Results
96-04-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires replacement of the relays in the forward electronics rack of the braking system of the landing gear with new relays. This amendment is prompted by reports of loss of the systems of the braking/steering control unit (BSCU) on these airplanes due to electrical overvoltage of the relays. The actions specified by this AD are intended to prevent such electrical overvoltage of the relays, which could result in the loss of the BSCU systems, and subsequent loss of the antiskid functions and nose wheel steering of the airplane.
51-09-03: 51-09-03 TAYLORCRAFT: Applies to All Series Aircraft Below Serial Number 13001 Incorporating a Pushpull Type Fuel Shutoff Control. Compliance required not later than June 1, 1951. To prevent accidental operation of the fuel shutoff valve during flight, a safety device must be installed on this control. The device is to prevent inadvertent operation of the fuel shutoff valve by requiring a definite and positive movement by the pilot before the control can be operated. Taylorcraft P/N B12-947-3 or equivalent is considered satisfactory. P/N B12-947 which was previously installed in some Taylorcraft airplanes must be replaced by this improved part. (Taylorcraft Service Bulletin No. 66 dated December 6, 1950, covers this same subject.) This supersedes AD 47-13-01.
2005-19-27: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 series airplanes. This AD requires inspecting to determine the serial numbers and flight cycles of the fuel jettison valves and removing certain valves as applicable. This AD also requires doing a one-time inspection for cracks of the remaining jettison valves and removing any cracked valves. This AD also requires modifying the diameters of the six attachment holes in the wing bottom skin panel before installing a new or serviceable jettison valve. This AD results from reports of fuel leaks in the fuel jettison system located on the wings. We are issuing this AD to prevent fuel leaks from the fuel jettison outlets, which could result in fuel vapors coming into contact with ignition sources, and consequent fire or explosion.
98-06-12: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS-350B, BA, B1, B2, and D helicopters, and Model AS 355E, F, F1, F2, and N helicopters. This action requires replacing certain tailboom attachment bolts located above the cargo compartment floor. This amendment is prompted by two reports of attachment bolts strength properties not meeting design specifications during manufacture. The actions specified in this AD are intended to identify and remove the weaker bolts and to prevent the separation of the tailboom from the helicopter, and subsequent loss of control of the helicopter.
51-25-01: 51-25-01 CESSNA: Applies to All Model T-50 Aircraft. Compliance required prior to February 1, 1952, and as noted. To preclude trapping water in the horizontal stabilizer forward of the rear spar which may result in glue line deterioration between laminations, compliance with the following items is necessary: 1. Grommets must be installed sufficiently near the forward face of the rear spar and outboard edge of all ribs to drain any water which may be trapped. All grommets not so located must be relocated accordingly. Marine-type grommets are recommended at least at the inboard ribs. 2. All grommets which are plugged must be opened preferably with a sharp-edged tool and/or relocated in accordance with item 1 above. Special care should be taken to make sure that foreign matter is not allowed to build up on the inside around the drain openings. 3. Where grommets are mislocated, plugged, clogged with dirt or extraneous matter or have not been installed, the rear spar must be inspected for deterioration by cutting small triangular openings at the ribs adjacent to the fuselage and at alternate ribs outboard. If lamination separation is disclosed, a new spar should be installed or the stabilizer replaced with one having drainage provisions in accordance with item 1 above. Upon accomplishment of the above, the grommet openings should be inspected at each 100 hours thereafter to maintain proper drainage. This inspection should include insertion of a bent or curved tool through the grommet openings to ascertain that dirt or other extraneous matter has not built up around the opening to restrict drainage. Where grommets are found clogged, inspection and compliance in accordance with item 3 above should be repeated. This supersedes AD 44-26-01.
