Results
2013-15-21: We are superseding airworthiness directive (AD) 2004-13-06 for certain Airbus Model A319 and A320 series airplanes. AD 2004-13-06 required repetitive detailed inspections to detect cracks in the keel beam side panels, and repair if necessary. This new AD requires repetitive eddy current inspections for cracking in the keel beam side panels, and corrective actions if necessary. This AD was prompted by reports of cracks on the side panels of the keel beams. We are issuing this AD to detect and correct fatigue cracks on the side panels of the keel beams, which could result in reduced structural integrity of the airplane.
75-09-01: 75-09-01 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-2172. Applies to L-1011-385-1-193L airplanes, Serial Nos. 1064, 1079, 1114, 1120, and 1125, certificated in all categories. After receipt of this AD, occupancy of the under floor lounge is prohibited until the conformity of the under floor lower lounge floor boards and the related applicable components is verified to establish adherence to the configuration defined by FAA Sealed Drawing List L-1011- 385-1, No. 385-1, supplement entitled, "FAA List for Model L Peculiars" and "Model L Peculiars Drawing List Addendum", dated May 10, 1974, or FAA-approved equivalent configuration. The conformity inspection shall be accomplished by the Chief, Aircraft Engineering Division, FAA Western Region, or his authorized representative. This amendment becomes effective April 21, 1975, for all persons except those to whom it was made effective by telegram, dated March 18, 1975.
85-11-07 R1: 85-11-07 R1 CESSNA: Amendment 39-5115. Applies to Models P210N, P210R (Serial numbers P21000001 through and including P21000855), and T210R (Serial numbers 21064898 through and including 21064929) airplanes, certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent possible separation of the turbocharger oil reservoir outlet fitting and subsequent rapid loss of engine lubricating oil, accomplish the following: (a) Prior to further flight: (1) Remove the right side engine cowling to the extent necessary to examine the turbocharger oil reservoir. (2) Visually inspect using a strong light the top oil outlet fitting for cracks in the vicinity of the weld securing the fitting to the upper surface of the turbocharger oil reservoir. NOTE: Cracking of the turbocharger oil reservoir outlet fitting may not be evidenced by an oil leak in the vicinity of the oil reservoir installation. Therefore, inspection of the reservoir will depend upon careful cleaning in addition to the use of a strong light. (3) If no cracks are detected in the outlet fitting of the turbocharger oil reservoir, reinspect this area at each additional 25 hours time-in-service thereafter, or in the alternative, replace the turbocharger oil reservoir as follows: (A) For Model P210N (serial numbers P21000001 through P21000834) airplanes remove the existing reservoir and install a Cessna Part Number 2150106- 32 reservoir in accordance with the installation procedures contained in Paragraphs (c)(1) through (c)(6) of this AD. (B) For Model P210R (serial numbers P21000835 through and including P21000855), and T210R (serial numbers 21064898 through and including 21064929) airplanes remove the existing reservoir and install a Cessna Part Number 2150106-33 reservoir in accordance with the installation procedures contained in Paragraphs (c)(1) through (c)(6) of this AD. (b) The repetitive inspections requiredby Paragraph (a) (3) of this AD may be discontinued when the modification in Paragraph (a) (3) (A) or Paragraph (a) (3) (B) of this AD is accomplished. (c) If any cracks are detected in the outlet fitting in accomplishing Paragraph (a) (2) of this AD, prior to further flight, remove the existing turbocharger oil reservoir and install a Cessna Part Number 2150106-32 reservoir (for Model P210N serial numbers P21000001 through P21000834) or Part Number 2150106-33 reservoir (for Model P210R serial numbers P21000835 through and including P21000855) and Model T210R, (serial numbers 21064898 through and including 21064929) airplanes available from Cessna Aircraft Company using the following procedure: (1) Install the check valve with the arrow pointing away from the oil reservoir outlet fitting. (2) Use a wrench on the reservoir fitting to isolate the torque when tightening the check valve. (3) Attach the breather vent line. (4) Mount the rubber flexible hanger to the firewall and reservoir. (5) Initially secure the oil inlet and outlet lines by hand. Then use a wrench on the oil reservoir inlet fitting and the check valve fitting to isolate the effects of tightening the oil scavenge hoses. Tighten the oil scavenge hoses to the turbocharger oil reservoir. (6) Run the engine to check for oil leaks and eliminate any leaks prior to returning the airplane to service. (d) An equivalent method of compliance may be used if approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, Central Region, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. Cessna Single Engine Service Bulletin SE85-11, dated June 7, 1985, covers the subject matter of this AD. This amendment becomes effective on August 9, 1985, to all persons except those to whom it has already been made effective by priority letter from the FAA dated June 6, 1985, and is identified as AD 85-11-07.
