Results
98-11-04 R1: This amendment corrects information in an existing airworthiness directive (AD), applicable to all Boeing Model 737-100 and -200 series airplanes, that currently requires that the FAA-approved maintenance inspection program be revised to include inspections that will give no less than the required damage tolerance rating for each Structural Significant Item, and repair of cracked structure. The actions specified in that AD are intended to ensure the continued structural integrity of the entire Boeing Model 737-100 and -200 fleet. This amendment corrects the requirements of the current AD by allowing operators not to change their programs if they determine that the existing inspections are effective for the new or affected SSI. This amendment is prompted by a review of the requirements of the existing AD.
99-06-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires repetitive flow checks of the hydraulic pump drain system to ensure that the system is not clogged, and correction of any discrepancy. This amendment also requires replacement of the existing magnetic seals of the accessory gearbox assembly with new, improved seals. Replacement of certain seals terminates the requirement for repetitive flow checks. This amendment also requires replacement of the engine drain modules with drain manifolds. 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 contamination of the engine accessory gearbox oil with hydraulic fluid, which could result in an in-flight engine shutdown.
98-12-23: This amendment adopts a new airworthiness directive (AD) that applies to certain British Aerospace (BAe) Model H.P. 137 Jetstream Mk. 1, Jetstream Model 3101, Jetstream Model 3201, and Jetstream 200 series airplanes. This AD requires replacing the windshield wiper arm attachment bolts and windshield wiper arm on all of the affected airplanes; and measuring the material thickness of the upper and lower toggle attachment brackets on the nose landing gear of the affected airplanes, and replacing the toggle attachment bracket lugs. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent the windshield wiper arm from corroding, detaching from the airplane during flight, and penetrating the fuselage, which could result in possible injury to the pilot and passengers; and to prevent collapse of the nose landing gear caused by design deficiency, which could result in loss of control of the airplane during landing operations.
98-03-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires removal and replacement of the center screw of the crew seat belt buckle. 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 failure of the center screw of the crew seat belt buckle, which could result in injury to the flightcrew during an emergency landing.
98-19-13: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-19-13, which was sent previously to all known U.S. owners and operators of BHTC Model 407 helicopters by individual letters. This AD requires, on or before the accumulation of 50 hours total time-in-service (TIS) on the engine-to-transmission driveshaft (driveshaft), replacing the driveshaft with an airworthy driveshaft. This amendment is prompted by analysis and test data which revealed that the life limit of the driveshaft is less than that which is stated in the applicable maintenance manual. The actions specified by this AD are intended to prevent failure of the driveshaft, loss of engine drive to the rotor system, damage to critical structural components, and subsequent loss of control of the helicopter.
98-20-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes, that requires repetitive inspections to detect corrosion on the fuselage skin panels that surround the emergency exits immediately aft of the wing; and follow-on corrective actions, if necessary. 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 detect and correct corrosion on the fuselage skin panels that surround the emergency exits immediately aft of the wing, which could result in reduced structural integrity of the fuselage pressure vessel.
97-07-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires the replacement of weight limitation placards in the aft main baggage bay and in the aft right stowage compartment with new placards indicating lower maximum weight limits. It also requires a revision of the Airplane Flight Manual to delete references to the current higher weight limits for these areas. This amendment is prompted by a report indicating that existing weight limitations could result in failure of the front bulkhead of the aft main baggage bay and doors of the aft right stowage compartment during emergency dynamic landing conditions. The actions specified by this AD are intended to prevent such failure, which consequently could result in injury to passengers and flight crew, and hinder evacuation of the airplane through the exit adjacent to this bulkhead.
99-13-03: This amendment adopts a new airworthiness directive (AD) that is applicable to BHTC Model 206L-4 helicopters. This action requires a reduction in the retirement lives of certain collective idler links and collective levers, and re-identifying certain collective idler links and collective levers. This amendment is prompted by the discovery of two types of collective idler links and collective levers--manufactured from different materials--that are identified with the same part numbers but should have substantially different retirement lives. The actions specified in this AD are intended to prevent use of a collective idler link (link) or collective lever (lever) beyond its retirement life, which could lead to failure of the link or lever and subsequent loss of control of the helicopter.
98-20-30: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A320 series airplanes equipped with a bulk cargo door, that requires repetitive inspections to detect fatigue cracking of the upper frame flanges; and repair, if necessary. This amendment also requires modification of the upper frame flanges of the bulk cargo door, which constitutes terminating action for the repetitive inspections. 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 fatigue cracking of the upper frame flanges, which could result in reduced structural integrity of the airplane.
