Results
2003-09-06: This amendment adopts a new airworthiness directive (AD), that is applicable to General Electric Company (GE) CF6-50 series turbofan engines. This amendment requires removal from service of eight serial number (SN) low-pressure turbine (LPT) stage 1 disks, part number (P/N) 9061M21P03, at the next engine shop visit. This amendment is prompted by a report of the potential for iron-rich inclusions introduced during manufacture in the affected disks. The actions specified by this AD are intended to prevent LPT stage 1 disk cracking, due to iron-rich inclusions introduced during manufacture, leading to uncontained disk failure.
65-13-04: 65-13-04 GRUMMAN: Amdt. 39-80 Part 39 Federal Register June 12, 1965. Applies to Model G-159 Aircraft Equipped with Bendix Nose Gear Strut Assembly, P/N 1722-40 or 2570890. Compliance required as indicated. To prevent failure of the nose gear trunnion, accomplish the following: (a) Inspect the nose gear trunnion, Bendix P/N 171467 in accordance with (c) within the next 20 hours' time in service after the effective date of this AD unless replaced within the next 20 hours' time in service after the effective date of this AD, or unless already inspected within the last 80 hours' time in service, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection. (b) Within the next 20 hours' time in service after replacement of a nose gear trunnion, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, inspect the replacement trunnion in accordance with (c). (c) Inspect the retract shaft attachment lugs on the nose gear trunnion forward flanges for cracks in the radii above and below the area where the retract shaft attachment lugs blend into the trunnion flanges, using the dye penetrant method with a 10 power or greater glass or an FAA-approved equivalent. (d) Replace cracked trunnions with a trunnion of the same part number or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, before further flight except that the aircraft may be flown in accordance with the provisions of FAR 21.197, after approval by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, to a base where the repair can be made. This directive effective June 12, 1965.
75-06-01: 75-06-01 UNITED AIRCRAFT OF CANADA LIMITED and PRATT & WHITNEY AIRCRAFT: Amendment 39-2118 as amended by Amendment 39-2182, 39-2208 and 39-2574 is further amended by Amendment 39-2858. Applies to all PT6A-6, -6A, -6B, -6/C20, -20, -20A, -20B, -27, -28, and -34 series turboprop engines. Compliance required as indicated unless previously accomplished. To ensure the early detection of reduction gearbox deterioration which could result in an engine failure and provide for improved blade containment accomplish the following: (a) Within the next 50 hours in service after effective date of this AD, unless previously accomplished, remove the main engine oil filter element and visually inspect the element for magnetic and non-magnetic metal particles. (1) If the inspection reveals less than 40 non-magnetic metal and no magnetic metal particles, clean oil filter and reinspect after every 50 hours in service. (2) (i) If the inspection reveals more than 40 non-magnetic metal particles, clean oil filter and reinspect after 10 hours in service. (ii) If the reinspection, in accordance with paragraph (a)(2) (i) reveals less than 40 non-magnetic metal particles, clean oil filter and reinspect after every 50 hours in service thereafter. (iii) If the reinspection, in accordance with paragraph (a)(2) (i) reveals more than 40 non-magnetic metal particles, clean oil filter and reinspect after 10 hours in service. (iv) If the reinspection, in accordance with paragraph (a)(2) (iii) reveals more than 40 non-magnetic metal particles, the engine must be removed from service for an overhaul inspection. (v) If the reinspection in accordance with paragraph (a)(2) (iii) reveals less than 40 non-magnetic metal particles, clean oil filter and reinspect after every 50 hours in service thereafter. (3) (i) If the inspection reveals less than 40 magnetic metal particles clean oil filter and reinspect after 10 hours in service. (ii)If the reinspection in accordance with paragraph (a)(3) (i) reveals the presence of similar quantity of magnetic metal particles, the engine must be removed from service for an overhaul inspection. (iii) If the reinspection in accordance with paragraph (a)(3) (i) reveals the presence of lesser quantity of magnetic metal particles clean oil filter and reinspect every 50 hours time in service thereafter. (4) (i) If the inspection reveals more than 40 magnetic metal particles, clean oil filter, drain and change oil, perform a ground run for one hour and reinspect oil filter. If the inspection after one hour ground run reveals more than 40 magnetic metal particles, the engine must be removed from service for an overhaul inspection. (ii) If the inspection after one hour ground run reveals less than 40 magnetic metal particles, clean oil filter and reinspect after 10 