CPY Document - Luftfartstilsynet
Contents
1. LUFTFARTSDIRE KTORATET Avd for Luftfartsinspeksjon MAULE FORNEBU OSLO Dep SAMMENDRAG THF Oslo 02 12 13 40 LUFTDYKTIGHETSPABUD AFTN ENFBYA E Tlgr CIVILAIR OSLO 1946 1970 Telex 11032 Oslo LDP Med hjemmel i lov om luftfart av 16 desember 1960 47 2 ledd og 214 Kgl res av 8 desember 1961 litra K og Samferdselsdeportementets brev datert 23 mars 1964 fastsetter Luftfartsdirektoratet f lgende forskrift 8 68 BESKYTTELSE AV BENSINLEDNING UNDER FORRESTE SETE I MAULE Forandringen er Mandatory og gjelder for f lgende modeller av Maule Mu Mic MLT MLS M h 210 M 4 210C M h 220C og M l4 2208 Med serie nr 68 94 1C 10C 1T 3T 18 35 1001 1045 1001C 1062C 20010 200LC og 20018 Bensinledningen i cockpit p nevnte fly ligger s n r justerings h ndtaket for setet at det er mulighet for gripe feil n r man skal flytte setet og derved lage bensinlekkasje innvendig i flyet Luftfartsdirektoratet bestemmer derfor at fabrikkens p budte for andring i Service Letter nr 13 av 29 august 1967 skal gj res gjeldende for alle norskregistrerte fly av nevnte typer Forandringen g r ut p at det skal monteres beskyttelsesplater p senterseksjonen foran bensinr ret slik at det ikke lenger er mulig gripe feil Platenes fasong og befestigelse fremg r av skisser i nevnte S L fra Maule som kan f s fra fabrikken eller fra for handleren i Norge 19 68 FORANDRING AV SIDETR2. argjile ca stem gta a 2 rier ak va Motordrevne luftfart y Maule la Erstatter Maule 1 48 75 forts 44 79 Tid for utf relse Innen 30 flytimer regnet fra 20 juli 1975 Referanser FAA AD 75 11 02 og Maule Aircraft Corporation Service Letter 31 omhandler samme sak KONTROLL AV FREMRE R RFESTE MELLOM HALEFLATE OG SKROG Pabudet gjelder Maule Aircraft Corp modeller M 4 og M 5 med serienr M 4 serienr 4 til 94 M 4 210C serienr 10010 til 11117C 1001 til 1045 M l 2205 20018 1S til 3S M 4 220C 2001C til 2190C 1T til 3T M 4 180 3001C til 3006C 1C til lic M 5 alle s M 5 210C serienr 6001C til 62060 M 5 235C serienr 7001C til 7283C M 5 2200 50010 til 5057C M 5 180c 8001C til 8004C M 5 210Tc 9001C P budet omfatter For unng brudd p r ret som fester fremre del av haleflatene til bak kroppen skal paragraf 1 og 5 i Maule Aircraft Corp Service Bulletin No 1 datert 3 mai 1979 eller senere revisjoner utf res Dersom sprekker blir funnet skal delene skiftes ut med nye deler fra Maule Aircraft Corp f r f rste flyging Forandre haleflate til skrog festet som vist i ovennevnte Service Bulletins paragraf 3 og 14 Tid for utf relse Innen 25 timers gangtid etter 2 august 1979 eller 60 dager etter denne dato det som kommer f rst Referanser FAA AD 79 12 01 A x Canta vet a august 1979 LUFTFARTSVERKET Hoveda
3. What must I do to address this problem To address this problem accomplish the following Inspect all Nicopress For Group 1 airplanes Accomplish in accordance sleeve terminal ends for Within the next 25 hours with the ACTION TO BE correct size compression time in service TIS after TAKEN AND TOOLS May 30 2000 the effective REQUIRED section of date of this AD and Maule Mandatory Service Bulletin No 20 dated December 27 1999 For Group 2 airplanes Within the next 100 hours TIS after May 30 2000 the effective date of this AD Prior to further flight after the inspection required by this AD Adjust or replace any terminal compressions that are outside of the limits specified in the service information Accomplish in accordance with the ACTION TO BE TAKEN AND TOOLS REQUIRED section of Maule Mandatory Service Bulletin No 20 dated December 27 1999 Accomplish in accordance with the ACTION TO BE TAKEN AND TOOLS REQUIRED section of Maule Mandatory Service Bulletin No 20 dated December 27 1999 As of May 30 2000 the effective date of this AD Do not install a Nicopress sleeve without assuring that the terminal compressions are within the limits specified in the service information e Can I comply with this AD in any other way 1 You may use an alternative method of compliance
4. 7357 facsimile 404 305 7348 LUFTFARTSVERKET Hovedadministrasjonen Luftfartsinspeksjonen Postboks 8124 Dep 0032 Oslo MOTORDREVNE LUFTFART Y Ta 22942351 LUFTDYKTIGHETSPABUD Telex 71032 enfb n LDP MAULE 4 Med hjemmel i lov av 11 juni 1993 nr 101 om luftfart kap XV 15 4 jf kap IV 4 1 og Samferdselsdepartementets bemyndigelse av 25 mars 1994 fastsetter Luftfartsverket f lgende forskrift om luftdyktighet 96 041 OMPLASSERING AV GASCOLATOR OG DRIVSTOFFPUMPE P budet gjelder Maule Aerospace Technologies Inc Model M 4 210 S N 1001 t o m 1045 Model M 4 210C S N 1001C t o m 1080C som har installert Dual Exaust System 5230F Pabudet omfatter Utf r tiltak som beskrevet i vedlagte kopi av FAA AD 96 10 05 Tid for utf relse Innen neste 50 timers ettersyn etter 21 06 96 hvis ikke allerede utf rt Referanse FAA AD 96 10 05 Gyldighetsdato 01 06 96 naaa a n a aaa aaastal MERK For at angjeldende flymateriell skal vere luftdyktig m p budet v re utf rt til rett tid og notat om utf relsen f rt inn i vedkommende journal med henvisning til denne LDPs nummer AIRWORTHINESS DIRECTIVE Q Bilag til LDP 96 041 REGULATORY SUPPORT DIVISION U S Department P O BOX 26460 of Transportation OKLAHOMA CITY OKLAHOMA 73125 0460 Federal Aviation Administration The following Airworthiness Directive issued by the Federal Aviation Administration in accordance with t
5. 9476 Docket No 95 CE 97 AD Applicability M 4 M 5 M 6 M 7 MX 7 MXT 7 Series and Models MT 7 235 and M 8 235 Airplanes all serial numbers certificated in any category that are equipped with part number P N 2079E rear wing lift struts and P N 2080E front wing lift struts NOTE 1 This AD applies to each airplane identified in the preceding applicability revision regardless of whether it has been modified altered or repaired in the area subject to the requirements of this AD For airplanes that have been modified altered or repaired so that the performance of the requirements of this AD is affected the owner operator must request approval for an alternative method of compliance in accordance with paragraph b of this AD The request should include an assessment of the effect of the modification alteration or repair on the unsafe condition addressed by this AD and if the unsafe condition has not been eliminated the request should include specific proposed actions to address it Compliance Required within the next 30 calendar days after the effective date of this AD unless already accomplished NOTE 2 The compliance times and inspection intervals indicated in this AD take precedence over the compliance times and inspection intervals called for in the Maule Service Bulletin SB No 11 Issued October 30 1995 NOTE 3 The paragraph structure of this AD is as follows Level 1 a b c etc Level 2 1 2 3 etc
