EFTA00812370.pdf

r SE0UIENCEo.IUMBER 11111M110111111 ACTION CARD ROUTINE PROJECT 6030187 166-CAV-AMO-2014 1999M weon:Itnet 9(Ratser tat ra R w iarAArr Qr.) Wt.' 00i 71 us COV COM 737 324471 vP4B8 14 GIMES m.,..cemOci,A1Tha 'tweet 10.9%18 482100 at. icre 807 AWR.9 NA NA Ill.CrO,at DEG. La. 0£0 , YA.C4 REPAIt 46 NECK YES S2 MiC a1 0. VA.' K: 0 it yrs 6) ..,41 3 1 floill y -2-4,-7 DISCREPANCY. O n, (" -7 *". Customer request- perform test 5 engine runs RESOLUTION. MECH INS? PLUGS?... I `1 61 ire....1 Cron. Irkr.... C-orvdcir cr.rel 3r-rt..x.k_ ;n 3ro 7.4",e ' Sa Per"%c•-• iliNC-- r eartenkr OAR. COirti , I ttuelLS / ") r2 14 CDT tapani 737 Ainn. a-rt-a2 „ze.-7,772 ADeerg- 1O0O qc..[ oc -foci cror-t. ruiticA. Air CD° OX13€3e0( Pc r cot- r^stic c,.. Poc-x_r i:LS Li". 4 I.-X.- C.-kt.r.,....L u(.,,;•-. 4:.A..... 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COMPLETE THE ATTACHED FORM ENGINE DATA AND RECORD SHEET FIGURE 501/71-00-00.990.803-F00 (SHEET 1OF 2) AND RECORD IN THE ADDITIONAL DATA REQUIREMENTS SECTION, THE BAROMETRIC VALUE AT THE TIME OF RUN. P/N: S/N • LABOR HRS: COST: REPAIR STATION' CORRECTIVE ACTION: Pfr Pot 1b 5 / ES r afrift- fr__eveihded la 43 P.' _ AIn fn TASK I 00-_00 - 100 - - fop. TECHNICIAN SIGNATURE' Z- ";;;;;C'esIC KIND Of CERTIFICATE & NO • 166-CAY-AMO-2014 INSPECTED BY: ,••Nti ,• 24:J KIND OF CERTIFICATE & NO • 166-CAY-AMO-2014 30-MAY-2017 0 CAMP SYSTEMS 1 of 1 WID: 24560128.1 Total Pages • Initial . Return completed copy via email to EFTA00812371  Operator: aOsco AVIATION Work Card No.: 170530-2-2 Serial No: 32806 (YD405) Model: 737-8AWF31 REVISION 20 RegNo. VP-CBB Date Loggec: 30-MAY-2017 Workorder No.: WO 170530088 DATE(DD/PIMM(YTYY) HOURS CYCLES Due At Accomplished ul M o gi I It.,VIS-le 4192 _1 Task No Task Description 170530-2-2 PERFORM ACCELERATION CHECK PER AMM TASK 71.00-0 0-700.824-F00 (TEST 8) P/N: S/N: LABOR HRS: COST: REPAIR STATION' CORRECTIVE ACTION' ( fr eer/A r 3 &Ca feito-n? ter: I PIFr Am AS I -00 -OO ••110O -•v34—A2,9 #s7-- bnezt n71) .4m,1 TECHNICIAN SIG KIND OF CERTIFICATE & NO.- 166-CAY-AMO-2014 INSPECTED BY: :a y es- 3., etil KIND Of CERTIFICATE & NO.- 166-CAY-AMO-21114 30-MAY -2017 CD CAMP SYSTEMS WID: 24560130-1 1 of I Total Pages- Initial Return completed copy via email to EFTA00812372  CAMP ,_CHEE.1 Operator: BOSCO AVIATION Work Card No.: 170530-3-3 I Serial No: 32806 (YD405) Model: 737-8AWB3 REVISION 20 RegNo. VP-C8B Date logged. Workorder No.: WO 170530am DATE(DOMMM/YYYY) CYCUES DueAt ACcoallished log*.Le Task No Task Dosaiption 170530-3-3 POWER ASSURANCE CHECK AT ALL THREE SPEEDS (65, 70 AND 75% NI) P/N: LABOR HRS: COST: REPAIR STATION' CORRECTNEACToN: tot D ASS4Itaroce qt.oo -Po- loo -813 - Foo cingeeks- Per 8')3r) /1-rn in afren 7 TECHNICIAN SIG /„.. .a.____ ic KIND Of CERTIFICATE & NO • 166-CM-A610-2014 INSPECTED BY: D"A t2 KIND OF CERTIFICATE & NO • 166-CAY-AMO-2014 30-MAV-2017 0 CAMP SYSTEMS WID: 24560131.1 1 of 1 Total Pages , Initial Return completed copy via email to EFTA00812373  Insi•••••••Ier...