Results
2021-21-08: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AB139 and AW139 helicopters. This AD was prompted by a report of damage (burns) on the tail rotor blades (TRBs). This AD requires an inspection of each TRB for the general condition and any evidence of burns and replacement if necessary, 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.
69-11-03: 69-11-03\tBOEING: Amdt. 39-766 applies to Model 707-300B and 707-300C series airplanes listed as follows. AA Serial No. 20170, PA Serial Nos. 20030, 20031, 20033, and 20034, LU Serial No. 20123, OA Serial No. 20035, TP Serial No. 19969, LY Serial No. 20097, PK Serial No. 19866, NW, RD, PK and EJ airplane serial numbers on which rudder power control units purchased as spares from Bertea have been installed. \n\tCompliance required as indicated unless already accomplished. \n\tTo prevent cracking of the control rod end of the rudder power control unit, accomplish the following: \n\tPrior to next flight, remove any rudder power unit, Boeing Part Number 10-60815, having Bertea Serial Number 760 through 818 and replace with a power unit of the same part number but of a different serial number than noted above. Power units Numbers 760 through 818 may be returned to service when the rod end, Bertea Part Number 60043-9 (Schafer Part Number YTD 112A), has been replaced in accordance with FAA approved instructions from the manufacturer (Bertea). The airplane may not be ferried under the provisions of FAR 21.197(b) and (c). Airplanes may be ferried after issuance of individual special flight permits under the provisions of FAR 21.197(a)(1) and FAR 21.199 after a pre-takeoff determination that the rudder operates normally in the "Boost On" mode. Pursuant to FAR 21.199(a)(6), the limitations in the special flight permit will prohibit flights over congested areas or which may otherwise endanger persons or property on the ground. \n\tThis amendment becomes effective upon publication in the FEDERAL REGISTER for all persons except those to whom it was made effective immediately by telegram dated April 14, 1969.
2004-09-29: The FAA is adopting a new airworthiness directive (AD) for Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Turbine Engine Company, and AiResearch Manufacturing Company of Arizona) (Honeywell) TPE331-10 and -11 series turboprop engines with certain part numbers (P/Ns) and serial numbers (SNs) of first stage turbine disks. This AD requires initial and repetitive fluorescent penetrant inspections (FPIs) and eddy current inspections (ECIs) of the affected first stage turbine disks. This AD results from a report of a first stage turbine disk found cracked at the disk bore. The crack originated from a localized; melt related, low-alloy area of the disk. We are issuing this AD to prevent cracked first stage turbine disks from causing uncontained disk separation, resulting in engine damage and shutdown and damage to the airplane.
98-18-08: This amendment adopts a new airworthiness directive (AD) that applies to certain Bombardier Inc. (formerly deHavilland Inc) Model DHC-3 (Otter) airplanes that have been modified in accordance with A.M. Luton Supplemental Type Certificate (STC) No. SA3777NM. This AD requires modifying the airplane s electrical system. The actions specified by this AD are intended to prevent electrical system failure caused by inadequate electrical system design, which could result in the loss of the engine instruments or a possible electrical fire in the airplane s cockpit.
2021-21-10: The FAA is adopting a new airworthiness directive (AD) for certain Pacific Aerospace Limited Model 750XL 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 chafing damage in the port wing skin caused by the fuel system finger filters. This AD requires inspecting the wing internal skin for chafing and taking any necessary corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
53-18-01: 53-18-01 CESSNA: Applies to All Model T-50 Aircraft. Compliance required by November 1, 1953. As a result of reported failures of the outer bearing in the Goodrich Model 751A/M, G-3- 49A, 7.50-10 main gear assembly, each resulting in loss of a wheel, the following should be accomplished if the outer bearing has not been replaced since the airplane was converted from military to civil operation. If the outer bearing has been replaced subsequent to that time, compliance only with item 1 is required. 1. Not later than the date specified above, replace the 1 7/16-inch washer located between the axle nut and the inner bearing cone with a washer 1 7/8 inch outside diameter, 0.953 + 0.005 inch inside diameter and 0.093 + 0.005 inch thick manufactured from SAE 1010 or equivalent. This precautionary measure will not prevent bearing failure but may prevent the wheel from coming off the axle during landing in the event of a bearing failure. 2. At the time of item 1 and at every 100 hours of operation thereafter until the bearing is replaced, check wheel side movement, inspect bearing and replace bearing as necessary. Replacement should be accomplished with Timken Cone No. 07100 and Cup No. 07196 or an equivalent bearing. (B.F. Goodrich Co. Service Bulletin No. 36, revised April 20, 1953, covers this same subject and supplies information for the fabrication of the new washer and for ordering proper replacement bearings.)
