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75-11-04: 75-11-04 UNITED AIRCRAFT: Amendment 39-2207. Applies to all United Aircraft of Canada Limited PT6A-6, -6A, -6B, -6/C20, -20, -20A, -20B, -27, -28, -34 series turbo-prop engines and PT6B-9 turboshaft engines, incorporating an unmodified power turbine shaft housing assembly part number 3010548. Compliance required as indicated. To aid the early detection, and thereby prevention of PT6A or PT6B engine distress especially in the reduction gearbox of engines incorporating power turbine shaft housing assembly part number 3010548 yet unmodified, accomplish the following: For the PT6A-20, -20A, -20B, -6/C20 engines affected, compliance required within the next fifty hours in service after effective date of this AD. For the PT6A-6, -6A, -6B, -27, -28, -34 and PT6B-9 engines affected, compliance required at the next engine overhaul shop visit, but no later than 3500 hours in service after effective date of this AD. 1. Unless previously accomplished, remove the reduction gearbox oil drain plug part number MS9015-08 and discard the preformed packing part number MS9388-115. Install magnetic chip detector part number 3014794 or 3019373 with a new preformed packing part number MS9388-115 and torque to 45 to 55 lb. in. and lockwire. Install cap part number MS25043-12D or connector part number MS3106-R-12S-3S with connected electrical wiring suitably supported and leading out to a more accessible area within the engine nacelle enclosure. 2. Within the next twenty-five hours in service after installation of the magnetic chip detector and every twenty-five hours in service thereafter, check magnetic chip detector for electrical continuity using any utility ohmmeter. If a resistance of 100 ohms or less is indicated, remove and clean the magnetic chip detector, and inspect the main engine oil filter in accordance with AD 75-06-01. Aircraft may be flown to a base for performance of maintenance required by this AD per FAR 21.197 or FAR 21.199. Upon submission of substantiating data through an FAA maintenance inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection times specified in this Airworthiness Directive. This amendment is effective May 20, 1975.
87-03-06 R1: 87-03-06 R1 BEECH: Amendment 39-5513 as amended by Amendment 39-5557. Applies to Model 99, 99A, A99A, B99 and C99 (Serial Numbers U-1 thru U-240); 100 and A100 (Serial Numbers B-1 thru B-247); and B100 (Serial Numbers BE-1 thru BE-137), airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To detect looseness of the elevator outboard hinge attachment to the stabilizer and prevent loss of integrity of the hinge attachment, accomplish the following: (a) Upon the accumulation of 1000 hours total time-in-service (TIS) or within the next 100 hours TIS after the effective date of this AD, whichever comes later, and thereafter at intervals not to exceed 100 hours TIS for Model 99 Series or 150 hours TIS for Model 100 Series airplanes, visually inspect each elevator outboard hinge attachment as follows: (1) Hold the elevator steady at the trailing edge. (2) Push up and down onthe elevator leading edge and visually inspect for movement of the elevator hinge bearing bracket. (b) If movement of the hinge bearing bracket is detected in (a)(2) above, prior to further flight, replace the hinge attach rivets with bolts in accordance with the instructions in Beech Service Bulletin No. 2132, revised December 1986. (c) Unless previously required by paragraph (b) of this AD, on all airplanes with more than 1000 hours total TIS, within the next 600 hours TIS after the initial inspection required by paragraph (a) of this AD, install bolts in place of the four hinge attach rivets in accordance with the instructions in Beech Service Bulletin No. 2132 revised December 1986. (d) The repetitive inspections required by paragraph (a) of this AD may be discontinued after bolts have been installed per paragraphs (b) or (c). (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (f) The repetitive inspection intervals, required by this AD may be adjusted up to 10 percent of the specified interval so as to coincide with other scheduled maintenance. (g) 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, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Beech Aircraft Corporation, 9709 East Central, P.O. Box 85, Wichita, Kansas 67201; or the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Amendment 39-5513 became effective on February 20, 1987. This amendment, 39-5557, becomes effective March 12, 1987.
2017-10-20: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Models PA-31, PA-31-300, PA-31-325, and PA-31-350 airplanes. This AD was prompted by fatigue cracking in the fuselage station (FS) 332.00 bulkhead common to the horizontal stabilizer front spar attachment. This AD requires repetitive inspections to detect cracks in the bulkhead and any necessary repairs. This AD also provides an optional modification if no cracks are found that will greatly reduce the likelihood of the specified cracks. We are issuing this AD to correct the unsafe condition on these products.
