### Commercial **Airplanes** 

# 767 Service Bulletin **ALERT Number: 767-53A0228**  Original Issue: July 28, 2011 ATA System: 5350 **SUBJECT:** FUSELAGE - Fuselage Section 45 - Overwing Emergency Exit Hatch Openings - Lower Main Sill - Inspection Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2011 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 1 of 54 5.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 2 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION ........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 1. Existing Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 2. Data supplied with this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 3. Installation Drawings Used in the Preparation of this Service Bulletin. . . . . . . . . . . . 27 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 27 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 29 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 29 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 FIGURE 1: LEFT SIDE - OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 883.5 - INSPECTIONS [Group 1; Group 4, Configuration 1]. . . . . . . . . . . . . . . . . 39 FIGURE 2: LEFT SIDE - FORWARD OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 883.5 - INSPECTIONS [Group 2; Group 4, Configuration 2]. . . . . . . . . . 41 FIGURE 3: LEFT SIDE - AFT OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 903.5 - INSPECTIONS [Group 2; Group 4, Configuration 2]. . . . . . . . . . . . . 43 FIGURE 4: LEFT SIDE - OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 903.5 - INSPECTIONS [Group 3; Group 4, Configuration 3]. . . . . . . . . . . . . . . . . 45 FIGURE 5: RIGHT SIDE - OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 883.5 - INSPECTIONS [Group 1; Group 4, Configuration 1]. . . . . . . . . . . . . . . . . 47 FIGURE 6: RIGHTSIDE - FORWARD OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 883.5 - INSPECTIONS [Group 2; Group 4, Configuration 2]. . . . . . . . . . 49

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 3 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**FIGURE 7: RIGHT SIDE - AFT OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 903.5 - INSPECTIONS [Group 2; Group 4, Configuration 2]. . . . . . . . . . . . . 51 FIGURE 8: RIGHT SIDE - OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 903.5 - INSPECTIONS [Group 3; Group 4, Configuration 3]. . . . . . . . . . . . . . . . . 53

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 4 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**

### Commercial **Airplanes** 

# 767 Service Bulletin **ALERT Summary**  **Number: 767-53A0228** Original Issue: July 28, 2011 ATA System: 5350 **SUBJECT:** FUSELAGE - Fuselage Section 45 - Overwing Emergency Exit Hatch Openings - Lower Main Sill - Inspection THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. **CONCURRENT REQUIREMENTS** None. **BACKGROUND** Cracking has been reported on the lower main sill inner chord of the overwing emergency exit hatch opening at Body Station (STA) 884, Stringer 18R. The cause of the cracking is fatigue. If cracking exists in the lower main sill of the overwing emergency exit hatch opening and is not repaired, it could result in reduced structural integrity of the overwing emergency exit hatch opening and consequent rapid decompression of the airplane. The problem was discovered on a regular maintenance visit on an airplane that had completed 42,079 flight cycles. This service bulletin gives instruction to find and repair cracking of the lower main sill inner chord and surrounding structure. Boeing Service Related Problem (SRP) 767-SRP-53-0358 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 767 FTD 53-10001 is related to this service bulletin. **ACTION** Disarm the off-wing escape system. Remove seats, overwing emergency exit hatches, sidewall panels and sidewall insulation as necessary to get access to the lower main sills of the overwing emergency exit hatch openings. **Group 1-2; Group 4, Configuration 1-2:** At STA 883.5, do a surface High Frequency Eddy Current (HFEC) and detailed inspections of the lower main sill inner chord. Also, do a detailed inspection of the surrounding structure. If any crack, corrosion damage, or other irregularity is found, do the applicable SRM repair or contact Boeing for repair instructions.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 5 of 54**Group 2-3; Group 4, Configuration 2-3:** At STA 903.5, do a detailed inspections of the lower main sill inner chord and surrounding structure. If any crack, corrosion damage, or other irregularity is found, do the applicable SRM repair or contact Boeing for repair instructions. Install all removed sidewall insulation, sidewall panels, overwing emergency exit hatches and seats. Arm the off-wing escape system. Put the airplane back to a serviceable condition. **Group 4, Configuration 4:** No work is necessary. This configuration is for airplanes not yet delivered that will have no overwing emergency exit hatches. **EFFECTIVITY** 767-200/-300 series airplanes with overwing emergency exit hatches. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. **COMPLIANCE** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Refer to Paragraph 1.E., Compliance. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service bulletin. **MANPOWER WORK PACKAGE 1 - LEFT SIDE**  **Elapsed Hours Total Task Hours**  **Airplanes** 5.00 9.00 Group 1; Group 4, Configuration 1 7.65 13.95 Group 2; Group 4, Configuration 2 4.35 8.35 Group 3; Group 4, Configuration 3
**WORK PACKAGE 2 - RIGHT SIDE Elapsed Hours**  **Total Task Hours Airplanes**  5.00 9.00 Group 1; Group 4, Configuration 1 7.65 13.95 Group 2; Group 4, Configuration 2 4.35 8.35 Group 3; Group 4, Configuration 3 Refer to Paragraph 1.G., Manpower.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 6 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT MATERIAL INFORMATION**  None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 7 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 8 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**

BLANK PAGE

### Commercial **Airplanes** 

# 767 Service Bulletin **ALERT Number: 767-53A0228**  Original Issue: July 28, 2011 ATA System: 5350 **SUBJECT:** FUSELAGE - Fuselage Section 45 - Overwing Emergency Exit Hatch Openings - Lower Main Sill - Inspection THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplane(s) shown below. **NOTE:** This service bulletin is for the airplanes identified below. The effectivity list shown below is complete for airplanes through line number 1017. At least one airplane after line number 1017 is also affected by this service bulletin, and these airplanes are in Group(s) 2,4. These airplanes will be added to the service bulletin's MyBoeingFleet.com (MBF) \"get effectivity\" result when they are added to the MBF Fleet Profile Page.
**DESCRIPTION CONFIGURATION**  **GROUP** 767-200 airplanes through line number 1020 with a single forward overwing emergency exit hatch on each side of the airplane. - 1
767-200/-300 airplanes through line number 1020 with two overwing emergency exit hatches on each side of the airplane. - 2
767-300 airplanes through line number 1020 with a single aft overwing emergency exit hatch on each side of the airplane. - 3

