Results
2017-13-02: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by reports that during the assembly of structural elements on some airplanes, lack of established procedures and tools caused boring and torqueing defects to be present at some locations. This AD requires a detailed visual inspection of bore holes for defects, replacement of bolts, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
81-18-01 R1: This amendment revises an existing airworthiness directive (AD) for Bell Helicopter Textron, Inc. (BHTI) Model 206A, 206B, 206A-1, 206B-1, 206L, and 206L-1 helicopters that currently establishes a retirement life for the main rotor trunnion (trunnion) based on hours time-in-service (TIS). This amendment retains those requirements but revises the AD to remove the trunnion, part number (P/N) 206-011-120-103, from the applicability. This amendment is prompted by the issuance of another AD for the BHTI Model 206L and 206L-1 helicopters that requires a different method of calculating the retirement life for the trunnions. The actions specified by this AD are intended to prevent failure of the trunnion due to fatigue cracks and subsequent loss of control of the helicopter.
2023-02-08: The FAA is superseding Airworthiness Directive (AD) 2021-09- 13, which applied to certain ATR-GIE Avions de Transport R[eacute]gional Model ATR42-500 airplanes. AD 2021-09-13 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that additional new or more restrictive airworthiness limitations are necessary. This AD retains the requirement of AD 2021-09-13. This AD also 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.
2001-25-02: This amendment adopts a new airworthiness directive (AD) for Enstrom Helicopter Corporation (EHC) Model TH-28 and 480 helicopters. This AD requires establishing a life limit for certain upper and lower main rotor hub plates of 5000 hours time-in-service (TIS), creating a component history card or equivalent record, and replacing each main rotor hub plate (hub plate) having 5000 or more hours TIS with an airworthy hub plate. This AD is prompted by a recent reliability-based stress analysis that indicates a 5000-hour TIS life limit should be imposed on certain hub plates. The actions specified by this AD are intended to prevent failure of a hub plate, loss of control of the main rotor, and subsequent loss of control of the helicopter.
2001-25-03: This amendment adopts a new airworthiness directive (AD) that applies to certain Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. This AD requires you to inspect one time for understrength rivets on the elevator torque tube and rudder hinge and replace any understrength rivets. This AD is the result of CDC notifying FAA that understrength rivets were mixed in production supplies. The actions specified by this AD are intended to detect and replace understrength rivets in the elevator and rudder, which could result in failure of the control surfaces. Such failure could lead to a loss of control of the airplane in flight.
63-27-05: 63-27-05 VICKERS: Amdt. 39-864. Amendment 658 (28 F.R. 13931) as amended by Amendment 39-126 (30 F.R. 11029) is further amended by Amendment 39-864. Applies to Viscount Models 744, 745D and 810 Series Airplanes. Compliance required as indicated. Fatigue failures have occurred in the fuselage leading edge frame and associated structure. To preclude further failures accomplish the following: (a) Fuselage frame: (1) Within 200 landings after the effective date of this AD on aircraft which have attained 8,000 landings, unless already accomplished within the preceding 500 landings, conduct initial visual inspection for cracks in accordance with the applicable Vickers Preliminary Technical Leaflet referenced herein. Accomplish repair in (2) or (3) as applicable, before further flight if the inspection reveals any of the following: (i) Cracks in the frame joint pressing or in the floor beam or in the floor beam joint plates - either in the flanges or running towards the flanges or in the heel line of the flanges. (ii) Any single crack not defined in (a)(1)(i), greater in length than 1.5 inches. (iii) Two or more cracks not defined in (a)(1)(i). (2) Model 744 and Model 745D cracked frame joint pressings must be repaired/reinforced per Modification D.3059, or any alternative scheme which has been approved by the Chief, Aircraft Certification Division, Europe, Africa and Middle East Area. (3) Model 810 Series aircraft. Figure 2, PTL 106 Issue 3 of later ARB- approved issue illustrates a temporary repair scheme, applicable only where unacceptable cracks, confined to the areas indicated in Figure 1 of the reference PTL are present. Unacceptable cracks, outside those areas must be repaired/reinforced in accordance with Mod. FG.1928 part (b). Any alternative scheme which has been approved by the Chief Aircraft Certification Division, Europe, Africa and Middle East Area may be used. (4) Subsequent to the initial inspection, per (1), aircraft are considered serviceable if the following repetitive inspections of the frame structure are accomplished at the periods indicated. (i) Within every 700 landings: (a) When no cracks are present. (b) Where any acceptable single crack not greater in length than 1.5 inches is present. (c) When VTO/700/169 or any other temporary