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2011-18-02: We are adopting a new airworthiness directive (AD) for the products listed above with certain part number (P/N) fan rotor spinners installed. This AD requires removing from service certain fan rotor blade retainers, and removing from service the fan rotor spinner support that was installed with those fan rotor blade retainers. This AD was prompted by a fan rotor spinner support found cracked at the attachment lugs. We are issuing this AD to prevent high-cycle fatigue cracking of the fan rotor spinner support attachment lugs, leading to separation of the fan rotor spinner assembly, uncontained failure of the engine, and damage to the airplane.
90-24-02: 90-24-02 BOEING: Amendment 39-6804. Docket No. 90-NM-96-AD. \n\n\tApplicability: Model 757 series airplanes, as listed in Boeing Service Bulletin 757-30- 0015, Revision 1, dated January 25, 1990, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo detect undersized wiring in the flight compartment number 1 window heat system, accomplish the following: \n\n\tA.\tWithin 90 days after the effective date of this AD, inspect for the presence of undersized wires in the number 1 window heat system, in accordance with Boeing Service Bulletin 757-30-0015, Revision 2, dated August 2, 1990. If undersized wires are found, prior to further flight, replace with wires of appropriate size, in accordance with Boeing Service Bulletin 757-30-0015, Revision 2, dated August 2, 1990.\t\n \n\tB.\tWithin 30 days after detecting any undersized wires, submit a report of findings to the Manager, Manufacturing Inspection District Office, FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington 98055-4056. \n\n\tC.\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 (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\n\tD.\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 Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may beexamined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington 98055-4056. \n\n\tThis amendment (39-6804, AD 90-24-02) becomes effective on December 17, 1990.
96-08-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires visual and dye penetrant inspection(s) to detect cracks of the nose rib of the rudder, and stop drilling and blending of minor cracks. This amendment also requires replacement of the nose rib with a new nose rib and reinforcement of the nose rib, if extensive cracking is detected or if an operator elects to terminate the repetitive inspections. This amendment is prompted by the result of an inspection that revealed a cracked nose rib on the front spar of the rudder due to vibration-related stress. The actions specified by this AD are intended to prevent such stress and cracking, which could result in the deformation of the nose rib; this condition may lead to friction and jamming between the fin and the rudder and subsequent reduced controllability of the airplane.
2004-07-16: This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model C-235 series airplanes, that requires modification of the electrical wiring of the rudder trim control unit. This action is necessary to prevent the flight crew from being able to inhibit the aural warning for the landing gear up. If the flight crew of the next flight or possibly of the same flight is unaware that the aural warning had been disabled, they could inadvertently land the airplane with the landing gear not down and locked. This action is intended to address the identified unsafe condition.
2021-15-02: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by reports of deficiencies in the primary flight control computer (PFCC) software and the remote electronics unit (REU) software. This AD requires installation of a software update to correct deficiencies in the PFCC and REU software, as specified in a Transport Canada Civil Aviation (TCCA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
78-01-04: 78-01-04 BOEING: Amendment 39-3112 as amended by Amendment 39-3132. Applies to all Boeing 707-300/400/300B/300C series airplanes upon the accumulation of, or with more than 8,000 landings. \n\tVisually inspect the horizontal stabilizer center section rear spar upper chord for cracks between terminal fittings in accordance with Boeing Service Bulletin 3331 or with the method specified in paragraph B at the time interval specified in paragraph A below. Chords found cracked are to be reworked in accordance with one of the methods noted in paragraph C or replaced with a chord of the same part number prior to further flight. \n\tA.\tInspect within the next 375 landings after the effective date of this AD and thereafter at intervals not to exceed 375 landings. Report all cracks found during the initial inspection to the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, noting airplane identification, hours time in service, crack locations and magnitude. \n\tB.\tInspection may be accomplished by gaining access to the upper rear surface of the center section and examining the exposed surfaces of the upper chord using a bright light and a mirror at the aft upper and lower surfaces of the chord. If indications of a crack are found, eddy-current or penetrant inspection should be used to confirm presence of crack. \n\tC.\tRework in accordance with one of the following: \n\t\t1.\tAn FAA approved repair provided by the Boeing Company. \n\t\t2.\tA method approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tD.\tWith permission of the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, the airplane may be flown in accordance with FAR 21.197 to a base where the inspection or repair can be accomplished. \n\tThe 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). \n\tAll persons affected by this directive who have notalready received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tAmendment 39-3112 became effective January 15, 1978. \n\tThis Amendment 39-3132 becomes effective March 1, 1978.