2005-19-23: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 767 series airplanes. That AD currently requires repetitive inspections to detect discrepancies of the eight aft-most fastener holes in the horizontal tangs of the midspar fitting of the strut, and corrective actions if necessary. That AD also provides an optional terminating action for the repetitive inspections. This new AD adds repetitive inspections for cracks of the closeout angle that covers the two aft-most fasteners in the lower tang of the midspar fitting, and related investigative and corrective actions if necessary. This AD also reduces the inspection interval of the upper tang of the outboard midspar fitting; and provides an optional terminating action for the repetitive inspections. This AD results from a report of a crack in a closeout angle that covers the two aft-most fasteners in the lower tang of the midspar fitting; and the discovery of a crack in the lower tang of the midspar fitting under the cracked closeout angle. We are issuing this AD to prevent fatigue cracking in the primary strut structure and reduced structural integrity of the strut, which could result in separation of the strut and engine. \n\nEFFECTIVE DATE: This AD becomes effective October 27, 2005. \n\n\tThe Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 767-54A0101, Revision 4, dated February 10, 2005, listed in the AD as of October 27, 2005. \n\n\tOn June 9, 2004 (69 FR 24947, May 5, 2004), the Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 767-54A0101, Revision 3, dated September 5, 2002. \n\n\tOn May 15, 2001 (66 FR 18523, April 10, 2001), the Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 767-54A0101, Revision 1, dated February 3, 2000.
98-05-07: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that requires replacement of the stringer joint pieces at the left side of the fuselage with new, improved parts. 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 the fuselage structure at the stringer joint at station 130 on the left side of the airplane from cracking, which could result in rapid decompression of the airplane at the forward fuselage area.
67-27-06: 67-27-06 ROLLS-ROYCE: Amdt. 39-488 Part 39 Federal Register October 3, 1967. Applies to Dart Model 542-4 and 542-10 engines. Compliance required as indicated, unless already accomplished. To prevent failure of fuel and oil hoses, accomplish the following: (a) For fuel hoses, P/N's RU.21448, RK.38339A, RK.29902, RK.38340A, RU.21447, RK.29900A, RK.38361, RU.21455A, RK.29901A, and oil pressure indicator hose P/N RU.21440A, with 700 or more hours total time in service on the effective date of this AD, within the next 100 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 150 hours' time in service from the last inspection, inspect for cracks and crazing in accordance with Rolls-Royce Alert Service Bulletin Da 73-A49 or later ARB- approved issue, or an FAA-approved equivalent. (b) For fuel hoses, P/N's RU.21448, RK.38339A, RK.29902, RK.38340A, RU.21447, RK.29900A, RK.38361, RU.21455A, RK.29901A, and oil pressure indicator hose P/N RU.21440A, with less than 700 hours' time in service on the effective date of this AD, before the accumulation of 800 hours' time in service and thereafter at intervals not to exceed 150 hours' time in service from the last inspection, inspect for cracks and crazing in accordance with Rolls-Royce Alert Service Bulletin Da 73-A49 or later ARB-approved issue, or an FAA-approved equivalent. (c) If cracking or crazing of the hose is detected during the inspections required by (a) and (b), before further flight, replace with a new assembly. (d) The repetitive inspections required under (a) or (b) for the fuel hoses may be discontinued following the incorporation of ARB-approved Rolls-Royce Modification 1467, or an FAA-approved equivalent. (e) The repetitive inspections required under (a) or (b) for the oil pressure indictor hoses may be discontinued following the incorporation of ARB-approved Rolls-Royce Modification 1453, or an FAA-approved equivalent. Thisamendment effective October 3, 1967.
2005-19-21: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-202, -223, -243, and -343 airplanes; and certain Model A340-313 airplanes. This AD requires a one-time inspection for discrepancies of the attachment bolts of the windshield central retainer, and corrective actions if necessary. This AD results from a report indicating that, during production, the windshield central retainer may have been installed with attachment bolts that were too short, which prevented the thread of the bolt from fully engaging in the self-locking nut. We are issuing this AD to prevent loosened attachment bolts, which could result in loss of the windshield and consequent reduced structural integrity of the airplane.
