Results
99-23-02: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA-365N, SA 365N1, and AS-365N2 helicopters, that requires replacing certain defective electrical modules with airworthy electrical modules. This amendment is prompted by the discovery of several defective electrical modules. The actions specified by this AD are intended to prevent loss of electrical continuity, which could cause loss of critical rotorcraft electrical systems and subsequent loss of control of the helicopter.
99-23-01: This amendment supersedes an existing airworthiness directive (AD), applicable to Robinson Model R44 helicopters, that currently requires removing and replacing the pilot's cyclic control grip assembly (grip assembly) with an airworthy grip assembly. This amendment requires the same actions as the current AD but would change a part number (P/N) referenced in the current AD. This amendment is prompted by the discovery of an error in the P/N of the current AD. The actions specified by this AD are intended to prevent use of a grip assembly that may crack, resulting in failure of the grip assembly and subsequent loss of control of the helicopter.
99-22-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that requires a one-time detailed visual inspection of the upper decompression panel on the flight deck door to verify that a minimum overlap dimension exists, and corrective action, if necessary. This amendment is prompted by reports indicating that, during production, some upper decompression panels were installed incorrectly on the flight deck door. The actions specified by this AD are intended to detect an incorrectly installed upper decompression panel, which could cause the emergency exit panel on the flight deck door to become inoperable, thereby preventing crewmembers from performing essential duties during an emergency evacuation.
2008-13-05: We are superseding an existing 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: Defective burner hoses have been identified which might develop a leak. A significant leak, if it was ignited, could hazard the balloon and occupants. Since the issue of AD G-2003-0010 there have been occurrences of hose failure in batches not identified in the earlier bulletins. LHAB Service Bulletin (SB) No 11 supersedes the earlier SBs and revises the applicability as required. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective July 23, 2008. As of April 1, 2008 (73 FR 13113, March 12, 2008), the Director of the Federal Register approved the incorporation byreference of Lindstrand Hot Air Balloons Ltd. Service Bulletin No. 11, Issue 1, dated September 24, 2007, listed in this AD.
2003-11-11: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 series airplanes, that currently requires repetitive eddy current inspections for cracking of the main landing gear (MLG) main fittings, and replacement with new or serviceable MLG main fittings if necessary. That AD also requires servicing the MLG shock struts; inspecting the MLG shock struts for nitrogen pressure, visible chrome dimension, and oil leakage; and performing corrective actions, if necessary. This amendment clarifies the applicability, adds certain repetitive inspections, reduces an initial inspection threshold, and removes a provision to extend the repetitive interval for the eddy current inspection. 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 failure of the MLG main fittings, which could result incollapse of the MLG upon landing.
99-22-14: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Pratt & Whitney JT8D-200 series turbofan engines, that currently requires installation of high pressure turbine (HPT) containment hardware. This amendment requires removing low pressure turbine (LPT)-to-exhaust case bolts and nuts and replacement with improved LPT-to-exhaust case bolts and nuts, and installation of improved HPT containment hardware. This amendment is prompted by uncontained HPT events resulting from HPT shaft fractures and LPT flange separations resulting from LPT blade failures. The actions specified by this AD are intended to prevent damage to the airplane resulting from uncontained engine debris following an HPT shaft fracture or an LPT blade failure. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of December 28, 1999.
99-22-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes. This action requires an inspection of the crew rest area heat exchangers to detect deflection or interference with the flight control cables; and various follow-on actions. This action also requires replacement of certain nutplate attachment rivets that attach the heat exchangers to the airframe with stronger rivets. This amendment is prompted by a report of interference between insulation blankets adjacent to the heat exchangers and flight control cables. The actions specified in this AD are intended to prevent a reduction in maximum rudder and elevator surface deflection due to the separation of heat exchangers from the body frame, which could result in reduced controllability of the airplane.