6. Level 3 i ii iii etc Level 2 and Level 3 structures are designations of the Level 1 paragraph they immediately follow To prevent corrosion of the wing lift strut which if not detected and corrected could cause the wing to separate from the airplane accomplish the following a Inspect the two rear wing lift struts P N 2079E and the two front wing lift struts P N 2080E for internal corrosion in accordance with the INSTRUCTIONS and INSPECTION PROCEDURE sections specified in Maule SB No 11 Issued October 30 1995 1 If evidence of corrosion damage is found prior to further flight accomplish one of the following i Replace the damaged strut with an airworthy strut of the same part number that has been treated internally with corrosion preventative in accordance with the INSPECTION PROCEDURE section specified in Maule SB No 11 Issued October 30 1995 or ii Replace the damaged strut with a sealed wing lift strut P N 2200E or P N 2201E as applicable in accordance with the instructions specified in PART II of the INSTRUCTIONS section of Maule SB No 11 Issued October 30 1995 2 If no evidence of corrosion damage is found prior to further flight treat the strut internally with corrosion preventative in accordance with the NOTE in the INSPECTION PROCEDURE section in Maule SB No 11 Issued October 30 1995 b An alternative method of compliance or adjustment of the compliance time that provides an equivalent le
7. actions to address it Compliance Required within the next 50 hours time in service after the effective date of this AD uniess already accomplished To prevent an airplane engine fire caused by the close proximity of the fuel gascolator and electric fuel pump to the exhaust system accomplish the following a Relocate the gascolator and fuel pump from above the air egress to the left side of the airplane in accordance with Maule Service Bulletin No 10 dated September 16 1994 b Special flight permits may be issued in accordance with sections 21 197 and 21 199 of the Federal Aviation Regulations 14 CFR 21 197 and 21 199 to operate the airplane to a location where the requirements of this AD can be accomplished c An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager Atlanta Aircraft Certification Office ACO Campus Building 1701 Columbia Avenue suite 2 160 College Park Georgia 30337 2748 The request shall be forwarded through an appropriate FAA Maintenance Inspector who may add comments and then send it to the Manager Atlanta ACO NOTE 2 Information concerning the existence of approved alternative methods of compliance with this AD if any may be obtained from the Atlanta ACO d The relocation required by this AD shall be done in accordance with Maule Service Bulletin No 10 dated September 16 1994 This incorporation b
8. certificated in any category GROUP 1 AIRPLANES Models J Serial Numbers 34001C M 7 260C 30001C through 30004C 30007C through 30011C 30013C 29001C 28001C through 2801 1C MT 7 260 27001C and 27003C 26002C through 26007C 25001C through 25037C 25040C 25041C and 25044C 24001C 23001C through 23056C 23058C and 23059C MX 7 180B 22001C through 22016C MXT 7 180A _ 21001C through 21067C 21070C 21072C 21076C 210770 21079C and 21081C MX 7 180A 20001C through 20063C MX 7 160 19001C through 19046C MXT 7 160 17001C throug 17008C MT 7 235 gt 18001C through 18041C 180440 and 18047C M 8 235 15001C through 15005C MXT 7 180 14000C through 14095C 7 180 11066C through 11097C 10081C through 10122C 7 235 4078C 4080C 4083C 4086C and 4089C through 4132C M 6 235 _ 7508C 7510C 7516C and 7518C through 7521C i 2 2000 09 06 ROUP 2 AIRPLANES Serial Numbers a Models Bee Dee M 4 M 4 3 through 94 Bee Dee 3 14 and M 4 15 94 MA Stroup MAC d iC through le Meas 18 28 and 38 MAT IT 27 and 3T 4 M 4 210 1001 through 1045 M 4 210C 1001C through 1117C M 4 220C 2001C through 2190C 4 M 4 180C 3001C through 3006C M 5 200 8015C and 8022C M 5 210C 6001C through 6206C M 5 220C 5001C through 5057C M 5 235C 7001C through 7248C 7250C through 7353C A7354C 73
9. etc Level 2 1 2 3 ete Level 3 1 ii iid ete Level 2 and Level 3 structures are designations of the Level 1 paragraph they immediately follow a Upon accumulating 2 years on a lift strut affected by this AD within 3 calendar months after the effective date of this AD or within 2 years after the last inspection accomplished in accordance with AD 95 26 18 superseded by this action whichever occurs later remove the wing lift struts in accordance with the INSTRUCTIONS section of Maule Service Bulletin SB No 11 dated October 30 1995 and accomplish one of the following the actions in either paragraph a 1 a 2 a 3 or a 4 including all subparagraphs of this AD 1 Inspect the wing lift struts for corrosion in accordance with the INSPECTION PROCEDURE section of Maule SB No 11 dated October 30 1995 i If no perceptible dents as defined in the above SB are found in the wing lift strut and no corrosion is externally visible apply corrosion inhibitor to each strut in accordance with Maule SB No 11 dated October 30 1995 Re inspect the wing lift struts at intervals not to exceed 24 calendar months provided no perceptible dents or external corrosion is found 2 98 15 18 Bilag til LDP 98 075A stober 30 1995 Re inspect the wing lift struts at intervals not to exceed 24 calendar months provided no perceptible sents or external corrosion is found ii Ifa perceptible dent as defined in the above SB
10. is found in the wing lift strut or external corrosion is found prior to further flight accomplish one of the installations and subsequent actions presented in each paragraph specified in paragraphs a 3 and a 4 of this AD 2 Inspect the wing lift struts for corrosion in accordance with the Appendix to this AD The inspection procedures in this Appendix must be accomplished by a Level 2 or Level 3 inspector certified using the guidelines established by the American Society for Non destructive Testing or MIL STD 410 i If no external corrosion is found and all requirements in the Appendix to this AD are met prior to further flight apply corrosion inhibitor to each strut in accordance with Maule SB No 11 dated October 30 1995 Reinspect the lift struts at intervals not to exceed 24 calendar months provided no extemal corrosion is found and all of the requirements included in the Appendix of this AD are met ii If external corrosion is found or if any of the requirements in the Appendix of this AD are not met prior to further flight accomplish one of the installations and subsequent actions presented in each paragraph specified in paragraphs a 3 and a 4 of this AD 3 _ Install original equipment manufacturer OEM part number wing lift struts or FAA approved equivalent part numbers that have been inspected in accordance with the specifications presented in either paragraph a 1 or a 2 of this AD and are found to be airw
