t67manual.pdf

March 18, 2018 | Author: Barut Brkk | Category: Flap (Aeronautics), Stall (Fluid Mechanics), Takeoff, Aerospace Engineering, Aeronautics
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November 2004Temporary Amendment No 10 to TP T67M200lFM FIREFLY T67M200 PILOT'S NOTES INSERTION OF LEAVES INSERT Page 1 of 3 Page 2 of 3 Page 3 of 3 - facing page P D-I (Supplement O) - facing page P D-2 (Supplement D) - facing page P D-3 (Supplement D) TEMPORARY AMENDMENT RECORD SHEET h i Record the incorporation of tstemporary amendment leaflet THIS INSTRUCTION SHEET Complete the deta~ls below and return this complete sheet to Slingsby Aviation Ltd Technical Publications Department Iacknowledge receipt of Temporary Amendment No 10 to T67M200IFM Company: GrAiih &mn~cuyt!cd! , , f ? S f ~ . < ;di!dn Date: z g . 7 .. .. d . ... .. . 0 . , .. , ,, 2....o ..., , , PILOTS NOTES FIREFLY T67M200 PILOTS NOTES rncorporatlng t h e CAA approved fl~ght manual Registration : Constructors No. TC-CBA 2030 CAA Approved Date: Au&t 1985 TP T67M200lFM . I I) . NOTAMS or a e r o n a u t i c a l Information Circulars. ~ u b l i c a t i o n i n .. a r e t r i e v a l system.T67M200/FM . . Rules Regulations. Procedures and I n f o r m a t i o n c o n t a i n e d i n t h e A i r N a v i g a t i o n Order. e l e c t r o n i c . . r i g h t s reserved. N o t h i n g i n t h i s Manual must be . mechanical. s t o r e d A l l . r e c o r d i n g or otherwise. . w i t h o u t t h e pri'or p e r m i s s i o n o f t h e p u b l i s h e r s .FIREFLY T67M200 C o p y r i g h t c 1985 S l i n g s b y A v i a t i o n PLC. . Rules o f t h e A i r and A i r T r a f f i c C o n t r o l Regulations. $ may be reproduced. photocopying. CAA Approved August 1985 TP . No p a r t a f t h i s . o r t r a n s m i t t e d i n any form o r by any means. t h e UK A i r P i l o t . . F i r s t p u b l i s h e d i n Great B r i t a i n b y S l i n g s b y A v i a t i o n PLC 1985 P u b l i s h e d & p r i n t e d i n G r e a t B r i t a i n by S l i n g s b y A v i a t i o n P i c .t a k ~ nas superseding t h e L e g i s l a t i on. t h e A i r N a v i g a t i o n (General) R e g u l a t i o n s . ..................................... ...............TSiMZOO/FM 1 1 ................................. ........... D e s c r i p t i o n and Use Handling C e n t r e o f G r a v i t y Computer and I l l u s t r a t i o n s Suppl enents 0-1 0-3 0-5 0-9 9-11 0-13 1 2 3 4 5 6 i 8 9 CAA Approved August 1985 TP ..... .. Leading P a r t i c u l a r s ana Dimensions L i m i t a t i o n s and P l a c a r d s N o r r a l Procedures Emergency Procedures Performance and F l i g h t P l a n n i n g Systems Layout..................... .. .................................................................................SLINGSBY FIREFLY T67M200 CO?(IEi~TS Section 0 T i t l e Page Contents Notes t o Readers Index and Record o f Amendments Amendment H i g h l i g h t s L i s t o f Associ a t e d P u b l i c a t i o n s Section Section Section Section Section Section Section Section Section k e ........AVlATlCN PLC PILOTS NOTES FIREFLY T67M200 ?ILOTS NOTES ........................................... ........................... PILOTS NOTES FIREFLY T67M200 INTENTIONALLY BLANK . . -. Check L i s t s 4. The more d e t a i l e d i n f o r m a t i o n necessary f o r t h e maintenance o f t h e a i r c r a f t i s contained i n t h e r e l e v a n t maker's p u b l i c a t i o n s l i s t e d on Page 0-13. checks and emergencies a r e l a i d o u t i n S e c i i o n j 2. 6 CAA A p r i l 1998 A8 TP . those t o which reference might be r e q u i r e d d u r i n g a i r c r a f t o p e r a t i o n a r e a l s o l a i d out i n t h e F l i g h t Reference Cards..%.... DAI 2243/46 CAA Approval No A u t h o r i t y o f t h i s Manual This manual forms p a r t o f t h e UK CAA documentation f o r t h e a i r c r a f t shown be1 ow and incorporates t h e CAA approved A i r c r a f t F l i g h t Manual a t Section 1 t o 4.PILOTS NOTES FIREFLY T67M200 NOTICE TO READERS Introduction > 1. 3 and 4.. p a r t s o f 5 and 8 p l u s any CAA Supplements: t h e l i m i t a t i o n s l i s t e d i n Section 2 must be observed as must any f u r t h e r l i m i t a t i o n s i n t h e CAA Supplements a t t h e end o f t h e manual.T67M200/FM ro roved . Pages i n Sections 5 and 8 which a r e n o t s u b j e c t t o CAA approval have t h e words CAA Approved omitted from t h e page references. . The l i m i t a t i o n s . Sections 1 t o 4.?be. engine..... This manual complies w i t h FAR 23 and B r i t i s h C i v i l A i r w o r t h i n e s s Requirements where required. This manual i s produced by Slingsby A v i a t i o n L t d and incorporates t h e CAA approved f l i g h t manual. systems and handling i n f o r m a t i o n necessary f o r t h e o p e r a t i o n o f t h e F i r e f l y . p a r t s o f Sections 5 and 8 p l u s any CAA Supplements form t h e F l i g h t Manual and c a r r y CAA approval... .1. Signed Date .. Statement o f I n i t i a l C e r t i f i c a t i o n 2. p r o p e l l e r . i t combines a l l airframe.. The amendment service consists of Permanent Amendments and Amendment Highlights (obtainable from Slingsby Aviation PLC) as fol 1ows : a) Amendments will be issued as necessary and will be consecutively numbered. Each page of t h i s manual bears a section and page number. b) Amendment Highlights Where amendments contain s i g n i f i c a n t changes t o operating information t h i s will be summarised on an Amendments Highlight sheet which will come with the amendment. When reference i s made t o l e f t and r i g h t .J{SL. The procedures outlined in t h i s manual form the basis of good operating procedures b u t consideration of airmanship may. Where amendments contain significant additions o r a i t e r a t i o n s t o < and where text has t h e t e x t . . P.NGSLIY A\lIArIoN LTn PILOTS NOTES FIREFLY T67M200 Amendments 5. these directions a r e invariably intended t o represent directions as seen by a p i l o t correctly seated in the a i r c r a f t . on occasions. d i c t a t e other courses of action. 10. They will be issued as replacement sheets where practicable and will have t h e amendment l i s t number and date presented on i t . When numbers appear in brackets in the t e x t they r e f e r t o the key in t h e fold-out i l l u s t r a t i o n s in Section 8. A complete new Amendments Highlight sheet will be issued with each amendment l i s t and the previous 2 permanent Amendments Lists highlights will be retained on it... 11. 9. The pages of any part of the manual can be checked by referring t o the l i s t of contents f o r each chapter which l i s t s the f i r s t and l a s t e f f e c t i v e page f o r each chapter and section. these will be marked > been removed will be marked < > . All gauged o r measured quantities quoted indicated values unless otherwise stated..O-6 CAA Approved . Convention i n t h e Text 7. a document number and a date of issue. o r clockwise and anti-clockwise. in the text are 8.. Adherence t o Procedures 6. fore and a f t . Warnings a r e inserted in the text only when they contain information of p a r t i c u l a r safety significance which might not be evident t o an operator unfamiliar with the a i r c r a f t type and design. t h i s i s t o be i n c o r p o r a t e d i n S e c t i o n 9 of t h i s manual and i t s i n c l u s i o n recorded i n t h e supplement r e c o r d a t t h e b e g i n n i n g o f S e c t i o n 9. no standard chapter can be I n i o r m a t i on on a l l v a r i able-standard or.PILOTS NOTES FIREFLY T67M200 Supplements 12 Where d i f f e r e n t o p t i o n s e x i s t f o r t h e f i t t i n g o r where a d d i t i o n a l or r c o d i f i e d equipment may be f i t t e d . CAA Approved August 1985 TP . i n c o r p o r a t e d i n t h e manual.T67M200/FM . non-standard equipment i s t h u s i s s u e d i n dn a p p r o p r i a t e supplement. PILOTS NOTES FIREFLY T67M200 - INTENTIONALLY BLANK .T67M200/FM .~ - CAA Approved August 1985 TP . . kl 3 4 '> D K S i -3 pJwed ' r F P . u ~ ~ IOS~M ~ M/W (38 3' P f izcfi.i s t No: Date Issued - Date Incorporated Signature 1 R. ~~-.iarr!% \4Y? Dewnbi~ I9M &M ixTE.'> s E k ~ i ib a~ Y f D c . 2 .k i~u'k.O-9 CAA Approved August 1985 TP .T67M200/FM . .PILOTS NOTES FIREFLY T67M200 INDEX AND RECORD OFAENDMENTS ZSSUED BY THE CONSTRUCTOR Amendments Amendment L.. .PILOTS NOTES FIREFLY T67M200 I NTENTI0NALL.Y BLANK CAA Approved August 1985 TP T67M200/FM . 10A CAA Approved April 1998 A8 TP T67M200lFM .PILOTS NOTES FIREFLY T67MZOU RECORD OF TEMPRORARY AMENDMENT LEAFLETS (TAL) / TAL CONTENT DATE ISSUED DATE INCORPORATED P 0 . PILOTS NOTES FIREFLY T'67M200 INTENTIONALLY BLANK P 0-106 CAA Approved April 1998 A8 TP T67M200iFM . 7.1 by t h e United Kingdom Civil Aviation Authority Date...: .-11 CAA Approved A p r i 1 1998 A8 TP .3 added M i n o r t e x t changes Paragraph 4 1 3 added Paragraph 4 1.T67M200/FM ..7. t h e p r e v i o u s 2 permanent amendment l i s t s w i l l be r e t a i n e d .. P..-3 1-4 Section 2 contents 2-2 2-4 2-5 2.. -qg . .....-6 2-8 2-9 Section 3 contents 3-1 3-5 3 -8 3-9 t o 3-11 3-12 3-13 & 3-14 Section 4 contents 4..O.. Amendment L i s t No: 8 Subject Minor t e x t correction Record o f Temporary Amendment i e a f i e t s (TAL~ Amendment H i g h l i g h t s New Pages (Check l i s t ) New f i g u r e Minor t e x t change Mod 458 and 468 i n f o r m a t i o n added Mod 129 and 822 i n f o r m a t i o n added Amended page numbers M i n o r t e x t change Mod 656 and 7576 i n f o r m a t i o n added M i n o r t e x t changes M i n o r t e x t changes M i n o r t e x t changes Mod 656 i n f o r m a t i o n added Mod 7578 i n f o r m a t i o n added Mod 129 and 810 i n f o r m a t i o n added M i n o r l a y o u t change Paragraph 3.3 added M i n o r t e x t changes M i n o r t e x t changes Mod 312 i n f o r m a t i o n added M i n o r t e x t changes Paragraph 3..d < ~A\lIATION LTO ' . N m PILOTS NOTES FIREFLY T67M200 AMENDMENT HIGHLIGHTS A c o m p l e t e new sheet w i l l be i s s u e d w i t h each amendment l i s t .-2 1.....3 added Minor t e x t correction AS: p o s i t i o n e i i o i j up-dated Correction t o tables Pages (s) 0-11 ( t h i s page) 0-15 & 0-16 1-1 1... .) Amendment L i s t No. 8 Subject Page (s) -.KSW A\'iATION LTO PILOTS NOTES FIREFLY T67M200 AMENDMENT HIGHLIGHTS (Con't.T67M200/FM .)-LC Section 6 contents 6-7 and 6-8 6-8A and 6-8B 6-9 and 6-10 6. 5 and 6 P.-11 6-14 6-160 6-28 6-35 and 6-36 7-3 .0-12 CAA Approved A p r i l 1998 A8 TP .-'{S~.. 7-4 7-5 and 7-6 7-12 and 7-13 8-516 t o 8-9/10 NOTE T h i s amendment d e l e t e s TAL's 4. M i n o r t e x t change C o r r e c t i o n t o page i e i Amend page numbers M i n o r t e x t change Mod 300 and 336 Fuel s e l e c t o r c o n t r o l l a b e l s added M i n o r t e x t change New f u e l system diagram M i n o r t e x t change M i n o r l a y o u t change Mod 656 i n f o r m a t i o n added M i n o r t e x t change M i n o r t e x t changes Mod 656 i n f o r m a t i o n added Minor t e x t change Minor t e x t change Page r e f e r e n c e c o r r e c t i o n 5-40 and 5-5 7 5-1 A^ r l r l L U . elevant t o make Navigation > CAA Approved March 1997 A1 TPaT67M200/FM .~{SLPHGSGY AV~ATICN PLC PILOTS NOTES FIREFLY T67M200 LIST OF ASSOCIATED PUBLICATIONS > ENGINE PROPELLER RADIOS . PROPELLERWERK HOFFMANN HO-V123 I n s t r u c t i o n Manual Cmrnunications ) ) Handbooks r.- AVCO LYCCMING AEIO-360 S e r i e s O p e r a t i o n Manual. . Contents 1-1 to 1-4 Section 2 .T67MZOO/FM / .- 7 Amdt No 8 7 ' August 1985 April 1998 August 1985 April 1998 March 1987 August 1985 April 1988 July 1988 April 1988 April 1998 March 1987 April 1998 April 1998 April 1998 March 1988 April 1998 September 1987 April 1998 December '1988 April 1998 April 1998 April 1988 I April 1998 April 1990 April 1998 April 1990 April 1990 April 1998 April 1998 December 1988 April 1998 April 1998 August 1985 September 1987 July 1988 August 1985 March 1988 August 1998 March 1988 August 1998 August 1990 August .Contents to 3-1 3-2 to 3.15 to 6-16A 6-16B 6-17 .1 1 6-12 and 6-1 3 6-14 6.10 0-10A to 0-12 0-13 0-14 0-15 and 0-1 6 Section I.1998 March 1987 - 8 1 8 5 8 8 1 8 7 8 4 8 2 8 6 8 8 7 8 I ' 8 7 7 8 8 6 8 8 I -= =- 1 CAA Approved A p r i l 1998 A8 TP ..Contents 5-1 5-2 5-3 5-4 5-4A 5-4B 5-5 5-6 5.-7 to 5-12 Section 6 .Contents 2-1 2-2 2-3 2-4 to 2-9 2-10 Section 3 .PILOTS NOTES FIREFLY T67M200 CHECKLIST Number of pages is 133 (plus relevant supplements and temporary amendments) consisting of the following : Page No to 0-4 0-1 0-5 0-6 to 0.=: = ..2 6-3 6-4 and 6-5 6-6 6-7 to 6.Contents to 4-8 Section 5 .-4 3-5 3-6 3-7 to 3-74 Section 4 .Contents Contents (continued) to 6-1 6. Contents to 7-2 '7-3to 7-6 7-7 and 7-8 7-9 7-10 to 7-11 '7-12 and 7-13 7-.33 6-34 6--35and 6-36 6 3 7 and 6-38 Section 7 -. Contents 8-1I2 and 8-3 8-4 8-516 to 8-9110 d Page No March 1988 December 1988 August 1985 March 1988 August 1985 March 1988 August 1990 Augusi I985 March 1988 March 1988 March 1988 March 1988 April 1998 A u g ~ ~1985 st August 1985 April 1998 August 1985 August 1985 August 1985 April 1998 August 1985 March 1988 April 1990 August 1985 April 1998 P.PILOTS NOTES FIREFLY T67M200 6-18 and 6-18A 6-19 and 6-20 6-2 1 6.0-16 CAA Approved April 1998 A8 T P T67M200/FM .I4 Section 8 -.-22 6-23 to 6-23 6-26 6-27 6-28 (5.29 and 6-30 6-31 6-32 and 6. .. . . . . . . .. . . .. < Dimensions and Leading P a r t i c u l a r s . 1-2. . . . . . . .T67M200/FM . . . . . . . . .2 '3 View P l a n w i t h p a i n t r e s t r i c t i o n s . 1-1 . . . . . . . . . . . .PILOTS NOTES FIREFLY T67M200 SECTION 1 LEADING PARTICULARS AND DIMENSIONS CONTENTS > 1. . . l . . . . .. . . . . .4 CAA Approved J u l y 1988 A5 TP . . . . . . L a s t e f f e c t i v e page i s P . . . . . .1 1. . . . . . . Y T67M200 INTENTIONALLY BLANK CAA Approved A u g u s t 1985 Tp T67M200/FM . .PILOTS NOTES F1REFL. PILOTS NOTES FIREFLY T67M200 > 1. T 6 7 M 2 0 0 / F M .1 3 VIEW PLAN WITH P A I N T RESTRICTIONS All Dimensions in Metres KEY TO COLOUR RESTRICTIONS Unrestricted I Only colours approved by the manufacturer (Lighter colours and shades are preferable to dark ones) CAA Approved April 1998 A8 TP . ......................... uP 16" +lo Down 12.........= O v e r a l 1 1 ength Overall height ................................................. 3" ............................... : ...................................................................................25' Down 11-75" + l o Movements (Pre Mod 392) > +lo (Post Mod 392) .1-2 CAA Approved A p r i 1 1998 A8 TP ................................................. 3"304 P r o f i l e and i n c i d e n c e a t t h e wing r o o t NACA 23 015 P r o f i l e and i n c i d e n c e a t t h e t i p NACA 23 013 A i 1e r o n Surface area .................. P o s i t i o n 1) 18" +lo-Z0down Takeoff ( L a n d i n g ( P o s i t i o n 2) 40" +lo-3"down P................ .PILOTS NOTES FIREFLY 1'67M200 1..... 74m2 ............52m2 each ............. 0°20' ............. 7...................T67M200/FM .................. 1......................................................... 0............ ..................... 10............... ?........................60m2 ...........2 DIMENSIONS AND LEADING PARTICULARS O v e r a l l Dimensions Wing span ....................................UP 14" +lo Mass b a l a n c e (Pre Mod 276) (Post Mod 276) .............60m ................................. Balanced t o 43 kg mm + 5 k g m m ( T r a i 1 i n g Edge Down) t o 77 kg mm + 5 k g mm ( T r a i l i n g Edge Down) < Flap T o t a l s u r f a c e area Deflections . ........ 12.............................................................................................................................................323111 .....................?5m Surface area Dihedral ....... Balanced ................ 00 ....4 bar (35 p s i ) (Post Md 468) o c P..5 bar (50 p s i ) ........ .. 4 + 1" 2 Elevator surface area ...99m Movements ................................6......................... .................................... 1...........................00 .....80mZ 2 Rudder ........................5... . e 30"+1° o Each s i d c Undercarri aqe Tricycle Type Forward shock absorber Mainwheel shock absorber Track oleo-pneumatic pressure 7 bar (100 p s i ) oleo-pneumatic pressure 5 ....... ..................................81111 movements (Pre Md 458) .................. 5 bar (80 p s i ) . .......... .................. 0 .............. ..7 bar (25 p s i ) (Pre Mod 468) pressure 2...... ........................... uP 2O0*2" Down 2Z0+3"-0" Trim t a b movements .... s i d e 30°t2" o Each (Post Md 458) . ................................................ ..................................................495111 Rear Tyre ......-0% 100% +5% Fin Surface area Rudder Surface area > ........65m2 Incidence t o fuselage reference ......6 pressure 1.......PILOTS NOTES FIREFLY T67MZ00 Tai l p l ane Fixed s u r f a c e area .............................44m Wheel Base Front Tyre > .............................................. ........................................................ 2. Up & Down 24"+b0-2" Elevator mass balance .................. ... 0... 1.....................0......5 pressure '3....... ......................................l-3 CAA Approved Aoril 1998 A 8 .................. ........30 from -18°C t o 21°C SAE 20 Below -12°C S t r a i g h t m i n e r a l o i l f o r f i r s t 50 h r s then ashless d i s p e r s a n t grade may be used....7 l i t r ' e s ) ... Hoffmann HO-V123K-KV/180DT ........ ..........7 1 it r e s ) Useable f u e l 2 x 1 7 .......................... F i x e d windscreen w i t h canopy h i n g i n g upwards and rearward c Luggage ............ Lycoming AEIO-360-A1E r a t i n g s .. 30 kg (66 l b s ) P ........................................... Tank c a p a c i t y 2 x 17................HO-V123K-V/180R Hoffmann DT < z ....... h i n g i n g One p i e c e canopy upwards and rearward ... Cleveland d i s c brakes w i t h d u p l i c a t e t o e brakes and w i t h p a r k i n g brake.......................................................... .. 2 seats s i d e by s i d e Mod 129) Canopy (Pre (Post Mod 129) .... ........ ......... MIL Spec..................... ................................. An a l t e r n a t i v e warm a i r s u p p l y a u t o m a t i c a l l y opens i f t h e engine a i r i n t a k e becomes blocked...............40.......... Propulsion U n i t Engine Engine Fuel Oil ...... Hoffmann HO-V123K-V/180 ................o r 50 Above 15.................................T67M200/FM .....5"C ........................ P r o p e l l e r (Post Mod 333) (Pre Mod 333) (Post Mod 822) Cockpit > ........................75 Imp Gal (80...............AVGAS ......................................... from -1°C t o 32°C SAE 40 SAE 40 o r ..... L-22851 Grade SAE 15W-50 o r 20W-50 A l l Temperatures SAE 60 Above 27OC SAE.. 1-4 CAA Approved A p r i l 1998 A8 TP .....PILOTS NOTES FIREFLY T67M200 Wheel Brakes Mainwheels o n l y ...................... 3 1 Imp Gal (78......... 200 bhp a t 2700 rpm 100LL.... . .. 2-9 2 ..... . .. .... .. 3 O p e r a t i n g Temperatures ...... ... .. 2 . .... ... .... . .... . . . . . 2-5 L i m i t a t i o n s f o r I n v e r t e d F l i g h t ...2 2. 2 .2-9 .. .. .. ... . .... . .... . .. . ... .. .... .... ... . .. .. ....5. .. . . .4 2.. 2-3 L i m i t a t i o n s f o r A e r o b a t i c s .... ... ... .... . .... ... .. ..... . .2 2 .. ... .... ........ ...... ..... .. . 2-4 F l i g h t i n I c i n g C o n d i t i o n s ... . 7 . .2-4... . .... .. .. ...... .. .. . . . ... . . . .. .. 5 2 . . . . .. .. .. . . .. . .... ... . ..... ... ..6 2. .. ... ..6 Placards . 5.... . . ....... .... ..5. ... ... . . ... . . ..... .. .... 2 .... 1 ... . . .. .... ... . .2-3.... .. .. 1 I n s t r u m e n t Markings .. . .. . .. . . . ......... . . . .... .T67M2001FM ... .. . . .. .. . .. .. 2-3 2. .. . .. . ....... . . . ...9 CAA Approved A p r i l 1998 A8 TP ..5. ... . .. ........ ... . . . . .. .. .. .....5 .. .... . ...... .. . 2-9 < 2 . . . .... . ... .. . .. ..... 2-1 Engine L i m i t a t i o n s .... . . . .... ... . 2-5 ... ... ... ....... .. . . .. . .... . . ..5 ...... ... . . ...2 Maximum T a k e o f f and L a n d i n g A l t i t u d e .. .. . .. . .. .7. . . . .. .. ............2-9... . . .. .... . . . .. . ..... .. . .. .. 2-2 A i r f r a m e L i m i t a t i o n s . . . . . . . ... ... . . ... . .... . 2. .. . .. . ... . .. . . 8 Paint Finish ... . . ...... .. .. . . .. .. ... .. ... . .. .. ... ... ...... .. ..... .. . . ... . . . . .... .2-5.. 2-3 Weights f o r T a k e o f f and Landing ... . .. . .7 2.. .. .5.. .. . .... F l i g h t i n I M C or a t N i g h t .. ..... . . . ....... ..... . . . . . ... . .... 2-1 Maximum Occupants 2.... ..... . ....... . .... 2-3 Loading .1 ..... ... .... . ... ..... .....7... .. . ...8 C e n t r e o f G r a v i t y Measurement and L i m i t a t i o n s ... ...... ..... ... .. .. 7 Operational Limitations ...... 2-5 2. . Minimum Crew 2..... . ..... ... . . . L i m i t i n g Speeds (IAS) ... . .... .. > 2... .... . 6 . . ... 2-9 L a s t e f f e c t i v e page i s P 2 .. . . ... . . . . .. . . . . . . . .. . .. .. . ..........4 2 . . .. Class and Category o f C e r t i f i c a t i o n . ... ... .. .. 2 ...... . ...<<SUW~~~ A\... . ..... .2-7. . . . ... . . .... ... . .. ..... .. 2 L a b e l s .. .. .. . . 1 Maximum O p e r a t i n g A1 t i t u d e .. . . ... .. .........5. ..... ... .. .. ... . . .3 . ...... .. ... . .. .. . ...... .. . . .. .. .... . . .. ... ...5. .. . . .. .... . ... . . 6. .. ....... ....... 3 2.. . . . ....... . . .. .. .... . .. .... . .. ... .... . . . ..... . .. .... ... ... IATION LTO y PILOTS NOTES FIREFLY T67MZ00 SECTION 2 LIMITATIONS AND PLACARDS CONTENTS & 2..... . . . . ... . ... .1 2... . ... .. PILOTS NOTES FIREFLY T67M200 INTENTIONALLY BLANK CAA Approved August 1985 ~ p T67M200/FM . . S e c t i o n R Radio.AVIATION PLC PILOTS NOTES FIREFLY T67M200 2. a i r c r a f t i s c l a s s i f i e d as an Aeroplane ( l a n d p l a n e ) ..3 MAXIMUM OCCUPANTS The t o t a l number o f persons c a r r i e d i n c l u d i n g crew s h a l l n o t exceed two. T ~ ~ P I ~ C O / F M . as necessary f o r t h e a i r c r a f t t o be c l a s s i f i e d i n Performance Group E...A i r w o r t h i n e s s Standards: normal.30' Nose down.27. B r i t i s h C i v i l A i r w o r t h i n e s s Requirements as f o l l o w s : S e c t i o n K L i g h t Aeroplanes. Speci a1 C o n d i t i o n . E l e c t r i c a l Power S u p p l i e s f o r A i r c r a f t R a d i o Systems. u t i l i t y & a e r o b a t i c c a t e o g r y aeroplanes a t amendments 23 .4 RPM - ENGINE LIMITATIONS The maximum e n g i n e speed i s 2700 RPM. b e r e s t r i c t e d t o a n o t h e r c a t e g o r y and a p a r t i c u l a r use and t h i s w i l l be s t a t e d on t h e C e r t i f i c a t e o f A i r w o r t h i n e s s . n o r t h e number of s e a t s w h i c h i s approved f o r use d u r i n g t a k e .A p r i l 1974. CFR 1 4 p a r t 23 . The S l i n g s b y T67M200 t y p e o f a i r c r a f t has been c e r t i f i e d b y t h e CAA on t h e b a s i s o f c a n p l i a n c e w i t h U.November 1978. I s s u e 4 .S. Current A i r w o r t h i n e s s Notices. The maximum o i l sump c a p a c i t y i s 8 US Q u a r t s ..A p r i l 1974. T h i s a e r o p l a n e may. The minimum s a f e q u a n t i t y i n t h e sump i s 4 US q u a r t s and a t t h i s l e v e l p r o l o n g e d o p e r a t i o n beyond t h e f o l l o w i n g maximum p i t c h a t t i t u d e s must b e avoided: Nose up . C h a p t e r s 2-2 t o 2-5 i n c l u s i v e . 2. I s s u e 6 .Canposite Mater ia1 C o n s t r u c t i o n . S e c t i o n N Noise. .o f f and 1a n d i ng. O i l Contents No overspeed i s p e r m i t t e d .1 CLASS AND CATEGORY OF CERTIFICATION this F o r t h e p u r p o s e o f t h e F i r s t Schedule o f t h e A i r N a v i g a t i o n Order. The S l i n g s b y T67M200 t y p e o f a i r c r a f t i s e l i g i b l e f o r c e r t i f i c a t i o n i n t h e U n i t e d Kingdom i n t h e T r a n s p o r t Category (Passenger ). > When f l o w n f o r p u b l i c t r a n s p o r t . c o m p l i a n c e w i t h p e r f o r m a n c e Group E o f t h e A i r N a v i g a t i o n (General) R e g u l a t i o n s must be e s t a b l i s h e d u s i n g t h e o p e r a t i n g t e c h n i q u e s and parameters l a i d down i n t h e f l i g h t manual. 2. I s s u e 2 ..20° P.2-1 CAA A proved March y987 A1 TP . p l u s s p e c i a l c o n d i t i o n s as d e f i n e d b y t h e CAA. however. . 2.2 MINIMUM CREW < The minimum crew f o r o p e r a t i o n o f t h e a i r c r a f t i s one p i l o t . 8 b a r (55 p s i ) 1. 2 bar ( 90-psi) 7.7 l i t r e s ) Unuseable f u e l i s 2 x 0. The minimum f u e l grade i s 100LL..2-2 CAA Approved A p r i l 1998 A8 TP ..1 b a r (60 p s i ) 3 ..T67M200/FM .75 Imp G a l l (80. eg a t 2200 RPM t h e m a n i f o l d pressure must not be allowed t o exceed 26 inches. C . P . Maximum d i f f e r e n c e between l e f t and r i g h t magneto RPM drops a t 1800 RPM. Maqneto Check Maximum RPM drop when s w i t c h i n g e i t h e r magneto o f f a t 1800 RPM. Tank c a p a c i t y 2 x 17.PILOTS NOTES FIREFLY T67M20O O i l Pressure on Start-Up The engine must be shut down i f t h e o i l pressure has n o t s t a r t e d t o r i s e w i t h i n 30 seconds o f s t a r t i n g t h e engine.0 bar (100 p s i ) - Minimum 4. .ylinder Head Temperature 175 RPM 50 RPM Maximum p e r m i s s i b l e temperature F o r continuous operation c y l i n d e r head temperatures should be maintained below 446°F (230°C) O i l Temperatures Maximum p e r m i s s i b l e > Engine o i l temperature should n o t be below 60°C d u r i n g continuous operation. O i l Pressure Durinq Aerobatic Manoeuvres Avoid f l i g h t a t zero ' G ' s t a t e f o r more than 10 seconds as i n these modes t h e o i l system w i l l n o t scavenge.44 Imp Gall ( 2 l i t r e s ) .7 bar (25 p s i ) M a n i f o l d Pressure/RPM L i m i t a t i o n The m a n i f o l d pressure measured i n inches o f mercury must n o t be allowed t o exceed t h e RPM measured i n hundreds by more than an increment o f 4. O i l Pressures Maximum Normal Operating S t a r t and Warm-up Id1 ing 6 . . 2 bar 6.6.2 bar 4.2 t o 6.7 bar 1.Instrument Markinqs Oil Pressure Standard e l e c t r i c gauge Minimum oi 1 pressure Low o i l pressure Normal operating range High o i l pressure Maximum oi 1 pressure M d 681 d i r e c t reading gauge o Minimum oi 1 pressure Low o i l pressure Normal operating range High o i l pressure Maximum oi 1 pressure 1 s t Red l i n e From 1st Red l i n e t o s t a r t Green a r c Green arc From end Green a r c t o 2nd Red 1 i ne 2nd Red 1i ne 25 psi 25 psi t o 55 psi 55 psi t o 90 psi 90 psi t o 115 psi 115 psi Beginning of Red a r c Ye1 low a r c Green a r c Yellow a r c Beginning of Red a r c 1.1 .7 t o 4.AVIATION LTO PILOTS NOTES FIREFLY T67M200 2.2 t o 7 bar 7 bar 'TAL 8/P. 1 of 1 CAA Approved January 2003 T67M200/FM . -.1 and 8.5.- Cat N -. where landings have t o be c a r r i e d o u t a t AUW's between 2150 and 2250 l b s r e f e r t o S e c t i o n 5 Paragraph 5.5. The f o r e and a f t datum i s t h e forward face o f t h e bulkhead f i r e w a l l (Frame 1) being < The l i m i t s o f t h e c e n t r e o f g r a v i t y a t MTWA a r e as f o l l o w s .o f f NOTE -> Cat A 975kg (2150 l b s ) .>{SLINGSBY .4 Landing Performance Post Mod 358.2-3 CAA Approved A p r i 1 1998 A8 TP . < P.2 2.3 Weiqhts f o r Take-off and Landinq Pre Mod 358 The maximum weight f o r t a k e .1 AIRFRAME LIMITATIONS - Centre o f G r a v i t y Measurement and L i m i t a t i o n s T h e datum f o r measurement o f t h e c e n t r e o f g r a v i t y i s as f o l l o w s : > a) b) The l e v e l l i n g datum i s achieved by use o f a r i g g i n g board along t h e t o p o f t h e f u s e l a g e ( r e f T67M200 Maintenance Manual). measured a f t o f datum: Pre Mod 358 Forward 1 i m i t Aft l i m i t 82 3mm 888mm Post Mod 358 823mm 875mm NOTE For l i m i t s a t other weights r e f e r t o S e c t i o n 8 8.5 2.2 a) b) Loadinq The maximum number o f occupants The maximum baggage l o a d i n baggage compartment 30 kg (66 l b s ) 2.--.5. kg (2250 l b s ) 1020 I n cases o f emergency o n l y .o f f and l a n d i n g Post Mod 358 The maximum weight f o r t a k e .T67M200/FM . 2..7\ AVIATION LTD PILOTS NOTES FIREFLY T67M200 Ground Runninq The maximum CHT o f 26OoC must n o t be exceeded d u r i n g ground r u n n i n g and o p e r a t i o n a t f u l l t h r o t t l e should not exceed 3 minutes. 5 Limitations for Aerobatics up t o AUW 975 kg (2150 l b s ) Aerobatic manoeuvres with f l a p s extended a r e not p e r m i t t e d .5. .5. c P . See Paragraph 3.T67M200/FM . temp.6 F l i q h t i n Icinq Conditions > H 02 zmf zr nxnd .PILOTS NOTES FIREFLY T67M200 2. 2-4 CAA Approved April 1998 A8 TP .5.5 5 e ba4 Flaps up + 4 4 g -29 Flaps down t2g -1g Maximum permissible s t r u c t u r e temperature f o r a e r o b a t i c s i s 50°C Entry Speeds ( k t s ) (IAS) Slow r o l l S t a l l turn entry S t a l l turn rotate Loop Roll off t h e t o p F l i c k r o l l max Spin 2.7 The a i r c r a f t i s not c l e a r e d f o r f l i g h t i n t o known i c i n g c o n d i t i o n s . below 50°C) Flaps up +6g -39 Flaps down t2g -1g When s t r u c t u r a l temperature reaches 50°C or more DO NOT c a r r y out aerobatics : 7 A L i0 2.4 Limitinq Speeds (IASL VNE Never exceed speed 180 kts 140 kts 140 kts VNO Normal operating l i m i t speed VA Manoeuvring speed > Flap l i m i t i n g speeds Post Mod 656 Takeoff p o s i t i o n (18") Landing p o s i t i o n (40") Pre Mod 656 Both f l a p p o s i t i o n s 120 kts 98 kts 88 kts 2. ' G ' Limitation ( s t r u c t . Tail S l i d e s and Inverted Spins a r e not p e r m i t t e d . T67M200/FM .2 t o 7 bar 7 Bar $ S\ 1 "' ..7 bar 1 .. 5 .i : .PILOTS NOTES FIREFLY T67M200 2. 2.6 PLACARDS 2.2-5 CAA Approved April 1998 A 8 TP .6.2 b a r 4. /I " Low o i l pressure Normal operati$ Ye1 low-arc .2 t o 6..1 Instrument Markinqs Oil Temperature Maximum temperature Ye1 low a r c be1 ow 40°C Green a r c Red Line Oil P r e s s u r e > 40°C t o 1 1 8 O C 118°C Minimum p r e s s u r e . 2 .- 1.7 F l i q h t i n I C o r a t Night M F l i g h t i s permitted in I C day and f o r night f l i g h t . o i .~ ~ ' ~ r e s s u r e . M For f l i g h t by night o r IFR r e f e r t o t h e Air Navigation L e g i s l a t i o n f o r equipment r e q u i r e d .s ' ~ e g i g n i n gof Red a r c . 7 t o 4. Q "- L-- range Gieen arc Ye1 low a r c High .2 b a r 6.700 rpm 2.700 rpm Green a r c Yellow a r c Beginning of Red a r c P. 8 L i m i t a t i o n s f o r Inverted F l i q h t When low on f u e l only fuel in c o l l e c t o r tank w i l l be a v a i l a b l e .5.~ ginning of Red a r c Cylinder Head Temperatures Normal o p e r a t i n g range High c y l i n d e r head temperature Maximum temperature Tachometer Normal o p e r a t i n g range Maximum rpm Green a r c Red l i n e 700 t o 2./-t6ximum p r e s s u r e . <{SLINGSBYLTo AvlnrlON PILOTS NOTES FIREFLY T67M200 AS1 Markinqs VNE Radial red l i n e Ye1 l o w a r c Green a r c 180 knots 140 t o 180 knots 56 t o 140 knots Cautionary zone Norma? o p e r a t i n g range Flap sp2ed range (Landing f l a p 40") Post Mod 656 Pre Mod 656 OAT Gauqe /5&uc+.T67M200/FM .2-6 CAA Approved 8 April 1998 A TP .7d[ White a r c White a r c 49 t o 98 knots 49 t o 88 knots < / p l ~ e r d k e 3-S? S t r u c t u r e temperature Maximum Red l i n e 50°C P .. 2 Labels 7 4 . 4 0 2*6.2 ye ~.PILOTS NOTES FIREFLY T67M200 2. ~ prg. 975 STRUCTURAL TEMPERATURE BELOW 50°C ABOVE 50°C + 4 49 +2g -29 -1g FLAPS UP FLAPS DOWN A L T I T U D E LOSS I N A S T A L L RECOVERY +6g +2g -39 -19 1 5 0 F T (46m) F L I G H T I N T O KNOWN OR FORECAST I C I N G CONDITIONS PROHIBITED AIRCRAFT C E R T I F I C A T E D FOR F L I G H T I N IMC.G*A& zg .OF2 0 0 8 T h e f o l l o w i n g i n f o r m a t i o n i s t o be f u r n i s h e d o n p l a c a r d s w e l l w i t h i n sight of Pilot.T67M200/FM . DAY AND FOR NIGHT F L I G H T AEROBATIC MANOEUVRES - UP TO A L L UP WEIGHT 975 Kg (2150 l b s ) MAXIMUM P E R M I S S I B L E STRUCTURE TEMPERATURE FOR AEROBATICS I S 50°C ENTRY SPEEDS (KTS) SLOW ROLL STALL TURN ENTRY S T A L L TURN ROTATE LOOP ROLL OFF THE TOP F L I C K ROLL MAX SPIN li0 (IAS) 110 50 120 140 80 SEE F L I G H T MANUAL CAA A p p r o v e d Apri 1 1998 A8 T P .6. PRE MOO 3 5 8 NO SMOKING LIMITATIONS VNE (KTS) ( I A S ) MANOEUVRING SPEED VA (KTS) ( I A S ) FLAP OPERATING SPEED (KTS) ( I A S ) MAX TOTAL WEIGHT AUTHORISED (KG) MAX g LOADS 180 140 88 < -. +ec.8g -l.PILOTS NOTES FIREFLY T67M200 > POST MOO 358/PRE MOD 6 5 6 NO SMOKING LIMITATIONS VNE (KTS) (IAS) < MANOEUVRING SPEED VA (KTS) ( I A S ) FLAP OPERATING SPEED (KTS) ( I A S ) 1 MAX TOTAL WEIGHT AUTHORISED FOR TAKEOFF (KG) MAX TOTAL WEIGHT AUTHORISED FOR LANDING ( k g ) MAX LOADS UP TO 9 7 5 KG FLAPS UP FLAPS DOWN MAX LOADS ABOVE 9 7 5 KG FLAPS UP FLAPS DOWN A L T I T U D E LOSS I N A STALL RECOVERY +3. DAY AND FOR NIGHT F L I G H T AEROBATIC MANOEUVRES - UP TO A L L UP WEIGHT 9 7 5 K g ( 2 1 5 0 lbs) MAXIMUM P E R M I S S I B L E STRUCTURE TEMPERATURE FOR AEROBATICS I S 50°C ENTRY SPEEDS (KTS) SLOW ROLL (IAS) 1 S T A L L TURN ENTRY STALL TURN ROTATE LOOP ROLL OFF THE TOP F L I C K ROLL MAX SPIN ABOVE 9 7 5 KG AEROBATICS PROHIBITED P.T67M200/FM 50 1 1 80 SEE F L I G H T MANUAL .-i -1g '-r>L.b\+ %s ' i iL~-.. 49 F L I G H T I N T O KNOWN OR FORECAST I C I N G CONDITIONS PROHIBITED AIRCRAFT C E R T I F I C A T E D FOR F L I G H T I N IMC.49 +2g -29 I ..2-7A CAA A p p r o v e d A p r i 1 1998 A 8 TP .6g +29 -19 1 5 0 F T (46rn) 975 1 I STRUCTURAL TEMPERATURE BELOW 50°C ABOVE 50°C +6g +2g -39 -1g +4. 8g +2g -1. 