Citation SERVICE BULLETIN - Cessna

Citation SERVICE BULLETINSB560XL-32-30

TITLE

LANDING GEAR - NOSE LANDING GEAR DOOR MECHANISM IMPROVEMENT

EFFECTIVITY

MODEL SERIAL NUMBERS

560XL -5293 thru -5593

The equivalent of this service bulletin has been incorporated on production airplanes -5594 and On.

REASON

To make sure the nose landing gear will extend even though the oleo is partially extended.

DESCRIPTION

This service bulletin provides parts and instructions to replace the nose landing gear door center hingesand associated linkages and adds a guard to the nose landing gear uplock actuator.

COMPLIANCE

RECOMMENDED. This service bulletin should be accomplished at a scheduled maintenance period orphase inspection.

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.

FLIGHT CREW OPERATIONS

No Change.

Feb 15/2006 560XL-32-30Page 1 of 15

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 © 2006

Feb 15/2006 560XL-32-30Page 2


APPROVAL

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

This information shall be considered an amendment to the Cessna Manufacturer's Maintenance Manualand should be completed within the scheduled time period.

MANPOWER

WORK PHASE MAN-HOURS

Modification *

MATERIAL - Cost and Availability

PART NUMBER AVAILABILITY COST

SB560XL-32-30 * *

* 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

Color Chemical FilmTreatment

Alodine 1201 Henkel (Parker Amchem)32100 Stephenson HighwayMadison Heights, MI 48071

To protect the bare aluminum.

Corrosion-ResistantPrimer

513 x 419 PRC - Desoto International5430 San Fernando RoadGlendale, CA 91209

To protect against corrosionand prepare surface for finalfinish.

Loctite Primer T 7471 Henkel Loctite Corporation1001 Trout Brook CrossingRocky Hill, CT 06067-3910

To promote and acceleratethe proper curing of Loctiteanaerobic adhesive oninactive metals.

Loctite AnaerobicAdhesive

271 Henkel Loctite Corporation1001 Trout Brook CrossingRocky Hill, CT 06067-3910

To hold the rocker armassembly bolt in place.

CHANGE IN WEIGHT AND BALANCE

MODEL 560XL

WEIGHT INCREASE -0.75 pounds

RESULTANT MOMENT -51.87 inch-pounds

MOMENT/100 -0.52 inch-pounds

REFERENCES

Cessna Model 560XL (Excel) Maintenance Manual

Cessna Model 560XL (Excel) Structural Repair Manual


PUBLICATIONS AFFECTED

Cessna Model 560XL (Excel) Illustrated Parts Catalog

ACCOMPLISHMENT INSTRUCTIONS

1. Prepare the airplane for maintenance.

A. Make sure that all switches are in the OFF/NORM position.

B. Disconnect electrical power from the airplane.

(1) Disconnect the airplane battery.

(2) Disconnect external electrical power.

C. Attach maintenance warning tags to the battery and external power receptacle that have "DO NOTCONNECT ELECTRICAL POWER - MAINTENANCE IN PROGRESS" written on them.

2. Lift the airplane until the tires are three inches above the floor. (Refer to the Maintenance Manual,Chapter 7, Lifting - Maintenance Practices.)

3. (Refer to Figure 1, View A-A.) Remove and discard the 6642620-4 Rocker Arm Assembly and associatedhardware from the nose wheel well.

4. (Refer to Figure 1, View A-A.) Remove and discard the 6242218-2 Nose Landing Gear Door Pushrodsand associated hardware that is connected to the nose landing gear door center hinges.

5. (Refer to Figure 1, View A-A.) Remove and discard the 6213056-14 or the 6613501-1 Center Hinges andassociated hardware from each nose landing gear door.

NOTE: It is not necessary to remove the L-Brackets that attach the 6213056-14 or the 6613501-1 CenterHinges to the nose landing gear door.

6. (Refer to Figure 1, View C-C.) Install the 6613086-15 Guard.

