Results
97-23-06: 97-23-06 SCHWEIZER AIRCRAFT CORPORATION: Amendment 39-10194. Docket No. 96-SW-05-AD. Applicability: Model 269A, A-1, B, and C, and TH-55A helicopters, with main rotor transmission ring gear (ring gear), part number (P/N) 269A5104-5, identified by the letters EGC (Eastern Gear Corporation), ACR (ACR Industries), or the manufacturer code number 23751 (EGC) or 57152 (ACR), installed, certificated in any category. NOTE 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (f) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the ring gear, loss of drive to the main rotor gearbox, and a subsequent forced landing, accomplish the following: (a) Inspect the ring gear teeth for surface deterioration which includes pitting, excessive wearing, cracking or corrosion in accordance with Schweizer Service Bulletin B-244.2, dated February 19, 1996, as follows: (1) Before further flight, if a clicking or tapping sound or other unusual noise or unusual vibration is detected while operating the helicopter, or if a metal particle is found on the magnetic drain plug during routine maintenance; (2) Beforeinstalling a main rotor transmission which contains an affected ring gear on the helicopter; (3) Within the next 50 hours time-in-service (TIS) after the effective date of this AD, or at the next annual inspection, whichever occurs first. (b) Thereafter, inspect the ring gear teeth at intervals not to exceed 50 hours TIS in accordance with Schweizer Service Bulletin B-244.2, dated February 19, 1996. (c) If surface deterioration which includes pitting, excessive wearing, cracking or corrosion is discovered, before further flight, remove the transmission from service and replace the ring gear with a ring gear, P/N 269A5104-7, serial number (S/N) S2100 or higher number. (d) At the next main rotor transmission overhaul, remove and replace the ring gear, P/N 269A5104-5, identified on the face of the ring gear by the letters EGC, ACR, or the manufacturer code number 23751 (EGC) or 57152 (ACR) and replace it with a ring gear, P/N 269A5104-7, S/N S2100 or higher number. (e) Installation of a ring gear, P/N 269A5104-7, S/N S2100 or higher number constitutes a terminating action for the requirements of this AD and must be annotated on a component log card. A new component log card must be created if a component log card is not in the applicable maintenance records. (f) 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, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, New York Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York Aircraft Certification Office. (g) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the helicopter to a location where the requirements of this AD can be accomplished, provided no clicking or tapping sound or other unusual noise or unusual vibration was detected on any previous flight. (h) The inspections shall be done in accordance with Schweizer Service Bulletin B-244.2, dated February 19, 1996. 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 Schweizer Aircraft Corporation, P.O. Box 147, Elmira, NY 14902, ATTN: Publications Dept. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (i) This amendment becomes effective on December 10, 1997.
98-24-14: 98-24-14 CESSNA AIRCRAFT COMPANY: Priority Letter issued on November 13, 1998. Docket No. 98-CE-111-AD. Applicability: The following airplane models and serial numbers, certificated in any category, that are equipped with any WYE tube, P/N 9910299-25 or P/N 9910299-26, in the engine exhaust system: Model Serial Numbers 340A 215 through 1817 414A 1 through 1212 NOTE 1: This AD allows the aircraft owner or pilot to check the maintenance records to determine whether any WYE tube, P/N 9910299-25 or P/N 9910299-26, has been installed in the engine exhaust system since May 1998. See paragraph (c) of this AD for authorization. NOTE 2: Cessna is considering issuing service information pertaining to this subject. This AD takes precedence over any existing or future service information on this subject. NOTE 3: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repairedin the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated in the body of this AD, unless already accomplished. To detect and correct exhaust leaks caused by nonwelded exhaust system components, which could result in aluminum fuel lines bursting with consequent fuel spillage, an airplane fire, and/or an explosion, accomplish the following: (a) Prior to further flight after receipt of this priority letter AD, remove from service any P/N 9910299-25 or P/N 9910299-26 engine exhaust system WYE tube. These P/N 9910299-25 or P/N 9910299-26 WYE tubes may be replaced with any of the following in accordance with the instructions in the applicable maintenance manual or other applicable FAA-approved document: (1) P/N 9910299-8 (for the P/N 9910299-25) or P/N 9910299-9 (for the P/N 9910299-26) WYE tubes; or (2) Any other FAA-approved engine exhaust system WYE tube that is not P/N 9910299-25 or P/N 9910299-26. (b) As of the receipt of this priority letter AD, no person shall install, on any affected airplane, any P/N 9910299-25 or P/N 9910299-26 engine exhaust system WYE tube. (c) The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may check the maintenance records to determine whether any WYE tube, P/N 9910299-25 or P/N 9910299-26, has been installed in the engine exhaust system since May 1998. If one of these WYEtubes is not installed, the AD does not apply and the owner/operator must make an entry into the aircraft records showing compliance with this AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). (d) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Rm. 100, Mid-Continent Airport, Wichita, Kansas, 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from Wichita ACO. (e) Information related to this priority letter AD may be examined at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.(f) Priority letter AD 98-24-14, issued November 13, 1998, becomes effective immediately upon receipt.
