Download British Gliding Association Airworthiness Compendium
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British Gliding Association Airworthiness Compendium Compendium of Airworthiness Directives, Mandatory Modifications, special Inspections and Check List of Defects Foreword and instructions for use The lay out of the compendium is now listed under aircraft manufacturers name and is in a format to allow more room for detail and reference information. Where two manufacturers make one type a cross reference is made. From 2002 each entry will have a status as follows: M R O I Mandatory for aircraft with a BGA or CAA C of A Recommended by the BGA or manufacturer Optional (usually modifications) For information (usually guidance for inspectors or general information) To research a particular aircraft look under the following: 1 2 3 4 5 6 Aircraft manufacturer section Engine and propeller section (if applicable) Equipment section Special inspections – All types Tug and Motor glider issues (if applicable) Review all TNS issued after the compendium issue date. Page 1 BGA Compendium 01/02 General information COMPILED FROM: Airworthiness Directives (ADs), Service Bulletins (SBs), Tech Notes (TNs), Technical Instructions (TIs), Defect Reports, CAA Mandatory Modification and Inspection Summary, CAA Airworthiness Directives Vol. 1 & 2, CAA Foreign ADs Vol. III. etc. Also experiences by BGA inspectors and operators. TUG’s The BGA compendium does NOT cover Glider Tug aircraft. Reference should be made to the applicable Airworthiness publications and manufacturers information. UPDATED: by BGA Technical News Sheets (TNS) - bi-monthly. From 2002 the TNS number will be aligned with the compendium. I.e. 01/02/02 will become 02/02, 03/04/02 will become 04/02, 05/06/02 will become 06/02 and on. Indicating month and year of publication COMPLIANCE: - Unless stated otherwise, the AD’s listed in this compendium are mandatory for BGA registered gliders and Motor Gliders. Notes: 1 AD’s are issued by National Airworthiness Authorities, generally to make manufacturers’ SB’s, TI's or Mods mandatory and to state time limits as to when they must be carried out. 2 Items marked ”M” have been reviewed by the BGA and must be carried out as specified and entered in the log book Mods or Pink Pages section. 3 All other entries listed in this compendium are for guidance to aid inspections, and it is recommended that they are carried out annually, i.e. at C of A, except when stated otherwise. From 2002 all entries will have a status indicator to assist inspectors to interpret the requirements. CLUB TECHNICAL OFFICERS are asked to make all relevant airworthiness information available to club members and private owners. CLUB COMMITTEES are reminded of their corporate responsibility to maintain high standards of airworthiness. BGA INSPECTORS are required to keep a record of their work, such as copies of 267 forms or a diary. CAA AIRWORTHINESS NOTICES detail repair and operational procedures for light aircraft, of which much is also applicable to gliders, is available from: Documedia Ltd, 37 Windsor St, Cheltenham, Glos, GL52 2DG tel. 01242 235151. Also available on the Internet [www.srg.caa.co.uk] JAA PUBLICATIONS Copies of JAR22 and other JAA publications are available from Rapidoc, Willoughby Road, Bracknell, Berkshire, RG12 8DW. Tel. 01344 861666. FURTHER INFORMATION The LBA publish AD’s on the Internet [www.lba.de] also many manufacturers have their own web sites (see contacts) were Tech Notes can be downloaded. There are many more Tech Notes than listed in the Compendium; these are mainly for optional modifications. For details either contact the agent or manufacturer direct. ERRORS Please notify the BGA, in writing by letter or e-mail if any errors are found in this publication. [[email protected]] Page 2 BGA Compendium 01/02 BGA Airworthiness Compendium Contents and check list of pages Title Page Issue Title Forward 1 2 1 2 1 01/02 01/02 01/02 01/02 TBA Diamond (formally Hoffmann) Eiri Avion 1 2 1 2 01/02 01/02 01/02 01/02 1 1 1 01/02 01/02 01/02 1 1 1 1 1 1 2 3 1 2 3 4 5 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 Contents Contacts Special Inspections ALL types Motor Glider & Tug issues Elliots of Newbury Flug und Fahrzeugwerhe Sportavia (Fournier/Aviostar) Glasflugel Grob Aer Pegaso Aeromot Avia Stroitel Birmingham Guild, Yorkshire Sailplanes, Swales Bolkow Breguet Caproni Carmam Centrair DG Flugzeubau (formally Glaser Dirks) IAR SA Brasov Issoir Aviation LET MDM Pilatus PZL Swidnik PZL Page Issue 1 1 2 1 1 1 1 2 3 1 2 3 4 5 6 1 2 1 1 2 1 1 1 1 2 3 4 5 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 Title Page Issue PZL continued 6 7 01/02 01/02 Rollanden Schneider 1 2 3 4 1 2 3 4 1 2 3 4 5 6 1 2 3 4 5 6 7 8 9 1 2 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/02 01/01 01/02 01/02 01/02 01/02 01/02 01/02 Scheibe Schempp-Hirth Schleicher Slingsby Continued Page 1 BGA Compendium 01/02 BGA Airworthiness Compendium Contents and check list of pages Title Page Issue Slingsby continued 3 4 5 6 7 01/02 01/02 01/02 01/02 01/02 Sportine Avijacia Stemme Valentin Wassmer 1 1 1 1 01/02 01/02 01/02 01/02 Engines 1 2 3 4 01/02 01/02 01/02 01/02 Propellers 1 2 01/02 01/02 Equipment 1 2 3 01/02 01/02 01/02 Page 2 BGA Compendium 01/02 Special Inspections All Types General information for guidance of inspectors collated from Airworthiness Directives applicable to all types, experience of incidents, published articles and general information. Note: Deleted entries in this section have been entered into relevant sections within the compendium. (Aircraft manufacturers, Engine, Propeller or Equipment) 1. AIRBRAKES after repairs & repaints check opening & locking with wings bent. Insufficient clearance around paddle ends can prevent them being opened in flight. TNS 06/96 2. BALLAST WEIGHTS (& BAGS etc) must be secured. For preference use bolted in ballast weights. Record if ballast weights are fitted, especially if out of sight. TNS 12/00 3. BGA FORMS 267 - to be signed for each item listed. “Mandatory Mods & Inspections” (Item 53). Compliance with this compendium & current TNSs must be checked and entered in log books 4. BUNGEE HOOKS should be removed to prevent hang-ups on cable parachutes. 5. CABLES - is the swaging satisfactory? Hemp cored cables must be replaced. Ref TNS 08/93. Stainless steel for control cables not recommended in applications with high chafing or tight turns on small pulleys. It has very poor fatigue properties. TNS 06/91, Piper SB 1048 Lubrication of SS control cables. 6. Assess the need for end-to-end inspections at annual check TNS 08/00 7. CANOPY LOCK AND JETTISON SYSTEMS -inspect at every DI. Test jettisons annually. 8. CONTROL SURFACE TAPE must be renewed regularly. Loose tape can cause major control problems. TNS 12/97 & 06/99. BGA inspection 011/12/2000 issue 1 detailing annual inspections on control tape and seals. TNS 12/00 9. CONTROL RODS - can be damaged by root ribs during trailer transport. Secure them. 10. CONTROLS L’Hotellier connectors MANDATORY inspections LBA AD 1993-001/3 and AD 1994-001/2 applicable to all types 11. GROUND LOOPING INCIDENTS- inspections in depth are required to establish the integrity of both structures and control systems. Ref BGA GRP Inspection Guidelines in Technical Procedure Manual. 12. INSTRUMENTATION TUBING - PVC loosens with age & leaks, glue it or use neoprene. 13. INSTRUMENT PANEL sharp metal edges are very dangerous. Leg protection must be fitted. Glass-fibre panels are much safer. “ASW” glass panels are designed to break up during an accident. Instrument installations (compasses) impeding canopy jettison BGA 021/10/2001 iss1 recommended inspection. 14. LIGHTNING STRIKE inspections of GRP gliders. TNS 12/88 & wooden glider control cables TNS 04/87. The need for bonding is emphasised TNS 08/00. 15. LIMITATIONS - must be permanently and legibly placarded, (including engine limitations). Page 1 BGA Compendium 01/02 Special Inspections All Types 16. OTTFUR rings distort and jam in Tost hooks. Use only Tost rings for all launching. TNS 06/97 Ottfur hooks new & product support - CAIR Aviation Ltd tel. 01293 543832 see TNS 12/97 for maintenance data. 17. SEATBACKS “slot in” types eg PW5, Vega & Jantar must be secured such that they can’t come loose under negative “G”. TNS 06/89 18. SEAT TRIM Seat trim obstructing exit from glider Recommended inspection BGA 019/06/2001 iss1. 19. STIFF NUTS may be used to replace split pin locked castellated nuts in any position where the nut is done up tightly. For example where a nut & bolt clamp up a bearing or a bush. 20. TRIM TABS - dangers of unsecured drive systems. TNS 12/88 21. VENTS & DRAINS - do they work? (Have you checked?) All components must have vents & drains. 22. WEIGHT AND BALANCE all types are normally to be re-weighed every EIGHT years. Inaccuracies and incorrect placarding can be fatal. TNS 02/87. Applications for increases in AUW can be made to the BGA. Some notes on procedures are given in TNS 06/99 23. WHEEL BRAKES Gliders with front skids may be operated without wheel-brakes. Other gliders that had wheel brakes as original equipment may not be operated if they are un-serviceable. 24. WOOD AND FABRIC STRUCTURES - over-tautening of fabric. TNS 10/88 always follow fabric manufacturers’ instructions. Attach fabric correctly; use adhesive not dope for synthetics. TNS 08/98 25. AIRFRAME LIFE INSPECTIONS all glass types of German origin, and others must be inspected at 3 000 hours and every subsequent 1 000 hours as per manufacturers special instructions. Additional inspections on some types at 6 000 hours – see aircraft section for specific instructions. 26. WINCH GUILLOTINES all winches must be equipped by end of 2000. 27. NYLON PEEL PLY Use approved materials and follow manufacturers instructions TNS 08/00, 09/00, 12/00. 28. DUPLICATE INSPECTIONS reminder that duplicate inspections are required if a control system or critical point is disturbed TNS 08/00. 29. SELF SUSTAINER SAILPLANES reminder to include 267T “Turbo” supplement when applying for SSS C of A renewal TNS 12/00. Removal of requirement for SSS airtest at C of A inspection TNS 02/01 30. TORQUE LOADING reminder to follow manufacturers specified torque loading TNS 12/00 31. HEAVY LANDINGS recommend “weight off” inspections following heavy landings TNS 12/00 32. BGA WEIGHT INCREASE CONSSESION 3% of AUW or 5% of NLP subject to conditions and limitations on BGA gliders 02/01 Page 2 BGA Compendium 01/02 Motor Glider and Tug issues General information for guidance of inspectors collated from experience of incidents, published articles and general information. Note: Deleted entries in this section have been entered into relevant sections within the compendium. 1. Airworthiness Notices - CAA Mandatory reading for all tug & SLMG owners & inspectors. From Documedia, 37 Windsor Street, Cheltenham, Glos, GL52 2DG, Tel: 01242 235151, Fax: 01242 584139 or on the internet [www.srg.caa.co.uk] 2. CAP 520 “Light Aircraft Maintenance” should be purchased by all those who maintain civil registered aircraft. From Documedia, Tel 01242 235 151 TNS 08/99 3. Gas collators in fuel systems inspect the retention system for wear TNS 10/98 4. Fuel contamination (whether MOGAS or AVGAS) has been recurring. Reported in GASILs and AAIB bulletins throughout the year. TNS 12/88, 02/88 5. Fuel hoses advise on selection and maintenance of fuel hoses 08/01 6. Gypsy induction flame - traps may disintegrate and be swallowed by the engine. TNS 12/88 7. Light Aircraft Maintenance Schedule (LAMS) Latest issue is lAMS/A/1999/BGA issue 1, amendment 1. 8. Lycoming, Gypsy (and other types) cylinder studs must be correctly torqued and regularly re-torqued to minimise the probability of cylinder separation from the crank case and cracking the cylinder head. All in accordance with maintenance manual or instructions. 9. Heat exchangers (cabin & carb air) to be pressure tested to 20psi at C of A. ref CAA AN40 TNS 08/92 10. Motor glider performance data & min rates of climb for C of A air tests TNS 10/98. 11. PA-25 Pawnee Wing root cluster Improved design to eliminate the inspection TNS 04/97 & TNS 08/97. Booker Air Services (01494 442501) can carry out the Failed landing gear. TNS 06/97 Deeside GC have embodied new STC mod eliminating most of repetitive NDT full details on web site [www.pawnee.soaring.org.uk] TNS 02/00 GASIL 2/97 recommends check cables to limit damage if u/c fails TNS 08/97 Parking brake malfunction FAA AD 85-02-05 TNS 12/97 “Magna Flite” starter motors found unsatisfactory on 0-540 engines TNS 02/99. Alternative hot air shutter failure causes power loss TNS 04/99. 12. Propellers check bolt torque and locking regularly. Must be to manufacturers' instructions to prevent damaged installations and propellers coming off. TNS 12/97 13. PVC tubing shrinks and becomes hard and brittle with prolonged exposure to fuel. Replace “site tubes” regularly and use fuel proof tube for all other applications. TNS 04/99 Page 1 BGA Compendium 01/02 Motor Glider and Tug issues 14. Schweitzer type banner towing hooks Mod to add bearing to reduce release loads, very strongly recommended. BGA Mod “BGA/T/1/85” ref TNSs 08/86 & 02/88 15. Scott tail-wheel axis vertical bolts should be replaced to prevent loss of the tail-wheel assembly. 16. Tail-wheel leaf spring failures TNS 06/88 17. Undercarriage pivot bolts should be replaced (or crack detected) at frequent intervals to prevent failures which may lead to significant damage. PA-18s, PA-25s, Citabrias, Bellanca Scouts, Austers etc. 18. Unleaded MOGAS CAA Airworthiness Notice 98C See TNS 12/99 19. Water in Fuel identification of water see TNS 06/97 20. Bulk Fuel Avgas contaminated by Diesel. Ensure safeguards and policy to prevent TNS 02/00 21. Engines General reminder that engines, propellers, magnetos, hoses have lives refer to LAMS schedule and manufacturers data TNS 08/00 22. Duplicate inspections Reminder that duplicate inspections are required if a control system or critical point is disturbed. TNS 08/00 23. Torque loading reminder to follow manufacturers specified torque loading TNS 12/00 24. Heavy landings Recommend “weight off” inspections following heavy landing TNS 12/00 25. Weighing BGA recommends that Motor Gliders and Tugs are reweighed every eight years Airworthiness Notice 38 gives guidance for weighing after painting.. Page 2 BGA Compendium 01/02 Aeromot (Brazil) Status Subject Detail Reference information TNS AD 97-04-02, SB-200-79-036 AD 97-07-01, SB 200-53-042 AD 97-09-06R1, SB 200-32-044 AD 98-05-05 AD2001-10-01, SB200-27-078 10/98 10/97 04/98 06/98 10/01 Contact: X-Imangu UK Ltd, 01904 738653 Department De Aviaco Civil Airworthiness Directives AMT 100 & 200 X-Imangu M M M M M Flexible hoses Tailplane front bolt Landing gear fork bolts Landing gear failure Flight controls Page 1 BGA Compendium 01/02 replacement inspection replacement Inspection of elevator driving rod Aer Pegaso (Italy) Status Subject Detail Reference information TNS Contact: Registro Aeronautico Italiano Airworthiness Directives AER PEGASO M M M M M M M M M M M-100S Rudder cable Fuselage panels Tail end structures Structures Winch launch Wing structure Aileron spar Elevator Lower Rudder Lower Rudder inspection use birch reinforcement modification max. speed 54 Kts plywood rib 16 inspect at centre hinges Control inspection Inspection of welds Replacement of hinge AD 61-9/M100 S-1 AD 62-10/M100 S-2, MB No3 AD 62-43/M100 S-3 AD 65-9/M100 S-4, MB No05,06 &07 AD 67-15/M100 S-6, TB 9/M100S AD 69-62/M100 S-5, TB 8/M100S AD 69-78/M100 S-7 AD 69-132/M100 S-8, TB 10/M100S AD 70-96/M100 S-9 AD 71-56/M100 S-10, TB 11/100S CVT M-200 M Rudder detached Canopy catches insecure Page 1 BGA Compendium 01/02 lower hinge failed - inspect daily modify them 10/90 & 10/86 06/93 Avia Stroitel (Russia) Status Subject Detail Reference information TNS Contact: Russia Sailplanes Ltd. 01432 851886 ME 7 & 8 (The ME 8 is not a BGA certified type) M M Elevator trim assembly Elevator operating lever Security of control systems AC4 NIL Page 1 BGA Compendium 01/02 inspect for cracks/deterioration at fin base became detached - inspect before next flight mandatory inspections before next flight 08/98 06/99 08/99 Birmingham Guild, Yorkshire Sailplanes, Swales (UK) Status Subject Detail Reference information suspect riveting missing rivets fouls fairlead nuts fouling no threaded insert stiffnuts not in safely secure with ‘Loctite’ rivets missing in tube in fuselage near wing root - inadequate clearance bond failure Allowing rudder to jam on fin shroud repair by fitting bushes cracks near the wing root screws not in safely SDL/135/Mod 2 TNS Contact: Vintage Glider Club BG-135, YS55 (Consort), SD3- 15T M M M M M M M M M M Aileron root drive Spar at wing root Aileron push rod Tailplane final drive Release knob failure Flying controls bolts too short Tailplane spigots U/C attachments Air brake mechanism jamming Aileron t/e bonded joint Rudder cable stops slippage Fuselage to wing lugs worn oval Spar rear web Air brake hinge brackets Page 1 BGA Compendium issue 01/02 SDL/135/2/74 10/74 03/75 10/75 10/75 04/76 09/77 07/78 10/79 12/88 08/90 Bolkow (Germany) Status Subject 5.4 5.5 Detail Reference information TNS cracks aft of seat replace if necessary AD 75-25 AD 76-268, SB 27-60/1 06/75 08/76 Contact: LBA Airworthiness Directives 5.6 BÖLKOW (MBB) Phoebus M M Rudder control arm Elevator drive fork end deformed Page 1 BGA Compendium 01/02 Breguet (France) Status Subject Detail Reference information TNS Contact: 905 Fauvette M Tailplane Centre section Air brake Page 1 BGA Compendium 01/02 rigging pin not secured modify system main spar (alloy) fitting corroded failure of pivots at pilots lever 10/84 10/84 10/86 Caproni (Italy) Status Subject Detail Reference information TNS aileron modifications to be incorporated replacement in undercarriage compartment. all flying tail to be modified AD 76-117-A21-6 AD 76-83, SB 76-06 TN 79/01 07/76 07/76 08/79 02/90 Contact: CAPRONI M M M M Calif A-21 & A-21S Wing flutter Drain holes Rudder pulley In flight break up Page 1 BGA Compendium 01/02 Carmam (France) Status Subject Detail Reference information TNS Contact: For M200 also see under Aer Pegaso JP36-15 M Lightning strike protection U/C retraction lever fit bonding rubber grip stops lock functioning secure the grip Rudder