Results
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.
75-02-04: 75-02-04 GENERAL DYNAMICS: Amendment 39-2069. Applies to Models 22, 22M, 30, and 30A series airplanes, certificated in all categories. Compliance required as indicated. To reduce potential fire hazard existing in lavatory waste containers of General Dynamics Models 22, 22M, 30, and 30A series airplanes, accomplish the following: (a) Within 300 hours time in service from the effective date of this airworthiness directive, unless already accomplished within the last 1,000 hours, perform a thorough inspection of all electrical appurtenances, including wiring, terminal boxes, switches and hot water heaters physically located within lavatory waste container areas for wear, abrasion and corrosion. Repair or replace as necessary. (b) By December 31, 1975, unless already accomplished, modify the existing lavatory waste containers in accordance with the following General Dynamics Service Bulletins, as applicable, or later FAA-approved revisions, or in a manner approved bythe Chief, Aircraft Engineering Division, FAA Western Region: MODEL SERVICE BULLETIN NUMBER 22 25-102A 22M 25-25A 30, 30A 25-34A (c) Aircraft may be operated to a base for accomplishment of maintenance required under this airworthiness directive, per FAR's 21.197 and 21.199. This amendment becomes effective January 24, 1975.
67-06-05: 67-06-05 SCHEIBE-FLUGZEUGBAU: Amdt. 39-351 Part 39 Federal Register February 24, 1967. Applies to Model Bergfalke II/55 Gliders, all Serial Numbers, and Model Bergfalke III Gliders, Serial Numbers 5500 through 5586. Compliance required as indicated. To detect cracks on the aileron bell crank, Drawing No. 104B.41-S3, located in the outer wing section, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished within the last 40 hours' time in service and thereafter at intervals not to exceed 50 hours' time in service from the date of the last inspection, visually inspect the aileron bell cranks, Drawing No. 104B.41-S3, in the left and right outer wing section for cracks using a mirror, and at least a two-powered glass. If cracks are detected during any of these inspections, comply with (b) of this AD. (b) Replace aileron bell cranks, Drawing No. 104B.41-S3, found cracked during the inspectionprovided for in (a) before further flight with a new reinforced aileron bell crank, Drawing No. 104B.41-S3-E1. (c) The requirements of this AD are not applicable to those gliders that have been equipped with aileron bell cranks, Drawing No. 104B.41-S3-E1, in the outer wing section. (Scheibe-Flugzeugbau Technical Information Bulletin I/66 pertains to this subject.) This directive effective March 1, 1967.