Results
75-01-05: 75-01-05 AVCO LYCOMING: Amendment 39-2063. Applies to all Avco Lycoming T5313B turboshaft engines. Compliance required, unless already accomplished, prior to the accumulation of 100 hours time in service after the effective date of this AD. To prevent possible centrifugal compressor impeller assembly vane failures leading to performance deterioration and partial or complete power loss, remove centrifugal compressor impeller assemblies, part numbers 1-100-078-03, 1-100-078-04, and 1-100-078-10 and replace with centrifugal compressor impeller assembly, part number 1-100-078-08. Equivalent methods of compliance must be approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. NOTE: (Avco Lycoming Service Bulletin Number 0042 pertains to this subject.) This amendment becomes effective January 17, 1975
2012-24-06: We are adopting a new airworthiness directive (AD) for certain Saab AB, Saab Aerosystems Model 340A (SAAB/SF340A) and SAAB 340B airplanes. This AD was prompted by reports of stall events during icing conditions where the natural stall warning (buffet) was not identified. This AD requires replacing the stall warning computer (SWC) with a new SWC, which provides an artificial stall [[Page 73280]] warning in icing conditions, and modifying the airplane for the replacement of the SWC. We are issuing this AD to prevent natural stall events when operating in icing conditions, which, if not corrected, could result in loss of control of the airplane.
2012-24-08: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by reports of flight crew failure to activate air data probe heat. This AD requires modifying the anti-icing system for the angle of attack sensor, the total air temperature, and the pitot probes. We are issuing this AD to prevent ice from forming on air data system sensors and consequent loss of or misleading airspeed indication on all airspeed indicating systems, which could lead to loss of control of the airplane.
74-11-01: 74-11-01 MITSUBISHI HEAVY INDUSTRIES, LTD: Amendment 39-1844 as amended by Amendment 39-1859 is further amended by Amendment 39-3125. Applies to Mitsubishi Models MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, MU-2B-30, and MU-2B-35 airplanes except those airplanes modified in accordance with Mitsubishi Service Recommendation No. 027 dated September 12, 1974, or an FAA-approved equivalent. Compliance is required as indicated. To detect cracks and optical distortion in the front windshield outer panes that could result from the discharge of unusually hot defogging air caused by an air conditioning system failure, accomplish the following: (a) Before further flight and thereafter prior to the first takeoff each day, from outside the aircraft, visually check the outer lower edge of the left hand and right hand front windshield outer panes for cracks and small oval shaped optical distortions. The check required by this AD may be performed by the pilot. NOTE: Distortions generally appear at the same intervals as those of the defogging air outlet holes, approximately 0.5 inches apart, and in an area approximately 0.8 inches above the top of the outside bottom windshield retainer edge. Particular attention should be given to these areas during the checks required by paragraph (a). (b) If cracks or small oval shaped optical distortions are found during a check required by paragraph (a), before further flight, accomplish the following and continue to check in accordance with paragraph (a) of this AD: (1) Replace the windshield outer pane in which a crack or optical distortion is found in accordance with the performance rules of FAR 43.13. NOTE: Mitsubishi replacement windshield part numbers are as follows: Aircraft with electrically heated windshields incorporated in accordance with Mitsubishi Service Recommendation No. 014 - Windshield part numbers 010A-931026-11 and -12. Other Aircraft - Serial numbers 4 through and including 7 - Windshield partnumbers 010A-310260-1 and -2; Serial numbers 8 and up -Windshield part numbers 010A-31450-1 and -2. (2) Correct the malfunctioning of the air conditioning system in accordance with the performance rules of FAR 43.13. (c) Notwithstanding the compliance time for repair specified in paragraph (b) of this AD, the aircraft may be flown in accordance with FAR 21.197 to a base where the repair can be performed; provided that, the aircraft is not pressurized. NOTE: Mitsubishi Heavy Industries Limited MU-2 Service Bulletin No. 163, dated March 4, 1974, pertains to this subject. Mitsubishi Maintenance Manuals for the Model MU-2B and MU-2B-10, -15, -20, -25, -30, and -35 airplanes contain information relating to the replacement of windshield panes and the trouble shooting of cabin air conditioning systems. Amendment 39-1844 was effective upon publication in the Federal Register as to all persons except those persons to whom it was made effective upon receipt of the airmail letter dated April 19, 1974, that contained this amendment. Amendment 39-1859 became effective upon publication in the Federal Register. This Amendment 39-3125 becomes effective January 30, 1978.
75-17-17: 75-17-17 LOCKHEED: Amendment 39-2317. Applies to Model L-1011-385-1 Series airplanes certificated in all categories, configured with aft service center flight attendant rest seats. Compliance required within 300 flight hours time in service after effective date of this AD unless already accomplished. To provide protection from the lack of adequate oxygen for the occupants of the aft service center flight attendant's rest seat under emergency conditions and to provide the required information sign notifying occupants of this seat when safety belts should be fastened, and when smoking is prohibited, accomplish one of the following: (a) Install an automatically presented oxygen unit and passenger infomation sign for occupants of the aft service center flight attendant's rest seat, approved by the Chief, Aircraft Engineering Division, FAA Western Region; or (b) Remove the aft service center flight attendant's rest seat; or (c) Remove existing placard (Lockheed P/N 1564393-101) prohibiting use during takeoff landing and turbulent flight and install in its place a placard prohibiting rest seat occupancy. Flight attendant's rest seat installation modified by (b) or (c), above, may be reconfigured back to the original seat installation upon accomplishment of (a), above. This amendment becomes effective September 11, 1975.