A. Remove and discard four NAS7034-7042H Huck Bolts from the nose landing gear uplock supportstructure. (Refer to the Structural Repair Manual, Chapter 51, Fastener Installation And Removal -Description And Operation.)

B. Match drill four Number 30 (0.128 inch diameter) holes in the 6613086-15 Guard to align withthe nose landing gear uplock support structure.

C. Ream the drilled holes to a diameter between 0.1625 and 0.1645 inch.

CAUTION: The HL18PB5-5 Hi-Loks must be installed with the head inboard toward the uplockhook. If the Hi-Loks are not installed correctly the HL70-5 Collar may interfere withthe operation of the nose landing gear uplock hook.

D. Install the 6613086-15 Guard with four HL18PB5-5 Hi-Loks and four HL70-5 Collars.

7. Do a modification of the 6614010-21 Stiffener and 6617125-3 Support Angle.

A. (Refer to Figure 2, View A-A.) Remove material from the 6614010-21 Stiffener.

B. (Airplanes -5293 thru -5372.) (Refer to Figure 2, View B-B.) Remove material from the 6617125-3Support Angle.

C. Protect all bare aluminum with color chemical film treatment and corrosion-resistant primer. (Referto the Structural Repair Manual, Chapter 51, Protective Treatment of Metal.)

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8. Install the 6613086-1 Nose Landing Gear Rocker Arm Assembly.

A. (Refer to Figure 1, Detail A.) Install two 6613086-16 Nose Landing Gear Door Pushrods on the6613086-1 Nose Landing Gear Rocker Arm Assembly.

NOTE: Install the 6613086-16 Nose Landing Gear Door Pushrods with the non-adjustable rod endconnected to the 6613086-1 Nose Landing Gear Rocker Arm Assembly.

(1) Make sure that the length of the 6613086-16 Nose Landing Gear Door Pushrods is at least9.04 inches from the center of the bearings.

(2) Install each 6613086-16 Nose Landing Gear Door Pushrod with one NAS6304-13D Bolt, oneNAS1149C0463B Washer, two NAS1515M7L Washers, one NAS1149C0463B Washer, oneMS17826-4 Nut and one MS24665-134 Cotter Pin.

NOTE: The NAS1515M7L Washer will be installed between the non-adjustable rod end andthe 6613086-1 Nose Landing Gear Rocker Arm Assembly.

B. Apply T 7471 Primer and 271 Anaerobic Adhesive to the threads of the NAS6604L10 Bolts.

C. (Refer to Figure 1, View A-A.) Install the 6613086-1 Nose Landing Gear Rocker Arm Assembly withtwo NAS6604L10 Bolts and two NAS1149C0432B Washers.

D. (Refer to Figure 1, View A-A.) Attach each 6642621 Control Rod to the 6613086-1 Nose LandingGear Rocker Arm Assembly with one NAS6305-11D Bolt, one NAS1149C0532B Washer, twoNAS1515M9L Washers, one NAS1149C0532B Washer, one MS17826-5 Nut and one MS24665-136Cotter Pin.

NOTE: The NAS1515M9L Washer will be installed between the rod end and the 6613086-1 NoseLanding Gear Rocker Arm Assembly.

9. Install the hinge assemblies.

A. (Refer to Figure 1, View A-A.) Install the 6613086-5 Hinge Assembly in the airplane with oneAN3-11A Bolt, one NAS1149F0332P Washer and one MS21042L3 Nut.

B. Retract the landing gear.

C. Close the left nose landing gear door.

D. Make sure that the 6613086-5 Hinge Assembly is between the hinge brackets on the nose landinggear door and is in contact with the inner door skin.

E. Identify the hole locations on the 6613086-5 Hinge Assembly for the 0.193 inch diameter holes.

F. Open the left nose landing gear door.

G. Drill two Number 10 (0.193 inch diameter) holes in the 6613086-5 Hinge Assembly.

H. Deburr the drilled holes.

I. (Refer to Figure 1, View A-A.) Install the 6613086-6 Hinge Assembly in the airplane with oneAN3-11A Bolt, one NAS1149F0332P Washer and one MS21042L3 Nut.