„/- clif4P Work Order Tally Sheet Report SERIAL: 32806 (YD405) REGNO : VP-C88 DATE IN : UTC:5/30/2017 MODEL NAME : BB) 737-7001GW/-8 DATE OUT : UTC:5/30/2017 11:00:00 PM 00/-900ER WORK ORDER C: WO 17053003B ICAO : KIND SERVICE CENTER : COMLUX MALTA LTD. ITEM NO DESCRIPTION TECHNICIAN INSPECTOR 170530-1-1 ENGINE. PERFORM TEST 5- POWER 4 71-0O.O0-700-813-F00. COMPLETE THEASSURANCE CHECK AS PER 8737 AMM TASK TECH : ATTA efrOPC INSP SHEET FIGURE 501,71-00-00-990-803-F00 CHED FORM ENGINE DATA AND RECORD ADDITIONAL DATA REQUIREMENTS SEC (SHEET 1 OF 2) AND RECORD IN THE v.-411? OF RUN. TION. THE BAROMETRIC VALUE AT THE TIME 170530-2-2 ENGINE, PERFORM ACCELERATION CHE (TEST 8) CK PER AMM TASK 71.00.00-700.824-F0 0 Srn t :747.2...-<?5- • TECH u *CC*./a INSP 170530-3-3 ENGINE. POWER ASSURANCE CHE CK AT ALL THREE SPEEDS (85. 70 AND 75% NI) Xfaree7 - TECH : eiL—O-66O/O INSP : 30MAY-2017 0 CAMP SYSTEMS 1 of 1 EFTA00812374  CFM56 ENGINES (CFM56-7) I AirdtZEIA,S 1 737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL DATE 30 MAY -2-0 n AIRPLANE DA TA ENGINE DATA AIRPLANE NO. FUEL TYPE ENG ENGINE MODEL ENGINE 5/N VP- C. e (3 POS HMI P/N -see--f-m- 3£-r A TAM FUEL QUANTI T Y 71S..2-7/ AZ 14:59v1.1s- p6k)mtp9vp.2v NO. 1 "709'0 2 762,7/£3.3 f-3L;`1,1 53 7 asshi-W13c5- -^—' NO. 2 7'100 REMARK C TR BARD PC.B.S.S ; 3D. pet. 2 720 gE(... resi TA.,' o'veztt)cluirmiehrkPce. pQ L. Pcx. 2. Weir 07Y&10ceni i car ;4,2 et». TOT AL 2 7) bo ENGINE START DA TA START LEVER ADV. ENG INITIAL LIGNTUP STARTER MAX. MAX .• TIME TO OIL POS MOTORING TINE rc TIRE CUTOUT EGT VIBRATION xN2 FF IDLE (SEC> <SEC) CZN2/ < 'O <SEC> OTT TENS' PRESS (UNITS) I .713 58.3 s-30•tic:3 LS tg 2 • 75' 3'! .1 Sb s"15:3 659 fl 77 HYDRAULICS 3O • 1 ADDITIONAL DATA REQUIREMENTS FT° Hy') HID SYS PRESS ENG SYS CITY En P05 (MOP s I a e _ TEST NO. 5 .- POVER ASSURANCE CHECK ENG TARGET OAT RECORDED VALUES POS OF (,)0) FN I '.142 EGI 6s- g ' 2 75 75 k6.1 (2‘.f I,6 1 bbl P 4•I S Se. R9•'( .5"433 1 -75- -71 1 -71. I 7c 421 90.9 I, 17 2 7c '711 71.1 91.0 61C, I 7S" 761 -7E.1 q )-$ 41 tori 7$ 7b.i - lb 1 9). • 3. - _/S5 - G4146$ S0006511TD0_VI Engine Data and Record Sheet Figure 501/71-00-00.990-803-F00 (Sheet 1 of 2) EFFECTIVITY BBJ ALL 71-00-00 Page 507 D633A101-B8J AGEING PIXOPRIZ~ • Cer•Vi ~Pei Oct 15/2015 Wa" • he Fil•OWM OWak EFTA00812375  C A MP Andibl.••••••••"Ir Work Order Contents Report SERIAL: 32806 (YD40S) REGNO W-(38 MODEL NAME : EEO 737-7001GW/-800/-900ER DATE IN : UTC:30-May-2017 12:00 AM DATE OUT WORK ORDER alt: WO 170530088 : UTC:30-May-2017 11:00 PM IOO : KIND SERVICE CENTER : COMLUX MALTA LTD. WOMKCARD DESCRIPTION STATUS M 1705304-1 ENGINE, PERFORM TEST S - POWER ASSURANCE CHECK AS PER VP OPEN COMPLETE DIE ATTACHED FOOT ENGINE DATA AND RECORD SHEET AMM TASK 71-0040-7C0-613-F00. 