Results
95-12-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires installation of reinforcement plates at certain fuselage stations. This amendment is prompted by a report indicating that cracks were found in the frame strips at certain fuselage stations on a Model F28 Mark 0100 series airplane test article due to fatigue-related stress. The actions specified by this AD are intended to prevent such fatigue-related cracking, which could result in reduced structural integrity of the fuselage pressure vessel.
76-22-11: 76-22-11 WEATHERLY AVIATION COMPANY: Amendment 39-2765. Applies to Model 201B and 201C airplanes prior to Serial Number 1011 certificated in all categories. Compliance required as indicated. To prevent an inadvertent activation of the parking brakes and loss of airplane control during ground operation due to a failure of the pilot to move the parking brake levers to the fully off position, accomplish the following: (a) Within the next 200 hours time in service after the effective date of this AD, unless previously accomplished, replace the parking brake handles with a parking brake cable installation in accordance with Weatherly Aviation Company, Inc., Service Note No. 5, dated October 21, 1976, or later FAA-approved revision. (b) The Chief, Aircraft Engineering Division, FAA Western Region, may approve equivalent modifications. (c) Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate airplanes to a base for the accomplishment of this AD. This amendment becomes effective November 15, 1976.
94-01-14: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Canadair Model CL-600-2B19 (Regional Jet) series airplanes. This action revises the FAA-approved Airplane Flight Manual (AFM) to require that both integrated drive generators (IDG) be operational for dispatch. This AD also requires repetitive inspections of the IDG oil level, and replenishing with oil, if necessary; and, for certain airplanes, an inspection of the oil level, and replacement of the IDG with a serviceable unit. This AD also specifies an optional terminating action for the repetitive inspections and AFM revision. This amendment is prompted by reports of failures of the IDG constant speed drive (CSD) on Canadair Model CL-600-2B19 series airplanes. The actions specified in this AD are intended to prevent loss of engine oil and subsequent engine shutdown during flight.
95-02-06: This amendment supersedes Airworthiness Directive (AD) 91-08-01, which currently requires the following on Jetstream Aircraft Limited (JAL) Jetstream Model 3101 airplanes: revising the maximum speed for flaps at 50 degrees from 153/149 knots indicated airspeed (KIAS) to 130 KIAS; and limiting the maximum flap extension to 20 degrees anytime ice is present on the airplane. This action requires incorporating a flap system modification as terminating action for the requirements of AD 91-08-01. The actions specified by this AD are intended to prevent sudden pitch down of the airplane during icing conditions, which could lead to loss of control of the airplane.
94-22-02: 94-22-02 CONSOLIDATED AERONAUTICS: Amendment 39-9051; Docket No. 94-CE-21-AD. Applicability: Lake Model 250 airplanes (all serial numbers), certificated in any category, that are equipped with a Bendix/King KFC 150 automatic flight control system. Compliance: Required within the next 10 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent automatic flight control system malfunctions caused by failure of the elevator autotrim to disengage, which could result in flight path deviations, accomplish the following: (a) Pull the two circuit breakers, one marked "A/P" and the other marked "TRIM", and attach a collar or tie-wrap to them to prevent resetting. (b) Fabricate a placard with the words: "Use manual trim only.", and install this placard on the instrument panel within the pilot's clear view. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 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 initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (e) Information related to this AD may be examined at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. (f) This amendment becomes effective on November 4, 1994.
