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airworthiness directive - Civil Aviation Safety Authority

1. For Requirement 2 Before further flight after the Requirement 1 inspection For Requirement 3 Before further flight after the snap ring impulse coupling assembly is replaced This Amendment becomes effective on 1 September 2005 This Directive supersedes AD ELECT 68 which will be cancelled AD ELECT 68 required repetitive inspections of riveted and snap ring impulse coupling assemblies and if necessary their replacement when they were worn beyond limits This Directive requires a reduced inspection interval for magnetos with riveted impulse coupling assemblies installed on certain Lycoming engine models The Directive does not lower the inspection interval for magnetos with snap ring impulse coupling assemblies The Directive also limits the applicability to certain Lycoming engine models These actions result from data provided by the manufacturer to the United States Federal Aviation Administration that showed a need to reduce the inspection intervals for riveted impulse coupling assemblies used on certain Lycoming engine models Note 5 Teledyne Continental Ignitions Systems Service Bulletin SB643B dated 6 April 2005 provides the manufacturer recommended periods for inspection overhaul for TCM magnetos installed on engine types that are not specifically referenced in this Amendment Inspection periods specified in this Amendment supersede those in SB643B The original issue of this Directive was issued to aid in the prevention
2. COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES AIRWORTHINESS DIRECTIVE On the effective date specified below and for the reasons set out in the background section the CASA delegate whose signature appears below revokes Airworthiness Directive AD ELECT 4 Electrical Equipment AD ELECT 4 Magnetos BTH Earthing Modification 2 2009 Requirement CANCELLED This AD is cancelled on 12 February 2009 Background This unique Australian AD raised prior to 1964 required a modification to Magnetos BTH AG4 SG4 and MCI types with contact breaker covers to ensure positive connection of the magneto switch lead to the magneto earthing spring and bush assembly Compliance was before installation in an aircraft As all affected batteries would have been modified by now this AD is considered to be no longer required James Coyne Delegate of the Civil Aviation Safety Authority 23 December 2008 Page 1 of 1 COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES AIRWORTHINESS DIRECTIVE On the effective date specified below and for the reasons set out in the background section the CASA delegate whose signature appears below revokes Airworthiness Directive AD ELECT S Electrical Equipment AD ELECT 5 Magneto Impulse Starters Modi
3. 9 Make an appropriate engine log book entry recording magneto serial number to indicate that this AD and Bendix Service Bulletin No 623A have been complied with 10 Inspect all spare impulse coupling assemblies cam assemblies and magnetos following the same procedures described in Steps 3 and 4 of this Airworthiness Directive If both flyweights are found acceptable identify the cam assembly by applying yellow Dykem or yellow lacquer to the heel of each flyweight Stamp F on Data plate as described in Step 7 Note 1 The magneto should be removed from the engine only to the extent necessary to perform the inspection described herein Depending on the engine application it may not be necessary to remove the harness from the magneto for the inspection procedure Note 2 All magnetos with the impulse coupling recessed into the magneto flange must have the impulse coupling removed from the magneto to perform the inspection This is a bench operation and will require the magneto to be removed from the engine and the harness removed from the magneto Note 3 Whenever an impulse coupling is removed from a magneto it must be removed following manufacturer s published procedures paying strict attention to Notes and Conditions Follow manufacturers published procedures cautions and torque settings upon re assembly The cotter pin Bendix P N 10 90751 18 removed during disassembly must be discarded and replaced Note 4 FAA Emergency AD82 20 0 sp
4. Compliance For Para 1 Within 100 hours time in service after 31 March 1983 For Para 2 Within 200 hours time in service after 31 March 1983 Background To prevent false indication that emergency power is available COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 44 Slick Magnetos Bearing Inspection 2 87 Amdt 1 and Modification CANCELLED Background Bearing Requirements are now included in AD ELECT 46 COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES AIRWORTHINESS DIRECTIVE On the effective date specified below and for the reasons set out in the background section the CASA delegate whose signature appears below revokes Airworthiness Directive AD ELECT 45 Electrical Equipment AD ELECT 45 Aircraft Batteries Exide 2 2009 Type 6AC9 and 6AC11 Requirement CANCELLED This AD is cancelled on 12 February 2009 Background This unique Australian AD raised in 1984 required an inspection and replacement of Exide type 6AC9 and 6AC11 batteries with S nos 32659 to 33117 following the manufacturer issuing a recall notice due problems being experienced with epoxy resin used to seal them Compliance was 1 Inspect for leakage upon receipt of AD and thereafter at each Daily inspection until battery
5. after 18 April 1991 and those Magnetos with less than 700 hours TTIS prior to exceeding 800 hours TTIS As all affected magnetos would have been retired by now this AD is considered to be no longer required James Coyne Delegate of the Civil Aviation Safety Authority 23 December 2008 Page 1 of 1 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 19 Slick Magneto Impulse 11 70 Amdt 1 Coupling Replacement CANCELLED COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 20 Applicability Requirement Compliance Eisemann Magneto Coils 5 69 P N H27 958 Inspection and Replacement All Eisemann magnetos type AM 4 AM 6 LA 4 and LA 6 installed on but not necessarily limited to the following engines Continental A 50 A 65 A 75 A 80 C 75 C 85 C 115 C 125 E 165 and E 185 series Franklin Aircooled 2A4 4AC 4A4 6AC 6AL 6A8 6A4 6V4 6AG4 series Menasco C4 D4 D4 87 series Inspect coils P N H27 958 for a yellow inspection stamp consisting of a letter and numeral Remove from further service those coils bearing the following yellow stamps A76 B76 C76 D76 F76 G76 H76 J76 K76 L76 M76 D86 E86 F86 G86 H86 J86 K86 Instal
6. 001 Electrical Equipment AD ELECT 74 Amdt 1 continued Compliance Background NEW DRIESSEN LOGO OLERMER GERMANYO a E OLD LERMEN LOGO b t are pliera Fig 1 Lermer Water Boiler c if four or more electrical terminals are connected engrave adjacent to the equipment label Complies with AD F 2004 132 d if less than four electrical terminals are connected scrap the water boiler and install an airworthy one For Airbus aeroplanes embodiment of the following applicable SB is considered an acceptable mean of compliance for the requirements of this AD A300 25A0474 A300 25A6170 A330 25A3174 A310 25A2146 A320 25A1299 340 25A4192 Note 2 Direction G n rale de l Aviation Civile of France DGAC AD F 2004 132 refers The action set out in the Requirement section must be taken before 31 December 2004 The effective date of this AD is 5 May 2014 DGAC advised that an A330 aircraft made an in flight turn back due to overheat of a galley water boiler Page 2 of 3 COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 CASR 1998 CIVIL AVIATION SAFETY AUTHORITY Regulation 39 001 Electrical Equipment AD ELECT 74 Amdt 1 continued m Mike Higgins Investigations revealed that some of the Lermer water boilers listed above have a deficiency in the electrical circuit design In fact the overheat protector may be installed in serial with the relay control and in c
7. 10 15 30 and 40 Service Bulletin DC10 33 073 series aeroplanes listed in the effectivity 18 June 1996 statement of the service bulletin Heath Tecna McDonnell Douglas Model DC 8 series Alert Service Bulletin Mark I 33 A2 aeroplanes retrofitted with Heath Tecna Revision 1 Mark I interior 24 July 1996 COMMONWEALTH OF AUSTRALIA CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Compliance Background Heath Tecna Alert Service Bulletin Mark I 33 A3 Revision 1 24 July 1996 Heath Tecna Alert Service Bulletin Mark I 33 A4 Revision 1 Civil Aviation Regulations 1998 PART 39 107 Boeing Model 707 series aeroplanes retrofitted with Heath Tecna Mark I interior Boeing Model 727 series aeroplanes retrofitted with Heath Tecna Mark I interior 24 July 1996 Heath Tecna Alert Service Bulletin Mark I 33 A5 Revision 1 24 July 1996 Boeing Model 737 series aeroplanes retrofitted with Heath Tecna Mark I interior Heath Tecna Alert Service Bulletin Spmk 33 A1 Revision 1 24 July 1996 Boeing Model 727 series aeroplanes retrofitted with Heath Tecna Spacemaker II or Spacemaker Ia interior Heath Tecna Alert Service Bulletin Spmk 33 A2 Revision 1 24 July 1996 Boeing Model 737 series aeroplanes retrofitted with Heath Tecna Spacemaker II or Spacemaker Ia interior 3 No Day Ray fluorescent light ballast having a part number listed in the Applicability Statement of this Directive may be insta
8. As all affected aircraft would have been inspected and modified by now this AD is considered to be no longer required James Coyne Delegate of the Civil Aviation Safety Authority 23 December 2008 Page 1 of 1 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 17 Magneto Bendix Scintilla NK Distributor Block Inspection CANCELLED COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES AIRWORTHINESS DIRECTIVE On the effective date specified below and for the reasons set out in the background section the CASA delegate whose signature appears below revokes Airworthiness Directive AD ELECT 18 Amdt 3 Electrical Equipment AD ELECT 18 Slick 4000 4100 Series Sealed Non Repairable 2 2009 Amdt 3 Magnetos Retirement Life Requirement CANCELLED This AD is cancelled on 12 February 2009 Background This unique Australian AD raised in 1966 against Slick Service Bulletin SB No 2 80B required all Slick 4000 4100 series sealed non repairable magnetos to be retired from service due to the possibility of these magnetos being run beyond their designed life The AD did not apply to Slick 4200 series magnetos which can be overhauled Compliance was Magnetos with greater than 700 hours TTIS within 100 hours TIS
9. Background c The installation of a manually operated pump and retention of the Bob Fields Aerocessories STC provisions except that the electric system must be deactivated in accordance with Requirement 1 of this Directive noting that the design of the modification incorporating the pump must be approved by a person that either holds a delegation or an instrument of appointment under Regulation 35 of the Civil Aviation Regulations 1988 d Modify the electric door seal inflation system in accordance with the procedures in Bob Fields Accessories Service Bulletin No BFA 001 1 Remains unchanged as Before further flight 2 Remains unchanged as Before further flight 3 Remains unchanged as Before further flight 4 As of the effective date of this Amendment This Amendment becomes effective on 25 January 2001 The FAA has received numerous reports of occurrences of overheated components associated with the electric door seal inflation system on aircraft equipped with Bob Fields Aerocessories inflatable door seals installed in accordance with the applicable FAA STC One occurrence resulted in an in flight fire other occurrences have resulted in a the electric door seal pump being heavily charred b the pump assembly and resistors of the electric door seal pump being partially melted and c vinyl plastic and insulation material in the proximity of the electric door seal inflation system being found burned The original
10. Bulletin ASM 8 dated 30 May 1972 which was mandated by Amendment to this Directive has been supplemented by Service Bulletin ASM 9 dated 15 December 1972 The latter Service Bulletin provides more up to date information to ensure the correct part number fan and backing plate package is used COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 25 Slick Magneto Hub Impulse 2 98 Amdt 1 Coupling Replacement CANCELLED Background This AD previously mandated use of the manufacturers Service Bulletins which have now been incorporated into the magneto manufacturer s Service Manual COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES AIRWORTHINESS DIRECTIVE On the effective date specified below and for the reasons set out in the background section the CASA delegate whose signature appears below revokes Airworthiness Directive AD ELECT 26 Electrical Equipment AD ELECT 26 Nickel Cadmium Batteries Double D 2 2009 Washers Inspection and Removal Requirement CANCELLED This AD is cancelled on 12 February 2009 Background This unique Australian AD raised in 1973 required Sonotone or Marathon type CA 9 and MA 9 Nickel Cadmium Batteries to be inspected and modified to prevent the possibility of a short circu
11. Facsimile 1 813 522 5820 Alternately the documents may be viewed at the CASA Airworthiness Information Unit Alan Woods Building 25 Constitution Avenue Canberra ACT The original compliance was as specified in the Requirement Document with an effective date of 6 October 1990 This amendment is effective from 29 February 1996 Numerous incidents of smoke and fire have been reported on aircraft using SELA and ALC fluorescent lighting system components These incidents have been attributed to high voltage arcing or overheating of the lamp connector or remote power unit Action in accordance with this Directive is necessary in order to prevent smoke fire and possible electric shock or electromagnetic interference to flight critical or essential systems This amendment is issued following the issue of AD ELECT 67 which addresses fluorescent lighting components manufactured by ALC No changes other than minor editorial changes and the removal of references to ALC components in the Requirement Statement have been made in this amendment COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AIRWORTHINESS DIRECTIVE For the reasons set out in the background section the CASA delegate whose signature appears below revokes Airworthiness Directive AD AD ELECT S7 and issues the following AD under subregulation 39 1 1 of CAR 1998
12. OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 63 TCM Bendix Magneto Capacitor 9 94 Amdt 1 Applicability 1 Teledyne Continental Motors TCM Ignition Systems formerly Bendix new or rebuilt magnetos Models SC 20 SC 200 and S 1200 Part Number Series 10 S500XXX X 10 600XXX X and 10 349XXX X respectively with Manufacturing Serial Numbers J2793XXX R through J3193XXX R KO193XXX R through K3093XXX R and LO193XXX R through L2293XXX R inclusive 2 All TCM or Bendix Model SC 20 SC 200 and S1200 magnetos regardless of Manufacturing Serial Number that have been fitted with a replacement capacitor Part Number 10 349276 subsequent to 27 October 1993 Note The X in the part and serial numbers represents numbers that have no significance in determining applicability only the first five digits are needed The R at the end of the manufacturing serial number indicates a rebuilt magneto while the absence of the R indicates a new magneto Requirement Action in accordance with Teledyne Continental Ignition Systems Critical Service Bulletin CSB641 dated 1 February 1994 Note FAA Priority letter AD 94 06 09 refers Compliance The compliance for the original issue of this Directive was within ten hours time in service after 25 March 1994 The compliance for this amendment is unless pr
