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2000-08-09: This amendment adopts a new airworthiness directive (AD), applicable to Robinson Helicopter Company (RHC) Model R22 helicopters. This action requires replacing certain serial number sprag clutches with an airworthy sprag clutch as specified in this AD. This amendment is prompted by several reports of clutch assemblies with cracked or fractured sprag ends. The actions specified by this AD are intended to prevent a sprag clutch failure, loss of main rotor RPM during autorotation, and subsequent loss of control of the helicopter.
2015-03-06: We are superseding Airworthiness Directive (AD) 2007-22-10 for all Airbus Model A330-200, A330-300, A340-200, A340-300, A340-500, and A340-600 series airplanes. AD 2007-22-10 required repetitive inspections of the left-hand and right-hand wing main landing gear (MLG) rib 6 aft bearing lugs (forward and aft) to detect any cracks on the two lugs, and replacement if necessary. Since we issued AD 2007-22- 10, we have received reports of additional cracking of the MLG rib 6 aft bearing forward lug. This new AD expands the applicability and reduces certain compliance times. We are issuing this AD to detect and correct cracking of the MLG rib 6 aft bearing lugs, which could result in collapse of the MLG upon landing.
88-03-04: 88-03-04 AIRBUS INDUSTRIE: Amendment 39-5833. Applies to Model A300 B2 series airplanes, as listed in Airbus Industrie (AI) Service Bulletin A300-32-369, dated December 12, 1986, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent collapse of the main landing gear (MLG), accomplish the following: A. Prior to each lower tie rod accumulating 7,000 landings or within the next 500 landings, whichever occurs later, and thereafter at intervals not to exceed 1,500 landings, perform an ultrasonic inspection of the MLG lower tie rods, in accordance with AI Service Bulletin A300- 32-369, dated December 12, 1986. Replace defective lower tie rods before further flight. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. Special flight permitsmay be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective February 28, 1988.
2015-03-05: We are superseding Airworthiness Directive (AD) 2012-09-07 for certain Airbus Model A319-111, -112, and -132 airplanes; Model A320- 111, -211, -212, -214, and -232 airplanes; and Model A321-111, -211, - 212, and -231 airplanes. AD 2012-09-07 required an electrical bonding test between the gravity fill re-fuel adaptor and the top skin panels on the wings; and, if necessary, an inspection for corrosion of the component interface and adjacent area; and repairing the gravity fuel adaptor if necessary. This new AD adds airplanes to the applicability and requires inspecting those airplanes to determine if a repair was done, and doing the electrical bonding test and corrective action if necessary. This AD was prompted by a determination that more airplanes are [[Page 8514]] subject to the identified unsafe condition. We are issuing this AD to detect and correct corrosion and improper bonding, which, in combination with a lightning strike in this area, could create a source ofignition in a fuel tank, resulting in a fire or explosion and consequent loss of the airplane.
99-23-22 R2: This amendment rescinds Airworthiness Directive (AD) 99-23-22 R1, which is applicable to various transport category airplanes equipped with Mode "C" transponder(s) with single Gillham code altitude input. That AD requires repetitive tests to detect discrepancies of the Mode "C" transponder(s), air data computer, and certain wiring connections; and corrective actions, if necessary. The requirements of that AD were intended to prevent false advisories that direct the flightcrew to change course and either climb or descend, which could result in the flightcrew deviating the airplane from its assigned flight path, and a possible mid-air collision. Since the issuance of that AD, test data have been collected that demonstrate that the repetitive tests are unnecessary.
2014-22-51: We are publishing a new airworthiness directive (AD) for Airbus Helicopters (formerly Eurocopter France) Model EC130T2 helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires repetitively inspecting the attachment points where the fan attaches to the main gearbox (MGB) oil cooler hopper (hopper) and replacing any cracked hopper with an airworthy hopper. This AD is prompted by several cases of a cracked hopper. The cracks were found on the hopper at the fan attachment points. These actions are intended to detect a crack in the hopper at a fan attachment point to prevent failure of the fan attachment, interference of the fan with the control rod of the front servo-control or with the flight control bellcrank, and subsequent loss of control of the helicopter.
2000-08-06: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA-366G1 helicopters, that requires replacing certain electrical modules with airworthy electrical modules. This amendment is prompted by the discovery of several defective electrical modules. The actions specified by this AD are intended to prevent loss of electrical continuity, which could cause loss of critical systems and subsequent loss of control of the helicopter.
2000-08-04: This amendment adopts a new airworthiness directive (AD), applicable to Robinson Helicopter Company (RHC) Model R44 helicopters. This action requires replacing certain serial number (S/N) sprag clutches with an airworthy sprag clutch as specified in this AD. This amendment is prompted by several reports of sprag clutch failures. The actions specified by this AD are intended to prevent a sprag clutch failure, loss of main rotor RPM during autorotation, and subsequent loss of control of the helicopter.