11. issue a special flight permit under sections 21 197 and 21 199 of the Federal Aviation Regulations 14 CFR 21 197 and 21 199 to operate your airplane to a location where you can accomplish the requirements of this AD h Are any service bulletins incorporated into this AD by reference You must accomplish the actions required by this AD in accordance with Maule Mandatory Service Bulletin No 20 dated December 27 1999 The Director of the Federal Register approved this incorporation by reference under 5 U S C 552 a and 1 CFR part 51 You can get copies from Maule Aerospace Technology Inc 2099 Georgia Hwy 133 South Moultrie Georgia 31768 You can look at copies at FAA Central Region Office of the Regional Counsel 901 Locust Room 506 Kansas City Missouri or at the Office of the Federal Register 800 North Capitol Street NW suite 700 Washington DC i When does this amendment become effective This amendment becomes effective on May 30 2000 FOR FURTHER INFORMATION CONTACT Cindy Lorenzen Aerospace Engineer FAA Atlanta Aircraft Certification Office One Crown Center 1895 Phoenix Boulevard suite 450 Atlanta Georgia 30349 elephone 770 703 6078 facsimile 770 703 6097 Issued in Kansas City Missouri on April 27 2000 Michael Gallagher Manager Small Airplane Directorate Aircraft Certification Service BLANK
12. 235 M 8 235 MX 7 160 MXT 7 160 MX 7 180A MXT 7 180A MX 7 180B MXT 7 420 M 7 235B M 7 235A M 7 235C NOTE 1 This AD does not apply to airplanes equipped with four Maule sealed lift struts P N 2200E and P N 2201E These sealed lift struts are identified by two raised weld spots on the upper end of the strut just below the serial number plate Removal of the upper cuff is needed to locate the weld spots NOTE 2 This AD applies to each airplane identified in the preceding applicability provision regardless of whether it has been modified altered or repaired in the area subject to the requirements of this AD For airplanes that have been modified altered or repaired so that the performance of the requirements of this AD is affected the owner operator must request approval for an alternative method of compliance in accordance with paragraph e of this AD The request should include an assessment of the effect of the modification alteration or repair on the unsafe condition addressed by this AD and if the unsafe condition has not been eliminated the request should include specific proposed actions to address it Compliance Required as indicated in the body of this AD unless already accomplished To prevent failure of the wing lift struts caused by corrosion damage which could eventually result in the wing separating from the airplane accomplish the following NOTE 3 The paragraph structure of this AD is as follows Level 1 a b c
13. 4c 608TC Pabudet omfatter For hindre bensinlekkasje i fremre del av kabinen skal f lgende kontroll og modifikasjon utf res l Vri bensinsystemets velgekran i posisjon off 2 Demonter den del av bensinsystemets returledning fra motorens fuel injector som g r fra brannskottet til samletanken Returledningen er installert p venstre side i fremre del av kabinen 3 Kontroll av den korte returledningen Kontroller den korte delen av returledningen som er plassert mellom brannskottet og enveisventilen for sprekker i omr det rundt flensene Dersom en finner sprekker skal ledningen skiftes ut med ny etter gene relle anvisninger gitt i FAA Advisory Circular 43 13 4 Utskifting av den lange returledningen Den del av returlednigen som er plassert mellom enveisventilen og samlertanken skal skiftes ut med ny som gir en mer fleksibel inn montering Den nye returledningen skal v re 8 lang i 1 4 aluminiums r r av godkjent kvalitet og skal v re utstyrt med godkjente fittings Se FAA Advisory Circular 43 13 for retningslinjer P midten av retur ledningen skal det b yes til en l kke med en diameter p 1 5 2 0 Ved montering av returledninger skal l kken plasseres horisontalt 5 Monter enveisventilen med pilen pekende bakover 6 Utf r funksjonspr ve av den sammenmonterte returledningen med hensyn til bensinlekkasje l Anm Maule Aircraft Corporation Service Letter 3l omhandler samme sak forts
14. 62C through 7365C A7366C A7367C 7368C through 7376C 7445C 7451C 7460C 7467C 7470C 7478C through 1 7480C 7484C through 7487C and 7515C M 5 210T 9001C through 9010C gt M 6 235 7249C 7356C 7379C through 7444C 7446C through 7450C 7452C through 7459C 7461C through 7466C 7468C 7469C through 7514C and 7517C M 6 180 8020C 8043C and 8065C through 8067C M 7 235 4001C through 4077C 4079C 4081C 4082C 4084C 4085C 4087C and 4088C MX 7 235 10001C through 10080C MX 7 180 11001C through 11065C MX 7 420 13001C through 13003C U S Register must comply with this AD c What problem does this AD address The actions specified by this AD are intended to detect and correct improper crimping of the Nicopress sleeve which could cause a control cable to slip from the sleeve M 4 220S 2001S A7355C 7356C 7357C A7358C 7359C A7360C A7361C M 5 180C 8001C through 8014C 8016C through 8019C 8021C 8023C through 8042C 8044C through 8064C and 8068C through 8094C 7471C through 7475C 7488C through 7507C 7509C 7511C M 7 235 12001C and 12002C These airplanes were manufactured as Model M 7 235 airplanes and then modified in accordance with STC SA2661S0 This modification changed the model designation of these airplanes to M 7 420 b Who must comply with this AD Anyone who wishes to operate any of the above airplanes on the This could result in loss of rudder elevator aileron or flap control 3 2000 09 06 d
15. IMRORETS OPPLAGRINGER P MAULE Forandringen gjelder for fly av typene Maule M 4 S N 3 til og med 94 n M ic W 1C tr 1 tr 10C tt MLS tt 18 tt n n 35 tt MLT tt 1T tt n 37 M h 210 12001 1045 M h 2100 1001 106LC M lh 2208 20018 4 920038 M h 2200 20010 4 20060 Luftfartsdirektoratet bestemmer herved at trimrorets opplagringer i sideroret p de ovenfor nevnte fly skal forandres i henhold til Maule Aircraft Corp Service Letter No 14 s snart som mulig og senest ved f rste 25 timers ettersyn Service Letter No 14 datert 19 februar 1965 f s ved henvendelse til forhandleren av flytypen Ref FAA AD No 68 7 8 og LVA 305 68 For ct angjeldende flysater 2 skol v re blitavktig utf re pen fart oe io venkormerge dryrmgl me z Pest Ker DP 17 69 LUFTDYKTIGHETSPABUD Maule 2 FORANDRING AV TRINSE FOR BALANSERORS WIRE PA KONTROLLS YLEN I MAULE Forandringen gjelder f lgende fly av typen Maule M S N 3 til og med 94 M T S N 1T til og med 3T M LC S N 1C til og med 11C M 1S S N 18 til og med 38 M 4 210 8 N 1001 til og med 1045 M 4 210C S N 10010 til og med 1075C 1079C og 1080C M l 220C S N 20010 til og med 20290 og 20320 P grunn av at lageret i den forreste trinse for balanserors wire som er montert nederst p kontrolls ylen p de ovenfor nevnte fly kan l sne og trinsen derved falle av bestemmer Luftfartsdirektoratet at f lgende forandring skal utf res
