Results
2001-23-05: This amendment adopts a new airworthiness directive (AD) that applies to all SOCATA--Groupe Aerospatiale (SOCATA) Models TB 9, TB 10, TB 20, TB 21, and TB 200 airplanes that do not have factory Modification 165, any edition, incorporated on the front seats. This AD requires you to modify the front seats that have solid metal seat pans. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to eliminate the potential for the front seats to inadvertently unlock from their fixed positions. Such uncontrolled movement could prevent the pilot from making the necessary flight maneuvers to control the airplane.
2023-02-12: The FAA is adopting a new airworthiness directive (AD) for certain Continental Aerospace Technologies, Inc. (Continental) GTSIO- 520, IO-470, IO-520, IO-550, IOF-550, LIO-470, LIO-520, LTSIO-520, O- 470, TSIO-470, TSIO-520, TSIO-550, TSIOF-550, and TSIOL-550 model reciprocating engines with a certain Superior Air Parts, Inc. (SAP) cylinder assembly or intake valve installed. The affected cylinder assemblies and intake valves are installed as a replacement part under parts manufacturer approval (PMA) on certain affected Continental engines. This AD was prompted by three intake valve failures on reciprocating engines that resulted in engine damage and emergency landing or aborted takeoff. This AD requires replacement of the affected engine intake valve. The FAA is issuing this AD to address the unsafe condition on these products.
2025-12-04: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A11 airplanes. This AD was prompted by an investigation of an in-service hydraulic fluid leakage event that indicated the potential use of an uncalibrated torque wrench when tightening the union fittings at the pressure and return interfaces of all three rudder hydraulic power control units (PCUs). This AD requires properly torquing the rudder PCU hydraulic fittings and applying the torque seal on the rudder PCU hydraulic fittings. The FAA is issuing this AD to address the unsafe condition on these products.
2001-23-04: This amendment adopts a new airworthiness directive (AD) that applies to all SOCATA--Groupe Aerospatiale (SOCATA) Models TB 9, TB 10, TB 20, TB 21, and TB 200 airplanes. This AD requires you to repetitively inspect the lower rudder hinge fitting for cracks. This AD also requires you to repair any crack found in accordance with a repair scheme obtained from the manufacturer through the Federal Aviation Administration (FAA). This AD is the result mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to detect and correct fatigue cracks in the lower rudder hinge fitting. This condition could cause the lower rudder to detach from the control linkage with consequent loss of control of the airplane.
88-12-11: 88-12-11 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-5896. Applies to all SNIAS Alouette/Lama Model SA 315B, SE 3160, SA 316B, SA 316C, SA 3180, SA 318B, SA 318C, and SA 319B helicopters, equipped with main gearbox P/N 3160S62-00-000 or P/N 319A62-00-000; freewheel P/N 3160S60-10-000; and clutch P/N 3160S63-20-000, P/N 3180S63-10-000, or P/N 319A63-00-000, certificated in all categories. Compliance is required as indicated (unless already accomplished). To prevent failures of the main drive shaft and freewheel assemblies by ensuring proper operation of the main gearbox oil jet, P/N 3160A62-01-002, and to improve sealing at the freewheel attachment joints, accomplish the following: (a) Within the next 100 hours time in service or upon observance of a freewheel coupling and seal oil leak, whichever is earlier, comply with Alouette Service Bulletin 65-81, Issue 2, dated February 14, 1979, or Lama Service Bulletin 65-06, Issue 2, dated February 14,1979, as applicable. (b) After compliance with paragraph (a) of this AD, accomplish the following: After the first flight following the installation of a new or overhauled main gearbox, then every 100 hours time in service, comply with section 1(c) of Alouette Service Bulletin 05-65, dated February 14, 1979, or Lama Service Bulletin 05-14, dated February 14, 1979, as applicable. NOTE: Service Bulletin 05-65 supersedes Service Bulletin 05-42, dated November 10, 1971, and Service Bulletin 05-14 supersedes Service Bulletin 05-01, dated November 10, 1971. (c) An alternate method of compliance, which provides an equivalent level of safety, may be used when approved by the Manager, Aircraft Certification Division, Department of Transportation, Federal Aviation Administration, Fort Worth, Texas 76193-0100, or by the Manager, Brussels Aircraft Certification Office, AEU-100, c/o American Embassy, Brussels, Belgium, APO NY 09667. The procedures shall be done in accordancewith Allouette Service Bulletin 65-81, Issue 2, dated February 14, 1979, or Lama Service Bulletin 65-06, Issue 2, dated February 14, 1979, as applicable. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Aerospatiale Helicopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005. Copies may be inspected in the Rules Docket, Office of Regional Counsel, FAA, Southwest Region, 4400 Blue Mound Road, Building 3B, Room 158, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L Street, NW., Room 8401, Washington, D.C. This amendment supersedes AD 73-13-02, Amendment 39-1666, as amended by Amendment 39-2527. This amendment, 39-5896, becomes effective May 20, 1988.
