Results
97-25-07: This amendment supersedes an existing airworthiness directive (AD), applicable to GE Aircraft Engines (GE) CT7 series turboprop engines, that currently requires eddy current inspection (ECI) of disk holes of stage 1 and 2 gas generator turbine (GGT) disks for cracks, and, if necessary, replacement with serviceable parts. This amendment increases the initial cyclic compliance threshold while decreasing the calendar time for performing the ECI. This amendment is prompted by corrections to the applicable alert service bulletin (ASB) serial number (S/N) tables. The ASB contained S/Ns which appeared in more than one table creating confusion over which cyclic limit applied to each S/N. The actions specified by this AD are intended to prevent a stage 1 or 2 GGT disk failure, which could result in an uncontained engine failure and damage to the aircraft.
97-11-02 R1: This amendment revises an existing airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that currently requires an inspection to determine the thickness of the intercostal that attaches the third crew member seat to the floor structure in the flight compartment, and replacement, if necessary. That action was prompted by a report from the manufacturer indicating that intercostals have been installed that are not of sufficient thickness (and consequent strength) to support the third crew member seat during emergency landing dynamic conditions. The actions specified by that AD are intended to prevent the failure of this intercostal during an emergency landing, which could consequently result in injury to the flight crew. This amendment revises the applicability of the existing AD by removing several airplanes.
80-18-51: 80-18-51 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 4143. Applies to Model SA-330 series helicopters, certificated in all categories. Compliance required as indicated. To prevent friction between the electrical wires and hydraulic lines, which could result in leakage of hydraulic fluid and possible fire, accomplish the following: Prior to further flight, unless already accomplished within the last 50 hours time in service, inspect the electrical wires and hydraulic lines between fuselage stations 5295 and 5600 for chafing against each other and the airframe, and separate and secure electrical wires and hydraulic lines as necessary to prevent chafing. Any chafed electrical wires or hydraulic lines must be replaced before further flight. Report defects found to the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. (Reporting approved by the Office of Management and Budget under OMB No. 04- R0174.) This amendment becomes effective June 18, 1981, as to all persons except those persons to whom it was made immediately effective by telegraphic AD T80-18-51, issued August 29, 1980, which contained this amendment.
2005-18-18: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757 airplanes. This AD requires inspections of certain wire bundles in the left and right engine-to-wing aft fairings for discrepancies; installation of back-to-back p-clamps between the wire and hydraulic supply tube at the aft end of the right-hand strut only; and associated re-routing of the wire bundles, if necessary. This AD results from a report indicating that a circuit breaker for the fuel shutoff valve tripped due to a wire that chafed against the structure in the flammable leakage zone of the aft fairing, causing a short circuit. We are issuing this AD to prevent chafing between the wire bundle and the structure of the aft fairing, which could result in electrical arcing and subsequent ignition of flammable vapors and possible uncontrollable fire.
2016-26-03: We are superseding Airworthiness Directive (AD) 2013-23-02 for all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, CN-235-300, and C-295 airplanes. AD 2013-23-02 required an inspection of the feeder cables of certain fuel booster pumps for damage (including, but not limited to, signs of electrical arcing and fuel leaks), and replacement if necessary. This new AD retains those requirements and also requires modification of the electrical installation of the fuel booster pumps. This AD was prompted by a report of an in-flight problem with the fuel transfer system. We are issuing this AD to address the unsafe condition on these products.
2016-07-24: We are adopting a new airworthiness directive (AD) for all Textron Aviation, Inc. Models 310 through 310R, E310H, E310J, T310P through T310R, 310J-1, 320 through 320F, 320-1, 335, 340, 340A, 401 through 401B, 402 through 402C, 411, 411A, 414, 414A, and 421 through 421C [[Page 21251]] airplanes (type certificates 3A10, 3A25, and A7CE previously held by Cessna Aircraft Company). This AD requires replacement and repetitive inspections of the hardware securing the elevator trim push-pull rod. This AD was prompted by lessons learned in accident investigation support, analysis of past accidents, and NTSB determinations of probable cause. That information indicates that following the loss of the attachment hardware connecting the elevator trim tab actuator to the elevator trim tab push-pull rod, the elevator tab may jam in a position outside the normal limits of travel. We are issuing this AD to correct the unsafe condition on these products.