J. Close the right nose landing gear door.

K. Make sure that the 6613086-6 Hinge Assembly is between the hinge brackets on the nose landinggear door and is in contact with the inner door skin.

L. Identify the hole locations on the 6613086-6 Hinge Assembly for the 0.193 inch diameter holes.

M. Open the right nose landing gear door.

N. Drill two Number 10 (0.193 inch diameter) holes in the 6613086-6 Hinge Assembly.

O. Deburr the drilled holes.

P. (Refer to Figure 1, View A-A.) Attach the hinge assemblies to the nose landing gear doors with fourAN3-6A Bolts, four NAS1149C0332B Washers and four MS21042L3 Nuts.


Q. Extend the landing gear.

10. (Refer to Figure 1, View B-B.) Connect each of the 6613086-2 Nose Landing Gear Door Pushrodsto the 6613086 Hinge Assemblies with one NAS6304-18D Bolt, two NAS43DD4-4FC Spacers, oneNAS1149C0463B Washer and one MS17826-4 Nut.

NOTE: The MS24665-134 Cotter Pins will be installed after the doors are adjusted.

11. Remove the warning tags and connect external power to the airplane.

12. Connect external hydraulic power cart to the hydraulic system. (Refer to the Maintenance Manual,Chapter 29, Hydraulic System - Maintenance Practices.)

13. Make sure that the nose landing gear doors are properly adjusted.

A. Adjust the external hydraulic power cart flow to less than 0.5 gallons per minute (GPM).

CAUTION: Turn off the external hydraulic power immediately if interference is suspected. Makethe necessary adjustment before the test is started again. Do not allow any of thecomponents to get damaged while the nose landing gear is retracted.

B. Retract the nose landing gear.

C. (Refer to Figure 3.) Measure the distance between the nose landing gear doors and the airplane skin.

(1) If the distance is 0.10 inch to 0.15 inch go to Step 13D.

(2) If the distance is less than 0.10 inch trim the nose landing gear door.

(a) Remove material from the nose landing gear door(s) until there is a 0.10 inch to 0.15 inchgap between the door and the nose skin.

(b) Protect all bare metal with color chemical film treatment and corrosion resistant primer.(Refer to the Structural Repair Manual, Chapter 51, Protective Treatment Of Metal.)

D. Look for interference with the nose landing gear door linkages, rocker arm assembly and noselanding gear doors.

E. Adjust the nose landing gear doors as necessary. (Refer to the Maintenance Manual, Chapter 20,Nose Landing Gear And Doors - Adjustment/Test.)

F. Do Step 13D and 13E as many times as necessary to get the proper fit.

G. Adjust the external hydraulic power cart flow to 6.0 GPM.

H. Extend and retract the landing gear 10 times to make sure that there is no interference.

(1) Extend and retract the landing gear with full input to the left rudder pedal.

(2) Extend and retract the landing gear with full input to the right rudder pedal.

(3) Make sure that the nose gear doors and linkage do not stop the extension or retraction of thenose landing gear.

NOTE: The nose gear tire may lightly contact the forward nose gear door hinge while holdingfull left or right rudder input.

I. Extend the landing gear.

J. Turn off the external hydraulic power cart.

K. (Refer to Figure 1, View B-B.) Install one MS24665-134 Cotter Pin in the NAS6304-18D Bolt thatattaches the 6613086-2 Nose Landing Gear Door Pushrods to the 6613086 Hinge Assemblies.

14. Disconnect external hydraulic power from the hydraulic system. (Refer to the Maintenance Manual,Chapter 29, Hydraulic System - Maintenance Practices.)

15. Remove external power from the airplane.

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16. Protect all bare metal with color chemical film treatment and corrosion-resistant primer. (Refer to theStructural Repair Manual, Chapter 51, Protective Treatment Of Metal.)

