dent map form no sj tsd 027

ENTRY DETAILSCLEARANCE DETAILS

ALLOWABLE DAMAGE REPAIR

DATE GRID REF DESCRIPTION OF DAMAGE SRM REF AUTH TLP REF REMARKS TLP REF AUTH DATE REMARKS

21/8/06 -- -- Fwd cargo door skin dent 52-30-01 GMF -- -- -- -- -- --

21/8/06 -- -- RH Wing L/E skin dent 51-70-01 GMF -- -- -- -- -- with in limits

21/8/06 -- -- 51-70-02 GMF -- -- -- -- -- --

21/8/06 -- -- 53-00-01 GMF -- -- -- -- -- --

21/8/06 -- -- Aft cargo door flaper dent 51-70-01 GMF -- -- -- -- -- --

21/8/06 -- -- 53-00-01 GMF -- -- -- -- -- --

21/8/06 -- -- LH Wing outb aft flap dent -- GMF -- -- -- -- -- --

17.02.08 -- -- -- -- -- -- -- -- --

DAMAGE/REPAIR MAPPING CHART RECORD

FormNo SJ/TSD/027 Issue 1

AIRCRAFT REG: VT-SPC

CHART NO.

SRM/DESIGN REF

D=0.046"W=2"D=0.0180"W=4"L=10"

RH Wing inb main flap skin dent

D=0.052"W=1"

Lower fuselage dkin dent BTW STA 807-827 STR 25-27 RH

D=0.048"W=2.3"L=6.2"D=0.135W=1.5"

Fuselage skin dent BTW STA 1016-1040 STR 15-16 LH

D=0.026"W=2.2"D=0.067"W=2.2"

RH HORIZONTAL STABLIZER LEADING EDGE DENT

L=1.5"W=0.7"Y=0.07"

permanent repair at 5000 hrs.

ENTRY DETAILSCLEARANCE DETAILS

ALLOWABLE DAMAGE REPAIR

DATE GRID REF DESCRIPTION OF DAMAGE SRM REF AUTH TLP REF REMARKS TLP REF AUTH DATE REMARKS

13/10/07 -- -- 51-00-00 SJ-88 -- -- -- -- --

10/8/2006 -- -- 53-00-01 GMF -- -- -- -- -- with in limits





AIRCRAFT REG: VT-SPD

CHART NO.

SRM/DESIGN REF

Dent on LH side horizontal Stabilizer

W = 5.5"Y = 0.161"L = 2.185"

Repeat insp at 400 FHPermanent repair at 5000

Dent on LH fuselage skin STA927-947.5 STR 17-18

D=0.030L=3"W=2.50"

Dent on RH fuselage skin STA328 STR 21-22

D=0.045L=2"W=1.75"

Dent on LH side fuselage skin STA 1006-1016

A=2.5"Y=0.0380

CLEARANCE DETAILSALLOWABLE DAMAGE REPAIR

TLP REF

15-Nov-00 -- -- -- -- -- -- -- 5-Oct-01

5-Oct-01 -- -- 53-00-01 -- -- -- 53-00-01 -- -- 15-Nov-01

5-Oct-01 -- -- 53-00-01 -- -- -- 53-00-01 -- -- 15-Nov-02

5-Oct-01 -- -- 53-00-01 -- -- -- 53-00-01 -- -- 5-Oct-01

31-Oct-01 -- -- -- -- -- -- 51-70-10 -- -- 31-Oct-01

23-Aug-02 -- -- -- -- -- -- 52-00-01 -- -- 23-Aug-02

3-Oct-01 -- -- 53-00-01 -- -- -- -- -- -- --

14-Oct-04 -- -- 57-70-01 -- -- MEASURED WITHIN LIMITS -- -- -- -- --

2-Dec-02 -- -- 53-00-01 -- -- MEASURED WITHIN LIMITS -- -- -- -- --


7-Jun-05 -- -- 53-00-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 53-00-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 53-00-01 -- -- -- -- -- -- --



AIRCRAFT REG: VT-SPEENTRY DETAILS

DATE CHART NO.

GRID REF

DESCRIPTION OF DAMAGE SRM REF AUTH TLP REF

REMARKS SRM/DESIGN REF

AUTH DATE REMARKS

EXISTING REPAIRBS 867, STR 26L-26RH

53-00-07&

53-00-01

53-00-07&

53-00-01

PERMANENT REPAIR BY FUA







EXISTING REPAIRSPOILER #9 LOWER PANEL

REPAIRED ACC SRM

EXISTING REPAIRAFT CARGO DOOR

REPAIRED ACC SRM

DENTBS 905, STR 17-18 RH

REWORKED AND MEASURED WITHIN LIMITS

DENT GROUND SPOILER #12 UPPER SURFACE

SCRATCHESBS 967, STR 19 LH

DENT AFT TO BS 1016, BELOW S-13L


L=200mm, W=120mmMEASURED WITHIN LIMITS

DENT AFT TO BS 1016, ABOVE S-13L

L=75mm, W=65mm, Y=0.5mmMEASURED WITHIN LIMITS

DENT AFT TO BS 1016, NEAR S-12L


7-Jun-05 -- -- 53-00-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 53-00-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 53-00-01 -- -- -- -- -- -- --


7-Jun-05 -- -- 53-00-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 53-00-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

DENT AFT TO BS 1016, NEAR S-12L


DENT AFT TO BS 1016, ABOVE S-13L




SCRATCHESBS 500 A, STR 20 RH

DENTAFT TO BS 500 A BETWEEN S-19R/S-20R


DENTBETWEEN 500A/500B & BETWEEN S-19R/S-20R


DENTFWD CARGO DOOR OUTER SKIN


SRATCHESFWD CARGO DOOR OUTER SKIN

L=12mm, Y=0.15mmMEASURED WITHIN LIMITS

















7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

7-Jun-05 -- -- 52-30-01 -- -- -- -- -- -- --

14-Oct-04 -- -- -- -- MEASURED WITHIN LIMITS -- -- 14-Oct-04

18-Oct-04 -- -- 57-53-01 -- -- -- -- -- --

15-Oct-04 -- -- -- -- -- -- 15-Oct-04 --

9-Dec-04 -- -- DENT ON BS 312-320 STR 19RH 57-53-01 -- -- 57-53-01 -- -- 9-Dec-04 --

7-Jun-05 -- -- DENT ON BS 905 STR 22RH 53-00-01 -- -- 53-00-01 -- -- 7-Jun-05 --























SEVERAL SCRATCHESBS 430, STR 13 RH

51-10-02&

53-00-01

51-10-02&

53-00-01

REWORKED ACC SRM

DENTLH I/B AFT FLAPUPPER SURFACE

MEASURED WITHIN LIMITS ACC SRM

SEVERAL SCRATCHESBS 344, STR 16 RH

51-10-02 & 53-00-01

REWORKED AND MEASURED WITHIN LIMITS

51-10-02 & 53-00-01

MEASURED WITHIN LIMIT ACC SRM

L= 52mm W= 10mm Y= 0.5mm WITHIN LIMIT

7-Jun-05 -- -- 51-70-05 -- -- -- 51-70-05 -- -- 7-Jun-05

7-Jun-05 -- -- 51-70-10 -- -- -- 51-70-10 -- -- 7-Jun-05

7-Jun-05 -- -- 57-53-01 -- -- 57-53-01 -- -- 7-Jun-05 --

9-Jun-05 -- -- SPOILER # 4 UPPER SKIN 57-70-01 -- -- 57-70-01 -- -- 9-Jun-05 --

9-Jun-05 -- -- SPOILER # 9 UPPER SKIN 57-70-01 -- -- 57-70-01 -- -- 9-Jun-05 --

9-Jun-05 -- -- SPOILER # 8 UPPER SKIN -- -- -- -- -- -- -- -- --

9-Jun-05 -- -- SPOILER # 10 UPPER SKIN -- -- -- -- -- -- -- -- --

7-Oct-07 -- -- 57-53-01 -- -- 57-53-01 -- -- 7-Oct-07

-- -- -- 52-30-01 -- -- 52-30-01 -- -- -- CLOSED

-- -- -- 52-30-01 -- -- 52-30-01 -- -- -- CLOSED

-- -- -- 51-70-01 -- -- 51-70-01 -- -- -- CLOSED

-- -- -- 54-10-01 -- -- 54-10-01 -- -- -- CLOSED

-- -- -- 53-00-01 -- -- 53-00-01 -- -- -- CLOSED

-- -- -- 53-00-01 -- -- 53-00-01 -- -- -- CLOSED

-- -- -- DENT ON HORIZONTAL L/E SKIN -- -- -- -- -- -- -- CLOSED

-- -- -- -- -- -- -- -- -- -- CLOSED

T/R INBD TRANSLATING SLEEV ENG #2

PERMANENT REPAIR

RH INBD AFT FLAP UPPER SKIN CORROSION

PERMANENT REPAIR

DENT ON LH O/B AFT FLAP LOWER SKIN

L=36 mm Y = 1mm WITHIN LIMIT

L = 48mm W = 28mm Y = 0.10mm WITHIN LIMIT

L =47mm W= 28mm Y = 0.10mm WITHIN LIMIT

DENT ON RH INBD AFT FLAP LEADING EDGE

H = 8" W + 14" Y +0.20" REWORKED ACC SRM MEASURED WITHIN LIMITS

REPETITIVE INSPECTION EVERY 400 FH

DENT ON FWD CARGO DOOR SKIN

A = 1.25" D + 0.04" W/Y 31.2" MEASURED W/I LIMIT ACC SRM

DENT ON FWD CARGO DOOR SKIN

A = 2.0" D = 0.02" MEASURED W/I LIMIT

DENT ON RH WING LEADING EDGE (RHPYLON FAIRING AT WING STA 278.50

REWORKED ACC TO SRM WITHIN LIMIT

DENT ON ENG #2 NOSE COWL DENT POST 4 O' CLOCK

MEASURED WITHIN LIMIT ACC TO SRM L =1.75" W = 1.0" D = 0.024"

DENT ON FUSELAGE SKIN BTW STA 1006-1016 STR 13L-14L

MEASURED WITHIN LIMIT ACC TO SRMD = 0.042" W = 2.0"

DENT ON FUSELAGE SKIN BTW STA 1016-1040 STR 13L-15L

MEASURED WITHIN LIMIT 2 DENTS 1. D =0.037" W =2"2. D = 0.028" W = 1.8"

D = 0.031" W = 1.5" L = 2.5" WITHIN LIMIT

DENT ON RH HORIZONTAL L/E SKIN

WITHIN LIMIT D =0.068" W = 1.25" L = 2.5"

-- -- -- -- -- -- -- -- -- -- CLOSED

20-Jul-08 -- -- 55-10-01 -- -- 55-10-01 -- -- 20-Jul-08 CLOSED

5-Apr-08 -- -- 57-42-01 -- -- -- -- -- -- --

20-Jul-08 -- -- DENT ON RH O/B FLAP LWR T/E 57-53-01 -- -- PREVIOUS DENT WITHIN LIMIT 57-53-01 -- -- 20-Jul-08

24-Jul-08 -- -- -- -- -- -- 24-Jul-08

21-Jul-08 -- -- -- -- -- -- 21-Jul-08

21-Jul-08 -- -- 51-70-10 -- -- DELAMINATION AREA 4"X5" 51-70-10 -- -- 21-Jul-08

21-Jul-08 -- -- 51-70-10 -- -- DELAMINATION AREA 1.5"X1" 51-70-10 -- -- 21-Jul-08

22-Jul-08 -- -- 51-70-10 -- -- OLD REPAIR PEELED OFF 51-70-10 -- -- 22-Jul-08

26-Jul-08 -- -- 51-70-10 -- -- 51-70-10 -- -- 26-Jul-08

28-Aug-08 4 H21 53-00-01 SJ-88 8737 Within limits -- -- -- -- --

1-Sep-08 3 F14 57-42-01 SJ-97 8763 WITH IN LIMITS -- -- -- -- --

20-Apr-09 1 Q13 57-53-01 SJ-88 10143 OUT OF SRM LIMITS -- 10145 SJ-40 21-Apr-09

DENT ON SLAT #3 LEADING EDGE SKIN

WITHIN LIMIT D = 0.078" W = 1.25" L =3"

DENT ON LH HORIZONTAL L/E SKIN

REPAIRED ACC SRM (FLUSH REPAIR)

SLAT # 3 LH LEADING EDGE SKIN

WITHIN LIMIT D = 0.050" W = 1.75" L = 1.8"

REPAIRED ACC SRM

DENT ON AFT CARGO DOOR OUTER SKIN

52-30-01 & 51-70-01

Y =0.015" W = 1.350" WITHIN LIMIT

52-30-01 & 51-70-01

REWORKED ACC SRM NDT INSPECTED

DENT ON RH HORIZONTAL L/E SKIN PNL # 2

55-10-01 & 51-

70-01

D = 0.008" W = 0.8" WITHIN LIMIT

55-10-01 & 51-70-01

REWORKED ACC SRM NDT INSPECTED

RH WING I/B AFT FLAP LWR SKIN

REPAIRED ACC SRM

RH WING O/B AFT FLAP LWR SKIN

REPAIRED ACC SRM

LH WING O/B AFT FLAP LWR & UPPER SKIN

REPAIR DONE ACC TO SRM

LH WING SPOILER # 1 UPPER SURFACE

DELAMINATION AREA 3" DIAMETER

REPAIR DONE ACC TO SRM

REFERENCE OF ABOVE ENTERED RECORDS

Minor Dent Between STA 196.5 and STA 203.8 Section 41L=2.8', W= 2.5', Y=0.08'

DENT ON # 3 SLATW= 1.2" , Y=0.042"

LH OUTBOARD AFT T/E FLAP INBOARD SIDE a) UPPER SKIN PANEL OF 11.00" X 10.5" IS DISBONDED (PREVIOUSLY REPAIRED) & b) HONEY COMB IS EXPOSED OF 8.5" X 8.5" SIZE