98-01-04: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F27 Mark 050 series airplanes. This action requires a one-time inspection of the main landing gear (MLG) locklinks to determine if the lockwire that secures both platform bolts is in one piece and in position; and corrective action, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent collapse of the MLG due to failure of the locklinks to lock in the down position.
2005-20-35: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A320-111 airplanes. The existing AD currently requires repetitive inspections for cracking in the front and rear faces and at the crown fittings of the upper stringers of the center wing box and applicable repairs. This new AD requires continuing the repetitive inspections at revised thresholds and intervals, and applicable repairs. This AD results from a manufacturer survey of airplanes affected by the existing inspection program that led to the consequent revision of the thresholds and intervals of the repetitive inspections. We are issuing this AD to detect and correct fatigue cracking of the upper stringers of the center wing box, which could lead to loss of structural integrity of the wing.
2002-02-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 707 and 720 series airplanes, that requires installation of a new support structure for the trailing edge beam and main landing gear uplock mechanism. This action is necessary to prevent cracking in the frame and adjacent structure near the attach bolt of the main landing gear uplock mechanism, which could lead to compromised structural integrity. This action is intended to address the identified unsafe condition.
97-26-21: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100, 747-200, 747-300, 747SR, and 747SP series airplanes. This action requires a one-time inspection to detect cracking of the longeron splice fittings at stringer 11, on the left and right sides at body station 2598, and replacement of any cracked fitting with a new fitting. This amendment is prompted by reports that fatigue cracking was found on longeron splice fittings. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in reduced controllability of the horizontal stabilizer.
97-26-06: This amendment adopts a new airworthiness directive (AD), applicable to all EMBRAER Model EMB-120 series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the ice protection systems, and to add information regarding operation in icing conditions. This amendment also requires installing an ice detector system and revising the AFM to include procedures for testing system integrity. This amendment is prompted by reports indicating that flightcrews experienced difficulties controlling the airplane during (or following) flight in normal icing conditions, when the ice protection system either was not activated when ice began to accumulate on the airplane, or the ice protection system was never activated. These difficulties may have occurred because the flightcrews did not recognize that a significant enough amount of ice had formed on the airplane to require activation of the deicing equipment. The actions specified bythis AD are intended to ensure that the flightcrew is able to recognize the formation of significant ice accretion and take appropriate action; such formation of ice could result in reduced controllability of the airplane in normal icing conditions.
80-12-14: 80-12-14 PIPER (TED SMITH): Amendment 39-3801. Applies to Aerostar Model 600, 601, 601P Serial Nos. 0001 through 0799 airplanes certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent the reentry of an engine fire into the underwing structure behind the engine nacelle, accomplish the following: (a) Within the next 300 hours' time in service, or ninety days after the effective date of this AD, whichever occurs sooner, install a metal fairing, P/N 230090-1 and -2, in place of the existing fiberglass fairing, P/N 230023-501 and 502, in accordance with Piper Service Bulletin So 600-83, dated November 21, 1979. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modification required by this AD. (c) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective June 19, 1980.
2005-18-20: The FAA is adopting a new airworthiness directive (AD) for Goodrich De-icing and Specialty Systems "FASTprop" propeller de- icers, part numbers P4E1188 series, P4E1601 series, P4E2200 series, P4E2271-10, P4E2575-7, P4E2575-10, P4E2598-10, P5855BSW, P6199SW, P6592SW, P6662SW, and P6975-11, installed. This AD requires inspection, repair, or replacement of those "FASTprop" propeller de-icers that fail daily visual checks. This AD results from reports of Goodrich "FASTprop" propeller de-icers becoming loose or debonded, and detaching from propeller blades during operation.
97-26-08: This amendment adopts a new airworthiness directive (AD) that applies to Mooney Aircraft Corporation (Mooney) Models M20F, M20J, and M20L airplanes. This action requires removing the fuel cap retaining lanyard from the fuel filler cap assemblies. A report of lost engine power during flight because of fuel starvation prompted the action. The investigation revealed that the airplane fuel float became trapped by the fuel cap retaining lanyard, keeping the float from following the fuel level. This condition caused the pilot to get a false fuel quantity reading. The actions specified by this AD are intended to prevent loss of engine power and fuel depletion during flight caused by a false fuel gauge reading.
