# J\#IANDATORY

**SERV1 CE**  

# BUlLETlN ITLE . 'NII\JG3 -SEALING OF FUEi.. VENT SURGE TANK FOR LIGHTNING ?ROTECTlON IN WINGLET

**NSTAL ATlON**  

### 1 . Pl anning I nformation A. Effectivity ( 1) Airplanes Hawker 800XP and Hawker 850XP. if equipped with one of the following kits : 140-1701-1 . 140-1702-1 . 140-1703-1 . 140-1703-5. 140-1703-7 or 140-1704-1 . NOTE The above-listed kits meet the intent of this Service Bulletin if purchased from Hawker Beechcraft Corporation (HBC) after the release date of this Service Bulletin . No further action is required . Hawker 900XP, Serials HA-0156 and HA-0159 . If you are no longer in possession of the airplane , please forward this information to the present owner. (2) Spares None . B . Reason This Service Bulletin is being issued because the winglet installation may have omitted sealant in the left and right fuel vent surge tank between ribs 14 and 15 . Sealant is required for lightning protection. C. Description This Service Bulletin is being issued to inspect for sealant in the left and right fuel vent surge tank between ribs 14 and 15 . If the required sealant is missing , it shall be applied to the affected areas .

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# SB 57-4112 1 of 13

# _J;lmv.ker 

# <Veechcraft MANDATORY] 

# SERVICE BULLETIN D. Compliance An Airworth iness Directive will be requested on the matter covered by this Service Bulletin. Hawker Beecncraft Corporation considers this to be a Mandatory Service Bulletin . It must be accomplished no later than 600 flight hours or 12 months from issuance of this Service Bulletin , whichever occurs first. 

### E. Approval The engineering data contained in this Service Bulletin is FAA approved. Prior to accomplishment, owners/operators of airplanes registered in countries other than the United States shall consult with their local Aviation Regulatory Authority. Incorporation of this Service Bulletin restores the airplane to original Type Design . 

### F. Manpower The following information is for planning purposes only : Estimated man-hours for Part A: 

### 2 hours Estimated man - hours for Part B : 36 hours Suggested number of technicians : 1 The above is an estimate based on experienced, properly equipped technicians complying with this Service Bulletin . 

### G. Weight and Balance Negligible . It is the responsibility of the owner/operator to maintain compliance with the applicable Airworthiness Regulations. 

### H. Electrical Load Data No change . I. 

### Software Accomplishment Summary Not applicable . 

### J. References Kit 140-1701-1 ; Kit 140-1702- 1; Kit 140-1703-1 ; Kit 140-1703-5 ; Kit 140-1703-7; Kit 140-1704-1. Aircraft Maintenance Manual (AMM) , Chapter 12 , Chapter 20 , and Chapter 28 . Issued : February, 2013 

# 58 57-4112 2 of 13

# .-~~DWKelw 

# · J:ieechcraft

K. Publications Affected None . 

# SERVICE BULLETIN

L. Interchangeability of Parts Not applicable . M. Warranty Credit 

# MANDATORY

Warranty credit for labor and parts to the extent noted under MANPOWER and MATERIAL will be allowed on all airplanes meeting all the following criteria :

(1) Airplane owners must have active Standard Warranty coverage and/or an active HBC Maintenance program with applicable Service Bulletin coverage for the subject airplane when the Service Bulletin is issued. (2) Standard Warranty coverage and/or HBC Maintenance Program w ith applicable Service Bulletin coverage must be active for the subject airplane on the day the work is accomplished . (3) The work shall be accomplished in accordance with the criteria defined in Paragraph 1 . D ., COMPLIANCE . (4) The work shall be accomplished in accordance with criteria defined in Paragraph 3 , ACCOMPLISHMENT INSTRUCTIONS. (5) The work shall be accomplished at an HBC ASC facility Hawker rated to perform maintenance on the specific model of Hawker Beechcraft airplane . (6) While work shall be accompl ished in accordance with the criteria defined in Paragraph 1 . 0 , COMPLIANCE , warranty coverage offered in this Service Bulletin will expire 

### 12 months from the last day of the month this Service Bulletin is issued . {7) Claims for compliance with this Service Bulletin (SB) are to be filed as a W3 -type claim against SB 57-4112 . (8) After the Service Bulletin has been accomplished, a warranty claim must be submitted to HBC within 

### 60 days of the Service Bulletin completion date . (9) HBC w i ll not provide compensation for fuel removed to perform the accomplishment instructions of this Service Bulletin . 

