Results
2022-21-06: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CF34-8C and CF34-8E model turbofan engines. This AD was prompted by a report of a crack found on the low-pressure turbine (LPT) stage 5 disk at the forward arm area. This AD requires the removal of the affected LPT stage 5 disk and replacement with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2000-07-27: This amendment adopts a new airworthiness directive (AD) that is applicable to various transport category airplanes equipped with certain Honeywell air data inertial reference units (ADIRU). This action requires inspection of a failed ADIRU to determine its modification status, and replacement of an unmodified failed ADIRU with a serviceable ADIRU. This action also provides for optional terminating action for the requirements of the AD. This amendment is prompted by reports of dual critical failures of inertial reference units on ADIRU's during flight. The actions specified in this AD are intended to prevent loss of the main sources of attitude data, consequent high pilot workload, and a significant increase in the likelihood of pilot error.
99-13-08 R1: This amendment revises an existing airworthiness directive (AD), applicable to all Lockheed Model L 1011-385 series airplanes, that currently requires inspections to detect cracking and other discrepancies of certain web-to-cap fasteners of the rear spar between inner wing station (IWS) 310 and IWS 343, and of the web area around those fasteners; various follow-on actions; and modification of the web-to-cap fastener holes of the rear spar between IWS 299 and IWS 343, which, when accomplished, defers the initiation of the inspections for a certain period of time. The actions specified by that AD are intended to prevent fatigue cracking in the web of the rear spar of the wing, which could result in failure of the rear spar of the wing and consequent fuel spillage. This amendment, for certain airplanes, extends the compliance time for the modification of the web-to-cap fastener holes, and eliminates references to modification of the outboard spar.
86-05-12: 86-05-12 HARTZELL PROPELLER PRODUCTS DIVISION: Amendment 39-5333. Applies to Hartzell Model HC-B3TN-5( )/T10282( ) propellers installed on Fairchild Model SA226-TC aircraft modified by Garrett STC SA344GL or Par Air STC SA4872SW with TPE331-10UA engines. Compliance required prior to accumulating 1,000 hours time in service since new or 300 hours time in service since overhaul, or within 30 days after the effective date of this AD, whichever occurs later, unless already accomplished. To prevent propeller blade separation near the hub which could result in engine separation from the aircraft, accomplish the following: (a) Remove propeller from aircraft. (b) Accomplish the following in accordance with Hartzell Service Bulletin No. 136C dated March 3, 1986, or FAA approved equivalent: (1) Disassemble propeller and visually inspect the blade pilot tube bore area. Particular attention shall be made to area between the inner needle bearing assembly and bearing spacer. (2) Remove all evidence of scratches, tool marks, corrosion, etc. in the blade pilot tube bore area. Do not exceed the maximum rework limitations defined in the service bulletin. (3) Etch the blade pilot tube bore area prior to penetrant inspection. Ensure removal of all etching solution. (4) Penetrant inspect the blade pilot tube bore area. (5) Coat the blade pilot tube bore area with alodine. (6) Install bearing spacer and inner needle bearing assembly. Pilot tube bore must be lubricated to facilitate bearing installation. (c) Replace, prior to further flight, all blades showing evidence of cracks or other unairworthy conditions with airworthy blades. (d) Place the following WARNING in the Limitation Section of the FAA approved airplane flight manual supplement: "The TPE331-10UA engine is capable of developing in excess of the maximum allowable torque approved for this installation. Use of torque in excess of the maximum approved limits may cause propeller failure." NOTES: (1) Propeller blades with serial numbers subsequent to F74359 have had the intent of this AD incorporated during manufacture and are not affected by this AD. (2) This AD does not apply to propellers installed on TPE331-3 engines unless the propellers were previously installed on TPE331-10UA engines for at least 1000 hours time in service since new or at least 300 hours time in service since overhaul. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FAR) 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018. Hartzell Service Bulletin No. 136C dated March 3, 1986, identified and described in this document is incorporated herein and made a part hereof pursuant to 5 U.S.C.552(a)(1). All persons affected by this directive who have not already received this document from the manufacture may obtain copies upon request to Hartzell Propeller Products Division, TRW Aircraft Components Group, 350 Washington Ave., Piqua, Ohio 45356. This document also may be examined at the Office of Regional Counsel, FAA, Attn: Rules Docket No. 86-ANE-9, 12 New England Executive Park, Burlington, Massachusetts 01803, weekdays, except Federal holidays, between 8:00 a.m. and 4:30 p.m. This amendment becomes effective June 27, 1986, as to all persons except those persons to whom it was made immediately effective by priority letter AD 86-05-12 issued March 7, 1986, which contained this amendment.