2017-10-15: We are adopting a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, CN- 235-300, and C-295 airplanes. This AD was prompted by a reported inability to extend the external handle of the emergency door from its recess due to a jammed spring mechanism. This AD requires a one-time functional check of each emergency door handle, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2001-23-07: This amendment adopts a new airworthiness directive (AD) that applies to certain Reims Aviation S.A. (Reims) Model F406 airplanes. This AD requires you to repetitively inspect the canted rib upper cap in the center wing carry-through area for cracks, and, if cracks are found, immediately repair the cracks or modify this area depending on the extent of any cracks found. This AD also requires you to modify the canted rib upper cap at a certain time period as terminating action for the repetitive inspections. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to detect and correct cracks in the canted rib upper cap in the center wing carry-through area, which could result in structural failure of the wing with possible loss of control of the airplane.
94-20-02: 94-20-02 AIRBUS INDUSTRIE: Amendment 39-9030. Docket 94-NM-121-AD. Applicability: All Model A320 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent severely reduced controllability of the airplane during approach under certain conditions, accomplish the following: (a) Within 10 days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the information specified in Airbus A320/A321 Flight Manual Temporary Revision 9.99.99/20, dated June 14, 1994. NOTE 1: This may be accomplished by inserting a copy of Airbus A320/A321 Flight Manual Temporary Revision 9.99.99/20, dated June 14, 1994, in the AFM. When this temporary revision has been incorporated in the general revisions of the AFM, the general revisions may be inserted in the AFM, provided the information contained in the general revisions is identical to that specified in Temporary Revision 9.99.99/20. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Operations Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The revision to the AFM shall be done in accordance with Airbus A320/A321 Flight Manual TemporaryRevision 9.99.99/20, dated June 14, 1994. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on October 7, 1994.
48-11-05: 48-11-05 BELL: Applies to Model 47B Series. Compliance required at next 25-hour inspection. To provide increased strength, install main rotor drag brace, Bell P/N 47-110-146-2, in place of the existing part. (Bell Service Bulletin 47C31 also covers this subject.)