76-07-12: 76-07-12 BENDIX IGNITION SWITCHES: Amendment 39-2575 as amended by Amendment 39-3024. Applies to all aircraft employing magnetos and using Bendix ignition switches listed in the table below except switches identified by four digit date code (new) adjacent to the model number or a white dot (modified) on the support plate adjacent to the Bendix logo. Bendix Switches Rotary Action, Key or Lever Actuated Switch Function Bendix (series) Part Numbers Twist-to-Start 10-357XXX, 10-126XXX Twist-to-Start/Push-to-Prime 10-357XXX, 10-126XXX Push-to-Start 10-357XXX, 10-126XXX, 10-157XXX Compliance required as indicated: 1. For switches subject to this AD, conduct the following checks within the next 100 hours' time in service and each 100 hours thereafter to detect possible switch malfunction: (a) Observing regular ground run-up procedures, allow the engine to reach operating temperatures and perform a normal magneto check. (b) With the engine at normal idle, rotate the switch key or lever through the "OFF" detent to the extreme limit of its travel in the "OFF" direction. (c) If the engine stops firing, this indicates an airworthy switch. (d) If the engine continues to run with the switch in the extreme "OFF" direction indicating a malfunctioning switch, prior to the next flight accomplish Part III outlined in Bendix Service Bulletin No. 583, dated April 1976, for Repair and Replacement or use an alternate method approved by Chief, Engineering and Manufacturing Branch, Eastern Region. 2. The aircraft may be flown in accordance with FAR 21.197 to a place where these modifications can be accomplished. 3. The checks required by this AD may be performed by the pilot. 4. Upon submission by an operator with substantiating data, an FAA Maintenance Inspector subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region may adjust the compliance times specified in this AD if the request contains substantiating data to justify the increase for the operator: (NOTE: If the engine continues to run when complying with paragraph 1 and repair or replacement cannot or will not be accomplished immediately, the magneto (primary circuit) should be grounded in accordance with Bendix Service Bulletin No. 583, dated April 1976.) Amendment 39-2575 was effective April 14, 1976. This amendment 39-3024 is effective August 30, 1977.
2004-14-23: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires a one-time inspection to identify the serial number of the actuator of the thrust reverser blocker door, and corrective action if necessary. This action is necessary to prevent inadvertent deployment of the thrust reverser door, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2000-08-01: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc Tay 650-15 series turbofan engines. This AD requires the establishment of cyclic life limits for stage 1 high pressure turbine (HPT) and stage 1 low pressure turbine (LPT) disks operating under new flight plan profiles. This amendment is prompted by reports that, on some engines, cracks in the stage 1 HPT and stage 1 LPT disks could initiate and propagate at a faster rate than forecast under the flight plan profiles originally published at the time the engine design was certified. The actions specified by this AD are intended to prevent crack initiation and propagation leading to turbine disk failure, which could result in an uncontained engine failure and damage to the aircraft.
63-10-05: 63-10-05 MOONEY: Amdt. 561 Part 507 Federal Register May 4, 1963. Applies to M20 Airplanes Serial Numbers 1002 Through 1200, and M20A Airplanes Serial Numbers 1201 Through 1540, With Empennage Attach Brackets P/N 3009, Installed. Compliance required within 25 hours' time in service after the effective date of this AD, unless already accomplished. Replace empennage attach bracket P/N 3009 and bearing plate P/N 3449 with bracket P/N 3471. (Mooney Service Letter No. 20-60 dated November 17, 1959, also covers this change.) This supersedes AD 59-09-01. This directive effective June 4, 1963.
97-21-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires flow checks of the hydraulic pump drain system to ensure that the system is not clogged, and correction of any discrepancy. Additionally, this amendment requires replacement of the existing seal of the accessory gearbox with a new, improved seal assembly; this replacement terminates the requirement for repetitive flow checks. This amendment is prompted by reports indicating that hydraulic fluid had contaminated the engine oil system as a result of failure of the seal of the hydraulic pump shaft. The actions specified by this AD are intended to prevent clogging of the hydraulic pump drain system, which could cause failure of the seal of the hydraulic pump shaft and subsequent contamination of the engine accessory gearbox oil; this condition could result in an in-flight engine shutdown.