2017-09-09: We are adopting a new airworthiness directive (AD) for certain Zodiac Seats California LLC seating systems. This AD was prompted by a determination that the affected seating systems may cause serious injury to the occupant during forward impacts when subjected to certain inertia forces. This AD requires removing affected seating systems. We are issuing this AD to address the unsafe condition on these products.
2001-22-16: This amendment supersedes Airworthiness Directive (AD) 95-02-18, which applies to certain Raytheon Aircraft Company (Raytheon) Beech Models 1900, 1900C (C-12J), and 1900D airplanes. AD 95-02-18 requires you to repetitively inspect the engine truss assemblies for cracks, repair or replace any cracked engine truss assembly, and install reinforcement doublers. This AD requires engine truss assembly replacement, periodic inspections and replacements, and the eventual incorporation of a cowling support installation kit as terminating action. The repetitive inspections of AD 95-02-18 will be retained until mandatory engine truss assembly replacement. This AD is the result of continued reports of fatigue cracks found on engine trusses on airplanes in compliance with AD 95-02-18. The actions specified by this AD are intended to detect and correct cracked engine truss assemblies, which could result in failure of the engine truss assembly and consequent loss of airplane control.
75-09-13: 75-09-13 TELEDYNE CONTINENTAL MOTORS: Amendment 39-2178. Applies to the following Teledyne Continental Motors Model engines manufactured prior to August 10, 1973, installed on, but not necessarily limited to Cessna T-310, 320, 340, 401, 402, 411, 414 and 421 series, Rockwell International Model Aero Commander 685 and Beech V35-TC, V35A-TC and V35B-TC series airplanes: New Engine Remanufactured Engine Engine Model Serial Number Serial Number TSIO-470-B Applies to all S/N's 100080 and below TSIO-470-C Applies to all S/N's 108534 and below TSIO-470-D Applies to all S/N's 138544 and below TSIO-520-B 500018 and below *176191 and below TSIO-520-D 505001 and below *180029 and below TSIO-520-E 502125 and below 182395 and below GTSIO-520-C 602001 and below 155370 and below GTSIO-520-D 601005 and below 219161 and below GTSIO-520-H *600137 and below 218046 and below GTSIO-520-F 603028 and below 224203 and below Model Airplane on Airplane Engine Model Which Installed Serial Numbers TSIO-520-J Cessna 414 00489 and below TSIO-520-K Cessna 340 00318 and below *The following individual engines are not affected by this AD: TSIO-520-B, S/N's 176170, 176185, 176186, 176187; TSIO-520-D, S/N 180028; GTSIO-520-H, S/N 600119. Compliance required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. (1) To detect cracked turbocharger oil inlet adapters inspect the turbocharger oil inlet adapter located at the turbocharger center housing for cracks and/or oil seepage. If there is evidence of oil leakage or cracks, the adapter must be replaced with steel adapter TCM P/N 640793 or Cessna P/N 5655204-2. When replacing the aluminum adapter with the steel adapter on the following model airplanes, the oil fitting which mates with the turbocharger oil inlet adapter must be replaced, unless already accomplished, with the appropriate steel fitting listedbelow. Applicable Replacement Make Model Airplane S/N's Steel Fitting Beech V35-TC All AN 816-6 V35A-TC AN 816-6 V35B-TC AN 816-6 Cessna 320-D, -E All MS20823-6 320-F 320F0001 thru MS20823-6 320F0034 401 & 402 0001 thru 0155 MS20823-6 (2) If there is no evidence of cracks or oil seepage, inspect at intervals not to exceed 25 hours' time in service from the last inspection until replaced with turbocharger oil inlet adapter TCM P/N 640793 or Cessna P/N 5655204-2. Replacement of the aluminum adapter TCM P/N 628675 or Cessna P/N 5655204-1 with steel adapter P/N 640793 or Cessna P/N 5655204-2 or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, is required within one year from the effective date of this AD. This amendment becomes effective April 24, 1975.
