Results
99-21-33: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.27 Mark 050 series airplanes. This action requires a one-time inspection to detect improper installation of countersunk screws used to attach the access panels to the bottom skin of the center wing; and corrective action, if necessary. 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 detect and correct such improper installation, which could result in fatigue cracking of the bottom skin of the center wing and consequent reduced structural integrity of the airplane.
92-14-10: 92-14-10 DE HAVILLAND, INC.: Amendment 39-8292. Docket No. 92-NM-32-AD. Supersedes AD 83-07-25, Amendment 39-4631. Applicability: Model DHC-7 series airplanes; as listed in de Havilland Service Bulletin 7-27-46, Revision B, dated December 17, 1982, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent inadvertent deployment of the ground spoilers and loss of lift, accomplish the following: (a) Within 15 hours time-in-service or 7 days after April 25, 1983 (the effective date of AD 83-07-25, Amendment 39-4631), whichever occurs first, perform a functional check of the ground spoiler control system, in accordance with the Accomplishment Instructions of de Havilland Alert Service Bulletin 7-27-46, Revision A, dated November 19, 1982; or de Havilland Service Bulletin 7-27-46, Revision B, dated December 17, 1982. (b) If the check required by paragraph (a) of this AD shows incorrect indications, operate theairplane in accordance with the Airplane Flight Manual Minimum Equipment List Supplement No. 4 until the requirements of paragraph (d) of this AD are accomplished. (c) Repeat the functional checks required by paragraph (a) of this AD at intervals not to exceed 15 hours time-in-service, or 7 days, whichever occurs first. (d) Within 6 months after the effective date of this AD, accomplish either paragraph (d)(1) or (d)(2) of this AD, as applicable, in accordance with de Havilland Service Bulletin 7-27- 46, Revision B, dated December 17, 1982: (1) For airplanes having serial numbers 1 through 73, inclusive, that have been retrofitted with Modification No. 7/1732; and airplanes having serial numbers 74 through 83, inclusive, 85, 86, and 89: Incorporate Modification No. 7/2296, in accordance with the service bulletin. (2) For airplanes having serial numbers 1 through 73, inclusive, that have not been retrofitted with Modification No. 7/1732; and airplanes having serial numbers 84, 87, 88, and 90 through 93, inclusive: Incorporate Modification No. 7/2294, in accordance with the service bulletin. (e) Incorporation of Modification No. 7/2296 or 7/2294, as required by paragraph (d)(1) or (d)(2) of this AD, constitutes terminating action for the repetitive functional checks required by paragraph (c) of this AD. (f) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, New York Aircraft Certification Office (ACO), ANE-170, FAA, Engine and Propeller Directorate. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the New York ACO. (g) Special flight permits may be issuedin accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (h) The functional checks and modifications shall be done in accordance with de Havilland Service Bulletin 7-27-46, Revision A, dated November 19, 1982; and de Havilland Service Bulletin 7-27-46, Revision B, dated December 17, 1982, which contains the following list of effective pages: Page Number Revision Level Date 1-4 B December 17, 1982 5-7 A November 19, 1982 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 de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, ValleyStream, New York; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (i) This amendment becomes effective on August 20, 1992.
