Results
58-04-02: 58-04-02 HARTZELL: Applies to All HC-93Z20-2C and -2B Propellers. The -2C Propellers Are Installed on All Beech E50 and F50 Aircraft, and -2B Propellers Are Installed on Some Cessna T-50 With Lycoming R-680 Engines and on Mansdorf Conversion of Grumman G- 44 With Lycoming R-680 Engines (STC SA4-2). Compliance required prior to next flight for propellers with hub Serial Numbers 100A through 361A and above. The recent failure of an A-1307 split ring, which the records show had less than 180 hours' operating time, permitted the propeller blade to leave the hub. In order to minimize the possibility of the occurrence of this type of serious failure, the present split ring must be replaced with a strengthened split ring. Accordingly, replace A-1307 split ring with A-1331 split ring. This also requires replacing A-1303 bearing with A-1303A bearing. Modified propellers should be stamped HC-93Z20-2B1 or -2C1. New propellers so stamped will incorporate modified split rings and bearings. (Hartzell Service Bulletin No. 55 covers this same subject.)
2000-04-22: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc (RR) RB211-524G2-T-19; RB211-524G3-T-19; RB211-524H2-T-19; RB211 Trent 768-60; and RB211 Trent 772-60 turbofan engines. This AD requires the replacement of the joint bolt assemblies that secure the high-pressure compressor (HPC) to the high-pressure turbine (HPT) of the RB211-524 series and Trent 768 and 772 series turbofan engines. This amendment is prompted by six incidents of bolt failure, one of which resulted in a damaged stage 6 HPC disk following an impact with a separated bolt head. The actions specified in this AD are intended to prevent failure of the HPC-to-HPT joint bolt assemblies, which could result in a cracked stage 6 HPC disk, possible uncontained engine failure, and damage to the airplane.
2020-22-09: The FAA is superseding Airworthiness Directive (AD) 2001-16- 13, which applied to certain Airbus SAS Model A330 series airplanes. AD 2001-16-13 required a roto-test inspection of fastener holes of certain fuselage joints for cracks, reinforcement of the fuselage between certain frames, and, if necessary, a high frequency eddy current (HFEC) inspection and repair. As published, the applicability of AD 2001-16-13 inadvertently identified the model designations as serial numbers. This document corrects that error. This new AD requires a roto-test inspection of fastener holes of certain fuselage joints for cracks, reinforcement of the fuselage, and, if necessary, an HFEC inspection and repair. The FAA is issuing this AD to address the unsafe condition on these products.
2020-22-14: The FAA is superseding Airworthiness Directive (AD) 2018-07-16 for all Austro Engine GmbH model E4 and E4P diesel piston engines. AD 2018-07-16 required initial and repetitive replacement of the waste gate controller and the control rod circlip. This AD retains the requirements of AD 2018-07-16 and requires engine modification by installing a waste gate control-rod fail-safe bridge and new spring- loaded circlip that terminates the initial and repetitive replacement requirements of AD 2018-07-16. This AD was prompted by the development of a modification of the waste gate control rod by adding a fail-safe bridge and spring-loaded circlip. The FAA is issuing this AD to address the unsafe condition on these products.
2018-11-08: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200 and -300 series airplanes. This AD was prompted by a report of two cracks at a certain frame inner chord. This AD requires a detailed inspection for any material review board (MRB) filler installed in the area from the frame web to the stub-beam fitting at certain stations to determine if the filler extends above the frame-to-stub-beam joint, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
66-07-05: 66-07-05 MOONEY: Amdt. 39-201, Part 39, Federal Register February 24, 1966. Applies to Models M20C, Serial Numbers 2663, 2808, 2816, 2825, 2863, 2913, 2920, 2930, 2945, 2957, 2960, 2961, 2969, 2971, 2995, 2998, 2999, 3002, 3008, 3018, 3019, 3021, 3040, 3050, 3056, 3065, 3084, 3086, 3136, 3146; M20D; M20E, Serial Numbers 309, 431, 461, 494, 528, 529, 536, 538, 544, 545, 551, 553, 554, 558, 571, 573, 577, 579, 580, 582, 584, 586, 587, 589, 599, 602, 604, 606, 614, 615, 620, 625, 627, 636, 637, 639, 641, 646, 650, 652, 653, 654, 657, 658, 666, 668, 669, 675, 677, 686, 690, 694, 711, 718, 720, 721, 726, 730, 737, 744, 747, 751, 752, 756, 758, 761, 772, 781, 782, 785, 787, 809, 812, 813; Airplanes Equipped with Mooney Aircraft Company Electrically Actuated Landing Gear. Compliance required within the next 100 hours' time in service or at the next periodic inspection, whichever comes first, after the effective date of this AD, unless already accomplished. To prevent further instancesof inoperative aural gear warning, modify electric gear warning wiring system in accordance with Mooney Aircraft Service Letter No. 20-130, dated September 29, 1965, or later FAA-approved revision. This directive effective March 26, 1966.