84-12-03: 84-12-03 CASA: Amendment 39-4880. Applies to CASA Model 212 series airplanes, certificated in all categories, as indicated in the applicability statement of each of the following service bulletins. Compliance is required within the time interval specified in each of the following paragraphs after the effective date of this AD, unless already accomplished: A. To prevent damage to the D.C. generating circuit, within the next 200 hours time in service, install a new 5 amp fuse and replace the existing 50 amp fuse with a 35 amp fuse in accordance with CASA Service Bulletin 212-24-22 dated November 7, 1979. B. To prevent the loss of rudder and elevator control, within the next 200 hours time in service, replace the rudder and elevator-to-shaft attach fittings with new design fittings in accordance with CASA Service Bulletin 212-27-12, Revision 3, dated June 12, 1980. C. To prevent damage to the wing flap actuation system, within the next 200 hours time in service, replace the hydraulic cylinder with a new design cylinder in accordance with CASA Service Bulletin 212-27-13 dated December 17, 1980. D. To prevent interference with flight controls, within the next 200 hours time in service, modify the flight deck floor structure in accordance with CASA Service Bulletin 212-27- 14 dated November 18, 1980. E. To prevent damage to the wing flap hydraulic system, within the next 200 hours time in service, replace the hydraulic system relief valve with a new design valve in accordance with CASA Service Bulletin 212-27-15, Revision 1, dated November 30, 1981. F. To prevent bearing failures, within the next 200 hours time in service, replace the existing wing flap control hinge bearings with a stainless steel bearing in accordance with CASA Service Bulletin 212-27-19 dated July 1, 1982. G. To prevent relative displacement between the elevator shaft support fittings and the elevator shaft, within the next 500 hours time in service, install safety rings in accordance with CASA Service Bulletin 212-27-23 dated October 7, 1982. H. To prevent the risk of a fire from fuel collecting forward of the nacelle fire wall, within the next 500 hours time in service, install electric fuel shutoff valves in accordance with CASA Service Bulletin 212-28-11, Revision 1, dated September 2, 1981. I. To ensure proper joint strength, within the next 200 hours time in service, replace the existing nuts in the outer wing-to-center section splice in accordance with CASA Service Bulletin 212-51-01 dated July 7, 1981. J. To ensure proper fitting, within the next 200 hours time in service, replace the existing mount bolts with longer bolts in accordance with CASA Service Bulletin 212-51-02 dated September 22, 1981. K. To ensure proper rudder travel, within the next 200 hours time in service, replace the rudder hinge fittings with new fittings in accordance with CASA Service Bulletin 212-55-07 dated July 1, 1982. L. To prevent damage to the wing flap structure, within the next 200 hours time in service, retorque the attachment fitting fasteners in accordance with CASA Service Bulletin 212- 57-12 dated September 22, 1981. M. To ensure engine fire wall integrity, within the next 200 hours time in service, reduce the clearance space between the engine screen control rods and the firewall at the penetration point in accordance with CASA Service Bulletin 212-73-03, Revision 1, dated July 14, 1982. N. 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. O. 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 July 23, 1984.
2001-22-14: This amendment adopts a new airworthiness directive (AD) that applies to certain Overland Aviation Services (OAS) fire extinguishing system bottle cartridges that were distributed during a certain time period and are installed on aircraft. This AD requires you to remove from service any of these fire extinguishing system bottle cartridges. This AD is the result of several incidents where the fire extinguishing system bottle cartridges activated with excessive energetic force. In one instance, the discharge valve outlet screen fractured and the screen material went through the distribution manifold. The actions specified by this AD are intended to prevent damage to fire extinguishing system components caused by a fire extinguishing system bottle cartridge activating with excessive energetic force, which could result in the fire extinguishing system operating improperly.
2017-11-01: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, and -200C series airplanes. This AD is intended to complete certain mandated programs to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This AD requires various repetitive inspections for cracking of certain lugs on the rear spar and horizontal stabilizer, related investigative and corrective actions if necessary, and replacement of the center section rear spar upper chord as applicable. We are issuing this AD to address the unsafe condition on these products.
2010-26-02: We are superseding an existing 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: To prevent possible in-flight failure of the vertical stabiliser, leading to loss of control of the aircraft * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2025-12-06: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS332L1 helicopters. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the airworthiness limitations section (ALS) of the existing maintenance manual (MM) or instructions for continued airworthiness (ICAs) and the existing approved maintenance or inspection program, as applicable. The FAA is issuing this AD to address the unsafe condition on these products.