93-13-08: 93-13-08 AEROSTAR AIRCRAFT CORPORATION: Amendment 39-8621. Docket No. 92-CE-51-AD. Supersedes AD 92-11-08, Amendment 39-8258 which superseded AD 80-02-09, Amendments 39-3665 and 39-3991. Applicability: The following model and serial number airplanes, certificated in any category: Models Serial Numbers PA-60-600 Aerostar 600 60-0001-003 through 60-0933-8161262 PA-60-601 Aerostar 601 61-0001-004 through 61-0880-8162157 PA-60-601P Aerostar 601P 61P-0157-001 through 61P-0860-8163455 PA-60-602P Aerostar 602P 62P-0750-8165001 through 60-8365021 PA-60-700P Aerostar 700P 60-8223001 through 60-8423025 NOTE 1: The manufacturing and ownership rights of the affected model airplanes were previously owned by the Piper Aircraft Corporation, but these rights were recently transferred to the Aerostar Aircraft Corporation. Compliance: Required as indicated, unless already accomplished. To prevent loss of directional control of the airplane during ground operation caused by torque link failure, accomplish the following: (a) Within the next 100 hours time-in-service (TIS) after the effective date of this AD, accomplish either (1) or (2) below: (1) Replace the existing main landing gear torque links with improved design torque links, part number (P/N) 400126-501 and 400126-503 (left main landing gear) and P/N 400126-502 and 400126-504 (right main landing gear), in accordance with the INSTRUCTIONS section of Aerostar Service Bulletin (SB) No. 746C, dated September 15, 1992. NOTE 2: Aerostar SB No. 746C, dated September 15, 1992, references the availability of Main Landing Gear Torque Link Replacement Kit No. 765-155 revision G. This kit contains the improved torque links and all hardware necessary to install these links. This kit may be obtained from the manufacturer at the address specified in paragraph (d) of this AD. (2) Dye penetrant inspect (using FAA-approved methods) the main landing gear torque links for cracks. (i) If cracks are found, prior to further flight, replace the cracked torque links with improved designed torque links part number (P/N) 400126-501 and 400126-503 (left main landing gear) and P/N 400126-502 and 400126-504 (right main landing gear), in accordance with the INSTRUCTIONS section of Aerostar SB No. 746C, dated September 15, 1992. (ii) If no cracks are found, reinspect at intervals not to exceed 100 hours TIS. (iii) The repetitive inspection requirement is no longer required when both the left and right main landing gear torque links are replaced with improved design torque links, part number (P/N) 400126-501 and 400126-503 (left main landing gear) and P/N 400126-502 and 400126-504 (right main landing gear), in accordance with the INSTRUCTIONS section of Aerostar SB No. 746C, dated September 15, 1992. This installation may be accomplished at any time regardless of whether cracks are found during the inspection. NOTE 3: Operators should ensure that proper strut inflation is maintained as improper strut inflation could put extreme impact upon the torque links. In addition, improper use of the hydraulic nose gear steering mechanism at high speeds could also lead to overstressed torque links. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Seattle Aircraft Certification Office, 1601 Lind Avenue, S.W., Renton, Washington 98055-4056. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Seattle Aircraft Certification Office. NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained fromthe Seattle Aircraft Certification Office. (d) The replacement required by this AD shall be done in accordance with Aerostar Service Bulletin No. 746C, dated September 15, 1992. 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 the Aerostar Aircraft Corporation, Customer Service Department, South 3608 Davison Boulevard, Spokane, Washington 99204. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment (39-8621) supersedes AD 92-11-08, Amendment 39-8258 which superseded AD 80-02-09, Amendments 39-3665 and 39-3991. (f) This amendment becomes effective on August 20, 1993.
2022-17-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH (AHD) Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. This AD was prompted by reports of the air conditioning system (ACS) malfunctioning. This AD requires deactivating the ACS and prohibits installing the affected parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2014-05-20: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757 airplanes. This AD was prompted by reports of fractured rudder pedal pushrod connecting bolts in a rudder pedal assembly. This AD requires repetitive replacements of the rudder pedal pushrod connecting bolts and repetitive inspections of the rudder pedal assembly bolt holes in each of the captain and the first officer rudder pedal assemblies, and if necessary, repair or replacement of worn rudder pedal assemblies. We are issuing this AD to prevent fracture of the rudder pedal pushrod connecting bolts during pedal use, which could result in large involuntary inputs to the rudder and nose-wheel steering and an asymmetric application of braking, if pedal brakes are applied, leading to a runway excursion.
99-21-31: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires removing the control quadrant, securing the power lever cam screws with Loctite, and reinstalling the control quadrant. 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 cam screws of the engine power levers from backing out and interfering with the movement of the engine power levers, which could result in limited engine power, and consequent reduced controllability of the airplane.
