Results
2004-11-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model BAe.125 series 800A (including C- 29A and U-125 variant) and 800B airplanes; and Model Hawker 800 (including U-125A variant) and 800XP airplanes; that requires a functional test of the engine fire extinguishing wiring for the appropriate installation; verification of the correct wiring connector installation; correction of wiring if necessary; and installation of new marker bands. This action is necessary to prevent incorrect wiring of the engine fire extinguisher bottles, which could result in one or both fire extinguisher bottles being discharged into the wrong engine nacelle. This action is intended to address the identified unsafe condition.
2021-23-19: The FAA is adopting a new airworthiness directive (AD) for certain Pacific Aerospace Limited Model 750XL airplanes. 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 identifies the unsafe condition as insufficient separation of ground terminations for individual power sources and static grounds. This AD requires inspecting and separating, if applicable, the battery and generator common ground connections on the airframe. The FAA is issuing this AD to address the unsafe condition on these products.
2021-23-09: The FAA is superseding Airworthiness Directive (AD) 2015-16-07 R1, which applied to certain Reims Aviation S.A. (type certificate now held by ASI Aviation) Model F406 airplanes. AD 2015-16-07 R1 required inspecting the left-hand and right-hand rudder control pedal torque tubes and replacing with a serviceable part as necessary. Since the FAA issued AD 2015-16-07 R1, the European Aviation Safety Agency (EASA) superseded its mandatory continuing airworthiness information (MCAI) to correct an unsafe condition on these products. This AD retains the requirements of AD 2015-16-07 R1, expands the applicability, and requires repeating the inspections using updated procedures. The FAA is issuing this AD to address the unsafe condition on these products.
73-07-08: 73-07-08 PRATT & WHITNEY: Amendment 39-1616 as amended by Amendment 39-1630. Applies to all Pratt & Whitney JT3D-1, JT3D-1-MC6, JT3D-1-MC7, JT3D-3 and JT3D-3B model engines containing fuel control to fuel return line elbow P/N 424790 and jam nut P/N 217477. Compliance required within the next 500 hours time in service after the effective date of this AD and every 1000 hours in service thereafter, or until modified in accordance with the service bulletin referenced in paragraph (b)(2) or equivalent method approved by the Chief, Engineering and Manufacturing Branch, New England Region. To prevent the possibility of fuel leakage due to loosening of fuel control to fuel pump return tube elbow P/N 424790, and jam nut P/N 217477, check jam nut torque value. (a) If found to be a minimum of 285 in-lbs., continue in service operation. (b) If the jam nut is found to be less than 285 in-lbs., break the connection and examine the mating threads of the elbow P/N 424790 and fuel control cover P/N 704972-1 on their loaded sides for wear. NOTE: The loaded side will be on the fuel side (inside) rather than the air side (outside) of the cover. (1) If the threads are not worn remake the fitting according to the instructions given in the Overhaul Manual, P/N 411568, Section 72-00, Fits and Clearances. (2) If the threads of the elbow. P/N 424790, or fuel control cover P/N 704972-1, are found worn replace with new or serviceable parts of same part number or with P/N 483848 elbow and associated hardware in accordance with Pratt & Whitney Service Bulletin No. 1511 Revision 4, dated June 20, 1969, or later FAA approved revision. (c) Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust repetitive inspection intervals specified in this AD. Amendment 39-1616 became effective April 11, 1973. This amendment 39-1630 becomes effectiveupon publication in the Federal Register.
96-12-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Beech (Raytheon) Model BAe 125 series 800A and Model Hawker 800 airplanes, that requires modification of the airframe structure in the lower area of the fuselage aft of the wing rear spar. For certain airplanes, this amendment also requires a functional test to determine if a particular bolt fouls the flap control system. This amendment is prompted by reports of restricted control of the aileron due to water accumulation that froze in the area around an aileron pulley located in the lower area of the fuselage aft of the wing rear spar. The actions specified by this AD are intended to prevent such water accumulation, which could freeze and result in restricted control of the ailerons; subsequently, this could reduce the pilot's ability to initiate roll control during critical phases of flight.
2004-11-02: This amendment adopts a new airworthiness directive (AD), [[Page 31001]] applicable to certain Saab Model SAAB SF340A and Model SAAB 340B series airplanes, that requires inspections of the internal and external structure of the nacelles for cracks, deformations, or other damage, and corrective actions if necessary. This action is necessary to prevent fatigue cracks in the outer flange of the nacelle frame, which could result in reduced structural integrity of the nacelle supporting structure. This action is intended to address the identified unsafe condition.
