### Commercial **Airplanes** 

# 727 Service Bulletin **SPECIAL ATTENTION Number: 727-55-0094**  Original Issue: March 21, 2012 ATA System: 5520 **SUBJECT:** STABILIZERS - Horizontal Stabilizer - Elevator Rear Spar Stiffener Assembly, Inspection and Replacement 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2012 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 1 of 47 3.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 2 of 47 **BOEING SERVICE BULLETIN 727-55-0094**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION ........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 1. Existing Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 2. Data supplied with this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 3. Installation Drawings Used in the Preparation of this Service Bulletin. . . . . . . . . . . . 17 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 18 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 19 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 20 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 FIGURE 1: LEFT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - INSPECTION . . . . . 24 FIGURE 2: LEFT SIDE ELEVATOR UPPER SKIN PANEL - PARTIAL REMOVAL. . . . . . . . . . . 26 FIGURE 3: LEFT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - REMOVAL. . . . . . . 28 FIGURE 4: LEFT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - INSTALLATION. . . . 30 FIGURE 5: LEFT SIDE ELEVATOR UPPER SKIN PANEL - INSTALLATION. . . . . . . . . . . . . . 33 FIGURE 6: RIGHT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - INSPECTION. . . . . 36 FIGURE 7: RIGHT SIDE ELEVATOR UPPER SKIN PANEL - PARTIAL REMOVAL. . . . . . . . . . 38 FIGURE 8: RIGHT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - REMOVAL. . . . . . 40 FIGURE 9: RIGHT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - INSTALLATION . . . 42 FIGURE 10: RIGHT SIDE ELEVATOR UPPER SKIN PANEL - INSTALLATION. . . . . . . . . . . . . 45

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 3 of 47 **BOEING SERVICE BULLETIN 727-55-0094**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 4 of 47 **BOEING SERVICE BULLETIN 727-55-0094**

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### Commercial **Airplanes** 

# 727 Service Bulletin **SPECIAL ATTENTION Summary**  **Number: 727-55-0094** Original Issue: March 21, 2012 ATA System: 5520 **SUBJECT:** STABILIZERS - Horizontal Stabilizer - Elevator Rear Spar Stiffener Assembly, Inspection and Replacement BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. **CONCURRENT REQUIREMENTS** None. **BACKGROUND** This service bulletin is sent to inspect for cracks in the elevator rear spar stiffener assembly at the Right Side Elevator Station 56.70 and the Left Side Elevator Station 63.30. These locations are common to the Tab Control Rod tunnel. Service Bulletin (SB) 727-55-0089 addresses elevator rear spar web cracking at the elevator tab hinge fittings. That service bulletin contains a rear spar replacement modification. The elevator rear spar stiffener assembly has been inspected as part of that service bulletin and, or as needed, replaced in the process of replacing the elevator rear spar. Fit-up stress in the elevator rear spar stiffener assembly can be present after accomplishment of SB 727-55-0089 and can cause cracking. During accomplishment of SB 727-55-0089 an operator reported a crack on the elevator rear spar stiffener assembly. Undetected cracks in the elevator rear spar stiffener assembly and spar web could adversely affect elevator stiffness, which can lead to elevator vibration and possible interference with the tab control rod, which can result in unsafe flight conditions. Boeing Service Related Problem (SRP) 727-SRP-55-0051 is related to this service bulletin. This table is provided to operators for planning purposes only. Refer to the applicable sections for more information.
**Reference Affected**  **Planning Data** Paragraph 1.A.2., Spares Affected No Spares Affected Paragraph 1.E., Compliance No AD Related Paragraph 1.H., Weight and Balance Changes No Weight and Balance Change Paragraph 1.I., Electrical Load Data No Electrical Load Changed Paragraph 1.K., Publications Affected No Publications Affected Paragraph 1.K., Publications Affected No Airplane Flight Operations Affected (Flight CrewOperations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/Parts No Kits/Parts Required