2-7B CAA A p p r o v e d A p r i l 1998 A8 TP .UP TO A L L UP WEIGHT 975 Kg (2150 lbs) MAXIMUM P E R M I S S I B L E STRUCTURE TEMPERATURE FOR AEROBATICS I S 50°C ENTRY SPEEDS K I A S 110 S T A L L TURN ENTRY S T A L L TURN ROTATE LOOP ROLL OFF THE TOP F L I C K ROLL MAX SPIN ABOVE 9 7 5 K g AEROBATICS PROHIBITED P .T67M200/FM 140 110 80 SEE F L I G H T MANUAL . DAY AND FOR NIGHT FLIGHT AEROBATIC MANOEUVRES .PILOTS NOTES FIREFLY T67MZ00 POST MOD 656/PRE MOD 7 5 7 8 LIMITATIONS NO SMOKING VNE MANOEUVRING SPEED VA FLAP L I M I T I N G SPEEDS TAKEOFF P O S I T I O N (18") LANDING P O S I T I O N ( 4 0 " ) MAX TOTAL WEIGHT AUTHORISED (TAKE OFF) MAX TOTAL WEIGHT AUTHORISED (LANDING) MAX LOADS UP TO 9 7 5 K g FLAPS UP FLAPS DOWN MAX LOADS ABOVE 9 7 5 K g FLAPS UP FLAPS DOWN A L T I T U D E LOSS I N A S T A L L RECOVERY + 3 . 8 g -1 6 g +29 -1g +3.4g +2g -29 -1g 120 KIAS 9 8 KIAS 180 KIAS 140 KIAS 1 5 0 F T (46m) F L I G H T I N T O KNOWN OR FORECAST I C I N G CONDITIONS P R O H I B I T E D AIRCRAFT C E R T I F I C A T E D FOR F L I G H T I N IMC.69 -1g STRUCTURAL TEMPERATURE BELOW 50°C ABOVE 50°C +6g i.29 -39 -1g +4.. 4g +2g -29 -1g + 3 .' { s U ~ ~ ~ ~ ~ ' A\'I&TiON LTD PILOTS NOTES FIREFLY T67M200 LIMITATIONS NO SMOKING VNE MANOEUVRING SPEED VA FLAP L I M I T I N G SPEEDS TAKEOFF P O S I T I O N ( 1 8 O ) LANDING P O S I T I O N ( 4 0 " ) MAX TOTAL WEIGHT AUTHORISED (TAKE OFF) MAX TOTAL WEIGHT AUTHORISED (LANDING) MAX LOADS UP TO 9 7 5 K g FLAPS UP FLAPS DOWN MAX LOADS ABOVE 9 7 5 K g FLAPS UP FLAPS DOWN A L T I T U D E LOSS I N A S T A L L RECOVERY F L I G H T I N T O KNOWN I C I N G CONDITIONS PROHIBITED AIRCRAFT C E R T I F I C A T E D FOR F L I G H T I N IMC..69 -1g 1 5 0 F T (46m) UP TO A L L UP WEIGHT 975 Kg (2150 lbs) MAXIMUM P E R M I S S I B L E STRUCTURE TEMPERATURE FOR AEROBATICS I S 50°C SLOW ROLL STALL TURN ENTRY STALL TURN ROTATE LOOP ROLL OFF THE TOP F L I C K ROLL MAX SPIN 50 ENTRY SPEEDS K I A S 110 80 SEE F L I G H T MANUAL CAA A p p r o v e d A p r i l 1998 A8 TP .6g +2g -19 +3..8g +29 -1. DAY AND FOR NIGHT F L I G H T AEROBATIC MANOEUVRES - 180 KIAS 140 KIAS 120 K I A S 98 K I A S STRUCTURAL TEMPERATURE ABOVE 50°C BELOW 50°C +6g +2g -39 -1g +4.T67M200/FM . 8 g -1. 7 L i t r e s 20.6.PILOTS NOTES FIREFLY T67M200 2.31 Imo Gal Mod 2928 A/C 78.on each w i n q upper s u r f a c e 78.2 Labels (continued) N o t i c e above t h e luqqaqe compartment 30 Kg MAX FOR C OF G AND TOTAL WEIGHT LIMITATIONS A f t o f t h e r e f u e l l i n q caps .T67M200/FM .77 US G a l l s P o s t Mod 310B A/C Fuel t y p e and c o n t e n t s .7 Litres 17. as above. i n L i t r e s Imp G a l l s and US G a l l s a r e combined on a f u e l f i l l e r / w i n a i o i n t v i n v l coverina A t t h e f o o t o f t h e f l a p c o n t r o l l e v e r on t h e c e n t r a l f a i r i n q Takeoff Landing On t h e t r i m i n d i c a t o r i n f r o n t o f t h e t r i m c o n t r o l U (Nose Up) N (Neutral) D (Nose Down) On t h e u n d e r s i d e o f t h e o i l f i l l e r access f l a p MIL-L-22851 SAE 15W50 O SAE 20W50 R On canopy frame one each s i d e o f l a t c h mechani* (POST NO0 129) CANOPY MUST ALWAYS REMAIN CLOSED AND LATCHED DURING FLIGHT UNLESS EMERGENCY EVACUATION I S INTENDED Page 2-7D CAA Approved March 1988 A4 TP . one s i d e o f l e v e r ( P o s t Mod 129) On i n s t r u m e n t panel below canopy l o c k i n q l e v e r (Mod 810) ( S i n g l e p i e c e canopy a i r c r a f t ) II I IMPORTANT! ALWAYSCHECKTHATLATCH IS FULLY ENGAGED II On t h e t o p o f t h e i n s t r u m e n t panel CAUTION I TURN OFF STROBE LIGHT WHEN TAXIING NEAR OTHER AIRCRAFT OR WHEN FLYING I N FOG O CLOUDS. STANDARD POSITION R LIGHTS MUST BE USED FOR ALL NIGHT OPERATIONS 1 WITH FLAPS EXTENDED ARE NOT PERMITTED Below f u e l c o n t e n t s qauqes 34.2 Labels (continued) Under s i d e o f canopy l a t c h c o v e r (POST MOD 129) > On r e a r f a c e o f canopy l a t c h cover. .62 IMP GALLS Mod 2928 A/C USABLE FUEL 41.6 US GALLS Page 2-8 CAA Approved A p r i 1 1998 A8 TP T67M200/FM .PILOTS NOTES FIREFLY T67M200 2.6. OPERATIONAL - LIMITATIONS When Mod 177B or 2728 a r e i n c o r p o r a t e d t h e a i r c r a f t must n o t be f l o w n i n t h e v i c i n i t y o f known or f o r e c a s t thunderstorm o r l i g h t n i n g ' I L L I Y I L ) r -^+l..1'67M200/F'M .i+'..1 o f 1 CAA ~ p p r . o v e d August 1988 TP . TAL 2/P.7 .TEMPORARY LIMITATIONS FOR POST MOD 1778 AND 272B AIRCRAFT 2. . 2.8 -P A I N T FINISH C e r t a i n areas o f t h e a i r c r a f t have c o l o u r r e s t r i c t i o n s .7.PILOTS NOTES FIREFLY T67M200 2.7.2 Maximum Takeoff and Landinq A l t i t u d e -.T67M200/FM . Ine maximum t a k e o f f and i a n a i n g a l x i x u d e i s 8000 f t d e n s i t y a l t i t u d e . 1 .000 f t w i t h o u t oxygen equipment being f i t t e d .1 Maximum Operatinq A l t i t u d e The maximum p e r m i s s i b l e operating a l t i t u d e i s 12. (2) There i s no defined lower l i m i t f o r t h e a i r c r a f t s t r u c t u r e . . 2. Minimum o p e r a t i n g temperature i s -20°C b e f o r e w i n t e r i s a t i o n i s required.1 ) . these a r e i n d i c a t e d on t h e 3 View Plan ( p . The above r e s t r i c t i o n s are t o a s s i s t i n keeping t h e c r i t i c a l areas of' s t r u c t u r e cool.. Page 2-9 CAA Approved A p r i l 1998 A8 TP .7. Operatinq Temperatures 2.3 Maximum o p e r a t i n g temperature i s I S A +23"C. (1) F o r operations below OAT -20°C c o n s u l t t h e engine and propel 1 e r handbooks f o r procedure. PILOTS NOTES FIREFLY T67M200 INTENTIONALLY BLANK P a g e 2-10 CAA A p p r o v e d March 1988 A 4 . ...7 ...................................4 3..............6 3........11.... 3-14 ....... 3-7 Taxying ....2............................................... 3-5 3 .............10.. ............2 E x t e r n a l Check .. 3-11 3..3-14 ....................2 S t a r t i n g t h e Engine and A f t e r S t a r t Checks .. 3-9 ............................3 F i n a l Checks .... 3 A e r o b a t i c s o r S p i n n i n g ...........................................1 .........PILOTS NOTES FIREFLY T67MZ00 SECTION 3 NORMAL PROCEDURES CONTENTS 3....... 10 .........2 3................... 3-13 3.....7................................. 3-8 S t a r t i n g t h e Engine Pre-take o f f V i t a l Actions Take o f f and Climb E r e c t Spin Recovery ..........1 P r e ............................. 3-12 3-12 R e j o i n Checks ...................................3 3...............lo.................................. 3-12 ................................ 3-11 ..... 3-10 .. 3-1 ... 3-13 3 ........anding Checks and Speeds .....7 .....................................3 F i t t i n g F l y i n g C o n t r o l Locks (Mod 316) L a s t e f f e c t i v e page i s P.... 3-8 T e s t i n g t h e Engine ....................................................................Gyro Instruments 3........2 Non-Standard Recovery 3.................2............................... 1 I n i t i a l Check 3.............l S t o p p i n g t h e Engine 1..........................9 > 3 .............................. 3-2 3.......... 2 C i r c u i t Speeds 3........... 3-13 .....5 3............... . .................................................. '3-1 .................. ...1 B e f o r e S t a r t i n g t h e Engine 3. 3-13 c ............s t a r t C o c k p i t Checks ........... 3-12 < P r a c t i c e Forced Landings ...1 Standard Recovery Technique 3......... L...................2 3................8 3.................11......1 Downwind Checks 3.......1..................... 3-14 ... 3-5 3....10 ..........1 Checks A f t e r Landing 3 ....................................... 3-14 CAA Approved A p r i l 1998 A8 TP T67M200/FM .................................7................................................. SUN-^ AVlAT IC>N PLC PILOTS NOTES FIREFLY T67M200 1NTENTIONALL.Y BLANK CAA Approved A u g u s t 1985 TP. T67M200/FM . .......PILOTS NOTES FIREFLY T67M200 3........o f f On ... Off CAUTION - off STROBE POSITION LIGHT NOT TO BE USED I N CLOUD................on OAT gauge below 50°C . Cockpit (ground crew a s s i s t e d ) Magnetos ..... h e r Cancel f l a s - ..1) 3... n Check 1 i g h t / h o r S t r u c t u r a l temperature ( i n hot c o n d i t i o n s ) P i t o t head .........check s t r u c t u r a l temperature .............. O f f ................. and l o o k f o r any obvious signs o f leaks....T67M200/FM .........................................1 BEFORE STARTING THE ENGINE I n i t i a l Check (Section 7........... Off Nav l i g h t s ........ check On .. key On (Pump P a r k i n g Brake .......................................... Check t h a t chocks a r e i n p o s i t i o n ( i f r e q u i r e d ) ..... P... On Master s w i t c h ..check ( i f required) Landing l i g h t s ( i f required) Master s w i t c h ....... i c e o r hoar f r o s t have been removed...................1.. Press t e s t s w i t c h .. On f o r 20 secs check ............ MIST OR ON THE GROUND.....3-1 CAA Approved A p r i l 1998 A8 TP ........................................ check t h a t t h e towing arm and p i t o t cover p l u s any snow...11 Check l o a d i n g and C o f G Approachi nq t h e A i r c r a f t Observe t h e general appearance o f t h e a i r c r a f t .... On off ....................... Note p o s i t i o n S t a l l warning .................o f f check - Strobe l i g h t ( i f f i t t e d ) .......... P i t o t heater out brakes) A1 t e r n a t o r warning ...... t h a t a f i r e e x t i n g u i s h e r i s a v a i i a b i e ...................... Check heat P i t o t h e a t e r ............................................On R o t a t i n g beacons ( i f f i t t e d ) Trim ........ i n f l a t i o n Con f i l t e r i s clean o i l leaks Check foam ..... . . n d i t i o n ... ..... d i s c c o n d i t i o n inflation . . movement. .. . .... a r ' / c o n d i t i o n H .c...... ..... p l a y .. . . e Undercarriage Brake Tyre . Condition.i t t e d .... ... .. . .. .l y . . . e x t e n s i o n Co ........2 E x t e r n a l Check ( r e f i l l u s t r a t i o n 8 3 P r i n c i p a l Features) -. o p e r a t i n g arm. . Conditio s u r f a c e s . creep..H s i d e Nosewheel o l e o Nosewheel t y r e Ram a i r i n l e t Landing .. ... .... .i t i o n P..f. . ...... .i t. a1 i g n e d .....l. L e f t wing Flap Aileron Nav 1 i g h t / s t r o b e Leading edge Fuel cap .....i o n . ... . Condi ti on/extension.. ... ... ... .....l e .o.. s t i f f n u t ..3-2 CAA Approved September 1987 A2 TP T67M200/FM .......... '7 f a s t e n e r s . .. . . . C o n d i t i o n ..... . . .. > S t a r t a t l e f t w i n g i n b o a r d t r a i l i n g edge. . . .. Condition... .o.1. .C o r... ..t. .... . leaks. .. .... .e a r Cl Forward f u s e l a g e Fresh a i r i n t a k e Cowling 1.. Fuel d r a i n . 2 p i n s . . .....e.. drains clear .. security ... . ..t y .... .. . .... . .....d i t i o n .PILOTS NOTES FIREFLY T 6 7 M 2 0 0 3. Cond l i g h t s . . r.......n. ............ Securi ... .Check f o r water c o n t a m i n a t i o n Access panel Wing ....n P i t o t head . ... . ............. ... ... .... ... . . ... drains clear C o n d i t i o n .. Secure.. . .. .... . and l o c k e d ...C. . ... .... Damage......... ... s t i f f n u t .. . .. ... ... p l a y .. . .. ...d. . . ... . .. .c. creep.... .... ...... . .. .n. . .PILOTS NOTES FIREFLY T67M200 > 3. . .. . e x t e n s i o n . Security. .. . . . R i g h t Wing 1. . . . .o. . .i. . . . . . . . .i . . .3-3 CAA Approved September 1987 A2 TP . .d.d. .n. movement. . . panel secure Contents. p l a y .o. t . . . .. .. . . .. . n t o f i t t e d and l o c k e d .. . ..i.. .C. .. . ..f. . . . Clear 6 fasteners. . . . . B r a k e .Check . creep.r water c o n t a m i n a t i o n .d. . . .d. .i Access panel . . . . . . . . . ..o n . . Aileron Flap .. . i n f l a t i o n Wing s u r f a c e s . clean P . . . .. . drains clear s t i f f n u t . . . . ndi . . . . . ..eading edge F u e l cap . . . . . . . . . . . . . . C o n d i t i o n . . . . . . . .. . . .i t. . . . Secure.. . . . . a1 igned . . . .C o n d i t i o n . . . . . . . .. . . . . . . .. . Condi U n d e r c a r r i a g e .. . . . . .T67M200/FM . . . . . . . . . Condition. . . . . . . . .. . . Condition. 2 pins . . o p e r a t i n g arm. Temp. i t i o n . . . . . .C. . . . .. . . . .. s e c u r i t y E:ngine c o o l i n g i n l e t s Cowling R s i d e H Oil . . . . . . .t i o n . . . . . . . . . .C o . . . . F r e s h a i r i n t a k e . . . . . on on drains clear Nav a e r i a l s ( i f f i t t e d ) Rear fuse1 age and T a i l p l a n e Condition. . . . . . . . . (under a / c ) ( i f f i t t e d ) Canopy RH s i d e .. . d i s c c o n d i t i o n . . . . C . . . . .. . .C . . . . .. . Fuel d r a i n Tyre . . . . . . . .i . . . .. s e c u r i t y .. .. .2 E x t e r-Check ( c o n t i n u e d ) nal - Forward f u s e l a g e ( c o n t i n u e d ) Propeller Spinner . . .. . o . . . .. .. . . .C o n. .i o n . . . . . . . .C o n d . .. .. . . . l e a k s . . . Nav l i g h t / s t r o b e . . ..t. . . . .1.. .t i o n . C l e a r . p l a y ... ... .Damage. . .o r r e c t l y . . . ... s t i f f n u t . . . . probe . . . . . i. . . . . s e c u r i t y R o t a t i n g beacon . . .. . . . .C o n d i t i o n . . . . . . . . . . d r a i n s c l e a r . . Condition play. . c l e v i s pin... .. . . ..o n d i t i o n C s i d e . . . . . Plugout.o. . .t i.i. . .. C o n d i t i o n ..o. . . . . .. . . . . . . . . .. . .1. . . . movement.. . c l e v i s p i n Rudder T a i l bumper Trim tab . . .. . . . C o n d i t i o n . .clear F i n f a i r i n g . . .. . C .t. . . . . ... . .. . . . . . ... . i R o t a t i n g beacon ( f i n ) ( i f fitted) Fin . . .. .. . . . . . .t. . . . .. . . .o. . E l e v a t o r LH s i d e . . movenlent T a i l p l a n e LH s i d e S t a t i c v e n t LH clear Canopy LH s i d e ..n .t . . . ..C o n d i. Cable.. . .n. . .. . . . o. . . .o. .2 --E x t e r n a l Check ( c o n t i n u e d ) > Rear f u s e l a g e and T a i l p l a n e ( c o n t i n u e d ) VHF a e r i a l ( i f f i t t e d ) S t a t i c v e n t RH s i d e .... ..n d i t i o n . .. P 3-4 CAA Approved September 1987 A2 TP T67M200/FM . ..C... security. . . .. . ..p o s i t i o n ... . C.. .n. . . Secure f ' a i l p l a n e RH s i d e . . .. . . . . . drains clear .a1 i g n e d Secure.n. . c l e a n . . . .. .d. . . . Condition. .. . . C o n d i t i o n . . . n . .. . .... locking nuts Alignment (check w i t h nosewheel ) . . Plug out.i o .PILOTS NOTES FIREFLY T67M200 3. . .. . E l e v a t o r RH s i d e Access panel Strobe l i g h t ( i f fitted) .. ondi i . . . .C o n . di . . . . .. . . . . . . .. play.. .. . secure . . . . . . . ................ ................................ .. . A required s . Vacuum gauge ................... .. .................... .......t i c l e s Check f o r loose a r If s o l o secure RH harness < F i r s t aid k i t Escape axe ....... On Alternator warn Cockpit 1 i g h t s Nav l i g h t s .. ... ................................ ....1 P r e ..... . Plugged ......................................T67M200/FM .........PILOTS NOTES FIREFLY T67MZ00 3.................. . .................... Zero ..... .......... ....... . Off Master switch ........................................................ ............. .. NAV aids ...... .s t a r t Cockpit Checks > Cockpit .. Stowed Secure Ensuring locating pin i s f u l l y engaged ......................... f u l l and f r e e movement .. Cancel flasher .. .... ... ........ ............ ........... ........ s required A Intercomm ............. Strap in (5 s t r a p s ) ............................ Rudder pedals ........... Stowed F i r e extinguisher Baggage ... All off Off Radios ....... . ........... ..2...... in E l evator/Ai 1 eron..... . ... ............. .. ... ..... Stowed .............. Out CAA Approved April 1998 A8 TP .... .... ............. ............................ .. ......................... Off .. Off E l e c t r i c fuel pump .... ................. ....... Helmetlheadset Flying controls Lights .................. ................ ... . ........ ..... .length Adjust f o r leg < Harness .... .............. S t a l l warn l i g h t S t a r t e r engd ............ Out 1 i g h t ..... Off A1 ternator .... ............ ................ ...... On P i t o t heat ........... ........2 STARTING THE ENGINE 3. . ...f .. . .. . . .. . .. . .... . Note RPM gauge . . . ... .. . .. . . C i r c u i t breakers Throttle . .. . . . . ... . .. Trim . . .. . . . . . . . . . . ... . .l. . .. ... .i f A l l i n . . .. . . . .. . . .. . . . ... .. .. .....Zero o r ambient -" * > Ameter . . . . . .. . ... F l i g h t i n s t r u w n t s .. C . . .. . . . P r o p e l l e r .... . . ..zero. ... .. . . . .. . .l . .. . .. . .. . . . . .Set zero.. . ... l .u. ... ... ... . l e a v e a t l e a n cut. . ... Clock . .. . . ... .. .. ... . Check . .. . .. . . .C o n d i t i o n AS1 . ... . . . . . .. .-... .. ..PILOTS NOTES FIREFLY T67M200 3 2 1 .. .. . .. V S I . . . . . . . l e a v e up F & . .... .. . . . 3--6 CAA ~ ~ ~ r ' o v e d December 1988 A6 TP . . . . . .u l l check -.. . ..C.. . . compare n o t e sub-scale r e a d i n g . . ... . . .l ... . .... . . . . (Continued) Reset .... .. . . . . . .. .. .. . . . ... . ... .Zero . .. ..-e . .. . . Check V u e l contents F u e l cock . . . . . . . . . .. Check ( b o t h gauges) On ( S e l e c t tank w i t h l o w e s t quantity) < Alternator switch ......0 0 f t / m i n ..+. .. . . . Check max RPM f u l l movement..e t. . .. . .. ... . . . . . . ... .. . . . . . .. . .. -1. . . . . Check .. . .. . ...l e a v e . .. .. . u . . . . . . . . . .. . . .. . . . .. . . .l e a r P . . ... range . .. .. . . .. . . ..... . ... . . .. .off .... . . . .... .s t a r t C o c k p i t Checks Pr Accelerometer M a n i f o l d pressure .. . . . . . . ... ... . .. . . . ... ...and ... .. f . ... .. .. .... . . .. .. . . . ...o r r e c t . .. .. .... .... . . . . . ...T67M200/FM . .. . ..... . . . . . .. neutral Canopy w . . Zero . ... . . .. .. . . . . .. . . friction adjusted.. . . . . . . .. ... . ..mvement. . . . .. . .. . . .. . .Zero ..... .. . . . . . . . . . .. . . . e s ) On (Pump b r a k " F l a p ... . Off < > P a r k i n g brake . .. . .. ... . . .. . .. .. ... . . ... .. . . . ... .. A l t i m e t e r . . . .. .. . . E.... .. . .. ... . leave closed f u l l movewnt... . .. leave a t P r o p e l l e r Governor C o n t r o l Mixture control . . not investigate . ... . . .. . . .. .. . . . .Secure . .ngine temps/press .. . .. .. . . . . . . .. . n o t e sub-scale r e a d i n g Standby a l t i w t e r ( i f fitted) ...S. . . . .. ...2 S t a r t i n q t h e Enuine and A f t e r S t a r t Checks A1 t e r n a t o r > ... .2. . . .. .. . .... .1 o f 2 C'AA Approved March 2004 T67M20O/FM . . . . . On.. check warning l i g h t o u t NOTE Avoid l o n g p e r i o d s o f o p e r a t i o n w i t h t h e t h r o t t l e a t i d l e as t h i s can l e a d t o spark p l u g f o u l i n g . . . . < TAL 9/P. .3. . ... .........................................................30 Risen w i t h i n S t a r t e r warning RPM ........ On ......... Lean c u Engine hot procedure Open inch Throttle . \ Throttle ................... rich and Smoothly to full immediotely to OFF .......... Set 1200 t o warm .....l Slowly t o f u l ..........................................' Mixture ....................................................................................2........................ On Electric fuel pump ............2 S t a r t i n q t h e Enqine and A f t e r S t a r t Checks Engine c o l d ............... ... Left CAUTION WITH CANOPY OPEN DO NOT EXCEED 1500 RPM r Starter ........................................ Magneto .......... Press............. Both ........................................... t o f f ............ (check s t a r t e r warning l i g h t on d u r i n g s t a r t ) ............ re1 ease when engine fires rich Mixture Magneto ................ 1 i g h t out O i l pressure STOP ENGINE IMMEDIATELY A1 t e r n a t o r Radios Nav a i d s X 1 ......... Full rich E l e c t r i c f u e l pump ......... Mixture ...... Indicating ....... Check o u t ......... f u e l pump < until Electric ................. Open (%inch t o %inch) a s l i g h t fuel flow i s i n d i c a t e d on t h e f u e l pressure guage...........................................................................................PILOTS NOTES FIREFLY T67M200 3.... Mixture........f f O ..................................... As r e q u i r e d Suction .......................... i f n o t ....... check warning ] ] up secs. On.... PILOTS NOTES FIREFLY T67M200 3.2.2 S t a r t i n q t h e Enqine and A f t e r S t a r t Checks ( c o n t i n u e d ) > . Horizon .......................... E r e c t i n g - a d j u s t datum (Operate q u i c k e r e c t knob on e l e c t r i c a r t i f i c i a l horizon Mod 312) w i t h compass Direction indicator Radio ......................... Synchronise .......... .............................. Check on 2 f r e q s i f p o s s i b l e Obtain taxy clearance Altimeter > + Ammeter ........................................c a t i o n s Check s e t t i n g / i n d i ................................t i v e charge Shows p o s i ........ Check l i g h t o u t and l o c k e d o r f u l l y open A l t e r n a t o r f a i l u r e warning Canopy $ ............................Closed CAUTION SHOULD STARTER WARNING LIGHT FAIL TO EXTINGUISH AFTER STARTER BUTTON I S RELEASED CLOSE DOWN ENGINE 3.3 TAXYING Brakes ........... Checked (Both s i d e s i f manned) Rudder.. .............................................. v e l a v a i l a b 1 e Check f u l l t r a Instruments ................................... Check compass, D I , horizon, t u r n c o - o r d i n a t o r and ADF f o r c o r r e c t 3.4 TESTING THE ENGINE ed and l o c k e d > > < > P.3-8 CAA Approved A p r i l 1998 A8 TP .T67M200/FM J<sLJNGsBY 7 AVIATION LTO PILOTS NOTES FIREFLY T67M200 3.4 TESTING THE ENGINE CAUTION W E CLOSING THE CANOPY PRIOR T FLIGHT, CHECK ALIGNMENT HN O OF WITNESS LINE O CANOPY OPEN/CLOSE PLACARD AND BOTTOM N O RELEASE HANDLE, TO ENSURE THAT THE LATCH MECHANISM I S F I N THE FULLY LOCKED POSITION ............................ Closed and locked Parking brake ..................... On (Pump brakes) Safety ............................ Clear behind Fuel cock ......................... Check on (Change tanks) Fuel pressure ..................... 0.5 t o 8 p s i O i l pressure ...................... Green 4.2 t o 6.2 b a r O i l temp .......................... Green 40°C t o 118OC Cylinder head temp ................ Green 100°C t o 230°C R M ............................... Set between 2000-2100 R M P P Suction ........................... Green (4.5 t o 5.5 i n Hg) Magneto drop ................... . Max 175 RPM, no more than . . Canopy Propeller 50 RPM d i f f e r e n c e between L and R ......................... Exercise p ottc more nthanl 4 times i h co tro RPM drop n 500 I d l i n g ............................ Check i d l i n g 800 RPM minimum O i l Pressure During Normal 0 e r a t i o n Because o f t h e greater l e n a t h o f the o i l f l o w ~ a t h rom t h e sump t o t h e o i l pump, t h e urn6 has t o work harder' than normal t o 'draw o i l through' these Yines: t h e r e s u l t a n t pressure drop t h r o u h these l i n e s r e s u l t s i n a lowered o i l pressure. This e f f e c t w i l be more marked when t h e engine i s c o l d and u n l i k e a standard engine, t h e i n d i c a t e d o i l pressure w i l l normally tend t o r i s e as t h e engine warms up. Thus i t i s not necessarily an i n d i c a t i o n o f t r o u b l e i f t h e o i l pressure minima are o n l y j u s t met on s t a r t - u p . re__ 9 CAA' Approved June 2001 PP .T67M200/FM ...... On ( i f conditions require) Green Oil temp/press .t o 5........... Suction .......... ....... Flaps . .. P 2-9 CAA Approved April 1998 A 8 TP ............................... a n d locked Closed .. \ ~ ~ .................................. .. Tight and secure ( I n e r t i a reel types locked) Full Controls el ev/ai 1 .........5 PRE-TAKEOFF VITAL ACTIONS > Stiff T h r o t t l e f r i c t i o n ....... t h e indicated o i l t o r i s e as t h e engine warms up....... on (Left or Riaht) Check ............ 64 kts no f l a p .............. .T67M200/FM ........ On Magnetos Both On E l e c t r i c Fuel pump ...................................... . Synchronised .... Set a t N Trim Harness .. .............................5 Erect Horizon ................... Fuel contents ....PILOTS NOTES FIREFLY T67M200 / Propeller bedween P a n d R/ Idling Oil ~ r e s s d eDurinq h o r n d o p e r a t i o n Because of the g r e a t e r length o i l flow p rom t h e sump t o the o i l has t work harder t ormal t o draw o i l throug theseh ei n e s : t l pump drop through these l i n e s r e s u l t s in a e f f e c t will be more marked when the a standard engine................. .......note wander Direction indicator .. indication of trouble i f t h e o i l pressure minima are on1 y j u s t met on s t a r t ................... UD o r takeoff Check l i f t o f f speed PRE MOD 358 MTWA 2150 lbs (975 k q ) 50 kts takeoff f l a p (18") 53 k t s no f l a p s POST MOD 358 MTWA 2250 lbs (1020 k q ) 55 kts takeoff f l a o (18") .5 in Hg) Green (4....... ........................ ................... gauges) Check (Both Fuel cock ....and f r e e movement Canopy ................ Strobe l i g h t .......... ..............u p r"'p9 3... P i t o t heater .. ...... 3.... ..................................... ............ 3..T67M200/FM ro roved ...... Engine f a i l u r e on t h e ground....... A v a i l a b i l i t y o f emergency l a n d i n g areas o u t s i d e t h e airfield....THE GROUND UNTIL TAKEOFF SPEED THEN ROTATE T LIFT-OFF ATTITUDE O (2) I F CANOPY W S NOT LOCKED BEFORE TAKEOFF MAKE N ATTEMPT A O TO LOCK I T IN FLIGHT .... ~-~ ...KEEP SPEED TO SAFE MINIMUM AND LAND A SOON A POSSIBLE S S CAA A p r i l 1998 A8 TP . 3........... .......PILOTS NOTES FIREFLY T67M200 PRE-TAKEOFF EMERGENCY BRIEF The f o l l o w i n g p o i n t s must be b r i e f e d : 1.... . Engine f a i l u r e above 300 ft............. Runway s u r f a c e t y p e and c o n d i t i o n Runway l e n g t h S u r f a c e wind............ ......................................... 2...........Ful 1 RPM Check 2600 RPM t o 2650 RPM Manifold ~ r e s s u r e J u s t below ambient O i l oresshre Green O i 1 temp Not r e d C y l i n d e r head temp Below max AS1 Increasing Raise nosewheel .. WARNINGS (1) I N STRONG CROSSWIND CONDITIONS LEAVE NOSEWHEEL ON . . 4.... ......... ....... The f o l l o w i n g p o i n t s must be considered: 1. Engine f a i l u r e below :300 ft.6 TAKEOFF AND CLIMB Takeoff T h r o t t l e ................ 2... t h r o t t l e ........... a t 30 k t s IAS L i f t o f f speed PRE MOD'338 MTWA 2150 i b s (975 kq) 50 k t s t a k e o f f f l a p (18") 53 k t s no f l a p POST MOD 338 MTWA 2250 l b s (1020 kq) 55 k t s t a k e o f f f l a t (18') 64 k t s no f l a p Climb 75 k t s t a k e o f f f l a p (18") 80 k t s no f l a p ......... ....... ....... ...o r d i n a t o r .................................... Aoolv f u l l rudder t o oooose t h e i n d i c a t e d d i r e c t i o n o f t u r n ~ b \ d ' a i l e r o n sf i r m l y n e b t r a l ....... < Departure Checks A1 t i m e t e r Temps & press Avionics ...PILOTS NOTES FIREFLY T67M200 After Takeoff Checks > Brakes ...77"C t o 21............3-11 CAA Approved A p r i l 1998 A8 TP .. Check ..........................1 a) ERECT S P I N RECOVERY Standard Recoverv Technique Close t h e t h r ................. Raise a t 75 k t s -...... On/of'f Flaps .... C e n t r a l i s e rudder.(At a s a f e h e i g h t ) Off Fuel pressure Check .......................1l0C t o 32..............67'C Above 15........T67M20O/FM ..... o t t l e ........................ Level t h e wings w i t h a i l e r o n Recover from t h e d i v e WARNING e f 9 h i WITH C O G AT REARWARD LIMIT THE PILOT MUST BE F PREPARED T MOVE CONTROL COLUMN FULLY FORWARD TO O RECOVER FROM S P I N P ........... Temps & press Green E l e c t r i c a l f u e l pump ................... ...55OC -1...2Z°C -17........................................11°C Below -12.......7 3... Raise t h e f l a p s ... Check d i r e c t i o n o f s p i n on t h e t u r n c o ........r e q u i r e d Set as ..22" Desired O i l Temp 82°C 82°C 82°C Maximum O i l Temp 3................. As requi red O i l Temperatures Average Ambient A i r Above 26.................... Move c o n t r o l column progressive1 y forward u n t i 1 s p i n s t o p s ......7................................. ............. Such out-of-sequence control actions will delay recovery and increase the height l o s s ..... Make joining c a l l mil 1 i b a r s e t t i n g .. Synchronise check comms and navigation a i d s ...2 Incorrect Recovery A high rotation r a t e spin may occur i f the correct recovery procedure i s not followed. .............................................7.... - Move t h e control column FULLY AFT the spin stops. p a r t i a l l y o r f u l l y ... 3.... c....................... Select and Altimeter ........... BEFORE t h e application of f u l l anti-spin rudder.. Check (both gauges) .PILOTS NOTES FIREFLY T67M200 3............... Set correct CAA Approved April 1998 A 8 TP ......... Aerobatics o r Spinninq ..s p i n rudder and f u l l y forward control column... .. b.. Check gauges green... Direction i n d i c a t o r Radio .. Check on (Select Mixture rich tank with highest quantity) ....... Descend a t 78 kts W r engine and c l e a r plugs as required am 3....7.........T67M200/FM ..... Up t o 10 minutes may be required for a gyro instrument t o resume normal operation....... .8 PRACTICE FORCED LANDINGS Mixture rich........9 REJOIN C E K HC S Fuel contents Fuel cock Engine ...........3 Aerobatics o r spinning may cause t h e a r t i f i c i a l horizon or directional gyro t o topple.. Check t h a t FULL anti-spin rudder i s applied... p a r t i c u l a r l y i f the control column i s moved forward..Gyro Instruments 3.... t h e following procedure may be used t o expedite recovery a . i f the a i r c r a f t has not recovered within 2 complete rotations a f t e r application of f u l l a n t i ..... then SLOWLY FORWARD until Central i s e t h e controls and recover t o level f l i g h t (observing the "g" l i m i t a t i o n s ) ............ ...... ......................................10.... ..................10 3.............. ... Landing ........ .............3 Final Checks .....3-13 CAA Approved April 1998 A 8 TP ........... Altimeter . On E l e c t r i c fuel pump....10.. Off - parking brake off ..t QFE s e Tight and locked Harness .... .................... ............... ......................... ... Set as required ........ RPM t o max o r Right) selected) Fuel cock Fuel ............................... Altimeter ........ ..................... Fuel pressure .................................... .. tank .. ...................... Clearance received Flap ... Correct QFE s e t .'T67M200/FM ....... ....... P.PILOTS NOTES FIREFLY T67M200 3.................. Mixture rich and locked.............. ................ Green As required Flaps .................... 3........ ....................2 C i r c u i t Speeds I Position Down Wind Normal I -79 65 Flapless Position Speed / / F i n a l Turn Finals Threshold I I Takeoff Landing Landing I 3. Temps and press green...........1 LANDING CHECKS AND SPEEDS Downwind Checks Brakes Engine ~7 .10...... (Left Check ( f o r contents ... Check o n ..... .......................................................... ........... On (Pump brakes) Run a t 1000 RPM f o r 1 m i n u t e Off Radios O ............................. S e l e c t up ............................................................................................. ....PILOTS NOTES FIREFLY T67MZ00 3.................. ................................ When e n g i n e s t o p s .................................................11............ .. Off (Check a1 t e r n a t o r Alternator f a i l warning operates) Check f o r dead c u t Magnetos Closed Throttle Cutoff M i x t u r e ................................................................11 3................... Magnetos Off Off Master s w i t c h Off F u e l cock Down F lals ..................................................... Off E l e c t r i c f u e l pump Off Flaps Up ................. ( c a r e f u l 1y move assy i n t o forward s t i c k position) ................. .... Leave on i f a i r c r a f t Par in g b r a k e n o t chocked .. ......... :..... 3.............................t r o l F i t t o con sticks and f l a p s ....................3 F i t t i n q f l y i n q c o n t r o l l o c k s (MOO 316) Flaps Control l o c k ............................... ..2 > Stoppinq t h e Enqine Parking brake ........................................... Off Strobe l i g h t (if f i t t e d ) Off R o t a t i n g beacon ( i f f i t t e d ) Off P i t o t h e a t ............f Navigation Aids Off Nav l i g h t s ........................ ..........................................1 AFTER LANDING Checks A f t e r L a n d i n q L a n d i n g 1 i g h t ...... 3............... ....................f ......................11.................... ............... ........................................11........................ ...2 o f 2 CAA Approved March 2004 T67M200/FM ........2 Stoppinq t h e Engine RPM ........... t h e n reduce t o 1200 p r i o r t o s h u t down...Closed TAL 9/P .............. < Throttle ....3..... ........11.............. .. I n c r e a s e t o 1800 f o r 15-20 seconds... ..... . .....7 4.................. 4.. 4.......... 4-7 O i l P r e s s u r e F a i l u r e ... 2 RPM Overspeeds o r w i 11 n o t Decrease 4...... 1...................... 