98-05-04: This amendment supersedes Airworthiness Directive (AD) 87-18-09, which currently requires inspecting (one-time) the sides of the front and rear wood spars for compression cracks on certain American Champion Aircraft Corp. (ACAC) Model 8GCBC airplanes, and repairing or replacing any wood spar with compression cracks. This AD requires repetitively inspecting the front and rear wood spars for damage, including installing any necessary inspection holes; and repairing or replacing any damaged wood spar. Damage is defined as cracks; compression cracks; longitudinal cracks through the bolt holes or nail holes; or loose or missing nails. This AD results from in-flight wing structural failure on one of the affected airplanes that was in compliance with the one-time inspection requirement of AD 87-18-09, plus 4 other ACAC Model 8GCBC accidents and 11 service difficulty reports (SDR s) of compression cracked spars. The actions specified by this AD are intended to detect compressioncracks and other damage in the wood spar wing, which, if not corrected, could eventually result in in-flight structural failure of the wing with consequent loss of the airplane.
98-05-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Aeromot-Industria Mecanico Metalurgica Ltda. (Aeromot) Models AMT-100 and AMT-200 powered gliders. This AD requires replacing all main landing gear attaching nuts and bolts with ones of improved design. This AD is the result of mandatory continued airworthiness information (MCAI) issued by the airworthiness authority for Brazil. The actions specified by this AD are intended to prevent failure of the main landing gear, which could result in loss of control of the glider during landing operations.
51-10-04: 51-10-04 CESSNA: Applies to Model 190 Aircraft, Serial Numbers 7004 Through 7594. Inspection required not later than May 1, 1951, and every 25 hours of operation thereafter until new cowl mounting ring channels and channel stiffening angles are installed. Due to cracking and failures of the cowl mounting ring channels which, if undetected, may result in the cowl moving forward into the propeller, the cowl mounting channels must be closely inspected for cracks with particular attention being paid to the sections which bear against the cowl mounting lugs. This inspection must be repeated every 25 hours of operation until the presently installed 1010 steel cowl mounting channels are replaced with 4130 steel cowl mounting channels, Cessna P/N 0352161, 0352163, and 0352163-1, and aluminum alloy cowl channel reinforcing angles, Cessna P/N 0352146, 0352147-1, 0352147-2, 0352152-5, and 0352152-6 are installed. In the event that inspection reveals any indication of cracks, the new cowl mounting channels and reinforcing angles must be installed immediately. (Cessna Service Letter No. 13 dated March 29, 1951, covers this same subject.)
2005-19-14: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A318-100, A319-100, A320-200, A321-100, and A321- 200 series airplanes; and Model A320-111 airplanes. This AD requires modification of the electrical bonding of all structures and systems installed inside the center fuel tank. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent electrical arcing in the center fuel tank due to inadequate bonding, which could result in an explosion of the center fuel tank and consequent loss of the airplane.
2011-01-07: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During maintenance on a 328-100 aeroplane, a crack was found on a trim tab fitting assembly. The cause of the cracking was identified as stress corrosion. This condition, if not corrected, could lead to in-flight failure of the tab fitting, possibly resulting in loss of control of the aeroplane. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2017-06-13: We are adopting a new airworthiness directive (AD) for certain Textron Aviation Inc. (Textron) Model 680 airplanes. This AD was prompted by Textron's report of a manufacturing defect that affects the durability of the aft canted bulkhead metallic structure. This AD requires repetitive inspections of the aft canted bulkhead; repair if necessary; and a modification, which would terminate the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
2005-19-15: The FAA is superseding an existing airworthiness directive (AD), which applies to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes. That AD currently requires operators to determine the number of flight cycles accumulated on each component of the main landing gear (MLG) and the nose landing gear (NLG), and to replace each component that reaches its life limit with a serviceable component. The existing AD also requires operators to revise the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness in the aircraft maintenance manual to reflect the new life limits. This new AD requires revising the ALS to incorporate extended and more restrictive life limits for structurally significant items. This AD is prompted by engineering analysis of fleet operations which resulted in more restrictive life limits. We are issuing this AD to prevent failure of certain structurally significant items, including the MLG and the NLG, which could result in reduced structural integrity of the airplane. DATES: This AD becomes effective October 26, 2005. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of October 26, 2005. On August 3, 2004 (69 FR 38816, June 29, 2004), the Director of the Federal Register approved the incorporation by reference of BAE Systems (Operations) Limited Service Bulletin J41-05-001, Revision 2, dated March 15, 2002; BAE Systems (Operations) Limited Service Bulletin J41- 05-001, Revision 3, dated January 9, 2004; and BAE Systems (Operations) Limited Service Bulletin J41-32-078, dated April 12, 2002.