LH OBD FLAP REPLACED WITH SERVICEABLE ONE

20-Apr-09 1 Q13 57-53-01 SJ-40 10145 -- -- -- -- --

28-Aug-09 4 SJ-88 11045 WITH IN LIMITS -- -- -- -- --

24-Sep-09 -- -- 57-53-01 SJ-76 11203 -- -- -- --

8-Oct-09 4 Q15 57-53-01 SJ-88 WITHIN LIMITS -- -- -- -- --

25-Nov-09 -- -- -- -- 11693 -- -- -- -- --

4-Mar-10 1 E-16 55-10-01 SJ-48 12426 -- -- -- -- --

10-May-10 4 I18 DENT 52-30-01 -- -- 52-30-01 STR00087 10-May-10 WL SRM 52-30-01







10-May-10 1 J17 DENT 52-30-01 -- -- STR-12 10-May-10

10-May-10 2 N5 DENT 52-30-01 -- -- WPL-158 10-May-10

GAUGE/NICK ON MAIN T/E FLAP TRAILING EDGE

WITHIN SRM LIMITSREPEAT INSPECTION EVERY 400 FH AND PERMANENT REPAIR BEFORE 5000 FH

N10&

N11

TWO SCRATCHES AT LOWER FUSELAGE BELOW AFT CARGO COMPARTMENT OF SECTION 461) L=1.5", DEPTH=0.009"2) L=0.5", DEPTH=0.008"

53-00-01&

53-66-01

DENT FOUND ON THE LH OBD AFT FLAP LELENGTH=7.5", WIDTH=1.5", DEPTH=0.468"

DENT FOUND OUT OF SERVICEABLE LIMITS

FLAP REPLACEDWITH SERVICEABLE ONE

WING TE OBD MAIN FLAP1. GAUGELENGTH=0.60", DEPTH=0.009"2. DENTLENGTH=2.5", WIDTH=1.9", DEPTH=0.06"

11345, 11346, 11347

LH OBD AFT FLAP REPLACED DUE LOAN ITEM TO BE RETURNED

FLAP INSTALLED IS A REPAIRED FLAP

DENT ON RH SIDE HORIZONTAL STABILIZERL=4.5", A=1.5", Y=0.20"

DENT FILLING C/O AS PER SRM 51-70-01REPEAT 400 FH.PERMANENT REPAIR WITHIN 5000 FH / 18 MO

REFERENCE OF C6 CHECK ENTRIES

MAS-2386

MAS-2386

MAS-2386

MAS-2386

MAS-2386

MAS-2386

MAS-2386

MAS-2386

MAS-2386

MAS-2386

MAS-2386

MAS-2386

MAS-2386

MAS-2386

MAS-2386

738-EO-53-4889

MAS-2308

SKIN REPAIR 738-EO-53-4889

MAS-2386

738-EO-55-4890

MAS-2308

PERMANENT REPAIR 738-EO-

55-4890

10-May-10 1 J21 DENT 52-30-01 -- -- WPL-167 10-May-10

10-May-10 4 I17 DENT 52-30-01 -- -- 52-30-01 STR83 10-May-10

10-May-10 4 I18 DENT 52-30-01 -- -- 52-30-01 STR84 10-May-10

10-May-10 4 I17 DENT 52-30-01 -- -- 52-30-01 STR85 10-May-10

10-May-10 4 I18 DENT 52-30-01 -- -- 52-30-01 STR86 10-May-10

10-May-10 4 J18 DENT 52-30-01 -- -- 52-30-01 STR94 10-May-10

10-May-10 4 JI18 DENT 52-30-01 -- -- 52-30-01 STR95 10-May-10

10-May-10 4 J18 DENT 52-30-01 -- -- 52-30-01 STR96 10-May-10

10-May-10 2 L21 -- -- -- 53-10-15 STR-28 10-May-10

10-May-10 3 I4 DENT 53-10-01 SYS-137 DENT FOUND WITHIN LIMITS

10-May-10 4 L12 DENT 57-53-01 SYS-673 DENT FOUND WITHIN LIMITS

10-May-10 4 J9 DENT 51-70-10 DOUBLER REPAIR 51-70-10 WPL-186 10-May-10

10-May-10 2 G16 DENT 57-42-01 SYS-530 DENT FOUND WITHIN LIMITS

10-May-10 3 J13 DENT -- -- -- -- 51-70-00 WPL-283 --

10-May-10 2 D15 DENT 57-70-01 SYS-532 DENT FOUND WITHIN LIMITS

MAS-2386

737-EO-55-4891

MAS-2308

PERMANENT REPAIR 737-EO-

55-4891MAS-2386

MAS-2386

WITHIN LIMITS SRM 52-30-01

MAS-2386

MAS-2386


MAS-2386

MAS-2386


MAS-2386

MAS-2386


MAS-2386

MAS-2386


MAS-2386

MAS-2386


MAS-2386

MAS-2386


CRACK ON EXTRNAL POWER RECEPTACLE CUT-OUT AFT EDGE

MAS-2308

DOUBLER REPAIR

MAS-2308MAS-2308MAS-2308

WPL-186

MAS-2308

DOUBLER REPAIR

MAS-2308

MAS-2308

DOUBLER REPAIR

MAS-2308

ENTRY DETAILS CLEARANCE DETAILSALLOWABLE DAMAGE REPAIR

-- -- -- 54-10-01 GMF -- Within limits -- -- -- -- --

9-Dec-07 -- -- 53-00-01 GMF -- Within limits -- -- -- -- --

9-Nov-07 -- -- 54-10-01 GMF -- Within limits -- -- -- -- --

9-Nov-07 -- -- RH inboard aft flap dent 57-53-02 GMF -- Within limits -- -- -- -- --

9-Nov-07 -- -- 57-52-02 GMF -- Within limits 51-70-10 -- -- -- --

9-Nov-07 -- -- 57-53-02 GMF -- Within limits 51-70-10 -- -- -- --




15-Nov-07 1 J-19 55-10-01 SPJ 5295 55-10-01 -- TKT 21-Mar-09

21-Mar-09 1 K-17 53-00-01 TKT -- WITHIN LIMITS -- -- -- -- --

21-Mar-09 1 J-17 53-00-01 TKT -- WITHIN LIMITS -- -- -- -- --



AIRCRAFT REG: VT-SPF

DATE CHART NO.

GRID REF



TLP REF

AUTH DATE REMARKS

#1 Engine on Lip SkinW=4", D=1/16", L=3/4", W/Y = 64Scracth on LH side on fuselage skin STA 792L=0.001"Dent on LH engine nose inlet cowl at post 05 clockD=0.027", L=4.5", W=3.1"

RH outboard aft flap dentD=0.049, A=1.6"

LH outboard aft flap dentD=0.037", A=1.7"

Dent on fuselage skin BTW STA 1006-1016, STR 13-15LD=0.050", L=1.5"

Dent on fuselage skin BTW STA 1016-1026,STR 13-14LD=0.020", L=1.5"Tail bumper fairing dentD=0.125", L=1.5"

LH Horizontal Stabilizer Leading Edge Skin( L) = 2.4 ", (Y) = 0.19 "(L) = 2.75 ", (Y) = 0.125"

Repeat 400 FH Permanent repair at 5000 FH or 18 month

PERMANENT REPAIR C/O

DENT ON LH FUSELAGE SKIN BETWEEN STA 1006-1016 AND STRG 14-15DENT ON LH FUSELAGE SKIN BETWEEN STA 1006-1026 AND STRG 14-15

17-May-09 2 SJ-07 8789 WITHIN LIMITS -- -- -- -- --

N4,N5 M5,M6 J19, J20, N15

SERIES OF DENTS FOUND ON LH & RH HORIZONTAL STABILIZER LE SKIN & RH WING FIXED LE INBOARD SKIN

55-10-01&

57-41-02

CLEARANCE DETAILSALLOWABLE DAMAGE REPAIR

20-Jan-08 1 K-19 51-70-01 SJ-20 4302 -- -- 15-Jul-09

20-Jan-08 1 K-19 55-10-01 SJ-*38 4317 WITHIN ALLOWABLE LIMITS -- -- -- -- --

19-Mar-08 2 S-11 57-42-01 SJ-88 4753 DENT FOUND WITHIN LIMIT -- -- -- -- --

4-Aug-08 2 M-6 55-10-01 SJ-96 5758 DENT WITHIN LIMITS -- -- -- -- --

7-Sep-08 -- -- 54-10-01 SJ-97 5938 -- -- -- -- --

23.Sep.08 4 J-19 52-30-01 SJ-23 6001 DENT WITHIN LIMITS 6001 SJ-23 -- --

26.Dec.08 1 K-5 52-10-01 SJ-47 6540 DENT WITHIN LIMITS -- -- -- -- --

3-Feb-09 -- -- -- 6833 DENT WITHIN SRM LIMITS -- -- -- -- --



AIRCRAFT REG: VT-SPH ENTRY DETAILS

DATE CHART NO.

GRID REF



TLP REF

AUTH DATE REMARKS

DENT ON LH HORIZONTAL STABLIZER LEADING EDGEL = 3.3, Y = 0.3, A = 2.5

REPEAT AT 400FH PERMANENT REPAIR WITH IN 5000 HRS,18 MONTHS

Air Works

LE SWAPPED WITH SPS


DENT ON LH HORIZONTAL STABLIZER LEADING EDGEY = 0.03125, A = 1.715DENT ON NO. 6 SLAT LEADING EDGE SKINL = 2.325, W = 1.280, Y = 0.040DENT ON #2 L.E. PANEL OF STARBOARD HORIZONTAL STABILIZERY=0.03", L=2.5", A=2.2"DENT ON NO # 2 ENGINEACQUISTIC PUNTURED AT 5 O CLOCK POSITIOND=0.25inch

HOLE IS WITHIN LIMITS REPEAT INSPECTION AT EVERY 25 CYCLES

DENT ON FORWARD CARGO DOOR EXIT. SKIN CLOSE TO DOOR HANDLE. W=2.6" L=6/32" Y=2/32"

SRM 53-30-01 SRM 51-

70-01

0.5 INCH CRACK AT UN PRE-SRIED AREA OF L1 DOOR OUTER SKIN WITH IN LIMITS OF SRM 52-10-01DENT FOUND ON SCREW JACK COMPARTMENTL=3.3", W=2.5", Y=0.08"

53-00-01&

53-80-01

3-Feb-09 -- -- -- -- -- -- -- -- --

04.Feb.09 4 H18 SJ-88 6834 WITHIN LIMIT AS PER AMM -- -- -- -- --

04.Feb.09 3 N17 SJ-88 DENTS WITHIN SRM LIMITS -- -- -- -- --

04.Feb.09 3 O-18 SJ-88 6833 DENT WITHIN SRM LIMITS -- -- -- -- --

20-Jul-10 2 I-7 SJ-88 SJ-88 DENT WITHIN SRM LIMITS -- -- -- -- --

MULTIPLE DENT ON AFT OF AFT ENTRY DOOR EMERGENCY LIGHT1. L=2.1", W=1.6", Y=0.04"2. L=1.7", W=1.55", Y=0.05"3. L=2.6", W=2.1", Y=0.06"

53-70-01&

53-00-01

ALL 3 DENTS FOUND WITHIN SRM LIMITS.

ONE SCRATCH OF 0.003" DEPTH IS OBSERVED WITHIN 3.0" REDIUS OF STATIC PORT.

AMM 34-11-02

03 MINOR DENTS ARE OBSERVED BETWEEN STA1006 & STA 1016. DENT DIMENSION ARE AS FOLLOWS:- 1.L=2.1", W=1.6", Y=0.04" 2.L=1.7", W=1.55",Y=0.05" 3.L=2.6", W=2.1", Y=0.06"

53-70-01 53-00-01

6833 6834

ONE DENT OBSERVED BETW STA 1016 & STA1042 NEAR WL=208.1 L=3.3", W=2.5", Y=0.08"

53-80-01 53-00-01

Dent on Vertical fin. Length (L) # 2.0 Width (W) # 0.7" Depth (Y) # 0.04"


15-May-07 3 E-4 -- -- -- WITHIN LIMITS -- -- -- -- --

1-Feb-08 -- -- -- -- 3506 -- -- 3-Feb-08

9-Aug-08 2 Q-12 57-42-01 SJ-95 4753 WITHIN LIMITS -- -- -- -- --

17.Jan.10 3 H-3 53-00-01 -- 53-00-01 -- 18.Jan.10 --

17.Jan.10 4 I-19 53-00-01 -- 53-00-01 -- 18.Jan.10 --



AIRCRAFT REG: VT-SPJ

DATE CHART NO.

GRID REF



TLP REF

AUTH DATE REMARKS

Section 41W = 2.51", Y = 1/64", L = 3.5"

DENT ON RH INBOARD WING FIXED LEADING EDGE SKIN L=7", Y=.035'', W=5"

AIWS SPJ/3506

IA Engine

er

Dent refurbished, wing contour restored

DENT W=2.5" , Y=1/64"

After paint stripping, inspection is C/O and found a Dent on L/H F/S External skin as marked between F/S B.S 219.5 - B.S 224.8 and along S-17L - S-19L

MAS- 2393

Damage Blendout/Repair Accomplishment as per SRM 53-00-01 Fig103. Detail G. Damage Dimension After Blendout/Repair: Length : 4" , Width : 3.25" , Max Depth : 0.046".

MAS-2393

After Paint Stripping, Inspection was carried out and found A Dent on R/H F/S skin as marked between F/S B.S 360- B.S 380 and along S-21R - S-22R

MAS- 2393

DAMAGE BLENDOUT/REPAIR ACCOMPLISHMENT AS PER

SRM 53-00-01 FIG.103 DETAIL G.

MAS-2393

18.Jan.10 4 J-17 53-00-01 -- 53-00-01 -- 18.Jan.10 --

18.Jan.10 1 53-00-01 -- 53-00-01 -- 18.Jan.10 --

18.Jan.10 1 53-00-01 -- 53-00-01 -- 18.Jan.10 --

21.Jan.10 3 O-16 -- -- 21.Jan.10 --

21.Jan.10 3 N-17 -- -- 21.Jan.10 --

SCRATCH MARKS FOUND ON R/H EXTERNAL F/S SKIN BETWEEN F/S BODY STA 500B - STA 500C AND S-22R TO S-23R AS MARKED.

MAS- 2393

SCRATH MARKS ON R/H EXTERNAL F/S SKIN BETWEEN F/S BODY STA 500B- STA 500C AND S-22R TO S-23R REMOVED AS PER SRM 53-00-01 ALLOWABLE DAMAGE 1 FIGURE 103 AND IS WITHIN THE ALLOWABLE DAMAGE DIMENSION FOR F/S SKIN ALLOWABLE DAMAGE AT ZONE 2 UNDER CHART A AS PER SRM 53-00-01 FIG.104, SATIS. PLS REFER TO IRV SYS-00319 FOR HFEC INSPECTION & IRC SYS-00391 FOR SKIN THICKNESS CHECK.

