Aircraft-logs.com

Results
2012-10-52: We are adopting a new airworthiness directive (AD) for Cessna 206, 207, and 210 airplanes with Hartzell Engine Technologies (HET) turbochargers, part numbers (P/Ns) 406610-0005 and 406610-9005, installed. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires removing the affected turbochargers from service before further flight. This AD was prompted by a report of an HET turbocharger causing an engine in-flight power rollback. We are issuing this AD to prevent turbocharger bearing seizure, failed turbocharger components, and damage to the airplane.
2021-26-11: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd. & Co KG (RRD) RB211 Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 895-17 model turbofan engines. This AD was prompted by reports of single engine events caused by water contamination, which led to corrosion on the fuel pump that resulted in loss of engine thrust. This AD requires replacing the fuel pump 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.
52-27-02: 52-27-02 DOUGLAS: Applies to Model DC-6 Aircraft (Fuselage Numbers 1 to 166, Inclusive). \n\n\tCompliance required as indicated. \n\n\tThe following inspections and rework pertain to the outboard front spar splice plate, Douglas P/N 4325272 at Station 166 in the area of the inboard nacelle. This special inspection does not apply to splice plates that have been reworked by removing the aft attach tab or to new redesigned splice plates or when Douglas Service Bulletin 532 has been accomplished. \n\n\t1.\tInspection. \n\n\t\tA.\tConduct following inspection as soon as practical but not later than the next 50 hours operation unless already accomplished and continuing thereafter at intervals of regular inspection periods nearest to 500 flying hours from the time of initial inspection until the splice plate is replaced. Using at least an 8-power magnifying glass and/or dye check method or equivalent, make inspections for cracks in the chordwise direction in the area of the milled radius of the aft attach tab of the lower front spar splice plate. Alternate inspection procedures which will provide equivalent safety may be approved. If cracks are found, incorporate the rework of the item 2 before the next scheduled flight. \n\n\t\tB.\tThe above inspection must be continued periodically at intervals not to exceed 400 flying hours on all splice plates that have been reworked as per item 2A until the splice plate is replaced. If a crack is found beyond the stop drill hole prior to the replacement period as indicated in item 2C the splice plate must be replaced before the next scheduled flight. \n\n\t2.\tRework. \n\n\t\tA.\tIf cracks are found less than 1 3/8 inches long, stop drill using a 1/4-inch drill and ream with 17/64-inch reamer. The drill hole center must be located at a distance of 1 3/8 inches from the aft edge of the splice plate in line with the crack. \n\n\t\tB.\tIf cracks are found greater than 1 3/8 inches long, the splice plate must be replaced before the next flight.C.\tSplice plates reworked in accordance with item 2A must be replaced within 1,500 flying hours from time rework is accomplished. \n\n\t(Douglas Service Letter No. 123, dated May 29, 1952, also covers this same subject.)
96-09-10: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Textron Lycoming reciprocating engines, that currently requires replacement of sintered iron impellers in oil pumps. This amendment continues to require replacement of sintered iron impellers, but also requires replacement of aluminum impellers. This amendment is prompted by reports of additional oil pump failures caused by aluminum impellers, which do not have the reliability of the hardened steel impellers. The actions specified by this AD are intended to prevent an oil pump failure due to impeller failure, which could result in an engine failure.
2004-12-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model BAe.125 series 800A, 800A (C-29A), and 800B airplanes; and Model Hawker 800 airplanes, that requires a one-time inspection of certain wire bundles for discrepancies and related corrective action. This action is necessary to find and fix chafing and damage to the wire bundles, which could result in electrical arcing and heat damage in a potential fuel zone and possible fire or explosion in the fuel tank. This action is intended to address the identified unsafe condition.
2021-19-15: The FAA is superseding Airworthiness Directive (AD) 2019-01- 08, which applied to certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. AD 2019-01-08 required modifications for galley mounted attendant seat fittings. This AD was prompted by a report that showed a non-compliance exists on some in-service galley attendant seat fitting installations, and a determination that additional airplanes are subject to the unsafe condition. This AD requires modifications for galley mounted attendant seat fittings. The FAA is issuing this AD to address the unsafe condition on these products.
