Results
2021-05-03: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model EC225LP helicopters. This AD requires various inspections of the left-hand side (LH) engine fuel supply (fuel supply) hose and depending on the inspection results, reinstalling the fuel supply hose or removing the fuel supply hose from service. Additionally, this AD requires installing an improved part and prohibits installing a certain part-numbered LH fuel supply hose on any helicopter unless it is installed by following certain procedures. This AD was prompted by a report of an incorrect installation of the LH fuel supply hose causing restricted fuel flow to the LH engine. The FAA is issuing this AD to address the unsafe condition on these products.
2004-12-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes. This AD requires replacement of a certain transformer rectifier unit (TRU) with a certain new TRU. This action is necessary to prevent ignition of the input filter capacitors of the TRU in position 2 of the avionics compartment, which could potentially result in smoke in the cockpit. This action is intended to address the identified unsafe condition.
48-07-01: 48-07-01 CESSNA: Applies to 120 and 140 Aircraft Serial Numbers 8001 Through 14329. Compliance required by May 1, 1948, and at each annual inspection thereafter. Inspect the two bolts attaching the horizontal stabilizer to the fin post for tightness and proper length. If no bolt threads extend through the fiber lock rings of the anchor nuts inside the stabilizer attachment fitting, or if the bolts show any indication of having backed off when checked with a wrench, they should be replaced with AN 4-5A bolts on Serial Nos. 10091 and up, or AN 3-5A bolts on earlier serial numbers. In making the tightness check use caution to avoid stripping the threads in the anchor nut. If the new bolts do not develop at least 3 inch- pounds torque in the anchor nut, AN 4-H5A or AN 3-H5A (drilled head) bolts should be substituted and safetied together with wire. Check the clearance of the elevator horn and horn bolts with respect to the cutouts in the fin spar and increase it to a minimum of 1/8 inch wherever necessary. (Cessna Service Letter No. 52 covers this same subject.)
47-41-02: 47-41-02 BELL: (Was Mandatory Note 14 of AD-1H-2.) Applies to Models 47B and 47B3 Helicopters. Compliance required prior to next flight after receipts of parts from Bell Aircraft Corp., but, in any event, not later than January 1, 1948. To prevent excessive vibration and subsequent failure of the main oil line from the oil cooler to the oil filter, two additional supports must be installed for this oil line, one each at the bends near the oil filter and oil cooler. (Bell Service Bulletin 47C28 (revised), dated July 1, 1947, covers this same subject.)
2012-13-01: We are adopting a new airworthiness directive (AD) for all Saab AB, Saab Aerosystems Model 340A (SAAB/SF340A) and SAAB 340B airplanes. This AD was prompted by reports indicating that wear of the elevator pushrods has occurred on some airplanes after extended time in service. This AD requires determining if a certain part number is installed, performing a detailed inspection for individual play between the elevator pushrod assembly and degradation of elevator pushrod assembly, and replacing the affected elevator pushrod assembly with a new elevator pushrod assembly if necessary. We are issuing this AD to prevent a free elevator from affecting the pitch control authority, which may result in reduced controllability of the airplane.
2004-12-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 series airplanes, that requires repetitive inspections of the intercostals that back up the door stops and hinges at door 2 left and door 2 right for cracks, and corrective action, if necessary. This amendment also provides for an optional terminating action for the repetitive inspections. This action is necessary to prevent fatigue cracks from propagating in the intercostals, which could lead to the loss of a door in flight and subsequent rapid decompression. This action is intended to address the identified unsafe condition.
47-21-19: 47-21-19 REPUBLIC: (Was Mandatory Note 9 of AD-769-2.) Applies to Model RC-3 Aircraft Serial Numbers 5 to 238, Inclusive. Compliance required not later than the next 25 hours of operation subsequent to July 1, 1947, but in no case later than September 1, 1947. Inspect parking brake, battery, mixture and carburetor heat flexible controls for presence of brass ferrule or AN 742D3 clamp on split sleeve at operating end of these controls. If clamp or ferrule is not installed, split metal sleeve can open permitting casing to slide out when control is actuated thus rendering the control ineffective. The above clamp should be installed immediately. (Seabee Service News No. 10, dated January 13, 1947, covers this subject.)