detached Canopy catches insecure lower hinge failed inspect daily modify them BGA 12/81 M-200 M Page 1 BGA Compendium 01/02 10/90 & 10/86 06/93 Centrair (France) Status Subject Detail Reference information TNS Contact; Societe Nouvelle Centrair, Aerodrome – 36300 LE BLANC France. +02 54 37 07 96 DGAC and LBA Airworthiness Directives Centrair 101 - Pegasus M M M M M M M M R M I R R Rudder Fuselage Aileron flutter Tow release guide fitting Rudder travel Trim spring failure Tailplane attachment (front) Elevator Rudder pedals cracked Airbrake operating handle Wheel brake control Rudder travel restricted Rudder & hook system jam Limitations L’Hotellier connections Battery A/B & U/C handles Air brake controls in fuselage Fixed undercarriages Speed Brake lever Air brakes Flying controls Manual revisions Control cables Flying controls Page 1 BGA Compendium 01/02 Top rudder hinge cracked SB 101-4 frame inspection SB 101-6 increase mass balance SB 101-7 min slack in cable 12 mm SB 101-8 restricted by pedal adjustment recurring fitting un-bonded, inspect annually hinge mountings cracks inspect "S" cable guides & tubes SB 101-11 colour fades - replace handle AD 91-113, SB 101-12 foul on u/c airbrake handle operated wheel brakes SB 101-15 by unsecured instrument pipes & wires rudder pedal plastic tubes jam on winch hook with rudder adjusted fully forward Reduced max rough air speed (VRA) and max aerotow (VA ) AD 93-145A, SB 101-17 annual check (BGA requires locking pins or sleeves) SB 101-18/1 Reinforce mount for front battery, new factory supplied part SB 101-19 confusion avoidance fit different shaped handles (minor mod) MM 101-10 weld failure mandatory change of part & annual inspections AD 1995-261(A)R2, SB 101-16/3 inspect for cracks SB 101-20 Replacement required if not already accomplished AD 1995-26(A) R1, SB 101-16 r4 Apply simulated air loads to check paddle mount bolts for jamming Aileron hinge pin inspection AD2001-247A, SB101-22 Flight and MM revision status list Cable swaging instructions SB101-23 Modifications to rudder pedals SB101/24 12/84 04/85 10/86 04/85 10/89 12/89 08/90 06/91 06/91 & 08/96 08/91 10/92 04/94 10/97 06/94 12/97 06/97 10/98 04/99 12/99 04/00 02/01 06/01 06/01 10/01 12/01 Centrair (France) Status Subject Detail Reference information TNS inspect for debonding cracked & failed inspect "S" tubes for cracks colour fades, replace handles not secured inspection annual check (BGA requires locking pins or sleeves) after inspections mandatory change of part Modification required to rear jettison Kit 201BE1580 Extension of service life Aileron hinge pin inspection Flight and MM revision status list Cable swaging instructions Modifications to rudder pedals SB 201-06 SB 201-07 AD 91-073, SB 201-08 AD 91-113, SB 201-09 AD 92-088, SB 201-11 AD 95-085A SB 201-15/1 AD 95-060A, SB 201-12 (2) AD 1999-055(A), SB 201-16 AD 1999-055(A)R1 AD 1995-060(A)R1 AD2001-248A, SB201-19 10/88 08/90 06/91 08/91 06/92 06/95 12/97 02/98 04/99 04/00 04/01 06/01 06/01 10/01 12/01 check mass balance & backlash to be painted red min slack in cable 12 mm to avoid PIOs correct application & maintenance of tape inspect "S" cable guides & tubes & welds for cracks colour fades - replace handle use suspended until wings are modified to Mod 11 Reduction of max. rough air speed by unsecured instrument pipes & wires AD 85-19, SB 20-6 SB 20-7 SB 20-8 AD 87-148, SB 20-12 SB 20-11 & 12 AD 91-073, SB 20-13 AD 91-113, SB 20-14 AD 92-223A/1, SB 20-16/1 AD 93-004(A), SB 20-17 Centrair 201 A, B & B1-Marianne M M M M M M M M M M I R R Tailplane LE Air brake handle, lower arm Rudder pedals Airbrake operating handles Aileron mass balance Elevator control L’Hotellier connections Life extension to 12 000 hrs Air brake controls in fuselage Rear canopy Service life Flying controls Manual revisions Control Cables Flying controls SB201-20 SB201-21 ASW 20F & FL M M M M M M M Flutter - flaps & ailerons Canopy opening knobs Tow release guide fitting Trim knob modification Aileron vibration Rudder pedals cracks & failures Airbrake operating handle Wing extensions Limitations Rudder travel restricted Page 2 BGA Compendium 01/02 04/85 04/85 12/87 & 02/88 12/87 06/91, 10/99 & 08/96 08/91 10/93 01/93 04/94 Centrair (France) Status Subject L’Hotellier connections M Air brake controls in fuselage M Flying controls I Manual revisions R Control Cables R Flying controls Detail annual check (BGA requires locking pins or sleeves) weld failure mandatory change of part & annual inspections Aileron hinge pin inspection Flight and MM revision status list Cable swaging instructions Modifications to rudder pedals Reference information SB 20-19/1 AD 1995-260(A)R2, SB 20-18/4 AD2001-246A, SB20-21 Lifting of BGA restrictions after inspection Flight and MM revision status list Cable swaging instructions BGA 001/05/2000 Iss2 SB20-22 SB20-23 TNS 12/97 04/99 06/01 06/01 10/01 12/01 Alliance 34 (and SF34B) M I R Fuselage Manual revisions Control Cables Page 3 BGA Compendium 01/02 SB34-03 08/00 06/01 10/01 DG Flugzeugbau (Glaser-Dirks) (Germany) Status Subject Detail Reference information TNS Contact; UK Agents McLean Aviation 01904 738653 LBA Airworthiness Directives, Tech notes can be downloaded from the internet. DG-100 M M M M M M M I M M O I M O O M Rudder cables Water ballast Wheel brake cable Rudder hinge (top) Aileron & u/c control Tailplane attachment Elevator control lever mounting Airbrake control system Service life Canopy Service manual Rudder cable conduit Debris in the wings Canopy jettison procedure etc Rudder separation in flight Tailplane mounting (Elan) L’Hotellier connectors Seat harness Airbrake system Aerotow hook Wingtips Service life U/C lever Canopies Page 1 BGA Compendium 01/02 inspect at pedals check for leaks incorrect routing may foul elevator control excess play allows rudder to disconnect foul in cockpit modify lock assembly washer missing rod failure in centre section Increase Emergency release Revision detached in rear fuselage fouls controls opening lever to be red inspect speed restriction & non-aerobatic until welds are inspected Safety device Instructions for new harness inspect & modify as necessary Optional installation Retrofit special inspections to increase life above 3000 hours must be fully home (against fuselage side) to lock U/C down single piece canopies, improved canopy securing System & safer jettison AD 76-261, TN 301-2 AD 76-262, TN 301-3 AD 77-123, TN 301-4 AD 77-61, TN 301-5 AD 78-164, TN 301-6 07/76 07/76 08/76 08/76 06/77 03/78 12/78 & 03/79 08/79 AD 85-126, TN 301-11 AD 85-80, TN 301-12 TN 301-13 AD 86-136, TN 301-14 AD 89-131, TN 301-15 TN 301-16 TN 301-17 AD 97-011, TN 301-18 TN 301-19 TN 301-20 AD 85-126 & 85-80, TN301/5 TN 301/21 02/83 08/83 07/86 12/88 08/89 02/97 02/98 12/99 02/00 DG Flugzeugbau (Glaser-Dirks) (Germany) Status Subject DG-200 & 202 Detail Reference information M reinforce spar nylon conduits in rear fuselage loose amendments – canopy release opening lever to be red inspect rudder adjacent to bottom hinge Safety device Instructions for new harness inspect & modify as necessary Optional installation special inspections to increase life above 3000 hours single piece canopies, improved canopy securing System & safer jettison Parking brake combined with airbrake securing device AD 79-232, AD 79-313, TN 323-1 M M O O M O M O Speed & weight restriction Rudder circuit becomes stiff Flight and MM Canopy jettison procedure etc Rudder separation L’Hotellier Seat harness Airbrake system Aerotow hook Service life Canopies Brakes TNS 02/83 AD 85-80, TN 323-5 AD 86-136, TN 323-6 07/86 12/88 TN 323-7 TN 323-8 AD 97-011, TN 323-9 TN 323-10 AD 85-80 02/98 TN 323/11 TN323/12 02/00 04/01 02/97 DG-300 M M M M M M I Elevator auto-connect misaligned Canopy jettison procedure etc Aileron mass balance Weight and C of G revised U/C jammed Wing root rib mod Control system bearings U/C lever travel restricted Air brake slots Water ingress Canopies Seat harness Page 2 BGA Compendium 01/02 optional guide block introduced opening lever to be red increased flight manual revisions by bungee key rings at air brake drive, VNE restricted until completed at wing root corroded by locking paw fouling introduce drains Possible water ingress into elevator Controls in fin single piece canopies, improved canopy securing Instructions for new harness System & safer jettison AD 86-136, TN 359-9 AD 87-1, TN 359-11 TN 359-13 AD 89-22, TN 359-4 BGA 009/10/2000 issue 1 TN 358-18 TN 359-19 04/87 & 08/85 07/86 04/87 04/88 02/89 04/89 06/89 04/90 12/91 10/00 02/00 DG Flugzeugbau (Glaser-Dirks) (Germany) Status Subject DG-400 Detail Reference information TNS M M M M M Max cockpit weight Starter wiring revised Power plant vibration Fuel & ignition system mods Canopy jettison procedure etc increased to 242 pounds TN 826-8 TN 826-9 AD 84-157, TN 826-11 TN 826-12 AD 86-138, TN 826-16 02/85 02/85 02/85 04/86 07/86 M M M M M M M M M M M M M Powerplant modifications Flexible wing tanks (fuel) Inspections Fuel shut off valve gaskets Power plant cable guides Engine extent/retraction Power plant wiring Empty C of G range Pneumatic fuel pump Locking of wing tip pins Rudder sealing Undercarriage collapse prevention Propeller shaft failures Electrical regulators Airbrake system Noise reduction Modification of Powerplant Unleaded MOGAS (95 octane) AD 91-149, TN 826-24, TN826-25 AD 83-171, TN 826-3 AD 84-155, TN 826-6 AD 85-219, TN 826-14 AD 85-223, TN 826-15 AD 87-108, TN 826-18 AD 87-109, TN 826-19 AD 88-99, TN 826-20 AD 88-99, TN 826-20 AD 88-99, TN 826-20 AD 93-010 SI 6-1 AD 96-243, TN 826-32 AD 96-242, TN 826-33 AD 97-011, TN 826-34 TN 826-36 AD90-43, TN 826-22 12/91 12/83 04/93 04/93 04/93 04/88 04/93 04/93 04/93 04/93 04/93 06/96 10/96 10/96 02/97 02/98 04/90 M M M Engine Service life Canopies O M Brakes Powerplant Page 3 BGA Compendium 01/02 crack checks & change engine mount to accept fuel with alcohol opening lever to be red 3 year life on fuel lines and L’Hotellier connectors modify tanks Rotax 505 engine, canopy jettison & tow release replace fouling modify inspection manual revisions plugged piece of hose loose engine vibration- damage fit plastic block beside lever strengthened shaft to be fitted life limit on some Bosch regulators inspect & modify as necessary fit DG 800 propeller & new fairing (non mandatory) In accordance with AD fuel system compatibility with Unleaded MOGAS change the drain valve seal. Part No 60504402 to be fitted TN 826-35 EGT gauges recommended to prevent engine overheating & failure special inspections to increase life above 3000 hours AD 85-126 & 85-80, TN 826-35 single piece canopies, improved canopy securing System & safer jettison TN 826-39 Parking brake combined with an airbrake securing device TN826-40 Inspection of rear plate AD 2001-346, TN 826-42 02/96 02/98 02/98 02/00 04/01 10/01 DG Flugzeugbau (Glaser-Dirks) (Germany) Status Subject Detail Reference information No negative ‘G’ until airbrake mod is carried out fit strengthened lever fit wider pulley (near hook) change every 4 years special inspections to increase life above 3000 hours Front landing gear inspection & modification Elevator control in vertical fin Modification to prevent flutter Ball bearings and articulated rod ends in the cockpit area rudder sealing & coolant reservoir FM changes Inspection of Teflon bush AD 93-009, TN 348/3 S&T AD 94-295/2, TN 348/4T AD 92-357, TN 348-2-2 AD 1998-048, TN 348/9 AD 1998-048, TN 348/9 AD 85-126 & 85-80, TN348/9 TN 348/13 AD1999-341, TN348/12 AD94-242 AD2001-079, TN348/15 AD 93-009 TN 843/3S, TN843/3T AD 96-154, TN 348/8 AD 1999-383?, TN 348-13 TNS DG-500 & DG-505 All marks M M M M M M M M M M M M Rudder sealing introduced Limitations Airbrake/wheel brake controls Belly hook cable jumps off pulley Wheel brake hydraulic fluid Service life Landing gear Flight Controls Air Brakes (ELAN) Ball bearings Flight manual revisions Fin Tank Landing gear 04/93 12/94 & 02/95 10/92 02/98 02/98 02/98 06/00 04/01 04/93 DG-500M, MB & 500/22M in addition to DG500 requirements M M M M M M M M M Airbrake/wheel brake controls Manual rev. Rudder & Cooling Propeller mounting plate cracks Belly hook cable jumps off pulley Wheel brake hydraulic fluid Service life SOLO engine modifications Landing gear Unleaded MOGAS (95 octane) Engine Ball bearings Flight Controls Page 4 BGA Compendium 01/02 fit strengthened lever AD 92-358, TN 843/3-2 Details in AD AD 93-010, TN 843/5 mods & 25 hour inspections AD 97-224, TN 843/8 fit wider pulley (near hook) AD 1998-023, TN 843/9 change every 4 years AD 1998-023, TN 843/9 special inspections to increase life above 3000 hours AD 85-126 & 85-80, TN843/7 Drive belt tension AD 1999-383, TN 843/13 Front landing gear inspection & modification TN 843/14 fuel system compatibility with Unleaded MOGAS change the drain valve seal. Part No 60504402 to be fitted TN 843/8 EGT gauges recommended to prevent engine overheating & failure Ball bearings and articulated rod ends in cockpit area AD2001-080, TN843/16 Elevator control in vertical fin AD1999-341, 843/12 10/92 08/97 02/98 02/98 02/98 02/00 06/00 02/96 02/98 02/01 DG Flugzeugbau (Glaser-Dirks) (Germany) Status Subject DG-600M, DG-600-18M M M M Flight Manual amendments Electronic stall warning system Unleaded MOGAS (95 octane) Engine Service life Canopies Detail Reference information TNS TN 866-1 TBA (Mandatory) 10/90 04/91 fuel system compatibility with Unleaded MOGAS change the drain valve seal. Part No 60504402 to be fitted TN 866/6 EGT gauges recommended to prevent engine overheating & failure special inspections to increase life above 3000 hours AD 85-126 & 85-80, TN866/6 single piece canopies, improved canopy securing system & safer jettison TN866/8 02/96 02/98 02/98 02/00 DG-800A, LA, B & S M M M M M O O O R I M Mikuni carburettors Ignition coil wiring Revised flight manual Fit internal flaperon & rudder seals Engine Mods and manual changes SOLO engines (DG-800B) Engine extension/retraction Powerplant Unleaded MOGAS (95 octane) Engine Brakes Wings Muffler (Solo engine) Manual revisions Production change Powerplant Page 5 BGA Compendium 01/02 needle arm levers fretted unsupported TN 873-5 performance improvement (non mandatory) TN 873/8 at 25 hour inspection (before 31/05/99) AD 1999-167, TN 873/12 modifications, drive belt tension reduced AD 1999-377, TN 873/16 SOLO engine inspections TN 873/19 Powerplant and manual revisions AD1999-269, TN873/13 fuel system compatibility with Unleaded MOGAS change the drain valve seal. Part No 60504402 to be fitted TN 873/8 EGT gauges recommended to prevent engine overheating & failure Parking brake combined with an airbrake securing device TN873/20, TN384/6 Dimple tape turbulators on the lower surface TN873/21, TN384/7 Muffler lifting cable and rubber return cord TN873/22 Flight and maintenance manual revisions TN873/23 V/Tail, steerable tail wheel, Powerplant & electrics. 800-13-00 Inspection of rear plate AD 2001-340, TN873/25 04/95 04/95 02/96 08/97 06/99 02/00 08/00 02/96 02/98 04/01 04/01 04/01 04/01 04/01 10/01 Diamond Aircraft (formally Hoffmann) (Austria) Status Subject Detail Reference information TNS AD 82-236, TN 2 AD 82-237-2, TN 3/2 AD 83-156, TN 6 AD 83-157-2, TN 7/2 AD 84-205, TN 11 AD 85-34, TN 12 CAA CAA CAA CAA CAA CAA AC AD 60, AD 85-128-2, TN 13/1 CAA 002-08-85 AD 86-177-3 CAA 010-08-85 AC AD 53, AD 87-93, TN 15/2 AC AD 54, AD 87-94, TN 17 AC AD 52/2, AD 86-177-3, TN 19 AC AD 55, AD 88-108, TN 24 08/85 10/85 12/86 12/86 06/87 06/87 08/87 08/88 08/90 02/92 12/93 12/93 08/96 06/00 Contact: UK Agent- Airborne Composites (Tim Dews) 01985 40981 LBA and Austro Control Airworthiness Directives HOFFMAN H-36 Dimona & HK-36 & HK-36-R Super Dimona M M M M M M M Aileron, elevator, wings Wing Fuel tank Engine brackets Fuel systems Aerobatics & spins Fuel tank M M M M M M M Tailplane Flight limitations & placarding Elevator drive inspection Tail/elevator unit Shoulder harness fixings Wing to fuselage joint Wings Fin skin separation Extension of service life Exhaust system Air brake system Elevator root rib Engine software M M M M Page 1 BGA Compendium 01/02 water accumulation Composite skin inspection capacity check inspect and modify vapour lock prohibited gel coat detached and restricts fuel flow, Optional - fit aluminium fuel tank 50 hrs inspection, forward attachment rod end changed (CAA letter 9/97/CtAw/119) after rigging front fixing inspection inspection additional bracing dimensional check main bolts at top rudder hinge inspect from 3 000 to 6 000 hours (Super Dimona) modify (Super Dimona) modify modification before 3000 hours or if damaged Check software version of engine TCU AC AD 65, SB 25/1 AD 74, SB 33 AD 74, SB 34 AD 85, SB 51 AD 99, SB 66/1 Iss2 Eiri Avion (Finland) Status Subject Detail Reference information TNS pin security in fuselage replace with 3/32” Mil spec 1511 replace inspect SB M227/64/2 SB M278/64/2 SB M300/65/2 SB M784/78 04/88 front fitting modify secure connector with Fokker pin free operation of locking pin shroud jamming worn against flap drive operating rod knob insecure 450 Kg AUW, max water 140 Kg lubricate with Molycote Modification of Tost Europa hook check for voids “LIV” replace with LEKO/1 Inspection & modification of flap gear rack fit bonding hang up in hook access hole, cut clearance failure, worn on u/c lever bolt ends 5 mm minimum clearance tanks too long /pipes restricted drill drain holes & grease hinge pins play in rear torque tube incomplete bonding inspect & repair as necessary SB M1 SB M3 SB M4 SB M5 SB M6 SB M7 SB M10 SB M12 AD 735/77, SB M14 AD 733, SB M17 AD 746/77, SB M15 AD 736/77, SB M16 Contact; National Board of Aviation Finland Airworthiness Directives Vasama Pik 16C Wings M Rudder cables M Rudder pulleys M Push rod end fittings loose Pik 20 series M M M M M M M M M M M M Tailplane Elevator disconnects Undercarriage Elevator and T P Rudder cables Flap drive Weight increase Flaps Tow hook Spar bonding Safety harness Flaps Lightning strike protection Tow rings Rudder cable Wheel fouls landing gear Water ballast - slow draining Flap hinge covers Landing gear Wing skin Page 1 BGA Compendium 01/02 AD 779/78, SB M 18 SB M19 SB M20&21 SB 79/04/01 SB 79/04/07 SB M20D-24 10/75 10/75 10/75 10/75 10/75 10/75 07/76 10/76 07/77 09/77 10/75 10/75 04/78 01/79 06/79 06/79 06/79 06/80 Eiri Avion (Finland) Status Subject M Rudder lower hinge failure Landing gear M Rudder travel