2017-10-17: We are superseding Airworthiness Directive (AD) 2014-16-19 for all Airbus Model A330-200 Freighter, -200, and -300 series airplanes. AD 2014-16-19 required revision of the maintenance or inspection program to include certain fuel airworthiness limitations. This new AD requires revision of the maintenance or inspection program, as applicable, to include new fuel airworthiness limitations. This new AD also removes certain airplanes from the applicability of AD 2014-16-19. This AD was prompted by the issuance of more restrictive fuel airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
59-12-02: 59-12-02 LOCKHEED: Applies to All Models 049, 149, 649, 749 and 1049 Series Aircraft. Compliance required as indicated. The following inspections have been established as a result of recently found corrosion and cracking on the wing Station 80 bathtub fittings, P/N's 251245 and 251246 on Model 049, 149, 649, 749 Series aircraft and Model 1049-54 aircraft and P/N's 310008 and 310009 on the remaining Model 1049 Series aircraft. These inspections shall be accomplished on all aircraft which have accumulated 12,000 or more flight-hours. Inspect affected aircraft at the next block overhaul or within 4,000 flight-hours, whichever occurs first. Inspect all aircraft for cracked bathtub fittings as follows: (1) Inspection may be made by removing the wing-to-fuselage fillet and dye checking the forward and aft edges on the neck of the bathtub fittings lugs of both the inner and stub wing fittings. (2) Replace any cracked bathtub fittings. Inspect each inner wing andstub wing Station 80 fitting for corrosion as follows: (1) Visually inspect the inner and stub wing Station 80 joint bathtub fittings adjacent to the DD8 rivets and rivet attachments taking particular care to note any imperfections or paint defects. Probe further whenever defects in paint are discovered in order to detect any corrosion. (2) Replace any wing Station 80 bathtub fittings on which corrosion cleanup exceeds a depth of 0.025-inch or a diameter of 0.70 inch (approximate diameter of a dime) around rivet attachments. Remove corrosion if within the allowable and treat per Lockheed Report 8882, (also 7789 and 5886) paragraph 1-67N, revised July 15, 1957, or equivalent. (3) Inspect the stub wing and inner wing skin upper surface for corrosion around the bathtub fitting screw holes. Also inspect the stub wing and inner wing upper skin lower surfaces between corrugations for corrosion. Maximum allowable skin cleanup without resorting to a doubler repair is 0.020-inch deep or an area not exceeding one inch wide and three inches long, provided screw holes are not enlarged. Areas of skin corrosion exceeding these allowable limits should be repaired in accordance with applicable Structural Repair Manual procedures. Clean up and protect corroded areas per Lockheed Report 8882, (also 7789 and 5886) revised July 15, 1957, or equivalent. It must be determined that any corrosion is confined to the skin only and does not penetrate into the corrugations. Reinstall all screw attachments flush in to the cleaned up areas. (4) Inspect the bathtub fitting end lugs for corrosion. Maximum permissible combined depth of corrosion on mating fitting lugs should not be such as to increase the total gap between mating faces in excess of 0.020 inch. Replace fittings which cannot be cleaned up within this tolerance. The special inspection note above may be extended an additional 12,000 flight-hours for each wing on which all fittings are replaced. Otherwise reinspection at 4,000 flight-hour periods or block overhaul whichever occurs first is required to insure detection of cracked or corroded Wing Station 80 bathtub fittings or attachments. (Lockheed Service Letter FS/231053 covers this same subject.)
87-09-01: 87-09-01 MESSERSCHMITT-BOLKOW-BLOHM GmbH (MBB): Amendment 39-5616. Applies to Models BO-209-150FV, -150RV, -160FV, -160RV, and -150FF "MONSUN" airplanes (all serial numbers) certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To preclude inflight wing separation, accomplish the following: (a) Before further flight: (1) Inspect and modify the wing spar carry-through lower cap strip in the fuselage area in accordance with the "Inspection of Wing Spar Carry-Through" paragraph of MBB Technical Instruction No. 209-1/87, dated January 26, 1987 (hereinafter referred to as MBB TI No. 209-1/87), and the manufacturer's maintenance manual procedures, as follows: (i) Jack up the airplane and remove both main landing gear struts. (ii) Remove both landing gear brackets, Part Number (P/N) 209-21233 and P/N 209-21243. (iii) Drill out the rivets (four each) on each side of the right and left-hand elongated holes (the passage for the landing gear strut through the wing spar carry-through). (iv) Examine the surface quality adjacent to each elongated hole and the associated four rivet holes, and remove any visible flutes or score marks by polishing. (v) Carry out an ultrasonic test of the area adjacent to the elongated holes for cracks. If any crack is detected, accomplish paragraph (b) of this AD. (vi) Carry out an eddy