2012-11-13: We are adopting a new airworthiness directive (AD) for the Aeronautical Accessories, Inc. (AAI), High Landing Gear Aft Crosstube Assembly (aft crosstube) installed on certain Bell Helicopter Textron, Inc. (Bell) and Agusta S.p.A. (Agusta) model helicopters as an approved Bell part installed during production or based on a Supplemental Type Certificate (STC). This AD requires certain recurring visual, dimensional, and fluorescent penetrant inspections of each aft crosstube, and replacing any cracked crosstube. This AD also requires establishing a life limit and creating a component history card or equivalent record for one of the affected part-numbered aft crosstubes. This AD was prompted by three reports of failed crosstubes because of cracks. The actions are intended to prevent failure of a crosstube, collapse of the landing gear, and subsequent loss of control of the helicopter.
2021-23-01: The FAA is adopting a new airworthiness directive (AD) for all Stemme AG Model Stemme S 12 gliders. This AD was prompted by mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as an airspeed indicator (ASI) with speed markings inconsistent with the approved and published values. This AD requires inspecting the ASI markings and, depending on findings, either replacing the ASI or amending the existing aircraft flight manual (AFM) until the ASI is replaced. The FAA is issuing this AD to address the unsafe condition on these products.
2000-01-19: This amendment adopts a new airworthiness directive (AD) applicable to Eurocopter Deutschland GMBH (ECD) Model EC 135 P1 and EC 135 T1 helicopters. This action requires inspecting main rotor expansion bolt safety wires, bolt heads, and bolt nuts; replacing any unairworthy expansion bolt with a hexagon bolt; and, as necessary, replacing any bolt nut before further flight. This AD also requires replacing each expansion bolt, regardless of condition, no later than January 31, 2000. This amendment is prompted by reports of main rotor blade expansion bolt nuts becoming loose. This condition, if not corrected, could result in severe vibration during flight and subsequent loss of control of the helicopter.
2004-12-16: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F series airplanes, that currently requires repetitive inspections to verify operation of the remote control circuit breakers (RCCB) of the alternating current (AC) cabin bus switch, and replacement of any discrepant RCCB with a new RCCB. This amendment requires the existing actions per a later service bulletin revision. The actions specified by this AD are intended to prevent propagation of smoke and fumes in the cockpit and passenger cabin due to one or more inoperable RCCBs of the AC cabin bus switch during smoke and fume isolation procedures. This action is intended to address the identified unsafe condition.
67-03-06: 67-03-06 LOCKHEED: Amdt. 39-341 Part 39 Federal Register January 20, 1967. Applies to Models 188A and 188C Series Airplanes Except Those Which Incorporate the P/N 2007-3 Piston in the Main Landing Gear Door Actuating Cylinders. Compliance required as indicated. To detect cracking in the radius of the junction of the piston head and piston rod of part number 1662-3, accomplish the following: (a) Within the next 50 landings after the effective date of this AD, unless already accomplished within the last 50 landings before the effective date of this AD, and thereafter at intervals not to exceed 100 landings from the last inspection until 700 landings after the effective date of this AD has been reached, accomplish the following or an equivalent approved by the Chief, Aircraft Engineering Division, FAA, Western Region. (1) Inspect visually the MLG door actuating cylinders for indications of loss of hydraulic fluid through the air vent filters of the cylinder. Ref: Item14, Figure 3, Section 32-2 of Electra Parts Catalog. (2) If leakage is noted during the inspection required in (a)(1) before further flight, comply with the accomplishment instructions of Lockheed Service Bulletin 88/SB-642, Section 2, Part II, Items A through I. Items E and F of the Accomplishment Instructions notwithstanding, replace a cracked P/N 1662-3 piston with a P/N 2007-3 piston, or an uncracked P/N 1662-3 piston with less than 2,050 landings, or an uncracked P/N 1662-3 piston with more than 2,050 landings that has been shot peened in accordance with Lockheed Service Bulletin 88/SB-642, Section II, Item F. Shot peening is not required on previously shot-peened P/N 1662-3 pistons. All P/N 1662-3 pistons with less than 2,050 landings must be shot peened, if uncracked, before the accumulation of 2,050 landings. Those P/N 1662-3 pistons with more than 2,050 landings, if uncracked, must be shot peened before further flight. (b) Within the next 700 landings after the effective date of this AD, unless already accomplished within the last 700 landings before the effective date of this AD, and thereafter at intervals not to exceed 1,400 landings from the date of the last inspection, comply with the accomplishment instruction required in (a)(2). (c) The requirements of this AD may be discontinued when the P/N 1662-3 piston is replaced by a P/N 2007-3 piston. (d) For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type. (e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD, to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. (Lockheed Service Bulletin 88/SB-642 covers this same subject.) This directive effective January 20, 1967.
