Results
71-16-01: 71-16-01 de HAVILLAND AIRCRAFT of CANADA LTD: Amdt. 39-1250. Applies to de Havilland Type DHC-6 Aircraft, Serial Numbers 1 through 299, inclusive. Compliance required, unless already accomplished, within 30 days after the effective date of this AD for aircraft which have been in service for 12 months or more from the date of first flight. For aircraft which have been in service less than 12 months, compliance required within 30 days after the accumulation of 12 months' service. To preclude the possibility of engine flameout due to fuel starvation in the event of separation of the flapper valve seal in fuel cells No. 4 and No. 5, replace No. 4 and No. 5 flapper valve assemblies, P/N C6PF1026-3, with new like parts and repeat replacement thereafter at 12- month intervals until such time as DHC modifications 6/1406 is incorporated in accordance with instructions contained in DHC Service Bulletin No. 6/269, dated February 19, 1971, or an equivalent modification approved bythe Chief, Engineering & Manufacturing Branch, Federal Aviation Administration, Eastern Region. This amendment is effective August 3, 1971.
2003-11-24: This amendment adopts a new airworthiness directive (AD) that is applicable to all Dornier Model 328-100 series airplanes. This action requires installation of retainers instead of washers in the upper and lower torsion bars of the rudder tab. This action is necessary to prevent a spring tab torsion bar from slipping through its retaining adapters, which could result in a loose spring tab; the loss of both tension springs could allow the spring tab to flutter and result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
48-13-01: 48-13-01 BEECH: Applies to All D18S, D18C Airplanes Equipped With Pilot's Reclining Seats and Having the Generator Control Box Mounted on Bulkhead No. 5. To be accomplished not later than July 1, 1948. To prevent a short circuit between the hot terminal of the generator control box and bulkhead No. 5, rivet a 0.016 phenolic sheet 13/4 x 3 inches between the bulkhead web and the first horizontal angle immediately above the generator control box. The sheet should extend downward from the angle to the web cutout and provide positive insulation between the web and the hot post of the generator control box. If a phenolic strip has previously been installed at this point, an additional strip will not be necessary. (Beech Service Letter No. D18-23 covers this same subject.)
2003-16-18: The FAA is adopting a new airworthiness directive (AD) that applies to Rolls-Royce plc (RR) RB211 Trent 875-17, Trent 877-17, Trent 884-17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan engines with intermediate pressure (IP) turbine discs, part numbers (P/Ns) FK21117 and FK33083 installed. This AD requires removal from service of these IP turbine discs based on newly established reduced turbine disc life limits. This AD is prompted by reports of two IP turbine blade release incidents as a result of dust caps separating from the blades and subsequent improved modeling analysis. We are issuing this AD to prevent uncontained IP turbine disc failure and damage to the airplane.
71-06-05: 71-06-05 ROLLS-ROYCE: Amdt. 39-1172. Applies to Rolls-Royce Dart engine models 506, 510, 511, 511-7E, 514, and 514-7 installed on, but not necessarily limited to British Aircraft Corporation Viscount 744 and 745D; Fairchild F-27 and F-27B; and Fokker F-27 airplanes. Compliance is required as indicated, unless already accomplished. (a) For all engines installed on airplanes having an average daily utilization rate of more than three hours flight time per day, comply with paragraph (c) within the next 4,000 hours' time in service after the effective date of this AD, or at the next engine overhaul, whichever occurs first. (b) For all engines installed on airplanes having an average daily utilization rate of three hours flight time or less per day, comply with paragraph (c) within the next 2,000 hours' time in service after the effective date of this AD, or at the next engine overhaul, whichever occurs first. (c) Replace Rolls-Royce turbine disc retaining bolt P/N RK 33044 with P/N RK 43376 in accordance with Rolls-Royce Dart Aero Engine Service Bulletin Number Da 72-347, Revision 2, dated July 24, 1970, or later ARB-approved revision, or an FAA-approved equivalent. (d) For the purpose of complying with this AD, the average daily utilization rate shall be determined on the basis of the average daily utilization rate for the 12-month period immediately preceding the effective date of this AD. This amendment becomes effective April 12, 1971.
