Results
2001-10-04 R1: This amendment revises AD 2001-10-04, which concerns certain Air Tractor, Inc. (Air Tractor) AT-400, AT-500, and AT-800 series airplanes. AD 2001-10-04 superseded AD 2000-14-51 and lowers the safe life for the wing lower spar cap on these airplanes. The AD was the result of numerous reports of cracks in the 3/8-inch bolthole of the wing lower spar cap on the affected airplanes. We inadvertently included certain AT-800 series airplanes in the Applicability of this AD. Those AT-800 series airplanes that are equipped with the factory-supplied part number 80540 computerized fire gate should not be affected by AD 2001-10-04. This action revises the AD to reflect this change and to provide information for applying for an alternative method of compliance with this AD. The actions specified by this AD are intended to prevent fatigue cracks from occurring in the wing lower spar cap before the originally established safe life is reached. Fatigue cracks in the wing lower spar cap, if notdetected and corrected, could result in the wing separating from the airplane during flight.
79-10-04: 79-10-04 CANADAIR: Amendment 39-3459. Applies to Models CL-44D4, and CL-44J aircraft. Compliance required within the next 1700 hours in service and, if applicable, upon application for U.S. registration and airworthiness certification, after the effective date of this AD unless already accomplished. 1) (Docket No. 78-EA-82) In order to fireproof the engine fire extinguishing system fittings in inboard and outboard nacelles, accomplish the following: a. Wrap the fittings with asbestos tape and then coat them with a suitable end dip as described in Paragraphs "2" and "3" of Canadair Service Bulletin No. CL-44D4-480, dated December 11, 1972, or an equivalent alteration. 2) (Docket No. 78-EA-85) To minimize the chance of over-pressurizing the outer auxiliary fuel tanks during pressure refueling, and to eliminate wear caused by possible interference between float arm and valve casing, accomplish the following: a. Alter the modulator and shut-off pilot valves by riveting a fabricated angle to the float, re-identify them; re-identify the fuel level control valve assembly; and functionally check the altered valves all in accordance with the "Modification Procedure" of Canadair Service Bulletin No. CL-44-485, dated April 5, 1978. 3) (Docket No. 78-EA-86) In order to reduce the probability of flammmable fluid fires within the engine cowling areas and reduce the risk of damaging engine oil and fuel drain lines located on the engine bottom cowls, accomplish the following: a. Alter the engine cowling and drain lines in accordance with the "Modification" paragraph of Canadair Service Bulletin No. CL-33D4-486 dated May 12, 1978, or an equivalent alteration. Any equivalent method of compliance must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance time may be changed by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. The aircraft may be flown in accordance with FAR 21.197 to a location where the AD can be accomplished. Compliance with this AD must be noted in the logbook of the aircraft by referencing the AD number and the specific item complied with: ex. AD 79-10-04 (2) if item (2) is being accomplished. This amendment becomes effective May 9, 1979.
94-10-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires dye penetrant inspections and proof pressure testing to detect cracks or ruptures of the crossover pneumatic duct, and repair or replacement, as necessary. This amendment also requires stress relieving of the crossover pneumatic duct assembly. This amendment is prompted by reports of ruptured engine bleed air crossover ducts. The actions specified by this AD are intended to prevent failure of the engine bleed air crossover duct, which could result in loss of pneumatics and damage to adjacent structure.
2007-25-17: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747- 200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. This AD requires repetitive inspections for cracking of the station (STA) 1241 bulkhead fittings just above the canted pressure deck; a one-time determination of the edge margin at seven fastener positions on each side of the airplane; and related investigative/corrective actions if necessary. This AD results from a report that an operator found a 1.65- inch crack on the STA 1241 bulkhead fitting on the left side of a Boeing Model 747-200F series airplane that had accumulated 17,332 total flight cycles. We are issuing this AD to detect and correct cracking in the STA 1241 bulkhead fittings, which could result in reduced structural integrity of the airplane.