96-12-18: This amendment adopts a new airworthiness directive (AD) that is applicable to all McDonnell Douglas Model DC-10 series airplanes and Model MD-11F airplanes. Among other things, this amendment requires repetitive leak checks of the lavatory drain system and repair, if necessary; provides for the option of revising the FAA-approved maintenance program to include a schedule of leak checks; and requires the installation of a cap on the flush/fill line. This amendment is prompted by continuing reports of damage to engines and airframes, separation of engines from airplanes, and damage to property on the ground, caused by "blue ice" that forms from leaking lavatory drain systems on transport category airplanes and subsequently dislodges from the airplane fuselage. The actions specified by this AD are intended to prevent such damage associated with the problems of "blue ice."
2021-23-11: The FAA is adopting a new airworthiness directive (AD) for certain Learjet Inc. Model 45 airplanes. This AD was prompted by a report of a fuel leak due to a cracked fuel line between the engine fuel control and the engine fuel flow meter. This AD requires replacing the existing fuel flow meter bracket assembly with a redesigned bracket assembly and reporting information to the FAA. The FAA is issuing this AD to address the unsafe condition on these products.
65-14-05: 65-14-05 LOCKHEED: Amdt. 39-95 Part 39 Federal Register June 26, 1965. Applies to Model 1329 Aircraft Serial Numbers 5001 through 5057. Compliance required within the next 25 hours' time in service after the effective date of this AD unless already accomplished. To prevent improper engine fire and overheat warning indications, accomplish the following: Inspect in the following manner all engine fire (forward) and overheat (aft) detector electrical systems to ascertain that each detector is properly connected to the correct fire warning control unit: (a) Disconnect electrical connector from the control unit corresponding to the detector element to be checked. (b) Connect one lead of a Simpson 260 meter, or equivalent, to pin C or D of the fire warning control unit connector, ships, wiring, and one lead to ground. (c) Set the meter to read a resistance of 10,000 Ohms or greater, depending on the unit being checked and the temperature of the unit. (d) Applyheat to a segment of the detector element being checked, using a heater blower with a temperature range of 500 degrees to 750 degrees F., or equivalent, and observe the meter reading. The blower should be held approximately 1/2 inch from the element. Make sure no wind interferes to cut down the heat conduction to the element and to assure a good meter reading. (e) In approximately 5 to 10 seconds of elapsed time after application of heat, the meter reading should decrease at a moderate rate. A decreasing resistance reading indicates correct wire connections. (f) After the above procedure is followed and the results are not as required, a complete check of the fire warning circuitry for the engine in error must be made using Lockheed Drawing No. JR156 (wiring diagram). Correct all discrepancies. (g) When all circuits are in proper operating condition, the aircraft may be returned to service. Other means of compliance with the requirements of this directive may be utilized if approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. (Lockheed Alert Service Bulletins Nos. 329-202 and 329-202A cover this same subject.) This directive effective June 26, 1965.
2021-23-14: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by reports of erratic electrical system status on the push button annunciators (PBAs) and the engine instrument and crew alerting system (EICAS). This AD requires revising the existing airplane flight manual (AFM) to incorporate procedures to be applied during erroneous electrical status indication conditions. The FAA is issuing this AD to address the unsafe condition on these products.
67-09-03: 67-09-03 BRITISH AIRCRAFT: Amdt. 39-372 Part 39 Federal Register March 21, 1967. Applies to Model BAC 1-11 400 Series Airplanes. Compliance required as indicated. To prevent interference between the flap jack screw and flap carriage assembly, accomplish the following: (a) Within the next 500 hours' time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 1,000 hours' time in service, measure the clearance between the head of the nut on flap screw jack P/N CH526-010 and the inside faces of the lower rollers on the aft flap carriages P/N AK09 A1263 and AK09 A1265 and AK09 A1266 at all 8 screw jack positions in accordance with BAC Alert Service Bulletin 27-A-PM2469 or later ARB-approved issue. If clearance is less than 0.025 inch, rework the nut stop head radius in accordance with BAC Service Bulletin No. 27-A-PM2469 or later ARB-approved issue. (b) The repetitive inspections required in (a) may be discontinued if the airplanes are modified in accordance with BAC Service Bulletin 27-A-PM2469 paragraph (a) or (b) and PM2469 paragraph (c) and PM2469 paragraph (d) or (e) and PM2469 paragraph (f) or (g) or later ARB-approved issue. This directive effective April 20, 1967.
2004-10-15: The FAA adopts a new airworthiness directive (AD) for certain GARMIN International Inc. GTX 330/GTX 330D Mode S transponders that are installed on aircraft. This AD requires you to install GTX 330/330D Software Upgrade Version 3.03, 3.04, or 3.05. This AD is the result of observations that the GTX 330 and GTX 330D may detect, from other aircraft, the S1 (suppression) interrogating pulse below the Minimum Trigger Level (MTL) and, in some circumstances, not reply. The GTX 330/330D should still reply even if it detects S1 interrogating pulses below the MTL. We are issuing this AD to prevent interrogating aircraft from possibly receiving inaccurate replies due to suppression from aircraft equipped with the GTX 330/330D Mode S Transponders when the pulses are below the MTL. The inaccurrate replies could result in reduced vertical separation or unsafe TCAS resolution advisories.
