Results
96-26-01: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Aircraft Engines (GE) CT7 series turboprop engines, that requires replacement of the gas generator turbine stage 2 forward cooling plates prior to the published cyclic life limits. The AD also defines the new, reduced cyclic life limits for the affected forward cooling plates. This amendment is prompted by reports of gas generator turbine stage 2 forward cooling plate failures. The actions specified by this AD are intended to prevent gas generator turbine stage 2 forward cooling plate failure, which could result in an uncontained engine failure.
2004-25-18: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney Canada (PWC) PT6A-60A and PT6A-65B turboprop engines. This AD requires replacing Woodward propeller governor assemblies, part number (P/N) 8210-212H. This AD results from six incidents during airplane acceptance flight testing where directional control of the airplane was difficult to maintain during landing. We are issuing this AD to prevent loss of directional control and damage to the airplane.
84-18-03 R1: 84-18-03 R1 GARLICK HELICOPTERS, HAWKINS AND POWERS AVIATION, INC., WILCO AVIATION, CALIFORNIA DEPARTMENT OF FORESTRY, PILOT PERSONNEL INTERNATIONAL, INC., AND INTERNATIONAL HELICOPTER, INC. (BELL HELICOPTER TEXTRON, INC.): Amendment 39-4899 as amended by Amendment 39-4997. Applies to Model UH-1 series helicopters certificated in the restricted category. Compliance is required within 10 hours time in service, unless already accomplished, after September 6, 1984, for Garlick Helicopters, Hawkins and Powers Aviation, Inc., and Wilco Aviation UH-1 series helicopters. Compliance is required within 10 hours time in service, unless already accomplished, after the effective date of this amendment for California Department of Forestry, Pilot Personnel International, Inc., and International Helicopter, Inc., UH-1 series helicopters. To detect any improperly repaired or cracked main rotor pitch change link clevis and to prevent possible failure of a clevis, accomplish the following one-time inspection of each clevis, P/N 204-011-136-1 (FSN 5340-00-839-3934). (a) Visually inspect the exposed surfaces of the clevis using a 5-power or higher magnifying glass. If any surface with pits has a golden or silver color within a pit, the clevis has been replated and must be removed before further flight. (b) Visually inspect the exposed threaded area of the clevis shank, above the jam nut, for crack indications. If a crack indication is found, the part must be removed and additionally inspected for cracks using magnetic particle or equivalent inspection method. (c) If a clevis has been replated or has a crack, the clevis must be removed before further flight. Install a serviceable clevis as prescribed in the appropriate military model maintenance or overhaul manual. (d) Compliance with UH-1 series aircraft military message dated July 13, 1984, from Commander AVSCOM satisfies this AD. Amendment 39-4899 became effective September 6, 1984.This Amendment 39-4997 becomes effective on February 22, 1985.
2023-04-10: The FAA is superseding Airworthiness Directive (AD) 2020-26- 07, which applied to all Dassault Aviation Model MYSTERE-FALCON 900 airplanes. AD 2020-26-07 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that a new airworthiness limitation is necessary. This AD continues to require the actions in AD 2020-26-07, and also requires revising the existing maintenance or inspection program, as applicable, to incorporate a new airworthiness limitation; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
86-23-02: 86-23-02 PILATUS BRITTEN-NORMAN LIMITED: Amendment 39-5452. Applies to Pilatus Britten-Norman Limited (PBN) Models BN-2 and BN-2A Islander airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished by incorporation of Modification NB/M/99O as noted in Britten-Norman Service Bulletin (S/B) No. BN.2/SB.113, Issue 2, dated April 14, 1986. To prevent undesirable oscillations, flutter or control system wear, accomplish the following: (a) Shake the elevator and aurally (by ear) determine if the mass balance weight is loose. Examine for any sign of movement, i.e., rust marks or grey lead deposits. In cases of uncertainty drill a small hole (5/32 in. dia) in the lower case and insert a probe to feel for lead movement. Alternatively dismantle the trimming weight assembly by removal of the blind riveted end covers and by removing the balance discs (note position and sequence for re- assembly). (1) If a loose balance weight is found prior to further flight, accomplish the following: (i) Remove the elevator; (ii) Drill out rivets, remove the trim weight assembly and detach the complete case from the tip rib. (iii) Lift out the profiled lead block. (iv) Clean the case internally to remove any corrosion by the use of emery cloth. Keep clean; do not wipe with oily or greasy rag or bond of adhesive will be impaired. (v) Clean the lead block to obtain a corrosion free face to the steel case and permit free fit into the case with an approximate 0.020 in. to 0.030 in. clearance. (vi) Prepare and apply a quantity of 3M's EC2216 epoxy adhesive to the case and press in the weight to obtain a layer of adhesive all around to fill the gap between the case and lead. Allow to cure approximately 12 hours at 60 degrees to 65 degrees Fahrenheit and re-assemble to the elevator structure. (vii) Re-assemble trim weights and check elevator balance, adjust trim weights if necessary to restore CAA-UK approved manufacturer's correct balance. NOTE: EC2216 may be substituted by similar "low flow" epoxy adhesive provided that the gap can be adequately sealed. (2) If no defect is found, reassemble and return the airplane to service. (b) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the documents, referred to herein upon request to Pilatus Britten-Norman Limited, Bembridge, Isle of Wight, England; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on December 8, 1986.