66-30-02: 66-30-02 BOEING: Amdt. 39-316 Part 39 Federal Register December 13, 1966. Applies to Model 727 Series Airplanes. \n\n\tCompliance required as indicated, unless already accomplished. \n\n\tTo minimize fuselage fire hazards resulting from fuel line ruptures during excessively hard landings involving structural damage, accomplish the following; \n\n\t(a)\tWithin the next 1,500 hours' time in service after the effective date of this AD, remove aluminum fuel lines, P/N 69-16668-1, in the fuselage (three places) located between Body Stations 887 and 1183, and replace with flexible fuel lines, P/N 10-60536-2, in accordance with Boeing Service Bulletin No. 28-26, dated April 27, 1966, or later FAA-approved revision or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(b)\tWithin the next 7,000 hours' time in service after the effective date of this AD, reroute the generator electrical leads (three places) and encase in teflon tubing between Fuselage Stations 850 and 1183 in accordance with Boeing Service Bulletin No. 24-30, revised May 18, 1966, or later FAA-approved revision, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis directive effective January 12, 1967.
2021-26-09: The FAA is adopting a new airworthiness directive (AD) for certain Brantly Helicopters Industries U.S.A. Co., Ltd., Model 305 helicopters and Brantly International, Inc., Model B-2, B-2A, and B-2B helicopters. This AD was prompted by a report of a crack in the tail rotor (T/R) hub. This AD requires repetitive inspections of the T/R hub and depending on the results, removing the T/R hub from service. The FAA is issuing this AD to address the unsafe condition on these products.
77-13-17: 77-13-17 MCCAULEY PROPELLERS: Amendment 39-2943. Applies to the following two-bladed and three-bladed constant speed "Non-Feathering" and "Full Feathering" type McCauley propellers, which were modified by Hoosier Aircraft Accessory, Inc., Indianapolis, Indiana during the period of December 8, 1972 thru June 30, 1975. These propellers are installed on, but not limited to the aircraft models listed below. Constant Speed "Non-Feathering" Propellers Model (Note 1) Hub Serial No. (Note 2) Aircraft Model (Note 3) (A) Two Bladed 2A34C22 () 713477 Maule M-5-220C; 714270 M-4-180C, S, T D2A34C67 () 692205 Cessna R172E, -F, -G, and -H; FR172E, -F, -G, and - H, Maule M-4-210C, -210S, - 210T; M-5-210C (B) Three Bladed D3A32C77 () 661184 Cessna P206A, TP206A, 726348 210F, and T210F D3A32C88 () 724926 Cessna P206, P206A, - B, -C, -D, -E; Cessna TP206A, -B, - C, -D, -E; TU206F (S/N U20602200 and up) Cessna 210F, -G, -H, - J, -K, -L; T210G, -H, -J, -K, and -L Constant Speed "Full-Feathering" Propellers Model (Note 1) Hub Serial No. (Note 2) Aircraft Model (Note 3) (A) Two Bladed D2AF34C30 () 700468 Beech 58, 58A or 701342 2AF34C30 () 705241 705242 D2AF34C52 () 728611 Cessna 310I 730034 730556 2AF34C55 () 682955 Beech 95-55, 95-A55, 684789 95-B55, 95-B55A 697330 95-B55B, 95-C55, 713643 95-C55A, D-55, D- 55A, 726670 E-55, E-55A Series 728131 728141 D2AF34C59 () 642020 Cessna 337; 337A, -B, -C, or 723964 -D, -E, and -F Series 2AF34C59 () Burns BA42 D2AF34C61 () 66394 Cessna 336; 337, 337A, or 675836 -B, -C, -E and -F 2AF34C61 () 683257 Series; T337B, -C, -D, 684839 -E and -F Series; F337E, 686708 F337F 691475 727098 736922 741911 745073 750643 D2AF34C71 () 685300 Cessna 310P, -Q, -R; 694684 T310P, -Q; 320D, -E and340 D2AF34C81 () 651926 Cessna 310J, E310J, 671750 310K, 310L, and 310N 672239 673494 682298 741088 741102 D2AF34C91 () 722029 Cessna T337B, T337C, T337D, T337E and T337F; and FT337E, FT337F (B) Three Bladed 3AF34C74 () 661086TR Cessna 411, 411A 662363TR 692379 3AF32C75 () 702047 Beech 95-C55, 95- C55A, 702051 D55, D55A, E55, and E55A D3AF32C80 () 66986 Cessna 310K, -L, and - N or 661000 Colemill Executive 600 3AF34C80 () 665633 (STC SA518SO - Cessna 738455 310J, -K, -L, -N 738586 Conversion) 744076 3AF32C87 () 68588 Cessna 310P, -Q, -R; 683600 TP310P, -Q, -R; 320D, 683602 -E, -F; 340 685410 Colemill Executive 600 692770 (STC SA518SO Cessna 694218 310I Conversion) 705807 