2012-22-18: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-243, -243F, -341, -342, and -343 airplanes equipped with Rolls-Royce Trent 700 engines. This AD was prompted by reports of extensive damage to engine air intake cowls as a result of acoustic panel collapse. This AD requires repetitive inspections of the three inner acoustic panels of both engine air intake cowls to detect disbonding, and corrective actions if necessary. We are issuing this AD to detect and correct disbonding, which could result in detachment of the engine air intake cowl from the engine leading to ingestion of parts, which could cause failure of the engine, and possible injury to persons on the ground.
2012-22-03: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747- 200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. This AD was prompted by reports of cracks in the main entry door number 1 upper main sill outer chord, along the bend radius of the chord on several airplanes. This AD requires a general visual inspection to identify any existing structural repair manual (SRM) repairs of the upper main sill outer chord of the left and right side main entry door number 1, repetitive detailed inspections for cracks in the upper main sill of the door(s); and related investigative and corrective actions, if necessary. This AD also requires repetitive inspections for airplanes on which a certain repair is done, and corrective actions if necessary, and reduces certain compliance times. We are issuing this AD to detect and correct cracks in the main entry door number 1 upper main sill outer chord, along the bend radius of the chord, which could result in loss of structural integrity of the airplane.
75-13-01: 75-13-01 SIKORSKY AIRCRAFT: Amendment 39-2238 as amended by Amendment 39-2879. Applies to S-58A, S-58B, S-58C, S-58D, S-58E, S-58F, S-58G, S-58H, S-58J, S- 58BT, S-58DT, S-58ET, S-58FT, S-58HT, S-58JT helicopters certificated in all categories, including Military Type HSS-1, HSS-1F, HSS-1N, HUS-1, HUS-1A, HUS-1AN, HUS-1G, HUS- 1Z, H-34A, H-34C, H-34J, CH-34A, CH-34C, HH-34F, SH-34G, SH-34H, SH-34J, UH-34D, UH-34E, UH-34G, UH-34J, VH-34C and VH-34D helicopters. To prevent operation with fatigue cracks in the main rotor magnesium stationary stars, P/Ns S1610-24013-0, S1610-24013- 1, and S1610-24013-2, accomplish the following: (a) Prior to the first flight of each day, conduct visual inspections of stationary star for cracks in the areas around the recesses and edges surrounding the recesses, inboard of all of the trunnion lugs. (b) For stationary stars with more than 250 hours time in service: Within 5 hours time in service after the effective date of this AD, unless alreadyaccomplished, and at 50 hour intervals thereafter, conduct dye penetrant inspections of the areas described in paragraph (a) for cracks. (c) If a crack is found during the above inspections, replace the cracked stationary star with a star that has been inspected in accordance with paragraph (b) above and found to be free of cracks, prior to flight. Sikorsky Alert Service Bulletin 58B10-10 covers this inspection. Amendment 39-2238 became effective upon publication in the FEDERAL REGISTER for all persons except those to whom it was made effective immediately by telegram dated May 16, 1975. This amendment 39-2879 becomes effective May 20, 1977.
2012-22-05: We are superseding an existing airworthiness directive (AD) for certain Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. That AD currently requires performing a detailed visual inspection for cracks of the pistons on the main landing gear (MLG), and replacing the affected pistons if necessary. This new AD also requires modifying the MLG by installing a piston containing a certain part number, and revising the airplane maintenance program. This AD was prompted by a new modification developed to safeguard the integrity of the MLG assembly and improve surface protection of the affected area of the MLG piston. We are issuing this AD to prevent MLG failure, possibly resulting in loss of control of the airplane during the landing roll- out.
73-11-06: 73-11-06 MAULE: Amdt. 39-1646. Applies to Models M-4-180 and M-4-220 certificated in all categories as indicated below. Compliance required within the next 50 hours' time in service after the effective date of this airworthiness directive. To prevent possible engine overheat during climb and to obtain a correct cylinder head temperature reading accomplish the following or an equivalent approved by Chief, Engineering and Manufacturing Branch, Southern Region: 1. For Model M-4-220C serial numbers 2135C through 2175C and 2177C: Install Maule slug P/N 6002B-3 in the No. 4 cylinder head thermocouple hole in accordance with Maule Service Letter No. 25. The slug is to be installed prior to relocation of cylinder head sender unit. 2. For Model M-4-180C serial numbers 3001C through 3006C; Model M-4-220S, Serial Number 2001S; Model M-4-220C; Serial Numbers 2001C through 2126C, 2129C through 2175C, and 2177C: Relocate the cylinder head temperature sender to the No. 4 cylinder head in accordance with Maule Service Letter No. 24. 3. For Model M-4-180C, Serial Numbers 3002C through 3006C, and Model M-4-220C Serial Numbers 2053C through 2126C, 2129C through 2175C and 2177C: Install engine top baffle, Maule P/N 5031X-3, in accordance with Maule Service Letter No. 26. This amendment becomes effective May 29, 1973.