Results
98-08-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0070 and Mark 0100 series airplanes, that requires a one-time visual inspection to detect heat damage of the fuselage skin and stubwing structure. This proposal also would require either repetitive leak tests of the seals of the bleed air system, or repair of any heat-damaged structure, as necessary; and replacement of corrujoint seals with new improved seals. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent the leakage of hot air from the corrujoint seals of the low- and high-pressure check valves located in the stubwings, which could result in heat damage to the fuselage skin and stubwing structure, and consequent reduced structural integrity of the airplane.
89-19-06: 89-19-06 BOEING: Amendment 39-6321. (Docket No. 89-NM-52-AD) \n\tApplicability: Model 757 series airplanes, equipped with Air Cruisers escape slides having the part numbers listed in Air Cruisers Service Bulletin 105-25-28, Revision 2, dated March 28, 1989, and with Air Cruisers slide/rafts having the part numbers listed in Air Cruisers Service Bulletin 105-25-29, dated March 2, 1989, certificated in any category. \n\n\tCompliance: Required within 18 months after the effective date of this AD, unless previously accomplished. \n\n\tTo ensure that the escape slides or slide/rafts deploy properly, accomplish the following: \n\n\tA.\tInstall a cable retainer and cover flap, in accordance with Air Cruisers Service Bulletin 105-25-28, Revision 2, dated March 28, 1989, or Air Cruisers Service Bulletin 105-25- 29, dated March 2, 1989, as applicable. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124, or Air Cruisers Company, P.O. Box 180, Belmar, New Jersey 07719. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6321) becomes effective on October 14, 1989.
2009-04-02: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney (PW) PW4090 and PW4090-3 turbofan engines with front turbine hub, part number (P/N) 53L601, installed. This AD reduces the published life limit of those front turbine hubs, from 12,000 cycles- since-new (CSN) to 9,370 CSN. This AD also removes from service those front turbine hubs using a drawdown schedule. This AD results from PW updating the low-cycle-fatigue (LCF) life analysis for front turbine hubs, P/N 53L601. We are issuing this AD to prevent an uncontained failure of the front turbine hub, resulting in an in-flight engine shutdown and possible damage to the airplane.
99-15-11: This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace HP137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes. This AD requires repetitively removing the nose landing gear steering selector valve and installing either a new nose landing gear steering selector valve or one that has been overhauled in accordance with the appropriate component maintenance manual. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent the inability to steer the airplane because of wear in the nose landing gear steering selector differential, which could result in loss of control of the airplane during take-off, landing, or taxi operations.
2007-04-10: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-400 series airplanes. That AD currently requires replacement of the decompression panels that are located in the smoke barrier between the passenger and main deck cargo compartment with new panels of an improved design. This new AD requires modification of the decompression panels on the smoke barrier in the main deck cargo compartment, or replacement of the smoke barrier with an improved smoke barrier, as applicable. This new AD also requires repetitive inspections of the decompression (vent) panels on the smoke barrier and corrective actions if necessary. This new AD also adds airplanes to the applicability. This AD results from reports of decompression panels on the smoke barrier opening in flight and on the ground without a decompression event. We are issuing this AD to prevent inadvertent opening or tearing of decompression panels, which could result in degraded cargo fire detection and suppression capability, smoke penetration into an occupied compartment, and an uncontrolled cargo fire, if a fire occurs in the main deck cargo compartment.
98-01-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Industrie Model A320 series airplanes, that requires an inspection to detect moisture and migrated bushings of the guide fittings of the safety locking pins of the passenger doors, removal of any moisture, application of grease, and reinstallation of any migrated bushing. This amendment also requires installation of a greasing nipple on the guide fitting of the locking pin and on three telescopic rods on the passenger doors. This amendment is prompted by reports of difficulty opening the passenger doors due to jamming of the locking pin. The actions specified by this AD are intended to prevent such jamming of the locking pin, which could result in inability to open the passenger door. This condition, if not corrected, could impede or delay passengers from exiting the airplane during an emergency.
