Results
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.
88-13-08: 88-13-08 PARTENAVIA COSTRUZIONE AERONAUTICHE S.p.A: Amendment 39-5953. Applies to models P 68, P 68B, P 68C, P 68C-TC, P 68 "Observer", and P 68-TC "Observer" (all serial numbers (S/N)) airplanes certificated in any category. Compliance: Required initially within 6 calendar months after the effective date of this AD unless already accomplished within the last 24 calendar months preceding the effective date of this AD, and thereafter at intervals not to exceed 24 calendar months or 500 hours time-in- service, (TIS) whichever occurs first, unless already accomplished. To prevent engine mount failure, whirl mode flutter, and structural failure of the wing, accomplish the following: (a) For S/N 1 thru 368, at the time of the initial inspection specified in this AD, modify the engine skin panels for inspection access in accordance with the instructions in Section 1 of Partenavia Service Bulletin (S/B) No. 70, Rev. 1, dated May 13, 1987. (b) For S/N 1 thru 368, visually inspect the upper and lower engine mounts and attachments for surface corrosion and cracks in accordance with the instructions in Section 1 of the above S/B. If cracks or surface corrosion are found, prior to further flight repair the affected structure in accordance with the instructions in paragraph (d) of this AD. (c) For S/N 369 and subsequent, visually inspect the upper and lower engine mounts and attachments for surface corrosion and cracks in accordance with the instructions in Section 3 of the above S/B. If cracks or surface corrosion are found, prior to further flight repair the affected structure in accordance with the instructions in paragraph (d) of this AD. (d) If cracks or surface corrosion are found as a result of the inspections specified in paragraphs (b) or (c) of this AD, prior to further flight, repair the affected structure as follows: (1) If the surface corrosion or crack extends no deeper than 75/1000 (7.5 percent) of the original local thickness, so that no less than 92.5 percent of the original local thickness remains, repair using the procedures described in Section 1 of Partenavia S/B No. 70, Rev. 1, dated May 13, 1987. (2) If any crack or surface corrosion extends deeper than 75/1000 (7.5 percent) of the original local thickness, so that less than 92.5 percent of the original local thickness remains including blistering, pitting, or flaking, prior to further flight, remove and replace the affected part with a serviceable part as described in Section 2 of Partenavia S/B No. 70, Rev. 1, dated May 13, 1987. (e) Within one week following each inspection specified in paragraph (b) or (c) of this AD, submit a written report of the result of that inspection to include whether or not damage was found, part number(s) involved, extent, location, and description of any damage found, and a brief description of remedial measures. Submit the reports to the FAA, ACE-109, 601 East 12th Street, Kansas City, Missouri 64106.If an inspection was made previous to this AD, forward the requested data within one week of receipt of this AD. (Report approved by the Office of Management and Budget under OMB No. 2120-0056.) (f) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (g) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, B-1000, Brussels, Belgium; Telephone (322) 513.3830 ext. 3710/2711. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Partenavia Costruzione Aeronautiche, S.p.A., Via Cava, Casoria-Naples, Italy; Telephone 81 759-0946 (Product Support); or may examine these documents at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment, 39-5953, becomes effective onJuly 13, 1988.
2000-26-03: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 and A300-600 series airplanes, that currently requires wiring modifications to the engine and auxiliary power unit (APU) fire detection system. This amendment requires new wiring modifications for the engine and APU fire detection system. 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 the fire warning from terminating prematurely, which could result in an unnoticed, uncontained engine/APU fire.
2019-14-10: The FAA is superseding Airworthiness Directive (AD) 2018-02- 11, which applies to certain Airbus SAS Model A330-301, -321, -322, and -342 airplanes. AD 2018-02-11 requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. Since the FAA issued AD 2018-02-11, the agency received a report of additional cracking found on different airplane models, and of an update to the fatigue and damage tolerance analysis. This AD requires repetitive detailed inspections of the horizontal stabilizer (HS) center box (CB) top skin integral flange area, and repair if necessary. This AD also expands the applicability to include additional airplane models. The FAA is issuing this AD to address the unsafe condition on these products.
2007-01-13: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A310-300 airplanes. This AD requires replacing the existing non-return valve (NRV) of the auxiliary center tanks (ACTs) of the fuel system with a new, improved NRV. This AD results from a report that it was not possible to transfer fuel from ACTs 1 and 2 during flight, and no electronic centralized aircraft monitor warnings were triggered. Investigation revealed a faulty static inverter and blown fuse, resulting in failure of certain fueling bus bars and subsequent failure of the automatic ACT fuel transfer. We are issuing this AD to prevent these failures, combined with failure of the NRV to close. If the NRV is open during flight, the fuel supply to the engines may be reduced during cross-feed operation to the extent that fuel starvation could occur and result in engine flameout.
