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77-13-06: 77-13-06 PILATUS AIRCRAFT LTD. AND FAIRCHILD HILLER: Amendment 39- 2928. Applies to Pilatus Model PC-6 airplanes (all variants) with serial numbers up through 743 and Fairchild Hiller Model PC-6 airplanes, serial numbers 2001 through 2019, 2021 through 2038, and 2040 through 2049, certificated in all categories. Compliance is required as indicated. To prevent a possible landing flap nose rib fatigue failure, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD, unless already accomplished within the last 25 hours time in service, and, thereafter, at intervals not to exceed 100 hours time in service since the last inspection, visually inspect all the end ribs of the landing flaps for cracks in accordance with Pilatus Service Bulletin No. 124, paragraph 2.1, dated January 1976, or an FAA-approved equivalent. (b) If a crack is found during any inspection required by paragraph (a) of this AD, before further flight, repair the crack in accordance with paragraphs 2.1 and 2.2 of Pilatus Service Bulletin No. 124, dated January 1976, or an FAA-approved equivalent. (c) Within the next 1,000 hours time-in-service after the effective date of this AD, unless already accomplished, reinforce the landing flap nose end ribs in accordance with paragraph 2.3 of Pilatus Service Bulletin No. 124, dated January 1976, or an FAA-approved equivalent. (d) The repetitive inspections required by paragraph (a) of this AD may be discontinued after the reinforcement has been accomplished in accordance with paragraph (c) of this AD, and all cracks have been repaired in accordance with paragraph (b) of this AD. (Fairchild Hiller Service Bulletin PC-6-51-3 pertains to this same subject.) This amendment becomes effective July 25, 1977.
98-09-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that requires a modification of the lapjoint below the chine line at certain fuselage stations. 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 fatigue cracking in the lapjoint below the chine line at certain fuselage stations, which could result in reduced structural integrity of the fuselage.
2004-08-18: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Dornier Model 328-300 series airplanes, that currently requires repetitive inspections of motive flow check valves and adjacent parts for fuel leaks, and replacement of the valves if leaks are detected. This amendment requires new repetitive engine operational tests. This amendment also requires replacement of the motive flow check valves with new parts, which would constitute terminating action for the repetitive inspections and engine operational tests. The actions specified by this AD are intended to prevent leakage of fuel from the motive flow check valves, which could result in fuel vapors coming into contact with fuel ignition sources and consequent fuel tank explosion and fire. This action is intended to address the identified unsafe condition.
2021-16-05: The FAA is superseding Airworthiness Directive (AD) 2016-12- 51, which applied to all Airbus Helicopters Model AS332L2 and Model EC225LP helicopters. AD 2016-12-51 prohibited all further flight of Model AS332L2 and Model EC225LP helicopters. This AD requires replacing certain second stage planet gear assemblies, removing certain epicyclic modules, installing a full flow magnetic plug (FFMP), revising the existing \n\n((Page 50227)) \n\nrotorcraft flight manual (RFM) for your helicopter, repetitively inspecting the main gearbox (MGB) particle detectors, repetitively inspecting the MGB oil filter and oil cooler, and corrective action if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The actions specified in this AD terminate the flight prohibition. The FAA is issuing this AD to address the unsafe condition on these products.
95-11-17: This amendment supersedes Airworthiness Directive (AD) 90-13-12, which currently requires modifying the airplane electrical system and revising the emergency procedures section of the Airplane Flight Manual (AFM) on certain Jetstream Aircraft Limited (JAL) Jetstream Models 3101 and 3201 airplanes. This action retains the requirements of AD 90-13-12 for those airplanes that do not have modified inverters installed and the inverted transfer function restored. The Federal Aviation Administration (FAA) has determined that installing modified inverters along with restoring the inverter transfer function corrects the problems in the power supply addressed by AD 90-13-12. The actions specified by this AD are intended to prevent alternating current system failures, which, if not detected and corrected, could result in damage to the airplane navigational systems.
2004-08-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-200 series airplanes. This action requires certain modifications of the rudder servo controls. This action is necessary to prevent failure of the driving finger of the rudder servo control and consequent loss of the rudder servo control function in driving the rudder to its commanded position, which, if combined with an engine failure during takeoff or go around, could result in loss of control of the airplane. This action is intended to address the identified unsafe condition.
