FIELD ENGINEERING AUTHORIZATION REPAIR
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NO. : B737NG-EAR-57-20384 DATE : MAY 30 , 2016
AIRCRAFT DESC. : EX PK-LHY W.O REF : 469050
SUBJECT : NO : B737NG-EAR-57-20384
PERMANENT REPAIR DENT AT LEADING DATE : MAY 30th, 2016
EDGHE R/H OUTBOARD AFT FLAP PN
REFERENCE : SEE REFERENCE
113A3700-26 SN 003764
CATEGORY : RECOMENDED A/C TYPE : B737-900ER
SECTION : BASE MAINTENANCE
TYPE : PERMANENTECTIVITY
REPAIR EFFECTIVITY : SEE EFFECTIVITY
DUE DATE : SEE COMPLIANCE
PRIORITY : NORMAL WT/ARM CHANGE : NONE
QA, REPAIR, PPC, CAME,
ATTENTION : EST. MAN HOURS : SEE MAN HOURS
CAMO, BM, LM
REASON OF REVISION
NONE
REASON
During maintenance Phase 19 of PK-LHY at Lion Air's Hangar Batam, found dent at leading
edge R/H outboard aft flap, with dimension length: 13.50 inch, depth: 0.24 inch, width: 1.8
inch.
DESCRIPTION
This Engineering Authorization Repair provides instruction for permanent repair dent at
leading edge R/H outboard aft flap.
EFFECTIVITY
PREPARED BY CHECKED BY APPROVED BY
ROZI DINI HARBI KURNIA KRISHARYONO ASEP R.BACHTIAR
DISTRIBUTION QA REPAIR PPC BM LM CAME CAMO FILE
BT-TSF-01-017/R0, Issued date May 2016 PAGE 1 OF 22
FIELD ENGINEERING AUTHORIZATION REPAIR
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NO. : B737NG-EAR-57-20384 DATE : MAY 30 , 2016
AIRCRAFT DESC. : EX PK-LHY W.O REF : 469050
PART PART NUMBER SERIAL NUMBER
RH OUTBOARD AFT FLAP
113A3700-26 003764
( EX PK-LHY )
PREPARED BY CHECKED BY APPROVED BY
ROZI DINI HARBI KURNIA KRISHARYONO ASEP R.BACHTIAR
DISTRIBUTION QA REPAIR PPC BM LM CAME CAMO FILE
BT-TSF-01-017/R0, Issued date May 2016 PAGE 2 OF 22
FIELD ENGINEERING AUTHORIZATION REPAIR
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NO. : B737NG-EAR-57-20384 DATE : MAY 30 , 2016
AIRCRAFT DESC. : EX PK-LHY W.O REF : 469050
COMPLIANCE
Perform this repair immediately after this EAR published.
EST. MAN HOURS
24 MAN HOURS
WEIGHT AND BALANCE
NONE
REFERENCES
B737-900ER SRM 57-53-01 REPAIR 6
NDTM 51-00-00 PART 6
B737-900ER SRM 51-10-02 PARAGRAPH 10
AMM 51-21-72 PARAGRAPH 5
SRM 51-40-02 PARAGRAPH 4
BAT-SP-0001
BAT-SP-0004
BAT-SP-0012
PUBLICATION AFFECTED
Publication Chapter / Section
None None
MATERIAL REQUIREMENTS
DISBOND AT R/H OUTBOARD AFT FLAP LOWER SURFACE
No Description Part Number QTY
Repair Plate
1 Aluminum Sheet Bare 2024 T42 1
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FIELD ENGINEERING AUTHORIZATION REPAIR
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NO. : B737NG-EAR-57-20384 DATE : MAY 30 , 2016
AIRCRAFT DESC. : EX PK-LHY W.O REF : 469050
(0.071 inch)
Aluminum Sheet Bare 2024 T42
2 Doubler 1
(0.071 inch)
Continued...
No Description Part Number QTY
3 Rivet BACR15CE5D8 70 EA
4 Sealant BMS 5 95 B2, or PS 870 B2 1 Kit
5 Primer BMS 10-11, Type I 1 Kit
6 Paint (Coating) BMS 10-60 Type II 1 kit
7 Alodine Alodine 1200 200 cc
SPECIAL TOOL AND EQUIPMENT
NONE
ACCOMPLISHMENT INSTRUCTION
CAUTION : Obey all of the procedures, requirements and precautions in this task
when you perform this engineering authorization for safety and
securities.
Make sure the procedures used during this Engineering Authorization
implementation give sufficient protection to persons and equipments.
CAUTION : Keep the work area, wires and electrical bundles clean of metal
particles or contamination when you use tools. Un-wanted material,
metal particles or contamination caught in wire bundles can cause
damage to the bundles. Damaged wire bundles can cause sparks or
other electrical damage.
BT-TSF-01-017/R0, Issued date May 2016 PAGE 4 OF 12
FIELD ENGINEERING AUTHORIZATION REPAIR
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NO. : B737NG-EAR-57-20384 DATE : MAY 30 , 2016
AIRCRAFT DESC. : EX PK-LHY W.O REF : 469050
NO DESCRIPTION PERFORMED BY DATE
Read all step of this FEAR making sure that you
have understood of the work to be performed. If
you have any discrepancy or if any step is not clear
consult to engineering that originated this FEAR.
1 Get access to the damage area.
Remove the damaged leading edge skin from the
2
aft flap assembly.
Cut and remove the damaged part of the leading
edge skin as shown in Figure 2. Refer to 51-10-02
3
paragraph 10 for the procedures to remove the
damage.
Make the cut in the shape of a rectangle with the
4
longer sides parallel to the leading edge ribs.
Make sure there is a minimum of two rows of repair
5
fasteners around the edges of the cutout.