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 5 of 47**Reference Affected**  **Planning Data** Paragraph 2.C.2., Parts and Materials Supplied by the Operator Yes Operator Supplied Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin No Special Tooling Required

**ACTION** Do a detailed inspection for cracks in the elevator rear spar stiffener assembly at the Right Side Elevator Station 56.70 and the Left Side Elevator Station 63.30. If any crack is found, remove the elevator rear spar stiffener assembly and install a new elevator rear spar stiffener assembly, and shim as necessary to fill any gaps. Repeat the inspections at the time given in Paragraph 1.E., Compliance. **EFFECTIVITY** All 727, 727-100, 727-100C, 727-200, 727-200F, 727C Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s). **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 replacement given in this service bulletin. **MANPOWER Elapsed Hours**  **Total Task Hours Airplanes**  17.90 17.90 Group 1
**MATERIAL INFORMATION** Operator Supplied Parts/Materials. Refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 6 of 47 **BOEING SERVICE BULLETIN 727-55-0094**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 7 of 47 **BOEING SERVICE BULLETIN 727-55-0094**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 8 of 47 **BOEING SERVICE BULLETIN 727-55-0094**

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### Commercial **Airplanes** 

# 727 Service Bulletin **SPECIAL ATTENTION Number: 727-55-0094**  Original Issue: March 21, 2012 ATA System: 5520 **SUBJECT:** STABILIZERS - Horizontal Stabilizer - Elevator Rear Spar Stiffener Assembly, Inspection and Replacement BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes Refer to Service Bulletin Index D6-9825 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplane(s) shown below.
**DESCRIPTION CONFIGURATION**  **GROUP** All 727, 727-100, 727-100C, 727-200, 727-200F, 727C airplanes.

- 1

Airplane Models: 727, 727-100, 727-100C, 727-200, 727-200F, 727C **Group Variable Number**  1 E0001 - E0042 1 E0101 - E0140 1 E0201 - E0216 1 E0301 - E0351 1 E0401 - E0423 1 E3001 - E3006 1 E3011 - E3014 1 E3021 - E3040 1 E3059

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 9 of 47**Group Variable Number**  1 E3061 - E3077 1 E3101 - E3103 1 E3111 - E3118 1 E3141 - E3152 1 E3171 - E3177 1 E3201 - E3206 1 E3221 - E3224 1 E3241 - E3290 1 E3341 - E3350 1 E3401 - E3421 1 E3451 - E3452 1 E3471 - E3474 1 E3501 - E3513 1 E3516 - E3523 1 E3551 - E3553 1 E3571 - E3578 1 E3601 - E3604 1 E3621 - E3622 1 E3651 - E3655 1 E3677 1 E3681 - E3684 1 E3701 - E3704 1 E3751 - E3755 1 E3781 - E3784 1 E5001 - E5011 1 E5031 - E5068 1 E5101 - E5116 1 E5141 - E5143 1 E5161 - E5164 1 E5201 - E5203 1 E5221 - E5245 1 E5251 - E5252 1 E5271 - E5281

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 10 of 47 **BOEING SERVICE BULLETIN 727-55-0094 Group**  **Variable Number** 1 E5301 - E5306 1 E5351 - E5353 1 E5381 - E5382 1 E5401 - E5424 1 E5426 - E5429 1 E5433 1 E5435 1 E5451 - E5455 1 E5481 - E5483 1 E5501 - E5502 1 QA001 - QA046 1 QA051 - QA099 1 QA101 - QA199 1 QA201 - QA225 1 QA301 - QA349 1 QA351 - QA376 1 QA378 1 QA401 - QA499 1 QA501 - QA537 1 QA551 - QA579 1 QA581 - QA585 1 QA601 - QA688 1 QA701 - QA753 1 QA801 - QA805 1 QA851 - QA899 1 QA901 - QA946 1 QA949 1 QB001 - QB002 1 QB031 - QB049 1 QB051 - QB068 1 QB101 - QB110 1 QB114 - QB119 1 QB121 - QB149