99-23-12: This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that requires repetitive inspections to detect damage and discrepancies of various control cables and certain fairleads/swivel guides for the autopilot, elevator, rudder, aileron, and engine; and corrective actions, if necessary. 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 failure of the pilot s control cables for the autopilot, elevator, rudder, aileron, and engine, which could result in reduced controllability of the airplane.
2015-02-15: We are adopting a new airworthiness directive (AD) for all Quest Aircraft Design, LLC Model KODIAK 100 airplanes. This AD requires inspecting the inboard upper and lower elevator skins for cracking, repairing cracks, and installing doublers. This AD was prompted by a report that fatigue cracks were found in the lower elevator skins. We are issuing this AD to correct the unsafe condition on these products.
2000-07-22: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300-600 series airplanes, that requires repetitive inspections to detect cracking of the doubler angle and discrepancies of the fasteners that connect the doubler angle and the bottom panel of the center wing box, and corrective actions, if necessary. 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 detect and correct fatigue cracking in the doubler angle and discrepancies of the fasteners that connect the doubler angle and the bottom panel of the center wing box. Such cracking and discrepancies could result in reduced structural integrity of the airplane.
2000-07-29: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes, that currently requires a one-time operational test of the fire shut-off valves (FSOV) to determine if the FSOV's are functioning correctly, and replacement of failed parts with new or serviceable parts. This amendment requires repetitive performance of the operational test. This amendment also limits the applicability to airplanes installed with certain FSOV's. 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 detect and correct failure of the FSOV's to close, which could result in failure of the engine fire shut-off system, and consequent inability to extinguish an engine fire.
80-06-05: 80-06-05 SLICK ELECTRO, INC.: Amendment 39-3718. Applies to the following Slick magneto models and associated serial and impulse coupling numbers: MAGNETO MODEL NO. (1) SERIAL NO. (1) (2) IMPULSE COUPLING NO. (1) 447 & 447R 9040001 thru 9040049 M2374 662 & 662R 9020462 thru 9070000 M2362 664 & 664R 9040001 thru 9040086 M2370 680 & 680R 9020462 thru 9070000 M2369 4151 & 4151R 9020017 thru 9070000 M1709 4152 & 4152R 9020017 thru 9070000 M1709 4181 & 4181R 9020017 thru 9070000 M1709 4201 & 4201R 9020210 thru 9070000 M3007 4251 & 4251R 9030001 thru 9070000 M3163 4281 & 4281R 9030001 thru 9070000 M3007 4230 & 4230R 9040001 thru 9040197 M3068 6210 8090073 thru 9070000 M3050 6214 8050001 thru 9070000 M3089 (3) M2371, M3100, & M3165 NOTES: (1) Any of the units listed were manufactured subsequent to January 1979. (2) Any magneto serial numbers between and including the lower and upper limits as shown are affected by this AD. (3) These coupling numbers are for parts used as spares and also must be tested. The magneto models as listed above are installed on, but not limited to, the following engines: Lycoming AEIO-360 AEIO-320 IO-320 O-235 O-320 O-360 Continental A-65-8 A-75-8 C-85-8 C-90-8 O-200-A O-300-A, -B, -C, -D O-470-U IO-360-KB IO-470 IO-520-A, -B, -F TSIO-470 TSIO-520-T Compliance is required as indicated unless already accomplished. To prevent a possible magneto failure and subsequent engine or accessory malfunction, accomplish the following: Prior to the next ten (10) hours of aircraft time in service, or within the next thirty (30) calendar days from the date of this AD, whichever occurs first, complete the following comparative hardness test procedures: 1. Remove the impulse coupling magneto(s) from the engine per engine manufacturer's instructions. 2. Remove the impulse coupling assembly from the magneto frame per Slick's maintenance and overhaul instructions. 3. Establish a reference level of acceptable metal hardness by sliding a fine cut mill file over the flat surface of either pawl. The file will slide freely and will only burnish the hard surface of the pawl. 4. By a similar filing action, test for the hardness of each of the two rivet heads. 5. If there is resistance to sliding and material is removed from the rivet head, the rivet has not been heat treated and the coupling assembly must be replaced. Return the defective coupling assembly to a Slick Electro, Inc. distributor. 6. If hardness of the rivet heads and pawls are equivalent, reassemble and identify AD compliance by metal stamping a letter "C" on the Slick insignia located on the side of the magneto identification plate. 7. If the results of the comparative hardness test on the rivet(s) are questionable, the coupling assembly must be replaced. This amendment becomes effective March 28, 1980, as to all persons except those to whom it was made immediately effective by the airmail letter dated February 4, 1980, which contained this amendment.