repair scheme approved by the aircraft manufacturer or by the Chief, Aircraft Certification Division, Europe, Africa and Middle East Area, has been incorporated. (ii) At routine overhaul periods not later than every 12,000 flying hours: After reinforcement of the frame structure by incorporation of Mod. D3059 (for 744 and 745D) or Mod. FG.1928 part (b) (for 810), or any alternative reinforcement approved by the aircraft manufacturer, or by the Chief, Aircraft Certification Division, Europe, Africa and Middle East Area. (Continental Air Lines Repair/Reinforcing Scheme 753-43079 has been approvedby the aircraft manufacturer for aircraft repaired/reinforced prior to the effective date of this AD.) (b) Inspection of top spigot and socket fittings and attachment bolts: (1) From effective date of this AD within 1,000 landings on aircraft which have already attained 12,000 landings or within 2,000 landings on aircraft which have accumulated between 8,000 and 12,000 landings, unless already accomplished, conduct initial visual in situ inspection of the spigot and socket fittings for cracks and the associated attachment bolts for damage, in accordance with the applicable PTL referenced herein. Cracked fittings or damaged bolts must be replaced before further flight. Initial inspection of replacement fittings with new original type fittings need not be conducted until these fittings have accumulated 8,000 landings. (2) Subsequent to the initial inspection in (b)(1) conduct repetitive inspections within every 2,000 landings until Mod. D3072 Part (a) or part (d) (for744 and 745D) Mod. FG 1928 Part (a) or Part (d) (for 810) is embodied. Inspect modified fittings at routine overhaul periods not later than every 12,000 hours' time in service. (3) Modified fittings shall be used in pairs. Single modified fittings shall not be used to replace unserviceable unmodified items. (4) Modification D.3129 (for 744 and 745D) Modification FG. 2011 (for 810) introduce oversize top fitting attachment bolts. Strict compliance with paragraph B(2)(i), (ii), or (iii) of the applicable referenced PTL is required should operators incorporate these oversize bolts on a voluntary basis. (c) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Division, Europe, Africa and Middle East Area, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for that type of airplane. (British Aircraft Corporation (Operating) Ltd. PTL 242 Issue 3 or later ARB-approved issue (700 Series) and Modifications D.3059, D.3072 and D.3129 (for 744 and 745D airplanes) PTL 106 Issue 3 or later ARB-approved issue (800/810 Series) and Modifications FG. 1928 and FG. 2011 (for 810 Series airplanes) cover this subject.) This directive effective January 21, 1964. Revised August 26, 1965. Revised October 30, 1969.
2017-12-06: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4- 600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD is intended to complete certain mandated programs [[Page 27980]] intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This AD requires inspecting the forward passenger doors to identify the part number, and for affected doors, inspecting to identify existing repairs and doing corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-12-03: We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney Division (PW) PW2037, PW2037M, and PW2040 turbofan engines. This AD was prompted by an unrecoverable engine in-flight shutdown (IFSD) after an ice crystal icing event. This AD requires installing a software standard eligible for installation and precludes the use of electronic engine control (EEC) software standards earlier than SCN 5B/I. We are issuing this AD to correct the unsafe condition on these products.
2001-22-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-22-51, which was sent previously to all known U.S. owners and operators of Agusta S.p.A. (Agusta) Model A119 helicopters by individual letters. This AD requires removing a certain part-numbered tail rotor blade (blade) on or before accumulating 50 hours time-in-service (TIS). This AD also requires visually or dye penetrant inspecting each blade at specified time intervals and removing any cracked blade before further flight. This AD is prompted by the discovery of a fatigue crack on a blade during an inspection. The actions specified by this AD are intended to prevent failure of a blade and subsequent loss of control of the helicopter.
2001-25-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-8-33, -43, -51, -52, -53, and -55 series airplanes; Model DC-8F-54, and -55 series airplanes; and Model DC-8-61, -61F, -62, -62F, -63, -63F, -71, -71F, -72, -72F, -73, and -73F series airplanes. This action requires repetitive inspections of the electrical connectors of the explosive cartridge wiring of the engine fire extinguisher containers to verify if the identification number labels are installed and legible; repetitive electrical tests of all explosive cartridge wiring of the engine fire extinguisher containers to verify proper installation and function; and corrective actions, if necessary. This action is necessary to detect and correct cross-wired electrical connectors of the fire extinguishing system, which could release fire extinguishing agent into the incorrect engine nacelle in the event of an engine fire.