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 11 of 47 **BOEING SERVICE BULLETIN 727-55-0094 Group**  **Variable Number** 1 QB151 - QB158 1 QB201 - QB220 1 QB301 - QB316 1 QB351 - QB352 1 QB401 - QB407 1 QB451 - QB458 1 QB501 - QB575 1 QB601 - QB629 1 QB651 1 QB701 - QB705 1 QB801 - QB810 1 QB901 - QB904 1 QD001 - QD012 1 QD031 - QD046 1 QD085 - QD088 1 QD101 - QD105 1 QD121 - QD127 1 QD141 - QD149 1 QD161 - QD164 1 QD191 - QD192 1 QD201 - QD239 1 QD281 - QD284 1 QD301 - QD305 1 QD321 - QD330 1 QD351 1 QD401 - QD403 1 QD407 1 QD410 1 QD421 - QD427 1 QD441 - QD453 1 QD471 - QD475 1 QD501 - QD518 1 QD551 - QD558

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 12 of 47 **BOEING SERVICE BULLETIN 727-55-0094 Group**  **Variable Number** 1 QD571 - QD572 1 QD581 - QD583 1 QD601 - QD607 1 QD621 - QD624 1 QD641 1 QD661 - QD663 1 QD681 - QD685 1 QD691 - QD692 1 QD701 - QD702 1 QD711 - QD717 1 QD741 1 QD761 - QD769 1 QD781 - QD782 1 QD791 1 QD801 - QD804 1 QD821 - QD828 1 QD901 - QD910 1 QD931 - QD932 1 QD951 - QD954 1 QD971 - QD973 1 QD991 - QD992 1 QE001 - QE002 1 QL001 - QL008 1 QL031 - QL032 1 QL081 1 QL501 - QL515 2. Spares Affected None. **B. Concurrent Requirements** None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 13 of 47 **BOEING SERVICE BULLETIN 727-55-0094 C. Reason**  This service bulletin is sent to inspect for cracks in the elevator rear spar stiffener assembly at the Right Side Elevator Station 56.70 and the Left Side Elevator Station 63.30. These locations are common to the Tab Control Rod tunnel. Service Bulletin (SB) 727-55-0089 addresses elevator rear spar web cracking at the elevator tab hinge fittings. That service bulletin contains a rear spar replacement modification. The elevator rear spar stiffener assembly has been inspected as part of that service bulletin and, or as needed, replaced in the process of replacing the elevator rear spar. Fit-up stress in the elevator rear spar stiffener assembly can be present after accomplishment of SB 727-55-0089 and can cause cracking. During accomplishment of SB 727-55-0089 an operator reported a crack on the rear spar stiffener assembly. Undetected cracks in the elevator rear spar stiffener assembly and spar web could adversely affect elevator stiffness, which can lead to elevator vibration and possible interference with the tab control rod, which can result in unsafe flight conditions. Boeing Service Related Problem (SRP) 727-SRP-55-0051 is related to this service bulletin. **D. Description** Do a detailed inspection for cracks in the elevator rear spar stiffener assembly at the Right Side Elevator Station 56.70 and the Left Side Elevator Station 63.30. If any crack is found, remove the elevator rear spar stiffener assembly and install a new elevator rear spar stiffener assembly, and shim as necessary to fill any gaps. Repeat the inspections at the time given in Paragraph 1.E., Compliance. **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. 1.

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.
**Affected Maintenance Zones Zone**  **Model** 3-93, 3-94 727, 727-100, 727-100C, 727- 200, 727-200F, 727C **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 14 of 47 **BOEING SERVICE BULLETIN 727-55-0094 Table 1: Inspection for cracks in the Elevator Rear Spar Stiffener Assembly**  **Repeat Interval (Not to Exceed)**  **Compliance Time Action**  **Condition** 4,000 flight hours, 3,000 flight cycles, or 24 months, whichever occurs first. (a) Within 4,000 flight hours, 3,000 flight cycles, or 24 months, whichever occurs first from the original issue date of this service bulletin. Do a Detailed Inspection for cracks in the elevatorrear spar stiffener assembly in accordance withAccomplishment Instructions 3.B., PART 2 and PART 3. All airplanes.