2016-24-51: We are publishing a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires inspecting certain bearings. This AD is prompted by a report of a failed bearing. We are issuing this AD to address the unsafe condition on these products.
97-26-14: This amendment adopts a new airworthiness directive (AD) that applies to all MAULE Models MX-7-420 and MXT-7-420 airplanes, and all Models M-7-235 and M-7-235A airplanes that are modified in accordance with Maule STC SA2661SO, which incorporates a certain gas turbine engine, certain amphibious floats, and certain propellers. This AD requires amending the Limitations Section of the airplane flight manual (AFM) to prohibit the positioning of the power levers below the flight idle stop while the airplane is in flight. This AFM amendment will include a statement of consequences if the limitation is not followed. This AD results from numerous incidents and five documented accidents involving airplanes equipped with turboprop engines where the propeller beta was improperly utilized during flight. The actions specified by this AD are intended to prevent loss of airplane control or engine overspeed with consequent loss of engine power caused by the power levers being positioned belowthe flight idle stop while the airplane is in flight.
61-21-01: 61-21-01 CANADAIR: Amdt. 348 Part 507 Federal Register October 17, 1961. Applies to Model CL-44D4 Aircraft, Serial Numbers 14, 16, 19 through 23, 25 and 26. Compliance required within the next 25 hours' time in service unless already accomplished within the last 10 hours' time in service and at intervals not to exceed 35 hours' time in service. To preclude failure of the tail pipe door structure, the following must be accomplished: (a) Inspect the following tail pipe compartment access panels for fatigue cracking using dye penetrant or equivalent in the area of the attachment holes. Part Numbers to be inspected are 44-10721, 44-10721-1, 44-10722, 44-10722-1, 44-10726, 44-10721-990, 44- 10721-991, 44-10722-990, 44-10722-991, 44-10726-990, 44-10751, 44-10751-1, 44-10752, 44- 10752-1, and 44-10753. (b) If cracks are found, panels must be replaced, repaired or reinforced in accordance with Canadair Service Bulletin No. CL-44D4-138 or equivalent, or modified in accordance with a Department of Transport and FAA approved modification prior to further flight except ferry flight in accordance with the provisions of CAR 1.76. Following the incorporation of the interim repair or reinforcement covered in Service Bulletin No. CL-44D4- 138, or replacement, the inspections specified in (a) must be continued at intervals not exceeding 35 hours' time in service. If further cracks are found after repair or reinforcement per Canadair Service Bulletin CL-44D4-138, the parts shall be replaced or modified in accordance with Canadian Department of Transport and FAA approved modification. (c) The special inspections required by this airworthiness directive may be discontinued after incorporation of the Canadian Department of Transport and FAA approved modification of the affected parts. (d) Upon request of the operator, an FAA maintenance inspector, subject to approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This directive effective October 17, 1961.
71-11-02: 71-11-02 AVCO LYCOMING: Amdt. 39-1208 as amended by Amendment 39-1403. Applies to all IO- 360A and -C Series engines with serial numbers 1734-51A through 4412-51A and all such series engines remanufactured between 1 September 1965 and 11 October 1967. Compliance required as indicated, unless already accomplished. To prevent valve failures replace the intake and exhaust hydraulic tappet plunger assembly P/N 76290 with P/N 78290 at the time in service specified below: (a) Engines with less than 400 hours in service on P/N 76290 as of the effective date of this AD, shall comply prior to the accumulation of 450 hours in service. (b) Engines with 400 or more hours in service on P/N 76290 as of the effective date of this AD shall comply within the next 50 hours in service. (Note: Lycoming Service Bulletin No. 328 covers this subject.) Amendment 39-1208 was effective May 19, 1971. This Amendment 39-1403 is effective March 14, 1972.
2016-26-01: We are adopting a new airworthiness directive (AD) for certain Agusta Model AB139 and AW139 helicopters. This AD requires performing operational checks of both hydraulic systems. This AD was prompted by an assessment of the hydraulic systems of the helicopter following an accident. These actions are intended to prevent the unsafe condition on these products.