hours in service. (iii) If the reinspection after 10 hours in service reveals a similar quantityof magnetic metal particles, the engine must be removed from service for an overhaul inspection. (iv) If the reinspection after 10 hours in service reveals a lesser quantity of magnetic metal particles, clean oil filter and reinspect every 50 hours in service thereafter. (b) For the PT6A-6, -6A, -6B, -6/C20, -20, -20A, -20B, -27, -28 and 34 engines, within the next 8000 hours in service after the effective date of the AD, alter part number 3010548, power turbine shaft housing assembly in accordance with paragraph 2, accomplishment instructions in United Aircraft of Canada Limited Engine Service Bulletin No. 1138 or approved equivalent, or replace said assembly with any other power turbine shaft housing assembly listed as eligible in the engine parts catalog. (c) For the PT6A-6, -6A, -6B, -6/C20, -20, -20A and -20B engines within the next 2000 hours in service after the effective date of this AD alter all the power turbine blades in accordance with paragraph 2, accomplishment instructions in Pratt & Whitney Aircraft of Canada Limited Engine Service Bulletin No. 1233, or approved equivalent alteration. (d) For the PT6A-27, -28 and -34 engines, within the next 4000 hours in service after the effective date of this AD install the improved power turbine containment ring in accordance with paragraph 2, accomplishment instructions in Pratt & Whitney Aircraft of Canada Limited Engine Service Bulletin No. 1220 or approved equivalent alterations and modified combustion chamber liner and related parts in accordance with paragraph 2, accomplishment instructions in Pratt & Whitney Aircraft of Canada Limited Engine Service Bulletin No. 1216, or approved equivalent alterations. (e) For the PT6A-20, -20A, and -20B, -6/C20 engines within the next 4000 hours in service after the effective date of this AD install the improved power turbine containment ring in accordance with paragraph 2, accomplishment instructions in Pratt & Whitney Aircraft of Canada Limited Engine Service Bulletin No. 1246 or approved equivalent alterations and modified combustion chamber liner and related parts in accordance with paragraph 2, accomplishment instructions in Pratt & Whitney Aircraft of Canada Limited Engine Service Bulletin No. 1245 or approved equivalent alterations. The main oil screen inspection requirements of this AD are no longer required when the engines have been modified as required by paragraph (b), (c), (d), and (e) as applicable. Aircraft may be flown to a base for performance of maintenance required by this AD per FAR 21.197 or FAR 21.199. Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection times specified in this Airworthiness Directive. All equivalent alterations must be approved by the Chief, Engineering and Manufacturing Branch of the Eastern Region of the FAA. Amendment 39-2118 was effective March 10, 1975. Amendment 39-2182 was effective April 28, 1975. Amendment 39-2208 was effective May 20, 1975. Amendment 39-2574 was effective April 14, 1976. This amendment 39-2858 is effective April 1, 1977.
48-03-06: 48-03-06 BELL: Applies to All 47B Series Through Serial Number 78. Compliance required at next 25-hour inspection. If the play between the two bolts which connect links 47-612-048, to the side and aft sprag systems and the adapter plate, exceeds 0.010 inch, bushing 78B6-8-11 should be added to the tube assembly fittings and the clevis end of the link; bushings 75B6-8-11-5 should be added to the opposite end of the link; and bushings 75B6-8-8, 47-612-053-1 or 47-612-053-2 should be installed in the adapter plate. (Bell Service Bulletin 47C62 dated December 2, 1947, covers this subject and gives more detailed reaming and dimensional information.)
2012-16-03: We are adopting a new airworthiness directive (AD) for all HPH s. r.o. Models 304C, 304CZ, and 304CZ-17 sailplanes. 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 the lack of a drain hole in the elevator control rod, which may allow water to accumulate in the control rod and lead to possible corrosion. This condition could cause the elevator control rod to fail, which could result in loss of control of the sailplane. We are issuing this AD to require actions to address the unsafe condition on these products.
67-12-05: 67-12-05 PILATUS: Amdt. 39-387, Part 39, Federal Register April 4, 1967. Applies to Model PC-6 Series Airplanes, Serial Numbers to 632. Compliance required with the next 200 hours' time in service after the effective date of this AD, unless already accomplished. To prevent rubbing and wear of the two pulley flanges as a result of a change in direction of the aileron control system cables in excess of 3 degrees from the plane of their pulleys, install fairleads at the pulley support bracket on bulkhead Number 3 in accordance with Pilatus Service Bulletin No. 68 or later Swiss Federal Air Office-approved issue, or an FAA-approved equivalent. This directive effective May 4, 1967.