16. SA2661SO includes the procedures for incorporating the following items on the Maule Models M 7 235 and M 7 235A airplanes an Allison 250 B17C gas turbine engine Edo Model 797 2500 amphibious floats and Hartzell Model HC B3TF 7A T10173 11R or HC B3TF 7A T10173F 11R propellers NOTE 2 This AD applies to each airplane identified in the preceding applicability provision regardless of whether it has been modified altered or repaired in the area subject to the requirements of this AD For airplanes that have been modified altered or repaired so that the performance of the requirem ts of this AD is affected the owner operator must request approval for an alternative methed of conpliance in accordance with paragraph e of this AD The request should include an assessment of the effect of the modification alteration or repair on the unsafe condition addressed by this AD and if the unsafe condition has not been eliminated the request should include specific proposed actions to address it Compliance Required within the next 30 days after the effective date of this AD unless already accomplished To prevent ioss of airplane control or engine overspeed with consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight accomplish the following fa Amend the Limitations Section of the airplane flight manual AFM by inserting the following language Positio
17. al setup procedure may be necessary However the tolerance requirement of step 13 and the record keeping equirement of step 14 must be satisfied If battery power will be employed check to see that the battery has been properly charged The testing will take pproximately two hours Screen brightness and contrast should be set to match environmental conditions Verify that the instrument is set for the type of transducer being used i e single or dual element and that the requency setting is compatible with the transducer If a removable delay line is used remove it and place a drop of couplant between the transducer face and the delay ine to assure good transmission of ultrasonic energy Reassemble the delay line transducer and continue Program a velocity of 0 231 inch microsecond into the ultrasonic unit unless an alternative instrument calibration rocedure is used to set the sound velocity j Obtain a step wedge or steel shims per item 3 of the EQUIPMENT REQUIREMENTS Place the probe on the hickest sample using couplant Rotate the transducer slightly back and forth to ring the transducer to the sample djust the delay and range settings to arrive at an A trace signal display with the first backwall echo from the steel near he left side of the screen and the second backwall echo near the right of the screen Note that when a single element ransducer is used the initial pulse and the delay line steel interface will be off of the sc
18. d of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager Atlanta Aircraft Certification Office ACO One Crown Center 1895 Phoenix Boulevard suite 450 Atlanta Georgia 30349 1 The request shall be forwarded through an appropriate FAA Maintenance Inspector who may add nments and then send it to the Manager Atlanta ACO 2 Alternative methods of compliance approved in accordance with AD 95 26 18 are considered approved as alternative methods of compliance for this AD NOTE 4 Information concerning the existence of approved alternative methods of compliance with this AD if any may be obtained from the Atlanta ACO The removal the lift strut inspection in paragraph a 1 of this AD the applications and the installation required by this AD shall be done in accordance with Maule Service Bulletin No 11 dated October 30 1995 This incorporation by reference was previously approved by the Director of the Federal Register as of January 26 1996 61 FR 623 January 9 1996 Copies may be obtained from Maule Aerospace Technology Inc 2099 GA Hwy 133 South Moultrie Georgia 31768 Copies may be inspected at the FAA Central Region Office of the Regional Counsel Room 1558 601 E 12th Street Kansas City Missouri or at the Office of the Federal Register 800 North Capitol Street NW suite 700 Washington DC g This amendment superse
19. des AD 95 26 18 Amendment 39 9476 h This amendment becomes effective on September 9 1998 FOR FURTHER INFORMATION CONTACT Cindy Lorenzen Aerospace Engineer FAA Atlanta Aircraft Certification Office One Crown Center 1895 Phoenix Boulevard suite 450 Atlanta Georgia 30349 telephone 770 703 6078 facsimile 770 703 6097 Bilag til LDP 98 075A 98 15 18 3 APPENDIX TO AD 98 15 18 PROCEDURES AND REQUIREMENTS FOR ULTRASONIC INSPECTION OF MAULE WING LIFT STRUTS EQUIPMENT REQUIREMENTS A portable ultrasonic thickness gauge or flaw detector with echo to echo digital thickness readout capable of eading to 0 001 inch and an A trace waveform display will be needed to accomplish this inspection An ultrasonic probe with the following specifications will be needed to accomplish this inspection 10 MHz or jigher 0 283 inch or smaller diameter dual element or delay line transducer designed for thickness gauging The ransducer and ultrasonic system shall be capable of accurately measuring the thickness of AISI 4340 steel down to 020 inch An accuracy of 0 002 inch throughout a 0 020 inch to 0 050 inch thickness range while calibrating shall Je the criteria for acceptance Either a precision machined step wedge made of 4340 steel or similar steel with equivalent sound velocity or at east three shim samples of same material will be needed to accomplish this inspection One thickness of the step wedge yr shim shall b
20. dings can result 5 Take readings inside each square on the grid or at 1 4 inch increments along the ruler and record the results When taking a thickness reading rotate the transducer slightly back and forth and experiment with the angle of contact to produce the lowest thickness reading possible Pay close attention to the A scan display to assure that the thickness gate is triggering off of maximized backwall echoes l NOTE A reading shall not exceed 041 inch If a reading exceeds 041 inch repeat steps 13 and 14 of the STRUMENT SETUP section before proceeding further 0 If the A trace is unsteady or the thickness reading is clearly wrong adjust the signal gain and or gate setting to obtain reasonable and steady readings If any instrument setting is adjusted repeat steps 13 and 14 of the INSTRUMENT SETUP section before proceeding further 7 In areas where obstructions are present take a data point as close to the correct area as possible NOTE The strut wall contains a fabrication bead at approximately 40 of the strut chord The bead may interfere with accurate measurements in that specific location 8 A measurement of 0 024 inch or less shall require replacement of the strut prior to further flight 9 If at any time during testing an area is encountered where a valid thickness measurement cannot be obtained due to a loss of signal strength or quality the area shall be considered suspect These areas may have a remain