2017-06-09: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by a report indicating that the fire block in the closets and video control stations, and fire blocking tape in the floor panel opening in the forward and aft main passenger cabin, might be missing on some airplanes. This AD requires installing a fire block in the closets and video control stations, as applicable, and installing fire blocking tape in the floor panel openings in the forward and aft main passenger cabin. We are issuing this AD to address the unsafe condition on these products.
2017-06-10: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of interior emergency lights remaining ``ON'' following routine operational checks of the emergency light system. This AD requires changing the wiring gauge for the affected emergency lights power supplies wiring to prevent overheating in the wires. We are issuing this AD to address the unsafe condition on these products.
2017-06-05: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-6, DC-6A, C-118A, R6D-1, DC-6B, and R6D-1Z airplanes. This AD was prompted by a report of a fuel leak in a Model C-118A airplane that resulted from a crack in the wing lower skin. This AD requires repetitive radiographic, electromagnetic testing high frequency (ETHF), and electromagnetic testing low frequency (ETLF) inspections for cracking of the wing lower skin, and repairs if necessary. We are issuing this AD to address the unsafe condition on these products.
67-23-06: 67-23-06 MOONEY: Amdt. 39-455, Part 39, Federal Register August 5, 1967. Applies to Model M20C (Mark 21) Airplanes, Serial Numbers 2623 through 2737 and 2739 through 3198; Model M20D (Master) Airplanes Serial Numbers 201 through 260; and Model M20E (Super 21) Airplanes, Serial Numbers 101 through 850. Compliance required as indicated unless already accomplished. Service experience indicates that it is necessary to replace Dukes fuel pumps now in service with a redesigned Dukes fuel pump as follows: (a) For Model M20E (Super 21) airplanes equipped with Dukes fuel pump: (1) Within the next 25 hours' time in service after April 12, 1965, replace Dukes fuel pump, Part Number 4140-00-19, Serial Numbers 101, 102, 103, 150 through 312, with Dukes fuel pump, Part Number 4140-00-19A, with pump Serial Numbers above 1550, in accordance with Mooney Service Bulletin M20-121B (Revision B, 11-4-66). (2) Within the next 100 hours' time in service after April 12, 1965, replace Dukesfuel pump, Part Number 4140-00-19, Serial Numbers 313 through 613, with Dukes fuel pump, Part Number 4140-0019A, with pump Serial Numbers above 1550, in accordance with Mooney Service Bulletin M20 - 121B (Revision B, 11-4-66). (3) Within the next 100 hours' time in service after the effective date of this AD, replace Dukes fuel pump, Part Number 4140-00-19A. Serial Numbers 614 through 1550 with Dukes fuel pump, Part Number 4140-00-19A with pump serial number above 1550 in accordance with Mooney Service Bulletin M20-121B (Revision B, 11-4-66). (b) For Models M20C (Mark 21) and M20D (Master) airplanes equipped with Dukes fuel pump: (1) Within the next 25 hours' time in service after April 12, 1965, replace Dukes fuel pump, Part Number 4140-00-21, Serial Numbers 100, 102, 103, 150 through 244, with Dukes fuel pump, Part Number 4140-0021A with pump Serial Numbers above 1158, in accordance with Mooney Service Bulletin M20-121B, (Revision B, 11-4-66). (2) Within the next 100hours' time in service after April 12, 1965, replace Dukes fuel pump, Part Number 4140-00-21, Serial Numbers 245 through 409, with Dukes fuel pump, Part Number 4140-00-21A with pump serial numbers above 1158, in accordance with Mooney Service Bulletin Number M20-121B (Revision B, 11-4-66). (3) Within the next 100 hours' time in service after the effective date of the AD, replace Dukes fuel pump, Part Number 4140-00-21A, Serial Numbers 410 through 1158, with Dukes fuel pump, Part Number 4140-00-21A with pump serial numbers above 1158, in accordance with Mooney Service Bulletin M20-121B (Revision B, 11-4-66). (c) For Model M20E, Serial Numbers 101 through 263, Model M20C, Serial Numbers 2623 through 2690, and Model M20D, Serial Numbers 201 through 226, concurrent with the fuel pump replacement in (a) and (b) above, remove Mooney electric fuel pump mounting bracket, Part Number 610032, and install re-designed pump bracket, Part Number 610048, in accordance with Mooney Service letter 20-120, dated March 18, 1964. This AD supersedes AD 65-06-05. This amendment effective September 5, 1967.