MAS-2393

M-12 L-13

FOUND LIGHT STRIKE MARKS AT QT : 5 LOCATION FROM STA 663.75 TO STA 1016 AT RIVET HEADS AND SKIN

MAS-2025

CARRIED OUT REPAIR AS PER B737 SRM 53-00-01 REPAIR 13 PARA 4 REV. 37 DATED 10.NOV.2009.

MAS-2025

P-5 P-6 O-7 O-8

FOUND LIGHT STRIKE MARKS AT QT: 7 LOCATION BETWEEN STA 360 TO STA 663.75 ON RIVET HEADS AND SKIN.

MAS-2025

CARRIED OUT REPAIR AS PER B737 SRM 53-00-01 REPAIR 13 PARA 4 REV. 37 DATED 10.NOV.2009.

MAS-2025

CORROSION FOUND AT SKIN BET STA 927-947, ABOVE STR 23L.

53-10-02 53-00-01

MAS- 2363

CORROSION BLENDED OUT IAW SRM 53-10-02 AND SRM 53-00-01 FIGURE 103.MIN DEPTH AFTER BLENDED 0.063" WITHIN LIMITS OF SRM 53-00-01. SATIS. REFER TO CROSS REFERENCE DOCUMENTS FOR DETAILS.

53-10-02 53-00-01

MAS- 2363

CORROSION FOUND ON SKIN AT STA 1016 BETWEEN STA 19L -STR23L.

53-10-02 53-00-01

MAS- 2363

CORROSION BLENDED OUT IAW SRM-53-00-01 FIGURE103.MIN DEPTH AFTER BLENDED 0.07" WITHIN LIMITS OF SRM 53-00-01. REFER TO CROSS REFERENCE DOCUMENT FOR DETAILS.

53-10-02 53-00-01

MAS- 2363

21.Jan.10 3 N-15 -- -- 21.Jan.10 --CORROSION FOUND AT SKIN NEAR VACUUM BLOWER OUTLET.

53-10-02 53-00-01

MAS- 2363

CORROSION BLENDED OUT IAW SRM 53-10-02 AND SRM 53-00-01 FIGURE 103.MIN DEPTH AFTER BLENDED 0.0115" WITHIN LIMITS OF SRM 53-00-01. SATIS. REFER TO CROSS REFERENCE DOCUMENTS FOR DETAILS.

53-10-02 53-00-01

MAS- 2363


DATE DESCRIPTION OF DAMAGE SRM REF AUTH REMARKS AUTH DATE REMARKS

8-May-07 2 51-10-01 SJ-11 1844 WITHIN LIMITS 55-10-01 4143 GMF 6-Jun-08

2-Jun-08 4 F-7 -- -- -- -- 4149 GMF 2-Jun-08

14-Oct-08 3 I-10 DENT ON WING LEADING EDGE 57-41-01 SJ-40 4942 WITHIN LIMITS -- -- -- -- --

3-Feb-09 -- -- 54-10-01 SJ-88 5568 -- -- -- --

28-Aug-09 4 G-21 53-00-01 SJ-46 6987 WITHIN LIMITS -- -- -- -- --

29-Oct-09 4 F-7 57-57-01 SJ-143 7431 WITHIN LIMITS -- -- -- -- --

19-Feb-10 2 R10 57-53-01 -- WITHIN LIMITS -- -- -- -- --



19-Feb-10 4 I7 57-53-01 -- WITHIN LIMITS -- -- -- -- --



AIRCRAFT REG: VT-SPK

CHART NO.

GRID REF

TLP REF

SRM/DESIGN REF

TLP REF

N-5M-6 L-6

MINOR DENTS ON RH HORIZONTAL STABILIZER LEADING EDGE SKIN

DENT REPAIR C/o AS PER

SRM

RH OUTB GFT FLAP DENT A=3.25" Y=0.1185" A=1" Y=0.0256

57-53-02&

51-70-10

REPAIR C/o AS PER SRM

57-53-02 FIG 2 SRM 51-70-10 REPAIR 3 & 4

PUNCTURE AT APPROX. 3 O CLOCK POSITION ON PERFORATED SKIN OF INNER BARREL OF ACOUSTIC PANEL. DIMENSION OF PUNCTURE IS 0.045

PUNCTURE FOUND WITHIN SRM LIMITS. PUNCTURE SEALED WITH BMS 5-95REPEAT INSPECTION EVERY 25FC. PERMANENT REPAIR IF FURTHER DETERIORATION IS OBSERVED.

Permanent Repair C/O in

'C' Check.

DENT ON FWD. RH FUSELAGE AREA BEHIND RADOME W = 4.5'', Y = 0.109"DENT ON RH O/B AFT FLAP. O/B SIDEW=2.75", Y=3"/32 = 0.093,RH WING O/B AFT FLAP UPPER SKIN BULGED UP12' FROM O/B EDGEW=2", Y=0.030"

MAS 2415

#12 SPOILER UPPER SKIN DENT 15" FROM I/B EDGEW=2.25", Y=0.070"

MAS 2415

#12 SPOILER UPPER SKIN DENT 29" FROM I/B EDGEW=0.45", Y=0.030"

MAS 2415

RH WING O/B AFT FLAP LOWER SURFACE DENT 12" FROM O/B EDGEW=2.75", Y=0.093"

MAS 2415


19-Feb-10 1 Q6 53-00-01 -- WITHIN LIMITS -- -- -- -- --

19-Feb-10 1 J16 53-00-01 -- WITHIN LIMITS -- -- -- -- --

19-Feb-10 3 F17 57-53-01 -- WITHIN LIMITS -- -- -- -- --

DENT 10" AFT OF BS 178NEAR RH WINDSHIELDW=3.5", Y=0.1:

MAS 2005

SCRATCH OF FWD ENTRY DOOR BETWEEN STR9L-10L BLENDEDLENGTH=1", DEPTH=0.003:

MAS 2005

DENT AFT OF BS1006 - BS1016 STR 12-14LA=0.5, B=1.25, C=1 & A=0.5, B=1.25, C=1

MAS 2005

DENT LOCATED 17.5" FROM OB & 2.5" FROM TEW=1.6", D=0.050"

MAS 2005



21-Sep-07 4 G9 57-53-01 SJ-22 2356 WITHIN LIMIT 51-70-10 -- 2-Aug-08

2-Aug-08 57-53-01 -- WITHIN LIMIT -- -- -- -- --

2-Aug-08 53-00-01 -- WITHIN LIMIT -- -- -- -- --

2-Aug-08 -- -- -- -- 51-70-01 -- 2-Aug-08

2-Aug-08 -- -- -- -- 51-70-01 -- 2-Aug-08

3-Aug-08 57-42-01 -- WITHIN LIMIT -- -- -- -- --

14-Jun-09 2 M6 55-10-01 SJ-37 6363 WITHIN LIMIT -- -- -- -- --

21-Mar-10 2 N17 53-00-01 -- WITHIN LIMIT -- -- -- -- --

21-Mar-10 2 N16 53-00-01 -- WITHIN LIMIT -- -- -- -- --

21-Mar-10 2 N15 53-00-01 -- WITHIN LIMIT

21-Mar-10 3 M17 53-00-01 -- WITHIN LIMIT

21-Mar-10 3 L8 53-00-01 -- WITHIN LIMIT

21-Mar-10 2 J14 -- -- -- 51-70-01 -- 21-Mar-10 --



AIRCRAFT REG: VT-SPL

CHART NO.

GRID REF

TLP REF

SRM/DESIGN REF

TLP REF

DENT ON AFT FLAPL=3.5'", W=4", D=0.25"

JORAMCO

REPAIRED AS PER SRM

51-70-10

DENT ON RH WING O/B AFT FLAP LE AREAY=0.012", W=1.060"

JORAMCO

DENT ON FWD RH FUSELAGE BETWEEN STA 360 & STA 380STRG 21 & STRG 22Y=0.018, W= 1.240

JORAMCO

IMPACT DAMAGES ON LH & RH WING SPOILER #6 & #7 LWR SURFACES

JORAMCO

REPAIRED AS PER SRM

51-70-01

IMPACT DAMAGES ON LH & RH WING I/B AFT FLAPS TE LWR SURFACES

JORAMCO

REPAIRED AS PER SRM

51-70-01

DENT ON LH WING SLAT #3 AT MID FRAME AREAY=0.055", W=4.330"

JORAMCO

MINOR DEPRESSION ON RH HORIZONTAL STABILIZER LE.A=2.0" , Y=.02" , A/Y=100DENT ON STA 390 STR 22RDEPTH = 0.030", WIDTH = 2"

MAS 2386

MINOR SCRTACH FWD OF FWD CARGO DOOR

MAS 2386

MINOR SCRTACH FWD OF FWD CARGO DOOR

MAS 2386

DENT AT BS 1006 TO BD 1016 LH B/W S11L TO S13L

MAS 2131

FOUND DENT AT BS 9928 TO BS 1016 RH B/W S15R TO S16R

MAS 2131

DENT AT #5 SPOILER (3 LOCATIONS)

MAS 2308



1-Aug-07 1 K20 55-10-01 SJ-21 1592 -- -- -- --

10-Jul-08 1 K-10 55-10-01 SJ-92 4227 WITHIN LIMITS -- -- -- -- --

11-Jul-08 4 J-18 53-00-01 SJ-46 -- WITHIN LIMITS -- -- -- -- --

11-Aug-08 1 J-17 53-00-01 -- WITHIN LIMITS -- -- -- -- --

17-Nov-08 3 K-12 57-53-02 SJ-97 4845 WITHIN LIMITS -- -- -- -- --

5-Dec-08 3 L12 57-53-02 SJ-48 4960 -- -- -- -- --

22-Feb-09 2 O-15 57-41-01 SJ-65 5501 5504 SJ-88 24-Feb-09

1-Apr-09 1 K-19 55-10-01 SJ-07 5749 WITHIN LIMITS -- -- -- -- --

28-Jun-09 4 J19 51-10-01 SJ-23 6341 WITHIN LIMITS -- -- -- -- --

12-Sep-09 3 G-15 57-53-02 SJ-07 6849 WITHIN LIMITS -- -- -- -- --

14-Nov-09 -- -- 57-43-02 SJ-143 7312 WITHIN LIMITS -- -- -- -- --

29-Jan-10 2 N-16 53-00-01 SJ-95 7877 WITHIN LIMITS -- -- -- -- --

5-Mar-10 2 P12 57-70-01 N/A N/A 10-Mar-10



AIRCRAFT REG: VT-SPM

CHART NO.

GRID REF

TLP REF

SRM/DESIGN REF

TLP REF

DENT ON PORT HORIZONTAL STABILIZER LEO=160mm, N=30mmQ=1mm, M=15mm

REPEAT AT 400FH PERMANENT REPAIR WITH IN 5000 HRS/18 MONTHS

DENT REMOVED IN 1C CHECK

DENT ON L.H HORIZONTAL SATBLIZER LEL=2.05", W=1.0", D=0.025"DENT OF FUSELAGE LENTH=4", DEPTH=1/32"DENTL=1.7", Depth=0.029"

JORAMCO

DENT ON INBOARD TRAILING EDGE LH SIDE FLAP.L=3", W=2.120" , W=0.070"DENT ON LH SIDE INBOARD AFT FLAP

DENT WITHIN LIMIT OF SERVICEABILITY

DENT ON RH WING LE JUST ABOVE STALL STRIP

DENT DIMENSIONS BEYOND SRM LIMITS. REPAIR TO BE CARRIED BEFORE FURTHER FLT

57-41-01BM # 1-1220141755

PERMANENT REPAIR C/O.

Dent on LH stabilizer leading edge with in srm limitsL=2.75", W=1/16", A=0.5", L/Y=45.8

Small surface scratch on RH static port. L=4" ,W=0.04", D=0.0001DENT ON LH AFT FLAP.W=1.5 INCH Y=0.0625 INCHDENT ON #3 KRUGER FLAPW=4", Y= 0.937", W/Y= 42.68SCRATCH ON AFT OF THE FWD. CARGO COMPARTMENT DOORL=45mm, WIDTH=6mm, DEPTH =0.025mm

REFERENCE OF C2 CHECK ENTRIES

DENT + DISBOND AROUND ZONE 2 AND ZONE 3 AREA 52.25 IN RH WING SPOILER # 9

MAS-2420

BEYOND ALLOWABLE LIMIT IN SRM

SRM 57-70-10 REPAIR 4

MAS-2420

5-Mar-10 4 J10 57-53-70 N/A -- -- -- --

5-Mar-10 4 H18 53-00-01 10-Mar-10

5-Mar-10 2 E15 57-70-01 -- --

8-Mar-10 3 M17 53-00-01 N/A WITHIN SRM LIMITS -- -- -- --



10-Mar-10 3 J13 DENT: LH I/B AFT FLAP -- -- N/A -- WPL-004

10-Mar-10 3 G15 N/A

10-Mar-10 3 L12 PUNCTURE: LH I/B AFT FLAP N/A

10-Mar-10 -- N/A -- -- -- --

10-Mar-10 1 K19 55-10-01 N/A -- -- -- --

10-Mar-10 2 O 15 55-41-01 N/A N/A 11-Mar-10

10-Mar-10 4 J14 57-43-02 N/A DENT WITHIN SRM LIMITS -- -- -- --

10-Mar-10 72-21-12 N/A FOUND WITHIN LIMITS. -- -- -- --

10-Mar-10 2 M17 53-00-01 N/A FOUND WITHIN LIMITS.

DENT ON RH WING FLAP FAIRING OUTBD#07 MAX WIDTH:1.2 IN DEPTH: 0.045 IN

MAS-2420

WITH IN ALLOWABLE LIMIT IN SRM

SCRATH ON ALT STATIC PORT PLATE

51-10-01 53-00-01 MM 34-11-02

MAS-2386

MAS IRC

SYS-00035

WITH IN LIMITS IN SRM 53-00-01

IRC SYS

-00035

MAS-2386

MULTIPLE DENT + DISBOND AROUND ZONE 2 AREA.

MAS-2308

WPL-27

WPL-36

BEYOND ALLOWABLE LIMIT IN SRM

EO-738 EO-57-4788

WPL-27 WPL-36

DENT : FUSELAGE SKIN STA1006-1016, STR-00016

MAS-2363


MAS-2363


MAS-2363


Fig 202

MAS-2308

DENT: LH O/B AFT FLAP LEADING EDGE.


MAS-2005

SYS-00066 WPL-00037


Fig 202

MAS-2308

SYS-00041 WPL-0004

ENGINE DAMAGE MAPPING

BLADES # 15/16

LOCAL DSTORTION FOUND WITHIN LIMITS OF AMM REF 72-21-02

MAS-2415

FOUND WITHIN LIMITS OF SERVICEABILITY.