2021-15-11: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200, -300, -800, and -900 series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reports that certain oxygen supply solenoid valves are a potential source of increased flow resistance within the flightcrew oxygen system. This AD requires a special detailed inspection (flow test) of certain solenoid valves, and replacement if necessary, 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.
76-10-01: 76-10-01 BELL: Amendment 39-2610 as amended by Amendment 39-2927. Applies to Bell Models 205A and 205A-1 helicopters certificated in all categories. Compliance required as indicated. To prevent possible loss of the tail boom as a result of possible fatigue cracks in the tail boom and fuselage attach fittings in the tail boom and fuselage, accomplish the following. (a) For helicopters with less than 500 hours' total time in service after the effective date of this AD, conduct the visual inspections of this AD prior to attaining 550 hours' total time in service and thereafter at intervals not to exceed 50 hours' time in service from the last inspection. (b) For helicopters with 500 or more hours' total time in service on the effective date of this AD, conduct the visual inspections of this AD within the next 50 hours' time in service and thereafter at intervals not to exceed 50 hours' time in service from the last inspection. (c) Inspect the upper tail boom attach fittings for cracks, using a light and mirror, by removing the forward dome light of the baggage compartment. Inspect the fittings in the area of the most forward rivets. Special attention must be given to inspecting the upper left-hand fitting. (d) Inspect the lower tail boom attach fittings for cracks, using a light and mirror, by removing the forward access door on the tail boom. (e) Inspect the four tail boom attach fittings on the fuselage bulkhead, using a light and mirror, for cracks around the tail boom attach bolt and most aft fasteners. Special attention must be given to inspecting the lower left-hand fitting. (f) Inspect, visually, the four tail boom barrel nut bores for cracks, after removing the plug buttons. Determine that not less than one thread or more than two threads of the tail boom attachment bolts protrude through each barrel nut. (g) If cracks are found, replace the affected fitting prior to further flight in accordance with an FAA approved procedure. (h) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, Flight Standards Division, FAA Southwest Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. (i) This AD no longer applies to tailbooms that have been modified, repaired, and sealed as specified in Part II of Bell Helicopter Textron Service Bulletin No. 205-77-4 dated March 11, 1977, or later approved revisions. (j) This AD does not apply to helicopters having S/N 30260 or higher. (k) 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 Textron, 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. (Bell Helicopter message dated April 29, 1976, to all 205A/205A-1 operators pertains to this subject.) Amendment 39-2610 became effective May 18, 1976. This Amendment 39-2927 becomes effective July 1, 1977.
2004-07-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -100B, -100B SUD, -200B, - 200C, -200F, -300, 747SR, and 747SP series airplanes equipped with Pratt & Whitney JT9D-3, -7, -7Q, and -7R4G2 series engines. This amendment requires drilling witness holes through the cowl skin at the cowl latch locations in the left-hand side of the cowl panel assembly of each engine. This action is necessary to prevent improper connection of the latch, which could result in separation of a cowl panel from the airplane. Such separation could cause damage to the airplane, consequent rapid depressurization, and hazards to persons or property on the ground. This action is intended to address the identified unsafe condition.