21. dministrasjonen Avd for luftfartsinspeksjon Postboks 18 1330 Oslo lufthavn Motordrevne luft Tueton os o 59 39 40 LUFTDYKTIGHETSP BUD fart y Tigr CIVILAIA OSLO Maule 2 Telex 17011 Idal n LDP mae PE Med hjemmel i lov om luftfart av 16 desember 1960 214 og 43 jfr kgl res av 8 desember 1961 litra K og Samferdselsdepartementets bemyndigelse av 23 mars 1964 fastsetter Luftfartsverket f lgende forskrift om luftdyktighet LT 81 REPARASJON OG UTSKIFTING AV SIDERORSPEDALENES V BAR R R P budet gjelder Maule Aircraft Corp modeller M 4 med serienr 1001 til og med 1045 og M l 210C med serienr 1001 C til og med 1117 C Pabudet omfatter For amp forhindre svikt i siderorspedalens y par og tilh rende struktur skal V bar r ret kontrolleres for sprekker ved hjelp av en lupe som forst rrer minst 10 ganger Anmerk Maule Aircraft Corp Service Bulletin nr 2 datert 17 februar 1981 eller senere revisjoner viser fremgangs m te for demontering for gj re rorpedalr ret tilgjengelig Dersom ingen sprekker blir funnet skal r ret modifiseres som vist i S B 1 Dersom sprekker blir funnet skal pkt 2 eller 3 utf res f r f rste flyging 9 Dersom sprekker p 1 tomme eller mindre blir funnet skal V bar r ret skiftes ut med modifisert r r med delnr 4130F 12 som angitt i S B eller sprekken stoppbores sveises og forsterkes som vist i 5 B og i h t Advisony Circular 43 13A Chapter 2 Ai
22. e less than or equal to 0 020 inch one shall be greater than or equal to 0 050 inch and at least one other tep or shim shall be between these two values t Glycerin light oil or similar non water based ultrasonic couplants are recommended in the setup and inspection rocedures Water based couplants containing appropriate corrosion inhibitors may be utilized provided they are emoved from both the reference standards and the test item after the inspection procedure is completed and adequate orrosion prevention steps are then taken to protect these items NOTE Couplant is defined as a substance used between the face of the transducer and test surface to improve ransmission of ultrasonic energy across the transducer strut interface NOTE If surface roughness due to paint loss or corrosion is present the surface should be sanded or polished mooth before testing to assure a consistent and smooth surface for making contact with the transducer Care shall be aken to remove a minimal amount of structural material Paint repairs may be necessary after the inspection to prevent urther corrosion damage from occurring Removal of surface irregularities will enhance the accuracy of the inspection echnique NSTRUMENT SETUP Set up the ultrasonic equipment for thickness measurements as specified in the instrument s user s manual 3ecause of the variety of equipment available to perform ultrasonic thickness measurements some modification to this ener
23. ewn 30 dager etter 1998 02 01 dersom ikke allerede utf rt Referanse FAA AD 97 26 14 Gyldighetsdato 1998 02 01 a aaa MERK For at angjeldende flymateriell skal v re luftdyktig m p budet v re utf rt til rett tid og notat om utf relsen f rt inn i vedkommende journal med henvisning til denne LDPs nummer Bilag til LDP 98 018 AIRWORTHINESS DIRECTIVE Q REGULATORY SUPPORT DIVISION U S De 5 Department P O BOX 26460 of Transportation OKLAHOMA CITY OKLAHOMA 73125 0460 Federal Aviation Administration The following Airworthiness Directive issued by the Federal Aviation Administration in accordance with the provisions of Federal Aviation Reguiations Part 39 applies to an aircraft model of which our records indicate you may be the registered owner Airworthiness Directives affect aviation safety and are regulations which require immediate attention You are Far Sun that no person may operate an aircraft to which an Airworthiness Directive applies except in accordance with the requirements of the Airworthiness Directive reference ubpart 39 3 97 26 14 MAULE Amendment 39 10257 Docket No 97 CE 40 AD Applicability The following airplane models certificated in any category Models MXT 7 420 and MX 7 420 airplanes all serial numbers and Models M 7 235 and M 7 235A airplanes all serial numbers that are modified in accordance with Maule Supplemental Type Certificate STC SA266180 NOTE 1 Maule STC
24. he provisions of Federal Aviation Regulations Part 39 applies to an aircraft model of which our records ingicale you may be the registered owner Airworthiness Directives affect aviation safety and are regulations which requir immediate attention You are cautioned that no person may operate an aircraft to which an Airworthiness Directive applies except in accordance with the requiraments of the Airworthiness Directive reference FAR Subpart 39 3 96 10 05 MAULE AEROSPACE TECHNOLOGIES INC Amendment 39 9610 Docket No 95 CE 22 AD Applicability The following airplane models and serial numbers certificated in any category that have Dual Exhaust System 5230F installed Model Serial Numbers M 4 210 1001 through 1045 M 4 210C 1001C through 1080C NOTE 1 This AD applies to each airplane identified in the preceding applicability provision regardless of whether it has been modified altered or repaired in the area subject to the requirements of this AD For airplanes that have been modified altered or repaired so that the performance of the requirements of this AD is affected the owner operator must request approval for an alternative method of compliance in accordance with paragraph c of this AD The request should include an assessment of the effect of the modification alteration or repair on the unsafe condition addressed by this AD and if the unsafe condition has not been eliminated the request should include specific proposed