1OF 2) AND RECORD IN THE ADDITIONAL DATA REQUIREMENTS FIGURE 501771-00-00-990-803400 (SHEET TIME OF RUN. SECTION, THE SAROVETRIC VALUE AT THE 2.0 1705304-2 ENGINE, PERFORM ACCELERATION CITEOC PER AMM TASK 71-00-00-700424400 (TESTS) OPEN 3.0 170530-3-3 MINE, POWER ASSURANCE CHECK AT AU. THREE SPEEDS (65, 70 AND 75%01) OPEN Proparmt By: Siwkhart DM*: &en& &Hart 30 Okay 2017 Approved By: Date: 30-MAY-2017 CAMP SYSTEMS 1 at 1 EFTA00812376 L CFM56 ENGINES (CFM56-7) gifirosArAfc 737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL (b) Look at the inside surfaces of the fan cowl panels or thrust reverser as applicable for new fuel, oil or hydraulic stains. (c) Do the leak check again after you replace or repair the tubes, tube flanges. fittings or components. F. Put the Airplane Back to Its Usual Condition SUITASK 7140-0.410.013•00 WARNING: OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS. INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (1) If they were opened, do this task: Close the Thrust Reverser (Selection), TASK 78-31-00-010.804-F00. SUBTASK 7140.00.410.014-F00 (2) Do this task: Close the Fan Cowl Panels. TASK 71-11-02-410-801-F00. END OF TASK TASK 71-00-00-700-813-F00 7. Test 5 - Power Assurance Check (Figure 503, Figure 504. and Figure 505) A. General (1) The Power Assurance Check is not a good test for performance analysis of the engine. Do not use only the Power Assurance Check to accept or reject an engine. The power assurance run is usually not sufficiently stable to accurately calculate the engine's health. You can get a more reliable performance analysis by doing a test cell operation or on-wing performance trend monitoring. (2) Do this test to make sure the engine will get takeoff power without the EGT or N2 at redline limits. (3) For a specific %N1, this check will calculate the maximum EGT and the %N2 target values. (4) This check can be done at one of three different N1 speeds: t is recommended that the initial check be done at 65% N1. If th e , is operator policy, men do a subsequent test at the higher N1 speeds. (5) This procedure will also give the steps to adjust the EGT limit (make an altitude correction of the maximum EGT) when you operate the airplane at an airport above sea level. The actual EGT margin is based on the airplane route structure. B. References Reference Title 24-22-00-860-811 Supply Electrical Power (P/B 201) 71-00-00-700-819-F00 Stop the Engine Procedure (Usual Engine Stop) (P/B 201) 71-00-00-800-807-F00 Start the Engine Procedure (Selection) (P/B 201) 73-21-00-700-808-F00 IDENT/CONFIG (P/8 501) 73-21-0D-740-803-F00 EEC BITE TEST - RECENT FAULTS (P/B 501) C. Tools/Equipment Reference Description STD-1122 Thermometer - Alcohol/Mercury (or equivalent meter meets task requirements) EFFECTIVITY BBJ ALL 71-00-00 Page 520 D633A101-BBJ Jun 15/2015 BOEING OROVRIETAPY .Cocrighe t'unp.c.thee Mot • See Me Dam lee delak EFTA00812377 L CFM56 ENGINES (CFM56.7) 0 _4117E/ACC 737-600,70018001900 AIRCRAFT MAINTENANCE MANUAL D. Power Assurance Check SUBTASK 114040-970-00S-F00 CAUTION: DO NOT USE THE TOTAL TEMPERATURE INDICATION FROM THE AIRPLANE FOR THE AMBIENT AIR TEMPERATURE. THIS WILL PREVENT AN INCORRECT TRIM TARGET SELECTION. CAUTION: DO NOT PUT A MERCURY THERMOMETER ON THE AIRPLANE. MERCURY (FROM A BROKEN THERMOMETER) CAN CAUSE DAMAGE TO THE AIRPLANE COMPONENTS. (1) Use a thermometer, STD-1122 to get the ambient air temperature (OAT) in the shade of the nose wheel well. (a) Record the OAT