Results
76-04-10: 76-04-10 PIPER AIRCRAFT: Amendment 39-2531. Applies to Model PA-31-350, S/Ns 31-5001 to 31-7552073 inclusive. Compliance required within the next 100 hours' time in service after the effective date of this AD unless already accomplished. To prevent the hazards associated with toxic fumes from the battery being drawn into the cabin, accomplish the following: (a) Relocate and modify the battery drain and vent system in accordance with Piper Service Bulletin No. 460A, dated January 23, 1976, or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance time specified in this AD may be increased by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region. This amendment is effective March 5, 1976.
2007-13-12: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: EASA EAD 2006-0072-E was issued on 31st March 2006 following a further failure of the forward support of the Main Wing Outboard Flap (MWOF), caused by corrosion. This condition, if not corrected, may cause surface twisting during deployment at landing. The analysis of that event highlighted the need for the reduction of the previous inspection interval which was mandated by ENAC through AD 2004-523, approved by EASA with reference 2004-12521. We are issuing this AD to require actions to correct the unsafe condition on these products.
2000-25-54: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2000-25-54, which was sent previously to all known U.S. owners and operators of Agusta (Agusta) S.p.A. Model A109E helicopters by individual letters. This AD requires, before each start of the engines, visually checking both sides of each tail rotor blade (blade) for a crack and, at specified intervals, inspecting each blade for a crack using a 5-power or higher magnifying glass. Dye-penetrant inspecting each blade for a crack is also required at specified time intervals. If a crack is found, replacing the blade with an airworthy blade is required before further flight. This amendment is prompted by five reports of cracked tail rotor blades. The actions specified by this AD are intended to prevent failure of a blade and subsequent loss of control of the helicopter.
2007-13-02: The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas Model DC-8-62, DC-8-62F, DC-8-63, DC-8-63F, DC-8-72, DC-8-72F, and DC-8-73F airplanes. This AD requires deactivating certain components (the sump heater, scavenge valve, and scavenge pump) of the center wing fuel tank. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent certain conditions related to these components, which could lead to a possible ignition source in the fuel tank and a potential fire or explosion.
75-20-07: 75-20-07 PIPER: Amendment 39-2373. Applies to PA-36-285 serial numbers 36- 7560001 through 36-7560121 inclusive. Compliance required within the next 10 hours time in service after the effective date of this airworthiness directive. To determine proper installation of the front bearing plate bolt on the control system torque tube accomplish the following: a. Remove fuselage belly panel directly beneath the pilot seat. b. Refer to figure 5-1, sketch A of PA-36 Service Manual and locate front bearing plate to torque tube attachment bolt. c. Insure bolt (item 14) is tight and exhibits proper thread engagement in barrel nut (visible through aperture in torque tube): a minimum of 1 1/2 threads should be visible. d. If proper thread engagement is not found, remove forward bolt (item 14) and install proper length bolt (AN4-13A or equivalent). e. Recheck controls for proper operation. This amendment becomes effective September 22, 1975.
2007-12-25: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Model GIV-X, GV, and GV-SP series airplanes. This AD requires revising the airplane flight manuals (AFMs) of those airplanes, and doing repetitive functional checks of the forward water drain/supply valves and applicable corrective actions. This AD also provides for optional terminating action for the repetitive functional checks. This AD results from reports of failed forward water drain/ supply valves on numerous airplanes, and reports of ice striking the wing-to-body fairings and engine nose cowls of several airplanes. We are issuing this AD to prevent leakage from failed water drain/supply valves allowing the build-up of ice on the airplane, which could separate and strike the airplane structure aft of the failed valves; become ingested by a propulsion engine; or become a hazard to persons or property on the ground.
2001-03-03: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (BHTI) Model 214B and 214B-1 helicopters. This action requires, within 10 hours time-in-service (TIS), determining the hours TIS for certain main rotor outboard strap fitting assemblies and creating appropriate records. This action also requires, if any main rotor outboard strap fitting assembly (strap fitting) is determined to have 2,500 or more hours TIS or the hours TIS cannot be determined, replacing the strap fitting with an airworthy strap fitting before further flight. This action also establishes a 2,500-hour retirement life for the strap fitting and revises the Airworthiness Limitations section accordingly. This amendment is prompted by fatigue testing that indicates a fatigue crack may occur in the strap fitting with resulting failure. The actions specified in this AD are intended to prevent failure of a strap fitting, separation of a main rotor blade, and subsequent lossof control of the helicopter.
2001-03-02: This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney Canada (PWC) models PW306A and PW306B turbofan engines. This amendment requires removing compressor rotor 2nd, 3rd, and 4th stage drum assemblies and impellers from service before exceeding new, lower cyclic life limits. This amendment is prompted by the results of test analyses that indicate certain compressor rotor 2nd, 3rd, and 4th stage drum assemblies and impellers do not have full published life. The actions specified in this AD are intended to prevent premature cracking of compressor rotor 2nd, 3rd, and 4th stage drum assemblies and impellers which could result in an uncontained engine failure and damage to the airplane.
2000-25-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2000-25-51 that was sent previously to all known U.S. owners and operators of Rolls-Royce Deutschland GmbH (formerly BMW Rolls-Royce GmbH) model BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan engines. This action requires that certain high pressure turbine (HPT) stage 1 disks, part numbers (P/N's) BRH20009, BRH20010, BRH12167, BRH12168, BRH12466, and BRH12467; and stage 2 disks, P/N's BRH19349 and BRH19350, be removed before exceeding the new reduced cyclic limit, and replaced with a serviceable disk. This amendment is prompted by a reduction of the life limit for several high pressure turbine (HPT) stage 1 and stage 2 disks. The actions specified in this AD are intended to prevent an uncontained failure of the HPT stage 1 or stage 2 disk due to exceeded life-cycle limits.
75-16-02: 75-16-02 PIPER: Amendment 39-2270. Applies to Models PA-31P, Serial Nos. 31P-1 through 31P-7530019 and PA-31T, Serial Nos. 31T-400002 through 31T-7520022 certificated in all categories except aircraft incorporating Piper Kit No. 76-923, Rudder and Nose Gear Steering Cable Replacement or equivalent. To prevent possible hazards in flight associated with restricted rudder travel due to rudder nose gear steering cable entwinement, accomplish the following: 1. Within the next fifty hours in service from the effective date of this AD, replace the existing rudder nose gear steering cable installation in accordance with the instructions and parts contained in Piper Kit No. 760-923, Rudder and Nose Gear Steering Cable Replacement or equivalent. 2. Equivalent replacement must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (Piper Service Bulletin No. 446 refers to this subject.) This supersedes Amendment, AD 72-26-2. This amendment is effective July 29, 1975.