97-23-15: This amendment adopts a new airworthiness directive (AD), applicable to all Fairchild Model F-27 series airplanes, that requires revising the Airplane Flight Manual (AFM) to prohibit positioning power levers below the flight idle stop during flight, and to provide a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the propeller ground beta range was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
98-06-34: This amendment adopts a new airworthiness directive (AD), applicable to all Aerospatiale Model ATR-42 and ATR-72 series airplanes, that requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits positioning the power levers below the flight idle stop during flight, and to provide a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the ground propeller beta range was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
97-13-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Gulfstream American (Frakes Aviation) Model G-73 (Mallard) series airplanes, that requires revising the Airplane Flight Manual (AFM) to prohibit positioning the power levers below the flight idle stop, and to provide a statement of consequences of positioning the power levers below the flight idle stop. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the propeller beta was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
98-07-01: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires inspections and tests for damage of the engine power cables, and replacement of any damaged cable with a new cable. This amendment also provides for optional modification of the engine power control cable pulley assembly. This amendment is prompted by a report of failure of an engine power cable, which could cause loss of function of the power control levers on the console. The actions specified by this AD are intended to prevent loss of function of the power control levers on the console, and subsequent loss of normal control of engine power.
97-11-03: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 series airplanes, that requires inspections of the lower door surrounding structure to detect cracks and corrosion, and repair, if necessary. This amendment also requires inspections to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the door structures; and repair, if necessary. In addition, this amendment will also require modification of the passenger/crew door frames, which, when accomplished, terminates certain inspections. This amendment is prompted by reports indicating that corrosion was found behind the scuff plates at exit and cargo doors, and fatigue cracks originated from certain fastener holes located in adjacent structure. The actions specified by this AD are intended to detect and correct such corrosion and fatigue cracking, which could result in reduced structural integrity of the door surroundings.
98-04-10: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 and A300-600 series airplanes, that requires repetitive inspections for cracking of the lugs of hinge brackets of inner airbrakes (spoilers) No. 1 and No. 2, and corrective action, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent detachment of the spoilers and consequent reduced controllability of the airplane.
99-03-11: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Model 60 airplanes. This AD requires modifying the aircraft cabin heat control wiring. This AD is the result of an incident on one of the affected airplanes where the circuit control that operates the aircraft cabin heater overheated and caused the cabin heater to shut down during in-flight operation. The actions specified by this AD are intended to prevent this circuit from overheating because of the current wiring design, which could result in possible smoke/fire if the heating system continued to operate in an "over-temperature" condition. Comments for inclusion in the Rules Docket must be received on or before April 8, 1999.
98-04-34: This amendment adopts a new airworthiness directive (AD), applicable to all Mitsubishi Model YS-11 and YS-11A series airplanes, that requires revising the Airplane Flight Manual (AFM) to specify procedures that will prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
98-08-06: This amendment adopts a new airworthiness directive (AD) that applies to AERMACCHI S.p.A. S.205 series and Models S.208 and S.208A airplanes. This AD requires inspecting all flight control cables (elevator control, aileron control, rudder, flaps, nose gear steering, parking brake, safety belts, and autopilot systems) for cracks in the eye end, and replacing any control cable with any crack in the eye end. 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 loss of critical airplane functions because of cracked flight control cables, which could result in loss of control of the airplane if occurring during flight.
98-05-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Cessna Model 750 airplanes. This action requires repetitive lubrication of the aileron feel cartridge assembly shaft. This action also requires replacement of the roll feel and centering bungee assembly with an improved assembly, which constitutes terminating action for the repetitive lubrication. This amendment is prompted by reports of partial to full jamming of the aileron control circuit during flight of the airplane. The actions specified in this AD are intended to prevent the possibility of accumulation of ice on the aileron feel cartridge assembly shaft, which could result in jamming of the aileron control circuit, and consequent reduced controllability of the airplane.
98-11-09: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-145 series airplanes, that requires a one-time visual inspection of the pilot valve harness tubes for bulges and cracks, cleaning the tubes, applying sealant at the tube end opening, and replacing any discrepant tubes with serviceable tubes. This amendment also requires replacement of the pilot valve harness tubes and vent valve tubes with new tubes having improved anti-corrosion protection. 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 cracking of the pilot valve harness tubes, which could allow fuel to enter the conduit and leak overboard; this condition could result in increased risk of a fuel tank explosion and fire.
98-09-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires a one-time, detailed visual inspection for discrepancies of the electrical bundles in the power generation compartment, and corrective actions, if necessary. 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 chafing and consequent damage to the electrical generation wires in the 101VU panel, which could result in a loss of electrical generation channels.