13. The AD requires that the action set out in the requirement section being action that the delegate considers necessary to correct the unsafe condition be taken in relation to the aircraft or aeronautical product mentioned in the applicability section a in the circumstances mentioned in the requirement section and b in accordance with the instructions set out in the requirement section and c at the time mentioned in the compliance section AD ELECT 57 Landing Gear Dunlop Fan 11 2001 Amdt 1 and Transducer Installation Applicability Dunlop Fan and Transducer Installation Part Numbers AHA1578 AHA1684 AND AHA1685 Note 1 Aircraft known to be fitted with these Fan and Transducer installations include but are not limited to BAe 146 aircraft Requirement Replace the fan and transducer installation in accordance with Dunlop Limited Aviation Division Service Bulletin SB 32 1039 Note 2 Incorporation of Modification C2640 in accordance with Dunlop Limited Aviation Division SB AHA 1684 AHA 1685 32 1047 dated 19 September 1990 in BAe 146 aircraft is considered terminating action for this Directive for those aircraft Note 3 Compliance with this Service Bulletin has been classified mandatory by the UK CAA Compliance Remains unchanged as Initially prior to 28 February 1991 and thereafter at intervals not exceeding 1500 landings Operators with positive records of both transducer drive shaft and splined drive replacement may al
14. You may review a copy of the service information at the FAA Office of the Regional Counsel Southwest Region 2601 Meacham Blvd Room 663 Fort Worth Texas 76137 6 5 You may also review a copy of this service information that is incorporated by reference at the National Archives and Records Administration NARA For information on the availability of this material at NARA call 202 741 6030 or go to http www archives gov federal register cfr ibr locations html Issued in Fort Worth Texas on April 26 2013 Kim Smith Directorate Manager Rotorcraft Directorate Aircraft Certification Service
15. assembly P No 3E1883 2 fitted to Hartzell HC B3TN and HC B4TN series propellers Compliance was prior to issue of the next maintenance release after 31 January 1986 As all affected terminal clamp assemblies would have been inspected by now this AD is considered to be no longer required James Coyne Delegate of the Civil Aviation Safety Authority 23 December 2008 Page 1 of 1 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 48 Mechanical Products Inc Circuit Breakers 9 89 Amdt 3 Applicability 1 Mechanical Products Inc circuit breakers as follows Series Part No Military Rating Amps Manufacturers Designator Date Code 4001 MS22073 1 thru 5 8501 thru 8636 4200 MS26574 0 5 thru 5 8430 thru 8636 4310 0001 and 4310 019 MS3320 1 thru 5 8605 thru 8636 8500 Nil 1 thru 5 8514 thru 8636 2 Mechanical Products Inc circuit breakers commercialised by E C E Co as follows Mechanical Products Equivalent ECE Rating Amps Manufacturers Series P N Reference No Date Code 4001 001 120DU0 1 1 thru 5 8501 thru 8636 4001 004 124DU0 1 1 thru 5 8501 thru 8636 4001 007 125DUO1 1 thru 5 8501 thru 8636 4310 001 170 171 DU01 1 thru 5 8605 thru 8636 Note 1 may be any digit in the range 1 thru 5 may be any three digits in the range 010 thru 050 Note 2 The first two digit
16. be fitted with S E L A Laboratoire Abadie fluorescent lighting systems include but are not limited to AMD BA Falcon 10 20 50 900 BAe Jetstream 3101 and 3201 CASA 235 Embraer EMB 120 and SAAB Scania SF340A aircraft Note 2 Fluorescent lighting system components manufactured by SELA and those manufactured by Aerospace Lighting Corporation ALC are very similar in size shape colour and part number however they may be identified by trademark The SELA RPU can be identified by a starburst pattern incorporating the text laboratoire abadie France The ALC RPU can be identified by a stylised ALC logo with Aerospace Lighting Corp in smaller print beneath the logo The SELA lamp connector is only stamped in yellow ink The ALC lamp connector has ALC moulded into the body of the conical piece of the connector The ALC lamp can be positively identified by the presence of a small hole in the locking channel of each blue plastic end piece Action in accordance with United States Federal Aviation Administration FAA AD 90 07 08 Revision 1 Operators of affected aircraft who elect to comply with para a of the FAA AD are required to have an Australian Flight Manual amendment specifying the required action In lieu of inserting a copy of the FAA AD in the Flight Manual operators intending to take this course of action must prepare and submit a suitable flight manual amendment to their local Civil Aviation Safety Authority CASA Distric
17. previous issues of this Directive a Fabricate a placard that incorporates the following words utilising letters that are at least 2 5mm 0 1 inches in height and install the placard on the instrument panel within the pilot s clear view ELECTRIC DOOR SEAL INFLATION SYSTEM INOPERATIVE Add the following statement to the Limitations section of the Flight Manual ELECTRIC DOOR SEAL INFLATION SYSTEM INOPERATIVE This task may be accomplished by inserting a copy of this Airworthiness Directive into the Limitations section of the Flight Manual 3 For pressurised aircraft or for aircraft that do not have an operating manual door seal inflation system unless already accomplished in accordance with previous issues of this Directive COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES a Fabricate a placard that incorporates the following words utilising letters that are at least 2 5mm 0 1 inches in height and install the placard on the instrument panel within the pilot s clear view ELECTRIC DOOR SEAL INFLATION SYSTEM INOPERATIVE THIS AIRCRAFT CAN ONLY BE OPERATED IN UNPRESSURISED FLIGHT b Add the following statement to the Limitations section of the Flight Manual ELECTRIC DOOR SEAL INFLATION SYSTEM INOPERATIVE THIS AIRCRAFT CAN ONLY BE OPERATED IN UNPRESSURISED FLIGHT This task may be accomplished by inse
18. replaced and 2 Replace battery upon detecting a cracked battery or within 50 hours TIS after 30 June 1984 if battery found serviceable after compliance with Para 1 As all affected batteries would have been replaced by now this AD is considered to be no longer required James Coyne Delegate of the Civil Aviation Safety Authority 23 December 2008 Page 1 of 1 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 46 Slick Magnetos 2 98 Amdt 6 CANCELLED Background This AD previously mandated use of the manufacturers Service Bulletins which have now been incorporated into the magneto manufacturer s Service Manual COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES AIRWORTHINESS DIRECTIVE On the effective date specified below and for the reasons set out in the background section the CASA delegate whose signature appears below revokes Airworthiness Directive AD ELECT 47 Electrical Equipment AD ELECT 47 Propeller De lce Terminal Clamp Assembly 2 2009 Requirement CANCELLED This AD is cancelled on 12 February 2009 Background This unique Australian AD raised in1986 against B F Goodrich Service Bulletin SB No E 85 71 required an inspection for cracks of the propeller de icer terminal clamp
19. 0 PA 28S 160 PA 28S 180 PA 28R 180 PA 28R 200 PA 28R 201 PA 28R 201T PA 28RT 201 and PA 28RT 201T SA4237WE Piper Models PA 23 PA 23 160 PA 23 235 PA 23 250 and PA E23 250 SA4238WE Piper Models PA 30 PA 39 and PA 40 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES SA4385WP Piper Models PA 31 PA 31 300 PA 31 325 and PA 31 350 SA4288WE Piper Models PA 32 260 PA 32 300 PA 32S 300 PA 32 301 PA 32 301T PA 32R 300 PA 32R 301 PA 32R 301T PA 32RT 300 and PA 32RT 300T SA2511NM Bellanca Models 17 30 17 31 and 17 31TC SA2510NM Bellanca Models 17 30A 17 31A and 17 31ATC SA4316WE Wing Aircraft Company Model D 1 Requirement 1 Unless already accomplished in accordance with previous issues of this Directive deactivate the electric door seal inflation system by accomplishing the following a b d Disconnect the battery Locate the air pump and identify the power wire to the air pump Trace the power wire to its connection to the aircraft s original electrical power system Disconnect the power wire at its attachment to the aircraft s electrical power system and stow the wire end Reconnect the battery before returning the aircraft to service 2 For non pressurised aircraft or for aircraft that have an operating manual door seal inflation system unless already accomplished in accordance with
20. 0 0049999 October 1978 November 1978 December 1978 January 1979 February 1979 March 1979 April 1979 May 1979 June 1979 July 1979 August 1979 September 1979 October 1979 November 1979 December 1979 January 1980 February 1980 March 1980 April 1980 The above magneto models are installed on but not limited to the following engines A 65 A 75 C 75 C 85 Teledyne Continental C 90 O 200 10 360 TSIO 360 Lycoming O 470 10 470 10 520 TSIO 520 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Document Compliance Background 0 235 H2C 0 320 E1J 0 360 C1E 0 235 K2C 0 320 E2D 0 360 C1F 0 235 L2C 0 320 E2G 0 360 C2E 0 320 A2D 0 320 E3D 0 360 F1A6 0 320 D1D AEI0 320 E1B AEI0 360 B 1G6 0 320 D2G AEI0 320 E2B AEI0 360 H1A 0 320 D2J 0 360 A4K 0 320 D3G 0 360 A4M Slick SB1 81 Lycoming SB457A Cessna SIL SE81 30 and FAA AD 81 16 05 also refer Within the next 100 hours time in service after 30 November 1981 The manufacturer has indicated that a situation exists in a certain group of coils that could facilitate cracking of the coil potting compound and a subsequent shorting failure The above group include coils which have already failed in service both in Australia and overseas COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDUL
21. 000 64755 E33 4 010SB dated 20 October 2000 62197 001 001 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Compliance Background E33 4 011SB dated 21 October 2000 64753 001 003 E33 4 012SB dated 24 October 2000 64763 201 003 E33 4 013SB dated 23 October 2000 64769 001 005 64769 001 007 E33 4 014SB Revision 1 dated 6 November 2000 64771 001 001 E33 4 015SB dated 23 October 2000 64790 1 E33 4 016SB Revision 1 dated 6 November 2000 64771 001 003 3 Replace the affected wires in accordance with the applicable SB listed above Note 2 Luftfahrt Bundesamt LBA Germany AD 2000 379 refers For Requirement Within 50 hours time in service after the effective date of this Directive For Requirement 2 Before further flight For Requirement 3 At the next C of the aircraft on which the equipment is installed This Airworthiness Directive becomes effective on 25 January 2001 The equipment manufacturer has advised the LBA that the crimping of the present thermal limiter Faston Terminals P N 3 520133 2 may be insufficient for the current carried through those terminals This condition could cause an increased resistance in the terminal resulting in an increased temperature of the terminal and or melting of the terminal insulation This Directive requires an initial inspection of the terminals to detect any damage and if nece
22. 05 7274 55 1 1 2 8500 002 105 8500 005 2 7274 55 2 8500 002 2 8500 005 3 7274 55 3 8500 002 3 8500 005 5 7274 55 5 8500 002 5 Compliance For Mechanical Products Inc circuit breakers within 100 hours time in service after 31 May 1987 For Mechanical Products Inc circuit breakers commercialised by E C E Co within 100 hours time in service after 10 August 1989 Background 1 Mechanical Products Inc have advised that a quantity of circuit breakers have been shipped which may be improperly manufactured An internal contact carrier may rotate within these units which may create an electrical shock hazard or cause the circuit breaker to not fulfil its protection function 2 Amendment 2 to this Directive is issued to include Mechanical Products Inc circuit breakers commercialised by E C E Co 3 Amendment 3 to this AD is issued to e clarify the applicable series of ECE commercialised circuit breakers e provide additional information to aid in identifying ECE commercialised circuit breakers e revise the compliance date for ECE commercialised circuit breakers and e clarify which Mechanical Products circuit breakers in the 4310 series are affected COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 49 Bendix Magneto Distributor Block 8 95 CANCELLED Background Teledyne Continental Ignition System
23. 40 HIO 540 IO 540 0 540 and TIO 540 series engines are known to be installed on but not limited to aircraft manufactured by the Cessna Aircraft Company Maule Aerospace Technology Corporation Mooney Aircraft Corporation The New Piper Aircraft Inc and Raytheon Aircraft Company Formerly Beech Aircraft Company Requirement 1 Inspect the impulse coupling assembly for wear using paragraphs 1 2 through 1 4 5 of the Detailed Instructions of TCM MSB645 Page 1 of 4 COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 75 Amdt 1 continued Installing a Shower of Sparks ignition system in place of a magneto system that has a riveted impulse coupling assembly or a snap ring impulse coupling assembly is optional terminating action for the repetitive inspection requirements More information on installing a Shower of Sparks ignition system may be found in TCM Service Information Letter SIL648 dated 18 October 1994 2 Replace any impulse coupling assembly that fails the inspection with a serviceable riveted or snap ring impulse coupling assembly Paragraphs 2 through 2 6 of the Detailed Instructions of TCM MSB645 and TCM Service Bulletin 639 dated March 1993 contain information on replacing the impulse coupling assembly 3 Ifasnap ring impulse coupling assembly is replaced with a riveted impulse coupling ass
24. 601 CL 601 3A and 3R Cessna 550 and 560 Dassault Aviation Mystere Falcon 20 and 50 Embraer EMB 120 Gulfstream G 159 G 1159 G 1159A and G IV Israel Aircraft Industries 1124 and 1125 Jetstream 3100 Learjet 35 and 36 Saab SF 340A Sikorsky S 76A COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Requirement Compliance Background Note 2 The following information is provided as an aid to the identification of fluorescent lighting system components manufactured by ALC Components manufactured by ALC and those manufactured by SELA Laboratoire Abadie SELA are very similar in size shape colour and part number however they may be identified by trademark The ALC power unit can be identified by a stylised ALC logo with Aerospace Lighting Corp in smaller print beneath the logo while the SELA power unit can be identified by a starburst pattern incorporating the text laboratoire abadie France The ALC lamp connector has ALC moulded into the body of the conical piece of the connector while the SELA lamp connector is only stamped in yellow ink The ALC lamp can be positively identified by the presence of a small hole in the locking channel of each blue plastic end piece 1 Inspect the cabin fluorescent lighting system in accordance with ALC Information Bulletin IB 90 001 dated 15 August 1992 Part IV Fluorescent Lighting Syste