2001-10-13: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Britax Sell Gmbh & Co. OHG water boilers, coffee makers, and beverage makers. This action requires inspecting the wiring for indications of overheating or electrical arcing, and if indications are found, replacing the wiring. This amendment is prompted by reports of discolored and partially melted wires. The actions specified in this amendment are intended to prevent a fire in the galley compartment due to inadequate crimping of the electrical terminal contact pins, which could result in smoke in the cockpit and cabin and loss of control of the airplane.
2020-01-14: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 series airplanes. This AD was prompted by a report that indicated that bleed and air conditioning systems were contaminated by hydraulic fluid, and by an investigation that revealed that hydraulic fluid contaminations caused the failure of check valves installed on the hydraulic reservoir air pressurization system. This AD requires repetitive functional tests of the hydraulic reservoir air pressurization lines, and repair or replacement if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
94-09-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires replacement of certain pneumatic duct couplings with redesigned couplings. This amendment is prompted by reports of failures of certain duct couplings installed on the wing leading edge pneumatic duct. The actions specified by this AD are intended to prevent such failures, which could lead to structural damage to the wing leading edge, flight control problems, or fire.
2007-25-19: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-400 series airplanes. This AD requires repetitive inspections to detect discrepancies of the forward and rear heat exchanger shells of the air distribution system of the crew rest area, and applicable corrective actions. This AD also requires an inspection to identify the part number, shop code, and build date of the forward and rear heat exchanger shells of the air distribution system of the crew rest area, and applicable corrective actions, which end the repetitive inspections. This AD results from a report of an uncommanded up and down pitch movement of an airplane in flight and resistance in the elevator controls on the ground during taxi. We are issuing this AD to prevent cracking and buckling of the forward or rear heat exchanger shell of the air distribution system of the crew rest area, which could result in jamming of the rudder and/or elevator control cables and consequent reduced controllability of the airplane.
2001-11-01: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9-32 series airplanes modified per Supplemental Type Certificate SA4371NM, that requires an inspection to determine if certain ground wires on the water heater of each lavatory are installed, and corrective action, if necessary. The actions specified by this AD are intended to detect improper grounding of a water heater, which, coupled with an internal short in the water heater, could result in heat or smoke damage or a fire on the airplane. This action is intended to address the identified unsafe condition.
2019-25-55: The FAA is adopting a new airworthiness directive (AD) for The Boeing Company Model 737-300, -400, and -700 series airplanes, modified to a Bedek Division Special Freighter (BDSF) by Supplemental Type Certificate (STC) ST01566LA, ST01961SE, or ST02556SE, with a 9G rigid barrier. An emergency AD was sent to all known U.S. owners and operators of these airplanes. This AD requires complying with loading restrictions and methods. This AD was prompted by a review of the manufacturing process for the 9G rigid barrier installed on BDSF conversions that identified a manufacturing non-compliance. The FAA is issuing this AD to address the unsafe condition on these products.
94-10-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 and MD-11F series airplanes. This action requires deactivation of the Visual Omnidirectional Receiver/Localizer (VOR/LOC) option by revising the program pin wiring for the Flight Management Computer/Flight Control Computer (FMC/FCC). This amendment is prompted by reports of uncommanded roll mode changes on these airplanes during takeoff and landing due to incorrect initialization of VOR/LOC logic within the FMC. The actions specified in this AD are intended to prevent the airplane from deviating from its intended flight path due to an uncommanded change in the course of direction.