93-18-05: 93-18-05 MCDONNELL DOUGLAS HELICOPTER COMPANY and HUGHES HELICOPTERS, INC.: Amendment 39-8690. Docket Number 92-ASW-33. Applicability: Model 369D, 369E (Serial No. 0001E thru 0508E), 369F (Serial No. 0003 thru 0091), 369FF (Serial No. 0003 thru 0091), and 369H series helicopters, equipped with fuel vent line emergency shutoff valve assemblies, part number (P/N) 369H8108, 369H8108-501 or 369H8108-503, certificated in any category. Compliance: Helicopters with less than 2,400 hours' time-in-service on the effective date of this AD shall be inspected on or before attaining 2,500 hours' time-in-service, and thereafter, at an interval not to exceed 100 hours' time-in-service from the last inspection until an improved fuel vent line emergency shutoff valve assembly (assembly) is installed in accordance with paragraph (d) of this AD. Helicopters with 2,400 hours' or more time-in-service on the effective date of this AD shall be inspected in accordance with this AD within thenext 100 hours' time-in-service, and thereafter, at an interval not to exceed 100 hours' time-in-service from the last inspection until an improved assembly is installed in accordance with paragraph (d) of this AD. To prevent erroneously high inflight fuel quantity indications due to a blocked fuel vent line in the assembly, accomplish the following: (a) Remove the assembly from the helicopter as required by the appropriate Model 369 maintenance manual. (b) Inspect the fuel vent line emergency shutoff valve (valve) in accordance with Part I, Fuel Vent Line Emergency Shutoff Valve Inspection, of McDonnell Douglas Helicopter Company Service Information Notice HN-234, DN-181, EN-73, FN-60, dated January 17, 1992. (c) If the inspections conducted in accordance with the requirements of paragraph (b) uncover an incorrectly closed or obstructed valve, before further flight install an airworthy assembly in accordance with the appropriate Model 369 maintenance manual.(d) Install assembly, P/N 369H8108-505 or higher dash number, as follows, unless already accomplished: (1) For helicopters with 2,400 hours' or more time-in-service on the effective date of this AD, install the assembly on or before attaining the next 600 hours' time-in-service. (2) For helicopters with less than 2,400 hours' time-in-service on the effective date of this AD, install the assembly before attaining 3,000 hours' time-in-service. (e) 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, Propulsion Branch, Los Angeles Aircraft Certification Office, 3229 E. Spring Street, Long Beach, California 90806-2425. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Propulsion Branch, Los Angeles Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Manager, Propulsion Branch, Los Angeles Aircraft Certification Office. (f) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished. (g) The inspection shall be done in accordance with MDHC Service Information Notice HN-234, DN-181, EN-73, FN-60, dated January 17, 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 McDonnell Douglas Helicopter Company, 5000 East McDowell Road, Mesa, Arizona 85205-9797, Attention: Field Service Department. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 4400 Blue Mound Road, bldg 3B, room 158, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective December 21, 1993.
92-19-01: 92-19-01 AEROSPATIALE: Amendment 39-8358. Docket No. 92-NM-126-AD. Supersedes AD 89-09-05 R1, Amendment 39-6393. Applicability: All Model ATR42 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To minimize the potential hazards associated with operating in icing conditions including freezing rain, accomplish the following: (a) Within 10 hours time-in-service after May 3, 1989 (the effective date of AD 89-09-05, Amendment 39-6197), incorporate the following statement into the Limitations Section of the FAA-approved Airplane Flight Manual (AFM). This may be accomplished by including a copy of this AD in the AFM. "When operating in icing conditions, as defined in the AFM, or when freezing rain is forecast or reported, use of the autopilot is prohibited. WARNING: Prolonged operation in freezing rain should be avoided. Ice accretion due to freezing rain may result in asymmetric wing lift andassociated increased aileron forces necessary to maintain coordinated flight. Whenever the aircraft exhibits buffet onset, uncommanded roll, or unusual control wheel forces, immediately reduce angle-of-attack and avoid excessive maneuvering." (b) Within 60 days after December 15, 1989 (the effective date of AD 89-09-05 R1, Amendment 39-6393), install vortex generators, in accordance with Aerospatiale Service Bulletin ATR42-57-0018, Revision 1, dated June 28, 1989. This action constitutes terminating action for the AFM limitation required by paragraph (a) of this AD, regarding use of the autopilot when operating in icing conditions, and the limitation may be removed from the AFM. (c) Operations may continue with a configuration consisting of one vortex generator missing per wing, provided that the two missing vortex generators form a symmetrical pair in relation to the airplane centerline. 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. (e) 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. (f) The installation shall be done in accordance with Aerospatiale Service Bulletin ATR42-57-0018, Revision 1, dated June 28, 1989, which contains the following list of effective pages: Page Number Revision Level Date 1, 3, 5-13 1 June 28, 1989 2, 4 Original May 3, 1989 This incorporation by reference wasapproved 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. 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. (g) This amendment becomes effective on September 18, 1992.