4-3 F a i l u r e ....... 1 RPM w i 11 n o t I n c r e a s e ............................................................................................................9 4 .......................................2 E n g i n e F i r e .......1 .... 4-7 4 ...............P r o p e l l e r Stopped .4 4................................................................................2 4.....................1 ............................. 4-6 4-6 Communication F a i l u r e ................6 4.............................................. 3 C o c k p i t F i r e ..........................-7 . 4-1 < Fires Forced Landing Ditching Engine 4....... 1 0 ...............................11 P o r t e l e c t r i c a l a r t i f i c i a l h o r i z o n f a i l u r e L a s t e f f e c t i v e page i s 4-8 CAA Approved A p r i l 1998 A8 TPaT67M200/FM ... P r o p e l 1 e r Governor F a i 1 u r e ............. 1 E l e c t r i c a l F i r e ...........5 4........8 4......1 .........................................PILOTS NOTES FIREFLY T67M200 SECTION 4 EMERGENCY PROCEDURES CONTENTS 4............ 4-1 4........................... 4-5 Engine F a i l u r e ... 4-7 ................. 4-2 ..... 4-4 ......................P r o p e l l e r T u r n i n g Fumes i n t h e C o c k p i t . 4-6 A1 t e r n a t o r F a i l u r e .......................... 1 0 ...............3 4............................ 4-1 4-1 4 ................................................10 .................................................................... 4-8 4..................................... PILOTS NOTES FIREFLY T67M200 INTENTIONALLY BLANK CAA Approved A u g u s t 1985 TP .T67M200/FM . . 4............................. ........ .......... Off Radio T r a n s m i t emergency c a l l A1 t e r n a t o r ....... ...... F i n a l l y r e s t o r e power t o t h e a1 t e r n a t o r .............................. .........1 ........... M i n RPM M i x t u r e ................... Off ............................. I T SHOULD BE USED WITH CARE............ 2 Engine .................... .......... O f f Magnetos Off E l e c t r i c F u e l pump Off C o c k p i t h o t a i r . .............. .........2 Engine F i r e T h r o t t l e ...... .................... ...... Open F i r e E x t i n g u i s h e r ........... ...................................... ..... ..t h e e n g i n e w i l l c o n t i n u e t o r u n b u t a l l e l e c t r i c a l s e r v i c e s have been l o s t ......... ............ .. ............. Closed P r o p e l 1e r ..... T r i p a1 Land as soon as p o s s i b l e ....1 FIRES WARNING THE EXTINGUISHER I N THE COCKPIT I S BCC AND GIVES OFF TOXIC FUMES I N A CONFINED SPACE............ ..... .. .. DO NOT ATTEMPT RESTART ....................... ..3 Cockpit F i r e On ground Cockpit a i r v e n t i l a t i o n intakes .. ...... ..... ........... ......................1 Electrical Fire A1 t e r n a t o r Master switch C i r c u i t breakers ....... C a r r y o u t F o r c e d Landing > 4.....1....... ENSURE ONLY SUFFICIENT EXTINGUISHING I S USED TO PUT OUT FIRE THEN OPEN ALL FRESH AIR VENTS 4........ Should t h e ammeter show an e x c e s s i v e d i s c h a r q e when a p a r t i c u l a r c i r c u i t breaker i s r e s e t then leave t h a t c i r c u i t breaker i n t h e t r i p p e d position.........1... 1 ...... ........... S h u t down (para Fire) 4 ..... C o c k p i t Open and Evacuate P..... ......................... ......4-I CAA Approved A p r i l 1998 A8 TP . .......T67M200/FM .... .......Off ................D i s c h a r g e a t s o u r c e o f f i r e Engine Canopy .. Off Master switch Off .................... Cut-of f F u e l cock .......r { ~ UAVIATION LB 0y MGS IT PILOTS NOTES FIREFLY T67M200 4........ A f t e r a l l c i r c u i t b r e a k e r s have been t r i p p e d t h e b a t t e r y power may be r e s t o r e d t o e n a b l e s e l e c t i v e r e s e t t i n g o f c i r c u i t b r e a k e r s i f necessary...1... ......... . . C .........70 k t s L a n d i n g f l a p ..... e s 70 k t s ....4-2 CAA Approved A p r i 1 1998 A8 TP..... Open h a l f w a y t o c l e a r smoke and remove f i r e extinguishant traces c a r r y o u t d r i l l s 4...... 1ocked C l o s e d and G l i d i n g speeds ........................ F i r e Extinguisher - .......... Off Throttle . 3 nm p e r 1000 f t i n s t i l l a i r ..g i v about ( 1 ....... * E l e c t r i c f u e l pump A1 t e r n a t o r ..... O f f ............o. ..........1.......... Off .. ................... ........... ..... . Cutoff * M i x t u r e ............1 E l e c t r i c a l F i r e and/or 4..........70 k t s T a k e o f f f l a p .P o s t Mod 333) o r (1........... *Magnetos ............. T67M200/FM .........s.............. ...................e d .t Discharge a fire source o f Canopy D i r e c t V i s i o n Window ............ .....l M i n RPM Propel l e r ........................................ . 60 k t s Items marked * must b e completed even f o l l o w i n g an e n q i n e f a i l u r e a f t e r take o f f .........5 nm p e r 1000 f t i n s t i l l a i r p r e Mod 733) *Radio ............1.... T i g h t and .65 k t s Thresh01 d speed ................ ... Off ............ 1 Emergency c a l .. necessary Assess ( I f 4............ P............. Off locked *Master s w i t c h *Harness *Canopy ....PILOTS NOTES FIREFLY T67M200 > In flight Cockpit A i r V e n n t i l a t i o n Closed and H e a t e r I n t a k e s .......2 Engine F i r e ) F i r e Damage .......2 FORCED LANDING Glide ........ ... ............. .... ......... ........ *Fuel c o c k ...l e a n C ... ....... DITCHING I S BEST CARRIED OUT WHILST ENGINE POWER I S AVAILABLE TO CONTROL THE RATE OF DESCENT............. 300 f t m i n R a t e o f descent DO NOT ROUND OUT C o n t i n u e descent i n t o t h e w a t e r .... Completed ...........T67M200/FM ...C l o s e d o r e x c e p t canopy l o c k e d open ( P o s t Mod 28...........3 a/c) .......... 60 k t s . T i g h t and locked ......... CAUTIONS I N BOTH CASES THE AIRCRAFT MAY TURN ON ITS BACK......... W i t h o u t Power Avai l a b 1 e F o r c e d l a n d i n g checks Canopy Flaps Speed ............................. W i t h Power A v a i 1a b l e Harness Canopy Flaps Speed ................l i s h e d As e s t a b R a t e o f descent DO NOT FULLY ROUND OUT Check r a t e o f d e s c e n t b u t f l y t h e a i r c r a f t i n t o t h e water........l l y down Fu .... P..3 DITCHING WARNINGS I F ABOVE 2000 FT AMSL CONSIDER ABANDONMENT BY PARACHUTE.......... LAND INTO WIND PREFERABLY ON THE CREST OF A WAVE............................... WITH CANOPY I N OPEN POSITION DURING FLIGHT SUCTION CONTROLLED INSTRUMENTS WILL BE MORE DIFFICULT TO READ DUE TO INDICATOR NEEDLE FLUTTER......4-3 CAA Approved A p r i 1 1998 A8 TP ...............................PILOTS NOTES FIREFLY T67M200 4.............................................. 60 k t s ........................... I N A STRONG WIND.. I F THE SWELL I S HEAVY LAND ALONG THE SWELL.open Closed o r l o c k e d (Post Mod 283 a/c) ....... F u l 1 y down ......SJ............. RELEASE THE SEAT HARNESS AND EXIT VIA THE OPEN CANOPY BEFORE INFLATING L........................................... ... .. . .. ..... . . Lean c u t ..... .....l o w l y t o f u l l S ... ........ I f d i v i n g t o s t a r t t h e engine care must be taken on t h e p u l l ....... ........ ............... .................. I F THE ENGINE STOPPED WITH UNUSUAL MECHANICAL NOISE... ...... On ( L e f t o r R i g h t ) Fuel cock LH Magnetos .......... ....... .. A1 t e r n a t o r . ... . ............ ................... ... ................ .. DO NOT ATTEMPT RESTART. ... ................. Propel 1e r . ..... d i v e t o s t a r t p r o p e l l e r t u r n i n g (approx 115 k t s ) ... Max RPM Mixture . ........ ... ........ i f s t a r t e r i s i n o p e r a t i v e ..................... ...... Mixture Alternator Throttle .8 0 0 FT I f t h e p r o p e l l e r stopped d u r i n g aerobatics. .... power Increase rich slowly A l l o w engine t o warm up D I V I N G TO RESTART THE ENGINE USES 6 0 0 ....... . Off ...........4 ENGINE FAILURE - PROPELLER STOPPED WARNINGS EARLY PREPARATION FOR AN EMERGENCY LANDING I S PREFERABLE TO FOLLOWING DRILLS AND THEN BEING LEFT WITH TOO LITTLE HEIGHT TO CARRY OUT A SAFE LANDING. .... .... .. ... R e s t a r t Procedure Master s w i t c h ....... t h e engine may be s t a r t e d immediately u s i n g t h e s t a r t e r b u t t o n so l o n g as t h e r e was no mechanical n o i s e when t h e engine stopped. T h r o t t l e .... ........ ......o f f .. .. Check 114 i n c h open .... Fuel pressure ... on .............. ...o u t n o t t o exceed t h e g l i m i t s ( r e f S e c t i o n 2) . ..... . . ....... ............... 4-4 CAA Approved A p r i l 1998 A8 TP ....On .PILOTS NOTES FIREFLY T67M200 4.............. Check (Both gauges) Fuel contents .......... On E l e c t r i c f u e l pump ........... EITHER operate s t a r t e r OR. ............. .. T67M200/FM . When engine s t a r t s .... BUT CARRY OUT FORCED LANDING........ Check .... P . ..... ........... .. .... MAGNETOS Both Right Left Both I F NO IMPROVEMENT ... ......................................................................................5 ENGINE FAILURE .......................... - CARRY OUT FORCED LANDING P ..... Min RPM (Speed fully aft) Cutoff M i x t u r e ............ F u e l cock On L e f t o r R i g h t Tank Mixture Lean ................................ i f no b e t t e r ........T67M200/FM .-'{SLINGSPY LTm avln. Closed .... Off Throttle Propeller CARRY OUT FORCED LANDING.................lON PILOTS NOTES FIREFLY T67M200 4............PROPELLER TURNING WARNING EARLY PREPARATION FOR AN EMERGENCY LANDING I S PREFERABLE TO FOLLOWING DRILLS AND THEN BEING LEFT WITH TOO LITTLE HEIGHT TO CARRY OUT A SAFE LANDING................................ Off E l e c t r i c f u e l pump ......... R e s t a r t Procedure FUEL control Magnetos ......................................... Off Not Zero (Both Tanks) F u e l c o n t e n t s ....................4-5 CAA Approved A p r i l 1998 A8 TP ..t e r i f no b e t ................................ ........................................... F u e l cock ...... i f no b e t t e r ........c u t o f f 1/4 i n c h OPEN Throttle On E l e c t r i c f u e l pump Check Fuel pressure ........................................... ......................... ............... MECHANICAL I f t h e r e i s no o i l p r e s s u r e o r i f t h e r e i s unusual mechanical n o i s e : ..... ... I f t h e s m e l l i s p e t r o l .Set A1 t e r n a t o r ..... > I n any event... Try alternate frequencies..........PILOTS NOTES FIREFLY T67M200 4.... I f s m e l l i s e l e c t r i c a l ...T67MZOO/FM ... with all essential services 4..... T u r n r a d i o s o f f ..... iAND AS SOON AS POSSiBiE 4........................ do n o t make any e l e c t r i c a l s e l e c t i o n a t a l l as a s p a r k c o u l d l e a d t o f i r e ....... Land a t n e a r e s t s u i t a b l e a i r f i e l d ...Off Check a l l e n g i n e i n s t r u m e n t s f o r any s i g n o f m a l f u n c t i o n ... Change headset i f p o s s i b l e ... reduce e l e c t r i c a l l o a d s t o a minimum. P..... ............... ............ o p e r a t i n g i s i n excess o f 30 minutes.......4-6 CAA Approved A p r i l 1998 A8 TP .Off' E x c i t a t i o n c/b ..On .... . t h e b a t t e r y d u r a t i o n .....e l e c t r i c a l f i r e d r i l l .Set A1 t e r n a t o r c / b ............7 ALTERNATOR FAILURE A1 t e r n a t o r .. gauges e t c ) .......... P l u g i n headset on o t h e r s i d e - use o t h e r t r a n s m i t t e r b u t t o n .......6 FUMES I N THE COCKPIT Cockpit h o t a i r/demist Fresh a i r vents .. F u l l y open ................... a l l o w t o c o o l f o r 5 minutes and t h e n t r y a g a i n .. t o conserve b a t t e r y l i f e . ... ........8 COMMUNICATIONS FAILURE Check volumes and s e l e c t i o n s on r a d i o s and c o n t r o l panel Check c i r c u i t breakers............... Descend o u t o f c l o u d b e f o r e s e r v i c e s f a i l ( r a d i o .... I f t h e a l t e r n a t o r o u t p u t cannot be regained.................... < (e) Land at nearest a v a i l a b l e a i r f i e l d .............i t h t h r o t t l e control w .. P. .10..... (c) Reduce speed t o 80 k t s .4-7 CAA Approved A p r i 1 1998 A8 TP ...10 4. 4.9 OIL PRESSURE FAILURE WARNING PROLONGED USE O P W R AFTER ENGINE OIL PRESSURE F O E FAILURE WILL LEAD TO ENGINE MECHANICAL DAMAGE F u l l t h r o t t l e may be used i n emergency but engine f a i l u r e i s l i k e l y t o f o l l o w l o s s o f o i l pressure..T67M200/FM . (b) Leave RPM c o n t r o l i n mid-range.. 4. - open (c) Exercise t h e RPM c o n t r o l s l o w l y throughout t h e whole range (d) I f t h e RPM s t i l l does n o t respond...... Krm Throttle .............PILOTS NOTES FIREFLY T67M200 4.. p a r t i c u l a r l y i f much power i s used..use o f more than about 314 t h r o t t l e may cause RPM t o overspeed... (b) Check t h a t m a n i f o l d pressure i s above 15" t h r o t t l e i f necessary t o achieve t h i s ......10... (d) Land a t nearest a v a i l a b l e a i r f i e l d ........1 PROPELLER GOVERNOR FAILURE RPM w i l l not Increase (a) Check t h a t engine o i l pressure has not f a i l e d ...... leave t h e RPM c o n t r o l i n mid-range and use engine power observing t h e RPM/Manifold pressure l i m i t s i n S e c t i o n 2............except f o r closed emergency C a r r y o u t f o r c e d landina a t nearest a v a i l a b l e s i t e ...2 RPM Overspeeds o r w i l l not Decrease (a) Use t h r o t t l e t o keep RPM i n l i m i t s ....... ..T67M200/FM .J { A\............ back-up battery LAND A SOON A POSSiaiE S S CAUTION AFTER LANDING TURN SWITCH BACK TO D W POSITION OR BATTERY W I L L O N DISCHARGE EVEN W I T H MASTER S W I T C H OFF P4-8 CAA Approved A p r i l 1998 A8 TP .. ~ ~ ~ ~ ~ PILOTS NOTES FIREFLY T67M200 4.UP will give at least position half-hour of The emergency operation.........lATION LTO ~ L .11 PORT ELECTRICAL ARTIFICIAL HORIZON FAILURE (MOO 312) Back-up b a t t e r y s w i t c h .. . . . . . . . 5 . . .. Cast e f f e c t i v e page i s P.. . .. .. . .... ... . .. ... . . .. .. . . 3 . . . ... .. . . . . . . . . . .. . f u e l and d i s t a n c e t o descend . .. .. S t a l l Speeds .3 . . .. . . . . . . .. . . .. .. . .. . Improved Technology P r o p e l l e r . .. . .. .. . .. .. . . .10 Time.. . . .. . . . . AS1 P o s i t i o n E r r o r s A1 t i m e t e r P o s i t i o n E r r o r s .. ... .. . . .1. . . . 56 Endurance Performance ... . . . . . . .. . .... . . . . .1.. ... . . . . .. . . .. . . . . . 1 Climb Speeds . .. h. . . . . ... .. . . . ... .PILOTS NOTES FIREFLY T 6 7 M 2 0 0 SECTION 5 PERFORMANCE AND FLIGHT PLANNING CONTENTS 5 1 General 5 . . C r u i s e Performance Range .1. . . . .. . .5 5. . . .. . . . . . . . .. . ..-1 5-1 5. . . .. . . .. . . . . . . . . . ... . . . . . . . . 6 59 5. . . .. . . .. . . . .. . . . . . 1... .. . Maximum Crosswind Components . .. . . . . .8 .. . . . . . .5-12 CAA Approved December 1988 A6 TP T67M200/FM .5A 51. f u e l and d i s t a n c e t o c l i m b .. . .. . .2 5 1.14 x5. .. . F l i g h t Over Water Speed . . .. . ... . . .. . .. 5 5 A . . . . . . . . . . . . . ... . . Time. . . . . . . x 5. . 5-4 5. . . ..-2 5-3 5-4 > 5 2 Performance Group . 5-1 5-1 5-1 5. .. ... . .. . . ... . .. . . .. . . . . . . . ... .... .. . . . . .. .. .. . . . ... . 1 5. . . . . . .. . .... . . . .. . . . . . . 5 . ..6 . . . .. . . . .. . ..... . . .. . .. . .. . . . . . . . . . ... ... . .. . . . . . . . . . . . .. . .. ... 3 2 Rate o f Climb i n ISA Temperatures A . . . . . .c 5 7 . . .. . . .. . . . .. .. . < A T a k e o f f Performance Climb ..3 5. . . ... .. . .. . . . . . . .... . . . ... . . . . . . . . ... . 5-8 5-10 5--11 5-12 5. . . .. . . . .. .. . . .-4 5-5 5-6 5-7 54 L a n d i n g Performance G l i d e Performance . .. .. . . . . . . ... . . . . . .. . ... . . . .. .. .. Y T67M200 INTENTIONAtLY BLANK CAA Approved A u g u s t 1985 TP . T67M200/FM .PILOTS NOTES FIREF1. 4 A l t i m e t e r P o s i t i o n Errors The maximum a l t i m e t e r s t a t i c e r r o r i s -30 f t 5.5 141.. This means t h a t t h e r e i s no s p e c i f i c provision f o r performance a f t e r engine f a i l u r e .1 Performance Group -.5A Improved Technoloqy P r o p e l l e r POST MOD 333 i n t r o d u c e s an improved technology p r o p e l l e r . graph page 5-6) a l l o t h e r performance t a b l e s a r e unaffected. c P.5 Maximum Crosswind Components > The maximum demonstrated crosswind component f o r t a k e o f f and landing i s 25 kts. Water Speed The d e c l a r e d " f l i g h t over water" speed of t h e a i r c r a f t i s a true a i r s p e e d of 100 kts.5 1. 5.PILOTS NOTES FIREFLY T67M200 5.7 80 81 90 91 98 99 60 60. 5..T67M200/FM ... .1.1. .IC 9 C l i q h t Over .3 A i r Speed I n d i c a t o r P o s i t i o n E r r o r s Flaps R e t r a c t e d IAS (Kts) 50 60 70 180 C S (Kts) 51 61 71 A 182 Takeoff Flap IAS (Kts) 50 CAS (Kts) 50 Landing Flap IAS (Kts) 50 CAS (Kts) 51.5-1 CAA Aooroved April i998 A 8 TP ..5 151 162 172 5.5 70 71 80 81 90 91 100 102 110 112 120 122 80 90 100 81 91 100. The performance d a t a has been measured i n accordance with both S e c t i o n K BCAR and F R Part 23.5 121.1.1. Other than i n the g l i d e ( r e f ..1.31.5 110 120 130 140 150 160 170 111. This a i r c r a f t i s c l a s s i f i e d in Performance Group E of BCAR..2 60 61 70 70. A E 1 .1 GENERAL 5. 1.T67M200/FM .PILOTS NOTES FIREFLY T67M200 5.5-2 CAA Approved April 1990 A7 TP .6 Stall Speeds - At Forward C o f G AIRCRAFT WEIGHT (LBSI K. 2 TAKEOFF PERFORMANCE The i n f o r m a t i o n i s d e r i v e d fr. @ Dry grass (6 hs long) FO~ operatian h headwind cond'lbnrlhefoll~ng mrredlans may be applied: Decrease distances by 1O%for each 9 knols 20% olthe totattakeofld'btance Far operalkkn in talwind candnsns the follaw'ng w m d l i n must be applied: m Wet grass (8 ins long): > < 3a% of lheto1allakeoff dmance c lncteased'istance by 10% for each 3 5 knots In me ewntof a napless tskeofl~haflrpeed 53 Mr lAS. 1317 1496 1699 1966 2246 2575 20'C Gmund Rall 737 838 962 1111 1273 1462 Totalto dearSOR. LEVEL RUNWAY -ZERO WlND Gross W i t Takeoff Speed LimMf A1508 Pressure Andude R (m) SeaLeiel 1000 (305) 2000 (610) 3000 (914) 4000(1219) 5000(1524) 0'C Gmund Roll 683 780 890 1034 1188 1365 Tatalto clear50R.speed at50 men heQhtaf74 kls IAS) the totallakeoffdaance should be inmared by 29% P 5-3 CAA Approved A p r i l 1998 A8 TP . speed of at50 nscreen heght of 72 Ms 14s) me tala1takeofld'bianceshould be ncreased by29% POST M D 3 5 8 . LEVEL RUNWAY -ZERO WlND Totalto dearSon 1455 1638 1878 2174 2485 2851 Ground Roll 948 1082 1234 1434 1644 1877 10'C Totalto clear50R 1504 1708 1940 2245 2564 2940 Gmund Roll 986 1121 1273 1466 1703 1955 Ibs(kg) 2250 (1020) For operaran on grass ~nwaysthetolal Iakeafld'etances scheduledfor p a d runways must be increased as follows > Foropemlon h headwnid wndllonsthe following w m d a n r may be appl'ed: Decrease d'atancer by 10% for each 9 knals (0 Diygrass (8 b long): x Wetgnss (8 ins long): > < 20% ofthe totattakeoffd'aance oro opera tan iolaiMnd w n d ' l t l a n s t h e f a l i ~ r r e m n must be applied' w 30% ofthetotal takeoffd'aance O s Increase distance by 10%for each 3 5 knots In the eientof a Raplesslakeoh(ll0ff speed af €4Ms 14S.om t h e t a b l e and r e p r e s e n t s t h e t a k e o f f d i s t a n c e s r e q u i r e d f r o m r e s t t o t h e 5 0 f t (15m) h e i g h t p o i n t .MTWA 2250 LBS (1020 O / Gm58 Werght Takeoff Sped Laon Al50R 55Ms 69Kts Presure Anlude n (m) SeaLeiel lOOO(305) 2000(810) 3000(914) 4000(1219) 5000(1524) O'C Gmund Roll 914 1043 1190 1383 1589 1826 T67M200 TAKEOFF DISTANCE lltl I 20°C Totalto dearst 1558 1763 1997 2319 2650 3038 Gmund Roll 1105 1264 1446 1654 1894 2179 30'C Totsllo dearMR 1729 1968 2242 2562 2924 3360 Gmund Roll 1233 1410 1610 1843 2086 2421 40'C Tola110 dear5OR 1913 2176 2479 2833 3204 3712 CONDITIONS : FLAP 18' 1 FULL THROTTLE PRIOR TO BRAKES RELEASE! PAVED.PILOTS NOTES FIREFLY T67M200 5. 1365 1544 1749 2031 2321 2561 1 Gmund Roll 826 945 1081 1237 1416 1629 bs(kgj 2150 (9751 50 MS 87615 30°C Totalto dear50R 1514 1724 1964 2244 2561 2943 Gmund Rall 922 1054 1204 1378 1560 1810 40'C Totallo dear500 1676 1906 2171 2481 2806 3251 For operal'bn an grass wnwaysthetotal lakeoff d'aances scheduled far paied runways must be increased a5follows. PRE-MOD 3 5 8 MTWA 2150 LBS (975 k q ) CONDITIONS :FLAP 18'1 FULL THROTTLE PRIOR TO BRAKES RELEASE I PAVED.T67M200/FM . . 1274 1435 1645 1904 2177 2497 Gmund Roll 709 809 923 1072 1229 1411 10'C Tolalto dearSon. 2 Rate o f Climb i n ISA Temperatures ALTITUDE (Feet) < Note: I n h o t weather. reduce the r a t e o f c l i m b by 25 f e e t p e r minute f o r every 5°C above t h e standard temperature a t t h e a l t i t u d e i n question .3 CLIMB - 5.000 f t ( r e f e r t o l i m i t a t i o n s s e c t i o n : 2.1).1 Climb Speeds The b e s t r a t e o f climb speed a t maximum AUW 975 kg (2150 l b s ) i s 80 k t s I A S w i t h o u t f l a p i n ISA temperatures.3.T67M200/FM .PILOTS NOTES FIREFLY T67M200 5. CAA Approved A p r i l 1990 A7 TP .3. 5.7. S e r v i c e c e i l i n g i s 16. PILOTS NOTES FIREFLY T67M200 I N ' T E N T I O N A L L Y BLANK P.T67M200/FM . 5-4A CAA Approved A p r i l 1990 A7 TP . -.. >. .POWER OFF -MODEPATE BPAKING -HARD DRY RUNWAY . 1884 1953 2026 2102 2181 Gmund Rail 917 951 987 1024 1062 1102 3VC Totalto dear 5OR. . ~. ZERO WlND Gms Weoht Indicated AiSpeed Al50R Prersure Anitude R (ml Sea Lee1 1000 (305) 2000 (610) 3000 (914) 4000 (1219) 5000 (1524) O'C Gmund Roll 826 857 889 922 Ibs(kg) 2150 (9751 65 KIE 957 993 Totalto dear M R 1755 1820 1888 1958 2032 2109 Gmund Roll 857 888 921 956 992 1030 1O'C Totalto dearMt 1819 1887 1957 2030 2107 2187 20'C Gmund Roll 887 920 954 990 1027 1066 Total10 dear5OR. PRE M D 358 O CONDITIONS : FLAP 40.c 15% ofme total landing titstance For opeman mtaUwind wnd'llonr the follaving mma'an mus &applied: 30% of the total landinadbtance E - Increase diaance by 10% for each 2 knots In me een1of a napless landing (approach speed of 74 m 1 5 the total landing atstance 4) should be increased by 20% CAA Approved A p r i l 1998 A8 TP T67M2001FM .a i r c r a f t t o rest .P I L O T S NOTES F I R E F L Y T67M200 5. 1948 2012 2095 2173 2256 40% Gmund Roll 948 983 1109 1057 1097 1139 Tatalto dear50H 2012 2087 2164 2245 2330 2418 22M 2341 Far operation an grass runwaysthe Iota1landing dbiances Scheduled for paved wnways must & haeased as follows: For operation n headvnnd conditionsthefollaw'ng wrrea'ons may be applied: I'I I Decrease & acr &ne l by 10% for each 8 knots (0 ow grass (8 ins long): lih Weioias 1 ms I o n 1 8 .4 LANDING PERFORMANCE The i n f o r m a t i o n i s d e r i v e d from t h e t a b l e and r e p r e s e n t s t h e l a n d i n g d i s t a n c e r e q u i r e d from a h e i g h t o f 5 0 f t (15m) t o b r i n g t h e. 5) must be c a r r i e d o u t .3. where l a n d i n g s have t o be c a r r i e d o u t a t AUW's between 2150 l b s and 2250 l b s ground r o l l and t o t a l l a n d i n g d i s t a n c e s s h o u l d be as shown i n t h e f o l l o w i n g t a b l e Heavy l a n d i n g checks-'(ref 7. > (9 Decreasedibtances by 10% for each 8 knoll Dlygiass (8 ins long): 15% ofthe total landing distance Far operain n t a i M d modi~ions fallwnng coriecinn must be a W i the (3 Weisrass (8 ins long): 30% oflhe total landing dblance 2 - I Increase dlrtance by l o % for each 2 knoll > < 10 the e*ed o f a napless iand'kg (approach speed cf 74 kll MS)the total landing dinance should be haeased by20% P.A { ~ A\.lATION mOy u K LT PILOTS NOTES FIREFLY T67M200 POST MOO 358 I n cases o f emergency o n l y .T67M200/FM .5-5 CAA Approved A p r i 1 1998 A8 TP . For operafan n headvlnd conditlansthe fallwnng corredanr may be a W i . > < For operalion on grass runwaysthetolal landing #&lances Ynmuled forpayed lunwal.must be mmased ar follows. DISTANCE TRAVELLED (N. T h i s g i v e s t h e maximum g l i d e a n g l e w h i c h i s 1 i n 8 2 P o s t Mod 333 o r 1 i n 9 P r e Mod 333. 5-6 CAA Approved December 1988 A6 TP.PILOTS NOTES FIREFLY T67M200 5.5 GLIDE PERFORMANCE A t maximum t o t a l w e i g h t o f 975 k g (2150 l b s ) > S e t speed t o 70 k t s ( I A S ) .Miles) P . T67M200/FM . Engine O f f - Propeller Windmilling - Flaps Retracted - No Wind. .PILOTS NOTES FIREFLY T67M200 5 6 ENDURANCE PERFORMANCE - I N HOURS MAX FUEL CONTENTS 34. o m .wm 7 - m m h4 1 .5-7 > < A p r i 1 1998 A8 TP . '91'9s * * L C - m m m Y 'A EL 0 Y rn m . O l e ' O d U ) 3 * 6 m a U) m mm n0 I - 5e 2 k . = 2 = I - I : B W I - I ( I -low "- b -z 2 * I I t . 5 8 US Gal) 157. I t ---m . m * O .. . .62 Imp Gal ( 4 1 .. m m o m o m 0 L rn 75 U P.x LOO h N m0 V) VI -z nn 'A Z -4 o w * m m w w m m * L " . I . A N NN ..-. ) m m Y . .4 l i t r e s ) 0 N N . D * o m .. . .T67M200/FM . z Y -. I h . 4 m . m u . m w m U 0 E e m .-A P . . . I I m b . * V) d I-' . 7 C R U I S E PERFORMANCE l[...Nm* o m a l --- * sgEa om- WZ. P. T 6 7 M 2 0 0 1 F M .1 1.99 mm-am .4 0 C.ddd -. I I t 9 -"a- .&<dm' "NO" '=--m ..) ' 5 44. L. 4 ." ' 0'" . 4 mN* 004 N N N --.5-8 > < A p r i l 1998 A 8 TP .x l[lA5i'l =mc> i i i l - * ... -*a. ? z 4 E .PILOTS NOTES FIREFLY T67M200 5.. .4 #..4 - " = c. 1 r-mN N A ..il I I I :s i -40 . u rn yz. : Y? 9 m m -.- -000- 1 -om. . 5-9 > < A p r i 1 1998 A8 TP .PILOTS NOTES FIREFLY T67M200 P .T67M200/FM . T67M200/FM .58 US G a l ) (157.5-10 > < A p r i l 1 9 9 8 A8 TP .62 Imp Gal (41.PILOTS NOTES FIREFLY T67M200 5.4 l i t r e s ) I N P.8 RANGE PERFORMANCE (PRE MOD 358) MAX FUEL CONTENTS 34. T67M200/FM .62 Imp Gal (41.PILOTS NOTES FIREFLY T67M200 5.4 l i t r e s ) P.5-10A > < A p r i l 1998 A8 TP .58 U Gal) (157.8A RANGE PERFORMANCE (POST MOD 358) - IN S MAX FUEL CONTENTS 34. PILOTS NOTES FIREFLY T67M200 5. F U E L AND D I S T A N C E TO CLIMB MAXIMUM RATE OF CLIMB (PRE MOD 358) .9 T I M E . PILOTS NOTES FIREFLY T67MZ00 5.5-11 > < A p r i 1 1998 A8 TP . m m m m m m P..T67M200/FM .9A TIME. FUEL AND DISTANCE TO CLIMB (POST MOD 358) MAXIMUM RATE OF C L I M B m r 62 u nn 2 ': U L. - nv . T 6 7 M 2 0 0 / F M ..PILOTS NOTES FIREFLY T67MZ00 5.10 TIME.5-12 > < A p r i l 1998 A8 TP . FUEL AND DISTANCE TO DESCEND PRE MOD 3 5 8 MAX AUW 2 1 5 0 LBS ( 9 7 5 KG) AND POST MOD 3 5 8 MAX AUW FOR TAKE OFF 2 2 5 0 LBS ( 1 0 2 0 KG) P. DESCRIPTION AND USE CONTENTS 6....... ................ ....................... ............1......3............. ................... .......... 6-9 Fuel M i x t u r e / C u t ..... ............... ............ .............. .... ........................ Normal Use ..............2.......1......... ....... .... ... ..............1 General D e s c r i p t i o n ............. 6-1 6-1 Engine L u b r i c a t i o n System ..3................... .................. .......... ...... ........ ........ .....3.2...... ...... ...1............ Fuel System Diagram .........3..............3............2 6 ........ ......... 6-10 M a l f u n c t i o n i n g .... ......6A 6.... ..................... ... ..1............3 6.....1........... 6-2 ..2 6............ .................. ................... .....................3 The E l e c t r i c a l System .. ............. ... ...... ....6 Fuel D i s t r i b u t o r .......... ....... 6-9 6.... .... 6-6 6 1. ..................2... .........3................ ......2 .......3 Fuel Contents Gauge .. 5 Tachometer M a n i f o l d Pressure 6-4 6..... .. ..7 6.... .... 6-15 The E l e c t r i c a l C i r c u i t Diagram ...3..........................2................ 6-12 6 3 .. . ........................ .< ................ ..... .....2..... ...............7 P r o p e l l e r and Constant Speed U n i t ................ ..2....11 .......2..... 6-9 6.................... ... 6-7 6..... 6 6...... .............1..... .. .I. . .. T67M2001FM ...PILOTS NOTES FIREFLY T67M200 SECTION 6 SYSTEMS LAYOUT..........1 6........................................ ................5 Fuel Control U n i t ...1............ .............. .. ...... .. ..... ......... 6-7 6............. ...... . ..................... ......... .... ........................ ..2............ .... ................... .... 6-7 6...................6-11...2.. 6-14 Malfunctioning 6-14 Emergency back-up b a t t e r y f o r p o r t e l e c t r i c a l a r t i f i c i a l h o r i z o n (MOD 312) 6-14 .2.. ...1 9 Normal Use . C i r c u i t Breaker Layout ...7 T h r o t t l e .............9 .... ............ .... 6-8 6.... 6..... 6-16 Deswiption 6-12 6-12 Battery A1 t e r n a t o r 6-12 6-12 C i r c u i t Breakers ........ 6-1 The Engine .......8 6-6 6... ..... ... The Airframe and Engine Fuel System ............... .....8 6.........6-11 ............4 6 ..... .. ............. ......3.... ... ..... ........... ........... ............. .............4 6-4 6 ..... ... .................1 General 6............. 9 6...............10 Malfunctions ........ Magnetos ... 6.. 6-8 6........ 3 6....6 Starter 6-4 6...... 6-5 6................... .. .......... ... ........... .... 6-1 General D e s c r i p t i o n ....... ..2............ ................ ........ ... ... 6-16 C i r c u i t Breaker Layout .................. ....................3........... ...... ....1 The Engine and P r o p e l l e r 6.. ...... ..... ...... . .10 6....2 Fuel Tank ....... .. .... Normal Use o f t h e System ............... .......... 6-8 6........... 5 6 ....4 Fuel Pressure Gauge ......... .o f f C o n t r o l ...8 6 ....... A p r i l 1988 A8 TP ............ . 6................................................... 6-25 6...........5.2 6.. 33 Normal Use ...10 Normal Use .........7. 6-29 The S t a l l Warning .6...............5..7 6............... 6-25 6...6............ 6.................. 6-26 General D e s c r i p t i o n .........6-17 S a f e t y Equipment ........ 6..1 6...........................7........10 6....6................5..3 The Nosewheel ...17 Access t o t h e C o c k p i t . 6.... 6-26 P i t o t and S t a t i c I n s t r u m e n t s ........ 6-35 August 1985 TP T67M200IFM ............................ 6-23 6......................6....................6................................6-17 A i r c r a f t S e c u r i t y ..... 6 ..............5......27 ..o r d i n a t o r ...... 6-20 C o c k p i t L i g h t i n g ..................6....... 6-20 6....................5 Nosewheel S t e e r i n g ............. The S u c t i o n S u p p l y ...................................... 6-35 General D e s c r i p t i o n ....................................... ....3 6. 6-26 The P i t o t and S t a t i c Systems .4 6....................4 . 6-29 S u c t i o n D r i v e n I n s t r u m e n t s .................................... .........5...8 Ground H a n d l i n g Arms .....................................................9 6................ 6-23 6. 6-19 A i r c r a f t E x t e r n a l L i g h t i n g . 24 6................................................ 6-35 C o n t r o l Column ....................7........1 6....... 6-25 F l i g h t Instruments 6...... ..6 6.. 6-30 The M a g n e t i c Compass ..........4 General Equipment ......... 6................. 6-24 6.. 6... 7 T a i 1 Bumper ..5 ..6 Wheelbrakes .............6.................... 34 F l y i n g C o n t r o l s and F l a p s 6..... 6-31 The T u r n C o ........................6.......5..........9 P i c k e t i n g .........2 T y r e s ..11 6................................................PILOTS NOTES FIREFLY T67M200 ...............................5 U n d e r c a r r i age ............1 G e n e r a l D e s c r i p t i o n ............................7........................6-17 S e a t s and Harnesses .... 6-24 6..... 6-20 C o c k p i t V e n t i 1 a t i on and H e a t i n g ........7 .................34 M a l f u n c t i o n i n g .....5..........2 6.........6......................................................................................5..............6............35 E l e v a t o r and Trimmer ............. 6-17 Canopy ..............8 6......... 6-23 6............5 6...4 The Mainwheels ....................6............6 6..6....5........................... 6-24 6. 6-25 6.3 6... 6-32 M i s c e l l a n e o u s I n s t r u m e n t s .......................... 6-35 A i l e r o n s ........ ......... 6............. ...... 6 . .................5 7 6..............7 The Magnetic Compass ........ .............................. ....5 ......... ...............3 6 .... 35 August 1985 TP ...... .. 6.. 5 6....... 4 General Control Elevator and Trimmer ............................ .. ...................................... ....7 ........... ........ 1 0 Normal Use 6-34 6 ....................................... 9 Miscellaneous Instruments .....3 6 ..... .......... .....7 ....... ........... .................-26 6 .-26 6........ .... .............................. ..6 1 1 i ght Instruinents 6 .5.................. ......................... .................. ................ ..................... 3 P i t o t and S t a t i c Instruments 6-27 6 6 .......... ............ .................... ..............................1 6..5.............. ....5 Undercarri age 6 5...................... 6 6... General D e s c r i p t i o n 6-23 Tyres ........................................................... ............................................ ...... 11 Malfunctioning 6-34 .... ......... ... ............ 6-23 The Nosewheel ........ .................... ........................ .. ........................................ 6 ... .................... 5 S u c t i o n Driven Instruments 6-29 6.....5............... 6-35 Colu:ni> ........ ......................7 ...... .................. ....... ............ ........... 6 .... ............ ....... ................... ..8 The T u r n Co-ordi nator 6-32 6 ...1 G ... ... 