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 9 of 54**DESCRIPTION CONFIGURATION**  **GROUP** 767 airplanes after line number 1020. These airplanes are not yet delivered and their configuration is unknown. - 4
Airplanes with a single forward overwing emergency exit hatch on each side of the airplane. 1
Airplanes with two overwing emergency exit hatches on each side of the airplane. 2
Airplanes with a single aft overwing emergency exit hatch on each side of the airplane. 3
Airplanes with no overwing emergency exit hatches. 4

Airplane Models: 767-200, 767-300 **Group Variable Number**  1 VA001 - VA020 1 VA301 - VA315 1 VA501 - VA530 1 VA701 - VA719 1 VA801 - VA810 1 VB001 - VB002 1 VB051 - VB055 1 VB101 - VB125 1 VB201 - VB202 1 VB251 - VB253 1 VB281 - VB284 2 VB301 - VB302 2 VB321 - VB332 1 VB371 - VB373 1 VB401 1 VB441 - VB444 1 VE001 - VE003 1 VE021 - VE023 1 VE041 - VE043

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 10 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT Group**  **Variable Number** 1 VE061 - VE069 1 VE083 - VE086 1 VE101 - VE104 1 VE116 - VE118 1 VE121 - VE126 1 VE141 - VE152 1 VE171 - VE172 1 VF001 - VF002 1 VF041 - VF042 1 VF051 1 VF061 - VF062 1 VF071 - VF072 1 VF091 - VF093 2 VF101 - VF102 1 VF161 - VF162 1 VF171 - VF172 1 VF180 - VF184 1 VF251 2 VK001 - VK016 2 VK021 - VK022 2 VK031 - VK056 2 VK081 - VK113 2 VK141 - VK148 3 VK161 - VK164 2 VK171 2 VK181 2 VK186 3 VL001 - VL006 3 VL011 2 VL701 - VL703 3 VL751 - VL755 2 VL931 - VL932 2 VL941

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 11 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT Group**  **Variable Number** 2 VN001 - VN041 2 VN051 - VN064 2 VN081 - VN099 2 VN151 - VN158 2 VN163 - VN168 3 VN171 - VN174 2 VN191 - VN198 3 VN211 - VN212 2 VN221 - VN225 3 VN231 - VN234 3 VN241 - VN243 2 VN251 - VN276 2 VN291 - VN293 3 VN301 - VN314 2 VN422 - VN427 2 VN436 2 VN491 - VN513 3 VN634 - VN636 2 VN651 - VN658 2 VN671 - VN672 2 VN676 2 VN681 - VN691 2 VN731 - VN732 2 VN751 - VN753 3 VN791 - VN792 2 VN811 - VN813 2 VN931 - VN936 2 VN966 - VN972 1 VR051 - VR060 1 VR081 1 VR084 1 VR086 - VR089 1 VR106 - VR109

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 12 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT Group**  **Variable Number** 2 VR401 2 VR421 - VR423 2 VR426 2 VR441 2 VR461 2 VR471 - VR472 3 VS061 2 VS066 - VS070 2 VS073 - VS078 2 VS091 - VS104 2 VS111 - VS113 2 VS131 - VS133 2 VS176 - VS177 2 VS186 - VS187 2 VS196 - VS203 2 VS206 - VS208 2 VS231 2 VS266 - VS274 2 VS291 - VS293 2 VS301 - VS303 2 VS366 - VS367 2 VS381 - VS382 2 VS391 - VS392 2 VS401 2 VS466 - VS472 2 VS486 3 VS496 - VS497 3 VS506 - VS507 2 VS526 2 VS546 - VS549 2 VS701 - VS736 2 VS751 - VS759 2 VS821 - VS825

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 13 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT Group**  **Variable Number** 2 VS841 - VS844 2 VS861 2 VS896 2 VS901 - VS912 2 VS921 - VS928 2 VS931 - VS933 2 VS951 - VS954 2 VS961 - VS967 2 VS971 - VS975 1 VV001 2. Spares Affected None. **B. Concurrent Requirements** None. **C. Reason** Cracking has been reported on the lower main sill inner chord of the lower main sill of the overwing emergency exit hatch opening at Body Station (STA) 884, Stringer 18R. The cause of the cracking is fatigue. If cracking exists in the lower main sill of the overwing emergency exit hatch opening and is not repaired, it could result in reduced structural integrity of the overwing emergency exit hatch opening and consequent rapid decompression of the airplane. The problem was discovered on a regular maintenance visit on an airplane that had completed 42,079 flight cycles. This service bulletin gives instruction to find and repair cracking of the lower main sill inner chord and surrounding structure. Boeing Service Related Problem (SRP) 767-SRP-53-0358 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 767 FTD 53-10001 is related to this service bulletin. **D. Description** Disarm the off-wing escape system. Remove seats, overwing emergency exit hatches, sidewall panels and sidewall insulation as necessary to get access to the lower main sills of the overwing emergency exit hatch openings.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 14 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT Group 1-2; Group 4, Configuration 1-2:**  At STA 883.5, do a surface High Frequency Eddy Current (HFEC) and detailed inspections of the lower main sill inner chord. Also, do a detailed inspection of the surrounding structure. If any crack, corrosion damage, or other irregularity is found, do the applicable SRM repair or contact Boeing for repair instructions. **Group 2-3; Group 4, Configuration 2-3:** At STA 903.5, do a detailed inspections of the lower main sill inner chord and surrounding structure. If any crack, corrosion damage, or other irregularity is found, do the applicable SRM repair or contact Boeing for repair instructions. Install all removed sidewall insulation, sidewall panels, overwing emergency exit hatches and seats. Arm the off-wing escape system. Put the airplane back to a serviceable condition. **Group 4, Configuration 4:** No work is necessary. This configuration is for airplanes not yet delivered that will have no overwing emergency exit hatches. **NOTE:** If the damaged area is more than the specified limits, write to Boeing for repair instructions. Give the size and location of the damage. When possible, send sketches and photographs. If the damage includes corrosion, send data on the length, width, and largest depth of clean up. Send to: BOEING COMMERCIAL AIRPLANES GROUP ATTENTION: MANAGER, AIRLINE SUPPORT The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1:**
**Affected Maintenance Zones Zone**  **Model** 241, 242 767-200 **Group 2,4:**
**Affected Maintenance Zones Zone**  **Model** 241, 242 767-200, 767-300 **Group 3:**
**Affected Maintenance Zones Zone**  **Model** 241, 242 767-300

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 15 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT E. Compliance**  The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. **Group 1; Group 4, Configuration 1: Table 1: Overwing Emergency Exit Hatch Opening - Lower Main Sill - Inspection and Repair - WORK**  **PACKAGE 1 - LEFT SIDE Repeat Interval**  **(Not to Exceed) Compliance Time**  **(Whichever Occurs Later) Action**  **Condition**