47-27-02: 47-27-02 DOUGLAS: (Was Service Note 4 of AD-762-7.) Applies to All C-54-DC Series and DC-4 Airplanes. \n\n\tInspection required at intervals not to exceed 170 hours. \n\n\tOpen the quick-opening type inspection doors in the bottom of the outer wing and center wing section surfaces forward of the front spar and aft of the center spar. Inspect spar web structure for loose rivets, cracks, or other irregularities. Pay particular attention in the fuel tank areas for evidence of fuel leaks which will indicate cracked spar webs or rivets and seam leaks. \n\n\tAll spar web cracks which are found after accomplishment of AD 46-27-01 (Service Bulletin C-54-205. "Rework - Integral Fuel Tanks") or cracks that are located in areas to which the Service Bulletin C-54-205 does not apply, should be repaired in accordance with Douglas Drawing No. 5354811, "Service Rework-Station 463, Outer Wing, Center Spar", and No. 3344236, "Repair-Integral Tank Spar Web Crack". \n\n\tRevised March 21, 1961.
2012-12-14: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200 and -300 series airplanes. This AD was prompted by reports of fatigue cracking on the lower main sill inner chord of the hatch opening of the overwing emergency exit. This AD requires repetitive inspections for cracking, corrosion damage, and any other irregularity of the lower main sill inner chord and surrounding structure, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking on the lower main sill inner chord of the hatch opening of the overwing emergency exit, which could result in reduced structural integrity of the hatch opening of the overwing emergency exit and consequent rapid decompression of the airplane.
2021-24-21: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model EMB-500 and EMB-505 airplanes. This AD was prompted by a report that the operational envelope does not contain airspeed limitations and procedures for operating the airplane at static air temperatures below -54 [deg]C. This AD requires revising the airplane flight manual (AFM) to incorporate new and revised airspeed limitations and procedures. The FAA is issuing this AD to address the unsafe condition on these products.
86-26-01: 86-26-01 DEHAVILLAND AIRCRAFT COMPANY OF CANADA, A DIVISION OF BOEING OF CANADA, LTD.: Amendment 39-5496. Applies to all Model DHC-8-101 and - 102 series airplanes, certificated in any category, equipped with upper and lower fore rudder mounting brackets, P/N's 85530097-105 and -107. Compliance required as indicated, unless previously accomplished. To prevent the failure of the fore rudder upper and lower mounting brackets and fin rear spar web accomplish the following: A. Within the next 100 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 200 hours time-in-service, conduct a visual inspection of the upper and lower fore rudder mounting brackets in accordance with the Accomplishment Instructions of de Havilland Aircraft Company of Canada Service Bulletin No. 8-55-7, dated October 3, 1986. 1. If cracks are found in the mounting brackets, prior to further flight: a. Conduct a visual inspection of the upper spar web for cracks in the vicinity of the mounting brackets in accordance with the Accomplishment Instructions of de Havilland Aircraft Company of Canada Service Bulletin No. 8-55-7, dated October 3, 1986. b. Reinforce the fore rudder mounting brackets by installing de Havilland Modifications 8/0647 in accordance with the Accomplishment Instruction of de Havilland Aircraft Company of Canada Service Bulletin No. 8-55-7, dated October 3, 1986. 2. If, after accomplishing the visual inspection required by paragraph A.1.a., above, cracks are found in the spar web, prior to further flight, replace the cracked spar web with a new web in accordance with de Havilland Dash 8 Maintenance Manual (PSM 1-8-2), or accomplish an FAA-approved repair. B. Within 500 hours time-in-service after the effective date of this AD, install de Havilland Modification 8/0647 in accordance with the Accomplishment Instructions of de Havilland Aircraft Company of Canada Service Bulletin No. 8-55-7, dated October 3, 1986. Prior to installation of Modification 8/0647, conduct the visual inspections required by paragraph A., above, and perform the repair required by paragraph A.2., above, if necessary. C. Incorporation of de Havilland Modification 8/0647 constitutes terminating action for the repetitive inspection of paragraph A.., above. D. 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, New York Aircraft Certification Office, FAA, New England Region. E. Special 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. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to The de Havilland Aircraft Company of Canada, A Division ofBoeing of Canada Ltd., Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. This amendment becomes effective January 5, 1987.