61-16-04: 61-16-04 BRANTLY: Amdt. 319 Part 507 Federal Register August 4, 1961. Applies to Model B-2 Helicopters as indicated. Compliance required within the next 25 hours' time in service after the effective date of this directive. Failures of the right forward mount lug of the upper transmission case have occurred on three Brantly B-2 helicopters. These failures are fatigue in nature and apparently are associated with an undesirable pre-stress in the mount lug introduced during assembly procedures. Since this condition is likely to exist in other such aircraft, it is necessary to require the following modifications: (a) Applies to all Model B-2 helicopters prior to Serial Number 56 except Serial Numbers 16, 31, 44, 51, 52, and 53. (1) Remove the main rotor and transmission and the three vertical control rods which protrude through the steel plate at the top of the forward firewall. (2) Rework the upper surface of the left and right forward transmission mountpads as follows: Insert a 5/16-inch diameter bolt downward through an AN 960-516 washer into the transmission mount bolt hole. File approximately 0.015 inch from the top surface of the mount pad except where protected by the washer. Remove bolt and washer. (3) Rework the lower surface of the left and right forward transmission mount pads as follows: Enlarge the lower 1/4 inch of the 5/16-inch diameter transmission mount bolt hole by drilling upward with a 21/64-inch drill. Use of a drill stop is strongly recommended to avoid exceeding the 1/4-inch depth of this rework. (4) Apply zinc chromate finish to reworked areas and reinstall transmission, rotor assembly, and control rods in accordance with Brantly Maintenance Manual procedures. (Brantly Service Bulletin No. 9 covers this same subject.) (b) Applies to all Model B-2 helicopters prior to Serial Number 103 except those with 0.375-inch thick mount lugs on P/N B2-104-2 upper transmission case. (1) Remove the NAS 145-22 bolt through the right forward transmission mount lug and the two AN 3-24A bolts through the upper transmission case (P/N B2-104-2) immediately inboard of the mount lug. (2) Install transmission bracket P/N B2-151-19 on top of the right forward transmission case mount lug and attach with new bolts and nuts through mating holes in transmission case previously exposed by (b) (1). These parts are furnished by Brantly Helicopter Corporation as their Modification Kit No. 20. (3) Insure a close fit of faying surfaces between the upper transmission case and bracket P/N B2-151-19 by accomplishing the following steps: Break sharp edges of the upper transmission case ledge to avoid interference with the inner radii of the new bracket; remove material from the upper transmission case ledge or from the lower surface of the bracket in contact with the case lug, as necessary. Failure to insure proper fit of this bracket will introduce undesirable pre-stress into thetransmission mount lug. (Brantly Service Bulletin No. 14 covers this same subject.) This directive effective August 14, 1961.
92-11-04: 92-11-04 BRITISH AEROSPACE: Amendment 39-8254. Docket No. 91-NM-166-AD. Applicability: British Aerospace Model ATP airplanes; as listed in British Aerospace Service Bulletin ATP-24-34, dated April 25, 1991, and British Aerospace Service Bulletin ATP-33-8, Revision 2, dated April 11, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent inaccurate navigation when using the standby compass, accomplish the following: (a) Within 14 days after the effective date of this AD, fabricate and install a temporary placard near the standby magnetic compass, worded as follows: "WARNING: OPERATION OF CABIN ROOF AND SIDEWALL LIGHTING, PITOT HEAT, AND STALL WARNING SYSTEMS MAY INDUCE EXCESSIVE ERROR IN THE MAGNETIC COMPASS READINGS." (b) Within 8 months after the effective date of this AD, accomplish the following: (1) Modify the earthing arrangements to the pitot static and stall warning systems (Modification 10194A) and to the overhead stowage units (Modification 10194B), as applicable, in accordance with British Aerospace Service Bulletin ATP 24-34, dated April 25, 1991. (2) Modify the roof and sidewall light wiring (Modification 35113A) in accordance with British Aerospace Service Bulletin ATP-33-8, Revision 2, dated April 11, 1991. (3) Accomplish a compass swing of the standby compass in accordance with British Aerospace Service Bulletin ATP-24-34, dated April 25, 1991. (4) Remove the temporary placard installed in accordance with paragraph (a) of this AD. (c) An alternative method 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, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113.(d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The modifications shall be done in accordance with British Aerospace Service Bulletin ATP-24-34, dated April 25, 1991; and British Aerospace Service Bulletin ATP-33-8, Revision 2, dated April 11, 1991. These service bulletins contain the following list of effective pages: Service Bulletin No. Page Number Revision Level Date ATP-24-34 1-3, 5-21, Original April 25, 1991 23, 25, 27, 29, 31, 33, 35, 37, 39, 41, 43, 45, 47, 49, 51, 53-54 4, 22, 24, (These pages are not used) 26, 28, 30, 32, 34, 36, 38, 40, 42, 44, 46, 48, 50, 52 ATP-33-8 1 2 April 11, 1991 Revision 2 2-5, 19-20, 1 September 5, 1990 31, 33 6-18, 21, 23, Original April 29, 1990 25, 27,29, 35, 37, 39-40 22, 24, 26, (These pages are not used) 28, 30, 32, 34, 36, 38 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (f) This amendment becomes effective on July 23, 1992.