2019-14-14: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by a determination that a certain aircraft maintenance manual (AMM) task provided instructions for a visual inspection of composite and metallic vertical tailplane (VTP) attachment fittings, but the inspection method did not specify detection of delamination length, which could possibly extend beyond the defined allowable limits. This AD requires a review of airplane maintenance records, and, depending on the results, one-time detailed and ultrasonic inspections of the affected parts and applicable corrective actions, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
77-20-01: 77-20-01 SIKORSKY AIRCRAFT: Amendment 39-3045 as amended by Amendment 39- 3064. Applies to all Sikorsky Model S-64E and S-64F helicopters. Compliance required as indicated, unless already accomplished. 1. To prevent cracking and possible failure of main transmission lower planetary plates, P/N 6435-20229-102, inspect for cracks in accordance with Sikorsky Service Bulletin No. 64B35-7 prior to the accumulation of 1300 hours time in service, or within the next 30 hours time in service after receipt of this telegram, whichever is later, and every 70 hours time in service thereafter. Cracked plates must be removed before further flight. 2. Effective October 30, 1977, P/N 6435-20229-102 plates with 2000 or more hours total time in service must be removed from service. 3. For P/N 6435-20229-102 plates with 1300 or more hours total time in service after receipt of this telegram, inspect main transmission oil filter pack daily for magnesium chips. If chips are found, remove main transmission from service before further flight. 4. In lieu of Paragraphs 1, 2, and 3 above, plates may be inspected, reworked, and reidentified as P/N 6435-20229-102-TS-107 in accordance with Sikorsky Service Bulletin 64B35-7A or later FAA approved revisions. 5. Reworked plates, P/N 6435-20229-102-TS-107, shall be retired prior to the accumulation of 2,600 hours total time in service. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. Sikorsky Alert Service Bulletin No. 64B35-7 refers to this subject. Amendment 39-3045 became effective upon receipt of telegraphic AD for all operators which received notice by telegraphicAD and became effective upon publication in the Federal Register for all others. This amendment 39-3064 becomes effective upon publication in the Federal Register.
83-05-09: 83-05-09 BOEING: Amendment 39-4585. Applies to all Boeing Model 747 series airplanes certificated in all categories listed in Boeing Service Bulletin 747-32-2261 Rev. 1, or later FAA approved revisions. To prevent wing landing gear jury strut spindle failures, accomplish the following: \n\n\tA.\tUnless already accomplished within the last 375 landings, within the next 375 landings after the effective date of this AD or prior to the accumulation of 7625 landings, whichever is later, and thereafter at intervals not to exceed 750 landings, magnetic particle or dye penetrant inspect the wing landing gear jury strut spindles for cracks in accordance with Table I of Boeing Service Bulletin 747-32-2261 Rev. 1, or later FAA approved revisions. Cracked parts are to be replaced prior to further flight. \n\n\tB.\tUpon the installation of the improved spindles in accordance with Boeing Service Bulletin 747-32-2261 Rev. 1, or later FAA approved revisions, the requirements of this AD are terminated. \n\n\tC.\tAlternate means of compliance with this AD which provides an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\tFor purposes of complying with this AD, subject to acceptance by the assigned FAA Principal Maintenance Inspector, the number of flight cycles may be determined by dividing each airplane's hours time in service by the operator's fleet average from takeoff to landing for the airplane type. If the gear/jury strut spindle cycles and hours are different from the airplane cycles and hours, the gear/jury strut spindle times shall be used. \n\n\tE.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD.\n \n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request toBoeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington.\n \n\tThis amendment becomes effective April 18, 1983.
2019-15-03: The FAA is adopting a new airworthiness directive (AD) for all 328 Support Services GmbH Model 328-100 airplanes. This AD was prompted by a report indicating that undetected cracks may develop at the roll spoiler bearing arms. This AD requires a one-time non-destructive test (NDT) inspection for cracks in the roll spoiler bearing arms and, if necessary, corrective actions. The agency is issuing this AD to address the unsafe condition on these products.
