Results
78-09-03: 78-09-03 DOWTY ROTOL, LTD.: Amendment 39-3196. Applies to Dowty Rotol Type R193/4-30-4/50 and R193/4-30-4/61 propellers of the following serial numbers which may be installed on, but not necessarily limited to, Fairchild Model F27A, F27F, F27J, FH-227, and FH- 227-1; and Fokker F-27 Mks. 200, 400, 500 and 600 airplanes: 193/60/167 DRG/34/61 DRG/66/62 DRG/284/63 DRG/120/64 DRG/4/61 DRG/35/61 DRG/19/63 DRG/285/63 DRG/121/64 DRG/5/61 DRG/2/62 DRG/22/63 DRG/286/63 DRG/122/64 DRG/6/61 DRG/3/62 DRG/24/63 DRG/287/63 DRG/123/64 DRG/7/61 DRG/33/62 DRG/25/63 DRG/320/63 DRG/138/64 DRG/9/61 DRG/35/62 DRG/26/63 DRG/321/63 DRG/141/64 DRG/13/61 DRG/36/62 DRG/72/63 DRG/337/63 DRG/142/64 DRG/14/61 DRG/37/62 DRG/134/63 DRG/14/64 DRG/158/64 DRG/25/61 DRG/41/62 DRG/136/63 DRG/17/64 DRG/207/64 DRG/26/61 DRG/42/62 DRG/222/63 DRG/36/64 DRG/208/64 DRG/27/61 DRG/49/62 DRG/224/63 DRG/78/64 DRG/292/66 DRG/33/61 DRG/50/62 DRG/226/63 DRG/79/64 DRG/296/66 Compliance is required as indicated, unless already accomplished. To reduce the possibility of propeller hub and driving center assembly failure due to corrosion, and subsequent possible propeller failure, accomplish the following: (a) Within the next 1000 hours time in service after the effective date of this AD, or at the next scheduled propeller overhaul, whichever occurs first, inspect the propeller hub and driving center assembly in accordance with Dowty Rotol Service Bulletin 61-882, dated March 11, 1977 (hereinafter SB 61-882), and the therein referenced Dowty Rotol Propeller Overhaul Manual Pub. No. 61-2-2, Repair Scheme Manual Pub. No. 923; and Process Specification Manual Pub. No. 872, or FAA-approved equivalents. (b) If, as a result of the inspection required by paragraph (a) of this AD, propeller hub or driving center assembly corrosion is found to exceed the limits specified in Dowty Rotol Overhaul Manual 61-2-2 and Repair Scheme Manual Publication No. 923 Repair Schemes 650013110 and 650013120 or an FAA-approved equivalent, before further operation, replace the propeller hub and driving center assembly with a serviceable propeller hub and driving center assembly or an FAA-approved equivalent. (c) The equivalent means of compliance specified in paragraphs (a) and (b) of this AD must be approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Region, Federal Aviation Administration, c/o American Embassy, Brussels Belgium. This amendment becomes effective May 22, 1978.
2010-04-13: We are adopting a new airworthiness directive (AD) for the products listed above. 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: An A300-600 operator reported two events of IPECO pilot seat moved in the aft position, one during take-off roll and one during climb out. The investigation of these events showed that a broken/ missing spring contributed to the seat not being correctly locked. An unwanted movement of pilot or co-pilot seat in the aft direction is considered as potentially dangerous, especially during the take-off phase when the speed of the aeroplane is greater than 100 knots and until landing gear retraction. * * * * * The unsafe condition is potential loss of control of the airplane during take-off and landing. We are issuing this AD to require actions to correct the unsafe condition on these products.
97-09-02R3: This amendment revises an existing airworthiness directive (AD) for CFMI CFM56-5C series turbofan engines. That AD currently establishes new life limits for certain high pressure turbine rotor (HPTR) front shafts, HPTR front air seals, and booster spools. This action removes the booster spool, part number (P/N) 337-005-210-0, and the HPTR front shaft, P/Ns 1498M40P03, 1498M40P05, and 1498M40P06, from the parts listed with lowered life limits in the existing AD. This amendment results from a life management review completed by the manufacturer. We are issuing this AD to prevent low-cycle fatigue (LCF) failure of certain HPTR front air seals, which could result in an uncontained engine failure and damage to the airplane.
77-06-04: 77-06-04 ENSTROM: Amendment 39-2855. Applies to Enstrom Model F28C helicopters with serial numbers 364, 367, 373 and 374 and Model 280C with serial numbers 1007, 1020, 1060, 1062, 1065 certificated in all categories. Before further flight, unless already accomplished, remove from service the tail rotor assembly P/N 28-150000-3 and replace with an airworthy assembly which has been assembled using forged blade grip fittings P/N 28-150013-11. The removed tail rotor assembly should be returned to Enstrom Helicopter Corporation, Menominee, Michigan 49858. This amendment becomes effective March 31, 1977, to all persons except those to whom it was made effective earlier by air mail letter dated March 2, 1977.