90-02-22: 90-02-22 DEHAVILLAND: Amendment 39-6471. Applicability: Models DHC-2 Mk. I (including L-20A, YL-20, U-6, and U-6A), and DHC-2 Mk. II (serial numbers 1 through 1056) airplanes certificated in any category. Compliance: Required as indicated in the body of the AD. To ensure the structural integrity of the horizontal tailplane to fuselage front attachment brackets, accomplish the following: (a) Within the next 200 hours time-in-service (TIS), or prior to the accumulation of 1000 hours TIS, whichever occurs later after the effective date of this AD, unless already accomplished per the requirements of AD 54-11-01, and thereafter at intervals not to exceed 1000 hours TIS: (1) Inspect attachment brackets, part number (P/N) C2-FS-543A and P/N C2-FS-544A for cracks and distorted rivets in accordance with paragraph `A' of the "ACCOMPLISHMENT INSTRUCTIONS" in deHavilland Service Bulletin (S/B) No. 2/42, Revision C, dated February 2, 1989. (2) Prior to furtherflight replace any distorted rivets as indicated in the above S/B, paragraph "B", and any cracked brackets as indicated in paragraph "C" of the Service Bulletin. (b) At each interval not exceeding 1000 hours TIS since the last bolt replacement, replace all 1/4 inch diameter forward attachment bolts on the tailplane front attachment brackets with new bolts, P/N AN174-H12A, in accordance with S/B No. 2/42 Rev C. (c) The repetitive inspections or modifications in paragraph (a) of this AD are not required on airplanes modified in accordance with deHavilland Modification No. 2/1338, or Agriculture Modification No. 2/984, as applicable. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where the requirements of this AD may be accomplished. (e) An alternate method of compliance or adjustment of the initial or repetitive compliance times, which provides an equivalent level of safety, may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region, 181 South Franklin Avenue, Valley Stream, New York 11581. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York Aircraft Certification Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Boeing of Canada, Ltd.; deHavilland Division, Garratt Boulevard, Downsview, Ontario, Canada M3K 1Y5; Telephone (416) 633-7310; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This AD supersedes AD 54-11-01. This amendment (39-6471, AD 90-02-22) becomes effective on February 13, 1990.
2021-13-11: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2D15 (Regional Jet Series 705) and CL-600-2D24 (Regional Jet Series 900) airplanes. This AD was prompted by a report that the lower aft outboard supporting structure of galley 2 does not meet certification requirements for all flight and/or emergency landing loads. This AD requires modifying the floor structure between certain fuselage stations. The FAA is issuing this AD to address the unsafe condition on these products.
76-17-04: 76-17-04 ARMSTRONG WHITWORTH: Amendment 39-2701. Applies to all Model AW-650 Series 101 airplanes certificated in all categories. Compliance is required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To detect cracks in the undercut at the bottom of the main undercarriage sliding cylinder and prevent possible failure of the main landing gear, accomplish the following: (a) Inspect the undercut at the bottom of the main undercarriage sliding cylinder with magnetic particle fluid in accordance with Accomplishment Instructions 2A(1) through 2A(6) of Dowty Rotol Service Bulletin No. 32-49D, dated August 15, 1975, or an FAA-approved equivalent. (b) If a crack in the sliding cylinder is detected during the inspection required by paragraph (a) of this AD, replace the main undercarriage sliding cylinder before further flight with a serviceable part of the same part number or an FAA-approved equivalent. This amendment becomes effective on September 9, 1976.
91-05-04: 91-05-04 BOEING: Amendment 39-6907. Docket No. 90-NM-153-AD. \n\n\tApplicability: Model 747-400 series airplanes, listed in Boeing Service Bulletin 747-26- 2138, Revision 1, dated March 1, 1990, and Boeing Service Bulletin 747-26-2141, Revision 1, dated July 12, 1990, certificated in any category. \n\n\tCompliance: Required within the next 12 months after the effective date of this AD, unless previously accomplished. \n\n\tTo preclude cross connection of fire extinguishing wiring during maintenance, accomplish the following: \n\n\tA.\tFor airplanes identified in Boeing Service Bulletin 747-26-2138, Revision 1, dated March 1, 1990: Modify the engine fire extinguishing system in accordance with that service bulletin. \n\n\tB.\tFor airplanes identified in Boeing Service Bulletin 747-26-2141, Revision 1, dated July 12, 1990: Modify the fire control module in accordance with that service bulletin. \n\n\tC.\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 (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\n\tD.\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 Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. \n\n\tThis amendment (39-6907, AD 91-05-04) becomes effective on March 25, 1991.