Aileron mass balances Heavy landing M Elevator control M Elevator control Elevator controls M Cable release M Landing gear Detail Reference information rudder separation modify AD M1232/84, SB M 20-26 corroded AD M851/79, SB M22 restricted at extreme pedal adjustment, limit adjustment detached annual inspection for corrosion AD M1479/87 rudder lower hinge failed foul in cockpit with flap lever leaf spring foul in cockpit by misaligned trim spring fouling seat pan uniball joint thread stripped relocation to improve pilot access No locking on main wheel axle drill holes and fit wire-locking TNS 06/83 06/84 12/87 04/89 06/90 02/94 10/92 06/93 06/97 Pik 20E (Powerplant) in addition to PIK20 series M M M M M M M M M M Starting circuit Engine down lock fouled Fuel tank chafed Fuel tank chafed Fuel flow restricted Electrical system Fuel gauge inaccurate Power plant wiring Fuel flow Prop hub Electrical bonding Intermittent ignition faults Fuel System propeller Page 2 BGA Compendium 01/02 dual solenoids by restraint cable modify if necessary by tow release cable clip - re-clip by seat back cable tube clamps pipe clamps too tight & dirt in fuel mods to reduce consumption calibrate damaged restricted by hose at filter check flow rates bearing failure connection by pylon failed cracked spark plug connector inspection of fuel hose clips Inspection of propeller hub mounting CAA Notice No 33, SB M20 E SB M20 E3 SB M20 E4 SB H2SE-1A CAA - AN 36, AD 90-239 AD M1200/83 AD M1737/90R1 08/79 04/80 04/80 02/94 06/80 12/80 12/82 12/82 10/94 & 12/85 08/99 & 10/90 06/94 02/99 Elliots of Newbury (UK) Status Subject Detail Reference information TNS Contact: Vintage Glider Club Oly 1&2 Control cables Rudder Elevator mass balance Elevator and ailerons Elevator Rudder hinge damaged in wheel box lower hinges cracked insecure cracks cracks in ply “spar web” near to actuator (sketch in TNS) lower bearing displaced 02/73 12/76 08/90 08/91 & 10/91 10/98 04/00 deteriorated fractured by careless rigging castle nut & split-pin insecure inspect & replace as necessary Mandatory inspection Mandatory modification 02/73 04/77 06/94 & 08/80 03/81 12/96 08/97 Oly 460 Series M M Aileron bungees Airbrake lever on root rib Elevator hinge Spar fitting washers cracked Main spar failure - corrosion Page 1 BGA Compendium 01/02 BGA/OLY/460 Series 1/97 Flug Und Fahrzeugwerhe (Switzerland) Status Subject Detail Reference information TNS excess play alignment at base of fin lack of strength - reinforce reinforce distorted inspect annually & after heavy landings annual crack check inspect annually AD 16-18 SB 04 09/73 01/74 03/79 03/79 12/81 02/97 Contact: FLUG UND FAHRZEUGWERHE Diamant 16.5 & 18 M M M M Elevator controls Elevator controls Harness attachment Wing spar root stubs Elevator drive rod fork end Lower rudder hinge failures Rudder pedal rear support failure Page 1 BGA Compendium 01/02 SB 105 AD 80-18-09, SB 07 & 08 TN 09 AD Sportavia (Fournier / Aviostar) (France / Germany) Status Subject Detail Reference information TNS AD 67-39/1, SB 2 AD 75-76 06/83 06/83 06/98 Contact: DGAC Airworthiness Directives FOURNIER / SPORTAVIA / AVIOSTAR RF-3 M M M Wing skin Limitations Main U/C fork failed Restrictions RF 4 and RF4D M Rear fuselage Main U/C fork failed M Fuselage M Tailplane RF-5 & 5B M Rear fuselage M Elevator mass M Airbrake system bolts in wings Wing fold M Fuselage M M M Propeller Fin Tailplane Page 1 BGA Compendium 01/02 inspection for cracks and inspection of glued joints normal category only placard “spinning prohibited” inspect Airworthiness Data Sheet bottom & rudder post inspect for water damage inspect Inspection/repair of aft fuselage and vertical fin spar Inspection/replacement of the rear stabiliser mounts AD64-20 CAA AD 83-49, SB S-02-82 06/83 06/98 AD83-15, TN S-02-82 AD85-207, TN S-01-85/1 bottom & rudder post inspect for water damage CAA AD 83-49, SB S-02-82 balance to be fitted (RF 5B), Mod 23 CAA AD 79-533/2 inspect & replace as necessary AD 92-351, SB S-02-91 unlocked on take off Remove ground handling bar from the fuselage and inspect for grinding marks in the longitudinal direction of the fuselage centre-line AD72-24 Replacement of propeller boss bolts and centring bushes AD72-25, WI A04-72 & SL S-02-72 Inspection/repair of aft fuselage and vertical fin spar AD83-15, TN S-02-82 Inspection/replacement of the rear stabiliser mounts AD85-207, TN S-01-85/1 06/83 06/83 12/92 02/95 & 12/95 Glasflugel (Germany) Status Subject Detail Reference information TNS Contact; UK Agents Southern Sailplanes 01488 71774 LBA Airworthiness Directives Libelle - Std, H201, H201B, H301 & H301B M M M M M M M M M M Rudder cable conduits Rudder control stops Tailplane rigging Wheel axle failures Seat pan Elevator Heavy landing damage Trim springs broken Elevator vibration Elevator attachment Rudder actuator Rudder cables (2.5 mm diameter) Wing spar spigots Extension of service life Control surface mass balance Spar stubs annual inspection Aileron drive shaft in fuselage Elevator travel FM amendment Club Libelle (Glasflügel 205) M Tailplane Rudder actuator M Elevator drive M Rudder cables (2.5 mm diameter) Page 1 BGA Compendium 01/02 see also section 5.2.1 to be secured, glued into place reinforce in wheel box AD 73-80 attachment guides reinforcement AD 75-168, TN 201-20, TN 301-30 inspect for bending & cracking distorts & fouls release cable reinforce as necessary linkage at base of stick cracked mandatory replacement TN 201-22 inspect inter elevator links and brackets inspect for cracks, wear & corrosion minimise backlash cracks in tailplane bracket annual crack check mandatory (many have been found cracked) replace all hemp cored cables AD 87-83, TN 201-26 mounting plates corroded 6 000 to 12 000 hrs with inspections(201 & 201B) AD 94-265, TN 201-29 limits changed ref BGA separation of laminate from fittings & fittings corrosion TN201-31,TN301-36 centre reinforce or replace or crack check annually TN 201-33 restricted with gear up interference with wheel brake cable High altitude flight AD 84-11, TN 201-25 rigging guides reinforcement serial Nos→107 annual crack check mandatory bracket modification replace all hemp cored cables AD 75-168, TN 205-6 AD 88-28, TN 205-16 AD 88-07-05 10/75 & 08/73 10/75 09/77 03/79 12/80 05/81 02/88 & 06/84 08/85 12/85 04/88 06/88 04/93 12/94 04/96 04/96 04/96 & 06/96 04/97 10/75 08/87 04/88 06/88 Glasflugel (Germany) Status Subject M Extension of life Spar stubs annual inspection Detail from 3000 to 6000 hrs after inspections separation of laminate from fittings & fittings corrosion Reference information AD 88-280/2, TN 205-15 TN205-19 TNS 04/89 04/96 rigging attachment guides reinforcement Serial Nos 1→3 bolts fouling in wheel well annual crack check mandatory or fit improved design bracket modification replace all hemp cored cables from 3000 to 6000 hrs after inspections hinge pins not secured worn mounting studs separation of laminate from fittings & fittings corrosion High altitude flight AD 75-168, TN 206-1 modify limits relaxed limits changed AD 80-221, TN 206-9 AD 97-311, TN 206-18 AD 1997-311/2, TN 206-19 12/80 12/97 02/99 AD 86-221, TN 401-19, TN 604-2 AD 71-10, TN 401-10 AD 79-233, TN 401-16 AD 81-266, TN 401-17 AD 87-83, TN 401-20 02/87 Hornet A, B &C (Glasflügel 206) M M M M M M M Tailplane Air brake/aileron Rudder actuator Elevator drive Rudder cables (2.5 mm diameter) Extension of life Elevator Canopy lifting frame Spar stubs annual inspection FM amendment AD 88-28, TN 206-12 AD 88-07-05 AD 88-280/2, TN 206-12 TN 206-16 AD 91-111, TN 206-16 TN206-17 AD 84-11, TN 206-11 10/75 08/76 08/87 & 04/98 04/88 06/88 04/89 10/91 10/91 04/96 Hornet C (only) M M M Aileron mass balance Aileron mass balance Control surface mass balance Glasflügel 401 (Kestrel 17) & Glasflügel 604B Glasflugel 401 see Slingsby T59, Kestrel 17 for general information M M M M Rudder drive Rudder cables Airbrake drive rod Service life Rudder cables (2.5 mm diameter) Page 2 BGA Compendium 01/02 annual inspection mandatory Inspection & replacement ends failure at weld replace rod ends in wings 3,000 to 6,000 hrs after inspections replace all hemp cored cables 06/79 06/88 Glasflugel (Germany) Status Subject M Control surface Spar stubs annual inspection M FM amendment Detail mass balance limits changed separation of laminate from fittings & fittings corrosion High altitude flight Reference information AD 96-139, TN 401-25 AD 96-133, TN 401-24, TN604-5 AD 84-11, TN 604-1, TN 401-18 inoperative check that pip pins are fully home annual crack check mandatory or fit improved design bracket modification worn mounting studs lower mounting tube fatigue failure at fixing pin hole Extension of service life at 3000 hrs Extension of service time and supplements Carbon fibre aileron mass balance High altitude flight AD 79-322 TNS 04/96 04/96 Mosquito & Glasflügel 304 M M M M M M M Canopy jettison Rudder actuator Elevator drive Canopy lifting frame Rudder pedal Life extension Life extension Ailerons FM amendment Page 3 BGA Compendium 01/02 08/79 08/87 & 04/98 AD 88-28, TN 303-12, AD 88-28, TN 304-3 04/88 AD 91-111, TN 303-18 10/91 12/98 AD 88-281, TN 303-13, TN 304-4 AD 2000-318, TN 303-22 TN 304-9 10/00 AD 95-102, TN303-21 AD 84-11, TN 303-10, TN 304-2 Grob (Germany) Status Subject Detail Reference information TNS Contact: UK Agent Soaring Oxford 01869 881495 LBA Airworthiness Directives Single Seat Astir Series M M M M M M M M Aileron connectors Marks to align tailplane Fixed wheel variants Rudder pedal slide unit Speed brake paddle Aluminium fuselage main frames Lower rudder hinge Airbrake bellcrank in wings Elevator control rods Elevator vertical drive Wing to fuselage attachments Top harness attachments Retractable u/c hinge bars Wing root spigot Inner elevator hinges Undercarriage lever retaining bolt Airbrake stops Elevator drive cracked Frame at base of the fin Life extension C of G ranges Tow hook back release Page 1 BGA Compendium 01/02 disconnect & rods jam (not CS) TN 306-15 reinforcement of wheel mount BGA Mod Astir/1/83 inspect for cracks AD 83-43, TN 306-21 lever arm cracked inspect frequently for cracks (not CS) cracks in GRP failure - replace with solid type TN 306-26 corroded in rear fuselage loose rivets balls missing (should be six per socket) secure around transverse tube and through buckle 3 times RS 306 & 320 circlips come off - replace with split pins replacement mandatory for all models AD 91-005/2, TM 306-29, TM 320-5 mountings cracked/detached AD 89-209/2, TN 306-27/1 loose in GRP inspection AD 92-356, TN 306-31 replace AD 94-317 fractured by ground loops - causes tail end flutter 3000 to 12000 hours after inspections & mods TN 306-30/2 mm differ after serial 1438, 1002→1437 - 250 to 425 aft, 1438→1536 - 310 to 480mm aft If wire launched with adverse yaw may have difficulty Releasing 10/87 & 08/79 03/81 04/83 06/83 03/82 & 12/83 04/84 06/85 06/85 08/87 08/87 10/87 12/87 & 01/93 12/98 & 06/88 02/91 08/91 06/92 12/92 12/94 06/95 & 04/95 06/96 04/99 02/00 Grob (Germany) Status Subject CS only Detail Reference information M M M M M M safety clip to secure bolt installation reinforcement serial numbers →1175 fit stops inspect pulley bearings cracked at thread - replace replace check for wear annually - fit oversized ball plunger not seating (optional mod) debonding inspection replacement mandatory for all models TN 102-4 AD 76-226, TN 102-3 TN 102-7 AD 77-235, TN 102-6 TN 306-17 TN 306-17 TN 306-17 08/76 08/76 09/77 11/77 09/81 09/81 09/81 08/92, 12/86 & 08/86 04/87 AD 92-356, TN 306-31 12/92 AD 91-005/2, TM 306-29, TM 320-5 02/91 replace operating lever with solid type foul with pedals fully forward - mod as required safety device required check for full deflection in all positions ailerons jammed replacement inspection replacement mandatory for all models AD 78-30, TN 102-8 M M Control column pivot Tow hook Ailerons Hook release Tailplane attachment ball Tailplane rear attachment pins Tailplane front location ball Tailplane locking insecure Rudder hinges Airbrake stops Wing root spigot TNS CS, CS77 and Jeans M M M M M M M Rudder system Rudder pedal/tow release Inspection cover - top fuselage Rudder pedal adjustment Water ballast control detached Elevator drive lever Airbrake stops Wing root spigot AD 80-96, TN 306-13 AD 94-317/2, TN 306-30&33 AD 92-356, TN 306-31 AD 91-005/2, TM 306-29, TM 320-5 03/78 04/80 06/80 08/91 10/94 12/94 & 06/95 12/92 02/91 Grob 102 Club Astir II, III & IIIb and Std Astir II & III M M Canopy locks Rudder pedal slide unit Inner elevator hinges Page 2 BGA Compendium 01/02 (Mk II s only) fit improved springs inspect for cracks loose TN 306-14 AD 83-43, TN 306-21 TN 306-27 08/80 06/83 12/89 Grob (Germany) Status Subject Airbrake stops M Elevator flutter M Wing root spigot Detail inspection Vne restrictions replacement mandatory for all models Reference information AD 92-356, TN 306-31 AD2001-317/2, MSB306-36/2 AD 91-005/2, TM 306-29, TM 320-5 springs modify improved springs replace inspection to 12 000 hours and service manual changes Markings to ensure correct assembly replacement mandatory for all models AD 80-178, TN 320-2 TN 320-5 AD 92-356, TN 320-6 AD 1998-480, TN 320-7 AD 80-303, TM 320-3 AD 91-005/2, TM 306-29, TM 320-5 TNS 12/92 & 10/94 12/01 02/91 Speed Astir II & IIB M M M M M M Canopy jettison & flap lock Canopy locks Wing root spigots Airbrake stops Life increase Elevator Wing root spigot 08/79 08/80 02/91 12/92 02/99 02/91 Twin Astir, Twin Astir Trainer, G-103 Twin II, G-103A Twin II Acro, G-103C Twin III & Twin III Acro M M M M M M M M M M M M Wheel brake back plate Airbrake locking lever Aileron & airbrake controls Controls L’Hotellier connectors Flight manual Rudder Pedals Cable release knob Rudder cables Airbrake lever failure (front) Airbrake lever failure (front) Rear rudder pedals Airbrake stops fail Side hinged rudders Front canopy lock Aft hook release knob Page 3 BGA Compendium 01/02 torque stud fractured replace with solid type serial numbers→3040 screws loose serial numbers→3255 Change elevator trim tube replace with stronger type correction of pages Inspection jams ailerons - modify damaged at “S” bends replace failure parallel lever - replace levers foul wing skins & jams brakes out delamination of fin skin at hinges colour code for open/shut modifications to prevent it jamming the stick AD 79-258, TN 103-5 AD 79-331, TN 315-6 TN 315-13 AD 81-125/2, TN 315-12 AD 83-6 AD 82-132, TN 315-20 AD 85-222, TN 315-29 AD 85-191, TN 315-30 AD 85-236, TN 315-31 AD 87-140, TN 315-32 07/78 06/79 08/79 05/81 09/81 12/83 06/84 12/85 10/98 12/85 12/85 08/86 08/87 08/87 Grob (Germany) Status M M M M M M M M M M M M M M M M M Subject Detail Rear rudder pedal lever replace Elevator push-rod corrosion (G 103A) lower end of fin rod Wing root end spigots replace Control systems (G 103 & 103A) inspections & mods Foul between aileron & airbrake controls in centre section Aileron mass balance cracks - inspect Airbrake handle (G 103C Acro III) fit new hinged lever Tow hook front mounting bracket cracked Manual & placard amendments G-103C only Rudder pedal unit (G-103C only) fit new spindle & guide Rudder drive failure at fork end at rudder Aileron lever placard for correct assembly Wing to fuselage joiners inspect after ground loops Airbrake stops inspection Life extension to 6000 hrs Life extension from 3000 to 12 000 hrs. after inspections & mods Airbrake lever (over centre) replace G.103 Twin III extended limitations Rudder cable pulleys cracked Front rudder pedals (G 103C) slide rod fractured Emergency exit fit placard detailing procedure Canopy jettison handles disengaged from jettison systems - check Rear release cable jams between panel & coaming. Hook held open Airbrake over-centre adjustment must be correct to avoid un-demanded opening Option to remove belly hook fit dummy hook (aerotow only) Front rudder pedals mounting plate partial disbonding - inspect Rear stick knurled nut cracks replace Control cables Cable release failed at swage at release hook arm Service life Inspections at 3000 hrs Elevator incorrect rigging, fit markings Page 4 BGA Compendium 01/02 Reference information AD 87-168, TN 315-33 AD 88-1 , TN 315-14 AD 88-176, TN 315-36 AD 88-175, TN 315-37 AD 89-5/2TN 315-38 TN 315-39 TN 315-40 TN 315-41 AD 89-005/2, TN 315-38/1 AD92-356, TN 315-49 AD 81-268, TM 315-15 AD 92-190/2, SB 315-45/2 AD 92-309/2, TN 315-47/2 AD 93-134 TM 315-35/2 AD 1999-216, SB 315-61/2 AD 84-58, TN315-26 AD 81-53, TM 315-11 TNS 10/87 04/88 10/88 10/88 02/89 02/86 & 04/89 08/89 02/91 & 10/89 12/89 12/89 06/90 06/90 02/91 12/92 08/96 04/93 08/93 01/93 & 12/94 06/96 06/96 08/97 10/97 12/97 04/98 12/98 08/99 04/00 Grob (Germany) Status Subject Grob G-103 Twin 3 SLMG Detail Reference information TNS M M upper pulley wheel inspection replace swage failed AD 92-352, TM 869-4 AD 92-354, TM 869-5 12/92 12/92 04/00 Drive belt failure Transmission drive pin Cable release Grob G-109 & G-109B M M M M M M M M M M M M M M M M M Flight manual revisions Main landing gear Flight manual revision Main undercarriage beams Flight manual changes Flying controls Flight and maintenance manuals Elevator two inner hinges Spar spigot Quiet exhaust system Corrosion of bolts Hot air shutter valves Bendix Magnetos (G 109B) Aileron & airbrake bell crank Rudder Extension of service life Elevator and trim tabs Exhaust system Airbrake stops Fuel cock Undercarriage Pulleys in wheel brake system Carb float valves & diaphragms Valve seats Page 5 BGA Compendium 01/02 fractures C of G range and spin recovery fit new type mandatory modifications to avoid aileron flutter change of pages replace crack check every 300 hours non-mandatory mod in wing root attachments cracked, failed & and butterfly screws loose impulse coupling inspection attachments corroded bell crank cracked & failed beyond 3 000 hrs after inspections & mods drain holes leaks & install CO2 detectors & 100hr inspections inspection replacement of seal 1000 flight inspections and change of parts cracked replace nylon with aluminium inspection inspection AD 83-6, TN 817-8 AD 85-132, TN 817-19 AD 83-104, TN 817-10 AD 83-104, TN 817-10 TM 817-17 AD 85-218/2, TN 817-20 AD 86-219, TN 817-22 AD 88-50, TN 817-25 CAA AD 006-10-88, TN 817-20 TM 817-26 AD 92-189, TN 817-34/2 AD 90-315, TN 817-29 AD92-198, TN 817-28/1 AD 92-350, TN 817-35 AD92-359, TN 817-32 AD 92-356, TN 817-36 AD 87-142/2, TN 817-23/1 AD 