94-12-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 series airplanes, that requires replacement of certain bolts that are currently installed in various flight critical components of the airplane. This amendment is prompted by reports of incidents involving corrosion and fatigue cracking in transport category airplanes that are approaching or have exceeded their economic design goal; these incidents have jeopardized the airworthiness of the affected airplanes. The actions specified by this AD are intended to prevent reduced structural integrity of various flight critical components of the airplane.
77-05-03: 77-05-03 HUGHES HELICOPTERS: Amendment 39-2845. Applies to Hughes Model 369D helicopters Serial No. 0003 through 0049, certificated in all categories, that were manufactured without protective boots on the tail rotor output shaft. Compliance required as indicated unless already accomplished. To prevent binding of the tail rotor control system and damage to the tail rotor output shaft, accomplish the following: (a) Within 30 calender days from the effective date of this AD, disassemble the tail rotor control assembly, install Hughes P/N 369D21806 rotating boot and Hughes P/N 369D21807 stationary boot, and reassemble in accordance with Hughes Handbook of Maintenance Instruction. (b) Equivalent replacement parts may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. (c) Special flight permits may be issued in accordance with 21.197 and 21.199 to operate helicopters to a base for the accomplishment of the installation requiredby this AD. This amendment becomes effective March 7, 1977.
77-15-03: 77-15-03 CANADAIR: Amendment 39-2976. Applies to Canadair CL-215-1A10 airplanes, Serial Number 1001 thru 1040, and 1046, certificated in all categories. Compliance is required prior to U.S. Airworthiness Certification. To ensure correct engagement of shoulders of input quadrant P/N 215-90252 in left and right outboard bearing assemblies P/N 215-90255 or 215-90291, accomplish the following: On both ends of the elevator torque tube, measure the dimensions between the face of the shoulder of the input quadrant and the face of the bearing inner race. The two dimensions are to be added and their total compared to the following: (a) Aircraft 1001 thru 1015 and 1021 thru 1030, using bearing P/N 215-90255: If greater than 0.200 inches, alter assembly in accordance with the Modification and Procedure paragraph of Canadair Service Bulletin CL-215-201, dated 1/13/76, or approved equivalent alteration. (b) Aircraft 1016 thru 1020 and 1031 thru 1040, and 1046, using bearing P/N 215- 90291: If greater than 0.100 inches, alter assembly in accordance with the Modification and Procedure paragraph of Canadair Service Bulletin CL-215-201, dated 1/13/76, or approved equivalent alteration. Equivalent alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Canadair Service Information Circular 115-CL-215 pertains to this subject. This amendment is effective July 27, 1977.
78-09-02: 78-09-02 BELL: Amendment 39-3203. Applies to Bell Model 212 helicopters, certificated in all categories, that are equipped with emergency float kits 212-706-021 or 212-706-042 and that are operated under conditions that require ditching capability or aircraft floatation devices. Compliance required as indicated. To permit opening of the passenger emergency exits in the event of a ditching and deployment of the emergency float bags, accomplish the following, unless already accomplished in accordance with data previously approved by the FAA (including STC No. SH2746SW issued April 4, 1978): Prior to further flight, after the effective date of this AD, modify the forward and aft passenger emergency exit on each side of the helicopter in accordance with information and/or data approved by the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region, except that the helicopter may be flown in accordance with FAR 21.197 to a base where the work may be performed.This amendment becomes effective May 9, 1978.
