Results
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.
2007-24-14: The FAA is adopting a new airworthiness directive (AD) for Hartzell Propeller Inc. Model HC-E5N-3( ), HC-E5N-3( )(L), and HC-E5B- 5( ) propellers. This AD requires a onetime eddy current inspection of the propeller hub mounting bolt holes and replacement of the propeller hub if cracked. This AD results from the discovery of a five-bladed propeller hub with a large crack on the mounting flange of the hub. We are issuing this AD to prevent propeller hub failure, blade separation, damage to the airplane, and possible loss of airplane control.
2019-23-04: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 727 airplanes. This AD was prompted by the FAA's analysis of the Model 727 fuel system review conducted by the manufacturer. This AD requires modifying the fuel quantity indicating system (FQIS) to prevent development of an ignition source inside the body-mounted auxiliary fuel tanks due to electrical fault conditions. As an alternative to the modification, this AD allows deactivating the body-mounted auxiliary fuel tanks. The FAA is issuing this AD to address the unsafe condition on these products.
2007-24-03: 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 found the development of cracks in the forward fuselage right hand (RH) side skin during full-scale fatigue tests. Those cracks may quickly reach their critical length, reducing the aircraft structural integrity, with possible rapid decompression of the aircraft. We are issuing this AD to require actions to correct the unsafe condition on these products.
94-09-10: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 757 series airplanes. This action requires revising the Non-Normal Procedures Section of the FAA-approved Airplane Flight Manual (AFM) to include procedures that will enable the flight crew to identify fuel system leaks and to take appropriate action to prevent further fuel loss. This amendment is prompted by reports that flight crew procedures related to fuel system leaks are not defined adequately in the FAA-approved AFM for these airplanes. The actions specified in this AD are intended to ensure that the flight crew is advised of the potential hazard related to fuel exhaustion due to undetected leakage, and the procedures necessary to address it.
2007-24-06: We are superseding an existing 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 SMA SR305-230 and SR305-230-1 reciprocating engines. The MCAI states the following: Over a period of time, the alteration of one electronic control unit (ECU) electronic component can cause a rapid uncontrolled power increase. Several occurrences have already been reported during engine start or during engine warm-up. This condition, if not corrected, could result in the loss of control of the aircraft if the pilot fails to react appropriately by switching to the mechanical backup mode. We are issuing this AD to prevent a rapid uncontrolled power increase and possible loss of control of the airplane.
2001-10-06: This amendment supersedes an existing airworthiness directive (AD) that applies to Sikorsky Aircraft Corporation (Sikorsky) Model S-76A, S-76B, and S-76C helicopters and currently requires, before further flight, performing a fluorescent penetrant inspection (FPI) of the main rotor shaft assembly (shaft). Also, a recurring FPI and visual inspection for a cracked shaft are required by that AD. That AD also requires replacing the shaft with an airworthy shaft before further flight if a crack is found. This amendment requires replacing certain serial numbered shafts with an airworthy shaft before further flight. This amendment is prompted by further investigation and a determination that the inspections can be safely eliminated if certain serial-numbered shafts are removed from service before further flight. The actions specified by this AD are intended to prevent failure of the shaft and subsequent loss of control of the helicopter.
94-08-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and Model DC-9-80 series airplanes, and C-9 (military) airplanes, that currently requires inspections to detect cracking in the skin and doublers around the upper anticollision light cutout, and repair, if necessary. This amendment expands the applicability to include additional Model DC-9-80 series airplanes and Model MD-88 airplanes, and requires the performance of stress coining procedures on the plate nut clearance holes or installation of shims and an external doubler. This amendment is prompted by a report that stress coining procedures were not performed on the plate nut clearance holes of the upper anticollision light doublers during production of certain airplanes. The actions specified by this AD are intended to prevent crack growth in the doublers, which could result in damage to the adjacent structure, and subsequent loss of cabin structural integrity.
2007-24-12: The FAA is adopting a new airworthiness directive (AD) for certain Eclipse Aviation Corporation Model (Eclipse) EA500 airplanes. This AD requires you to inspect the fuel filler adapters for primer and/or paint in the surround and, if present, remove the primer and/or paint. This AD results from an observation during a factory walk-around that the fuel filler surround was primed instead of being bare metal. We are issuing this AD to inspect and, if necessary, remove any paint and/or primer to restore the fuel filler adapter lightning strike protection. A lightning strike on the filler cap with insulating primer on the surround could result in the strike not dissipating to the surround. This could lead to arcing and ignition of fuel vapor inside the fuel tank.