25. 9000203 33 20 01 is considered an approved equivalent modification Prior to 26 February 1989 Instances have occurred where the fuse and thermal protector currently provided within the ballast have failed to protect the ballast from failure This has resulted in the emission of smoke and flames from the ballast COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 53 Bendix Magneto Clear Case Coils 12 94 Amdt 2 CANCELLED Background The actions required by this Directive are now addressed in AD ELECT 66 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 54 Sealed Lead Acid Aircraft Batteries 7 90 Applicability All installed Gates Varley Tungstone Energy Products Hawker Energy Products sealed lead acid batteries listed below 18 AH batteries with the following 25 AH batteries with the following product numbers product numbers 9750 0730 9750 0734 9750 0738 9750 0640 9750 0650 9750 0740 9750 0742 9750 0744 9750 0658 9750 0660 9750 0772 9750 0750 9750 0781 Note 1 Aircraft known to have batteries of this type fitted include but are not limited to BAe 125 Series Shorts Skyvan Series and BAe Jetstream series Note 2 Gates Varley SB M1 89 Issue 2 made mandatory by CA
26. A UK also refers Requirement Remove from the aircraft and carry out a capacity test in accordance with the aircraft maintenance manual or other approved procedure Compliance 1 18 AH batteries in the serial number range A1810 to A7637 and 25 AH batteries in the serial number range B0095 to CO 575 initially 6 months after initial installation in an aircraft and thereafter at intervals not exceeding 3 months 2 18 AH batteries with serial numbers below A1810 and above A7637 and 25 AH batteries with serial numbers below B0095 and above CO 575 initially 6 months after initial installation then after a further 6 months and thereafter at intervals not exceeding 3 months Background Affected batteries have been found to exhibit an unexpected loss of capacity which reduces the time for which the battery can power emergency services in the event of a power failure COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 55 Texas Instruments Circuit Breakers 8 93 Amdt 2 Applicability Texas Instruments three phase circuit breakers models 6TC6 7 5 6TC6 10 6TC20 Requirement Compliance Background 7 5 and 6TC20 10 date coded 8150 or earlier Note Aircraft known to have these circuit breakers installed include but are not limited to aircraft manufactured by Boeing Commercial Airplanes and Lockheed
27. Amdt 39 8955 refers 1 Prior to 15 September 1995 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES 2 Prior to further flight 3 With effect 15 September 1994 Background The FAA received a report of injuries to cabin crew members that resulted from an explosion of a galley water heater caused by the failure of the pressure relief valve Although that heater was fitted with an integral check valve the FAA has determined that the possibility exists for the pressure relief valve to fail in other water heaters or coffee makers without the integral check valve Compliance with this Directive will decrease the likelihood of galley water heaters and coffee makers exploding causing either injuries to passengers and crew or structural damage to the aircraft COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 65 Marathon Power Technologies 10 94 Applicability Requirement Compliance Background PC 250 Static Inverter Marathon Power Technologies PC 250 series static inverters where installed to provide a source of emergency or standby electrical power Note These inverters are known to be installed in but not limited to the following aircraft models Hawker 800 and BAe 125 Series 800 prior to Cons
28. COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 1 Relay Leach Modification 2 98 CANCELLED Background No longer required COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 2 Ignition Switches Briggs and Stratton Inspection 10 69 CANCELLED COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 3 Circuit Breakers Inspection 2 86 CANCELLED Background Experience with circuit breaker testing has revealed that the testing has proved to be overly conservative does not improve reliability of breakers and may introduce other faults in aircraft wiring Moreover wiring and circuit breaker reliability is such that incidents due to circuit breakers failing to operate under overload conditions and causing wiring damage smoke fire are Extremely Improbable There is some evidence to suggest that circuit breakers should be manually where possible operated periodically however the evidence does not justify requiring periodic operation Future requirements for testing will be restricted to specific breaker types shown to be or suspected of being unreliable
29. Corporation If not previously accomplished inspect the circuit breakers listed above to determine the date code If the date code is 8150 or earlier replace the circuit breaker Note FAA AD 90 09 10 Boeing SBs 747 24 2135 757 24 0054 767 24 0060 and Lockheed SB 093 24 134 refer The Compliance for the previous issue of this Directive was prior to 12 November 1990 Compliance for this issue is prior to 22 October 1993 Some aircraft have experienced inflight fires which have been attributed to overheating of Texas Instruments circuit breakers Compliance with this AD is considered necessary to prevent potential overheating of these affected circuit breakers which could result in an onboard fire Amendment to this Directive was issued to correct a typographical error only Amendment 2 is issued to correct errors in the reference documentation and to clarify the requirement COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 56 Cabin Fluorescent Lighting System Components 3 96 Amdt 1 Applicability Requirement 1 Fluorescent lighting system lamp connectors P No 3185 1A manufactured by S E L A Laboratoire Abadie 2 Fluorescent lighting system remote power units RPU P No TR992 TR992A TR992 1 TR992 3 TR992 4 and TR992 5 manufactured by S E L A Laboratoire Abadie Note 1 Aircraft known to
30. E OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 41 Bendix Distributor Gear 2 98 Electrode Inspection Replacement CANCELLED Background This AD previously mandated use of the manufacturers Service Bulletins which have now been incorporated into the magneto manufacturer s Service Manual COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 42 Bendix Impulse Couplings 1 86 Amdt 1 Applicability All Bendix Magnetos with type designations as follows Requirement S4LN 21 1225 1227 S4 RN 21 1225 1227 S6LN 21 23 25 1225 1227 S6RN 21 23 25 1225 1227 S4LN 200 P N 10 163005 7 D 2021 2031 All D 3000 except Bendix Blue Label Impulse Coupled Magnetos Serial Number 8236001 and above and except Bendix Red Label Impulse Coupled Magnetos with the following Serial Numbers and above S 20 Series B 001171 or A297043 S 200 Series B 001732 or A297043 S 1200 Series B 001162 or A297043 D 2000 Series 35550 D 3000 Series B 000249 or 5806 Bendix Service Bulletin No 623 A and FAA AD 82 20 0 refer For all affected impulse couplings having less than 300 operating hours 1 Remove magneto from the engine in accordance with engine aircraft manufacturers published instructions 2 Place the magneto in a suitable work stand with the impulse coupling facing up 3 Use finger pressure to push inward on
31. Electrical Equipment AD ELECT 9 Magneto Bendix Scintilla Lubrication 8 72 CANCELLED COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 10 Magneto Bendix Scintilla Lubrication 8 72 Amdt 1 and Modification CANCELLED COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES AIRWORTHINESS DIRECTIVE On the effective date specified below and for the reasons set out in the background section the CASA delegate whose signature appears below revokes Airworthiness Directive AD AD ELECT 1 1 and issues the following AD under subregulation 39 001 1 of CASR 1998 The AD requires that the action set out in the requirement section being action that the delegate considers necessary to correct the unsafe condition be taken in relation to the aircraft or aeronautical product mentioned in the applicability section a in the circumstances mentioned in the requirement section and b in accordance with the instructions set out in the requirement section and c at the time mentioned in the compliance section Electrical Equipment AD ELECT 11 Leach Relays Control Terminal Insulation 2 2009 Amdt 1 Applicability Applicability All Leach type 5038 5039 5058 5059 5060 5061 relays Requirement Modify relays by increasi
32. INESS DIRECTIVES Electrical Equipment AD ELECT 37 JET Electronics and Technology Inc 12 85 Amdt 2 Standby Power Supply Modification Applicability Al J E T PS 823 Models Requirement If the modification number listed below has been marked off then no further action is required in this part JET Part No Model Modification No 501 1075 01 PS 823A 18 501 1975 02 PS 823B 17 501 1075 03 PS 823C 15 501 1075 04 PS 823D 14 501 1075 05 PS 823A T 21 501 1075 06 PS 823B T 19 501 1075 07 PS 823C T 17 501 1075 07 PS 823D T 16 If the applicable modification number has not been marked off install modifications in accordance with JET SB No SB501 1075 16F Compliance Within 100 hours time in service after 28 February 1981 Background Part 2 of this Directive is cancelled following reassessment after discussion with manufacturer JET who advised of factors not available at time of issue of Amendment 1 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 38 Bendix Distributor Gear 8 81 Applicability Document Compliance Background Electrode Inspection Replacement All D 3200 Series pressurised blue magnetos with S Nos 100 thru 1422 installed on Avco Lycoming TIO 540 J2BD used on Piper PA31 350 and LTIO 540 J2BD used on STC SA1151SO and STC SA970SO Colemill conversion of PA31 PA31 325 and PA31 350
33. July 1991 or serviced since January 1990 Note The water heaters and coffee makers are known to be installed in but not limited to the following aircraft series Airbus Industrie Model A300 A310 and A320 Boeing Model 727 737 747 757 and 767 Canadair Model CL 600 1A11 CL 600 2A12 CL 600 2B16 and CL 600 2B19 Dassault Aviation Model Mystere Falcon Model 50 200 and 900 de Havilland Model DHC 8 Fokker Model F27 and F28 Gulfstream Model G 1159 and G IV Lockheed L 1011 and McDonnell Douglas Model DC 9 DC 9 80 DC 10 and MD 11 1 Perform a one time inspection of the water heater or coffee maker in accordance with Nordskog Industries Service Bulletin SB 93 35 to determine if a NUPRO pressure relief valve having part number SS 2C4 65 has been installed 2 Ifa NUPRO pressure relief valve part number SS 2C4 65 has been installed then either a replace the pressure relief valve with a new improved NUPRO pressure relief valve part number SS CHF2 65 or b deactivate the water heater or coffee maker and install a placard stating Not to be used 3 NUPRO pressure relief valves part number SS 2C4 65 held as spares are not to be fitted to water heaters or coffee makers identified in Nordskog Industries Service Bulletin SB 93 35 and these water heaters or coffee makers are not to be fitted to an aircraft as replacement items if a NUPRO pressure relief valve part number SS 2C4 65 is installed Note FAA AD 94 14 03
34. NWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 30 Bendix Magneto Coil Retainer Plug Inspection 2 98 Amdt 2 CANCELLED Background This AD previously mandated use of the manufacturers Service Bulletins which have now been incorporated into the magneto manufacturer s Service Manual COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 31 Bendix Magneto Capacitor 2 98 Malfunction Inspection CANCELLED Background This AD previously mandated use of the manufacturers Service Bulletins which have now been incorporated into the magneto manufacturer s Service Manual COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 32 Superseded 3 80 Amdt 1 Superseded by AD ELECT 35 Amdt 1 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 33 Bendix Magneto Rear Bearing 2 98 Overheating Inspection CANCELLED Background This AD previously mandated use of the manufacturers Service Bulletins which have now been incorporated into the magneto manufacture
35. R part 91 subpart K we suggest that you notify your principal inspector or lacking a principal inspector the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC g Additional Information The subject of this AD is addressed in European Aviation Safety Agency EASA AD No 2010 0237R2 dated December 14 2010 h Subject Joint Aircraft Service Component JASC Code 3340 Exterior lighting i Material Incorporated by Reference 1 The Director of the Federal Register approved the incorporation by reference of the following service information under 5 U S C 552 a and 1 CFR part 51 2 You must use this information as applicable to do the actions required by this AD unless the AD specifies otherwise i Nightsun XP Searchlight Safety and Service Bulletin No SL 0810 01 Amendment No 2 dated September 24 2010 ii Nightsun XP Searchlight System Kit and Procedure to Incorporate EASA AD 2010 0183 Conformance 034374 Revision NC dated September 28 2010 The date of this document is identified only in the Change Record on page 2 of this service information 3 For Spectrolab Nightsun XP Searchlight service information identified in this AD contact Spectrolab Inc ATTN Saul Vargas 12500 Gladstone Ave Sylmar CA 91342 telephone 818 365 4611 fax 818 361 5102 or on the internet at http www spectrolab com 4
36. STC 980NW Machen Industries conversion of Piper Aerostar 600 STC SA762 NW Machen Industries conversion of Beechcraft Bonanza B35 and A36 series Bendix SB No 618 Note FAA AD 81 12 06 Within 100 hours time in service after 31 August 1981 and thereafter at intervals not exceeding 100 hours time in service if gears pass inspection and are not replaced by serviceable gears The distributor gear electrode has come loose in service on a number of D 3200 series magnetos overseas If this condition exists the distributor gear electrode may contact the distributor block stationary electrodes causing contamination in the distributor Engine misfiring could result from the subsequent arcing within the distributor This in turn could result in rough engine operation cylinder or engine damage COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 39 Bendix Starting Vibrator Inspection and 11 81 Modification Applicability All starting vibrators with P Nos 10 176485 121 10 176485 122 10 176485 241 10 176485 242 10 382780 12 and 10 38270 24 having a manufacturing date of 901 thru 101 or 8010 thru 8101 permanently stamped on the vibrator These vibrators are installed in but not limited to the following aircraft powered by reciprocating engines Bell Textron Model 47 series helicopters Brantley Hynes Model B2 series
37. Searchlight System A through D 033338 3 Nightsun XP Searchlight System A through D 033338 4 Nightsun XP Searchlight System A through D 033704 IFCO Nightsun XP Searchlight System A through C 033704 1 IFCO Nightsun XP Searchlight System A through C b Unsafe Condition This AD defines the unsafe condition as the Searchlight Gimbal disconnecting from the helicopter and remaining attached solely by the internal cable harness or separating totally This condition could result in damage to the helicopter and injury to persons on the ground c Effective Date This AD becomes effective June 20 2013 d Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time e Required Actions 1 Before further flight insert a copy of Nightsun XP Searchlight Safety and Service Bulletin No SL 0810 01 Amendment No 2 dated September 24 2010 into the Normal Procedures section of the Rotorcraft Flight Manual 2 Before the first flight of each day visually check the searchlight installation for a gap between the top shroud rubber edging P N 033381 and the side covers P N 033286 with slight 5 pressure applied to either side of the searchlight The edging must remain in physical contact with the side covers when slight pressure is applied to the searchlight 3 The actions required by paragraph e 2 of this AD may be perfor
