J\#IANDATORY 

SERV1 CE BUlLETlN 

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

NSTAL ATlON 

1. Planning Information 

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. 

Tnc cxpor. cf tnoso ccmm.au,t•cs tcct'I'IOiogy r.r o;ctrware a·c sub1ect 10 Inc US Exr:urt Acw•n strm en Re').JI;:t ~ns D•vers1cn cantra")' to U S lllw IS oro;.1b1:od For gu cilncn on 

J(cmt corr.:ol rcq..Jsrtments on~acr lhe Commerce Oeo.-mmcn· s Bureau ol r~uon 

AdllW'I1Sira~•o1 al rttp •'/ .......... w o s dec ~;ov 

H3Wr(Cf re~hcr~'1 Cc;oorat•cn (H8Cl ~st.es St!fv cc l,fcnratiCn icr tho berelit ot oNncrs 

ana fucP:'l L:ase cpcr;uors 111 tt:e form ot two c.a$:;os of Serv~cc Bullettrs Tl"'o f1rst c 3SS Ma"\datofy s~"-'ICO Bu"ehns (red bo•cJt:r) IOCh..Jdes changes. mspecu:>n OJn:1 moo 1

1C31u:ms rna: ccu :::l ;)rfCCt saf&ty or c.r;Jsnwo·th ness f tnC also t5Sl.C5 Sc::viCe Bu'.cllns wtlh ro red border 

.,._.:1tcn nro d~Stgn.J~cd .1::; f!lll'er rucommonc:ed cr cpt ocnoltn tr1~ ccmpl·ance ~ec: on\'nlt':ll l ltH:t tl.ttfll n In tho ::ase of recommended Sorv.ce Bu'tcllns. HBC fcc.s t•'11J crl.1ngcs mOC'1fiC.:111ons. •1l;llo'1J e'Tlcn1s c r nsoect•ons Wtll benct.t l"le cr.vncr/ooerator ~nd a.tno.;gn htg"lly re"'....crrrntmcnd. RecOfrJnenccd Servtce Aullet~ns are r.ot cons«:eH~d maroatorv ilt thn ~1 11e of tssuance In tM c<1se oi Op1t:::nnl r~t ce Buli~Hns. co.-no 1<1nca w1111 the cn.Y~ges mod llc.Jtlcns unp~ovc"'11en ts ot mspactrons •S ill the O' .... net/coc-r.ltor's :scrc~l()f'l 

Issued: February, 2013 

Doth c .:~sscs are avo.ulil:>'o on me w~b m l'ltt:> 1/pub::s nif,Y r(c rbee ~cr3n cern a1d ,:,w!cd 10 

(a) o ·.vna's of fecord on ~he FAA /\1rt:mf; s1r:n en Oraneh L,s: om:l tt'e HBC Safe:v o1 I I ght lr lo11 nat.an ISOFI) L·st 

n.J) Jhose h.lv1ng n puol catiOnS S.J.OSCrl pt•on 

IMn·maton on !)et~e tv of fhght lnfcnnahon tSOFn or Sl.b:sc.r chon can oo obt<liMO through t!le H.:r.vkef eeChcr.1~ Co:oorat•on Tochn·C'-11 MamJCI:I Oist:.outiC'Ifl Con:e: TMOC } As 

Mn'lda~ 'Y SerJ·cc Ol.~let ns ana Servtce But et·ns a·e l!:isued !he SePJ.te Hl.llctn r~'l3 ~· lrde.< w•Ll be upda!ed and .l'J<llla::>le cnhr,e at hap //pubs n()'Nr<.e b~cncrull com '.V.:m.1nty 

WI I oe ~U0'.\ 0<1 only Wilen spec:frcally cnf ne~ 1"'1 1"1e SC."\\ICe 8 t..11etl.., o1f'ld tr: a:cc·aJ'1CO Wlltl 

H~ C W<~~ranty Po'•c-1 

Unless o:heiW•se dos 1~1ated HBC Mar.catcry Scrvtee Bt.:.lel ns Scrv.ce Bt.l c:<1s 3nd HBC K •ts are i'lpprnvea fer m5t.1 11il:IOI"' on HBC mrp :-~nes n ong1nat or HBC nod fic<l ccnhqurnt•cn!i 

cnlv HRC Mand.:1:ory Stlrv.ce au·•ot ns Serv'Cc Oullettns an:j Kits may not bo comp:u tlo 'HIIh a rrulancs mod If-ad ov $ r c .nstaii.:HIOn5 0!' rrodtftc.;:mons Olher than HBC .Oppt'O'/UC l'.t~S 

SB 57-4112 

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_J;lmv.ker <Veechcraft 

MANDATORY] 

SERVICE BULLETIN 

D. Compliance 

An Airworthiness 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 

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.-~~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 with 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 accomplished 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 will 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) 

1 0511 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-mail: HBC_Parts@hawkerbeechcraft.com 

Issued: February, 2013 58 57-4112 

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..... :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 

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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 

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MANDATORY ] 

SERVICE BULLETIN 

(4) Inspect to determine if sealant exists on doubler plate edges, doubler plate rivets, and adjacent skin 

in the top and bottom of the fuel surge tank. Refer to Figures 1 through 4. 

(a) If sealant exists, no further action is reauired. 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 

assembly, 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 in 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 

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.... ~~ '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 permissible 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 

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MANDATORY 

SERV~CE BULLETIN 

For every 10° above 7r Fahrenheit, the sealant application time is reduced by 

half, and for every 1 oo below 7r Fahrenheit, the application time is doubled. 

Sealant can be exposed to fuel after 48 hours. 

(a) Apply 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) Apply 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 doubler 

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 wiring 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) Install access panels that were removed in Step (2) and Step (3) of Part A. Use the retained 

hardware. 

(1 0) Fuel the aircraft in accordance with AMM Chapter 12-28-00. 

(11) Reconnect the airplane batteries, remove warning notices, and restore power. 

Issued: February, 2013 SB 57-4112 

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----- 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 

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.... 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 

,I ! . .. • 

..•. ,..- ; 

.. -, ~-

'- - -':• · .. -

, A .. . -;. ~ . - .. · . ....... : . ·- .......... >,'· ... 

'·' 

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 

841120}./\1 

SB 57-4112 

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.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 

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..~7~ ldeechcraft 

----- MANDATORY 

SERVICE BULLETlN 

REMOVE ACCESS PANEL.~ 

?/N 25-3WS903-1/2. 

RETAIN ATTACHMENT HARDWARE. 

REMOVE ACCESS PANEL. 

PiN 25-8WS905-1A 

RETAIN ATTACHMENT HARDWARE. 

}J 

BOTTOM SKIN SHOWN 

VIEW LOOKING DOWN 

DETAILA ~ 

Issued: February, 2013 

Sealant Coverage for Lower Skin 

Figure 3 

•", .. --... 

' : . ! -·: :.:~ • • 

. ... - / 

, :·-:-- ~- -, A 

/-::-_-:·_-_'--· _-· __ --- --- · .. ·- · _': • .. ··""' --..:::: 

RIB 14 

+ + + + .. .... -.----- -- .. - .. -...... --

APPLY SEALANT TO 

THE DOUBLER 

PLATE EDGE, ALL 

THE WAY AROUND 

B41t201 /\1 

SB 57-4112 

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... 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 

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