2007-17-07: We are adopting a new airworthiness directive (AD) for the products listed above. 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: The Bombardier CL-600-2B19 airplanes have had a history of flap failures at various positions for several years. Flap failure may result in a significant increase in required landing distances and higher fuel consumption than planned during a diversion. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
80-14-01: 80-14-01 PIPER AIRCRAFT CORPORATION: Amendment 39-3818. Applies to Model PA-32-260, serial numbers 32-7800001 through 32-7800008; PA-32-300, serial numbers 32-7740109 through 32-7940290; PA-32R-300, serial numbers 32R-7780215 through 32R-7880068; Model PA-32RT-300, serial numbers 32R-7885001 through 32R-7985105; and Model PA-32RT-300T, serial numbers 32R-7787001, and 32R-7887002 through 32R-7987126 airplanes certificated in all categories. Compliance required within the next 50 hours time in service after the effective date of this AD unless already accomplished. To prevent fuel leakage and potential fire hazard, accomplish the following: (a) De-fuel the aircraft in accordance with the Piper Service or Maintenance Manual for the appropriate model aircraft. (b) Remove the right hand and left hand fuel tanks in accordance with the Piper Service or Maintenance Manual for the appropriate model aircraft. (c) 1. For Model PA-32-260 series aircraft, serial numbers 32-7800001 through 32-7800008, and PA-32-300 model aircraft, serial numbers 32-7740109 through 32- 7840202, modify the fuel tank vent system in accordance with the instructions listed in the "Fuel Tank Vent Modification and Vent Hose Replacement Kit," Piper Part Number 763-934V. 2. For Model PA-32-300 series airplanes, serial numbers 32-7940001 through 32-7940290, Models PA-32R-300, PA-32RT-300 and PA-32RT-300T series airplanes, modify the fuel tank vent system in accordance with the instructions listed on the "Fuel Tank Vent Hose Replacement Kit," Piper Part Number 764-011V. (d) Reinstall the fuel tanks in accordance with instructions in the appropriate Piper Service or Maintenance Manual. NOTE: Do not allow lines or hoses to twist during installation. (e) Refuel the aircraft and check for leaks and fuel quantity gauge function. (f) Make an appropriate maintenance record entry. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. NOTE: Piper Service Bulletin 646A pertains to this subject. This amendment becomes effective July 10, 1980.
2001-06-06: This amendment adopts a new airworthiness directive (AD) that applies to certain Cessna Aircraft Company (Cessna) Model 172 airplanes. This AD requires you to inspect the main landing gear pivot assemblies for cracks, replace any cracked main landing gear pivot assemblies, and install new bushings on the pivot assembly shaft. This AD is the result of many service difficulty reports of cracked main landing gear pivot assemblies on the affected airplanes. The actions specified by this AD are intended to detect, correct, and prevent future cracks on the original design landing gear pivots. Cracked main landing gear pivots could fail resulting in gear-up landings or loss of braking.
2001-06-05: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA - Groupe AEROSPATIALE (Socata) Model TBM 700 airplanes equipped with Option No. OPT 70-35-001 (gaseous oxygen system). This AD requires you to incorporate a modification that relocates the oil breather vent location. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent oil from entering the gaseous oxygen system service compartment. Such oil contamination could result in a fire or explosion.
80-12-03: 80-12-03 PIPER AIRCRAFT CORPORATION: Amendment 39-3783. Applies to Model PA-44-180, Serial Numbers 44-7995001 through 44-8095020, airplanes certificated in all categories. Compliance is required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. To prevent nose landing gear retraction during landing rollout or ground operations, accomplish the following: a. Replace the nose landing gear downlock hook and bushing in accordance with Piper Aircraft Corporation Service Bulletin No. 678, dated March 24, 1980, and Piper Service Kit No. 764-010V, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. b. Make appropriate maintenance record entry. This amendment becomes effective June 3, 1980.
79-03-02: 79-03-02 PIPER: Amendment 39-3402 as amended by Amendment 39-3777. Applies to Piper Model PA-38-112 Serial Nos. 38-78A0001 thru 38-80A0063 certificated in all categories. To prevent vertical movement of the bottom rudder hinge bearing and possible interference between the bottom surface of the rudder fairing tip and the vertical fin top surface, accomplish the following: (a) Within the next 25 hours in service after the effective date of this AD: (1) Deflect the rudder so that the bottom hinge is accessible. (2) Inspect the bottom hinge bracket for a loose bearing, which will be evident by any portion of the bearing outer-race protruding below the lower surface of the bracket. (3) If a loose bearing is indicated, install Piper Kit 763 881 or equivalent, before further flight. (b) Within the next 50 hours of service, after the effective date of this AD, unless already accomplished, install Piper Kit 763 881 or equivalent. (c) The affected airplane may be flown in accordance with FAR 21.197 to a location where the AD may be accomplished. (d) Equivalent inspections, repairs and alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (e) Upon submission of substantiating data through an FAA Maintenance Inspector the compliance times specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Piper Service Bulletin No. 613, dated August 11, 1978, pertains to this subject. Amendment 39-3402 was effective January 31, 1979. This Amendment 39-3777 is effective May 28, 1980.