77-16-02: 77-16-02 DOWTY ROTOL: Amendment 39-2995. Applies to Dowty Rotol propeller types R245/4-40-4.5/13, R259/4-40-4.5/17 installed on but not necessarily limited to Convair 600 series airplanes and R209/4-40-4.5/2 installed on but not necessarily limited to Nihon YS-11 and 11A airplanes, except those propellers incorporating modification VP 2869 contained in Dowty Rotol Service Bulletin 61-875, Rev. 1 dated October 20, 1976. Compliance is required as indicated. To prevent pitch lock piston cracking and subsequent inability to feather the propeller, accomplish the following: (a) For propeller pitch lock pistons with 19,000 or more flights on the effective date of this AD, before further flight, comply with paragraph (d) of this AD. (b) For propeller pitch lock pistons with less than 19,000 flights on the effective date of this AD, comply with paragraph (c) of this AD. (c) For propeller pitch lock pistons, P/N RA 70089: (1) Prior to the accumulation of 15,000 flights or within the next 100 flights, whichever occurs later, unless already accomplished within the last 900 flights, unless otherwise required by paragraph (e) of this AD, and thereafter at intervals not to exceed 1,000 flights from the last inspection until reaching 19,000 flights, inspect the pitch lock piston for cracks around the outside diameter at the location of the 0.025 inch radius in accordance with the procedures and instructions in Dowty Rotol Service Bulletin 61-873, Revision 1, dated October 20, 1976, or an FAA-approved equivalent. (2) If a crack is found during an inspection required by paragraph (c)(1), before further flight, comply with paragraph (d) of this AD. (d) Replace the pitch lock piston with either - (1) A new zero time part, P/N RA 70089, in accordance with Dowty Rotol Service Bulletin 61-873, Revision 1, dated October 20, 1976, or an FAA-approved equivalent, and thereafter comply with paragraphs (c), (d), and (e) of this AD; or (2) A new redesigned pitch lock piston and cylinder cover bush in accordance with Dowty Rotol Service Bulletin 61-875, dated October 20, 1976, or an FAA- approved equivalent. (e) Prior to the accumulation of 19,000 flights on propeller pitch lock piston P/N RA 70089, comply with paragraph (d) of this AD. (f) For the purposes of this AD, a flight is defined as a single takeoff and landing. (g) This AD requires no further action after compliance with paragraph (d)(2) of this AD. This amendment becomes effective August 31, 1977.
76-18-09: 76-18-09 MESSERSCHMITT-BOLKOW-BLOHM GmbH (MBB): Amendment 39- 2718. Applies to Model BO-105A and BO-105C helicopters, certificated in all categories, incorporating Teledyne Hydra-Power hydraulic actuators, P/N 105-45021, with the following serial numbers: 1012, 1014, 1015, 1016, 1017, 1018, 1019, 1021, 1023, 1027, 1028, 1029, 1030, 1032, 1034, 1035, 1037, 1038, 1040, 1041, 1043, 1044, 1045, 1046, 1049, 1056, 1057, 1062, 1064, 1065, 1066, 1069, 1071, 1075, 1091, 1093, 1101, 1104, 1109, 1113, 1119, 1121, 1123, 1126, 1127, 1156, 1160, and 1161 which have piston rods, P/N D133-750.08E, with S/N's 101 through 440. Compliance is required as indicated, unless already accomplished. To prevent possible failure of the main rotor hydraulic actuator and loss of control of the helicopter, accomplish the following: (a) Before the accumulation of 600 hours total helicopter time in service or within the next 25 hours time in service after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 600 hours time in service from the last inspection until modified in accordance with paragraph (e) of this AD, comply with paragraph (b) of this AD. (b) Inspect the piston rods, P/N D133-750.08E, in the hydraulic actuators, P/N 105- 45021, for cracks, using a dye penetrant method in accordance with Paragraph 2.B. of the "Accomplishment General" section of MBB Service Bulletin No. 40-19, dated June 2, 1975, or an FAA-approved equivalent. (c) If a crack is found in a piston rod during an inspection specified in paragraph (b) of this AD, before further flight, replace the cracked piston rod with a serviceable part of same part number and continue to inspect in accordance with paragraph (b) of this AD at intervals not to exceed 600 hours time in service until the modification specified in paragraph (e) of this AD is accomplished. (d) Comply with paragraph (e) of this AD as follows: (1) For helicopters with less than 1800 hours totaltime in service on the effective date of this AD and for which it has been less than 4 years since the original issuance of its airworthiness certificate, comply with paragraph (e) of this AD in accordance with paragraph (i) or (ii), whichever occurs later. (i) Before the accumulation of 1800 hours total time in service or within four years of the date of original issuance of its airworthiness certificate, whichever occurs sooner. (ii) Within the next 25 hours time in service after the effective date of this AD. (2) For helicopters with 1800 hours or more total time in service on the effective date of this AD or helicopters for which the effective date of this AD is four years or more after the date of original issuance of its airworthiness certificate, comply with paragraph (e) of this AD within the next 25 hours time in service after the effective date of this AD. (e) Disassemble the Teledyne Hydra-Power actuator, P/N 105-45021, and replace the piston rods, P/N D133-750.08E, which have S/N's 101 through 440 with serviceable parts of the same part number which have serial numbers other than 101 through 440. This amendment becomes effective on October 1, 1976.