2017-09-03: We are superseding Airworthiness Directive (AD) 2013-03-12 for all Dassault Aviation Model MYSTERE-FALCON 50 airplanes. AD 2013-03-12 required revising the maintenance program to incorporate certain maintenance requirements and airworthiness limitations. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new or revised maintenance requirements and airworthiness limitations. This AD was prompted by issuance of a revision to the airplane maintenance manual (AMM) that introduces new or more restrictive maintenance requirements and/or airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2010-25-05: 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: Due to manufacturing problems of BR700-710 HP stage 1 and 2 turbine discs it was necessary to re-calculate the Declared Safe Cyclic Life (DSCL) for all BR700-710 HP turbine discs. The analysis concluded that it is required to reduce the approved life limits for the HP turbine disc part numbers that are listed in Table 1 and Table 2 of this AD (MCAI). Exceeding the revised approved life limits could potentially result in non-contained disc failure. We are issuing this AD to prevent-failure of the high-pressure turbine (HPT) stage 1 and stage 2 discs, uncontained engine failure, and damage to the airplane.
2001-22-11: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 737-600, -700, and -800 series airplanes, that currently requires an inspection of the power distribution panels (PDP) to verify proper installation of the power feeder terminals and associated hardware, and corrective actions, if necessary. The existing AD also requires repetitive torque checks of the terminal attachment screws. This amendment adds a requirement for repetitive replacement of the PDP rigid bus assembly with a new assembly and provides an optional terminating action for the repetitive torque checks and the repetitive replacement of the PDP rigid bus assembly. This amendment is prompted by reports of loss of electrical power from the engine-driven generators or the auxiliary power unit due to overheating, melting, and subsequent failure of the power feeder terminals at the PDPs. The actions specified by this AD are intended to prevent such conditions, which could result in increased risk of fire and the loss of electrical power from the associated alternating current power source.
2001-22-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes; and certain Boeing Model 747, 757, 767, and 777 series airplanes; that requires replacing the rudder pedal pushrod fasteners for both the captain's and first officer's pedal assemblies with new, improved fasteners. This action is necessary to prevent loss of rudder control due to improperly torqued fasteners that connect the pushrod to the rudder pedal assembly, which could result in loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
47-14-01: 47-14-01 BELLANCA: (Was Mandatory Note 5 of AD-773-5.) Applies to Models 14- 13, 14-13-2 Serial Numbers 1060 to 1409, Inclusive. Compliance required prior to June 1, 1947. Replace the aluminum alloy inboard flap hinge brackets with X4130 steel brackets, Bellanca P/N 7998-1. Bellanca Service Bulletin No. 7 dated January 14, 1947, covers this same subject.)
2023-01-08: The FAA is adopting a new airworthiness directive (AD) for certain Continental Aerospace Technologies GmbH TAE 125-02-99 and TAE 125-02-114 model reciprocating engines. This AD was prompted by manufacturer reports of fractured main bearing studs. This AD requires the removal and replacement of certain main bearing studs. The FAA is issuing this AD to address the unsafe condition on these products.
2017-09-06: We are superseding Airworthiness Directive (AD) 2015-15-03 for all General Electric Company (GE) GEnx turbofan engine models. AD 2015- 15-03 precluded the use of certain electronic engine control (EEC) full authority digital engine control (FADEC) software on GEnx turbofan engines. This AD requires removing a specific part and replacing it with a part eligible for installation and specifying the EEC FADEC software version for the affected GEnx turbofan engines. This AD was prompted by GE implementing final design changes that remove the unsafe condition. We are issuing this AD to correct the unsafe condition on these products.
2001-22-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 series airplanes, that requires repetitive eddy current inspections for cracking of the main landing gear (MLG) main fittings, and replacement with a new or serviceable MLG, if necessary. This action also requires servicing the MLG shock struts; inspecting the MLG shock struts for nitrogen pressure, visible chrome dimension, and oil leakage; and performing corrective actions, if necessary. The actions specified by this AD are intended to prevent failure of the MLG main fitting, which could result in collapse of the MLG upon landing. This action is intended to address the identified unsafe condition.
2017-08-12: We are adopting a new airworthiness directive (AD) for GROB Aircraft AG Models GROB G 109 and GROB G 109B 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 broken pivots of the tail wheel mounting bracket resulting from corrosion and damage due to wear. We are issuing this AD to require actions to address the unsafe condition on these products.
2001-22-08: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 series airplanes, that requires replacing the main landing gear (MLG) torque link dampers with modified and reidentified dampers. This action is necessary to prevent degradation of the dampers, which could result in MLG high amplitude oscillation in a lateral torsional mode, and consequent MLG damage or separation of the MLG from the airplane. This action is intended to address the identified unsafe condition.