on the data sheet. SUBTASK T14040470404-F00 (2) Use the OAT to get the %N1 Target speed, the Max EGT and Max %N2 for the applicable engine model and thrust rating (Figure 503, Figure 504. and Figure 505). NOTE: The 7826 and 7B26/B1 engine models are equivalent in thrust rating. The 7827 and e ngine models are equivalent in thrust rating. (a) Record the %N1 Target, Max EGT and Max %N2 on the data sheet. (b) To do a check of the thrust rating, refer to the Ident/Config page, do this task: IDENT/CONFIG. TASK 73-21-00-700-808-F00 1) Record the trim level for the N1 Modifier Adjustment used in the Test Results. SUBTASS 7tMMM04OtP00 (3) Do this task: Supply Electrical Power. TASK 24-22-00-860-811. SUBTASK 1140-00460401400 WARNING: MAKE SURE YOU OBEY ALL THE INSTRUCTIONS AND PRECAUTIONS WHEN YOU OPERATE AN ENGINE AT HIGH POWER. REFER TO THE ENGINE GROUND SAFETY PRECAUTIONS TASK. IF YOU DO NOT OBEY THE INSTRUCTIONS AND PRECAUTIONS, INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (4) Do this task: Start the Engine Procedure (Selection), TASK 71-00-00-800-807-F00. (a) Make sure the BLEED 1 and BLEED 2 switches are in the OFF position. (b) Set the applicable GEN switch to the OFF position and release. NOTE: This will remove the load from the IDG, if it is not already removed. 1) Make sure the applicable GEN OFF BUS light comes on. (c) Let the engine become stable at the idle-power position for five minutes. SUBTASK T140.00440.0104, 00 (5) Make sure that the applicable switches on the overhead panel. P5. are in the OFF position: (a) WING ANTI-ICE (b) ENG ANTI-ICE 1 or 2. SUBTASK 714040460-175400 (6) Make sure the PROBE HEAT "A" or "Be switch on the overhead panel, P5, is in the ON position. NOTE: For engine operation at high power, the EEC can go into Alternate Mode operation if neither pitot probe is heated. EFFECTIVITY 88J ALL 71-00-00 Page 521 0633A101-BBJ Jun 15/2015 SOONG PROANETARY - CoarAil QUngNWf AtoA. Ste EA 030* fre delas EFTA00812378 L CFM56 ENGINES (CFM56-7) gifiroreArc 737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL SUSTAIN( 71•00•00400411400 (7) Monitor all engine parameters. (a) Carefully monitor the EGT and N2 indications. SUBTASK 71-00•00469•165400 (8) Slowly move the applicable forward thrust lever to the N1 target speed that you got for the applicable MPA power level: (a) It is recommended that the 1ni is check e done at 65% N1. If that test fails. or if it is operator policy, then do a subsequent test at the higher N1 speeds. (b) If this is a subsequent check at a higher speed, make sure the engine runs at the idle-power position for a minimum of 10 minutes before you increase the engine speed again. SUBTASK 71•00-00410-034400 (9) Let the engine become stable at this power assurance target for a SUBTASK TI•40•06410496400 (10) arameters from the power assurance target on the data s ee . SUSTASK 7140-00-SWISAFOO (11) Slowly move the applicable forward thrust lever to the idle-power position. SUSTASK 7140404704$400 (12) When this check is complete. make a decision if an additional check is necessary as follows: (a) If the test was satisfactory, you can do one of these steps: 1) Do the above check again at the higher N1 speed; or, 2) Continue to the steps to stop the engine. BBJ 001-004, 006, 008-018, 020, 021, 023-026. 