2004-09-35: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires removing the two direct current (DC) over- voltage/feeder-fault test switches from the Test 2 Panel of the generator control unit, and follow-on actions. This action is necessary to prevent loss of the DC generators, which could result in the loss of normal electrical power to the airplane and increased pilot workload. This action is intended to address the identified unsafe condition.
59-10-09: 59-10-09 PRATT & WHITNEY: Applies to Following Turbo Wasp JT3C-6 Engines: JT3C-6 Engines Prior to Serial Numbers P630735B, Except P630406B Through P630413B, P630607B Through P630609B, P630614B Through P630618B, P630623B Through P630635B, and P630637B. JT3C-6 Engines Prior to Serial Numbers P630742D, Except P629708D, P630612D, P630315D, P630317D, P630319D Through P630325D, P630610D Through P630613D, P630619D Through P630622D, and P630636D. Compliance required as indicated. As a result of two third-stage turbine blade failures, it will be necessary to replace by 300 hours' of blade operating time, the P/N 271303 blade prior to change J-3 and P/N 371603 blade prior to change C-3. Third stage turbine blades P/N 271303, change J-3 and P/N 371603, change C-3, or later, do not require this replacement. (P&W Service Bulletin, Chapter 72-8 dated April 3, 1959, of the Heavy Maintenance Manual, P/N 367069 covers this same subject.)
98-16-02: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-16-02 which was sent previously to all known U.S. owners and operators of Eurocopter France Model SA 3180, SA 318B, SA 318C, SE 3130, SE 313B, SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 helicopters by individual letters. This AD requires an initial and recurring visual inspections of the upper and lower surfaces of the tail rotor blade (blade) skin for cracks. If a crack is found, replacing the blade with an airworthy blade is required. This amendment is prompted by a report of a crack on the blade skin near an attachment bolt on the blade cuff stem. This condition, if not corrected, could result in fatigue failure of a blade and subsequent loss of control of the helicopter.
2021-21-01: The FAA is superseding Airworthiness Directive (AD) 2019-05- 06, which applied to certain Airbus Helicopters Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. AD 2019-05-06 required replacing the retaining ring, inspecting the hoist cable hook assembly, and, if necessary, replacing the elastomeric energy absorber. This AD continues to require the actions specified in AD 2019-05-06, and also requires a modification or replacement of the hoist cable hook assembly that would terminate the repetitive inspections and retaining ring replacements, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a report that a hook detached from the hoist cable. The FAA is issuing this AD to address the unsafe condition on these products.
98-06-29: 98-06-29 BOEING: Amendment 39-10407. Docket 97-NM-65-AD.\n\n\tApplicability: Model 747-400 series airplanes; as listed in Boeing Alert Service Bulletin 747-25A3137, dated March 13, 1997; certificated in any category.\n\n\tNOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.\n\n\tCompliance: Required as indicated,unless accomplished previously.\n\n\tTo prevent chafing of the galley power feeder and static ground wiring on passenger oxygen system tubing in the forward ceiling area above the Door 4 galley, which could result in a fire, accomplish the following:\n\n\t(a)\tWithin 18 months after the effective date of this AD: Perform a one-time inspection of the separation between the galley power feeder and static ground wiring, and the adjacent passenger oxygen system tubing in the forward ceiling area above the door 4 galley, in accordance with Boeing Alert Service Bulletin 747-25A3137, dated March 13, 1997. If the separation is outside the limits specified in the alert service bulletin, prior to further flight, reroute the wiring, and install clamps and sleeves, in accordance with the alert service bulletin.\n\n\t(b)\tAn alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO.\n\n\tNOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO.\n\n\t(c)\tSpecial flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.\n\n\t(d)\tThe actions shall be done in accordance with Boeing Alert Service Bulletin 747-25A3137, dated March 13, 1997. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.\n\n\t(e)\tThis amendment becomes effective on April 24, 1998.
2004-09-34: The FAA is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CF6-80E1 model turbofan engines with high pressure turbine (HPT) stage 2 (S2) nozzle guide vanes (NGVs) part number (P/N) 1647M84G09 or 1647M84G10, installed. That AD currently requires flex borescope inspections of HPT S2 NGVs installed in CF6-80E1 model turbofan engines. This AD requires the same actions but at reduced compliance intervals. This AD results from inspection findings of HPT S2 NGVs that show cracks from distress could occur sooner and grow faster than originally predicted. We are issuing this AD to prevent failure of HPT rotor blades from HPT S2 NGV distress, which could result in an uncontained engine failure.
2021-22-12: The FAA is adopting a new airworthiness directive (AD) for certain Honda Aircraft Company LLC (Honda) Model HA-420 airplanes. This AD was prompted by a report that the flap pushrod assemblies are susceptible to corrosion. This AD requires removing and cleaning the inner diameter of the flap control pushrods and repetitively applying corrosion inhibiting compound (CIC) to this area. The FAA is issuing this AD to address the unsafe condition on these products.