6-33 6 6 .................... ........... ..............9 6 ..... .............. ... ........................ 6-17 Aircraft Security 6-17 Canopy .. 6-35 A i l e r o n s .. .....................................5 ..... .... 6-20 .... .... ................... .............. 6. 20 Cockpit L i g h t i n g 6-20 Cockpit V e n t i l a t i o n and Heating . 6 . .......... ..................... ...... ............... ......... ... 10 .... ...........................4 Gener a1 Equi pment .............. .......6 The S t a l l Warning 6-30 6 ...7................ .... a f t External Lighting 6................................ ... 6 ................... 6-31 6 ........... .. ............... ............. ..... . 6. 6-35 D e s c r i p t i o n . .......... 6-17 S a f e t y Equipment 6-17 Access t o t h e Cockpit ..........................................23 ......... 6-24 The Mai nwheels 6-24 Nosewheel S t e e r i n g 6-24 Wheel br akes 6-24 Tai 1 Bumper 6-25 Ground Handling Arms 6-25 Picketing 6-25 Normal Use 6-25 ......... 6-17 S e a t s and Harnesses ..................................................... 6............. 4 The S u c t i o n Supply 6-29 6 ................................................ ....................-............... .... 6....... 8 6 ............................ ....4 6........... .... ......................................... .....................................................5 2 6.......PILOTS NOTES FIREFLY T67h1200 & 6..........2 6..... .......... .............. ... 6 1 General D e s c r i p t i o n 6-26 6 ..6............... ....... ............................................ 2 The P i t o t and S t a t i c Systems 6........................ ........ 6-19 A i r c r .........5 ................. 5... ...................... ............ . 6....................... 7 F l y i n g C o n t r o l s and Flaps 6 . .......6-35 ...T67M200/FM ....... ............... . .....8 riudder Control L.................7 6......... 6-38 Last e f f e c t i v e pzye i s P....................1....6-...... 6-35 .........................................PILOTS NOTES FIREFLY T67M200 c..6 5................................8 6...7...9 6...........7.5-......... 6-35 ........................7.........................36 ............. 6-37 Radio Equipment ........7........ocks Flaps Normsl ilse Maifunctioning ...T67M200/FM .5 --- 6....... 6-37 ........'38 August 1985 T P ......... =({SLINGSBY AVIATION PLC PILOTS NOTES FIREFLY T67M200 I N T E N T I O N A L L Y BLANK A u g u s t 1985 TP .T67M2OG/FM PILOTS NOTES FIREFLY T67M200 6.1 6.1.1 THE ENGINE AND PROPELLER Gener a1 D e s c r i p t i o n - The a i r c r a f t i s powered by a 4 c y l i n d e r 4 s t r o k e p e t r o l engine d r i v i n g a 3 bladed v a r i a b l e p i t c h p r o p e l l e r which r o t a t e s c l o c k w i s e as viewed by t h e a i l o t . The p r o a e l l e r i s d r i v e n d i r e c t l y f r m t h e engine. F u e l i s p r o v i d e d t o t h e c y l i n d e r s by a f u e l i n j e c t o r system equipped w i t h t h r o t t l e and m i x t u r e c o n t r o l s ; t h e r e i s p r o v i s i o n f o r o i 1 and f u e l s u p p l i e s t o a l l o w s u s t a i n e d power d u r i n g i n v e r t e d f l i g h t . . Engine i g n i t i o n i s p r o v i d e d by t w i n magnetos. The engine i s an Avco-.Lycoming AEIO-360-A1E r a t e d a t 200 HP a t 2700 RPM. A p u l l e y on t h e p r o p e l l e r d r i v e p r o v i d e s power f o r t h e b e l t - d r i v e n a l t e r n a t o r ; d r i v e s f r m t h e back o f t h e engine power t h e vacuum pump, mechanical f u e l pump, t w i n magnetos and engine speed tachometer: a drive from t h e f r o n t o f t h e engine s u p p l i e s engine speed i n f o r m a t i o n t o t h e p r o p e l l e r c o n s t a n t speed u n i t . 6.1.3 Engine L u b r i.c a t i o n System - General The wet sump engine o i l system p r o v i d e s f o r l u b r i c a t i o n o f t h e i n t e r n a l b e a r i n g s under pressure. There are no p i l o t - o p e r a t e d c o n t r o l s , b u t B o t h gauges a r e marked i n d i c a t o r s show t h e o i 1 p r e s s u r e and temperature. w i t h y e l l o w ( c a u t i o n a r y ) , green (normal) and r e d (danger bands and knowledge o f t h e c o r r e s p o n d i n g temperatur elpressur e n u m e r i c a l values i s unnecessary. O i l F i l l e r and Sump The o i l sump f i l l e r i s l o c a t e d under a f l a p on t h e t o p r i g h t -hand s i d e o f t h e engine cowling, and i n c o r p o r a t e s a d i p s t i c k . The d i p s t i c k i s marked i n U Quarts; S t h e maximum l e v e l i s t h e 8 U q u a r t mark S The maximum o i 1 consumption i s 0.484 and t h e minimum l e v e l i s 4 US q u a r t s . U quarts/hour a t r a t e d power and 0.272 US q u a r t s l h o u r at 75% r a t e d power. S The o i 1 f i l l e r cap s h o u l d be t i g h t e n e d by hand on1 y. A procedure f o r e s t a b l i s h i n g t h e normal o p e r a t i n g l e v e l of o i l c o n t e n t s f o r each i n d i v i d u a l engine i s l a i d out i n t h e Avco-Lycoming Operations Manual and should be f o l l o w e d c a r e f u l l y . The normal o p e r a t i n g l e v e l may be as low as 7 U q u a r t s and, i f t h e engine i s f i l l e d above i t s "normal" l e v e l i t w i l l S i m m e d i a t e l y dump t h e excess o i l d u r i n g f l i g h t . . O i l Cooler An a i r - c o o l e d o i l cooler i s mounted on t h e l e f t - h a n d s i d e o f t h e engine. An i n t e g r a l t h e r m o s t a t i c v a l v e d i r e c t s o i l t h r o u g h t h e c o o l e r or bypasses i t dependant on o i l temperature. Cooling a i r supply i s taken f r m t h e back b a f f l e p l a t e s on t h e l e f t - h a n d p a i r o f c y l i n d e r s , t h e a i r f i r s t e n t e r i n g t h e main i n t a k e a t t h e f r o n t o f t h e cowling. The a i r exhausts w i t h t h e r e s t of t h e engine c o o l i n g a i r a t t h e b o t t m o f t h e lower engine c o w l i n g . P.6-1 August 1985 TP .T67M200/FM PILOTS NOTES FIREF1.Y T 6 7 M 2 0 0 I n v e r t e d F l i g h t O i l System The engine i n v e r t e d f l i g h t o i l system i n c o r p o r a t e s a pump, a g e o v e r v a l v e and an o i l s e p a r a t o r . The o i l s e p a r a t o r a l l o w s t h e t o p o f t h e engine crankcase t o be vented t o atmosphere and c o l l e c t s any o i l d r o p l e t s i n t h e vented a i r f o r r e t u r n t o t h e engine sump. I n i n v e r t e d f l i g h t t.he " t o p " o f t h e engine becomes t h e sump and t h e sump becomes t h e t o p : t o s t o p t h e o i l f r o m b e i n g vented d i r e c t 1 , y t o atmosphere a s t e e l b a l l i n t h e s e p a r a t o r m v e s under g r a v i t y t o b l o c k t h e v e n t c o n n e c t i o n f r o m what i s now t h e bottom o f t h e e n g i n e . On r e t u r n t o normai f i i g h t t h e b a i l f a i l s bacic again and normal v e n t i n g t a k e s p l a c e . The changeover v a l v e d i r e c t s o i l t o t h e o i l pump: i n normal f l i g h t o i l i s taken f r o m t h e sump; i n i n v e r t e d f l i g h t o i l i s taken v i a t h e o i l b r e a t h e r p i p e a t t h e t o p of t h e e n g i n e ( w h i c h becomes t h e sump), t h e v a l v e changing o v e r a u t o m a t i c a l l y under g r a v i t y , t h u s a l l o w i n g a supply o f o i l t o t h e pump under b o t h normal and i n v e r t e d f l i g h t Extreme manoeuvres ( e g v e r t i c a l f l i g h t ) w i l l r o b t h e pump o f a l l o i l supply and t h i s g i v e s r i s e t o t h e l i m i t a t i o n s i n S e c t i o n 2,.4. D u r i n g t r a n s i t i o n from normal f l i g h t t o i n v e r t e d f l i g h t o r back a g a i n t h e o i l p r e s s u r e may f l i c k e r momentarily, d r o p p i n g b y 1 0 t o 30 p s i b u t i t should r i s e again w i t h i n m e ~3econ8. Due t o t h e l o n g e r p a t h f o r o i l f r o m sump t o pump i n i n v e r t e d f l i g h t , t h e s u s t a i n e d o i l p r e s s u r e i n i n v e r t e d I f the o i l pressure i n f l i g h t w i l l be 5.-10 p s i l o w e r than i n normal f l i g h t i n v e r t e d f l i g h t s t a b i l i z e s a t more than 20 p s i below t h e normal f l i g h t f i g u r e t h i s s i g n i f i e s a f a u l t i n t h e o i l supply system and t h e a i r c r a f t s h o u l d be r i g h t e d i m m e d i a t e l y and t h e f a u l t i n v e s t i g a t e d on t h e ground.. On s t a r t - u p , t h e o i l pressure should r i s e t o t h e y e l l o w o r green s e c t o r i f i t does n o t , t h e engine should be stopped w i t h i n t h i r t , y seconds; i m m e d i a t e l y o r severe i n t e r n a l damage may r e s u l t . The engine i s v e r y s l o w t o warm up and c a r e should be t a k e n t o observe engine o i l t e m p e r a t u r e and p r e s s u r e minima and maxima. There a r e no o i l temperature minima f o r run-up o r t a k e o f f b u t t h e engine run-.up should n o t be commenced u n t i l t h e e n g i n e has been warmed up f o r f o u r minutes from c o l d ; t a k e o f f s h o u l d o n l y be c o n t i n u e d i f t h e engine a c c e l e r a t e s smoothly as t h e t h r o t t l e i s opened and 2550 RPM i s o b t a i n a b l e i m m e d i a t e l y t h e t h r o t t l e i s opened f u l l y a t t h e b e g i n n i n g o f t h e t a k e o f f r u n Engine l i f e i s maximised i f t h e o i l i s warmed t.o 40°C b e f o r e takeoff. The engine may over.coo1 d u r i n g a prolonged g l i d e w i t h t h e e n g i n e t h r o t t l e d f u l l y back and t h i s may l e a d t o v e r y poor and slow e n g i n e a c c e l e r a t i o n when t h e e n g i n e t h r o t t l e i s subsequently opened This c o o l i n g takes place a t the e n g i n e c y l i n d e r s and w i l l be apparent on t h e c y l i n d e r head temperature gauge P r o l o n g e d g l i d e s a r e most l i k e l y d u r i n g engine f a i l u r e p r a c t i c e and, t o a v o i d > t h e problem o f o v e r - c o o l i n g , t h e engine should be c l e a r e d as r e q u i r e d by < opening t h e t h r o t t l e t o f u l l power f o r a t l e a s t t h r e e seconds and c l o s i n g i t again t o i d l e A d d i t i o n a l l y t h e t h r o t t l e should be opened s l o w l y on t h e climb out. 6.1.4 Magnetos - Two B e n d i x magnetos a r e employed; the,y a r e mounted a t t h e back o f t h e e n g i n e , t h e ' l e f t ' one b e i n g a t e l e v e n o ' c l o c k and t h e ' r i g h t ' one a t one o'clock. Each o f t h e f o u r engine c y l i n d e r s has two s p a r k i n g p l u g s ; both magnetos work t o g e t h e r , each one s u p p l y i n g one s p a r k i n g p l u g i n each c y l i n d e r so t h a t f o r s a f e t y , t h e engine w i l l c o n t i n u e t o r u n i f one magneto f a i l s . P. 6-2 September 1987 A2 TP .T67M200/FM t h e RPM s h o u l d be < w i t h i n 50 RPM o f t h a t achieved w i t h ' L ' s e l e c t e d . b. i t c o u l d n o t be s w i t c h e d o f f . 'The purpose o f t h i s check i s t o ensure t h a t t h e r e i s a drop i n engine RPM when a magneto i s s w i t c h e d o f f b u t t h a t t h e engine c o n t i n u e s t o r u n . . i t may n o t i m m e d i a t e l y be a p p a r e n t as t h e engine w i l l c o n t i n u e t o r u n . To ensure t h a t e i t h e r o r b o t h can be s w i t c h e d o f f i f r e q u i r e d . and t h e RPM i s m o n i t o r e d t o check t h a t t h e s w i t c h e d o f f by s e l e c t i n g 1 engine r u n s smoothly and t h e RPM drop does n o t exceed 175 ( i e t h e RPM does n o t f a l l below 1825 RPM). t h i s w i l l n o t n o r m a l l y be d i s c o v e r e d as i t i s t h e usual p r a c t i c e t o stop t h e engine by c u t t i n g o f f t h e f u e l . I n t h e 'OFF' p o s i t i o n b o t h magnetos a r e e a r t h e d and so w i l l produce no spark. I f t h a t magneto m a l f u n c t i o n e d . 8 4) c o n t r o l s b o t h magnetos and i s marked OFF . a d d i t i o n a l l y . t h e engine s h o u l d a g a i n c o n t i n u e t o r u n smoothly and t h e RPM s h o u l d be above 1825. t h e n t h e magneto t h a t has been s w i t c h e d o f f i s permanently l i v e and t h e engine i s i n a dangerous c o n d i t i o n because: 1. . .J{~umzw AVIATION P ~ C PILOTS NOTES FIREFLY T67M200 The magneto s w i t c h ( F i g . I n t h e ' 1 ' p o s i t i o n t h e l e f t magneto alone i s now l i v e and i n t h e 'BOTH' p o s i t i o n . An i n d i v i d u a l check o f t h e performance o f each magneto i s c a r r i e d o u t b e f o r e t a k e o f f i n t h e Engine Run. b u t t h e 'Dead C u t ' check has two purposes as follows: a. It may a l s o happen t h a t one magneto becomes permanently l i v e . P . F o r s t a r t i n g t h e engine. Then t h e l e f t magneto i s s w i t c h e d o f f by s e l e c t i n g R . . F o r t h i s reason a " d e a d / l i v e U magneto check i s c a r r i e d o u t i m m e d i a t e l y a f t e r s t a r t i n g and i m m e d i a t e l y b e f o r e s t o p p i n g t h e e n g i n e .s t a b i l i z e a t 2000-2100 RPM. b o t h magnetos are l i v e The l e f t magneto i s f i t t e d w i t h an impulse and spark r e t a r d d e v i c e which makes t h e engine easy t o s t a r t : t h e d e v i c e o n l y o p e r a t e s a t v e r y l o w RPM and t h u s t h e magneto i s p r o v i d i n g a n o r m a l l y t i m e d spark a t a l l RPM s e t t i n g s available t o the p i l o t . The magnetos should t h e n be s e l e c t e d t o ' B O T H ' ..6--3 J u l y 1988 A5 TP . Should t h e r e be no RPM drop. . 2~ 3 The engine c o u l d n o t be stopped by s w i t c h i n g o f f t h e magnetos (eg f i r e d r i l l ) .BOTH. The magneto s w i t c h i s r e t u r n e d t o 'BOTH' and t h e RPM a l l o w e d t o r e . There i s a r i s k o f t h e engine s t a r t i n g when t h e p r o p e l l e r i s t u r n e d d u r i n g e n g i n e e r i n g work on t h e ground > The magneto performance check i s done b e f o r e each f l i g h t and i s c a r r i e d o u t t h e r i g h t magneto i s t h e n b y s e t t i n g 2000-2100 RPM w i t h 'BOTH' s e l e c t e d . i n t h e 'R' p o s i t i o n t h e r i g h t magneto i s made l i v e w h i l s t t h e l e f t magneto i s e a r t h e d and t h u s t h e r i g h t magneto s h o u l d produce s p a r k s . ( I f the engine i s n o t w i t h i n t h e s e l i m i t s an e n g i n e e r i n g i n v e s t i g a t i o n i s r e q u i r e d ) . To ensure t h a t each magneto can r u n t h e engine.R L . t h e magneto s w i t c h s h o u l d b e s e l e c t e d t o ' L ' and then t o 'BOTH' when t h e e n g i n e f i r e s Prolonged r u n n i n g w i t h one magneto s w i t c h e d o f f w i l l l e a d t o o i l i n g up o f i t s s p a r k i n g p l u g s and a consequently l a r g e magneto "drop" I f one magneto becomes dead d u r i n g e n g i n e o p e r a t i o n .T67M200/FM . The ' h o u r s ' f i g u r e on t h e f a c e o f t h e i n s t r u m e n t assumes a c o n s t a n t RPM and may t h e r e f o r e under. operated b y a push-button on t h e c e n t r e console.1.1.. P T h i s c o n d i t i o n can i n a d v e r t e n t l y be encountered when i n c r e a s i n g or d e c r e a s i n g power s e t t i n g s .6 M a n i f o l d Pressure The m a n i f o l d p r e s s u r e g i v e s t h e o p e r a t o r a d i r e c t i n d i c a t i o n o f how h a r d t h e engine i s w o r k i n g w h i l s t t h e RPM t e l l s him how f a s t t h e engine i s g o i n g round. E l e c t r i c a l power i s a v a i l a b l e t o t h e s t a r t e r t h r o u g h t h e s t a r t e r b u t t o n when t h e master i s s w i t c h e d on.7 It i s Starter The s t a r t e r i s l o c a t e d a t t h e f r o n t o f t h e engine under t h e p r o p e l l e r d r i v e . A s t a r t e r warning l i g h t i l l u m i n a t e s when t h e s t a r t e r i s engaged. any other cause (wrong m i x t u r e s e t t i n g . induction icing. P. t h e engine should n o t be made t o work t o o hard a t l o w RPM.6.PILOTS NOTES FIREFLY l'67M200 A c e r t a i n t y p e o f magneto f a i l u r e can occur where one magneto e i t h e r sparks i n t e r m i t t e n t l y o r sparks w i t h t h e wrong t i m i n g . . T % ~ M ~ O O / F M . i t should l i g h t o n l y w h i l s t t h e s t a r t e r b u t t o n i s pressed and s h o u l d i t f a i l t o go out when t h e b u t t o n i s r e l e a s e d . If t h e m a n i f o l d p r e s s u r e i s t o o h i g h f o r t h e RPM b e i n g used. i t cannot t h e r e f o r e be used t o measure engine o p e r a t i n g time. t h e engine must be stopped immediately o r mechanical damage w i l l ensue. 6. 6. When t h e engine i s r u n n i n g .. so a s i m p l e r u l e t o remenber i s . t h i s can l e a d t o rough I f rough r u n n i n g occurs and cannot be a t t r i b u t e d t o r u n n i n g o f t h e engine. The m a n i f o l d p r e s s u r e gauge shows t h e p r e s s u r e of a i r b e i n g f e d t o t h e c y l i n d e r s and hence. when d e c r e a s i n g power "THROTTLE BACK" f i r s t .1.5 Tachometer --- A d r i v e f r m t h e back o f t h e engine i s t r a n s m i t t e d b y a s l e e v e d c a b l e t o a tachmeter i n the cockpit The f a c e of t h e t a c h m e t e r i s graduated f r o m 0 t o 3500 RPM and i s marked w i t h a r e d l i n e a t t h e l i m i t i n g engine RPM o f 2700 RPM. o i l pressure failure) each magneto can be switched off i n t u r n t o check f o r malfunctioning. t h e higher t h e pressure. As i s t h e case w i t h most p i s t o n engines.. s h o u l d l a n d a t t h e n e a r e s t s a f e l a n d i n g ground as c o n t i n u e d engine o p e r a t i o n now depends on a s i n g l e magneto. Should normal engine r u n n i n g be r e s t o r e d w i t h one magneto s w i t c h o f f t h e a i r c r a f t should n o t t a k e o f f and. The s t a r t e r c i r c u i t i s n o t r o u t e d t h r o u g h t h e ammeter and thus t h e s t a r t i n g c u r r e n t i s n o t shown on t h e ammeter. t h e harder t h e engine i s working.. i f a l r e a d y a i r b o r n e .when i n c r e a s i n g power "REV UP" f i r s t .read a g a i n s t r e a l time. d e t o n a t i o n and engine damage may r e s u l t : t o avoid t h i s c o n d i t i o n the m a n i f o l d p r e s s u r e ( i n inches o f mercury) should never be a l l o w e d t o exceed t h e RPM ( i n hundreds) by more t h a n 4.or over. t h e b u t t o n b e i n g o b s t r u c t e d when t h e f u e l cock i s s e l e c t e d t o 'OFF'. opening t h e t h r o t t l e admits more a i r t o t h e m a n i f o l d and a l l o w s t h e p r e s s u r e t o rise. eg t h e maximum m a n i f o l d p r e s s u r e a l l o w e d a t 2200 R M i s 26 inches o f mercury.4 Au u s t 1985 TP . 6. t h e p r o p e l l e r w i l l be f u l l y f i n e and t h e t h r o t t l e w i l l c o n t r o l t h e RPM. w i l l move t h e p r o p e l l e r t o a lower and lower p i t c h u n t i l i t i s a t minimum p i t c h ( f u l l y fine). I n t h e event o f any damage. opening t h e t h r o t t l e w i 11 i n c r e a s e t h e RPM u n t i l t h e engine i s developing enough power t o d r i v e t h e p r o p e l l e r round a t t h e v a l u e s e t by t h e RPM c o n t r o l . the constant speed u n i t w i l l a t t e m p t t o keep t h e RPM at t h e v a l u e s e t by t h e RPM c o n t r o l and. r e f e r e n c e should be made t o t h e makers handbook which g i v e s d e t a i 1s o f a c c e p t a b l e i m p e r f e c t i o n s . c h i p s or s u r f a c e c r a n ng b e i n g detected. The blades have c o u n t e r . c r a c k s . . . E v e n t u a l l y . as t h e engine slows down. The f u n c t i o n o f t h e constant speed u n i t i s t o vary t h e p i t c h o f t h e pr ope1 l e r b l a d e s t o keep t h e p r o p e l l e r RPM a t t h e value s e l e c t e d by t h e RPM ' c o n t r o l . Conversely. The d e s i r e d RPM i s s e t i n t h e constant speed u n i t by movement of t h e RPM c o n t r o l . t h e blades can o n l y be moved f r c m f u l l y c o a r s e by a p p l y i n g enough p r e s s u r e t o t h e p i s t o n i n t h e hub t o overcome t h e f o r c e generated by t h e counter-. t h e p r o p e l l e r w i l l speed up. The source o f p r e s s u r e i s t h e o i l pump and t h e amount of p r e s s u r e allowed t o go t o t h e p i s t o n i s c o n t r o l l e d by t h e c o n s t a n t speed unit.. Thus. Conversely. t h e constant speed u n i t p r o g r e s s i v e l y reduces t h e p r o p e l l e r p i t c h t o keep t h e s e t RPM. At ground i d l e t h e engine i s not d e v e l o p i n g enough power t o keep t h e RPM above about 800 . The p r o p e l l e r r o t a t e s c l o c k w i s e as seen by t h e p i l o t . once t h e s e t RPM i s reached. t h e blades w i l l develop more l i f t ( t h r u s t ) b u t w i l l a l s o develop more drag. P . I t works on t h e p r i n c i p l e t h a t i f t h e p i t c h o f t h e p r o p e l l e r blades i s increased. t h e u n i t then e i t h e r l e t s o i l i n under p r e s s u r e t o decrease t h e p r o p e l l e r p i t c h or l e t s o i l o u t a l l o w i n g t h e p i t c h t o i n c r e a s e u n t i l t h e s e t RPM i s reached. t h e constant speed u n i t w i l l keep t h e RPM t h e same by c o a r s e n i n g t h e p r o p e l l e r as t h e t h r o t t l e i s opened further.8 P r z l l e r and Constant Speed U nit The p r o p e l l e r i s a Hoffmann 3 b l a d e d v a r i a b l e ..w e i g h t s attached at. The l e a d i n g edges a r e covered w i t h a r e p l a c e a b l e m e t a l s t r i p .PILOTS NOTES FIREFLY T67M200 6.. . t h e u n i t can no longer m a i n t a i n t h e set RPM. b o t h o f which t e n d t o move t h e p r o p e l l e r t o f i n e p i t c h . Thus i t can be seen t h a t .1... The c o n s t a n t speed u n i t can o n l y f u n c t i o n c o r r e c t l y when t h e engine i s d e v e l o p i n g enough power t o t u r n t h e p r o p e l l e r at t h e RPM s e t by t h e RPM c o n t r o l . t h i s i n c r e a s e i n drag w i 11 slow t h e p r o p e l l e r RPM down. t h e p r o p e l l e r i s f u l l y f i n e . i f t h e p i t c h i s decreased. .weights. The p r o p e l l e r hub i s h i d d e n by t h e spinner which i s secured t o t h e p r o p e l l e r back p l a t e b y screws. even a t minimum p i t c h . When t h e t h r o t t l e i s c l o s e d on t h e ground t h e engine develops v e r y l i t t l e power.6-5 August 1985 Tp T67M2001FM .p i t c h p r o p e l l e r . I f t h e RPM then v a r i e s f r o m t h e s e t value t h e c o n s t a n t speed u n i t changes t h e p i t c h u n t i 1 t h e c o r r e c t RPM i s r e g a i n e d . as t h e t h r o t t l e i s p r o g r e s s i v e l y c l o s e d f r cm f u l l y open. once t h e e n g i n e i s r u n n i n g . a t a c e r t a i n t h r o t t l e p o s i t i o n . t h e RPM w i l l t h e n f a l l as t h e t h r o t t l e i s c l o s e d beyond t h i s p o s i t i o n . when t h e p r o p e l l e r i s t u r n i n g t h e s e c o u n t e r w e i g h t s e x e r t a f o r c e on t h e b l a d e s t o make them move t o t h e f u l l y coarse p o s i t i o n . a t low t h r o t t l e s e t t i n g s . t h u s t h e hub cannot be inspected on a d a l l y b a s i s P r o p e l l e r p i t c h i s v a r i e d by t h e movement o f a p i s t o n i n t h e p r o p e l l e r hub: t h i s p i s t o n i s connected t o a l l 3 p r o p e l l e r blades and moves them s i m u l t a n e o u s l y t o vary t h e i r p i t c h f r m low p i t c h ( f u l l y f i n e ) t o h i g h p i t c h ( f u l l y coarse).. t h e i r r o o t s . The c o u n t e r w e i g h t s a r e heavy enough t o overcome t h e s p r i n g f o r c e and t h e n a t u r a l c e n t r i f u a l force. 25% over t h e engine t a k e o f f RPM l i m i t of 2700) t h e p r o p e l l e r must be r e t u r n e d t o t h e manufacturer or a u t h o r i s e d agent f o r i n s p e c t i o n .. The e x a c t overspeed RFM should be noted Above 3375 RPM The p r o p e l l e r should be r e t u r n e d t o t h e manufacturer a u t h o r i s e d a g e n t f o r i n s p e c t l o n and no f e r r y f l l ght should be made.. C r u i s i n g Power During F i r s t 50 hrs Engine L i f e C r u i s i n g s h a r l d be done a t 65% . CAUTi ON - Move p r o p e l l e r speed c o n t r o l smoothly Do not o p e r a t e the c o n t r o l a b r u p t l y . 3105 RPM t p 3375 RPM i f the p r o p e l l e r overspeeds between 3105 RPM and 3375 RPM ( r e p r e s e n t i n q an overspeed of 15% . Rapid movement of c o n t r o l governor s t a b i l i z e s .speed may cause surging or overspeeding u n t i l the < Up t o 3105 RPM i f t h e p r o p e l l e r overspeeds between 2700 PRM and 3/05 RPM ( a n o v e r s p e e d ' o f 0% .9 The d r i l l s f o r the normal use of t h e engine a r e given i n S e c t i o n 3 and in t h e F l i g h t R e f e r e n c e C ~ r d s(FRCs). s U ~ PILOTS NOTES FIREFLY T 6 7 M 2 0 0 i n p r a c t i c e . Normal Use 01 6. 6.6-6 March 1988 A4 T P T67M200lFM .1. T h i s means t h a t l w e r p i t c h change f o r c e s a r e required The p i t c h w i l l change f a s t e r t h a n w i t h m e t a l blades.15% over t h e engine t a k e o f f RPM l i m i t of 2700) a normal propel 1 er p e r i o d i c 100 hour i n s p e c t i o n must be c a r r i e d o u t .10 Malfunctions - T h e m e r g e n c i e s a r e covered i n S e c t i o n 4 and a r e reproduced in t h e emergency check l i s t s ( r e d pages) of t h e FRCs P.75% power u n t i l 50 hrs e n g i n e l i f e has accumulated or o i l consumption has s t a b i l i s e d . I t i s only on when reducing t o low t h r o t t l e s e t t i n g s t h a t t h e power output of t o o low t o a l l o w t h e c o n s t a n t speed u n i t t o work and then contr 01 s t h e RPM. a t normal f l i g h t power s e t t i n g s . The l i m i t a t i o n s a r e given i n S e c t i o n 2 of t h i s manual and c r i t i c a l l i m i t a t i o n s a r e sumnarised i n t h e FRCs. Over . s e t s t h e RPM t h e ground or t h e engine i s the t h r o t t l e > The p i t c h change f o r c e s of Hoffmann c u n p o s i t e blades a r e much lower than t h o s e of m e t a l b l a d e s . t h e RFW c o n t r o l and t h e t h r o t t l e c o n t r o l s t h e manifold p r e s s u r e .1.= ( {AVIATION -!LC ~ ~ ~ . 75 Imp G a l l s ) o f which 78. I n both cases t h e d r a i n i s taken from t h e lowest p o i n t o f t h e tank and t h i s w i l l c o l l e c t any water t h a t may be present i n t h e f u e l from condensation or contamination. Attached t o t h e f u e l feed p i p e i n s i d e t h e tank i s a f l o p tube which i s f i t t e d w i t h a f i l t e r and non-eturn v a l v e assembly. The f u e l c o n t r o l has 3 s e t t i n g s FUEL OFFILEFT TANKIRIGHT TANK.1 General D e s c r i p t i o n Fuel i s contained i n two separate wing tanks. 4 ) when t h e master s w i t c h i s cn i t can be f e d from one o r valve. Each tank c o n t a i n s a f l o a t metering u n i t which s u p p l i e s i n f o r m a t i o n t o t h e e l e c t r i c f u e l contents gauges ( F i g . CAUTION THE SPRING LOADED SCREW WILL REMAIN I N THE UP POSITION I F I T I S INADVERTENTLY TURNED. The f l o p tube i s contained i n a c o l l e c t o r tank.6-7 A p r i l 1998 A8 TP . 6. When s e l e c t i n g l e f t t a n k from t h e o f f p o s i t i o n t h e s p r i n g loaded s e l e c t o r knob w i l l r i d e over t h e s l o p i n g face o f t h e b a l k and w i l l n o t r e q u i r e l i f t i n g . I n o r d e r t o s e l e c t o f f t h e knob must be p u l l e d towards t h e p i l o t and t u r n e d towards t h e o f f p o s i t i o n thus l i f t i n g i t over t h e b a l k . THEREFORE CARE MUST BE TAKEN TO ENSURE THAT THE FUELHAS CEASED TO FLOW AFTER THE SAMPLE HAS BEEN TAKEN. . t h e f u e l cannot be i n a d v e r t e n t l y t u r n e d o f f ' .ensure t h a t .31 Imp G a l l s ) a r e usable. t o t h e engine by pump (EDP).. Both f i l l e r caps i n c o r p o r a t e a p o s i t i v e l o c k and rubber s e a l i n g washer t o prevent f u e l l o s s d u r i n g i n v e r t e d f l i g h t . The tank f i l l e r s a r e l o c a t e d on t h e upper s u r f a c e o f t h e wing 1eading edge. . . o t h e r o f t h e tanks. Fuel f l o w s from t h e tank t o a s e l e c t o r v a l v e c o n t r o l l e d by a f u e l c o n t r o l (Fig.PILOTS NOTES FIREFLY T67M200 6. Vent pipes from each tank a r e l e d separately. Fuel t y p e i s AVGAS 10DLL.2. when s w i t c h i n g from r i g h t t o l e f t tank. The engine i s i n j e c t i o n system which > < Fuel d r a i n s a r e f i t t e d t o both t a n k s . steep t u r n s . The f u e l can be sampled b e f o r e each f l i g h t by pressing up on t h e s p r i n g loaded screw and c o l l e c t i n g t h e f u e l which flows out i n a s u i t a b l e wide necked glass c o n t a i n e r .2 Fuel Tanks The two GRP tanks form i n t e g r a l p a r t s o f each wing inboard l e a d i n g edge structure. 8 . t h i s ensures adequate supply o f f u e l t o t h e engine d u r i n g i n v e r t e d f l i g h t or. T67M2001FM . .8. t o vent from under t h e fuselage inboard o f Rib 1 p o r t and starboard.2. The b r e a t h e r box assembly i n c o r p o r a t e s a f l a p p e r v a l v e t o minimise f u e l l o s s i n i n v e r t e d f l i g h t .2 THE AIRFRAME AND ENGINE FUEL SYSTEM 6. from a b r e a t h e r box assy. Fuel t o t h e engine i s drawn from t h e bottom o f t h e inboard s i d e o f t h e t a n k through a f u e l feed pipe. v i a a L e f t I R i g h t s e l e c t o r means o f an e l e c t r i c pump or an engine d r i v e n equipped w i t h a continuous flow fuel i n c o r p o r a t e s a f u e l pressure sensor. From t h e f u e l c o n t r o l f u e l Passes through a f i l t e r t o an P.7 l i t r e s (17. The c a p a c i t y o f each tank i s 80.7 l i t r e s (17. Post Mod 327 A b a l k i s f i t t e d t o t h e panel t o .4) mounted on t h e c e n t r e lower instrument panel such t h a t t h e s t a r t e r b u t t o n i s o b s t r u c t e d when t h e f u e l i s t u r n e d o f f . . t h e e l e c t r i c pump s h o u l d be s w i t c h e d on and t h e f u e l cock and c o n t e n t s checked. I l l u s t r a t i o n 8.5. . 6. I f t h e f u e l p r e s s u r e gauge reads v e r y l o w t h e l i k e l y r e c t i f i a b l e causes a r e f u e l pump f a i l u r e o r f u e l s u p p l y f a i l u r e . The gauge i s marked i n l i t r e s and I m p e r i a l G a l l o n s .. P o s t Mod 292B f u e l gauges a r e marked i n l i t r e s and US Gals. . The c o n t e n t s m e t e r i n g f l o a t i s l o c a t e d away f r o m t h e f i l l e r neck and t h u s t h e c o n t e n t s gauge may be used t o g i v e an i n d i c a t i o n o f f u e l l e v e l d u r i n g r e f u e l l i n g . P..2. A v e n t f r o m t h e emerges under t h e e n g i n e c o w l i n g f o r w a r d o f t h e nosewheel l e g .4) The f u e l p r e s s u r e gauge i s mounted on t h e l e f t .T67M200/FM . I t i s c a l i b r a t e d f r o m 0-10 p s i The f u e l p r e s s u r e sensor i s mounted on t h e f u e l d i s t r i b u t o r i n l e t so t h a t t h e p r e s s u r e recorded i s t h e same as t h a t being experienced a t t h e i n j e c t o r s . i t i n c o r p o r a t e s a bypass v a l v e so t h a t f u e l can f l o w when e n g i n e i s n o t t u r n i n g o r t h e pump has f a i l e d . each f u l l t a n k c o n t a i n s 78. o i l p r e s s u r e and f u e l p r e s s u r e gauges. I t s u p p l i e s f u e l t o a f u e l d i s t r i b u t o r which d i r e c t s f u e l t o t h e a p p r o p r i a t e c y l i n d e r where i t i s i n j e c t e d d i r e c t 1 y i n t o t h e i n l e t p o r t .3 Fuel Contents Gauqes ( R e f . The r e l a t i o n s h i p between f u e l p r e s s u r e and f u e l f l o w i s g i v e n i n S e c t i o n 6.8. They r e q u i r e e l e c t r i c a l power which i s s u p p l i e d t h r o u g h t h e m a s t e r s w i t c h . Pump o u t p u t i s capable o f s u p p l y i n g f u e l t o t h e e n g i n e a t maximum power w i t h t h e EDP f a i l e d I n c r u i s i n g f l i g h t t h e e l e c t r i c f u e l pump can be s w i t c h e d o f f and f u e l drawn by t h e EDP w i l l be drawn t h r o u g h t h e bypaSs i n c o r p o r a t e d i n t o t h e pump.h a n d i n s t r u m e n t panel on a gauge shared w i t h t h e m a n i f o l d p r e s s u r e i n d i c a t o r . . 6.2. 