85-03-06 R1: 85-03-06 R1 BOEING: Amendment 39-4998 as amended by Amendment 39-5205. Applies to Model 737 series airplanes certificated in all categories listed in Boeing Service Bulletin 737-53- 1031, Revision 3, dated October 28, 1983. To prevent rapid decompression resulting from undetected cracking of the wing-to-body drag angle, accomplish the following (unless previously accomplished) prior to the accumulation of 8,000 landings on Group I airplanes, or 35,000 landings on Group II airplanes, or within 1 year or 4,000 landings from the effective date of this AD, whichever occurs later: \n\n\tA.\tVisually inspect the upper drag angles for cracks in accordance with the Flight Safety Addendum of Boeing Service Bulletin 737-53-1031, Revision 3, or later FAA approved revisions. Repeat the visual inspections at intervals not to exceed 4,000 landings.\n \n\tB.\tIf cracks are found, replace cracked parts with new aluminum parts and continue the inspections of paragraph A., above, or modify in accordance with the Accomplishment Instructions in Boeing Service Bulletin 737-53-1031, Revision 1, or later FAA-approved revisions. \n\n\tC.\tModification of airplanes in accordance with Accomplishment Instructions of Boeing Service Bulletin 737-53-1031, Revision 1, or later FAA-approved revisions, constitutes terminating action for this AD. \n\n\tD.\tAirplanes may be flown to a maintenance base for drag angle replacement or modification in accordance with FAR 21.197 and 21.199 with prior approval of the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tE.\tFor purposes of complying with the AD, subject to acceptance by the assigned FAA Principal Maintenance Inspector, the number of landings may be determined by dividing each airplane's time in service by the operator's fleet average time from takeoff to landing for the airplane type. \n\n\tF.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, Northwest Mountain Region, Seattle, Washington. \n\n\tG.\tUpon request by the operator, an FAA Principal Maintenance Inspector, subject to prior approval by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the repetitive inspection intervals in this AD, if the request contains substantiating data to justify the increase for the operator. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tAmendment 39-4998 became effective March 11, 1985. \n\tThis Amendment 39-5205 becomes effective February 3, 1986.
2025-04-08: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2B19 (Regional Jet Series 100 and 440), CL-600-2C10 (Regional Jet Series 700, 701, and 702), CL-600- 2C11 (Regional Jet Series 550), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by the determination that radio altimeters cannot be relied upon to perform their intended function if they experience interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band). This AD requires installing a new radio frequency (RF) bandpass filter on the coaxial line between the radio altimeter and the receive antenna in the aft equipment compartment. The FAA is issuing this AD to address the unsafe condition on these products.
86-07-06: 86-07-06 BOEING: Amendment 39-5270. Applies to Model 747 series airplanes, listed in Boeing Service Bulletin 747-54-2111, Revision 1, dated November 22, 1985, certificated in any category. To prevent failure of the forward lug of an inboard pylon upper link, accomplish the following, unless already accomplished: \n\n\tA.\tWithin the next 850 landings after the effective date of this AD or prior to the accumulation of 8,000 landings, whichever occurs later, perform a close visual or ultrasonic inspection of the forward lug of the inboard pylon upper link for cracks in accordance with Boeing Service Bulletin 747-54-2111, Revision 1, dated November 22, 1985, or later FAA- approved revision. \n\n\tNOTE: Definition of close visual (detailed) inspection method: Close intensive visual inspections of highly defined structural details or locations searching for evidence of structural irregularity. Using adequate lighting and where necessary, inspection aids such as mirrors, etc., surfacecleaning and access procedures may be required to gain proximity. \n\n\tB.\tCracked parts must be replaced or modified prior to further flight. The part may be modified, if cracking is within rework limits, by the installation of bushings of a new design in accordance with Boeing Service Bulletin 747-54-2111, Revision 1, dated November 22, 1985, or later FAA-approved revision. \n\n\tC.\tIf no cracks are found, perform repetitive inspections, as described in paragraph A., above, at the following intervals: \n\n\t\t1.\tIf the immediately prior inspection was a close visual inspection, reinspect within the next 850 landings. \n\n\t\t2.\tIf the immediately prior inspection was an ultrasonic inspection, reinspect within the next 1,700 landings. \n\n\tD.\tInstallation of inboard pylon upper links that have been modified in accordance with Boeing Service Bulletin 747-54-2111, Revision 1, dated November 22, 1985, or later FAA- approved revision, is considered to be terminating action for the requirementsof this AD. \n\n\tE.\tCompliance with this AD does not terminate the inspection requirements of the Supplemental Structural Inspection Document (SSID) Airworthiness Directive AD 84-21-02 (Amdt. 39-4936; 49 FR 44890), if applicable. \n\n\tF.\tUpon the request of an operator, an FAA Principal Maintenance Inspector, subject to prior approval of the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the inspection times specified in this AD to permit compliance at an established inspection period of that operator, if the request contains substantiating data to justify the change for that operator. \n\n\tG.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tH.\tSpecial flight permits may 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. \n\n\tAll persons affected by this proposal who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective May 8, 1986.