2021-23-04: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model A109E helicopters. This AD was prompted by reports of cracking in the center fuselage frame assembly in the intersection of the lateral pylon and floor spar at station (STA) 1815 on the left- and right-hand sides. This AD requires repetitive inspections of the intersection of the lateral pylon and floor spar at STA 1815 for cracking and, depending on the findings, repair, 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.
2021-23-10: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AW109SP helicopters. This AD was prompted by reports of an ineligible hydraulic pump being installed on Model AW109SP helicopters. This AD requires inspecting each hydraulic pump for damage and, depending on the inspections results, removing parts from service and accomplishing other corrective actions. This AD also requires removing certain parts from service before they exceed their life limits. The corrective actions are required to be accomplished 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.
2004-10-08: The FAA adopts a new airworthiness directive (AD) for all Alexander Schleicher GmbH & Co. Segelflugzeugbau (Alexander Schleicher) Model ASH 25M sailplanes equipped with fuel injected engine IAE50R-AA. This AD requires you to inspect the fuel line for correct fittings, and, if any incorrect fitting is found, replace the fuel line. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect and correct any fuel lines with improper fittings, which could result in fuel leakage and a possible fire hazard.
2004-10-09: This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model BAe 146 series airplanes, that requires repetitive detailed inspections for heat damage to any in-line splice in the auxiliary power unit (APU) and integrated drive generator (IDG) feeder cable circuits, and corrective action if necessary. This AD also provides for optional terminating action for the repetitive inspections. This action is necessary to prevent overheating of the in-line splices of the APU and IDG feeder cables, which can lead to smoke, fumes, and possible fire in the flight deck and cabin. This action is intended to address the identified unsafe condition.
2021-23-20: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 and 787-9 airplanes. This AD was prompted by reports that shimming requirements were not met during the assembly of certain structural joints, which can result in reduced fatigue thresholds of the affected structural joints. This AD requires repetitive inspections for cracking of certain areas of the front spar pickle fork and front spar outer chord and repair of any cracking found. The FAA is issuing this AD to address the unsafe condition on these products.
68-23-05: 68-23-05 LOCKHEED: Amendment 39-688. Applies to all Lockheed Model 188A and 188C airplanes. (1) Within the next 50 hours' time in service after the effective date of this AD, unless previously accomplished within the preceding 575 hours' time in service, visually inspect, either internally or externally, No. 1 upper wing plank at No. 2 and 3 nacelles from the forward edge of plank No. 1 aft 4 inches and between wing station 168 and wing station 174, except for those portions of that area hidden by spar cap or rib elements, to detect any evidence of cracks originating at that point and extending aft and outboard. Where the required visual inspection cannot be performed because of existing repairs, the prescribed area will be inspected in accordance with an inspection procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region. (2) If cracks exist, appropriate repair must be accomplished before further flight in a manner approved by the Chief, AircraftEngineering Division, FAA Western Region. (3) After initial inspection, such inspection shall thereafter be performed at intervals not to exceed 625 hours' time in service. (4) The repetitive inspection required by (3) may be discontinued upon completion of the appropriate preventive repair installation described in Section I.C.I. or preventive reinforcement of Section I.C.II. of Lockheed Service Bulletin No. 85/SB-665 dated November 11, 1968, (or later FAA approved revision) or upon completion of an equivalent repair approved by the Chief, Aircraft Engineering Division, FAA Western Region. (5) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA western 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 that operator. Airplanes with cracked wing planks may be flown in accordance with special flight permits issued pursuant to FAR 21.197 to a base where repair can be accomplished. Effective July 5, 1968. Revised December 6, 1968.
2004-10-14: The FAA is adopting a new airworthiness directive (AD) that supersedes an existing AD, for Lycoming Engines (formerly Textron Lycoming), direct-drive reciprocating engines (except O-145, O-320-H, O- 360-E, LO-360-E, LTO-360-E, TO-360-E, O-435, and TIO-541 series engines). That AD currently requires inspection of the crankshaft gear installation and rework or replacement of the gears where necessary after a propeller strike, sudden stoppage, at overhaul, or whenever gear train repair is required. This AD requires the same actions but makes the correction that the existing gear retaining bolt and lockplate be removed from service and new hardware installed, and revises the definitions for sudden stoppage and propeller strike. This AD removes the requirement to perform inspections at overhaul and during repair of the gear train, because Lycoming has incorporated those procedures from their Service Bulletin into their Overhaul Manual. This AD results from a change to the definition of a propeller strike or sudden stoppage. We are issuing this AD to prevent loosening or failure of the crankshaft gear retaining bolt, which may cause sudden engine failure.