2007-25-05: 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: It has been discovered that a batch of sleeves and pins of the Rolls-Royce Trent 700 Thrust Reverser Unit (TRU) hinge n[deg] [number] 5 has not been subjected to the correct precipitation hardening. This production quality issue, if not corrected, can lead to the complete failure of the hinge n[deg] 5--the remaining hinges may not sustain ultimate load--resulting in the worst case to the TRU release from the pylon, which constitutes an unsafe condition. The degradation of the mechanical specifications of these parts puts into question the current design life goal of these parts. * * * The unsafe condition is possible detachment of the thrustreverser unit from the airplane, which could result in reduced controllability and possible damage to the airplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2001-10-15: This document adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and -145 series airplanes. This action requires a one-time inspection to detect incorrect wiring of electrical connectors to the pressure switches and cartridges on the fire extinguisher bottles for the engines and the auxiliary power unit (APU); disconnection and reconnection of the wiring, as necessary; and adjustment of the length of the harnesses on the fire extinguisher bottles to avoid future misconnections. This action is prompted by the issuance of mandatory continuing airworthiness information issued by a foreign civil airworthiness authority. This action is necessary to prevent the issuance of erroneous commands or the receipt of erroneous information pertaining to the fire extinguisher system for the engines and the APU, which could result in the inability to put out a fire in an engine or in the APU. This action is intended to address the identified unsafe condition.
2001-10-11: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-90-30 series airplanes. This action requires an inspection of the wiring of the primary and alternate static port heaters for chafing, loose connections, and evidence of arcing, and to determine what type of insulation blanket is installed in the area of the static port heaters; and corrective actions, if necessary. This action is necessary to ensure that insulation blankets constructed of metallized MylarTM are removed or protected from the area of the static port heater. Such insulation blankets could propagate a small fire that is the result of an electrical short of the static port heater and could lead to a much larger fire and smoke in the cabin. This action is intended to address the identified unsafe condition.
94-09-18: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company (GE) CF6-6/-45/-50 series turbofan engines, that requires an inspection for cracks in the stage 1 high pressure turbine (HPT) disk rim bolt holes, and stage 2 HPT disk rim and inner bolt holes; and replacement, if necessary, with serviceable parts. This amendment is prompted by a report of an uncontained stage 1 HPT disk failure which resulted in an aborted takeoff. The actions specified by this AD are intended to prevent an uncontained stage 1 or stage 2 HPT disk failure, which could result in an inflight engine shutdown, rejected takeoff, or damage to the aircraft.
2019-25-11: The FAA is adopting a new airworthiness directive (AD) for certain Viking Air Limited Model CL-215-1A10 and CL-215-6B11 (CL-215T Variant) airplanes. This AD was prompted by reports of cracks on the wing lower skin under the drag angle at a certain wing station (WS). This AD requires a one-time inspection of the wing lower skin under the drag angle at a certain WS to determine if a certain repair or modification has been accomplished; repetitive visual inspections of certain fuselage structures; repetitive eddy current inspections of the front spar along a certain WS reference line, the drag angle, and all fastener holes; repetitive structural gap checks of a certain surface; and corrective actions if necessary. This AD also requires replacing certain rivets with certain fasteners, and corrective actions if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2001-10-09: This amendment adopts a new airworthiness directive (AD) that applies to certain Honeywell KC 225 automatic flight control systems (AFCS) that are installed on airplanes. This AD requires you to inspect the KC 225 AFCS to determine the computer modifications (Mods) that are incorporated, deactivate any units with only Mods 1 and/or 2 incorporated, and fabricate and install an appropriate placard if the unit is deactivated/inoperative. The AD would provide, as an alternative method of compliance, the option of installing a unit that incorporated MOD 3 or higher. This AD is the result of several reports that the AFCS is disconnecting without warning in a gross mistrim configuration. The actions specified by this AD are intended to prevent an undesirable autotrim command that the autopilot cannot detect in the required time. The airplane could then deviate from the selected altitude or the autopilot could disconnect without warning, which could result in heavy loads at the control column. Such loads in the pitch axis could result in loss of control of the airplane.
2007-24-15: 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: One P 180 aircraft experienced a jamming of its longitudinal flight control cables. Investigations revealed that its fuselage drain holes were plugged, and water was trapped in the lower fuselage. As a consequence of plugged drain holes, water can accumulate and freeze when the aircraft reaches and holds altitudes where temperature is below the freezing point. If not corrected this may cause the loss of control of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
94-09-05: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-7 series airplanes, that requires a one-time inspection to assess the adequacy of the clearance between various adapter plates and seal retaining angles on the fuselage side access panel, and modification of both the forward and rear seal retention angles. This amendment is prompted by reports of incidents involving corrosion and fatigue cracking in commuter-class airplanes that are approaching or have exceeded their economic design goal. The actions specified by this AD are intended to prevent degradation of the structural capabilities of the affected airplanes.