- Within 3,000 flight cycles after the original issuedate of this service bulletin Before 37,500 total flight cycles Do a HFEC inspection of the lower main sill inner chord around STA883.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 1, Step 2.b., and All airplanes

Do detailed inspections of the lower main sill inner chord and surrounding structure around STA883.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 1, Step 2.b. 3,750 flight cycles (a) Within 3,750 flight cycles after the initial detailed inspection Repeat the detailed inspections of the lower main sill inner chord and surrounding structure around STA883.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 1, Step 2.b., and No crack, corrosiondamage, or other irregularity is found

7,500 flight cycles (a) Within 7,500 flight cycles after the initial HFEC inspection Repeat the HFEC inspection of the lower main sill inner chord around STA 883.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 1, Step 2.b. (a) Before further flight Repair in accordance with Para- graph 3.B., Work Instructions WORK PACKAGE 1, Step 2.b.(1) Any crack is found in the lower main sill inner chord Before further flight Contact Boeing for instructions and do the work instructed by Boeing Any corrosion damage or other irregularity is found in the lower main sill inner chord

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 16 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT Group 1; Group 4, Configuration 1:**  **Table 1: Overwing Emergency Exit Hatch Opening - Lower Main Sill - Inspection and Repair - WORK PACKAGE 1 - LEFT SIDE**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition** 

- Before further flight Contact Boeing for instructions and do the work instructed by Boeing Any crack, corrosiondamage, or other irregularity is found in the structure other than the lower main sill inner chord (a) Accomplishment of the repair in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 1, Step 2.b.(1) terminates the inspections in this service bulletin at this location. **Group 1; Group 4, Configuration 1: Table 2: Overwing Emergency Exit Hatch Opening - Lower Main Sill - Inspection and Repair - WORK**  **PACKAGE 2 - RIGHT SIDE Repeat Interval**  **(Not to Exceed) Compliance Time**  **(Whichever Occurs Later) Action**  **Condition**

- Within 3,000 flight cycles after the original issuedate of this service bulletin Before 37,500 total flight cycles Do a HFEC inspection of the lower main sill inner chord around STA883.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 2, Step 2.b., and All airplanes

Do detailed inspections of the lower main sill inner chord and surrounding structure around STA883.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 2, Step 2.b. 3,750 flight cycles (a) Within 3,750 flight cycles after the initial detailed inspection Repeat the detailed inspections of the lower main sill inner chord and surrounding structure around STA883.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 2, Step 2.b., and No crack, corrosiondamage, or other irregularity is found

7,500 flight cycles (a) Within 7,500 flight cycles after the initial HFEC inspection Repeat the HFEC inspection of the lower main sill inner chord around STA 883.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 2, Step 2.b. (a) Before further flight Repair in accordance with Para- graph 3.B., Work Instructions WORK PACKAGE 2, Step 2.b.(1) Any crack is found in the lower main sill inner chord

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 17 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT Group 1; Group 4, Configuration 1:**  **Table 2: Overwing Emergency Exit Hatch Opening - Lower Main Sill - Inspection and Repair - WORK PACKAGE 2 - RIGHT SIDE**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition**  Before further flight Contact Boeing for instructions and do the work instructed by Boeing Any corrosion damage or other irregularity is found in the lower main sill inner chord

- Before further flight Contact Boeing for instructions and do the work instructed by Boeing Any crack, corrosiondamage, or other irregularity is found in the structure other than the lower main sill inner chord (a) Accomplishment of the repair in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 2, Step 2.b.(1) terminates the inspections in this service bulletin at this location.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 18 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT Group 2; Group 4, Configuration 2:**  **Table 3: Overwing Emergency Exit Hatch Openings - Lower Main Sill - Inspection and Repair - WORK PACKAGE 1 - LEFT SIDE**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition** 
Within 3,000 flight cycles after the original issuedate of this service bulletin Before 37,500 total flight cycles Do a HFEC inspection of the lower main sill inner chord around STA883.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 1, Step 3.b., and All airplanes

Do detailed inspections of the lower main sill inner chord and surrounding structure around STA883.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 1, Step 3.b. 3,750 flight cycles (a) Within 3,750 flight cycles after the initial detailed inspection Repeat the detailed inspections of the lower main sill inner chord and surrounding structure around STA883.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 1, Step 3.b., and No crack, corrosiondamage, or other irregularity is found

7,500 flight cycles (a) Within 7,500 flight cycles after the initial HFEC inspection Repeat the HFEC inspection of the lower main sill inner chord around STA 883.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 1, Step 3.b. (a) Before further flight Repair in accordance with Para- graph 3.B., Work Instructions WORK PACKAGE 1, Step 3.b.(1) Any crack is found in the lower main sill inner chord Before further flight Contact Boeing for instructions and do the work instructed by Boeing Any corrosion damage or other irregularity is found in the lower main sill inner chord

- Before further flight Contact Boeing for instructions and do the work instructed by Boeing Any crack, corrosiondamage, or other irregularity is found in the structure other than the lower main sill inner chord

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 19 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT Group 2; Group 4, Configuration 2:**  **Table 3: Overwing Emergency Exit Hatch Openings - Lower Main Sill - Inspection and Repair - WORK PACKAGE 1 - LEFT SIDE**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition** 

- Within 3,000 flight cycles after the original issuedate of this service bulletin Before 37,500 total flight cycles Do detailed inspections of the lower main sill inner chord and surrounding structure around STA903.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 1, Step 3.c. All airplanes

3,750 flight cycles (b) Within 3,750 flight cycles after the initial detailed inspection Repeat the detailed inspections of the lower main sill inner chord and surrounding structure around STA903.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 1, Step 3.c. No crack, corrosiondamage, or other irregularity is found

(b) Before further flight Repair in accordance with Para- graph 3.B., Work Instructions WORK PACKAGE 1, Step 3.c.(1) Any crack is found in the lower main sill inner chord Before further flight Contact Boeing for instructions and do the work instructed by Boeing Any corrosion damage or other irregularity is found in the lower main sill inner chord

- Before further flight Contact Boeing for instructions and do the work instructed by Boeing Any crack, corrosiondamage, or other irregularity is found in the structure other than the lower main sill inner chord (a) Accomplishment of the repair in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 1, Step 3.b.(1) terminates the inspections in this service bulletin at this location. (b) Accomplishment of the repair in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 1, Step 3.c.(1) terminates the inspections in this service bulletin at this location.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 20 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT Group 2; Group 4, Configuration 2:**  **Table 4: Overwing Emergency Exit Hatch Openings - Lower Main Sill - Inspection and Repair - WORK PACKAGE 2 - RIGHT SIDE**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition** 