2011-21-12: We are adopting a new airworthiness directive (AD) for the Erickson Air-Crane (Erickson Air-Crane) Model S-64F helicopters. The amendment requires, at specified intervals, certain inspections of the rotating swashplate assembly (swashplate) for a crack. If a crack is found, this AD also requires, before further flight, replacing the swashplate with an airworthy swashplate. This AD is prompted by a report from the manufacturer of a swashplate cracking during fatigue testing. We are issuing this AD to prevent loss of a swashplate due to a fatigue crack, loss of control of the main rotor system, and subsequent loss of control of the helicopter.
98-08-09: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-08-09 that was sent previously to all known U.S. owners and operators of certain Lockheed Model L-1011-385 series airplanes by individual notices. This AD requires revision of the Airplane Flight Manual (AFM) to prohibit operation of the fuel boost pumps when fuel quantities are below certain levels, and to add new maintenance procedures for operating the airplane with an inoperative fuel boost pump assembly or with an inoperative flight station fuel quantity indicating system. This AD also requires the installation of a placard on the engineer's fuel panel to advise the maintenance crew that operation of the fuel boost pumps when less than 1,200 pounds of fuel are in the corresponding wing fuel tank is prohibited. This action is prompted by reports of internal electrical failures in the fuel boost pump of the wing fuel tanks that could result in either electrical arcing or localized overheating. The actions specified by this AD are intended to prevent such electrical arcing or overheating, which could breech the protective housing of the fuel boost pump and expose it to fuel vapors and fumes, and consequent potential fire or explosion in the wing fuel tank.
98-04-43: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR72 series airplanes, that requires removal of certain landing gear attachment pins, and replacement of the pins with serviceable pins. 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 wear of the attachment pins, which could result in collapse of the main landing gear.
2011-22-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: [T]he FAA has published SFAR 88 (Special Federal Aviation Regulation 88). In their letters referenced 04/00/02/07/01-L296, dated March 4th, 2002, and 04/00/02/07/03-L024, dated February 3rd, 2003, the [Joint Aviation Authorities] JAA recommended the application of a similar regulation to the National Aviation Authorities (NAA). Under this regulation, all holders of type certificates for passenger transport aircraft with either a passenger capacity of 30 or more, or a payload capacity of 3,402 kg (7,500 lb) or more which have received their certification since January 1st, 1958, are required to conduct a design review against explosion risks. ** * * * The unsafe condition is insufficient electrical bonding of the over- wing refueling cap adapter, which could result in a possible fuel ignition source in the fuel tanks. We are issuing this AD to require actions to correct the unsafe condition on these products.
2004-08-17: The FAA is adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes. This AD requires you to inspect any upper and lower wing strut attach fitting nut for existence of the corresponding cotter pin and do any necessary corrective action. This AD is the result of a report of one airplane having loose and improperly tied nuts on the wing struts upper attachment bolts. We are issuing this AD to detect and correct loose and improperly tied nuts on the wing struts, which could result in an attachment nut coming off the bolt. This could lead to the failure of the wing structure with consequent loss of control of the airplane.
2011-22-02: We are adopting a new airworthiness directive (AD) for all Airbus Model A310 series airplanes; Model A300 B4-600, B4-600R, and F4- 600R series airplanes; and Model C4-605R variant F airplanes (collectively called A300-600 series airplanes). This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: An operator reported several cases of wire damages at the pylon/ wing interface. Analysis revealed that wires damages are due to installation quality issue resulting from lack of information in installation drawings and job cards. Moreover detailed analysis has highlighted that the Low Pressure Valve (LPV) wires were not segregated by design. * * * * * If left uncorrected, the wire chafing could impact fire protection and detection system. It may also induce dormant failure on LPV preventing its closure leading to a permanent and uncontrolled fire (in case of fire ignited upstream the High Pressure Valve (HPV)). * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
94-10-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires a visual inspection of an area beneath the flooring for foreign objects and debris, removal of any foreign object or debris found, and installation of a protective guard on the rear cabin attendant seat. This amendment also requires a revision to the FAA-approved maintenance program to include repetitive visual inspections of the area above the protective guard for foreign objects and debris, and removal of any foreign object or debris found. This amendment is prompted by reports that foreign objects and debris have been found in the area around the elevator and rudder trim cables below the floor. The actions specified by this AD are intended to prevent foreign objects and debris from lodging in the control circuits and jamming the elevator and rudder trim systems.