### 2. Materiallnformation A. Materials - Price and Availability Contact information : Hawker Beechcraft Parts & Distribution (HBP&D) 10511 East Central Avenue Wichita , KS 67206 USA Phone : 316-676-3100 or 1-888 -727-4344 Fax: 316-676-3222 or 316-676-3327 E-ma i l: HBC_Parts@hawkerbeechcraft .com Issued : February, 2013 

# 58 57-4112 3 of 

### 13

# .....:lmMter

**~eechcraft** 

# --- MANDATORY 

# SERVICE BULLET) B. Industry Support Not applicable . C. Airplanes (1) The following parts required for accomplishment of this Service Bulletin may be ordered through a Hawker Beechcraft Authorized Service Center or HBP&D : Part Number Description Quantity Per Airplane 100-214-8815 0-Ring (Preformed Packing) 2 AGS1186-3 Seal 8 1

00-230-8815 0-Ring (Preformed Packing) 4 100-226-8815 0-Ring (Preformed Packing) 2 Hawker Beechcraft Corporation expressly reserves the right to supersede, cancel and/or declare obsolete , without prior notice , any parts or publications that may be referenced in this Service Bulletin. (2) The following materials may be obtained locally : Material Item I Part Number Description Quantity Per Airplane 20-95-301-001 , Item 335A Adhesion Promoter As Required (Ref. AMM Chapter 20) 20-95-201-001 , Item 201 Aliphatic Naphtha As Required (Ref. AMM Chapter 20) 20-95-301-001 , Item 351 Sealant As Required (Ref. AMM Chapter 20) A-A-1491 . CCC-C-440 , Or Cotton Cheesecloth As Required Equivalent A-A-53513 or 1877711 Gloves , Polyethylene , Industrial Air Solvent Handling As Required D. Spares Not applicable . 

### E. Reidentified Parts None. Issued: February, 2013 

# SB 57-4112 4 of 13

# MANDATORY 

# SERV CE BULLETIN F. Tooling • Price and Availability Not applicable . 

### 3. Accomplishment Instructions This Service Bulletin shall be accomplished as follows:

A. Airplane NOTE Should any difficulty be encountered in accomplishing this Service Bulletin, contact Hawker Beechcraft Corporation at 1-800-429-5372 or 316-676-3140. 

# I WARNING 

# I Observe all Warnings and Cautions contained in the airplane manuals referenced in this Service Bulletin. Whenever any part of this system is dismantled, adjusted, repaired or renewed, detailed investigation must be made on completion to make sure that distortion, tools, rags or any other loose articles or foreign matter that could impede the free movement and safe operation of the system are not present, and that the systems and installations in the work area are clean. (1) Remove all power from the airplane and disconnect the batteries. Display warning notices prohibiting reconnection of airplane electrical power. NOTE The following instructions apply to the left and right fuel vent surge tanks . Part 

### A: Inspection of Left and Right Fuel Vent Surge Tanks for Sealant

(1) Defuel the aircraft and purge the fuel cell in accordance with Aircraft Maintenance Manual (AMM) , Chapter 12-28-00 and Chapter 28-10-15. (2) Remove wing fuel surge tank access panel, P/N 25-8WS903-1/-2, as follows : (a) Remove 27 bolts , PIN 25-WS3195-5 , in accordance with guidelines provided in Structural Repair Manual (SRM), Chapter 51-43-00-001 . Each bolt may be used again if the finish is undamaged and the thread is in good condition. Refer to Figure 2 and Figure 