6.4). i t i s p r o t e c t e d b y a c i r c u i t b r e a k e r l o c a t e d on t h e r i g h t o f t h e i n s t r u m e n t panel. The gauge senses t h e f u e l p r e s s u r e d i r e c t l y t h r o u g h a p i p e and.PILOTS NOTES FIREFLY T67M200 > e l e c t r i c a l l y o p e r a t e d f u e l pump..2.7 l i t r e s ( 1 7 ' 3 1 Imp g a l l s ) useable f u e l . f o r t h i s reason.6-8 A p r i l 1998 A8 TP . They a r e p r o t e c t e d by a c i r c u i t b r e a k e r which a l s o c o n t r o l s t h e e l e c t r i c a l s u p p l y t o t h e o i l temperature. I n t h e event o f e n g i n e m a l f u n c t i o n a check o f t h e gauge p r e s s u r e w i l l c o n f i r m whether t h e problem i s caused by a f u e l s u p p l y problem.4) the the EDP The < The f u e l gauges a r e mounted a t t h e t o p o f t h e i n s t r u m e n t p a n e l .4 Fuel P r e s s u r e Gauqe (Ref I l l u s t r a t i o n 8. The f u e l p r e s s u r e s u p p l i e d t o t h e d i s t r i b u t o r i s c o n t r o l l e d by t h e f u e l c o n t r o l u n i t which responds t o t h r o t t l e demands~ The amount o f f u e l f e d t o t h e e n g i n e i s d i r e c t l y p r o p o r t i o n a l t o t h e f u e l p r e s s u r e and t h u s t h e f u e l p r e s s u r e gauge may b e expected t o read h i g h when t h e t h r o t t l e i s open and l o w when t h e t h r o t t l e i s c l o s e d : i t s h o u l d n e v e r read z e r o when t h e e n g i n e i s r u n n i n g . The EDP i s mounted c e n t r a l l y a t t h e back o f t h e engine f o r w a r d o f f i r e w a l l ..5 Fuel C o n t r o l U n i t The f u e l c o n t r o l u n i t t a k e s t h e p l a c e o f t h e c a r b u r e t t o r .. mounted on t h e lower c e n t r e console.2. a r e s t r i c t o r i s p u t i n t h e p r e s s u r e l i n e t o t h e gauge so t h a t f u e l i s n o t pumped i n t o t h e c o c k p i t i f t h e p i p e breaks. The pump i s c o n t r o l l e d by a FUEL PUMP ON/OFF SWITCH (Fig. p i l o t has no c o n t r o l s f o r t h e EDP. PILOTS NOTES FIREFLY T67MZ00 PRE MOD 3 0 0 A ! FUEL RIGHT TANK I STARTER 6I I LEFT TANK POST . MOD 3 0 0 A . RIGti'T 'TANK FUEL. . < STARTER LEFT TANK FUEL SELECTOR CONTROL LABELS WITHOUT BALK P6-8A A p r i l 1998 A8 TP .T67M200/FM SUN^^^^ A\fIATION LTD PILOTS NOTES FIREFLY T67M200 PRE MOD 336 1 FOR FUEL O F F PULL ANDTURN 1 7 R1GH.T I POST' MOD 336 TANK TANK PULL AND TURN OFF I FUEL SELECTOR CONTROL LABELS WITH BALK I P6-8B A p r i 1 1998 A8 TP .T67M200/FM J{S.INGSBYLTo a\llnTioN PILOTS NOTES FIREFLY T67M200 The f u e l c o n t r o l u n i t senses t h e a i r f l o w through t h e m a n i f o l d i n t o t h e engine and provides t h e appropriate amount o f f u e l t o g i v e t h e c o r r e c t a i r / f u e l mixture. I t a c t u a l l y achieve t h i s by v a r y i n g t h e f u e l pressure; t h i s changes t h e f u e l f l o w and gives t h e c o r r e c t m i x t u r e . Opening t h e t h r o t t l e w i l l increase t h e a i r f l o w i n t h e m a n i f o l d and t h e f u e l c o n t r o l u n i t schedules a higher f u e l flow. A t a l t i t u d e the' r e d u c t i o n i n d e n s i t y r e s u l t s i n a lower m a n i f o l d a i r f l o w being sensed b y t h e u n i t which a u t o m a t i c a l l y schedules a lower f u e l flow, a v o i d i n g an o v e r - r i c h m i x t u r e . The f u e l c o n t r o l u n i t i s s e t t o p r o v i d e a maximum power ( r i c h ) f u e l l a i r m i x t u r e throughout t h e o p e r a t i n g range but weakening t h e m i x t u r e t o economy c r u i s e s e t t i n g s can be achieved by use o f the mixture control. The f u e l c o n t r o l u n i t depends on t h e supply o f f u e l under pressure t o f u n c t i o n c o r r e c t l y and f a i l u r e o f t h e pressure supply w i l l r e s u l t i n power f a i l u r e . Both t h e engine d r i v e n f u e l pump and t h e e l e c t r i c f u e l pump can i n d i v i d u a l l y p r o v i d e s u f f i c i e n t pressure f o r c o r r e c t f u e l supply. Under normal circumstances only t h e engine d r i v e n pump i s used. A f a i l u r e o f t h i s pump w i l l r e s u l t i n power l o s s and low o r zero f u e l pressure; normal engine performance can be r e s t o r e d by use o f t h e e l e c t r i c f u e l pump. A f a i l u r e i n t h e f u e l c o n t r o l u n i t or impact i c i n g on t h e t h r o t t l e o r a i r pressure sensing pipes w i l l cause reduced f u e l or a i r f l o w and w i l l l e a d t o l o s s o f power: i c i n g c o n d i t i o n s must be avoided as t h e r e i s no p r o v i s i o n f o r m a n i f o l d o r t h r o t t l e i c e clearance. 6.2.6 Fuel D i s t r i b u t o r (Ref I l l u s t r a t i o n 8.4) The f u e l d i s t r i b u t o r i s downstream o f t h e f u e l c o n t r o l u n i t and d i r e c t s f u e l t o t h e i n l e t p o r t o f each c y l i n d e r i n t u r n as they commence t h e i r i n d u c t i o n s t r o k e . There are no p i l o t c o n t r o l s o r i n d i c a t o r s b u t t h e f u e l pressure experienced a t t h e i n d i c a t o r i s shown on t h e f u e l pressure gauge i n t h e c o c k p i t . 6.2.7 T h r o t t l e (Ref I l l u s t r a t i o n 8.4) A t h r o t t l e i s provided f o r left-handed use by each p i l o t . The l e f t - h a n d t h r o t t l e i s o f t h e l e v e r type and i s l o c a t e d on t h e l e f t c o c k p i t w a l l , i n c o r p o r a t i n g a s p i n d l e f r i c t i o n damper. The r i g h t - h a n d t h r o t t l e (Item 6 F i g 8.4) i s on t h e c e n t r e lower. instrument panel and i s o f t h e p l u n g e r type.. The two t h r o t t l e s are ganged t o g e t h e r and thus operate simultaneous1 y.. The t h r o t t l e i s f u l l y open when t h e c o n t r o l s a r e f u l l y forward. 6.2.8 Fuel M i x t u r e / C u t o f f Control (Ref I l l u s t r a t i o n 8.4) The m i x t u r e / c u t o f f c o n t r o l i s s i t u a t e d on t h e c e n t r e lower console and i s of t h e p l u n g e r type.. The m i x t u r e i s f u l l y r i c h when t h e c o n t r o l i s f u l l y forward and p r o g r e s s i v e l y weakens as t h e c o n t r o l i s p u l l e d back: t h e f u e l i s completely c u t o f f when t h e c o n t r o l i s f u l l y back. 'The c o n t r o l i s o f t h e v e r n i e r type and incorporates a c e n t r a l push b u t t o n t o r e l e a s e t h e v e r n i e r . . An a d j u s t a b l e f r i c t i o n d e v i c e i s a l s o provided which t u r n s c l o c k w i s e t o increase f r i c t i o n . The f r i c t i o n c o n t r o l should always be s e t t i g h t as v i b r a t i o n may otherwise cause t h e s e t t i n g t o ' creep ' .. P .6-9 A p r i l 1998 A8 TP .,T67M200/FM J{SLINGSBY A\tlArIoN LTo PILOTS NOTES FIREFLY T67M200 For t a k e o f f . induction icing) immediately s e l e c t the mixture t o f u l l y rich in case incorrect mixture was t h e cause of the t r o u b l e . Should the engine ever seem t o be suffering from power loss with no other symptoms (eg mechanical noise.6-10 April 1998 A 8 < . check fuel gauge indicators. a t power s e t t i n g s of not above 75%.2. Periodically monitor fuel gauge indicators. Weakening beyond t h i s point will cause rough running and may lead t o RPM surging as the constant speed unit attempts t o maintain RPM under conditions of fluctuating power. speed and a l t i t u d e and will need r e s e t t i n g i f any of these conditions change.. T . Fuel asymmetry before commencing aerobatics and spinning manoeuvres should not exceed 14 l i t r e s ( 3 Imp G a l l s ) .4C). both tanks. For ease of reference the adjustable pointer may be pre-set t o peak EGT CAUTIONS (1) (2) ENGINE DAMAGE MAY BE C U E BY M X U LEANING AT HIGHER A SD AI M M THAN RECOMMENDED CRUISE POWER SETTINGS. Once the master switch 1s on. G . After take off switch off booster pump > Durinq Fliqht Switch ON e l e c t r i c fuel pump f o r takeoff. During f l i g h t i n c r u i s e conditions. I n the cruise i t may be weakened t o reduce fuel pressure t o t h e value derived from t h e performance graph a t Section 5. o i l system malfunction.. Switch from one tank t o the other from time t o time during long f l i g h t s t o maintain the balance of fuel in t h e tanks.8A Exhaust Gas Temperature (EGT) Gauqe (Mod 313) An E . gauge i s mounted a t the bottom right-hand s i d e of t h e instrument panel (Fig. The e f f e c t of assymmetry of fuel greater than 14 l i t r e s will not hazard t h e a i r c r a f t b u t does lead t o s l i g h t increase in control s t i c k aileron forces and l e s s precise aerobatic manoeuvres. Sample fuel f o r a contamination check i f required ( F i r s t f l i g h t of each day). 8. 6. 6. the mixture can be leaned until the needle of t h e EGT gauge j u s t peaks.2. temperature. The mixture should always be s e t f u l l y rich before changing a n y t h r o t t l e s e t t i n g or commencing any climb o r descent. THE E N G I N E M S NOT BE OPERATED AT ANY TIME ON THE LEAN UT SIDE OF PEAK EGT. climb and a t low levels AMSL f u l l y rich should always be selected and locked. leave fuel on and carry out engine s t a r t i n g d r i l l . Switch off e l e c t r i c fuel pump f o r cruise unless engine driven fump f a i l s . t h i s stops lubricating o i l being washed from t h e cylinder walls and minimises the chance of the engine f i r i n g i f the propeller i s turned. The engine should normally be stopped on t h e ground by s e t t i n g t h e mixture t o cutoff so t h a t fuel i s n o t i e f t in the cylinders a f t e r t h e engine has stopped. This s e t t i n g i s the recommended lean mixture position. A probe placed i n t o the exhaust pipe operates the gauge without need for any additional power supply. P. This fuel pressure s e t t i n g gives the mixture which i s the most e f f i c i e n t f o r that p a r t i c u l a r RPM.9 Normal Use Before Fliqht Ensure t h a t there i s s u f f i c i e n t fuel f o r the f l i g h t and t h a t t h e fuel caps a r e both secure Check t h a t both vent pipes a r e c l e a r . 11 Fuel System Diaqram FUEL QUANTITY INDICATORS FLOP TUBE WITH FILTER AND NON-RETURN VALE -VENT PIPES MIXTURE CONTROL FUEL CONTROL UNIT (below the engine) 7 HROTTLE CONTROL FUEL FUEL PRESSURE INDICATOR FUEL DISTRIBUTOR (top of the engine) ELECTRICAL MECHANICAL FUEL PRESSURE -' -' -- P.10 Malfunctioninq These a r e covered i n Section 4 and i n t h e FRCs .. -- 6.2. i t i s advisable t o s e l e c t one tank u n t i l t h e engine begins t o f a l t e r and then s w i t c h t o t h e o t h e r t a n k c o n t a i n i n g t h e remaining f u e l .r e d s e c t i o n .PILOTS NOTES FIREFLY T67M200 Switch on e l e c t r i c f u e l pump when beginning a l a n d i n g approach. Should a low f u e l s i t u a t i o n a r i s e .6-11 A p r i l 1998 A8 .2. 6. 1 General D e s c r i p t i o n -. I t can s u p p l y a l l e l e c t r i c a l s e r v i c e s b u t demands on i t s h o u l d b e k e p t t o a p r a c t i c a b l e minimum u n t i l a l t e r n a t o r o u t p u t i s a v a i l a b l e . The a l t e r n a t o r i s capable o f f u l l o u t p u t a t grourrd i d l e RPM (700 RPM) and w i l l t h u s r e t a i n o u t p u t a t w i n d m i l l RPM (800 RPM) a t g l i d i n g speed f o l l o w i n g an e n g i n e f a i l u r e . i t w i l l n o t produce any o u t p u t when t h e p r o p e l l e r has s t o p p e d . A b a t t e r y p r o v i d e s 24V D f o r a l l e l e c t r i c a l s e r v i c e s . An e n g i n e . t h e master must n e v e r be s w i t c h e d o f f when t h e a l t e r n a t o r i s on and t h e engine r u n n i n g . r a t e d a t 5 amps. p r o t e c t s t h e main a l t e r n a t o r o u t p u t .3.4) i n d i c a t e s t h e r a t e o f b a t t e r y charge o r d i s c h a r g e and s h o u l d b e c a r e f u l l y m o n i t o r e d when t h e a l t e r n a t o r i s s w i t c h e d on.3 THE ELECTRICAL SYSTEM 6.and u n d e r . t h i s w i l l r e t a i n b a t t e r y c a p a c i t y f o r s t a r t i n g t h e engine and f o r u s e i n t h e a i r should t h e a l t e r n a t o r f a i l b e f o r e i t has f u l l y charged t h e b a t t e r y .PILOTS NOTES FIREFLY T67M200 6. Over.. No e l e c t r i c a l s e r v i c e s except t h e c l o c k w i l l o p e r a t e u n t i l t h e master s w i t c h i s o n .4) i n d i c a t e s t h e r a t e o f b a t t e r y charge o r d i s c h a r g e . An ammeter ( F i g .d r i v e n a l t e r n a t o r charges t h e b a t t e r y . 6. 8 . p r o t e c t s t h e e x c i t a t i o n c i r c u i t and t h e o t h e r . 4 ) . 8. The a l t e r n a t o r s h o u l d b e s w i t c h e d on once t h e e n g i n e i s r u n n i n g and s h o u l d b e s w i t c h e d o f f b e f o r e t h e e n g i n e has been s h u t down. The a l t e r n a t o r r e q u i r e s an e x c i t a t i o n c u r r e n t t o b e a p p l i e d t o i t s f i e l d c o i l s b e f o r e i t w i l l s t a r t d e l i v e r i n g c u r r e n t even though i t i s b e i n g t u r n e d by t h e engine. The ammeter ( F i g 8. Once t h e e n g i n e i s running.T67M200/FM < > < . r a t e d a t 60 amps. Two c i r c u i t b r e a k e r s p r o t e c t t h e a l t e r n a t o r . A l l c i r c u i t s a r e p r o t e c t e d by c i r c u i t b r e a k e r s which a r e a c c e s s i b l e t o t h e p i l o t i n f l i g h t . t h r o u g h t h e e x c i t a t i o n s w i t c h ( F i g 8 . The charge r a t e w i l l s t e a d i l y f a l l f r o m about +10 t o +2 amps as t h e b a t t e r y becomes f u l l y charged. t h e a l t e r n a t o r may be s w i t c h e d on t o charge t h e b a t t e r y . t h e ammeter s h o u l d i m m e d i a t e l y be expected t o i n d i c a t e about 120 amps b u t s h o u l d f a l l t o no more t h a n +10 amps a f t e r about 60 seconds o r t h e b a t t e r y i s l i k e l y t o ' b o i l 1 and s p i l l a c i d .6-12 March 1988 A4 TP. No emergency b a t t e r y i s f i t t e d . a r e d warning l i g h t marked ALT ( F i g 8. Any equipment C r e q u i r i n g AC i n c o r p o r a t e s i t s own s o l i d s t a t e i n v e r t e r t h u s e l i m i n a t i n g t h e need f o r any s e p a r a t e AC d i s t r i b u t i o n system.2 B a t t e r y The 24 v o l t b a t t e r y r a t e d a t 15 ampere hours i s l o c a t e d i n t h e luggage compartment. . t h i s c u r r e n t i s s u p p l i e d f r o m t h e busbar.3 Alternator > < > < 5 The 24 v o l t 70 amp P r e s t o l i t e a l t e r n a t o r i s d r i v e n by a f r i c t i o n b e l t f r o m a p u l l e y on t h e p r o p e l l e r d r i v e s h a f t . The f l a s h i n g can b e stopped b y p r e s s i n g t h e w a r n i n g b u t t o n f o r more t h a n h a l f a second which w i l l cause t h e l i g h t t o r e v e r t t o steady r e d . as a l t e r n a t o r damage may o c c u r . . 6. P.3. 4 ) .v o l t a g e c o n t r o l boxes a r e mounted on t h e main e l e c t r i c a l panel b u t no c o n t r o l s o r i n d i c a t o r s a r e available t o the p i l o t . one.3.4) f l a s h e s whenever t h e master i s on and t h e a l t e r n a t o r i s n o t g i v i n g any o u t p u t . The b a t t e r y i s connected t o t h e DC busbar by a b a t t e r y r e l a y which i s o p e r a t e d by t h e m a s t e r s w i t c h ( F i g . Same c i r c u i t b r e a k e r s s e r v e more t h a n one c i r c u i t b u t t h i s i s n o t always i n d i c a t e d on t h e panel. D e t a i l s o f a l l c i r c u i t breakers. A l t e r n a t o r f a i l u r e w i l l be i n d i c a t e d by t h e ALT l i g h t f l a s h i n g and t h e ammeter i n d i c a t i n g a d i s c h a r g e .4 C i r c u i t Breakers (Ref I l l u s t r a t i o n s 6.6-. The a l t e r n a t o r e x c i t a t i o n s h o u l d be s w i t c h e d o f f and t h e c i r c u i t breakers checked and r e s e t i f necessary.9) < The c i r c u i t b r e a k e r s a r e a l l a c c e s s i b l e t o t h e p i l o t i n f l i g h t . i f t h e c i r c u i t b r e a k e r t r i p s a second t i m e t h e c i r c u i t s h o u l d be s w i t c h e d o f f and no f u r t h e r attempt made t o r e s e t i t . . t h e c i r c u i t b r e a k e r s h o u l d be a l l o w e d t o c o o l f o r a b o u t 30 seconds and t h e n i t may be r e s e t . CIRCUIT BREAKER SET CIRCUIT BREAKER TRIPPED > I f a c i r c u i t b r e a k e r t r i p s . 3 .3. < P. They may be r e s e t by p u s h i n g t h e head back t o t h e ' s e t ' p o s i t i o n .3.3. t h e c i r c u i t which i t was p r o t e c t i n g may be s w i t c h e d on again. t h e i r l o a d i n g s and t h e c i r c u i t s p r o t e c t e d by them a r e g i v e n on t h e diagram o f t h e e l e c t r i c a l system i n t h i s c h a p t e r a t 6 . 'The c i r c u i t b r e a k e r s may be t r i p p e d by t h e p i l o t by p u l l i n g out t h e head o f t h e c i r c u i t b r e a k e r u n t i l t h e w h i t e p o r t i o n i s v i s i b l e . 7 . Once a c i r c u i t b r e a k e r has been r e s e t . > 6.i n c h f r o m t h e panel and a w h i t e p o r t i o n on i t s stem i s c l e a r l y v i s i b l e .13 March 1988 A4 TP .~ { s &\JIATION LTO * W L . Under no c i r c u m s t a n c e s s h o u l d a c i r c u i t b r e a k e r ever b e h e l d p r e s s e d i n as t h i s can r e s u l t i n an e l e c t r i c a l f i r e . The ampere r a t i n g s a r e stamped on t h e head o f each o n e . ~ ~ PILOTS NOTES FIREFLY T67MZOO WARNING The m a s t e r s w i t c h s h o u l d n o t be s w i t c h e d o f f when t h e a l t e r n a t o r i s switched on w i t h t h e e n g i n e r u n n i n g as t h i s may r e s u l t i n damage t o t h e a l t e r n a t o r c o n t r o l components.8 and 6.T67M200/FM . t h e a l t e r n a t o r may t h e n be switched on b u t i f a c i r c u i t b i e a k e r t r i p s a g a i n t h e a l t e r n a t o r s h o u l d be switched o f f and t h e f a u l t i n v e s t i g a t e d on t h e g r o u n d . When a c i r c u i t b r e a k e r t r i p s i t p r o t r u d e s about h a l f . t h e c i r c u i t which i t i s p r o t e c t i n g s h o u l d b e s w i t c h e d o f f ( i f t h e r e i s a s w i t c h ) b e f o r e any a t t e m p t i s made t o r e s e t t h e c i r c u i t breaker. T67M200/FM . h o r i z o n (MOD 312) The p o r t e l e c t r i c a l a r t i f i c i a l horizon.3. 6. P. Ourinq f l i q h t : as r e q u i r e d .PILOTS NOTES FIREFLY T67M200 6. WITHOUT E N G I N E RUNNING. F l a t b a t t e r y : Should t h e engine i t w i l l be s e r v i c e a b l e one.4C). Mod socket f i t t e d t o p o r t C i r c u i t breaker t r i p : t h e r e be too l i t t l e power i n t h e b a t t e r y t o s t a r t necessary t o have t h e b a t t e r y changed o r t o f i t a 314 makes p r o v i s i o n f o r an e x t e r n a l power supply s i d e o f centre f u s e l a g e .6-14 A p r i l 1998 A8 TP . M o n i t o r t h e charge r a t e p e r i o d i c a l l y .3.6 Malfunctioning Alternator failure: F a i l u r e w i l l be i n d i c a t e d by t h e r e d ALT warning ( F i g 8.3. i s provided w i t h an emergency back-up b a t t e r y which i s c o n t r o l l e d by a guarded s w i t c h mounted on t h e instrument panel ( F i g 8. S e l e c t s e r v i c e s After fliqht: Switch o f f t h e a l t e r n a t o r b e f o r e engine shutdown and s w i t c h o f f t h e master once t h e engine has stopped.4) indicating a discharge. ON Before F l i g h t Ensure t h a t t h e emergency s w i t c h i s i n t h e D W p o s i t i o n and t h a t t h e 10A (emergency b a t t e r y supply) c i r c u i t breaker i s i n t h e s e t (pushed i n ) p o s i t i o n . Use o f Avionics: Avionics should o n l y be switched on and o f f w h i l s t t h e a l t e r n a t o r i s running t o p r o t e c t them from t r a n s i e n t v o l t a g e fluctuations. S e l e c t t h e master s w i t c h on before s t a r t i n g t h e engine and leave i t on u n t i l t h e engine has been shut down. 6.4) i l l u m i n a t i n g and the ammeter ( F i g 8.. See 6 . Once t h e engine i s running s e l e c t t h e a l t e r n a t o r e x c i t a t i o n switch t o ON and monitor t h e ammeter readings t o ensure t h a t t h e i n i t i a l charge r a t e o f about 20 amps f a l l s t o 10 amps i n 60 seconds and about 2 amps i n 5 minutes.5 Normal Use o f t h e System Before f l i q h t : Check e l e c t r i c a l services as d e t a i l e d i n t h e FRCs. CAUTION I F A V I O N I C GROUND CHECKS ARE REOUIRED. S e l e c t s e r v i c e s as required. DO NOT OPERATE MASTER OR STARTER SWITCHES WHILST RADIOS ARE TURNED ON. where f i t t e d . The d r i l l f o r attempting t o r e s t o r e a l t e r n a t o r output i s given i n t h e FRC. 4 i n t h i s chapter.5A Emerqency backup b a t t e r y f o r p o r t e l e c t r i c a l a r t . 3 . . CIRCUIT BREAKERS SHOWING LOADING 1 P. 0. .6--15 December 1988 A6 TP T6'7M200/FM ..3.--- .7 The Electrical Circuit Diagram EXTERM POWER SUPPLY SOCKET PORT NIIYI ITROBE I DETAIL ' A COMBINED NILVISTROBE WWG TIPLIGHIS MOO 297 i CO-ORDINATOR AllERNATOR WARNING LlGHT LOW VOLTAGE WARNING-SENSOR CO-ORDINATOR .s - SWITCHES UNDER CONTROL p .1 . .PILOTS NOTES FIREFLY T67M200 6. U 6 . PORT ART HORIZON (Mod 311) . P . HORIZON '-.\ A TAXI1 POS ?or.8 C i r c u i t Breaker L a y o u t (Basic A/C) > 'URUCO (?J@GQ@OQQ@ (MOD 3471 5 n i l i e i l I U T LTS luau c . 3 9 C i r c u i t Breaker L a y o u t (Mod 2 9 3 ) ~"(YIONICS I T A A 7 r A iNSTLrs "A" LT L O *CON PUYW SIlll P.PILOTS NOTES FIREFLY T67M200 6.3. lt. 11R08E @@@ (Mod 2971 -. -. "W LT RIM?/ Eilll PITO. COMBINED NAV I S T R O B E LIGHTS EXCJ" .O.."ST B L I M A P L.6-16 December 1988 A6 TP T67M200/FM .*.. r . . 9 - C i y c u i t Breaker L a y o u t (Mod 293) "NLT LO1 KY O NYPl STALL PRO.8 C i r c u i t Breaker.' \ -- (Post Mod 403) L J P. HT ALT WARN1 .3. (Post Mod 403) TAXI1 POS em* un mr u*s rr i ~ u LT o ! : 6. L a y o u t ( B a s i c A/C) ALT WARN1 PORT TURN CO ..3.T67M200/FM .6-16A A p r i l 1990 A7 TP ..PILOTS N O T E S FIREFLY T 6 7 M 2 0 0 6. IH P.6-168 April 1998 A 8 TP .T67M200/FM . The port a r t i f i c i a l horizon i s then supplied from a separate emergency back-up battery.10 Circuit Breaker Layout (POST MOD 402) AVIONICS INSTIMAP STALL POS FUEL NAY L T STROBE PUMP PITOT HT INST ALT POS STROBE 4 3 (Mod 297) COMBINED NAVISTROBE LIGHTS ! : Durinq Flight If t h e low volts warning l i g h t (marked ALT) remains O n f o r more than 5 min o r the warning flag of the port a r t i f i c i a l horizon appears s e l e c t UP position on the guarded switch.3. After Flight Before leaving a i r c r a f t turn a r t i f i c i a l horizon emergency back-up battery switch back t o DOWN position or BATTERY WILL DISCHARGE E V E N WT MASTER SWITCH OFF.. This will give a t l e a s t half-hour of operation.PILOTS NOTES FIREFLY T67M200 6. Land as soon as possible. Therefore t h e removal o f t h e magneto k e y and l o c k i n g o f t h e canopy w i l l t o t a l l y i m m o b i l i s e the aircraft.T67M200/FM < . It f u l l y down when t h e t h a t personnel w i l l 6. < > (POST MOD 129) The canopy l a t c h mechanjsm i n c o r p o r a t e s a k e y o p e r a t e d l o c k . The r e a r o f t h e canopy i s l o c k e d t o t h e a i r c r a f t b y a r u n n e r w h i c h can move f o r e and a f t i n a t r a c k b u t P.o p e r a t e d l o c k t o p r e v e n t u n a u t h o r i s e d access t o the aircraft.s removal w i t h one hand.4.4.6-17 March 1987 A1 TP. t h e t r i g g e r on t h e head o f t h e b o t t l e . t h e e n g i n e cannot b e s t a r t e d w ~ t h o u t a key t o s w i t c h on t h e magnetos and t h u s t h i s k e y s h o u l d be removed i f i t i s f e l t necessary t o immobilise the a i r c r a f t . t h e two p a r t s f o r m i n g t h e canopy assembly. The a r e a s o u t b o a r d and i n f r o n t o f t h e walkway a r e t h e f l a p and w i n g upper s u r f a c e and t h e l e a d l n g edge. 6.1 GENERAL EQUIPMENT S a f e t y Equipment The s a f e t y equipment f i t t e d i n t h e a i r c r a f t i s a f i r e e x t i n g u i s h e r . ? l s o t h e e n g i n e cannot b e s t a r t e d w i t h o u t a key t o s w i t c h on t h e magnetos. The e x t i n g u i s h e r i s mounted on t h e back w a l l o f t h e c o c k p i t i n a c l i p t h a t p r e v e n t s i n a d v e r t e n t o p e r a t i o n The e x t i n g u i s h e r i s o p e r a t e d b y squeezing b u t a11oiv. The f i r s t a i d k i t i s stowed on t h e back o f t h e b u l k h e a d b e h i n d t h e p i l o t s s e a t s and t h e axe i s mounted on t h e back w a l l beside the f i r e extinguisher. T h e r e i s no p r o v i s i o n f o r jettison. t h e s e areas a r e n o t s t r e s s e d f o r w a l k i n g on and c a r e must b e t a k e n when g e t t i n g i n and o u t o f t h e c o c k p i t t o see t h a t t h e y a r e n o t damaged. I t opens b y h i n g e i n g upwards and r e a r w a r d s t o a l l o w access t o t h e c o c k p i t and can be l o c k e d and u n l o c k e d i n t h e c l o s e d p o s i t i o n f r a n b o t h i n s i d e and o u t s i d e t h e c o c k p i t .PILOTS NOTES FIREFLY T67M200 6. 6.4.2 Access t o t h e C o c k p i t Access t o t h e c o c k p i t i s b y a walkway on each wing. 1s a s e n s i b l e p r e c a u t i o n t o leave t h e f l a p s a t a i r c r a f t i s n o t i n use t o make i t l e s s l i k e l y I n a d v e r t e n t 1 y t r e a d on them.3 Aircraft Security > (PRE MOD 129) T h e r e i s no p r o v i s i o n f o r a k e y .4 Canopy < > (PRE MOO 129) The one-piece per spex t r a n s p a r e n c y p r o v i d e s e x c e l 1e n t a1 1-round v i s i o n . The f i r e e x t i n g u i s h e r i s f i l l e d w i t h BCF and i t s u s e s h o u l d b e m i n i m i s e d i n a c o n f i n e d space.4. There i s no p r o v i s i o n f o r engine f i r e w a r n i n g or e x t i n c t i o n .4 6. and when combined w i t h t h e l o w wing m o u n t i n g g i v e s an u n u s u a l l y good f i e l d o f view f o r b o t h p i l o t s .s l i p material. The walkways go frwn t h e t r a i l i n g edge t o l e v e l w i t h t h e c o c k p i t and a r e s u r f a c e d w i t h n o n . The p e r s p e x b u b b l e t r a n s p a r e n c y i s screwed t o a r o u g h l y o v a l frame. a f i r s t a i d k i t and a c r a s h axe. When the c o n t r o l s are i n t h e unlocked p o s i t i o n the hooks are s t i l l i n a p o s i t i o n t o engage on t h e canopy l o c k b a r and t h e c o n t r o l s have t o be moved f u r t h e r i n the unlocked d i r e c t i o n . moving simul taneousl y . > Opening t h e Canopy Operate the c o n t r o l . The o t h e r c o n t r o l i s positionec c e n t r a l l y on t h e fuselage immediately i n f r o n t o f t h e can0p.y s e a l s the c o c k p i t from a i r b l a s t and noise. ~~ -~ March 1988 A4 TP .a n d . Hinged f r e s h a i r vents are b u i l t i n t o the s l i d i n g panels The canopy i s stopped from s l i d i n g too f a r rearwards by a stop i n the t r a c k o f the r e a r attachment p o i n t . t h i s a c t i o n p u l l s t h e canopy down hard on the foam s t r i p round the c o c k p i t edge and effective1.y i s locked by two hooks which engage on a b a r attached € E ' T F T r o n t r a i l o f the canopy. h o l d i n g t h e c o n t r o l i n t h i s p o s i t i o n . These hooks are then p u l l e d down and locked by an over-centre l o c k mechanism. both s i d e s . Canopy Lock The can0p. One c o n t r o l i s p o s i t i o n e d a t t h e c e n t r e top o f the i n s t r u m e n t panel and i s o f t h e plunger type. i t i s a r o t a r y c o n t r o l p o i n t i n g f o r e .. i t should always be moved i n a c o n t r o l l e d manner and never slammed open o r s h u t . . The canopy i s f i t t e d w i t h s l i d i n g c l e a r .. The canopy may now be r a i s e d f u l l y . . t o move t h e hooks o u t o f t h e way t o a l l o w the canopy t o open o r c l o s e . r a i s e the canopy about 3 inches and then r e l e a s e the c o n t r o l .T67M200/FM .y.a f t when locked and p o i n t i n g across t h e a i r c r a f t when unlocked. the f r o n t o f the canopy l i f t s up. i n t h e < u n l o c k e d a n d then p u l l or t u r n i t as f a r as i t w i l l go a g a i n s t t h e a c t i o n o f a s p r i n g .. The canopy should n o t be l e f t i n an i n t e r m e d i a t e p o s i t i o n as t h e r e i s t h e r i s k o f i t f a l l i n g shut and causing damage o r i n j u r y . e x t e r n a l o r i n t e r n a l .PILOTS NOTES FIREFLY T67M200 cannot l i f t up. The a c t i o n o f p u l l i n g and l o c k i n g t h e hooks i s achieved by o p e r a t i n g one o f the two canopy c o n t r o l s . The two c o n t r o l s are ganged t o g e t h e r . when f u l l y f o r w a r d i t i s i n the locked p o s i t i o n . When opening.v i e w panels. hingeing on two r a d i u s rods attached t o the c o c k p i t edge and canopy frame. against the a c t i o n o f a spring.. . PILOTS NOTES FIREFLY T67M200 Clo n -sii n g pull g t h e Canopy B e i n g p r e p a r e d t o t a k e t h e w e i g h t of t h e canopy, s t a r t t h e canopy f o r w a r d and t h e n l w e r i t u n t i l i t has about 3 i n c h e s l e f t t o go., Operate t h e c o n t r o l ( i n t e r n a l or e x t e r n a l ) f u l l y i n t h e unlocked p o s i t i o n a g a i n s t t h e a c t i o n o f a s p r i n g , lcwer t h e canopy f u l l y and r e l e a s e the control. Ensure t h a t t h e l o c a t i n g clamps a t e i t h e r s i d e of t h e canopy are p r o p e r l y p o s i t i o n e d and t h a t t h e canopy i s c e n t r a l and t h e n check t h a t Using v e r y f i n pressure, b o t h hooks have engaged on t h e l o c k i n g bar o p e r a t e e i t h e r c o n t r o l i n t h e l o c k i n g d i r e c t i o i i u n t i l i t reaches t h e locked position. . WARNING It i s p o s s i b l e t o move t h e c o n t r 01s t o t h e l o c k e d p o s i t i o n w i t h o u t t h e hooks b e i n g engaged on t h e bar - THE CANOPY I S THEN NOT LOCKED - i t i s a b s o l u t e l y v i t a l t o check t h a t t h e hooks a r e b o t h engaged on t h e l o c k i n g bar A D t h e c o n t r o l i s N i n t h e l o c k e d p o s i t i o n b e f o r e t h e canopy can be declared l o c k e d . < Normal Use of t h e L a n o u B e f o r e each f l i g h t t h e canopy should be c a r e f u l l y i n s p e c t e d f o r damage and cracks, p a r t i c u l a r l y r o u n d t h e screw h o l e s where t h e transparency i s attached t o t h e frame. The canopy should be c l o s e d and l o c k e d b e f o r e t h e engine i s s t a r t e d . To check t h a t t h e canopy i s l o c k e d , 6 p o i n t s must be checked: B o t h L o c a t i n g clanps c o r r e c t l y engaged, Both L o c k i n g hooks c o r r e c t l y engaged, B o t h L o c k i n g handles i n t h e l o c k e d p o s i t i o n . . WARNING Should you becane aware d u r i n g f l i g h t t h a t t h e canopy i s n o t c o r r e c t l y l o c k e d MAKE NO ATTEMPT T O MOVE ANY O THE CANOPY F CONTROLS I N THE A I R . Reduce t h e speed t o 7C kt; and land a t the nearest s u i t a b l e a i r f i e l d . (POST MOO 129) The canopy c o n s i s t s o f a f i x e d windscreen separated b y a carbon f i b r e hoop f r c m an upvard and backward h i n g i n g perspex t r a n s p a r e n c y . A l a t c h mechanism i s f i t t e d t o t h e upper f o r w a r d edge o f t h e transparency and can be operated b y handles f r m e i t h e r i n s i d e o r o u t s i d e t h e a i r c r a f t , . The r e a r of t h e moveable p a r t o f t h e canopy i s f i x e d t o t h e a i r c r a f t by a runner which can s l i d e f o r e and a f t i n a t r a c k b u t cannot l i f t up. When opening t h e f r o n t l i f t s up, h i n g i n g on 2 r a d i u s arms a t t a c h e d t o t h e c o c k p i t s i l 1 and canopy frane. The canopy i s p r e v e n t e d f r a n s l i d i n g t o o f a r rearwards by a S t o p incorporated i n t o the t r a c k of t h e rear attactment . P ..6-18A March 1988 A4 TP . T67M200/FM PILOTS NOTES FIREFLY T67M200 INTENTIONALLY BLANK -'{SLIMGSBY .To AVIATION PILOTS NOTES FIREFLY T67M7.00 6.4.4 Canopy, Canopv Lock The canopy i s locked b,y the 2 hooks o f t h e canop,y l a t c h assembly, attached t o the moveable transparency, which engage on t h e l a t c h p i n p a r t o f t h e l a t c h block assembly, l o c a t e d c e n t r a l l y on t h e forward hoop. The l a t c h mechanism has been designed so t h a t i n t h e open p o s i t i o n both i n t e r n a l and external handles s t i c k o u t whereas i n the closed p o s i t i o n they l a y f l a t . P o s i t i v e v i s u a l i n d i c a t i o n as t o whether t h e l a t c h mechanism i s locked i s provided by witness marks, t h e white l i n e on t h e OPEN/CLOSED placard a l i g n i n g w i t h t h e bottom o f the handle (6.4.4A). The canopy l a t c h mechanism incorporates a key operated 1ock. 6.4.4A Canopv Latch Witness Marks I ' When latch is properly closed the line on the label will line up with PO!NT'A cdalai167m26011alch cdr TAL7lP.2 o f 2 CAA Approved June 2001 TP. T67M200/FM . . " *0 enin t h e Canopy To disengage t h e l a t c h mechanism from i n s l d e or o u t s i d e a steady p u l l on t h e handle i s needed u n t i l t h e mechanism i s The canopy may now be t r i g g e r e d and t h e handle snaps i n t o t h e open p o s i t i o n opened f u l l y . . 6.6-19 December 1988 A6 TP T67M200/FM . i t s h o u l d always be moved i n a c o n t r o l l e d manner and never slammed open or s h u t The canopy s h o u l d never be l e f t i n an i n t e r m e d i a t e p o s i t i o n as t h e r e i s a r i s k o f i t f a l l i n g shut and causing damage The canopy must always remain c l o s e d and l a t c h e d d u r i n g f l i g h t unless emergency e v a c u a t i o n i s i n t e n d e d (see P 2 . i n s i d e or o u t s i d e o f t h e c o c k p i t . V a r i a t i o n s i n l e g l e n g t h are a l l o w e d for by r u d d e r pedal a d j u s t m e n t P . Cushions a r e f i t t e d . The s e a t s a r e n o t a d j u s t a b l e f o r h e i g h t b u t a d d i t i o n a l cushions can be used t o c o r r e c t p i l o t head h e i g h t . and t h e s e may be removed when p a r a c h u t e s a r e w o r n .OTS NOTES FIREFLY T67M200 EXTERNAL HANI3L.E EXTERNAL.5 S e a t s and Harnesses - The moulded b u c k e t s e a t s can be used w i t h o r w i t h o u t p a r a c h u t e s . HANDLE INTERNAL HANDLE HANDLE CANOPY CL.PIL.y l a t c h which engage on t h e l a t c h c e n t r a l l y on t h e forward hoop.4.7 ) p o s t Mod 283 A s p l i t canopy s l i d e l o c k i s i n t r o d u c e d t o r e t a i n the canopy i n the open-position The l o c k i s o p e r a t e d f r o m a l e v e r i n s i d e t h e c o c k p i t a t the rear o f the c e n t r e console C l o s i n t h e Cano y P u l l canopy f o r w a r d u n t i l i t cannot move any f u r t h e r b d t c h handle i s i n t h e open p o s i t i o n and t h u s t h a t t h e canopy i s f u l l y home. b e i n g a t t a c h e d w i t h v e l c r o s t r i p s .OSED CANOPY OPEN i n t e r n a l and hooks of the can0p. Press t h e handle i n t o t h e c l o s e d p o s i t i o n . t h e r e b y engaging t h e 2 hooks onto t h e l a t c h p i n and s e c u r i n g t h e canopy i n t h e c l o s e d p o s i t i o n . so t h a t i n t h e open p o s i t i o n b o t h o u t whereas i n t h e c l o s e d p o s i t i o n i h e y i n d i c a t i o n as t o whether t h e l a t c h . 