2003-16-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes, and Airbus Model A310 series airplanes. This AD requires replacement of Honeywell inertial reference units (IRU) with new or modified Honeywell IRUs. For certain airplanes, this proposal also would require replacement of Litton IRUs, mode selector units (MSU), and an inertial sensor display unit (ISDU) with new Honeywell IRUs, MSUs, and a new ISDU. This action is necessary to prevent loss of positioning data and a display of incorrect attitude data, which could compromise the ability of the flightcrew to maintain the safe flight and landing of the airplane. This action is intended to address the identified unsafe condition.
2003-11-23: The FAA is adopting a new airworthiness directive (AD) for certain IAE V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 turbofan engines. This AD requires initial and repetitive inspections of the master magnetic chip detector (MCD) or the No. 1, 2, 3 bearing chamber MCD. This AD is prompted by reports of No. 3 bearing failures that resulted in in-flight engine shutdowns (IFSDs) and significant smoke in the cockpit and cabin. The actions specified in this AD are intended to prevent failure of the No. 3 bearing, which could result in IFSDs and smoke in the cockpit and cabin.
2024-24-02: The FAA is adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A. (Safran) Model ARRIUS 2F engines. This AD was prompted by a report of an uncommanded in-flight shut-down (IFSD) of a Safran Model ARRIUS 2F engine, followed by an investigation that revealed the IFSD was due to a missing lubricating and balancing groove on one of the bearings of the fuel control unit (FCU) fuel pump related to a non-conforming manufacturing process. This AD requires removal of the affected fuel pump from service and replacement with a serviceable part, 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.
2016-07-11: We are adopting a new airworthiness directive (AD) for all Weatherly Aircraft Company Models 201, 201A, 201B, 201C, 620, 620A, 620B, 620B-TG, and 620TP airplanes. This AD requires visually inspecting the center and outer wing front spar lower hinge fittings for cracks and corrosion [[Page 18462]] and taking all necessary corrective actions. This AD also requires sending the inspection results to the FAA. This AD was prompted by a report of cracks found on the center wing front spar lower hinge fitting. We are issuing this AD to correct the unsafe condition on these products.
70-10-06: 70-10-06 CESSNA: Amendment 39-990 as amended by Amendment 39-1008. Applies to Models 172I (Serial Numbers 17256513 through 17257161) and 172K (Serial Numbers 17256493, and 17257162 through 17259043) Airplanes. Compliance: Required as indicated, unless already accomplished. To prevent the loss of engine oil caused by failure of the metal oil pressure instrument line, accomplish the following: Within 50 hours' time in service from June 1, 1970, but by no later than June 30, 1970, replace the metal oil pressure instrument line between the engine and the firewall with a flexible hose assembly in accordance with the instructions contained in Cessna Service Letter No. SE70-10, dated May 5, 1970, or Cessna Service Letter No. SE70-10, Supplement No. 1, dated June 9, 1970, or any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Amendment 39-990 effective May 19, 1970. This amendment becomes effective upon publication in the FEDERAL REGISTER.
2008-26-06: The FAA is superseding emergency airworthiness directive (AD) 2008-19-51 that we sent previously to all known U.S. owners and operators of RRC AE 3007A series turbofan engines. That AD requires performing initial and repetitive eddy current inspections (ECIs) on the high-pressure turbine (HPT) stage 2 wheel for cracks. This AD continues to require those same inspections, but revises the compliance schedule for the initial inspection and specifies the affected HPT stage 2 wheels by part number (P/N). This AD results from reports of cracked HPT stage 2 wheels. We are issuing this AD to detect cracks in the HPT stage 2 wheel, which could result in a possible uncontained failure of the HPT stage 2 wheel and damage to the airplane.
2016-07-06: We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes. This AD was prompted by reports of cracking of the main fitting of the nose landing gear (NLG) and a determination that a new safe-life limitation for affected NLG main fittings has not been mandated. This AD requires replacing affected NLG main fittings that have exceeded the safe-life limitation with a new or serviceable fitting. We are issuing this AD to prevent collapse of the NLG, which if not corrected, could lead to degradation of direction control on the ground or an un-commanded turn to the left, and a consequent loss of control of the airplane on the ground, possibly resulting in damage to the airplane and injury to occupants.