BT-TSF-01-017/R0, Issued date May 2016 PAGE 5 OF 12
FIELD ENGINEERING AUTHORIZATION REPAIR
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NO. : B737NG-EAR-57-20384 DATE : MAY 30 , 2016
AIRCRAFT DESC. : EX PK-LHY W.O REF : 469050
INSPECTOR
Do HFEC inspection around cut out area to ensure no
cracks exist per B737 NDTM part 6, 51-00-00.
6
NDT Result:
Make the repair plate and doubler with Aluminum
7 sheet Bare 2024 T42 (0.071 inch) as shown in
figure 2.
NO DESCRIPTION PERFORMED BY DATE
Make the contour of the repair parts the same
as the contour of the initial skin.
8
NOTE: MAKE SURE THAT THE REPAIR
DOUBLER DOES NOT OVERLAP THE CHEM-
MILLED RADIUS OF THE SKIN
9 Assemble the parts as shown in Figure 2.
10 Drill and countersink the fastener holes.
11 Disassemble the parts as shown in figure 2.
Remove the nicks, scratches, gouges, and sharp
12 edges from the repair parts and the bare surfaces
of the initial skin.
BT-TSF-01-017/R0, Issued date May 2016 PAGE 6 OF 12
FIELD ENGINEERING AUTHORIZATION REPAIR
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NO. : B737NG-EAR-57-20384 DATE : MAY 30 , 2016
AIRCRAFT DESC. : EX PK-LHY W.O REF : 469050
Do HFEC rotary inspect any open fastener holes INSPECTOR
to ensure no cracks exist refer to B737 NDTM
13 Part 6, 51-00-00.
NDT Result:
Apply a chemical conversion coating to the
14 repair part and the bare surfaces of the initial
part. Refer to BAT-SP-0001.
Apply one layer of BMS 10-11, Type I primer to
15 the repair parts and the bare surfaces of the
initial Skin refer to AMM 51-21-72 paragraph 5.
Install the repair parts with BMS 5-95 sealant
16 between the mating surfaces. Refer to BAT-SP-
0004.
NO DESCRIPTION PERFORMED BY DATE
Install fastener BACR15CE5D8 refer to SRM 51-
17
40-02 paragraph 4.
Fill the space between the [1] repair plate and
18 the initial skin with BMS 5-95 sealant. Refer to
BAT-SP-0004.
Apply one layer of BMS 10-60, type II enamel to
19
the repair area. Refer to BAT-SP-0012
Inspect all repair area or repair part installed (if INSPECTOR
20 any). Confirmation that the repair has been
accomplished without any deviation.
Record all (actual) consumable material used in
21
this Accomplished Instruction to Table 1.
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FIELD ENGINEERING AUTHORIZATION REPAIR
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NO. : B737NG-EAR-57-20384 DATE : MAY 30 , 2016
AIRCRAFT DESC. : EX PK-LHY W.O REF : 469050
Record the final repair photo and attach to Figure
22
3 as report if this EAR performed (Carried Out).
Put the part/component back to a serviceable
23
condition.
All above steps have been done without any deviation and put the part back to serviceable
condition.
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FIELD ENGINEERING AUTHORIZATION REPAIR
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NO. : B737NG-EAR-57-20384 DATE : MAY 30 , 2016
AIRCRAFT DESC. : EX PK-LHY W.O REF : 469050
Figure 1. Outboard Aft Flap Position
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FIELD ENGINEERING AUTHORIZATION REPAIR
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NO. : B737NG-EAR-57-20384 DATE : MAY 30 , 2016
AIRCRAFT DESC. : EX PK-LHY W.O REF : 469050
FIGURE 2. AFT FLAP LEADING EDGE SKIN REPAIR
(Sheet 1 of 2)
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FIELD ENGINEERING AUTHORIZATION REPAIR
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NO. : B737NG-EAR-57-20384 DATE : MAY 30 , 2016
AIRCRAFT DESC. : EX PK-LHY W.O REF : 469050
FIGURE 2 AFT FLAP LEADING EDGE SKIN REPAIR
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FIELD ENGINEERING AUTHORIZATION REPAIR
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NO. : B737NG-EAR-57-20384 DATE : MAY 30 , 2016
AIRCRAFT DESC. : EX PK-LHY W.O REF : 469050
(Sheet 2 of 2)
Curing Ambient
Part Qty. Exp. Batch
No. Description Time Temp.
Number (actual) Date Number
(Minute) (C0)
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FIELD ENGINEERING AUTHORIZATION REPAIR
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NO. : B737NG-EAR-57-20384 DATE : MAY 30 , 2016
AIRCRAFT DESC. : EX PK-LHY W.O REF : 469050
Table 1. List of Actual Consumable Material Used
PICTURE AFTER REPAIR
BT-TSF-01-017/R0, Issued date May 2016 PAGE 13 OF 12
FIELD ENGINEERING AUTHORIZATION REPAIR
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NO. : B737NG-EAR-57-20384 DATE : MAY 30 , 2016
AIRCRAFT DESC. : EX PK-LHY W.O REF : 469050
BT-TSF-01-017/R0, Issued date May 2016 PAGE 14 OF 12
FIELD ENGINEERING AUTHORIZATION REPAIR
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NO. : B737NG-EAR-57-20384 DATE : MAY 30 , 2016
AIRCRAFT DESC. : EX PK-LHY W.O REF : 469050
Figure 3. Final Repair Picture
STATION: STARTED TIME: FINISHED TIME :
RII : YES NO ACTUAL MAN HOURS :
INSPECTED BY RELEASED BY
AUTH. NO.
SIGN STAMP DATE SIGN DATE
STAMP
BT-TSF-01-017/R0, Issued date May 2016 PAGE 15 OF 12