2007-01-12: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Model Mystere-Falcon 50 and 900, and Falcon 900EX airplanes; and Model Falcon 2000 and Falcon 2000EX airplanes. This AD requires an inspection of the identification plates of the outboard slats to determine the type of identification plates and the part numbers. For certain airplanes, this AD also requires a revision to the Limitations and Normal Procedures sections of the airplane flight manual to provide procedures for operation in icing conditions; and replacement of the anti-icing manifold with an anti-icing manifold of the correct type design if necessary. For certain airplanes, this AD also requires related investigative and corrective actions if necessary. This AD results from a finding that the outboard slats for Model Mystere-Falcon 50 airplanes have been erroneously authorized, in limited cases, as interchangeable for use on Model Mystere-Falcon 900 and Falcon 900EX airplanes; and Model Falcon 2000 and Falcon 2000EX airplanes. We are issuing this AD to prevent failure of the anti-icing manifold of the outboard slats, which could result in loss of control of the airplane.
2007-01-14: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires revising the Airworthiness Limitations Items (ALI) of the maintenance requirements manual to require additional inspection requirements of the maintenance requirements manual for certain principal structural elements (PSEs) related to fuselage cutouts and to reduce an inspection threshold for an existing ALI task on the aft entry door. This AD results from data obtained from the manufacturer's fatigue testing. We are issuing this AD to detect and correct fatigue cracking of certain PSEs, which could result in reduced structural integrity of the airplane.
82-27-09: 82-27-09 EMBRAER: Amendment 39-4527. Applies to Model EMB-110, Serial Number 110001 and up, airplanes certificated in any category. COMPLIANCE: Required as indicated unless already accomplished. To prevent loss of the airplane's primary flight controls, within the next 100 hours time-in- service after the effective date of this AD on airplanes having more than 1000 hours time-in-service or prior to the accumulation of 1100 hours time-in-service on airplanes having less than 1000 hours time-in-service and within 1000 hours time-in-service thereafter, accomplish the following: a. Inspect the primary flight control cables in accordance with the instructions contained in EMBRAER Service Bulletin No. 110-27-064, dated September 28, 1982. 1) If cables are within the limits prescribed in Section II of "Maintenance Manual - Flight Controls," lubricate and rerig in accordance with EMBRAER Service Bulletin No. 110-27-064 and applicable Maintenance Manuals. 2) Ifcables are worn and/or have broken wires beyond the limits of Section II of "Maintenance Manual - Flight Controls," remove and replace cables in accordance with Section III of "Maintenance Manual - Flight Controls." b. The time-in-service between the repetitive inspections required herein may be adjusted up to plus 10 percent of any specified inspection interval required by this AD to facilitate accomplishing these inspections concurrent with other scheduled maintenance on the airplane. c. Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. d. An equivalent method of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, ACE-115A, FAA, P.O. Box 20636, Atlanta, Georgia 30320. This amendment becomes effective on January 10, 1983.
87-10-11: 87-10-11 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-5976. Final copy of Telegraphic AD. Applies to the following helicopters certificated in any category (Airworthiness Docket No. 87-ASW-22). (a) Model 206A and 206B helicopters equipped with the following mast assemblies, P/N 206-010-332-121: Serial Numbers FAJF-58340 thru 58353, 58395 thru 58398, 58400, 58402 thru 58408, 58421 and 58423 thru 58434. NOTE: The following model 206B serial numbered helicopters were delivered with the affected masts: 3933, 3934, 3937 thru 3940, 3942, 3944 thru 3946, 3953 thru 3955, and 3958. (b) Model 206L, 206L-1, and 206L-3 helicopters equipped with the following mast assemblies, P/N 206-040-535-105: Serial Numbers NJF-935 thru 973, 1000, 1003, 1004, 1006 thru 1012, 1014 thru 1019, 1022 thru 1024, 1026, 1040 thru 1042, 1046, 1050 thru 1057, 1059, 1066, 1068, 1073, 1079, 1086, 1087, 1089 thru 1097, 1099, 1101, 1102, 1123, 1124, 1129, 1135, 1141, 1143, 1145, 1146, 1149, 1151, 1153, 1156, 1157, 1161, 1162, 1165, 1167, and 1169 thru 1172. NOTE: The following Model 206L-3 serial numbered helicopters were delivered with the affected masts: 51173 thru 51175, 51178, 51179, 51181, 51183 thru 51185, 51187 thru 51191, 51194 thru 51205, and 51208 thru 51211. Compliance is required as indicated, unless already accomplished. To prevent failure of the main rotor mast, accomplish the following: (a) Before further flight, determine if an affected serial number main rotor mast is installed on the helicopter. (b) Within the next 25 hours' time in service after receipt of this AD but no later than May 31, 1987, remove the affected serial number main rotor mast from service and replace it with an airworthy part. (c) An alternate method of compliance or adjustment of the compliance time, which provides an equivalent level of safety, may be used when approved by the Manager, Helicopter Certification Branch, Aircraft Certification Division, FAA, Southwest Region, Fort Worth, Texas 76193-0170. NOTE: Bell Helicopter Alert Service Bulletin Nos. 206-87-37, dated 4/23/87 and 206-87-44, dated 4/23/87 pertain to this AD. This amendment becomes effective August 8, 1988, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD No. 87-10-11 issued May 19, 1987, which contained this amendment.