### 3 . (b) Remove wing fuel surge tank access panel , P/N 25-8WS903-1/-2 . (3) 

### Remove wing access panel , P/N 25-8WS905-1A, as follows : (a) Remove 10 bolts, PIN 25-WS3195-1 , in accordance with guidelines provided in SRM , Chapter 51-43-00-001. Each bolt may be used again if the finish is undamaged and the thread is in good condition . Refer to Figure 2 and Figure 3. {b) Remove wing access panel , P/N 25-8WS905-1A. Issued : February, 2013 

# SB 57-4112 5 of 13

# MANDATORY 

# ] SERVICE BULLETIN (4) Inspect to determine if sealant exists on doubler plate edges , doubler plate rivets , and adjacent skin i n the top and bottom of the fuel surge tank . Refer to Figures 1 through 4 . (a) If sea lant ex ists , no further action is re aui red . Proceed to Final Check . (b) If sealant does not exist , proceed to Part B. 

### Part 8: Application of Sealant in the Left and Right Fuel Vent Surge Tanks

(1) Determine if duct, P/N 25-8PV219-1A , and intake assembly, PIN 25-8PV217-1A/2A, need to be removed to make it possible to remove duct assembly, P/N 25-8PV223-1A/2A. Refer to Figure 1 . (a) If the duct assembly, PIN 25-8PV223-1A/2A, can be removed with the associated parts in place , proceed to Step (2) . (b) If the duct assembly, PIN 25-8PV223-1A/2A, can not be removed with the associated parts in place , proceed to Step (1)(c). (c) Inboard of rib 14 , remove intake assembly, PIN 25-8PV217-1A/2A. Remove duct, PIN 25-8PV219-1A. Discard seals . Proceed to Step (2) . (2) Accomplish the following in the wing surge tank between ribs 14 and 15 : (a) Locate float switch , PIN 3515000-106 , that is attached to rib 15 . (b) Outboard of rib 15, disconnect wiring that corresponds to overfill float switch , PIN 3515000-106 , and high-level float switch , PIN 3515000-107 . The high - level float switch is attached to rib 14 . Remove the overfill float switch , PIN 3515000-106 . Do not remove the high-level float switch. Discard seals . Use applicable guidelines in AMM , Chapter 28-44-43-401 . (c) Wiring runs from the high-level float switch , PIN 3515000-107, to conduit assembly, PIN 25-8PV201-15A/16A. A bond jumper connects conduit assembly, PIN 25-8PV223-1 A/2A. Disconnect the bond jumper at both ends . Retain the bond jumper. (d) Remove conduit assembly, PIN 25-8PV201 - 15A/16A. (e) The wiring shall be coiled and temporarily attached outside of the wing through the access panel between ribs 14 and 15 . NOTE It is advised to use the access area inboard of rib 14 to assist in removal 

### of duct assemb ly, PIN 25-8PV223-1A/2A. (f) Remove duct assembly, PIN 25-8PV223-1A/2A. (g) Protect any open holes from sealant that will be added i n the following steps . 

# I WARNING 

# I Solvents and sealants are flammable and toxic to skin, eyes, and respiratory tract. Skin and eye protection is required. Avoid repeated or prolonged contact. Keep away from flames or sources of heat. Use in a well-ventilated area or respiratory protection equipment may be required. Issued : February, 2013 