94-004, TN 817-39 TM 4601-7 TM 4601-8 12/84 06/85 06/85 06/85 12/86 04/88 02/90 06/90 06/91 10/86, 12/92 & 10/91 08/92 06/92 08/92 08/92 12/92 12/92 12/92 12/92 10/93 & 04/94 04/94 02/94 12/94 Grob (Germany) Status M M M M M M R Subject Detail Spark plugs Champion REN 30 S approved Engine operator’s manual new introduced Rudder system fit damper and new bellcrank Engine mounting frames (G109 B) inspect for abrasions Tail wheel springs damage rudder push-rod Pitch change bolt failure various causes detailed in TNS Canopy jettison control jammed by screws that attach roof trim G109B - CAA flight manual change quoted performance reduced Unleaded fuel permitted after mods (banned by CAA - AN 98/98A) Fuel filter Replacement of fuel filter Flying controls modifications to avoid aileron flutter CAA Variation of LBA AD 85-218/2 Flying controls inspection of air brake control rod Page 6 BGA Compendium 01/02 Reference information TM 4601-9 TM 4601-10 AD 94-262, TM817-38 AD 95-362, TM 871-45 CAA Ref 1236/41491 SB.817-46 SL 109-1 CAA AD 012-11-86, TN817-20 BGA 022/10/2001 iss1 TNS 12/94 12/94 12/94 12/95 06/97 02/98 06/98 04/99 02/00 & 08/99 06/00 12/86 10/01 IAR S.A. Brasov (Romania) Status Subject Detail Reference information TNS Contact: IAR S A Brasov, 2200 Brasov, PO Box 198 Romania. +40 68 465108 Service bulletins classed as mandatory by Romanian CAA IS-28 B2 M Drain holes M Airbrake/trim controls M Release cable/rudder adjustment M Rudder pedal bearings M Seat back fittings M Wing junction locking Canopy locks insecure M Accelerometer Wing root locating pins Aileron push-rod Air brake/wheel brake M Air brake ball joint Air brake “snap” connector Flaps Structural safe life increased M Dual fork end in aileron circuit M Locking wire (brass) M Airbrake handle breaks off IS-28M2 & IS-28M2A M Product improvement M M M M U/C structure strengthening Placard Landing gear Maintenance & flight manual Page 1 BGA Compendium 01/02 inspect & clear as necessary foul in cockpit foul mod as required secure in housing SB E0-6 SB E0-7 modify (non - mandatory) required for aerobatics inspect for scores that may lead to cracking bent at aileron interconnect may restrict airbrake travel - adjust failed at thread, check adjustments behind seat unlocked - tab washer failure cracked at root rib to 10 000 hours/30,000 flights after inspections replace to be replaced inspect before next flight & reinforce before 1/1/2000 SB E0-9 SB E0-13 SB E0-14 SB E0-10 The following Mods should have been embodied before 1983: -145, 147, 149, 153, 154, 155, 156, 165 & 167 IS-28M2/CO-2 and fitting micro switches CR-6 & 7 landing gear lock IS-28M2/EO-3, Mod 198 down lock indicator IS-28M2/CO-4 amendments IS-28M2/EO-5 10/75 10/75 09/77 04/78 01/79 01/79 01/81 03/81 12/82 12/82 12/82 12/82 02/83 06/85 06/85 12/85 12/87 06/99 04/84 04/78 04/84 04/84 04/84 IAR S.A. Brasov (Romania) Status M M M M M M M M M IS-29 M Subject Overhaul life Flying controls Speed limitations Life increase after inspections Rudder box axle rivet Aileron controls Wheel brake Rudder pedal stops Airbrake handle breaks off Detail brass locking wire to be replaced (see CAA 014-11-82) placards & flight manual amendments to 4000 hours/25 000 landings replace inspect rods for bending & cable locking wire Bowden cable support replace with modified type replace with modified type inspect before next flight & reinforce before 1/1/2000 Tailplane mass balance Flaps jammed negative U/C structural failures Drain holes inadequate Release cable Flap lever Structural life limitations Airbrake lever fouls flap lever secure at tailplane backlash in press button linkage inspect drill extra as necessary failure at split ferrule cracked near locking mechanism M M AUW increase U/C structural failure Airbrake handle breaks off from 590 Kg to 610 Kg reinforcement introduced inspect before next flight & reinforce before 1/1/2000 IS-32 M M Life limitation Airbrake handle breaks off 3 000 hours 15 000 launches inspect before next flight & reinforce before 1/1/2000 M M Reference information IS-28M2/EO-8 IS28M2/EO-10 IS28M2/EO-11 IS28M2/EO-12 IS28M2/EO-13 CAA 014-11-82 IS28M2/EO-14 IS28M2/EO-14 SB E0-11 unlocks flaps - modify system TNS 04/84 04/84 06/85 06/86 06/86 06/99 10/75 01/76 08/76 09/78 09/78 04/80 12/85 04/90 IS-30 Page 2 BGA Compendium 01/02 SB CR3 EO-2 10/86 04/87 06/87 & 06/99 04/87 06/87 & 06/99 Issoir Aviation (France) Status Subject Detail Reference information TNS Contact: D-77 Iris and E-78 Silène M Lightning strike protection Page 1 BGA Compendium 01/02 fit bonding BGA LET (Letecké Závody) (Czech Repulic) Status Subject Detail Reference information TNS Contact; LETECKE ZAVODY, as, 686 04 Kunovice, Czech Republic. +420 632 554496. E-mail [[email protected]] Service bulletins made mandatory by the Czech CAA and UK CAA Airworthiness directives Blanik L-13 and Vivat Motor Glider M Towing equipment M Controls M Canopy R Instruments R Controls R Canopy hinges R Wing R Controls Rudder cable M Nose hook jamming M Top rudder hinge Nose hook R Technical Manual M Air brake torque tube Life extension Tail wheel R Technical Manual M Cable release M Wing root spar M Outer elevator hinges on TP Fin spar M R R Top harness Airbrake lever Reinforce wings Flight manual Instructions Page 1 BGA Compendium 01/02 Mod to hook & replacement of cable CAA 0838 PRE 78 To be labelled CAA 0839 PRE 78 Deletion of canopy retaining strap CAA 0840 PER 78 Inspection of LUN1211.1 T/B indicator No 61> SB L13/010 Inspection of rudder pedals SB L13/019 Modification to prevent cable hang up on hinges SB L13/021 Modification to wing spar web SB L13/023 Inspection & replacement of control rods SB L13/025 failures at under-floor pulleys tension cables correctly SB L13/030 incorrect hook tongue adjustment bracket on fin failures rudder detaches SB L13/034 & L13/40 inadvertent release weak & broken springs & foot operation by passenger Alterations SB 13/042 cracked at wing root reinforce Mod SK-L13.208 to 25 000 launches & 5 225 hrs after spar inspections SB L13/045, LET/8/4512/78 strut failure damages elevator, reinforce strut Alterations SB L13/046 lever mount on bulkhead No 1, reinforce SB L13/047 spacer cracked inspections required SB L13/048 & L13/053 cracked inspect and repair as necessary SB L13/052 frames 13 & 14 cracked, repair schemes attachments cracked clevis pins jam on cockpit side cover plates Amendment For pilots and Flight manual amendment SB L13/055 SB L13/056 SB L13/058 10/75 04/75 06/75 & 10/75 10/75 03/75 04/84 02/77 & 07/77 03/78 12/81 01/79 01/81 & 12/81 01/82 01/82 07/82 LET (Letecké Závody) (Czech Repulic) Status Subject R Service life Undercarriage Tow release Overhaul periods Wing upper spar boom M Wing root spar strap Cracking of wing ribs M Elevator drive M Tailplane M M I M TBO Extension Fuselage Type certificate Detail Data unification of overhaul life fatigue failures inspect system & mounts frequently layshaft brackets in nose cracked, inspect manufacturers recommended root end - corrosion cracked, inspections required inboard of speed brakes incorrect rigging colour code front attachment frame in fuselage NDT & replacement Correction to SB L13/085 Inspection B,C,D & TBO extended Bulkhead 13 cracking Change in Type certificate owner Reference information SB L13/059 modifications Inspection of 2,3 & 4 types extended Change in Type certificate owner SB L-23 009&010 SB L-23/038 IB L23/040b 10/92 06/00 12/01 Replace wing attachments & spar root pins at 1500 hours AD-1-024/98 06/98 FAA AD 78-23-14 SB L13/061 SB L13/062 AD-4-099/98, SB L13/082a AD-T-112/1999R1, SB L13/085a SB L13/092b BGA 012/03/2001 issue1 IB L13/094b TNS 08/83 & 06/84 10/84 06/86 08/88 04/93 06/94 02/76, 12/83 & 04/99 02/00 & 04/00 06/00 04/01 12/01 Super Blanik L-23 M M I Tail wheel & attachment TBO Extension Type certificate Solo L33 M Wings Page 2 BGA Compendium 01/02 MDM (Poland) Status Subject Detail Reference information TNS Introduction of safety clamp for trim spring Bevel gear inspections (used SZD parts) BO 15/00 BGA 018/05/2001 issue 2 10/00 06/01 Contact: MDM Fox M M Elevator trim Air brakes Page 1 BGA Compendium 01/02 Pilatus (Switzerland) Status Subject Detail Reference information TNS Contact: Dietmar Poll, EWMS Technomanagement Ltd, Newmatt 18, CH-1736 St Silvester, Switzerland. PILATUS B4 M M M M M M M M R Canopy catch Crotch strap Aileron Control systems Seat latch pins fouling Gear down lock cracks Rudder cables Elevator drive rods Airbrake system Drag spar pin improperly engaged Drag spar bushes Fin to fuselage joint corrosion Tailplane Page 1 BGA Compendium 01/02 fit limiting cable SB 1001 fouls rudder cables SB 1002 bell crank pin fouling SB 1003 lubrication SL 101 serial numbers 1→140 SL 102 fit thicker locking plate escape from keyholes guides - wire or tape around guides rivets loose in fittings fit stops & check rivets for looseness SB 1004 inspect & modify if necessary to be secured may fall out of de-rigged gliders inspect for paint cracks Tailplane mounting inspection following H/Landing, Ground loop Or severe turbulance BGA 018/05/2001 issue 2 07/76 12/76 12/85 04/86 08/88 10/75 & 10/90 04/96 06/01 PZL (Poland) Status Subject Contact: And Detail Reference information TNS Alstar PZL Glider, U1. Cieszynska 325, 43-300 Bielesko-Biala, Poland. Fax +48 33 8123739 Jerzy Biskup, Glider Service, 43-316 Bielsko-Biala, ul. Bociana 13, Poland. +48 33 8662080 Bocian SZD-9bis-1D & 1E M Main wheel seizure lubricate Centre section steel tube structure cracks at welds – inspect Elevator rod fork end fatigue failure caused by bending. Adjust inspect/ replace with steel as necessary Air brake cables frayed in centre section Rudder hinges cracks & failures aggravated by incorrect adjustment of stops Rudder hinge (lower) fractured modification recommended Rudder systems failures below floor, cables, pulleys & pulley bearings Spar boom spanwise cracks in depth inspections required after suspect overloading Spar root inspection cracks & corroded & undersized bolts Elevator horn attachment rivets sheared inspect frequently Frame forward of fin cracks at elevator drive mounting Wing/fuselage fittings crack check /repair scheme Wing/fuselage fittings allowable repairs Tailplane support structure cracks Rudder pedal mounting (front) cracks/failure of front bracket near pivot holes Rudder pedals (rear) bent pedal fouls floor & restricts travel Air brake handle fractured below the slide Winch tow hook - attachments structural failure - reinforce/repair Cable releases dual pulley assembly cracked Undercarriage failures damaged components Undercarriage failures cracks around wheel-box Air brakes - stop over-ridden drive failure at paddle - rod end cracked Extension of life above 3000 hours after inspections Aileron operating horn (centre) detached from aileron spar Control cable recommended lives hemp core - 1000 hrs/ 6 yr. steel core - 1500 hrs/ 12 yr. Page 1 BGA Compendium 01/02 SB BE 016-79 SB BE 020-86 SB BE 027-86 SB 007/94 09/73 06/80 & 10/79 12/79 04/80 12/79, 06/80 & 12/80 09/81 03/75 & 02/84 04/84 08/84 & 06/84 06/84 08/87 10/79 12/87 04/88 03/82 & 10/88 12/88 02/91 02/87 & 12/91 02/92 09/81 & 02/92 08/95 & 10/95 10/89 & 04/92 10/92 06/93 10/94 PZL (Poland) Status Subject Air brakes - pilots lever M Trim cable failure at tab I Canopy Detail failure adjacent to front seat install swivel to prevent cable fatigue Rear canopy unlatched in flight Foka (SZD-24) Wing failure (USA) inspection of glued joint Heavy landings may displace elevator lever in centre section Control cable recommended lives hemp core - 1000 hrs/ 6 yr. steel core - 1500 hrs/ 12 yr. Reference information TNS 02/91 & 04/95 04/89, 04/97 & 12/98 04/01 SB 007/94 01/75 09/81 10/94 SB 007/94 08/76 02/77 08/79 08/79 04/80 10/94 SB 29/KR03A/93 04/94 SB 007/94 BE-35 KR-03A/99 10/94 08/99 Cobra Rudder cables pulleys Rudder cables Rudder cables pulleys Tailplane attachment Wheel hub cracked at bolt-holes Control cable recommended lives seized in rear fus. leads to cable wear and failure failure/corroded foul instrument panel thread stripped repair with “Helicoil” inserts repair by TIG welding hemp core - 1000 hrs/ 6 yr. steel core - 1500 hrs/ 12 yr. Puchatek KR-03A M M Tailplane Replacement of tailplane fittings Control cable recommended lives hemp core - 1000 hrs/ 6 yr. steel core - 1500 hrs/ 12 yr. Fatigue life/flying time Limited to 5000 hours Pirat (SZD 30) M M M M Elevator hinges Rear fuselage Rear fuselage Aileron hinges Seat back Page 2 BGA Compendium 01/02 inspect/replace cracks at inspection panel reinforce at fin joint replace centre hinges insecure SB 006 & 007/73 SB 009/73 SB 011/73 SB 012/74 10/74 PZL (Poland) Status Subject Trim cable Control rod ends Tow release cable Tailplane Rudder cables M Rudder lower hinge M Control cable Air brakes M Tow release jammed Main wheel hub plates Life extension M Rudder deflections Aileron operating horns Rudder cables jamming Control cable recommended lives Glued joints Aileron connecting rod in c/s Detail failure at tab loose and swaging cracked - leading to failure frayed at Bowden outlet cracks in spar end and at fin slot repeated failures stiff nut missing contaminated with glue bell crank bracket & fork end failures in centre section loose ferrule fouls on pulley - secure ferrule cracked at bolt holes to 3 200 hrs & flight restrictions beyond 2 600 hrs extended rudder loose at frame, pulley & guards displaced hemp core - 1000 hrs/ 6 yr. steel core - 1500 hrs/ 12 yr. inspection of wing centre section broken at end of thread during rigging or de-rigging Reference information SB 030/90 SB 032/92 SB 007/94 SB-033/93 TNS 06/75 06/91 & 10/75 04/76 12/76 06/77 07/77 12/80 06/79 & 03/82 04/83 06/84 10/91 10/92 06/93 12/93 10/94 04/94, 06/91, 01/93, 12/93 08/97 Jantar- all models also see separate sections M M M M U/C fails to lock down Seat back Rudder cables Push rod roller guides Wing to fuselage connection Trim spring Push rods Push rods Aileron actuator bushes Flying controls Page 3 BGA Compendium 01/02 prevent pushrod guide tube in cockpit rotating insecure with neg. G - secure it corroded in conduits - inspect rollers’ brass bearings fail – inspect compensation for free play fouls on floor wear on guide rollers splitting at end fitting swages - inspect corroded - system friction increased Inspection of NYLON air brake gears (identified by ball type self connecting wing controls) SB 027/86 SB 032/87 SB 063/88 SB 043/92 BGA 017/04/2001 iss2 06/77 12/85 12/86 08/87 04/88 1988 10/92 08/94 10/97 06/01 PZL (Poland) Status Subject Detail Jantar- all “T” tailed models Also see separate sections M Lower rudder hinge Lower rudder hinge Tailplane centre rib Elevator travel Elevator bellcrank Reference information wooden supports come loose – inspect split pin failed - inspect/replace inspect for looseness restricted by bellcrank foul in fin in base of fin corroded – inspect TNS 02/87 & 06/77 02/90 & 03/81 03/81 04/88 04/91 Jantar 1 (SZD- 38A) M Flap lever Spar root Flap plywood pushrod supports Main spar spigots Life extension Control cable recommended lives cracks adjacent to drive point strengthening come loose - inspect frequently for asymmetric flap replace at 1500 hours to 4500 hours after spigot replacement hemp core - 1000 hrs/ 6 yr. steel core - 1500 hrs/ 12 yr. SB 032/87 SB 036/89 SB 007/94 06/77 07/77 01/78 06/94 & 04/88 02/90 & 06/94 10/94 SB 030/87 SB 031/87 SB 007/94 04/88 02/90 10/94 SB 04/76 Jantar 2 & 2B (SZD- 42-1 & 2) Nose ballast weights inspect mounting Extension of life from 1500 to 3000 hours after wing spigot replacement Control cable recommended lives hemp core - 1000 hrs/ 6 yr. steel core - 1500 hrs/ 12 yr. Standard Jantar 1 (SZD 41A) M Extension of life from 3000 to 6000 hours after wing spigot replacement Procedure for changing spar spigots Control cable recommended lives hemp core - 1000 hrs/ 6 yr. steel core - 1500 hrs/ 12 yr. Standard Jantar 2 (SZD 48 & 48/1) Page 4 BGA Compendium 01/02 SB 026/86 SB 037/89, SB 044/93 SB 007/94 08/86 02/94, 02/90 & 10/93 10/94 PZL (Poland) Status M M M Subject Detail Rudder deflection 29°±1°(was 30°±2°) rudder/fin overlap to be 5mm min Extension of life from 3 000 to 6 000 hours after wing spigot replacement Extension of life serial numbers 1266 & 1268 Procedure for changing spar spigots Control cable recommended lives hemp core - 1000 hrs/ 6 yr. steel core - 1500 hrs/ 12 yr. Air brake Air brake drive gear mounting part detached in wing Reference information SB 01/78 SB 026/86 SB 035/88 SB 037/89 SB 007/94 TNS 01/79 08/86 02/90 02/94 10/94 06/00 SB 026/86 SB 042/92 SB 007/94 08/86 10/92 10/94 Standard Jantar 3 (SZD 48/3) M Extension of life from 1500 to 3000 hours Weighing data C of G position v empty weight chart Control cable recommended lives hemp core - 1000 hrs/ 6 yr. steel core - 1500 hrs/ 12 yr. Ogar (SZD 45) M M M M M M Air brake levers cracked GRP fuel tank Elevators stiff Lower air brake paddle severed Control cable recommended lives Propeller Carburettor membrane Tail wheel Muffler Life extension inspect airbrake system regularly check bonding every 50 hours corrosion on torque tube inspect & adjust system as per manual hemp core - 1000 hrs/ 6 yr. steel core - 1500 hrs/ 12 yr. TBO of propeller hub Compliance with Limbach SB Replacement of fittings Inspection of brackets Inspections to extend service life CAA AD-0837/PRE/78 SB 007/94 BE–014/78 BE- 020/80 BE-021/80 BE-024/84 BE/R-026/96 09/85 06/83 02/87 02/88 10/94 04/00 04/00 04/00 04/00 04/00 Puchacz (SZD 50/1 & 3) M M M Controls jammed below front seat Wheel hub bolts Life extension to 6000 hours Rudder hinge (top) failure Main wing pin Page 5 BGA Compendium 01/02 (by foreign objects) guard introduced replace in steel inspections from 1000 hours onwards annual inspection security SB-10/50/3/83 SB-32/50/03/86 SB-34/50/03/87 SB-33/50/03/87 10/83 12/86 04/88 06/88 10/88 PZL (Poland) Status M M M M M M M M M M M M R Subject Tailplane pin Pulley in trim circuit Rudder cable Rear canopy lanyard Rear tow release Rudder cable system Rudder cable fatigue failure Canopy jettison pins - migrate Asymmetric air brakes Flying controls Trim drive cables (solid wire) Undercarriage bungees Rear rudder pedals cable detached Air brakes Control rod ends Control cable recommended lives Air brakes Air brake paddle Ailerons Airbrake operating lever Lower rudder hinge Wing Control sticks Canopy Wing Flying controls Airbrakes Detail