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.
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.)