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74-09-02: 74-09-02 PIPER: Amendment 39-1816. Applies to Model PA-32-260 Airplanes, Serial Numbers 32-7300001 through 32-7300024 and Model PA-32-300, Serial Numbers 32-7340001 through 32-7340081, certificated in all categories. Compliance required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To provide an unobstructed view of the stall warning light, accomplish the following: Relocate stall warning light in accordance with Piper Service Bulletin Number 403 or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, P.O. Box 20636, Atlanta, Georgia 30320. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 522(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Piper Aircraft Corporation, Vero Beach Division, Vero Beach, Florida 32960. These documents may also be examined at the FAA, Southern Region, 3400 Whipple Avenue, East Point, Georgia 30344 and at 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 at the FAA, Southern Region office. This amendment becomes effective April 18, 1974.
98-07-14: This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 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.
2007-20-02: The FAA is adopting a new airworthiness directive (AD) for all Viking Air Limited Model DHC-7 airplanes. This AD requires an inspection of certain SM-200 servo drive units (power servo motor and housing assemblies) for certain markings, related investigative action if necessary, and modification if necessary. This AD results from a report that some SM-200 servo drive units that were not in configuration MOD H are installed on Model DHC-7 airplanes. MOD H prevents the internal clutch fasteners from backing out. We are issuing this AD to prevent the possibility of internal clutch fasteners from backing out, which could cause an inadvertent servo engagement and consequent reduced controllability of the airplane.
2007-19-08: 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: While they were gaining access to the THS (trimmable horizontal stabilizer) fuel tank for maintenance check, several operators have found one or several of the 8 THS hoist point fitting bases cracked or broken-off. The breakage resulted in metallic debris being released within the Trim Tank. The origin of the damage is most probably due to interference with the THS hoisting lugs that are stowed in the hoist point fittings in the reverse position, being screwed too deep inside the THS hoist fittings. Damaged hoist point fittings could cause the release of metallic debris within the THS fuel system. * * * Compliance with the requirements of this AD will also eliminate potential contributing factor[s] to ignition risks. We are issuing this AD to require actions to correct the unsafe condition on these products.
2019-23-11: The FAA is adopting a new airworthiness directive (AD) for all Gulfstream Aerospace Corporation (Gulfstream) Model GVI airplanes. This AD requires revising the airplane flight manual (AFM) for your airplane by adding an airplane flight manual supplement (AFMS), which contains operating limitations and abnormal procedures for loss of rudder or yaw damper. This AD was prompted by a report of an inflight rudder surface shutdown that resulted in lateral-directional oscillations of the airplane. The FAA is issuing this AD to address the unsafe condition on these products.
73-14-02: 73-14-02 PIPER: Amdt. 39-1673. Applies to PA-34-200 airplanes, Serial Numbers 34-E4 and 34-7250001 and up equipped with exhaust systems Piper Part Numbers 96465-00 and 96466-00. Compliance required within the next 10 hours time in service after the effective date of this AD or before the accumulation of 60 hours time in service whichever occurs later and thereafter at intervals not to exceed 25 hours time in service from the last inspection. To insure that cracks are not present in the exhaust system, accomplish the following: (a) Remove both right and left nose cowls, Piper Part Numbers 96500-34 and 96500-35, and open both right and left cowl doors on both right and left engines. Inspect the entire exhaust system for any evidence of cracks or failed ducts or flanges. Use an inspection mirror as required, a minimum 100 watt light and a minimum four power magnifying glass. (b) If the exhaust systems are found to contain cracked or broken ducts, flanges or parts, replace with new replacement parts or repair the affected parts in accordance with Advisory Circular 43.13-1 before further flight. Piper Service Bulletin No. 373A pertains to this subject. This supersedes amendment 39-1564 (37 F.R. 25221) AD 72-25-01. This amendment becomes effective June 29, 1973.
82-23-05: 82-23-05 GULFSTREAM AMERICAN: Amendment 39-4492. Applies to Model 685 (S/Ns 12000 through 12043, and 12045 through 12066) airplanes certificated in any category. COMPLIANCE: Required within 25 hours after the effective date of this AD, unless already accomplished. To prevent possible contamination of cabin air by engine exhaust, accomplish the following: (a) Replace the existing induction air elbow with an improved P/N 610597-501 elbow and inspect the exhaust system in accordance with Gulfstream American Corporation Service Bulletin No. 192 dated August 20, 1982. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent method of compliance with this AD may be used if approved by the Manager, Aircraft Certification Division, ASW-100, Southwest Regional Office, FAA, Fort Worth, Texas 76101; telephone (817) 624-4911, extension 511. This amendment becomes effective on November 15, 1982.
84-02-07: 84-02-07 AVCO LYCOMING WILLIAMSPORT DIVISION: Amendment 39-4856. Applies to Avco Lycoming Model LTS101-600A-2 gas turbine engines. Compliance is required as indicated (unless already accomplished). To prevent power loss and power turbine overspeed, accomplish the following: 1. Replace, concurrently, the output gear assembly and torquemeter gear assembly with a new output gear assembly, part numbers (P/Ns) 4-081-120-10, -15, -16, or -17, and a new torquemeter gear assembly, P/Ns 4-081-070-12, -15, -19, -25, or -26, for those engines which have had the torquemeter gear assembly replaced without concurrent replacement of the output gear assembly, and which presently have output gear assembly P/Ns 4-081-120-11, -12, -13, or -14 installed, within the next 25 operating hours. 2. Replace, concurrently, the output gear assembly and torquemeter gear assembly with a new output gear assembly, P/Ns 4-081-120-10, -15, -16, or -17, and a new torquemeter gear assembly, P/Ns 4-081-070-12, -15, -19, -25, or -26, for those engines which have had the output gear assembly replaced without concurrent replacement of the torquemeter gear assembly, and which presently have output gear assembly P/Ns 4-081-120- 11, -12, -13, or -14 installed, within the next 25 operating hours. 3. Replace, concurrently, the output gear assembly and torquemeter gear assembly with a new output gear assembly, P/Ns 4-081-120-10, -15, -16, or -17, and a new torquemeter gear assembly, P/Ns 4-081-070-12, -15, -19, -25, or -26, for those engines having output gear assembly P/Ns 4-081-120-11, -12, -13, or -14 installed, within the next 100 operating hours or before reaching 1,000 operating hours, whichever occurs later. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulation (FAR) 21.197 and 21.199 to a base where the AD can be accomplished. Upon request of an operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, FAA, New England Region. This amendment becomes effective May 7, 1984, as to all persons except those persons to whom it was made immediately effective by priority letter AD 84-02-07, issued January 27, 1984, which contained this amendment.
2019-23-15: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
72-24-02: 72-24-02 PIPER: Amendment 39-1557. Applies to Model PA-28-140, PA-28-150, PA- 28-160, PA-28-S-160, PA-25 (150 HP) airplanes, equipped with Lycoming O-320 engines and Marvel Schebler carburetors Model MA-4SPA, Part Number 10-3678-32 certificated in all categories. Compliance required within the next 10 hours' time in service after the effective date of this airworthiness directive, unless already accomplished: To prevent power interruption as a result of abrupt throttle movement, accomplish the following: (a) Attach the following operating limitation placard to the instrument panel near the throttle control in full view of the pilot using 1/8" minimum size type: "DO NOT OPEN THE THROTTLE RAPIDLY. (IDLE TO FULL THROTTLE IN 2 SECONDS MINIMUM.)" The placard may be fabricated by the owner/operator. This amendment becomes effective November 17, 1972.