6--20 December 1988 A6 TP T67M200/FM . > POST M D 297 Combined n a v / s t r o b e wing t i p l i g h t s are f i t t e d .PILOTS NOTES FIREFLY T67M200 The harness i s a 5 . a l l o w i n g t h e b r i l l i a n c e l e v e l t o be a d j u s t e d t o t h e d e s i r e d s e t t i n g . 4 ) C o c k p i t l i g h t i n g c o n s i s t s o f p i l l a r lamps f o r t h e i n s t r u m e n t panel and a map light The i n s t r u m e n t l i g h t i n g c o n t r o l i s a combined o n / o f f and dimmer s w i t c h .p i e c e f u l l body r e s t r a i n t type w i t h a quick-. t h i s i s done by pushing f o r w a r d t h e metal t a g t h a t p r o t r u d e s upwards from the t o p o f the l o c k i n g b o x . The s h o u l d e r s t r a p s are connected t o a c e n t r a l i n e r t i a r e e l s t r a p which i s c o n t r o l l e d f r o m a l o c k i n g mechanism l o c a t e d between t h e seats 6. The map l i g h t i s mounted on t h e bulkhead between t h e p i l o t s seats The map l i g h t s w i t c h i s on t h e i n s t r u m e n t panel l e f t of c e n t r e As no emergency battery l i g h t s are f i t t e d it i s essential t o carry a torch i n the cockpit during night f l y i n g P.OFF/Switch up BOTH (LANDING) LIGHTS 6. two shoulder s t r a p s and a n e g a t i v e G r e s t r a i n t s t r a p . one a t each w i n g t i p and one on t h e rudder t r a i l i n g edge.6 A i r c r a f t External Lighting Navigation Lights The a i r c r a f t i s f i t t e d w i t h 3 n a v i g a t i o n l i g h t s .4. an o n / o f f s w i t c h ( F i g 8 4 ) on t h e i n s t r u m e n t panel l e f t o f c e n t r e c o n t r o l s t h e l i g h t s once t h e master i s on A n t i .7 Cockpit L i g h t i s - one o n l y or both CNE(TAX1 ?L!GHT/Switch d o w - (Ref I l l u s t r a t i o n 8 .release f i t t i n g which r e l e a s e s a l l s t r a p s s i m u l t a n e o u s l y I t comprises two l a p s t r a p s .4.c o l l i s i o n L i g h t s A r o t a t i n g beacon i s f i t t e d under t h e fuselage The l i g h t i s c o n t r o l l e d b y an o n / o f f s w i t c h ( F i g 8 4 ) on t h e i n s t r u m e n t panel l e f t o f c e n t r e once t h e master i s on POST M D 205 A second r o t a t i n g beacon i s f i t t e d t o the t o p o f t h e f i n and i s O c o n t r o l 1 ed b y t h e same s w i t c h . they a r e O c o n t r o l l e d by independant nav l i g h t and s t r o b e l i g h t switches ( F i g 8 4 8 ) < L a n d i n g I T a x i Lamp Two s i n g l e f i l a m e n t l a n d i n g lamps are f i t t e d on t h e f r o n t o t the engine cowling B o t h lamps s h i n e s t r a i g h t ahead The l i g h t s a r e c o n t r o l l e d by a s i n g l e t h r e e p o s i t i o n s w i t c h ( F i g 8 4 ) such t h a t o n l y one lamp can be on a t a t i m e POST M D 347 The w i r i n g i s m o d i f i e d t o enable e i t h e r .c l o c k w i s e t o u n l o c k t h e tongues from t h e f i t t i n g The shoulder s t r a p s may be r e l e a s e d s e p a r a t e l y l e a v i n g t h e l a p s t r a p s and n e g a t i v e G s t r a p s t i l l l o c k e d . O l a n d i n g l i g h t s t o be s e l e c t e d as f o l l o w s : M i d d l e p o s i t i o n . t h e quick r e l e a s e f i t t i n g i s permanently a t t a c h e d t o t h e outboard l a p s t r a p and t h e o t h e r s t r a p s have w t a l tongues which f i t i n t o i n d i v i d u a l s l o t s i n t h e fitting. A c r u c i f o r m d i s c on t h e f r o n t o f t h e f i t t i n g i s spring-loaded t o t h e l o c k e d p o s i t i o n and can be r o t a t e d about 40" b o t h c l o c k w i s e and a n t i . A i r f r o m I t e m 4 i s passed t h r o u g h t h i s u n i t which e n c i r c l e s t h e exhaust p i p e 2 / RAM A I R INTAKE (Cold a i r system) ADJUSTABLE LOUVRE II 3 COLD A I R DEFLECTOR 4 RAM A I R INTAKE (Hot a i r system) 5 HEAT EXCHANGER P. To v a r y t h e volume and d i r e c t i o n of cold air flow.... Provides supply o f warm a i r t o t h e heat exchanger (ITEM 5 ) . ----. l o t Re-directs parts of the cold a i r f l o w down t o t h e f o r w a r d c a b i n area One f o r each p i l o t Mounted on p o r t a i r d e f l e c t o r forward o f engine.--ITEM DESCRIPTION One on each s i d e of a i r c r a f t .PILOTS NOTES FIREFLY T67M200 C o c k p i t Air C o n d i t i o n i n g Diagram m::.. One f o r each p...: t-j HOT AIR YEW l N INST WNEL W R T SiOE -----.~67M200/FM .6-21 August 1985 TP . 4) i s a p u s h f p u l l knob.. one on each s i d e of t h e f u s e l a g e j u s t i n f r o n t o f t h e canopy . . p u l l / o f f knob adjacent t o the l o u v r e P 6--22 March 1988 A4 TP . . 4 ) and t o t h e f e e t by a pushfon.. The c o n t r o l ( F i g 8. a d i r e c t feed i s l e d f r on a 3 wa. . . when p u l l e d p a r t l y o u t t o The f i r s t s t o p i t pr. ..8 - C o c k p i t V e n t i l a t i o n and H e a t i n g - Separate cockpi t h o t and c o l d a i r systems a r e p r o v i d e d . The a i r s u p p l y canes from an a i r i n t a k e f i t t i n g mounted on t h e p o r t a i r d e f l e c t o r f o r w a r d of t h e engine and goes t h r o u g h an exhaust p i p e heat exchanger b e f o r e e n t e r i n g t h e c o n t r o l box f o r d i r e c t i o n as d i c t a t e d b y c o n t r o l knob p o s i t i o n . F i t t e d on i n s t r u m e n t panel adjacent t o a d j u s t a b l e l o u v r e (ITEM 2 ) .ovides p a r t i a l h o t a i r t o t h e f r o n t t r a n s p a r e n c y and hot a i r t o t h e p i l o t s f e e t . . P o s i t i o n e d on t h e f o r w a r d console be1 ar t h e main i n s t r ument panel There a r e 3 main p o s i t i o n s . Heat o f f 2. .. 1. T67M2OOfFM < . > 6. The c o l d a i r s u p p l y cones f r o n two i n t a k e s . 3. . FULLY OUT. . - SCREEN DE-MIST OUTLET Positioned forward of t h e instrument panel One f o r each p i 1 o t . . HOT AIR [:ONTROL.. The hot a i r systen can p r o v i d e f o r f r o n t transparency d m i s t . Heat t o screen and ca b i n Heat t o s c r e e n only.. FULLY I N ..4. f o r c o c k p i t h e a t i n g or f o r a c a n b i n a t i o n o f b o t h . When PUSHED I N a i r t o occupants f e e t ON. AVIONICS COOLING ( K i n g a v i o n i c s f i t AfC) C o l d a i r f r c m s t a r board naca i n t a k e i s d i r e c t e d o n t o a v i o n i c s through holes bored i n a d i s t r i b u t i o n p i p e .y junction i n t o the central unit of t h e a v i oni cs stack .. Each p i l o t has h i s own supply. One f o r each p i 1 ot The c o n t r o l may be t u r n e d t o 1 ock i n any p o s i t i o n . COLD A I R TO CABIN CONTROL HALF OUT . SCREEN/CABiN and SCREEN ONLY . There a r e 3 main s e t t i n g s OFF. .PILOTS NOTES FlREFLY T 6 7 M 2 0 0 H T A I R D I STRIBUTI ON B X O O D i r e c t s the hot a i r i n t o the cockpit .. The a i r can be d i r e c t e d t o t h e p i l o t ' s f a c e or body by a d j u s t a b l e l o u v r e s ( F i g 8 . when p u l l e d f u l l y out i t provides f u l l h o t a i r f o r f r o n t transparency d e n i s t i n g only. PULLED OUT a i r t o occupants f e e t OFF.. Although t h e r e a r e 3 optimum p o s i t i o n s any p o i n t i n between may be s e l e c t e d t o gi ve a greater degree o f contr 01 .. ' to the tyres. the marks on the hub and t y r e ar. Other t y r e damage may include scald marks and f l a t spots (bald patciies). The tyr es are e l e c t r i c a l l y conductive and thus t h e r e i s no need f o r any earthing s t a t i c discharge wires. these pressures are marked on t h e undercarriage legs. . The correct i n f l a t i o n pressures for the t y r e s are 24 psi f o r mainwheels and 50 psi f o r t h e nosewheel . engi neering advice should be sought before tyres with t h i s damage are used.e lined up.5. if t h e t y r e moves round on t h e h u b . NO CREEP ACCEPTABLE CREEP UNACCEPTABLE CREEP The t y r e should never be used i f the wear i s such t h a t any part of t h e tread i s no longer v i s i b l e or i f any cut i s s u f f i c i e n t l y deep t o have penetrated the rubber tread t o t h e cords of the t y r e car case. mai nrhee. Whilst the two marks a r e s t i l l touching each other the amount of any creep i s acceptable b u t the wheel must be removed f o r examination when t h e marks are no longer touching each other. s .5 THE UNDERCARRIAGE 6.1 General Description The fixed t r i c y c l e undercarriage i s f i t t e d with shock absorbers and pneumatic The nosewheel i s steerable and disc brakes are fitte. with the t y r e . t h e r e i s a danger t h a t the inner tube valve may be torn leading t o sudden t y r e deflation. Tvres I Ail t h e tyres a r e tubed and thus.-'<SLINGSL)Y AVIATION PLC PILOTS NOTES FIREFLY T67M200 6. For t h i s reason 'creep' marks are painted on t h e t y r e and hub such t h a t . 6-5-2 . tube and valve in the correct position. P -6-23 August 1985 TP T67M200/FM . A s e t of br'ake pedals i s f i t t e d t o both s e t s of rudder bars.'-and--taro mechanism and t h i s spring action tends t o give t h e rudders a r t i f i c i a l " f e e l " i n the a i r as t h e nosewheel always remains connected t o the rudder controls. 6. they can only be released by moving t h e control t o OFF.ber s t r u t .. Once t h e parking brake control has been moved t o ON the brakes can be applied if they are not already on. %he l e f t wheel brake being operated by The the l e f t rudder pedal and t h e r i g h t braki by the right rudder pedal. t i p s t o s t r i k e the ground.. 6. more pressure being applied at the discs as the pedais a r e pushed f u r t h e r . Thus care must be taken when taxying over uneven ground or when braking hard and t h e control column must be kept in a position t h a t does not tend t o force t h e nose down. P. The brakes can be locked in t h e f u l l y on position by f i r s l : applying the brakes f u l l y and then moving t h e parking brake lever back t o t h e ON position: in t h i s position t h e pr.5. They are hydraulically operated by pedals on the rudder bars.5 Nosewheel Steerinq "- The nosewheel i s steerable by the rudder pedals and acts in t h e same sense as the rudder: when the r i g h t rudder pedal i s pressed with the a i r c r a f t moving the a i r c r a f t nose swings t o t h e r i g h t .4 The Mainwheels strut The mainwheels each incorporate an oleo-.pneumati c shock absorber Correct oleo-pressures should give leg extensions of about 3 inches.3 - The Nosewheel .essure fed t o t h e brakes i s then trapped i n t h e system. nosewheel i s self-centering by a spring.hand seat on the back of the bulkhead. When t h e a i r c r a f t i s not moving i t for this takes a l o t of f o r c e t o twist the nosewheel from side t o side.--6. The parking brake i s released by moving the parking brake lever t o OFF. A hole i n the t o p of each s i d e of the nose~iheel fork allows connection of a ground handling arm. See 6.5.5.rrhee1s.. Correct oleo-pressures must give a leg extension of about 3 inches as the combi nati on of low oleo-pressure and rough groiind could cause the propeller.pneumati c shock absor. once on.~{s'. system f o r f u i l and f r e e movement on the ground i s t o find a safe area and The apply f u l l rudder i n each d i r e c t i o n whi 1st t h e a i r c r a f t i s moving.T67M200/FM .6 Wheelbrakes Independent brakes are f i t t e d t o the mzin. - The nosevineel incorporates an oleo.Y AVIATION PLC PILOTS NOTES FIREFLY T67M200 5. reason t h e rudder pedals should n o t be moved when t h e a i r c r a f t i s s t a r i o a a r : ~ and the rudder should n o t be moved during the pre-flight check or excessive The only nethod of checking t h e ?udder s t r a i n may be p u t on the system.5 f o r d e t a i l s of the nosewheel steering.5. Braking action i s progressive. hydraulic reservoir i s behind the left-. 0 . A collar on the parking brake lever has t o be pulled up t h e lever snank before the lever can be ~noved from ON t o OFF or froin OFF t o ON. 6-24 August 1985 TP .5. PILOTS NOTES FIREFLY T67M200 The brakes a r e v e r y p o w e r f u l and should be used w i t h c a u t i o n on wet o r s l i p p e r y s u r f a c e s i f s k i d d i n g i s t o be avoided: under t h e s e circumstances i t i s p r e f e r a b l e t o a p p l y t h e brakes w i t h a pumping a c t i o n so t h a t . When n o t i n use t h e ground h a n d l i n g arm can be stowed i n t h e luggage comoartment. B e f o r e t a k e o f f and l a n d i n g p o s i t i v e l y check t h a t t h e p a r k i n g brake i s o f f After . Check t h e o l e o s f o r t h e c o r r e c t extension Apply t h e p a r k i n g b r a k e b e f o r e s t a r t i n g t h e engine and t e s t t h e b r a k e s i m m e d i a t e l y t a x y i n g i s commenced W h i l s t t a x y i n g check t h a t t h e nosewheel responds f u l l y and c o r r e c t l y t o rudder d e f l e c t i o n i n b o t h directions. creep and damage and i n s p e c t t h e T h e e l b r a k e s f o r damage o r l e a k s . 6. i f a wheel t e n d s t o l o c k . Examine t h e t a i l bumper t o see if i t has been touched on t h e ground. 6. B o t h arms p r o t r u d e f o r w a r d t h r o u g h t h e p r o p e l l e r d i s c and cannot be used when t h e engine i s running^ E i t h e r should be removed by t h e p i l o t b e f o r e e n t e r i n g t h e c o c k p i t t o f l y as the. The bumper i s t h e r e t o minimise t h e damage t o t h e f u s e l a g e s h o u l d t h e t a i l t o u c h t h e ground b u t i f i t i s known t h a t t h e t a i l has touched o r i f t h e bumper shows signs o f having 'ouched. A l a r g e r t o w i n g arm can be used t o tow t h e a i r c r a f t on t h e ground.y c a n n o t be seen b y e i t h e r p i l o t once they a r e s t r a p p e d in. one i s under t h e t a i l j u s t i n f r o n t o f t h e t a i l bumper and two o t h e r s are on each wing under s u r f a c e about 2 f t i n f r o m the t i p s 6.9 Picketing Three p i c k e t i n g r i n g s a r e f i t t e d .Flight When l e a v i n g t h e a i r c r a f t . i t i s a b l e t o s t a r t r o t a t i n g again b e f o r e any s k i d develops 6.5.10 Normal Use Before F l i g h t I n s p e c t t h e t y r e s f o r c u t s .5. t r e a d .7 T a i l Bumper A t a i l bumper i s f i t t e d a t t h e r e a r o f t h e fuselage under t h e r u d d e r . an e n g i n e e r i n g i n v e s t i g a t i o n s h o u l d be c a r r i e d o u t t o ensure t h a t no r e p a i r s t o t h e a i r c r a f t s t r u c t u r e a r e needed.. 6-25 August 1985 7 P T 67M200/FM .5.8 Ground H a n d l i n g Arms The ground h a n d l i n g arm a t t a c h e s t o the nosewheel f o r k and a l l o w s t h e nosewheel t o be t u r n e d w h i l s t t h e a i r c r a f t i s b e i n g handled on t h e ground. ensure t h a t t h e p a r k i n g b r a k e i s l e f t on u n l e s s t h e mainwheels a r e chocked t o p r e v e n t movement Picket the a i r c r a f t i f necessary P . M i s h a n d l i n g o f t h e c o n t r o l s d u r i n g t a k e o f f o r l a n d i n g may r e s u l t i n t h e t a i l bumper t o u c h i n g t h e ground..5. . on t h e l e f t o f t h e i n s t r u m e n t panel C o n v e n t i o n a l p i t o t and s t a t i c sources s u p p l y airspeed. powers an a r t i f i c i a l h o r i z o n and a d i r e c t i o n a l gyro: t h e a i r c r a f t DC e l e c t r i c a l Sy st= --. S t a t i c pressure i s supplied t o t h e a i r s p e e d i n d i c a t o r .6.. P 6-26 March 1%8 A4 TP T67M200/FM ..2 The P i t o t and S t a t i c Systems b y a pressure head under t h e p o r t w i n g o u t b o a r d of can be heated b y an e l e c t r i c a l el anent f o r w h i c h t h e p i t o t heater s w i t c h ( F i g 8. c l o c k . where f i t t e d . and o u t s i d e a i r t m w r a t u r e gauge: a magnetic canpass p r o v i d e s heading i n f o r m a t i o n : an accleroneter provides ' g ' information.4) when t h e master p i t o t p r e s s u r e f o r t h e a i r speed i n d i c a t o r .6 6. where f i t t e d . .1 - FLIGHT INSTRUMENTS Gener a1 D e s c r i p t i o n -- One s e t o f f l i g h t i n s t r u m e n t s i s p r o v i d e d . .. The t w o Sources a r e i n t e r c o n n e c t e d and a r e needed t o g i v e a s t a b l e source of s t a t i c p r e s s u r e under changing a i r c r a f t a t t i t u d e . p i t o t head heater. Pressure e r r o r c o r r e c t i o n s are g i v e n i n S e c t i o n 5. one on each side o f t h e f u s e l a g e about h a l f way back. The head power i s s u p p l i e d t h r o u g h i s on The h e a d s u p p l i e s < Two s t a t i c sources are f i t t e d .. -. a l t i m e t e r and v e r t i c a l speed i n d i c a t o r . These must be r m o v e d b e f o r e f l i g h t .. v e r t i c a l speed and a1 t i t u d e i n d i c a t o r s : an engi n e . s t a l l warning. turn co-or di n a t o r .FIREFLY PILOTS NOTES T67M200 6. P i t o t p r e s s u r e i s sensed t h e m a i nwheel.6. . > 6.. s the el ectrica! a r t i f i c i a! horizon.d r i ven vacuum pump. B l a n k i n g plugs can be f i t t e d o n t h e ground t o prevent t h e i n g r e s s o f m o i s t u r e or i n s e c t s . .. 000 f e e t .-'<S‘. but a r e i n p r a c t i c e o n l y c a i i b r a t e a t o '20.6-27 A p r i l 1990 A7 TP . Pressure e r r o r c o r r e c t i o n s a r e given i n Section 5.995 f e e t . a r e standard 3-needle instruments graduated from 0 t o 9 w i t h a mark every 115th u n i t . A sub-scaie and r o t a r y s e t t i n g knob a l l o w f o r t h e s e t t i n g o f v a r y i n g r e f e r e n c e pressures.lATION LTO PILOTS NOTES FIREFLY T67M200 6.6.000 f e e t .000 f e e t i n one r e v o l u t i o n and thus t h e graduations represent 1. .T67M200/FM .000 f e e t and t h e marks 2.000 f e e t i n one r e v o l u t i o n and thus t h e graduations represent 100 f e e t each w i t h a mark every 20 f e e t .000 f e e t and t h e marks 200 f e e t .HG*D~ &\. 4 ) and second a l t i m e t e r where f i t t e d . P. The s m a l l e s t needle covers 100. A s m a l l e r needle covers 10.000 f e e t .3 P i t o t and S t a t i c Instruments Altimeter The a l t i m e t e r ( F i g 8 . t h e graduations r e p r e s e n t i n g 10. t h e s c a l e i s c a l i b r a t e d i n m i l l i b a r s . one needle covers 1. The instruments could thus read up t o 99. The instruments should read w i t h i n 50 f e e t o f a known c o r r e c t h e i g h t when t h e a p p r o p r i a t e pressure r e a d i n g i s s e t and should thus agree w i t h each o t h e r w i t h i n 100 f e e t . standard markings on t h e face t o i n d i c a t e s i g n i f i c a n t speeds as given i n S e c t i o n 2. a mechanical stop which pr.T67M200/FM . The Airspeed I n d i c a t o r The airspeed i n d i c a t o r ( F i g 8.4) i s I t incorporates c a l i b r a t e d from 3.events t h e needle from over-running t h e end o f e i t h e r scale.6-28 A p r i l 1998 A8 TP . The instrument should read w i t h i n 100 f t / m i n o f zero when on t h e ground.000 f t / m i n up t o 3. There a r e numbers on t h e s c a l e every 1.000 f t / m i n down..4) i s a s i n g l e I t has needle instrument w i t h readings from 40 k t s t o 200 k t s .J<~UNG*By A\lIATION LTD PILOTS NOTES FIREFLY T67M200 V e r t i c a l Speed I n d i c a t o r The v e r t i c a l speed i n d i c a t o r ( F i g 8. Pre Mod 656 Post Mod 656 P .000 f t / m i n and marks f o r each 100 f t / m i n w i t h a l a r g e r mark a t each 500 f t / m i n . Pressure e r r o r c o r r e c t i o n s a r e given i n S e c t i o n 5. t h e amount O f s u c t i o n For t h e generated b e i n g i n d i c a t e d on a gauge i n t h e c o c k p i t ( F i g 8 . The g y r o i n s t r u m e n t s w i l l t a k e about 2 minutes t o reach o p e r a t i n g speed a f t e r s t a r t . s h o r t p e r i o d s . The gauge r e a d i n g w i l l be below t h i s f i g u r e when t h e e n g i n e RPM a r e l e s s t h a n about 1500 RPM b u t t h e g y r o s w i l l n o t slow down enough t o a f f e c t i n s t r u m e n t r e a d i n g s i f t h e RPM i s below t h i s f i g u r e f o i . The bank i n d i c a t i o n s are c a l i b r a t e d a t t h e t o p o f t h e i n s t r u m e n t and show loo. 6. p a r t i c u l a r l y under i n s t r u m e n t f l y i n g c o n d i t i o n s .6.5 i n Hg.. none of t h e s u c t i o n . 4 ) i n d i c a t e s t h e p i t c h m n k angles o f t h e a i r ' c r a f t .4 The S u c t i o n Supply > A s u c t i o n purrp. An a i r c r a f t s.6-29 J u l y 1988 A5 TP . 20°.PILOTS NOTES FIREFLY T67M200 6. M D 312 i n t r o d u c e d an e l e c t r i c a l a r t i f i c i a l h o r i z o n w i t h s w i t c h a b l e b a c k .5 t o 5.6.. Thus the s u c t i o n gauge should be m o n i t o r e d p e r i o d i c a l l y d u r i n g f l i g h t . d r i v e n i n s t r u m e n t s have any s o r t o f f a i l u r e i n d i c a t o r on them. .u p O b a t t e r y t o replace t h e suction d r i v e n instrument. . 4 ) s u c t i o n i n s t r u m e n t s t o be r e l i a b l e . u p and w i l l remain r e l i a b l e f o r about 1 m i n u t e a f t e r s u c t i o n f a i l u r e . . 30°.5 Suction Driven Instruments The A r t i f i c i a l H o r i z o n The a r t i f i c i a l h o r i z o n ( F i g 8 . t h e gauge r e a d i n g should be 4. where f i t t e d . 60" and 90" o f bank. A f a i l u r e o f t h e s u c t i o n supply i s i n d i c a t e d o n l y on t h e gauge.ymbol datum i n t h e c e n t r e o f t h e i n s t r u w n t can be a d j u s t e d w i t h a knob on t h e i n s t r u m e n t t o a l l o w f o r alignment o f t h e i n s t r u m e n t f o r p i l o t s o f d i f f e r e n t s i t t i n g h e i g h t . i s d r i v e n b y t h e engine.T67M200/FM . P . . As l o n g as t h e c o r r e c t s u c t i o n p r e s s u r e i s m a i n t a i n e d and t h e a i r c r a f t a l t i t u d e i s k e p t w i t h i n t h e i n s t r u m e n t 1i m i t s . d i g i t . The knob m8y t t e n be r e ! eased. .PILOTS NOTES FIREFLY T67M200 > The D i r e c t i o n a l Gyro The d i r e c t i o n a l gyro ( F i g 8. e v e r y lo0. To a l i g n t h e i n d i c a t o r w i t h t h e m a g n e t i c canpass t h e s e t t i n g knob must k pushed i n and k e p t i n w h i l s t i t i s t h e n r o t a t e d . There a r e marks a t e v e r y i n t e r m e d i a t e 5' and r e a d i n g t o g r e a t e r accuracy r e q u i r e s i n t e r p o l a t i o n . o n i t t i n g t h e l a s t and u n r e l i a b l e . 6-30 March 1988 A4 TP. Thus a h e a d i n g 2%" i s shown as 29. The g y r o w i l l r e n a i n a c c u r a t e f o l l o w i n g manoeuvres o f up t o 60° o f bank and p i t c h b u t i t s accuracy should always be checked a f t e r any v i o l e n t manoeuvri ng. r e c o u p l i n g t h e f a c e o f t h e i n s t r u m e n t t o t h e g y r o : t h e knob s h o u l d t h e n be t w i s t e d t o ensure t h a t i t has d i s c o n n e c t e d f r a n t h e face. The numbers on t h e s c a l e i n c r e a s e clockwise. < . I t s h o u l d be m o n i t o r e d r e g u l a r l y t o ensure t h a t i t i s c o r r e c t l y a l i g n e d w i t h t h e m a g n e t i c canpass. t h e d i r e c t i o n g y r o s h o u l d m a i n t a i n accuracy t o w i t h i n 10" p e r hou r..4) i s used t o g i v e c o r r e c t h e a d i n g i n f o r m a t i o n d u r i n g t u r n s when t h e m a g n e t i c canpass can be unsteady I t i s c a l i b r a t e d from 0-360" w i t h numbers. T67MZOO/FM .. t h i s a c t i o n uncouples t h e f a c e o f t h e i n s t r u m e n t f r o n t h e g y r o and a l l a v s i t t o be t u r n e d t o gi ve t h e same r e a d i n g as t h e m a g n e t i c canpass. Note: A i r c r a f t w i t h MOD 303 K i n g KGS5SA CCMPASS SYSl M WILL NOT have a d i r e c t i o n a l gyro f i t t e d P . t h e y a r e s e t t o o p e r a t e between 5 and 10 k t s b e f o r e t h e s t a l l . a c t i v a t i n g t h e w a r n i n g d e v i c e .7 The M a g n e t i c Compass The m a g n e t i c c m p a s s ( F i g 8.. i e t h e e r r o r i s t Z O . I f you r e q u i r e h e a d i n g 040°. 2. The w a r n i n g i s a c t i v a t e d b y a vane on t h e p o r t wing l e a d i n g edge w h i c h i s h e l d d w n b y g r a v i t y .. < Compass C o r r e c t i o n C a r d Examples 1. as t h e a n g l e o f a t t a c h o f t h e wing i n c r e a s e s .6. s t e e r 158' on x h i s c m p a s s I f you r e q u i r e h e a d i n g 2s0.. s t e e r 119" on t h i s c m p a s s . . The c m p a s s c o r r e c t i o n card l i s t s headings e v e r y 30°and g i v e s t h e i n d i c a t e d canpass r e a d i n g t h a t must be s t e e r e d t o achieve t h i s h e a d i n g .4) i s a p e n d u l o u s l y suspended permanent magnet w i t h l i q u i d danping. you must s t e e r 122" o n t h e m a g n e t i c c m p a s s . and can be t e s t e d b e f o r e f l i g h t by s w i t c h i n g t h e m a s t e r on and a p p l y i n g l i g h t f i n g e r p r e s s u r e t o l i f t t h e vane.6. For exanple. 4. p r o v i s i o n i s made f o r c o r r e c t i o n o f e r r o r s and a c m p a s s e r r o r c a r d i n d i c a t e s where r e s i d u a l e r r o r s need t o be a p p l i e d t o o b t a i n c o r r e c t headings. > 6. 3.. The system i s e l e c t r i c a l l y powered t h r o u g h t h e m a s t e r s w i t c h and a c i r c u i t breaker.6. . As t h e system i s g r a v i t y c o n t r o i i e d and i s s e t f o r e r e c t f i i ght i t cannot be used for inverted f l i g h t . The card i n your aeroplane w i l l n o t have t h e same f i g u r e s as t h i s example. s t e e r 297" on t h i s canpass. t h i s means t h a t i f you want t o f l y a heading o f 120°. P 6-31 March 1 9 8 8 A4 TP T67M200/FM .6 -- PILOTS NOTES FIREFLY T67M200 The S t a l l Wr a - S t a l l warning i s g i v e n t o t h e p i l o t b y a buzzer and a w a r n i n g l i g h t w h i c h cane on when t h e w i n g a n g l e o f a t t a c k i s approaching t h e s t a l l i n g a n g l e .. a s t a g e i s reached where t h e a i r f l o w i s caning f r o m under t h e vane and l i f t s i t up. S t e e r i n g an intermediate heading w i l l r e q u i r e i n t e r p o l a t i o n o f t h e e r r o r s shown on t h e c a r d . A sample c a r d i s shown be1 cw a l o n g w i t h s m e worked exanples. i t may say ' f o r 120' s t e e r 1 2 2 " ' . s t e e r 041' on t h i s canpass. I f you r e q u i r e h e a d i n g 160°. I f you r e q u i r e h e a d i n g 120°. 6.8 The Turn Co-ordinator PILOTS NOTES -FIREFLY T67M200 The t u r n co-ordinator (Fig 8 . T67M200/FM .ystem f a i l u r e In t h e event of f a i l u r e of t h e a r t i f i c i a1 h o r i z o n . t h i s r e s u l t s i n t h e i n s t r u m e n t being r e s p o n s i v e t o r o l l a s we1 1 as yaw. i t i s c a l i b r a t e d t o shav a r a t e one t u r n ( 3 O per second) i n e i t h e r d i r e c t i o n but i s not c a l i b r a t e d beyond t h i s . a small red warning f l a g appears on t h e f a c e of t h e instrument when no e l e c t r i c a l power i s a v a i l a b l e ..ymbol which a p p a r e n t l y i n d i c a t e s t h a t t h e a i r c r a f t nose i s i n t h e level p o s i t i o n . power being s u p p l i e d by t h e master through a c i r c u i t breaker. rendering i t more d i r e c t r e a d i n g t h a n t h e conventional t u r n i n d i c a t o r and making i s p o s s i b l e t o r o l l i n t o and out of t u r n s without having t o allow f o r instrument l a g . if t h e a i r c r a f t i s t u r n i n g a t more than r a t e one i t i s not p o s s i b l e t o a s c e r t a i n t h e a c t u a l r a t e of t u r n f r a n t h i s instrument. g r e a t c a r e must be t a k e n not t o be m i s l e d by t h e a i r c r a f t s. 4 ) provides t h e p i l o t with t u r n information < only. Being e l e c t r i c a l l y driven t h e i n s t r u m e n t s w i l l not be a f f e c t e d by a s u c t i o n s. The i n s t r ument p r e s e n t a t i o n makes use of an a i r c r a f t symbol s i m i l a r t o the a r t i f i cia1 h o r i z o n but i t gives no p i t c h i n f o m a t i o n .> 6. P. .6-32 March 1988 A 4 TP. The turn co-ordinator enploys a gyro whose inner gimbal i s not q u i t e h o r i z o n t a l . The qYro i s e l e c t r i c a l l y d r i v e n . . t h e t u r n co-ordi nator becones a primary f l i ght i n s t r u m e n t . ..4) The Clock The c l o c k i s e l e c t r i c a l l y powered. The t e m p e r a t u r e probe i s mounted on the s i d e o f t h e f u s e l a g e j u s t i n f r o n t o f t h e f r e s h a i r l o u v r e i n t a k e E l e c t r i c a l power i s s u p p l i e d b y t h e master t h r o u g h a c i r c u i t b r e a k e r 8 . > Mod 305 A b a t t e r y o p e r a t e d d i g i t a l c l o c k ( F i g 8. The i n s t r u m e n t r e q u i r e s no Dower The O u t s i d e A i r Temperature Gau e An e l e c t r i c a l o u t s i d e a i r t e m p e r a t u r e gauge g i v e s an i n s t a n t a n e o u s r e a i n g i n " C . < The Accelerometer An a c c e l e r o m e t e r shows i n s t a n t a n e o u s ' g ' r e a d i n g s and maxlmum and minimum p o i n t e r s show t h e maximum and minimum ' g ' e x p e r i e n c e d s i n c e t h e i n s t r u m e n t was l a s t r e s e t .PILOTS NOTES FIREFLY T67M200 6. A secondary use o f t h e OAT Gauge i s o b t a i n e d by p r e s s i n g t e s t s w i t c h which t h e n i n d i c a t e s t e m p e r a t u r e o f t h e main GRP s t r u c t u r e a t t h e w i n g / f u s e l a g e j u n c t i o n The sensor i s p l a c e d i n s i d e t h e p o r t s i d e o f t h e c o c k p i t s t r u c t u r e .9 Miscellaneous Instruments ( R e f 11l u s t r a t i o n 8. dependent on t h e make o f i n s t r u m n t . It i s permanently connected t o t h e b a t t e r y t h r o u g h a f u s e n o t accessible t o the p i l o t .6. The maximum and minimum p o i n t e r s can be r e s e t b y t w i s t i n g t h e r e s e t t i n g knob i n a c l o c k w i s e d i r e c t i o n . o r b y pushing t h e knob i n . . A l i m i t o f 50°C i s p l a c e d on t h e a i r c r a f t s t r u c t u r e above which a e r o b a t i c s may n o t be performed and ' g ' l i m i t s f o r WTWA ( S e c t i o n 2 . a s m a l l s p r i n g b e i n g rewound b y I t has a c o n v e n t i o n a l f a c e w i t h f u l l sweep a s o l e n o i d every few m i n u t e s . second hand.4B) i s f i t t e d i n p l a c e o f t h e o r i g i n a l equipment. 2 ) a p p l y .. below t h e i n s t r u m e n t p a n e l . 6 . 48) i s f i t t e d t o t h e r i g h t hand s i d e o f t h e i n s t r u m e n t panel . check t h a t t h e c m p a s s . remove t h e p i t o t cover and s t a t i c v e n t p l u g s and t e s t t h e s t a l l w a r n i n g systen. s u c t i o n d r i v e n instruments w i l l continue t o f u n c t i o n b u t a t o r c h would then be needed t o r e a d them a t n i ght . S u c t i o n F a i l u r e The s u c t i o n gauge w i l 1 i n d i c a t e below t h e green s e c t i o n and t h e a r t i f i c i a l h o r i z o n and d i r e c t i o n a l i n d i c a t o r w i l 1 becane u n r e l i a b l e . i s r e p l a c e d b y a second e l e c t r i c a l i n s t r u m e n t w i t h a s w i t c h a b l e back-up b a t t e r y . The p r e s s u r e i n s t r u m e n t s and e l e c t r i c a l l y d r i v e n i n s t r u m e n t s w i l l c o n t i n u e t o function.o r d i n a t o r . S w i t c h on t h e p i t o t head heater before t a k e o f f i f required. s t a l l warni ng. < MOD 312 The o r i g i n a l s u c t i o n d r i v e n A r t i f i c i a l H o r i z o n mounted on t h e l e f t hand s i d e of t h e i n s t r u m e n t panel.PILOTS NOTES FIREFLY T67M200 > The E l e c t r i c a l A r t i f i c i a l Horizon Mod 293 an e l e c t r i c a l a r t i f i c i a1 h o r i z o n ( F i g 8. . Once t h e engine has been s t a r t e d . T67M200/FM . . a l i g n t h e d i r e c t i o n a l g y r o w i t h t h e m a g n e t i c canpass and s e t t h e datum on t h e a r t i f i c i a l h o r i z o n . check t h e s u c t i o n system. ( a l t e r n a t o r and b a t t e r y b o t h dead). ... r e f e r t o t h e a c c e l e r m e t e r t o ensure t h a t t h e ' g o l i m i t s are n o t exceeded. a r t i f i c i a l h o r i z o n and t u r n co-ordi nator g i v e c o r r e c t i n d i c a t i o n s i n t u r n s i n both d i r e c t i o n s .