38. aised in 1964 required all Bendix starters type 756 fitted to aircraft where the starter is necessary for propeller unfeathering and to be modified by replacing all planetary pinions P N 46916 with pinions P N 644718 and identifying with a P painted in red adjacent to the starter nameplate Compliance was before 31 March 1965 As all affected aircraft would have been modified by now this AD is considered to be no longer required James Coyne Delegate of the Civil Aviation Safety Authority 23 December 2008 Page 1 of 1 COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES AIRWORTHINESS DIRECTIVE On the effective date specified below and for the reasons set out in the background section the CASA delegate whose signature appears below revokes Airworthiness Directive AD ELECT 16 Electrical Equipment AD ELECT 16 Magneto Bendix Scintilla 2 2009 Distributor Gear Inspection Requirement CANCELLED This AD is cancelled on 12 February 2009 Background This unique Australian AD raised in 1966 against Bendix Scintilla Service Bulletin SB No 510 required all S600 series Bendix Scintilla magnetos fitted with distributor gears P N 10 357060 or 10 357060A to be inspected until modified by incorporation of gears P N 10 357060B Compliance was at intervals not exceeding 100 hours TIS until incorporation of gears P N 10 357060B
39. ames Coyne Delegate of the Civil Aviation Safety Authority 23 December 2008 Page 1 of 1 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 13 Magneto BTH Slow Speed Wheel Inspection 2 74 Amdt 2 Applicability BTH Type AG4 Requirement Thoroughly inspect the teeth of the CX133241 1 Slow Speed Wheel for cracks or damage using at least a X5 magnifying glass Remove from service any defective Slow Speed Wheels Compliance Before installation in an aircraft following each reconditioning completed after 28 February 1974 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 14 Magneto Bendix Scintilla Inspection NK CANCELLED COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES AIRWORTHINESS DIRECTIVE On the effective date specified below and for the reasons set out in the background section the CASA delegate whose signature appears below revokes Airworthiness Directive AD ELECT 15 Electrical Equipment AD ELECT 15 Engine Starter Bendix Modification 2 2009 Requirement CANCELLED This AD is cancelled on 12 February 2009 Background This unique Australian AD r
40. ase of relay contact sticking the continuous source of power to the heating element cannot be cut This situation may lead to the emission of a burning smell together with smoke and possible injury to the aeroplane s occupants In response to this situation CASA issued AD ELECT 74 dated 5 August 2004 to require the inspection of applicable water boilers Water boilers with overheat protection having less than 4 electrical terminals are discarded those with 4 or more electrical terminals are marked as having been inspected and returned to service CASA issued AD ELECT 74 Amdt 1 to correct a typographical error in the DGAC AD number referenced in Note 2 of this AD There are no changes to the technical requirements of the AD and the dates for compliance remain unchanged Delegate of the Civil Aviation Safety Authority 28 April 2014 Page 3 of 3 COMMONWEALTH OF AUSTRALIA CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Civil Aviation Safety Regulations 1998 PART 39 107 AIRWORTHINESS DIRECTIVE On the effective date specified below and for the reasons set out in the background section the CASA delegate whose signature appears below revokes Airworthiness Directive AD AD ELECT 75 and issues the following AD under subregulation 39 001 1 of CASR 1998 The AD requires that the action set out in the requirement section being action that the delegate considers necessary to correct the unsafe condition be taken in
41. b Inc ATTN Saul Vargas 12500 Gladstone Ave Sylmar CA 91342 telephone 818 365 4611 fax 818 361 5102 or on the internet at http www spectrolab com You may review the referenced service information at the FAA Office of the Regional Counsel Southwest Region 2601 Meacham Blvd Room 663 Fort Worth Texas 76137 Examining the AD Docket You may examine the AD docket on the Internet at http www regulations gov or in person at the Docket Operations Office between 9 a m and 5 p m Monday through Friday except Federal holidays The AD docket contains this AD any incorporated by reference service information the economic evaluation any comments received and other information The street address for the Docket Operations Office phone 800 647 5527 is U S Department of Transportation Docket Operations Office M 30 West Building Ground Floor Room W12 140 1200 New Jersey Avenue SE Washington DC 20590 FOR FURTHER INFORMATION CONTACT Matt Fuller Senior Aviation Safety Engineer Safety Management Group Rotorcraft Directorate FAA 2601 Meacham Blvd Fort Worth Texas 76137 telephone 817 222 5110 email matthew fuller faa gov SUPPLEMENTARY INFORMATION Discussion On March 8 2012 at 77 FR 13993 the Federal Register published our notice of proposed rulemaking NPRM which proposed to amend 14 CFR part 39 to include an AD that would apply to certain Spectrolab Nightsun XP Searchlights The NPRM proposed to requir
42. bH previously Lermer water boilers with any of the following a Part Number L13471 L13471 05 L13471 11 or L13471 19 b Type Number 1010099 6 1010099 10 1010099 6 1 or 1010099 6 2 However this AD does not apply to water boilers that have been engraved with either a one of the following Airbus Service Bulletin SB numbers A300 25A0474 A310 25A2146 A300 25A6170 A320 25A1299 A330 25A3174 A340 25A4192 or b the words Complies with AD F 2004 132 Note 1 These water boilers are known to be installed on but not limited to Airbus A300 A310 A300 600 A318 A319 A320 A321 A330 and A340 series aeroplanes Requirement Get access to the water boiler in accordance with the applicable aircraft maintenance manual and identify the water boiler If a water boiler bears one of the following Lermer Part Numbers or Type Numbers a Part Number L13471 L13471 05 L13471 11 or L13471 19 b Type Number 1010099 6 1010099 10 1010099 6 1 or 1010099 6 2 carry out the following a check the logo on the identification plate at the rear side of the water boiler see fig 1 If the new DRIESSEN logo exists no further action is required b if the old Lermer logo exists inspect the overheat protection of the water boiler in accordance with Lermer GmbH CMM 25 30 31 page block 300 Page of 3 COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 CASR 1998 CIVIL AVIATION SAFETY AUTHORITY Regulation 39
43. celled Reports are still being received of clear case coils being identified during magneto servicing compliance with this Directive whilst ensuring that all coils of this type are finally removed from Australian aircraft will also ensure that older style rotating magnets are removed This amendment is issued to clarify the applicability statement and reflects the issue of a revision to the FAA Airworthiness Directive no further action is required if magnetos are in compliance with the original issue of this Directive COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 67 Aerospace Lighting Corporation Cabin 3 96 Fluorescent Lighting System Components Applicability This Directive is applicable to the following Aerospace Lighting Corporation ALC products Lamp Connectors part number P N 31 85 1 A Series 66 fluorescent lamps Power Units P N TR 991 TR 992 AL 0546 and AL 0514 and Power Supplies P N 18 95D and AL 0598 Note 1 These products are utilised in cabin fluorescent lighting systems and are known to be installed on but not limited to the following aircraft series Airbus Industrie A310 Avion Marcel Dassault Aviation Falcon 10 Boeing 727 737 747 and 757 Raytheon Corporate Jets formerly BAe HS 125 600 700 800 and 1000 Bombardier Canadair CL 600 IA11 2A12 2B16 2B19 CL
44. ch may be fitted with this battery include but are not limited to Cessna 650 Requirement Action in accordance with SAFT SB 0005 FAA Telex AD T85 03 51 also refers Compliance 1 For batteries installed in aircraft before further flight after 20 October 1988 2 For uninstalled batteries before installation in an aircraft Background Inspection of SAFT 40 AH Type 40976 batteries has revealed that the battery cell terminals can penetrate the rubber insulation under the lid and short circuit to ground thus potentially resulting in fire and or loss of battery power Amendment to this Directive is issued to clarify the Compliance date COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 52 Bruce Industries Fluorescent Lamp Ballast 1 89 Applicability Requirement Compliance Background All Bruce Industries Inc fluorescent lamp ballasts P No 05241 1 Aircraft which may be fitted with these ballasts include but are not limited to Boeing 727 aircraft and aircraft modified in accordance with Supplemental Type Certificate STC numbers SA 1081 NW SA 1315 NM SA 1952 NM SA 4042 WE and UK Civil Aviation Authority Airworthiness Approval Note No 17027 Issue 2 Note FAA AD 88 11 08 also refers Install new fuse in power line in accordance with Bruce Industries Inc ASB A05241 33 20 01 Note Hitco ASB A
45. cluding the cell links and cell tops for evidence of heat damage 2 a Replace each cell having a polystyrene case with an equivalent cell having a nylon case OR 2 b Replace any battery containing any polystyrene cell cases with a battery which is approved for aircraft use containing all nylon cells For Para 1 Within 30 hours time in service after 28 January 1972 and thereafter at intervals not exceeding 7 days for a battery that is used for an engine or A P U start or attempted start until replacement of the battery in accordance with para 2 For Para 2 Any battery found to have evidence of heat damage before further flight and for any other battery before 1 August 1972 Note 1 Polystyrene cell cases can be identified by their clear or slight yellow plastic appearance Marathon Sonotone batteries manufactured prior to 1969 Type CA20 CA20H and CA21H contained polystyrene cell cases Marathon batteries manufactured in 1969 or later and those manufactured by others contain nylon cells which can be identified by their milky white or bluish appearance Note 2 Any battery rebuilt since new may contain a mixture of polystyrene and nylon cells COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 24 Prestolite Alternator Fan Replacement 3 94 Amdt 1 CANCELLED Background Prestolite Service
46. considered to be no longer required James Coyne Delegate of the Civil Aviation Safety Authority 23 December 2008 Page 1 of 1 COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES AIRWORTHINESS DIRECTIVE On the effective date specified below and for the reasons set out in the background section the CASA delegate whose signature appears below revokes Airworthiness Directive AD ELECT 7 Electrical Equipment AD ELECT 7 Magneto BTH Gear Modification 2 2009 Requirement CANCELLED This AD is cancelled on 12 February 2009 This unique Australian AD raised prior to 1964 against BTH Mod CM 419 or ANO 107 2 16 3 4 requiring a modification to the BTH gear of all BTH type AG4 and SG4 magnetos Compliance was before installation in an aircraft As all affected magnetos would have been modified by now this AD is considered to be no longer required James Coyne Delegate of the Civil Aviation Safety Authority 23 December 2008 Page 1 of 1 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 8 Magneto Bosch Cam Bearing Modification 10 69 CANCELLED COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES
47. corrected could lead to a gap between the rubber edging of the top shroud and the Gimbal frame resulting in excessive vibration and degradation of pointing accuracy and stability performance If the nut were to entirely disengage the Searchlight Gimbal could disconnect from the helicopter and remain attached solely by the internal cable harness or separate totally resulting in damage to the helicopter or injury to persons on the ground Comments After our NPRM 77 FR 13993 March 8 2012 was published we received comments from one commenter Request One commenter requested that the NPRM 77 FR 13993 March 8 2012 refer to the most recent amendment to Spectrolab s Nightsun XP Safety and Service Bulletin No SL 0810 01 Amendment 2 No 3 dated September 27 2010 Spectrolab service bulletin We disagree that this change is necessary because that amendment does not affect the proposed AD s requirements The commenter also stated that the NPRM 77 FR 13993 March 8 2012 refers to EASA AD No 2010 0183 which had been superseded and requested that our AD instead refer to the EASA AD revision EASA AD No 2010 0237R2 dated December 14 2010 We agree Our NPRM referred to EASA AD No 2010 0237R2 in our Discussion and Additional Information sections Finally the commenter requested that the NPRM 77 FR 13993 March 8 2012 include a statement that for Agusta aircraft compliance with the Agusta Westland Bollettino Tecnico 139 231
48. d TR182 COMMONWEALTH OF AUSTRALIA CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Civil Aviation Regulations 1998 PART 39 107 SA4286WE Cessna Models 206 P206 P206A P206B P206C P206D P206E TP206A TP206B TP206C TP206D TP206E U206 U206A U206B U206C U206D U206E U206F U206G TU206A TU206B TU206C TU206D TU206E TU206F and TU206G SA4287WE Cessna Models 320 320A 320B 320C 320D 320E 320F and 320 1 SA4180WE Raytheon Beech Models H35 J35 K35 M35 N35 P35 S35 V35 V35A V35B 35 33 35 A33 35 B33 35 C33 35 C33A E33 E33A E33C F33 F33A F33C G33 36 A36 A36TC and B36TC SA4184WE Raytheon Beech Models 95 B95 B95A E95 95 55 95 A55 95 B55 95 B5A 95 B55B 95 C55 D55 E55 56TC 58 and 58A SA4239WE Raytheon Beech Models 58P 58PA 58TC and 58TCA SA4240WE Raytheon Beech Models 50 B50 C50 D50 D50A DS50B DS0C D50E D50E 5990 E50 F50 G50 H50 and J50 SA4282WE Raytheon Beech Models 35 A35 B35 C35 D35 E35 F35 G35 and 35R SA4178WE Mooney Models M20 M20A M20C M20D M20E M20F M20G M20J and M20K SA4234WE The New Piper Aircraft Inc Piper Models PA 34 200 PA 34 200T and PA 34 220T SA4179WE Piper Models PA 24 PA 24 250 PA 24 260 and PA 24 400 SA4235WE Piper Models PA 44 180 and PA 44 180T SA4236WE Piper Models PA 28 140 PA 28 150 PA 28 160 PA 28 180 PA 28 235 PA 28 151 PA 28 181 PA 28 161 PA 28 236 PA 28 201T PA 285 16
49. d on but not limited to Agusta S p A Agusta Model AB139 and Model AW139 helicopters Sikorsky Aircraft Corporation Sikorsky Model S 92A helicopters and Eurocopter Deutschland GmbH Eurocopter Model EC135 and Model MBB BK 117 C 2 helicopters This AD requires before further flight inserting information into the Normal Procedures section of the Rotorcraft Flight Manual RFM a daily check of the searchlight and at a specified time interval or if certain conditions are found modifying any affected searchlight gimbal assembly This AD was prompted by a report of a searchlight vibrating and an investigation that revealed that the gimbal azimuth top nut was loose A loose nut if not detected and corrected could result in a gap between the rubber edging of the top shroud and the gimbal frame leading to degradation of pointing accuracy and stability performance of the searchlight and excessive vibration If the nut were to entirely disengage the searchlight could disconnect partially or totally from the helicopter resulting in damage to the helicopter and injury to persons on the ground The actions of this AD are intended to ensure that the searchlight remains firmly attached to the helicopter DATES This AD is effective June 20 2013 The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of June 20 2013 ADDRESSES For service information identified in this AD contact Spectrola