Riley (STC SA1181SW- 710281 Cessna 340 Conversion) 712311 713792 723589 737625 737974 739577 743892 743893744411 746518 748219 3AF34C92 () 682034 Cessna 421, 421A, and -B or 682054 3AF32C92 () 685899 686191 720868 721301 733370 734880 3AF32C93 722256 Cessna 414 722257 Notes: (*) - Denotes suffix letter(s). Some models have one or more suffix letter designations, others have none. (1)&(2) - Propeller model and hub serial numbers are stamped on the side of the propeller hub. The listing of hub serial numbers refers to specific hub serial numbers not series. In the event a spinner is installed, the spinner should be removed to check the model and hub (S/N) designations. The aircraft's records should likewise be checked to endure that the model and hub serial number coincide with the records. In the event an error is noted, the records should be corrected accordingly. Prior to further flight, spinners should be reinstalled where applicable. (3) - If no listing of aircraft serial numbers is indicated, applies to all applicable serial numbers of a particular aircraft model or series. Compliance required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To preclude the possibility of blade actuating pin failures resulting from using an incorrect actuating pin, or improper rework of the ferrules and installation of the blade actuating pins and washers (i.e., a blind actuating pin hole not tapped to the proper depth can cause stripped threads on the ends of the actuating pin resulting in severe stress and may prevent actuating pin from seating properly on the washer), accomplish the following: A. Disassemble the propeller and inspect the blade actuating pins, washers McCauley Service Bulletins No. 99 dated December 8, 1972, No. 99-1 dated December 14, 1972, No. 99-2 dated April 23, 1973, and No. 99-3 dated August 11, 1975, or later Federal Aviation Administration approved revisions. B. Prior to further flight repair or replace as necessary, any improperly installed blade actuating pins, washers and ferrules, and reassemble the propeller in accordance with McCauley Service Bulletins No. 99 dated December 8, 1972, No. 99-1 dated December 14, 1972, No. 99-2 dated April 23, 1973, No. 99-3 dated August 11, 1975, and Service Manuals 710930 and 720415, or later Federal Aviation Administration approved revisions. C. When the above propellers are released for service, compliance with this Airworthiness Directive shall be noted in the Aircraft's Records. D. The Responsible propeller repair station will notify the Federal Aviation Administration, Chief, Engineering and Manufacturing Branch, AGL-210, 2300 East Devon Avenue, Des Plaines, Illinois 60018, by certified mail of the results of these inspections. The disposition of the affected propeller(s) including the blade and hub serial numbers of the propellers (as received and where applicable, as returned to service) must be reported. (Reporting approved by the Office of Management and Budget under OMB No. 04-R-174.) The manufacturer's specifications and procedures identified in this directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by the directive who have not already received these documents from the manufacturer, may obtain copies upon request to McCauley Accessory Division, Cessna Aircraft Corporation, Box 7, Roosevelt Station, Dayton, Ohio 45417. These documents may also be examined at the Great Lakes Regional Office, 2300 East Devon Avenue, Des Plaines, Illinois 60018, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this airworthiness directive which includes incorporated material in full is maintained by the FAA at its Headquarters in Washington, D.C. and the Great Lakes Region. This amendment becomes effective: July 6, 1977.
2004-12-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and A300 B4 series airplanes, that requires modification of the 107VU electronics rack in the avionics compartment to ensure that fluid does not enter the rack. This action is necessary to prevent the loss of electrical power during flight, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.