25. igital display does not agree with the thickest thickness follow your instruments calibration recommendations to produce the correct thickness reading A slight adjustment in the velocity may be necessary to get both the thinnest and the thickest reading correct Document the changed velocity value 11 Place couplant on an area of the lift strut which is thought to be free of corrosion and ring the transducer to surface Minor adjustments to the signal and gate settings may be required to account for coupling improvements resulting from the paint layer The thickness gate level should be set just high enough so as not to be triggered by irrelevant signal noise An area on the upper surface of the lift strut above the inspection area would be a good location to complete this step and should produce a thickness reading between 0 034 inch and 0 041 inch 12 Repeat steps 8 9 10 and 11 until both thick and thin shim measurements are within tolerance and the lift strut measurement is reasonable and steady 13 Verify that the thickness value shown in the digital display is within 0 002 inch of the correct value for each of the three or more steps of the setup wedge or shims Make no further adjustments to the instrument settings 14 Record the ultrasonic versus actual thickness of all wedge steps or steel shims available as a record of setup INSPECTION PROCEDURE l Clean the lower 18 inches of the wing lift struts using a cleaner tha
26. ing wall thickness of less than 0 020 inch which is below the range of this setup or they may have small areas of localized corrosion or pitting present The latter case will result in a reduction in signal strength due to the sound being scattered from the rough surface and may result in a signal that includes echoes from the pits as well as the backwall The suspect area s shall be tested with a Maule Fabric Tester as specified in Maule Service Bulletin No 11 dated October 30 1995 10 Record the lift strut inspection in the aircraft log book Bilag til LDP 98 075A 98 15 18 5 Za Pencil Marks N Flexible Ruler Bottom View of Forward Lift Strut Bottom View of Rear Lift Strut Figure 1 AD 98 15 18 LUFTFARTSTILSYNET 1 TILSYNSAVDELING Postboks 8050 Dep 00310slo Besgksadresse MOTORDREVNE LUFTFART Y edusgate 2 Oslo LUFTDYKTIGHETSP BUD MAULE 7 post poctimottak coa dep no L D P Med hjemmel i lov av 11 juni 1993 nr 101 om luftfart kap XV 15 4 jf kap IV 4 1 og Samferdselsdepartementets bemyndigelse av 25 mars 1994 fastsetter Luftfartstilsynet f lgende forskrift om luftdyktighet 2000 041 NICOPRESS SLEEVE TERMINAL ENDS P budet gjelder Maule Aerospace Technology Inc modeller og serienummer som beskrevet i vedlagte kopi av FAA AD 2000 09 06 P budet omfatter Utf r tiltak som beskrevet i vedlagte kopi av FAA AD 2000 09 06 Tid for utf
27. ith this AD if any may be obtained from the Atlanta ACO Information related to this AD may be examined at the FAA Central Region Office of the Regional Counsel Room 1558 601 E 12th Street Kansas City Missouri 64106 g This amendment 39 10257 becomes effective on January 28 1998 FOR FURTHER INFORMATION CONTACT Wayne A Shade Aerospace Engineer FAA Atlanta Certification Office 1895 Phoenix Boulevard suite 450 Atlanta Georgia 30349 telephone 770 703 6094 facsimile 770 703 6097 saa LUFTDYKTIGHETSPABUD 27082 en LDP Med hjemmel i lov av 11 juni 1993 nr 101 om luftfart kap XV 15 4 jf kap IV 4 1 og Samferdselsdepartementets bemyndigelse av 25 mars 1994 fastsetter Luftfartsverket f lgende forskrift om luftdyktighet 98 075A KONTROLL UTSKIFTING AV WING LIFT STRUT P budet gjelder Alle Maule modeller som er listet i vedlagte kopi av FAA Corrected AD 98 15 18 P budet omfatter Utf r tiltak som beskrevet i vedlagte kopi av FAA Corrected AD 98 15 18 Tid for utf relse Til de tider som beskrevet i vedlagte kopi av FAA Corrected AD 98 15 18 med virkning fra denne LDP s gyldighetsdato Anm Denne LDP erstatter og opphever LDP 96 018 Referanse FAA Corrected AD 98 15 18 Gyldighetsdato 1998 12 01 SSeS rir MERK For at angjeldende flymateriell skal v re luftdyktig m p budet v re utf rt til rett tid og notat om utf relsen f rt inn i vedkommende journal med hen
28. ning of power levers below the flight idle stop while in flight s prohibited Such positioning could lead to loss of airplane control or may result in an engine overspeed condition and consequent loss of engine power b This action may be accomplished by incorporatirig a copy of this AD into the Limitations Section of the AFM c Amending the AFM as required by this AD may be performed by the owner operator holding at least a private pilot certificate as authorized by section 43 7 of the Federal Aviation Regulations 14 CFR 43 7 and must be entered into the aircraft records showing compliance with this AD in accordance with section 43 9 of the Federal Aviation Regulations 14 CFR 43 9 d Special flight permits may be issued in accordance with sections 21 197 and 21 199 of the Federal Aviation Regulations 14 CFR 21 197 and 21 199 to operate the airplane to a location where the requirements of this AD can be accomplished e An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager Atlanta Aircraft Certification Office ACO Campus Building 1701 Columbia Avenue suite 2 160 College Park Georgia 30337 2748 The request shall be forwarded through an appropriate FAA Maintenance Inspector who may add comments and then send it to the Manager Atlanta ACO NOTE 3 Information concerning the existence of approved alternative methods of compliance w
29. o For hindre trinsen i falle av opplagringsbolten i tilfelle som nevnt skal det monteres en stor skive p forsiden av trinsen og opp lagringsbolten skal skiftes ut med lengre bolt Den nye bolten settes inn forfra med skivene i f lgende orden AN960 516 skive AN365 52h mutter l AN5 27 bolt med hode forover 2 AN970 5 skive 3 AN960 516 skive 4 Trinse 5 Kontrolls ylen 6 T Forandringen skal utf res ved f rste 25 timers ettersyn Ref FAA AD No 69 20 2 og Maule Service Letter No 19 datert 4 september 1969 omhandler samme sak LUFTFARTSVERKET Hovedadministrasjonen Avd for luftfartsinspersjon Postboks 18 1330 Oslo lufthavn Telefor Oslo 02 21840 LUFTDYKTIGHETSP BUD Telex 17011 Idet n LDP Motordrevne luft fart y Maule la Erstatter Maule 1 Med hjemmel i lov om luftfart av 16 desember 1960 214 og 43 jfr kgl res av 8 desember 1961 litra K og Samferdselsdepartementels bemyndigelse av 23 mars 1964 fastsetter Luftfartsverkel f lgende forskrift om luftdyktighet 48 75 l a eneee mme tr ar oe e a aaa aa Sugust 1979 KONTROLL OG MODIFIKASJON AV BENSINSYSTEMET P MAULE P budet gjelder Maule Aircraft Corporation modell M 4 210 M 4 210C og M 5 210C med f lgende serienr M l 210 serienr 1001 til og med 1045 M 4 210C serienr 10010 til og med 1117C M 5 210C serienr 6001C til og med 6069C 6072C 6076C 6077C 6079C 6080c 608