50. dt 1 continued Background This AD was originally issued on 1 January 1963 and is now amended to remove reference to ANO 107 2 6 2 1 which has since been cancelled James Coyne Delegate of the Civil Aviation Safety Authority 22 December 2008 Page 2 of 2 COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES AIRWORTHINESS DIRECTIVE On the effective date specified below and for the reasons set out in the background section the CASA delegate whose signature appears below revokes Airworthiness Directive AD ELECT 12 Electrical Equipment AD ELECT 12 Briggs and Stratton AAF Type B5 2 2009 Ignition Switches Modification Requirement CANCELLED This AD is cancelled on 12 February 2009 Background This AD was probably raised in 1963 requiring removal of all Briggs and Stratton AAF Type B5 ignition switches or in accordance with AD GENERAL 11 As AD GENERAL 11 was superseded by this AD the validity of the contents of this AD was compromised Compliance was not entered in this AD however records show that compliance was originally required forthwith Although not entered in this AD the contents would have been applicable to the requirements of FAA AD 53 26 01 with a compliance requirement of not later than 1 April 1954 Given the extended period this AD has been in place this AD is considered to be no longer required J
51. e before further flight inserting information into the Normal Procedures section of the RFM a daily check of the searchlight and at a specified time interval or if certain conditions are found modifying any affected searchlight gimbal assembly An owner operator pilot holding at least a private pilot certificate may perform the visual check and must show compliance by updating the helicopter maintenance records in accordance with 14 CFR 43 9 a 1 4 and 91 417 a 2 v This visual check is authorized because it requires no special tools and can be performed equally well by a pilot or mechanic this authorization is an exception to our standard maintenance regulations The proposed requirements were intended to ensure the searchlight remains firmly attached to the helicopter after a report that the searchlight was vibrating The European Aviation Safety Agency EASA which is the Technical Agent for the Member States of the European Union has issued EASA AD No 2010 0237R2 dated December 14 2010 to correct an unsafe condition for the Spectrolab Nightsun XP Searchlights installed on the following model helicopters Agusta AB139 and AW139 Sikorsky S 92A and Eurocopter MBB BK 117 C2 and EC 135 series EASA advises of a reported incident where vibration was associated with the Spectrolab Nightsun XP Searchlight and states that an investigation revealed the Gimbal Azimuth Top Hex Nut was loose EASA advises that this condition if not detected and
52. ear Pay particular attention to the bearing inner and outer race If there is any sign of overheating or an indication that the rotor shaft has been turning in the inner race or the outer race turning in the end head the alternator must be removed and repaired If the rotor shaft has been turning in the bearing inner race the rotor and bearing must be replaced If the bearing outer race has been turning in the end head the bearing and end head must be replaced Check the bearing grease for any sign of overheating or contamination such as dirt or metal filings If the grease is a dark brown or black colour or is so contaminated the alternator must be removed and the bearing replaced If the bearing shows no sign of discoloration overheating wear or contamination the bearing only not the entire cavity should be regreased with Caltex RPM Grease SRI 2 only Note The following SBs refer to this inspection Prestolite ASMIO Rolls Royce T 324 Continental TCM M75 30 and FAA AD 76 02 07 Within 100 hours time in service after 30 July 1976 and thereafter at intervals not exceeding 100 hours time in service or 500 hours time in service for alternators modified as per Rex Aviation Modification RA C 1541 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 29 Superseded 5 78 Superseded by AD ELECT 33 COMMO
53. ecifies the above checks For impulse couplings having less than 300 operating hours Compliance with AD ELEC 27B should ensure detection of excessive wear in longer time components Within next 100 hours of engine operation after 30 November 1982 1 This Directive is amended to highlight the latest revision to the referenced Service Bulletin Torque figures and procedures are revised 2 Engine stoppage attributed to failure of the magneto impulse coupling has occurred in two aircraft less than 200 hours operating time It was found that the impulse coupling flyweights had been improperly heat treated soft and had worn rapidly and jammed It is believed this damaged the engine accessory drive resulting in engine failure COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 43 J E T Emergency Power 3 83 Supply Inspection Modification Applicability All J E T power supplies Model PS835 series Requirement 1 If the installation incorporates a panel located battery test switch install a temporary placard near the test switch which reads as follows To test emerg pwr supply 1 Disregard emerg pwr sw test position 2 A C master batt sw off 3 Emerg pwr sw on 4 Ck operation of accessory instr 2 Modify as required by JET Alert SB A SB501 1228 7 FAA AD 82 21 04 Amendment 39 4475 refers
54. embly strike out the A on the magneto data plate Note 3 FAA AD 2005 12 06 Amdt 39 14122 refers Compliance For Requirement 1 a Magnetos that have not previously been inspected Initially as specified in Table 2 and thereafter as specified in Table 3 Table 2 Type of Impulse Impulse Coupling Time in Inspect Coupling Assembly Service TIS as of the Effective Date of this Directive Riveted 100 or more hours time since new Within 10 hours TIS after the or overhaul TSN or TSN is effective date of the original unknown issue of this Directive Fewer than 100 hours TSN Before accumulating 100 hours TSN Snap ring 450 or more hours TSN Within 50 hours TIS after the effective date of the original issue of this Directive Fewer than 450 hours TSN Before accumulating 500 hours TSN Note 4 Previous inspections may have been accomplished in accordance with AD ELECT 68 FAA AD 96 12 07 b Magnetos that have previously been inspected Repeat the inspections as specified in Table 3 Page 2 of 4 COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 75 Amdt 1 continued Background Table 3 Type of Impulse Coupling Assembly Inspect Riveted Within 100 hours time since the last inspection Snap ring Within 500 hours time since the last inspection
55. enter shaft to rotate out Spectrolab has also issued Nightsun XP Searchlight System Kit and Procedure to Incorporate EASA AD 2010 0183 Conformance 034374 Revision NC approved September 28 2010 Kit and Procedure Once modified in accordance with the Kit and Procedure the Nightsun XP gimbals are re identified with a new nameplate and overlay from a P N 033295 1 to 033295 3 or P N 033295 2 to 033295 4 EASA classified this modification as mandatory and issued EASA AD No 2010 0237R2 dated December 14 2010 to ensure the continued airworthiness of helicopters with the affected system installed Costs of Compliance We estimate that this AD affects 6 helicopters of U S registry We also estimate that it will take minimal time to insert the service bulletin into the RFM and about 3 work hours per helicopter to modify the searchlight At an average labor rate of 85 per work hour this amounts to 255 per helicopter Required parts will cost about 1 000 per helicopter Based on these figures we estimate the cost of this AD on U S operators to be 1 255 per helicopter or 7 530 for the fleet Authority for This Rulemaking Title 49 of the United States Code specifies the FAA s authority to issue rules on aviation safety Subtitle I section 106 describes the authority of the FAA Administrator Subtitle VII Aviation Programs describes in more detail the scope of the Agency s authority We are issuing this rulemaking under the authority desc
56. equirement section and c at the time mentioned in the compliance section AD ELECT 73 Britax Sell Galley Equipment 1 2001 Applicability Galley equipment manufactured by Britax Sell GmbH amp Co OHG Herborn Germany with Part Numbers P N as listed below equipped with a Tank Assembly P N 62203 001 005 62197 015 001 64761 025 001 64769 025 003 64771 025 005 64771 025 001 or 64790 331 001 Note 1 Affected Serial Numbers are listed in the applicable Britax Sell GnbH amp Co OHG Service Bulletins SB referenced below Equipment Part Number Remote Water Boiler 62204 001 029 62204 001 031 62204 001 037 62204 001 043 62204 001 047 and 62204 001 049 Coffee Maker 64755 64753 001 003 64763 201 003 64769 001 005 64769 001 007 and 64790 1 Water Boiler 62197 001 001 Beverage Maker 64771 001 001 and 64771 001 003 Requirement 1 Inspect the Faston Terminal P N 3 520133 2 with blue Nylon insulation connected to the contact pins of Thermal Limiters P N AC 1544 or P N AC 1693 as applicable for electrical arcing discoloration or signs of over heating such as insulation melting 2 If any damage is detected during the Requirement inspection replace the affected wires in accordance with the applicable SB as follows Service Bulletin Number Equipment Part Number E33 4 007SB Revision 1 dated 30 October 2000 62204 001 029 62204 001 031 62204 001 037 62204 001 043 62204 001 047 62204 001 049 E33 4 009SB dated 24 October 2
57. ery shunt jumper between terminals 2 and 3 of the female plug on the battery temperature probe cable If the shunt is missing install a shunt P No 161 211 and ensure correct operation of the temperature probe system Note DGAC AD 90 198 056 B also refers 1 For batteries fitted to aircraft within 50 hours time in service after 21 February 1991 2 For uninstalled batteries before installation in an aircraft Advice has been received that the temperature probe shunt may be not installed or missing on some SAFT 1606 1 batteries which may result in nil operation of the temperature sensing system and therefore failure to detect a potentially dangerous overheated battery condition COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 59 Ignition Switches 11 93 Amdt 1 Applicability Ignition switches manufactured by ACS Products Company or Gerdes Products Requirement Compliance Background Company fitted to but not limited to the following aircraft models Piper PA 38 112 Schweizer GA 164 series and 2 37 series Cessna 150 series 152 series 172 series 177 series 180 182 series 185 U206 207 210 series Note Serial number ranges for Cessna aircraft are identified in Cessna Service Bulletin SEB91 5 Revision 1 dated 14 June 1991 1 Inspect the ignition switch for wear or corrosion and lub
58. eviously accomplished in accordance with the original issue of this Directive then within 50 hours time in service from 18 August 1994 Background TCM Ignition Systems have advised that quality assurance testing has revealed the potential for capacitors Part Number 10 349276 to have an intermittent open circuit condition This condition is isolated to two batch lots 93 40 and 93 42 and is readily identifiable by inspection of the capacitor If not corrected the condition could result in a Hot Magneto ie the magneto is not grounded when the magneto ignition switch is placed in the off position The inspection mandated by this Directive is designed to correct this situation This amendment is issued to correct the serial number range of the new or rebuilt magnetos that may be affected Note TCM Ignition Systems Service Information Letter SIL642 provides an explanation of manufacturing or serial numbering system used on TCM Ignition System products COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 64 Nordskog Water Heaters and Coffee Makers 10 94 Applicability Requirement Compliance Nordskog water heaters and coffee makers without an integral check valve identified in Nordskog Industries Inc Service Bulletin SB 93 35 dated 21 October 1993 which were either manufactured between January 1990 and
59. ffee maker in accordance with Nordskog Industries Service Bulletin SB 93 34 to determine if a NUPRO pressure relief valve having part number SS 2C4 65 has been installed 2 Ifa NUPRO pressure relief valve part number SS 2C4 65 has been installed then either a replace the pressure relief valve with a new improved NUPRO pressure relief valve part number SS CHF2 65 or b deactivate the water heater or coffee maker and install a placard stating Not to be used 3 NUPRO pressure relief valve part number SS 2C4 65 held as spares are not to be fitted to water heaters or coffee makers identified in Nordskog Industries Inc Service Bulletin SB 93 34 dated 21 October 1993 and these water heaters or coffee makers are not to be fitted to aircraft as replacement items if a NUPRO pressure relief valve part number SS 2C4 65 is installed Note FAA AD 93 23 01 Amdt 39 8735 refers 1 Prior to 7 January 1994 2 Prior to further flight 3 With effect 8 December 1993 COMMONWEALTH OF AUSTRALIA CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Civil Aviation Regulations 1998 PART 39 107 Background The FAA recently received reports of injuries to cabin crew members that resulted from explosions of galley water heaters One report stemmed from an incident in which a water heater exploded in the galley tore a hole through the the galley wall and landed in the cockpit injuring two flight attendants and the co pi
60. fication 2 2009 Requirement CANCELLED This AD is cancelled on 12 February 2009 Background This unique Australian AD raised prior to 1964 against DH Mod G2242 Part 3 or ANO 107 2 16 2 4 requiring a modification to Magneto impulse starters BTH type Z1 2 fitted with pawls P No CX55288 Compliance was before installation in an aircraft As all affected magnetos would have been modified by now this AD is considered to be no longer required James Coyne Delegate of the Civil Aviation Safety Authority 23 December 2008 Page 1 of 1 COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES AIRWORTHINESS DIRECTIVE On the effective date specified below and for the reasons set out in the background section the CASA delegate whose signature appears below revokes Airworthiness Directive AD ELECT 6 Electrical Equipment AD ELECT 6 Magneto BTH Contact 2 2009 Breakers Assembly Modification Requirement CANCELLED This AD is cancelled on 12 February 2009 Background This unique Australian AD raised prior to 1964 required a modification to all BTH type AG4 SG4 and MC1 magnetos fitted with contact breakers having an automatic earthing device by replacing with contact breakers that do not have this provision Compliance was before installation in an aircraft As all affected magnetos would have been modified by now this AD is
