Results
80-12-14: 80-12-14 PIPER (TED SMITH): Amendment 39-3801. Applies to Aerostar Model 600, 601, 601P Serial Nos. 0001 through 0799 airplanes certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent the reentry of an engine fire into the underwing structure behind the engine nacelle, accomplish the following: (a) Within the next 300 hours' time in service, or ninety days after the effective date of this AD, whichever occurs sooner, install a metal fairing, P/N 230090-1 and -2, in place of the existing fiberglass fairing, P/N 230023-501 and 502, in accordance with Piper Service Bulletin So 600-83, dated November 21, 1979. (b) 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 the modification required by this AD. (c) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective June 19, 1980.
2005-18-20: The FAA is adopting a new airworthiness directive (AD) for Goodrich De-icing and Specialty Systems "FASTprop" propeller de- icers, part numbers P4E1188 series, P4E1601 series, P4E2200 series, P4E2271-10, P4E2575-7, P4E2575-10, P4E2598-10, P5855BSW, P6199SW, P6592SW, P6662SW, and P6975-11, installed. This AD requires inspection, repair, or replacement of those "FASTprop" propeller de-icers that fail daily visual checks. This AD results from reports of Goodrich "FASTprop" propeller de-icers becoming loose or debonded, and detaching from propeller blades during operation.
97-26-08: This amendment adopts a new airworthiness directive (AD) that applies to Mooney Aircraft Corporation (Mooney) Models M20F, M20J, and M20L airplanes. This action requires removing the fuel cap retaining lanyard from the fuel filler cap assemblies. A report of lost engine power during flight because of fuel starvation prompted the action. The investigation revealed that the airplane fuel float became trapped by the fuel cap retaining lanyard, keeping the float from following the fuel level. This condition caused the pilot to get a false fuel quantity reading. The actions specified by this AD are intended to prevent loss of engine power and fuel depletion during flight caused by a false fuel gauge reading.
2016-24-51: We are publishing a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires inspecting certain bearings. This AD is prompted by a report of a failed bearing. We are issuing this AD to address the unsafe condition on these products.
97-26-14: This amendment adopts a new airworthiness directive (AD) that applies to all MAULE Models MX-7-420 and MXT-7-420 airplanes, and all Models M-7-235 and M-7-235A airplanes that are modified in accordance with Maule STC SA2661SO, which incorporates a certain gas turbine engine, certain amphibious floats, and certain propellers. This AD requires amending the Limitations Section of the airplane flight manual (AFM) to prohibit the positioning of the power levers below the flight idle stop while the airplane is in flight. This AFM amendment will include a statement of consequences if the limitation is not followed. This AD results from numerous incidents and five documented accidents involving airplanes equipped with turboprop engines where the propeller beta was improperly utilized during flight. The actions specified by this AD are intended to prevent loss of airplane control or engine overspeed with consequent loss of engine power caused by the power levers being positioned belowthe flight idle stop while the airplane is in flight.
61-21-01: 61-21-01 CANADAIR: Amdt. 348 Part 507 Federal Register October 17, 1961. Applies to Model CL-44D4 Aircraft, Serial Numbers 14, 16, 19 through 23, 25 and 26. Compliance required within the next 25 hours' time in service unless already accomplished within the last 10 hours' time in service and at intervals not to exceed 35 hours' time in service. To preclude failure of the tail pipe door structure, the following must be accomplished: (a) Inspect the following tail pipe compartment access panels for fatigue cracking using dye penetrant or equivalent in the area of the attachment holes. Part Numbers to be inspected are 44-10721, 44-10721-1, 44-10722, 44-10722-1, 44-10726, 44-10721-990, 44- 10721-991, 44-10722-990, 44-10722-991, 44-10726-990, 44-10751, 44-10751-1, 44-10752, 44- 10752-1, and 44-10753. (b) If cracks are found, panels must be replaced, repaired or reinforced in accordance with Canadair Service Bulletin No. CL-44D4-138 or equivalent, or modified in accordance with a Department of Transport and FAA approved modification prior to further flight except ferry flight in accordance with the provisions of CAR 1.76. Following the incorporation of the interim repair or reinforcement covered in Service Bulletin No. CL-44D4- 138, or replacement, the inspections specified in (a) must be continued at intervals not exceeding 35 hours' time in service. If further cracks are found after repair or reinforcement per Canadair Service Bulletin CL-44D4-138, the parts shall be replaced or modified in accordance with Canadian Department of Transport and FAA approved modification. (c) The special inspections required by this airworthiness directive may be discontinued after incorporation of the Canadian Department of Transport and FAA approved modification of the affected parts. (d) Upon request of the operator, an FAA maintenance inspector, subject to 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 October 17, 1961.
71-11-02: 71-11-02 AVCO LYCOMING: Amdt. 39-1208 as amended by Amendment 39-1403. Applies to all IO- 360A and -C Series engines with serial numbers 1734-51A through 4412-51A and all such series engines remanufactured between 1 September 1965 and 11 October 1967. Compliance required as indicated, unless already accomplished. To prevent valve failures replace the intake and exhaust hydraulic tappet plunger assembly P/N 76290 with P/N 78290 at the time in service specified below: (a) Engines with less than 400 hours in service on P/N 76290 as of the effective date of this AD, shall comply prior to the accumulation of 450 hours in service. (b) Engines with 400 or more hours in service on P/N 76290 as of the effective date of this AD shall comply within the next 50 hours in service. (Note: Lycoming Service Bulletin No. 328 covers this subject.) Amendment 39-1208 was effective May 19, 1971. This Amendment 39-1403 is effective March 14, 1972.
2016-26-01: We are adopting a new airworthiness directive (AD) for certain Agusta Model AB139 and AW139 helicopters. This AD requires performing operational checks of both hydraulic systems. This AD was prompted by an assessment of the hydraulic systems of the helicopter following an accident. These actions are intended to prevent the unsafe condition on these products.
2005-18-17: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires a one-time inspection of the fuel and hydraulic tubes, and corrective actions if necessary. This AD also requires modifying fairlead plate assemblies. This AD results from reports of chafing between fuel and hydraulic tubes and the fairlead plate where the tubes pass through the firewall. We are issuing this AD to prevent chafing of the fuel and hydraulic tubes, which could lead to fuel and/or hydraulic fluid leakage in the engine nacelle area and consequent fire or explosion.
2010-23-21: 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: Viking Air Limited has completed a system safety review of the aircraft fuel system against fuel tank safety standards introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002-043. The identified non-compliances were then assessed using Transport Canada Policy Letter No. 525-001, to determine if mandatory corrective action is required. The assessment showed that supplemental maintenance tasks would be required to prevent potential ignition sources within the fuel system, which could result in a fuel tank explosion. * * * We are issuing this AD to require actions to correct the unsafe condition on these products.