89-04-10: 89-04-10 GULFSTREAM: Amendment 39-6156. Final copy of Priority Letter issued February 16, 1989. Applicability: Model G-IV airplanes, Serial Numbers 1060 through 1088; and all G-IV airplanes, Serial Numbers 1000 through 1059, which have been modified by Gulfstream Product Enhancement Program # 16 (PEP-16); certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent inadvertent pusher activation during rotation on takeoff, accomplish the following: A. Within 24 hours after the effective date of this Airworthiness Directive (AD), and until modifications required by paragraph B., below, are accomplished, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the following limitation. This may be accomplished by inserting a copy of this AD in the AFM: "OPERATIONS AT AIRFIELDS WITH A PRESSURE ALTITUDE BELOW SEA LEVEL ARE PROHIBITED." B. Within 14 days after the effective date of this AD, replace Sundstrand Stall Warning Computer, part number (P/N) 965-0041-034 (any Mod Number), with Sundstrand Stall Warning Computer, P/N 965-0041-036, in accordance with Gulfstream Customer Alert Bulletin Number 4, dated February 1, 1989. C. An alternate means of compliance or adjustment of compliance times, which provides an acceptable level of safety, may be used when approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region. NOTE: If appropriate, the request should be forwarded through a Principal Avionics Inspector, (PAI), who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not received copies of the service information from the manufacturer, may obtain copies upon request to Gulfstream Aerospace Corporation, Technical Operations Department, Travis Field, P.O. Box 2206, Savannah, Georgia 31404-2206. This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or at the FAA, Central Region, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia. This AD was effective earlier to all recipients of Priority Letter AD 89-04-10, dated February 16, 1989. This amendment (39-6156, AD 89-04-10) becomes effective April 3, 1989.
98-11-02: This amendment adopts a new airworthiness directive (AD) that is applicable to all Fokker Model F28 Mark 0070 and Mark 0100 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with instructions not to arm the liftdumper system prior to commanding the landing gear to extend. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent inadvertent deployment of the liftdumpers during approach for landing, and consequent reduced controllability and performance of the airplane.
86-20-09: 86-20-09 ROLLS-ROYCE plc (formerly Rolls-Royce Limited): Amendment 39-5425. Applies to Rolls- Royce (R-R) RB211-22B turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent disk failures that can cause uncontained engine failures, accomplish the following: (a) Remove from service, prior to further flight, all intermediate pressure compressor (IPC) stage 6 to 7 rotor assemblies listed individually by serial numbers in Appendices 1 and 2 of R-R Mandatory Service Bulletin (SB) RB.211-72-6427. Revision 2, dated June 30, 1984, or FAA approved equivalent, that have accumulated total cycles in service since new, on the effective date of this AD, in excess of the service life specified in those appendices. (b) Remove from service all IPC stage 6 to 7 rotor assemblies listed individually by serial number in Appendices 1 and 2 of R-R Mandatory SB RB.211-72-6427, Revision 2, dated June 30, 1984, or FAA approved equivalent, on or before attaining the service life specified in their respective appendix. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. R-R Mandatory SB RB.211-72-6427 dated June 30, 1984, 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 manufacturer may obtain copies upon request to Rolls- Royce plc, P.O. Box 31, Derby DE2 8BJ, England. This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Rules Docket Number 85-ANE-35, Room 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. This amendment becomes effective on November 4, 1986.