2001-21-07: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that currently requires, for certain airplanes, revising the Airplane Flight Manual, and, for all airplanes, performing repetitive inspections for wear or damage of the inlet check valves and inlet adapters of the override/jettison pumps, and corrective actions, if necessary. This amendment applies to fewer airplanes than the existing AD and requires rework of certain components, which ends the repetitive inspection requirement. These actions are necessary to ensure that the flight crew is advised of the hazards of dry operation of the override/jettison pumps of the center wing fuel tank, and to prevent wear or damage to the inlet check valves and inlet adapters of the override/jettison pumps, which could result in a fire or explosion in the fuel tank during dry (no fuel) operation. This action is intended to address the identified unsafe condition. \n\n\tTheincorporation by reference of Boeing Alert Service Bulletin 747-28A2212, Revision 2, dated May 14, 1998, as listed in the regulations, was approved previously by the Director of the Federal Register as of August 24, 1998 (63 FR 42210, August 7, 1998).
2017-08-09: We are adopting a new airworthiness directive (AD) for DG Flugzeugbau GmbH Model DG-500MB gliders that are equipped with a Solo 2625 02 engine modified with a fuel injection system following the instructions of Solo Kleinmotoren GmbH Technische Mitteilung (TM)/ Service Bulletin (SB) 4600-3 ``Fuel Injection System'' and identified as Solo 2625 02i. 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 possible in-flight engine shut-down and engine fire due to failure of the connecting stud for the two fuel injector mounts of the engine redundancy system. We are issuing this AD to require actions to address the unsafe condition on these products.
64-13-04: 64-13-04 WALTER KIDDE: Amdt. 749 Part 507 Federal Register June 18, 1964. Applies to Aircraft Incorporating Inflatable Escape Slides or Life Rafts Utilizing Walter Kidde Series 1 Actuating Valve P/N's 891771, 891178, 891178-01, 890881-01, 890683, and 890881 Which Have Had Their Seat Assemblies, Walter Kidde P/N 801906 Replaced or Modified With Parts Purchased Since April 1, 1963, and All Series 2 Actuating Valve P/N's 891771-01, 891178-02, 890881-02. Compliance required as indicated. During recent demonstrations of inflatable escape slides and life rafts, certain Walter Kidde inflation valves did not provide adequate inflation and required excessive pull forces to actuate the valve. Effective July 1, 1964, all Walter Kidde valves specified herein which are used in escape slides or life rafts installed in civil aircraft shall be modified as follows or in accordance with an FAA Western Region, Aircraft Engineering Division, approved equivalent: (a) Remove seat assembly Walter Kidde P/N 801906 and install a new nylon seat assembly Walter Kidde P/N 843045. (b) Functionally test the valve by installing it, along with anti-recoil fitting Walter Kidde P/N 6531, on an appropriately charged bottle and discharging the bottle. During this functional check, the pull load required to actuate the valve is to be determined and is not to exceed 30 pounds. Do not install valves which require a pull in excess of 30 pounds. (NOTE: If Walter Kidde P/N 6531 anti-recoil fitting is not available, the bottle should be adequately constrained.) (c) Reidentify the reworked valves in accordance with Walter Kidde Service Bulletin No. 168 dated May 8, 1964. NOTE: Walter Kidde valve P/N's 891771, 891178, 891178-01, 890881-01, 890683 and 890881 which have not had seat assemblies replaced or modified with parts purchased since April 1, 1963, are not affected by the provisions of this AD. (Walter Kidde Company Service Bulletin No. 168 dated May 8, 1964, withAddendum No. 1 dated May 15, 1964, and Addendum No. 2 dated June 2, 1964, and Boeing Alert Service Bulletins Nos. 2000 dated May 11, 1964, and 2000A dated May 15, 1964, cover this same subject. Note that where the applicability specified in these Bulletins is not the same as that in the AD, the applicability specified in the AD applies.) This directive effective June 18, 1964.
2001-22-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Short Brothers Model SD3 series airplanes, that requires an inspection to find discrepancies of the hydraulic pipelines to the 7P panel and adjacent electrical wiring harnesses, and corrective action, if necessary. This action is necessary to find and fix such discrepancies, which could result in electrical arcing between the hydraulic lines and adjacent wiring, and a potential fire. This action is intended to address the identified unsafe condition.