88-19-05: 88-19-05 BOEING: Amendment 39-6002. Applies to Model 767 series airplanes, equipped with Pratt and Whitney JT9D-7R4D, -7R4E, or -7R4E4 engines, or General Electric CF6-80A or -80A2 engines, certificated in any category. \n\n\tCompliance required within 180 days after the effective date of the AD, unless previously accomplished. \n\n\tTo preclude the spread of engine fire to other parts of the airplane through a gap in the engine firewall, accomplish the following:\n \n\tA.\tAccomplish either paragraph A.1., or A.2., below. \n\n\t\t1.\tInstall a firewall seal to cover a gap located between the engine core cowl and thrust reverser cowl at the pylon to cowl fillet fairing, in a manner approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\t\t2.\tInstall a firewall seal assembly in accordance with Boeing Alert Service Bulletin 767-54A0027, dated June 2, 1988, for airplanes equipped with Pratt and Whitney JT9D- 7R4D, -7R4E, or -7R4E4 engines; or Boeing Alert Service Bulletin 767-54A0028, dated June 10, 1988, for airplanes equipped with General Electric CF6-80A or -80A2 engines. \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 may add any comments 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. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment, 39-6002, becomes effective September 26, 1988.
89-19-03: 89-19-03 BOEING: Amendment 39-6315. (Docket No. 89-NM-164-AD) \n\tApplicability: Model 767 series airplanes, as listed in Boeing Alert Service Bulletin 767- 25A0135, dated July 6, 1989, certificated in any category.\n \n\tCompliance: Required within 30 days after the effective date of this AD, unless previously accomplished. \n\n\tTo ensure structural integrity of cabin partitions with a wall-mounted flight attendant seat, accomplish the following: \n\n\tA.\tReplace the upper mounting bolts of cabin partitions, in accordance with Boeing Alert Service Bulletin 767-25A0135, dated July 6, 1989. \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. 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 (39-6315, AD 89-19-03) becomes effective on September 19, 1989.
2006-09-01: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. That AD currently requires repetitive detailed and ultrasonic inspections of the thrust links of the rear engine mounts for any crack or fracture and corrective actions if necessary. This new AD requires repetitive replacement of the thrust links with new or overhauled thrust links, which ends the repetitive detailed and ultrasonic inspections. This AD results from the finding of fractured and cracked forward lugs of the rear engine mount thrust link on the number one strut on two airplanes. We are issuing this AD to prevent cracked or fractured thrust links that could lead to the loss of the load path for the rear engine mount bulkhead and damage to other primary engine mount structure, which could result in the in-flight separation of the engine from the airplane and consequent loss of control of the airplane.
99-22-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80 and C-9 (military) series airplanes, and Model MD-88 airplanes, that requires revising the wiring of the air conditioning pneumatic supply control, if applicable, and revising the wiring of the pneumatic augmentation valve. This amendment is prompted by a report indicating that the pneumatic augmentation valve may go fully open when an engine fails during initial climb prior to deactivation of the second segment climb switch. The actions specified by this AD are intended to prevent opening of the pneumatic augmentation valve, which could result in significant loss of thrust from the remaining engine and consequent inadequate initial climb performance of the airplane.
2006-08-10: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CT64-820-4 turboprop engines with certain part number (P/N) rotating parts. The parts are in the compressor rotor assembly, gas generator turbine rotor assembly, and power turbine rotor assembly that are subject to low-cycle fatigue. This AD requires removing from service these affected rotating parts at reduced compliance times. This AD results from the manufacturer's discovery of cracks in some rotating parts. We are issuing this AD to prevent cracks in the rotating parts that could cause compressor and turbine wheel fracture and uncontained engine failure. An uncontained engine failure could cause possible damage to the airplane.
89-16-08: 89-16-08 GENERAL ELECTRIC COMPANY: Amendment 39-6259. Applicability: General Electric Company (GE) CF6-80A/A1/A2/A3 turbofan engines. Compliance: Required as indicated, unless already accomplished. To provide increased fire protection in the event of a fire escaping from the LPT recoup manifold which could lead to fuel leakage and possible engine fire, accomplish the following prior to August 31, 1989: (a) Install on CF6-80A/A2 engines, two zirconia-coated fire shields, Part Numbers (P/N) 1306M85G01 and 1306M86G01, in accordance with GE CF6-80A series Alert Service Bulletin (ASB) A72-512, Revision 1, dated May 24, 1988. (b) Install on CF6-80A1/A3 engines, fire shield, P/N 1306M84P02, in accordance with GE CF6-80A series ASB A72-510, Revision 2, dated November 14, 1988. (c) 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. (d) Upon submission of substantiating data by anowner or operator through an FAA Airworthiness Inspector, an alternative method of compliance with the requirements of this AD or adjustments to the compliance time specified in this AD, may be approved by the Manager, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service, 12 New England Executive Park, Burlington, Massachusetts 01803. The installation of the required fire shields shall be done in accordance with the procedures given in GE CF6-80A series ASB A72-512, Revision 1, dated May 24, 1988 (CF6-80A/80A2 engines) or ASB A72-510, Revision 2, dated November 14, 1988, (CF6-80A1/A3 engines). This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from General Electric Aircraft Engines, CF6 Distribution Clerk, Room 132, 111 Merchant Street, Cincinnati, Ohio 45246. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the office of the Federal Register, 1100 L Street, Room 8301, Washington, DC 20591. This amendment (39-6259, AD 89-16-08) becomes effective on August 31, 1989.