- Within 3,000 flight cycles after the original issuedate of this service bulletin Before 37,500 total flight cycles Do a HFEC inspection of the lower main sill inner chord around STA883.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 2, Step 3.b., and All airplanes

Do detailed inspections of the lower main sill inner chord and surrounding structure around STA883.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 2, Step 3.b. 3,750 flight cycles (a) Within 3,750 flight cycles after the initial detailed inspection Repeat the detailed inspections of the lower main sill inner chord and surrounding structure around STA883.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 2, Step 3.b., and No crack, corrosiondamage, or other irregularity is found

7,500 flight cycles (a) Within 7,500 flight cycles after the initial HFEC inspection Repeat the HFEC inspection of the lower main sill inner chord around STA 883.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 2, Step 3.b. (a) Before further flight Repair in accordance with Para- graph 3.B., Work Instructions WORK PACKAGE 2, Step 3.b.(1) Any crack is found in the lower main sill inner chord Before further flight Contact Boeing for instructions and do the work instructed by Boeing Any corrosion damage or other irregularity is found in the lower main sill inner chord

- Before further flight Contact Boeing for instructions and do the work instructed by Boeing Any crack, corrosiondamage, or other irregularity is found in the structure other than the lower main sill inner chord

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 21 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT Group 2; Group 4, Configuration 2:**  **Table 4: Overwing Emergency Exit Hatch Openings - Lower Main Sill - Inspection and Repair - WORK PACKAGE 2 - RIGHT SIDE**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition** 

- Within 3,000 flight cycles after the original issuedate of this service bulletin Before 37,500 total flight cycles Do detailed inspections of the lower main sill inner chord and surrounding structure around STA903.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 2, Step 3.c. All airplanes

3,750 flight cycles (b) Within 3,750 flight cycles after the initial detailed inspection Repeat the detailed inspections of the lower main sill inner chord and surrounding structure around STA903.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 2, Step 3.c. No crack, corrosiondamage, or other irregularity is found

(b) Before further flight Repair in accordance with Para- graph 3.B., Work Instructions WORK PACKAGE 2, Step 3.c.(1) Any crack is found in the lower main sill inner chord Before further flight Contact Boeing for instructions and do the work instructed by Boeing Any corrosion damage or other irregularity is found in the lower main sill inner chord

- Before further flight Contact Boeing for instructions and do the work instructed by Boeing Any crack, corrosiondamage, or other irregularity is found in the structure other than the lower main sill inner chord (a) Accomplishment of the repair in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 2, Step 3.b.(1) terminates the inspections in this service bulletin at this location. (b) Accomplishment of the repair in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 2, Step 3.c.(1) terminates the inspections in this service bulletin at this location.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 22 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT Group 3; Group 4, Configuration 3:**  **Table 5: Overwing Emergency Exit Hatch Opening - Lower Main Sill - Inspection and Repair - WORK PACKAGE 1 - LEFT SIDE**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition** 

- Within 3,000 flight cycles after the original issuedate of this service bulletin Before 37,500 total flight cycles Do detailed inspections of the lower main sill inner chord and surrounding structure around STA903.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 1, Step 4.b. All airplanes

3,750 flight cycles (a) Within 3,750 flight cycles after the initial detailed inspection Repeat the detailed inspections of the lower main sill inner chord and surrounding structure around STA903.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 1, Step 4.b. No crack, corrosiondamage, or other irregularity is found

(a) Before further flight Repair in accordance with Para- graph 3.B., Work Instructions WORK PACKAGE 1, Step 4.b.(1) Any crack is found in the lower main sill inner chord Before further flight Contact Boeing for instructions and do the work instructed by Boeing Any corrosion damage or other irregularity is found in the lower main sill inner chord

- Before further flight Contact Boeing for instructions and do the work instructed by Boeing Any crack, corrosiondamage, or other irregularity is found in the structure other than the lower main sill inner chord (a) Accomplishment of the repair in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 1, Step 4.b.(1) terminates the inspections in this service bulletin at this location. **Group 3; Group 4, Configuration 3: Table 6: Overwing Emergency Exit Hatch Opening - Lower Main Sill - Inspection and Repair - WORK**  **PACKAGE 2 - RIGHT SIDE Repeat Interval**  **(Not to Exceed) Compliance Time**  **(Whichever Occurs Later) Action**  **Condition**

- Within 3,000 flight cycles after the original issuedate of this service bulletin Before 37,500 total flight cycles Do detailed inspections of the lower main sill inner chord and surrounding structure around STA903.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 2, Step 4.b. All airplanes

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 23 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT Group 3; Group 4, Configuration 3:**  **Table 6: Overwing Emergency Exit Hatch Opening - Lower Main Sill - Inspection and Repair - WORK PACKAGE 2 - RIGHT SIDE**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition**  3,750 flight cycles (a) Within 3,750 flight cycles after the initial detailed inspection Repeat the detailed inspections of the lower main sill inner chord and surrounding structure around STA903.5 in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 2, Step 4.b. No crack, corrosiondamage, or other irregularity is found

(a) Before further flight Repair in accordance with Para- graph 3.B., Work Instructions WORK PACKAGE 2, Step 4.b.(1) Any crack is found in the lower main sill inner chord Before further flight Contact Boeing for instructions and do the work instructed by Boeing Any corrosion damage or other irregularity is found in the lower main sill inner chord