# SB 57-4112 6 of 13

# .... **~~** 

# 'Jdeechcraft MANDATORY 

# SERVICE BULLETIN (3) Three doubler plates require sealant protection on the fuel surge tank upper skin : Doubler plate, PIN 25-8WS6047 ; Doubler plate , P/N 25-8WS6049 ; Doubler plate , P/N 25-8WS6057 . One doubler plate requires sealant protection on the fuel surge tank lower skin : Doubler plate. P/N 25-8WS6061 . The doubler plate edges and rivets , along with adjacent skin , shall be covered with sealant as defined in the following Step (4), along with Figures 2, 3 and 4 . Clean these areas as follows : (a) Dispense Aliphatic Naphtha onto cheese cloth in accordance with AMM Chapter 20-95-201 -001 , Item 201 . Do not wipe the cloth into the solvent. (b) Use the cloth to clean the surface. Turn the cloth frequently. Change to a new cloth as soil becomes evident. (c) Before the Naphtha evaporates, dry the surface using a clean , lint-free cloth . Repeat Steps (3)(a) through (3)(c) until the drying cloth shows no sign of soil removal. (d) Clean the surface again , in accordance with the above procedure, if the surface is not sealed within 24 hours. (e) Apply a thin coat of adhesion promoter, P/N PR-148, by brush or clean gauze pad . Wipe off excess with clean gauze pad . Dry time ranges from 15 minutes at 70° Fahrenheit to 45 minutes at 40 ° to 60 ., Fahrenheit ambient conditions. If sealing is not completed within 8 hours , repeat the process. (4) Accomplish the following on the upper and lower 

### skin of the wing surge tank, between ribs 14 and 15 : NOTE 

### Prior to application of sealant in the steps below, it is permissible to verify the process by conducting a practice application on scrap material. Additional sealant may be applied , if necessary. Due to limited access in this area , visual inspection will be required to verify minimum sealant thickness . It is permiss ible to use a long nozzle extruder, brush , non-metallic spatula or clean gauze pad . Use the sealant manufacturer's technical data sheet for application times, tack free times, and cure times . Issued: February, 2013 

# SB 57-4112 7 of 13

# MANDATORY



# SERV~CE 

# BULLETIN F

or every 1 0° above 

# 7 r Fahrenheit , the sealant application time is reduced by half, and for every 1

# o o

below 

# 7 r Fahrenheit, the application time is doubled . Sealant can be exposed to fuel after 48 hours . (a) App ly sealant , PIN PR-1440 , to all fasteners that are installed on upper skin doubler plates , PIN 25-8WS6047 , P/N 25 -8WS6049 , and P/N 25-8WS6057 . In addition , apply the same sealant to the lower skin doubler plate, PIN 25-8WS6061 . (b) Establish a minimum of 0.12-inch sealant coverage over each fastener. (c) App ly sealant , P/N PR-1440 , to all exposed edges of the four doubler plates. (d) Establish a minimum of 0. 15-inch sealant coverage over all exposed edges of the doub ler plates. (e) Establish a minimum of 0.25-inch sealant coverage extending from the doubler plate edges to the skin . (5) Remove any protective covers that were installed over open holes in Step (2)(g) . (6) Install duct assembly, P/N 25-8PV223-1A/2A, using new seal , P/N 100-230-8815 . Establish clearance of 0. 12/0 .35-inch between the tube end fitting extending out from the fitting in the rib . Refer to Figure 1 . (7) Use applicable new seals , P/N 100-226-8815 , and PIN 100-230-8815 , to install duct, P/N 25 -8PV219-1A , and intake assembly, PIN 25 -8PV217-1A/2A, if these items were removed in Part B , 

### Step (1 ) . Establish clearance of 0 .29/0 .63- inch between duct and intake assembly. Refer to Figure 

### 1 . If these items were not removed in Part 

### B, Step (1 ) , proceed to the following Step (8) . (8) Accomplish the following to move float switches into position : (a) Use the coiled wiring that was disconnected from the high-level float switch , P/N 3515000-107 , to install the conduit assembly, P/N 25-8PV201-15A/16A. 

### (b) Install overfill float switch , P/N 3515000-106 , to rib 15 with four (4) new seals , P/N AGS1186-3 and seal , PIN 100-214-8815. Use applicable guidance in AMM , Chapter 28-44-43-401 . (c) Outboard of rib 15 , reconnect wi ring for overfill float switch , PIN 3515000-106 , and high-level float switch , PIN 3515000-107 . Use applicable guidance in AMM , Chapter 28-44-43-401 , and Chapter 28-22-143-401 . {d) Connect the bond jumper between the conduit assembly and duct assembly, P/N 25 -8PV223- 1A/-2A. 