2001-10-03: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF34-1A, -3A, -3A1, -3A2, -3B, and -3B1 turbofan engines. This action requires a one-time inspection, and if necessary replacement of certain fan disks for electrical arc-out indications, and assigns a reduction in the life limit of certain fan disks. This amendment is prompted by a report of a crack that was found during a visual inspection as part of routine engine maintenance. The actions specified in this AD are intended to prevent rupture of the fan disk due to cracks that initiate at an electrical arc-out, which could result in an uncontained failure of the engine.
2001-10-04: This amendment supersedes Airworthiness Directive (AD) 2000-14-51, which requires inspection of the wing lower spar cap for cracks on Air Tractor, Inc. (Air Tractor) Models AT-501, AT-502, and AT-502A airplanes, and modification or replacement of any cracked wing lower spar cap. This AD lowers the safe life for the wing lower spar cap on Air Tractor AT-400, AT-500, and AT-800 series airplanes. This AD is the result of numerous reports of cracks in the \3/8\-inch bolthole of the wing lower spar cap on the affected airplanes. 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 not detected and corrected, could result in the wing separating from the airplane during flight.
2011-10-07: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCA I) 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: DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France Airworthiness Directive (AD) 1992-106-132(B) * * * was issued to require a set of inspection- and modification tasks which addressed JAR/FAR [Joint Aviation Regulation/Federal Aviation Regulation] 25-571 requirements related to damage-tolerance and fatigue evaluation of structure. * * * * * The unsafe condition is reduced structural integrity of the wings. We are issuing this AD to require actions to correct the unsafe condition on these products.
94-07-04: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company (GE) CF6-80A series turbofan engines, that requires an inspection for cracks in the stage 1 high pressure turbine (HPT) disk rim bolt holes. 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 HPT disk failure, which could result in an inflight engine shutdown, aborted takeoff, or damage to the aircraft.
2007-24-04: The FAA is superseding an existing airworthiness directive (AD) for CFM International, S.A. CFM56-5C4/1 series turbofan engines. That AD currently requires that the low pressure turbine (LPT) conical support, part number (P/N) 337-002-407-0, be removed from service at or before reaching the cyclic life limit of 9,350 cycles-since-new (CSN). This AD requires that the same P/N LPT conical support be removed from service before reaching the new, relaxed cyclic life limit of 20,000 CSN. This AD results from CFM International, S.A. performing a life extension study of the LPT conical support, P/N 337-002-407-0. We are issuing this AD to prevent LPT conical supports from remaining in service beyond their certified cyclic life limit, which could result in an uncontained engine failure and damage to the airplane.
2004-22-10: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-400 and -400F series airplanes. This AD requires a detailed inspection(s) for cracks and fractures of the side guide support fittings in the lower lobe cargo compartments; and applicable investigative/corrective actions and operational limitations, if necessary. This AD also requires a terminating action for the repetitive inspections. This AD is prompted by reports of cracked/fractured side guide support fittings in the aft, lower lobe cargo compartment. We are issuing this AD to prevent cracked/fractured side guide support fittings in the lower lobe cargo compartments, which could result in unrestrained cargo shifting in flight and damaging the airplane structure or systems, and consequent reduced controllability of the airplane.
2000-03-03 R1: This amendment revises an existing airworthiness directive (AD), applicable to General Electric Company CF34 series turbofan engines, that currently requires revisions to the Engine Maintenance Program specified in the manufacturer's Instructions for Continued Airworthiness (ICA) for General Electric Company (GE) CF34 series turbofan engines. Those revisions require enhanced inspection of selected critical life-limited parts at each piece-part exposure. The existing AD also requires that an air carrier's approved continuous airworthiness maintenance program incorporate these inspection procedures. This amendment removes inspection requirements for parts removed from engines mounted on-wing. This amendment is prompted by the high removal rate and subsequent piece-part exposure of fan disks due to certain maintenance procedures. This additional exposure has resulted in fan disk focused inspection rates that exceed the intent of the focused inspection initiative. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
2017-24-01: We are adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR42-500 airplanes and Model ATR72-212A airplanes. This AD requires an inspection for routing attachments of electrical harness bundles and for wire damage, and corrective actions if necessary. This AD was prompted by reports of electrical harness bundle chafing with a window blinding panel in the fuselage due to missing routing attachments. We are issuing this AD to address the unsafe condition on these products.