2013-15-11: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 727 airplanes. This AD was prompted by a report of cracking in the left-side chord of the fin closure rib on the vertical stabilizer. This AD requires repetitive inspections of the left and right side chords of the fin closure rib for cracking and corrosion, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct cracking and corrosion in the left- and right-side chords of the fin closure rib, which could lead to widespread cracking in the chords that might weaken the fin closure rib structure and result in loss of airplane control due to lack of horizontal stabilizer support.
2013-15-14: We are superseding airworthiness directive (AD) 2008-06-29, which applied to all The Boeing Company Model 737-300, -400, and -500 series airplanes. AD 2008-06-29 required repetitive inspections of the downstop assemblies on the main tracks of the No. 2, 3, 4, and No. 5 slats and the inboard track of the No. 1 and 6 slats to verify if any parts are missing, damaged, or in the wrong order; other specified actions; and related investigative and corrective actions if necessary. This new AD retains these requirements and adds an inspection of the slat can interior for foreign object debris (FOD), and removal of any FOD found; modification of the slat track hardware; an inspection for FOD and for damage to the interior surface of the slat cans; and related investigative and corrective actions, if necessary. This AD was prompted by development of a modification by the manufacturer, which, when installed, would terminate the repetitive inspections. We are issuing this AD to prevent loose or missing parts in the main slat track downstop assemblies, which could puncture the slat track housing and result in a fuel leak and consequent fire.
75-17-10: 75-17-10 SLINGSBY SAILPLANES: Amendment 39-2312. Applies to T59D Kestrel gliders certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent structural failure of the elevator actuator bracket, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 5 hours' time in service, visually inspect the elevator actuator bracket P/N 59A-30-11 for cracks in the inside welded corners. (b) If cracks are found, prior to further flight, replace the elevator actuator bracket, P/N 59A-30-11, with a machined aluminum bracket, P/N 59A-03-8A/B/C, in accordance with Slingsby Sailplanes Technical Instruction No. 65, Issue 2, dated May 23, 1974, or an FAA- approved equivalent. (c) The inspections required by paragraph (a) of this AD may be discontinued after a machined aluminum elevator actuator bracket, P/N 59A-03-8A/B/C, has been installed in place of P/N 59A-30-11 in accordance with Slingsby Sailplanes Technical Instruction No. 65, Issue 2, dated May 23, 1974, or an FAA-approved equivalent. This amendment becomes effective August 18, 1974.
97-17-08: This amendment adopts a new airworthiness directive (AD) that is applicable to Raytheon Aircraft Company (Raytheon) Model 1900D airplanes (formerly known as Beech Aircraft Corporation Model 1900D airplanes) that have not had the propeller removed and re-installed since factory installation. This action requires inspecting the propeller mounting bolts for the proper torque and replacing or re-torquing any propeller bolt with the wrong torque level. The manufacturer discovered some under-torqued propeller mounting bolts during factory installation of the propeller. The actions specified by this AD are intended to prevent fatigue cracking and failure of the propeller mounting bolts, which if not detected and corrected, could result in loss of the propeller. Comments for inclusion in the Rules Docket must be received on or before October 30, 1997.
2013-16-04: We are adopting a new airworthiness directive (AD) for all Eclipse Aerospace, Inc. Model EA500 airplanes equipped with Avio, Avio with ETT, or Avio NG 1.0 avionics suites. This AD was prompted by a report of potential aircraft hardware failure in the autopilot control panel and the center switch panel. This AD requires either incorporating updates to the aircraft computer system software or incorporating a temporary revision to the aircraft flight manual. We are issuing this AD to correct the unsafe condition on these products.