2007-24-10: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) provided by the European Aviation Safety Agency (EASA) to identify and correct an unsafe condition on Turbomeca Arriel 2S1 and 2S2 turboshaft engines. The MCAI states the following: During assembly of a new HP/LP fuel pump, the drain screw on the fuel filter unit failed when it was tightened to the torque value specified in the assembly schedule (12 Nm). Investigation of the screw showed that it was fully conformed to its specification, in terms of both dimensions and material. The mechanical calculations show, however, that a torque value of 12 Nm is too high for this screw, exceeding the elastic limit of the material. Failure of the affected screw could cause a fuel leak, resulting in an engine flame-out or engine fire. We are issuing this AD to prevent a fuel leak as a result of a ruptured fuel filter drain screw that could lead to engine flame-out or an engine fire.
94-08-06: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JT9D-7R4 series turbofan engines, that requires initial and repetitive fan blade leading edge inspections, and either installation of fan blade sets with modified fan blade shrouds or rework of the fan blade shrouds as a terminating action to the inspections. This amendment is prompted by reports of flutter-induced fan blade fractures. The actions specified by this AD are intended to prevent fan blade fracture and uncontained engine failure, resulting in possible damage to the aircraft.
2001-10-07: This amendment adopts a new airworthiness directive (AD), that is applicable to General Electric Co. (GE) CF6-80C2 turbofan engines with certain stage 1 high pressure turbine (HPT) rotor disks installed. This amendment requires initial and repetitive inspections of certain HPT rotor disks for cracks in the bottom of the dovetail slot. This amendment is prompted by a report of an uncontained failure of an engine during a high-power ground run for maintenance. The actions specified by this AD are intended to detect cracks in the bottoms of the dovetail slots that could propagate to failure of the disk and cause an uncontained engine failure.
2019-25-18: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by a report of a wing stall (wing drop/ uncommanded roll) during landing flare, due to ice on the wing leading edges that was not detected by the anti-ice system. This AD requires revising the existing airplane flight manual (AFM) to include a limitation and normal operating procedure for the wing anti-ice system. The FAA is issuing this AD to address the unsafe condition on these products.
94-09-11: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Raytheon Corporate Jets Model BAe 125-1000A and Hawker 1000 series airplanes. This action requires inspections of the thrust reverser system for integrity, and correction of any discrepancy found. This amendment is prompted by a report that there is a possibility of failure of the drive links (or attachments) on the thrust reversers of these airplanes due to the single link design concept of the thrust reverser link and lock system. This condition, if not corrected, could result in inadvertent deployment of a thrust reverser during flight. The actions specified in this AD are intended to prevent a significant reduction in the controllability of the airplane due to an in-flight deployment of a thrust reverser. Comments for inclusion in the Rules Docket must be received on or before June 28, 1994.
77-13-05: 77-13-05 CANADAIR: Amendment 39-2930. Applies to CL-215 Airplanes, Serial Numbers 1001 through 1040 and 1046, certificated in all categories. Compliance required prior to U.S. airworthiness certification, unless already accomplished: (a) Inspect the right hand canopy sill for missing rivets forward and aft of bulkhead 234.5 as indicated in Figures 1 and 3 of the Canadair Information Circular (S.I.C.) No. 129-CL- 215 dated May 12, 1976, or an approved equivalent inspection. (b) If rivets have been omitted forward of the bulkhead, between stations 223 and 229, install three NAS 1103-4 bolts with MS2104L3 Nuts and Strip Washer as shown in Figure 2 of the S.I.C. or an approved equivalent alteration. (c) If rivet spacing aft of the bulkhead is greater than 1.25 inch install intermediate rivets as indicated in Figure 3 of the S.I.C. or an approved equivalent alteration. (d) Equivalent inspections, alterations or parts must be approved by Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This Amendment becomes effective June 29, 1977.