Results
95-15-08: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model Viscount 744, 754D, and 810 airplanes, that requires an inspection to detect corrosion of the tailplane assemblies, and correction of discrepancies. This amendment is prompted by a report of corrosion on the main spar top and bottom forward boom of the tailplane assemblies and reports of cracking in the upper root joint attachment fitting. The actions specified by this AD are intended to detect and prevent such cracking or corrosion of the main spar forward booms or the upper root joint attachment fitting, which consequently could lead to the failure of the tailplane assemblies; this condition could result in reduced controllability of the airplane.
78-08-12: 78-08-12 PIPER AIRCRAFT CORPORATION: Amendment 39-3194. Applies to Piper Aircraft Corporation Model PA-31T certificated in all categories. To provide additional information on flap system operation, insert the following CAUTION or Piper PA-31T, Revision 12 of December 27, 1977, in the FAA Approved Airplane Flight Manual, Piper Report 1740 or Revision 4, dated December 9, 1977, to the Pilot's Operating Handbook, Piper Report 2048. CAUTION When selecting an "Approach" flap position and the selector is inadvertently moved beyond the "Approach" detent, the selector must be returned to its original position and then back to "Approach" in order to reprogram the selector. Returning the selector to the "Approach" detent without re-programming will return the flaps to their original position. This amendment is effective April 26, 1978.
2007-16-01: This amendment adopts a new airworthiness directive (AD) for Enstrom Helicopter Corporation (Enstrom) Model F-28, F-28A, F-28C, F- 28C-2, F-28C-2R, F-28F, F-28F-R, 280, 280C, 280F, 280FX, TH-28, 480, and 480B helicopters. This action requires a visual check to determine if a certain serial-numbered main rotor blade retention pin (retention pin) is installed, and removing and replacing any affected retention pin with an airworthy retention pin. This amendment is prompted by a report from the manufacturer that some retention pins were not manufactured in accordance with specifications cited on the engineering drawing. The actions specified in this AD are intended to prevent failure of a retention pin, separation of a main rotor blade from the helicopter, and subsequent loss of control of the helicopter.
78-01-02: 78-01-02 PIPER: Amendment 39-3107. Applies to Piper Models PA-31 and PA-31-325 Serial Nos. 31-7612001 thru 31-7612080, 31-7612082 thru 31-7612091, 31-7612096, 31-7612099, 31-7612101, 31-7612102, 31-7612104, 31-7612105, 31-7612107 and 31-7612108, PA-31-350 Serial Nos. 31-7652001 thru 31-7652015, 31-7652017 thru 31-7652162, and 31-7652164 thru 31-7652170 certificated in all categories. To prevent adverse stability or handling qualities due to incorrect tension in the elevator bungee, accomplish the following within the next 25 hours in service after the effective date of this Airworthiness Directive unless already accomplished. (a) Inspect the elevator bungee spring for correct tension, (30 lb. + 1 lb. for model PA-31 and 37 lb. + 1, -0 for models PA-31-325 and PA-31-350). (b) If the tension is not correct, before further flight alter the link in accordance with the "Instructions" section of Piper Service Bulletin No. 549 dated February 16, 1977, or equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (c) Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the compliance time specified above. This amendment is effective January 3, 1978.
2001-04-12: This amendment adopts a new airworthiness directive (AD) for Eurocopter France Model EC120B helicopters. This action requires visually checking the engine to main gearbox coupling tube assembly (tube) for a crack and replacing any cracked tube. This amendment is prompted by a report of a crack detected on a tube. The actions specified by this AD are intended to prevent a tube failure, loss of engine drive, and a subsequent forced landing.
2007-15-07: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. This AD requires repetitive high frequency eddy current inspections for cracks of the fuselage skin at stringer 5 left and right between stations 340 and 350, and corrective actions if necessary. This AD results from reports of fatigue cracks in the fuselage skin near stringer 5 between stations 340 and 350. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin near stringer 5. Cracks in this area could join together and result in in-flight depressurization of the airplane.
77-21-03: 77-21-03 PIPER: Amendment 39-3056. Applies to Model PA-36-285, Serial Nos. 36-7360001 through 36-7760003 certificated in all categories. To prevent hazards in flight associated with rudder spar cracks, accomplish the following: (a) Within the next 50 hours in service from the effective date of this AD unless previously accomplished within the past 50 hours in service and at intervals not to exceed 100 hours in service from the last inspection, inspect the rudder spar at hinge attachment points for cracks using a magnifying glass of at least ten power. (b) If cracks exist replace the rudder assembly with a new rudder assembly Piper Part No. 98125-04 or equivalent. (c) Upon the incorporation of rudder assembly, Piper Part No. 98125-04 or equivalent, compliance with the requirements of this AD may be dispensed with. (d) Equivalent inspection and repairs must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (e) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the inspection intervals specified in this AD. (Piper Service Bulletin No. 518 refers to this subject.) This amendment is effective October 18, 1977.
2001-04-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-600, -700, -800, and -700C series airplanes. This action requires initial and repetitive inspections of the elevator tab assembly to detect any damage or discrepancy; and corrective actions, if necessary. This action is necessary to prevent excessive in-flight vibrations of the elevator tab, which could lead to loss of the elevator tab and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2019-16-15: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney (PW) PW1519G, PW1521G, PW1521GA, PW1524G, PW1525G, PW1521G-3, PW1524G-3, PW1525G-3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A model turbofan engines. This AD was prompted by corrosion found on the high-pressure compressor (HPC) front hub, which could result in certain HPC front hubs cracking before reaching their published life limit. This AD requires revisions to the Airworthiness Limitations Section (ALS) of the manufacturer's Instructions for Continued Airworthiness (ICA) and air carrier's approved Continued Airworthiness Maintenance Programs (CAMP) to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
2018-05-08: We are superseding Airworthiness Directive (AD) 2013-19-12 for GA 8 Airvan (Pty) Ltd Models GA8 and GA8-TC320 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and address an unsafe condition on an aviation product. The MCAI describes the unsafe condition as the fuel system integral sump tank not meeting FAA regulations. We are issuing this AD to require actions to address the unsafe condition on these products.