-ordinator. Electrical A i r c r a f t not f i t t e d w i t h s u c t i o n s u p p l i e d i n s t r u m e n t s w i l l be f i t t e d w i t h a s w i t c h a b l e back-up b a t t e r y (MOO 312) f o r t h e e l e c t r i c a l l y operated A r t i f i c i a l Horizon.6-34 March 1988 A4 TP.11 Malfunctioning Failure I n t h e u n l i k e l y event o f a t o t a l e l e c t r i c a l f a i l u r e t h e p i t o t head heater. check The p r e s s u r e i n s t r u m e n t s and i t s c i r c u i t breaker and r e s e t i f necessary. Check t h a t t h e pcwer f a i l u r e w a r n i n g f l a g i s n o t showing on t h e t u r n co. When manoeuvring.6. Re1 a t e t h e o u t s i d e a i r t e m p e r a t u r e t o c o n d i t i o n s o u t s i d e t h e a i r c r a f t f o r warning o f i c i n g . P. 6. I f any one o f t h e s e s e r v i c e s f a i l w i t h o u t s i g n s o f any other f a i l u r e .10 Normal Use B e f o r e s t a r t i n g t h e engine. Reset t h e d i r e c t i o n a l gyro p e r i o d i c a l l y and r e s e t t h e a l t i m e t e r sub-scal e s e t t i n g s as a p p r o p r i a t e . t u r n c o .6. d i r e c t i o n a l gyro. . . Check and cross-check t h e a l t i m e t e r s w i t h a known p r e s s u r e s e t t i n g and ensure t h a t t h e a i r s p e e d and v e r t i c a l speed i n d i c a t o r s a r e w i t h i n l i m i t s . Once t a x y i n g . I n f l i g h t . 6. c l ock and o u t s i d e a i r temperature gauge w i l l a1 1 s t o p w o r k i n g . monitor t h e s u c t i o n and e l e c t r i c a l s y s t m s f o r f a i l u r e . > < P.... 6. This i s achieved by p r e s s i n g t h e whole pedal assembly forwards w i t h pressure d i r e c t e d towards t h e t o p o f t h e pedals u n t i l t h e assembly i s f e l t and heard t o have c l i c k e d i n t o a locked p o s i t i o n .7.. t h i s i s described i n t h i s s e c t i o n a t 6. t h i s i s acceptable. . and f l a p s . Movement i s t r a n s m i t t e d from t h e pedals t o t h e rudder by cables and p u l l e y s .PILOTS NOTES FIREFLY T67M200 6.5) i n t h e c o c k p i t operates t h e trimmer.4 Ailerons D i f f e r e n t i a l F r i s e a i l e r o n s occupy t h e outboard t h i r d o f each wing t r a i l i n g edge. The l e f t . The two s e t s o f pedals a r e interconnected so t h a t movement o f one s e t r e s u l t s i n i d e n t i c a l movement o f t h e other.5.f l i g h t inspection. A trimmer p o s i t i o n i n d i c a t o r ( I t e m 2 F i g .7..3 The E l e v a t o r and Trimmer (Ref I l l u s t r a t i o n 8.7.1 General D e s c r i p t i o n The f l y i n g c o n t r o l s comprise conventional e l e v a t o r s .6.-..2 Control Columns The two c o n t r o l columns a r e l i n k e d t o g e t h e r so t h a t movement o f one always r e s u l t s i n i d e n t i c a l movement o f t h e other.5) Mass and horn balanced e l e v a t o r s a r e f i t t e d t o both s i d e s o f t h e t a i l p l a n e t r a i l i n g edge.7 FLYING CONTROLS AND FLAPS 6... N f o r n e u t r a l and D f o r nose down.7. About 6 m (114 inch) o f up-and--down p l a y can be f e l t a t t h e trimming t a b when i t i s tested f o r s e c u r i t y during the p r e . they cannot be disconnected or . E l e v a t o r trimming i s a v a i l a b l e t o t h e . 8. press-to-transmit button. Fore and a f t movement o f t h e c o n t r o l columns i s t r a n s m i t t e d t o t h e e l e v a t o r c o n t r o l s u r f a c e by rods and b e l l cranks. -A.5 and 6. The system i s balanced f u l l y nose up ( c o n t r o l columns f u l l y r e a r ) on t h e ground w i t h no airspeed o r engine a i r f l o w .I ~ ~The top o f each c o n t r o l column i n c o r p o r a t e s a v ~. The rudder pedals can be a d j u s t e d t o a l l o w f o r l e g l e n g t h by p u l l i n g g e n t l y on t h e t o p o f t h e pedal and a t t h e same t i m e s l i d i n g t h e pedal assembly t o t h e r e q u i r e d p o s i t i o n .i l o t . 8. L a t e r a l movement o f t h e c o n t r o l columns i s t r a n s m i t t e d t o t h e a i l e r o n s by c o n t r o l rods and b e l l cranks. No trimming i s p o s s i b l e i n f l i g h t b u t t h e p o r t a i l e r o n i s f i t t e d w i t h a metal t r i m t a b which can be a d j u s t e d on t h e ground by ground engineers o n l y . The rudder pedals a l s o p r o v i d e f o r nosewheel s t e e r i n g and wheel braking.T67M200/FM . movement being t r a n s m i t t e d by a s o l i d core cable. e l l l . rudder. t h e c a b l e t e n s i o n b e i n g maintained by s p r i n g s which h o l d t h e rudder pedals forward. A f t e r adjustment ensure t h a t t h e pedal assembly i s properly locked i n position. .7. 6.5.6-35 A p r i l 1998 A8 TP . a i l e r o n s . A handwheel (Item 1 Fig. t r i m p o s i t i o n s a r e m marked U f o r nose up. p 6.5) i s f i t t e d i n t h e c o c k p i t j u s t i n f r o n t o f t h e o p e r a t i n g wheel.5 Rudder The rudder i s operated by e i t h e r p a i r o f l i n k e d rudder pedals..h a n d e l e v a t o r incorporates a trimming t a b covering about h a l f t h e e l e v a t o r t r a i l i n g edge. 6. up.7.. the spring balance tends t o pull the flaps down and t h i s makes i t d i f f i c u l t t o disengage t h e lock. So t h a t t h e r e will be no a i r loads f e l t when operating t h e f l a p s in t h e a i r . 5 ) The f l a p s occupy the inboard two-thirds of each t r a i l i n g edge. and care must be taken when lowering them on t h e ground t o stop them from slamming t o the down position. P./ATION LTD PILOTS NOTES FIREFLY T67M200 6. 6. On the ground. the button should be released so t h a t i t i s f r e e t o engage the lock a t the new position.7 c Flaps (Ref I l l u s t r a t i o n 8 . f l a p lever in the Flaps Up . a small portion of t h e extreme inboard t r a i l i n g edge not being used so t h a t i t can form a walkway. locks t h e the elevator f u l l y down. The control lever (Item 3 Fig. Depending upon t h e l i k e l y wind conditions and t h e direction in which t h e a i r c r a f t i s parked. and 40" (landing).5) i s positioned on the centre console and can be locked i n any of t h e 3 flap positions. the controls may be locked with t h e elevators in the u p position by using the right-hand p i l o t s buckle s t r a p and l a p s t r a p . i f i t i s not. In t h i s position the nosewheel/ground f r i c t i o n prevents movement of t h e rudder i n windy conditions. t o achieve t h i s i t i s necessary t o push the f l a p lever in t h e UP direction t o balance the spring pressure before attempting t o press the button i n .6 Control Lock > A control lock i s introduced by Md 316 or M d 435. A t when secured by the ailerons neutral and This consists of a sockets which locate on t h e r e a r faces of t h e the centre of the bar i s a f u r t h e r socket which. o o transverse bar with control columns.6-36 Apri 1 1998 A8 . t o check t h a t the locking indicator i s v i s i b l e .HG*By &\. then the flaps are not correctly locked and may move t o a d i f f e r e n t position without action by the P i l o t . a dark coloured spring-.J<~L. passing them around the left-hand control column and taking u p t h e slack.. t h e lever i s then f r e e t o move. There i s no stowage f o r the control lock. To move t h e f l a p from one selection t o another. The rudder/nosewheel should be l e f t on f u l l right lock. I t i s important. The f l a p s a r e correctly locked when the button in the end of' t h e s e l e c t o r lever protrudes f a r enough t o enable t h e white band locking indicator on i t t o be seen.loaded button in the end of the control lever protrudes f a r enough t o show a white ring a t the base of the button. As t h e f l a p s approach the required position. a spring i s f i t t e d which a s s i s t s down selection.. This r e s u l t s in t h e f l a p s being strongly biased in t h e down direction on t h e ground. 18" (takeoff). 8. . o The f l a p control has 3 positions. when the lock i s f u l l y engaged.position. the button must f i r s t be pressed in t o disengage t h e lock. p a r t i c u l a r l y when raising t h e f l a p s . which must be removed from the a i r c r a f t before f l i g h t . N portion of the flaps i s stressed f o r walking o n .7. After landing maintain d i r e c t i o n a l rudder. f r e e and c o r r e c t movement. an undemanded r o l l occurs. control using t h e combination of t h e as necessary. I f . check t h e e l e v a t o r s and a i l e r o n s f o r f u l l . CENTER Flap Lever L o c k i n g n. Leave t h e f l a p s in t h i s p o s i t i o n and land a t the nearest suitable airfield. r a i s e t h e f l a p s at a locking indicator i s then v i s i b l e .7. nosewheel s t e e r i n g and brakes 6. f r e e and c o r r e c t movement. Check t h e c o r r e c t operation of t h e f l a p s a t a l l 3 s e t t i n g s and leave then up f o r taxying. i f they a r e not or i f d i f f i c u l t y i s experienced in holding an out-of-trim r o l l f o r c e . r e t u r n t h e f l a p s t o t h e previous s e t t i n g . check t h e condition of t h e control s u r f a c e s and t a b s and ensure t h a t a l l d r a i n holes a r e c l e a r .PILOTS NOTES FIREFLY T67M200 There i s no f l a p p o s i t i o n i n d i c a t o r as both f l a p s can e a s i l y be seen from either seat. check t h e rudder and nosewheel f o r f u l l .7. immediately following f l a p s e l e c t i o n . Once taxying.9 -Malfunctioni2 -s a f e height and speed. Ensure t h a t t h e trimmer moves over t h e f u l l range.t o r dica 6. Once in t h e a i r c r a f t . ensuring t h a t t h e For landing. P . After t a k e o f f . . v i s u a l l y check t h a t both f l a p s a r e in t h e same p o s i t i o n .8 Normal Use Before f l i g h t .6-37 August 1985 TP T67M200/FM . use t h e f l a p s as r e q u i r e d . e. f. A transponder with or without height encoding. i.T67M200/Ffl . b. A loudspeaker. j. ILS and markers. h. g.8 RADIG EPUIFMENT ine a v a i i a b i e r i d i o f i t s msge p r o v i s ~ o n f o r some or a i l of t h e f o l l o w i n s facilities: a. ra An audio c o n t r o l panel. VCR. A hand microphone. d.6-38 August 1965 TP . intercommunication between ere# members. ADF. P. c.AVIATION PLC PILOTS NOTES FIREFLY T67M200 6. More s o p h i s t i c a t e d equipment i s a v a i l a b l e s u b j e c t t o s p e c i a l order. DME. S i n g l e or two VHF communicatio~?~ d i o s . ..... 7-11 7............................ .14 A e r o b a t i c s ..3...........11 E r e c t S p i n Recovery .............................................2... 7-7 ' g ' S t a l l i n g ...........................2.4 T e s t i n g t h e C c n s t a n t Speed U n i t .. 7-7 7...... 7...PILOTS NOTES FIREFLY T67M200 SECTION 7 HANDLING CONTENTS 7...1 Y e f o r e S t a r t i n g t h e c n g l n e ...........i Take of-? ........... 7-11 7............ 7-4 7..... 7-7 7...3 Climb ...............................................................2.......... 3 T e s t i n g t h e Engine .............. 7-7 7........ 7......................... 7-8 7.......................................................2 Crosswinti Take off ...............1 7....... 7 ..................13 T a i l s i i d e s .................... 7-1 7.........3............lO C i r c u i t and l a n d i n g s .............................................2.....2 S t a r t i n g t h e Engine ...........2.......5 S t a l l i n g i n Level F l i g h t ........................ 1 ...........................2.....................2 C i r c u i t P r o c e d u r e .... 7-3 7...............2 Handling i n F l i g h t ................ 7-1 7 ....1.................2..............12 I n v e r t e d S p i n n i n g ................... a s t e f f e c t i v e page i s P ............ 7-3 7......8 7 7...........1 ........... 7-9 7...1.....3 3 r i ......6 S t a l l i n g i n a T'cirn ....... 7.... 7 ... L i 3 August 1985 TP ....2.....................................2..........3 as S e f o r e F l i g h t ......9 7...........*.. 7-11 7............... 7-11 7..........2....9 E r e c t S p i n n i n g ........2....... 7-9 7.5 Taxying .....2...............15 I n v e r t e d F l i g h t .......T67M20G/FM .................1............2...10 E r e c t Spin C h a r a c t e r i s t i c s ..............3 Landings ....3...............3........ 7-2 7...................... 7 .........7 7............3 7.. 7-6 7.2 '7.........2..1 Approaching t h e Landing P a t t e r n ....4 A f t t r Landing .... 7 ..2.. 7-3 7.............1....8 F l i c k ihanoeuvres ..4 General F l y i n g ..... 7-2 7...... T67M200/FM .PILOTS NOTES FIREFLY T 6 7 M 2 0 0 INTiNTiONALLY BLANK August 1985 TF . PILOTS NOTES FIREFLY T67M200 7. many of which wi 1 1 vary from the above and 113y on occasions be more successful.. will n o t s t a r t i t shou!d be l e f t f o r 15 minutes t o allow the s t a r t e r t o A normal s t a r t should then be attenipted. Switch the fuel purnp o f f . a wait ~~-l. 7.. A t a l l other times the engine should be s e t t o 1200 4PM t o reduce the danger of sparking plug fouling. and attempt another s t a r t withoct re-oriming. warnings on the sisnificance of tne S t a r t e r warning l i g h t . operate the s t a r t e r f o r 5 seconds. Should the engine f a i 1 t o s t a r t after a raaxin~liii ofdlLl seconds s i a r t e r use. If the s t a r t e r motor i s oper axed f o r a t o t a l of. .g~onds 1. Whatever d r i 11 i s used the limitations on s t a r t e r use must be observed. always be carried out with the mixture control i n i t i a l l y in the lean cut off position as described above. which mee%s the requirement of the CAA!LAMS schedule.ing dri 1 1 can be applied whether the engine i s hot or cold. With the fuel o n .ny.s. If the engine i s hot i t may be Starting should found easjer t o s t a r t the engine without any priming.1 Before S t a r t i n c_ ..A the Enoine : . ieaive t h e mixture a t cutoff and the magneto on If the engine s t i l l i e f t .and move the mixture control smoothly t o f u l l y rich. the s t a r t e r ..flight inspection as detailed in the FKCs. the t h r o t t l e 2 quarter open and the mixture at cutoff.Engine Sta e S t a r t the engine using tke checks and d r i l i s i n the F'RCs. release. Experience has provided cool. Leave the magneto on Left and the fuel a t cutoff.7-1 August 1985 TP T67M200/FM .r t i n u h. s e l e c t magnetos t o . t h i s will drain the fuel f r m the cylinders and the engine may actually s t a r t . Note the ine same priming and start.~~i~nut~es-~sho~~l~~ t o s t a r t so that the s t a r t e r motor can caol and the battery s t a b i i i z e .a. Iamediately the engine f i r e s . if i t s t a r t s .~~.will r e ? a i : l within limits for the e n t i r e f l i g h t (Section a . P. I t i s important t h a t the engine i s not l e f t ar.1.2-. ? j .n.nay be t h a t the engine i s over-primed. I f i t does not s t a r t . i t . Move the mixture control t o f u l l rich u n t i l a s l i g h t b u t steady fuel flow i s noticed atid return the mixture control t o cutoff. many permutations of ?:he f a i i e d s t a r t i n g dri 11. The following d r i l l should then be followed t o avoid running out of s t a r t e r time.1. Select the l e f t (impulse) magneto and engage the s t a r t e r . s e t the t h r o t t l e at a quarter open.- Check that the a i r c r a f t documentation i s in order and t h a t no dated or airframe hours lifed i ~ e a ~are due attentjon.?O. s Caiculate the centre of gravity t o ensure Chat i t . quickly return the t h r o t t l e t o a quarter open a~nd p u t the mixture t o f u l l y rich.:both~".. open the t h r o t t l e f u l l y . Carry o u t a pre. idling on the ground for longer than i s necessary during taxying. Tbe most likely cause of f a i l u r e t o s t a r t i s over-priming so the d r i l l should be followed carefully.&fli nute be observed before any further attempt period. switch the fuel pump on.-. r e . a d d i t i o n a l l y . should be c r o s s e d s l o w l y . I t may be To taxy.7-2 August 1985 TP .5 Taxying Do n o t a t t e m p t t o move t h e r u d d e r p e d a i s when t h e a i r c r a f t i s n o t moving. t h i s check i s t h e o n l y one w h i c h can easi l y a s c e r t a i n whether a magneto i s permanently l i v e . Repeat t h e whole p r o c e d u r e a second t i m e t o change t h e o i 1 i n t h e p r o p e l l e r hub. r e .'.3 . To t e s t t h e u n i t . . c l o s e t h e t h r o t t l e and r e l e a s e t h e p a r k i n g b r a k e . 7. T e s t i n g t h e C o n s t a n t Speed U n i t The t e s t o f t h e c o n s t a n t speed u n i t a c h i e v e s two o b j e c t i v e s .1.PILOTS NOTES FIREFLY T67M200 7. I t i s done a t 1800 RPM by s e l e c t i n g ' R ' and c h e c k i n g t h a t t h e RPM does decrease b u t n o t b y 'Both' i s t h m more t h a n i 7 5 w h i l s t t h e engine c o n t i n u e s t o r u n smoothly. The brakes s h o u l d n o t be used a l o n e f o r t u r n i n g as t h i s w i l l l e a d t o If v e r y t i g h t t u r n i n g i s e x c e s s i v e s i d e loads on t h e nose t y r e and l e g . i t i s checked t h a t t h e RPM d i f f e r e n c e between ' L ' and ' R ' i s n c t more t h a n 50. position. To t u r n t h e a i r c r a f t on t h e ground t h e nosewheel s t e e r i n g must be used. c l o s e t h e t h r o t t l e and r e . S e t 1200 RPM and s e l e c t magneto t o 'R1. r e q u i r e d t h e {udder should be moved f u l l y i n t h e r e q u i r e d d i r e c t i o n and Uneven ground l i g h t br a k i ng a p p l i e d on t h e appr o p r i a t e f i n s i de) wheel.a p p l y t h e t o e brakes m o m e n t a r i l y t o e n s u r e t h a t t h e y a r e working. 7.s e l e c t ' b o t h ' and r e p e a t t h e check w i t h As t h e engine i s n o r m a l l y stopped by c u t t i n g o f f t h e f u e l . e n s u r i n g t h a t t h e r e i s an RPi'l drop b u t t h a t t h e e n g i n e aoes n o t stop. Move t h e p r o p e l l e r c o n t r o l back t o maximum RPM b e f o r e t h e RPM f a l l s b y more t h a n 500. use t h e t h r o t t l e t o s e t 1800 RPM l e a v i n g t h e p r o p e l l e r Then move t h e p r o p e l l e r c o n t r o l t o t h e minimum RPM c o n t r o l a t maximum RPM.T67M200/FM . a l l o w i n g t h e p i t c h change mechanism t o move more s m o o t h l y and f r e e l y . magneto '1.Tes- t h e Enaine - The dead c u t / l i v e magneto check i s c a r r i e d o u t a f t e r s t a r t i n g . necessary t o u s e some power t o s t a r t t h e a i r c r a f t moving b u t . N o t e t h a t t h e RPM s t a r t s t o f a l l . The e n g i n e r u n s h o u l d o n l y be done a f t e r 4 m i n u t e s warm-up o r w i t h t h e engine o i 1 t e m p e r a t u r e a t l e a s t i n t h e y e l l o w / g r e e n .1. P. s e c o n d l y i t c i r c u l a t e s t h e c o l d o i l i n t h e p r o p e l l e r hub and r e p l a c e s i t w i t h warmed o i l . Firstly it checks t h a t t h e p r o p e l l e r p i t c h responds t o t h e demands o f t h e p r o p e l l e r RPM c o n t r o l .4 -. as soon as i t moves. I t s h o u l d be done on t h e f i r s t f l i g h t o f each day and whenever t h e e n g i n e i s c o l d .1. The same p r o c e d u r e i s t h e n r e p e a t e d f o r t h e ' L ' magneto and.s e l e c t e d and t h e RPM a l l o w e d t o s t a b i l i z e a t 1800 f o r a few seconds. a t approximate1 y 30 kts. allowing the speed t o increase t o A t 200 f t . Takeoff performances are given in Section 5. 7-3 April 1998 A8 .2 Crosswind Takeoff > If the wind i s approaching the crosswind l i m i t of 25 k t s . There i s l i t t l e tendency for the a i r c r a f t t o swing f o r reasons of torque or slipstream e f f e c t s as the a i r c r a f t has been designed t o minimise these c h a r a c t e r i s t i c s . I t should be remembered t h a t t h i s mixture s e t t i n g i s appropriate f o r only one combination of manifold pressure. which should be done on every f l i g h t and -. a l t i t u d e and engine RPM. the manifold pressure will stay steady b u t then s t a r t decreasing. and a change in any of these factors will result in the need t o reset t h e mixture. carry out the takeoff checks from the FRCs. t h e nosewheel should not be raised until the takeoff speed when the a i r c r a f t should be rotated cleanly t o the climbing a l t i t u d e . Line the a i r c r a f t u p on the takeoff path.A'lNiON LTD PILOTS NOTES FIREFLY T67M200 7. The nosewheel should be l i f t e d just c l e a r of the ground as soon as t h e elevator becomes e f f e c t i v e .not just on the f i r s t f l i g h t of each day.3 Climb < I n i t i a l l y climb a t a shallow angle. There i s l i t t l e sink or trim change whilst the flaps are raised unless the a i r c r a f t i s significantly below the correct speed. checking t h a t the RPM i s approximately 2650 . 7. release the brakes and open the t h r o t t l e f u l l y in about 2 seconds. 7. As the mixture i s weakened. a t sea level ISA conditions and 80 kts clean. o i l temperature and cylinder head temperature are not red. 75 kts with takeoff f l a p MTWA The mixture should be l e f t a t f u l l y rich a t a l l power s e t t i n g s above 75% unless t h i s r e s u l t s in rough running.-{'N' q S.2. in t h i s case progressively weaken the mixture and observe the manifold pressure. Any tendency f o r the upwind wing t o l i f t during a crosswind takeoff should be corrected by the use of ailerons. The a i r c r a f t will i n i t i a l l y climb a t approximately 1100 ft/min..2 HANDLING I FLIGHT N 7.2700 RPM.2. I t i s unlikely that any mixture adjustments will be needed below 5000 f t amsl in the climb.1 Takeoff After t e s t i n g the engine. leave t h e mixture a t t h i s s e t t i n g . richen the mixture again until smooth running i s regained and the manifold pressure returns t o the original figure. Climb a t 80 kts a t full t h r o t t l e . until the flaps a r e up. apply the brakes momentarily t o stop any vibration from the rotating mainwheels and r a i s e the flaps in stages. P. Some uneven engine running may also be apparent a t t h i s point. increasing t o the appropriate speeds.2. keeping the nosewheel j u s t c l e a r of the ground by progressive easing forward of the control column as the speed increases The a i r c r a f t can be flown off a t 50 kts (Pre mod 358) 55 kts (Post mod 358) with takeoff f l a p or 53 kts (Pre mod 358) 64 kts (Post mod 358) f l a p l e s s . Check that the RPM i s between 2600 RPM and 2650 RPM and that the oil pressure. 7-4 Apri 1 1998 A 8 TP . The directional trim changes associated with power and speed a l t e r a t i o n s require the use of only small rudder. The flaps can be operated with l i t t l e e f f o r t in the a i r a t the normal c i r c u i t speeds. The propeller turns clockwise. 7. Post Md 656 maximum speeds a r e 120 kts o o (IAS) takeoff position and 98 kts (IAS) landing position.. even a t f u l l aileron deflection.. c r u i s e and endurance are given in Section 5 . p a r t i c u l a r l y during s t a l l i n g o r aerobatics when the changed f l i g h t characteristics and 1 imitations may r e s u l t in unexpected a i r c r a f t behaviour or overstressing. Flaps The maximum speed f o r operating the flaps i s 88 kts IAS f o r both f l a p positions Pre M d 656. Power Mixture Chanqes Alterations in power s e t t i n g s cause pitch/yaw movements.. Care must be taken t o ensure t h a t the flap lever i s locked in the selected position a f t e r operation.. The engine performance figures f o r climb. There i s l i t t l e trim change unless the flaps are operated a t the extreme of the speed limit. P. Should the flaps be l e f t unlocked they will tend t o move t o the down position a t low speed. Trimmer T h 2 elevator trimmer i s very powerful and care should be exercised i n i t s use.4 General Flyinq Introduction The limitations and centre ot gravlty requlrements should always be checked before any f l i g h t t o ensure t h a t the a i r c r a f t parameters r i l l be complied with. b u t more e f f o r t i s needed a t the upper speed l i m i t .T67M200/FM . There are no rudder o r aileron trimmers available t o the pi l o t .2. pedal movements t o maintain balanced f l i g h t . The out-of-trim forces require firm b u t manageable pressure i f the trimmer i s operated t o e i t h e r extreme within the speed range. t h i s may be s i g n i f i c a n t . the following pitchiyaw changes occurring w i t h power a l t e r a t i ons: Power Increase Pitch Yw a Nose Up Nose Left Power Decrease Nose Down Nose Right The mixture control should invariably be s e t t o f u l l y rich before any change in power s e t t i n g i s made as the change may result in too weak a mixture and consequent rough running o r high cylinder head temperatures. Fl yinq Controls The flying controls are we1 1 -balanced and very l i t t l e rudder i s required with aileron application as the ailerons cause l i t t l e asymmetric drag. Mixture adjustments in the cruise should be made using the same procedure a s outlined for the climb.PILOTS NOTES FIREFLY T67M200 The mixture should always be s e t t o f u l l y rich before descending as the weaker mixtures applicable t o f l i g h t a t a l t i t u d e are too weak f o r correct engine operation a t lower levels. t h e movements being proportional t o the power change. thus the engine may not respond correctly t o t h r o t t l e opening a t the bottom of the descent i f weak mixture i s s t i l l selected. K*LW LTO AVIATION PILOTS NOTES FIREFLY T67M200 There i s s i g n i f i c a n t change i n l i f t c h a r a c t e r i s t i c s and l i t t l e drag penalty with takeoff f l a p (18") . The ai 1 erons have exceptional drag balance during ai 1eron application. The s a f e s t speed t o f l y i s 70 kts as t h i s represents a good speed f o r a i r c r a f t c o n t r o l l a b i l i t y and i s a l s o the best climbing angle speed. The best climb angle performance requires half f l a p a t 70 kts and t h i s should be p u t down whilst f l y i n g a t reduced airspeed as i t a l s o r e s u l t s in a lower nose position giving a b e t t e r f i e l d of view. There i s no tendency f o r t h e a i r c r a f t t o become unstable in pitch a t extremes of speed o r ' g ' . Sideslippinq The a i r c r a f t can be side-slipped well and t h e r a t e of height l o s s can be incr'eased marked1 y by t h i s method.. very l i t t l e rudder i s needed t o maintain balanced f l i g h t during r o l l ing manoeuvres. even with f u l l aileron appal ication.-!{sL. P. ENGINE - Idle INDICATED AIR SPEED N sideslip o - 65 Kts Full r i g h t rudder Full l e f t rudder Reduced V i s i b i l i t y Flyinq In poor v i s i b i l i t y i t may be f e l t prudent t o f l y a t reduced airspeed. landing f l a p (40") s e l e c t i o n r e s u l t s in very l i t t l e more l i f t b u t a large increase in drag.T67M200/FM . should near obstacles be sighted. The a i r c r a f t i s s t a b l e in pitch and i s e a s i l y trimmed. The following figures give a guide.7-5 Apri 1 1998 A 8 TP . The trim changes a r e as follows. t h e a i r c r a f t staying in level f l i g h t during a l l flap selections: 88 kts Flap from up t o takeoff nose Flap from takeoff t o landing pitch Flap from landing t o takeoff pitch Flap from takeoff t o u p Nose pitches down 50 k t s Very slight down pitch Nose pitches further down Nose pitches up slightly Nose pitches up more strong1 y S l i g h t pitch nose down Negligible Negligible S t a b i l i t y The a i r c r a f t i s n e u t r a l l y s t a b l e in r o l l and has n i l aileron breakout force which gives good response and a good rate of roll . allowing best climb performance. I c i n q Conditions The a i r c r a f t i s not c l e a r e d f o r f l i g h t i n c o n d i t i o n s as t h e r e i s no a i r f r a m e or wing p r o t e c t i o n .6 k t s 52 5 k t s 48. c o n d i t i o n s must be avoided and every e f f o r t must be made t o f l y o f them i f they are encountered i n a d v e r t e n t l y .PILOTS NOTES FIREFLY T67M200 Turbulence I f turbulence becomes v i o l e n t enough t o cause concern. v a r y i n g w i t h h e i g h t . 7. A i l e r o n s remain e f f e c t i v e up t o t h e s t a l l b u t care should be taken i n t h e use o f a i l e r o n s t o keep t h e wings l e v e l i f t h e s t a l l should be prolonged. The second precaution against o v e r . c o v e r i n g across t h e ground about n i n e times t h e h e i g h t l o s t i n s t i l l a i r . .2. power o f f 1 Takeoff f 1ap.2 o r 1. This gives a s a f e margin o f speed over t h e s t a l l i n g o r o v e r s t r e s s i n g c o n d i t i o n s t h a t can r e s u l t from turbulence. power o f f I 53 2 k t s 48. M i l d wing drop may occur i n any c o n f i g u r a t i o n b u t t h i s can always be h a l t e d by t h e a p p l i c a t i o n o f opposite rudder d u r i n g recovery.9 k t s andin in^ f l a p . .O o r 1. t h e a i r c r a f t should be flown a t 75 k t s w i t h t h e f l a p s up. power o f f / I Post Mod 358 1020 kg (2250 l b ) 56.5 S t a l l i n g i n Level F l i g h t The a i r c r a f t has l i t t l e aerodynamic s t a l l warning i n l e v e l f l i g h t . The average g l i d i n g performance i s as f o l l o w s . The engine p r o t e c t i o n can a u t o m a t i c a l l y a l l o w f o r a i r f i l t e r b l o c k i n g . icing These clear icing Glidinq The a i r c r a f t g l i d e s w e l l a t 70 k t s . temperature and weight. The approximate s t a l l i n g speeds (IAS) a r e as f o l l o w s : Pre Mod 358 975 kg (2150 l b ) 56. e . t h e approaching s t a l l being s i g n a l l e d by t h e warning buzzer.c o o l i n g i s t o open up t h e t h r o t t l e ver'y s t e a d i l y i n about 4 seconds when overshooting a t t h e bottom o f t h e g l i d e I t must be remembered t h a t t h e r e i s a s i g n i f i c a n t d i f f e r e n c e i n t h e r a t e o f descent between engine i d l i n g and p r o p e l l e r w i n d m i l l i n g and r e a l i s t i c p r a c t i c e should concentrate on t h e much more l i k e l y cause o f a f a i l e d engine.5 k t s 7 - [ z e r o f l a p .5 Nm/1000 ft (PRE Mod 333) 1:8.3 Nm/1000 ft (POST Mod 333) During a prolonged g l i d e t h e r e i s a r i s k o f o v e r . Speed Engine O f f Propel 1er Windmilling 70 k t s Rate o f Descent 800 f t / m i n (PRE Mod 333) 1000 f t / m i n (POST Mod 333) G l i d e Angle S t i l l Air 1:g. i .9 k t s I Regulation o f s t a l l warning horn 10 k t s above s t a l l i n g speed. F i r s t l y t h e engine should be warmed and t h e plugs c l e a r e d by opening t h e t h r o t t l e smoothly t o f u l l power and back when r e q u i r e d i n g l i d e . Two precautions should be taken t o counter t h i s r i s k . p r o p e l l e r w i n d m i l l i n g .c o o l i n g t h e engine which m i g h t r e s u l t i n t h e engine subsequently not responding p r o p e r l y t o t h r o t t l e opening. 2.2. a p p l i e d .y.i r: a r e done and how pr ompt and c o r r e c t t i l e r e c o v e r y z c t i o n 2. t h e r o l l w i 11 s t o p and a u t o r o t a t i o n o r s p i n n i n g w i 11 n o t develop. Recovery i s e f f e c t e d by a p p l y i n g enough rudder t o s t o o any F a r t h e r w i n g drop and. b u t t h i s tendency can be i m m e d i a t e l y c o n t r o l l e d by c o n v e n t i o n a l r e c o v e r y action. D e l i b e r a t e f l i c k manoeuvres should n o t be e n t e r e d above 80 k t s IAS. a i r c r a f t w i l l e i t h e r r o i l o u t o f t h e t u r n o r r o l l i n t o the t u r n and t h i s i s n o t e n t i r e l y p r e d i c t a b l e or c o n s i s t e n t .y. As t h e ' g ' f o r c e s d u r i n g f l i c k manoeuvres w i l l exceed 2 ' g i . t h e a i r c r a f t may e n t e r a s p i r a l d i v e w i t h t h e speed i n c r e a s i n g v e r y r a p i d l y and t h e r i s k t h a t VNO (140 k t s ) w i l l be exceeded d u r i n g rec0ver. 7.. I f t h e c o n t r o l column i s i m m e d i a t e l y moved f o r w a r d t o u n s t a l l t h e wirigs. a t t h e sarne t i m e . very l i t t l e c o n t r o l column movement i s n o r m a l l y necess3r.6 S t a l l i n g i n a 'Turn I n a l e v e l t u r n t h e bank w i 11 e i t h e r i n c r e a s e o r decrease a t t h e s t a l l . A t t h e s t a l l t h e r a t e o f p i t c h decreases and. 7.2.:y a p p l i e d i. t h e y should never be attempted w i t h t h e f l a p s extended.7-7 August 1985 TP. moving t h e c o n t r o l coiunln Forward t o u n s t a l i If t h e wings.nq - ( a ) Er!try H e i g h t The h e i g b t l o s s i s :bout 250 f t p e r t u r n and r e c o v e r y These h e i g h t l o s s e s may vary.s p i n or a n t i s p i n c o n t r o l a p p l i c a t i o n i s the flick. t h e r e i s aerodynamic s t a i l w a r n i n g 1 f 1 t h e fcrm o f e l e v a t o r b u f f e t f e l t t h r o u g h t h e c o n t r o l column. i h e engine power i s a v a i l a b l e i t s h o i ~ l d be fu. 7. t h e a i r c r a f t w i 11 s e t t l e i n t o a c o n v e n t i o n a l s p i n a f t e r one t o two t u r n s a f t e r tinless c c r r e c t p r o . i f t h e a i r w a f t i s d e i i b e u a t e l y p u l l e d t o t h e s t a l l i n g a n ~ l e o f atCack ab3ve t h e s t a l l i n g speed. I f t h i s occurs d u r i n g a t u r n the. i f f u r t h e r back p r e s s u r e i s a p p i i e d t h e a i r c r a f t w i l l t e n d t o d r o p a wing. dependent on hcw mary t a k e s about 539 f t t w n s o f t h e sr. The r a t e of' r o t a t i on i s i n i t i a1 l y v e r y r a p i d b u t t h e a i r c r a f t responds immedi a t e l y t o corrective control action. T67M200. Dependent on t h e a i r s p e e d a t e n t r y . This b u f f e t occurs j u s t before the a i r c r a f t s t a l l s .PILOTS NOTES FIREFLY T67M200 W i t h p r a c t i c e a f u l l s t a l i may be recoveued w i x h i n 50 f t b u t i f t h e r e c o v e r y i s i n i t i a t e d a t t h e sound a f t h e s t a l l w a r n i n g t h e r e should be rio h e i g h t l o s s i n any c o n f i g u r a t i o n .'FM .8 ' F l i c k ' Manoeuvres.