97-01-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Textron Lycoming reciprocating engines. This action requires removal from service of defective piston pins, and replacement with serviceable parts. This amendment is prompted by a report of failure of a piston pin. The actions specified in this AD are intended to prevent piston pin failure, which could result in engine failure.
2004-23-01: The FAA adopts a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes with any Lear Romec RR53710B type or Lear Romec RR53710K fuel booster pump (Pilatus part number 968.84.11.401; 968.84.11.403; or 968.84.11.404) installed. This AD requires you to check the airplane logbook to determine whether any installed fuel booster pump has been modified with spiral wrap to protect the wire leads and has the suffix letter "B" added to the serial number of the fuel booster pump identification plate. If any installed fuel booster pump has not been modified, you are required to inspect any installed fuel booster pump wire lead for defects; if defects are found, replace the fuel booster pump with a modified fuel booster pump with spiral wrap that protects the wire leads; or if no defects are found, install spiral wrap to protect any wire leads and add the suffix letter "B" to the serial number of the fuel booster pump identification plate. The pilot is allowed to do the logbook check. If the pilot can positively determine that the fuel booster pump wire leads with spiral wrap are installed following the service information and that the suffix letter "B" is included in the serial number of the fuel booster pump identification plate, no further action is required. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct any defects in the leads of any fuel booster pump, which could result in electrical arcing. This failure could lead to a fire or explosion in the fuel tank.
85-19-06: 85-19-06 BURKHART GROB: Amendment 39-5131. Applies to model G102 Astir CS Gliders (serial numbers 1001 through 1536 inclusive) certificated in any category. Compliance is required as indicated unless already accomplished. To Prevent failure of the air brake locking levers, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD cut inspection holes in the wing root ribs and inspect the air brake levers (P/Ns 102-4123 and 102- 4124) in accordance with Instruction 1 of Grob-Werke Technical Information TM 306-26, dated March 25, 1985. (b) If solid cast aluminum levers are found, accomplish paragraph (d). (c) If cast aluminum levers with a centerhole are found, accomplish the following: (1) Install inspection windows in the wing and replace page 3 and add page 26a to the flight manual in accordance with Instruction 2 of Grob-Werke Technical Information TM 306-26, dated March 25, 1985, no later than March 31, 1986. (2) Within the next 10 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 10 hours, inspect the airbrake locking levers for cracks in accordance with Instruction 3 of Grob-Werke Technical Information TM 306-26, dated March 25, 1985, until accomplishment of Instruction 4 of Grob-Werke Technical Information TM 306-26, dated March 25, 1985. If cracks are found, replace airbrake locking lever with a serviceable part before further flight. (d) Replace the cast aluminum airbrake levers with the sheet aluminum airbrake levers in accordance with Instruction 4 of Grob-Werke Technical Information TM 306-26, dated March 25, 1985, no later than 3000 hours time in service. NOTE: Dimensions shown in TM 306-26 are in millimeters. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Aircraft Certification Office, AEU-100, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium 09667-1011, telephone 513.38.30. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Brussels Aircraft Certification Office may adjust the compliance time specified in this AD. Grob-Werke GmbH Technical Information TM 306-26 dated March 25, 1985, 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 to Burkhart Grob of America Incorporated, 1070 Navajo Drive, Bluffton Airport Complex, Bluffton, Ohio 45817. These documents also may be examined at the Office of the Regional Counsel, FAA, New England Region, Room 311, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective on September 19, 1985.
2023-04-16: The FAA is superseding Airworthiness Directive (AD) 2020-21- 20, which applied to certain Dassault Aviation Model FALCON 900EX airplanes. AD 2020-21-20 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance requirements and/or airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2020-21-20 and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations; as specified in European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2004-25-05: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747- 200C, 747-200F, 747-300, 747SP, and 747SR series airplanes. This AD requires repetitive inspections to detect cracks and fractures of the strut front spar chord assembly at each strut location, and repair if necessary. This AD is prompted by a report of a fractured front spar chord assembly for strut No. 3, which resulted in the loss of the strut upper link load path. We are issuing this AD to prevent loss of the strut upper link load path and consequent fracture of the diagonal brace, which could result in in-flight separation of the strut and engine from the airplane.