DENT ON LH STABILIZER LE SKIN L=2.75", W=1/16", A=O.5",L/Y=45.8"

MAS-2137

FOUND WITH IN SRM LIMITS OF SEFRVICEABILITY

DENT BETWEEN 4th & 5th RIB ON RH WING LEADING EDGE SKIN DENT DIMENSION ARE AS BELOW. W=11.5", L=4", Y=0.75", W/Y=15.33"

MAS-2420

DENT DIMENSIONS ARE BEYOND ALLOWABLE LIMITS. SRM57-41-01

57-41-01 REPAIR 2,

EO NO# SP-EO-01-57-501 W/O

NO=SPM-OO789

MAS-2420


AS EO NO#SP-EO-01-

57-501

DENT OBSERVED ON#3 KPVE FLAP W=4", L=0.0937", Y=3/32" W/Y=42.68"

MAS-2420

ENGINE MAPPING

CHART

BLADES#12 & 15

NIKS FOUND ON BLADE #12 & #13 WITHIN LIMITS AS PER AMM 72-21-02

MAS-2396

SCRATCH AT AFT FWD CARGO DOOR L#45MM, W#O6MM,D#0.025MM

MAS-2386



2-Oct-07 2 M-6 55-10-01 SJ-98 342 -- -- -- --

3-Mar-09 -- -- 57-10-10 TKT -- -- -- -- -- --

3-Apr-09 1 J-19 55-10-01 SJ-96 3673 -- -- -- -- --

1-Aug-09 55-10-01 SJ-96 4488 -- -- -- -- --



AIRCRAFT REG: VT-SPO

CHART NO.

GRID REF

TLP REF

SRM/DESIGN REF

TLP REF

DENT ON RH HORIZONTAL STABILIZER LE.

ALL0WABLE. INSPECTION AT EVERY 400FH PERMANENT REPAIR AT 5000FH OR 18 MONTHS

REPAIR C/O IN C CHECK

CARCK ON CENTER WING REAR SPAR VAPOR BARRIER WEB

REPEAT INSPECTION EVREY 600 FC & PERMANENT REPAIR NOT LATER THAN 24 MONTHS

TWO DENTS ON PORT SIDE HORIZONTAL STABILIZER LE SKIN

DENTS WITHIN SRM LIMITS NO FURTHER ACTION / INSPECTION REQUIRED

DENT OBSERVED STBD SIDE HORIZONTALSTABLIZER LE

MAPPING OF DENT C/O AS PER SRM 55-10-01



2-Oct-07 2 M-6 55-10-01 SJ-98 342 -- -- -- --

26-Jun-08 -- N-17 -- SJ-20 -- -- 53-00-01 2310 -- 3-Jul-08



24-Mar-09 4 I-17 -- -- -- -- 53-00-01 -- TKT 26-Mar-09

24-Mar-09 4 I-17 -- -- -- -- 53-00-01 -- TKT 26-Mar-09

24-Mar-09 4 I-16 -- -- -- -- 53-00-01 -- TKT 26-Mar-09

24-Mar-09 4 I-18 -- -- -- -- 53-00-01 -- TKT 26-Mar-09




AIRCRAFT REG: VT-SPP

CHART NO.

GRID REF

TLP REF

SRM/DESIGN REF

TLP REF

DENT ON RH HORIZONTAL STABILIZER LE.

ALL0WABLE. INSPECTION AT EVERY 400FH PERMANENT REPAIR AT 5000FH OR 18 MONTHS

RH HORIZONTAL STABILZER SWAPPED WITH SPO

REPAIR C/O IN C CHECK

OF SPOFOUND A SCRATCH ON RIGHT SIDE OF FUSELAGE LOCATION SECTION 43 FWD OF CARGO DOOR

PERMANENT REPAIR BY IA

DENTS ON FUSELAGE SKIN BETWEEN STA 1006-1016 AND LH STR 13-14DENTS ON FUSELAGE SKIN BETWEEN STA 1016-1040 AND LH STR 13-14 LIGHTNING STRIKE ON FUSELAGE SKIN AT FASTENER BETWEEN STA 500G-500D AND RH STR 19


LIGHTNING STRIKE ON FUSELAGE SKIN AT FASTENER BETWEEN STA 500F AND RH STR 18-19


LIGHTNING STRIKE ON FUSELAGE SKIN AT FASTENER BETWEEN STA 500G AND RH STR 18-19


LIGHTNING STRIKE ON FWD CARGO DOOR OUTER SKIN AT FASTENER


SCRATCH ON FUSELAGE SKIN BETWEEN STA 685-706 AND RH STR 2-3


24-Mar-09 2 H-6 55-30-01 TKT -- WITHIN LIMITS -- -- -- -- --

24-Mar-09 2 L-6 55-10-01 TKT -- WITHIN LIMITS -- -- -- -- --

14-Aug-09 3 H-15 57-53-01 SJ-07 5026 WITHIN LIMITS -- -- -- -- --

11/10/2009 3 H-14 57-53-01 SJ-20 5432 -- -- -- --

20/10/2009 3 H-15 57-53-01 SJ-86 5530 -- -- -- --

25/05/2010 57-53-01 SJ-88 7130 -- -- -- -- --

18/07/2010 4 15-KL 53-60-70 SJ-95 7537 -- -- -- -- --

18/07/2010 3 9-KL 53-60-70 SJ-95 7537 -- -- -- -- --

SCRATCH ON FUSELAGE SKIN BETWEEN STA 601-616 AND RH STR 2-3PUNCTURE ON VERTICAL STAB LE SKIN BETWEEN STA 166.5-175.9DENT ON RH HORIZONTAL STABILIZER LE SKIN BETWEEN STA 86.66-95.96DENT ON LOWER SKIN PANEL OF O/B T.E AFT FLP L=5.75", W=3.75", Y=1/8", W/Y=30

DENT ON LH TE AFT O/B FLAP L.E

ALLOWED FOR 100 C AS PER BOEING MESSAGE 09-0092-02B

Flap replaced on 29/10/09

DENT ON LH TE AFT O/B FLAP L.E

FURTHER EXTENSION OF 100 C AS PER BOEING MESSAGE ROJ-ROJ- 09-0092-04B

Flap replaced on 29/10/09

Reff TLP 7130, During inspection as per AMM 05-51-54, found RH side wing lower inboard fixed trailing edge panel damaged, dent on inboard trailing edge main flap (RH Side) and junction box (#00033) mounting hardware damaged.

1).Dent on RH side wing Inboard Trailing edge Main flap inspected as per SRM 57-53-01. General Condition of dent found satisfactory. Coin tap test C/O no delamination observed at the impact area. Dent dimensions are as follows, Depth#4.2" , width# 3.2" and depth(y) # 0.075" w/y # 42. Dent dimension are found within SRM Allowable damage limits. Damage mapping chart filled. 2).Junction box (00033) monthly inspection for damage continue.

RH ECS RAM AIR INLET DUCT FWD EDGE (192 BK) MAX WIDTH : 7/16 INCH MAX DEPTH: 7/32 INCH

WITH IN LIMITS AS PER SRM 53-60-70.

LH ECS RAM AIR INLET DUCT PANEL FWD EDGE (192 BL) MAX WIDTH: 3/8 INCH. MAX DEPTH: 1/32 INCH.

WITH IN LIMITS AS PER SRM 53-60-70.


1-Sep-07 3 H3 Dent on fuselage 51-10-01 SJ11 139 -- 2-Apr-09

14-Apr-08 -- -- -- -- -- -- 53-00-01 1724 903 24-Apr-08 Repair done

10-Jul-08 3 N17 Dent on Fuselage 53-00-01 SJ-88 2295 With in limits -- -- -- -- --

12-Nov-08 2 N5 55-10-01 SJ-20 3355 -- 1-Apr-09

25-Nov-08 4 G8 57-53-01 SJ-38 2244 -- -- -- -- --

30-Mar-09 1 S3 -- -- -- -- -- 2-Apr-09

30-Mar-09 1 J17 53-00-01 Dent found within limit. -- -- -- -- --

30-Mar-09 1 J18 53-00-01 Dent found within limit. -- -- -- -- --

30-Mar-09 3 N17 -- -- -- -- -- 2-Apr-09

30-Mar-09 3 L12 -- -- -- -- -- 1-Apr-09

30-Mar-09 3 H15 -- -- -- -- -- 31-Mar-09



AIRCRAFT REG: VT-SPQ

DATE CHART NO.

GRID REF



TLP REF

AUTH DATE REMARKS

No restrictions As per SRM-51-10-01, except little extra fuel burn. However repair should be carried out as soon as possible

BM # 1-1246682733 27-Mar-09

THY 51 B1

1829

Permanent Repair

Fuselage skin damage between STA480-490on str at lower main sill

Dent on RH Horizontal Stabilizer Leading Edge SkinL=5", W=3", D=0.2"

1. Reinspect (Detailed visual inspection) every 400 hrs2. Permanent repair to be carried out within 5000Hrs/18months

SRM 55-10-01 Rep-202

THY 51 B1

1829

Permanent Repair

Dent observed on R.H. outboard Aft Flap Trailing Edge Skin

Dent found within limits . Coin tap test C/O for delamination . No delamination observed.

Dent on LH Fuselage Skin STA 188-196.5 and 8" down from LH Lap Strg 24

Boeing Msg. ROJ-ROJ-09-00-10-10B Dt.

27-Mar-09

THY 51 B1

1829

Permanent Repair

DENT ON THE FUSELAGE SKIN STA 1006-1016 AND LH STRG 13-15

THY 51B1 1829

DENT ON FUSELAGE SKIN BTW STA 1016-1040 AND LH STRN 13-14

THY 51B1 1829

SCRATCH ON LH FUSELAGE SKIN AFT PAX DOOR LOWER AFT EDGE AREA

SRM 53-00-01

THY 51 B1

1829

Permanent Repair

DELAMINATION ON LEFT SIDE WING BODY FAIRING (194FL) OUTER SURFACE.

SRM 51-70-04 Repair 2

THY 51 B1

1829

Permanent Repair

LH WING NUMBER 2 FLAP TRACK FIXED FAIRING OUTER SURFACE IS DAMAGED

SRM 57-53-70 Repair 1

THY 51 B1

1829

Permanent Repair

30-Mar-09 1 S14 -- -- -- -- -- 2-Apr-09

30-Mar-09 1 S3 -- -- -- -- -- 2-Apr-09

31-Mar-09 4 D4 -- -- -- -- -- 1-Apr-09

1-Apr-09 3 Q8 Dent found within limit. -- -- -- -- --

DENT ON LH WING #3 SLAT T/E WEDGE UPPER SURFACE


THY 51 B1

1829

Permanent Repair

DENT ON FUSELAGE SKIN STA 259.5 - 277 LH STRG 23-24

BM # 1-1246682733 27-Mar-09

THY 51 B1

1829

Permanent Repair

DENT ON HORIZONTAL STABLIZER L/E SKIN RH SIDE STA 216.83-226.13

SRM 55-10-01 Rep-202

THY 51 B1

1829

Permanent Repair

DENT ON O/B AFT FLAP LOWER SURFACE RH WING

SRM 57-53-01

THY 51B1 1829



29-Aug-07 2 M6 55-10-01 SJ-13 160 NIL -- -- -- -- --

1-Oct-07 -- -- 55-10-01 SJ-20 402 -- TKT 39886

30-Dec-08 4 H-19 53-00-01 SJ-88 3710 3718 SJ-88 39818

12-Mar-09 4 I-18 52-30-01 TKT -- WITHIN LIMITS -- -- -- -- --

12-Mar-09 4 0-11 52-30-01 TKT -- WITHIN LIMITS -- -- -- -- --



4-Oct-09 4 G-8 57-53-01 SJ-97 5459 WITHIN LIMITS -- -- -- -- --



AIRCRAFT REG: VT-SPR

CHART NO.

GRID REF

TLP REF

SRM/DESIGN REF

TLP REF

DENT ON RH HORIZONTAL STABILIZER LE SKIN

DENT ON LE STABILIZER RH SIDE SKINA=4", L=5.5", Y=1/8"

REPEAT INSPECTION EVERY 400FH PERMANENT REPAIR AT 5000FH OR 18 MONTH

SRM 55-10-01

PERMANENT REPAIR C/OHFEC INSPECTION C/O NO CRACK FOUND

A/C SKIN DAMAGE BETWEEN STA 360 & 380 AND STRG. S-22R & S23R

A/C FERRY FLIED TO DEL AS PER BOEING MSG NO. 1-1136686345-2 REGARDING NTO

SRM 53-00-01

BM # 1-1136686345-

2

PERMANENT REPAIR OF FUSELAGE SKIN C/O

DENT ON FWD CARGO DOOR OUTER SKINDENT ON AFT CARGO DOOR OUTER SKINDENT ON FUSELAGE SKIN BETWEEN STA 1006-1016 AND STRG. LH 12-14DENT ON FUSELAGE SKIN BETWEEN STA 1016-1040 AND STRG. LH 13-16DENT OBSERVED ON RH OUTBOARD AFT FLAPW = 1.9" , Y = 0.07"



10-Sep-08 3 G15 53-53-01 SJ-88 2000 BOTH DENTS WITHIN LIMITS -- -- -- -- --

18-Oct-08 1 J19 55-10-01 SJ-60 2197 -- -- -- --

26-Oct-08 2 M18 SJ-18 2243 -- -- 15-Jul-09

20-Jan-08 1 K-19 51-70-01 SJ-20 4302 -- -- 15-Jul-09

15-Jul-09 3 M17 53-00-01 -- WITHIN LIMITS -- -- -- -- --

15-Jul-09 1 R5 52-10-01 -- WITHIN LIMITS -- -- -- -- --

15-Jul-09 4 R6 52-40-01 -- WITHIN LIMITS -- -- -- -- --



AIRCRAFT REG: VT-SPS

CHART NO.

