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Herker Beechcraft
MANDATORY
SERVICE BULLETIN TITLE: WINGS - SEALING OF FUEL VENT SURGE TANK FOR LIGHTNING PROTECTION IN WINGLET INSTALLATION
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.
Tomstation Regulars Owersion coitary to 05 law is prombed for gu cance oft Administration Regulations. Diversion contrary to U.S For guidance on export control requirements. contact the Commerce Department's Bureau Administration at http /www.bis.doc.gov Hawker Beecheraft Corporation (HBO) Issues Service Information for the benefit of owners Mandatory Service Bulletins (red border) includes changes, inspection and modifications that and fixed base operators in the form of two classes of Service Bulletins. The first class could affect safety or crashworthiness HBC also issues Service Bulletins with no red border which are designated as either recommended or optional in the compliance section within the bulletin In the case of recommended Service Bulletins, HBC feels the changes.
modifications, improvements or inspections will benefit the owner/operator and although highly recommended. Recommended Service Bulletins are not considered mandatory at the time of issuance In the case of Optional Service Builetins, complance with the changes modifications improvements or inspections is at the owner/operator's discretion Both classes are available on the web at htto //pubs hawkerbeechcraft com and mailed to Owners of record on the FAA Aircraft Registration Branch List and the H8O Safety of Flight Inforation (SOFI) List
(b) Those having a publications supscription the Hawker Beechcraft Corporation Technical Manual Distrbution Center (TMDC) Information on Safely of Flight Information SOFI) or subsorbonen Center TO C An Mandatory Service Bulletins and Service Bulletins are issued, the Service Bulletin Master Index will be updated and available online at http i/pubs nawkerbeechcraft com will be allowed only when specially cefined in the Service Bulletin and in accordance with HBC Warranty Policy Unless otherwise designated, HBC Mandatory Service Builetins, Service Bulletins and HBC Kits are approved for installation on HBC airplanes in onginal or HBC modified configurations enly. HBC Mandatory Service Bulletins Service Bulletins and Kits may not be compatible with airplanes modified by STC installations or modifications other than HBC approved kits Member of GAMA Issued: February, 2013 SB 57-4112 1 of 13
Hawker Beechcraft
MANDATORY
SERVICE BULLETIN D. Compliance An Airworthiness Directive will be requested on the matter covered by this Service Bulletin.
Hawker Beechcraft 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 SB 57-4112 2 of 13
Hawker Beechcraft
MANDATORY
SERVICE BULLETIN K. Publications Affected None.
L. Interchangeability of Parts Not applicable.
M. Warranty Credit 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.D, 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. Material Information 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-mail: HBC_Parts@hawkerbeechcraft.com Issued: February, 2013 SB 57-4112 3 of 13
Hawker Beechcraft
MANDATORY
SERVICE BULLETIN 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 O-Ring (Preformed Packing) 2 AGS 1186-3 Seal 8 100-230-8815 O-Ring (Preformed Packing) 4 100-226-8815 O-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 / 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
Hawker Beechcraft
MANDATORY
SERVICE BULLETIN F. Tooling - Price and Availability Not applicable.
3. Accomplishment Instructions This Service Bulletin shall be accomplished as follows:
NOTE Should any difficulty be encountered in accomplishing this Service Bulletin, contact Hawker Beechcraft Corporation at 1-800-429-5372 or 316-676-3140.
WARNING 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.
A. Airplane
(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 25-8WS903-11-2, as follows:
(a) Remove 27 bolts, P/N 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, P/N 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
Hawker Beechcraft
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 required. Proceed to Final Check.
(b) If sealant does not exist, proceed to Part B.
Part B: Application of Sealant in the Left and Right Fuel Vent Surge Tanks
(1) Determine if duct, P/N 25-8PV219-1A, and intake assembly, P/N 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, P/N 25-8PV223-1A/2A, can be removed with the associated parts in place, proceed to Step (2).
(b) If the duct assembly, P/N 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, P/N 25-8PV217-1A/2A. Remove duct, P/N 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, P/N 3515000-106, that is attached to rib 15.
(b) Outboard of rib 15, disconnect wiring that corresponds to overfill float switch, P/N 3515000-106, and high-level float switch, P/N 3515000-107. The high-level float switch is attached to rib 14.