2021-16-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. This AD was prompted by a report that geometrical non-conformities were found in the root section of the tail rotor blade (TRB). This AD requires a one-time inspection (dimensional check) of the TRB for conformity and, depending on the findings, replacement of certain affected parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits rework, repair, or modification of affected parts in the affected area of the TRB assembly root. The FAA is issuing this AD to address the unsafe condition on these products.
2004-08-12: The FAA adopts a new airworthiness directive (AD) for all Schempp-Hirth Flugzeugbau GmbH (Schempp-Hirth) Models Ventus-2a, Ventus-2b, Discus-2a, and Discus-2b sailplanes. This AD requires you to inspect and modify the elevator mass balance. For Models Discus-2a and Discus-2b sailplanes only, this AD also requires you to replace the elevator pushrod. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect and correct problems within the sailplane elevator control system before they lead to flutter and sailplane instability. This could eventually result in loss of sailplane control.
2021-17-05: The FAA is superseding Airworthiness Directive (AD) 2014-04-06 for all Safran Helicopter Engines, \n\n((Page 49905)) \n\nS.A. (Safran Helicopter Engines) Arrius 2B1, 2B1A, 2B2, and 2K1 model turboshaft engines. AD 2014-04-06 required initial and repetitive inspections of the hydro-mechanical metering unit (HMU) high-pressure pump drive gear shaft splines, cleaning and inspections of the sleeve assembly splines, and replacement of the sleeve assembly on the affected high-pressure pump drive gear shaft or replacement of the HMU if the HMU fails inspection. This AD was prompted by in-flight shutdowns caused by interrupted fuel supply at the HMU. This AD requires revised inspections and continues to require cleaning of the sleeve assembly splines, and replacement of the sleeve assembly on the affected high-pressure pump drive gear shaft or replacement of the HMU if the HMU fails an inspection. The FAA is issuing this AD to address the unsafe condition on these products.
94-26-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 series airplanes, that requires accomplishment of certain structural modifications. This amendment is prompted by reports of incidents involving fatigue cracking and corrosion in transport category airplanes that are approaching or have exceeded their economic design goal. These incidents have jeopardized the airworthiness of the affected airplanes. The actions specified by this AD are intended to prevent degradation in the structural capabilities of the affected airplanes. This action also reflects the FAA's decision that long term continued operational safety should be assured by actual modification of the airframe rather than repetitive inspections.
93-07-03: 93-07-03 AEROSPATIALE: Amendment 39-8535. Docket 92-NM-163-AD. Applicability: All Model ATR42-300 series airplanes, and all Model ATR72-100 and - 200 series airplanes; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the pressurization valves to close in the event of ditching, and to prevent interruption of electrical power to certain electrical equipment used during approach and landing, accomplish the following: (a) Within 30 days after the effective date of this AD, remove the electrical switches, part numbers 9PD and 12HM, and identify the date codes in accordance with Aerospatiale Service Bulletin ATR42-31-0023, dated May 15, 1992 (for Model ATR42-300 and -320 series airplanes); or Aerospatiale Service Bulletin ATR72-31-1006, dated May 15, 1992 (for Model ATR72-100 and -200 series airplanes); as applicable. (1) If the date code is identified as A6, A7, A8, A9, AO, AN, AD, B1, B2, B3, B4, B5, B6, or B7, prior to further flight, replace the currently-installed switch with a serviceable switch marked with a date code other than those listed above. (2) If the date code is other than those listed in paragraph (a)(1) of this AD, reinstall the switch. No further action is necessary. (b) As of the effective date of this AD, no person shall install an electrical switch, part numbers 9PD and 12HM, having a date code of A6, A7, A8, A9, AO, AN, AD, B1, B2, B3, B4, B5, B6, or B7, on any airplane. (c) 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, Standardization Branch, ANM-113. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The removal and identification shall be done in accordance with Aerospatiale Service Bulletin ATR42-31-0023, dated May 15, 1992 (for Model ATR42-300 and -320 series airplanes); or Aerospatiale Service Bulletin ATR72-31-1006, dated May 15, 1992 (for Model ATR72-100 and -200 series airplanes); as applicable. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on May 10, 1993.