GRID REF

TLP REF

SRM/DESIGN REF

TLP REF

TWO MINOR DENTS ON LH OUTBOARD TRAILING EDGE FLAP SKIN

DENT ON LH HORIZONTAL STABILIZER LEADING EDGE

DENT IS PERMITTED WITH LIMITATIONS AS PER SRM

LE REPLACE WITH VT-SPT

SCRATCH OBSERVED ON STATIC PORT ON STARBOARD SIDE DURING TRANSIT CHECK

53-00-01&

51-10-03

VISUAL INSPECTION EVERY 25 FC. PERMANENT REPAIR AT 3000 FC / 12 MONTHS

Air Works


DENT ON LH HORIZONTAL STABLIZER LEADING EDGEL = 3.3, Y = 0.3, A = 2.5(EX VT-SPH)

REPEAT AT 400FH PERMANENT REPAIR WITH IN 5000 HRS,18 MONTHS

Air Works PERMANENT

REPAIR C/O

DENT ON AFT OF PRESSURE BULKHEADW=2", DEPTH=0.060"

Air Works

DENT ON FWD LH ENTRY DOOR NEAR LOWER HINGE FITTINGL=2", DEPTH=0.060"

Air Works

MINOR DENT NEAR AFT EDGE HINGEL=3", DEPTH=0.090"

Air Works



19-May-08 -- -- -- -- -- -- -- 25-May-08

30-Apr-09 -- -- 54-30-01 SJ-20 2986 -- -- -- -- --

11-Jul-09 1 R-4

14-Jul-09 -- -- STARCO -- -- -- -- -- --

14-Jul-09 -- -- STARCO -- -- -- -- -- --

14-Jul-09 -- -- STARCO -- -- -- -- -- --



AIRCRAFT REG: VT-SPT

CHART NO.

GRID REF

TLP REF

SRM/DESIGN REF

TLP REF

SECTION 41-LOWER LOBE SKIN DAMAGE REPAIR

BMN1-837601171-3

108/2008

Permanent repair done

TWO SCRATCHES AND ONE DENT OBSERVED ON #1 ENG THRUST REVERSER TRANSLATING SLEEVE SKIN

All the three damages sealed as per SRM. Permanent repair within 400 FH

BURN MARK -FUSELAGE SKIN- STA 188-203.8,S27R-S27L - TWO POINTS.

53-00-01REPAI

R 13

1.REMOVE THE DAMAGED SOLID RIVETS 1-1 DRILL ONE SIZE LARGER THAN ORG DIAMETER. 2.PERFORM HFEC INSPECTION OF THE FASTENERS HOLE FOR CRACKES AROUND SKIN. RESULT: NO CRACK FOUND. 3.APPLY ALODINE TO THE BARE SURFACE OF THE REPAIR AREA. 4.INSTALL THE SOLID FASTENERS USING NAS1097 TYPE.

EROSION -PANEL (192BL, 192BR)- FUSELAGE

53-40-70 51-70-04

1.ACCORDING SRM51-70-04 REPAIR 10, REPAIR THE EROSION PANEL. 2. RESTORE THE FINISH.

MISSING -FINISH - I/ FLAP LOWER SURFACE -L/H WING

51-70-01 51-21-99

1.REMOVE THE REPAIR AREA PAINT AND CLEAN. 2.FILL THE DENT WITH EC2216 3.LET THE REPAIR CURE SMOOTHLY 4.RESTORE THE PRIMER WITH CA7700 5.RESTORE THE TAP COAT WITH CA8000/B707.

14-Jul-09 -- -- STARCO -- -- -- -- -- --

14-Jul-09 -- -- STARCO -- -- -- -- -- --

14-Jul-09 -- -- THE PANEL 193CL IS ERODE 51-70-04 STARCO -- -- -- -- -- --

14-Jul-09 -- -- THE PANEL 193CR IS ERODE 51-70-04 STARCO -- -- -- -- -- --

14-Jul-09 -- -- 55-30-01 STARCO -- -- -- -- --

14-Jul-09 -- -- 51-70-04 STARCO -- -- -- -- -- --

14-Jul-09 -- -- STARCO -- -- -- -- -- --

14-Jul-09 -- -- 57-41-01 STARCO -- -- -- -- -- --

MISSING -FINISH -I/B FLAP LOWER SURFACE - R/H WING

51-70-01-2R

1.REMOVE THE REPAIR AREA PAINT AND CLEAN. 2.FILL THE DENT WITH EC2216 3.LET THE REPAIR CURE SMOOTHLY 4.RESTORE THE PRIMER WITH CA7700 5.RESTORE THE TAP COAT WITH CA8000/B707.

CRACK- BULKHEAD -WING CENTER SECTION REAR SPAR

SR ID:1-13971320

42

ACCORDING SERVICE REQUEST 2D:1-1397132042, REPAIR THE DAMAGE.

1.ACCORDING SRM51-70-04 REPAIR 10, REPAIR ERODE PANEL. 2.RESTORE THE FINISH.1.ACCORDING SRM51-70-04 REPAIR 10, REPAIR ERODE PANEL. 2.RESTORE THE FINISH.

HF ANTENNA AREA PAINT PEELING OFF

ACCORDING SRM55-30-01 ALLOWABLE DAMAGE 4 PARA.C SRM51-20-08 PARA 4(D) SRM51-20-08 PARA 8 REPAIR DAMAGED HF ANTENNA SURFACE FINISH.

SRM55-30-01 ALLOWABLE DAMAGE 4 PARA.C SRM51-20-08 PARA 4(D) SRM51-20-08 PARA 8

REFER DAMAGE/REPAIR MAPPING CHART RECORD- NO.1 ENGINE O/B T/R 1.SCRATCH VERTICAL APPEAR 8 O'CLOCK LENGTH 605 INCH 2.DENT BELOW APPEAR 8 O'CLOCK DEPTH 1.35INCH 3.VERTICAL SCRATCH APPEAR BELOW 7 O'CLOCK

1.ACCORDING SRM51-70-04 REPAIR10, REPAIR SCRATH OF RECORD(1) (3) 2.ACCORDING SRM51-70-04 REPAIR14 REPAIR DENT OF RECORD (2) 3.RESTORE THE FINISH

REFER DAMAGE/REPAIR MAPPING CHART RECORD- DENT ON APU COWL PANEL L=2.0 INCH, W=1.4 INCH, D=1.1R INCH REF SRM51-10-01

52-40-01 51-10-01

1.REMOVE THW PAINT ON THE SURFACE OF THE DENT AREA. (2). DO AN INSPECTION WITH HFEC FOR CRACK IN DENT SURFACE AREA. RESULT: 3. RESTORE THE FINISH ON THE SURFACE OF THE DENT AREA.

ERODE -PANEL 521MB -LEFT SLAT

1.ACCORDING SRM57-41-01 REPAIR 1, REPAIR DAMAGED AREA. 2.RESTORE THE FINISH.

14-Jul-09 -- -- -- STARCO -- -- -- -- -- --

27.Aug.10 3

DENT -FUSELAGE SKIN - STA1006-STA1016 S-13L - S-15L -TOTAL ONE AREA DEPTH:0.5MM

1.REMOVE THE EXTERNAL FINISH IN THE DENT AREA. 2.DO AN INSPECTION OF THE DENT WITH HFEC FOR CRACK AROUND DENT ON THE SKIN RESULT: NO CRACK FOUND 3.APPLY ALODINE ON THE SURFACE OF THE DAMAGED AREA. 4.APPLY PRIMER USING BMS 10-79 TYPE II AND FILL THE DEPTH WITH.

K-20 L-19

Dent on LH Horizontal Leading Edge at three location 1). A=9.5" , y=0.410" , L=0.5" on top 0.75" on bottom and W=3.25" 2). A=9.0" , Y= 3/32" and W= 2.5" 3). A=9.75" , Y= 18/32" , W=4" and L= 1.25" top 2.5" bottom. Dent found out of limits.



26-Jul-08 4 H 18 53-00-01 SJ-88 1358 DENT WITH IN LIMIT -- -- -- -- --

26-Jul-08 2 L6 DENT ON HS LE AT STA 55-10-01 SJ-88 1358 DENT WITH IN LIMIT -- -- -- -- --

1-Oct-08 -- -- -- -- -- -- 57-53-01 1751 196/08 1-Oct-08

20-Jul-08 4 17 I 53-00-01 SJ-97 1328 DENT WITH IN LIMIT

11-Aug-08 4 17 I-J 53-00-01 SJ-65 1444 DENT WITH IN LIMIT

1-Sep-09 4 G-8 -- SJ-16 4215 51-70-10 -- -- --

10.Sep.09 -- -- 53-00-01 -- -- -- -- --



AIRCRAFT REG: VT-SPU

CHART NO.

GRID REF

TLP REF

SRM/DESIGN REF

TLP REF

DENT ON FUSELAGE STA 351.2 AND STA 360 AND S21R &S22R

DENT FOUND ON RH AFT TRAILING EDGE FLAP AND LEADING EDGE HS

DETAILED VISUAL INSPECTION AT EVERY 5000 FH

DENT FOUND AFT OF FWD CARGODENT FOUND AFT OF FWD CARGO HOLDTWO DENT ON RH AFT OUTBOARD FLAP LOWER SURFACE, LARGE DENT: 3"X3" DEPTH 1/8, SMALL DENT: 1.03"X1.03" ,DEPTH 1/8".

PERMANENTB REPAIR TO BE C/O IN 5 DAYS

DOUBLE DIAMETER 6"

RH AFT R1 DOOR LOWER SIDE WITH DENT AT STA 351.2 AND SECTION 20R

Ops-1692

IDS-63534

AT R1 HFUS BTW.STA 348.2-360 & STR 20-21R DENT: Y=

0.032" W=3.00" DENT WITHIN LIMITS I.A.W SRM 53-00-01 SHEET 5. DENT FREE OF

CRACK REF TO NDT W/S 59

10.Sep.09 -- -- 55-00-01 -- -- -- -- --

29-Jun-10 -- -- 53-00-01 SJ-40 -- -- -- 29-Jun-10

AFT FWD CARGO DOOR STA 500A & S21R WITH DENT

Ops-1692

IDS-63543

AT R1 FUS BTW STA 500A-500B & STA 20-21R DENT:

Y=0.095" W=5.880" DENT WITH IN LIMITS I.A.W SRM 53-00-01SHEET 5. DENT FREE OF CRACK REF TO NDT W/S 58.

During Transit inspection (After A/C Arrival) found Dent on the fuselage aft of the FWD cargo door.

6158 / 6179

Dent observed between BS 500B and BS 500c Dent Mapping c/o as per SRM 53-00-01. found with in limits. Dent Dimension-- W= 3.75" , L=1.5" , Y= 1/8" & W/Y= 30. Damage chart up dated.

Repeat Inspection of

dent for crakat each 5000 FC

interval or more frequently to be

carred out.



18-Apr-07 No.1 M-8 -- SJ-56 -- Minor Damage -- -- -- -- With in Limits

18-Apr-07 No.2 H-19 -- SJ-56 -- Minor Damage -- -- -- -- With in Limits

27-Jun-07 No.3 J-17 53-70-15 SJ-37 -- -- -- -- -- With in Limits






27-Jun-07 No.9 -- Dent in N10 grid -- SJ-59 -- -- -- -- -- -- With in Limits

27-Jun-07 No.10 -- -- SJ-59 -- -- -- -- -- -- With in Limits

27-Jun-07 No.11 -- -- SJ-59 -- -- -- -- -- -- With in Limits

27-Jun-07 No. 12 -- -- SJ-59 -- -- -- -- -- -- With in Limits

11-Sep-07 -- -- 51-70-01 GMF -- -- -- -- -- With in Limits

11-May-07 -- -- 51-70-01 GMF -- -- -- -- -- With in Limits



11-Apr-07 -- -- 51-70-01 GMF -- -- -- -- -- With in Limits

24-Mar-08 1 S4 DENT W-4.5,Y0.095,L3.75 53-00-01 SJ-38 758 -- -- -- -- -- --24-Apr-08 4 P8 DENT W-2,Y1/16,W/Y 32 53-00-01 SJ-36 1030 NIL -- -- -- -- --

7-Feb-09 -- -- 54-10-01 SJ-41 2819 -- -- -- -- --

1-Aug-09 -- -- N008 Closed



AIRCRAFT REG: VT-SPW

CHART NO.

GRID REF

TLP REF

SRM/DESIGN REF

TLP REF

Dent on the cargo door scuff plate, rear warn

Dents at two location shallow and monor

Dent on LH side aft of aft entry door on fuselage

W=1.5"Y=1/32"W/Y=48>30


W=2"Y=1/32"W/Y=64>30


W=1"Y=1/32"W/Y=32>30


W=1"Y=1/32"W/Y=32>30


W=1"Y=1/32"W/Y=32>30


W=1.1/4"Y=1/32"W/Y=40>30

Panel strip with scratches aft cargo door surrounding area07 Minor dent on scuff plate in aft cargo door frameHair line scratches on fwd cargo door near handle

Dent on Lower fuselage STA 312 between STR 20-21 RH side

1. W=1.5" Y=0.033" 2. W=1.5" Y=0.028" W/Y= >30

Dent on fuselage skin STA 1006-1016 STR 12-13L

D=.032"W=2.4"


D=.03"W=2"


D=.037"W=1.8"

Dent on RH wing O/b flap: AFT flap lower surface

1. Y=.031" W=1"2. Y=.031" W=1.5"3. Y=.036" W=1.2"4. Y=.018 W=1"

PUNCTURE OBSERVED NEAR 12ºClOCK POSITION ON #1 ENGINE INLET COWL BARREL ACOUSTIC PANEL PERFORATED SKIN. DIMENSION OF DAMAGE IS 0.25"

PUNCTURE SEALED WITH BMS5-95.REPEAT INSPECTION EVERY 25FC. PERMANENT REPAIR REQUIRED IF FURTHER DETERIORATION IS OBSERVED.

Lighting Strike-Fuselage Skin-STA178-188, S-19r-S25R TOTAL 8 Location.

SRM 53-00-

01Repair13

Corrective Action:1.Remove the Paint of Damaged Area. (2). Remove the affected panel for Access of repair Area.(3).Remove the insulatio of repair area.(4).Remove the Affected parts of repair area for access.(5).Remove Damaged fastener per SRM 51-40-02. (6). Drill the hole 1/32 INCH. (7).Do a HEFC inspection to make sure no hole damange result no found. (8).Install solid fastener as PRE SRM51-40-00 (9).Re-install affected parts of repair area (10).Re-install affected parts of repair area.(11).Re-install the panel of Repair Area (12). Restore the surface protection.

1-Aug-09 -- -- N009 Closed

1-Aug-09 -- -- Holes-Floor-Aft Cargo (3EA) N003 Closed

1-Aug-09 -- -- N0010 Closed

1-Aug-09 -- -- N0011 Closed

Lighting Strike-Fuselage Skin-STA188-196.5 S19R-S21R Total 8 locations.