2025-05-13: The FAA is adopting a new airworthiness directive (AD) for certain Pratt & Whitney Canada Corp. (P&WC) Model PW535E and PW535E1 engines. This AD was prompted by a manufacturer design review that indicated certain flange bolts securing the gas generator case and turbine support case are susceptible to cracking at their current low- cycle fatigue (LCF) life. This AD requires repetitive borescope inspections (BSI) of the gas generator case to turbine support case retaining bolts for evidence of bolt cracks, bolt fracture, missing bolts, or loose bolts and replacement, if necessary, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2013-15-12: We are superseding airworthiness directive (AD) 2004-15-07, for certain Airbus Model A310 series airplanes. AD 2004-15-07 required repetitive inspections for fatigue cracking of the area around the fasteners of the landing plate of the aileron access doors of the bottom skin panel of the wings, and related corrective action. AD 2004- 15-07 also provided for an optional terminating action to end the repetitive inspections. This new AD reduces the initial inspection compliance time and intervals, and provides additional terminating action options. This AD was prompted by a reassessment of a previous fatigue threshold and inspection interval, which resulted in a determination that reduced inspection thresholds and intervals for accomplishment of the tasks are necessary. We are issuing this AD to detect and correct fatigue cracking of the area around the fasteners of the landing plate of the aileron access doors and the bottom skin panel of the wings, which could result in reducedstructural integrity of the wings.
97-26-05: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model HS 748 series airplanes. This action requires inspections of the inspection holes in all engine W frame socket fittings to determine if certain fasteners have been installed, or if the inspection holes have been reworked; and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent fatigue cracking at the inspection hole locations, due to the installation of certain fasteners or hole enlargement, which could result in failure of the engine mount structure and consequent separation of the engine from the airplane.
2021-17-10: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model A109A, A109A II, A109C, A109E, A109K2, A109S, and AW109SP helicopters, having a certain rotor brake kit installed. This AD was \n\n((Page 46763)) \n\nprompted by a report of un-commanded activation of the rotor brake system before take-off due to a jammed rotor brake control cable and subsequent partially open brake control valve. This AD requires repetitive inspections of the rotor brake control cable and replacement of the rotor brake control cable, if necessary, 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.
2013-15-09: We are adopting a new airworthiness directive (AD) for all Pratt & Whitney Division (PW) turbofan engine model PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 with a certain second- stage high-pressure turbine (HPT) air seal part number installed. This AD was prompted by discovery of cracks in second-stage HPT air seals. This AD requires inspection and removal from service of HPT air seals that fail inspection. We are issuing this AD to prevent failure of the second-stage HPT air seal, which could lead to an uncontained engine failure and damage to the airplane.
70-25-05: 70-25-05 AMERICAN AVIATION: Model AA-1. Amdt. 39-1118. Applies to American Aviation Model AA-1, Serial Number AA1-0001 through AA1-0125 airplanes certificated in all categories. Unless already accomplished, compliance required within the next 25 hours in service or within three (3) weeks from the effective date of this AD, whichever occurs first. To preclude binding of the trim actuator and elevator centering bungee in the existing bearing, comply with Item 1, "Bungee Mounting Plate Replacement," of American Aviation Service Letter No. 69-1A, dated July 10, 1969, or later revision or equivalent modification, either of which must be approved by the Chief, Engineering and Manufacturing Branch, FAA - Eastern Region. This amendment is effective December 8, 1970.
2000-12-02: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Pratt & Whitney PW4000 Series Turbofan Engines, that currently requires revisions to the Time Limits Section of the manufacturer s Engine Manuals (EM s) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action adds additional critical life-limited parts for enhanced inspection. This amendment is prompted by additional focused inspection procedures for other critical life-limited rotating engine parts that have been developed by the manufacturer. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
2003-11-04: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplanes, that requires inspections of the linear variable differential transducers (LVDTs) of the autopilot for discrepancies, and follow-on actions if necessary. This amendment is prompted by information from the manufacturer advising that certain LVDTs were delivered with an undersize nylok element on the threaded extension. The actions specified by this AD are intended to prevent failure of the LVDTs, which could result in an automatic pitch trim malfunction or an autopilot disconnect, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2025-05-06: The FAA is superseding Airworthiness Directive (AD) 2022-01-02, which applied to certain De Havilland Aircraft of Canada Limited Model DHC-8-400, -401, and -402 airplanes. AD 2022-01-02 required inspecting for corrosion of the nacelle to wing rear spar attachment pins, and the nacelle to landing gear attachment pins, and doing all applicable corrective actions. This AD was prompted by a determination that some operators were unable to identify the airplanes subject to each requirement. This AD continues to require the actions specified in AD 2022-01-02, clarifies the affected airplanes for each required action, and revises the applicability by removing Model DHC-8-400 airplanes; as specified in Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2013-15-08: We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney Canada Corp. (P&WC) PW118A, PW118B, PW119B, PW119C, PW123, PW123B, PW123C, PW123D, PW123E, PW123AF, PW124B, PW125B, PW126A, PW127, PW127E, PW127F, PW127G, and PW127M turboprop engines. This AD was prompted by reports of fractures of the first-stage power turbine (PT) blade. This AD requires inspection of the first-stage PT blades and the removal from service of those blades that fail the inspection or their replacement with blades eligible for installation. We are issuing this AD to prevent fracture of the first-stage PT blade, possible engine fire, and damage to the airplane.