- i f p r o .9 E r e c t 5pifin.s p i n c o n t r o l i s a p p l i e d above t h e s t a l l i n g speed t h e a i r c r a f t w i l l f l i c k and enter a s p i n i n t h e d i r e c t i o n o f t h e a p p l i e d c o n t r o l . D i s o r i e n t a t i o n may occur d u r i n g t h e i n i ti a1 h i g h r o t a t i o n r a t e of t h e a i r c r a f t and i t i s recommended t h a t f l i c k manoeuvres a r e n o t a t t e m p t e d by i n e x p e r i e n c e d p i l o t s b e f o r e adequate d e m o n s t r a t i on and s u p e r v i s i o n has been r e c e i v e d .nmediatel:/. A s p i r a l d i v e i s r e c o g n i z e d by a r a p i d i n c r e a s e i n a i r s p e e d w i t h t h e r a t e o f r o t a t i o n p r o b a b l y s l o w i n g down as t h e s p i n changes t o a s p i r a l d i v e . t h e a i r c r a f t may e n t e r e i t h e r a s p i r a l d i v e o r a h i g h r o t a t i o n a l s p i n .s p i n c o n t r o l i s n o t m a i n t a i n e d t h r o u g h o u t t h e spin. The average l o a d f a c t o r t h r o u g h o u t i s 1.=({SUNGSBY AviATloN PLc PILOTS NOTES FIREFLY T67M200 is. I f t h e c o r r e c z c o n t r o l movements a r e n o t a p p i i e d a s p i r a l d i v e may d e v e l o p as shown b y an a i r s p e e d i n c r e a s i n g above 80 ~t. i.. 1t i s recommended t h a t i n e x p e r i s n c e d p i l o t s a l l o w a f u r t h e r 1000 f t t o t h e e n t r y h e i g h t .h a a a c t e r i s t i c s n C A t e n t r y . . r e c o v e r y i s as g i v e n i n S e c t i o n 3. The a i r c r a f t r o l l s almost t o t h e i n v e r t e d d u r i n g t h e f i r s t h a l f t u r n o f t h e s p i n and t h e n t h e s p i n p r o g r e s s i v e l y s t a b i l i z e s over about 3 t u r n s . 7. If f u l l p r o . A high r o t a t i o n a l s p i n i s r e c o g n i z a b l e by a s t e e p e r nose down a t t i t u d e and a h i g h e r r a t e o f r o t a t i o n t h a n i n a normal spin. 3. t h e a i r c r a f t p i t c h e s nose up s l i g h t l y w h i l s t r o l l i n g r a p i d l y i n t h e d i r e c t i o n o f applied rudder. a i r s p e e d w i 11 be h i g h e r t h a n a normal s p i n b u t w i l l n o t i n c r e a s e r a p i d l y . P. 2.7-8 August 1985 TP T67M200lFM . ( b ) S p i n E n t r y A t s t a l l warning a p p l y f u l l rudder i n t n e i n t e n d e d d i r e c t i o n of s i n ana a t t h e same t i m e b r i n g c o n t r o l column c e n t r a l l y f u l l y Sack.2.26.d be c o n p l e t e b y 1500 f t above ground l e v e l . The r a t e o f r o t a t i o n i s about 150' per second o r 2 1 seconds p e r t u r n . Hold t h e s e c o n t r o l p o s i t i o n s . Para.11 -. Close t h e t h r o t t l e Raise t h ? f l a p s Check t h e d i r e c t i o n o f s p i n as i n d i c a t e d by t h e t u r n c o .7.10 E r e c t -. They may be used as a b a s i s f o r p l a n n i n g r e c o v e r y which sh0ul.E r e c t S p i n Recovery - The f o l l o w i n g a c t i o n s a r e a composite s p i n r e c o v e r y p r o c e d u r e and a l l o w f o r e r e c t s p i n s e n t e r e d f r o m any c o n f i g u r a t i o n . 7. The IAS s t a b i l i z e s a t about 75 k t s t o t h e r i g h t and 80 k t s t o t h e l e f t . Thus t h e e n t r y h e i g h t f o r a 4 t g r n s p i n f o r an i n e x p e r i e n c e d p i l o t should be: 4 t u r n s 4 x 250 Recovery f l i n Height S a f e t y A1 lowance 1000 f t 500 f t I500 f t 1000 f t 4000 f t above ground l e v e l .2. ending up w i t h about 50° o f bank and t h e nose about 40° below t h e h o r i z o n . The wings can be l e v e l l e d b y u s i n g a i l e r o n w i t h r u d d e r s c e n t r a l and t h e d i v e t h e n recovered using e l e v a t o r ( w h i l s t observing t h e ' g ' l i m i t s ) .2 I n c o r r e c t recover:^.o r d i n a t o r 3. 13 -i l s l i d e s Ta The a i r c r a f t i s l i k e l y t o s u f f e r c o n t r o l s u r f a c e damage i f a l l o w e d t o If t a i l s l i d e and t h i s manoeuvre s h o u l d n o t be c a r r i e d o u t d e l i b e r a t e l y . 7. t h e most common m i s t a k e s b e i n g t h e use o f l e s s t h a n f u l l o p p o s i t e r u d d e r and slow or i n s u f f i c i e n t f o r w a r d movement o f t h e c o n t r o l column.PILOTS NOTES FIREFLY T67M200 4. F a i l u r e t o a p p l y t h e c o r r e c t s p i n r e c o v e r y a c t i o n s may d e l a y o r p r e v e n t e x i t f r a n t h e s p i n .2.7-9 August 1985 TP T67MZOO/FM .14 Aerobatics The recommended e n t r y speeds f o r an i n e x p e r i e n c e d p i l o t a r e as f o l l o w s : R o l l i n g i n t o and o u t o f inverted f l i g h t Stabilized inverted flight Slow r o l l S t a l l turn entry 90 k t s 80 k t s Roll o f f the top 110 k t s 110 k t s F l i c k r o l l max 140 k t s 80 k t s Stall turn rotate L.7 f o r h i g h r o t a t i o n a l s p i n r e c o v e r y ) . 7.2.12 -n v e r t e d I Spinninq - The a i r c r a f t i s n o t c l e a r e d f o r i n v e r t e d s p i n n i n g . p r o g r e s s i v e l y and c o n t r o l column f o r w a r d u n t i l t h e s p i n s t o p s . As t h e c o n t r o l column i s moved f o r w a r d d u r i n g t h e r e c o v e r y a c t i o n s . 7. t h i s i s normal and should nor: be t a k e n as an i n d i c a t i o n t h a t t h e a i r c r a f t i s n o t recovering. c o n t r o l i s l o s t n e a r t h e v e r t i c a l t h e c o n t r o l s s h o u l d be c e n t r a l i s e d and f i r m l y h e l d t h e r e u n t i l t h e nose has dropped and f l y i n g speed r e g a i n e d .oop 50 k t s 120 k t s P. A p p l y and h o l d f u l l r u d d e r t o oppose t h e d i r e c t i o n o f s p i n H o l d i n g t h e a i l e r o n s n e u t r a l . immedi a t e 1 y t h e s p i n s t o p s .eve1 t h e wings w i t h a i l e r o n s and r e c o v e r f r a n t h e d i v e The a i r c r a f t w i l l no:mally s t o p s p i x i n g ? ! i t h i n 1 t u c n o f t h e a p p l i c a t i o n o f t h e r e c o v e r y a c t i o n (see S e c t i o n 3. . The r a t e of i t would move f r a n 6. 5. t o move i t a l l t h e way f o r w a r d t o t h e f r o n t c o n t r o l c o l ~ i m n movement should be such t h a t f u l l y back t o f u l l y f o r w a r d i n about 3 seconds f i r m l y move t h e I t may be necessary stop. c e n t r a l i s e t h e r u d d e r L. t h e s p i n may appear t o speed up momentari Ty b e f o r e s t o p p i n g . 7.2. I f a t a i l s l i d e i s t h o u g h t t o have o c c u r r e d t h e a i r c r a f t s h o u l d be f l o w n g e n t l y and l a n d e d f o r an e n g i n e e r i n g i n s p e c t i o n f o r damage. I f t h e t h r o t t l e was c l o s e d t h e engine w i l l p r o b a b l y s t o p t u r n i n g and an a i r s t a r t w i l l be necessar'y. L i m i t a t i o n s on t h e o i l p r e s s u r e i n d i c a t i o n s d u r i n g masoeuvres i n v o l v i n g i n v e r t e d f l i g h t a r e f u l l y d e s c r i b e d i n S e c t i o n 2.2.={SLINGSBYPLc AVIATION PILOTS NOTES FIREFLY T 6 7 M 2 0 0 7.15 -.7-10 August 1985 TP.I n v e r t e d Flight The en@ ne i s equipped w i t h an i n v e r t e d f l i g h t o i l s y s t m and t h e w i n g f z e l tanks i n c o t p o r a t e a f l o p tilbe s y s t m . T67M200/FM . and mast be observed. P.4. Allow t h e speed t o decrease t o 65 kts with landing f l a p ..2 C i r c u i t Procedure J o i n at 85 kts. P. L. To commence descent reduce the t h r o t t l e s e t t i n g t o achieve approximately 1500 RPM and lower takeoff f l a p .3 Landinqs Normal With the round-out complete and t h e t h r o t t l e closed.3. 7.PILOTS NOTES FIREFLY T67M200 7. t h u s i t i s erriilg c n the safe s i d e t o be s l i g h t l y high.ower landing f l a p as required and complete t h e f i n a l checks. Do not push t h e control column forward or the propeller t i p s could touch t h e ground.50 k t s dependent on t h e AUN. The two s t a g e s of f l a p a r e used as required t o achieve t h e touchdown point. 7.7-11 August 1985 TP . The f i n a l turn can be commenced in about t h e same position as f o r a normal c i r c u i t and the t h r o t t l e closed.. Keep s t r a i g h t with nosewheel s t e e r i n g and move t h e s t i c k progressively a f t as speed decreases. thus a1 1 p r a c t i s e s should be done with the aim of touching down 1 / 3 way down t h e landing s t r i p so t h a t t h e r e i s a margin of s a f e t y t o allow for t h e increased r a t e of descent i n the real c a s e . The power s e t t i n g required w i l l vary with the wind c o n d i t i o n s .. Maintain t h i s speed round t h e f i n a l turn u n t i l t h e wings are level on finals. 70 k t s takeoff f l a p and 63 k t s landing f l a p f o r threshold speed 58 k t s .. (75 kts i f a f l a p l e s s c i r c u i t i s being carried out).. A t h e g l i d e approach angle i s steeper than f o r a normal c i r c u i t i t s i s necessary t o ccinmence round-out s l i g h t l y higher but t h e landing i s the sane as f o r a normal approach. Glide Aftsr t h e end of t h e downwind leg t h e speeds t o be flown a r e 70 kts f l a p up.167M200/FM .3 CIRCUIT AND LANDINGS 7. allowing t h e m3in wheels t o touch down at 45 . The considerable drag of f u l l f l a p may be used t o dive off excess height up t o t h e l i m i t i n g speed of 88 kts. The threshold speed of 60 kts with landing f l a p or 65 kts f l a p l e s s i s achieved by t h r o t t l i n g back smoothly as t h e round-out i s commenced. Also i t i s usually l e s s hazardous t o run off t h e end of a landing s t r i p a t 19 k t s than t o f a l l s h o r t of t h e beginning a t 40 k t S .1 Approaching t h e Landing P a t t e r n Before joining t h e c i r c u i t or e n t e r i n g any landing procedure or approach p a t t e r n .3. Keep t h e nosewheel off the ground u n t i l the elevator becomes l e s s e f f e c t i v e then lower the nose gently a t approx 35 kts. Commence braking as necessary. t h e Rejoin Checks should be c a r r i e d o u t as l a i d out in the FRCs. Allow t h e speed t o reduce and enter a descent a t 70 kts.3. An actual forced landing would probably be made with the engine f a i l e d and windmilling which would r e s u l t i n a higher r a t e of descent than -with the engine i d l i n g . Carry out t h e pre-landing checks i n the downwind position. adjus\t the a t t i t u d e t o keep the a i r c r a f t off t h e ground. T67M200/FM . The round-out and l a n d i n g are t h e same as f o r a normal l a n d i n g except t h a t power should n o t be reduced u n t i l a f t e r t h e round-out has been commenced. The a i r c r a f t should be flown down t h e extended runway w i t h t h e wings l e v e l u s i ng t h e "crab " technique. t h e approaches w i l l be very f l a t . F l a p l e s s approach may be p r a c t i s e d but. Braking may then commence w i t h t h e s t i c k being moved progressi v e l y a f t as speed decreases. As t h e approach speeds a r e s i g n i f i c a n t l y lower than f o r a normal c i r c u i t . Reduce t h e power s l i g h t l y and a l l o w the speed t o f a l l t o 58 k t s when power w i l l need t o be increased t o stop t h e speed f a l l i n g f u r t h e r . I n h i g h crosswind c o n d i t i o n s t h e nosewheel should be g e n t l y lowered as soon as t h e mainwheels a r e on t h e ground so t h a t nosewheel s t e e r i n g i s a v a i l a b l e t o a s s i s t w i t h d i r e c t i o n a l c o n t r o l . care must be taken t o a v o i d an overshoot. The speed should be held a t 75 k t s throughout t h e f i n a l t u r n and. due t o t h e a i r c r a f t ' s e x c e l l e n t g l i d i n g performance.7-12 A p r i l 1998 A8 TP . The e l e v a t o r should be h e l d j u s t a f t o f c e n t r a l and t h e wings kept l e v e l w i t h a i l e r o n w h i l s t t h e t h r o t t l e i s opened f u l l y . With more than 15 k t s headwind a n e a r l y normal g l i d e path angle can be flown a t about 1200 RPM but. F l a p l e s s Landinq The a i r c r a f t has a very robust manual1 y operated f l a p system and thus f l a p f a i l u r e p r a c t i c e has l i t t l e relevance. p r o g r e s s i v e l y f l a t t e r approaches a r e r e q u i r e d . i t should be allowed t o reduce t o be 70 k t s f o r a t h r e s h o l d speed o f 65 k t s .PILOTS NOTES FIREFLY T67M200 S h o r t Landinq F l y a normal approach u n t i l lowering f u l l f l a p . j u s t p r i o r t o landing. A s l i g h t "snatch" may be f e l t on t h e rudder pedals when t h e nosewheel touches t h e ground as t h e nosewheel t r i e s t o a l i g n i t s e l f w i t h the d i r e c t i o n o f t r a v e l o f the a i r c r a f t . The a i l e r o n s should be h e l d d e f l e c t e d i n t o wind a f t e r l a n d i n g t o reduce t h e p o s s i b i l i t y o f t h e upwind wing l i f t i n g d u r i n g t h e ground r o l l . -Once t h e mai nwheels a r e on t h e ground t h e nosewheel should be lowered immediately but g e n t l y . w i t h l e s s headwind. once wings a r e l e v e l . c P. Any attempt t o a p p l y c o r r e c t i v e a c t i o n i s l i k e l y t o make t h e s i t u a t i o n worse r e s u l t i n g i n more serious bounces and probable undercarriage and propel 1 e r damage. t h e p i l o t must be ready t o counter any s i n k o r windshear e f f e c t w i t h immediate a p p l i c a t i o n of power. Abandoned Landinq A landing should be abandoned i f misjudgement o r c o n d i t i o n s r e s u l t i n a heavy bounce d u r i n g t h e attempt t o land. The round-out should be smooth and t h e a i r c r a f t should be landed on the mainwheels a t 53 k t s t o reduce t h e chance o f touching t h e t a i l bumper > Crosswind Landinq Landings a r e p e r m i t t e d w i t h i n t h e crosswind 1i m i t o f 2 5 k t s . The excel1 e n t l a t e r a l c o n t r o l a v a i l a b l e r e s u l t s i n no d i f f i c u l t y being experienced i n h o l d i n g t h e wings l e v e l as t h e a i r c r a f t i s yawed s t r a i g h t w i t h rudder. . 3.I~GSPY AvlnTloN LTo PILOTS NOTES FIREFLY T67M200 Touch-and-qo-Landinq A f t e r l a n d i n g r a i s e t h e f l a p s from t h e l a n d i n g (40") s e t t i n g t o t h e t a k e o f f (18") s e t t i n g . Goinq Round Aqain Open t h e t h r o t t l e f u l l y . The a i r c r a f t should then be f l o w n o f f t h e ground a t t h e normal speed o f 50 k t s and climbed a t a shallow angle t o reach a c l i m b i n g speed a p p r o p r i a t e t o t h e f l a p s e t t i n g as f o l l o w s : Takeoff f 1ap F l a p up 75 k t s 80 k t s A t 200 f t t h e f l a p should be r a i s e d . I n emergency c o n d i t i o n s where t h e remaining runway l e n g t h does not permit t h e t i m e t o r a i s e t h e f l a p t o 18" t h e a i r c r a f t responds r e a d i l y t o a f u l l f l a p f u l l power t a k e o f f from t h e ' r o l l I .3.7-13 A p r i 1 1998 A8 TP . 7.. T67M200 Maintenance Manual) must be c a r r i e d o u t b e f o r e next f l i g h t P.5 E m e r q e n c y y Landinqs (Post Mod 358) Should i t be necessary t o c a r r y out an emergency l a n d i n g a t weights above t h e maximum l a n d i n g weight o f 2150 l b s (975 kg) a "heavy or abnormal l a n d i n g i n s p e c t i o n " ( r e f . 7.J{SL. Climb a t t h e speed a p p r o p r i a t e t o f ! a p s e t t l n g and r a i s e t h e f l a p s above 200 ft as f o r a touch-and-go landlng.4 A f t e r Landinq Complete t h e a f t e r l a n d i n g and c l o s i n g down checks i n t h e FRCs.T67M200/FM . Note t h e f l i g h t times and d e t a i l s f o r e n t r y i n t h e a p p r o p r i a t e a i r c r a f t documents. M~.-'<S~.7-14 August 1985 TP . T67M2001FM .lATION LTO PILOTS NOTES FIREFLY T67M200 INTENTIONALLY BLANK P. A\. Centre Cons01 e ................. ................................................................................ .......... L a s t e f f e c t i v e page i s P................................................ P r i n c i p a l Features ( P r e Mod 1 2 9 ) P r i nci p a l F e a t u r e s ( P o s t Mod 129) Instrument Instrument Instrument Instrument Instr ment Panel Panel Panel Panel Panel ( B a s i c A/C) (Mod 274) (Mod 293) (Mod 311) (Mod 341) ................... ... ........... ....8-9/10 CAA Approved Mar ch 1988 A4 TP.............................. ........ ................................................... .. .PIL..............OTS NOTES FIREFLY T67M200 SECTION 8 CENTRE OF GRAVIT_Y_COWUTER AND ILLUSTRATIONS CONTENTS 9 Centre o f G r a v i t y Over 1 ay C e n t r e o f G r a v i t y Ccmputer .................................................................... .................................................................... T67M20O/FM .......................... T67M200FM .PILOTS NOTES FIREFLY T67M200 INTENTIONALLY BLANK CAA A p p r o v e d A u g u s t 1985 TP. S ARE PARALLEI 3~ 4 NOTE: MPTWA (Maximum P e r m i s s i b l e T a k e o f f Weight A u t h o r i s e d ) CAA Approved A p r i l 1990 A7 TP T67M200/FM ...< < s L /AVA? IONBL~ HG~ P C FIREFLY PILOTS NOTES T67M200 8. U s i n g t h e end o f t h i s l i n e as your new datum p o i n t .. o i n t p l o t t e d i n ( 1 ) over p o i n t ' X ' on Diagram 1 and draw a t r a c e along t h e p i l o t s l i n e r e p r e s e n t i n g the t o t a l weight o f p i l o t s t o be c a r r i e d . a l i g n i t w i t h p o s i t i o n ' X ' as b e f o r e and t r a c e a l o n g t h e f u e l l i n e t h e w e i g h t o f f u e l be c a r r i e d T h i s w i l l g i v e you t h e p o s i t i o n o f C f o r t a k e o f f G WHEN ALIGNING DIAGRAMS CHECK THAT ALL H0RIZONTAI. The t o p end of t h i s l i n e now becomes y o u r new datum p o i n t . which must be a l i g n e d w i t h p o i n t ' X ' .. Then draw a t r a c e a l o n g t h e baggage l i n e r e p r e s e n t i n g t h e amount o f baggage t o be c a r r i e d .IS WITHIN THE ARCA OF THE ENVELOPE.1 CENTRE OF GRAVITY OVERLAY - -MPTWA 1020Kg (POST MOD 3581 w -- 1000 CENTRE OF GRAVITY DISTANCE Fl 2M FIRE BULKHEAD (mm) INSTRUCTIONS FOR USE 1 2 P l o t on t h i s o v e r l a y t h e w e i g h t and CG o f t h e a i r c r a f t t o be checked. ENSURE THAT THIS CINE FA!. P o s i t i o n t h e . f n i o q muf6b wsn ruoy 29mossd won 3 n i f 2 i d f 'io bns qof 3riT . t n i o q muf6b wsn ~ u o y 3 n i l 2 i r i f 30 bns 3 d f pniaU 26 t o f r i e i s w 9df 3 n i l l3u? 3 d j pnoT6 3 3 6 ~ f bn6 970t3d 26 ' X I n o i f i a o q ? ? o g i 6 f 707 23 ?o n o i f i 2 o q grit uoy s v i p l l i w 2 i d T b s i ~ ~ f 3d f s u i i3 ..P .13!. b 3 i m 6 3 9d o f S f2um ri3idw .[:A TAHT 233H:l 2MARaAIa aMIM3I!A MH 3W :3TOM . E 3 n i l 3p6pp6d 9df en016 93673 6 w67b nsdT . b s i ~ r 6 s o f 3p6ep6d i o fnuomh 3rif p n i f n s a g ~ q 3 r 3d .(a?& OOM T Z 0 9 1 6>020f A OOOl W -& T 4 M w 3 w61b bn6 I mfile6iO no ' x ' f n i o q 7 9 V O ( I ) n i b s f f o r q f n i o 9 3df n o i f i z o q > f o T i q ?a f r i p i s u ! 6 f o f 9rif pni$nszs:qs: % n i l a j o l i q srif eoOr6 3 3 6 1 f 6 . ' X " f n i o q d t i w b g n p i r 6 3d . ZIHT TAHT 3RU2M3 r i f i w f i n e i 1 6 .1AFIAq 3RA 2..IATMOZIROH .!A3 3MI!.390J3VM3 3HT 30 A3RA 3HT MIHTIW 2J. PII-OTS NOTES FIREFLY T67M200 8.3 P R I N C I P A L FEATURES (PRE MOO 129) MARKER BEACON AERIAL [inside fuselage) \ COMM 1 AERIAL PITOT STATIC FUEL TANK VENT COMBINED PICKETING POINT ADF LOOP STROBE LIGHT AND SENSE AERIAL FIRST AID KIT FIRE EXTINGUSHER (port and starboard [port only) GLIDE SLOPE AERlA (beneath cockpit floo OIL FILLERIDIPsuci' ACCESS PANEL STALL WARNING DETECTOR I EATED PlTOT LANDING LIGHT / OIL SEPARATOR BREATHER PIPE MECHANICAL FUEL PUMP DRAIN \ $UEL TANK SAMPLERIDRAIN (port and starboard] A p r i 1 1998 A8 TP .T67M200/FM . . OLEO CHARGING ACCESS PANEL FIXED TAB OIL FILLER1DIPSTICK. 2-9 L 'ITOT POINT / OIL SEPARATOR BREATHER PIPE \ \ 'FUEL TANK SAMPLERIDRAIN [port and starboard] A p r i l 1998 A 8 TP ..PILOTS NOTES FIREFLY T67M200 8.GHT OR COMBINED NAVISTROBE (MOD 2971 (port and starboard) __7 PICKETING (r"r+ ""A ".--ACCESS PANEL GLIDE SLOPE AERIAL (beneath cockpit floor) 'd LANDING NAV L.".. a.3A P R I N C I P A L FEATURES (POST MOD 129) ROTATING BEACON (post mod 2051 COMM 1 AERIAL CANOPY LATCH EXTERNAL HANDLE STATIC VENT (port and starboard) ROTATING BEACON AERIAL ( ~ n s l d efuselage) REMOVABLE VOR AERIAL (inside tailplanel INSIDE COCKPIT FIRST AID KIT FIRE EXTINGUISH€ CRASH AXE MAIN UIC.". T67M200/FM ..sac""n. 8. 5. 7. HEAD TEMPERATURE GAUGE AMMETER DIMMER SWITCH C I R C U I T BREAKERS ALTERNATOR OUTPUT C I R C U I T BREAKER THROTTLE CONTROL L / H MAGNETIC COMPASS PRESS TO TRANSMIT SWITCH NAVl/VOR/LOC/GS NAVZ/VOR/LOC ACCELEROMETER P . 18. ~ 6 7 M 2 0 0 / F M . 30. E X C I T A T I O N SWITCH MASTER SWITCH FUEL PUMP SWITCH FUEL COCK STARTER BUTTON THROTTLE CONTROL R/H PROP SPEED CONTROL' MIXTURE CONTROL MAGNETO SWITCH HEATING CONTROL ADF A I R VENT (2 OFF) COLD A I R TO C A B I N CONTROL ( 2 OFF) OUTSIDE A I R TEMP GAUGE PRESS TO TEST STRUCT. 33. 45. 11. 43. 46. 50. 35. 39..4A INSTRUMENT PANEL (MOD 2 7 4 ) KEY 1.. 9. 31. 42. 47. 14. 13. 38. 24. 16. 26. 15. 41. 21. L I G H T ALTERNATOR WARNING LIGHT 27. 40. 28. 34. 2. 29. 19. 4. 37.. 20. LANDING L I G H T S SWITCH NAV L I G H T S SWITCH STROBE L I G H T SWITCH MAP L I G H T SWITCH STOP WATCH C L I P CLOCK RADIO PANEL RADIO PANEL TACHOURMETER MANIFOLDIFUEL PRESSURE GAUGE O I L PRESSURE GAUGE O I L TEMP GAUGE FUEL CONTENTS GAUGE/LEFT TANK FUEL CONTENTS GAUGEIRIGHT TANK CYL. 6. 12.PILOTS NOTES FIREFLY T67MZ00 8. 36. 32. 49. 25. 3. 22. 17. 51.8-7A/8A > < A p r i l 1998 A8 TP . TEMP TURN CO-ORDINATOR DIRECTIONAL GYRO VERTICAL SPEED INDICATOR ALTIMETER ( 2 OFF) A R T I F I C A L HORIZON AIRSPEED INDICATOR EATED P I T O T SWITCH VACUUM GAUGE S T A L L WARNING L I G H T STARTER ENGAGED W. 10. 48. 44. 23. 55. 43 44. 34. 54. 46. 41. 38. 51. 29.8-78/80 < > April 1 9 9 8 A 8 T P . 53. 48. 35. HEAD TEMPERATURE GAUGE AMMETER DIMMER SWITCH C I R C U I T BREAKERS ALTERNATOR OUTPUT C I R C U I T BREAKER ELECTRIC A R T I F I C I A L HORIZON MAGNETIC COMPASS THROTTLE CONTROL L/H PRESS TO TRANSMIT SWITCH P .NGSLIY A\.J<SL. 49. 33. TEMP HEATED P I T O T SWITCH MAP L I G H T SWITCH AVIONICS PANEL O I L PRESSURE GAUGE O I L TEMP GAUGE FUEL CONTENTS GAUGEILEFT TANK FUEL CONTENTS GAUGEIRIGHT TANK CYL.lATlON LTD PILOTS NOTES FIREFLY T67M200 8 . 37. 39. LANDING LIGHTS SWITCH NORMALIEMERGENCY PHONES SWITCH AVIONICS MASTER SWITCH D I G I T A L CLOCK NAV LIGHTS SWITCH ROTATING BEACON SWITCH STROBE LIGHTS SWITCH AVIONICS PANEL TACHOURMETER MANIFOLDIFUEL PRESSURE GAUGE OUTSIDE A I R TEMPERATURE GAUGE PRESS TO TEST STRUCTURAL. 45. 42.T67M200/FM . 50. 30. 40. 52. 36. 32. 31. 47. 4 8 INSTRUMENT PANEL (MOD 293) KEY EXCITATION SWITCH MASTER SWITCH FUEL PUMP SWITCH FUEL COCK STARTER BUTTON THROTTLE CONTROL R/H PROP SPEED CONTROL MIXTURE CONTROL MAGNETO SWITCH C A B I N HEAT CONTROL ADF NAV 2 ACCELEROMETER AIR VENT (2-OFF) COLD A i R TO CABIN CONTROL ( 2 OFF) MKR BEACON RECEIVER SLAVING ACCESSOR AND COMPENSATOR UNIT TURN CO-ORDINATOR P I C T O R I A L NAV INDICATOR VERTICAL SPEED INDICATOR ALTIMETER (2 OFF) A R T I F I C A L HORIZON AIRSPEED INDICATOR VACUUM GAUGE STALL WARNING L I G H T STARTER ENGAGED WARNING L I G H T ALTERNATOR WARNING L I G H T 28. 29.. 35. SWITCH. .T67M200/FM . 51. 31. . 42. 39. 37.. 32. . I IGHT .8-7C/8C > < A p r i l 1998 A8 TP . 36.PILOTS NOTES FIREFLY T67M200 8. 50.. 46. 53.. AVIONICS PANEL TACHOUR METER MANIFOLDIFUEL PRESSURE GAUGE OUTSIDE AIR TEMPERATURE GAUGE PRESS TO TEST STRUCTURAL TEMP EXHAUSE GAS TEMP GAUGE AVIONICS PANEL O I L PRESSURE GAUGE O I L TEMP GAUGE FUEL CONTENTS GAUGEILEFT TANK FUEL CONTENTS GAUGE~RIGHT TANK CYL. 30.4C INSTRUMENT PANEL (MOO 3 1 1 ) 51 H KEY E X C I T A T I O N SWITCH MASTER SWITCH FUEL PUMP SWITCH FUEL COCK STARTER BUTTON THROTTLE CONTROL R/H PROP SPEED CONTROL MIXTURE CONTROL MAGNETO SWITCH CABIN HEAT CONTROL ADF NAV 2 ACCELERCMETER A I R VENT ( 2 OFF) COLD A I R TO C A B I N CONTROL ( 2 OFF) MKR BEACON RECEIVER SLAVING ACCESSORY AND COMPENSATOR UNIT TURN CO-ORDINATOR P I C T O R I A L NAV INDICATOR VERTICAL SPEED INDICATOR ALTIMETER ( 2 OFF) ELECTRIC A R T I F I C A L HORIZON (2 OFF) AIRSPEED INDICATOR ART HORIZ. HEAD TEMPERATURE GAUGE AMMETER DIMMER SWITCH C I R C U I T BREAKERS ALTERNATOR OUTPUT C I R C U I T BREAKER MAGNETIC CCMPASS THROTTLE CONTROL L/H PRESS TO TRANSMIT SWITCH ELT ON SWITCH P . 54. 44. 38.T I P STROBE SWITCH MAP . . 52.. 14 . 40. LANDING L I G H T S SWITCH NORMALIEMERGENCY PHONES SWITCH HEATED P I T O T SWITCH D I G I T A L CLOCK NAV LIGHTS SWITCH ROTATING BEACON/W. 33. 45. 41. BACK-UP BATTERY SWITCH STALL WARNING L I G H T STARTER ENGAGED WARNING L I G H T ALTERNATOR WARNING L I G H T 28. 47. 48. 43.. 49.. .. . . . . STROBE L I G H T SWITCH 3 0 . 24. 15. MANIFOLDIFUEL PRESSURE GAUGE 3 8 . FUEL PUMP SWITCH FUEL COCK STARTER BUTTON THROTTLE CONTROL R/H PROP SPEED CONTROL MIXTURE CONTROL MAGNETO SWITCH HEATING CONTROL ADF VORIILS ACC~LERCMETER A I R VENT ( 2 OFF) COLD A I R TO CABIN CONTROL ( 2 OFF) MKR BEACON RECEIVER TURN CO-ORDINATOR DIRECTIONAL GYRO VERTICAL SPEED INDICATOR ALTIMETER M T I F I C A L HORIZON AIRSPEED INDICATOR VACUUM GAUGE STALL WARNING L I G H T STARTER ENGAGED W . 12. 21. 7. OUTSIDE A I R TEMPERATURE GAUGE 3 8 A . 20. 23. AMMETER 4 5 . DIMMER SWITCH 4 6 . RADIO PANEL 3 5 .T67M200/FM . 11. MOMENTARY BUTTON SMOKE GEN. 16. FUEL CONTENTS-GAUGEILEFT TANK 4 2 . 34. EXCITATION SWITCH 2. 22. 8. 5. PRESS TO TRANSMIT SWITCH P.4D INSTRUMENT PANEL (MOD 3 4 1 ) KEY 1. 17. 26. FUEL CONTENTS GAUGEIRIGHT TANK 4 3 . C I R C U I T BREAKERS 4 7 . 3 2 . LANDING L I G H T S SWITCH 2 8 . 25. L I G H T 13.PILOTS NOTES FIREFLY T67M200 8. CYL. 9. NAV L I G H T S SWITCH 2 9 . P R E S S TO TEST STRUCT TEMP 3 9 . HEATED P I T O T SWITCH 3 6 . ALTERNATOR OUTPUT C I R C U I T BREAKER 4 8 . MAGNETIC COMPASS 5 0 . CLOCK 33. MAP L I G H T SWITCH 31. 18. 4. HEAD TEMPERATURE GAUGE 4 4 . ALTERNATOR WARNING L I G H T 2 7 . ARM SWITCH SMOKE GEN.. 10. THROTTLE CONTROL L / H 4 9 . 19. TACHOUR METER 3 7 . O I L PRESSURE GAUGE 4 0 . 14. O I L TEMP GAUGE 4 1 . MASTER SWITCH 3.8-70/8D > < Apri 1 1998 A8 TP . 6. MANIFOLD/FUEL PRESSURE GAUGE 3 8 OUTSIDE A I R TEMPERATURE GAUGE 3 8 A PRESS TO TEST STRUCT TEMP 39. .A\.4 INSTRUMENT PANEL ( B A S I C A/C) E X C I T A T I O N SWITCH MASTER SWITCH FUEL PUMP SWITCH FUEL COCK STARTER BUTTON THROTTLE CONTROL R/H PROP SPEED CONTROL MIXTURE CONTROL MAGNETO SWITCH HEATING CONTROL ADF VOR/ILS ACCELEROMETER A I R VENT 12 OFF. ~- - A p r i l 1998 A8 TP . . . L I G H T 70 ~ - ALTERNATOR WARNING L I G H T LANDING LIGHTS SWITCH NAV LIGHTS SWITCH STROBE L I G H T SWITCH MAP L I G H T SWITCH STOP WATCH C L I P CLOCK CANOPY RELEASE/LOCKING LEVER RADIO PANEL HEATED P I T O T SWITCH TACHOUR METER . T67M200/FM . HEAD TEMPERATURE GAUGE AMMETER DIMMER SWITCH C I R C U I T BREAKERS ALTERNATOR OUTPUT C I R C U I T BREAK THROTTLE CONTROL L / H MAGNETIC COMPASS ' . .( 2 OFF) ~ ...NCONTRnl. .. O I L PRESSURE GAUGE O I L TEMP GAUGE FUEL CONTENTS GAUGE/LEFT TANK FUEL CONTENTS GAUGEIRIGHT TANK CYL..IIATION LTD PILOTS NOTES FIREFLY T67M200 8.. COLD A I R C A-R .MKR BEACON RECEIVER TURN CO-ORDINATOR ( 2 OFF) DIRECTIONAL GYRO VERTICAL SPEED INDICATOR ALTIMETER ( 2 OFF) ARTIFICAL HORIZO~ (2 OFF) AIRSPEED INDICATOR ( 2 OFF) VACUUM GAUGE STALL WARNING L I G H T STARTER ENGAGED W... 5 .CENTRE CONSOLE FLAPS TAKE OFf LANDING HEADPHONES 1.T67M200/FM . 6- P. 3.A\llATlON LTO PILOTS NOTES FIREFLY T67M200 8. FLAP CONTROL LEVER 2.8-9/10 > < A p r i l 1998 A8 TP . KEY TRIMMER HANDWHEEL TRIMMER P O S I T I O N IND. Company: Date: .August 1999 Amendment No 9 to 'TP T67M200lFM FIREFLY T67M200 PILOTS NOTES REMOVAL AND INSERTION OF LEAVES REMOVE Pages 0-1 1 and 0-12 (1 leaf) Section 9 contents (1 leaf) INSERT Pages 0-1 1 and 0-12 (1 leaf) Section 9 contents (1 leaf) O~erators with Mod 734AIC fitted only Supplement D (2 leaves) AMENDMENT RECORD SHEET Record the incorporation of this amendment list and destroy this instruction sheet THIS INSTRUCTION SHEET Complete the details below and return this sheet to Slingsby Aviation Ltd Technical Publication Department I acknowledge receipt of Amendment No 9 to TP T67M200lFM Signed. . PILOTS NOTES FIREFLY T67M200 AMENDMENT HIGHLIGHTS A complete new sheet will be issued with each amendment list.0-11 CAA Approved August 1999 A9 TP . the previous 2 permanent amendment 1 ists will be retained. Amendment List No: 9 Subject Pages (s) 0-11 (this page) Section 9 Contents Amendment Highlights Black and Yellow Colour Scheme (Mod 734A/C) NOTE Only aircraft with Mod 734A/C incorporated will be supplied with the supplement pages D-1 to D-314. P.T67M200/FM . PILOTS NOTES FIREFLY T67M200 INTENTIONALLY BLANK CAA Approved A u g u s t 1 9 9 9 A9 TP .T67M200/FM . PILOTS NOTES FIREFLY T67M200 Section 2 Parauraph 2.1 of 3 CAA Approved November 2004 T67M200/FM .7 Section 2 Paraqraph 2.5. Aerobatic manoeuvres Slow roll S t a l l t u r n entry S t a l l turn rotate Loop Roll off the top Flick roll max Spin - up t o a l l up weight 975kg (2150 ib) E n t r y Speeds (kts) (IAS) 110 110 50 115 125 70 See Paragraph 3.6.5 Limitations f o r Aerobatics Aerobatic manoeuvres w i t h flaps extended are not permitted. Tail Slides and Inverted Spins are not permitted.s t r u c t temp below 50°C Flaps up Flaps down +6g -39 +2g -1g When structural temperature reaches 50°C o r more DO NOT carry out aerobatics.1 Instrument Markinqs 9AT/Structural Temperature Gauqe Structure temperature Maxi mum Red Line TAL 10/P. 'g' Limitation . . 1 Instrument Markinqs OAT/Structural Temperature Gauqe S t r u c t u r e temperature Maximum Red L i n e 42°C P.PILOTS NOTES FIREFLY T67M200 SUPPLEMENT D BLACK AND YELLOW COLOUR SCHEME (MOD 734AlC) CONTENTS 9.6.D-1 CAA Approved August 1999 A9 TP .D.5 L i m i t a t i o n s f o r Aerobatics Aerobatic manoeuvres w i t h f l a p s extended are n o t permitted.D. 'go Limitation - s t r u c t temp below 42°C +6g -39 +29 . T a i l S l i d e s and I n v e r t e d Spins are n o t permitted.7 Slow r o l l Stall turn entry Sta!! t u r n r o t a t e Loop R o l l o f f the t o p F l i c k r o l l max Spin Section 2 Paraqraph 2.1 Revised S t r u c t u r a l Temperature L i m i t a t i o n s 9. Aerobatic manoeuvres - up t o a l l up weight 975kg (2150 l b ) E n t r y Speeds ( k t s ) (IAS) 110 110 50 115 125 70 See Paragraph 3.1 REVISED STRUCTURAL TEMPERATURE LIMITATIONS The temperatures given below o v e r r i d e those given i n t h e referenced paragraph numbers i n t h e r e l e v a n t sections o f t h i s manual.l g Flaps up Flaps down When s t r u c t u r a l temperature reaches 42°C o r more DO NOT c a r r y out aerobatics. Section 2 Paraqraph 2.5.T67M200/FM . DAY AND FOR NIGHT F i I G H T AEROBATIC MANOEUVRES SLOW ROLL STALL TURN ENTRY STALL TURN ROTATE LOOP ROLL OFF THE TOP F L I C K ROLL MAX SPIN ABOVE 9 7 5 K g AEROBATICS PROHIBITED +3.69 +2g -1g STRUCTURAL TEMPERATURE BELOW 42°C ABOVE 42°C +6g +2g -39 -1g +4.D-2 CAA A p p r o v e d A u g u s t 1 9 9 9 A9 TP .49 +2g -29 -1g 1 5 0 F T (46m) - UP TO A L L UP WEIGHT 9 7 5 K g (2150 l b s ) ENTRY SPEEDS K I A S 110 110 50 120 140 80 SEE F L I G H T MANUAL P. POST MOD 734A/C LIMITATIONS NO SMOKING VNE MANOEUVRING SPEED VA FLAP L I M I T I N G SPEEDS TAKEOFF P O S I T I O N (18') LANDING P O S I T I O N (40') 120 KIAS 9 8 KIAS 180 K I A S 140 KIAS I MAX TOTAL WEIGHT AUTHORISED (TAKE OFF) MAX TOTAL WEIGHT AUTHORISED (LANDING) MAX LOADS UP TO 9 7 5 Kg (FLIGHT PROHIBITED ABOVE 45OC) FLAPS UP FLAPS DOWN MAX LOADS ABOVE 9 7 5 K g (FLIGHT PROHIBITED ABOVE 4Z°C) FLAPS UP FLAPS DOWN ALTITUDE LOSS I N A STALL RECOVERY F L I G H T I N T O KNOWN I C I N G CONDITIONS PROHIBITED AIRCRAFT CERTIFICATED FOR F L I G H T I N IMC.8g -1.PILOTS NOTES FIREFLY T67M200 S e c t i o n 2 P a r a 2.2 Labels The f o l l o w i n g information i s t o be furnished on placards w e l l w i t h i n sight o f pilot.6.T67M200/FM . 8g -1.2 o f 3 CAA Approved November 2004 T67M200/FM .2 Labe'ls The f o l l o w i n g i n f o r m a t i o n i s t o be furnished on placards w e l l w i t h i n sight o f pi lot.69 +2g -1g TAL 10/P.6.PILOTS NOTES FIREFLY T67MZ00 Section 2 Para 2. !=!AX LOACS UP T0 '175 Kg (FLIGHT PROHIBITED ABOVE 55°C) FLAPS UP FLAPS D W ON MAX LOADS ABOVE 975 Kg (FLIGHT PROHIBITED ABOVE 50°C) FLAPS UP FLAPS D W ON STRUCTURAL TEHPERATURE BELOW 50°C ABOVE 50°C +6g +2g -39 -1g +4.4g +2g -2g -1g +3. . 3 o f 3 C A Approved A November 2004 T67M2001FM .-'{SLINGSBY LTo AvlATloN PILOTS NOTES FIREFLY T67M200 O Canogy Transparency Mod 734 A i r c r a f t n THIS AIRCRAFl HAS GEOGRAPHICAL RESTRICTIONS. ITALY and SPAIN i n r e s t r i c t e d t o north o f 43"N Latitude. TAL 101P. REFER TO FLIGHT WAIlUAL SUPPLMEWT D Section 2 Paraaraph 2.7 Operational Limitations Geoaraphi cal Restriction Mod 734 A i r c r a f t This a i r c r a f t i s r e s t r i c t e d t o operation w i t h i n these nations: BELGIUM CZRCH REPUBLIC DN AK EMR ESTONIA FINLAND GR AY EMN HUNGARY IRELAND LATVIA LITHUNIA LUXEMBOURG NETHERLANDS NR A O WY POLAND S t OVAKIA SLOVENIA S EE WDN SUITZERLAND UNITED KINGDOM Operation w i t h i n FRANCE. . .1.314 CAA Approved August 1999 A9 TP . .on OAT gauge below 42°C P.T67M200/FM .AVIATION LTO PILOTS NOTES FIREFLY T67M200 Post Mod 734A/C THIS AIRCRAFT I S RESTRICTED TO OPERATION I N THE U. D.K. . ONLY I I Section 3 P a r a q r a ~ h3. . .1 I n i t i a l Check (Structural temperature i n hot conditions) . Rotary switch Check s t r u c t u r a l temperature Left and Right . . . T67M200/FM . > - Mod 416A and 4168 A i r c r a f t D. C. Black and Yellow Colour Scheme (Mod 7'34A/C) August 1999 A9 TP .PILOTS NOTES FIREFLY T67M200 SECTION 9 SUPPLEMENTS CONTENTS n ... !ding T i p F l a r e s Mad ?3?B A i r c r a f t Large E x t e r n a l L e t t e r s Mod 374 A i r c r a f t Gel-Type B a t t e r y RG4-11M B. 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