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76-17-08 R1: 76-17-08 ENSTROM: Amendment 39-2700 as amended by Amendment 39-3043. Applies to Models F-28, F-28A, and 280 helicopters certificated in all categories, except for those helicopters which have the following main rotor shaft gear box serial numbers. 032FS 07-012-74PS 39-002-13PS 041PS 08-001-72S 44-011-76PS 067PS 10-002-72PS 44-019-76PS 070PS 19-024-74PS 53-003-73PS 091 34-029-75PS To detect tool marks, surface irregularities, and cracks which may develop into failure of the Main Rotor Shaft (Enstrom Part Number 28-13104) accomplish the following: A. Before further flight visually inspect the main rotor shaft in the area of the radius beneath the rotor hub shoulder, using an eight power or greater magnifying glass and report to the Enstrom Helicopter Corporation, Menominee County Airport, P.O. Box 277, Menominee, Michigan, Phone 906-863-9971, any evidence of circumferentially disposed tool marks or surface irregularities. B. Before further flight, unless previously accomplished within the last 20 hours time in service or one month, and every 20 hours or one month thereafter, whichever occurs first, inspect the main rotor shaft for cracks in the area of the radius beneath the rotor hub shoulder using a 3-step dye-penetrant method. The inspections are to be performed by maintenance personnel familiar with the dye-penetrant inspection method. C. Within 10 hours time in service or 15 days, whichever occurs first after each dye- penetrant inspection, visually check the main rotor shaft for cracks in the area of the radius beneath the rotor hub shoulder using an eight power or greater magnifying glass. D. Before further flight remove from service any main rotor shaft found to contain cracks or other evidence of damage and replace with an airworthy shaft of the same part number or later FAA approved part number. E. Immediately check in accordance with Paragraph B above any helicopter which develops unusual once-per-rotor-revolution vibration. Such vibrations serve as warning of imminent failure. F. Within the next 200 hours time in service or six months after the effective date of this amendment, whichever occurs first, remove main rotor shaft from service or return gearbox and shaft to Enstrom Helicopter Corporation for modification in accordance with Enstrom Service Directed Bulletin No. 0036. G. Repetitive inspections of paragraphs B and C above may be discontinued after main rotor shaft modification in accordance with Enstrom Service Directed Bulletin No. 0036. 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. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Enstrom Helicopter Corporation, Menominee County Airport, P.O. Box 277, Menominee, Michigan 49858. These documents may also be examined at the FAA Great Lakes Region, Engineering and Manufacturing Branch, AGL-210, 2300 East Devon Avenue, Des Plaines, Illinois. A historical file on this AD which includes the incorporated material in full is also maintained at that office. Amendment 39-2700 superseded Amendment 39-2472 (40 F.R. 59197), AD 75-26-19. Amendment 39-2700 became effective September 1, 1976 and was effective immediately for all recipients of the airmail letters dated August 6, 1976 which contained this amendment. This amendment 39-3043 becomes effective October 4, 1977.
83-08-01 R1: 83-08-01 R1 TRW HARTZELL PROPELLER: Amendment 39-4633. Letter issued April 29, 1983. Applies to all the TRW Hartzell Model HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC- B4TN-3, HC-B4TN-5, HC-B4MN-5, and HC-B5MP-3 turbopropellers. The HC-B( )TN-2, HC- B( )TN-3, and HC-B( )MP-3 propellers are installed on Pratt & Whitney Aircraft of Canada Model PT6A-( ) series engines. The HC-B( )TN-5 and HC-B( )MN-5 series propellers are installed on the AiResearch TPE-331-( ) series engines.\n \n\tCompliance required as indicated, unless already accomplished. To preclude propeller attach bolt failures or improperly secured propellers, accomplish the following:\n\n\tA.\tPrior to further flight, all new propeller installations and serviceable propellers which are being reinstalled must be installed as follows: \n\n\t\t(1)\tInstall the propeller oil seal to the engine flange after ensuring that the engine and propeller flanges are clean.\n \n\t\t(2)\tCarefully install propeller on the engine flange ensuring that complete and true contact is established.\n\n\t\t(3)\tApply MIL-T-5544 Petrolated Graphite or TRW Hartzell Lubricant P/N A3338 to bolt threads and bolt washer surfaces (and remainder of bolt if desired).\n \n\t\t(4)\tInstall eight new B-3339 bolts and eight new A-2048-2 washers through engine flange into propeller flange.\n \n\t\t(5)\tTorque all bolts, with a torque wrench and an appropriate adapter, to 40 ft.-lbs. and then to 80 ft.-lbs. following torque sequence "A" (shown to below). Final torque all bolts using "B" sequence (shown below) to 100 to 105 ft.-lbs. Safety all bolts in an FAA approved manner.\n\n\n\n\n \n\tNOTE: TRW Hartzell Instructions No. 140 dated March 15, 1982, also pertains to this subject.\n \n\tB.