54-25-02: 54-25-02 WRIGHT: Applies to All Models 975C18CB1, 972TC18DA1, and 972TC18DA2 Engines. Compliance required as indicated. I. Compliance required by November 1, 1955. To alleviate front intermediate cam drive gear failures and associated possible engine overspeeding, the following intermediate cam drive gears must be removed from the front cam drive gear train: P/N's 138608, 138608 N, 171385, 171238, or 171387. These gears may still be used in the rear cam drive configuration. Intermediate cam drive gears incorporating increased tooth width and thick hubs must be used in the front cam drive configuration. The following gears comply with this requirement: P/N's 171347, 171348, or 171994. II. Compliance required at next and each subsequent overhaul. To insure proper assembly of cam drive gear configurations, the following assembly instructions must be followed and applicable measurements recorded on engine build up sheets: TC18DA Overhaul Manual:Section V. Instruction 17. Section VIII. Instruction No. 2 plus referenced Table of Limits fits including Reference No. 238. (Wright Aeronautical Division Service Bulletins Numbers C18C-83 and TC18-92 cover these same subjects.)
2024-19-15: The FAA is superseding Airworthiness Directive (AD) 2023-13- 11, which applied to certain AVOX Systems Inc. (formerly Scott Aviation) oxygen cylinder and valve assemblies, and oxygen valve assemblies, installed on but not limited to various transport airplanes. AD 2023-13-11 required inspecting the oxygen valve assemblies, and oxygen cylinder and valve assemblies, to determine the serial number of the valve, cylinder, and entire assembly; inspecting certain assemblies and parts for correct spacing of the gap between the bottom of the packing retainer and top of the valve body on the assemblies, and replacing assemblies having unacceptable gaps. AD 2023- 13-11 also limited the installation of affected parts and required reporting inspection results and returning certain assemblies to the manufacturer. This AD was prompted by the determination that additional assemblies and parts are subject to the unsafe condition. This AD requires the actions specified in AD 2023-13-11 and expands the list of affected assemblies and parts. The FAA is issuing this AD to address the unsafe condition on these products.
2016-07-02: We are adopting a new airworthiness directive (AD) for certain Honeywell International Inc. (Honeywell) TFE731-4, -4R, -5AR, -5BR, and -5R turbofan engines. This AD was prompted by a report of certain interstage turbine transition (ITT) ducts failing to meet containment capability requirements. This AD requires replacing certain ITT ducts. We are issuing this AD to prevent failure of the ITT duct, which could lead to an uncontained part release, damage to the engine, and damage to the airplane.
2024-18-06: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-2A12 airplanes. This AD was prompted by reports that the pivot door pressure seals on the thrust reverser fixed structure were found disbonded or missing on several airplanes. This AD requires inspecting the pivot door pressure seals and accomplishing applicable corrective actions. This AD also requires a functional test of the thrust reversers. The FAA is issuing this AD to address the unsafe condition on these products.
2003-11-10: This amendment adopts a new airworthiness directive (AD), that is applicable to Turbomeca S.A. Arrius -2F turboshaft engines with certain serial number (SN) Fuel Control Units (FCUs). This amendment requires adjusting the FCU maximum fuel flow mechanical stop position to a higher fuel flow setting. This amendment is prompted by an FCU discovered to have a maximum fuel flow limit adjusted below the maximum required setting. The actions specified by this AD are intended to prevent reduced maximum available power during takeoff, landing, or an emergency, which could significantly affect helicopter performance and result in loss of the helicopter.
2001-20-13: This amendment adopts a new airworthiness directive (AD), that is applicable to certain models of Pratt & Whitney PW4000 series turbofan engines. This amendment requires operators to perform initial and repetitive inspections for cracking of high pressure compressor (HPC) front drum rotors based on cycle usage. This amendment also requires the removal from service of any cracked HPC front drum rotors. This amendment is prompted by reports that 11 HPC drum rotors have been found cracked on the spacer surface between the sixth and seventh stage disks. The actions specified by this AD are intended to detect premature cracking of the HPC drum rotor that could result in an uncontained engine failure and damage to the airplane.