99-06-15: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-06-15 which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron Canada (BHTC) Model 407 helicopters by individual letters. This AD requires installing a tail rotor pitch-limiting left-pedal stop, installing an airspeed limitation placard, marking a never-exceed velocity (Vne) placard on all airspeed indicators, and revising the Limitations section of the Rotorcraft Flight Manual (RFM). This amendment is prompted by three accidents involving in-flight tail rotor blade strikes against the tailboom. The actions specified by this AD are intended to prevent the tail rotor blades from striking the tailboom, which could result in separation of the aft section of the tailboom with the tail rotor gearbox and vertical fin, and subsequent loss of control of the helicopter.
2012-15-14: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-103, B4-203, and B4-2C airplanes, and Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called A300-600 series airplanes). This AD was prompted by reports of cracking in the forward lug of the main landing gear (MLG) rib 5 aft bearing attachment. This AD requires repetitive inspections for cracking of the left-hand (LH) and right- hand (RH) wing MLG rib 5 aft bearing forward lugs, and repair if necessary. We are issuing this AD to detect and correct cracking of the LH and RH wing MLG rib 5 aft bearing forward lugs, which could affect the structural integrity of the MLG attachment, resulting in MLG collapse during landing or rollout with consequent damage to the airplane and injury to occupants.
2012-15-12: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 767 airplanes. This AD was prompted by reports of cracks of the underwing longeron fittings in the wing center section. This AD requires repetitive inspections of the underwing longeron fitting for cracking, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct such cracking, which could result in loss of the primary load path between the fuselage and the wing box, and consequent catastrophic damage to the wing box and failure of the wing.
74-14-08: 74-14-08 GENERAL ELECTRIC: Amendment 39-1894. Applies to Models CF6-6D, 6D1, and 6H Turbofan Engines. Compliance required by September 30, 1974. To prevent expulsion from the engine of fifth stage low pressure turbine blades, unless already accomplished, install improved blade retainer P/N 9083M19P07 per the instructions of General Electric Service Bulletin (CF6-6) 72-399 Revision 1 dated March 20, 1974, or subsequent FAA approved revision. This amendment becomes effective July 12, 1974.
73-07-03: 73-07-03 GENERAL DYNAMICS: Amdt. 39-1612. Applies to Model 22M Series airplanes certificated in all categories. Compliance required as indicated. To detect cracks and prevent further failures of the actuator fitting, accomplish the following: (1) Within the next 150 hours' time in service after the effective date of this A.D., unless already accomplished within the last 250 hours' time in service, and thereafter at intervals not to exceed 400 hours' time in service from the last inspection, inspect the rudder boost actuator fitting P/N 30-15701-1 in accordance with General Dynamics 880M S.B. No. A27-47 dated 1 March 1973, or later FAA-approved revision. (2) If, as a result of the inspection required by paragraph (1), cracks are found, replace the defective fittings with an identical part. This amendment becomes effective March 29, 1973.
2012-15-01: We are adopting a new airworthiness directive (AD) for various aircraft equipped with Rotax Aircraft Engines 912 A series engine. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a deviation in the manufacturing process of fuel hoses installed on the pressure side of part number 893114 fuel pumps. The fuel hoses may not be fuel resistant, which could lead to detachment of particles from the fuel hose and cause irregularities in the carburetor function and possibly result in rough engine operation, engine misfire, in-flight engine shutdown, and forced landing. We are issuing this AD to require actions to address the unsafe condition on these products.
76-03-02: 76-03-02 SIKORSKY AIRCRAFT: Amendment 39-2507. Applies to S-61L, S-61N, S- 61NM, and S-61R helicopters certified in all categories including Military CH-3C, HH-3C, CH- 3E, and HH-3E helicopters using NAS 577-10 or NAS 577-10A barrel nuts for attaching the transmission main gearbox to the fuselage structure. Compliance required as indicated. To prevent fractures in the attaching nuts accomplish the following: Remove the NAS 577-10 or NAS 577-10A barrel nuts and replace with RMLH 2577-108 barrel nuts within the next 30 days after the effective date of this AD, unless already accomplished. (NOTE: Sikorsky Service Bulletin No. 61B35-36B covers this subject.) This supersedes Amendment 39-2202 (40 FR 24355), AD 75-12-13. This amendment becomes effective February 17, 1976.