Reference information replace SB-40/50/03/90 secure T-50 pulley SB-38/50/03/90 fouls radio junction box fouls rear stick jammed by perished rubber sleeve mod to eliminate possible jam SB-42/50-3/92 at rudder pedal - modify system lock into place gearbox failure incorrectly rigged on delivery failures deterioration - inspect stiff-nuts come off - fit split pins & castellated nuts paddle attachments worn- circlips missing swaging cracked hemp core - 1000 hrs/ 6 yr. steel core - 1500 hrs/ 12 yr. SB 007/94 failure at cross tube in fuselage axis bolts unsecured SB-047/50 jammed after heavy landing nose wheel frame broken - inspect weld failures - inspect plywood support failed - check every DI Inspection of wing front bracket console SP-0059-2000-A BE-048/SZD-50-3/2000 Inspection of control sticks for cracking BGA 002/07/2000 Iss 1 Inspection of fwd canopy locking lever BGA 005/08/2000 Iss 1 Action to take if cracks found in front bracket console SP-0094-2000A, BE-049/SZD-50-3/2000 Inspection of airbrake gears BGA 016/04/2001 iss1 Airbrake control inspection BGA 024/10/2001 iss1 TNS 06/90 06/90 12/91 12/91 04/92 10/92 06/93 01/93 & 10/92 12/92 01/93 10/93 12/93 12/93 08/94 08/94 10/94 04/95 03/94 10/96 12/96 08/99 08/00 08/00 08/00 12/00 04/01 10/01 Junior (SZD 51/1) M Modifications required for BGA certification Page 6 BGA Compendium 01/02 10/86 PZL (Poland) Status M M M M M M M M R M Subject Aileron mass balance Air brake lever push rod fails Rudder mass balance weight Lower rudder hinge Lower rudder hinge mounting Elevator drive locking sleeve Aileron mass balance Canopy jettison pin Elevator trim spring Tailplane fixing sleeve Swaged control rod ends Control cable recommended lives Airbrake bevel gears cracked Life extension Air brake Flying controls Flying controls Canopy Elevator trim Detail introduced to prevent flutter fit strengthened rod fouls screw head - modify system replace at 1000 hours or if damaged cracks in fin structure always check fully engagement after rigging corroded bolts - replace with stainless steel migrates - secure with soft copper wire several failures replacement cracked hemp core - 1000 hrs/ 6 yr. steel core - 1500 hrs/ 12 yr. inspect after ground loops from 1000 hours to 3000 hours after inspections Airbrake lever failure below handle Rudder pedal adjustment inspection Inspection of air brake gears latch inspection and modification Trim control knob inspection Reference information SB 002/85 SB 003/85 SB 004/88 SB 006/90 BGA 014/03/2001 iss1 BGA 017/04/2001 iss2 BGA 020/10/2001 iss1 BGA 023/10/2001 iss1 TNS 12/86 12/86 12/88 06/90 06/98 08/91 04/91 06/93 10/93 04/94 08/94 10/94 08/97 06/98 04/00 04/01 06/01 10/01 10/01 Revision of rudder deflections SB 6-55-1/92 SB 7-55-1/94 SB 007/94 SB 8-55-1/95 10/92 10/94 10/94 10/95 BGA 017/04/2001 iss1 04/01 SB 009/93 SB 007/94 SB 005/89 SZD - 55/1 M M M M Controls Revision of flight manual Control cable recommended lives Revision of flight manual Flying controls Page 7 BGA Compendium 01/02 hemp core - 1000 hrs/ 6 yr. steel core - 1500 hrs/ 12 yr. ASI with stall warning and life to 3000 hours Inspection of NYLON air brake gears (Identified by ball type self connecting wing controls) PZL Swindnik (Poland) Status Subject Detail Reference information TNS 6/PW-5/97 7/PW-5/97 6/PW-5/97/1 8/PW-5/97 9/PW-5/97 TSP1/079/2000 BS-17-00-13 10/97 10/97 02/98 02/98 04/98 08/00 08/00 02/01 06/01 Contact: UK agents - Joint Aviation Services Tel 01420 88664 PW5 Smyk M M M M M I I Canopy frame Canopy jettison system Errors corrected in previous SBs Canopy lock handles Maintenance manual revisions 1000 Hr inspection Total pressure Seats Ballast Page 1 BGA Compendium 01/02 check shape install new system replacement Reminder to report findings Installation of total pressure and K-1 probe Seat back peg jumped out of location during winch launch Special ballast installation BI-17-00-12 Rollanden-Schneider (Germany) Status Subject Detail Reference information TNS Contact: UK Agent Martyn Wells 01608 684217 LBA Airworthiness Directives LS-1 M M M M M M M M M M M M Ailerons Flight manual Wings Ailerons TP fitted upside-down Trim Release cable corrosion in conduit Inspection hole cover Rudder hinge washer not located Rudder/elevator/aileron bearings Elevator flutter prevention Trim spring failure Bonding lead to hook Elevator flutter Loose wing root rib pins Bent aileron push rod L’Hotellier connectors Improved venting Winch amendment Attachment bolts Clearance inspection modify to make this impossible Wear of guide rod inspect & replace if corroded Inspection rudder becomes disengaged inspect for missing washers replace spring at lever damage by u/c reposition if necessary backlash tolerance, Flight Manual inspection jammed in root rib (USA) annual inspections M Increase in service life to 12 000 hours M AD 71-45, TM 2 AD 72-138, TM 15 AD 74-70, TM 20 AD 74-96 AD 77-155 AD 78-162, TB 34 AD 78-163, TN 35 AD 78-290, TB36 AD 78-203 AD 79-44 AD 79-109, TB 38 AD 81-112, TB 41 AD 93-001/3, TB 56 & AD 93-155, TB 52 AD 1982-184/2, TB 40A 07/77 09/78 01/79 03/79 06/80 08/80 07/81 04/84 06/88 12/90 08/98 & 04/93 10/93 02/00 LS-3, 3a & 3-17 M M M Flight manual Revision Release cable corrosion in conduit inspect & replace if corroded Elevator flutter prevention replace spring Page 1 BGA Compendium 01/02 AD 77-257, TM 3002-1 AD 78-163, TN 3007 AD 79-109, TB 3013 09/78 06/80 Rollanden-Schneider (Germany) Status Subject Trim spring failure Canopy jettison M Bonding lead to hook M Flight & MM M Trim weight M Wheel brake lever on hub M Upper airbrake paddle Wing root pins become loose M Life increase M L’Hotellier connectors M Nose weight mounting bracket M Front elevator mounting bracket M Landing gear system nuts M Air brake drive at wing root M Flap Drive Springs M Air brakes M manual amendment O Tow hook Detail inspect annually jammed by long instruments damage by u/c reposition if necessary Amendments Attachment crack inspection reposition may foul control rod bolt file clearance if necessary inspect and repair if necessary from 3 000 to 6000 hrs inspections required annual inspections replace with new version new part number 4R8-19C not secure in fin tighten to correct torque replace 6 mm studs with 8 mm replace Requires action to prevent jamming air brakes. Flight and MM amendments Additional nose hook installation Reference information AD 81-112, TB 3026 AD 82-215, TB 3029 AD 82-214, TB 3033 AD 83-118, TB 3036 AD 88-81, TB 3038 AD 93-001/3,AD 93-155, TB 3042 AD 93-083, TB 3040 AD 93-155, TB 3043 AD 93-157, TB 3045 AD 93-156, TB 3044 AD 95-410 AD 2000-085, TB3051 AD 2001-331, TB3050 TB3052 TNS 08/80 05/81 07/81 08/83 12/86 06/88 08/88 08/98, 04/93 &10/93 04/93 &06/93 10/93 10/93 10/93 12/95 04/00 10/01 10/01 LS-4 & 4a M M M Bonding lead to hook damage by u/c drive reposition if necessary Air brakes won’t retract above 108 Kts enlarge cut-out in top blade Trim weight Attachment crack inspection AD 81-112, TB 4004 AD 81-113, TB 4005 AD 82-214, TB 4010 07/81 07/81 M Possible jamming of airbrakes fit open stop in cockpit Seat adjusting cable collet may foul airbrake lever bend seat support tube as necessary Wheel brake lever on hub reposition Wing root pins become loose inspect and repair if necessary Tost G88 (C of G) and E85 (nose) hooks introduction Nose weight mounting bracket replace with new version new part number 4R8-19C L’Hotellier connectors annual inspections AD 83-158, TB 4020 04/85 12/82 08/83 06/88 02/90 04/93 & 06/93 04/93 M M M M Page 2 BGA Compendium 01/02 AD 83-118, TB 4019 TB 4030 AD 93-083, TB 4033 AD 93-001 Rollanden-Schneider (Germany) Status M M M M M M M M Subject Detail Flight Manual (LS-6C) speed amendments Landing gear system nuts tighten to correct torque Front elevator mounting bracket not secure in fin Airbrakes jamming (LS-6C) trim brake cap Extension of service life to 12 000 hours inspections after 3000 hours U/C gas strut load 12-15 Kg at U/C joint Rudder pedal/canopy support structure cracks in fore & aft square tube Airbrake operating levers in fuselage cracks in over-centre push-rods Air brakes Requires action to prevent jamming air brakes. Reference information AD 87-254/2, TB 4027a TNS 04/93 10/93 10/93 02/95 08/97 AD 1999-270, TB 4042 AD 2000-076, TB4043 04/99 08/99 04/00 AD 93-157, TB 4036 AD 93-155, TB 4035 LS-6, 6B& 6C M M M M M M M M M M O Air brake stops Hydraulic damper introduced U/C gas strut Weight and balance revised Upper rudder hinge Rudder pedal adjustment Lower rudder hinge L’Hotellier connectors Lower air brake paddle mount Air brakes Flight controls Service life Canopy jettison Tow hook interference between airbrake and flap controls (LS 6A) VNE restriction lifted replace with aluminium bar and trim position indicator fitted limit of radial play 0,5 mm cable jam inspect & modify as necessary retaining nut lose (LS6 & 6B only) annual inspections cracks Requires action to prevent jamming air brakes. Jamming of air brakes in extended position Extension of service time and MM revision Obstruction of emergency canopy jettison Additional nose hook installation Rudder pedal adjustment Aileron missrigging Canopy jettison cable jam inspect & modify as necessary enlarge fuselage cut-out Obstruction of emergency canopy jettison AD 89-60 AD 86-140, TB 6010, TB6011 TB 6012 TB 6015 TB 6017 AD 91-110, TB 6022 TB3051 AD2000-082, TB6037 AD2001-110, TB6035 AD1999-266/2, TB6036/2 TB6040 08/89 04/88 04/88 10/88 10/88 06/91 02/92 04/93 & 10/93 02/94 04/00 02/01 04/01 04/01 10/01 AD 91-110, TB 7003 AD 91-172, TB 7004 AD1999-267/2, TB7011/2 06/91 12/91 04/01 AD 93-001/3 & 155 LS-7 M M M Page 3 BGA Compendium 01/02 Rollanden-Schneider (Germany) Status Subject M Flight controls M Service life Detail Jamming of air brakes Extension at 3000 hrs Reference information AD 2000-083, TB 7013 AD 2002-043, TB 7015 Structural modifications during manufacture Wing tip modifications only if TB8001 complied with. Obstruction of emergency canopy jettison cable conduits loose in fin - secure by gluing Check for corrosion and jamming Water ballast drain tubes modification Flight and MM revisions English version available Correction – water tank filling sequence Increase of service life after inspections Accomplishment list (included in compendium) TB8001 TB8002 AD1999-268/2, TB8004/2 TNS 02/02 LS-8 O 0 M M M M I R M M LS8-18 LS8 to LS8-18 Canopy jettison Rudder travel restriction Wing Air brake levers Water ballast Manual revision Maintenance manual Flight manual Service life Airworthiness Directives Page 4 BGA Compendium 01/02 AD2000-084, TB8005 AD 2000-86, TB 8006/2 AD2000-067, TB8007 TB8008 TB8009 AD2001-200, TB8010 04/01 04/99 04/00 08/01 08/01 Scheibe (Germany) Status Subject Detail Reference information TNS TM 653-28/4 AD74-323 AD 69-142 10/98 Contact: Scheibe-Flugzeugbau GMBH, +49 8131 72083. UK Contact: Peter Serge-Fink 01293 873214 LBA and CAA Airworthiness Directives SF24 M M Flexible hose life Control cables Hirth F10 engine Inspection/replacement of cable sleeves Operational and maintenance instructions SF 25 series General I I I R I Horizontal Stabiliser Flutter SF-25/T-61 elevator tab cables wire lock at tab Longerons corroded at fin post adjacent to microballoon filler Wheel assembly bolt failures fit larger (8mm) bolts Unleaded MOGAS approval (Limbach L1700 & 2000) SF-25/T-61 compass errors magnetised canopy frame Spar deterioration water in spoiler boxes SF-25/T-61 wing main pin holes worn & splayed oval T-61 ignition switch “live” test Crank case cracks numerous cases - inspect regularly SF-25/T-61 tailplane front attachment cracked SF-25 fuel flow restriction filter incorrectly installed Top harness attachments secure to transverse tube Rear exhaust valve burning Limbach improved cooling kit Tubing on fuel gauges hardens and leaks T-61 magneto to crankshaft coupling failure of type without reinforcing ring SF-25 carb heat system introduced, mandatory (CAA) Fuel shut off valve NK 490 fitted in place of Truma V8M Flexible hose life I I R I I I I R R I I M M I Page 1 BGA Compendium 01/02 AD 1966-119 TN 653-66 TI 102 Mod 134 SB 653-70 TM 653-28/4 etc 06/73 01/75 11/77 12/96 12/79 06/95 & 12/80 12/80 12/85 02/87 04/90 06/90 01/93 01/93 06/95 06/96 08/87 02/98 10/98 Scheibe (Germany) Status I I I I Subject Rear fuselage structure corrosion Aileron drive bearing failure Tailplane front mount Throttle cable disconnected Detail near fin attachments central hanger upper bearing between sticks cracked through inspect for cracks and poor welds check security at carburettor connection Reference information TNS 02/99 04/99 08/99 10/99 LBA Airworthiness Directives listed in CAA Foreign Airworthiness Directives Vol. III. M M M M M M M M M M M M M M M M M M M M Engine mounting (Stamo) Luggage compartment Carburettor heater Ignition Switch Cracks in lower mount bolts SF25B S/N 4601>46174. Securing of luggage S/N 4601 > Installation New type SF25B S/N 4601>46253 & 4801 >4828 SF25C S/N 4401>4448 Ailerons Bellcrank replacement SF25A Flight control cables Inspection of cable sleeves Electrical system Installation of smoothing capacitor SF25B & C with Dittel radio FSG-12, -15 or –16 Aileron drive lever Inspection / reinforcement SF25B & SF25C Fuel Quantity indication Incorrect indication SF25B S/N 4601>46258 & 4801>4868 SF25C S/N 4401>44133 & 4201>4252. Fuel filler Inspection SF25A all & SF25B S/N 4601>4645 Elevator support Inspection SF25B S/N 4801>4868 & SF25C S/N 4201>4255 Stabiliser/Tailplane Fwd Armature Inspection SF25A,B,C,D,E & K Fuel SOV Life limitation SF25B,C,D,E & K Wing Main wing joint SF25B,C,D & E Flight controls Bearings in control stick SF25C,E & K Flight controls Inspection of airbrake pulley SF25A,B,C,D,E & K. Working instruction 653-62-142/770-18-142 Fuel SOV TRUMA V8 valves Flight Controls Cracks in aileron steel pipe spar SF25B & C Wing centre pin Inspection Wing centre joint Additional limitations Page 2 BGA Compendium 01/02 AD 71-131, TB 2/71, Mod 120 AD 72-107, Mod 132 AD 73-15, Mod 133 AD 73-23, Mod 4 & 134 AD 74-54 AD 74-323 AD 75-91 AD 75-169, TI 653-5/75 04/76 AD 76-40, TN 653-1/76 AD 76-297, TN 653-6/76 AD 77-217, Sportavia TMS-02-77 AD 82-049, TN 653-40 AD 82-50/2, TN 653-41 AD 82-134/2 AD 1984-198/2, TN 653-47 04/76 02/90 09/82 02/85 & 04/00 AD 94-261, SB 653-62/770-18 AD 97-140, SB 653-67 AD 1999-340, SB 653-73 CAA AD 003-06-82 CAA AD 001-07-82, TI 103/T61 10/94 08/97 & 02/98 02/00 04/95 07/82 09/77 Scheibe (Germany) Status Subject SF-26A M M Spar deterioration Top rudder hinge Control cables Flying Controls Detail water penetration cracks/failure Inspection/replacement of cable sleeves Inspection of aileron bellcrank for cracks Reference information TNS 10/74 08/79 AD74-323 AD75-270, TN 232-1/75 SF-27A & M M M Elevator actuating lever Elevator torque tube Top rudder hinge Flexible hose life Control cables cracks at weld reinforce at weld cracked Inspection/replacement of cable sleeves TN 257 AD 75-48, TN 257-1/74 TM 653-28/4 etc AD74-323 01/74 06/75 02/92 10/98 SF-28A Tandem Falke M M Main wing pin Flight controls M M M M Unleaded MOGAS approval Fuel shut off valve Truma V8M Fuel shut off valve NK 490 Flexible hose life Elevator/aileron drive cracks Control cables Flying controls Electrical system M M Wing centre pin Wing centre joint M Page 3 BGA Compendium 01/02 correct locking Inspection of airbrake pulley Working instruction 653-62-142/770-18-142 (Limbach L1700 & 2000) 8 year (seals) life limitation fitted in place of Truma V8M reinforce before next flight Inspection/replacement of cable sleeves Inspection of rear control stick Installation of smoothing capacitor with Dittel radio FSG-12, -15 or –16 Inspection Additional limitations LTO 345 & 508, AD 82-135 12/80 & 04/95 AD 94-261, SB 653-62/770-18 TN 770-19 AD 97-140, SB 770-20 AD82-51/2, SB 770-13/2 TM 653-28/4 etc AD 1998-435, SB 770-23 AD74-323 AD81-237, TN770-12 AD 75-91 CAA AD 003-06-82 CAA AD 001-07-82, TI 103/T61 12/96 08/97 02/98 10/98 12/98 Scheibe (Germany) Status Subject Detail Reference information SF-34 M Wing root rib modification SF34 & 34B S/N 5102>5131 AD 89-73, TN 336-2(supersedes AD 88-162/2) M Spin recovery improved Aft C of G limit 2367 mm AD 96-241, TN 336-8 Rear fuselage frame disbonded inspect for bond failure (causes fin/TP flutter) M Fuselage inspection (SF34, SF34B) Inspection of aft fuselage and flight restrictions BGA 001/05/2000 iss1 M Fuselage inspection Inspection of aft fuselage and lifting of LBA flight restrictions (BGA restrictions remain) AD 2000-299, SB 336-9 M Control cables Inspection/replacement of cable sleeves AD74-323 M Flight controls Rear control stick inspection AD 2002-044, TB 336-10 MÜ-13E Bergfalke (1) M Spar deterioration reduction of span M CG hook mounting cracks caused by loose bolts M Elevator & airbrake connection “bolts” replace with new “bolts” in aircraft material M Control cables Inspection/replacement of cable sleeves AD 75-42 AD 79-501, TN 104-15 TN 104-18 AD74-323 Bergfalke II, II-55, III and IV CG hook mounting (Berg III only) cracks caused by loose bolts TN 104-2/76 M CG hook mounting (all) cracks caused by loose bolts AD 79-501, TN 104-15 Spar deterioration water in brake box M Main wing pin not fully through lower spar lugs, safety pin hole too low down TN 104-17 M Elevator & airbrake connection “bolts” replace with new “bolts” in aircraft material TN 104-18 Tailplane at front attachment damaged by water - inspect in depth Speed brake lever in centre section cracked – reinforce M Control cables Inspection/replacement of cable sleeves AD74-323 TNS 10/89 ??