83-22-06: 83-22-06 CESSNA: Amendment 39-4763. Applies to the following airplanes certificated in any category: \n\n\nModel\nSerial Number \n152\n15282032 thru 15284659, 15284661 thru 15284684, 15284686 thru 15284851, 15284853 thru 15285417, 15285419 thru 15285621, 15285623 thru 15285625, 15285627 thru 15285651, 15285653 thru 15285681, 15285683, 15285685 thru 15285693, 15285695 thru 15285700, 15285702 thru 15285713, 15285716 thru 15285719, 15285722 thru 15285724, 15285726 thru 15285728, 15285730 thru 15285731, 15285733 thru 15285744, 15285748, 15285750, 15285751, 15285753, 15285756, 15285757, 15285759, 15285760, 15285764, 15285765, 15285767, 15285769, 15285772, 15285773, 15285778, 15285779, 15285781, 15285783, \nA152\nA1520809 thru A1520990, A1520992 thru A1520997, A1520999 thru A1521020, A1521022, \n172N\n17271035 thru 17274009, \n172P\n17274010 thru 17275806, 17275809, 17275817 thru 17275854, 17275857, 17275861 thru 17275881, 17275883 thru 17275910, 17275912 thru 17275947, 17275949 thru 17275953, 17275955 thru 17275958, 17275960 thru 17275971, 17275973, 17275974, 17275976, 17275978, 17275980 thru 17275982, 17275984, 17275986 thru 17275992, 17275994, 17275995, 17275997, 17275999 thru 17276002, 17276005, 17276010, 17276012, 17276014, \n172Q\n17275869 thru 17275881, 17275883 thru 17275910, 17275912 thru 17275947, 17275949 thru 17275953, 17275955 thru 17275958, 17275960 thru 17275971, 17275973, 17275974, 17275976, 17275978, 17275980 thru 17275982, 17275984, 17275986 thru 17275992, 17275994, 17275995, 17275997, 17275999 thru 17276002, 17276005, 17276010, 17276012, 17276014, \n172RG\n172RG0001 thru 172RG1134, 172RG1137, \nR172K\nR1722930 thru R1723454, \n180K\n18053001 thru 18053203,\n182Q\n18266591 thru 18267715, \n182R and \n18267716 thru 18268103, 18268105 thru 18268107, \nT182\n18268109 thru 18268129, 18268131 thru 18268141, 18268143, 18268144, 18268146 thru 18268293, 18268295, 18268310, 18268312 thru 18268322, 18268324 thru 18268327, 18268330 thru 18268332, 18268335, 18268336, 18268339, 18268343, 18268345, 18268348, 18268350, \nR182 and\nR18200584 thru R18201912, R18201914 thru R18201933, \nTR182\nR18201935 thru R18201938, R18201940, R18201942, R18201943, R18201945, R18201946, R18201949, R18201950, R18201953, R18201954, \nA185F\n18503684 thru 18504334, 18504336, 18504337, 18504339 thru 18504395, 18504397, 18504398, 18504400, \nF152\nF15201529 thru F15201883, F15201885 thru F15201896, F15201898 thru F15201931, F15201933, F15201935, F15201936, \nFA152\nFA1520348 thru FA1520382, \nF172N\nF17201750 thru F17202039, \nF172P\nF17202040 thru F17202146, F17202148 thru F17202175, F17202177 thru F17202181, F17202183 thru F17202186, F17202189 thru F17202194, F17202197, F17202200, F17202202,\nFR172K\nFR17200631 thru FR17200675, \nFl82Q\nF18200095 thru F18200169, \nFR182\nFR18200021 thru FR18200070,\n\n\tCompliance: Required as indicated, unless already accomplished. \n\n\tTo prevent possible loss of an aileron hinge pin, accomplish the following: \n\n\ta)\tWithin the next 100 hours time in service, after the effective date of this AD, visually inspect each aileron hinge (6 total) for correct location of the cotter pin in accordance with Figure 1. of this AD or Cessna Service Information Letter SE83-18 dated July 29, 1983. \n\n\t \t1.\tIf the cotter pin holes are correctly located the airplane may be returned to service without further action. \n\n\t \t2.\tIf the cotter pin holes are incorrectly located, prior to further flight modify or replace aileron hinges in accordance with instructions in Figure 1. of this AD or Cessna Service Information Letter SE83-l8 dated July 29, 1983. \n\n\tb)\tAirplanes may be flown in accordance with FAR 21.197 to a base where this AD may be accomplished. \n\n\tc)\tAn equivalent method of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, Room 238, Terminal Building 2299, Wichita, Kansas 67209, telephone (316) 269-7000. \n\n\tThis amendmentbecomes effective on November 8, 1983. \n\n\n\n\n\n\n\n\n\nFigure 1. Aileron Hinge Inspection, Modification or Replacement.
