Section 6 of the maintenance manual. CAUTION: To prevent damage to the Lamiflex bearing, it is important to comply with blade grip placard cautioning against over-rotation of the grip when the pitch link is disconnected. (b) Remove Lamiflex thrust bearing cover assembly (P/N 28-14239). (c) Remove any dirt, grease, or other abrasive material from the space around the Lamiflex thrust bearing. (d) Inspect shim(s) (P/N 28-14293) for alignment/concentricity and clearance. (1) The shim(s) must be concentric with the Lamiflex thrust bearing. (2) Ascertain that the shim(s) do not protrude beyond the outer diameter of the Lamiflex bearing. (e) Inspect blade grip (P/N 28-14279) inner faces for possible wear grooves. (f) If there is shim misalignment, inadequate clearance, or wear grooves in grips, remove: cotter pin (P/N AN 380-4-8), retention nut (P/N 28-14335), shim(s) (P/N 28-14293), and Lamiflex thrust bearing (P/N 28-14310). (g) Inspect blade grips having wear grooves to establish repairability. Grips having a wear-groove depth greater than .125 inch must be replaced. Grips having a wear-groove depth of .125 inch or less are repairable. (h) Repair blade grips(s) by blending out groove(s) smoothly over a circular area having a diameter equal to the wear-groove length. Do not remove excessive material such that the resultant concave blended surface extends beyond the Lamiflex thrust bearing cover (P/N 28- 14239) allowing it to leak. NOTE: To perform this blending operation, it may be necessary to remove the grip from the main rotor retention assembly. Remove the grip(s) per instructions in Section 6 of the maintenance manual. (i) Inspect shim(s) for serviceability. Discard any shim that is deformed out-of- round, has a nonuniform thickness, or was removed from an assembly where grip wear grooves were discovered. (j) Replace discarded shim(s) with new shim(s) of the same nominal thickness. (k) Reassemble main rotor retention assembly and main rotor assembly in accordance with the instructions in Section 6 of the maintenance manual. (l) Any equivalent method of compliance with this AD must be approved by the Chief, Chicago Aircraft Certification Office, Federal Aviation Administration, 2300 Devon Avenue, Des Plaines, Illinois 60018. (m) In accordance with FAR 21.197, flight is permitted to a base where the inspection required by this AD may be accomplished. This amendment becomes effective August 4, 1982.
85-25-02: 85-25-02 KING RADIO CORPORATION: Amendment 39-5218. Applies to Models KFC 200, KFC 150, KAP 150 and KAP 100 autopilot systems utilizing Models KS 177 pitch servo, P/N 065-0050-04 and -012 and/or Model KS 178 roll servo, P/N 065-0051-01 and -02, S/N 2461 and below. These autopilot systems have been installed in accordance with Supplemental Type Certificates (STC) shown in the following table. Some airplane logbooks may not show evidence of the STC number: AUTOPILOT MODEL AIRPLANE MODEL STC AXIS AFFECTED KFC 200 Mooney M20J, M20K SA1771CE-D* pitch and roll KFC 150, KAP 150 Mooney M20J, M20K SA1561CE-D pitch and roll KAP100 Mooney M20J, M20K SA1561CE-D roll KFC 150, KAP 150 SOCATA Model TB-20 SA1785CE-D pitch *NOTE: KFC 200 installations in Mooney Models M20J, S/N 24-1418 and earlier except S/N 24-1368, and M20K, S/N 25-0790 and earlier except S/N 25-0740, airplanes (STCs SA1212CE and SA1464CE) are not affected by this AD. Compliance: Required as indicated unless already accomplished. To prevent loss of primary pitch and/or roll control, accomplish the following: (a) Within the next 5 hours time-in-service or within the next 10 calendar days after the effective date of this AD, whichever occurs first, modify the affected servo actuator(s) to provide for safetying of the cable guard attaching hardware in accordance with King Radio Alert Service Bulletin KS 177/178-3 dated December 4, 1985, as supplemented. (These servos are used on all affected KFC 150, KAP 150, and KAP 100, as well as some KFC 200 ((see NOTE above)) installations.) (b) Aircraft may be flown in accordance with Federal Aviation Regulation (FAR) 21.197 to a location where this AD can be accomplished. (c) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas, 67209. All persons affected by this directive may obtain copies of the documents referred to herein upon request to King Radio Corporation, 400 North Rogers Road, Olathe, Kansas 66062, or the FAA, Rules Docket, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective January 27, 1986, as to all persons except those persons to whom it was made immediately effective by priority letter AD 85-25-02, issued December 11, 1985, which contained this amendment.