SRM 53-00-01

Repair 13

Corrective Action:1.Remove the Paint of Damaged area.(2).Remove the Affect insulation of Repair area.(3).Drill out damaged fasteners per SRM 51-40-02.(4).Re-cut the hole 1/32 INCH Oversized per SRM 51-40-05.(5).Do a HFEC inspection to make sure no hole Damage per 737 NDT part6 51-03. (6).Restore the insulation of Repair area. (7).Restore the surface protection per SRM 51-20-01.

SRM 51-70-13 SRM 53-

60-53

Corrective Action:1.Remove the Damaged floor Panel and clean. (2).Cut out the Damaged area at floor panel. (3).Fabricate the repair dobuler.Use from 2024t3-080" (4).Pick up the hole at repair doubler (5).Protect the sorface at doubler.(6).Applprimer and paint on doubler .(7).Install the doubler to floor panel(WEI INSTALL). (8).Reinstall all the floor panel.

Lighting Strike-Fuselage Skin-STA 196.5-203 S-19R-S-21R Total 3 Locations.

SRM 53-00-01

1.Remove thw paint of the Damaged area.(2).Remove the Affect insulation of Reapir area.(3). Drill out Damaged Fastnners per SRM 51-40-05.(4)Re-cut the hole 1/32INCH oversized per SRM 51-40-05.(5). Do a HFEC inspection to make sure no hole Damage per 737NDT Part6 51-00-00 Result. (6).Install solid fastenners per SRM 51-10-03 (7).Restore the installtion of repair area (8).Restore the surface protectiong per SRM 51-20-01. (9).Re-Install the tube of repair area. (10).restore the surface protection.

Lighting Strike-FUSELAGE SKIN-STA 203.8-211.8 S-20R-S-23R TOTAL 8 LOCATIONS.

SRM53-00-01

1.REMOVE THE PAINT OF DAMAGED AREA. 2.REMOVE THE AFFECT INSULATION OF REPAIR AREA. (3).DRILL OUT DAMAGED FASTNNERS PER SRM51-40-02 (4).RE-CUT THE HOLE 1/32INCH OVERSIZED PER 51-40-05.(5) DO A HFEC INSPECTION TO MAKE SURE NO HOLE DAMAGE PER 737NDT PART6 51-00-00 RESULT (6).INSTALL SOLID FASTENNERS PER SRM51-10-03 (7).RESTORE THE INSTALLTION OF REPAIR AREA.(8) RESTORE THE SURFACE SURFACE PROTECTIONG PER SRM51-20-01.(9).RESTORE THE SURFACE PROTECTION PER SRM51-20-01

1-Aug-09 -- -- N0012 Closed

1-Aug-09 -- -- N0013 Closed

1-Aug-09 -- -- N0022 Closed

1-Aug-09 -- -- N0023 Closed

1-Aug-09 -- -- N0024 Closed

LIGHTING STRIKE-FUSELAGE SKIN-STA211.8-219.5 S-20R-S-22R TOTAL 8 LOCATIONS.

SRM 53-00-01

Repair 13

1.REMOVE THE PAINT OF DAMAGED AREA. 2.REMOVE THE AFFECT INSULATION OF REPAIR AREA. (3).DRILL OUT DAMAGED FASTNNERS PER SRM51-40-02 (4).RE-CUT THE HOLE 1/32INCH OVERSIZED PER 51-40-05.(5) DO A HFEC INSPECTION TO MAKE SURE NO HOLE DAMAGE PER 737NDT PART6 51-00-00 RESULT (6).INSTALL THE RIVET PER SRM 51-40-03 (7).RESTORE THE INSULATION OF REPAIR AREA. (8).RESTORE THE SURFACE PROTECTION PER SRM 51-20-01.

LIGHTING STRIKE-FUSELAGE SKIN-STA 219.8-224.5 S-21R-S23R TOTAL 8 LOCATIONS.

SRM 53-00-01

Repair 13

1.REMOVE THE PAINT OF DAMAGED AREA. 2.BLEND TO THE DAMAGE REF TO ALLOWABLE DAMAGE 1 (3).DO AHFEC INSPECTION ON REWORKED SURFACE FOR CRACK PER 737 NDT PART6 51-00-00 (4).INSPECT MATERIAL THICKNESS OF REWORK AREA PER 737 NDT PART6 51-00-00 ORG: REMAIN: (5).RESTORE CHEMICAL CONVERSION COATING TO BARE SURFACE OF REPAIR AREA PER SRM51-20-01 (6).RESTORE SURFACE PROTECTION PER SRM51-21-01

LIGHTING STRIKE-FUSELAGE SKIN-STA492.4-500 S-19R-S-22R TOTAL 8 LOCATIONS.

SRM53-00-01

REPAIR 13

1.REMOVE THE PAINT FROM DAMAGED AREA (2).REMOVE THE AFFECT INSULATION OF REPAIR AREA. (3).DRILL OUT DAMAGED FASTENERS PER SRM 51-40-02 (4).RE-CUT THE HOLE 1/32INCH OVERSIZED PER SRM 51-40-02. (5).DO A HFEC INSPECT TO MAKE SURE NO HOLE DAMAGE PER 737 NDT PART6 51-00-00 RESUL: (6).INSTALL SOLID RIVET PER SRM 51-40-03.(7).RESTORE THE INSTALLTION OF REPAIR AREA. (8).RESTORE THE SURFACE PROTECTION PER SRM 51-20-01.

LIGHTING STRIKE-FUSELAGE SKIN-STA500-500A S-21R-S23R TOTAL 5 LOCATIONS.

SRM53-00-01

1.REMOVE THE PAINT FROM DAMAGED AREA (2).REMOVE THE AFFECT INSULATION OF REPAIR AREA. (3).DRILL OUT DAMAGED FASTENERS PER SRM 51-40-05 (4).RE-CUT THE HOLE 1/32INCH OVERSIZED PER SRM 51-40-02. (5).DO A HFEC INSPECT TO MAKE SURE NO HOLE DAMAGE PER 737 NDT PART6 51-00-00 RESUL: (6).INSTALL SOLID FASTENNERS PER SRM 51-410-03(7).RESTORE THE INSTALLTION OF REPAIR AREA. (8).RESTORE THE SURFACE PROTECTION PER SRM 51-20-01.

LIGHTING STRIKE-FUSELAGE SKIN-STA500D-500E S-21R-S23R TOTAL 5 LOCATIONS.

SRM53-00-01

1.REMOVE THE PAINT FROM DAMAGED AREA (2).REMOVE THE AFFECT INSULATION OF REPAIR AREA. (3).DRILL OUT DAMAGED FASTENERS PER SRM 51-40-05 (4).RE-CUT THE HOLE 1/32INCH OVERSIZED PER SRM 51-40-02. (5).DO A HFEC INSPECT TO MAKE SURE NO HOLE DAMAGE PER 737 NDT PART6 51-00-00 RESUL: (6).INSTALL SOLID FASTENNERS PER SRM 51-410-03(7).RESTORE THE INSTALLTION OF REPAIR AREA. (8).RESTORE THE SURFACE PROTECTION PER SRM 51-20-01.

1-Aug-09 -- -- N0025 Closed

1-Aug-09 -- -- N0026 Closed

1-Aug-09 -- -- N0027 Closed

1-Aug-09 -- -- N0030 Closed

1-Aug-09 -- -- N0031 Closed

1-Aug-09 -- -- N0032 Closed

LIGHTING STRIKE-FUSELAGE SKIN-STA500E-500F S-19R-S-22R TOTAL 5 LOCATIONS.

SRM53-00-01

1.REMOVE THE PAINT OF DAMAGED AREA.(2).REMOVE THE INSULATION OF REPAIR AREA.(3).DRILL OUT THE DAMAGE PER SRM51-10-02.(4)DO A HFEC INSPECTION OF OPEN FASTENER HOLE FOR CRACKS REFER 737NDT PART6 51-00-00 RESULT---. (5).INSTALL A SOLID RIVET PER SRM 51-21-02 (6).RESTORE THE INSULATION OF REPAIR AREA. (7).RESTORE THE SURFACE PROTECTION PER SRM 51-21-01 AND AMM 51-21-00.

LIGHTING STRIKE-FUSELAGE SKIN-STA500F-500G S-20R-S-24R TOTAL 5 LOCATIONS.

SRM53-00-01

1.REMOVE THE PAINT OF DAMAGED AREA.(2).REMOVE THE INSULATION OF REPAIR AREA.(3).DRILL OUT THE DAMAGE PER SRM51-10-02.(4)DO A HFEC INSPECTION OF OPEN FASTENER HOLE FOR CRACKS REFER 737NDT PART6 51-00-00 RESULT---. (5).INSTALL A SOLID RIVET PER SRM 51-21-02 (6).RESTORE THE INSULATION OF REPAIR AREA. (7).RESTORE THE SURFACE PROTECTION PER SRM 51-21-01.

LIGHTING STRIKE-FUSELAGE SKIN-STA480-500 S-19L-S-22L TOTAL 5 LOCATIONS.

SRM53-00-01

1.REMOVE THE PAINT OF DAMAGED AREA.(2).REMOVE THE INSULATION OF REPAIR AREA.(3).DRILL OUT THE DAMAGE PER SRM51-40-02.(4).RE-CUT THE HOLE 1/32INCH OVERSIZED PER51-40-05 (5).DO A HFEC INSPECTION TO MAKE SURE NO HOLE DAMAGE PER 737NDT PART6 51-00-00 RESULT--- (6).INSTALL SOLID FASTNNERS PER SRM 51-10-03 (7).RESTORE THE INSTALLTION OF REPAIR AREA.(8).RESTORE THE SURFACE PROTECTIONG PER SRM51-20-01.

DENT-FUSELAGE SKIN-STA188-WL208 L/H

SRM 53-00-01

1.REMOVE THE PAINT AT DENT AREA AS PER AMM 51-21 (2).MEASUER THE DENT DIMENSION AND REPORT AS PER SRM 53-00-01. RESULT:

LIGHING STRIKE-FUSELAGE SKIN-STA727F-727G S-19R-S-21R TOTAL 2 LOCATIONS.

SRM53-00-01

1.REMOVE THE PAINT OF DAMAGED AREA. (2).REMOVE THE INSULATION OF REPAIR AREA. (3).DRILL OUT THE DAMAGE PER SRM51-10-02 (4).DO A HFEC INSPECTION OF OPEN FASTENER HOLE FOR CRACKS PER 737NDT PART6 51-00-00 (5).INSTALL A SELID RIVET PER SRM51-40-02. (6).RESTORE THE INSULATION OF REPAIR AREA. (7).RESTORE THE SURFACE PROTECTION PER SRM 51-21-10

LIGHTING STRIKE-FUSELAGE SKIN-STA727G-727H S-19R-S-22R TOTAL 2 LOCATIONS.

SRM53-00-01

1.REMOVE THE PAINT OF DAMAGED AREA. (2).REMOVE THE INSULATION OF REPAIR AREA. (3).DRILL OUT THE DAMAGE PER SRM51-10-02 (4).DO A HFEC INSPECTION OF OPEN FASTENER HOLE FOR CRACKS PER 737NDT PART6 51-00-00 RESULT---(5).INSTALL A SELID RIVET PER SRM51-40-02. (6).RESTORE THE INSULATION OF REPAIR AREA. (7).RESTORE THE SURFACE PROTECTION PER SRM 51-21-10

1-Aug-09 -- -- N0033 Closed

1-Aug-09 -- -- N0034 Closed

1-Aug-09 -- -- N0035 Closed

1-Aug-09 -- -- N0039 Closed

1-Aug-09 -- -- N0041 Closed

1-Aug-09 -- -- N0042 Closed

1-Aug-09 -- -- N0043 Closed

LIGHTING STRIKE-FUSELAGE SKIN-STA727H-727I S-19R-S-22R TOTAL 2 LOCATIONS.

SRM53-00-01

1.REMOVE THE PAINT OF DAMAGED AREA. (2).REMOVE THE INSULATION OF REPAIR AREA. (3).DRILL OUT THE DAMAGE PER SRM51-10-02 (4).DO A HFEC INSPECTION OF OPEN FASTENER HOLE FOR CRACKS PER 737NDT PART6 51-00-00 RESULT---(5).INSTALL A SELID RIVET PER SRM51-40-02. (6).RESTORE THE INSULATION OF REPAIR AREA. (7).RESTORE THE SURFACE PROTECTION PER SRM 51-21-10

LIGHTING STRIKE-FUSELAGE SKIN-STA727J-747 S-20R-S-22R TOTAL 2 LOCATIONS.

SRM53-00-01

REPAIR 13

1.REMOVE THE PAINT OF DAMAGED AREA.(2).REMOVE THE AFFECT INSULATION OF REPAIR AREA. (3).DRILL OUT DAMAGED FASTENERS PER SRM51-49-02. (4).RE-CUT THE HOLE 1/32INCH OVERSIZED PER SRM 51-40-05. (5).DO A HFEC INSPECT TO MAKE SURE NO HOLE DAMAGE PER 737NDT PART6 51-00-00 RESULT---(6).INSTALL THE RIVET PER SRM 51-40-03,(7).RESTORE THE INSULATION OF REPAIR AREA.(8).RESTORE THE SURFACE PROTECTION PER SRM 51-20-01.

LIGHTING STRIKE-FUSELAGE SKIN-STA747-767 S-20R-S-23R TOTAL 2 LOCATIONS.

SRM53-00-01

REPAIR 13

1.REMOVE THE PAINT FROM THE DAMAGED AREA.(2).REMOVE THE AFFECT INSULATION OF REPAIR AREA.(3).DRILL OUT DAMAGED FASTENERS PER SRM 51-40-02. (4).DO A HFEC INSPECT TO MAKE SURE NO HOLE DAMAGE PER 737NDT PART6 51-00-00 RESULT--- (5).INSTALL THE RIVET PER SRM 51-40-03. (6)RESTORE THE INSULATION OF REPAIR AREA. (7).RESTORE THE SURFACE PROTECTION PER SRM 51-20-01.

LIGHTING STRIKE-FUSELAGE SKIN-STA951-967 S-19R-S-21R OTAL 2 LOCATIONS.

SRM53-00-01

1.REMOVE THE PAINT FROM THE DAMAGED AREA.(2).BLEND OUT THE DAMAGE GIVEN INALLOWABLE AREA.(3).DO A HIGH FREQUENCY EDDY CURRENT INSPECT PROCEDURE ON THE SURFACE FOR CRACK REFER 737 NDT PART6 51-00-00 RESULT---- (4).PERFORM INSPECTION FOR THICKNESS REWORK AREA ORG THINKNESS: REMAIN THINKNESS: (5).RESTORE SURFACE PROTECTION PER SRM 51-21-01 AND AMM 51-21-00

LIGHTING STRIKE -FUSELAGE SKIN-STA 951-967 S-19L-S-21L TOTAL 1 LOCATIONS.

