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.