- Before further flight. Replace the left elevatorrear spar stiffener assembly in accordance withAccomplishment Instructions 3.B., PART 4. Any crack found in the left elevator rear spar stiffener assembly.

- Before further flight. Replace the right elevatorrear spar stiffener assembly in accordance withAccomplishment Instructions 3.B., PART 5. Any crack found in the right elevator rear spar stiffener assembly.

(a) The replacement of the elevator rear spar stiffener assembly in accordance with Accomplishment Instructions 3.B., PART 4 or PART 5 terminates the inspections given in Table1 for the replaced elevator rear spar stiffener assembly only. After replacement of the elevator rear spar stiffener assembly, do the post modification inspections in accordance with Table 2. **Table 2: Post Modification Inspection for cracks in the Elevator Rear Spar Stiffener Assembly Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition**  4,000 flight hours, 3,000 flight cycles, or 24 months, whichever occurs first. Within 96 monthsafter the replacement of the elevator rear spar stiffener assembly. Do a Detailed Inspection of the replaced elevatorrear spar stiffener assembly in accordance with theapplicable Accomplishment Instructions 3.B., PART 2 or PART 3.All airplanes with an elevator rear spar stiffener assembly replaced in accordance with this service bulletin.

(a) Before further flight. Replace the left elevatorrear spar stiffener assembly in accordance withAccomplishment Instructions 3.B., PART 4. Any crack found in the left elevator rear spar stiffener assembly.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 15 of 47 **BOEING SERVICE BULLETIN 727-55-0094 Table 2: Post Modification Inspection for cracks in the Elevator Rear Spar Stiffener Assembly**  **Repeat Interval (Not to Exceed)**  **Compliance Time Action**  **Condition** (a) Before further flight. Replace the right elevatorrear spar stiffener assembly in accordance withAccomplishment Instructions 3.B., PART 5. Any crack found in the right elevator rear spar stiffener assembly.

(a) The replacement of the elevator rear spar stiffener assembly in accordance with Accomplishment Instructions 3.B., PART 4 or PART 5 does not terminate the inspections given in Table 2. **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. **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 **Elapsed Hours Task Hours**  **Number of Persons Task**  1.50 1.50 1 Open Access 1.00 1.00 1 FIGURE 1 2.50 2.50 1 FIGURE 2 0.60 0.60 1 FIGURE 3 0.60 0.60 1 FIGURE 4 2.50 2.50 1 FIGURE 5