\tWithin the next 300 hours time in service after the effective date of this AD, accomplish the following on all applicable turbopropeller installations presently using P/N A- 2047 propeller attach bolts: \n\n\t\t(1)\tCheck the torque, with a torque wrench and an appropriate adapter,of all eight propeller attach bolts (with washers installed). Torque should be 100 to 125 ft.-lbs. with dry threads. (Caution: Do not use any lubricant with the A-2047 bolts. Safety all bolts in an FAA approved manner.)\n \n\t\t(2)\tIf the torque of any 1 of the bolts is found to be less than 100 ft.-lbs., remove all 8 bolts and washers and replace with new (B-3339) bolts and new (A-2048-2) washers in accordance with paragraphs A (1) through (5) herein. (Caution: Do not use an intermix of A-2047 and B-3339 bolts in the same installation.) NOTE: The A-2047 bolt has the letter "H" stamped inside a triangle on the bolt. The B-3339 bolt has the part number stamped inside the cupped head.\n \n\tC.\tUpon request of the operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018.\n \n\tThis amendment supersedes Amendment 39-3290 (43 FR 42731), AD78-18-01.\n \n\tAmendment 39-4633 became effective April 28, 1983.\n\n\tThis amendment becomes effective upon receipt.
98-05-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires replacement of electrical relays 15KF and 16KF, which control the auxiliary propeller control feathering system, with relays having increased load capacity. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the auxiliary propeller control feathering system, which, in the event of an engine failure combined with failure of the primary propeller pitch control, could result in the inability to feather the propeller, and consequent reduced controllability of the airplane.
98-21-03: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that requires replacement of the existing load limitation labels located in the main baggage compartment with new reduced load limitation labels. This amendment also provides for optional modification of the internal access door of the main baggage compartment, which, if accomplished, terminates the requirement for reduced load limitations. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the internal access door latches of the main baggage compartment in the event of an emergency landing, which could delay or impede passenger evacuation due to baggage spilling into the aisle and blocking the emergency exit door.
70-16-02: 70-16-02 DOWTY ROTOL: Amendment 39-1015 as amended by Amendment 39-1503. Applies to all Dowty Rotol propellers, installed on but not necessarily limited to the following airplanes: Fairchild Series F-27 and FH-227, Armstrong Whitworth AW 650, Grumman G-159, Viscount 700 and 810 series, Nihon YS-11, and Convair 240, 340, 440 turbopropeller conversions. Compliance is required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished. (a) Inspect the blade pitch change operating link and eyebolt fork assembly for - (1) Seizure (the link and eyebolt are seized if the torque required to move the link is 300 inch pounds or more); and (2) Cadmium plating on the mating surfaces between the operating link and eyebolt fork and the holes through the eyebolt fork and the operating link. (b) If the link and eyebolt fork are not seized and have not been cadmium plated, they may remain in service. (c) If the linkand eyebolt fork are not seized but cadmium plating is found in the prohibited areas, remove the plating by means of wet or dry silicon carbide paper, fine or medium grade, and conduct a magnetic crack test. If no cracks are found, the assembly may remain in service until the next propeller overhaul for air carrier airplanes and airplanes under a continuous maintenance program or for 3,300 hours' time in service after the effective date of this AD for all other airplanes. At the next propeller overhaul for air carrier airplanes and airplanes under a continuous maintenance program, or within 3,300 hours' time in service after the effective date of this AD for all other airplanes, heat treat the links and eyebolt forks found to have been cadmium plated in order to remove embrittlement in accordance with Dowty Rotol Service Bulletin No. 61- 754, dated June 12, 1970, or later ARB-approved issue or an FAA-approved equivalent. (d) If the link and eyebolt fork are seized, remove the linkand eyebolt fork from service and replace them with an assembly having a part number approved for that model propeller that has not been cadmium plated in the prohibited areas. (e) If the link or eyebolt fork are found to be cracked during the inspection in paragraph (c), remove the cracked part from service and replace it with a part having a part number approved for that model propeller that has not been cadmium plated. (f) The inspection required by paragraph (a) need not be performed and the propeller may remain in service if - (1) The operator can show that no cadmium plating exists in the prohibited areas of that propeller; or (2) It is a new propeller that has never been overhauled. Amendment 39-1015 became effective July 25, 1970. This Amendment 39-1503 becomes effective August 21, 1972.
