Results
2000-16-01: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 series airplanes, that requires replacement of certain ground block screws with new screws; and retermination of the circuit ground wires of the electrical power control unit (EPCU) to separate grounding points. This amendment is prompted by reports of complete loss of the primary electrical power on an airplane during flight. The actions specified by this AD are intended to prevent a loose electrical ground block of the circuit ground wires of the EPCU, which could result in complete loss of the primary electrical power of an airplane during flight.
2018-22-01: We are superseding Airworthiness Directive (AD) 88-12-10 for certain Honeywell International Inc. (Honeywell) TPE331 turboprop engines. AD 88-12-10 required reducing the life limit for certain second stage turbine rotors. This AD requires removing certain second stage turbine rotors from service at a reduced life limit. This AD was prompted by report that a TPE331-11U engine experienced an uncontained rotor separation. In addition, cracks were discovered through eddy current inspection (ECI) in the bore of the second stage turbine rotor assembly after publication of AD 88-12-10. We are issuing this AD to address the unsafe condition on these products.
2007-02-08: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 a report of a master cylinder yoke failure. We are issuing this AD to require actions to correct the unsafe condition on these products.
2021-18-07: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AB412 and AB412 EP helicopters. This AD was prompted by the results of a fatigue review. This AD requires establishing a life limit for certain part-numbered high landing gear aft crosstubes. The FAA is issuing this AD to address the unsafe condition on these products.
2021-16-13: The FAA is adopting a new airworthiness directive (AD) for Leonardo S.p.a. (Leonardo) Model A109S and AW109SP helicopters with a certain part-numbered vertical fin vibration absorber installation installed. This AD requires repetitive inspections of the vertical fin vibration absorber installation and the surrounding structure and depending on the inspection results, removing certain parts from service. This AD also prohibits installing certain part-numbered vertical fin vibration absorber installations on any helicopter. This AD was prompted by a report of cracks and damage detected on the vertical fin absorber installation and surrounding structure during scheduled inspections. The FAA is issuing this AD to address the unsafe condition on these products.
2018-22-08: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports that non-conforming FIREX squib wire harness connectors may have been installed, which could result in FIREX squib wire harness connectors being connected to the wrong FIREX bottle connectors on affected aircraft. This AD requires a visual inspection of the connections between the FIREX squib wire harness connectors and FIREX bottle connectors, installation of split ring lanyards on the FIREX squib wire harness connectors, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
95-08-09: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires modification of the support structure of the cargo liner. This amendment is prompted by a report of chafing and arcing in the vacuum waste exhaust heater that caused a spark to ignite the surrounding insulation blankets. The actions specified in this AD are intended to prevent fire and/or smoke due to chafing and arcing of the vacuum waste exhaust port heater.
2007-02-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 reports of interference between the wing spar lower boom and the wheel fairing attaching screw. We are issuing this AD to require actions to correct the unsafe condition on these products.
2018-21-06: We are superseding Airworthiness Directive (AD) 98-16-03 for SOCATA Model TB 9 and Model TB 10 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 fatigue cracking of the wing front attachments on the wing and fuselage sides. We are issuing this AD to require actions to address the unsafe condition on these products.
2000-15-21: This amendment adopts a new airworthiness directive (AD) that applies to Bell Helicopter Textron Inc. (BHTI)-manufactured Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P; and Southwest Florida Aviation SW204, SW204HP, SW205, and SW205A-1 helicopters. This AD requires removing and replacing certain main rotor mast (mast) assemblies. This AD is prompted by a BHTI-manufactured Model UH-1B accident due to fatigue failure of a thin-wall mast installed on the helicopter. The actions specified by this AD are intended to prevent fatigue failure of the mast and subsequent loss of control of the helicopter.
