Results
2001-04-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires inspection to determine the orientation of the Wiggins fuel couplers of the fuel tank vent line and scavenge line in the right wing at station 249, and follow-on corrective actions. This amendment is necessary to prevent contact between the nuts of the Wiggins fuel couplers and the stiffener on the access panel of the upper surface of the right wing, which could compromise the lightning protection of the fuel tank of the right wing in the event of a lightning strike, and could result in possible fuel tank explosion. This action is intended to address the identified unsafe condition.
2001-04-04: This amendment adopts a new airworthiness directive (AD) that applies to all Dornier Luftfahrt GMBH (Dornier) Models 228-100, 228-101, 228-200, 228-201, 228-202, and 228-212 airplanes that have windshield spray nozzle option SCN 3109 installed. This AD requires you to deactivate the windshield spray nozzle heating elements. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent the windshield spray nozzle heating system from overheating, which could result in smoke in the cockpit and prompt the crew to initiate emergency actions.
2007-13-18: 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: The aim of the Airworthiness Directive (AD) is to introduce a new life limit for engine and Nose Landing Gear (NLG) mounts installed on EADS SOCATA TB 9, TB 10 and TB 200 airplanes, as defined in the updated Airworthiness Limitations Section (ALS) of the relevant Aircraft Maintenance Manuals (AMM). We are issuing this AD to require actions to correct the unsafe condition on these products.
77-01-01: 77-01-01 PIPER AIRCRAFT CORPORATION: Amendment 39-2796. Applies to Model PA-28-140 serial numbers 28-7225001 through 7725086; Model PA-28-150/160/180 serial numbers 28-7205001 through 7505259; Model PA-28-151 serial numbers 28-7415001 through 7715200; Model PA-28-181 serial numbers 28-7690001 through 7790192; Model PA-28-235 serial numbers 28-721001 through 7610181; Model PA-28R-200 serial numbers 28R-7235001 through 7635459; Model PA-32-260 serial numbers 32-7200001 through 7700005; and Model PA-32-300 serial numbers 32-7240001 through 7740012 certificated in all categories. Compliance required as indicated. To prevent possible fuel exhaustion due to an erroneous fuel quantity gauge indication, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, unless (b) and/or (c) have been accomplished, attach the following Placard to the instrument panel near the fuel quantity gauges, in clear view of the pilot, using 1/8" minimum size type: "WARNING FUEL GAUGES MAY INDICATE AS MUCH AS 2 1/2 GALLONS WHEN TANKS ARE EMPTY." The placard may be fabricated by the owner/operator or Piper Part Number 35669-14 may be used. (b) Within the next 200 hours' time in service or 12 months, whichever occurs first, after the effective date of this AD, check each of the fuel quantity gauges for proper calibration in accordance with the following procedures. These checks may be performed by the pilot. (1) Place the airplane on a known level area in an approximately static level condition. (2) Insure that each fuel tank contains a minimum of five (5) gallons of fuel. (3) Start the engine and run at 1000 rpm for approximately two (2) minutes. Alternator portion of split master switch must be on. (4) Shut down the engine but leave the master switch on during steps (5), (6) and (7). (5) Defuel each airplane fuel tank. CAUTION: Insure that the aircraft and the defuelingvehicle are properly grounded and insure that proper fire protection equipment is available. (6) Repeat (3). (7) With the engine running, determine the fuel quantity indication for each gauge. (8) If the gauges indicate zero (0) or below, no further action is required. Return the airplane to service. (9) If a gauge indicates above zero (0), accomplish (c), or replace the erroneous gauge with a serviceable gauge, which has the appropriate Piper Part Number and is identified with a white dot on the lower right hand corner of the face. (c) The fuel quantity gauges that do not meet (b)(9) must be calibrated to a zero (0) indication in accordance with FAA approved Piper instructions by an FAA approved facility or by an FAA authorized Piper Aircraft Corporation employee. (d) When (b) and/or (c) have been accomplished, the placard required by (a) may be removed. (e) Alternate method of compliance must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. Piper Service Bulletin 533 also pertains to this same subject. This amendment becomes effective January 7, 1977.
76-19-07: 76-19-07 PIPER: Amendment 39-2733. Applies to Piper Models PA-24-250, Serial Nos. 24-1, 24-103 through 24-3641, and 24-3643 through 24-3687 and PA-24-260, Serial Nos. 24-3642, 24-4000 through 24-5047 certificated in all categories with Piper Kit Number 760 747 Stabilator Modification installed. To prevent possible hazards in flight associated with cracks occurring in the corners of the balance weight cutout of the stabilator balance weight tube assembly, accomplish the following within the next one hundred hours in service from the effective date of this AD unless previously accomplished. a. Replace the stabilator balance weight tube assembly in accordance with the directions contained in the "Instructions" section of Piper Service Bulletin Number 496 or approved equivalent replacement. b. Equivalent replacement must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective September 29, 1976.
2001-03-11: This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace HP137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes that are equipped with certain main landing gear (MLG) radius rods. This AD requires inspection of the MLG radius rods for cracks and replacement of any cracked rod. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to detect and correct cracks in the MLG radius rods. Such cracks could result in MLG failure during takeoff, landing, or taxi operations, with consequent loss of airplane control.
76-18-05: 76-18-05 PIPER: Amendment 39-2715. Applies to Models PA-30, Serial Nos. 30-1 through 30-2000, and PA-39, Serial Nos. 39-1 through 39-155 certificated in all categories. To prevent possible hazards in flight associated with cracks in the radius of the bend relief holes of the forward fin attachment channel assembly accomplish the following within the next 50 hours in service from the effective date of this AD unless previously accomplished. a. Visually inspect the forward fin attachment channel P/N 22903-00 around the radius of the bend relief cutouts for cracks using a magnifying glass of at least five power or an approved equivalent inspection. b. Cracked parts must be replaced with a part of the same number or equivalent that has been inspected in accordance with this AD and found acceptable prior to further flight, except that the Airplane may be flown in accordance with FAR 21.197 to a base where a repair can be made. c. Equivalent inspections and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (Piper Service Letter No. 777 refers to this subject.) This amendment is effective September 10, 1976.
76-11-06: 76-11-06 PIPER: Amendment 39-2629. Applies to Model PA-31P, S/Ns 31P-1 to 31P-7630001 inclusive, and 31P-7630003. Compliance required within the next 100 hours in service after the effective date of this AD unless already accomplished. To prevent the hazards associated with the possibility of the alternator switch bus bar link shorting to the adjacent fuselage bulkhead, accomplish the following: (a) Alter the existing switch bus bar link insulation in accordance with the "Instructions" paragraph in Service Bulletin No. 473, dated March 24, 1976, or with an approved alternate method. (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 and Manufacturing Branch, FAA Eastern Region who must also approve any alternate alteration. This amendment is effective June 4, 1976.
2007-13-10: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas DC-10-30 and DC-10-30F airplanes. This AD requires installing Teflon sleeving around the fuel pump wire harness inside the conduit in the aft supplemental fuel tank. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
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.