85-15-03: 85-15-03 AEROSPATIALE (SUD NORD): Amendment 39-5099. Applies to the Nord Model 262A series airplanes which have not incorporated STC SA2369SW, certificated in any category. Compliance required within 90 days after the effective date of this airworthiness directive (AD), unless already accomplished. To prevent undetected system failures or malfunctions in the windshield and turbine engine anti-icing systems, accomplish the following: A. Install additional fuses in the windshield anti-icing control circuitry for all windshield panels in accordance with Nord Service Bulletin No. 30-14, dated September 29, 1971 (which constitutes Nord modification No. 733), on Nord Model 262A series airplanes having serial numbers 8 through 20, 22 through 27, 29 through 35, 37 through 42, 47 through 50, 54, 56, 69, 74, and 84. B. Accomplish modifications to the turbine engine anti-icing control circuitry described in the planning section, paragraph I.C. of Nord Service Bulletin No. 30-15, dated October 29, 1971, as revised August 27, 1974 (which constitutes Nord modification No. 669). Accomplish the modifications in accordance with the Section II, Accomplishment Instructions, of the service bulletin on Nord Model 262A series airplanes having serial numbers 4 through 27, 29 through 35, 37 through 42, 47 through 50, 54, 56, 57, 69, and 84. C. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Standardization Branch, Aircraft Certification Division, FAA, Northwest Mountain Region. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective August 22, 1985.
2007-02-18: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Boeing Model 767-200, -300, and -300F series airplanes. That AD currently requires an inspection of visually accessible areas for indications of overheating of the heater tape attached to the potable water fill and drain lines in the forward and aft cargo compartments, exposed foam insulation or missing or damaged protective tape around the potable water fill and drain lines, and debris or contaminants on or near the potable water fill and drain lines. That AD also requires corrective action, as necessary. This new AD requires repetitive inspections of the forward and aft cargo compartments, as applicable, for discrepancies of the potable water supply and gray water drain lines; and applicable corrective actions if necessary. This AD also requires replacing the heater tapes on the potable water supply and gray water drain lines of the forward and aft cargo compartments, as applicable, withnew ribbon heaters, or deactivating and removing any defective heater tape and wrapping the drain line with foam insulation; either action ends the repetitive inspections. This AD results from a report of a fire in the aft cargo compartment. We are issuing this AD to prevent overheating of the heater tape on potable water fill and drain lines, which may ignite accumulated debris or contaminants on or near the potable water fill and drain lines, resulting in a fire in the airplane.