89-14-11: 89-14-11 BOEING: Amendment 39-6256. \n\tApplicability: Model 737 series airplanes, equipped with flight attendant seats, Trans Aero part number (P/N) 90835, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent possible failure of flight attendant seats, accomplish the following: \n\n\tA.\tWithin the next 12 months after the effective date of this amendment, unless previously accomplished within 12 months prior to the effective date of this amendment, inspect seat pan roller fittings, P/N 990862-3, and -4, for evidence of fatigue and/or deformation, in accordance with Trans Aero Service Bulletin No. 113, dated May 11, 1988. Repeat the inspection at intervals not to exceed 18 months. \n\n\tB.\tIf evidence of fatigue or deformation is found, prior to further use of the seat, replace the seat pan roller fitting with an airworthy part. Inspect the new fitting, in accordance with paragraph A., above, at intervals not to exceed 18 months. \n\n\tC.\tWithin 10 days after completion of the initial inspection required by paragraph A., above, submit a report of findings, positive or negative, to the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 17900 Pacific Highway South, C-68966, Seattle, Washington 98168. \n\n\tD.\tAn 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,\t Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will concur or make comments and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tE.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Trans Aero Industries, Inc., 502 North Oak Street, Inglewood, California 98302-2942, or to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Transport Airplane Directorate, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6256, AD 89-14-11) becomes effective on August 7, 1989.
2006-26-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300 B2 and B4 series airplanes. This AD requires revising the airplane flight manual (AFM) to include procedures for resetting the trim and pitch trim levers after each landing, determining which servomotor moves the pitch trim control wheel, and doing applicable other specified actions. This AD also provides for optional terminating actions for those requirements. This AD results from a report of a sudden nose-up movement after disengagement of the autopilot in cruise. We are issuing this AD to ensure that the flightcrew is aware of the procedures for resetting the trim and pitch trim levers after each landing and to prevent failure of the servomotors of the pitch trim systems during flight. Failure of the servomotors of the pitch trim systems could result in uncommanded nose- up movement of the control surface of the pitch trim systems after disengagement of the autopilot in cruise.
2000-15-01: This amendment adopts a new airworthiness directive (AD), applicable to CFM International (CFMI) CFM56-2, -2A, -2B, -3, -3B, -3C, -5, -5A, -5B, -5C series turbofan engines, that requires initial and repetitive visual inspections of the fuel pump filter cover helicoil inserts and bolts for damage, and, if necessary, repair or replacement with serviceable parts. This amendment also requires the installation of new or reworked fuel pumps that incorporate an improved filter cover retention design (D-bolts), or an on-wing repair of existing fuel pumps, as terminating action to the inspections. This amendment is prompted by reports that fuel pump filter cover helicoil inserts have loosened or pulled out. The actions specified by this AD are intended to prevent fuel leakage from between the fuel pump filter cover and gear housing, which could result in an engine fire and damage to the airplane.
2018-22-06: We are adopting a new airworthiness directive (AD) for all Pratt & Whitney (PW) PW2037, PW2037M, and PW2040 turbofan engines. This AD was prompted by an uncommanded high thrust event that occurred during approach on January 16, 2016, and during landing on April 6, 2016. This AD requires removal of the metering valve pilot valve (MVPV) within certain fuel control units (FCUs) and the MVPV's replacement with a part eligible for installation. We are issuing this AD to address the unsafe condition on these products.
94-26-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T94-26-51 that was sent previously to all known U.S. owners and operators of all McDonnell Douglas Model MD-11 series airplanes by individual telegrams. This AD requires a revision to the FAA-approved Airplane Flight Manual (AFM) to prohibit autoland operation below 100 feet above ground level (AGL), and the installation of certain flight control computer software. This AD provides for an optional terminating action for the AFM revision. This amendment is prompted by reports of a loose nut on a coaxial connector on a radio altimeter receiver/transmitter rack, and the transmittal of erroneous altitude data to the flight control computers below 100 feet AGL, which resulted in abnormal flare (pitch) control during autoland operation. The actions specified by this AD are intended to prevent abnormal flare (pitch) control, which could result in degradation of the landing capability of the airplane.\n\n\tThe incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of February 6, 1995.\n\tComments for inclusion in the Rules Docket must be received on or before March 21, 1995.