2023-05-12: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 767-2C series airplanes. This AD was prompted by arcing on an electrical terminal lug in a certain electrical power panel that caused heat and smoke damage, as a result of a loose power feeder terminal lug connection. This AD requires inspection of each terminal lug on certain electrical power panels for evidence of arcing and/or loose connection and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2004-25-09: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 707 airplanes and Model 720 and 720B series airplanes. This AD requires repetitive inspections of the left and right support ribs for the main landing gear (MLG) trunnion, related investigative/ corrective actions if necessary, and other specified actions. This AD is prompted by reports of in-service cracking of the support ribs for the MLG trunnion. We are issuing this AD to detect and correct corrosion and cracking of the support ribs for the MLG trunnion, which could result in collapse of the MLG.
2023-07-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by several unscheduled PW1500G engine removals due to certain crew alerting system (CAS) messages being displayed, high vibration, or debris found on the magnetic chip collector of a bearing compartment. This AD prohibits dispatch of an airplane with an affected engine having an applicable CAS message displayed, unless the bearing compartment chip collector and oil filter are inspected and any debris found is dispositioned, 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.
84-10-05: 84-10-05 MESSERSCHMITT-BOLKOW-BLOHM-GmbH: Amendment 39-4864. Applies to HFB-320 airplanes as listed in HFB-320 Service Bulletin 57-19 dated February 5, 1982, certificated in all categories. Compliance is required within the next 150 hours time in service or 90 days, whichever occurs first after the effective date of this AD for airplanes with 2400 hours total time in service on the effective date. All others must comply before accumulating 2550 hours time in service, but no later than 90 days after accumulating 2400 hours. To prevent failure of the upper surface wing structure accomplish the following, unless previously accomplished: A. Perform a one-time inspection of the wing upper skin in accordance with the service bulletin. Repair cracks per the manufacturer's instructions. B. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.C. 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. This amendment becomes effective May 29, 1984.
2004-25-12: The FAA is adopting a new airworthiness directive (AD) for all EMBRAER Model EMB-135 and -145 series airplanes. This AD requires a one-time inspection of each passenger service unit (PSU) to determine the serial number of the printed circuit board (PCB) installed in each PSU, replacement of the PCB if necessary, related investigative actions, and other specified actions. This AD is prompted by reports that PSUs on two airplanes emitted smoke. We are issuing this AD to prevent failure of a PSU, which could result in smoke or fire in the airplane's passenger cabin.