99-07-17: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-07-17 which was sent previously to all known U.S. owners and operators of Robinson Helicopter Company (RHC) Model R22 helicopters by individual letters. This AD requires, before further flight, inserting a Special Pilot Caution into the Normal Procedures section of the Rotorcraft Flight Manual (RFM). This amendment is prompted by several reports of sprag clutch assemblies with cracked or fractured sprag ends. The sprag clutch failures, determined to be due to a change in the manufacturing process, could result in loss of main rotor revolutions-per-minute (RPM) during autorotations. The intent of this AD is to alert pilots of the potential for the sprag clutch failing to overrun during autorotation, loss of main rotor RPM, and subsequent loss of control of the helicopter.
2003-08-15: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-200, -200C, -300, -400, and -500 series airplanes. This action requires a one-time mid-frequency eddy current (MFEC), a low-frequency eddy current (LFEC), and a detailed inspection for damage or cracking of stringer S-4L and S-4R lap joints and stringer clips between body station (BS) 540 and BS 727, and follow-on inspections and repair if necessary. This action is necessary to find and fix cracking of the fuselage lap joints, which could result in sudden decompression of the airplane.
2012-15-06: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP (Type Certificate previously held by Israel Aircraft Industries, Ltd.) Model Astra SPX, 1125 Westwind Astra, and Gulfstream 100 airplanes. This AD was prompted by a report indicating that sponge rubber padding was found between wheel well fuel lines and electrical harnesses. This AD requires inspecting for the presence of sponge rubber padding and for proper separation of the fuel lines and electrical harnesses in the wheel well area, and corrective actions if necessary. We are issuing this AD to detect and correct corrosion or chafing of the fuel lines, which could result in fuel leakage and possible fire in the wheel well area.
99-08-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires modification of the flight compartment door; repetitive inspections for wear of the flight compartment door hinges following modification; and repair or replacement of the hinges with new hinges, if necessary. This amendment is prompted by a report that the door lock mechanism of the flight compartment door jammed and could not be opened using the alternate release mechanism. The actions specified by this AD are intended to prevent failure of the alternate release mechanism of the flight compartment door, which could delay or impede the evacuation of the flightcrew during an emergency. Such failure also could result in the flightcrew not being able to assist passengers in the event of an emergency.
99-08-06: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model SE. 3160, SA. 316B, SA. 316C, and SA. 319B helicopters. This action requires inspecting the spar skin and main rotor blade (blade) root reinforcement strip area for a bonding separation, corrosion, or a crack, and replacing the blade, if necessary. This amendment is prompted by the in-flight failure of a blade. The actions specified in this AD are intended to detect a bonding separation, corrosion, or a crack in the area of the blade root reinforcement strip, which could result in failure of the blade and subsequent loss of control of the helicopter.
2012-15-04: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC155B1 helicopters with a certain automated flight control system installed. This AD requires changing the minimum required crew for instrument flight rules (IFR) operations from one pilot to two. This AD is prompted by a report that an EC155B1 helicopter experienced significant intermittent roll oscillations while coupled to the autopilot. These actions are intended to decrease the pilot's workload while experiencing any oscillations during landing, which could result in possible loss of control of the helicopter.
74-20-10: 74-20-10 LEIGH SYSTEMS: Amendment 39-1976 as amended by Amendment 39-2038, 39-2732, and 39-3000 is further amended by Amendment 39-3104. Emergency Locator Transmitter Leigh Systems Sharc 7 Series. Applies to all Leigh Systems Sharc 7 Emergency Locator Transmitters Serial Numbers all through 163500 equipped with lithium batteries. \n\n\tCompliance required as indicated. \n\n\tAs a result of chemical corrosion resulting in either failure of the Emergency Locator Transmitter (ELT) to operate or inadvertent activation, jamming the emergency frequencies of 121.5 MHz and 243.0 MHz accomplish the following: \n\n\tWithin the next 90 days and thereafter at each additional 60 day interval after the effective date of this Airworthiness Directive, accomplish the following: \n\n\t1.\tDeleted. \n\n\t2.\tConduct a visual inspection for evidence of corrosion in accordance with photo reproduction which is part of Leigh System's Service Bulletin No. 003A, dated May 15, 1974, or equivalent inspections approved by Chief, Engineering and Manufacturing Branch, FAA Eastern Region. \n\n\t3.\tIf no corrosion is found, prior to reinstalling, determine ELT transmits properly. ELT transmissions are authorized in the first five minutes of any hour or at other times if coordinated with the nearest FAA Tower or Flight Service Station for a total of three audio sweeps (Ref. FAA Advisory Circular 00-35A or 20-81). \n\n\t4.\tIf corrosion is found or if the ELT does not transmit properly, replace with an approved serviceable unit which has been inspected in accordance with paragraph 2; or replace with another TSO approved unit, prior to the next flight except that a ferry flight may be conducted in accordance with FAR 91.52(e)(2). \n\n\tNOTE: ELT's equipped with lithium batteries may be identified by inspecting the identification tags. Units marked in the weight range of 1.5 to 2.0 lbs. are lithium batteries. \n\n\tAmendment 39-1976 was effective October 1, 1974. \n\n\tAmendment 39-2038 was effective December 9, 1974. Amendment 39-2732 was effective September 29, 1976. \n\n\tAmendment 39-3000 was effective August 10, 1977. \n\n\tThis Amendment 39-3104 is effective December 30, 1977.