current test of the area adjacent to the associated rivet holes for cracks. If any crack is detected, accomplish paragraph (b) of this AD. (vii) Modify the four rivet holes adjacent to each of the above-mentioned elongated holes by reaming out the rivet holes, consolidating the rivet hole walls, re-reaming the holes, and inserting HI-LOK helical rivets, in accordance with instructions contained in MBB TI No. 209-1/87. (viii) Reinstall the landing gear brackets, P/N 209-21233 and P/N 209-21243. (ix) Replace unserviceable rubber bearings, P/N 209-51003.02, with new serviceable parts. (x) Reinstall the main landing gear struts. CAUTION: During reinstallation of the struts, scoring of the surface adjacent to the elongated holes of the spar carry-through must be avoided. If scoring damage occurs, repeat steps (a)(1)(iv) through (a)(1)(vi) of this AD. (2) Carry out an ultrasonic test for cracks in the transition radii of the fuselage mounted wing attachment brackets in accordance with instructions contained in MBB TI No. 209-1/87. If any crack is detected, accomplish paragraph (b) of this AD. (3) Visually inspect for cracks or deformation of the forward and aft frame plates which form the forward and aft metal webs of the wing spar carry-through in the adapter structure to the wing stub in accordance with instructions contained in MBB TI No. 209-1/87. If any crack is detected, accomplish paragraph (b) of this AD. (4) The inspection, corrective action, and modification specified in paragraph (a) of this AD must be performed at an appropriately rated FAA repair station by personnel specifically training by MBB. (b) If any crack is detected, before further flight, accomplish the following: (1) Inform the manufacturer at the address listed below of the crack(s) found. (2) Request a manufacturer repair procedure approved by the FAA. (3) Incorporate the FAA approved repair procedures. (c) Prior to further flight: (1) Change the "LIMITATIONS" section of the FAA approved Model BO-209 "MONSUN" Approved Flight Manual (AFM) using pen and ink, and operate the airplane in accordance with these limitations as follows: (i) Paragraph 2.9.2 of the AFM, change "above" to "up to," to read as follows: "Utility Category: Spinning with flaps retracted, lazy eights, chandelles, steep turns up to 60 degree bank." (ii) Paragraph 2.12.9 of the AFM, change "above" to "up to" in Section 2. "Utility Category" to readas follows: "2. Utility Category ... lazy eight up to 60 degree bank ..." (2) Fabricate and install on the canopy center line strip, visible to the pilots, the following placard using letters of a minimum 0.10 inch in height: "ACROBATIC FLIGHT PROHIBITED". (3) Modify the limitations placard mounted on the canopy center line strip by permanently deleting or obliterating the following words: "Only if accelerometer is installed: Slow roll 125 Kt, wing over, loop 135 Kt, steep turns above 60 degree bank 117 Kt." NOTE: The placard required by paragraph (c)(2) of this AD may be mounted in a suitable manner to cover the above-stated text to satisfy this requirement. (d) Upon accumulating 3000 hours time-in-service (TIS) and every 500 hours TIS thereafter, carry out an ultrasonic test of the wing spar carry-through lower cap strip area adjacent to the elongated holes and the associated four rivet holes with HI-LOK rivets for cracks in accordance with the MBB Technical Note 209-1/87, page 3, dated January 22, 1987. If any crack is detected, before further flight, accomplish the repairs specified in paragraph (b) of this AD. (e) If a ferry flight to an approved maintenance location is required: (1) Airplanes not previously used for acrobatics may be flown to the location in accordance with FAR 21.197. (2) Airplanes previously used for acrobatics must be visually inspected for cracks prior to the ferry flight in accordance with the "sketch" (page 4 of 4) of the MBB Technical Note No. 209-1/87, dated January 22, 1987. If any crack is found, further flight is prohibited until all actions of paragraphs (a) and (b) of this AD are accomplished. (f) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B-1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Messerschmitt-Bolkow-Blohm GmbH, Department 1QS 143, Post fach 801160, D-8000 Munchen 80, Federal Republic of Germany; or may examine the documents referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment, 39-5516, becomes effective on May 6, 1987.
2001-22-18: This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce, plc models Tay 650-15 and 651-54 turbofan engines. This amendment requires initial and repetitive visual and ultrasonic inspections of fan blades for cracks, and, if necessary, replacement with serviceable parts. In addition, this AD requires recording instances when engines are operated in a stabilized manner in newly prohibited ranges. This amendment is prompted by reports of fan blade failures. The actions specified by this AD are intended to prevent fan blade failures, which can result in an uncontained engine failure, engine fire, and damage to the airplane.
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.