2000-07-25: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-IV series airplanes. This action requires modification of the power feeder cable assemblies of the left and right engine alternators. This amendment is prompted by an incident of an in-flight engine fire on a Model G-IV series airplane due to chafing of the power feeder cable assembly of an engine alternator. The actions specified in this AD are intended to prevent interference and chafing between the alternator power feeder cables and adjacent structure, which could result in an electrical short circuit and consequent fire ignition source in the engine compartment.
88-05-02: 88-05-02 BRITISH AEROSPACE (BAe) PLC: Amendment 39-5858. Applies to Model DH/BH/HS 125 series airplanes listed in BAe 125 Service Bulletins 57-67 and 53-63, both dated February 27, 1987, certificated in any category. Compliance is required as indicated, unless previously accomplished. To detect fatigue cracking in the airplane structure, which could result in the inability of the structure to meet required loads, accomplish the following: A. For airplane serial numbers as listed in BAe-125 Service Bulletin 57-67 dated February 27, 1987: Prior to the accumulation of 12,000 flights, or within 8 months after the effective date of this AD, whichever occurs later, visually inspect the wing bottom skin for cracks at the flap outboard hinge fitting in accordance with that service bulletin. Repair detected cracks prior to further flight in accordance with an FAA approved method. B. For airplane serial numbers as listed in BAe-125 Service Bulletin 53-63, dated February27, 1987: Prior to the accumulation of 7,500 flights, or within 6 months after the effective date of this AD, whichever occurs later, visually inspect the fuselage skin beneath the canopy blister for cracks in accordance with that service bulletin. Repair detected cracks prior to further flight in accordance with an FAA approved method. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. 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 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, Inc., Service Bulletin Librarian, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the 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 becomes effective April 6, 1988.
2000-07-21: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires a general visual inspection of wiring behind the control panel of the auxiliary power unit (APU) located in the cockpit to detect chafing; repair if necessary; and modification of the wiring. This amendment is prompted by an incident of chafing of wire bundles of the control module of the APU. The actions specified by this AD are intended to prevent such chafing and resultant arcing due to insufficient clearance between the wire bundles and the airplane structure, which could result in smoke and fire in the flight deck.
2015-02-08: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Corporation (RRC) AE 2100 series turboprop engines and AE 3007A and 3007C series turbofan engines. This AD was prompted by reports of pitting in the wheel bores and subsequent RRC analysis that concluded that lower life limits are needed for the affected turbine wheels. This AD requires a reduction for the approved life limits of the affected turbine wheels. This AD also requires an eddy current inspection (ECI) of certain RRC engines with affected turbine wheels. We are issuing this AD to prevent uncontained failure of the turbine wheels, damage to the engine, and damage to the airplane.
2000-07-23: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100 series airplanes, that requires changing the power supply for the thunderstorm lights from the left secondary bus to the left essential bus. 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 a failure of the thunderstorm lights in the cockpit after loss of all generated electrical power. This condition could result in the cockpit instruments not being visible to the flight crew during certain emergency procedures, and consequent reduced controllability of the airplane.