- Before further flight Contact Boeing for instructions and do the work instructed by Boeing Any crack, corrosiondamage, or other irregularity is found in the structure other than the lower main sill inner chord (a) Accomplishment of the repair in accordance with Paragraph 3.B., Work Instructions WORK PACKAGE 2, Step 4.b.(1) terminates the inspections in this service bulletin at this location. **Group 4, Configuration 4:** No work is necessary. **F. Approval** This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 24 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT G. Manpower**  The table below shows an estimate of the task hours necessary to do this service bulletin for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: • Time to adjust to the workplace • Time to schedule the work • Time to inspect the work • Time to cure the materials • Time to make the parts • Time to find the tools. **Group 1; Group 4, Configuration 1: WORK PACKAGE 1 - LEFT SIDE**  **Elapsed Hours Task Hours**  **Number of Persons Task**  2.00 4.00 2 Open Access 1.00 1.00 1 FIGURE 1 2.00 4.00 2 Close Access 5.00 9.00 TOTAL FOR EACH AIRPLANE **Group 1; Group 4, Configuration 1: WORK PACKAGE 2 - RIGHT SIDE**  **Elapsed Hours Task Hours**  **Number of Persons Task**  2.00 4.00 2 Open Access 1.00 1.00 1 FIGURE 5 2.00 4.00 2 Close Access 5.00 9.00 TOTAL FOR EACH AIRPLANE **Group 2; Group 4, Configuration 2: WORK PACKAGE 1 - LEFT SIDE**  **Elapsed Hours Task Hours**  **Number of Persons Task**  3.15 6.30 2 Open Access 1.00 1.00 1 FIGURE 2 0.35 0.35 1 FIGURE 3 3.15 6.30 2 Close Access 7.65 13.95 TOTAL FOR EACH AIRPLANE

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 25 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT Group 2; Group 4, Configuration 2:**  **WORK PACKAGE 2 - RIGHT SIDE Elapsed Hours**  **Task Hours Number of Persons**  **Task** 3.15 6.30 2 Open Access 1.00 1.00 1 FIGURE 6 0.35 0.35 1 FIGURE 7 3.15 6.30 2 Close Access 7.65 13.95 TOTAL FOR EACH AIRPLANE **Group 3; Group 4, Configuration 3: WORK PACKAGE 1 - LEFT SIDE**  **Elapsed Hours Task Hours**  **Number of Persons Task**  2.00 4.00 2 Open Access 0.35 0.35 1 FIGURE 4 2.00 4.00 2 Close Access 4.35 8.35 TOTAL FOR EACH AIRPLANE **Group 3; Group 4, Configuration 3: WORK PACKAGE 2 - RIGHT SIDE**  **Elapsed Hours Task Hours**  **Number of Persons Task**  2.00 4.00 2 Open Access 0.35 0.35 1 FIGURE 8 2.00 4.00 2 Close Access 4.35 8.35 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes** None. **I. Electrical Load Data** Not changed.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 26 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT J. References**  1. Existing Data a. Boeing Service Letter 767-SL-51-036 b. Boeing Service Related Problem (SRP) 767-SRP-53-0358 c. 767 Aircraft Maintenance Manual (AMM) 25-21-01, 25-21-05, 25-25-01, 25-65-00, 52-21-01 d. 767 Fleet Team Digest (FTD) 53-10001 e. 767 Non-Destructive Testing (NDT) Manual Part 6, 51-00-01, Part 6, 51-00-19 f. 767-200 Structural Repair Manual (SRM) 53-50-07 g. 767-300 Structural Repair Manual (SRM) 53-50-07 h. 767-300BCF Structural Repair Manual (SRM) 53-50-07 2. Data supplied with this Service Bulletin None. 3. Installation Drawings Used in the Preparation of this Service Bulletin This drawing was used to prepare this service bulletin. This drawing is not necessary to make the specified changes, and is not supplied with this service bulletin. This drawing may not be applicable to all airplane configurations or operators.
**Title Drawing Number**  SILL INSTL - LOWER EMERGENCY EXIT 145T8310
**K. Publications Affected** 1. Publications: None. 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected are contained in Paragraph 1.E., Compliance of this service bulletin. **L. Interchangeability and Intermixability of Parts** Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 27 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 28 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**

BLANK PAGE**2. MATERIAL INFORMATION A. Material - Price and Availability**  None. **B. Industry Support Information** Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service bulletin. **C. Parts Necessary For Each Airplane** 1. Kits/Parts None. 2. Parts and Materials Supplied by the Operator None. 3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. **D. Parts Necessary to Change Spares** None. **E. Special Tooling - Price and Availability** None. **F. Special Tooling Necessary to do this Service Bulletin** No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 29 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 30 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**