2019-15-10: The FAA is adopting a new airworthiness directive (AD) for certain Safran Aerosystems (formerly Zodiac Aerospace Services) life jackets. This AD was prompted by reports of defective welding on certain life jackets around the inflation system. This AD requires removal and replacement of the affected life jackets. The FAA is issuing this AD to address the unsafe condition on these products.
85-12-03: 85-12-03 DeHAVILLAND: Amendment 39-5074. Applies to DeHavilland Model DHC-7 series airplanes, serial numbers (S/N) 3 thru 86, 89, 91, 94, and 95, certificated in all categories. To preclude the occurrence of a ground fire caused by engine fuel impinging on landing gear brakes under certain wind conditions, accomplish the following, unless already accomplished: A. Within the next nine months after the effective date of this AD, accomplish a modification of the engine fuel drain system in accordance with Modification No. 7/2175 and DeHavilland Service Bulletin 7-71-18, Revision A, dated January 20, 1984. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and modifications required by this AD. This amendment becomes effective July 5, 1985.
99-23-26: This amendment supersedes an existing airworthiness directive (AD), applicable to General Electric Aircraft Engines (GE) CF34 series turbofan engines, that currently requires installation of a main fuel control (MFC) that incorporates a flange vent groove and installation of an MFC with improved overspeed protection. This amendment requires replacement of Buna-N O-rings with Viton O-rings or a new location of the vent groove on the MFC mounting flange, or installation of an MFC with improved overspeed protection. This amendment is prompted by the determination that the location of the reworked vent groove was ineffective, and that replacement of Buna-N preformed packings with Viton preformed packings will alleviate the unsafe condition. The actions specified by this AD are intended to prevent uncommanded engine accelerations, which could result in an engine overspeed, uncontained engine failure, and damage to the airplane. The incorporation by reference of GE Alert ServiceBulletins (ASB s) No. A73-33, dated November 21, 1997; A73-33, Revision 1, dated May 29.1998; and A73-19, Revision 1, dated February 20, 1998, was approved by the Director of the Federal Register as of July 27, 1999. The incorporation by reference of GE ASB No. CF34AL 73-A0025, dated July 7, 1999; CF34BJ 73-A0040, dated July 7, 1999; CF34AL S/B 73-0026, dated August 12, 1999; and CF34BJ S/B 73-0041, dated August 12,1999, is approved by the Director of the Federal Register as of December 6, 1999. Comments for inclusion in the Rules Docket must be received on or before January 18, 2000.
82-25-10: 82-25-10 AVCO LYCOMING: Amendment 39-4511. Applies to Avco Lycoming ALF502L, L-2, R-3, and R-4 Turbofan Engines. Compliance is required as indicated unless already accomplished. To prevent engine power loss, uncontained engine failure, and in-flight engine shutdown, caused by separation of first stage compressor stator vane airfoils and/or separation of fourth stage turbine blade airfoils, one of which was not contained, accomplish the following: (a) Prior to December 16, 1982, and thereafter at intervals not to exceed 50 operating cycles since the last inspection, perform boroscope inspections of first stator vane segments in accordance with Avco Lycoming Service Bulletin ALF502-72-0012, Revision 2, dated June 17, 1982, until paragraph (b) is accomplished. (b) Prior to July 1, 1983, replace first stage compressor stator vane assembly with the improved first stage compressor stator vane assembly in accordance with Avco Lycoming Service Bulletin ALF502-72-0025,Revision 1, dated June 17, 1982. (c) Prior to December 16, 1982, conduct eddy current inspections of fourth stage turbine blades in accordance with Avco Lycoming Service Bulletin ALF502-72-0027 dated May 26, 1982. (d) Prior to July 1, 1983, replace fourth stage turbine nozzle with the improved fourth stage turbine nozzle in accordance with Avco Lycoming Service Bulletin ALF502-72-0021, dated April 16, 1982. (e) Later FAA approved revisions of the service bulletins, referred to in this AD, and/or equivalent means approved by the Manager, Engine Certification Branch, FAA, New England Region, may be used in lieu of the above listed service bulletins. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Manager, Engine Certification Branch, FAA, New England Region, may adjust the compliance date specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiatingdata to justify the increase for that operator. This amendment becomes effective December 16, 1982.