/96 08/98 08/00 10/00 02/02 04/75 02/80 08/85 02/77 02/80 05/79 02/85 08/85 08/86 10/89 Zugvogel III A & B M Elevator hinge pin Control cables Page 4 BGA Compendium 01/02 sheared at the weld Inspection/replacement of cable sleeves 06/92 AD74-323 Schempp-Hirth (Germany) Status Subject Detail Reference information TNS Contact: UK agents Southern Sailplanes: 01488 71774 LBA Airworthiness Directives Open Cirrus & VTC Cirrus Askubal fittings Rudder cable Undercarriage collapse M Flutter prevention (elevator) M Flutter prevention (rudder) Rudder springs Cracks in fuselage centre section M Air brake rod end failure Flight manual changes Rudder cables M Airbrake control ball joints M L’Hotellier connectors Extension of service M Extension of service life inspection tension inadequate may escape from uncaged pulleys cable stretches & escapes from uncaged pulleys fit solid drive bar & new mass balance limits increase mass balance tension inadequate causes cables to come off rollers in nose airbrake drive “turntable” support tubes replace 6 mm threads with 8 mm C of G position & loading plan failure at rudder pedal pulleys replace with improved type add safety pins and annual inspections to 6 000 hours from 3000 hours to 12000 hours after inspections AD 69-136, TN 1/69 AD 82-103, TN 265-6 AD 82-103, TN 265-6 AD 85-56, TN 265-8 TN 265-7 AD 93-013, TN 265-10 AD 93-001& AD 94-001 AD 86-15, TN 265-9 AD 1998-251, TN 265-9 Std Cirrus including Grob & VTC manufacture M Aileron rod in centre section LH rod jams if disconnected add “catcher” bar AD 76-8, TN 278-17 M Seat pan fouls tow release reinforce seat pan AD 76-7 , TN 278-18 M Cirrus (B&G) flight manual amendments weights & limitations changed TN 278-30 Canopy lock roll pin sheared M Airbrake drive ball joints replace with improved type change every 500 hours AD 79-051/4, TN 278-23 M L’Hotellier connectors add safety pins and annual inspections AD 93-001& AD 94-001 M Tailplane drive lower bearing outer race broken - change bearing type AD 80-243TN 278-25 M Tailplane ‘T’ fitting cracks at welded joint of pins inspect every 300 hours AD 80-244/2, TN 278-26 Wing attachment spherical bearings break up - fit improved type if necessary Rudder mass balance unbonded from rudder Elevator drive horizontal push rod bent and failure in base of fin after incorrect repairs Page 1 BGA Compendium 01/02 03/84, 10/83 & 10/73 12/80 & 07/77 08/82 11/82 04/84 04/84 04/85 06/85 12/91 01/93 04/93 & 04/94 06/98 04/76 04/76 09/77 09/77 12/96 04/93 & 04/94 12/80 12/80 & 10/92 05/82 08/88 02/91 Schempp-Hirth (Germany) Status Subject M Elevator vertical drive rod in fin Tailplane drive M Tailplane lock M In board aileron hinge Extension of service life from Tow release Detail Reference information replace (G models only) AD 92-360/2, TN 278-33 incorrect rigging of tailplane hook not around roller bearing inspect & modify if necessary serial numbers 573,586,593,595,597,598,599,601→ AD 95-015, TN 278-36 fractured at weld 3 000 to 12 000 hours after inspections AD 81-099/2, TN 278-28 Fitment of nose tow release mech. TN 278-37 Discus series Tow hook may be replaced with Europa G 88 M Static vents improved version eliminates water ingress M Elevator vertical drive rod replace up to nos. 446 (a&b), 98 (CS) up to serial number 100 (bT) M Extension of service life from 6 000 to 12 000 hours after inspections M Discus BT service life from 6 000 to 12 000 hours after inspections M Engine mounting cracked. M Aileron drive jammed below seat bellcrank bolt fouls on structure Ailerons jammed miss-assembled bolts foul in fus at auto-connect Rudder drain holes check that they are clear M Engine mount Inspection of engine mount structure Tow release Fitment of nose tow release mech. I Canopy Opened in flight due to loss of friction in catches O Wings Wing tip with winglets, S/N 1>12 O Wings Wing tip with winglets, S/N 13>97 M Landing gear Inspection and modification of landing gear TN 360-7 TN 360-8 AD 92-360/2, TN 360-9 AD 92-360/2, TN 863-3 AD 94-031, TN 360-11 AD 1999-305 AD 2000-074 AD 2000-074, TN 863-6 TN 360-37 TN360-15 TN360-16 AD2001-259, TN360-17 TNS 04/93 10/93 02/95 04/95 02/96 06/00 02/92 02/92 04/93 04/93 04/94 10/99 12/94 10/96 06/97 & 08/97 04/98 06/00 06/00 02/01 04/01 04/01 10/01 Janus A, B, C, Ce, CM & CT M M M Elevator drive may be damaged Elevator drive bracket Life extension from Elevator vertical drive rod replace Page 2 BGA Compendium 01/02 by persons standing on the control (B model only) modify or replace 3 000 to 12 000 hours after inspections (not “A” model) up to serial no. 284 AD 87-126/3, TN 295-19 AD 81-98/2,AD 86-274/2, TN 295-16 AD 92-360/2, TN 295-22 09/81 10/87 10/91 04/93 Schempp-Hirth (Germany) Status Subject Detail M L’Hotellier connectors add safety pins and annual inspections M Tailplane lock - inspection modify if necessary Tailplane attachment fittings on fin inspect for cracks M Flutter (adj. rear pedals model) (C only) VNE 108 Kts until modified M Flying controls (CM only) Elevator control system Undercarriage lever failed (C only) at weld at the drive rod tube M Elevator flutter - VNE 86 Kts (C only) until mass balance is fitted M Fuel system modification (CM & CT only) pipe pumps in parallel M Failure of propeller support strut (CM & CT only) inspection & replacement M Changes in engine accessories (CM & CT only) and changes in placards Improved propeller (optional) (CM & CT only) Hoffman HO-IIH-HM-158-BI27 Ignition and generator coils (CM only) fixings and starter gear cracks Engine mounting plate (CM & CT only) cracked M Elevator vertical drive rod replace up to serial number 36 (CM) up to serial number 19 (CT) Starter motor mounting (CM & CT only) failed Flight manual changes min seat loads (CM) M Extension of service life from (CM & CT only) 6 000 to 12 000 hours after inspections M Elevator flutter - VNE 86 Kts (CM & CT only) until mass balance is fitted Reference information AD 93-001/3, AD 94-001 AD 95-015, TN 295-26 AD 90-335, TN-295-21 AD90-335, TN809-8 AD 1999-265, TN-295-27 AD 86-135, TN 809-3 AD 85-164, TN 809-1 TN 809-4 TN 809-6 Rotax TB 535-5 AD 92-360/2, TN 809-9, TN 847-4 AD 92-360/2, TN 809-9, TN 847-4 TN 809-13 AD 1999-028, TN 809-14 AD 1999-265, TN 295-27, TN-809-15 TNS 04/93 & 04/94 02/95 10/96 02/91 & 04/93 10/93 08/99 & 10/99 10/86 12/86 & 06/97 04/87 10/88 08/89 06/91 04/93 04/93 02/95 06/98 04/99 08/99 Nimbus - 2, 2B, 2C, 2CS & 2M M M M M M M M Tail end flutter increase rudder mass balance Gross weight & speed increases (2B) 580 Kg max AUW, 250 Kg max non lifting Brake parachute lever to be gated & shroud taped to avoid bottom rudder hinge C of G tow hook replace S 72 hook with G 72 C of G tow hook G 72 may be replaced with Europa G 88 Flap - excessive backlash caused by corrosion from ballast tank leaks Cracks in ‘U’ bracket on tailplane (2B only) modify or replace Trim spring system failure (2C) sheared bolt at the gate Elevator vertical drive rod replacement (B &C models only) Extension of service life to 12 000 hours, inspections after 3 000 hours and before 1 May 1994 Page 3 BGA Compendium 01/02 TN 286-8, TN 286-22 TN 286-14 TN 286-26 06/75 02/76 & 12/86 01/78 12/80 02/92 11/82 AD 87-126/3, TN 286-24 AD 92-360/2, TN 286-28 AD 86-036/2, TN 286-22 12/91 04/93 04/94 Schempp-Hirth (Germany) Status Subject M L’Hotellier connectors Aileron rod end disconnected M Tailplane lock M Tailplane lock Detail add safety pins and annual inspections not locked at outer aileron (2B&C)Nos 86, 93, 96 → inspect & modify if necessary (2M) Nos 4→7 inspect & modify if necessary Reference information AD 93-001& AD 94-001 fixings and starter gear cracks (3DM) GRP blocks unglued (3T & 3DT) frayed replacement 3 - all 3T – all 3D - up to serial number 11 3DT - up to serial number 35 3DM - up to serial number 24 add safety pins and annual inspections special safety pins cracks in support structure Extension inspection Rotax TB 535-5 AD 95-015, TN 286-33 AD 95-015, TN 798-3 TNS 04/93 & 04/94 10/94 02/95 02/95 Nimbus- 3, 3D, 3DM, 3DT & 3T M M M Ignition and generator coils Fuel tank support structure Decompression cable Elevator vertical drive rod L’Hotellier connectors L’Hotellier connectors Front control column Service life AD 92-360/2, TN 286-28 AD 92-360/2, TN 831AD 92-360/2, TN 373-5 AD 92-360/2, TN 847-4 AD 92-360/2, TN 847-4 AD 93-001& AD 94-001 AD 2000-095, TN 874-8 AD 2000-075,TN 373-8 08/89 08/90 06/91 04/93 04/93 04/93 04/93 04/93 04/93 & 04/94 06/93 02/95 04/00 Nimbus- 4, 4D, 4DM, 4DT & 4T M R Engine Canopy Inspections & Modifications to SOLO engine Locking mechanism modification AD 1999-392, TN 868-9 TN 868-3 TN 868-4 BGA require anti-balance tab on this configuration fouled by brake arm fit new brake arm 3000 hours to 6000 hours after inspections (15B only) modify or replace TN 328-5 TN 328-7 AD 87-126/3, TN 328-8 02/00 & 06/00 12/01 Nimbus 15, 15B & 15C (Mini Nimbus) M M M All moving tailplane Landing gear Extension of service life from Cracks in ‘U’ bracket on tailplane Page 4 BGA Compendium 01/02 06/80 04/86 08/87 Schempp-Hirth (Germany) Status M M M Subject Release hook Elevator vertical drive rod Tailplane lock Potential control system fault Detail jammed by metal shroud replace (B & C models only) inspect & modify if necessary incorrect assembly of bolts in levers Reference information AD 92-360, TN 328-10 AD 95-015, TN 328-11 TNS 06/87 01/93 02/95 06/95 SHK & Standard Austria M M Elevator push-pull rod Elevator push-pull rod Tow release cable Fuselage Rudder controls Rear fuselage bulkhead Rudder/elevator assembly Pitch & yaw controls Restricted aileron control Rudder cables Rudder control lost Replacement of M6 castle nut Redsigned unit corroded glued joints mod to pulleys strengthen attachment loose on rear fuselage & struts cracked incorrectly rigged after repair from 123 mm to 65 mm - after damage repair worn at connection to mixer unit incorrectly assembled cable ends AD1/65 AD2/65 from 948 to 1157 lb after tow hook mount mod reinforce torque tube protection of pilot against injury jamming of brake cover strip foul stick replace up to serial number 568 6 000 to 12 000 hours after inspections 6 000 to 12 000 hours after inspections 6000 to 12000 hours after inspections Tension on SOLO engines Ferrite suppresser fouling aileron rod under seat Cracks in engine mount structure TN 349-7 AD 87-44, TN 349-9 AD 2-66 AD 67-001 AD 69-30, AD69-31, TN 9 08/87 08/90 08/92 06/93 06/99 Ventus a, b, bT, c, cM & cT M M M M M M M M M AUW increase Flap drive cracking at weld Fuel tank Air brakes Radio installations Elevator vertical drive rod Extension of service life Extension of service life from Service life increase (T & M) Drive belt GPS Suppresser Engine mount Page 5 BGA Compendium 01/02 AD 88-116, TN 825-10 AD 92-360/2, TN 349-28 AD 1999-001, TN 349-24 AD 1999-028, TN 349-14 AD 1999-304, TN 825-21 AD 1999-365 AD 2000-074, TN 825-23, TN 863-6 02/87 04/87 08/87 08/88 12/91 01/93 04/99 12/99 02/00 04/00 06/00 & 04/00 Schempp-Hirth (Germany) Status M I M R Subject Engine mount Canopy Flaps Tow hook Detail Attachment of fwd spindle drive and pylon Opened in flight due to loss of friction in catches Flap drive in fuselage modification retro fit of tow release mechanism Reference information AD 2000-342, TN 825-24 AD2001-258, TN349-9, TN825-29 TN 825-28 TNS 10/00 02/01 10/01 12/01 Ventus 2a, 2b, 2c, 2cT & 2cM M M I I O M M Flight & maintenance manual Flight & maintenance manual Modifications to SOLO engine Drive belt Canopy Noise certificate Fuel system Landing gear Propeller (SOLO engine) changes (2a, 2b & 2c) changes (2cT & 2cM) Tension on SOLO engines Opened in flight due to loss of friction in catches S/N 44 & 46>95 Fuel shut off valve and tank locking device Inspection and modification of landing gear Attachment of forward spindle bracket TN 349-23 TN 825-20 AD 1999-392, TN 825-27 AD 1999-365, TN 825-22 TN825-25 TN825-26 AD2001-259, TN349-25, TN825-27 AD2000-342, TN 825-24, Mod MB 825-27 06/98 06/98 02/00 02/00 02/01 04/01 04/01 12/01 Duo Discus M I R Undercarriage lever Canopy release Canopy Canopy Page 6 BGA Compendium 01/02 travel restricted handle rotated - loctite into place Failure of locking mech. At welded joint. Opened in flight due to loss of friction in catches Locking mechanism modification TN396-6 12/97 06/00 02/01 12/01 Schleicher (Germany) Status Subject Contact: UK Agent: - Peter Wells Detail Reference information TNS Tel 01844 201028 or 208157 Ka-2, 6, 7, 8, 13, 14, 18 - see also separate sections Wheel brake cables to be wire wiped at turnbuckle to prevent air brake restriction 10/66 M Control cables Inspection/replacement AD 74-323 Wings, damage by water/damp ply separation & spar damage 02/00, 10/83, 08/83 & 08/76 Rudder pedals (front) cracked and bent - clips broken 08/94 , 06/84 & 02/77 Rudder hinges (top & bottom) cracked 04/87, 02/84, 04/80 & 01/79 Rudder mounting brackets cracked 04/91 & 02/90 Lower rudder hinge mount cracked repair and reinforce with 2mm ply as necessary 06/97 M Rear stick comes out of mounting lock into place 04/83 Elevator drive (not Ka-6E & 14) check full engagement after repair 06/87 Rigging of ailerons both neutral with elevator neutral 08/87 M Elevators (not Ka-6E & 14) root rib glue failure, remove fabric to inspect every 3 years AD 72-7/2, TN 11, 21, 18, 23, 1, 12, 6. 12/89 & 02/90 Fin attachments (rear) damage by water and corroded 08/98, 06/95, 01/93 & 02/90 Steel tubes around wheel boxes rusted through - lack of drainage 04/90 Trim tab root rib glued joint failure tab detached - introduce drain holes 08/90 Rear fuselages (ASK 13 & K 7) structural failures 02/91 M Canopy strap on two seaters fouls rear stick/brake lever. Fit secondary strap. BGA Control connectors at wing root bending of thread - adjust correctly/fit airbrake system stop half connector top may be cut away to give clearance with bellcrank 02/91 Trim system turnbuckles failure at trim lever 08/91 Fin attachments ply cracked (front) & rotten at bottom 08/87 & 06/92 Canopy locks worn Ka 2/2b (& Ka 7?) canopies open during sideslips 08/97 Tailplane mounting bolt threads wear - replace bolts as necessary 06/99 Rudder Pedal Failure Ka13 Reported failure. 04/00 Unsecured ballast weight Attachment bolt failed 04/00 M Elevator drive Inspection of engagement BGA 003/08/2000 Iss 1 08/00 BGA 010/12/2000 Iss 1 12/00 M Elevator Re distribution of inspections AD 72-7/3 12/00 Bogus parts Problems with bogus parts 04/00 O Elevator drive (K13&18) Availability of non drilled elevator arms and fin brackets (ref. BGA 010/12/2000) 04/01 Page 1 BGA Compendium 01/02 Schleicher (Germany) Status Subject Airbrake systems Airbrake stops insecure ASK-13, K 7 & Ka 2/b I Cross-link in centre section Airbrake handle failures Airbrake paddles (lower) Airbrakes (Ka-2B & K-7) recommended airbrake travel Jammed open in flight Detail Reference information rivet them into place ‘A’ bracket at wing root - cracks near mounting holes adjust over centre correctly AD 9-173, TN 14 (not ASK-13) cracked and twisted - reinforce cracks at rivet and bearing holes delamination, lack of drain holes reduction of travel and loads K-7, restriction to prevent heavy landings Paddles should not quite clear cut-outs in wings. Operating arm attach. Bolt to paddle fouling wing box. Incorrectly positioned slot TNS 07/76 12/95, 02/95, 02/91 12/84, 10/80 & 02/92 04/89, 12/88 & 12/84 10/95, 04/94, 06/92 & 10/88 04/93 & 04/89 02/85 & 08/89 08/99 02/01 Rhönlerche 2 ("Ka 4") also see general and airbrake sections M M M Elevator tube Aileron clevis pins Wheel box/skid weld cracked below seat strengthen to face forwards inspect foul control shaft min skid thickness 20 mm AD 75-166, TN 13 AD 77-268, TN 14 AD 12-60 02/78 & 10/75 02/78 & 11/77 11/77 & 01/78 Ka-6BR & CR also see general and airbrake sections Wing ribs 1 & 2 Tailplane front mounting Elevator drive rod Tailplane rear mounting Canopy catch inspect for cracks damaged by carrying handle - delete handle damaged near elevator by misrigging cracked & worn fittings, loose & corroded bolts insecure 03/82 & 10/80 06/83 06/83 06/96, 04/94 & 06/91 06/94 Ka-6E also see general and airbrake sections Trim spring & lower mounting Airbrake paddles delaminated Tailplane insecure Air brakes Page 2 BGA Compendium 01/02 bracket corroded/cracked – inspect bolt and glue paddles to aluminium parts reinforce/repair mounting as necessary Cracks in air brake aperture 06/86 BGA 04/87 02/00 Schleicher (Germany) Status Subject Detail Reference information TNS K-7 also see general and airbrake sections I Fuselage centre section Rear canopies detach in flight Rudder cable Air brake pivots Jammed open in flight cracks in welds locating lugs removed or badly warn may catch under rear airbrake pivot nut, fit guard if necessary Pivot bolts may migrate if not locked Control stop jumped past stop tube 06/85 02/87 & 08/91 12/99 02/00 02/01 K-8 & ASK 18 also see general and airbrake sections M M M M M M M M Canopy locks Wing ribs 1&2 Control system Seat back to be fitted (K-8) Elevator hinge pins Rudder cables Elevator hinge Weight and balance revised Tailplane mountings Canopy retaining chord Rudder pedal bending Front wing pins Fuselage tubes Fuselage tubes Elevator push rod Elevator drive General ASW 12 M Wingspar M Water penetration of spars Page 3 BGA Compendium 01/02 not secure, 2mm minimum locking inspect for cracks lower mounting in fuselage centre - cracked - inspect to prevent parachute catching between tubes not secure - inspect fouling elevator rod cracked (ASK 18) cracked and corroded max strength 34 Kg repair as necessary max oversize corrosion inspection, internal wax oil recommended X-ray inspection is possible check for bending Inspection of engagement Re distribution of tech note Inspection boroscope inspection AD 80-158, TN 21 TN 3 AD 96-005, TN 24 AD 96-005, TN 24 AD 96-005, TN 24 AD 96-005, TN 24 BGA 003/08/2000 Iss. 1 TN 24 AD 89-115 AD 89-115, TN 4 08/80 & 07/76 10/80 03/82 11/82 12/86 02/92 06/92 08/92 04/93 04/96 04/96 04/96 04/96 04/97 04/96 & 04/97 08/00 12/00 10/89 Schleicher (Germany) Status Subject Detail Reference information TNS improperly locked (lack of lubrication) - colour code open/shut lug failure inoperative and hinge fractured - lack of lubrication max winch/auto speed increased to 60 kts corroded torque tube failure near drive lug weld Pivot bolts may migrate if not locked Failure of tube at attachment to pedal Unsecured ballast fouling controls due to bolt failure Inspection for bent elevator arms BGA 004/08/2000 Iss 1 inspection of aileron and air brake control support brackets BGA 008/10/2000 Iss 1 Inspection of engagement BGA 010/12/2000 Iss 1 Weak link of 1080kg (Black) should be used 02/87 10/75 02/91 12/93 02/94 04/97 02/00 04/00 04/00 08/00 10/00 12/00 ASK-13 - all also see general and airbrake sections M M Canopy opened in flight Wheel brake Canopy jettison Weak link reduced to 850 Kg Aileron balance weight supports Airbrake drive behind rear seat Air brake pivots Rudder pedals Ballast weights Elevator Controls Elevator drive Weak link ASK-13 JUBI built models only. also see general and airbrake sections M Spar root bolt holes oversize refit bolts with epoxy SB 13 12/91 Inspection/replacement obscured AD 74-323 AD 89-121, TN 6 10/89 Inspection/replacement rods fouling fouls AD 