17. Paint the affected areas as necessary. (Refer to the Maintenance Manual, Chapter 20, Exterior Finish -Cleaning/Painting.)

18. Lower the airplane and remove the jacks. (Refer to the Maintenance Manual, Chapter 7, Jacking -Maintenance Practices.)

19. 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, PO 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

SB560XL-32-30 1 Kit, consisting of the followingparts:

AN3-11A 2 Bolt Same Discard

AN3-6A 4 Bolt Same Discard

HL18PB5-5 4 Hi-Lok None

HL70-5 4 Collar None

MS17826-4 4 Nut Same Discard

MS17826-5 2 Nut Same Discard

MS24665-134 4 Cotter Pin Same Discard

MS24665-136 2 Cotter Pin Same Discard

NAS1149C0332B 4 Washer Same Discard


NAS1149C0463B 6 Washer NAS1149F0423B Discard


NAS1149F0332P 2 Washer Same Discard

MS21042L3 6 Nut Same Discard

NAS1515M7L 4 Washer NAS1515D7L Discard

NAS1515M9L 4 Washer NAS1515D7L Discard

NAS43DD4-4FC 4 Spacer None

NAS6304-13D 2 Bolt Same Discard

NAS6304-18D 2 Bolt AN4-13 orNAS6704D15

Discard


NEW P/N QUAN-TITY

KEY WORD OLD P/N INSTRUCTIONS/DISPOSITION

NAS6305-11D 2 Bolt Same Discard

NAS6604L10 2 Bolt Same Discard

6613086-1 1 Nose Landing Gear RockerArm Assembly

6642620-1 or6642620-4

Discard

6613086-16 2 Nose Landing Gear DoorPushrod

6242218-2 Discard

6613086-5 1 Hinge Assembly (left) 6213056-14 or6613501-1

Discard

6613086-6 1 Hinge Assembly (right) 6213056-14 or6613501-1

Discard

6613086-15 1 Guard None

SB560XL-32-30 1 Instructions

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Figure 1. Nose Landing Gear Door Improvement (Sheet 1)



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CitationSERVICE BULLETIN

SUPPLEMENTAL DATASB560XL-32-30

TITLE

LANDING GEAR - NOSE LANDING GEAR DOOR MECHANISM IMPROVEMENT

EFFECTIVITY

MODEL SERIAL NUMBERS

560XL -5293 thru -5593

The equivalent of this service bulletin has been incorporated on production airplanes -5594 and On.

MANPOWER

WORK PHASE MAN-HOURS

Modification 13.0

MATERIAL - Cost and Availability

PART NUMBER AVAILABILITY COST

SB560XL-32-30 * *

* 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 E-mail 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.

Feb 15/2006 560XL-32-30Page 1 of 2

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 © 2006

Feb 15/2006 560XL-32-30Page 2

CitationSERVICE BULLETIN

SUPPLEMENTAL DATASB560XL-32-30

WARRANTY CREDIT PROGRAM

This bulletin is recommended. Eligible airplanes may qualify for parts and labor coverage, as describedbelow.

Eligibility: Citations identified within the serial number effectivity of this service bulletin which arewithin the five year warranty period on the original issue date of this bulletin.

Parts Coverage: Authorized Citation Service Facilities, operators, or other maintenance facilities may submita Citation Credit Claim Form for the parts required to accomplish this bulletin.

Labor Coverage: Authorized Citation Service Facilities may submit a Citation Credit Claim Form for the labornecessary to accomplish this service bulletin. Please note Manpower Requirements forcoverage guidelines. If actual labor differs from coverage guidelines, claim actual labor anddetail all discrepancies.

CreditApplication:

All work must be completed and the Citation Credit Claim Form submitted before the dateshown below. Send the Citation Credit Claim, along with any required parts (see MaterialInformation), to the point of purchase.Parts to be returned to Citation Parts Distribution should be forwarded to:

Citation Warranty Administration7121 Southwest BoulevardWichita, KS 67215USA

Expiration: Mar 31/2008

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Citation SERVICE BULLETIN - Cessna