BLANK PAGE**3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION**  **CAUTION:** KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED 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. **NOTE:** 1. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s) give the recommended sequence of steps. The sequence of steps to do this service bulletin can be changed. 2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 3. Obey all of the warnings and cautions given in the specified manual sections. 4. The work instructions are divided into work packages. Task Hours and Elapsed Hours for each package are given in Paragraph 1.G., Manpower. You can do each work package independently. 5. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch 6. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. Alternate fasteners are listed in SRM Chapter 51 and Boeing Drawing 012W6100. 7. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required. 8. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 9. Boeing Service Letter 767-SL-51-036, Damage Reporting and Repair Plan/Design Guidelines, is an acceptable procedure to request information from Boeing for additional structural repair instructions. The Service Letter describes what information must be provided to Boeing before a structural repair can be provided. 10. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 31 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT B. WORK INSTRUCTIONS**  **Group 1-3; Group 4, Configuration 1-3: WORK PACKAGE 1 - LEFT SIDE**  1. Disarm the off-wing escape system. Refer to 767 AMM 25-65-00 as an accepted procedure.
2. **Group 1; Group 4, Configuration 1:** a. Do the following steps as necessary to get access to the lower main sill of the overwing emergency exit hatch opening around the frame at Body Station (STA) 883.5 (immediately aft of the overwing emergency exit hatch): (1) Remove seats within 6 inches forward and aft of the frame. Refer to 767 AMM 25-25-01 as an accepted procedure. (2) Remove the overwing emergency exit hatch. Refer to 767 AMM 52-21-01 as an accepted procedure. (3) Remove sidewall panels within 6 inches forward and aft of the frame. Refer to 767 AMM 25-21-01 as an accepted procedure. (4) Remove or fold back sidewall insulation within 6 inches forward and aft of the frame and 4 inches above and below the lower main sill. Refer to 767 AMM 25-21-05 as an accepted procedure. b. Do High Frequency Eddy Current (HFEC) and detailed inspections of the lower main sill around STA 883.5 in accordance with FIGURE 1. (1) If any crack is found in the lower main sill inner chord, repair in accordance with 767-200 SRM 53-50-07 REPAIR 1. (2) If any corrosion damage or other irregularity is found in the lower main sill inner chord, contact Boeing for repair instructions and do the work instructed by Boeing. (3) If any crack, corrosion damage, or other irregularity is found in structure other than the lower main sill inner chord, contact Boeing for repair instructions and do the work instructed by Boeing. c. Do the following to close access to the lower main sill of the overwing emergency exit hatch opening around the frame at STA 883.5:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 32 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**(1) Install removed sidewall insulation. Refer to 767 AMM 25-21-05 as an accepted procedure. (2) Install removed sidewall panels. Refer to 767 AMM 25-21-01 as an accepted procedure. (3) Install removed overwing emergency exit hatch. Refer to 767 AMM 52-21-01 as an accepted procedure. (4) Install removed seats. Refer to 767 AMM 25-25-01 as an accepted procedure. 3. **Group 2; Group 4, Configuration 2:** a. Do the following steps as necessary to get access to the lower main sill of the overwing emergency exit hatch openings around the frames at STA 883.5 (immediately aft of the forward overwing emergency exit hatch) and STA 903.5 (immediately forward of the aft overwing emergency exit hatch): (1) Remove seats within 6 inches forward and aft of the frames. Refer to 767 AMM 25-25-01 as an accepted procedure. (2) Remove the overwing emergency exit hatches. Refer to 767 AMM 52-21-01 as an accepted procedure. (3) Remove sidewall panels within 6 inches forward and aft of the frames. Refer to 767 AMM 25-21-01 as an accepted procedure. (4) Remove or fold back sidewall insulation within 6 inches forward and aft of the frames and 4 inches above and below the lower main sill. Refer to 767 AMM 25-21-05 as an accepted procedure. b. Do HFEC and detailed inspections of the lower main sill around STA 883.5 in accordance with FIGURE 2. (1) If any crack is found in the lower main sill inner chord, repair in accordance with 767-200 SRM 53-50-07 REPAIR 2, 767-300 SRM 53-50-07 REPAIR 2 or 767-300BCF SRM 53-50-07 REPAIR 2. (2) If any corrosion damage or other irregularity is found in the lower main sill inner chord, contact Boeing for repair instructions and do the work instructed by Boeing. (3) If any crack, corrosion damage, or other irregularity is found in structure other than the lower main sill inner chord, contact Boeing for repair instructions and do the work instructed by Boeing. c. Do detailed inspections of the lower main sill around STA 903.5 in accordance with FIGURE 3.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 33 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**(1) If any crack is found in the lower main sill inner chord, repair in accordance with 767-200 SRM 53-50-07 REPAIR 2, 767-300 SRM 53-50-07 REPAIR 2 or 767-300BCF SRM 53-50-07 REPAIR 2. (2) If any corrosion damage or other irregularity is found in the lower main sill inner chord, contact Boeing for repair instructions and do the work instructed by Boeing. (3) If any crack, corrosion damage, or other irregularity is found in structure other than the lower main sill inner chord, contact Boeing for repair instructions and do the work instructed by Boeing. d. Do the following to close access to the lower main sill of the overwing emergency exit hatch openings around the frames at STA 883.5 and STA 903.5: (1) Install removed sidewall insulation. Refer to 767 AMM 25-21-05 as an accepted procedure. (2) Install removed sidewall panels. Refer to 767 AMM 25-21-01 as an accepted procedure. (3) Install removed overwing emergency exit hatch. Refer to 767 AMM 52-21-01 as an accepted procedure. (4) Install removed seats. Refer to 767 AMM 25-25-01 as an accepted procedure.
4. **Group 3; Group 4, Configuration 3:** a. Do the following steps as necessary to get access to the lower main sill of the overwing emergency exit hatch opening around the frame at STA 903.5 (immediately forward of the overwing emergency exit hatch): (1) Remove seats within 6 inches forward and aft of the frame. Refer to 767 AMM 25-25-01 as an accepted procedure. (2) Remove the overwing emergency exit hatch. Refer to 767 AMM 52-21-01 as an accepted procedure. (3) Remove sidewall panels within 6 inches forward and aft of the frame. Refer to 767 AMM 25-21-01 as an accepted procedure. (4) Remove or fold back sidewall insulation within 6 inches forward and aft of the frame and 4 inches above and below the lower main sill. Refer to 767 AMM 25-21-05 as an accepted procedure. b. Do detailed inspections of the lower main sill around STA 903.5 in accordance with FIGURE 4.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 34 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**(1) If any crack is found in the lower main sill inner chord, repair in accordance with 767-300 SRM 53-50-07 REPAIR 3 or 767-300BCF SRM 53-50-07 REPAIR 3. (2) If any corrosion damage or other irregularity is found in the lower main sill inner chord, contact Boeing for repair instructions and do the work instructed by Boeing. (3) If any crack, corrosion damage, or other irregularity is found in structure other than the lower main sill inner chord, contact Boeing for repair instructions and do the work instructed by Boeing. c. Do the following to close access to the lower main sill of the overwing emergency exit hatch opening around the frame at STA 903.5: (1) Install removed sidewall insulation. Refer to 767 AMM 25-21-05 as an accepted procedure. (2) Install removed sidewall panels. Refer to 767 AMM 25-21-01 as an accepted procedure. (3) Install removed overwing emergency exit hatch. Refer to 767 AMM 52-21-01 as an accepted procedure. (4) Install removed seats. Refer to 767 AMM 25-25-01 as an accepted procedure. 5. Arm the off-wing escape system. Refer to 767 AMM 25-65-00 as an accepted procedure. 6. Put the airplane back to a serviceable condition. **Group 1-3; Group 4, Configuration 1-3: WORK PACKAGE 2 - RIGHT SIDE**  1. Disarm the off-wing escape system. Refer to 767 AMM 25-65-00 as an accepted procedure.
2. **Group 1; Group 4, Configuration 1:** a. Do the following steps as necessary to get access to the lower main sill of the overwing emergency exit hatch opening around the frame at STA 883.5 (immediately aft of the overwing emergency exit hatch): (1) Remove seats within 6 inches forward and aft of the frame. Refer to 767 AMM 25-25-01 as an accepted procedure. (2) Remove the overwing emergency exit hatch. Refer to 767 AMM 52-21-01 as an accepted procedure. (3) Remove sidewall panels within 6 inches forward and aft of the frame. Refer to 767 AMM 25-21-01 as an accepted procedure. (4) Remove or fold back sidewall insulation within 6 inches forward and aft of the frame and 4 inches above and below the lower main sill. Refer to 767 AMM 25-21-05 as an accepted procedure. b. Do High Frequency Eddy Current (HFEC) and detailed inspections of the lower main sill around STA 883.5 in accordance with FIGURE 5.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 35 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**(1) If any crack is found in the lower main sill inner chord, repair in accordance with 767-200 SRM 53-50-07 REPAIR 1. (2) If any corrosion damage or other irregularity is found in the lower main sill inner chord, contact Boeing for repair instructions and do the work instructed by Boeing. (3) If any crack, corrosion damage, or other irregularity is found in structure other than the lower main sill inner chord, contact Boeing for repair instructions and do the work instructed by Boeing. c. Do the following to close access to the lower main sill of the overwing emergency exit hatch opening around the frame at STA 883.5: (1) Install removed sidewall insulation. Refer to 767 AMM 25-21-05 as an accepted procedure. (2) Install removed sidewall panels. Refer to 767 AMM 25-21-01 as an accepted procedure. (3) Install removed overwing emergency exit hatch. Refer to 767 AMM 52-21-01 as an accepted procedure. (4) Install removed seats. Refer to 767 AMM 25-25-01 as an accepted procedure. 3. **Group 2; Group 4, Configuration 2:** a. Do the following steps as necessary to get access to the lower main sill of the overwing emergency exit hatch openings around the frames at STA 883.5 (immediately aft of the forward overwing emergency exit hatch) and STA 903.5 (immediately forward of the aft overwing emergency exit hatch): (1) Remove seats within 6 inches forward and aft of the frames. Refer to 767 AMM 25-25-01 as an accepted procedure. (2) Remove the overwing emergency exit hatch. Refer to 767 AMM 52-21-01 as an accepted procedure. (3) Remove sidewall panels within 6 inches forward and aft of the frames. Refer to 767 AMM 25-21-01 as an accepted procedure. (4) Remove or fold back sidewall insulation within 6 inches forward and aft of the frames and 4 inches above and below the lower main sill. Refer to 767 AMM 25-21-05 as an accepted procedure. b. Do HFEC and detailed inspections of the lower main sill around STA 883.5 in accordance with FIGURE 6.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 36 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**(1) If any crack is found in the lower main sill inner chord, repair in accordance with 767-200 SRM 53-50-07 REPAIR 2, 767-300 SRM 53-50-07 REPAIR 2 or 767-300BCF SRM 53-50-07 REPAIR 2. (2) If any corrosion damage or other irregularity is found in the lower main sill inner chord, contact Boeing for repair instructions and do the work instructed by Boeing. (3) If any crack, corrosion damage, or other irregularity is found in structure other than the lower main sill inner chord, contact Boeing for repair instructions and do the work instructed by Boeing. c. Do detailed inspections of the lower main sill around STA 903.5 in accordance with FIGURE 7. (1) If any crack is found in the lower main sill inner chord, repair in accordance with 767-200 SRM 53-50-07 REPAIR 2, 767-300 SRM 53-50-07 REPAIR 2 or 767-300BCF SRM 53-50-07 REPAIR 2. (2) If any corrosion damage or other irregularity is found in the lower main sill inner chord, contact Boeing for repair instructions and do the work instructed by Boeing. (3) If any crack, corrosion damage, or other irregularity is found in structure other than the lower main sill inner chord, contact Boeing for repair instructions and do the work instructed by Boeing. d. Do the following to close access to the lower main sill of the overwing emergency exit hatch openings around the frames at STA 883.5 and STA 903.5: (1) Install removed sidewall insulation. Refer to 767 AMM 25-21-05 as an accepted procedure. (2) Install removed sidewall panels. Refer to 767 AMM 25-21-01 as an accepted procedure. (3) Install removed overwing emergency exit hatch. Refer to 767 AMM 52-21-01 as an accepted procedure. (4) Install removed seats. Refer to 767 AMM 25-25-01 as an accepted procedure.
4. **Group 3; Group 4, Configuration 3:** a. Do the following steps as necessary to get access to the lower main sill of the overwing emergency exit hatch opening around the frame at STA 903.5 (immediately forward of the overwing emergency exit hatch):