85-19-07 R1: 85-19-07 R1 BURKHART GROB: Amendment 39-5132 as amended by Amendment 39-5202. Applies to Model G109 Powered Gliders (serial numbers 6001 through 6159 inclusive) and Model G109B Powered Gliders (serial numbers 6200 through 6317 inclusive) certificated in any category. Compliance is required as indicated unless already accomplished. To prevent failure of the main landing gear legs, accomplish the following: (a) Within the next 10 hours time in service, inspect the landing gear legs to determine if they are constructed with boreholes (P/N 109-5000.01) or without boreholes (P/N 109B-5000.01) in accordance with Instruction 1 of Grob-Werke Technical Information TM 817- 19, dated March 18, 1985. (b) If the landing gear is equipped with legs without boreholes no further action is necessary. (c) If the glider is equipped with landing gear legs with boreholes: (1) Within the next 10 hours time in service and thereafter at intervals not to exceed 25 hours time in service from the last inspection, inspect the legs for cracks in accordance with Instruction 2 of Grob-Werke Technical Information TN 817-19, dated March 18, 1985. If cracks are found, replace landing gear leg with a serviceable part before further flight. (2) Exchange landing gear legs with boreholes for landing gear legs without boreholes in accordance with Instruction 4 of Grob-Werke Technical Information TM 817-19, dated March 18, 1985, no later than January 31, 1986. NOTE: Dimensions shown in TM 817-19 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 Technical Information TM 817-19 dated March 18, 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, 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. Amendment 39-5132 became effective on September 19, 1985. This Amendment 39-5202 becomes effective on January 10, 1986.
2022-20-12: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GEnx-1B and GEnx-2B model turbofan engines. This AD was prompted by the detection of melt-related freckles in the forgings and billets, which may reduce the life of certain compressor discharge pressure (CDP) seals, interstage seals, high-pressure turbine (HPT) rotor stage 2 disks, and stages 6-10 compressor rotor spools. This AD requires revising the airworthiness limitations section (ALS) of the applicable GEnx-1B and GEnx-2B Engine Manual (EM) and the operator's existing approved maintenance program or inspection program, as applicable, to incorporate reduced life limits for these parts. The FAA is issuing this AD to address the unsafe condition on these products.
2022-20-07: The FAA is superseding Airworthiness Directive (AD) 2021-10-10 for all Airbus Helicopters Model SA330J helicopters. AD 2021-10-10 required repetitively inspecting the main gearbox (MGB) particle detector and the MGB bottom housing (oil sump) for metal particles, analyzing any metal particles that are found, and replacing the MGB if necessary. Since the FAA issued AD 2021-10-10, additional review concluded that installing an improved planet gear assembly is necessary. This AD continues to require repetitively inspecting the MGB particle detector and the MGB bottom housing (oil sump) for metal particles, and analyzing any metal particles that are found, and also requires replacing the planet gear assembly and repetitively inspecting and establishing an airworthiness limitation for that assembly 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.
2000-07-28: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Fokker Model F27 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with modified operational procedures to ensure continuous operation with the high pressure cock (HPC) levers in the lockout position. This amendment retains the requirements of the existing AD for the Normal and Abnormal Procedures Sections of the AFM, and requires incorporation of amended Limitations and Emergency Procedures Sections into the AFM. This amendment is prompted by a report that certain incorrect instructions had been included in the Emergency Procedures Section of the AFM revision required by the existing AD. The actions specified in this AD are intended to ensure that flightcrews follow correct procedures that will maintain the HPC levers in a permanent lockout position to prevent consequent burnout of the engines during flight.
47-20-02: 47-20-02 AERONCA: (Was Mandatory Note 2 of AD-761-2 and Mandatory Note 2 of AD-759-3.) Applies to 7AC Airplanes Having Serial Numbers 226 to 3721; and 11AC, Serial Numbers 1 to 351. Compliance required at next periodic inspection but not later than August 1, 1947. To prevent the oleo strut assembly from separating in flight, replace the fiber piston with aluminum pistons. (Supplementary to Aeronca Service Helps and Hints No. 12 dated February 11, 1947, covers this same subject.)
2022-21-06: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CF34-8C and CF34-8E model turbofan engines. This AD was prompted by a report of a crack found on the low-pressure turbine (LPT) stage 5 disk at the forward arm area. This AD requires the removal of the affected LPT stage 5 disk and replacement with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2000-07-27: This amendment adopts a new airworthiness directive (AD) that is applicable to various transport category airplanes equipped with certain Honeywell air data inertial reference units (ADIRU). This action requires inspection of a failed ADIRU to determine its modification status, and replacement of an unmodified failed ADIRU with a serviceable ADIRU. This action also provides for optional terminating action for the requirements of the AD. This amendment is prompted by reports of dual critical failures of inertial reference units on ADIRU's during flight. The actions specified in this AD are intended to prevent loss of the main sources of attitude data, consequent high pilot workload, and a significant increase in the likelihood of pilot error.