98-06-05: This amendment adopts a new airworthiness directive (AD) that applies to Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes that are equipped with a Rockwell Collins APS-65 autopilot system that incorporates an APC-65A autopilot computer. This AD requires incorporating airplane flight manual (AFM) and pilot s operating handbook (POH) supplements that include revised autopilot emergency disengagement procedures. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent pilot difficulty in disengaging the autopilot during flight, which could result in the pilot s lack of proper attention to critical flight tasks due to the increased pilot workload with possible consequent loss of airplane controllability.
2021-15-52: The FAA is adopting a new airworthiness directive (AD) for various restricted category helicopters originally manufactured by Bell Textron Inc. This AD was prompted by a fatal accident in which an outboard main rotor hub strap pin (pin) sheared off during flight, resulting in the main rotor blade and the main rotor head detaching from the helicopter. This AD requires removing certain pins from service and prohibits installing those pins on any helicopter. The FAA previously sent an emergency AD to all known U.S. owners and operators of these restricted category helicopters and is now issuing this AD to address the unsafe condition on these products.
2011-15-09: We are adopting a new airworthiness directive (AD) for the products listed above that would [[Page 42034]] supersede an existing AD. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: Two cases of the main landing gear (MLG) alternate extension system (AES) cam mechanism failure were found during line checks. The cam mechanism operates the cable to open the MLG door and releases the MLG uplock in sequence. In the case where it is necessary to deploy the MLG using the AES, the failure of the MLG AES cam mechanism on one side will lead to an unsafe asymmetrical landing configuration. * * * * * The unsafe condition is possible loss of control during landing. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
92-10-12: 92-10-12 BEECH AIRCRAFT CORPORATION: Amendment 39-8246. Docket No. 91-CE-96-AD. Supersedes AD 91-18-11; Amendment 39-8014. Applicability: The following model and serial number airplanes, certificated in any category: Model Serial Numbers 200 and B200 BB-2 and BB-6 through BB-1404 200C and B200C BL-1 through BL-72 and BL-124 through BL-137 200CT and B200CT BN-1 through BN-4 200T and B200T BT-1 through BT-33 A100-1 (U-21J) BB-3, BB-4, and BB-5 A200 (C-12A) BC-1 through BC-75 A200 (C-12C) BD-1 through BD-30 A200C (UC-12B) BJ-1 through BJ-66 A200CT (C-12D) BP-1, BP-22, and BP-24 through BP-51 A200CT (FWC-12D) BP-7 through BP-11 A200CT (RC-12D) GR-1 through GR-13 A200CT (C-12F) BP-52 through BP-71 A200CT (RC-12G) FC-1, FC-2, and FC-3 A200CT (RC-12H) GR-14 through GR-19 B200C (C-12F) BL-73 through BL-112 and BL-118 through BL-123 B200C (UC-12F) BU-1 through BU-10 B200C (RC-12F) BU-11 and BU-12 B200C (UC-12M) FC-1, FC-2, and FC-3 B200C (RC-12M) BV-11 and BV-12 Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished (superseded AD 91-18-11). To prevent separation of the aft cowling doors, which could result in occupant injury if decompression or structural damage occurs, accomplish the following: (a) Inspect and modify the aft engine cowling doors of both engine nacelles in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Beech Mandatory Service Bulletin (SB) No. 2416, Revision I, dated December 1991. (b) If the aft engine cowling doors of both nacelles have been inspected and modified in accordance with the original issue of Beech SB No. 2416, dated July 1991, (as required by superseded AD 91-18-11), then no further action is required by this AD. NOTE 1: The configuration of certain early model airplanes made compliance with the original issue of Beech SB No. 2416 impossible as required by superseded AD 91-18-11. Service (SVR) 025 was approved as an alternative method of compliance for portions of superseded AD 91-18-11 on some of the affected early model airplanes. (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) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office. (e) The inspections and modifications required by this AD shall be done in accordance with Beech Mandatory Service Bulletin No. 2416, Revision I, dated December 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 the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. 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, 1100 L Street, NW; Room 8401, Washington, DC. (f) This amendment (39-8246) supersedes AD 91-18-11, Amendment 39-8014. (g) This amendment (39-8246) becomes effective on June 12, 1992.