028-037.039, 040, 042, 043, 061, 064, 068, 070-072, 075. 076, 078, 079, 082, 083, 086, 087, 091-095, 097-099, 111-114, 116-119, 121, 122, 124, 125, 401, 404, 405, 407, 409, 410, 415417, 901-905 PRE SB 737.30A1063 a) Put the Probe Heat "A" and "B" switches on the overhead panel. P5, to the OFF position. BBJ 005, 007, 019, 022, 027, 038, 041, 062, 063, 066, 073, 077. 080, 085, 096, 120, 123, 126-399, 402, 403, 406, 408, 412.414, 418422, 906-999; BBJ 001-004, 006, 008-018, 020. 021, 023-026, 028-037, 039, 040, 042, 043, 061, 064, 068, 070-072, 075, 076, 078, 079, 082, 083, 086, 087, 091-095, 097-099, 111-114, 116-119, 121. 122, 124, 125, 401, 404, 405, 407, 409, 410, 415.417, 901-905 POST SB 737-30A1063 b) Put the Probe Heat "A" and "B" switches on the overhead panel, P5. to the AUTO position. BBJ ALL c) Do this task: Stop the Engine Procedure (Usual Engine Stop), TASK 71-00-00.700-819-F00. (b) If the test is not satisfactory, do the above check again at the higher N1 speed. EFFECTIVITY 71-00-00 BBJ ALL I O633A101-MU SOONG PRCORIETART • Ctenhi D kfrptainlind renri • $. US Wei S 444M Page 522 Jun 15/2016 EFTA00812379  L CFM56 ENGINES (CFM56-7) Z I tirt7LFIAor 737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL (a) Use these steps to find if there is a positive or negative difference between the N1 target and the N1 record: 1) If the N1 target is more than the N1 record, there is a positive difference. 2) If the N1 target Is less than the N1 record, there is a negative difference. (b) For each 0.1% of positive difference In N1, 0.8 degrees C must be added to the EGT, and 0.03% must be added to the N2 value that you recorded during the test. (c) For each 0.1% of negative difference in N1, 0.8 degrees C must be subtracted from the EGT, and 0.03% must be subtracted from the N2 value that you recorded during the test. Table 503/71-00-00-993-925-F00 Adjustments for Difference between N1 Target and N1 Record Parameter Correction Value/0.1 %N1 EGT 0.8 Degrees C N2 0.03% (d) If the engine has been configured with 7BUI or higher version of the EEC software, use kT6 G 27/83) the data for the applicable rating in the table below to adjust the N2 margin (Table 504). 5 rLE eg9 Yin NOTE: LT (7cs-1 Table 504/71-00-00-993-932-F00 Rating NT Margin Adjustment" VI 3,,,f 38r►`7`' 7924 or 7824/3 1.2 792291 or 7822/381 1.3% 7822 or 7822/3 1.5% g-Theets-----/ 1.7% •[ ie adjustment is applicable to SAC and DAC engines. [2) N2 Margin (Adjusted) • Calculated N2 Margin - N2 Margin Adjustment (e) This is an Example Calculation for the MPA Test Table - 70% Nt of the 7620 engine for an OAT of 10 degrees C (Figure 504): BBJ ALL; AIRPLANES WITH SINGLE ANNULAR COMBUSTOR (SAC) ENGINES Table 505171-00.00-993-908-F00 FROM MPA TEST TABLE - 70% Ni. OAT OF 10 DEG C N1 TARGET = 69.4%. EGT MAX =726 DEG C. N2 MAX = 91.8% TEST DATA RECORDS. N1 RECORD = 69.7%, EGT RECORD = 695 DEG