2015-16-04: We are adopting a new airworthiness directive (AD) for certain Kidde Graviner hand-operated fire extinguishers. This AD was prompted by a report that a fire extinguisher failed to operate when the activation lever was pressed. This AD requires modifying the affected fire extinguishers. We are issuing this AD to prevent fire extinguishers from failing to operate in the event of a fire, which could jeopardize occupants' safety and continuation of safe flight and landing.
99-26-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) series airplanes, that requires, for certain airplanes, removing the hydraulic tube assemblies from the main landing gear (MLG) bay, installing new re-routed hydraulic tube assemblies, and repositioning a fuel line, as applicable. For certain other airplanes, this amendment requires a general visual inspection to determine the routing of certain hydraulic and fuel lines, and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent damage to hydraulic and fuel lines resulting from failure of an MLG, which could cause a fire in the MLG wheel well.
98-08-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-500 series airplanes. This action requires a one-time inspection to verify the installation of certain stringer clips at the junction of frame 34 and stringer 6, and installation of stringer clips, 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 in the skin of the fuselage, which could result in loss of pressure inside the airplane.
2003-14-21: This amendment supersedes an existing airworthiness directive (AD) that is applicable to Lockheed Martin L-1011-385 series airplanes. That AD currently requires modifications of the engine turbine cooling air overheat monitoring panel at the flight engineer/second officer's console, pilot's caution and warning light panel on the main instrument panel, and the installation of a high speed gearbox (HSGB) overheat detector system into the monitoring system for the engine turbine air temperature. This amendment requires the same modifications. In addition, this amendment adds Lockheed Martin L-1011-385 series airplanes with RB211-22B-02 series engines to the applicability, requires installation of a revised engine front bearing housing assembly, installation of a revised speed probe loom electrical support assembly, and installation of a low pressure (LP) compressor shaft extreme axial movement detector system. Also, this amendment requires additional modifications to the engine turbine cooling air overheat monitoring panel at the flight engineer/second officer's console, pilot's caution and warning light panel on the main instrument panel. The actions specified by this AD are intended to prevent undetected fires originating within the HSGB from breaching the HSGB case, which could result in engine damage and increased difficulty in extinguishing a fire, and to prevent undetected LP compressor shaft location bearing failure, which could result in LP compressor and turbine shaft assembly failure, turbine overspeed, and possible uncontained engine failure.
2015-15-12: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, and A320 series airplanes modified by a particular supplemental type certificate (STC). This AD was prompted by reports of cracks found during inspections of the in-flight entertainment system radome assembly. This AD requires repetitive detailed inspections for cracks in the radome assembly, and replacement of the radome if necessary. We are issuing this AD to detect and correct cracks in the radome assembly, which could result in the radome (or pieces) separating from the airplane and striking the tail, consequently reducing the controllability of the airplane.
98-20-26: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, and -231 series airplanes, that requires repetitive inspections to detect missing or cracked bolts and fittings of the frame-to-pressure-floor connection; and corrective actions, if necessary. This amendment also provides for optional terminating action for the repetitive inspections of the affected fittings. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct fatigue cracking in the bolts and fittings of the frame-to-pressure-floor connection, which could result in reduced structural integrity of the airplane.