89-12-08: 89-12-08 ISRAEL AIRCRAFT INDUSTRIES (IAI): Amendment 39-6233. Applicability: Model 1121, 1121A, 1121B, 1123, 1124, and 1124A, series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect cracks in the hinge lugs of the horizontal stabilizer aft spar splice fitting (hinge assembly), accomplish the following: A. Within the next 75 flight hours time-in-service after the effective date of this AD, unless previously accomplished within the last 225 flight hours time-in-service, conduct a visual inspection of the horizontal stabilizer aft spar splice fitting (hinge assembly), Part Number 453005-501, in accordance with the following IAI service bulletins entitled "Horizontal Stabilizer Aft Spar Splice Fitting P/N 453005-501 (Hinge Assembly) Inspection", as appropriate: Model Service Bulletin 1121, 1121A, 1121B 1121-55-003, Revision 1, dated August 8, 1988 1123 1123-55-006, Revision 1, datedAugust 8, 1988 1124, 1124A 1124-55-020, Revision 2, dated August 8, 1988 B. If no cracks are found, repeat the inspection required by paragraph A., above, at intervals not to exceed 300 hours time-in-service. C. If cracks are found, replace the splice fitting prior to further flight, in accordance with the following IAI service bulletins entitled "Horizontal Stabilizer Assembly - Inspection, Repair, and Improvement (AFC 2037)," as appropriate: Model Service Bulletin 1121, 1121A, 1121B 1121-55-004, Revision 2, dated October 21, 1988 1123 1123-55-007, Revision 2, dated October 21, 1988 1124, 1124A 1124-55-021, Revision 3, dated October 21, 1988 D. Following replacement of the splice fitting, described in the above service bulletins, repeat the inspection required by paragraph A. of this AD at intervals not to exceed 300 hours time-in-service. E. An 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: 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, Standardization Branch, ANM-113. F. 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 already received the appropriate service documents from the manufacturer may obtain copies upon request to Israel Aircraft Industries, Delaware Office, P.O. Box 10086, Wilmington, Delaware 19850. 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. This AD supersedes AD 86-14-02, Amendment 39-5341, which became effective on August 4, 1986. This amendment (39-6233, AD 89-12-08) becomes effective on July 10, 1989.
2019-15-04: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report of a mis-installed no-back pawl discovered on a horizontal stabilizer trim actuator (HSTA). This AD requires an inspection to verify the horizontal stabilizer trim electronic control unit (HSTECU) part number, a software upgrade for certain HSTECUs, and installation of HSTECUs with upgraded software. The FAA is issuing this AD to address the unsafe condition on these products.
83-24-06: 83-24-06 CANADAIR: Amendment 39-4777. Applies to all Canadair Model CL-44D4 and CL-44J airplanes certificated in all categories. Compliance required as indicated unless previously accomplished. To ensure structural integrity of the upper main landing gear actuator eye attachment pins, accomplish the following within the next 100 hours time in service or 25 landings, whichever occurs first, after the effective date of this airworthiness directive (AD), unless accomplished within the last 1100 hours time in service or 275 landings, and thereafter at intervals not to exceed 1200 hours time in service or 300 landings, whichever occurs first. 1. Inspect both left and right upper main landing gear actuator eye attachment pins, P/N 44-87815, for cracks in accordance with paragraph 2.1 of Canadair Service Information Circular (SIC) No. 441-CL44, dated June 8, 1981. 2. Replace cracked parts with new or serviceable parts of the same part number prior to further flight. 3. Alternate means of compliance with the AD which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. 4. Aircraft may be ferried to a base for maintenance in accordance with Sections 21.197 and 21.199 of the Federal Aviation Regulations. 5. Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of an operator, if the request contains substantiating data to justify the adjustment period. This amendment becomes effective December 20, 1983.
2000-24-22: This amendment adopts a new airworthiness directive (AD) that applies to all S.N. CENTRAIR Model 201B gliders. This AD requires you to modify the rear canopy emergency release system. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to prevent the rear canopy retaining strap from not releasing properly during the emergency egress procedure because of the current design of the rear canopy emergency release system. This condition, if not corrected, will not allow the rear canopy to completely separate from the glider and could result in potential injury to the pilot during an emergency egress.
84-18-07: 84-18-07 WALTER KIDDE AND OVERLAND AVIATION SERVICE CO: Amendment 39-4915. Applies to Walter Kidde discharge cartridges Part Number (P/N) 873571, 876296, 897776, and 898558 manufactured prior to July 1984, and Overland Aviation Service Co. discharge cartridges P/N OA873571, OA876296, and OA876299 manufactured prior to August 7, 1984. Compliance: Required within thirty (30) calendar days or at installation on any aircraft, whichever occurs later, unless already accomplished. To prevent hazards in flight associated with the non-operation of the fire extinguisher caused by non-firing of the discharge cartridge(s), accomplish the following: (a) Pull the applicable circuit breakers and disconnect the fire extinguisher bottle electrical plugs from the discharge cartridge. Inspect the electrical receptacle of the cartridge for compressed aluminum foil, which may have the appearance of solder and remove if present. Reinstall the plug and reset the applicable circuit breaker. (b) An equivalent means of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, 1075 Innerloop Road, College Park, Georgia 30337; telephone (404) 763-7248. This amendment becomes effective on September 21, 1984.