46-12-02: 46-12-02 DOUGLAS: (Was Service Note 12 of AD-669-3.) Applies to DC3A Aircraft. \n\n\tInspection required immediately and every 100 hours thereafter on all aircraft which have beryllium copper engine mount to firewall attach fittings installed. \n\n\tInspect the engine mount to firewall attach fittings, P/N 5-81486-4 (with 4-power magnifying glass min.) in the fillet of the spot face for cracks or flaws in the material. If evidence of defects are found, replace with P/N 1042764. If cracks are not found, inspect every 100 hours until next engine change. P/N 5-81486-4 should be replaced with P/N 1042764 at engine change. \n\n\t(Douglas Service Bulletin No. 238 covers this same subject.)
94-08-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Jetstream Model 4101 airplanes. This action requires installation of fusible trunnion pins in the shock struts and drag braces of the main landing gear (MLG). This amendment is prompted by a report of incorrectly manufactured trunnion pins that may cause the MLG to compromise the structural integrity of the wing fuel tanks. The actions specified in this AD are intended to prevent damage to the wing fuel tanks and the resultant fuel spillage and fire hazard when the maximum intended design load limits are exceeded during landing.
94-24-09 R1: This amendment revises an existing airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that currently requires repetitive inspections to detect damage to the overwing fairings, and replacement or repair of structurally damaged fairings. That AD was prompted by a report indicating that an overwing fairing detached from an airplane. The actions specified by that AD are intended to prevent reduced controllability of the airplane due to loss of an overwing fairing. This amendment adds an optional terminating action for the currently required inspections, and limits the applicability of the rule.
95-03-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires an inspection to detect cracks in the cleats at certain rib stations of the wing, and replacement of the cracked cleats with new cleats. This amendment is prompted by a report that, during manufacture of the wings of these airplanes, cracks were discovered in the cleats at the left- and right-hand rib station 8200 of the wing due to improper installation of certain bolts. The actions specified by this AD are intended to prevent cracking of the cleats, which could result in reduced structural integrity of the wing.
92-06-04: 92-06-04 BRITISH AEROSPACE: Amendment 39-8184. Docket No. 91-NM-206-AD. Applicability: Model BAe 125-800A series airplanes, Post-Modification 253191A and Pre-Modification 253247A, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent internal arcing in the dimmer units and smoke emission into the cockpit, accomplish the following: (a) Within 60 days after the effective date of this AD, modify the instrument integral lighting system by installing dimmer units having Page Modification AR1477 incorporated, and perform functional tests of the pilot's and co-pilot's instrument integral lighting dimmer system, in accordance with British Aerospace Service Bulletin 33-44-7670A, Revision 1, dated April 4, 1991. (b) 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. (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 modification shall be done in accordance with British Aerospace Service Bulletin 33- 44-7670A, Revision 1, dated April 4, 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC 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. (e) This amendment becomes effective on April 21, 1992.
95-02-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires modification of the fixed engine cowling at the forward and aft crane beam attachment; and an inspection of the forward and aft crane beam to detect surface damage, and repair, if necessary. This amendment is prompted by several reports of rear cabin noise (engine rumble) during flight and while taxiing, which may have been caused by the interference between the forward and aft crane beams and the fasteners in the fixed engine cowling. The actions specified by this AD are intended to prevent chafing due to normal engine vibration, which could result in structural damage to the engine mount and possible separation of the engine from the airplane.