98-11-16: This amendment adopts a new airworthiness directive (AD) that applies to certain Dornier Luftfahrt GmbH (Dornier) Models 228-100, 228-101, 228-200, 228-201, 228-202, and 228-212 airplanes. This AD requires modifying the logic in the failure detection circuits of the landing gear uplock switches. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent a false warning indication of landing gear failure because of the design of the landing gear warning system, which could result in incorrect actions from the pilot based on the warning indications.
97-10-07: 97-10-07 CONSTRUCCIONES AERONAUTICAS, S.A., CASA: Amendment 39-10019. Docket 96-NM-144-AD. Applicability: All Model CN-235, CN-235-100, and CN-235-200 series airplanes; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent in-flight uncommanded activation of the propeller brake system, which could result in in-flight shutdown of the engine, accomplish the following: (a) Within 10 days after the effective date of this AD, disable the brake control valve of the propeller in accordance with Annex 1 of CASA Communication COM 235-82, Revision 3, dated January 31, 1995. (b) Prior to restoring propeller brake operation, replace the propeller brake control unit having part number (P/N) HP1410100-5 or HP1410100-7, with a new propeller brake control unit having P/N HP1410100-9, in accordance with CASA Service Bulletin SB-235-61-01, dated October 11, 1994; or CASA Service Bulletin SB-235-61-01M, Revision 2 (for military airplanes), dated January 25, 1996; as applicable. Accomplishment of this replacement constitutes terminating action for the requirements of paragraph (a) of this AD. (c) An alternative method of compliance or adjustment of the compliancetime that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. 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 2: 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 sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (e) Disabling the brake control valve of the propeller shall be done in accordance with Annex 1 of CASA Communication COM 235-82, Revision 3, dated January 31, 1995. The replacement shall be done in accordance with CASA Service Bulletin SB-235-61-01, dated October 11, 1994; or CASA Service Bulletin SB-235-61-01M, Revision 2, dated January 25, 1996; as applicable. CASA Service Bulletin SB-235-61-01M, Revision 2, dated January 25, 1996, contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1 1 November 27, 1995 2 2 January 25, 1996 3-11 Original October 11, 1994 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 Construcciones Aeronauticas, S.A., Getafe, Madrid, Spain. 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 June 16, 1997.
2020-26-04: The FAA is superseding Airworthiness Directive (AD) 2013-18- 08, which applied to certain The Boeing Company Model 737-200, -200C, - 300, -400, and -500 series airplanes. AD 2013-18-08 required repetitive inspections for cracking of certain skin panels of the fuselage, and of the fuselage skin along certain chem-milled lines, and corrective actions if necessary. AD 2013-18-08 also included a terminating action for the repetitive inspections of certain areas. This AD retains those actions, expands the nondestructive inspection (NDI) area, and adds airplanes to the applicability. This AD was prompted by reports of additional cracking in certain horizontal and vertical chem-milled step locations outside of those identified in AD 2013-18-08. The FAA is issuing this AD to address the unsafe condition on these products.
2001-18-06: This amendment supersedes two existing airworthiness directives (AD's), applicable to General Electric Company (GE) T58 and CT58 series turboshaft engines. The current AD's revised the counting method for hours in repetitive heavy-lift (RHL) service and reduced the life limit for rotating components. Life-limited rotating components must be removed from service in accordance with the multiplying factors and retirement lives contained in General Electric Alert Service Bulletin (ASB) CT58 A72-162 (CEB-258), dated July 9, 1979. This amendment requires applying an additional multiplying factor to life-limited rotating parts when the engine is used in heavy lifting operations. This amendment is prompted by a review of the current AD's, AD-69-23-02 and AD-79-23-04, and a determination that the requirements of those AD's may conflict. This amendment will prevent RHL and utility service multiplier factors from being applied incorrectly. The actions specified in this AD are intended toprevent low-cycle fatigue failure of rotating parts that could result in uncontained engine failure and damage to the rotorcraft.
