Results
2001-06-01: This amendment supersedes three existing airworthiness directives (AD's) that apply to certain The New Piper Aircraft, Inc. (Piper) Models PA-31, PA-31-300, PA-31P, PA-31T, and PA-31T1 airplanes. These AD's currently require you to repetitively inspect and/or modify the elevator structure. This AD initially retains the inspection and modification requirements that are currently required; adds certain other airplane models to the AD applicability; and requires a modification at a certain time period, as terminating action for the currently required repetitive inspections. This action coincides with the Federal Aviation Administration's (FAA) policy of incorporating modifications, when available, that will terminate the need for repetitive inspections. The actions specified by this AD are intended to continue to detect and correct damage to the elevator structure. A damaged elevator structure could lead to reduced or loss of control of the airplane.
2001-06-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires inspecting the endcaps of the main landing gear selector valve for leaks of hydraulic oil and, if leaks are detected, replacing the leaking endcaps or the entire selector valve. This amendment also requires eventual replacement or rework of certain selector valves, which will terminate the repetitive inspections. This amendment is prompted by a report of the collapse of the main landing gear due to an external leak of hydraulic oil in the landing gear selector valve, resulting from a fracture of the endcap. The actions specified by this AD are intended to prevent leaks of hydraulic oil from the main landing gear selector valve, which could result in the collapse of the main landing gear.
80-19-01: 80-19-01 PIPER AIRCRAFT CORPORATION: Amendment 39-3908. Applies to Model PA-28R-180 serial numbers 28R-30002 through 28R-7130013; Model PA-28R-200 serial numbers 28R-35001 through 28R-7635545; PA-28R-201 serial numbers 28R-7737001 through 28R-7837317; and PA-28RT-201 serial numbers 28R-7918001 through 28R-8018088 airplanes certificated in all categories. \n\n\tCompliance required within the next 50 hours time in service after the effective date of this AD unless already accomplished. \n\n\tTo prevent possible leakage of carbon monoxide into the cabin, accomplish the following: \n\n\t(a)\tRemove upper and lower engine cowling. \n\n\t(b)\tRemove and discard clips on muffler shroud end plates shown on Figure 1. \n\n\t(c)\tInspect for movement between the muffler shroud end plates and the muffler pipes. \n\n\t(d)\tIf there is no relative movement, the muffler assembly is acceptable and no modification is necessary. \n\n\t(e)\tIf relative movement is observed, accomplish the following: \n\n\t\t(1)\tRemove and disassemble the muffler and shroud assembly from the engine and inspect all parts for wear and cracking. Repair or replace as necessary. \n\n\tNOTE: During the inspection required inn (1), direct particular attention to the muffler shroud end plates and the mating area of contact on the muffler tubes. \n\n\t\t(2)\tRework the end plates to provide a 0.030 inch minimum gap between the plates after assembly as shown in Figures 1 and 2. \n\n\t\t(3)\tSlot the two 0.141 inch holes in the top of the shroud assembly to allow the screws to be installed without causing deformation of the shroud skin. \n\n\t\t(4)\tInstall the two screws holding the shroud assembly on the bottom side of the muffler prior to installing the strap clamps but do not tighten until the top screws are in place. \n\n\t\t(5)\tInstall the strap clamps, tightening to a torque of 25 to 30-inch pounds. \n\n\t\t(6)\tInstall and tighten the two top screws then tighten the bottom screws. \n\n\t\t(7)\tInspect the muffler and shroud assembly for tightness. If relative motion still exists between the muffler pipes and the muffler shroud end plates, repeat steps (1) through (6) until any relative motion is eliminated. \n\n\t\t(8)\tReinstall the muffler assembly in the aircraft using new exhaust gaskets, Lycoming part number 65321, and torque exhaust stack nuts to 120 to 170-inch pounds. \n\n\t(f)\tMake an appropriate maintenance record entry. \n\n\tAn equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. \n\n\tNOTE: Piper Service Bulletin No. 691, dated August 6, 1980, pertains to this subject. \n\n\tThis amendment becomes effective September 12, 1980. \n\n\n\n\nFIGURE 1 AD \n80-19-01 \n\n\n\n\nFIGURE 2 \nAD 80-19-01
77-03-04: 77-03-04 Bell: Amendment 39-2822; AD Applies to Bell Model 214B and 214B-1 helicopters, S/N 28001 through 28006, 28008, 28009, and 280011, certificated in all categories. Compliance required within 25 hours' time in service after the effective date of this AD unless already accomplished. To prevent a possible interference between a control tube and a fuselage fitting, trim the fuselage splice fitting of fuselage Station 129 in accordance with Bell Helicopter Textron Service Bulletin No. 214-76-6 dated November 1, 1976, or later approved revision. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Service Manager, Bell Helicopter Textron, P.O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Office of Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas. This amendment becomes effective February 14, 1977.