68-19-03: 68-19-03 BRITISH AIRCRAFT: Amendment 39-655. Applies to Viscount Model 810 Series airplanes. Compliance required within the next 125 landings after the effective date of this AD, or before the accumulation of 10,125 landings, whichever occurs later. To prevent cracking or distortion of forward landing flap assembly diaphragms P/Ns 80284-139/140, 80284-561/562, and 80284-711/712, and attachment plates P/N's 80284-131, 80284-565 and 80284-709, accomplish the following: (a) Replace the No. 1 forward landing flap assembly diaphragm P/Ns 80284-139 and 80284-140 with new landing flap assembly diaphragm P/Ns 81084-51 and 81084-52 in accordance with British Aircraft Corporation Modification Bulletin No. FG.2089, dated January 12, 1968 or later ARB-approved issue, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region. (b) Visually inspect Nos. 2 and 3 forward landing flap assembly diaphragms and attachment plates for cracks in accordance with British Aircraft Corporation Preliminary Technical Leaflet No. 136, Issue 1 (800/810 Series) or later ARB-approved issue, or an FAA- approved equivalent. Repeat this inspection at intervals not to exceed 600 landings from the last inspection until the accumulation of 20,000 landings and thereafter at intervals not to exceed 450 landings from the last inspection. (c) If cracks are detected during the inspection required by paragraph (b), before the next flight, replace the defective parts with serviceable parts of the same part number. Continue the repetitive inspections required by paragraph (b) for all replacement parts. (d) For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type. This amendment becomes effective October12, 1968.
72-11-03: 72-11-03 GRUMMAN AIRCRAFT: Amdt. 39-1451. Applies to G-21 and G-21A airplanes (converted military OA-9 and JRF series airplanes under TC 654) certificated in all categories. Compliance required within the next 25 hours in service after the effective date of this AD, unless already accomplished. In order to prevent engine fuel starvation due to fuel vaporization within fuel feed lines to the engines, accomplish the following: Install a permanent placard on or near the instrument panel in full view of the pilot using minimum 1/8 inch lettering to read: "Cross feed valve must be closed during all flight operations except for emergencies resulting from engine pump failure." (Grumman Customer Bulletin No. G21A 72-1 pertains to this subject) This amendment is effective May 30, 1972.
2021-21-04: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports that the sliding bushings in the forward engine mount system were missing. This AD requires an inspection (gap check) of the front and aft engine mounts to verify the proper installation of the sliding bushings, and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2021-23-03: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-400, -401, and -402 airplanes. This AD was prompted by a report of cracking found on a main landing gear (MLG) drag strut assembly. This AD requires a records review to determine if an affected MLG drag strut assembly is installed, repetitive detailed inspections for cracking of affected strut assemblies, a one-time magnetic particle inspection for cracking, and on-condition actions if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2012-03-51: We are adopting a new airworthiness directive (AD) for certain airplanes originally manufactured by Lockheed for the military as P2V airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires cleaning of the forward lower spar cap between wing stations 40 and 84.5 (right and left), and doing a detailed inspection for cracks, working fasteners, and other anomalies, including surface damage in the form of a nick, gouge, or corrosion; and repairing if necessary. This AD was prompted by a report of a significant crack in the principle wing structure. We are issuing this AD to detect and [[Page 9167]] correct cracks, working fasteners, and other anomalies in the principle wing structure, which could cause significant loss of structural integrity of the wing.
51-28-03: 51-28-03 RYAN: Applies to All Model ST-3KR (Military PT-22) Aircraft. To be accomplished by February 1, 1952, or next 100-hour inspection, whichever is first. The fuel selector valve handles for these aircraft are usually placarded "Always take off with fuel feeding from Reserve". However, there have been fatal accidents which resulted from failure to observe this procedure, or from failure to return to the Reserve position when landing with a low fuel supply. Therefore, the following placard must be installed, or the existing placard revised to read: "Always take off and land with fuel feeding from RESERVE".
2004-09-31: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-101, -102, -103, -106, -201, -202, -301, -311, and -315 airplanes on which engine oil coolers have been installed per LORI, Inc., STC SA8937SW. This amendment requires an inspection or a review of the airplane maintenance records to determine the part number and serial number of each engine oil cooler, and replacement of certain engine oil coolers with reworked engine oil coolers. This action is necessary to prevent oil leakage from the engine oil coolers, consequent in-flight engine shutdown due to low oil pressure, and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2021-20-22: The FAA is adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F28 Mark 0070 and Mark 0100 airplanes. This AD was prompted by a report of exfoliation corrosion found during an inspection of the wing front spar lower boom. This AD requires an inspection for corrosion of the wing front spar lower boom, and applicable corrective actions, 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.