90-17-19: 90-17-19 BOEING: Amendment 39-6705. Docket No. 89-NM-120-AD. \n\n\tApplicability: Model 747 series airplanes, except the Model 747SP, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent failure of the trailing edge flaps' carriage spindles, accomplish the following: \n\n\tA.\tIn accordance with the compliance schedule below, remove the aft link and thrust collars from the trailing edge flaps' carriage spindles and perform a detailed visual inspection of all exposed surfaces of the carriage spindles, including inner bore, and aft links to detect cracking and corrosion, in accordance with Boeing Service Bulletin 747-27-2280, Revision 3, dated November 30, 1989. \n\n\t\t1.\tPerform the initial inspection at the later of the following, unless previously accomplished within the last 11 months: \n\n\t\t\ta.\twithin 30 days after the effective date of this AD; or \n\n\t\t\tb.\tprior to the accumulation of 30,000 flight hours or 8 years on each new or previously overhauled flap carriage spindle, whichever occurs first. \n\n\t\t2.\tIf no cracking or corrosion is found, repeat the inspections required by paragraph A. of this AD, at intervals not to exceed 12 months until the carriage spindles are overhauled in accordance with paragraph B. of this AD. \n\n\t\t3.\tIf a cracked carriage spindle or aft link is found, prior to further flight, replace the part(s) in accordance with the service bulletin. \n\n\t\t4.\tIf corrosion is found on any part of the carriage spindle/aft link assembly, but not on the other assembly on the same flap perform a repetitive general visual inspection in accordance with the service bulletin at intervals not to exceed 2 months. Overhaul or replace corroded parts within 36 months after detection of the corrosion, but no later than 5 years after the effective date of this AD. \n\n\t\t5.\tIf corrosion is found on any part of both carriage spindle/aft link assemblies on the same flap, prior to further flight, overhaul or replace the part(s) in accordance with the service bulletin; or repair in accordance with a method approved by the Manager, Seattle Aircraft Certification Office, Transport Airplane Directorate. \n\n\tB.\tIn accordance with the schedule below, remove the carriage spindle and aft link, and overhaul in accordance with Boeing Service Bulletin 747-27-2280, Revision 3, dated November 30, 1989. \n\n\t\t1.\tPerform the initial overhaul at the latest of the following: \n\n\t\t\ta.\twithin 5 years after the effective date of this AD; or \n\n\t\t\tb.\tprior to the accumulation of 30,000 flight hours on any new or previously overhauled flap carriage spindle; or \n\n\t\t\tc.\tprior to the accumulation of 8 years on any new or previously overhauled flap carriage spindle. \n\n\t\t2.\tRepeat this overhaul thereafter at intervals not to exceed 30,000 flight hours or 8 years, whichever occurs first. \n\n\tC.\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tAirworthiness Directive 90-17-19 supersedes AD 88-04-06 R1, Amendment 39-6164.\n \tThis amendment (39-6705, AD 90-17-19) becomes effective on September 21, 1990.
2007-01-15: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. The existing AD currently requires repetitive inspections to detect cracks and fractures of the strut front spar chord assembly at each strut location, and repair if necessary. This new AD expands the inspection area by requiring repetitive inspections for any cracks or fracture of the strut front spar chord assembly in an area forward of the existing inspection area at each strut location, and repair if necessary. This AD results from a strut front spar chord assembly that was found fractured, forward of the inspection area required by the existing AD. We are issuing this AD to detect and correct cracks and fracture of the nacelle strut front spar chord assembly. Fracture of the front spar chord assembly could lead to loss of the strut upper link load path and consequentfracture of the diagonal brace, which could result in in-flight separation of the strut and engine from the airplane.