2007-18-03: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-300, -400, and -500 series airplanes. This AD requires an inspection of the seat locks and seat tracks of the flightcrew seats to ensure that the seats lock in position and to verify that lock nuts and bolts of adequate length are installed on the rear tracklock bracket, and corrective actions if necessary. This AD results from a report indicating that the captain's seat slid aft and jammed during taxi. We are issuing this AD to prevent uncommanded movement of the flightcrew seats during acceleration and take-off of the airplane, which could result in reduced controllability of the airplane.
2019-19-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200 Freighter, A330-200, and A330-300 series airplanes. This AD was prompted by an analysis conducted on Airbus SAS Model A330-200 Freighter, A330-200, and A330-300 series airplanes that identified structural areas that are susceptible to widespread fatigue damage (WFD). This AD requires reinforcement modifications of various structural parts of the fuselage, and applicable related investigative and corrective actions if necessary, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2018-07-19: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8 and 787-9 airplanes. This AD was prompted by a report that the parking brake and alternate pitch trim module (PBM) may unintentionally disengage. This AD requires replacing the PBM and doing a PBM installation test. We are issuing this AD to address the unsafe condition on these products.
2004-18-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777 series airplanes, that requires replacing four socket contacts on the four boost pumps of the main fuel tanks with new, high-quality gold-plated contacts, and sealing the backshell of the connector with potting compound. This action is necessary to prevent a possible source of ignition in a flammable leakage zone, which could result in an undetected and uncontrollable fire in the wheel well or wing trailing edge, and a possible fuel tank explosion. This action is intended to address the identified unsafe condition.
78-09-03: 78-09-03 DOWTY ROTOL, LTD.: Amendment 39-3196. Applies to Dowty Rotol Type R193/4-30-4/50 and R193/4-30-4/61 propellers of the following serial numbers which may be installed on, but not necessarily limited to, Fairchild Model F27A, F27F, F27J, FH-227, and FH- 227-1; and Fokker F-27 Mks. 200, 400, 500 and 600 airplanes: 193/60/167 DRG/34/61 DRG/66/62 DRG/284/63 DRG/120/64 DRG/4/61 DRG/35/61 DRG/19/63 DRG/285/63 DRG/121/64 DRG/5/61 DRG/2/62 DRG/22/63 DRG/286/63 DRG/122/64 DRG/6/61 DRG/3/62 DRG/24/63 DRG/287/63 DRG/123/64 DRG/7/61 DRG/33/62 DRG/25/63 DRG/320/63 DRG/138/64 DRG/9/61 DRG/35/62 DRG/26/63 DRG/321/63 DRG/141/64 DRG/13/61 DRG/36/62 DRG/72/63 DRG/337/63 DRG/142/64 DRG/14/61 DRG/37/62 DRG/134/63 DRG/14/64 DRG/158/64 DRG/25/61 DRG/41/62 DRG/136/63 DRG/17/64 DRG/207/64 DRG/26/61 DRG/42/62 DRG/222/63 DRG/36/64 DRG/208/64 DRG/27/61 DRG/49/62 DRG/224/63 DRG/78/64 DRG/292/66 DRG/33/61 DRG/50/62 DRG/226/63 DRG/79/64 DRG/296/66 Compliance is required as indicated, unless already accomplished. To reduce the possibility of propeller hub and driving center assembly failure due to corrosion, and subsequent possible propeller failure, accomplish the following: (a) Within the next 1000 hours time in service after the effective date of this AD, or at the next scheduled propeller overhaul, whichever occurs first, inspect the propeller hub and driving center assembly in accordance with Dowty Rotol Service Bulletin 61-882, dated March 11, 1977 (hereinafter SB 61-882), and the therein referenced Dowty Rotol Propeller Overhaul Manual Pub. No. 61-2-2, Repair Scheme Manual Pub. No. 923; and Process Specification Manual Pub. No. 872, or FAA-approved equivalents. (b) If, as a result of the inspection required by paragraph (a) of this AD, propeller hub or driving center assembly corrosion is found to exceed the limits specified in Dowty Rotol Overhaul Manual 61-2-2 and Repair Scheme Manual Publication No. 923 Repair Schemes 650013110 and 650013120 or an FAA-approved equivalent, before further operation, replace the propeller hub and driving center assembly with a serviceable propeller hub and driving center assembly or an FAA-approved equivalent. (c) The equivalent means of compliance specified in paragraphs (a) and (b) of this AD must be approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Region, Federal Aviation Administration, c/o American Embassy, Brussels Belgium. This amendment becomes effective May 22, 1978.
2010-04-13: 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: An A300-600 operator reported two events of IPECO pilot seat moved in the aft position, one during take-off roll and one during climb out. The investigation of these events showed that a broken/ missing spring contributed to the seat not being correctly locked. An unwanted movement of pilot or co-pilot seat in the aft direction is considered as potentially dangerous, especially during the take-off phase when the speed of the aeroplane is greater than 100 knots and until landing gear retraction. * * * * * The unsafe condition is potential loss of control of the airplane during take-off and landing. We are issuing this AD to require actions to correct the unsafe condition on these products.