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 37 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**(1) Remove seats within 6 inches forward and aft of the frame. Refer to 767 AMM 25-25-01 as an accepted procedure. (2) Remove the overwing emergency exit hatch. Refer to 767 AMM 52-21-01 as an accepted procedure. (3) Remove sidewall panels within 6 inches forward and aft of the frame. Refer to 767 AMM 25-21-01 as an accepted procedure. (4) Remove or fold back sidewall insulation within 6 inches forward and aft of the frame and 4 inches above and below the lower main sill. Refer to 767 AMM 25-21-05 as an accepted procedure. b. Do detailed inspections of the lower main sill around STA 903.5 in accordance with FIGURE 8. (1) If any crack is found in the lower main sill inner chord, repair in accordance with 767-300 SRM 53-50-07 REPAIR 3 or 767-300BCF SRM 53-50-07 REPAIR 3. (2) If any corrosion damage or other irregularity is found in the lower main sill inner chord, contact Boeing for repair instructions and do the work instructed by Boeing. (3) If any crack, corrosion damage, or other irregularity is found in structure other than the lower main sill inner chord, contact Boeing for repair instructions and do the work instructed by Boeing. c. Do the following to close access to the lower main sill of the overwing emergency exit hatch opening around the frame at STA 903.5: (1) Install removed sidewall insulation. Refer to 767 AMM 25-21-05 as an accepted procedure. (2) Install removed sidewall panels. Refer to 767 AMM 25-21-01 as an accepted procedure. (3) Install removed overwing emergency exit hatch. Refer to 767 AMM 52-21-01 as an accepted procedure. (4) Install removed seats. Refer to 767 AMM 25-25-01 as an accepted procedure. 5. Arm the off-wing escape system. Refer to 767 AMM 25-65-00 as an accepted procedure. 6. Put the airplane back to a serviceable condition. **Group 4, Configuration 4: AIRPLANES WITH NO OVERWING EMERGENCY EXIT HATCHES**  1. No work is necessary.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 38 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT This Figure applies only to: Group 1; Group 4, Configuration 1.** 

**FIGURE 1: LEFT SIDE - OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 883.5 - INSPECTIONS**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 39 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (b)

- - LOWER MAIN SILL IN- NER CHORD Inspect 1 (a)

- - LOWER MAIN SILL IN- NER CHORD Inspect 2 (c)

- - STRUCTURE Inspect 3(a) Do a surface HFEC inspection of the upper surface of the lower main sill inner chord for cracks in accordance with 767 NDT Part 6, 51-00-01 or 767 NDT Part 6, 51-00-19. (b) Do a detailed inspection of the upper surface of the lower main sill inner chord for cracks, corrosion damage, or other irregularity. Use 5-10x magnification. (c) Do a detailed inspection of all visible surfaces of the structure within 2 inches in all directions around the lower main sill inspection area shown in step 1. This inspection is to detect cracks, corrosion damage, or other irregularity.