99-21-32: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 series airplanes, that requires a one-time inspection to measure clearance and detect interference between the elevator cable pulley and the shroud frame of the ventral stairway, and modification of the shroud frame of the ventral stairway. This amendment is prompted by reports of pitch oscillation of several Model MD-90-30 series airplanes. The actions specified by this AD are intended to prevent interference between the elevator cable pulley and the shroud frame of the ventral stairway, which could result in pitch oscillation of the airplane, and consequent damage to the elevator cable pulley and reduced controllability of the airplane.
99-21-26: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Raytheon (Beech) Model 400, 400A, 400T, and MU-300-10 airplanes, that currently requires a revision to the Airplane Flight Manual (AFM) to provide pilots with special operating procedures during icing conditions. This amendment adds a requirement to modify the airplane ice protection system. This amendment also removes Model MU-300 airplanes from the applicability of the existing AD. This amendment is prompted by the development of a modification that will positively address the unsafe condition. The actions specified by this AD are intended to prevent uncommanded nose-down pitch at certain flap settings during icing conditions.
89-14-05: 89-14-05 AEROSPATIALE: Amendment 39-6244. Applicability: Model ATR42 series airplanes, Serial Numbers 003 through 138, certificated in any category. Compliance: Required within 10 days after the effective date of this AD, unless previously accomplished. To prevent loss of engine oil and engine shutdown, accomplish the following: A. Replace and lockwire the drain plug and adjacent locknut on the engine oil pressure manifold, in accordance with Aerospatiale Service Bulletin ATR42-79-0006, Revision 1, dated April 18, 1989. B. 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. C. 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 information from the manufacturer may obtain copies upon request to Aerospatiale, 216 Route de Bayonne, 31060 Toulouse, Cedex 03, France. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6244, AD 89-14-05) becomes effective on July 5, 1989.
89-08-04: 89-08-04 McDONNELL DOUGLAS: Amendment 39-6179. \n\n\tApplicability: Model DC-9, DC-9-80, and C-9 (Military) series airplanes, certificated in any category, as listed in McDonnell Douglas Model DC-9 Service Bulletin 27-173, Revision 1, dated May 20, 1982, and Service Bulletin 27-257, Revision 1, dated June 20, 1988. \n\n\tCompliance: Required within 12 months after the effective date of this airworthiness directive (AD), unless previously accomplished. \n\n\tTo eliminate lateral control difficulties after liftoff during takeoff, accomplish the following: \n\n\tA.\tFor McDonnell Douglas Model DC-9 and C-9 (Military) series airplanes, identified in McDonnell Douglas Model DC-9 Service Bulletin 27-173, Revision 1, dated May 20, 1982, and Service Bulletin 27-257, Revision 1, dated June 20, 1988: Install the Spoiler Position Sensing and Indication System and "spoiler deployed" annunciation takeoff inhibit feature in accordance with the accomplishment instructions of those service bulletins.B.\tFor McDonnell Douglas Model DC-9-81, and DC-9-82, and DC-9-83 series airplanes identified in McDonnell Douglas Model DC-9 Service Bulletin 27-257, Revision 1, dated June 20, 1988: Install the spoiler deployed annunciation takeoff inhibit feature in accordance with the accomplishment instructions of that service bulletin. \n\n\tC.\tFor all McDonnell Douglas Model DC-9-81, DC-9-82, and DC-9-83 airplanes with the production equivalent of McDonnell Douglas Model DC-9 Service Bulletin, 27-257, Revision, dated June 20, 1988, incorporated but presently de-activated: Re-activate the spoiler deployed annunciation takeoff inhibit feature in accordance with the airplane type design configuration. \n\n\tD.\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, Los Angeles Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Los Angeles Aircraft Certification Office. \n\n\tE.\tSpecial flight permits may be used 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 information from the manufacturer may obtain copies upon request to the McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-LOO (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 3229 East Spring Street, Long Beach, California. \n\n\tThis amendment (39-6179, AD 89-08-04) becomes effective on May 4, 1989.
