Results
2001-03-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires identifying the part and serial numbers of the pressure reducing valve on each air pressurization unit, testing pressure reducing valves and air pressurization units having affected serial numbers, and replacing faulty valves or units with new parts. The actions specified by this AD are intended to prevent the simultaneous failure of two air pressurization units, which could result in loss of three hydraulic circuits and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2018-05-01: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters. This AD requires inspecting the sliding cabin plug door (sliding door). This AD was prompted by the failure of the sliding door's jettison mechanism due to corrosion. The actions of this AD are intended to address an unsafe condition in these products.
76-11-01: 76-11-01 PIPER: Amendment 39-2623. Applies to PA-31P airplanes certificated in all categories. To prevent possible adverse airplane vibration effects at higher altitudes, accomplish the following within the next 25 hours in service after the effective date of this Airworthiness Directive, unless already accomplished: (a) Attach the following operating limitation placard on the pilot's side window molding in full view of the pilot: OPERATING SPEEDS ALT Vno Vne 1000 mph mph 13 230 278 15 230 268 17 230 258 19 221 248 21 212 238 23 203 228 25 194 218 27 185 208 29 176 198 (NOTE: Speeds shown are CAS) (b) Incorporate Piper PA-31P Airplane Flight Manual revision dated January 22, 1976 in Piper PA-31P Airplane Flight Manual 1615. (Piper Service Bulletin No. 478 refers to this same subject.) This amendment is effective May 31, 1976.
2001-03-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Learjet Model 45 airplanes. This action requires revising the airplane flight manual (AFM) to prohibit flight into known icing conditions; inspecting the anti-ice manifold assembly for missing material, and performing corrective actions if necessary; replacing the anti-ice manifold assembly with a new assembly, which terminates the AFM revision requirement; and revising the Learjet 45 maintenance program to incorporate additional inspections and maintenance practices for the anti-ice manifold assembly. This action is necessary to prevent metal fragments from breaking off the anti-ice manifold assembly due to fatigue, which could block a duct in the anti-ice system and result in an unannunciated loss of ice protection. This action is intended to address the identified unsafe condition.
2017-23-07: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracks found in the lower chord of the left wing rear spar. This AD requires repetitive inspections for cracking of the lower chord of the rear spar and lower aft skin and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
2001-02-11: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (BHTI) Model 204B helicopters that requires replacing any main rotor mast assembly (mast), part number (P/N) 204-011-450-001, within 25 hours time-in-service (TIS). This amendment is prompted by the crash of a restricted category Model UH-1B helicopter due to failure of a mast, P/N 204-011-450-001. The same mast P/N is used on the Model 204B helicopters. The actions specified by this AD are intended to prevent failure of the mast and subsequent loss of control of the helicopter.
2018-04-05: We are adopting a new airworthiness directive (AD) for certain Airbus Model A319-112, A319-115, A320-214, A320-232, and A321-211 airplanes. This AD was prompted by in-service experience and further analysis, which showed that the galley 5 without kick-load retainers, was unable to withstand the expected loading during several flight phases or in case of emergency landing. This AD requires modification of galley 5 trolley compartments by adding kick-load retainers. We are issuing this AD to address the unsafe condition on these products.
72-21-07: 72-21-07 PIPER AIRCRAFT CORP: Amendment 39-1540 as amended by Amendment 39-2586. Applies to PA23-250 airplanes, S/Ns 27-4575 to 27-4587 inclusive, 27-4589 to 27- 4620 inclusive, 27-4622 to 27-4672 inclusive, 27-4674 to 27-4682 inclusive, and 27-4684 to 27- 4694 inclusive, and PA-23-250 airplanes which have been altered by substitution of Piper P/N 32958-00, Section Assembly - Fuselage, Nose, 34552-00, Section Assembly - Fuselage, Nose, or 33346-05, Radome Assembly for Piper P/N 30517-00, Section Assembly - Fuselage, Nose, or 30517-06, Section Assembly - Fuselage, Nose, certificated in all categories. Compliance required within 30 days after the effective date of this AD, unless already accomplished. To improve the longitudinal stability characteristics and to prevent longitudinal stick force reversal during certain flight conditions, accomplish the alteration contained in Piper Service Bulletin No. 345, dated 7 Oct. 1971; or an equivalent method approved by the Chief,Engineering and Manufacturing Branch, FAA Eastern Region. Upon request through a maintenance inspector, accompanied by substantiating data, the compliance time specified in the AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Amendment 39-1540 was effective October 19, 1972. This amendment 39-2586 is effective April 29, 1976.
2007-13-14: 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: Two cases of rudder lower support with cracks have been reported, waiting for a technical solution, inspections are required. We are issuing this AD to require actions to correct the unsafe condition on these products.
2001-03-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B19 series airplanes. This action requires repetitive ultrasonic inspection to detect damage of the actuator lugs of the flight spoiler center hinge; corrective action, if necessary; and eventual replacement of the flight spoilers with new, improved spoilers. This action is necessary to prevent uncommanded deployment of a flight spoiler, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2018-04-08: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the gore web lap splices of the aft pressure bulkhead are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections of the gore webs, gore web lap splices, and repair webs, as applicable, of the aft pressure bulkhead, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products. \n\n((Page 8326))
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.
2007-09-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2007-09-51, sent previously to all known U.S. owners and operators of the specified MD Helicopters, Inc. (MDHI), model helicopters by individual letters. This AD requires, before further flight, removing each affected tail rotor blade assembly and inspecting the bore of the tail rotor blade root fitting. If the blade assembly does not have a smooth radius, the AD requires replacing it. The AD also requires identifying each airworthy tail rotor blade assembly with the applicable helicopter model. This amendment is prompted by a report of an accident after the loss of a tail rotor blade. The actions specified by this AD are intended to prevent the failure of a tail rotor blade and subsequent loss of control of the helicopter.
2004-15-14: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319-131, -132, and -133; A320-231, -232, and -233; and A321-131 and -231 series airplanes. This AD requires revising the airplane flight manual (AFM) to advise the flightcrew of procedures associated with the intermittent interruption of the electrical power. Under certain conditions, this AD also requires inspecting for signs of arcing and performing any necessary corrective actions. This AD also provides for optional terminating action for the requirements of the AD. This AD is prompted by reports of fretting and consequent arcing of the electrical harness of the integrated drive generator (IDG) at the pin-to-socket connector at the firewall. We are issuing this AD to prevent transient loss of certain systems and consequent reduced ability of the flightcrew to cope with adverse flight conditions.
2001-02-03: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 206A, B, L, L1, and L3 helicopters. This AD requires inspecting the collective lever assembly (assembly) for a raised forging boss, inspecting the assembly for adequate clearance between the collective lever and the swashplate outer ring (outer ring), and modifying any assembly with a raised forging boss and inadequate clearance before further flight. Modifying any assembly that has a raised forging boss and adequate clearance would be required before further flight after January 31, 2001. This AD is prompted by the discovery that a raised forging boss could result in control system interference. The actions specified by this AD are intended to prevent interference between the collective lever and the outer ring, damage to flight controls, and subsequent loss of control of the helicopter.
2018-04-02: We are adopting a new airworthiness directive (AD) for Viking Air Limited Models DHC-6-1, DHC-6-100, DHC-6-200, DHC-6-300, and DHC-6- 400 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and address an unsafe condition on an aviation product. The MCAI describes the unsafe condition as aileron cable wear; fouling at the wing root rib, fuselage skin, and wing root rib fairlead; and/or fraying of the cable from the root rib fairlead. We are issuing this AD to require actions to address the unsafe condition on these products.