74-323 AD 71-117, TN 6 ASK-14 also see general and airbrake sections M M Control cables Fuel tank transparency ASW-15 & 15B M M Control cables Elevator & aileron Rudder & fin shroud Page 4 BGA Compendium 01/02 Schleicher (Germany) Status Subject Detail Tow release cable damaged in conduit M M Elevator drive bell crank reinforced Undercarriage handle knob detached locking pin failed M Water penetration of spars boroscope inspection M Service life extended to 12,000 hours, inspections from 3 000 onwards Ailerons oscillate if too out of balance max 122 Kg mm TE heavy Reference information AD 82-221, TN 22 AD 88-95/2, TN 23 AD 81-91, TN 20 TNS 06/75 02/83 08/93 & 08/83 06/88 12/89 10/97 ASK 16 M M M M M Control cables Main wheel Weight increase Auxiliary (removable) fuel tanks Cylinder head Fuel tank transparency Control tubes in the wing Inspection/replacement hub bolt failures fit enlarged (8 mm) bolts to 1650 lbs optional mod temp limits obscured corroded AD 74-323 AD 77-234, TN 8 TN 3 TN 4 TN 6 AD 89-81, TN 10 Inspection/replacement fit clips to hoses by increasing water boroscope inspection caused by water ingress from 3 000 to 12 000 hrs after inspections AD 74-323 AD 76-11, TN 6 TN 8 AD 89-115, TN 12 01/78 & 11/77 01/78 01/78 01/78 10/89 02/92 ASW 17 & 17B M M M M M Control cables Water ballast leaks in fuselage Increased AUW to 610 Kg Water penetration of spars Soft balsa in tailplane Life extension ASK 18 also see general and airbrake sections See K8 section Page 5 BGA Compendium 01/02 AD 93-124, TN 13 04/76 01/78 10/89 04/89 10/93 Schleicher (Germany) Status Subject ASW 19 & 19B Detail Reference information M Inspection/replacement AD 74-323 Control cables Canopy latch rods bend on heavy landings - inspect M Rudder stiffened flutter avoidance M Water ballast outlet pipes moved to behind wheel M Rear fuselage inspection cover modify M Tow hook attachment strengthened ASW 19 becomes ASW 19B 454 Kg AUW 600 Kg instead of 500 Kg weak link M Control hinges missing rivets Rudder pedal “S” guides cracked M Elevator flutter modify elevator M Tow release cable too short 12 mm minimum slack M Canopy open/close knobs to be painted red M Elevator locking pin introduced M Rudder cable sever bend at rudder M Life increase from 3000 hours to 6000 hours after inspections Air brake mod (extra paddle) pivot bolts fouling original blade I Jamming of Airbrakes Paddle mounting bolts too long TNS 04/78 AD 76-258, TN 2 TN 3 AD 78-303, TN 7 01/78 TN 6 A & B AD 81-74 05/79 05/81 07/81 06/84 10/84 02/85 08/85 08/85 02/97 06/98 02/01 AD 84-65, TN 17 AD 84-115, TN 18 TN 17 AD 97-010, TN 25 01/79 ASW-20 series (Ref. also Centrair built ASW-20F) M M M M M M Hook installation Canopy latch rods Rear fuselage inspection cover Control hinges Aileron and flap flutter Flap vibration Control hinges Rudder pedals & “S” guides Flap control stops insecure Tow release cable too short Page 6 BGA Compendium 01/02 reinforced bend on heavy landings - inspect modify corroded rivets Avoidance backlash missing rivets cracked rivet into place if necessary 12 mm minimum slack AD 77-294, TN 1 AD 78-303, TN 4 01/78 04/78 01/79 12/79 AD 81-54 AD 81-74 AD 91-073 AD 84-115, TN 21 05/81 05/81 08/96 & 07/81 02/83 10/84 Schleicher (Germany) Status Subject Flap malfunction M Certification limits changed M Rudder cables M Canopy open/close knobs M Aileron flutter M Elevator trim mod Ballast dump valve inoperative M Max weight of non-lifting parts Elevator control restriction M Life increase Detail lock nuts at pilots' lever loose Schleicher data sheet 314 sever bend at rudder to be painted red incorrect use of tape to avoid PIOs corrosion of swages in cockpit (B & BL) increased by 10 Kg foul between incorrectly fitted bolts from 3000 hours to 12000 hours after inspections Reference information AD 87-141, TN 31 AD 87-148, TN 30 TN 35 AD 1998-255, TN 39/2 TNS 12/84 04/85 08/85 02/85 08/96 & 10/87 02/88 10/90 02/91 06/96 06/98 ASK-21 M M M M M M M M O M M M M M M Rudder jammed by flexible toe straps replace with rigid type or delete Accelerometer mandatory for aerobatics flight manual change Trim indicator Bowden cable fouls controls below floor - clip as necessary Cable release modify system Wheel fouls wheel box cut extra clearance if necessary Trim indicator restricts elevator modify Rudder pedal support cracked replace before 1 April 1987 U/C retention stud failures Rear canopy gas strut support structure reinforce to drawing 210.12.55 Rear canopy gas strut hinge pins inspect for wear Rear canopy unlocked in flight modify to latest standard Rudder pedal cable guides Nylon tube inserts, glue into place movement restricts rudder travel Speed brake lever at splitter output replace bellcrank by part 210.43.0005 Automatic elevator connector inspect parallel rocker Flight manual revisions spinning etc Rudder pedal jamming loose nylon tube Elevator vertical rod inspect for corrosion Front canopy jettison inoperative, incorrectly aligned nuts Extension of service life to 12 000 hours inspections after 3 000 hours Page 7 BGA Compendium 01/02 AD 81-92, TN 5B AD 84-2, TN 10 TN 18 TN 19 AD 38-2, TN 20 TN 15 TN 20 TN 20 AD 90-350, TN 8 & 22 AD 91-112, TN 23 AD 93-186, TN 26 AD 94-026, TN 24 03/81& 07/81 06/83 10/83 06/84 & 04/84 12/84 12/85 08/87 12/87 08/93 & 04/88 10/93 02/91 04/83 & 04/88 06/88 02/91 12/91 04/92 12/93 02/94 04/94 Schleicher (Germany) Status Subject Detail Reference information TNS to be changed annual check inspect system AD 85-90, TN 2 AD 91-148, TN 7 08/85 10/91 10/98 TN 2 12/85 04/87 08/88 02/91 12/91 02/94 10/97 ASW-22 & 22B M M Trim spring Elevator drive Flap lever failed to lock (weak spring?) ASK-23 & 23B M M M M Nose wheel box Trim spring Rudder travel restricted Automatic elevator connector Air brake lever fractures Main landing gear bulkhead Extension of service life reinforce failures by loose nylon tubes inspect parallel rocker at weld at pilots handle inspect to 12 000 hours, inspections after 3 000 hours AD 90-350, TN 8 AD 93-196, TN 10 AD 97-244, TN 12 ASW-24 M M M I M Minor modifications to Schleicher letter models pre serial number 50 Undercarriage support structure reinforce Fuselage drainage (ballast leaks) introduce Max. weight of non-lifting parts increased by 15 Kg Flying controls Aileron hinges dis-bonded from wing Engine support Inspection ASW 24E TN 2 02/90 02/90 02/90 02/91 04/01 AD 92-8, TN 2 ASH-25, 25E & ASH 25M M Max engine speed Elevator drive annual inspection Page 8 BGA Compendium 01/02 (25E) 7200 RPM for one minute and maintenance manual and C of G changes ASH 25E TN 2 02/91 AD 91-146, TN 4 10/91 Schleicher (Germany) Status Subject Detail M Elevator Inspection ASH 25 Improved propeller option (25E) part MT 130-L-108--1B Internal damage to flaps & ailerons Rohacell foam U/C main vertical member weld failure below shock absorber M Service life increased from 6 000 to 12 000 hours after inspections (-25 & 25M) M Service life increased from 6 000 to 12 000 hours after inspections (-25E) M Flight & maintenance manuals page changes M Elevator linkage inspections after heavy landings etc M U/C - locking of bolts fit lock plates at C of A M ASH 25M exhaust muffler cracks exchange for new unit Reference information AD 91-147, TN 6 TN 3B TNS AD 1998-486, TN14 AD 1998-486, TN12 AD 1998-486 AD 1998-486 AD 1998-486 AD 1999-376, TN 15 02/92 02/95 06/97 02/99 02/99 02/99 02/99 02/99 02/00 modifications change fan & temp sensor various inspections and actions replace with modified type change for improved type AD 97-009, TN 1 AD 98-347, TN 6 AD 1998-21 AD 1999-311, TN 8 06/95 02/97 10/98 12/98 10/99 Elevator high friction - inspect Amendments mass balance in fin rubs on rib Flight, Maint, and repair manual amendments AD1999-283, TN 5 AD 2000-305, TN 6 10/99 10/00 Flying controls Inspection of aileron hinge pins maintenance instruction (TN – tba) 10/01 ASH-26 & 26E O M M M M Rear fuselage Engine internal cooling Engine fire prevention Engine rotor cooling air fan Exhaust muffler modification ASW-27 M M ASW28 M Page 9 BGA Compendium 01/02 Siebert (Germany) Status Subject Detail Reference information TNS cracked - reinforce AD 81/17, TN 264-2 03/81 Contact: SIE 3 M Elevator mass balance mount Page 1 BGA Compendium 01/02 Slingsby (UK) Status Subject Detail Reference information TNS Mod.80 1962? 08/89 side plates cracked inter connect – failure threads cracked attachment at pylon front cracked at bolt-hole disconnection in flight clevis pin too long - safety pin fouls on tailplane drive rod failure at ball-end fitting in cockpit - inspect annually end fitting to drive tube rivet failure- inspect annually 1 & 4 cracked inspect annually damaged by lightening adjust to avoid fin loads Cracks in welds 10/93 & 08/80 12/93,10/91 & 06/83 10/83 06/84 08/85 02/96 & 08/95 09/85 & 06/86 04/87 08/89 06/93 Contact: Slingsby Aviation Ltd, Kirbymoorside, York. YO6 6EZ. 01751 432474 T 1 Grasshopper Air Cadet Operational Notes and Maintenance Manuals are available from the BGA Tutor (Cadet Mk 2) & T.31 (Cadet Mk 3, Tandem Tutor) M Main spar failure Rudder cable stops major modification adjust to avoid fin loads T.21A & B Sedbergh Tow hook Control stick Drag spar Elevator Elevator Elevator Main frames Control cables Rudder cable stops Wing root fittings T.41 Skylark 2 M M M M Shoulder harness Shoulder harness Canopy catch Canopy catch Rudder stops Fin spar inspection at the base Rudder cables Page 1 BGA Compendium 01/02 canvas seats non canvas seats improved type (lift off) improved type (hinged) adjust to avoid fin load annual & after heavy landings etc fouling on the fin Mod 96 Mod 97 Mod 98 Mod 99 (CAA) (CAA) (CAA) (CAA) TN 107/T50 06/87 08/87 04/88 Slingsby (UK) Status Subject T.42 Eagle M Canopy retention strap Wing spars Detail Reference information fouls rear stick strengthening Mod 1 Mod 5 TNS T.43 Skylark 3 & T.50 Skylark 4 M M Wing root strengthening Wing fittings Harness attachments Canopy catch worn Fin spar inspection at the base Rudder stops Aileron misrigging Aileron pip-pin connector Elevator misconnected Rudder horn Mod 7 severe corrosion inspect & treat as necessary excess backlash external lever does not function annual & after heavy landings etc adjust to avoid fin loads fit wing tips with ailerons neutral failed - aileron disconnected driver lower lug not in slot - loosens in flight severe corrosion 10/96 & 12/81 Mod 96 & 97 Mod 99 TN 107/T50 Skylark 3 06/83 08/87 06/87 10/92 06/93 04/97 02/99 T.45 Swallow M Canopy catches Fin spar Rudder stops insecure Cockpit torque tube insecure Mod 10 damaged by rudder cables after wearing through the fairlead resulting in rudder over-travel cracks 12/90 threaded end fractured adjacent to the brake cable frayed at pulley guard corroded adjust to avoid fin loads cracked at weld protruding bolt on brake paddle damaged by skid rubber air brake mechanism damaged damage airbrake rod cables wrapped around rod behind cockpit 08/74 03/75 08/84 12/82 08/87 10/93 06/97 08/98 08/98 04/88 T.49 A & B Capstan Cracks in bracing at frame 3 Air brake rod Tow release Rudder lower hinge Rudder stops Rudder-post Airbrakes jammed Fuselage skin Rudder cables Page 2 BGA Compendium 01/02 Slingsby (UK) Status Subject Detail T51 Dart 15, 15R, 15WR, 17, 17R, 17WR M M Undercarriage strengthening Drag spar safety pins too long Aileron flutter Longerons Centre section frames & diagonals Longerons inspection Spar Dural spar boom Elevator flutter Reference information Mod 66 become unlocked caused by excessive backlash (5 mm total play) cracked at frame 6in flight break up inspect annually & after any “event” cracked after heavy landings etc & annually corrosion at wing root corrosion at bond mandatory inspection every 5 years TI 109 iss 3 Revised inspection at issue 3 excess play between elevators TNS 08/79 10/76 & 10/83 04/85 08/85 08/87 04/93 & 12/91 12/97 & 08/00 10/98 T.53/YS-53 Sovereign M M M M M Airbrakes locked out Elevator lever mounting bracket Tailplane incidence change Wing centre section Wing attachment Wing attachment Centre sections cracks Frames 4 to 6 Wing mechanism jammed at fuselage frame 6 replace (at rear control box) inspection and strengthening bracket (frame 6) inspection and replacement bracket (frame 6) inspection of replacement parts at frames 4 & 6 corrosion and loose rivets Inspection of centre section TI 36, Mod 11 TI 40, Mod 15 AD 002-05-81, TI 66 & 68 AD 003-05-81,AD 004-05-81, TI 69 & 70 TI 90 TI 100 08/80 05/81 05/81 05/81 05/81 02/80 & 05/81 08/85 07/86 AD 001-10-82, TI 100/T53 T.59 A, C, D & H Kestrel 17, 19, 20 & 22 (Kestrel ”2”) See Glasflugel section for Glasflugel 401 aircraft M M M M M canopy Landing Gear Seal flaps and ailerons Fit servo tab to elevator Controls Aileron Wings Page 3 BGA Compendium 01/02 Modify canopy catch spigot mounting Reposition bolts on u/c operating shaft series I becomes series II, aft C of G limit from 14.76" to 15.83" Introduction of take off flap position on landing flap control mass balance limits changed to avoid wing flutter Inspection TI 43, Mod 4 Mod 5 TI 49, Mod 11 TI 52, Mods 9 & 13 Mod 15 TI 54 TI 62 1973 1973 1973 1973 Slingsby (UK) Status Subject Elevator Landing flap rods M Elevator actuator replacement Rudder actuator Airbrake Dive brakes M Air brake Root rib Rudder cables M Rudder cable failures (fatal) Controls Controls M New mass balancing limits Flap/aileron connections Critical areas M Rudder drive annual crack check 07/86 & 12/81 Undercarriage operating arm Flap drive shaft mount loose Flap and aileron ‘buzz’ M Elevator push rod inspection LE delamination Aileron skew-drives Aileron LE foul Tailplane front mounting lock Winch hook angle changed Water ingress at wing root rib Detail Actuator fitting inspection check for end bending by part number 59A-30-25 improved bearings fitted Tensions airbrake caps as necessaryto prevent flap flutter Operating limitations control system improvement ‘uniballs’ - loctite them in Inspection fit stop to prevent rudder pedals going fully forward. Repeated failures if pedal geometry is wrong Frequently inspect cables in the nose addendum 7 to pilot’s notes reversed at bell cranks - check after assembly Inspection for loose bolts mandatory ‘Magnaflux’ check weld failure R H side of wheel box damaged while rigging - caused flap flutter max total freeplays 1/8 “ & 1/16“ for internal corrosion water ballast leak drill extra drain holes & inspect annually assemble with loctite to minimise backlash with detached/loose gelcoat must be wire locked improved launch (optional) caused 12” x 6” of disbonding Reference information TI 63 TI 64 TI 65, Mod 18 TI 67, Mod 26 TNS 1974 10/75 TI 72 TI 75, Mod 28 TI 76, Mod 31 TI 77 TI 78, Mod 33 04/75 & 06/75 1975 10/75 04/76 04/77 01/76 07/76 TI 89 AD 002-01-82, TI 101/T59 TI 106, 09/82 10/83 06/88 & 09/85 02/87 08/88 & 06/87 06/88 06/90 BGA 04/99 12/99 T61 Series General I SF-25/T-61 elevator tab cables wire lock at tab I T-61 spar delamination at wing root I Longerons corroded at fin post adjacent to microballoon filler I T-61 aileron hinges cracked cracked at pin supporting plate weld I T-61 elevator push rod fitting cracks around holes at fork end in fus centre Page 4 BGA Compendium 01/02 TI 73 TI 74 06/73 11/74 01/75 06/75 06/75 Slingsby (UK) Status I I I I I I I M M I I I I M M I I R M M M I I I I I Subject Detail Fuel gauge misreading tube sagging - 50 hour check SF-25 aileron drive lever 50 hour check crack at weld on spar tube SF-25 tailplane rear mount cracks at pin attachment weld Wheel assembly bolt failures fit larger (8mm) bolts T-61 tailplane spar delamination inspect annually SF-25/T-61 compass errors magnetised canopy frame Spar deterioration water in spoiler boxes SF-25/T-61 wing main pin holes worn & splayed oval T-61 wing rigging instructions and pin mod T-61 ignition switch “live” test Crank case cracks numerous cases - inspect regularly SF-25/T-61 tailplane front attachment cracked SF-25 fuel flow restriction filter incorrectly installed Top harness attachments secure to transverse tube Rear exhaust valve burning Limbach improved cooling kit Tubing on fuel gauges hardens and leaks T-61 magneto to crankshaft coupling failure of type without reinforcing ring SF-25 carb heat system introduced mandatory (CAA) Fuel shut off valve Truma V8M 8 year (seals) life limitation Fuel shut off valve NK 490 fitted in place of Truma V8M Truma V8 fuel valves made after 1/6/96exchange valve for new Rear fuselage structure corrosion near fin attachments Aileron drive bearing failure central hanger upper bearing between sticks Tailplane front mount cracked through inspect for cracks and poor welds Throttle cable disconnected check security at carburettor connection Control stick Modification Reference information AD 76-40, TN 653-1/76 AD 75-169, TN 653-5/75 AD 77-217, TM-S 02-77 TI 81 CAA LTO 514, TI 103 TI 102 Mod 134 AD 82-50/2, SB 653-41 SB 653-70 AD 97-140, SB 653-67 AD 1984-198/2, SB 653-47/2 Airworthiness Directives and Mandatory Modifications listed in CAA MAMIS M Elevator M Engine mount studs M Canopy M Elevator ctr hinge M Elevator tab M Aileron M Rudder pedals Page 5 BGA Compendium 01/02 Change of control rigging pin T61A replacement of 10mm studs Addition of fasteners Inspection & replacement Inspection Inspection of operating lever Reduction of stops TI 42, Mod 3 TI 45, Mod 10 TI 50, Mod 15 TI 53, Mod 16 TI 55 AD 011-10-80, TI 79, Mod 17 AD 012-10-80, TI 80, Mod 18 TNS 04/76 04/76 09/77 11/77 03/79 12/79 06/95 & 12/80 12/80 07/82 12/85 02/87 04/90 06/90 01/93 01/93 06/95 06/96 08/87 02/90 02/98 08/97 02/99 04/99 08/99 10/99 04/00 Slingsby (UK) Status M M M M Subject Wing root fitting Tailplane Wings Wings Detail Pin inspection Forward bracket inspection Inspection of wing centre pin Inspection of wing centre joint additional limitations Reference information AD 009-11-80, TI 94 AD 003-01-82, TI 102/T61 AD 003-06-82 AD 001-07-82, TI 103/T61 jam ailerons to be shaken out fouls outboard hand hole Modification if Mod 12 not c/out do not pressure fill at more than 2½ PSI airspeed restriction - lifted when Mod 12 has been carried out replace TI 83 TI 84 TI 85, Mod 12 TI 86 TI 82 TI 87 issue 2 TI 88, Mod 27 TI 89 TI 91 TNS 04/90 04/95 07/82 T.65 A & D Vega & T.65C Sport Vega M M M M M M M M M M M M M Loose pieces of resin in the wings Aileron actuator Flap/airbrake Water tanks Airbrakes inadvertently opening Wing spigots Wing strengthening Critical areas Elevator actuator