Results
2008-20-05: This amendment supersedes an existing airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model 600N helicopters. The AD currently requires modifying the fuselage aft section within the next 24 months to strengthen the tailboom attachment fittings and upper longerons. This amendment retains the current required modification and adds the following requirements: Repetitively inspecting the tailboom attachment fittings; installing inspection holes and attachment bolt washers; modifying both access covers; and replacing broken attachment bolts. These additional requirements were inadvertently omitted from the current AD. This amendment is prompted by the need to correct our mistake and continue the repetitive inspections of the tailboom attachment fittings until the fuselage aft section is modified. This series of ADs is prompted by an accident due to failure of the tailboom attach points resulting in loss of control of the helicopter. The actions specified by this AD areintended to prevent failure of the tailboom attachment fittings, separation of the tailboom from the helicopter, and subsequent loss of control of the helicopter.
65-04-03: 65-04-03 CANADAIR: Amdt. 39-29 Part 39 Federal Register February 4, 1965. Applies to Model CL-44D4 aircraft. Compliance required as indicated. To prevent further failures of the elevator antiflutter gear box strut that could result in punctured elevator ribs or limited elevator travel, accomplish the following: (a) For aircraft having shafts P/N's 44A167729-4 and 44A167729-6 in the elevator antiflutter gear box strut assemblies with less than 5,400 hours' time in service on the effective date of this AD, comply with (c) prior to the accumulation of 5,450 hours' time in service, unless already accomplished within the last 250 hours' time in service, and at intervals thereafter not to exceed 300 hours' time in service from the last inspection. (b) For aircraft having shafts P/N's 44A167729-4 and 44A167729-6 in the elevator antiflutter gear box strut assemblies with 5,400 or more hours' time in service on the effective date of this AD, comply with (c) within the next50 hours' time in service after the effective date of this AD, unless already accomplished within the last 250 hours' time in service, and at intervals thereafter not to exceed 300 hours' time in service from the last inspection. (c) Remove the elevator control spring loaded strut assemblies, P/N's 44A167734-2 and 44A167734-6 and disassemble the shaft assemblies and inspect the shafts, P/N's 44A167729- 4 and 44A167729-6 for cracks using dye penetrant in conjunction with at least a 10-power glass or an FAA-approved equivalent. NOTE - When inspecting the shafts, particular attention should be directed at the location of the washer, P/N 44A28833. (d) Replace cracked parts with a new part of the same part number or an FAA- approved equivalent before further flight, except that the aircraft may be flown in accordance with the provisions of FAR 21.197 to the base where the repairs are to be accomplished. (e) Replacement shafts shall be inspected for cracks in accordance with(c) within 5,400 hours' time in service, and at intervals thereafter not to exceed 300 hours' time in service, from the last inspection. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, 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. This directive effective February 4, 1965.
2020-16-09: The FAA is superseding Airworthiness Directive (AD) 2009-25-09 for Eurocopter France (now Airbus Helicopters) Model SA330F, G, and J helicopters. AD 2009-25-09 required re-adjusting the torque of the main gearbox (MGB) flexible coupling bolts. Since the FAA issued AD 2009-25- 09, Airbus Helicopters has modified the MGB overhaul and repair procedures, which corrects the unsafe condition. Additionally, the FAA- validation for Model SA330F and G helicopters has been cancelled. This new AD retains the requirements of AD 2009-25-09 and revises the applicability by excluding Model SA330F and G helicopters and excludes MGBs that have been subject to the modified procedures. The actions of this AD are intended to address an unsafe condition on these products.