47-25-10: 47-25-10 CONVAIR: (Was Service Note 4 of AD-2-571-2.) Applies to All BT-13 Series Airplanes Equipped With Wood Elevator Tabs. Compliance required not later than September 1, 1947, and each 20 hours of operation thereafter. The elevator tabs should be closely inspected to determine if any sign of glue failure, dry rot, or cracking of plywood exists adjacent to glue joints. Attachment of aluminum alloy extension to tab may have weakened the trailing edges of wood tabs or weathering of wood may have caused deterioration. If any failure or deterioration is found, the tab should be immediately replaced or repaired in an adequate manner.
94-22-03: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that requires modification of the power transfer unit (PTU). This amendment is prompted by reports of fatigue cracks found in the drain port housings of the PTU's on several airplanes. The actions specified by this AD are intended to prevent failure of the PTU housing due to fatigue cracking, which could result in the loss of both hydraulic systems (until the PTU is shut off).\n\n\tThe incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of November 28, 1994.
2004-12-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 airplanes, that currently requires, among other actions, replacement of the existing air driven generator (ADG) wire assembly in the right air conditioning compartment with a certain new wire assembly. This amendment requires replacement of the ADG wiring and two associated clamps; inspection of the ADG wiring for correct wire identification, riding, and damage, and inspection of the associated routing/clamps for correct installation; and corrective actions if necessary. The actions specified by this AD are intended to prevent loss of the charging capability of the airplane battery due to chafing. Loss of the charging capability of the airplane battery, coupled with a loss of all normal electrical power, could prevent continued safe flight and landing of the airplane. This action is intended to address the identified unsafe condition.
2021-25-12: The FAA is superseding Airworthiness Directive (AD) 2017-19- 09, which applied to certain De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Model DHC-8-400 series airplanes. AD 2017-19-09 required modifying the nose landing gear (NLG) shock strut assembly. This new AD requires repetitive lubrications of the trailing arm of the NLG. This new AD also requires revising the existing maintenance or inspection program to include new and revised airworthiness limitations (life limits for certain bolts). This AD was prompted by reports of a certain bolt being found missing or having stress corrosion cracking. The FAA is issuing this AD to address the unsafe condition on these products.