2019-20-05: The FAA is superseding airworthiness directive (AD) 2018-15-01 for certain Rolls-Royce plc (RR) Trent 1000-A, Trent 1000-C, Trent 1000-D, Trent 1000-E, Trent 1000-G, Trent 1000-H, Trent 1000-A2, Trent 1000-C2, Trent 1000-D2, Trent 1000-E2, Trent 1000-G2, Trent 1000-H2, Trent 1000-J2, Trent 1000-K2, and Trent 1000-L2 model turbofan engines. AD 2018-15-01 required certain engines susceptible to intermediate- pressure turbine (IPT) blade failure not be installed on an airplane together with other engines with IPT blades of the same cyclic life. This AD requires removal of the IPT blade set at lower cyclic life limits and replacing it with a blade set eligible for installation. This AD also expands the applicability to include additional Trent 1000 turbofan engine models. This AD was prompted by the determination that certain IPT blades are susceptible to shank corrosion which leads to cracking and possible blade separation. The FAA is issuing this AD to address the unsafe condition on these products.
98-18-16: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, -212, and -231 series airplanes, that currently requires reinforcement of the tail section of the fuselage at frames 68 and 69. This amendment adds a requirement for reinforcement of the tail section of the fuselage at frames 65 to 67. This action also revises the applicability of the existing AD. This amendment is prompted by reports indicating that the tail section has struck the runway during takeoffs and landings. The actions specified by this AD are intended to prevent structural damage to the tail section when it strikes the runway, which could result in depressurization of the fuselage during flight.
2007-11-11: The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A318, A319, A320, and A321 airplanes. That AD currently requires a one-time inspection to determine the serial number of both main landing gear (MLG) sliding tubes, repetitive detailed inspections for cracking of the affected MLG sliding tubes, and corrective actions if necessary. This new AD retains these inspections and adds new repetitive inspections for cracking of the MLG sliding tubes. This AD also requires eventual replacement of both MLG shock absorbers. Doing this replacement terminates the repetitive inspection requirements of this AD. This AD results from a determination that additional inspections and mandatory replacement of the MLG shock absorbers are necessary. We are issuing this AD to detect and correct cracking in an MLG sliding tube, which could result in failure of the sliding tube, loss of one axle, and consequent reduced controllability of the airplane.DATES: This AD becomes effective June 29, 2007. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of June 29, 2007. On June 23, 2004, (69 FR 31867, June 8, 2004), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex A320-32A1273, Revision 01, dated May 6, 2004.
98-01-08: 98-01-08 TELEDYNE CONTINENTAL MOTORS with STC SE8594SW: Priority Letter issued on December 23, 1997. Docket No. 97-ANE-48-AD. Applicability: Teledyne Continental Motors (TCM) IO-520-A, -B, -BA, -C, -CB, -D, -E, -F, -K, -L, -M, -MB, -J; TSIO-520-A, -B, -D, -E, -F, -G, -H, -J, -K, -L, -M, -N, -P, -R, -T, -U, -UB, -AF, -CE, -VB, -WB, -NB, -LB, -KB, -JB, -EB, -DB, -BB; O-470-B, -G, -K, -L, -M, -P, -R, -S, -U; IO-470-C, -D, -E, -F, -G, -H, -L, -M, -N, -P, -R, -S, -U, -V; and IO-550-B, -C, and -G series reciprocating engines, with Performance Engineering exhaust roller rocker arms, Part Number (P/N) PE92E, installed, in accordance with Supplemental Type Certificate (STC) SE8594SW. These engines are installed on but not limited to Cessna 180, 182, 185, 206, 207, 210, 310, 335, 340, 401, 402, 414; Raytheon (Beech) 33, 35, 36, 55, 58; Bellanca 17-30; New Piper PA-46; Fletcher FU-24A aircraft. Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent exhaust roller rocker arm failure, which can result in bent push rods, ruptured rocker arm covers, loss of engine oil, engine power loss and roughness, and possible engine failure, accomplish the following: (a) Within 25 hours time in service after the effective date of this AD, remove from service all Performance Engineering exhaust roller rocker arms, P/N PE92E, and replace with serviceable parts, as follows: (1) For IO-520, TSIO-520, O-470, IO-470, and all IO-550 series engines except the IO-550-G, replace with serviceable TCM exhaust roller rocker arms, P/N 652130. (2) For IO-550-G series engines, replace with serviceable TCM exhaust roller rocker arms, P/N 652966. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Special Certification Office. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Special Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Special Certification Office. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (d) Priority Letter AD 98-01-08, issued December 23, 1997, becomes effective upon receipt.
98-20-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires relocation of the engine/master 1 relay from relay box 103VU to shelf 95VU in the avionics bay. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent a simultaneous cutoff of the fuel supply to both engines, which could result in a loss of engine power and consequent reduced controllability of the airplane.