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 16 of 47 **BOEING SERVICE BULLETIN 727-55-0094 Elapsed Hours**  **Task Hours Number of Persons**  **Task** 1.00 1.00 1 FIGURE 6 2.50 2.50 1 FIGURE 7 0.60 0.60 1 FIGURE 8 0.60 0.60 1 FIGURE 9 2.50 2.50 1 FIGURE 10 1.50 1.50 1 Close Access 0.50 0.50 1 Test 17.90 17.90 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes** None. **I. Electrical Load Data** Not applicable. **J. References** 1. Existing Data a. Boeing Service Bulletin 727-55-0089 b. Standard Overhaul Practices Manual (SOPM) 20-50-12 c. 727 Aircraft Maintenance Manual (AMM) 27-30-00, 27-30-11 d. Service Bulletin Index D6-9825 e. Boeing Service Related Problem (SRP) 727-SRP-55-0051 2. Data supplied with this Service Bulletin None. 3. Installation Drawings Used in the Preparation of this Service Bulletin
**Title Drawing Number**  REAR SPAR INSTL - INBD. ELEV HORIZ STAB 65-16935 The table above lists the applicable drawing used to prepare this service bulletin. The drawing is not necessary to make the specified changes, and is not supplied with this service bulletin. The drawing may not be applicable to all airplane configurations or operators.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 17 of 47 **BOEING SERVICE BULLETIN 727-55-0094 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 but no new DTIs are necessary. **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: March 21, 2012 727-55-0094 18 of 47 **BOEING SERVICE BULLETIN 727-55-0094 2. MATERIAL INFORMATION**  **A. Material - Price and Availability** The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin does not show the Boeing price and supply data. **B. Industry Support Information** Boeing warranty remedies are not available for the inspection and/or repair given in this service bulletin. **C. Parts Necessary For Each Airplane** 1. Kits/Parts None. 2. Parts and Materials Supplied by the Operator
**Notes Name**  **QTY Part Number /**  **Specification** (a) (c) Stiffener Assembly 2 69-19144-1 (a) Shim 8 BACS40R020B052F (a) (b) (d) Rivet 10 BACR15BB5D5C (a) (b) (d) Rivet 96 BACR15CE5D5C (a) (b) (d) Rivet 12 BACR15CE5D6C (a) (b) (d) Rivet 32 BACR15FP5E3C (a) (b) (d) Rivet 20 BACR15FP5E2C (a) (b) Bolt, Blind 4 BACB30VW5P03UX (a) (b) (e) Rivet 4 BACR15BA5D4C (a) Quantities shown are for both the left and right side elevator rear spar stiffener assembly replacement. (b) Refer to 727 Structural Repair Manual Chapter 51 for alternate fasteners. (c) The Boeing Company (V81205), 7755 E. Marginal Way, Seattle, WA 98108-4002, USA. (d) It is acceptable to use an oversize rivet of 1/32. (e) Use to make countersink repair washer.
3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 19 of 47 **BOEING SERVICE BULLETIN 727-55-0094 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: March 21, 2012 727-55-0094 20 of 47 **BOEING SERVICE BULLETIN 727-55-0094 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. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. 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 – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque limits to tighten nuts and bolts are in SRM Chapter 51 4. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. 5. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. 6. 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. 7. 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. 8. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. **B. WORK INSTRUCTIONS** 1. PART 1 - PREPARATION