97-03-17: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747 and 757 series airplanes, that requires repetitive visual inspections to detect discrepancies of the wire terminal assembly, electrical connector, and wire insulation on the fuel pump; and replacement of the fuel pump with a new fuel pump, if necessary. This amendment also requires repetitive insulation resistance tests of the fuel pump wiring. This amendment is prompted by reports of fuel leaks at the fuel boost and override/jettison pumps due to corrosion. The actions specified by this AD are intended to prevent such a fuel leakage, which could result in a fire at the location of the affected fuel pump.
73-24-02: 73-24-02 SEMCO: Amendment 39-1746 is further amended by Amendment 39-2741. Applies to Model 30-AL, Serial Numbers SEM C1, SEM C2, SEM 11 to SEM 118 inclusive, Model TC-4A, Serial Numbers SEM 81 to SEM 118 inclusive, and Model "Model T," Serial Numbers SEM 28, SEM 60, SEM 61, SEM 62, SEM 64 through SEM 73, SEM 76, SEM 77 and SEM 78 to SEM 118 inclusive balloons certificated in all categories. Compliance required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To prevent inadvertent fuel leakage accomplish either 1 or 2 below: 1. (a) Remove the Amflo quick change female coupler part number C-2 from the lower end of the Imperial fuel hose Part Number Y905. NOTE: This is the vertical fuel hose connecting the tank to the burner valve. (b) Install an Amflo quick change male plug Part Number CP-2 or an equivalent part approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, on the lower end of the Imperial fuel hose Part Number Y905. (c) Remove the Amflo quick change male plugs Part Number CP-1 from the fuel tank 1/4" brass tee. (d) Install an Amflo quick change female coupler Part Number C-1 or an equivalent part approved by Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, into the fuel tank 1/4" brass tee. 2. (a) Remove the Amflo quick change female coupler Part Number C-2 from the lower end of the Imperial fuel hose part number Y905. NOTE: This is the vertical fuel hose connecting the tank to the burner valve. (b) Remove the Amflo quick change male plug, Part Number CP-1, from the fuel tank 1/4" brass tee. (c) Install an AN 901-2 coupling and the Amflo quick change male plug part number CP-1 which was removed in step (b) or equivalent parts approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, onto the lower end of the Imperial fuel hose Part Number Y905. (d) Install an AN 911-2 nipple and the Amflo quick change female coupling Part Number C-2 which was removed in step (a) or equivalent parts approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, into the 1/4" brass tee at the fuel tank. Amendment 39-1746 became effective November 26, 1973. This amendment 39-2741 becomes effective October 20, 1976.
2025-05-04: The FAA is superseding Airworthiness Directive (AD) 2019-05- 02, which applied to certain Rolls-Royce Deutschland Ltd & Co KG (RRD) (type certificate previously held by Rolls-Royce plc) Model RB211-Trent 970-84 and RB211-Trent 972-84 engines. AD 2019-05-02 required repetitive inspections of the drains mast for any crack and replacement or repair of the drains mast if necessary. Since the FAA issued AD 2019-05-02, the manufacturer has developed a modification (improved drains mast and drains support bracket), which the FAA has determined mitigates the unsafe condition. This AD was prompted by cracks found in the transition duct area of the drains mast. This AD requires modification with improved drains mast and drains support bracket. The FAA is issuing this AD to address the unsafe condition on these products.
2013-16-06: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model BO-105A, BO-105C, BO- 105LS A-1, BO-105LS A-3, and BO-105S helicopters. This AD requires inspecting for debonding of the erosion protective shell (abrasion strip) on the leading edge of each main rotor blade. This AD was prompted by the discovery of abrasion strip debonding during an inspection on one Model BO-105 helicopter and also by an incident on a second Model BO-105 helicopter that lost its abrasion strip in-flight. The actions of this AD are intended to detect debonding of the main rotor blade abrasion strip, which could lead to an unbalanced main rotor, high vibrations, damage to the tail boom or tail rotor, and loss of control of the helicopter.