C N2 RECORD = 81% N1 TARGET < N1 RECORD, A NEGATIVE DIFFERENCE al DIFF = N1 RECORD - N1 TARGET = 69.7 - 69.4 = 0.3 EGT ADJ = EGT RECORD - (0.8/0.1)(N1 DIFF) = 695 - (0.8/0.1X0.3) = 692.6 DEG C N2 ADJ = N2 RECORD - (0.03/0.1XN1 DIFF) = 81% - (0.03/0.1X0.3) = 80.9% FIND EGTAND N2 MARGINS WITH THE VALUES OF EGTADJ AND N2 ADJ EGT MARGIN • EGT MAX - EGTADJ • 726 - 692.6 • 33.4 DEG C N2 MARGIN • N2 MAX • N2 ADJ • 91.8 - 80.9 • 10.9% EFFECTIVITY BBJ ALL 71-00-00 Page 523 D633A101-BBJ Jun 15/2016 BCCPC PROGRETARY .Cysylip , Ova Mel Work • Sof Ode pne to, details EFTA00812380 L CFM56 ENGINES (CFM56-7) gLATOSZAW 737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL BBJ ALL; AIRPLANES WITH SINGLE ANNULAR COMBUSTOR (SAC) ENGINES (Continued) Table 505/71-00-00-993-908-F00 (Continued) N2 Margin (Adjusted) = 10.9% (Calculated N2 Margin) - 1.7% (N2 Margin Adjustment) = 92%. I II12) ill Get the N2 margin adjustment from Table 504 (21 Adjust the N2 margin for engines configured with 7BUI or higher software. 88.1 ALL SUSTASK 114040704 3/400 (2) To adjust the EGT margin for altitude. do these steps: (a) Find the Altitude Correction Adjustment for the applicable engine and altitude in the table. 1) Use the highest altitude on the airplane's route structure. 2) The EGT corrections shown are for takeoff worst case flight condition and Includes ambient temperature and altitude effects. 3) Linear interpolation is necessary for altitudes between the table values. (b) Subtract the altitude adjustment value from the calculated EGT margin. Table 506/71-00-00-993-911-F00 Altitude Adjustment Factors ALTITUDE ENGINE MODEL I I) FEET 7820 7622 7822/81 7824 7624/61 7826 7626/82 7827 7827161 7826/81 'CO 24 0 0 0 5 7 0 0 0 24 0 0 0 5 7 0 0 1000 24 0 0 0 6 7 0 0 2000 24 0 0 0 7 8 0 0 3000 24 0 0 0 7 8 0 0 4000 24 0 0 0 8 6 0 0 5000 24 0 0 0 5 4 0 0 6000 18 0 0 0 3 0 0 0 7000 12 0 0 0 0 0 0 0 8000 6 0 0 0 0 0 0 0 9000 0 0 0 0 0 0 0 0 >9000 0 0 0 0 0 0 0 0 LE . /3F. AND -76E RATINGS (c) To continue the same Examp e Calculation for altitude adjustment, assume the highest airport is at 4000 feet. BBJ ALL; AIRPLANES WITH SINGLE ANNULAR COMBUSTOR (SAC) ENGINES Table 507/71-00-00.993-912-F00 FOR A 7820. 4000 FT ALTITUDE. ALTITUDE ADJUSTMENT FACTOR = 24 EGT MARGIN ALT = EGT MARGIN - ALTITUDE ADJUSTMENT FACTOR EFFECTIVITY BBJ ALL 71-00-00 Page 524 0633A101-BBJ Jun 15/2016 scow pRopissusy.sopr o., Unpubli1W5 Wylt • St. lib Per 10,600. 3 EFTA00812381  CFM56 ENGINES (CFM56-7) cofirostsca 737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL BB./ ALL; AIRPLANES WITH SINGLE ANNULAR COMBUSTOR (SAC) ENGINES (Continued) Table 507/71-00-00.993-912-F00 (Continued) - 33.4 - 24 = 9.4 DEG C BB.) ALL SWUM 71.0.WM.OSNW (3) To adjust the EGT margin for N1 modifiers, do these steps: (a) Find the N1 Modifier Adjustment for the applicable engine model and trim level. 1) To find the trim level, do this task: IDENT/CONFIG, TASK 73-21-00-700-808-F00. (b) Add the adjustment to the calculated EGT margin. Table 508/71.00-00-993409-F00 N1 Modifier Adjustments ENGINE MODEL in TRIM 7820 7822 7822/81 7824