2012-02-51: We are publishing a new airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (Bell) Model 206L, 206L-1, 206L-3, and 206L-4 helicopters with certain main rotor blades installed to reduce the life limit of those blades. This AD is prompted by two accidents and the subsequent investigations that revealed that, in each accident, a main rotor blade failed because of fatigue cracking. These actions are intended to prevent failure of the main rotor blade and subsequent loss of control of the helicopter.
2021-23-02: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-401 and - 402 airplanes. This AD was prompted by reports of loss of hydraulic fluid and annunciation of the check fire detect light. This AD requires doing a detailed visual inspection for chafing and proper clearance of the left-hand (LH) and right-hand (RH) main landing gear (MLG) primary zone advanced pneumatic detector (APD) sensing lines, the hydraulic tube assemblies, and the surrounding structure, and doing all applicable corrective action. The FAA is issuing this AD to address the unsafe condition on these products.
70-17-02: 70-17-02 MOONEY: Amdt. 39-1069 as amended by Amendment 39-1072. Applies to Mooney Model M-10 Airplanes. Compliance required before further flight after the effective date of this AD, unless already accomplished. To detect the use of improper screws attaching the left and right rudder pedal shaft assemblies (P/N 720098-1 and 720098-501, respectively) to the nose wheel steering tie rods (P/N 720084 and 720088, respectively), accomplish the following inspection and rework as required or an equivalent approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, FAA, Fort Worth, Texas: a. Remove seats and floorboard. b. Remove screws from left and right rudder pedal shaft assemblies attaching the nose wheel steering tie rods. The screws, nuts and washers should consist of: (1) NAS 221-16 screws (2) AN 363-1032 nuts (3) AN 960-10 washers c. Reinstall the correct hardware specified in b(1), (2) and (3) above. (NOTE: The M-10 Parts Catalog refers to AN 509-10R20 screws, left rudder pedal shaft assembly, P/N 720061, and right rudder pedal shaft assembly, P/N 620062, which are incorrect references.) d. Check the rudder and nose wheel rigging in accordance with the M-10 Service and Maintenance Manual number 10-S.M.-70 dated February, 1970, prior to the reinstallation of the floorboard and seats. Amendment 39-1069 effective on publication in the Federal Register. This amendment 39-1072 becomes effective August 31, 1970.
2021-22-21: The FAA is adopting a new airworthiness directive (AD) for all ASI Aviation (type certificate previously held by Reims Aviation S.A.) Model F406 airplanes. This AD was prompted by 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 identifies the unsafe condition as failure of a circuit breaker (CB) switch. This AD requires replacing certain CB switches and establishing a life limit for the CB switches. The FAA is issuing this AD to address the unsafe condition on these products.
2021-22-15: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS332L2 and EC225LP helicopters. This AD was prompted by a design deficiency. This AD requires modifying the hoist control power supply, 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.
87-26-06: 87-26-06 BRITISH AEROSPACE (BAe): Amendment 39-5806. Applies to all Model H.S. 748 series airplanes, pre-modification 7205, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent structural damage to the airplane due to fatigue cracking of the hydraulic accumulators, accomplish the following: A. Within 300 hours time-in-service after the effective date of this AD, conduct the inspections of the hydraulic brake accumulator, as specified in Paragraph 2.B(1) of BAe H.S. 748 Service Bulletin 29/42, dated February 10, 1986. Any discrepancies detected must be corrected prior to further flight. B. Within 1,000 hours time-in-service or one year after the effective date of this AD, whichever occurs first, and thereafter at intervals not to exceed 1,000 hours time-in-service or one year, whichever occurs first, conduct the inspections of the hydraulic brake accumulator, as specified in Paragraph 2.B(2) of BAe H.S. 748 Service Bulletin 29/42 dated February 10, 1986. Any system defects found must be corrected prior to further flight. C. Within 2,500 hours time-in-service, or two years after the effective date of this AD, whichever comes first, and thereafter at intervals not to exceed 2,500 hours time-in-service or two years, whichever occurs first, conduct the inspections of the hydraulic accumulator as specified in Dunlop Service Bulletin 29/175, dated February 4, 1986. Replace, prior to further flight, any units that do not meet the limits specified in the service bulletin. D. 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. E. 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 modifications 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 British Aerospace Group, Weybridge Division Greengate, Middleton, Manchester M24 1SA, England; and Dunlop Limited, Aviation Division, Dunlop House, Ryder Street, St. James's, London SW1Y.6PX, England. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way, Seattle, Washington. This amendment becomes effective February 1, 1988.