Remove the overfill float switch, P/N 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, P/N 3515000-107, to conduit assembly, P/N 25-8PV201-15A/16A. A bond jumper connects conduit assembly, P/N 25-8PV223-1A/2A.
Disconnect the bond jumper at both ends. Retain the bond jumper.
(d) Remove conduit assembly, P/N 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, P/N 25-8PV223-1A/2A.
(f) Remove duct assembly, P/N 25-8PV223-1A/2A.
(g) Protect any open holes from sealant that will be added in the following steps.
WARNING 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
Hawker Beechcraft
MANDATORY
SERVICE BULLETIN
(3) Three doubler plates require sealant protection on the fuel surge tank upper skin:
Doubler plate, P/N 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 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 tree times, and cure times.
Issued: February, 2013 SB 57-4112 7 of 13
Hawker Beechcraft
MANDATORY
SERVICE BULLETIN For every 10° above 77° Fahrenheit, the sealant application time is reduced by half, and for every 10° below 77° Fahrenheit, the application time is doubled.
Sealant can be exposed to fuel after 48 hours.
(a) Apply sealant, P/N PR-1440, to all fasteners that are installed on upper skin doubler plates, P/N 25-8WS6047, P/N 25-8WS6049, and P/N 25-8WS6057. In addition, apply the same sealant to the lower skin doubler plate, P/N 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 P/N 100-230-8815, to install duct, P/N 25-8PV219-1A, and intake assembly, P/N 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, P/N 100-214-8815. Use applicable guidance in AMM, Chapter 28-44-43-401.
(c) Outboard of rib 15, reconnect wiring for overfill float switch, P/N 3515000-106, and high-level float switch, P/N 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.
(10) 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 8 of 13
Hawker Beechcraft
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
Hawker Beechcraft
MANDATORY
SERVICE BULLETIN RIB 14 DETAIL A RIB 15
IF NECESSARY,
REMOVE INTAKE ASSEMBLY, P/N 25-8PV217-1A NOTE A - P/N 25-8PV217-2A RIB 14
IF NECESSARY, REMOVE VENT DUCT, P/N 25-8PV219-1A.
- NOTE B RIB 15 REMOVE DUCT ASSEMBLY, P/N 25-8PV223-1A/-2A.
LOCATION FOR HIGH-LEVEL FLOAT SWITCH, P/N 3515000-107 AND CONDUIT ASSEMBLY, P/N 25-8PV201-15A/-16A.
REMOVE OVER-FILL
FLOAT SWITCH, DETAIL B P/N 3515000-106.
NOTES:
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 FITTING EXTENDING OUT FROM THE FITTING IN THE RIB, FOR INSTALLATION PURPOSES IN PART B, STEP (6).
B411203.AI Duct Configuration for Fuel Vent Surge Tank Figure 1 Issued: February, 2013 SB 57-4112 10 of 13
Hawker Beechcraft
MANDATORY
SERVICE BULLETIN
DETAIL A ESTABLISH A MINIMUM OF
VIEW LOOKING UP
0.12 INCH SEALANT COVER APPLY SEALANT TO RIB 15 ON EACH RIVET. (TYPICAL)
THE DOUBLER
PLATE EDGE, ALL
THE WAY AROUND RIB 14
PLATE P/N 25-8WS6047 a7 277 PLATE P/N etr 25-8WS6049 1 27 Vete + era
PLATE P/N 25-8WS6057
TOP SKIN SHOWN
VIEW LOOKING UP DETAIL BE B411202 AI Sealant Coverage for Upper Skin Figure 2 Issued: February, 2013 SB 57-4112 11 of 13
Hawker Beechcraft
MANDATORY
SERVICE BULLETIN REMOVE ACCESS PANEL.
P/N 25-3WS903-1/2.
RETAIN ATTACHMENT HARDWARE.
REMOVE ACCESS PANEL, P/N 25-8WS905-1A.
RETAIN ATTACHMENT HARDWARE. RIB 15 RIB 14
ESTABLISH A MINIMUM OF
0.12 INCH SEALANT COVER ON EACH RIVET. (TYPICAL)
PLATE P/N -25-8WS6061
APPLY SEALANT TO
VIEW LOOKING DOWN BOTTOM SKIN SHOWN THE DOUBLER
DETAIL A E THE WAY AROUND PLATE EDGE, ALL B411201 AI Sealant Coverage for Lower Skin Figure 3 Issued: February, 2013 SB 57-4112 12 of 13