2016-06-11: We are adopting a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, and CN-235-300 airplanes. This AD was prompted by a report of cracks on the lugs of the inboard and outboard control rod fittings of the right hand (RH) and left hand (LH) side ailerons. This AD requires a one-time non-destructive test (NDT) inspection of the inboard and outboard control rod fittings of the RH and LH side ailerons for cracks and corrosion, and repair if necessary. We are issuing this AD to detect and correct cracks and corrosion on the lugs of the inboard and outboard control rod fittings of the RH and LH side ailerons, which could lead to reduced controllability of the airplane.
53-01-02: 53-01-02 BEECH: Applies to Models 35, A35, B35 and C35 Airplanes, Serial Numbers D-1 Through D-2900, Equipped With Beech 35-921171 or 35-924065 Fuel Selector Valve -Hand Pump Units. Compliance required as soon as possible but not later than June 1, 1953. To prevent binding or stiff operation of the fuel selector valve, accomplish inspections and rework in accordance with Beech service instructions as follows: (1) Install AN 934-6 "O" ring on indexing ball plug in place of lead washer, Beech P/N 105090-L-067-6-020, (2) Provide 1/32-inch clearance between selector valve cone and index ball retaining plug, (3) Install Beech 35-921217 spacer beneath fuel selector valve cone to restrict possible vertical cone movement to 1/32 inch. The 35-924065 and 35-921171 fuel units are identifiable by the feature permitting the fuel tank selector valve and hand emergency fuel pump to be operated by the same handle. (Beech Service Bulletin 35-22, A35-16, B35-9, C35-7, dated October 1, 1952, covers this same subject.)
2016-06-12: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300 series airplanes; and all Model A340- 200, -300, -500, and -600 series airplanes. This AD was prompted by reports that the potable water service panel access door was lost during flight. This AD requires modifying affected potable water service panel access doors. We are issuing this AD to prevent failure of the latching mechanism of the potable water service panel access door, which could result in the loss of the potable water service panel access door during flight, and resultant damage to the airplane (e.g., damage to the trimmable horizontal stabilizer) that could cause loss of control of the airplane.
2003-11-08: This amendment adopts a new airworthiness directive (AD) that is applicable to Turbomeca S.A. Arriel -1B, -1D, and -1D1 series turboshaft engines. This amendment requires replacement of modules M03 modified to TU 204 standard with modules M03 not modified to TU 204 standard. This amendment is prompted by several reports of 2nd stage gas generator turbine blade failures. The actions specified by this AD are intended to prevent 2nd stage gas generator turbine blade failure resulting in uncommanded engine in-flight shutdown.
2003-09-02: This amendment adopts a new airworthiness directive (AD), that is applicable to certain serial number (SN) Pratt and Whitney (PW) models PW4164, PW4168, and PW4168A turbofan engines. This amendment requires operators to initially and repetitively borescope-inspect 14th and 15th stage rubstrips located on the 13th and 14th stage stator set for wear. This amendment is prompted by reports of high pressure compressor (HPC) surges during the takeoff phase of flight that have been attributed to increased stage 14 and stage 15 HPC blade tip clearances caused by excessive wear on the HPC inner rear case rear hook. The actions specified by this AD are intended to prevent engine power loss during takeoff due to HPC surge.
2024-25-06: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, - 114, -115, -131, -132, -133, -151N, -153N, and -171N airplanes; Model A320 series airplanes; and Model A321 series airplanes. This AD was prompted by reports of jamming of, or inability to open, the main landing gear (MLG) door during maintenance operations. This AD requires repetitive inspection of the MLG doors, and, depending on findings, accomplishment of applicable corrective actions, and prohibits the installation of affected parts 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.
2016-06-09: We are adopting a new airworthiness directive (AD) for certain Turbomeca S.A. Makila 2A and 2A1 turboshaft engines. This AD requires tightening the nut attaching the swivel union to the engine power turbine module M04. This AD was prompted by two occurrences of commanded in-flight shutdown following low oil pressure warning. We are issuing this AD to prevent loosening of the nut and oil leakage from the low-pressure oil system, which could lead to in-flight shutdown of the engine and forced landing.