75-17-26: 75-17-26 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 2331. Applies to Model SA-341G "Gazelle" helicopters, certificated in all categories, Serial Numbers 1031 and lower, incorporating tail rotor servo jack P/N 67.370.004.00 or P/N 67.370.006.00. Compliance is required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished in accordance with Gazelle Service Bulletin No. 67.01, dated March 9, 1973. To prevent over-torquing of engine by application of tail rotor control, replace tail rotor servo jack P/N 67.370.004.00 or P/N 67.370.006.00, with tail rotor servo jack P/N 67.370.008.00. This amendment becomes effective on August 20, 1975.
99-20-13: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-20-13, which was sent previously to all known U.S. owners and operators of Eurocopter Canada Ltd. Model BO 105 LS A-3 helicopters by individual letters. This AD requires, before further flight, creating a component log card or equivalent record and determining the age and number of flights on each tension-torsion (TT) strap. The AD also requires inspecting and removing, as necessary, certain unairworthy TT straps. This amendment is prompted by an accident in which a main rotor blade (blade) separated from a Eurocopter Deutschland GMBH Model MBB-BK 117 helicopter because of fatigue failure of the TT strap. The Model MBB-BK 117 and the Model BO 105 LS A-3 helicopters use the same part-numbered TT strap. The actions specified by this AD are intended to prevent failure of a TT strap, loss of a blade, and subsequent loss of control of the helicopter.
99-21-24: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA-365C, C1, C2, N, and N1; AS-365N2; and SA-366G1 helicopters, that requires inspecting the tightening torque of the main rotor hub blade attach beam spherical thrust bearing bolts (bolts). This AD also requires either applying the specified torque or, if necessary, conducting a dye penetrant inspection for cracks in the metal components. Replacing the spherical thrust bearing (bearing) with an airworthy bearing is also required if a crack is found. This amendment is prompted by reports of cracks in the metal components of the bearing attachment joint. The actions specified by this AD are intended to prevent loosening of bearing bolts in flight, which may cause cracks in the metal components, failure of the bearing, and subsequent loss of control of the helicopter.
71-21-02: 71-21-02 BELL: Amendment 39-1304 as amended by Amendment 39-2048. Applies to Bell Models 205A and 205A-1 helicopters certificated in all categories equipped with tail boom assembly, part number 205-032-802-1, -3, -5, -9, or -11. Compliance required as indicated. To detect a possible fatigue crack in the vertical fin forward spar in the area of the first rivet hole above the tail fin and tail boom intersection at fuselage station 434 or fin station 70.3, accomplish the following: (a) Inspect tail booms having 600 or more hours total time in service on the effective date of this AD within 25 hours time in service therefrom, in accordance with the procedures listed in paragraph (c) unless already accomplished within the last 75 hours. (b) Inspect tail booms having less than 600 hours total time in service on the effective date of this AD before reaching 625 hours total time in service in accordance with the procedures listed in paragraph (c) unless accomplished withinthe last 75 hours. (c) Accomplish repetitive inspections in accordance with the procedures listed below at intervals of not more than 100 hours time in service from the last inspection: (1) Remove the 42 degrees gear box cover from the tail boom and open the tail rotor drive shaft cover on the vertical fin. (2) Remove and do not reinstall the one rivet in the spar cap angle at fin station 70.3 and remove the paint finish and clean the area around the rivet hole, inboard and outboard sides of spar, including radius of cap angle on the left side of the fin forward spar from fin station 69.5 to 71, using cloth and methyl ethyl ketone or equivalent. (3) Inspect the rivet hole and the clear area of the fin spar for cracks using a visual or a dye penetrant or equivalent inspection method. (4) If no cracks are found, protect the clear area of the spar and rivet hole using a clear lacquer or light film of clear grease or equivalent transparent protection. (5)If cracks are found, remove the tail boom and replace with an uncracked tail boom in accordance with the procedures in The Bell Model 205A or 205A-1 Maintenance and Overhaul Instructions before further flight. (d) Before the first flight of each day after the inspection in paragraph (c) is accomplished, conduct a check as follows: (1) Remove the 42 degrees gear box cover from the tail boom and open the tail rotor drive shaft cover on the vertical fin. (2) Visually check the rivet hole area and the clear area of the fin forward spar for cracks. (3) If cracks are found, remove