94-08-14: This amendment adopts a new airworthiness directive (AD), applicable to all Corporate Jets Model BAe 125-1000A series airplanes, that requires replacement of the white 'EMERG CONTCTRS' annunciator screen on roof panel 'CG' of the flight deck with an amber screen. This amendment is prompted by a report that the annunciator screen currently installed on these airplanes is not a color that would alert the flight crew that corrective action may be necessary. The actions specified by this AD are intended to ensure that the flight crew is alerted to conditions when standby electrical power is not available.
2007-23-17: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 206A and 206B helicopters. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority to identify and correct an unsafe condition on an aviation product. The aviation authority of Canada, with which we have a bilateral agreement, states in the MCAI: Reevaluation of the structural analysis indicates the need for the removal from service of bolts in this application. The removal of certain main rotor latch bolts is required because these bolts do not have a mandatory retirement life. Further evaluation has shown that these bolts fail prematurely due to fatigue. This fatigue failure may result in failure of the main rotor and subsequent loss of control of the helicopter. We are issuing this AD to require actions to correct this unsafe condition on these products.
2007-19-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2007-19-52, which was sent previously to all known U.S. owners and operators of the specified Bell Helicopter Textron Canada Limited (BHTC) model helicopters by individual letters. This AD requires replacing each affected tail rotor blade (blade) with an airworthy blade with a serial number not listed in the Rotor Blades, Inc. (RBI), attachment to the BHTC Alert Service Bulletin (ASB), listed in the applicability section of this AD. This amendment is prompted by three incidents in which blade tip weights were slung from blades during flight causing significant vibration. The actions specified are intended to prevent loss of a blade tip weight, loss of a blade, and subsequent loss of control of the helicopter.
2001-10-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and -145 series airplanes. This action requires applying torque to certain tubing fittings of the fire extinguishing systems of various areas of the airplane, and applying torque paint to the fittings. This action is necessary to ensure that certain tubing fittings of the fire extinguishing systems are properly torqued. Improperly torqued tubing fittings of the fire extinguishing systems of the baggage compartment, auxiliary power units (APU), and engines, if not corrected, could become loose and cause the fire extinguisher to inadvertently discharge. Inadvertent discharge of a fire extinguisher could result in reduced fire protection or the inability to extinguish a fire in the baggage compartment, APU, or engine. This action is intended to address the identified unsafe condition.
94-09-02: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires an inspection to detect damage of the auxiliary power unit (APU) power feeder cable installation, repair of damaged cables, and modification of the cable installation. This amendment requires an inspection of previously modified airplanes to determine whether a spacer or "stand off" has been installed, and installation of those items, if necessary. This amendment is prompted by reports of generator power feeder cables electrically shorting to the airplane structure due to chafing. The actions specified by this AD are intended to prevent the APU power feeder cable from chafing against adjacent structures, which could result in electrical shorting and arcing, and a fire below the cabin floor.
2007-22-10: We are superseding an existing 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: During MLG (main landing gear) lubrication, a crack was found visually in the MLG rib 6 aft bearing forward lug on one A330 in service aircraft. * * * This condition, if not detected and corrected, could affect the structural integrity of the MLG attachment. Failure of the forward lug could result in collapse of the MLG upon landing. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective November 16, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of November 16, 2007. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD as of February 15, 2007 (72 FR 4416, January 31, 2007). We must receive comments on this AD by December 3, 2007.
2001-09-14: This amendment adopts a new airworthiness directive (AD) that is applicable to Airbus Model A330-243, -341, -342, and -343 series airplanes equipped with Rolls Royce Trent 700 series engines. This action requires repetitive inspections of certain components, and corrective action, if necessary. This action is necessary to detect and correct fatigue cracking of the hinge assemblies and the 12 o'clock beam structure of the thrust reverser C-duct, which could cause failure of the thrust reverser hinge, resulting in separation of the thrust reverser from the airplane. This action is intended to address the identified unsafe condition.
2019-24-13: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318 series airplanes, Model A319-111, -112, - 113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, - 131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by a report that during a maintenance check, cracks were found in a stiffener of a certain lateral window frame. This AD requires repetitive high frequency eddy current (HFEC) inspections for cracking of a stiffener of a certain lateral window frame, and applicable related investigative and corrective actions, 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.