49-38-01: 49-38-01 CONVAIR: Applies to All Model 240 Aircraft Incorporating Original Type Nose Strut Outer Cylinder, Bendix P/N 156842. To be accomplished on No. 1 inspection on all nose landing gear struts whose total operating time exceeds 1,000 hours. Cracking of the nose gear landing struts in the areas directly below the drag link attachment legs, has been experienced on some CV-240 service aircraft whose total time exceeds approximately 1,000 hours. These cracks appear to be the result of repeated loadings experienced by the gear during landings. In order to insure the continued airworthiness of the aircraft, the nose landing gear shall be examined closely, using visual means, for evidence of any cracks in the areas directly below the drag strut attachment lugs. When cracks are found, it may be possible to repair the damage by grinding, blending and polishing, depending upon the extent and depth of the cracks. All struts not eligible for such repairs are to be retired from service. (Bendix Service Bulletin L. G. 509 covers the subject.) The above-described inspection may be discontinued on those struts which have been reinforced by the addition of a support clamp and eyebolts, or their equivalent, to alleviate the loading condition which caused the development of cracks. Struts reworked in accordance with Bendix Service Bulletin L.G. 511 and incorporating a support clamp and eyebolts in accordance with Bendix Service Bulletin L.G. 510 are eligible for service and do not require the above inspection. (Bendix Service Bulletin L.G. 310 covers this same subject.)
2015-02-27: We are superseding Airworthiness Directive (AD) 2013-19-19 for certain Eurocopter France Model AS332C, AS332L, AS332L1, AS332L2, and EC225LP helicopters. AD 2013-19-19 required replacing certain serial- numbered main gearbox (MGB) bevel gear vertical shafts and inspecting and replacing, if necessary, each MGB bevel gear vertical shaft (shaft). This new AD requires the same actions as AD 2013-19-19 but corrects an error in the term used to identify an inspection qualification and updates the type certificate holder's name. This AD is prompted by two incidents of emergency ditching after warning indications of loss of MGB oil pressure. These actions are intended to detect a cracked shaft, which could result in loss of MGB oil pressure, loss of the MGB lubrication system, and subsequent loss of control of the helicopter.
2000-07-16: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F series airplanes, that currently requires modification of the external power feeder cable clamping installation. This amendment also requires a detailed visual inspection of the external power feeder cables to detect chafed or damaged wires; and repair, if necessary. This amendment is prompted by reports of damage to the external power feeder cables located under the forward cargo compartment floor, which was caused by excessive cable length and/or maintenance personnel stepping on the cables. The actions specified by this AD are intended to prevent arcing from occurring under the forward cargo compartment floor as a result of damaged external power feeder cables, a situation that could lead to a fire at this location.
70-16-01: 70-16-01 WOODWARD: Amdt. 39-1054. Applies to Woodward Governor Company primary turbo propeller governors mounted on United Aircraft of Canada PT6A series engines installed in airplanes incorporating propeller reversing provisions and Woodward Governor Company overspeed turbo propeller governors mounted on United Aircraft of Canada PT6A series engines installed in airplanes having auto feathering provisions. Compliance: Required within the next 50 hours' time in service after the effective date of this AD, unless previously accomplished. To prevent uncontrolled feathering accomplish the following or an equivalent procedure approved by the Chief, Engineering & Manufacturing Branch, FAA, Central Region. A) On primary propeller governors inspect for safety wire security the three coil retaining screws on the lock pitch solenoid valve, Woodward P/N 1310-506 or 1310-511. B) On overspeed propeller governors inspect for safety wire security the three coil retaining screws on the autofeathering solenoid valve, Woodward P/N 1310-110 or 1310-115. C) If screws inspected in accordance with Paragraphs A and B are not secured by safety wire, prior to return to service, replace said screws with socket head screws, Woodward P/N 1039-240, torque 18 to 22 lb. in., and secure by AMS 5685 0.024 to 0.026 in. dia. safety wire. Screws must be removed, replaced and torqued one at a time to avoid valve disassembly. NOTE: It may be necessary to remove two solenoid valve base retaining screws, Woodward P/N 33048-201 to gain access to the coil retaining screws. Removal and replacement of these two screws should be accomplished in the manner prescribed for the coil retaining screws. Woodward Service Bulletin 33532B, Supplement 1 and United Aircraft of Canada, Limited, Engine Service Bulletin No. 198 pertain to this subject. The inspections and modifications prescribed in this AD may be accomplished by a certified mechanic with a powerplant rating.NOTE: Governors to which this AD applies are known to be installed on the following airplanes, but this listing is not necessarily all inclusive: Primary propeller governors - Beech Models 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, B90, 99, 99A, 100; DeHavilland Models 1, 100, 200, 300; Helio Models HST-550, HST-550A; Swearingen Model SA26-5; Pilatus Model PC-6/B-H2, PC-6/B1-H2; McKinnon Models G21C, G21D, G21E, G21G; Grumman Model G21A (Serial Number B52 only); and Beech 18 series airplanes modified per STC SA 1016 WE. Overspeed propeller governors - Beech Model 65-A90-1, 68-A90-2, 65-A90-3, B90, 99, 99A and 100 airplanes. This amendment shall become effective August 4, 1970.