the tail boom and replace with an uncracked tail boom in accordance with the procedure of The Bell Model 205A or 205A-1 Maintenance and Overhaul Instructions before further flight. (4) The above check may be performed by the pilot. NOTE: For the requirements regarding the listing of compliance and method of compliance with this airworthiness directive in the aircraft permanent maintenance record, see FAR 91.173. (e) Operators not having kept time in service records on individual tail booms should use helicopter hours time in service for the purpose of this airworthiness directive. (f) The inspections noted by this AD are no longer required when the tail fin forward spar is modified in accordance with Part 2, Bell Helicopter Company Service Bulletin No. 205A- 6 dated May 11, 1971 or Revision A dated June 14, 1971, or later approved revision or in accordance with an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, FAA. (g) This airworthiness directive is not applicable for tail boom assemblies P/N 205- 032-802-9, serial numbers BBBI-50026 and subsequent, P/N 205-032-802-11 serial numbers BBBI-50003 and subsequent; and fuselage assemblies P/N 205-200-010-178, serial numbers BBDN-50051 and subsequent, and serial number BBDN-00101 and subsequent serial numbers. The manufacturer's specifications and procedures identified and described in this directive are 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 these documents from the manufacturer may obtain copies upon request to the Service Manager, Bell Helicopter Company, P. O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. Amendment 39-1304 became effective October 30, 1971. This amendment 39-2048 becomes effective December 23, 1974.
99-21-23: This amendment adopts a new airworthiness directive (AD) that applies to all Avions Mudry et Cie (Avions Mudry) Model CAP 10B airplanes. This AD requires restricting the entry speed for performing flick maneuvers to 97 knots. Inserting a copy of this AD into the Limitations Section of the CAP 10B flight manual is also required, along with fabricating and installing a placard (in the cockpit of the airplane within the pilot s clear view) that indicates this limitation. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to provide the flight information necessary to the pilot so that excessive speed is not used during aerobatic maneuvers, which could result in the wing separating from the airplane.
2021-02-11: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH Model MBB-BK117 A-1, MBB-BK117 A-3, MBB-BK117 A-4, MBB-BK117 B-1, MBB-BK117 B-2, MBB-BK117 C-1, and MBB- BK117 C-2 helicopters. This AD requires inspecting the tail gearbox (TGB) bellcrank attachment arm (arm) for a crack. This AD was prompted by a report of a cracked TGB arm. The actions of this AD are intended to address an unsafe condition on these products.
2014-05-21: We are superseding airworthiness directive (AD) 2008-11-04 for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2008-11-04 required repetitive inspections for cracking in and around the upper and lower hinge cutouts of the forward entry and forward galley service doorways, and corrective actions if necessary. This new AD reduces the inspection threshold for cracking in and around the galley service doorway hinge cutouts, adds inspections of certain repaired structure at the forward entry and galley service doorway upper and lower hinge cutouts, expands the inspection area at the forward entry and galley service doorway upper and lower hinge cutouts, and removes certain airplanes from the applicability. This AD was prompted by multiple reports of cracks in the skin and/or bear strap at the forward galley service doorway hinge cutouts, and multiple reports of cracking under the repairs installed at the hinge cutouts. We are issuing this AD to detect and correct such cracking, which could result in rapid decompression of the airplane.
99-21-22: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-30, SD3-60, SD3 SHERPA, and SD3-60 SHERPA series airplanes, that requires a visual inspection to detect corrosion of the shear decks and ribs of the left and right stub wings; follow-on corrective actions, if necessary; and drilling of new drain holes in the lower shear decks. 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 corrosion of the stub wing shear decks and ribs, which could result in cracking or failure of the stub wing structure.
99-21-14: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA-360C, SA-365C, C1, C2, SA-365N, N1, AS-365N2, and SA-366G1 helicopters, that requires inspecting and, if necessary, replacing certain circuit breakers. This amendment is prompted by the manufacturer discovering the loss of electrical continuity between the terminals of a circuit breaker. The actions specified by this AD are intended to prevent loss of electrical power, loss of instrumentation, and subsequent loss of control of the helicopter.
