Textron Cessna 404 User manual

Multi-engine SERVICE LETTER MEL-05-01
REVISION TRANSMITTAL
TO: Cessna Distributors, Cessna Service Facilities, and affected Owners of Record
SUBJECT: Cessna Conquest Service Letter MEL-05-01 Revision 1: Notification of Release of Temporary
Revision Number 11 for the Model 404 Service Manual.
REASON
To provide corrected copies of the attached temporary revision.
Miscellaneous changes as required.
Please replace any copy of MEL-05-01 with the attached copy of MEL-05-01 Revision 1, which is printed in
its entirety.
NOTE: You must discard the temporary revision transmitted by MEL-05-01 and replace it with the temporary
revision transmitted by MEL-05-01 Revision 1.
LOG OF REVISIONS
Page No. Date
1 April 25, 2013
Original Issue - February 19, 2013 MEL-05-01
Revision 1 - April 25, 2013 Page1of1
Cessna Aircraft Company, Cessna Customer Service, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-5800, Fax [phone],
Email: [e-mail]
COPYRIGHT © 2013

Multi-engine SERVICE LETTER MEL-05-01
TITLE
TIME LIMITS/MAINTENANCE CHECKS - NOTIFICATION OF RELEASE OF TEMPORARY REVISION
NUMBER 11 FOR THE MODEL 404 SERVICE MANUAL
TO:
Cessna Distributors, Cessna Service Facilities, and affected Owners of Record
EFFECTIVITY
All Cessna Model 404 airplanes
DESCRIPTION
This service letter provides notification that Temporary Revision Number 11 (D2517-16TR11) dated
February 15, 2013 has been reissued for the Model 404 Service Manual.
The temporary revision revises the two sections of the Model 404 Service Manual that follow:
• Supplemental Inspection Document (SID) Section III 32-10-07, Main Landing Gear Trailing Link
• Section 4-10, Main Landing Gear.
COMPLIANCE
INFORMATIONAL. This service letter is for informational purposes only.
PUBLICATIONS AFFECTED
Model 404 Service Manual
Original Issue - February 19, 2013 MEL-05-01
Revision 1 - April 25, 2013 Page1of1
Cessna Aircraft Company, Cessna Customer Service, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-5800, Fax [phone],
Email: [e-mail]
This document contains technical data and is subject to U.S. export regulations. This information has been exported from the United States
in accordance with export administration regulations. Diversion contrary to U.S. law is prohibited. ECCN: 9E991
COPYRIGHT © 2013

TEMPORARY REVISION NUMBER 11
DATED 15 FEBRUARY 2013
MANUAL TITLE Model 404 Service Manual
MANUAL NUMBER - PAPER COPY D2517-16-13
TEMPORARY REVISION NUMBER D2517-16TR11
MANUAL DATE 1 August 1976 REVISION NUMBER 16 DATE 1 September2006
This Temporary Revision consists of the following pages, which affect and replace existing pages in the paper
copy manual and supersede aerofiche information.
SECTION PAGE
SID Section III - 32-10-07 1Thru6
Section 4-10 3Thru3B
REASON FOR TEMPORARY REVISION
1. Toaddallowabledamageinformationandassembly/disassemblyproceduresinSupplementalInspection
Document Section III 32-10-07, Main Landing Gear Trailing Link.
2. To revise Section 4-10 Main Landing Gear.
FILING INSTRUCTIONS FOR THIS TEMPORARY REVISION
1. For Paper Publications, file this cover sheet behind the publication’s title page to identify inclusion of the
temporary revision in the manual. Insert the new pages in the publication at the appropriate locations
and remove and discard the superseded pages.
2. For CD publications, mark the temporary revision part number on the CD label with permanent red
marker. This will be a visual identifier that the temporary revision must be referenced when the content
of the CD is beingused. Temporary revisions should be collected and maintained in a notebook or binder
near the CD library for quick reference.
EXPORT COMPLIANCE
1. This publication contains technical data and is subject to U.S. export regulations. This information has
been exported from the United States in accordance with export administration regulations. Diversion
contrary to U.S. law is prohibited. ECCN: 9E991
© Cessna Aircraft Company

© Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
MODEL 404
SUPPLEMENTAL INSPECTION DOCUMENT
SUPPLEMENTAL INSPECTION NUMBER: 32-10-07
1. Title Main Landing Gear Trailing Link
2. Effectivity
A. Airplanes 404-0001 thru 404-0859.
3. Inspection Compliance
INITIAL REPEAT
10,000 Landings or 15 Years 2,000 Landings or 4 Years
4. Purpose
A. Detailed inspection of the main landing gear trailing link for cracks due to fatigue, overload, and
corrosion.
5. Inspection Instructions
A. Remove the trailing link. Refer to the Service Manual for removal instructions.
B. Visually inspect the main landing gear trailing link for cracks, overload deformations and corrosion.
C. Magnetic Particle inspect the main landing gear trailing link. Refer to Section IV, Supplemental
Inspection Number 32-10-07, for specific instructions.
D. Reinstall trailing link in accordance with the Service Manual.
Access/Location Detectable Crack Size
Main landing gear trailing link 0.10 Inch (2.54 mm)
6. Disassembly and Assembly Procedures
A. Disassembly Procedures
(1) Remove the trailing link. Refer to Section 4-10, Main Landing Gear for main landing gear trailing
link removal instructions.
CAUTION: Make sure that the trailing link is not damaged when the axle is
removed. Damage to the trailing link can cause more repairs or
replacements.
(2) Remove the bolts and pins that attach axle to the trailing link.
(3) Discard the pins.
(4) Use an arbor press to push the axle out of the trailing link.
B. Assembly Procedures
(1) Coat the interface surfaces of the axle and trailing link with primer.
(2) Make sure to turn the axle to the correct position.
(3) Use an arbor press to push the axle into the trailing link while the primer is wet.
NOTE: Do not apply heat to the trailing link. You can freeze the axle to make the assembly
easier.
(4) Coat the pins with primer.
(5) Install the pins while the primer is wet.
D2517-16-13 Temporary Revision Number 11 - Feb 15/2013 32-10-07 Page 1
Section III © Cessna Aircraft Company Sep 1/2006

CESSNA AIRCRAFT COMPANY
MODEL 404
SUPPLEMENTAL INSPECTION DOCUMENT
7. Inspection Method
A. Visual/Magnetic Particle.
8. Repair/Modification
A. Replace the main landing gear trailing link if a crack is found. Refer to the Service Manual.
B. Allowable damage on Upper Machined Barrel and Lower Machined Barrel. Refer to Figure 2.
(1) The upper piston surface must not have dents, dings or corrosion, in more than five locations.
(2) The dents, dings and corrosion can be blended and refinished if the maximum depth of the
penetration is not more than 0.015 inch. The minimum wall thickness mustbe maintained. Refer
to Figure 2.
(3) The lower piston surface must not have dents, dings or corrosion blended in that area.
(4) The scratches which are not more than three inches in length or 0.015 inch in depth can be
blended out and refinished. The minimum wall thickness after blending must bewith in the limits
asshowninFigure2.
(5) The scratches or other damage that do not penetrate the hard coat anodized surface need only
to be lightly smoothed to remove any rough edges.
(6) The dents, dings or corrosion must be blended out in a ratio of 5:1 length or width to depth.
(7) The scratches which penetrate the hardcoat anodized surface must be blended out in a ratio of
5:1 width to depth.
(8) The surface finish of the blended area must be more than 16 micro inches RMS.
C. Allowable damage on Axle surface. Refer to Figure 3.
(1) The axle surface must not have dents, dings or corrosion, in more than three locations.
(2) The dents, dings and corrosion can be blended and refinished if the maximum depth of the
penetration is not more than 0.010 inch. The minimum wall thickness mustbe maintained. Refer
to Figure 3.
(3) Scratches which do not exceed three inches in length or 0.015 inch in depth may be blended out
and refinished. The minimum wall thickness after blending must be with in the limits as shown.
(4) Do not blend in the locations shown in Figure 3, except as noted.
(5) The dents, dings or corrosion must be blended out in a ratio of 5:1 length or width to depth.
(6) The surface finish of the blended area must be more than 16 micro inches RMS.
D. AllowabledamageforForkandAxleAssembly.RefertoFigure4.
(1) The aft fork surface must not have dents, dings or corrosion, in more than five locations.
(2) The dents, dings and corrosion can be blended and refinished if the maximum depth of the
penetration is not more than 0.010 inch. The minimum wall thickness mustbe maintained. Refer
to Figure 4.
(3) Scratches which do not exceed three inches in length or 0.010 inch in depth may be blended out
and refinished. The minimum wall thickness after blending must be with in the limits as shown.
(4) Do not blend in the locations shown in Figure 4.
(5) The dents, dings or corrosion must be blended out in a ratio of 5:1 length or width to depth.
(6) The surface finish of the blended area must be more than 16 micro inches RMS.
9. Comments
A. None.
D2517-16-13 Temporary Revision Number 11 - Feb 15/2013 32-10-07 Page 2
Section III © Cessna Aircraft Company Sep 1/2006

CESSNA AIRCRAFT COMPANY
MODEL 404
SUPPLEMENTAL INSPECTION DOCUMENT
Main Landing Gear -Trailing Link
Figure 1 (Sheet 1)
D2517-16-13 Temporary Revision Number 11 - Feb 15/2013 32-10-07 Page 3
Section III © Cessna Aircraft Company Sep 1/2006