2004-07-23: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires replacement of certain assistor springs and bearings with certain new assistor springs and bearings. This action is necessary to prevent possible collapse of a main landing gear upon landing and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
90-24-07: 90-24-07 MCDONNELL DOUGLAS HELICOPTER COMPANY (MDHC): Amendment 39-6784. Docket Number 90-ASW-10. Applicability: All MDHC Model 369D, 369E, and 369F/FF series helicopters certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent possible failure of the main rotor transmission drive assembly, which could result in loss of control of the helicopter, accomplish the following: \n\n\t(a)\tWithin the next 300 hours' time in service after the effective date of the AD or at the next annual inspection or the next time the transmission is removed, whichever occurs first, after the main rotor transmission is removed inspect the MS21250-04036 bolts which retain the debris cover, P/N 369D25174. Remove any bolts with the head inscription shown as unacceptable in Figure 1, and replace with MS21250-04038 bolts, which have a length of 2.887 plus/minus 0.010 inch. \n\n\tNOTE: MDHC Service Information Notice (SIN) DN-166.1, EN-57.1, and SINFN-45.1, dated March 14, 1990, or later revisions pertain to this subject. \n\n\t(b)\tInspect the thread protrusion of all bolts. Remove any bolt which does not protrude through the H14-4 nut for a length equivalent to two full threads (0.071 inch minimum), including the chamfer. Replace removed bolts with MS21250-04038 bolts. Torque the bolts to 50-70 inch pounds. Verify that the bolts protrude through the nut for a length equivalent to two full threads (0.071 inch minimum), including the chamfer. If more than four threads protrude through the nut, add AN960C416L or AN960C416 washers under the nut as required. Remove and reinstall parts in accordance with the manufacturer's instructions. \n\n\t(c)\tApply a white dot to the main transmission data plate to indicate that the transmission has been inspected and reworked in accordance with the manufacturer's instructions, and record compliance with this AD in the rotorcraft log book. \n\n\t(d)\tIn accordance with FAR Sections 21.197 and21.199, flight is permitted to a base where the requirements of this AD may be accomplished. \n\n\t(e)\tAn 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, Los Angeles Aircraft Certification Office, ANM-100L, FAA, Northwest Mountain Region, 3229 East Spring Street, Long Beach, California 90806-2425. \n\n\tThis amendment (39-6784, AD 90-24-07) becomes effective on December 10, 1990. \n\n\n\n\t\t\tFigure 1. Inspection/Definition of Bolt Heads.
2011-14-08: We are adopting a new airworthiness directive (AD) for the products listed above, except for those that are currently affected by similar action through any of five ADs applicable to Boeing products. This AD requires an inspection/records check to determine the manufacturer and part number of the oxygen mask assemblies installed, an inspection to determine the manufacturing date and modification status if certain oxygen mask assemblies are installed, and corrective action for certain oxygen mask assemblies. This AD was prompted by a report that several oxygen mask assemblies with broken in-line flow indicators were found following a mask deployment. We are issuing this AD to prevent the in-line flow indicators of the oxygen mask assembly from fracturing and separating, which could inhibit oxygen flow to the masks. This condition could consequently result in occupants developing hypoxia following a depressurization event.
2021-15-14: The FAA is adopting a new airworthiness directive (AD) for various restricted category helicopters, originally manufactured by Bell Textron Inc. (Bell). This AD was prompted by multiple events involving failure of the tail boom attach structure including the bolts. This AD requires revising the existing Rotorcraft Flight Manual (RFM) for your helicopter to incorporate pre-flight checks; removing paint and sealant, and cleaning; repetitive inspections of structural components that attach the tail boom to the fuselage; and depending on the outcome of the inspections, repairing or replacing components, or re-bonding the structure. The FAA is issuing this AD to address the unsafe condition on these products.
2004-07-13: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6-80C2 series turbofan engines. This AD requires replacing certain high pressure turbine (HPT) stage 1 disks at or before reaching a new reduced life cycle limit. This AD is prompted by an updated low-cycle-fatigue (LCF) analysis of the HPT stage 1 disk. We are issuing this AD to prevent LCF cracking and failure of the HPT stage 1 disk due to exceeding the life limit, which could result in an uncontained engine failure and damage to the airplane.