61. h data plates marked REMANUFACTURED and with serial numbers below 901001 Note 1 CASA has received reports of some confusion as to what is meant by S 20 S 200 S 600 and S 1200 A typical example is S6RN 25 where the S designates a single type ignition unit the 6 designates the number of engine cylinders the R designates right hand rotation the N is the manufacturer designator this did not change when TCM purchased the Bendix magneto product line and the number after the dash indicates the series a 25 is a S 20 series magneto while a 1225 is a S 1200 series magneto Note 2 If a Bendix magneto data plate has been replaced with an overhaul facility s data plate this Directive is still applicable to that magneto as the magneto is a Bendix magneto Note 3 Yellow Bendix or TCM service spare data plates may have been installed during field overhaul use the magneto model and serial number to determine the applicability of this Directive Note 4 The paint on some early data plates may have been obliterated and the data plate may appear silver in colour use the magneto model and serial number to determine the applicability of this Directive For Bendix S 20 and S 200 series magnetos inspect and if necessary replace Bendix ignition coils and rotating magnets identified in the Detailed Instructions of TCM Ignition Systems Mandatory Service Bulletin MSB644 dated 4 April 1994 with appropriate serviceable ignition c
62. helicopters Enstrom Model F28 F28A F28F 280 280F helicopters Model F28C and 280C helicopters equipped with Lycoming H10 360 E1BD engines Hughes Summa Corp Model 269 series helicopters Hiller Fairchild Industries Model UH 12 series helicopters Robinson Model R 22 series helicopters Document Bendix SB No 614 FAA AD 81 17 01 refers Compliance Within 100 hours time in service after 30 November 1981 Background The manufacturer has determined that the combination connector lock tab plate tolerance of some vibrators may have caused the detachment of the connector from the plate This detachment can cause grounding and loss of the magneto which could result in air safety being jeopardized COMMONWEALTH OF AUSTRALIA CIVIL AVIATION SAFETY AUTHORITY Civil Aviation Regulations 1998 PART 39 107 SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 40 Applicability Slick Magneto Coil 11 81 SLICK magnetos model No 4201 4201R 4216 4216R 4230 4230R 4250 4250R 4251 4251R 4252 4252R 4281 4281R 6210 6210R 6214 and 6214R The Serial Number range of these magnetos includes 8100000 8 109999 8110000 8119999 8120000 8 129999 9010000 9019999 9020000 9029999 9030000 9039999 9040000 9049999 9050000 9059999 9060000 9069999 9070000 9079999 9080000 9089999 9090000 9099999 9100000 9 109999 9110000 9119999 9120000 9 129999 0010000 0019999 0020000 0029999 0030000 0039999 004000
63. irement 2 Effective 19 August 1993 The manufacturer has received reports of Pulselite units overheating and failing due to under rated transistors together with location of the transistors relative to the heat sink fins The overheating may lead to a pungent smell followed by smoke entering the cockpit and in the worst case the possibility of enough heat being generated by the unit to damage surrounding areas Compliance with this Directive decreases the likelihood of overheating of the units occurring The compliance time required by the FAA has been extended by one calendar month COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 61 Nordskog Water Heaters and Coffee Makers 2 94 DM Applicability Requirement Compliance Nordskog water heaters and coffee makers identified in Nordskog Industries Inc Service Bulletin SB 93 34 dated 21 October 1993 as installed in but not limited to the following aircraft series Boeing Model 727 737 747 757 and 767 McDonnell Douglas Model DC 9 DC 9 80 DC 10 and MD 11 Airbus Industrie Model A300 A310 and A320 Gulfstream Model G 1159 and G IV de Havilland Model DHC 8 Dassault Aviation Mystere Falcon Model 50 and 900 Canadair Model CL 600 1A11 CL 600 2A12 CL 600 2B16 amp CL 600 2B 19 and Fokker Model F27 and F28 1 Inspect the water heater or co
64. issue of the Directive required the deactivation or alternatively the removal of the Bob Fields Aerocessories inflatable door seal system this will decrease the likelihood of an in flight fire resulting from the overheating of the door seal system components Amendment 1 was issued to reflect the alternate methods of compliance introduced by the FAA This Amendment also removed aeroplanes with STC SA4472NM incorporated from the applicability COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Amendment 2 removed aeroplanes with STC SA4213WE incorporated from the applicability and introduced an additional alternate method of compliance The Amendment also allows the installation of Bob Fields Aerocessories door seal inflation systems provided that SB No BFA 001 was incorporated The original issue of this Airworthiness Directive became effective on 12 October 1998 Amendment 1 of this Airworthiness Directive became effective on 31 December 1998 rt Eugene Paul Holzapfel Delegate of the Civil Aviation Safety Authority 11 December 2000 The above AD is notified in the Commonwealth of Australia Gazette on 20 December 2000 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 71 SAFT America Inc Nickel Cadmium Batte
65. it resulting in fire or explosion due to the socket head cap screws cutting through the lid gasket Compliance was before commencing the next deep cycle check after 31 October 1973 As all affected batteries would have been inspected and or modified by now this AD is considered to be no longer required James Coyne Delegate of the Civil Aviation Safety Authority 23 December 2008 Page 1 of 1 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 27 Bendix Impulse Coupling Flyweight 2 98 Amdt 6 Clearance Inspection CANCELLED Background Now addressed by AD ELECT 68 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 28 Prestolite Alternator SRE Bearing Inspection 9 79 Amdt 3 Applicability Requirement Compliance Prestolite ALV 9400 to ALV 9410 series gear driven alternators Remove the slip ring and bearing cover by using a small sharp chisel knife blade or screwdriver to pry it out of the alternator slip ring head Care must be taken not to damage the end head or bearing cover If the bearing cover is damaged during removal it must be replaced Without further disassembly visually inspect the bearing and shaft end for discoloration or any sign of overheating or w
66. l coils P N H27 958 bearing yellow inspection stamps other than those listed under 2 Within 35 hours time in service after 16 May 1969 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 21 Slick Magnetos 447 and 600 Series 2 98 Amdt 6 CANCELLED Background This AD mandates the use of the manufacturers published Service Bulletins which are already required to be complied with as approved maintenance data COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 22 Wood Electric Corp Circuit 2 98 Breakers Inspection and Modification CANCELLED Background No longer required COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 23 Nickel Cadmium Batteries with Polystyrene 1 72 Applicability Requirement Compliance Cell Cases Inspection and Replacement Any nickel cadmium battery containing polystyrene cell cases that is capable of being used to start an aircraft engine or A P U except those installed in aircraft which have the battery charging automatically controlled as a function of battery temperature 1 Visually inspect each battery in
67. lled in the upper or lower cabin sidewall of any aeroplane Note FAA AD 99 04 10 Amdt 39 11034 refers 1 Prior to 1 April 2000 2 Prior to further flight after the Requirement 1 inspection 3 As of the effective date of this Directive This Airworthiness Directive becomes effective on 22 April 1999 The Federal Aviation Administration has received reports of smoke fumes and or electrical fire emitting from passenger compartment baggage bins Investigation revealed that the incidents were due to the failure of the fluorescent light ballasts This Directive is intended to prevent fire in the passenger compartment resulting from failure of the fluorescent light ballasts in the cabin sidewalls COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AIRWORTHINESS DIRECTIVE For the reasons set out in the background section the CASA delegate whose signature appears below issues the following Airworthiness Directive AD under subregulation 39 1 1 of CAR 1998 The AD requires that the action set out in the requirement section being action that the delegate considers necessary to correct the unsafe condition be taken in relation to the aircraft or aeronautical product mentioned in the applicability section a in the circumstances mentioned in the requirement section and b in accordance with the instructions set out in the r
68. lot and at the same time cutting several electrical cables Investigation has revealed that the O ring jammed the poppet of the pressure relief valve resulting in over pressurisation Compliance with this Directive will decrease the likelihood of galley water heaters and coffee makers exploding causing injuries to passengers and crew and structural damage to the aircraft COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 62 Applicability Requirement Compliance Inventum Water Heaters 5 94 Inventum Galley Products Division Model DR1 and DR6 series Water Heaters part numbers and serial numbers as listed in Inventum Alert Service Bulletin ASB DR1 DR6 25 4 Revision A and ASB DR1 DR6 25 5 Revision A both dated 6 December 1993 Note The water heaters are known to be installed in but not limited to the following aircraft models Boeing 727 and 737 McDonnell Douglas DC 9 Fokker F28 except Mk 1000 Perform a one time inspection on all affected water heaters to determine whether a a pressure relief valve has been installed in accordance with Inventum Service Bulletin SB 25 330 dated 8 July 1976 SB 25 331 Revision 1 dated 28 September 1977 or ASB DR1 DR6 25 4 Revision A dated 6 December 1993 as applicable and b two 3 phase safety devices have been installed in accordance with Inven
69. low these components to continue in service until they have completed 1500 landings from the last replacement This Amendment becomes effective on 1 November 2001 Background Wear in the transducer drive splines can cause the transducer to produce false signals These signals may be interpreted as skids by the anti skid control box and may result in reduced braking performance or loss of braking COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES This amendment introduces terminating action for BAe 146 aircraft and minor formatting amendments The original issue of this Directive became effective on 29 November 1990 va ff Eugene Paul Holzapfel Delegate of the Civil Aviation Safety Authority 13 September 2001 The above AD is notified in the Commonwealth of Australia Gazette on 10 October 2001 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 58 SAFT 1606 1 Batteries 2 91 Applicability Requirement Compliance Background All SAFT 1606 1 batteries equipped with temperature probes and fitted to aircraft or held as spares Note Aircraft known to be fitted with this type of battery include but are not limited to Aerospatiale AS 350 and AS 355 helicopters Verify the presence of the batt
70. m Components Identification and Inspection Procedures sub paragraphs B 1 2 3 5 6 and 7 2 Remove and replace in accordance with the procedures in Part IV sub paragraphs B 4 8 and 9 of IB 90 001 dated 15 August 1992 any part or parts found to be damaged or improperly configured Note FAA AD 95 22 01 Amdt 39 9408 refers For Requirement If not previously accomplished in accordance with AD ELECT S56 then prior to 29 April 1996 For Requirement 2 Before further flight if any part or parts are found to be damaged or improperly configured during the Requirement 1 inspection or within five flights or 10 hours time in service whichever occurs first of a cabin fluorescent lighting system component failure Replacement of the following ALC parts in accordance with the following instructions constitutes terminating action for the repetitive inspection requirement following failure of a lighting system component a Remove power units P N TR 991 or AL 0546 and replace with protected power unit P N AL 5117 in accordance with ALC Installation Instruction No AL 11025M dated 15 March 1992 b Remove power units P N TR 992 or AL 0514 and replace with protected power unit P N AL 5112 in accordance with ALC Installation Instruction No AL 11024M dated 15 March 1992 c Remove power supplies P N 18 95D or AL 0598 and dimmer P N 22 311 or AL 0542 and replace with protected power supply unit P N AL 5118 or AL 5130 in acco
71. med by the owner operator pilot holding at least a Private Pilot Certificate and must be entered into the helicopter maintenance records in accordance with 14 CFR 43 9 a 1 4 and 91 417 a 2 v The record must be maintained as required by 14 CFR 91 417 121 380 or 135 439 4 If the edging does not remain in physical contact with the side cover when slight pressure is applied to the searchlight in accordance with the requirements of paragraph e 2 of this AD before further flight with an affected Spectrolab Nightsun XP Searchlight assembly system installed modify and re identify the gimbal assembly in accordance with paragraph e 5 of this AD 5 Within 100 hours time in service modify and re identify the gimbal assembly in accordance with Nightsun XP Searchlight System Kit and Procedure to Incorporate EASA AD 2010 0183 Conformance 034374 Revision NC approved September 28 2010 steps 1 through 13 6 Accomplishing paragraph e 5 of this AD is terminating action for the requirements of this AD Alternative Methods of Compliance AMOCs 1 The Manager Safety Management Group FAA may approve AMOCs for this AD Send your proposal to Matt Fuller Senior Aviation Safety Engineer Safety Management Group Rotorcraft Directorate FAA 2601 Meacham Blvd Fort Worth Texas 76137 telephone 817 222 5110 email matthew fuller faa gov 2 For operations conducted under a 14 CFR part 119 operating certificate or under 14 CF
72. n accordance with SAFT Aviation Batteries Service Bulletin Document No A00027 Rev F dated 15 January 1998 then the only action required by this Directive would be to install a compliance label on the battery as specified in SAFT Aviation Batteries Service Bulletin Document No A00027 Rev G dated 14 July 1998 Note 6 FAA AD 98 20 17 Amdt 39 10784 refers At the next scheduled battery maintenance that occurs three calendar months after the effective date of this Directive or within the next 15 calendar months after the effective date of this Directive whichever occurs first This Airworthiness Directive becomes effective on 3 December 1998 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Background Actions required by this Directive are intended to prevent the battery from shorting out or exploding if the heads of fasteners become sheared off Loss of battery power could result in loss of emergency power to electrical flight systems and other emergency power systems that would be required in the event of the loss of the aircraft primary power source COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 72 Fluorescent Light Ballasts 4 99 Applicability Requirement Day Ray Products Inc cabin sidewall fluorescen