SRM53-00-01

1.REMOVE THE PAINT OF DAMAGED AREA. (2).BLEND OUT THE DAMAGE GIVEN INALLOWABLE AREA. (3).INSPECT THE DAMAGE AREA USING HFEC PER 737 NDT PART6 51-00-00 RESULT---- (4).PERFORM INSPECTION FOR THICKNESS REWORK AREA REFER 737NDT PART4 51-00-00 ORG THINKNESS: REMAIN THINKNESS: (5).RESTORE SURFACE PROTECTION PER SRM 51-21-01 AND AMM 51-21-00

DENT-FUSELAGE SKIN-STA905-927 S-19R-S-22R- DEPTH:1.42MM DIAMETER:15MM

SRM53-00-01

1.REMOVE THE PAINT AT DENT AREA AS PER AMM 51-21 (2).MEASUER THE DENT DIMENSION AND REPORT AS PER SRM 53-00-01. RESULT:

CORROSION-FUSELAGE SKIN-STA905-927 S-19R-S-21R

SRM51-40-02 SRM53-00-01

1.REMOVE THE PAINT AT CORRSION AREA AS PER AMM 51-21 (2).REMOVE THE ORG FASTENERS AT CORRSION AREA AS PER SRM 51-40-02 (3).REMOVE THE CORRSION BY HAND AS PER SRM 53-00-01 (4).NDT MEASURE THE ORG THK AND REMAIN THK BY ULTRASONIC. RESULT:

1-Aug-09 -- -- N0045 Closed

1-Aug-09 -- -- N0048 Closed

1-Aug-09 -- -- N0056 Closed

1-Aug-09 -- -- N0059 Closed

1-Aug-09 -- -- N0060 Closed

1-Aug-09 -- -- N0062 Closed

1-Aug-09 -- -- N0076 Closed

1-Aug-09 -- -- N0088 Closed

1-Aug-09 -- -- N0089 Closed

1-Aug-09 -- -- N0090 Closed

THE FUSELAGE UPPER SHELL FOUND FASTENER HEADS PAINT PEELED-OFF

AMM51-21

SRM53-00-01

1.REMOVE THW PEELED PAINT 2.CLEAN THE REPAIR AREA. 3.RESTORE THE PRIMER WITH CA7700 4.RESTORE THE TOP COAT WITH CA8000/BAC7408.

LIGHT STRIKE-FUSELAGE SKIN-STA420-440,S-20R-S-23R TOTAL 3 LOCATION

SRM53-00-01

1.REMOVE THE PAINT OF THE DAMAGED AREA. 2.REMOVE THE AFFECT INSULATION OF REPAIR AREA. 3.DRILL OUT DAMAGED FASTNNERS PER SRM 51-40-05 4.RE-CUT THE HOLE 1/32INCH OVERSIZED PER 51-40-02 5.DO A HFEC INSPECTION TO MAKE SURE NO HOLE DAMAGE PER 737NDT PART6 51-00-00 RESULT---- 6.INSTALL SOLID FASTENNERS PER SRM 51-10-03. 7.RESTORE THE INSTALLATION OF REPAIR AREA. 8.RESTORE THE SURFACE PROTECTIONG PER SRM51-20-01

CORROSION-FORWARD ASSEMBLY ACCESS PANEL-FAIRING-WING(542AB/543AB/643AB/644AB)

SRM57-53-70

1.REMOVE THE FORWARD FAIRING (2).ACCORDING SRM57-53-70 REPAIR 1 REPAIR EROSSION AREA (3).RE-INSTALL THE FORWARD FAIRING.

HOLE-FLOOR FWD CARGO (1EA)

SRM51-70-01 SRM53-30-53

1.REMOVE THE DAMAGED FLOOR. 2.CUT OUT THE DAMAGED AREAS.AS PER SRM51-70-13. 3.FABRICATE THE REPAIR DOUBLER USE FROM 2024T3-0.080" 4.PICK UP THE HOLE AT REPAIR PARTS. 5.PROTECT THE REPAIR PARTS SURFACE. 6.INSTALL THE DOUBLER TO REPAIR AREAS. 7.REINSTALL THE PANEL.

DENT-FUSELAGE SKIN-STA 1006-1030 S-11L-S-15L

SRM53-00-01 SRM51-70-01

1.REMOVE THE PAINT FROM DAMAGED SURFACE AND CLEAN. 2.MEASURE THE DENT DIMENSION AND REPORT RESULT:

SCATCH-AFT CARGO DOOR-STA827-845,S17R-S19R

SRM52-30-01

1.REMOVE THE SCATCH AT AFT CARGO DOOR. 2.MEASURE THE ORG THK AND REMAIN THK. RESULT: 3.INSPECTION THE REWORK AREA FOR CRACK FREE. RESULT: 4.REPROTECT THE REWORK AREA. 5.RESTORE THE PAINT AT REWORK AREA.

BROKEN-NUTPLATE-AFT CEILING-FWD CARGO

SRM51-40-02

1.REMOVE THE DAMAGED PLATE NUT. 2.CLEAN THE REPAIR AREA. 3.INSTALL THE NEW FASTENERS TO CEILING.

DAMAGE FLAME-AFT CARGO-STA272I,STR-14L/R-17L/R

SRM51-70-01

1.DRESS OUT THE DAMAGED AT FRAME CLIP. 2.PERFORM INSPECTION FOR CRACK FREE. RESULT: 3.IF CRACK FREE REPROTECT THE REWORK SURFACE. 4.RESTORE THE PAINT, AT REWORK AREA.

BROKEN-NUT PLATE-FLOOR-AFT CARGO.

SRM51-40-02

1.REMOVE THE DAMAGED FASTENERS. 2.CLEAN THE REPAIR AREA. 3.REINSTALL THE NEW FASTNERS.

ERODE ACCESS PANEL 521ZB L/H WING

SRM51-70-05

REPAIR 9

1.REMOVE THE DAMAGED MATERIAL AND CLEAN THE REPAIR AREA. 2.MIXTURE CG1305+CHOPPED FIBERS AND FILL THE REPAIR HOLE. 3.LET THE REPAIR CURE SMOTH IT. 4.RESTORE THE HOLE

1-Aug-09 -- -- N0091 Closed

1-Aug-09 -- -- N0092 Closed

1-Aug-09 -- -- N0098 Closed

1-Aug-09 -- -- N0099 Closed

1-Aug-09 -- -- N0096 Closed

1-Aug-09 -- -- N0111 Closed

1-Aug-09 -- -- N0112 Closed

1-Aug-09 -- -- N0113 Closed

1-Aug-09 -- -- N0114 Closed

1-Aug-09 -- -- N0115 Closed

1-Aug-09 -- -- N0116 Closed

ERODE-DRAIN HOLE-LOWER SURFACE-MOVABLE FLAP FAIRING NO.1# & 2# -L/H WING

SRM57-53-70 P105

1.ACCORDING SRM57-53-70 PARA2 REPAIR THE ERODE AREA WITH EA934A/B 2.RESTORE THE FINISH.

BROKEN-NUT-TRAILING CORE-3# TRAILING EDGE FLAP-L/H WING

SRM51-40-02

1.REMOVE THE DAMAGE FASTENERS. 2.CLEAN THE REPAIR AREA. 3.INSTALL THE NEW FASTENERS.

LIGHTING STRIKER-LOWER SURFACE-WINGLET-L/H WING

SRM51-40-02

1.REMOVE THE LIGHTING STRIKE FASTENER. 2.PERFORM THE INSPECTION FOR CRACK FREE. RESULT: 3.IF CRACK FREE REINSTALL THE NEW FASTENERS. 4.APPLY THE PAINT TO REPAIR AREAS.

CRACK(DOUBT)-NO.2 SLAT-L/E-L/H WING

SRM51-40-00

1.REMOVE THE R/H VORTILION FROM#2 LEADING EDGE SLAT. 2.DO THE CHECK AROUND THE DOUTED CRACK, AND RECORD THE CHECK RESULT. RESULT:NO CRACK FOUND.

BROKEN-INTERCOSTAL TRACK-AFT CARGO.

SRM53-00-53

1.REMOVE THE BROKEN TRACK. 2.CUT OUT THE DAMAGED SECTION. 3.FABRICATE THE SPLICE SECTION AND DOUBLER USE FROM BAC1496-377-7075T62. 4.PICK UP THE HOLE AT REPAIR PARTS. 5.PROTECT THE SURFACE ON REPAIR PARTS. 6.APPLY THE PRIMER ON REPAIR PARTS. 7.INSTALL THE DOUBLER TO REPAIR SECTION(WET INSTALL). 8.REINSTALL THE TRACK.

LIGHTING STRIKE-OUTBOARD SURFACE-TRAILING EDGE WINGLET-R/H WING

SRM51-40-02

1.REMOVE THE DAMAGED RIVETS. 2.INSPECT THE RIVET HOLES BY EDDY CURRENT. RESULT: 3.WET INSTALL THE NEW RIVETS WITH BMS5-95 4.RESTORE SURFACE PROTECTION.

LIGHTING STRIKE-OUTBOARD SURFACE-TRAILING EDGE WINGLET-L/H WING

SRM51-40-02


LIGHTING STRIKE-STAB BL281.81-TRAILING EDGE WINGLET- L/H WING

SRM51-40-01


LIGHTING STRIKE-TRAILING EDGE-PANEL 326A-VERTICAL FIN

SRM55-30-30

1.REMOVE THE DAMAGED AT T/E. 2.MEASURE THE REMOVE DIMENSION. 3.IF WITH IN LIMIT REPROTECT THE REWORK AREA. 4.RESTORE THE PAINT AT REWORK AREA.

ERODE-LEADING EDGE-PANEL 326A-VERTICAL FIN (5 POINTS)

SRM55-30-30

THE CANOPY ERODE POINT REPAIR. 1.REMOVE DAMAGED MATERIAL AND CLEAN. 2.FILL THE DAMAGED AREA WITH EA934A/B. 3.LET THE REPAIR CURE SMOTH IT. 4.RESTORE THE FINISH.

BROKEN-NUTPLATE-FLOOR-FWD CARGO

SRM51-40-02

1.REMOVE THE DAMAGED FASTENERS. 2.CLEAN THE REPAIR AREA. 3.REINSTALL THE NEW FASTENERS.

1-Aug-09 -- -- MISSING- 2 NUT PLATES-621 VB N0118 Closed

1-Aug-09 -- -- DENT-INBOARD FLAP. N0119 Closed

1-Aug-09 -- -- DENT-GROUND SPOILER N0120 Closed

1-Aug-09 -- -- N0121 Closed

1-Aug-09 -- -- DENT-PANEL 651DB N0122 Closed

1-Aug-09 -- -- N0123 Closed

1-Aug-09 -- -- MISSING-NUT PLATE-621YB N0124 Closed

1-Aug-09 -- -- N0127 Closed

1-Aug-09 -- -- N0136 Closed

5-Feb-10 1 J18 Dent on LH Horizontal Stabilizer LE 55-10-01 SJ-23 With in Limits

1-Aug-10 -- -- N0015 Closed

1-Aug-10 -- -- N0017 Closed

SRM51-40-01


SRM57-53-70 P105

1.ACCORDING SRM57-53-70 PARA2 REPAIR THE DENT WITH EA934A/B 2.RESTORE THE FINISH.

SRM51-70-01

1.ACCRDING THE SRN51-70-01. USE EC2216A/B FILL THE DENT. 2.RESTORE THE FINISH.

BROKEN-NUT PLATE STRIP 621YB

SRM51-40-01


SRM57-53-70 P105

1.ACCORDING SRM57-53-70 PARA2 REPAIR THE DENT WITH EA934A/B 2.RESTORE THE FINISH.

EDODE-DRAIN HOLE-RIGHT WING KRUGER FLAP

SRM57-53-

70P105

1.ACCORDING SRM57-53-70 PARA2 REPAIR THE DENT WITH EA934AB 2.RESTORE THE FINISH.

SRM51-40-01

1.REMOVE THE DAMAGED FASTENERS. 2.REINSTALL THE NEW FASTENERS.

CORROSION-R/H & L/H INTER COSTAL TRACK FWD CARGO-STA5000G-STA500H.

SRM53-00-53

1.REMOVE THE LIGHT CORROSION AT F/W CARGO ZEE SECTION. 2.CLEAN THE REPAIR AREA. 3.PROTECT THE REPAIR AREA. 4.APPLY THE PRIMER AT REPAIR AREA.

MISSING PRINGTING-LOWER SURFACE-INNER FLAP-L/H WING

SRM51-21-99

1.REMOVE THE DAMAGED FINISH. 2.FILL THE DENT WITH EC2216A/B 3.LET THE REPAIR CURE SMOTH IT. 4.CLEAN THE REPAIR AREA. 5.RESTORE THE PRIMER WITH CA7700. 6.RESTORE THE TOP COAT WITH CA8000/B707.

52925293

1. L=3.5", 2. Y= 0.125", 3. W= 2.5". Repeat at every 400 FH.Permanent repair with in 5000FH/18 Months.

LIGHTING STRIKE-FUSELAGE SKIN STA251.5-268.23 S-20R-S-24R TOTAL 2 LOCATIONS.

SRM 53-00-01

Repair 13

1.REMOVE THE PAINT OF DAMAGED AREA. (2).REMOVE THE TUBE OF REPAIR AREA FOR ACESS. (3). REMOVE THE AFFECT INSULATION OF REPAIR AREA (4). DRILL OUT DAMAGED FASTENNERS PER SRM 51-40-02.(5).DRILL HOLE 1/32 INCH OVERSIZED (6).PERFORM HFEC INSPECTION TO MAKE SURE NO HOLE DAMAGE PER 737NDT PART6 51-00-00 RESULT--- (7).INSTALL SOLID FASTENNERS PER SRM 51-40-02. (8).RESTORE INSTALLTION OF REPAIR AREA. (9).RE-INTALL THE PANEL OF REPAIR AREA. (10).RESTORE THE SURFACE PROTECTIONG PER SRM51-20-01.

LIGHTING STRIKE-FUSELAGE SKIN STA312-328 S-21R-S-26R TOTAL 2 LOCATIONS.