### Final Check

(9) Insta ll access pane ls that were removed in Step (2) and Step (3) of Part A. 

### Use the reta ined hardware. ( 10) Fuel the aircraft i n accordance with AMM Chapter 12-28 -00 . (11) Reconnect the airplane batteries , remove warn ing notices , and restore power.
Issued : February, 20 13 

# SB 57-4112 8 of 13

# ----- MANDATORY 

# SERVICE BULLETIN (12) Ensure all work areas are clean and clear of tools and miscellaneous items of equipment. (13) Return airplane to service . B. Spares Not applicable . C. Record of Compliance Upon completion of this Service Bulletin, make an appropriate maintenance record entry.

Issued: February, 

### 2013 

# SB 57-4112 9 of 

### 13

# .... **7~** 

# 1feechcraft

DETAIL

# A IF NECESSARY, REMOVE INTAKE ASSEMBLY. P/N 25-8PV217-1A P/N 25-8PV217-2A 

# SERVICE BULLETlN

LOCATION FOR HIGH-LEVEL FLOAT SWITCH, P/N 3515000·107 AND CONDUIT ASSEMBLY, P/N 25-8PV201-15A/-16A . DETAIL 

# B NOTES: 

# MANDATORY

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IF NECESSARY , REMOVE VENT DUCT, P/N 25-8PV219-1A.

REMOVE DUCT ASSEMBLY, P/N 25·8PV223-1A/-2A .

A= 0.29/0.63-INCH CLEARANCE BETWEEN DUCT AND INTAKE ASSEMBLY FOR INSTALLATION PURPOSES IN PART B , STEP (7). B = 0 .12/0 . 35-INCH CLEARANCE BETWEEN THE TUBE END FITIING EXTENDING OUT FROM THE FITIING IN THE RIB, FOR INSTALLATION PURPOSES IN PART B , STEP (6).

Issued: February, 2013 Duct Configuration for Fuel Vent Surge Tank Figure 1 84 1 120}./\1 

# SB 57-4112 10 of 13

# .J7~ 

# Yeechcraft 

# --- MANDATORY 

# SERV CE BULLETIN

PLATE P/N 25-8WS6047
PLATE P/N 25-8WS6049

PLATE P/N 25-8WS6057

Issued: February, 2013 

### Sealant coverage for Upper Skin Figure 2 DETAIL 

# B 

# if . - · "": · 

# ... A

SB 57-4112 11 of 13

# ..~7~ 

# ldeechcraft



# - ---- MANDATORY 

# SERVICE BULLETlN
REMOVE ACCESS **PANEL.~** ?/N 25 -3WS903- 1/2. RETAIN ATTACHME NT HAR DWARE .
REMOVE ACCESS PANEL. Pi N 25-8WS905-1A RETAIN ATTACHMENT HARDWARE.



## }J BOTTOM SKIN SHOWN VIEW LOOKING DOWN DETAILA



## ~
Issued: February, 2013 Sealant Coverage for Lower Skin Figure 3 •" ,. . --... ' : . ! -·:

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### ... . - / 

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·- · _': • .. ··""' --..:::: RIB 14



### + + + + 

### .. .... -.----- -- 

### .. - 

### .. - ...... --

APPLY SEALANT TO THE DOUBLER PLATE EDGE, ALL THE WAY AROUND B41t201 /\1 

# SB 57-4112 12 of 13

# ... 7mvkel' CQeechcraft 

# SERVICE BULLETIN

Issued : February, 2013 Sealant Dimension Requirements Figure 4 

# MANDATORY

A= 0 . 15 MIN B 

# = 0.15 MIN C 

# = 0 .25 MIN



# SB 57-4112 13 of 13