99-13-08 R1: This amendment revises an existing airworthiness directive (AD), applicable to all Lockheed Model L 1011-385 series airplanes, that currently requires inspections to detect cracking and other discrepancies of certain web-to-cap fasteners of the rear spar between inner wing station (IWS) 310 and IWS 343, and of the web area around those fasteners; various follow-on actions; and modification of the web-to-cap fastener holes of the rear spar between IWS 299 and IWS 343, which, when accomplished, defers the initiation of the inspections for a certain period of time. The actions specified by that AD are intended to prevent fatigue cracking in the web of the rear spar of the wing, which could result in failure of the rear spar of the wing and consequent fuel spillage. This amendment, for certain airplanes, extends the compliance time for the modification of the web-to-cap fastener holes, and eliminates references to modification of the outboard spar.
86-05-12: 86-05-12 HARTZELL PROPELLER PRODUCTS DIVISION: Amendment 39-5333. Applies to Hartzell Model HC-B3TN-5( )/T10282( ) propellers installed on Fairchild Model SA226-TC aircraft modified by Garrett STC SA344GL or Par Air STC SA4872SW with TPE331-10UA engines. Compliance required prior to accumulating 1,000 hours time in service since new or 300 hours time in service since overhaul, or within 30 days after the effective date of this AD, whichever occurs later, unless already accomplished. To prevent propeller blade separation near the hub which could result in engine separation from the aircraft, accomplish the following: (a) Remove propeller from aircraft. (b) Accomplish the following in accordance with Hartzell Service Bulletin No. 136C dated March 3, 1986, or FAA approved equivalent: (1) Disassemble propeller and visually inspect the blade pilot tube bore area. Particular attention shall be made to area between the inner needle bearing assembly and bearing spacer. (2) Remove all evidence of scratches, tool marks, corrosion, etc. in the blade pilot tube bore area. Do not exceed the maximum rework limitations defined in the service bulletin. (3) Etch the blade pilot tube bore area prior to penetrant inspection. Ensure removal of all etching solution. (4) Penetrant inspect the blade pilot tube bore area. (5) Coat the blade pilot tube bore area with alodine. (6) Install bearing spacer and inner needle bearing assembly. Pilot tube bore must be lubricated to facilitate bearing installation. (c) Replace, prior to further flight, all blades showing evidence of cracks or other unairworthy conditions with airworthy blades. (d) Place the following WARNING in the Limitation Section of the FAA approved airplane flight manual supplement: "The TPE331-10UA engine is capable of developing in excess of the maximum allowable torque approved for this installation. Use of torque in excess of the maximum approved limits may cause propeller failure." NOTES: (1) Propeller blades with serial numbers subsequent to F74359 have had the intent of this AD incorporated during manufacture and are not affected by this AD. (2) This AD does not apply to propellers installed on TPE331-3 engines unless the propellers were previously installed on TPE331-10UA engines for at least 1000 hours time in service since new or at least 300 hours time in service since overhaul. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FAR) 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, 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. Hartzell Service Bulletin No. 136C dated March 3, 1986, identified and described in this document 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 manufacture may obtain copies upon request to Hartzell Propeller Products Division, TRW Aircraft Components Group, 350 Washington Ave., Piqua, Ohio 45356. This document also may be examined at the Office of Regional Counsel, FAA, Attn: Rules Docket No. 86-ANE-9, 12 New England Executive Park, Burlington, Massachusetts 01803, weekdays, except Federal holidays, between 8:00 a.m. and 4:30 p.m. This amendment becomes effective June 27, 1986, as to all persons except those persons to whom it was made immediately effective by priority letter AD 86-05-12 issued March 7, 1986, which contained this amendment.
99-23-12: This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that requires repetitive inspections to detect damage and discrepancies of various control cables and certain fairleads/swivel guides for the autopilot, elevator, rudder, aileron, and engine; and corrective actions, if necessary. 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 pilot s control cables for the autopilot, elevator, rudder, aileron, and engine, which could result in reduced controllability of the airplane.
2015-02-15: We are adopting a new airworthiness directive (AD) for all Quest Aircraft Design, LLC Model KODIAK 100 airplanes. This AD requires inspecting the inboard upper and lower elevator skins for cracking, repairing cracks, and installing doublers. This AD was prompted by a report that fatigue cracks were found in the lower elevator skins. We are issuing this AD to correct the unsafe condition on these products.
2000-07-22: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300-600 series airplanes, that requires repetitive inspections to detect cracking of the doubler angle and discrepancies of the fasteners that connect the doubler angle and the bottom panel of the center wing box, and corrective actions, if necessary. 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 detect and correct fatigue cracking in the doubler angle and discrepancies of the fasteners that connect the doubler angle and the bottom panel of the center wing box. Such cracking and discrepancies could result in reduced structural integrity of the airplane.