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 21 of 47 **BOEING SERVICE BULLETIN 727-55-0094**a. Depressurize the elevator hydraulic systems A and B. Refer to 727 AMM 27-30-00 as an accepted procedure. 2. PART 2 - LEFT SIDE INSPECTION a. Prepare the area for safe work. Refer to Part 1 as an accepted procedure. b. Get access to the aft section of the left elevator rear spar (stiffener assembly). Refer to FIGURE 1 for stiffener assembly location and access. c. Do a detailed inspection of the upper surface of the stiffener assembly in accordance with FIGURE 1. (1) If any crack is found, replace the stiffener assembly in accordance with PART 4. d. Get access to the tab rod cut-out. Refer to FIGURE 1 for stiffener assembly location. e. Do a detailed inspection of the lower surface of the stiffener assembly in accordance with FIGURE 1. (1) If any crack is found, replace the stiffener assembly in accordance with PART 4. f. If work on the elevators is complete, put the airplane back to a serviceable condition. Refer to part 6 as an accepted procedure. 3. PART 3 - RIGHT SIDE INSPECTION a. Prepare the area for safe work. Refer to Part 1 as an accepted procedure. b. Get access to the aft section of the right elevator rear spar (stiffener assembly). Refer to FIGURE 6 for stiffener assembly location and access. c. Do a detailed inspection of the upper surface of the stiffener assembly in accordance with FIGURE 6. (1) If any crack is found, replace the stiffener assembly in accordance with PART 5. d. Get access to the tab rod cut-out. Refer to FIGURE 6 for stiffener assembly location. e. Do a detailed inspection of the lower surface of the stiffener assembly in accordance with FIGURE 6. (1) If any crack is found, replace the stiffener assembly in accordance with PART 5. f. If work on the elevators is complete, put the airplane back to a serviceable condition. Refer to part 6 as an accepted procedure. 4. PART 4 - LEFT SIDE STIFFENER ASSEMBLY REPLACEMENT a. Prepare the area for safe work. Refer to Part 1 as an accepted procedure. b. Remove and keep the left side elevator tab. Refer to 727 AMM 27-30-11 as an accepted procedure.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 22 of 47 **BOEING SERVICE BULLETIN 727-55-0094**c. Partially remove the upper skin panel of the elevator, and get access to the stiffener assembly in accordance with FIGURE 2 . d. Remove the stiffener assembly in accordance with FIGURE 3. e. Install new stiffener assembly in accordance with FIGURE 4. f. Install the partially removed upper skin panel in accordance with FIGURE 5. g. Install the kept left side elevator tab. Refer to 727 AMM 27-30-11 as an accepted procedure. h. If work on the elevators is complete, put the airplane back to a serviceable condition. Refer to part 6 as an accepted procedure. 5. PART 5 - RIGHT SIDE STIFFENER ASSEMBLY REPLACEMENT a. Prepare the area for safe work. Refer to Part 1 as an accepted procedure. b. Remove and keep the right side elevator tab. Refer to 727 AMM 27-30-11 as an accepted procedure. c. Partially remove the upper skin panel of the elevator, and get access to the stiffener assembly in accordance with FIGURE 7 . d. Remove the stiffener assembly in accordance with FIGURE 8. e. Install new stiffener assembly in accordance with FIGURE 9. f. Install the partially removed upper skin panel in accordance with FIGURE 10. g. Install the kept right side elevator tab. Refer to 727 AMM 27-30-11 as an accepted procedure. h. If work on the elevators is complete, put the airplane back to a serviceable condition. Refer to part 6 as an accepted procedure. 6. PART 6 - PREPARE FOR SERVICE a. Pressurize the elevator hydraulic systems A and B. Refer to 727 AMM 27-30-00 as an accepted procedure. b. Do a functional test of the elevator tab. Refer to 727 AMM 27-30-00 as an accepted procedure. c. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 23 of 47 **BOEING SERVICE BULLETIN 727-55-0094 FIGURE 1: LEFT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - INSPECTION**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 24 of 47 **BOEING SERVICE BULLETIN 727-55-0094**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  (a) (c) 1 69-19144-1 Elevator Rear Spar Stiffener Assembly, Upper Surface Inspect 1

(b) (c) 1 69-19144-1 Elevator Rear Spar Stiffener Assembly, Lower Surface Inspect 2

(a) Do a detailed inspection of the upper surface of the elevator rear spar stiffener assembly for cracks. (b) Do a detailed inspection of the lower surface of the elevator rear spar stiffener assembly for cracks, inspect the exposed area along the length of the stiffener to within 0.5 inches from the vertical web. (c) Use of a Borescope is acceptable for this inspection.

**FIGURE 1: LEFT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - INSPECTION (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 25 of 47 **BOEING SERVICE BULLETIN 727-55-0094 FIGURE 2: LEFT SIDE ELEVATOR UPPER SKIN PANEL - PARTIAL REMOVAL**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 26 of 47 **BOEING SERVICE BULLETIN 727-55-0094**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  (a)

- - Fasteners Remove 1 **CAUTION:** WHEN YOU LIFT THE UPPER SKIN PANEL MAKE SURE YOU DO NOT CREASE THE UPPER SKIN PANEL. (b) 1
- Upper Skin Panel Lift 2 (a) Remove the fasteners shown as a circle symbol first. If access to the rear spar stiffener assembly is not possible continue to remove the fasteners moving forward until access is possible.(b) Lift back the skin panel fastener row by fastener row to get access to the elevator rear spar stiffener assembly.