2012-14-04: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-100, DHC-8-200, and DHC-8-300 series airplanes. This AD was prompted by reports of hydraulic accumulator screw cap or end cap failure. This AD requires replacing the affected parking brake accumulator. We are issuing this AD to prevent failure of the parking brake accumulator screw caps or end caps, which could result in loss of the number 2 hydraulic system and damage to airplane structures, and could potentially have an adverse effect on the controllability of the airplane.
2012-13-11: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model MBB-BK 117 (all versions) and BO-105LS A-3 helicopters. This AD requires inspecting the tail rotor pitch link spherical bearing for proper swaging. This AD is prompted by a report of a tail rotor pitch link with a spherical bearing that had migrated out of the bearing bore. The actions specified by this AD are intended to prevent failure of the tail rotor pitch link and subsequent loss of control of the helicopter.
75-24-13: 75-24-13 MCCAULEY PROPELLERS: Amendment 39-2435. Applies to the two- bladed constant speed and full feathering Model D2AF34C52/ 80GF-0 and D2AF34C52A/80GF- 0 series propellers having hub serial numbers 63000 through 659999, installed on but not limited to Cessna 310I type aircraft. Compliance required as indicated, unless already accomplished. To prevent hub failures, accomplish the following: A. Propellers with 1500 or more total hours in service as of the effective date of this Airworthiness Directive must be inspected and modified in accordance with Paragraph (D) within the next 100 hours in service after the effective date of this AD. B. Propellers with less than 1500 hours in service as of the effective date of this Airworthiness Directive must be inspected and modified in accordance with Paragraph (D) prior to the accumulation of 1600 hours in service. C. Propellers whose total hours in service are unknown will be assumed to have 1500 hours minimum and thus fall within the requirements for inspection and modification in accordance with Paragraph (A). D. Remove propeller from the aircraft, disassemble, inspect components and replace the hub in accordance with McCauley Service Manual No. 710930 and Bulletin No. 111 dated August 11, 1975, or later Federal Aviation Administration approved revisions, or an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Great Lakes Region. The manufacturer's specifications and procedures identified in this Directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 522(a)(1). All persons affected by this Directive who have not already received these documents from the manufacturer, may obtain copies upon request to McCauley Accessory Division, Cessna Aircraft Corporation, Box 7, Roosevelt Station, Dayton, Ohio 45417. These documents may also be examined at the Great Lakes Regional Office, 2300 East Devon Avenue, Des Plaines, Illinois 60018, and at FAA Headquarters, 800 Independence Avenue S.W., Washington, D.C. A historical file on this Airworthiness Directive which includes incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C. and at the Great Lakes Region. This amendment becomes effective November 26, 1975.
2012-14-13: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318-112 and -121 airplanes; Model A319-111, -112, -115, - 132, and -133 airplanes; Model A320-214, -232, and -233 airplanes; and Model A321-211, -212, -213, and -231 airplanes. This AD was prompted by reports of some fuselage nuts found cracked. This AD requires an inspection to determine if certain fuselage nuts are installed, a detailed inspection for cracking of fuselage nuts having a certain part number, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct fuselage nuts found cracked, which could result in reduced structural integrity of the airplane.
2018-05-03: We are adopting a new airworthiness directive (AD) for certain Safran Helicopter Engines, S.A., Arrius 2F turboshaft engines. This AD requires inspection and replacement of the magnetic heads installed on oil system electrical magnetic plugs. This AD was prompted by reports from the manufacturer of a batch of non-conforming magnetic heads installed on electrical magnetic plugs. We are issuing this AD to address the unsafe condition on these products.