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85-23-06: 85-23-06 CESSNA: Amendment 39-5225. Applies to Model T303 (Serial Numbers T30300001 thru T30300315) airplanes certificated in any category. Compliance: Required within the next 10 hours time-in-service from the effective date of this AD, unless already accomplished. To preclude the possibility of the fuel metering unit tee fittings from leaking and causing a fire, accomplish the following: (a) Remove both engine cowlings to the extent required to adequately examine the turbocharger inlet area and fuel metering units. Visually inspect the turbocharger inlet and surrounding area for evidence of significant damage caused by exhaust gas leakage. If noted, prior to further flight, repair the damage and eliminate the cause of the leak. (b) With the aircraft auxiliary fuel pumps on and the mixture control in the idle cutoff position, visually inspect the fuel metering unit tee fitting for cracking and leakage in the threaded area that goes into the fuel metering unit. If a crack and resultant leak is detected, prior to further flight replace the fitting, using a wrench on the fitting, to isolate the effects of attaching and tightening the fuel lines. Do not over torque the fitting when installing it on the metering unit. (c) The aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (d) Within five (5) days of accomplishing this AD, report, in writing, all defects found during accomplishment of this AD to the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. (Reporting approved by the Offices of Management and Budget under OMB No. 2120-0056.) (e) An equivalent method of compliance may be used when approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, Central Region, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. This amendment becomes effective on February 5, 1986, to all persons except those persons to whom it has already been made effective by priority letter from the FAA dated November 14, 1985, and is identified as AD 85-23-06.
2006-25-17: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires repetitive cleaning/inspecting of the drain hole of each pitot static probe and repetitive cleaning of the pitot lines in the pitot static system. This AD results from reports of incidents of airspeed mismatch between the pilot, co-pilot, and standby airspeed indications caused by contamination in the pitot static system. We are issuing this AD to prevent erroneous/misleading altitude and airspeed information from a contaminated pitot static system to the flightcrew, which could reduce the ability of the flightcrew to maintain the safe flight and landing of the airplane.
2021-14-13: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney (PW) PW2037, PW2037M, PW2040, and F117-PW-100 model turbofan engines. This AD was prompted by a report of an uncontained engine failure resulting from cracks in the knife edge of the high- pressure turbine (HPT) 2nd-stage air seal assembly. This AD requires fluorescent penetrant inspections (FPIs) and visual inspections of the HPT 2nd-stage air seal assembly and, depending on the results of the inspections, replacement of the HPT 2nd-stage air seal assembly with a part eligible for installation. This AD also requires replacement of the affected HPT 2nd-stage air seal assembly, depending on the engine model, at either the next engine shop visit or the next piece-part opportunity. The FAA is issuing this AD to address the unsafe condition on these products.
89-10-02: 89-10-02 AEROSPATIALE: Amendment 39-6201. Applicability: Model ATR42-300 series airplanes up to and including serial number 120, which have not been modified in accordance with Service Bulletin ATR42-28-0013, Revision 2, dated January 6, 1989, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent a fuel fire in the nacelle, accomplish the following: A. Within 300 flight hours after the effective date of this AD and thereafter at intervals not to exceed 300 flight hours, and at each engine removal/installation, inspect the engine fuel supply hoses for fuel leakage in accordance with Aerospatiale Service Bulletin ATR42-28-0012, dated September 9, 1988. If leakage is found, before further flight, repair or replace the leaking fuel line, in accordance with the service bulletin. B. Replacement of the engine fuel supply hoses in accordance with Aerospatiale Service Bulletin ATR42-28-0013, Revision 2, datedJanuary 6, 1989, constitutes terminating action for the repetitive inspections required by paragraph A., above. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. D. 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 inspections and/or modification required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined atthe FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6201, AD 89-10-02) becomes effective on May 29, 1989.