73. ng the insulation between the coil terminals and both the main contactor bar and the earthed metal yoke of the coil An approved method of compliance is as follows 1 Remove the two coil terminal screw assemblies 2 Forma piece of 3 in x 3 in fibrous insulating sheet of 0 015 inch minimum thickness into a hat section so that the hollow portion can fit over the existing insulated terminal strip with the remaining portions bearing against the moulded cover and the metal yoke respectively so as to provide an equal overhang of Insulation at each end of the terminal strip Cut a suitable hole to permit the passage of the coil end wires through the new insulation and cut appropriate holes in the hat section to correspond with the existing holes in the terminal strip Varnish the formed strip 3 Place the completed hat section in position and pass the coil wires through the appropriate hole Replace the coil terminal assemblies at the same time connecting up the coil wires and clamping the new insulation firmly in place on each side of the terminal strip Note Compliance with previous issue of this AD constitutes compliance with this AD Compliance Before installation in an aircraft This Amendment becomes effective on 12 February 2009 Page 1 of 2 COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 11 Am
74. nition switch failures caused by internal wear and arcing of the contact surfaces Compliance with this Directive will decrease the likelihood of an inability to control electrical power supply to the engine occurring COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES This amendment eases the compliance period of Requirement 2 due to spares not being readily available COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 60 Precise Flight Incorporated Pulselite 9 93 Applicability Requirement Compliance Background Precise Flight Incorporated Pulselite Units Model 1210 2405 2 serial numbers X00150 through X01371 inclusive Note These units may be installed in various small aircraft in accordance with FAA Supplemental Type Certificate SA4005NM 1 Either remove from service all Pulselite units identified in the applicability statement and return the aircraft to its original state or replace the Model 1210 2405 2 units with Model 1210 2405 2A units in accordance with Precision Flight Incorporated Service Bulletin PL9303001 dated 10 March 1993 2 New installations of Model 1210 2405 2 Pulselite units are prohibited Note FAA AD 93 12 04 Amdt 39 8610 refers Requirement 1 Prior to 19 August 1994 Requ
75. of failure of the magneto impulse coupling assembly and possible engine failure This Amendment continues the requirements of the original issue but corrects Table 1 by limiting the listing to magnetos installed on the specified Lycoming engines and adds a note in the background indicating where the manufacturer s recommended maintenance intervals may be found Page 3 of 4 COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 75 Amdt 1 continued The original issue of this Directive became effective on 19 July 2005 h f NY A David Villiers Delegate of the Civil Aviation Safety Authority 22 July 2005 Page 4 of 4 Federal Register Volume 78 Number 95 Thursday May 16 2013 Rules and Regulations Pages 28725 28727 From the Federal Register Online via the Government Printing Office www gpo gov FR Doc No 2013 11383 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Docket No FAA 2012 0221 Directorate Identifier 2010 SW 082 AD Amendment 39 17454 AD 2013 10 01 RIN 2120 AA64 Airworthiness Directives Spectrolab Nightsun XP Searchlight AGENCY Federal Aviation Administration FAA DOT ACTION Final rule SUMMARY We are adopting a new airworthiness directive AD for a certain Spectrolab Nightsun XP Searchlight Assembly searchlight installe
76. oils and rotating magnets COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Compliance Background For the Bendix S 600 series magnetos inspect and if necessary replace Bendix rotating magnets identified in the Detailed Instructions of TCM Ignition Systems Mandatory Service Bulletin MSB644 dated 4 April 1994 with appropriate serviceable rotating magnets Ignition coils of the S 600 series magnetos already incorporate the improved design For the Bendix S 1200 series magnetos inspect and if necessary replace Bendix ignition coils identified in the Detailed Instructions of TCM Ignition Systems Mandatory Service Bulletin MSB644 dated 4 April 1994 with appropriate serviceable ignition coils The rotating magnets of the S 1200 series magnetos already incorporate the improved design Note Previous compliance with AD ELECT 53 Amdt 2 or earlier issues of that Directive does not constitute full compliance with this Directive similarly compliance with Bendix Electrical Components Division Service Bulletin 560 or 560A would not constitute full compliance The original compliance remains unchanged as within the next 100 hours time in service after 10 November 1994 This amendment is effective from 14 September 1995 Note FAA AD 94 01 03 R2 Amdt 39 9271 refers The original issue of this Directive superseded AD ELECT 53 Amdt 2 which was can
77. on 9 2005 Requirement CANCELLED This AD is cancelled on 1 September 2005 Background This Directive is superseded by AD ELECT 75 which is only applicable to magnetos installed on certain Lycoming engine models Data supplied to the United States Federal Aviation Administration indicated that there was a significant difference in wear and reliability of magnetos installed on Lycoming 540 series engines as compared with other engines Teledyne Continental Ignitions Systems Service Bulletin SB643B dated 6 April 2005 provides the manufacturer recommended periods for inspection overhaul for magnetos installed on all engines David Villiers Delegate of the Civil Aviation Safety Authority 22 July 2005 Page 1 of 1 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 69 Steam Oven Motor Relay 10 98 DM Applicability Requirement Compliance Background B E Aerospace Inc Royal Inventum Company Inventum Galley Products Division Model DS900 series Steam Ovens part number P N 72070000 serial numbers S N 0001 through 0035 inclusive P N 72070100 S N 0001 through 0035 inclusive P N 72070500 S N 0002 through 0127 inclusive and P N 72070501 S N 0057 through 0133 inclusive Modify the motor relay in accordance with B E Aerospace Inventum Alert Service Bulletin 72070000 25 01 72070500 25 01 o
78. r s Service Manual COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 34 Bendix D2000 D2200 Series Magnetos Using Green 2 98 Distributor Blocks Inspection and Replacement CANCELLED Background This AD previously mandated use of the manufacturers Service Bulletins which have now been incorporated into the magneto manufacturer s Service Manual COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 35 Bendix Magneto Housing 2 98 Amdt 1 Distortion Inspection and Modification CANCELLED Background This AD previously mandated use of the manufacturers Service Bulletins which have now been incorporated into the magneto manufacturer s Service Manual COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 36 Slick Magneto Impulse Coupling Inspection 2 98 CANCELLED Background This AD previously mandated use of the manufacturers Service Bulletins which have now been incorporated into the magneto manufacturer s Service Manual COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTH
79. r 72070501 25 01 as applicable all at Revision A dated 1 May 1998 Note RLD AD 1998 067 AB dated 30 June 1998 refers Before installation in an aircraft as a replacement unit or prior to 1 January 1999 at the latest whichever occurs first This airworthiness directive becomes effective on 5 August 1998 The Netherlands Rijksluchtvaartdienst has received two reports of Inventem Model DS900 Steam Ovens generating smoke during flight Subsequent investigation revealed a component failure which caused the oven motor to continue running when it should have switched off This resulted in the motor overheating and causing smoke in the aircraft cabin This directive requires a modification incorporating a relay the modification is designed to ensure that the motor switches off and does not overheat COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AIRWORTHINESS DIRECTIVE For the reasons set out in the background section the CASA delegate whose signature appears below revokes Airworthiness Directive AD ELECT 70 Amdt 1 and issues the following AD under subregulation 39 1 1 of CAR 1998 The AD requires that the action set out in the requirement section being action that the delegate considers necessary to correct the unsafe condition be taken in relation to the aircraft or aeronautical product mentioned in the applicabilit
80. rdance with ALC Installation Instruction No AL 11023M Revision A dated 20 May 1994 Numerous incidents of smoke and fire have been reported on aircraft using SELA Laboratoire Abadie and ALC fluorescent lighting system components The cause of these incidents has been attributed to high voltage arcing or overheating of the lamp connector or remote power unit and prompted the issuing of AD ELECT 56 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES This Directive partially supersedes AD ELECT 56 and is applicable to components manufactured by ALC This Directive clarifies both the requirement and compliance statements whilst also providing an optional terminating action to the repetitive inspection following failure of a lighting system component Actions specified by this Directive are necessary in order to prevent smoke fire and possible electric shock or electromagnetic interference to flight critical or essential systems COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES AIRWORTHINESS DIRECTIVE On the effective date specified below and for the reasons set out in the background section the CASA delegate whose signature appears below revokes Airworthiness Directive AD ELECT 68 Electrical Equipment AD ELECT 68 Bendix Impulse Coupling Inspecti
81. relation to the aircraft or aeronautical product mentioned in the applicability section a in the circumstances mentioned in the requirement section and b in accordance with the instructions set out in the requirement section and c at the time mentioned in the compliance section Electrical Equipment AD ELECT 75 Amdt 1 TCM Magneto Impulse Coupling 9 2005 Applicability Teledyne Continental Motors TCM formerly Bendix magnetos that have a magneto part number P N listed in Table 1 installed on Lycoming AEIO 540 HIO 540 IO 540 O 540 and TIO 540 series engines Table 1 P N Model P N Model 10 51365 32 S6LN 21 10 79020 18 S6LN 25 10 51365 34 S6RN 21 10 79020 19 S6RN 25 10 51365 35 S6RN 21 10 79020 118 S6LN 25P 10 51365 39 S6LN 21 10 79020 119 S6RN 25P 10 51365 40 S6LN 21 10 500556 101 S6RSC 25P 10 51365 43 S6LN 21 10 500556 901 S6RSC 25P 10 51365 47 S6RN 21 10 349350 4 S6RN 1225 10 51365 48 S6RN 21 10 349350 5 S6RN 1225 10 51365 54 S6LN 21 10 349350 6 S6LN 1225 10 51365 57 S6LN 21 10 349350 7 S6LN 1225 10 52350 19 S6RN 23 10 349370 4 S6LN 1227 10 52350 20 S6LN 23 10 382560 11 D6LN 2031 10 79020 6 S6LN 25 10 382560 13 D6LN 2031 10 79020 10 S6RN 25 10 682560 11 D6LN 3000 10 79020 11 S6LN 25 10 682560 13 D6LN 3000 10 79020 16 S6LN 25 10 682560 131 D6LN 3000 10 79020 17 S6LN 25 Note 1 Table 1 is a partial reproduction of Table 1 from TCM Mandatory Service Bulletin MSB MSB645 dated 4 April 1994 Note 2 Lycoming AEIO 5
82. ribed in Subtitle VII Part A Subpart III Section 44701 General requirements Under that section Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices methods and procedures the Administrator finds necessary for safety in air commerce This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on helicopters identified in this rulemaking action Regulatory Findings This AD will not have federalism implications under Executive Order 13132 This AD will not have a substantial direct effect on the States on the relationship between the national government and the States or on the distribution of power and responsibilities among the various levels of government For the reasons discussed above I certify that this AD 1 Is not a significant regulatory action under Executive Order 12866 2 Is not a significant rule under DOT Regulatory Policies and Procedures 44 FR 11034 February 26 1979 3 Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction and 4 Will not have a significant economic impact positive or negative on a substantial number of small entities under the criteria of the Regulatory Flexibility Act We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket Lis
83. ricate the switch in accordance with ACS Service Bulletin SB92 01 Revision A dated 21 January 1993 or for Cessna aircraft Cessna Service Bulletin SEB91 5 Revision dated 14 June 1991 If corrosion or wear is detected either replace the damaged components or replace the ignition switch before further flight Note This requirement does not apply to ACS ignition switches that do not have a start position models A 150 1 and A 510 5 manufactured on or after 20 February 1989 that have not accumulated 2000 hours time in service Switches manufactured after 20 February 1989 may be identified by the presence of red paint in the screw heads on the back of the switch and by the manufacturing date stamped on the switch body 2 Inspect the ignition switch installation to determine if a diode or other surge suppressor is installed on the starter solenoid If one is not installed prior to further flight install a starter solenoid diode in accordance with ACS Service Bulletin SB92 01 Revision A dated 21 January 1993 or for Cessna aircraft Cessna Service Bulletin SEB91 5 Revision dated 14 June 1991 Requirement 1 Within 100 hours time in service after 24 June 1993 or at the next periodic servicing whichever occurs first and thereafter at intervals not to exceed 2000 hours time in service Requirement 2 Within 100 hours time in service after 24 June 1993 Note FAA AD 93 05 06 Amdt 39 8511 refers The FAA has received numerous reports of ig
84. ries 13 98 Applicability Requirement Compliance SAFT America Inc Nickel Cadmium batteries with the following part numbers manufactured prior to December 1997 SAFT America Part Number McDonnell Douglas Part Number 021929 000 43BO034LB02 021904 000 43BO34LB03 Note These batteries are known to be fitted to but not limited to McDonnell Douglas DC 9 and MD 80 series aeroplanes Replace all battery terminal screws verify that the battery contains design specification cells and if the battery contains non design specification cells replace those cells Accomplish these actions in accordance with the instructions section of SAFT Aviation Batteries Service Bulletin Document No A00027 Rev G dated 14 July 1998 Note 1 A plastic label indicating compliance with this Directive may be obtained from SAFT America Inc At the following address SAFT America Inc 711 Industrial Boulevard VALDOSTA GA 31601 Note 2 This label shall not cover the original part number of the battery Note 3 SAFT Aviation Batteries Service Bulletin Document No A00027 Rev G dated 14 July 1998 provides the option of purchasing this label from SAFT or manufacturing your own label Note 4 This label must be installed on the battery as depicted in Figures 3 and 4 on page 8 of SAFT Aviation Batteries Service Bulletin Document No A00027 Rev G dated 14 July 1998 Note 5 If the actions required by this Directive have been previously accomplished i
85. rting a copy of this Airworthiness Directive into the Limitations section of the Flight Manual 4 Bob Fields Aerocessories electrically inflatable door seals are not to be installed on any aeroplane unless the actions specified in Bob Fields Aerocessories Service Bulletin No BFA 001 dated 3 November 1998 have been incorporated Note 1 FAA AD 98 21 21 Revision 1 Amdt 39 1162 refers Note 2 Following are optional alternate methods of compliance a Removal of all provisions of the Bob Fields Aerocessories Inflatable door seals and installation of the original equipment manufacturer door seals or other approved equivalent that is of a different design to the referenced Bob Fields Aerocessories inflatable door seals b For Cessna P210 series pressurised aeroplanes or other aeroplanes that can obtain pressurisation without the door seals inflated 1 Fabricate a placard that incorporates the following words utilising letters that are at least 2 5mm 0 1 inches in height and install the placard on the instrument panel within the pilot s clear view ELECTRIC DOOR SEAL INFLATION SYSTEM INOPERATIVE 2 These aircraft can be operated pressurised with the electric door seal system inoperative in accordance with the applicable Flight Manual provisions for pressurised flight COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Compliance