**FIGURE 2: LEFT SIDE ELEVATOR UPPER SKIN PANEL - PARTIAL REMOVAL (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 27 of 47 **BOEING SERVICE BULLETIN 727-55-0094 FIGURE 3: LEFT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - REMOVAL**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 28 of 47 **BOEING SERVICE BULLETIN 727-55-0094**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step** 

- 1 69-19144-1 Elevator Rear Spar Stiffener Assembly Remove 1

- 17
- Fasteners Remove

**FIGURE 3: LEFT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - REMOVAL (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 29 of 47 **BOEING SERVICE BULLETIN 727-55-0094 FIGURE 4: LEFT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - INSTALLATION**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 30 of 47 **BOEING SERVICE BULLETIN 727-55-0094 FIGURE 4: LEFT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - INSTALLATION**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 31 of 47 **BOEING SERVICE BULLETIN 727-55-0094**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  (a) 1 69-19144-1 Elevator Rear Spar Stiffener Assembly Install (New) 1 (b) (c) (d) 2 BACS40R020B052F Shim Install (New) (a) Any gaps are not to exceed 0.003 inches. (b) Install shims as necessary to fill any gaps greater than 0.003 inches. (c) Cut shims to match the profile of the elevator rear spar stiffener assembly. (d) Make sure there is clearance for the tab rod cutout in the rear spar.

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure.
**More Data Hole Dia**  **Qty Identification**  **Name Code**  (a) 0.159 - 0.171 5 BACR15BB5D5C Rivet A (a) 0.159 - 0.171 12 BACR15CE5D5C Rivet B (a) It is acceptable to use an oversize rivet of 1/32.

**FIGURE 4: LEFT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - INSTALLATION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 32 of 47 **BOEING SERVICE BULLETIN 727-55-0094 FIGURE 5: LEFT SIDE ELEVATOR UPPER SKIN PANEL - INSTALLATION**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 33 of 47 **BOEING SERVICE BULLETIN 727-55-0094 FIGURE 5: LEFT SIDE ELEVATOR UPPER SKIN PANEL - INSTALLATION**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 34 of 47 **BOEING SERVICE BULLETIN 727-55-0094**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step** 

- 1
- Upper Skin Panel Install (Kept) 1

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure.
**More Data Hole Dia**  **Qty Identification**  **Name Code**  (c) 0.159 - 0.171 36 BACR15CE5D5C Rivet A (c) 0.159 - 0.171 6 BACR15CE5D6C Rivet B (c) 0.176 - 0.180 10 BACR15FP5E2C Rivet C (c) 0.176 - 0.180 16 BACR15FP5E3C Rivet D (a) (c) 0.159 - 0.171 6 BACR15CE5D6C Rivet E (a) (c) 0.159 - 0.171 6 BACR15CE5D5C Rivet F (b) 0.180 - 0.183 2 BACB30VW5P03UX Bolt, Blind G (a) Use as necessary if additional fasteners were removed for access. (b) Make a repair washer from BACR15BA5D4C rivets to fill countersink. (c) It is acceptable to use an oversize rivet of 1/32.

**FIGURE 5: LEFT SIDE ELEVATOR UPPER SKIN PANEL - INSTALLATION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 35 of 47 **BOEING SERVICE BULLETIN 727-55-0094 FIGURE 6: RIGHT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - INSPECTION**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 36 of 47 **BOEING SERVICE BULLETIN 727-55-0094**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  (a) (c) 1 69-19144-1 Elevator Rear Spar Stiffener Assembly, Upper Surface Inspect 1

(b) (c) 1 69-19144-1 Elevator Rear Spar Stiffener Assembly, Lower Surface Inspect 2

(a) Do a detailed inspection of the upper surface of the elevator rear spar stiffener assembly for cracks. (b) Do a detailed inspection of the lower surface of the elevator rear spar stiffener assembly for cracks, inspect the exposed area along the length of the stiffener to within 0.5 inches from the vertical web. (c) Use of a Borescope is acceptable for this inspection.