2008-23-07: We are adopting a new airworthiness directive (AD) for all Boeing Model 737 airplanes. This AD requires revising the airplane flight manual to include a new flightcrew briefing that must be done before the first flight of the day and following any change in flightcrew members, and to advise the flightcrew of this additional briefing. This AD results from continuing reports that flightcrews have failed to recognize and react properly to the cabin altitude warning horn. We are issuing this AD to prevent failure of the flightcrew to recognize and react properly to a valid cabin altitude warning horn, which could result in incapacitation of the flightcrew due to hypoxia (lack of oxygen in body) and consequent loss of airplane control.
2003-14-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model 382G series airplanes, that requires repetitive general visual inspections of certain bearings located in the emergency exit door for evidence of excessive wear; and repair of certain bearings, which would terminate the repetitive inspections. This action is necessary to prevent failure of the latch mechanism, which could result in the inability to open the emergency exit door in an emergency. This action is intended to address the identified unsafe condition.
2003-14-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, that requires the installation of protective tape on the fire and overheat control unit located in the flight compartment. The actions specified by this AD are intended to prevent fluid contamination inside the fire and overheat control unit, which could result in a false fire alarm and consequent emergency landing. This action is intended to address the identified unsafe condition.
97-01-13: This amendment adopts a new airworthiness directive (AD) that applies to Cessna Aircraft Company (Cessna) 100, 200, 300, and 400 series airplanes. This action requires checking the airplane maintenance records for any fuel, oil, or hydraulic hose, Cessna part number (P/N) S51-10, replaced between March 1995 and February 3, 1997 (the effective date of this AD); immediately checking any of these hoses for a diagonal or spiral external reinforcement wrap; and immediately replacing any of these hoses that have a diagonal or spiral external reinforcement wrap with one that has a crisscross external reinforcement wrap. This action was prompted by reports of operators experiencing a loss of engine power because of low fuel feed, in addition to Cessna discovering that the rubber hose installed at the factory on certain Cessna Models 208 and 208B airplanes was defective. The Cessna P/N S51-10 rubber hose is utilized on fuel, oil, and hydraulic hoses on the affected airplanes. Theactions specified by this AD are intended to prevent fuel, oil, or hydraulic systems failure caused by a collapsed hose.
2002-01-13: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires inspections to detect cracking and corrosion of the aft trunnion of the outer cylinder of the main landing gear (MLG) and various follow-on actions. That AD also currently requires termination of the inspections by repairing the outer cylinder and installing new aft trunnion bushings. This amendment prohibits the use of a particular corrosion inhibiting compound during accomplishment of the terminating action. This action is necessary to prevent the collapse of the MLG due to stress corrosion cracking of the aft trunnion of the outer cylinder. This action is intended to address the identified unsafe condition. \n\n\tThe incorporation by reference of Boeing Service Bulletin 767-32A0148, Revision 2, dated November 30, 2000, as listed in the regulations, is approved by the Director of the Federal Register as of March 1, 2002. \n\n\tTheincorporation by reference of a certain publication, as listed in the regulations, was approved previously by the Director of the Federal Register as of February 16, 1996 (61 FR 3552, February 1, 1996).\n\n\tThe incorporation by reference of a certain other publication, as listed in the regulations, was approved previously by the Director of the Federal Register as of November 29, 1996 (61 FR 55080, October 24, 1996).
2001-26-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-26-52, which was sent previously to all known U.S. owners and operators of Eurocopter Deutschland GmbH (ECD) Model EC135 helicopters by individual letters. This AD requires, before further Instrument Flight Rule (IFR) flight, inserting a copy of the AD into the Limitations Section of the Rotorcraft Flight Manual (RFM) and replacing each affected Smart Multifunction Display (SMD45H) as specified. Removing the AD from the RFM is required after replacing each affected SMD45H. This AD is prompted by the discovery of an error in the assembly of an internal connector of the SMD45H that sometimes results in an inversion of the display information. The SMD45H provides the flightcrew with essential flight and navigation information. The actions specified by this AD are intended to prevent erroneous flight or navigation display information, produced by a faulty SMD45H, and subsequentloss of control of the helicopter.