2003-19-09: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767 series airplanes, that requires repetitive inspections and tests for discrepancies of the drainage system of the canted pressure deck located in the wheel wells of the main landing gear (MLG) of the left and right wings, and corrective actions if necessary. This action is necessary to prevent ice accumulation on the lateral flight control cables and/or components due to water entering the wheel well of the MLG and freezing, which could restrict or jam control cable movement, resulting in loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
85-14-01: 85-14-01 DASSAULT - BREGUET: Amendment 39-5090. Applies to Mystere-Falcon 50 airplanes, serial numbers as follows: 014, 026, 035, 038, 039, 041, 045, 051, 053, 059, 069, 079, 081, 086, 087, 099, 105, 108, 124, 125; certificated in all categories. Compliance required within 90 days from the effective date of this AD, unless previously accomplished. To prevent a lanyard hang-up when the lanyard is pulled to initiate the flow of oxygen into the oxygen mask, accomplish the following: A. Each passenger emergency oxygen mask presentation box not located on the fuselage vertical center line must be inspected for orientation. Accomplish by manually opening the presentation box cover lids and inspecting to ensure that the presentation boxes are installed with the oxygen inlet fitting in the side of the oxygen box in the inboard position (pointed toward the fuselage center line). Any box not installed with this orientation must be removed and reinstalled in such a way that it isrotated 180 degrees so that the inlet fitting is in the inboard position. NOTE: AiResearch Aviation Service Bulletin No. 9.1 pertains to this subject. B. Alternate inspections, modifications, or other actions which provide an acceptable level of safety may be used when approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to ferry airplanes to a maintenance base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to AiResearch Aviation, 4150 Donald Douglas Drive, Long Beach, California 90808. These documents also may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Western Aircraft Certification Office, 15000 Aviation Boulevard, Hawthorne, California. This amendment becomes effective August 15, 1985.
94-10-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 707/720 series airplanes, that requires certain structural inspections of older airplanes. This amendment is prompted by reports of incidents involving fatigue cracking and corrosion in transport category airplanes that are approaching or have exceeded their economic design service goal. The actions specified by this AD are intended to prevent degradation of the structural capabilities of the affected airplanes. This amendment relates to the recommendations of the Airworthiness Assurance Task Force assigned to review Model 707/720 series airplanes, which indicate that, to assure long term continued operational safety, various structural inspections should be accomplished.
2020-12-14: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by a report that the anti-fretting coating on the piston rods of certain ram air turbine (RAT) deployment actuators may have been incorrectly applied. This AD requires a review of airplane maintenance records or an inspection of the RAT deployment actuator to determine the serial number and, depending on the findings, replacement with an upgraded RAT deployment actuator. The FAA is issuing this AD to address the unsafe condition on these products.
82-08-03: 82-08-03 AIRBUS INDUSTRIE: Amendment 39-4357. Applies to Model A300 series airplanes, certificated in all categories. Compliance is required before accumulating 10,000 hours time in service or 750 hours time in service after the effective date of this AD, whichever occurs later, unless already accomplished. To prevent progressive failures of the attachment fasteners between the inboard horizontal stabilizer leading edge and the spar box, accomplish the following: (a) Remove and replace the right and left side, upper and lower screws, anchor nuts and reinforcement plates from the inboard set out to and including the set at rib 4 of the inboard horizontal stabilizer leading edge in accordance with paragraph 2.B, "Modification," of Airbus Industrie Service Bulletin No. A300-55-006, Revision No. 4, dated March 21, 1980, or an FAA- approved equivalent. (b) If an equivalent means of compliance is used in complying with this AD, that equivalent means must be approvedby the Chief, Aircraft Certification Staff, ANE-190, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. This Amendment 39-4357 becomes effective May 1, 1982.
2003-19-05: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F (KC-10A and KDC-10), -40, and -40F airplanes; and certain Model MD-10-10F and -30F airplanes, that requires inspections for cracking and corrosion of the bolt assemblies and bushings on the hinge fittings of the inboard and outboard flaps of the left and right wings, and follow-on and corrective actions. This action is necessary to prevent failure of the bolt and bushing that attach the hinge fitting to the flap, which could result in loss of the flap and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2008-23-14: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: During inspection of undercarriage main beam sidestays, bolts attaching the undercarriage main beam sidestay to frame 29 were found with the heads of the bolts sheared off. Loose bolt assemblies were also found. If sheared or loose bolts are not detected and replaced, a possible consequence is the collapse of the main landing gear. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.