93-06-07: 93-06-07 DE HAVILLAND, INC.: Amendment 39-8532. Docket 92-NM-81-AD. Applicability: Model DHC-7 series airplanes, serial numbers 003 through 113, inclusive; Model DHC-8-102 and -103 series airplanes, serial numbers 003 through 321, inclusive; and Model DHC-8-301 and -311 series airplanes, serial numbers 100 through 320, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the loss of both hydraulic systems due to depletion of hydraulic fluid, accomplish the following: (a) For Model DHC-7 series airplanes: Within 1,000 hours time-in-service after the effective date of this AD, or within 6 months after the effective date of this AD, whichever occurs first, remove the existing Quantity Limiting Valves (QLV), from the left- and right-hand inboard nacelles; and modify or replace them with new QLV, Modification 7/2610; in accordance with de Havilland Service Bulletin S.B. 7-29-20, dated March 20, 1992. (b) For Model DHC-8-102 and -103 series airplanes and Model DHC-8-301 and -311 series airplanes that have accumulated 6,700 total hours time-in-service or more as of the effective date of this AD, or if 50 months or more have passed since the airplane was manufactured as of the effective date of this AD: Within 1,000 hours time-in-service after the effective date of this AD, or within 6 months after the effective date of this AD, whichever occurs first, remove the existing QLV from the left- and right-hand inboard nacelles; and modify or replace them with new QLV, Modification 8/1803; in accordance with de Havilland Service Bulletin S.B. 8-29-21, dated March 20, 1992. (c) For Model DHC-8-102 and -103 series airplanes and Model DHC-8-301 and -311 series airplanes that have accumulated less than 6,700 total hours time-in-service as of the effective date of this AD and if less than 50 months have passed since the airplane was manufactured as of the effective date of this AD:Prior to the accumulation of 7,700 hours time-in-service since the airplane was manufactured, or within 12 months after the effective date of this AD, whichever occurs first, remove the existing QLV from the left- and right-hand inboard nacelles; and modify or replace them with new QLV, Modification 8/1803; in accordance with de Havilland Service Bulletin S.B. 8-29-21, dated March 20, 1992. (d) 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, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (e) 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. (f) The removal, modification, and replacement shall be done in accordance with de Havilland Service Bulletin S.B. 7-29-20, dated March 20, 1992 (for Model DHC-7 series airplanes); or de Havilland Service Bulletin S.B. 8-29-21, dated March 20, 1992 (for Model DHC-8-102 and -103 series airplanes and Model DHC-8-301 and -311 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 de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on May 12, 1993.
94-04-18: This amendment supersedes Airworthiness Directive (AD) 92-24-01, which currently requires inspecting the elevator balance arm assemblies of certain Beech Aircraft Corporation Models 34C and T34C-1 airplanes to ensure that sufficient welds exist to secure the balance weight tube to the attachment plate, and also requires replacing the assembly if insufficient welds are found. The Federal Aviation Administration (FAA) has determined that the existing AD should also apply to certain Beech Model T34C airplanes. This action retains the requirements of AD 92-24-01 and incorporates these Beech Model T34C airplanes. The actions specified by this AD are intended to prevent separation of an elevator balance arm assembly from the elevator because of an insufficient weld, which could result in loss of control of the airplane.
2004-12-12: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes. This action requires repetitive inspections for cracks or evidence of damage/distortion of the anti-skid drive coupling clips for the hubcaps of the main landing gear (MLG) wheels; repetitive measurement of the gap and height dimensions of the coupling clips; corrective actions, if necessary; and eventual replacement of all coupling clips with new, improved coupling clips. This action is necessary to prevent excessive gaps in the anti-skid drive coupling clips for the hubcaps of the MLG, which could result in momentary loss of the normal braking system at low speeds, and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2012-12-01: We are superseding an existing airworthiness directive (AD) for all Airbus Model A300 B4-600, B4-600R and A300 F4-600R series airplanes, Model A300 C4-605R Variant F airplanes, and Model A310 series airplanes. That AD currently requires modifying the wiring in the right-hand electronics rack. This new AD requires replacing the cockpit multi-tank indicators (MTI), and for certain airplanes, replacing high-level, low-level, and overflow sensors and their harness connectors, and re-instating the low-level warning indication to the cockpit MTI. This AD was prompted by reports of failures of four fuel level sensor-amplifier and MTI units. This AD also adds Model A310 series airplanes to the applicability. We are issuing this AD to prevent degradation of the electrical insulation sleeves of the low- level indication lamps on the MTI, which could cause a short circuit that might result in high voltage being conveyed to the high- and low- level sensors in the wing tanks. This condition could cause the level sensor to heat above acceptable limits, possibly resulting in a fuel tank explosion, and consequent loss of the airplane.
2021-25-08: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AW189 helicopters. This AD was prompted by the determination that certain part-numbered fairings were never introduced into the main rotor (MR) tip lights kit design definition and were not certified for icing conditions. This AD requires replacing affected parts. This AD also prohibits, after modification of the helicopter as required, installing any affected part on any helicopter 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.