86-17-09: 86-17-09 BELL HELICOPTER TEXTRON, INC.: Letter issued August 21, 1986. Applies to all Bell Helicopter Model 212 helicopters, S/N 30501 through 30999, 31101 through 31273, and 31275; 32101 through 32142 and 32201 through 32262 that have T/R hub and blade assembly, P/N 212-011-701-001 installed, certified in any category. Compliance required as indicated unless already accomplished. To prevent failure of the tail rotor control, accomplish the following: (a) Within 25 hours' time in service after receipt of this AD, visually inspect the T/R hub assembly P/N 212-011-701-3, in accordance with Part 1 of Bell Helicopter Textron, Inc. (BHTI), Alert Service Bulletin (ASB) 212-86-39, Revision "A," dated July 23, 1986. (1) If the (P/N) 212-011-716-1 T/R trunnion housing is cracked or there is axial play in the T/R trunnion, or if there are excess balance washers, comply with Part II of the Alert Service Bulletin before further flight. (2) Repeat this inspection every 25 hours' time in service until paragraph (b) of this AD is accomplished. (b) Remove the 212-011-701-1 T/R hub and blade assembly and inspect the trunnion bearing housing, P/N 212-011-716-1, as detailed in Part II of BHTI ASB 212-86-39, Revision "A", dated July 23, 1986, within 150 hours' time in service or within 60 days after the issue date of this AD, whichever occurs first. Replace any housing having an end web thickness of .059 inch or less with a serviceable part. An alternate method of compliance or adjustment of the compliance time, which provides an equivalent level of safety, may be approved by the Manager, Helicopter Certification Branch, Aircraft Certification Division, FAA, Southwest Region. This airworthiness directive becomes effective upon receipt.
2006-25-10: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 and Model Avro 146-RJ airplanes. This AD requires calculating the current life of each lift spoiler jack, and eventually replacing each lift spoiler jack. This AD results from a review of all system components as part of the life- extension program for the affected airplanes that indicated the fatigue life limit of certain lift spoiler jacks cannot be extended from the current life limit. We are issuing this AD to prevent failure of the lift spoiler jack, and consequent increased drag and uncommanded roll inputs, which could reduce the flightcrew's ability to control the airplane.
2006-25-11: The FAA is adopting a new airworthiness directive (AD) for certain Lockheed Model L-1011 series airplanes. This AD requires a one- time detailed inspection of the C112 harness clamp assembly for proper installation, a one-time detailed inspection of the C112 and C162 harness assemblies for damage, and corrective actions if necessary. This AD results from a report of electrical arcing of the essential bus feeder cables behind hinged circuit breaker panel CB3 P-K. We are issuing this AD to prevent arcing of essential bus feeder cables due to improper installation of the harness C112 clamp assembly, which could result in loss of electrical systems and smoke and/or fire behind the CB3 P-K hinged circuit breaker panel in the flight compartment.
2021-11-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters. This AD was prompted by a report that damage (scorch marks) was found on an internal life raft installation that contained a half rescue kit. This AD requires identifying the part number and serial number of each half rescue kit located in the internal life raft installation and, depending on the findings, inspecting the life raft for damage, inspecting the condition of the flashlight battery, testing the flashlight battery, and replacing the life raft or flashlight battery (including the leak test) as applicable, as specified in a European Aviation Safety Agency (now 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.
2021-14-01: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report that certain airplanes have navigation units with outdated magnetic variation (MagVar) tables. This AD requires revising the existing airplane flight manual (AFM) and applicable corresponding operational procedures to update the flight management system (FMS) limitations. The FAA is issuing this AD to address the unsafe condition on these products.
2006-25-07: The FAA is adopting a new airworthiness directive (AD) for all EMBRAER Model EMB-135ER and -135KE airplanes and Model EMB-145, -145ER, -145MR, -145MP, and -145EP airplanes. This AD requires inspecting the fuel quantity indication system (FQIS) wire harness and the direct current (DC) fuel pump wire harness to determine if the harnesses are properly attached at their respective attachment points and properly separated from one another, and performing corrective actions if necessary. This AD results from a report that the FQIS wire harness may not be properly attached at its attachment points or properly separated from the DC fuel pump wire harness. We are issuing this AD to prevent chafing between those harnesses or chafing of the harnesses against adjacent airplane structure or components, which could present a potential ignition source that could result in a fire or explosion.