Revision 13 SB650-03-01

CitationSERVICE BULLETIN

REVISIONRevision 13 SB650-03-01

TRANSMITTAL SHEET

This sheet transmits Revision 13 to SB650-03-01.A. Added a note to Step 6E which gives instructions to restore the check valves to production configuration

if they were reversed.B. Added airplane -7092 to the serial effectivity.

NOTE: This revision replaces the original issue of SB650-03-01 and all previous revisions in their entirety.

NOTE: Change bars and pointing hands are not used in this publication to denote revised material. Thistransmittal sheet provides a complete description of the changes made by this revision, exceptfor editorial changes.

REVISION COMPLIANCE

NO EFFECT. Airplanes previously modified by this service bulletin are not affected by this revision.

SUMMARY OF REVISIONS

Original Issue May 18/1984

Revision 1 Jun 8/1984

Revision 2 Jul 19/1985


Revision 4 Apr 1/1993


Revision 6 Mar 17/1995


Revision 8 May 13/1997

Revision 9 Aug 22/1997


Revision 11 Nov 30/2004





TRANSMITTAL SHEET

This sheet transmits Revision 12 to SB650-03-01.A. Adds airplane -0080 to the EFFECTIVITY section.



REVISION COMPLIANCE


















TRANSMITTAL SHEET

This sheet transmits Revision 11 to SB650-03-01.A. Adds airplane -7067 to the EFFECTIVITY section and Step 4 of the ACCOMPLISHMENT

INSTRUCTIONS.B. Adds Cessna Model 650 Citation VII Wiring Diagram Manual to the REFERENCE section.C. Removes engineering drawings from the MATERIAL INFORMATION section and adds them to the

REFERENCE section.



REVISION COMPLIANCE















Citation SERVICE BULLETINSB650-03-01

TITLE

CERTIFICATION REQUIREMENTS - UNITED STATES TO CANADIAN CONVERSION

EFFECTIVITY

MODEL SERIAL NUMBERS

650 -0007, -0014, -0023, -0042, -0062, -0065, -0087, -0101,-0104, -0116, -0195, -7067, -7092

NOTE: This service bulletin may be accomplished only at a Cessna owned Citation Service Center; or, whenindividually approved through Citation Customer Services, at other Cessna authorized service facilities.

NOTE: This service bulletin is not compatible with SB650-27-48.

REASON

To modify an airplane to meet Canadian certification requirements.

DESCRIPTION

This service bulletin provides parts and instructions to install dual hydraulic unloading relief valves,spoiler asymmetry detection system and oil quantity placards, and to modify the spoiler hold-downelectrical system.

COMPLIANCE

OPTIONAL. This service bulletin may be accomplished at the discretion of the owner.

A service bulletin published by Cessna Aircraft Company may be recorded as “completed” in an aircraftlog only when the following requirements are satisfied:

1) The mechanic must complete all of the instructions in the service bulletin, including the intenttherein.

2) The mechanic must correctly use and install all applicable parts supplied with the service bulletinkit. Only with written authorization from Cessna Aircraft Company can substitute parts or rebuiltparts be used to replace new parts.

3) The mechanic or airplane owner must use the technical data in the service bulletin only asapproved and published.

4) The mechanic or airplane owner must apply the information in the service bulletin only to aircraftserial numbers identified in the “Effectivity” section of the bulletin.

5) The mechanic or airplane owner must use maintenance practices that are identified as acceptablestandard practices in the aviation industry and governmental regulations.

No individual or corporate organization other than Cessna Aircraft Company is authorized to make orapply any changes to a Cessna-issued service bulletin, service letter, or flight manual supplement withoutprior written consent from Cessna Aircraft Company.

Cessna Aircraft Company is not responsible for the quality of maintenance performed to comply with thisdocument, unless the maintenance is accomplished at a Cessna-owned Citation Service Center.

May 18/1984 650-03-01Revision 13 - Jun 27/2006 Page 1 of 6

Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-6000, Fax 1-316-517-8500

COPYRIGHT © 1984

May 18/1984 650-03-01Revision 13 - Jun 27/2006 Page 2


FLIGHT CREW OPERATIONS

No Change.

APPROVAL

FAA approval has been obtained on technical data in this publication that affects airplane type design.

This information is considered an amendment to the Cessna Manufacturer's Maintenance Manual.

MANPOWER

WORK PHASE MAN-HOURS

Modification *

MATERIAL - Cost and Availability

PART NUMBER AVAILABILITY COST

SB650-03-01-0 * *

SB650-03-01-1 * *

* Refer to the attached Service Bulletin Supplemental Data sheet for man-hours, material cost andavailability, and warranty information.

CONSUMABLE MATERIAL

In addition to the above kit(s), the following materials, or equivalent, are required for the accomplishmentof this service bulletin.

NAME NUMBER MANUFACTURER USE

Adhesive Eastman 910 Eastman Kodak Company343 State StreetRochester, NY 14650

Secure position ofpermaswage fittings intube subassemblies.