2025-01-08: The FAA is superseding Airworthiness Directive (AD) 2019-22- 02, which applied to all The Boeing Company Model 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747-8F, and 747-8 series airplanes. AD 2019-22-02 required identifying the part number, and the serial number if applicable, of the Captain's and First Officer's seats, and applicable on-condition actions for affected seats. AD 2019-22-02 also required a one-time detailed inspection and repetitive checks of the horizontal movement system (HMS) of the Captain's and First Officer's seats, and applicable on-condition actions. This AD was prompted by reports of uncommanded fore and aft movement of the Captain's and First Officer's seats. This AD requires the actions in AD 2019-22-02 and adds an inspection of previously omitted part numbers. The FAA is issuing this AD to address the unsafe condition on these products.
2025-02-08: The FAA is adopting a new airworthiness directive (AD) for certain DAHER AEROSPACE (DAHER) Model TBM 700 airplanes. This AD was prompted by certain existing emergency procedures in the pilot's operating handbook (POH) that cannot be fully accomplished since certain equipment cannot be disconnected by the pilot(s) from the flight deck. This AD requires revising the existing POH for your airplane to provide the flight crew with corrected emergency procedures. The FAA is issuing this AD to address the unsafe condition on these products.
2015-15-07: We are superseding Airworthiness Directive (AD) 2015-10-01 for certain Bombardier, Inc. Model DHC-8-400 series airplanes. AD 2015-10- 01 required inspection for correct assembly of the main landing gear (MLG) alternate extension system reservoir lid, and corrective action if necessary. This new AD revises the applicability. This AD was prompted by the discovery of two errors in the applicability of AD 2015-10-01. We are issuing this AD to, in the event of a failure of the primary MLG extension system, prevent failure of the alternate MLG extension system to fully extend the MLG into a down-and-locked position, which could result in collapse of both left-hand and right- hand MLG sides during touchdown.
99-05-13 R1 WD: This amendment withdraws Airworthiness Directive (AD) 99-05-13, which currently applies to Raytheon Aircraft Company (Raytheon) Beech 17, 18, 19, 23, 24, 33, 35, 36/A36, A36TC/B36TC, 45, 50, 55, 56, 58, 58P, 58TC, 60, 65, 70, 76, 77, 80, 88, and 95 series airplanes. AD 99-05-13 requires installing a placard on the fuel tank selector to warn of the no-flow condition that exists between the fuel tank detents. Since the issuance of AD 99-05-13, the Federal Aviation Administration (FAA) has re-evaluated all information related to this subject, and determined that the subject matter in this AD is an operational issue and does not address an unsafe condition. Accordingly, this action withdraws AD 99-05-13.
2008-23-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from 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: 1. The bolt of a bearing stand which is the pivot for a bell crank failed in a DG-500 ELAN Trainer. As the cause of the failure it is suspected that the nut fixing the bell crank had become loose. As the design is similar in the DG-1000 up to ser. no. 10-109 analogous instructions have to be executed for the DG-1000. 2. During aerobatics a suspension of the airbrake control hook up in the wing root failed. Therefore the suspension shall be reinforced. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
99-02-10: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that currently requires modification of the trimmable horizontal stabilizer (THS). This amendment adds a requirement for a one-time inspection of the flexible hoses of the elevator return lines on the THS to detect installation of incorrect clamps, or missing clamps or bonding leads; and for replacement of the clamps or bonding leads with new parts, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent leakage from hydraulic pipe fittings in the THS, which could result in failure of the THS and consequent reduced controllability of the airplane.
99-06-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 and MD-11 series airplanes, and KC-10 (military) series airplanes, that requires a one-time inspection for blockage of the lubrication holes on the forward trunnion spacer assembly, and a one-time inspection of the forward trunnion bolt on the left and right main landing gear (MLG) to detect discrepancies; and repair, if necessary. This amendment is prompted by reports of blockage by opposing bushings of the lubrication holes on the forward trunnion spacer assembly, and reports of flaking, galling, and corrosion of the forward trunnion bolt. The actions specified by this AD are intended to detect and correct such flaking, galling, and corrosion of the forward trunnion bolt, which could result in premature failure of the forward trunnion bolt and could lead to separation of the MLG from the wing during takeoff and landing.