2021-18-10: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited Model 429 helicopters. This AD was prompted by three reports of unexpected forces or uncommanded inputs to the directional (yaw) control system. This AD requires revising the existing Rotorcraft Flight \n\n((Page 49910)) \n\nManual (RFM) for your helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
2004-08-11: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, that requires a review of airplane maintenance records and an inspection of the nose landing gear (NLG) to determine the part number of the steering pinion, and follow-on/corrective actions as applicable. This action is necessary to prevent failure of the steering pinion in the NLG, which could result in loss of steering and possible damage to the airplane during takeoff and landing. This action is intended to address the identified unsafe condition.
2021-19-08: The FAA is adopting a new airworthiness directive (AD) for certain Robinson Helicopter Company Model R44 and R44 II helicopters. This AD was prompted by reports of cracked tail rotor blades (blades). This AD requires checking each blade for any crack and removing any cracked blade from service. This AD also requires removing all affected blades from service and prohibits installing any affected blade on any helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
76-09-05: 76-09-05 TURBOMECA: Amendment 39-2593. Applies to Turbomeca Astazou IIAd engines installed on, but not necessarily limited to, Aerospatiale Alouette II Models SA3180, SA318B, SA318C helicopters. Compliance is required as indicated unless already accomplished. To prevent axial compressor wheel failure due to corrosion and fatigue, accomplish the following: (a) Within the next 100 hours' time in service after the effective date of this AD, or before the accumulation of 1000 hours' time in service since new, whichever occurs later, remove the axial compressor wheels, P/Ns 0.236.15.014 Index A and 0.268.15.004, from the engine and inspect for a crack or evidence of corrosion. (b) If a crack is found, before returning the engine to service, comply with paragraph (d) of this AD. (c) If no crack is found but evidence of corrosion is found, before returning the engine to service, either - (1) Rework the wheel and reinstall in the engine in accordance with Turbomeca MOD TU 196 (Turbomeca Service Bulletin Astazou II, No. 72.205.0203, dated August 19, 1974), or an equivalent approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East, FAA, c/o American Embassy, APO New York 09667; or (2) Comply with paragraph (d) of this AD. (d) Replace the wheel with a new wheel, P/N 0.236.15.016, 0.268.15.011, or 0.268.15.010, modified in accordance with Turbomeca MOD TU 196 (Turbomeca Service Bulletin Astazou II, No. 72.205.0203, dated August 19, 1974), or an equivalent approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East, FAA, c/o American Embassy, APO New York 09667. This amendment becomes effective May 26, 1976.
2021-17-11: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Trent XWB-75, Trent XWB-79, Trent XWB-79B, and Trent XWB-84 model turbofan engines. This AD was prompted by reports of cracks in the intermediate-pressure compressor (IPC) rotor 1 (R1) blades installed on certain Trent XWB model turbofan engines. This AD requires initial and repetitive borescope inspections (BSIs) of the affected IPC R1 blades and, depending on the results of the inspections, replacement of all 34 IPC R1 blades. The FAA is issuing this AD to address the unsafe condition on these products.
2011-18-13: We are superseding an existing airworthiness directive (AD) that applies to the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During a routine inspection, cracks have been found on an aeroplane at the lower wing panel rear trailing edge inboard of flap lever arm 1 (rib 5). A subsequent inspection of the other aeroplanes in that operator's fleet revealed several more aeroplanes with cracks at the same location. This condition, if not corrected, could lead to structural failure of the affected wing panel, possibly resulting in the wing separating from the airplane with consequent loss of control. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2011-21-01: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: [T]he Federal Aviation Administration (FAA) has published Special Federal Aviation Regulation (SFAR) 88, and the Joint Aviation Authorities (JAA) has published Interim Policy INT/POL/25/ 12. The review conducted by Fokker Services on the Fokker F27 and F28 type designs in response to these regulations revealed that, under certain failure conditions, a short circuit can develop in the fuel pilot valve solenoid or in the wiring to the solenoid. Such a short circuit may result in an ignition source in the wing tank vapour space. This condition, if not corrected, could result in a wing fuel tank explosion and consequent loss of the aeroplane. * * * ** We are issuing this AD to require actions to correct the unsafe condition on these products.