SRM 53-00-01

Repair 13

1.REMOVE THE PAINT OF DAMAGED AREA. (2).REMOVE THE TUBE OF REPAIR AREA FOR ACESS. (3). REMOVE THE AFFECT INSULATION OF REPAIR AREA (4). DRILL OUT DAMAGED FASTENNERS PER SRM 51-40-02.(5).DRILL HOLE 1/32 INCH OVERSIZED (6).PERFORM HFEC INSPECTION TO MAKE SURE NO HOLE DAMAGE PER 737NDT PART6 51-00-00 RESULT--- (7).INSTALL SOLID FASTENNERS PER SRM 51-40-02. (8).RESTORE INSTALLTION OF REPAIR AREA. (9).RE-INTALL THE PANEL OF REPAIR AREA. (10).RESTORE THE SURFACE PROTECTIONG PER SRM51-20-01.

1-Aug-10 -- -- N0018 Closed

1-Aug-10 -- -- N0019 Closed

1-Aug-10 -- -- N0020 Closed

1-Aug-10 -- -- N0021 Closed

LIGHTING STRIKE-FUSELAGE SKIN -STA325.38-330.62 S-25R-S-27R TOTAL 2 LOCATION

SRM 53-00-01

ALLOWABLE

DAMAGE1

1.REMOVE THE PAINT OF DAMAGED AREA. (2). BLEND OUT THE DAMAGE GIVEN INALLOWABLE AREA. (3).INSPECT THE DAMAGE AREA USING HFEC PER 737NDT PART6 51-00-00 RESULT (4). PERFORM INSPECTION FOR THIKNESS REWORK AREA REFER 737 NDT PART4 51-00-00 ORG THINKNESS: REMAIN THINKNESS: (5).RESTORE SURFACE PROTECTION PER SRM 51-21-01 AND AMM 51-21-00

LIGHTING STRIKE-FUSELAGE SKIN-STA351.2-360.5 S-24R-S-26R TOTAL 2 LOCATIONS.

SRM 53-00-01

Repair 13

1.REMOVE THE PAINT FROM DAMAGED AREA (2).REMOVE THE AFFECT INSULATION OF REPAIR AREA. (3).DRILL OUT DAMAGED FASTENERS PER SRM 51-40-02. (4).RE-CUT DAMAGED FASTENERS PER SRM 51-40-02. (5).DO A HFEC INSPECT TO MAKE SURE NO HOLE DAMAGE PER 737 NDT PART6 51-00-00 RESUL: (6).INSTALL THE SOLID FASTENERS PER SRM 51-40-03.(7).RESTORE THE INSULATION OF REPAIR AREA. (8).RESTORE THE SURFACE PROTECTION PER SRM 51-20-01.


SRM 53-00-

01Repair13

1.REMOVE THE PAINT FROM DAMAGED AREA (2).REMOVE THE AFFECT INSULATION OF REPAIR AREA. (3).DRILL OUT DAMAGED FASTENERS PER SRM 51-40-02 (4).RE-CUT THE HOLE 1/32INCH OVERSIZED PER SRM 51-40-02. (5).DO A HFEC INSPECT TO MAKE SURE NO HOLE DAMAGE PER 737 NDT PART6 51-00-00 RESUL: (6).INSTALL THE RIVET PER SRM 51-40-03.(7).RESTORE THE INSULATION OF REPAIR AREA. (8).RESTORE THE SURFACE PROTECTION PER SRM 51-20-01.


SRM53-00-

01REPAIR 13

1.REMOVE THE PAINT FROM DAMAGED AREA (2).REMOVE THE AFFECT INSULATION OF REPAIR AREA. (3).DRILL OUT DAMAGED FASTENERS PER SRM 51-40-02 (4).RE-CUT THE HOLE 1/32INCH OVERSIZED PER SRM 51-40-02. (5).DO A HFEC INSPECT TO MAKE SURE NO HOLE DAMAGE PER 737 NDT PART6 51-00-00 RESUL: (6).INSTALL SOLID RIVET PER SRM 51-40-03.(7).RESTORE THE INSTALLTION OF REPAIR AREA. (8).RESTORE THE SURFACE PROTECTION PER SRM 51-21-01.



1-Aug-08 2 P13 51-42-01 SJ-88 1117 Dent is within limit -- -- -- --

39692 3 G15 53-53-01 SJ-88 2000 Dent is within limit -- -- -- --

39692 3 G15 53-53-01 SJ-89 2000 Dent is within limit -- -- -- --



AIRCRAFT REG: VT-SGA

CHART NO.

GRID REF

TLP REF

SRM/DESIGN REF

TLP REF

dent on no 5 L/E slat (STBD) LENGTH (L) #3.30" WIDTH (W) # 1.30"DEPTH(Y) # 0.04"W/Y # 32

Dent is within limit

First dent :- length (l) #0.7width # 0.6"depth# 0.005"


First dent :- length (l) #0.8width # 0.6"depth# 0.005"




2-Jun-08 -- -- SJ-18 023 WITHIM AMM LIMITS -- -- -- -- --

1-Aug-09 3 SJ-95 2795 WITHIN SRM LIMITS -- -- -- -- --

25-Jan-10 3 M18 DENT 53-00-01 -- WITHIN LIMITS -- -- -- -- --

26-Jan-10 2 L19 LIGHTNING STRIKE -- -- -- -- -- 28-Jan-10 --

26-Jan-10 2 L18 LIGHTNING STRIKE -- -- -- -- -- 28-Jan-10 --

26-Jan-10 2 K17 LIGHTNING STRIKE -- -- -- -- -- 28-Jan-10 --


26-Jan-10 2 J11 LIGHTNING STRIKE -- -- -- -- -- 28-Jan-10 --

26-Jan-10 1 P5 LIGHTNING STRIKE -- -- -- -- -- 28-Jan-10 --

26-Jan-10 1 P6 LIGHTNING STRIKE -- -- -- -- -- 28-Jan-10 --

26-Jan-10 1 N9 LIGHTNING STRIKE -- -- -- -- -- 28-Jan-10 --


28-Jan-10 4 O11 GPUGE -- WITHIN LIMITS -- -- -- -- --

28-Jan-10 4 O11 SCRATCH -- WITHIN LIMITS -- -- -- -- --



AIRCRAFT REG: VT-SGB

CHART NO.

GRID REF

TLP REF

SRM/DESIGN REF

TLP REF

TWO DENTS ON #5 ACOUSTIC PANEL (#1 ENGINE) 1. 1.5" X 2.4"2. 2.5" X 1.5"

AMM72-23-02

B-18&

B-19

A MINOR SURFACE SCRATCH ON LOWER SURFACE OF LEFT WINGLET.

SRM57-30-01

MAS 2179

53-00-01REPAIR 13

MAS 2179

53-00-01REPAIR 13

MAS 2179

53-00-01REPAIR 13

MAS 2179

53-00-01REPAIR 13

MAS 2179

53-00-01REPAIR 13

MAS 2179

53-00-01REPAIR 13

MAS 2179

53-00-01REPAIR 13

MAS 2179

53-00-01REPAIR 13

MAS 2179

737-EO-53-4616 REVA

MAS 2179

53-00-01FIG103

MAS 2363

52-30-01 FIG103

MAS 2363

7-Jul-10 2 N5 SJ-88 5008

Dent (RH Horizontal stabilizer leading edge skin). Length (L)= 2.8" Width (W) = 2.0" Depth (Y) = 0.080"

55-10-01 51-70-01

DENY found with in SRM limits. Temp Repair C/O as per SRM 57-70-01.

Dent insp to be c/o at each 400

FH. Permanent

repair to be c/o as or before

5000 FH or 18 Months.



13-Jun-09 4 H18 SJ-88 2510 WITHIN LIMITS -- -- -- -- --

21-Nov-09 2 O14 SJ-47 3644 WITHIN LIMITS -- -- -- -- --

7-Feb-10 4 G18 WITHIN LIMITS -- -- -- -- --

03.Mar.10 1 J17 DENT IS WITHIN LIMIT. -- -- -- -- --

03.Mar.10 1 N8 57-41-01 DENT IS WITHIN LIMIT. -- -- -- -- --

03.Mar.10 4 J17 53-00-00 DENT IS WITHIN LIMIT. -- -- -- -- --



AIRCRAFT REG: VT-SGC

CHART NO.

GRID REF

TLP REF

SRM/DESIGN REF

TLP REF

SCRATCH ON RH ALTERNATE STATIC PORT PERIPHERY.DEPTH= 0.008", LENGTH=1.6"

AMM34-11-02

DENT ON RH I/B FIXED LEADING EDGE JUST ABOVE STALL STRIPW=2", Y=0.0625" , W/Y=32

SRM 57-41-01

SCRATCH AT STAION 390, STR25R

SRM 53-00-00

MAS 2386

DENT BETWEEN BS1006 TO BS1016, S13L TO S14L L=2", W=1" DEPTH= 0.015"

53-00-01 FIG 103

MAS 2021

IRC SYS

-00012 (MAS)

DENT ON RH IB FIXED LE DUCT ABOVE STALL STRIP DEPTH=0.0625" WIDTH=2"

MAS 2005

IRC SYS

-00014 (MAS)

SCRATCH AT BS 390, STR 25R L=1", W=.5" DEPTH=.004"

MAS 2386

IRC SYS - 00168



9-Nov-09 1 T4 53-00-01 SJ-69 1997 DENT WITHIN LIMITS -- -- -- -- --

17.Aug.10 1 I-18 55-10-01 SJ-47 3981 DENT WITHIN LIMITS -- -- -- -- --



AIRCRAFT REG: VT-SGD

CHART NO.

GRID REF

TLP REF

SRM/DESIGN REF

TLP REF

DENT AHEAD OF STA 203.8 AT LEFT OUTBOARD OF FWD E & E COMPARTMENT

DENT ON LH LEADING EDGE HORIZONTAL STAB. WIDTH A=114mm Y=1.5mm

of 55



20-Nov-07 1 Q-11 57-41-01 SJ-14 137 WITHIN LIMITS -- -- -- -- --

18/10/07 51-70-01 GMF With in limits -- -- -- -- --





19/10/07 GMF With in limits -- -- -- -- --


19/10/07 GMF With in limits -- -- -- -- --

6-Jun-08 1 S-13 DENT ON #3 SLAT 57-42-01 SJ-21 1394 WITHIN LIMIT -- -- -- -- --

6-Jun-08 1 R-10 57-41-01 SJ-21 1394 WITHIN LIMIT -- -- -- -- --

6-Jun-08 1 P-12 57-70-01 SJ-21 1394 WITHIN LIMIT -- -- -- -- --

17-Apr-07 SJ-56 1430 WITHIN LIMIT -- -- -- -- --

9-May-07 SJ-11 1660 WITHIN LIMIT -- -- -- -- --

20-Nov-07 1 Q11 Dent on LH wing Inboard Fined LE 57-41-01 SJ-14 137 -- -- -- -- --



AIRCRAFT REG: VT-SGE

CHART NO.

GRID REF

TLP REF

SRM/DESIGN REF

TLP REF

DENT ON LH WING INBOARD LEW=2", L=2", Y=0.0625, W/Y=32Tail Compt door skin dentA=2", Y=0.051"

Dent on LH side fuselage skinSTA 1004-1016 STR 13-141. A=1", Y=0.030" W/Y=33.332. A=2.5", Y=0.074 W/Y=33.78

Dent on LH side fuselage skin STA 1004-1016 STR 14-151. A=1.5", Y=0.040" W/Y=37.502. A=1", Y=0.025 W/Y=40

Dent on LH side fuselage skin STA 1004-1016 STR 14-151. A=2.5", Y=0.036" W/Y=69.442. A=1.25", Y=0.038 W/Y=32.89Dent on LH side fuselage skin STA 1016-1040 STR 13-14A=2.25", Y=0.05"Dent on Left wing inboard spoiler no. 6A=2", Y=0.1025

57-70-0151-70-10

Dent at L/E RH wing ws BTW 150 -156A=3.25", Y=0.0975, A/Y=>30Dent at leading edge of LH stabA=2.5", Y=0.0525

DENT ON LE ABOVE #1 KRUEGER FLAPDENT ON #6 SPOILER INBOARD SIDE ON LOWER SURFACEDENT ON RH WING INBD LEADING EDGESMALL DENT ON VERTICAL STABLIZER LEADING EDGE

SRM55-30-01

W=2 Inch L=2 Inch Y= 0.0625 inch W/Y=32

of 55




AIRCRAFT REG: VT-SGE

23-Feb-09 Eng#1 SJ-07 With in AMM Limits. -- -- -- -- --



7-Apr-09 -- -- -- -- -- -- --

7-Apr-09 -- -- -- -- -- -- --

7-Apr-09 -- -- -- -- -- -- --

Area K

Distoration on LE Area K Blade no 5. Q= 1/16" N= 2.5"

72-21-02 Fig

605/606

TLP 2152

Area K

Distoration on LE Area K Blade No6. Q#3/32" N#2".

72-21-02 Fig

605/606

TLP 2152

Area K

Distoration on LE Area K Blade No22 Q#3/32" N#2"

72-21-02 Fig

605/606

TLP 2152

MULTIPLE DAMAGES ON AFT CARGO COMP. FLOOR PANEL 140BF.

SRM 51-40-02

THY51 B11748

NCR-0009

AFT CARGO COMP. (140BF) FLOOR PANEL HAS BEEN REPLACED. AFT CARGO FLOOR PANEL HAS BEEN PAINTED. AFT CARGO (140 BF) HAS BEEN INSTALLED.

DAMAGED FLOOR PANEL 140CF IN AFT CARGO COMP.

SRM 51-70-13

THY51 B1372

NCR-0010

AFT CARGO COMP. FLOOR PANEL HAS BEEN REPAIRED(140CF).

MULTIPLE DAMAGES ON AFT CARGO COMP. FLOOR PANEL 140AF.

SRM 51-40-02

THY51 B11748

NCR-0008

DAMAGED FLOOR PANEL IN AFT CARGO COMPARTMENT (140 AF) HAS BEEN REPLACED . AFT CARGO COMP. FLOOR PANEL HAS BEEN PAINTED. NEW FLOOR PANEL IN AFT. CARGO HAS BEEN INSTALLED.



24.Aug.10 57-41-01 SJ-17 450 -- 450 -- 24.Aug.10 --



AIRCRAFT REG: VT-SGG

CHART NO.

GRID REF

TLP REF

SRM/DESIGN REF

TLP REF

Bird hit observed. Dent on left wing Root (IN Board of L/P L.T) with blood stratter.

Dents found on Aluminum strakele Dent insp. c/o as per SRM 57-41-01 dent found with in limits .

dent map form no sj tsd 027

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