pin retention Seat pan fouls elevator control Aileron vibration Canopy lock Stern post detached from fin skin Elevator centre hinge-mounting Canopy jettison inoperative Tailplane mounting spigot Rudder travel restricted Rudder cables Elevator drive at base of fin Ailerons Elevator hinge Undercarriage mechanism wear Rudder Flap drive failure Tailplane Aileron Tailplane upper skin Tow release & brake cables Aileron actuator cover plate Undercarriage lever failure Page 6 BGA Compendium 01/02 06/84, 08/83 & 08/79 08/79 08/79 08/79 10/79 10/79 Inspection for loose bolts replace circlip with split-pin 04/80 cut clearance as necessary 10/80 mass balance increased (all models) AD 002-05-81,AD 004-01-82, TI 92, TI 95 12/80 screws loose in frame 12/80 inspect & repair as necessary 03/82 rib loose in TP - reinforce TI 104 11/82 check system annually TI 105 11/82 tongue cracked at bolt holes 02/83 at extremes of pedal adjustment limit pedal adjustment 06/84 damaged by a screw at tail wheel retraction hinge, inspect 06/84 delaminated 08/85 jammed by wheel retraction with one U/C mechanism bolt reversed 09/85 axis & drive misaligned align to avoid excess backlash & flutter 02/88 & 10/86 excess free play causes collapse 04/87 water drains blocked 06/87 at universal joint at pilots quadrant Pre Mod 16 aircraft only TN 108 08/90 & 08/87 attachments cracks in GRP inspect frequently 02/88 hinges and drive box corroded 08/88 unbonded from root rib 02/89 corroded & failed 06/89 jammed ailerons - always tape into place 06/89 at rod end bearing in cockpit 06/91 Slingsby (UK) Status Subject Undercarriage lever failure Flap drive yokes dis-bonded Canopy Tailplane attachment M Elevator Drive M Flying controls Page 7 BGA Compendium 01/02 Detail Reference information at weld on u/c noticed because of excess play in flaps locking lever must face upwards to prevent accidental canopy opening cracks inspection within 6 months and after ground loops etc TI 110/T65 BGA inspection of elevator drive U channel BGA 006/08/2000 iss1 Elevator disconnection and tailplane attachment BGA 013/13/2001 iss1, TI 104/T65 iss2 TNS 12/93 10/97 08/98 06/99 08/00 04/01 Sportine Aviacija (Latvia) Status Subject Detail Reference information TNS replace with genuine Tost hook every 500 hours / 5 years SB 012.5 04/93 12/96 Contact: Baltic Sailplanes 01856 467723 LAK 12 M Aft hook installations Inspections to be carried out Page 1 BGA Compendium 01/02 Stemme (Germany) Status Subject Detail Reference information TNS Contact: UK Agent Mike Jefferies 01277 823066 LBA Airworthiness Directives STEMME S10, V & VT M M M M M M M M M M Rudder cable turn buckle Pitot tube ‘O’ ring Fuel Filter Fuel Tailplane rear fitting Propeller blade fork Flap drive rocker replacement Elevator drive system cracks Rudder cable wear Wastage control & Oil tubes Air brakes & landing gear Propeller Page 1 BGA Compendium 01/02 replace replace Inspection of fuel filters and amendments to flight manual AVGAS 100LL only inspect for cracks exchange, inspect & modify before 31/3/99 inspections before next flight & parts replacement by 31/3/99 at “S” guides on the rudder pedals fit redesigned parts Inspections and modifications Pitch change fork and gearbox modifications AD 94-260, SB A31-10-018 AD 92-197, SB A31-10-003 AD 95-273, SB A31-10-021 AD 96-300, SB A31-10-022 AD 95-177/2, SB A31-10-020 AD 1998-324, SB A31-10-017 AD 1998-323-3, SB31-10-032 AD 1998-400, SB31-10-034 AD 2000-396, SB A 31-10-055 AD 1999-224/5, SB A 31-10-051 10/94 & 02/95 06/95 10/95 08/95 12/96 06/95 & 04/97 08/98 08/98 & 12/98 10/98 12/98 12/00 04/01 Valentin (Austria) (Germany) Status Subject Contact: Detail Taifun Mistral C Reference information TNS KORFF + Co. KG, Unternehmensbereich Luftfahrt, Dieselstrasse 6,D-63128 Dietzenbach, Germany +49 6074 4006 33 Eichelsdorfer GmbH, Hafenstr, 6, D-96052 Bamberg, Germany +49 951 61413 Mistral C M Flight controls Ailerons – residual momentum of ailerons AD 2001-089, TN329-013 02/01 Taifun 17E M M M M M M M M M M M M Flight controls elevator connection Landing gear actuating struts Electrical power push button starter Fuel valve emergency shut-off Stall characteristics improvement Stall warning device introduction Tailplane front mounting inspect/modify Rudder pedals inspection Airbrake & wheel brake torque tube weld inspection Revision of flight manual limitations & inspections Revision of empty weight & C of G Airbrake system torsion tube deformation- inspect Flap lever - cracks in weld replace with modified lever Wings Safety inspection of main wing attachment Page 1 BGA Compendium 01/02 AD 85-29, TN 3-818 AD 85-29, TN 3-818 AD 85-29, TN 3-818 AD 85-29, TN 3-818 AD 85-129, TN 4-818 AD 85-263, TN 8-818 AD 86-137, TN 10-818 TN 11-818 AD 87-84, TN 11-818 AD 87-135, TN 12-818 AD 91-134, SB 24-818 AD 94-114, SB 28-818 AD2000-392/2, SB 05/818 iss2 06/86 06/86 06/86 06/86 06/86 06/86 CAA CAA 02/88 CAA 10/87 10/91 06/94 10/00 & 02/01 Wassmer (France) Status Subject Detail Reference information TNS check for correct orientation bar cracks check & replace if necessary annual checks annual inspection replace any frayed cables incorrectly assembled AD 78-142(A) AD 79-42(A) AD 88-089(A)R1 AD 96-286(A), SB-39 02/98 02/98 02/98 02/97 06/99 fittings cracked - inspect insecure - modify AD 78-74-(A), SB-02 07/78 06/93 & 12/90 Contact: WASSMER WA 26P Squale & WA 28F Espadon M M M M L’Hotellier elevator connection Rear wing attachment Tailplane supports Rudder cable WA 28F Drag pin handle insecure WA 30 Bijave M M Wing to fuselage attachment Canopy catches (front and rear) Page 1 BGA Compendium 01/02 Engines Status Subject Detail Reference information TNS BOMBARDIER-ROTAX SERIES ENGINES Contact: UK Distributor – Skydrive Ltd, 01926 612188, e-mail [[email protected]] Rotax service bulletins can be downloaded from the Internet [www.rotax-aircraft-engines.com] Rotax General I I I I I I R I I Air supply Ignition UL engines 2 Stroke engines 2 Stroke engines 2 Stroke engines 2 Stroke engines Service instructions service bulletin Rotax 912 series M 912A. 912A. Engine M M M M M M 912A, F. Propeller gearbox 912A,F Starter 912A. Ignition 912A. Ignition 912A. Carburettors 912A. Electronic module M 912 A3. Gearbox M 912A & 912UL. Camshaft M 912A & 912F. Fuel pump M 912A, 912F. Stator Page 1 BGA Compendium 01/02 Pulse air supply tube restricted BOSCH spark plug cap shorting internally (broken) Reduction gearbox type C and E, SI amendment If left to dry out oil can thicken and turn to “varnish” Instructions for new design piston Change of exhaust gasket Check of the fuel pressure gauge Index Index Rework to ensure proper contact between attachment screws and stator Inspection and exchange of gearbox Engine starter inspection Production problems in ignition unit Ignition problems in areas of heavy radio Transmission Possible contamination of carburettors Problems with SMD Electronic module in areas of heavy radio transmissions Exchange of propeller gearbox Inspection of camshaft Exchange fuel pump and steel fuel line Inspection of engine Stator assay. SI-06-1998 R1 SI-2ST-001 SI-2ST-002 SI-2ST-003 Edition 6, 10/2001 Edition 11, 11/2001 AD75, TB912-02 AD 101 SB912-027R1, AD 98 912-026R3 AD80, TB912-06 AD82, TB912-07 AD83, TB912-09 AD84, TB912-08 AD89, TB912-19 AD92/1, TB912-18 AD94/1, TB912-20 AD98, SB912-026R3 06/01 06/01 08/01 08/01 10/01 10/01 10/01 04/00 06/00 04/97 04/98 06/00 Engines Status Subject 912 Fuel & Lube. Specs. M 912 series Valves M 912A,F,S. Mount ring M 912A,F Exhaust M 912A,F,S. Valves I 912 series Water pump R 912 series Lubrication O 912 series Lubrication I 912 series Fuel I 912 series Lubrication R 912 series Sprag clutch M 912 series Oil R 912 Fuel R 912 Fuel M 912 series Fuel O 912 Rocker arm M 912 Fuel pump M 912 Oil pump Detail Fuel and Lubricant specifications replacement of valve spring retainer Crack inspection Crack inspection Replacement of valve spring retainers Rotary water pump seal / impeller Verification of the lub. System & repl. Pressure spring Oil connections with UNF threads Modified carb. Flange Lubrication system Replacement of circlip in housing Selection of motor oil and operating tips Check of the fuel pressure gauge Fuel pressure indication problems Cracks, wear & distortion of carburettor flange new bushings Inspection/replacement Replacement of oil pump or shaft Reference information 18UL97R1-D/E 06/98 SB912-022 AD105, SB912-028, SB912-028UL. AD107R1, SB912-029, SB912-029UL. AD108, SB912-022 SI912-001 SI912-002 SI912-003 SI912-004 SI912-005 SI912-006 SI18-1997 R3 SI912-007 SI912-008 SB912-030, SB912-030UL SI912-009 AD109, SB912-031, SB912-031UL SB912-032, SB912-032UL Rotax 914 series M 914F. Mixture M 914F. Oil System M 914F. Oil System M 914F, Propeller gearbox M 914F Starter M 914F. Stator M 914 series M 914F Mount ring M 914F Exhaust M 914F Exhaust M 914F Valves 914 Fuel & Lube. Specs I 914 series Water pump Verification or calibration of the mixture enrichment jet Check of banjo bolt in turbo charger line Replacement of turbo oil pressure line and pipe clamps Inspection and exchange of gearbox Engine starter inspection Inspection of engine Stator assay. Replacement of valve spring retainer Crack inspection Crack inspection Crack inspection Replacement of valve spring retainers Fuel and Lubricant specifications Rotary water pump seal / impeller AD88, TB914-03 AD90, TB914-04 AD95, TB914-07 AD 101, SB914-010R1 AD 98, 914-014R3 AD98, SB914-014R3 SB 914-011 AD105, SB914-016, SB914-016UL. AD106, SB914-017, SB914-017UL. AD107R1, SB914-018, SB914-018UL. AD108, SB914-011 18UL97R1-D/E SI914-001 Page 2 BGA Compendium 01/02 TNS 04/01 06/01 06/01 06/01 08/01 08/01 10/01 10/01 10/01 12/01 12/01 12/01 10/98 04/00 06/00 06/00 04/01 06/01 06/01 06/01 06/01 06/98 Engines Status R I R O I I R M R M O Subject 914 series Mixture 914 series Wastegate 914 series Lubrication 914 series Lubrication 914 series Fuel 914 series Lubrication 914 series Sprag clutch 914 series Oil 914 Fuel 914 series Fuel 914 Rocker arm Rotax 500 series M 501 & 505. Piston pin bearing M 505 & 505A. Ignition M 582 & 532. Crankcase/gearbox Detail Optimising of mixture distribution Checking and Lubrication Verification of the lub. System & repl. Pressure spring Oil connections with UNF threads Modified carb. Flange Lubrication system Replacement of circlip in housing Selection of motor oil and operating tips Check of the fuel pressure gauge Cracks, wear & distortion of carburettor flange New bushings Reference information SI914-002 SI914-003 SI914-004 SI914-005 SI914-006 SI914-007 SI914-008 SI18-1997 R3 SI914-009 SB914-019, SB914-019UL SI914-010 Conversion to reinforced design Conversion to the new electronic box Failure of crankcase/gearbox thread bosses AD64, SB505-05 AD69, TB505-06 CAA 006-03-90, TCP900228/0720/FJ Operation and maintenance instructions for F10 aircraft engines – revision AD69-142 TNS 08/01 08/01 10/01 10/01 12/01 HIRTH F10 SERIES ENGINES M F10. Operation & maintenance LIMBACH SERIES ENGINES M L1700, L2000, L2400. Carburettor. Leaking carb. Floats due to manf. Errors M SL1700E, EA, EB, EC. Mixture. M L2000EA. Starter Unleaded Mogas Page 3 BGA Compendium 01/02 AD97-237, TB55 02/94 Mixture control – Rubber diaphragm of the governor piston AD76-238, TB12 10/87 Starter shaft support case of electric Starter use of AD97-003, TB52 TB50 & 53 04/97 10/99 Engines Status Subject Detail Reference information TNS VW DERIVATIVE POWERPLANTS I Stamo Engines Crankshaft Stamo Engines Use of Unleaded mogas Inspect for damage to the propeller shaft Propeller hub fixing bolt torque 20 MKG 12/99 04/00 04/00 GENERAL ENGINE INFORMATION M M M Aeroquip Hoses Slick Magnetos Stromberg Carburettors Unleaded Mogas Some are suspect See – Equipment section Inspections and service lives See – Equipment section Fit service kit at 500 hrs See CAA Airworthiness Notice 98 Bendix Magnetos Exhaust heat exchangers Motor Glider PVC Tubing Inspections and service lives See – Equipment section Annual pressure test at 20 psi AWN 40 Performance Data for C of A air test PVC tubing shrinks and becomes hard and brittle with prolonged exposure to fuel. Replace regularly. General Page 4 BGA Compendium 01/02 Reminder that engines, propellers, magnetos, hoses have service lives. 10/88 12/97 10/87 12/99 08/92 10/98 04/99 08/00 Propellers Status Subject Detail Reference information TNS Airworthiness Directives as listed HOFFMANN SERIES PROPELLERS (Luftfahrt-Bundesamt Airworthiness Directives) (LBA) UK Service Station – Skycraft Services Ltd, 01763 852150 M HO-V62 R/L 160T M HO-V 123 ()-()/180R M M HO27 & HO4/27 Overhaul Periods Hoffmann VP Propellers Calibration of tachometer and inspection of propeller blades. Introduction of improved blade root retention AD83-150/4, SB4C Inspection for cracks in the coating on the suction side near the blade shaft AD88-20, SB6 EB Strength problems on propeller mounting Bolts AD1998-322/2, SB61-11-03E10 RA See TNS Pitch change rod failure 06/91 10/00 MT PROPELLERS (Luftfahrt-Bundesamt Airworthiness Directives) (LBA) M M M M M MTV-1-() MTV series MTV series MTV-1-(), -7-(), -10-(), -17-(), -18-() and –20-() MT & MYV series M MTV-3-B, MTV-3-B-C M MTV-9 M MTV-3 Page 1 BGA Compendium 01/02 Possible loss of propeller blade Change of emergency procedures for powered gliders Correction to AD92-367 Replacement of the electric motor of the propeller servo Replacement of PU erosion strip to avoid sudden Loss of erosion sheet Hub, crack inspection and rework or replacement of the hub Propeller blades, inspection of the torque and if applicable replacement of the blade root lag screws Propeller blades, inspection of the torque and if AD90-214 iss2, SB TM4A AD92-367, SB TM6 see AD 92-367 AD93-088/2, SB TM7 06/93 AD94-098, SB8 AD97-006/5, SB12 AD1999-081/2 SB17A 04/97 Propellers Status Subject Detail applicable replacement of the blade root lag screws Reference information AD1999-082/2, SB17A TNS Propeller blade thickness inspection AD2001-345, SB 32.110/25/1 12/01 TOP PROPELLERS M All models Blades GENERAL PROPELLER INFORMATION Mount bolts Blades Page 2 BGA Compendium 01/02 Check bolt torque regularly to prevent damage Seal minor damage to propeller blades to prevent Moisture absorption and expensive repair. 12/97 Equipment Status Subject Detail Reference information TNS EQUIPMENT (Airworthiness Directives as detailed) General R Removable equipment R Cockpit equipment M Oxygen bottles I GQ Parachutes M Parachutes R Radio R Radio Controls M Control cables M L’Hotellier couplings M L’Hotellier QR. Cam type R Control connections R M Wedekind couplings Couplings Instruments & electrical R Instruments M Compasses I Electrical connectors M Landing gear warning horns M Altimeters Page 1 BGA Compendium 01/02 Barographs, Batteries, ballast weights, O2 bottles etc. safe and secure? Must not impede escape To be internally inspected every 5 years May have suspect canopies Plastic ripcord handles must be replaced with metal LBA AD80/13/0 Must be safe and secure, must not impede exit from aircraft Frequencies to be checked every 48 months Inspection of copper sleeves used on control cables DGAC 67-22 quick release couplings inspection LBA 1993-001/3 Inspections LBA 1994-001/2 L’Hotellier and other quick release types , inspect after rigging As well as positive control checks Safety connectors Check that locking pins cannot jam controls Altimeters, sub-scale to be checked every C of A Check swing every 2 years Milti plugs make no1 pin positive. AXR & XLR types have no 2 positive. Always fit fuses Check to see if case is live CAA AD 008-08-91 Check operation of baro. Knob does not cause de-synchronisation of sub scale and pointers on United, Kollsman, Aero, Narco, Bendix instruments CAA AD 006-02-97 R1 12/88 10/98 04/93 04/94 06/99 08/94 10/97 & 12/97 04/98 & 06/99 Equipment Status Subject Seats & harnesses M Harnesses General M Garinger Seat harnesses R Garinger Seat harnesses M Seat cushions M Autoflug Seat harness M Williams Seat harness M Seats R Seat trim I Seat harnesses M Seat harnesses Hoses M Fuel and Oil Hoses I I Aeroquip hoses Trelleborg Hoses Detail Reference information Must be installed so that webbing cannot creep through buckles loose nuts Anti slip mod kit Only energy absorbing types to be used in addition to manufacturers. E.g. “Dynafoam” Anti slip springs should always be fitted post 1992 blue QR boxes, return to have strengthening plunger fitted Slot in types must be secured to retain in negative “G” Obstructing exit from glider – inspection BGA 019/06/2001 iss1 Ensure correctly installed Non metal latching devices – replace CAA AD 005-10-91 Replacement of Aeroquip type 601 hoses Mfd. between 3/84 and 5/88 Some are suspect Faulty batch Mfd code 25 99 Skydrive Safety Bulletin 12/87 08/87 08/93 08/96 12/96 06/97 06/89 06/01 08/00 CAA AD 029-05-89, SB 003 010501 10/88 06/01 12/88 02/99 06/94 06/98 Magnetos M Bendix Magnetos M Bendix Magnetos M Bendix Magnetos M Bendix Magnetos M Bendix Magnetos Impuls coupling inspection Models S4LN, S6LN, Tracking of Distributor block Impulse coupling, coils & magnet inspections Capacitor replacement Impulse coupling inspection FAA 82-20-01, SB 623 FAA FAA 94-01-03R2 FAA 94-06-09 FAA 96-12-07 M Bendix switches Inspection of Key operated magneto switches FAA 76-07-12 M M M M R Slick Magnetos Slick Magnetos Slick magnetos Slick Magnetos Slick Magnetos Insp/replace coils Models 42xx, 42xxR, 62xx, 62xxR. FAA 81-16-05, SB 1-81 Impulse coupling inspection Model 447 FAA 74-18-05, SL1-73 Impulse coupling inspection Models 447, 41xx, 42xx, 62xx & R FAA 80-06-05 500 hour overhaul life 250hr Service life recommended by manufacturers to Single ignition Motor gliders Slick SB 1/89 Page 2 BGA Compendium 01/02 TNS 12/97 Equipment Status Subject Carburettors R Stromburg Carburettors M Stromburg Carburettors Detail Reference information TNS Float valve assy wear – flooding replace at 500hr Replacement of diaphragm AD76-283 (Limbach TB12) 10/87 10/87 Towing equipment R Tost hooks R Hooks general M Hooks general M Tost hooks R Tost hooks M VEB ALON 155 May be maintained “ON Condition” subject to regular inspections Check for wear, correct lubrication and clendleness If two hooks are fitted they both must operate from a single control Replacement of bracket (Universal 53 series S/N 1>29999) AD 1/66 TBO from 3 to 4 years AD 89-18/2, SB 60.230/2-4/88 inspection AD 95-260 Page 3 BGA Compendium 01/02 02/00