2022-15-07: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400 series airplanes. This AD was prompted by a report that after a certain circuit breaker tripped, power to the two pitot-static (P/S) probe heaters on the right-hand side was lost, and the flightcrew discovered conflicting procedures in the flightcrew operations manual/quick reference handbook (FCOM/QRH). This AD requires revising the existing airplane flight manual (AFM) to incorporate procedures to be applied during P/S probe heater failure conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2014-05-22: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 717-200 airplanes. This AD was prompted by multiple reports of cracking in the overwing frames. This AD requires repetitive inspections for cracking in the overwing frames, and corrective actions if necessary. We are issuing this AD to detect and correct such cracking, which could result in a severed frame and might increase the loading of adjacent frames, resulting in damage to the adjacent structure and consequent loss of structural integrity of the airplane.
2010-16-08: This amendment adopts a new airworthiness directive (AD) for the Schweizer Model 269D helicopters. This action requires installing a Scroll Housing Blade Containment Shielding Kit on each helicopter. This amendment is prompted by 21 reports of the blades of the oil cooler impeller separating, one of which punctured the engine and transmission oil cooler resulting in loss of engine oil pressure. The actions specified in this AD are intended to protect the oil cooler from uncontained oil cooler impeller blades that could damage the oil cooler and result in loss of engine and transmission oil pressure, and subsequent loss of control of the helicopter.
89-23-18: 89-23-18 SAAB-SCANIA: Amendment 39-6390. Docket No. 89-NM-65-AD. Applicability: Model SF-340A series airplanes, Serial Numbers -004 through -159, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To ensure the operation of the emergency lighting system when required during an emergency situation, accomplish the following: A. Within 60 days after the effective date of this AD, modify the emergency lighting activation circuit in accordance with SAAB Service Bulletin, SF340-33-028, Revision 1, dated January 26, 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 documents from the manufacturer may obtain copies upon request to SAAB-Scania Aircraft Division, Product Support, S-581 88 Linkoping, Sweden. These documents 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 (39-6390, AD 89-23-18) becomes effective on December 12, 1989.
2014-05-23: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD-100-1A10 (Challenger 300) airplanes. This AD was prompted by multiple reports of erratic electrical status indications on the push button annunciators and the engine instrument and crew alerting system. Certain of those reported incidents resulted in the airplane experiencing a momentary loss of electrical power and loss of flight displays. This AD requires modification of the direct current power centers. We are issuing this AD to prevent loss of electrical power, which could result in the loss of flight displays and reduced controllability of the airplane.
2014-05-06: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model EC135 and MBB-BK 117 C-2 helicopters. This AD requires inspecting the flight-control bearings repetitively, replacing any loose bearing with an airworthy flight- control bearing, and installing bushings and washers. This AD was prompted by the discovery during a routine inspection of loose flight control bearings because of incorrect installation. The actions of this AD are intended to prevent the affected control lever from shifting, contacting the helicopter structure, and reducing control of the helicopter.
2006-04-09: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), CL-600-2D15 (Regional Jet Series 705), and CL-600-2D24 (Regional Jet Series 900) airplanes. This AD requires replacing the Camloc fasteners on the sidewall of the center pedestal. This AD results from reports of the Camloc fasteners on the sidewall of the center pedestal disengaging and interfering with an inboard rudder pedal. We are issuing this AD to prevent these fasteners from disengaging and interfering with an inboard rudder pedal, which could reduce directional controllability of the airplane.
92-20-05: 92-20-05 FOKKER: Amendment 39-8379. Docket No. 92-NM-68-AD. Applicability: Model F28 Mark 0100 series airplanes; serial numbers 11244 through 11256, inclusive; 11259; 11260; and 11268 through 11278, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the wings, accomplish the following: (a) Prior to the accumulation of 18,000 landings or within 60 days after the effective date of this AD, whichever occurs later, replace the currently installed aluminum alloy rivets at the rib-to- auxiliary-spar attachment at wing station 10110 with nickel copper alloy rivets and Hilok bolts, in accordance with Fokker Service Bulletin SBF100-57-017, dated September 12, 1991. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The replacement shall be done in accordance with Fokker Service Bulletin SBF100-57- 017, dated September 12, 1991. 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on November 17, 1992.