76-16-02: 76-16-02 AIRBORNE MANUFACTURING COMPANY: Amendment 39-2685. Applies to Models 113A, 200CC, 200CW, 220CC, 220CW, 221CC, 222CW engine driven pumps. Compliance is required within the next 25 hours time in service, or by next annual inspection, whichever occurs first, after the effective date of this AD, unless already accomplished. To prevent loss of vacuum pressure with the accompanying loss of directional or attitude gyro function accomplish the following: Remove from service and replace with another serviceable approved vacuum pump all Airborne engine driven vacuum pumps manufactured prior to 1966 for which the model and serial numbers are listed below: Model Year Serial Numbers 113A 1960 1D1 thru 12D1199 inclusive 1961 1E1 thru 12E2288 inclusive 1962 1F1 thru 12F3411 inclusive 1963 1G1 thru 12G4230 inclusive 1964 1H1 thru 12H1688 inclusive 1965 1J1 thru 12J210 inclusive 200CC, 200CW 1963 5G43 thru 12G903 inclusive 1964 1H1 thru 12H5623 inclusive 1965 1J1 thru 12J9397 inclusive 220CC, 220CW 1964 2H1 thru 12H680 inclusive 1965 1J1 thru 4J393 inclusive 221CC, 222CW 1965 3J1 thru 12J371 inclusive Airborne Manufacturing Company Service Letter No. 16, dated January 29, 1976, also pertains to this subject. This amendment becomes effective August 11, 1976.
2021-15-06: The FAA is adopting a new airworthiness directive (AD) for certain Bell Helicopter Textron Canada Limited (now Bell Textron Canada Limited) Model 206A, 206B, 206L, 206L-1, 206L-3, and 206L-4 helicopters. This AD was prompted by a report that a certain tail rotor disc assembly, sold as an alternate part, does not conform to the approved configuration. This AD requires determining if an affected part is installed (by doing a maintenance records check or inspection), and if an affected part is found, replacement with a non-affected part. The FAA is issuing this AD to address the unsafe condition on these products.
91-06-09: 91-06-09 GLASFLUGEL: Amendment 39-6920. Docket No. 90-CE-37-AD. Applicability: Models H301 Libelle, H301B Libelle, Standard Libelle, Standard Libelle 201, Standard Libelle 201B, Standard Libelle 203, Kestrel 604, and BS-1 Gliders (all serial numbers), certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent failures in the rudder control system, accomplish the following: (a) Within the next 25 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished, replace all DIN specification 055, 6 by 7 inch rudder cables with a diameter of 2.55 mm (.098 in.) having a hemp core, with a 7 by 7, 3/32 inch cable, manufactured in accordance with MIL-W-83420D or MIL-W-1511A, with cable connections constructed in accordance with Actions 2 of Hansjorg Streifeneder Technical Note Nos. 201-26, 301-33, 401- 20, 501-4, all dated March 15, 1987. NOTE: The replacement cables may have been installed pursuant to superseded AD 71- 16-06, Amendment 39-1253, or superseded AD 88-07-05, Amendment 39-5865. (b) Within the next 100 hours TIS after the replacement of the cables required in paragraph (a) of this AD or within the next 100 hours after the effective date of this AD, whichever is applicable, and thereafter at intervals not to exceed 100 hours TIS, visually inspect the rudder cables for wear, fraying, corrosion, twisting or other damage. If damaged cables are found, prior to further flight, replace the damaged cables with cables and connections as specified in paragraph (a) of this AD. (c) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Office, Europe, Africa, and Middle East Office, FAA, c/o American Embassy 15 Rue de la Loi, B-1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. (d) All persons affected by this directive may obtain copies of the documents referred to herein upon request to Hansjorg Streifeneder, Glasflaser Flugzeug Service GmbH, Hofener Weg, D-7431 Grabenstetten, Federal Republic of Germany; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. Airworthiness Directive 91-06-09 supersedes AD 71-16-06, Amendment 39-1253, and AD 88-07-05, Amendment 39-5865. This amendment (39-6920, AD 91-06-09) becomes effective on April 8, 1991.