2005-18-17: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires a one-time inspection of the fuel and hydraulic tubes, and corrective actions if necessary. This AD also requires modifying fairlead plate assemblies. This AD results from reports of chafing between fuel and hydraulic tubes and the fairlead plate where the tubes pass through the firewall. We are issuing this AD to prevent chafing of the fuel and hydraulic tubes, which could lead to fuel and/or hydraulic fluid leakage in the engine nacelle area and consequent fire or explosion.
2010-23-21: 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: Viking Air Limited has completed a system safety review of the aircraft fuel system against fuel tank safety standards introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002-043. The identified non-compliances were then assessed using Transport Canada Policy Letter No. 525-001, to determine if mandatory corrective action is required. The assessment showed that supplemental maintenance tasks would be required to prevent potential ignition sources within the fuel system, which could result in a fuel tank explosion. * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
97-25-14: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-100, -200, and -300 series airplanes, that requires repetitive inspections of certain refuel/defuel tube assemblies in the engine nacelles for fuel leakage, and corrective action, if necessary. This amendment will also require eventual modification of all tube assemblies, which will terminate the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fuel leaks and consequent increased risk of engine fires.
81-03-03: 81-03-03 B.F. GOODRICH: Amendment 39-4027. Applies to the following brake assemblies with the following brake lining cups: \n\n\tBrake Assembly P/Ns \n\n\t2-1195-7, 2-1195-8, 2-1367, 2-1367-1, 2-1367-2, 2-1147, 2-1147-3 and 2-1190 \n\n\tBrake Lining Cups with part no./date codes as follows: \n\t\n\n342-58\n342-64\n342-94\n342-95 \nE12 80\nD18 80\nD10 80\nE7 80 \nE19 80\nD28 80 \n\n\nE20 80\nE17 80 \n\n\nG19 80\nG13 80 \n\n\nH9 80\nG19 80\n\n\n\n\tThese brake assemblies are used on but not limited to Boeing 727 and Lockheed L-1011 aircraft. \n\n\tWithin 60 days from the effective date of this AD, the above identified lining cups shall not be used on TSO'd brake assemblies unless the following has been accomplished: \n\n\ta)\tAll spare assemblies (i.e. brakes, pressure plates, lining carriers and torque plates) which have been assembled from inventory containing suspected cups, to be visually inspected at the lining cup button cavity for cracks using 4X or greater magnification. Remove cups with visible cracks and replace with serviceable parts. An alternative to the inspection is replacement of suspected cups with parts which are not in the suspected part no./date code groups. \n\n\tb)\tRecords must be kept to assure traceability of inspections and rework of all assemblies and brake assemblies which were assembled from inventory containing suspected cups. \n\n\tc)\tBrake assemblies installed on aircraft prior to the effective date of this AD do not require removal or inspection. \n\n\tB.F. Goodrich Service Bulletins No. 390 (for the Lockheed L-1011) and No. 391 (for the Boeing 727) dated October 9, 1980 also apply to the subject matter of this AD. \n\n\tThis amendment becomes effective January 28, 1981.
2010-23-08: 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: Following five reported cases of balance washer screw failure on similar RATs [ram air turbines]/air driven generators installed on other aircraft types, an investigation * * * determined that a specific batch of the screws had a metallographic non-conformity that increased their susceptibility to brittle fracture. * * * Failure of a balance washer screw can result in loss of the related balance washer, with consequent turbine imbalance. Such imbalance could potentially result in RAT structural failure (including blade failure), loss of RAT electrical power and structural damage to the aircraft and, if deployment was activated by a dual engine shutdown, could also result in loss of hydraulic power for the flight controls [and consequent reduced ability of the flightcrew to maintain the safe flight and landing of the airplane]. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2005-18-16: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF34-3A1 turbofan engines installed on Bombardier series Regional Jets with certain high pressure turbine (HPT) rotating components installed. This AD requires removal from service of certain HPT components prior to the parts exceeding their designated life limits. This AD results from the discovery that the manufacturer removed certain part numbers of HPT rotating components from the Life Limits section of the CF34 Engine Manual, SEI-756. The effect of this manual change was the removal of life limits from certain components that are eligible for installation in GE CF34-3A1 engines. We are issuing this AD to impose life limits on these HPT rotating components to prevent low cycle fatigue (LCF) cracking and failure of those components, which could result in uncontained engine failure and damage to the airplane.