Solvent Methyl N-Propyl(MEK)

Commercially available Cleaning.

Solvent Isopropyl Alcohol Commercially available Flush out hydraulic linesbefore installing.

TOOLING

NAME NUMBER MANUFACTURER USE

Permaswage hy-draulic power supply

DLT02MAPP1000 Deutsch Metal Components Division14800 S. Figueroa StreetLos Angeles, CA PO Box 61188

Power supply forpermaswage tool kits.

Permaswage tool, kit#1 (3/16 inch through3/8 inch tubing)

DLT30MAP-SKT3011

Deutsch Metal Components Division14800 S. Figueroa StreetLos Angeles, CA PO Box 61188

Swage tubing.


CHANGE IN WEIGHT AND BALANCE

MODEL 650

WEIGHT INCREASE +6.7 pounds

RESULTANT MOMENT +2101.0 inch-pounds

MOMENT/100 +21.0

REFERENCES

Cessna Model 650 Citation III, VI, and VII Maintenance Manual

Cessna Model 650 Citation III Wiring Diagram Manuals

Cessna Model 650 Citation VII Wiring Diagram Manual

The Cessna Engineering Drawings and documents below are necessary to accomplish this modificationfor all airplanes:

NOTE: The latest revision of each document and all applicable amendments, drawing change notices, andparts lists released at the time of modification must be used.

DRAWING NUMBER DRAWING TITLE

6200011 Canadian DOT Modification Kit - Optional

6218124 Spoiler Asymmetry Box Installation

The Cessna Engineering Drawings and documents below are necessary to accomplish this modificationfor all airplanes:

NOTE: The latest revision of each document and all applicable amendments, drawing change notices, andparts lists released at the time of modification must be used.

DRAWING NUMBER DRAWING TITLE

6217110 Plumbing Installation - Hydraulic Aft Fuselage

6217198 Aft Baggage Bulkhead Installation - Hydraulic

PUBLICATIONS AFFECTED

Cessna Model 650 Citation III, VI, and VII Illustrated Parts Catalog

ACCOMPLISHMENT INSTRUCTIONS

1. (Airplanes 650-0001 thru 650-0104) Install dual unloading relief valves as follows:

A. Remove 9914093-1 Relief Valve from the aft baggage bulkhead hydraulic panel. Cap the fittingswith one each MS21914-6 and MS21914-8 Caps.

B. Install two 70076 Unloading Relief Valves per Cessna Engineering Drawing 6217110. (Refer tothe Maintenance Manual, Chapter 20, Tube Bending Criteria and Permaswaging - MaintenancePractices.)

2. Install the spoiler asymmetry detection system as follows:

A. Install 6218002-5 Spoiler Asymmetry Box in the left side console per Cessna Engineering Drawing6218124.




B. (Airplanes 650-0001 thru 650-0065 not incorporating SB650-27-32.) Replace the 623845-104Spoiler Position Transmitters with the 86784-1 Transmitter. (Refer to the Maintenance Manual,Chapter 27, Speedbrake Position/Indicating System - Maintenance Practices.)

NOTE: The new transmitters may already have been installed as a spares replacement. A newbracket is required to install the new transmitter.

C. Wire the spoiler asymmetry detection system per the Wiring Diagram Manual, Chapter 27, SpoilerAsymmetry Detection.)

3. (Airplanes 650-0001 thru 650-0173.) Modify the spoiler hold-down wiring by performing the 6200011-2Auxiliary Power Junction Box Modification. (Refer to the Wiring Diagram Manual Citation Serial -0001Thru -0173, Chapter 27, Spoiler Asymmetry Detection.)

4. (Airplanes 650-0195 and 650-7067) Install K204 Auxiliary Hydraulic Latch/Spoiler Asymmetry Relayin the left power J-Box. (Refer to the Wiring Diagram Manual Citation Serial -0174 Thru -0199 and-7067,Chapter 27, Speed Brake Asymmetry Detection.)

5. Install 6200181-90 Oil Quantity Placard on the inside of each nacelle oil filler door. Position placards sothey can be read when the filler doors are open.

6. Perform a functional test of the unloading relief valves as follows: NOTE: Test the left and right unloadingrelief valves.

NOTE: A high-flow one gallon-per-minute or more) ground service unit, capable of supplying 4000 psi,must be available for this test. If one is not available, a high pressure hand pump may be used inplace of a ground service unit, but the left and right pressure lines from the engine pumps must becapped. Cap the lines by disconnecting them at a check valve on the aft baggage bulkhead andreversing the check valve.

A. Disconnect the engine-driven hydraulic pump pressure hose from the pump.

B. Connect a ground service unit or hand pump to the pressure hose.

C. Turn on the ground service unit or operate the hand pump and apply 3800 psi to the airplane system.

(1) Check for leaks at all unloading relief valve locations.

(2) Verify that the unloading relief valve does not open at 3800 psi.

D. Increase the hydraulic pressure from the ground service unit or hand pump and verify that theunloading relief valve opens at 4000 psi +100 or -100 psi.