85-08-08: 85-08-08 McCAULEY ACCESSORY DIVISION: Amendment 39-5046. Applies to the following Model D3A32C90 series propellers installed on, but not limited to, Bellanca 17-30, 17- 30A; Cessna A185E, F, A188B, P206A, TP206A, U206A, B, C, D, E, F, TU206A, B, C, D, E, F, 207, 207A, T207; and Navion A thru H: D3A32C90, D3A32C90-A, -B, -C, -J, -K, -L, -BLM, - CLM, -JLM, -KLM, -LM, and -M. Compliance is required as indicated unless already accomplished. To detect propeller hub cracks and prevent possible failure, accomplish the following: (a) Propeller models D3A32C90, D3A32C90-A, -B, -C, -J, -K, and -L: Within the next 50 hours time in service after the effective date of this AD or prior to accumulating 1200 hours total time in service, whichever occurs later, replace hubs with shot peened hubs and modify to the oil filled hub configuration in accordance with Supplement 1 to McCauley Service Manual No. 720415 dated January 7, 1977, or FAA approved equivalent. (b) Propeller models D3A32C90-BLM, -JLM, -KLM, -LM, and -M: Within the next 50 hours time in service after the effective date of this AD or prior to accumulating 1200 hours total time in service, whichever occurs later, inspect the hub in accordance with McCauley Service Letter 1974-3 dated March 29, 1974, or FAA approved equivalent, end modify to the oil filled hub configuration in accordance with Supplement 1 to McCauley Service Manual No. 720415 dated January 7, 1977, or FAA approved equivalent. (c) Propellers with unknown service histories must comply with paragraphs (a) or (b), as applicable, within the next 50 hours time in service after the effective date of this AD. (d) Modified propellers showing signs of red dyed oil leakage must be removed from service and replaced with a serviceable propeller. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Chicago Aircraft Certification Office, ACE-140C, 2300 East Devon Avenue, Des Plaines, Illinois 60018, telephone (312) 694-7130. The manufacturer's specifications and procedures identified and described in this directive are 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 these documents from the manufacturer may obtain copies upon request to McCauley Accessory Division, Cessna Aircraft Company, 3535 McCauley Drive, P.O. Box 430, Vandalia, Ohio 45377. These documents also may be examined at the Office of Regional Counsel, FAA, Attn: Rules Docket No. 85-ANE-1, 12 New England Executive Park, Burlington, Massachusetts 01803, weekdays, except Federal holidays, between 8:00 a.m. and 4:30 p.m. This amendment becomes effective May 13, 1985.
2014-04-10: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, -300 and -200 Freighter series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by a report that an airplane equipped with Angle of Attack (AOA) sensors installed with conic plates recently experienced blockage of all sensors during climb, leading to autopilot disconnection and activation of the alpha protection (Alpha Prot) when Mach number was increased. This AD requires, for certain airplanes, revising the airplane flight manual (AFM) to advise the flightcrew of emergency procedures for addressing AOA sensor blockage. This AD also requires replacing the AOA sensor conic plates with AOA sensor flat plates, which is a terminating action for the AFM revision. We are issuing this AD to prevent reduced control of the airplane.
2023-03-20: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-400, -400D, and -400F series airplanes. This AD was prompted by the FAA's analysis of the Model 747 airplane fuel system reviews conducted by the manufacturer, and by the determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
86-10-08: 86-10-08 FAIRCHILD: Amendment 39-5315. Applies to Models SA226 and SA227 airplanes (Serial Numbers (S/N) SA226-T, S/N T201 through T275, T277 through T291; SA226-T(B), S/N T(B)276, T(B)292 through T(B)417; SA226-AT, S/N AT001 through AT074; SA226-TC, S/N TC201 through TC419; SA227-TT, S/N TT421 through TT555; SA227-AT, S/N AT423 through AT631B; SA227-AC, S/N AC406, AC415, AC416, and AC420 through AC632) airplanes certificated in any category. Compliance: Required within the next 200 hours time-in-service or the next 30 calendar days, whichever comes first, after the effective date of this AD, unless already accomplished. To prevent the elevator gust lock from engaging in flight, accomplish the following: (a) Remove the elevator gust lock system components and install the alternate elevator gust lock and associated hardware in accordance with the instructions in Fairchild Aircraft Corporation Service Bulletin (S/B) 226-27-041 revised February 18, 1986, for the SA226 airplane models, or S/B 227-27-016 revised February 18, 1986, for the SA227 airplane models. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance may be used if approved by the Manager of the Airplane Certification Branch, ASW-150, Southwest Regional Office, FAA, Fort Worth, Texas 76101; telephone (817) 877-2070. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Fairchild Aircraft Corporation, Post Office Box 32486, San Antonio, Texas 78284, or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on May 28, 1986.