2019-15-01: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model CL-600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. This AD was prompted by a report that main landing gear (MLG) side stay actuators have been assembled using nonconforming split ball bearings. This AD requires verification of the serial numbers of the installed MLG side stay actuator assemblies, and replacement of the affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2019-15-06: The FAA is superseding Airworthiness Directive (AD) 2018-22-07 for all Engine Alliance (EA) GP7270, GP7272, and GP7277 model turbofan engines. AD 2018-22-07 required inspection of the stage 6 seal ring for correct installation and inspection of the high-pressure compressor (HPC) stages 2-5 spool for cracks and, depending on the results of the inspections, replacement of the HPC stages 2-5 spool with a part eligible for installation. This AD requires the same inspections but reduces the inspection interval and adds a repetitive inspection and a mandatory terminating action. This AD was prompted by a shop finding of axial cracks in the interstage 5-6 seal teeth of the HPC stages 2-5 spool spacer arm due to an incorrectly installed stage 6 seal ring. The FAA is issuing this AD to address the unsafe condition on these products.
99-02-18: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires removing the thermal insulating blankets from the upper rear nacelle structure; re-positioning the engine exhaust duct; and replacing the engine exhaust bracket with a new engine exhaust bracket, if necessary. For certain airplanes, this amendment also requires installing new stainless steel plates onto the upper rear nacelle structure. 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 fretting of the titanium thermal insulating blankets, which could result in an increased risk of fire in the engine exhaust duct of the tail pipe.
98-21-13: This amendment adopts a new airworthiness directive (AD) that applies to certain British Aerospace Jetstream Model 3101 airplanes. This AD requires replacing the elevator trim servo motor with a new motor of improved design; and inspecting the cable tension and electrical operation of the elevator and trim tab for proper operation, and making any necessary adjustments. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent the elevator trim servo motor drive gear assembly from remaining engaged when the autopilot is disengaged, which could result in the pilot having to manually overpower the elevator trim control and possibly lose directional control of the airplane during critical phases of flight.
2019-16-02: The FAA is adopting a new airworthiness directive (AD) for all GE Honda Aero Engines (GHAE) HF120 model turbofan engines with a certain fuel pump metering unit (FPMU) assembly. This AD was prompted by damage found on the permanent magnetic alternator (PMA) drive gear within the FPMU assembly. This AD requires removal of a certain FPMU assembly and its replacement with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
98-19-15: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-19-15, which was sent previously to all known U.S. owners and operators of Fairchild Aircraft, Inc. (Fairchild) SA226 and SA227 series airplanes. The AD applies to those airplanes that are equipped with Barber-Colman pitch trim actuators, part number (P/N) 27-19008-001 or P/N 27-19008-002. This AD requires incorporating information into the Limitations Section of the airplane flight manual (AFM) that imposes a speed restriction and a minimum pilot requirement. The AD resulted from reports of two incidents of abrupt movement of the horizontal stabilizer to or near the full airplane nose-up position. These two incidents involved mechanical failure of these Barber-Colman pitch trim actuators. The actions specified by this AD are intended to lessen the severity of airplane pitch up caused by mechanical failure of the pitch trim actuator, which could result in a pitch upset and structural failure of the airplane.
2007-03-04: We are adopting a new airworthiness directive (AD) for the products listed above. 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 of the wing MLG (main landing gear) rib 6 aft bearing forward lugs, which could result in reduced structural integrity of the MLG attachment. This AD requires actions that are intended to address the unsafe condition described in the MCAI.