30. or adjust the compliance time if i Your alternative method of compliance provides an equivalent level of safety and ii The Manager Atlanta Aircraft Certification Office ACO approves your alternative Submit your request through an FAA Principal Maintenance Inspector who may add comments and then send it to the Manager Atlanta ACO 2 This AD applies to each airplane identified in the preceding applicability provision regardless of whether it has been modified altered or repaired in the area subject to the requirements of this AD For airplanes that have been modified altered or repaired so that the performance of the requirements of this AD is affected the owner operator must request approval for an alternative method of compliance in accordance with paragraph e 1 of this AD The request should include an assessment of the effect of the modification alteration or repair on the unsafe condition addressed by this AD and if you have not eliminated the unsafe condition specific actions you propose to address it f Where can I get information about any already approved alternative methods of compliance Contact Cindy Lorenzen Aerospace Engineer FAA Atlanta Aircraft Certitication Office One Crown Center 1895 Phoenix Boulevard suite 450 Atlanta Georgia 30349 telephone 770 703 6078 facsimile 770 703 6097 4 2000 09 06 g What if I need to fly the airplane to another location to comply with this AD FAA can
31. orthy according to the inspection requirements included in these paragraphs Accomplish this installation in accordance with the applicable maintenance manual Thereafter inspect ase wing lift struts at intervals not to exceed 24 calendar months in accordance with the specifications presented in ither paragraph a 1 or a 2 of this AD 4 Install new Maule sealed wing lift struts P N 2200E or P N 2201E as applicable or FAA approved equivalent part numbers on each wing as specified in the INSTRUCTIONS section in Part II of Maule SB No 11 dated October 30 1995 b Ifholes are drilled into the sealed wing lift strut assemblies installed as specified in paragraph a 4 of this AD in order to attach cuffs door clips or other hardware inspect the wing lift struts at intervals not to exceed 24 calendar months using the procedures specified in either paragraph a 1 or a 2 including all subparagraphs of this AD c The repetitive inspections required by this AD may be terminated after installing new wing lift strut assemblies as specified in paragraph a 4 of this AD provided no holes are drilled in these strut assemblies as specified in paragraph b of this AD d Special flight permits may be issued in accordance with sections 21 197 and 21 199 of the Federal Aviation Regulations 14 CFR 21 197 and 21 199 to operate the airplane to a location where the requirements of this AD can be accomplished e An alternative metho
32. rcraft Metal Structure Section 2 Yelding 3 Dersom sprekker lengre 1 tomme blir funnet skal V bar r ret skiftes ut som i pkt 1 Tid for utf relse Innen 25 tiners gangtid etter 28 9 81 Referanser FAA AD 81 14 02 Amendment 39 4146 28 9 81 MERK For at angjeldende flymateriell skal v re luftdyktig m p budet v re utf rt til rett tid og notat om utf relsen f rt inn i ved Lammande surnslm rd hanvieninn til denne 1 OP s nummer LUFTFARTSVERKET LDP DRENERING AV DRIVSTOFFSYSTEMET P budet gjelder Maule Aerospace Technology modell M 4 og M 5 utstyrt med dreneringsplugger i P budet omfatter hoved og reservetankene 1 For lette drenering av drivstofftankene skal dreneringspluggene skiftes ut med Quick Drain Valves i henhold til Maule Service Bulletin nr 5 og Maule Service Letter nr 32 eller senere revisjoner av disse 2 F lgende revisjoner M 4 AFM Rev M 4 1800C M 4 220C M 5 210C M 5 220C Tid for utf relse Innen 50 timers gangtid Referanser FAA AD 84 09 07 skal inng i flygeh ndb kene M 5 180C Rev D M 5 210TC B M 5 235C A AFM datert 12 8 81 M 5 235C AFM datert 6 4 76 Supplement No 13 M 4 210 og M 4 210C AFM Supplement No 10 etter 8 2 85 MOTORDREVNE F re LUFTDYKTIGHETSPABUD Te k TOR One n LDP Med hjemmel om lov om luftfart av 11 juni 1993 kap IV 4 1 og kap XV 154 fastsetter Luftfartsve
33. reen to the left Adjust the gain to lace the amplitude of the first backwall signal at approximately 80 screen height on the A trace Ring the transducer on the thinnest step or shim using couplant Select positive half wave rectified negative alf wave rectified or filtered signal display to obtain the cleanest signal Adjust the pulse voltage pulse width and lamping to obtain the best signal resolution These settings can vary from one transducer to another and are also user lependent 9 Enable the thickness gate and adjust the gate so that it starts at the first backwall echo and ends at the second yackwall echo Measuring between the first and second backwall echoes will produce a measurement of the steel hickness that is not affected by the paint layer on the strut If instability of the gate trigger occurs adjust the gain gate evel and or damping to stabilize the thickness reading 4 98 15 18 Bilag til LDP 98 075A 9 Check the digital display reading and if it does not agree with the known thickness of the thinnest thickness follow your instrument s calibration recommendations to produce the correct thickness reading When a single element ansdueer is used this will usually involve adjusting the fine delay setting 10 Place the transducer on the thickest step of shim using couplant Adjust the thickness gate width so that the gate is triggered by the second backwall reflection of the thick section If the d
34. relse Til de tider som beskrevet i vedlagte kopi av FAA AD 2000 09 06 med virkning fra denne LDP s gyldighetsdato Referanse FAA AD 2000 09 06 Gyldighetsdato 2000 06 01 sn a ZCA ZZ TVAVA 7 MERK For at angjeldende flymateriell skal v re luftdyktig m p budet v re utf rt til rett tid og notat om utf relsen f rt inn i vedkommende journal med henvisning til denne LDPs nummer AIRWORTHINESS DIRECTIVE a REGULATORY SUPPORT DIVISION P O BOX 26460 OKLAHOMA CITY OKLAHOMA 73125 0460 U S Department of Transportation Federal Aviation _ Administration AD s are posted on the internet at http av info faa gov The following Airworthiness Directive issued by the Federal Aviation Administration in accordance with the provisions of Title 14 of the Code of Federal Regulations 14 CFR part 39 applies to an aircraft model of which our records indicate you may be the registered owner Airworthiness Directives affect aviation safety and are regulations which require immediate attention You are cautioned that no person may operate an aircraft to which an Airworthiness Directive applies except in accordance with the requirements of the Airworthiness Directive reference 14 CFR part 39 subpart 39 3 2000 09 06 MAULE AEROSPACE TECHNOLOGY INC Amendment 39 11715 Docket No 2000 CE 04 AD a What airplanes are affected by this AD This AD affects the following airplane models and serial numbers