2006-10-01: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, that currently requires installation of protective tape on the fire and overheat control unit located in the flight compartment. This amendment requires the installation of protective tape and adds repetitive inspections of the condition of the protective tape and related corrective action. This amendment also mandates eventual replacement of the existing fire and overheat control unit with a modified unit, which ends the repetitive inspections. Additionally, this amendment adds airplanes to the applicability in the existing AD. The actions specified by this AD are intended to prevent fluid contamination inside the fire and overheat control unit, which could result in a false fire alarm and consequent emergency landing. This action is intended to address the identified unsafe condition.
71-17-05: 71-17-05 BRANTLY ROTORCRAFT: Amdt. 39-1267 as amended by Amendment 39- 1339. Applies to B-2, B-2A, and B-2B type rotorcraft certified in all categories. Compliance required within the next 10 hours time in service after the effective date of this airworthiness directive and every 50 hours time in service thereafter. To preclude the possibility of impairing the structural integrity of the main rotor mast P/N 104-1, due to corrosion, accomplish the following: a. Remove mast plug P/N 151-18. b. Visually inspect the inner bore surface over the entire length of main rotor mast for presence of rust or corrosion using a light and mirror. The presence of any rust or corrosion which cannot be removed with a lint free cloth is cause for removal of the transmission assembly. c. Prior to reinstallation or replacement, accomplish the 1200 hour interval inspection in accordance with Brantly Maintenance Manual, Section 1.8.7. d. If the main rotor mast is free or can be freed of rust or corrosion following the inspection noted in paragraph (b), apply a thin film of Spec. Mil.-C-6925C preservative type lubricating oil to the entire length of the inner bore surface. Reinstall the mast plug with a new "O" ring packing P/N AN 6227-62. Install the plug and retain it in place with the same clevis pin, P/N AN 393-11 that retains hub retaining nut, P/N 150-1. Secure the clevis pin by installing washer, P/N AN960-10L and cotter pin P/N AN-380-2-1. e. Safety wire bolt, P/N 151-8 to hub retaining nut. f. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, Chief, Engineering & Manufacturing Branch, FAA, Eastern Region, may adjust the repetitive inspection interval specified in this airworthiness directive. Equivalent inspections must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Amendment 39-1267 was effective August 19, 1971. This amendment 39-1339is effective November 26, 1971
2000-05-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757-200, -200PF, and -200CB series airplanes, that currently requires repetitive inspections of the engine thrust control cable system to detect discrepancies of the wire rope, fittings, and pulleys; and replacement, if necessary. That AD also requires a one-time inspection to determine the part number of certain pulleys, and replacement of existing pulleys with new pulleys, if necessary; and modification of the engine thrust control cable installation. This new action corrects a certain part number. This AD is prompted by reports of failure of certain engine thrust control cables. The actions specified by this AD are intended to prevent failure of certain engine thrust control cables, which could result in a severe asymmetric thrust condition during landing, and consequent reduced controllability of the airplane.
2018-11-09: We are superseding Airworthiness Directive (AD) 2014-02-01, which applied to certain Bombardier, Inc., Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), Model CL-600-2D15 (Regional Jet Series 705), and Model CL-600-2D24 (Regional Jet Series 900) airplanes. AD 2014-02-01 required repetitive inspections of the rudder travel limiter (RTL) return springs and primary actuator, and corrective actions if necessary; and replacement of certain RTL return springs. This AD requires an inspection of the RTL return springs for signs of chafing; an inspection of the casing of the primary actuator for signs of chafing or missing paint; replacement of the RTL return springs; and an inspection of the lugs of the RTL limiter arm assembly for cracks, and modification or replacement, as applicable; and applicable corrective actions. This AD also adds airplanes to the applicability. This AD was prompted by reports that when installing the RTL return springs, the RTL limiter arm assembly lug(s) can become deformed. We are issuing this AD to address the unsafe condition on these products.