70-21-04: 70-21-04 HAWKER SIDDELEY: Amendment 39-1089. Applies to de Havilland Model DH.114 "Heron" airplanes. Compliance is required as indicated. To prevent failure of the fin to fuselage front attachment brackets at Bulkhead 6, accomplish the following: (a) For all airplanes, within the next 1200 hours' time in service from the effective date of the AD, and thereafter at intervals not to exceed 1200 hours' time in service since the last inspection, visually inspect Bulkhead 6 for cracking or signs of distortion in accordance with Hawker Siddeley Technical News Sheet, Series: Heron (114), No. F.15, Issue 3, dated May 4, 1970, or later ARB- approved issue or an FAA-approved equivalent. If cracking or signs of distortion are found, accomplish standard repairs before further flight. (b) For airplanes having right-hand and left-hand forward fin attachment fittings, P/Ns 14FS.1891 and 14FS.1892 (pre-modification No. Heron 609), or right-hand and left-hand forward fin attachment fittings, P/Ns 14FS.5007 and 14FS.5008 (post-modification Heron 609) installed on Bulkhead 6, within the next 300 hours' time in service after the effective date of this AD, unless already accomplished within the last 300 hours' time in service, and thereafter at intervals not to exceed 300 hours' time in service since the last inspection, visually inspect the forward fin attachment fittings for cracks in accordance with Hawker Siddeley Technical News Sheet, Series: Heron (114), No. F.15, Issue 3, dated May 4, 1970, or later ARB-approved issue or an FAA-approved equivalent. If there is doubt as to the results of this inspection, confirm the results of the inspection by a dye penetrant method. (c) For airplanes having right-hand and left-hand forward fin attachment fittings, P/Ns 14 FS.4669 and 14 FS.4670 (post-modification No. Heron 869) installed on Bulkhead 6, within the next 300 hours' time in service after the effective date of this AD, unless already accomplished within the last 900 hours' time in service, and thereafter at intervals not to exceed 1200 hours' time in service since the last inspection, visually inspect the forward fin attachment fittings for cracks in accordance with Hawker Siddeley Technical News Sheet, Series: Heron (114), No. F.15, Issue 3, dated May 4, 1970, or later ARB-approved issue or an FAA-approved equivalent. If there is doubt as to the results of this inspection, confirm the results of the inspection by a dye penetrant method. (d) If cracks are found in a forward fin attachment fitting during the inspections required by paragraphs (b) or (c), accomplish the following before further flight: (1) Replace both the right-hand and left-hand forward attachment fittings in accordance with de Havilland Aircraft Service Modification No. Heron 869, Amendment No. 1, dated May 15, 1959, or later ARB-approved issue or an FAA-approved equivalent. (2) Visually inspect the fin attachment fittings on Bulkhead 7 and the fin attachment fittings on the fin rear spar for cracks or any other signs of damage, and replace any fittings found to be cracked or damaged with new fittings of the same part number. (e) For all airplanes, after accomplishing the replacements and inspections specified in paragraph (d), continue to visually inspect the forward fin attachment fittings for cracks in accordance with Hawker Siddeley Technical News Sheet, Series: Heron (114), No. F.15, Issue 3, dated May 4, 1970, or later ARB-approved issue or an FAA-approved equivalent, at intervals not to exceed 1200 hours' time in service since the last replacements and inspections accomplished in accordance with paragraph (d). If cracks are found during any of these inspections, replace the cracked fittings before further flight in accordance with de Havilland aircraft Service Modification No. Heron 869, Amendment No. 1, dated May 15, 1959, or later ARB-approved issue or an FAA-approved equivalent. This amendment becomes effective November 5, 1970.