**FIGURE 6: RIGHT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - INSPECTION (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 37 of 47 **BOEING SERVICE BULLETIN 727-55-0094 FIGURE 7: RIGHT SIDE ELEVATOR UPPER SKIN PANEL - PARTIAL REMOVAL**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 38 of 47 **BOEING SERVICE BULLETIN 727-55-0094**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  (a)

- - Fasteners Remove 1 **CAUTION:** WHEN YOU LIFT THE UPPER SKIN PANEL MAKE SURE YOU DO NOT CREASE THE UPPER SKIN PANEL. (b) 1
- Skin Panel Lift 2 (a) Remove the fasteners shown as a circle symbol first. If access to the rear spar stiffener assembly is not possible continue to remove the fasteners moving forward until access is possible.(b) Lift back the skin panel fastener row by fastener row to get access to the elevator rear spar stiffener assembly..

**FIGURE 7: RIGHT SIDE ELEVATOR UPPER SKIN PANEL - PARTIAL REMOVAL (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 39 of 47 **BOEING SERVICE BULLETIN 727-55-0094 FIGURE 8: RIGHT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - REMOVAL**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 40 of 47 **BOEING SERVICE BULLETIN 727-55-0094**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step** 

- - 69-19144-1 Elevator Rear Spar Stiffener Assembly Remove 1

- 17
- Fasteners Remove

**FIGURE 8: RIGHT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - REMOVAL (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 41 of 47 **BOEING SERVICE BULLETIN 727-55-0094 FIGURE 9: RIGHT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - INSTALLATION**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 42 of 47 **BOEING SERVICE BULLETIN 727-55-0094 FIGURE 9: RIGHT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - INSTALLATION**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 43 of 47 **BOEING SERVICE BULLETIN 727-55-0094**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  (a) 1 69-19144-1 Elevator Rear Spar Stiffener Assembly Install (New) 1 (b) (c) (d) 2 BACS40R020B052F Shim Install (New) (a) Any gaps are not to exceed 0.003 inches. (b) Install shims as necessary to take-up any gaps. (c) Cut shims to match the profile of the elevator rear spar stiffener assembly. (d) Make sure there is clearance for the tab rod cutout in the rear spar.

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure.
**More Data Hole Dia**  **Qty Identification**  **Name Code**  (a) 0.159 - 0.171 5 BACR15BB5D5 Rivet A (a) 0.159 - 0.171 12 BACR15CE5D5C Rivet B (a) It is acceptable to use an oversize rivet of 1/32.

**FIGURE 9: RIGHT SIDE ELEVATOR REAR SPAR STIFFENER ASSEMBLY - INSTALLATION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 44 of 47 **BOEING SERVICE BULLETIN 727-55-0094 FIGURE 10: RIGHT SIDE ELEVATOR UPPER SKIN PANEL - INSTALLATION**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 45 of 47 **BOEING SERVICE BULLETIN 727-55-0094 FIGURE 10: RIGHT SIDE ELEVATOR UPPER SKIN PANEL - INSTALLATION**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 46 of 47 **BOEING SERVICE BULLETIN 727-55-0094**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  (a) 1
- Skin Panel Close 1 (a) If any additional fasteners were removed for access forward of the ones shown, replace with Code E fasteners at the center section of the doubler and Code F fasteners at the two outside sections of the doubler.

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure.
**More Data Hole Dia**  **Qty Identification**  **Name Code**  (c) 0.159 - 0.171 36 BACR15CE5D5C Rivet A (c) 0.159 - 0.171 6 BACR15CE5D6C Rivet B (c) 0.176 - 0.180 10 BACR15FP5E2C Rivet C (c) 0.176 - 0.180 16 BACR15FP5E3C Rivet D (a) (c) 0.159 - 0.171 6 BACR15CE5D6C Rivet E (a) (c) 0.159 - 0.171 6 BACR15CE5D5C Rivet F (b) 0.180 - 0.183 2 BACB30VW5P03UX Bolt, Blind G (a) Use as necessary. (b) Make a repair washer from MS20426D5-4 rivets to fill countersink. (c) It is acceptable to use an oversize rivet of 1/32.

**FIGURE 10: RIGHT SIDE ELEVATOR UPPER SKIN PANEL - INSTALLATION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 21, 2012 727-55-0094 47 of 47 **BOEING SERVICE BULLETIN 727-55-0094**