2000-05-14: This amendment supersedes two existing airworthiness directives (AD's), applicable to AlliedSignal Inc. ALF502 and LF507 series turbofan engines, that require rework or replacement of No. 4 and 5 bearing oil system hardware, initial and repetitive inspections of the oil system, optional installation of an improved oil filter bypass valve, and repetitive inspection of No. 4 and 5 bearing oil inlet tube, to ensure the integrity of the reduction gear system and overspeed protection system. This action would require replacement of the existing power turbine bearing housing assembly with a new, improved power turbine bearing housing assembly, and installation of a reworked or modified fourth turbine rotor disk assembly as a part of a design change to the new No. 4 bearing configuration that eliminates the requirement for repetitive inspections of oil system and No. 4 and 5 bearing oil inlet tube assembly. This amendment is prompted by one report of a contained power turbine rotor shaft separation forward of the Stage 4 low pressure turbine (LPT) rotor on an AlliedSignal Inc. ALF502R-5 engine. The LPT failure was caused by improper inspection of the engine oil system required by AD 97-05-11 R1. The actions specified by this AD are intended to prevent a No. 4 and 5 duplex bearing failure, which can result in a Stage 4 LPT rotor failure, an uncontained engine failure, and damage to the airplane.
2004-25-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-300 and -400ER series airplanes, that requires replacing the tie rods for the waste tank cradle, related investigative actions, corrective actions, and special retrofit action if necessary. This action is necessary to prevent possible failure of the main deck floor stanchions and consequent collapse of the main floor during an emergency landing, which could result in passenger injury and impede passenger evacuation from the airplane. This action is intended to address the identified unsafe condition.
2023-04-17: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-8 and 737-9 airplanes, and certain Model 737- 600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by reports of damage to the auxiliary power unit (APU) fuel line shroud located aft of the aft cargo area; investigation revealed that the placement of the pressure switch wire clamp assembly and its fastener allowed interference of the fastener against the APU fuel line shroud. This AD requires inspecting the APU fuel line shroud for damage, inspecting the pressure switch wire clamp for correct bolt orientation and horizontal distance from the APU fuel line shroud, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
63-04-02: 63-04-02 HILLER: Amdt. 535 Part 507 Federal Register February 12, 1963. Applies to All UH-12, UH-12A, UH-12B, and UH-12C Helicopters with P/N's 55008 and 55012 Tail Rotor Blades. Compliance required as indicated. To prevent failures of P/N's 55008 and 55012 tail rotor blades the following shall be accomplished: (a) Within the next 50 hours' time in service, unless already accomplished: (1) Replace all P/N's 55008 and 55012 tail rotor blades with P/N 55064 tail rotor blades in accordance with Hiller Service Bulletin No. 80. (2) On all helicopters equipped with the large diameter (1.375 inch) spar stabilizer, P/N 37003, install the stabilizer strut in accordance with Hiller Service Bulletin No. 75B. (3) On all helicopters equipped with the small diameter (1 inch) spar stabilizer, P/N 37001, install the stabilizer strut in accordance with Hiller Service Bulletin No. 83. (b) Until replacement with the P/N 55064 blade is accomplished, visually inspect the P/N's 55008 and 55012 tail rotor blades prior to each flight and refueling. The outer surface of the skin on both sides of the blade shall be inspected for cracks in the area of the outer tension torsion bar retention bolt and the adjacent rivet pattern through the outer end of the root fitting. Paint must be removed from the areas to facilitate inspection. Any blades found to be cracked must be removed and replaced with P/N 55064 blades prior to further flight. (Hiller Service Bulletins Nos. 75B, 80, and 83 pertain to this subject.) This supersedes AD 58-24-02. This directive effective February 12, 1963.