68-08-06: 68-08-06 SIAI-MARCHETTI: Amdt. 39-586. Applies to Model S.205/22R airplanes, Serial Numbers 213 and 370 through 374. Compliance required as indicated. To detect cracks on the welded angles of the nose gear brace cross member, P/N 205-9- 101, accomplish the following: (a) For airplanes with 175 or more hours' time in service on the effective date of this AD, accomplish the inspection required by paragraph (c) within the next 25 hours' time in service and thereafter at intervals not to exceed 25 hours' time in service from the last inspection. (b) For airplanes with less than 175 hours' time in service on the effective date of this AD, accomplish the inspection required by paragraph (c) before the accumulation of a total of 200 hours' time in service, and thereafter at intervals not to exceed 25 hours' time in service from the last inspection. (c) Inspect the welded angles of the nose gear brace cross member, P/N 205-9-101, using a glass of at least 5 power, or an FAA-approved equivalent inspection, in accordance with Siai-Marchetti Service Bulletin No. 205B14A, dated August 4, 1967, or FAA-approved equivalent. If cracks are detected during any inspection, replace cracked nose gear brace cross member with reinforced member, P/N 205-9-101-03, in accordance with Siai-Marchetti Service Bulletin No. 205B14A or an FAA-approved equivalent, before further flight. (d) The repetitive inspections required by paragraphs (a) and (b) may be discontinued after the reinforced nose gear brace cross member, P/N 205-9-101-03, is installed. This amendment becomes effective May 17, 1968.
2021-22-22: The FAA is adopting a new airworthiness directive (AD) for all Costruzioni Aeronautiche Tecnam S.P.A. Model P2006T 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 a manufacturing defect in the nose landing gear (NLG) piston tube. This AD requires replacing the NLG piston tube. The FAA is issuing this AD to address the unsafe condition on these products.
55-16-01: 55-16-01 BELL: Applies to All Model 47 Helicopters With 47-641-025-1 or 47-641-057- 1 Tail Rotor Hubs, and All Spares. Compliance required prior to next flight. Recent serious accidents have been caused by failure of the tail rotor hubs P/N 47-641- 025-1 and 47-641-057-1. Imperfections such as corrosion, tool marks, scratches, and pitting in the fillet set up stress concentrations which cause failure of the hub spindle. Consequently, immediate and complete inspection of the fillet area of the tail rotor hub must be accomplished as follows: 1. Inspect the inboard fillet area on both spindles of the hub for accuracy of the radius using a 10-power magnifying glass. Fillets must have a true continuous radius all around the spindles and also must have a smooth machine finish free of corrosion and pitting. When inspected under a magnifying glass, tool marks appear greatly exaggerated, and by a smooth machine finish is meant having extremely fine, uniform, closely-spacedand uninterrupted tool marks. No copper plating is allowed in the fillet. 2. Hubs not meeting these requirements must be replaced. (Bell Service Bulletin No. 96, Revision B dated July 15, 1955, covers this subject.) (This covers the same inspection as the CAA telegram of July 13, 1955.)
98-11-01 R2: This amendment clarifies information contained in Airworthiness Directive (AD) 98-11-01 R1, which currently requires replacing the fuel tank vent valves and drilling a 4.8 millimeter (0.1875 inch) hole in each fuel filler cap on certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. AD 98-11-01 R1 also requires inserting a temporary revision in the Pilot's Operating Handbook (POH) that specifies checking to assure that the fuel filler cap hole is clear of ice and foreign objects. The intent of AD 98-11-01 R1 was to provide the option of incorporating new modified fuel tank vent valves instead of the replacement, drilling, and POH insertion requirements. The new modified vent valves cannot be incorporated without removing the fuel tank vent valves installed as originally required by AD 97-23-04 and carried over in the current AD. This provision of removing those vent valves is currently not provided for. This document clarifies and corrects this procedure. The actions specified in this AD are intended to continue to prevent moisture from entering the fuel tank inward vent valve and then freezing after a cold soak at altitude, which could result in wing airfoil distortion and structural damage with consequent degradation of the airplane's handling qualities. The incorporation by reference of Pilatus Service Bulletin No. 28-003, Revision 1, dated September 30, 1997, as listed in the regulations, was previously approved by the Director of the Federal Register as of December 1, 1997 (62 FR 59993, November 6, 1997). The incorporation by reference of Pilatus Service Bulletin No. 28-004, dated March 27, 1998, as listed in the regulations, was previously approved by the Director of the Federal Register as of June 7, 1998 (63 FR 27195, May 18, 1998). The incorporation by reference of Pilatus Service Bulletin No. 28-005, dated May 4, 1998, was previously approved by the Director of the Federal Register as of September 22, 1998(63 FR 34565, June 25, 1998).