2005-19-18: The FAA is superseding an existing airworthiness directive (AD), which applies to all Short Brothers Model SD3-30 and SD3-60 airplanes equipped with certain fire extinguishers. That AD currently requires replacement of the covers for fire extinguisher adapter assemblies that are installed on certain bulkheads with new covers that swivel to lock the extinguishers in place; and replacement of nozzles and triggers on these fire extinguishers with better fitting nozzles and stronger triggers. The existing AD also currently requires the installation of new fire extinguisher point placards and a revision of the airplane flight manual (AFM) to instruct the flightcrew in the use of the new covers for these adapter assemblies. This new AD also requires modification of the fire extinguishing point adapter assembly of the forward and aft baggage bays as applicable. This new AD also adds airplanes to the applicability. For these new airplanes, this new AD requires a revision to the AFM for instructions on using the new fire extinguisher adapter. This AD results from reports of individuals experiencing fire extinguishant blowback when the extinguishant discharges through the fire extinguishing point adapters. We are issuing this AD to prevent fire extinguishant blowback, which could result in injury to a person using the fire extinguisher in the event of a fire. DATES: Effective October 26, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of October 26, 2005. The Director of the Federal Register previously approved the incorporation by reference of certain other publications, as listed in the regulations, as of June 8, 1998 (63 FR 24387, May 4, 1998).
67-24-03: 67-24-03 BRITISH AIRCRAFT: Amdt. No. 39-442, Federal Register July 8, 1967. Applies to Model BAC 1-11-200 and 400 Series Airplanes. Compliance required as indicated. To prevent failure of the rudder pedal reach adjuster lock unit housing P/N AB 32-509, accomplish the following: (a) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 200 hours' time in service, and thereafter at intervals not to exceed 250 hours time in service from the last inspection, visually inspect the rudder pedal reach adjuster lock unit housing P/N AB32-509 for cracks in accordance with British Aircraft Corporation BAC 1-11 Alert Service Bulletin No. 27-A-PM 2946, Issue I, or later ARB-approved issue. Cracked housings must be replaced before further flight with an unused or serviceable housing having the same part number or with a new housing P/N AB32-9011 and locking plunger P/N AB32-9013 in accordance with BAC 1-11 ServiceBulletin No. 27-PM 2946, or later ARB- approved issue, or FAA-approved equivalent. (b) If no cracks are detected during the inspection required by paragraph (a), lubricate the housing and conduct a functional check of the lock unit assembly in accordance with BAC 1-11 Alert Service Bulletin No. 27-A-PM 2946 or later ARB-approved issue. Correct defects found before further flight. (c) Within the next 1200 hours' time in service after the effective date of this AD, replace rudder pedal reach adjuster lock unit housing P/N AB32-509 with new housing P/N AB32-9011 and locking plunger P/N AB32-9013 in accordance with BAC 1-11 Service Bulletin No. 27-PM 2946, or later ARB-approved issue, or FAA-approved equivalent. (d) The repetitive inspections required by paragraph (a) and the functional checks required by paragraph (b) may be discontinued after the new housing P/N AB32-9011 and locking plunger P/N AB32-9013 are installed in accordance with paragraph (a) or (c) of this AD.This amendment effective July 13, 1967.