35. rket f lgende forskrift om luftdyktighet 96 018 KONTROLL OG UTSKIFTING AV WING LIFT STRUTS P budet gjelder Maule Aerospace Technology inc f lgende modeller M 4 M 5 M 6 M 7 MX 7 MXT 7 alle serier gt Og MT 7 235 M 8 235 alle serienummer h Pabudet omfatter K Er Utf r tiltak som beskrevet i PN haga FAA AD 95 26 18 Gyldighetsd i 01 03 96 L a a a a a aaaaaasasasaasasaseseoooseoeoooesesesest5l l MERK For at angjeldende flymateriell skal v re luftdyktig m p budet v re utf rt til rett tid og notat om utf relsen f rt inn i vedkommende journal med henvisning til denne LDPs nummer Bilag til LDP 96 018 AIRWORTHINESS DIRECTIVE Q REGULATORY SUPPORT DIVISION U S Department P O BOX 26460 of Transportation OKLAHOMA CITY OKLAHOMA 73125 0460 Federal Aviation to Administration The following Airworthiness Directive issued by the Federal Aviation Administration in accordance with the provisions of Federal Aviation Regulations Part 39 applies to an aircraft model of which our records indicate you may be the registered owner Airworthiness Directives affect aviation safety and are regulations which require immediate attention You are cautioned that no person may operate an aircraft to which an Airworthiness Directive applies except in accordance with the requirements of the Airworthiness Directive reference FAR Subpart 39 3 95 26 18 MAULE AEROSPACE TECHNOLOGY INC Amendment 39
36. t will remove all dirt and grease Dirt and ease will adversely affect the accuracy of the inspection technique Light sanding or polishing may also be required to reduce surface roughness as noted in the EQUIPMENT REQUIREMENTS section 2 Using a flexible ruler draw a 1 4 inch grid on the surface of the first 11 inches from the lower end of the strut as shown in Maule Service Bulletin No 11 dated October 30 1995 as applicable This can be done using a soft 2 pencil and should be done on both faces of the strut As an alternative to drawing a complete grid make two rows of marks spaced every 1 4 inch across the width of the strut One row of marks should be about 11 inches from the lower end of the strut and the second row should be several inches away where the strut starts to narrow Lay the flexible ruler between respective tick marks of the two rows and use tape or a rubber band to keep the miler in place See Figure 1 3 Apply a generous amount of couplant inside each of the square areas or along the edge of the ruler Re application of couplant may be necessary 4 Place the transducer inside the first square area of the drawn grid or at the first 1 4 inch mark on the ruler and ring the transducer to the strut When using a dual element transducer be very careful to record the thickness value with the axis of the transducer elements perpendicular to any curvature in the strut If this is not done loss of signal or inaccurate rea
37. vel of safety may be approved by the Manager FAA Atlanta Aircraft Certification Office Campus Building 1701 Columibia Avenue suite 2 160 College Park Georgia 30337 2748 The request shall be forwarded through an appropriate FAA Maintenance Inspector who may add comments and then send it to the Manager Atlanta Aircraft Certification Office NOTE 4 Information concerning the existence of approved alternative methods of compliance with this AD if any may be obtained from the Atlanta Aircraft Certification Office c The inspection and possible replacements required by this AD shall be done in accordance with Maule Service Bulletin No 11 Issued October 30 1995 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U S C 552 a and 1 CFR part 51 Copies may be obtained from Maule Aerospace Technology Inc 2099 GA Hwy 133 South Moultrie Georgia 31768 Copies may be inspected at the FAA Central Region Office of the Assistant Chief Counsel Room 1558 601 E 12th Street Kansas City Missouri or at the Office of the Federal Register 800 North Capitol Street NW 7th Floor suite 700 Washington DC d This amendment 39 9476 becomes effective on January 26 1996 FOR FURTHER INFORMATION CONTACT Cindy Lorenzen Aerospace Engineer FAA Atlanta Aircraft Certification Office Campus Building 1701 Columbia Avenue suite 2 160 College Park Georgia 30337 2748 telephone 404 305
38. visning til denne LDPs nummer Bilag til LDP 98 075A CORRECTED AIRWORTHINESS DIRECTIVE Q REGULATORY SUPPORT DIVISION U S Department P O BOX 26460 of Transportation OKLAHOMA CITY OKLAHOMA 73125 0460 Federal Aviation Administration The following Airworthiness Directive issued by the Federal Aviation Administration in accordance with the provisions of Federal Aviation Regulations Part 39 applies to an aircraft model of which our records indicate you may be the registered owner Airworthiness Directives affect aviation safety and are regulations which require immediate attention You are cautioned that no person may operate an aircraft to which an Airworthiness Directive applies except in accordance with the requirements of the Airworthiness Directive reference FAR Subpart 39 3 98 15 18 MAULE AEROSPACE TECHNOLOGY CORP Amendment 39 10669 Docket No 98 CE 01 AD Supersedes AD 95 26 18 Amendment 39 9476 Applicability The following airplane models all serial numbers certificated in any category that are equipped with part number P N 2079E or FAA approved equivalent part number rear wing lift struts or P N 2080E or FAA approved equivalent part number front wing lift struts Bee Dee M 4 M 4 M 4C M 45 M 4T M 4 180C M 4 1808 M 4 180T M 4 210 M 4 210C M 4 2108 M 4 210T M 4 220 M 4 220C M 4 2205 M 4 220T M 5 180C M 5 200 M 5 210C M 5 210TC M 5 220C M 5 235C M 6 180 M 6 235 M 7 235 MX 7 235 MX 7 180 MX 7 420 MXT 7 180 MT 7
39. y reference was approved by the Director of the Federal Register in accordance with 5 U S C 552 a and 1 CFR part 51 Copies may be obtained from Maule Aerospace Technology Inc Lake Maule Route 5 Box 318 Moultrie Georgia 31768 Copies may be inspected at the FAA Central R gion Office of the Assistant Chief Counsel Room 1558 601 E 12th Street Kansas City Missouri or at the Office of the Federal Register 800 North Capitol Street NW suite 700 Washington DC e This amendment becomes effective on June 21 1996 a FOR FURTHER INFORMATION CONTACT Ms Juanita Craft Lloyd Aerospace Engineer RAA Atlanta Aircraft Certification Office Campus Building 1701 Columbia Avenue suite 2 160 College Park Georgia 30337 2748 telephone 404 305 7373 facsimile 404 305 7348 MOTORDREVNE LUFTFART Y LUFTFARTSVERKET Hovedadministrasjonen Luftfartsinspeksjonen Postboks 8124 Dep 0032 Oslo am aana LUFTDYKTIGHETSPABUD Telex 71032 enfb n LDP MAULE 5 Med hjemmel i lov av 11 juni 1993 nr 101 om luftfart kap XV 15 4 jf kap IV 4 1 og Samferdselsdepartementets bemyndigelse av 25 mars 1994 fastsetter Luftfartsverket f lgende forskrift om luftdyktighet 98 018 REVISJON AV FLIGHT MANUAL Pabudet gjelder Alle Maule modeller som er listet i vedlagte kopi av FAA AD 97 26 14 Pabudet omfatter Utf r tiltak som beskrevet i vedlagte kopi av FAA AD 97 26 14 Tid for utf relse Inn
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