**FIGURE 1: LEFT SIDE - OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 883.5 - INSPECTIONS**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 40 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT This Figure applies only to: Group 2; Group 4, Configuration 2.** 

**FIGURE 2: LEFT SIDE - FORWARD OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 883.5 - INSPECTIONS**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 41 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (b)

- - LOWER MAIN SILL IN- NER CHORD Inspect 1 (a)

- - LOWER MAIN SILL IN- NER CHORD Inspect 2 (c)

- - STRUCTURE Inspect 3(a) Do a surface HFEC inspection of the upper surface of the lower main sill inner chord for cracks in accordance with 767 NDT Part 6, 51-00-01 or 767 NDT Part 6, 51-00-19. (b) Do a detailed inspection of the upper surface of the lower main sill inner chord for cracks, corrosion damage, or other irregularity. Use 5-10x magnification. (c) Do a detailed inspection of all visible surfaces of the structure within 2 inches in all directions around the lower main sill inspection area shown in step 1. This inspection is to detect cracks, corrosion damage, or other irregularity.

**FIGURE 2: LEFT SIDE - FORWARD OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 883.5 - INSPECTIONS**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 42 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT This Figure applies only to: Group 2; Group 4, Configuration 2.** 

**FIGURE 3: LEFT SIDE - AFT OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 903.5 - INSPECTIONS**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 43 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (a)

- - LOWER MAIN SILL IN- NER CHORD Inspect 1 (b)

- - STRUCTURE Inspect 2 (a) Do a detailed inspection of the upper surface of the lower main sill inner chord for cracks, corrosion damage, or other irregularity. Use 5-10x magnification. (b) Do a detailed inspection of all visible surfaces of the structure within 2 inches in all directions around the lower main sill inspection area shown in step 1. This inspection is to detect cracks, corrosion damage, or other irregularity.

**FIGURE 3: LEFT SIDE - AFT OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 903.5 - INSPECTIONS**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 44 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT This Figure applies only to: Group 3; Group 4, Configuration 3.** 

**FIGURE 4: LEFT SIDE - OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 903.5 - INSPECTIONS**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 45 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (a)

- - LOWER MAIN SILL IN- NER CHORD Inspect 1 (b)

- - STRUCTURE Inspect 2 (a) Do a detailed inspection of the upper surface of the lower main sill inner chord for cracks, corrosion damage, or other irregularity. Use 5-10x magnification. (b) Do a detailed inspection of all visible surfaces of the structure within 2 inches in all directions around the lower main sill inspection area shown in step 1. This inspection is to detect cracks, corrosion damage, or other irregularity.

**FIGURE 4: LEFT SIDE - OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 903.5 - INSPECTIONS**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 46 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT This Figure applies only to: Group 1; Group 4, Configuration 1.** 

**FIGURE 5: RIGHT SIDE - OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 883.5 - INSPECTIONS**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 47 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (b)

- - LOWER MAIN SILL IN- NER CHORD Inspect 1 (a)

- - LOWER MAIN SILL IN- NER CHORD Inspect 2 (c)

- - STRUCTURE Inspect 3(a) Do a surface HFEC inspection of the upper surface of the lower main sill inner chord for cracks in accordance with 767 NDT Part 6, 51-00-01 or 767 NDT Part 6, 51-00-19. (b) Do a detailed inspection of the upper surface of the lower main sill inner chord for cracks, corrosion damage, or other irregularity. Use 5-10x magnification. (c) Do a detailed inspection of all visible surfaces of the structure within 2 inches in all directions around the lower main sill inspection area shown in step 1. This inspection is to detect cracks, corrosion damage, or other irregularity.

**FIGURE 5: RIGHT SIDE - OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 883.5 - INSPECTIONS**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 48 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT This Figure applies only to: Group 2; Group 4, Configuration 2.** 

**FIGURE 6: RIGHT SIDE - FORWARD OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 883.5 - INSPECTIONS**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 49 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (b)

- - LOWER MAIN SILL IN- NER CHORD Inspect 1 (a)

- - LOWER MAIN SILL IN- NER CHORD Inspect 2 (c)

- - STRUCTURE Inspect 3(a) Do a surface HFEC inspection of the upper surface of the lower main sill inner chord for cracks in accordance with 767 NDT Part 6, 51-00-01 or 767 NDT Part 6, 51-00-19. (b) Do a detailed inspection of the upper surface of the lower main sill inner chord for cracks, corrosion damage, or other irregularity. Use 5-10x magnification. (c) Do a detailed inspection of all visible surfaces of the structure within 2 inches in all directions around the lower main sill inspection area shown in step 1. This inspection is to detect cracks, corrosion damage, or other irregularity.

**FIGURE 6: RIGHT SIDE - FORWARD OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 883.5 - INSPECTIONS**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 50 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT This Figure applies only to: Group 2; Group 4, Configuration 2.** 

**FIGURE 7: RIGHT SIDE - AFT OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 903.5 - INSPECTIONS**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 51 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (a)

- - LOWER MAIN SILL IN- NER CHORD Inspect 1 (b)

- - STRUCTURE Inspect 2 (a) Do a detailed inspection of the upper surface of the lower main sill inner chord for cracks, corrosion damage, or other irregularity. Use 5-10x magnification. (b) Do a detailed inspection of all visible surfaces of the structure within 2 inches in all directions around the lower main sill inspection area shown in step 1. This inspection is to detect cracks, corrosion damage, or other irregularity.

**FIGURE 7: RIGHT SIDE - AFT OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 903.5 - INSPECTIONS**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 52 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT This Figure applies only to: Group 3; Group 4, Configuration 3.** 

**FIGURE 8: RIGHT SIDE - OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 903.5 - INSPECTIONS**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 53 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (a)

- - LOWER MAIN SILL IN- NER CHORD Inspect 1 (b)

- - STRUCTURE Inspect 2 (a) Do a detailed inspection of the upper surface of the lower main sill inner chord for cracks, corrosion damage, or other irregularity. Use 5-10x magnification. (b) Do a detailed inspection of all visible surfaces of the structure within 2 inches in all directions around the lower main sill inspection area shown in step 1. This inspection is to detect cracks, corrosion damage, or other irregularity.

**FIGURE 8: RIGHT SIDE - OVERWING EMERGENCY EXIT HATCH OPENING - LOWER MAIN SILL - STA 903.5 - INSPECTIONS**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 28, 2011 767-53A0228 54 of 54 **BOEING SERVICE BULLETIN 767-53A0228 ALERT**  **ALERT**