75-22-07: 75-22-07 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 2401. Applies to SA341G helicopters, certificated in all categories, equipped with main gear boxes P/N 341A.32.1000.01, .02, .03, or .05 with less than 25 hours time in service since new or overhauled, and that have not been altered in accordance with AMS 07.7077. Compliance is required until the accumulation of 25 hours time in service on new and newly overhauled main gear box. To detect main gear box (MGB) defects, accomplish the following: (a) Before each flight after the effective date of this AD check the MGB magnetic plug for particles and check the main gear box for abnormal friction points or noise by slowly rotating the main rotor by hand. (b) Before the first flight of each day after the effective date of this AD or within intervals of 5 hours MGB time in service after the last inspection, whichever occurs first, check the MGB oil filter for foreign metallic particles. (c) If highly heated and laminated (black) particles appear on the magnetic plug, or if fine particles deposited on the magnetic plug are preceded or accompanied by bronze particles left in the main gear box oil filter, or if abnormal friction points or noise is detected on the main gear box, prior to further flight replace main gear box with a serviceable part of the same part number incorporating Modification AMS 07.7077, or an FAA-approved equivalent. The checks required by this AD may be performed by the pilot. (Aerospatiale's Service Bulletin No. 05.10 dated February 7, 1975, refers to this subject). This amendment becomes effective November 3, 1975.
71-18-02: 71-18-02 MCCAULEY: Amdt. 39-1274. Applies to Model 2AF34C55, 2AF34C55-A, B, C, D, E, F, G, H, HM, J, JM, K, KM, L, LM, M and N propellers. Compliance required as indicated, unless already accomplished. To prevent propeller counterweight assembly failures accomplish the following: (a) Propellers with 750 hours or more time in service as of the effective date of this airworthiness directive must be modified in accordance with paragraph (c) within the next 100 hours time in service. (b) Propellers with less than 750 hours in service as of the effective date of this airworthiness directive must be modified in accordance with paragraph (c) prior to the accumulation of 850 hours in service. (c) Modify propeller counterweight assembly in accordance with McCauley Service Bulletin Nos. 93 dated 21 April 1971 and 93-1 dated 30 June 1971 or later FAA approved revision or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Eastern Region.NOTE: McCauley Service Bulletin 93-2 lists serial numbers of 2AF34C55N propeller hub assemblies which were in compliance with this airworthiness directive when shipped from the manufacturer. This amendment is effective August 31, 1971.
70-25-08: 70-25-08 PRATT & WHITNEY: Amdt. 39-1084. Applies to all Pratt & Whitney aircraft JT8D series turbofan engines which incorporate Part Number 500507 seventh stage compressor rotor disc with serial numbers listed in Pratt & Whitney Service Bulletin No. 2817, Rev. No. 1, dated 18 September 1970. Compliance required as indicated after the effective date of this airworthiness directive unless already accomplished. To preclude seventh stage compressor rotor disc failures as the result of suspected material deficiency, accomplish the following: 1. Replace discs with 2700 cycles or more in service within the next 30 cycles in service. 2. Replace discs with 2300 cycles, but less than 2700 cycles in service, within the next 100 cycles in service, but prior to accumulation of 2730 cycles. 3. Replace discs with 2000 cycles, but less than 2300 cycles in service, within the next 300 cycles in service, but prior to the accumulation of 2400 cycles. 4. Replace discs with less than 2000 cycles in service prior to the accumulation of 2300 cycles. The manufacturer's Service Bulletin identified and described in this directive is 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 this document from the manufacturer may obtain copies upon request from Pratt & Whitney Aircraft Division of United Aircraft Corporation, East Hartford, Conn. This document may also be examined at the FAA, Eastern Region, Federal Building, J. F. Kennedy International Airport, Jamaica, N.Y., at the 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 in the Eastern Region. This amendment is effective December 15, 1970 and was effective October 2, 1970, for all recipients of the telegram dated October 2, 1970, which contained this amendment.
71-17-02: 71-17-02 BOEING: Amendment 39-1268. Applies to Boeing Model 747 Series airplanes certificated in all categories. \n\n\tCompliance required as indicated. \n\tTo prevent body gear steer input on takeoff or landing, accomplish the following: \n\n\ta.\tWithin 100 hours' time in service after the effective date of this AD, unless already accomplished amend the Boeing B-747 Airplane Flight Manual, Certificate Limitations Section (used by each operator) by incorporating the following: \n\n\t"MISCELLANEOUS \n\tBODY GEAR STEERING. When aligned with the runway for takeoff and prior to advancing thrust levers, deactivate the body gear steering and leave deactivated until reaching taxi speed after landing, or refused takeoff." \n\n\tAs an interim acceptable procedure, deactivation of the body gear steering may be accomplished by disarming the circuit breaker identified on the circuit breaker panel as "Body Gear Steering Arm and Ind". \n\n\tb.\tOn or before January 1, 1972, unless already accomplished, install manually operated body gear steering arm/disarm switch per Boeing Service Bulletin 32-2113, dated July 23, 1971, or later FAA approved revision, or an equivalent installation approved by the Chief, Aircraft Engineering Division, FAA Western Region. Upon accomplishment of this installation, discontinue use of the circuit breaker to disarm the body gear per (a) above. The Airplane Flight Manual amendment per (a) above continues in full force and effect. \n\n\tThis amendment becomes effective August 17, 1971.