2015-02-18: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-201, -202, -203, -301, -302, and -303 airplanes. This AD requires a one-time ultrasonic inspection for fractures of all aft mount-pylon bolts of each engine. This AD was prompted by a report of one bolt on the aft engine mount upper beam found totally broken. We are issuing this AD to detect and correct fracture of the aft mount- pylon bolts, which could result in failure of the engine mount and consequent detachment of the engine.
2000-07-18: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F series airplanes, that requires a one-time detailed visual inspection of the generator power feeder wires to detect chafed or damage wires; repair, if necessary; and a modification of the generator power feeder wire installation. This amendment is prompted by reports of generator power feeder wire chafing on the closeout rib of the wing leading edge at a certain station due to insufficient clearance between the generator power feeder wires and the closeout rib. The actions specified by this AD are intended to prevent chafed and burnt generator power feeder wires, which could result in arcing damage to a certain closeout rib of the wing leading edge and fire damage to the wing structure, and consequent reduced structural integrity of the wing.
2000-07-17: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires a general visual inspection to verify that the circuit breaker panel fully opens, follow-on inspections, and corrective actions, if necessary. This amendment is prompted by an incident of an operator not being able to fully open the observer's upper main circuit breaker panel due to a certain cable being too short. The actions specified by this AD are intended to ensure that the upper main circuit breaker panel opens fully. If the panel does not open fully, maintenance activities may be hindered and cause damage to the circuit breaker panel and wiring, which could result in electrical arcing and consequent smoke and fire in the flight compartment.
2015-02-03: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-601, B4-603, B4-605R, F4-605R, and C4-605R Variant F airplanes. This AD was prompted by reports of cracking found in the pylon box, which was due to the stresses resulting from the pressure applied by the thrust reverser cowl bumpers. This AD requires repetitive high frequency eddy current (HFEC) inspections for cracking; and replacement of all fittings if necessary, which terminates the repetitive HFEC inspections for the modified side only. We are issuing this AD to detect and correct cracks of the pylon rib 5, which could result in reduced structural integrity of the airplane.
2015-02-05: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 717-200 airplanes; Model DC-10-10, DC-10-10F, DC- 10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40 and DC-10-40F airplanes; Model MD-10-10F and MD-10-30F airplanes; Model DC-9-81 (MD- 81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; Model MD-88 airplanes; and Model MD-90-30 airplanes. This AD was prompted by reports of latent air data transducer degradation. This AD requires revising the maintenance or inspection program, as applicable, to incorporate special compliance items (SCIs). We are issuing this AD to prevent erroneous air data information, which could lead to a mid- air collision within reduced vertical separation minimum (RVSM) airspace.
2000-08-02: This amendment adopts a new airworthiness directive (AD) applicable to Agusta Model A109A, A109AII, and A109C helicopters. This action requires inspecting the main transmission to determine if certain Gleason crowns are installed and replacing any unairworthy Gleason crown with an airworthy Gleason crown. This amendment is prompted by the discovery of a cracked Gleason crown during an unscheduled transmission inspection prompted by abnormal noises coming from the transmission during main rotor deceleration. The actions specified in this AD are intended to prevent failure of the main transmission, loss of rotor drive, and subsequent loss of control of the helicopter.
2015-02-09: We are adopting a new airworthiness directive (AD) for Costruzioni Aeronautiche Tecnam srl Model P2006T airplanes. 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 cracking found in the engine exhaust pipe. We are issuing this AD to require actions to address the unsafe condition on these products.