2018-20-23: We are superseding Airworthiness Directive (AD) 2017-07-04 for General Electric Company (GE) GE90-110B1 and GE90-115B turbofan engines with certain high-pressure compressor (HPC) rotor stage 2-5 spools installed. AD 2017-07-04 required removing certain HPC rotor stage 2-5 spools from service at times determined by a drawdown plan. This AD requires [[Page 53977]] removing certain HPC rotor stage 2-5 spools from service before reaching the new reduced life limit and replacing them with parts eligible for installation. This AD was prompted by the publication of a GE service bulletin (SB) that increases the number of affected HPC rotor stage 2-5 spools and includes HPC rotor stage 2-5 spools that were inadvertently omitted from the applicability of AD 2017-07-04. We are issuing this AD to address the unsafe condition on these products.
2000-14-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires modifying the fuel pipe couplings and installing bonding leads in specified locations within the fuel tank. 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 ignition sources and consequent fire/explosion in the fuel tank.
99-09-52: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 99-09-52 that was sent previously to all known U.S. owners and operators of Bombardier Model CL-600-2B19 (Regional Jet Series 100) and CL-600-2B16 (CL-601-3R and CL-604) series airplanes by individual notices. This AD requires a one-time inspection of the cable harness of the integrated drive generator (IDG) in the right engine nacelle and the adjacent structure to verify clearances and detect chafing; a one-time inspection of both the left and right engine nacelles to detect chafing and verify clearances of the adjacent 10th stage bleed air check valve and fuel manifold pigtails; and repair or replacement of discrepant parts, if necessary. This action is prompted by reports of chafing of the insulation covering on the IDG cable harness and the main engine right fuel manifold. The actions specified by this AD are intended to detect and correct concurrent chafing of both the fuel manifold and the IDG wire and subsequent leakage of fuel, which could come in contact with live wiring and result in fire or explosion.
2006-20-14: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2006-20-14 that was sent previously to all known U.S. owners and operators of certain EMBRAER Model ERJ 170 and ERJ 190 airplanes by individual notices. This AD requires modification of certain flight deck door electronic equipment. This AD is prompted by a report indicating that this equipment is defective. We are issuing this AD to prevent failure of this equipment, which could jeopardize flight safety.
2003-10-03R1: This amendment revises an existing airworthiness directive (AD) that is applicable to Rolls-Royce plc (RR) model RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 turbofan engines. The existing AD will become effective on June 20, 2003, and requires removal from service of certain high pressure (HP) turbine discs before they reach newly established life limits. This amendment requires the same actions, but removes the model RB211-535E4-37 turbofan engine from the applicability. This revision to the existing AD is prompted by further data gathering by the FAA that demonstrates that the model RB211-535E4- 37 turbofan engine is not affected by machining-induced cracking within the currently published life of the HP turbine disc. The actions specified in this AD are intended to prevent machining-induced cracking of the HP turbine disc which could cause an uncontained HP turbine disc failure and damage to the airplane.
2018-20-22: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GE90-110B1, GE90-113B, and GE90-115B turbofan engines with a certain case combustor assembly (combustion case) installed. This AD requires removal of affected combustion cases from service and their replacement with a part eligible for installation. This AD was prompted by the discovery of a quality escape at a manufacturing facility involving unapproved welds on combustion cases. We are issuing this AD to address the unsafe condition on these products.
2000-09-15 R1: This amendment clarifies information contained in Airworthiness Directive (AD) 2000-09-15, which currently requires you to incorporate modifications to the airplane operating systems on all Mitsubishi Heavy Industries, Ltd. (Mitsubishi) MU-2B series airplanes. The Federal Aviation Administration (FAA) inadvertently omitted service information from the AD that is needed to accomplish these modifications on some of the affected airplanes. This document retains the requirements of AD 2000-09-15, and adds the service information to the AD. The actions specified in this AD are intended to continue to assist in preventing departure from controlled flight while operating in icing conditions.
98-16-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 and A321 series airplanes, that requires replacement of the fuel pump strainers with improved strainers. 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 blockage of fuel by the buildup of ice crystals, which could result in low fuel pressure, and consequent shutdown of the engine during critical phases of flight.