86. s advise that the requirements detailed in Bendix Engine Products Division Service Bulletin No 629 have been incorporated in the applicable magneto service support manuals COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES AIRWORTHINESS DIRECTIVE On the effective date specified below and for the reasons set out in the background section the CASA delegate whose signature appears below revokes Airworthiness Directive AD ELECT S0 Electrical Equipment AD ELECT 50 Rebling Nickel Cadmium Battery Quick 4 2008 Disconnect Receptacles DM Requirement CANCELLED This AD is cancelled on 11 February 2008 Background This unique Australian airworthiness directive was based on a Special Technical Instruction issued by the Royal Australian Air Force in 1987 rather that a State of design airworthiness directive As all aircraft would now be modified the unsafe condition no longer exists hbe hark David Punshon Delegate of the Civil Aviation Safety Authority 8 February 2008 Page 1 of 1 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 51 SAFT 40AH Type 40976 Batteries 10 88 Amdt 1 Applicability All SAFT 40 AH Type 40976 batteries P No 18585 fitted to aircraft or held as spares Note Aircraft types whi
87. s of the date code are the year of manufacture and the second two digits are the week in that year Note 3 All the above circuit breakers may be identified by their blue or black base colour Mechanical Products circuit breakers commercialised by ECE have an ECE reference number on the body of the circuit breaker Note 4 This Directive does not apply to circuit breakers produced or installed prior to 23 July 1984 the thirtieth week of 1984 or to circuit breakers which have been inspected by the manufacturer found free of defect marked with a white inverted Z or aT painted on the terminal end and have an additional date code with an R prefix As an example the unit may have the additional date code of R8642 where R designates a retest by Mechanical Products Note 5 Aircraft which may be fitted with circuit breakers commercialised by E C E Co include but are not limited to Aerospatiale SA 330 helicopters COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Note 6 FAA AD 87 06 09 and DGAC AD 87 073 IMP AB RI refer Requirement Remove from service circuit breakers which fall within the area designated in the applicability statement Some approved alternate Part No s are as follows Mechanical Products Inc Equivalent Part Numbers Suspect Part Numbers Klixon Mechanical Products Inc 8500 005 1 7274 55 1 8500 002 1 8500 005 1
88. ssary replacement of the wires before further flight with eventual replacement at the next C check These measures are intended to prevent overheating of the terminals which could cause smoke and or fire in the galley compartment Fa Aff Eugene Paul Holzapfel Delegate of the Civil Aviation Safety Authority 11 December 2000 The above AD is notified in the Commonwealth of Australia Gazette on 20 December 2001 COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 CASR 1998 CIVIL AVIATION SAFETY AUTHORITY Regulation 39 001 AIRWORTHINESS DIRECTIVE On the effective date specified below and for the reasons set out in the background section the CASA delegate whose signature appears below repeals Airworthiness Directive AD AD ELECT 74 and issues the following AD under subregulation 39 001 1 of CASR 1998 and subsection 33 3 of the Acts Interpretation Act 1901 The AD requires that the action set out in the requirement section being action that the delegate considers necessary to correct an unsafe condition be taken in relation to the aircraft or aeronautical product mentioned in the applicability section a in the circumstances mentioned in the requirement section and b in accordance with the instructions set out in the requirement section and c at the time mentioned in the compliance section Electrical Equipment AD ELECT 74 Lermer GmbH Water Boilers 9 2014 AMDT 1 Applicability This AD applies to Lermer Gm
89. t Office for approval Note 1 If any fluorescent lighting components referred to in the Applicability Statement are found to be installed in any emergency lighting system or any escape path lighting system the correct operation of which is a mandatory certification requirement for that aircraft then the disabling of such a system in accordance with an FAA AD is NOT permitted Note 2 FAA AD 90 07 08 R1 may be viewed at local CASA District Airworthiness Offices or a copy may be obtained by contacting Airworthiness Information Unit CASA GPO Box 2005 CANBERRA ACT 2601 Facsimile 06 268 5692 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Compliance Background Note 3 The aircraft manufacturers maintenance manual the installers maintenance manual SELA Technical Data Sheet TDS Reference 90 11980 dated 9 February 1990 and Bigorre Aerospace Corporation BAC How To Number 1 Manual dated 10 May 1989 contain information which supplements the instructions contained in this AD This information is important to proper maintenance and replacement of defective components and may be obtained as follows SELA Laboratoire Abadie Bigorre Aerospace Corporation BP No 1 65500 Suite 1107 Vic En Bigorre 6543 46th Street North France Pinellas Park FL 34665 Telephone 33 62 96 71 56 USA Facsimile 33 62 96 23 09 Telephone 1 813 525 8115
90. t light ballasts having the following part numbers 69 10 69 69 70 94 1 69 10 1 69 69 1 83 12 69 68 70 94 83 12 1 69 68 1 Note These fluorescent light ballasts are known to be fitted to but not limited to the following aircraft McDonnell Douglas Model DC 8 DC 9 DC 10 C 9 military and KC 10 military series aeroplanes and Boeing Model 707 727 and 737 series aeroplanes 1 Perform a one time visual inspection to determine the type of fluorescent light ballasts installed in the upper and lower cabin sidewall 2 If any ballast is found during the Requirement 1 inspection to have a part number listed in the Applicability Statement of this Directive remove the light ballast and replace it with a light ballast manufactured by Bruce Industries in accordance with the applicable service bulletin listed below Service Bulletin Number and Date Affected Aeroplanes McDonnell Douglas Model DC 9 30 40 and 50 series Service Bulletin DC9 33 103 aeroplanes listed in the effectivity 30 May 1996 statement of the service bulletin Note Replacement of light ballasts on DC 9 30 40 and 50 series aeroplanes in accordance with SB DC9 33 103 is considered acceptable compliance provided that no protective covers are installed on the light ballasts McDonnell Douglas Model DC 9 30 40 and 50 series Service Bulletin DC9 33 111 aeroplanes listed in the effectivity 6 May 1997 statement of the service bulletin McDonnell Douglas Model DC 10
91. t of Subjects in 14 CFR Part 39 Air transportation Aircraft Aviation safety Incorporation by reference Safety Adoption of the Amendment Accordingly under the authority delegated to me by the Administrator the FAA amends 14 CFR part 39 as follows PART 39 AIRWORTHINESS DIRECTIVES 1 The authority citation for part 39 continues to read as follows Authority 49 U S C 106 g 40113 44701 39 13 Amended 2 The FAA amends 39 13 by adding the following new airworthiness directive AD AIRWORTHINESS DIRECTIVE FAA Aviation Safety www faa gov aircraft safety alerts www gpoaccess gov fr advanced html 2013 10 01 Spectrolab Nightsun XP Searchlight Amendment 39 17454 Docket No FAA 2012 0221 Directorate Identifier 2010 SW 082 AD a Applicability This AD applies to Spectrolab Nightsun XP Searchlight Assembly Systems with gimbal assembly part number P N 033295 1 or 033295 2 installed on but not limited to Agusta S p A Model AB139 and Model AW139 helicopters Sikorsky Aircraft Corporation Model S 92A helicopters and Eurocopter Deutschland GmbH Model EC135 and Model MBB BK 117 C 2 helicopters certificated in any category The searchlight assembly system P Ns and revision level using one of the two affected gimbal assembly P Ns are listed in Table 1 to Paragraph a of this AD Table 1 to Paragraph a Affected Systems and P N System P N Nomenclature Affected revisions 033338 Nightsun XP
92. the toe of each flyweight so that the flyweight heel protrudes outward 4 Using a fine number 1 double cut 1 2 inch wide file at least 3 32 inch thick pass the file across the heel of the flyweight attempting to remove material If the flyweight has been properly heat treated the file will glide smoothly over the heel of the flyweight removing no material If the flyweight is not properly heat treated soft the file will not glide easily across the surface of the flyweight heel and material will be removed 5 If an improperly heat treated soft flyweight is found immediately remove and replace the cam assembly and or the impulse coupling assembly with an assembly meeting the requirement of this AD following procedures in the Magneto Overhaul Instructions and paying strict attention to Notes and Cautions 6 Inspect the impulse coupling stop pins for wear and replace as necessary COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Compliance Background 7 After flyweights have been identified stop pins inspected and the impulse coupling reinstalled on the magneto if removed identify the magneto by stamping a 1 16 inch letter F in the upper right corner of the identification plate to indicate that this AD and Bendix Service Bulletin No 623A have been complied with 8 Reinstall the magneto following manufacturer s published procedures
93. tructors Number 258248 DH BH HS BAe 125 Series 1 to 700 post modification 252740 Action in accordance with Marathon Power Technologies Service Bulletin 111692 014 Revision 1 dated 15 March 1993 Note CAA UK AD 005 05 94 refers Prior to 15 March 1995 The CAA UK has reported that PC 250 static inverters have failed because of moisture ingress Compliance with this Directive will ensure that the inverters are protected from moisture ingress COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Electrical Equipment AD ELECT 66 Bendix Magneto Coils and Rotating Magnets 10 95 Amdt 1 Applicability Requirement Teledyne Continental Motors TCM Ignition Systems formerly Bendix magnetos as listed below Magnetos manufactured by Bendix in Jacksonville FL and those manufactured by TCM in Atlanta GA as indicated on the data plate are excluded S 20 S 200 and S 600 series magnetos with either serial numbers below 2000000 without any letter prefix or with serial numbers below 16058 having the letter A prefix for example A16057 S 20 S 200 and S 600 series magnetos with data plates marked REMANUFACTURED and with serial numbers below 901001 S 1200 series magnetos with either serial numbers below 2000000 without any letter prefix or with serial numbers below 132844 having the letter A prefix S 1200 series magnetos wit
94. tum SB 25 340 dated 7 July 1977 SB 25 344 dated 18 January 1978 SB 25 345 dated 16 February 1978 SB 25 346 dated 16 February 1978 or ASB DR1 DR6 25 5 Revision A dated 6 December 1993 as applicable If a pressure relief valve and or two 3 phase safety devices as applicable have not been installed then either a remove the water heater from the aircraft and install a modified water heater or b deactivate the water heater and install a placard stating Not to be used Inventum Model DR1 and DR6 water heaters are not to be fitted to aircraft as replacement items unless modified in accordance with the referenced Inventum Service Bulletins Note RLD AD 93 168 AB dated 17 December 1993 refers 1 Prior to 1 July 1994 2 Prior to further flight after the Requirement 1 inspection 3 With effect 28 April 1994 COMMONWEALTH OF AUSTRALIA Civil Aviation Regulations 1998 PART 39 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Background The RLD has received a report of an aircraft Inventum DR6 galley water heater exploding during an overheat test in a maintenance facility Investigation revealed that the heater did not have a pressure relief valve or 3 phase safety devices installed Since this condition may exist on other similar Inventum water heaters this Directive is issued to prevent explosions of water heaters and subsequent injuries to passengers or cabin crew members COMMONWEALTH
95. would be terminating action for this AD We disagree The Agusta service bulletin recommends contacting or sending parts to Spectrolab to meet requirements Our AD refers to a Spectrolab document to meet the requirements for terminating action Adding compliance with the Agusta service bulletin as terminating action would be repetitive FAA s Determination We have reviewed the relevant information considered the comments received and determined that an unsafe condition exists and is likely to exist or develop on other products of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed Differences Between This AD and the EASA AD The differences between this AD and the EASA AD are We require modifying and re identifying the searchlight within 100 hours TIS while the EASA AD imposes a calendar date for compliance The EASA AD requires contacting the design change approval holder if discrepancies are found during the inspection of the searchlight installation and we do not require this action Related Service Information Spectrolab has issued Nightsun XP Searchlight Safety and Service Bulletin No SL 0810 01 Amendment No 2 dated September 24 2010 SB which describes a design change that incorporates two positive locking mechanisms A torque value and safety wire applied to the nut These locking mechanisms prevent the gimbal azimuth top nut from loosening and allowing the c
96. y section a in the circumstances mentioned in the requirement section and b in accordance with the instructions set out in the requirement section and c at the time mentioned in the compliance section AD ELECT 70 Inflatable Door Seal System 1 2001 Amdt 2 Applicability Bob Fields Aerocessories inflatable door seal systems installed either in accordance with Federal Aviation Administration FAA Supplemental Type Certificate STC or through FAA field approval that are installed on but not limited to the following aircraft Affected STC Make and Model Aircraft Affected SA3735NM Cessna Models 170 170A and 170B SA4136WE Cessna Models 310 310A 310B 310C 310D 310E 310F 310G 310H 3101 310J 310K 310L 310N 310P 310Q 310R T310P T310Q and T310R SA2226NM Cessna Models P210N and P210R SA3736NM Cessna Models 185 185A 185B 185C 185D A185E and A185F SA4177WE Cessna Models 175 175A 175B and 175C SA4212WE Cessna Models 210 210A 210B 210C 210D 210E 210F 210G 210H 210J 210K 210L 210M 210N T210F T210G T210H T210J T210K T210L T210M T210N 210 5 205 and 210 5A 205A SA4283WE Cessna Models 172 172A 172B 172C 172D 172E 172F 172G 172H 1721 172K 172L 172M and 172N SA4284WE Cessna Models 180 180A 180B 180C 180D 180E 180F 180G 180H 180J and 180K SA4285WE Cessna Models 182 182A 182B 182C 182D 182E 182F 182G 182H 182J 182K 182L 182M 182N 182P 182Q R182 an

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