98-04-50: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and F.28 Mark 0100 series airplanes, that requires modification of the wing leading edge torsion box. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent a possible ignition hazard due to accumulation of water and fuel between the front spar and auxiliary spar, which could result in increased risk of an in-flight fire.
51-01-01: 51-01-01 DOUGLAS: Applies to All DC-6 Aircraft. \n\n\tTo be accomplished as indicated below. \n\n\t(a)\tAll airplanes at each 300 hours of flight time-Inspect for broken studs at the front spar lower and upper fittings at wing joint Station 421. Also inspect lower forward front spar fittings, P/N 4332884 and -1, and upper forward fittings, P/N 4332885 and -1, for cracks in area approximately 2 inches outboard of fitting face. \n\n\t(b)\tIf broken stud is found, replace both studs at spar fittings with parts having threads rolled after heat treat, install bolt with threads rolled after heat treat at center spar, and replace lower fitting P/N 4332884 and -1 and upper fitting P/N 4332885 and -1 with newly designed heavier fittings P/N 4397872 and -1 and P/N 4397873 and -1, respectively. Return of an airplane to service prior to the availability of the newly designed fittings is permissible by installation of new fittings of the old design (P/N 4332884 and 4332885), providing replacementis made at or before 8,000 hours of service on those parts. Spotface new fittings after installation to align with adjacent fittings. \n\n\tIf records show previous case of broken parts at front spar fitting, and only corrective action taken was the replacement of studs with threads rolled after heat treat, inspect fittings at each 300 hours of operation until same replacement action outlined above is taken at next engine change period. \n\n\t(c)\tContinue inspections outlined in (a), until following replacement action is accomplished: \n\n\t\t1.\tIf not previously incorporated, install studs at the front spar and bolts at the center spar which have threads rolled after heat treat. (See AD 49-06-02.) \n\n\t\t2.\tReplace the lower forward front spar fittings P/N 4332884 and -1 with new heavier P/N 4397872 and -1 and replace the upper forward front spar fitting P/N 4332885 and -1 with new heavier P/N 4397873 and -1 spotfacing fittings after installation. \n\n\t(d)\tReplacement action outlined initem (c) 1 and 2, to be accomplished not later than January 1, 1952. \n\n\t(Douglas General Service Letter DC-6 No. 61 covers this same subject. Refer to Douglas Service Letter No. 66, Supplement No. 2 dated July 18, 1951, for wing alignment at Station 421.)
2005-19-17: The FAA adopts a new airworthiness directive (AD) for certain PZL-Swidnik S.A. (PZL-Swidnik) Models PW-5 ``Smyk" and PW-6U gliders. This AD requires you to inspect for the minimum dimension of the left side aileron, right side aileron, and airbrake push-rod ends for certain Model PW-5 ``Smyk" gliders; inspect for the minimum dimension of the aileron, airbrake, and elevator control push-rod ends for certain Model PW-6U gliders; and replace any push-rod end that does not meet the minimum dimension. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Poland. We are issuing this AD to detect and replace any push-rod end that does not meet the minimum dimension, which could result in failure of the control system. This failure could lead to loss of control of the glider.