NOTE: Pressure will drop to 200-300 psi if a high-flow ground service unit is used. Pressure willdrop to zero if a hand pump is used.

E. Shut off the ground service unit, disconnect from the airplane, and reconnect the pressure hose tothe engine-driven hydraulic pump.

NOTE: If the check valves were reversed, restore them to production configuration.

7. Bleed the hydraulic system and service the hydraulic reservoir. (Refer to the Maintenance Manual,Chapter 12, Servicing, Hydraulic System Reservoir - Servicing.)

8. Perform the Spoiler/Speedbrake System Operational Test, Auxiliary Hydraulic Pump Electrical ControlFunctional Test and Spoiler Asymmetry Hold-Down Functional Test. (Refer to the Maintenance Manual,Chapter 27, Spoiler/Speedbrake - Adjustment/Test.)

9. Ensure that the latest revision of the FAA Approved on Behalf of Transport Canada Airplane Flight Manualis available for use prior to operation of the airplane.

10. Record that this service bulletin has been completed.

A. Complete a Maintenance Transaction Report.

B. Put a copy of the completed Maintenance Transaction Report in the airplane logbook.


C. Send a copy of the completed Maintenance Transaction Report to: CESCOM, P.O. Box 7706,Wichita, KS 67277.

MATERIAL INFORMATION

NOTE: The parts included in this service bulletin cover installation for one airplane.

NEW P/N QUAN-TITY

KEY WORD OLD P/N INSTRUCTIONS/DISPOSITION

SB650-03-01-0 1 Kit, consisting of the followingparts:

M39029/4-110 2 Pin

M39029/5-115 2 Socket

M81044/12-22-9 36 inches Wire (StampedA1K192-A1K204)

M81044/12-22-9 36 inches Wire (StampedX1K192-X1K204)

M81044/12-22-9 36 inches Wire (StampedA2K192-A2K204)

M81044/12-22-9 36 inches Wire (StampedTJT111-X2K204)

M81044/12-22-9 36 inches Wire (StampedLLJT111-X2K204)

M81044/12-22-9 200 inches Wire (StampedAPT36-TPT111)

M81044/12-22-9 36 inches Wire (Stamped2BS143-GJF41)

M81044/12-22-9 36 inches Wire (Stamped3BS143-wJF41)

M81044/12-22-9 36 inches Electrical Wire

M81824/1-2 4 Splice

MS21042-08 4 Nut

MS25036-102 2 Terminal

MS27401-14 1 Relay

MS35206-242 4 Screw

1N4006 1 Diode

451116-141 1 Relay Socket

6200181-90 2 Placard - Oil Quantity Spoiler

6218002-5 1 Spoiler Asymmetry Box

6218124-2 1 Wire Bundle Assembly




NEW P/N QUAN-TITY


6218124-3 1 Wire Bundle Assembly

SB650-03-01 1 Instructions

Airplanes -0001 thru -0104, order the following kit in addition to the SB650-03-01 kit.

NEW P/N QUAN-TITY


SB650-03-01-1 1 Kit, consisting of the followingparts:

AN894D10-8 2 Reducer

AN6289-8 2 Nut

S2909J08 4 Sleeve

S2910-08 4 Nut

S2917D10 2 Tee

MS21902D10 2 Union

MS21909-8 2 Tee

MS21914-6 1 Cap

MS21914-8 1 Cap

MS28773-08 2 Retainer

MS28778-8 4 O-Ring

MS28778-10 2 O-Ring

70076 2 Valve, Unloading Relief

6207023-43 1 Line Assembly, Left

6207023-48 1 Line Assembly, Right

6207023-3 1 Line Assembly

6217198-3 1 Bulkhead Installation


SUPPLEMENTAL DATASB650-03-01

TITLE

CERTIFICATION REQUIREMENTS - UNITED STATES TO CANADIAN CONVERSION

EFFECTIVITY

MODEL SERIAL NUMBERS

650 -0007, -0014, -0023, -0042, -0062, -0065, -0087, -0101,-0104, -0116, -0195, -7067, -7092

MANPOWER

WORK PHASE MAN-HOURS

Modification *

MATERIAL - Cost and Availability

PART NUMBER AVAILABILITY COST

SB650-03-01-0 * *

SB650-03-01-1 * *

* Please contact Citation Parts Distribution for current cost and availability of parts listed in this servicebulletin. Phone at 1-800-835-4000 (Domestic) or 1-316-517-7542 (International). Send Email to:[email protected] or telefax at 1-316-517-7711.

Based on availability and lead times, parts may require advanced scheduling.

In cases where the required part(s) are available as exchange, order the exchange part and, uponcompletion, expedite the return of the removed core to avoid return penalties. Contact the Citation PartsDistribution Sales Desk for availability of exchange parts.

May 18/1984 650-03-01Revision L - Jun 27/2006 Page 1 of 1

Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-6000, Fax 1-316-517-8500

COPYRIGHT © 1984

Revision 13 SB650-03-01

Documents

Transcript of Revision 13 SB650-03-01