93-19-04: 93-19-04 PRECISION AIRMOTIVE (formerly Facet Aerospace Products (formerly Marvel-Schebler)): Amendment 39-8700. Docket 93-ANE-61. Supersedes Priority Letter AD 92-15-16 issued on July 9, 1992. Applicability: Precision Airmotive (formerly Facet Aerospace Products (formerly Marvel-Schebler)) Model MA3, MA3A, MA3PA, MA3SPA, and MA4SPA carburetors installed on but not limited to Textron Lycoming Model O-235, O-290, and O-320 series engines, and Teledyne Continental A-65, A-75, C-75, C-85, C-90, C-115, C-125, C-145, O-200, and O-300 series engines installed on but not limited to normally aspirated piston engine powered aircraft manufactured by Cessna, Piper, Beechcraft, and Mooney. Compliance: Required as indicated, unless accomplished previously. To prevent a disruption of fuel flow to the engine, resulting in engine power loss, engine failure, and damage to the aircraft, accomplish the following: (a) Prior to further flight, for carburetors repaired or rebuiltfrom November 1, 1991, through July 15, 1992, accomplish the following: (1) Visually inspect the float for Consolidated Fuel Systems (CFS) Part Number (P/N) CF 30-766 and remove the float if the date "10 91" is stamped on the top of the float lever arm, and replace with a serviceable float. NOTE: CFS Mandatory Service Bulletin CF-1-92, Revision 1, dated July 6, 1992, gives a listing of those known carburetors repaired or rebuilt during the suspect time period. NOTE: Guidance on replacing floats is contained in either Precision Airmotive (Facet) Aircraft Carburetor Service Manual, dated September 1984, or CFS Carburetor Float Kit Installation Instructions, CF 666-915. (2) Floats identified with Precision Airmotive P/N 30-766 with any date stamped on the float lever arm, or CFS P/N CF 30-766 with dates 8 89, 12 89, 1 90, 2 90, 8 90, 10 90, 1 91, 2 91, 4 91, 4 92, or 7 92 stamped on the float lever arm do not need to be removed. (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, Engine Certification Office. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the aircraft to a location where the requirements of this AD can be accomplished. (d) This amendment becomes effective on October 18, 1993.
94-08-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F-28 Mark 0100 series airplanes, that requires the installation of modified Flight Warning Computers and Flight Augmentation Computers. This amendment is prompted by reports of nuisance yaw-damper fault warnings and undetected horizontal trim motion, and the development of improved computers that eliminate these problems. The actions specified by this AD are intended to prevent nuisance warnings in the cockpit and undetected trim motion, both of which could compromise the safe takeoff of the airplane.
95-13-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Costruzioni Aeronautiche Giovanni Agusta S.p.A. (Agusta) Model A109A, A109AII, and A109C helicopters, that requires a modification of the tail boom vertical fin to create inspection openings that permit initial and repetitive visual inspections for cracks in the vertical fin rear spar attachment area. This amendment is prompted by four reports of cracks in the tail boom vertical fin rear spar attachment area. The actions specified by this AD are intended to prevent failure of the vertical fin attachment caused by cracks in the tail boom vertical fin rear spar attachment area, and subsequent loss of control of the helicopter.
95-05-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 and A300-600 series airplanes, that requires modification of the fuel tank jettison system. This amendment is prompted by a quality survey which revealed that the electrical bonding of the fuel jettison system has insufficient protection from a lightning strike. The actions specified by this AD are intended to prevent electrical arcing and resultant fire in the event of a lightning strike.
73-01-03: 73-01-03 AIR CRUISERS CO: Amendment 39-1580. Applies to all Model AD-8 life jackets manufactured on or before 15 October 1971. Compliance required within 120 days after the effective date of this AD, unless already accomplished. To preclude air chamber deflation from defective inflator manifold stem assemblies, accomplish alteration of the aforementioned life jackets in accordance with either: a. Air Cruisers Co. Service Bulletin No. 112-72-1, dated 6 March 1972; or b. Any other method approved as equivalent by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Upon request submitted through a maintenance inspector, accompanied by substantiating data, the compliance time specified in the AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective January 17, 1973.
66-29-04: 66-29-04 VICKERS: Amdt. 39-304 Part 39 Federal Register November 9, 1966. Applies to Viscount Models 744, 745D, and 810 Series Airplanes. Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished. To prevent fouling between the trailing edge of the elevator hinge beam shroud and the elevator skin lap joint, accomplish the following: (a) Visually inspect top and bottom shrouds on elevator hinge beam assemblies to unsure that clearance between trailing edge of shroud and forward edge of elevator skin lap joints or rivet heads is not less than 0.20 inch throughout full range of elevator movement. (b) If clearance is less than 0.20 inch, cut back trailing edge of hinge beam shroud to provide clearance of at least 0.20 inch but less than 0.25 inch throughout full range of elevator movement. (British Aircraft Corporation (B.A.C.) Ltd. Preliminary Technical Leaflet (PTL) No. 263, Issue 1, (700 Series) and No. 126, Issue 1) (800/810 Series) pertain to this subject.) This directive effective November 19, 1966.