2006-06-51: This document publishes in the Federal Register an amendment adopting emergency airworthiness directive (EAD) 2006-06-51 that we sent previously to all known U.S. owners and operators of GEAE CT7-8A turboshaft engines installed on Sikorsky S92 helicopters. This AD requires initial and repetitive inspections of the electrical chip detectors for the No. 3 bearing. This AD results from two failures of the No. 3 bearing in GEAE CT7-8A engines. We are issuing this AD to prevent failures of the No. 3 bearings and possible dual in-flight shutdowns of the engines.
86-21-02: 86-21-02 BRITISH AEROSPACE: Amendment 39-5420. Applies to BAe Model 146 series airplanes, as listed in BAe Service Bulletin 27-42-00671A, dated August 19, 1985, certificated in any category. Compliance is required within 60 days after the effective date of this AD, unless previously accomplished. To prevent control column oscillations, accomplish the following: A. Modify the elevator control system in accordance with BAe Service Bulletin 27- 42-00671A, dated August 19, 1985. B. 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. 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 the requirements of this AD. All persons affected by this directive who have not already received the appropriate service bulletin from the manufacturer may obtain copies upon request to British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041. This document may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This Amendment becomes effective October 24, 1986.
2020-11-07: The FAA is adopting a new airworthiness directive (AD) for MD \nHelicopters Inc., (MDHI) Model 369D, 369E, 369FF, 369H, 369HE, 369HM, \n369HS, 500N, and 600N helicopters. This AD was prompted by a report of \nnon-conforming main rotor (M/R) hub lead-lag bolts (bolts). This AD \nrequires removing certain bolts from service. The FAA is issuing this \nAD to address the unsafe condition on these products.
2006-04-13 R1: The FAA is revising an existing airworthiness directive (AD), which applies to certain Gulfstream Model GIV-X and GV-SP series airplanes. That AD currently requires revising the Limitations section of the airplane flight manual (AFM) by incorporating new procedures to follow in the event that the cockpit displays go blank or malfunction. This AD allows for the use of alternative AFM revisions for a certain subset of the existing applicability. This AD results from a report that all four of the cockpit flight panel display units simultaneously went blank during flight. We are issuing this AD to ensure that the flightcrew is advised of the appropriate procedures to follow in the event that the cockpit displays go blank or malfunction, which could result in a reduction of the flightcrew's situational awareness and possible loss of control of the airplane.
2020-11-04: The FAA is adopting a new airworthiness directive (AD) for certain Learjet Inc. Model 60 airplanes. This AD was prompted by a report of a reverse thrust command accelerating the airplane instead of decelerating the airplane. The acceleration with reverse thrust commanded occurred when the thrust reverser doors were in the stowed position instead of the deployed position. This AD requires installing a thrust reverser (T/R) Voice Command Warning System (VCWS) to alert the crew of a T/R malfunction. The FAA is \n\n((Page 30838)) \n\nissuing this AD to address the unsafe condition on these products.
2006-08-03: The FAA is adopting a new airworthiness directive (AD) for Sicma Aero Seat (formerly Farner) cabin attendant seats series 150 type FN and series 151 type WN. This AD requires installing two protection fairings over the upper seat structure to cover the gap between the upper and lower seats and prevent any contact with the bottom seat folding mechanisms. This AD results from a child catching its fingers in the folding mechanism of the bottom of the attendant seat. We are issuing this AD to prevent injury resulting from contact with the bottom folding mechanism.
89-10-09: 89-10-09 AEROSPATIALE: Amendment 39-6206. Applicability: All Model ATR42-200 and -300 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of a main landing gear wheel due to defective bearings, accomplish the following: A. Within 30 days after the effective date of this AD, inspect outboard bearings, Part Number (P/N) L910349, of the Loral main landing gear wheels, Loral P/N 5006856, 5006856-1, 5006856-2 and 5006856-3, and replace those having a "JV" date code, in accordance with Aerospatiale Service Bulletin ATR42-32-0018, Revision 2, dated November 15, 1988, and Loral Service Bulletin ATR42-32-40-8. Perform torqueing of the main gear axle nut, in accordance with Loral Service Bulletin ATR42-32-40-7. B. 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, StandardizationBranch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. 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/or modifications required by 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6206, AD 89-10-09) becomes effective on June 9, 1989.