CESSNA AIRCRAFT COMPANY
MODEL 404
SUPPLEMENTAL INSPECTION DOCUMENT
Main Landing Gear Shock Strut
Figure 2 (Sheet 1)
D2517-16-13 Temporary Revision Number 11 - Feb 15/2013 32-10-07 Page 4
Section III © Cessna Aircraft Company Sep 1/2006

CESSNA AIRCRAFT COMPANY
MODEL 404
SUPPLEMENTAL INSPECTION DOCUMENT
Axle Main Landing Gear
Figure 3 (Sheet 1)
D2517-16-13 Temporary Revision Number 11 - Feb 15/2013 32-10-07 Page 5
Section III © Cessna Aircraft Company Sep 1/2006

CESSNA AIRCRAFT COMPANY
MODEL 404
SUPPLEMENTAL INSPECTION DOCUMENT
Trailing Link Assembly - Main Landing Gear
Figure 4 (Sheet 1)
D2517-16-13 Temporary Revision Number 11 - Feb 15/2013 32-10-07 Page 6
Section III © Cessna Aircraft Company Sep 1/2006

CESSNA AIRCRAFT COMPANY
MODEL 404
MAINTENANCE MANUAL
(3) Remove fork (12) from trunnion (5) by removing roll pin (14) from fork pin (16), and remove
nut (10), washers and fork pin from trunnion. Remove spacer (13) from fork.
(4) Remove roller (17) from fork pin (16) by removing nut and bolt.
NOTE: If it is necessary to remove the axle from the trailing link assembly. Refer to
Supplemental Inspection Document Section III, 32-10-07 for assembly and
disassembly procedures.
(5) Disassemble strut assembly as follows:
(a) Tag and disconnect electrical wires, cut safety wire. Remove filler plug (36) and
packing (35).
(b) Loosen locknut and remove switch (23) from barrel (6).
(c) Remove air valve (33) and packing (34).
(d) Remove retainer ring (30), retainer scrapper, and scrapper ring and pull piston (9)
from barrel (6).
(e) Slide bearing (31) and spacer (32) from piston.
(f) Remove lock ring (25) from piston. Remove orifice plate (26) and isolation piston (27)
from piston.
(g) Remove seals (28 and 29) from isolation piston (27) and piston (9) and discard.
(h) Remove metering pin (24) from barrel (6).
(i) If bearings (22) are to be replaced, press bearings from barrel assembly and piston
assembly using an arbor press.
(j) If bearings (15) and bushings (18) are to be replaced, press bearings and bushings
out of the trunnion by using an arbor press.
(k) If bushings (11) are to be replaced, press bushings from fork (12).
B. Assemble Main Landing Gear.
WARNING: DO NOT APPLY AIR OR NITROGEN CHARGE TO STRUT UNTIL IT IS
PROPERLY SERVICED WITH HYDRAULIC OIL.
(6) Assemble strut assembly.
(a) If bearings (22) were removed from barrel (6) and piston (9), install bearings as
follows:
1) Prime bearing surfaces with Loctite Primer T. When the solvent odor of the
primer is no longer present, apply Loctite Retaining Compound No. 35 to bearing
surfaces and press bearing into place.
NOTE: Lubricate seals and mating parts liberally with clean MIL-H-5606
hydraulic fluid before installation and assembly.
(b) Install seal (28) on isolation piston (27) and insert isolation piston into piston (9) with
shallow cup toward air valve opening.
(c) Install orifice plate (26) in piston (9) and secure with lock ring (25).
(d) Install seal (29) on piston (9).
(e) Install metering pin (24) in barrel. Make sure shoulder of metering pin is fully seated.
NOTE: Air valve and switch must be on the same side and centerline of the strut.
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Jan /82

CESSNA AIRCRAFT COMPANY
MODEL 404
MAINTENANCE MANUAL
(f) Insert piston assembly into barrel. Slide spacer (32) into barrel bearing (31) scraper
ring and retainer scraper over piston. Secure bearing in barrel with retainer ring (30).
Safety wire retainer ring.
(g) Install switch (23) and adjust as follows:
1) With strut fully extended, screw switch in until actuation of switch occurs; then
make two complete revolutions past actuation point.
2) Secure switch in this location by tightening locknut. Safety wire locknut.
(h) Install air valve. Safety wire valve to strut.
(i) Install filler plug (36) and packing (35) and safety wire.
(j) Service strut. Refer to Service Main Gear Strut, Chapter 2.
CAUTION: BEARINGS (15) HAVE A TEFLON LINING. IF LINING SHOWS DAMAGE
OR IS WORN THROUGH REPLACE BEARING.
4-10 D2517-16-13 Temporary Revision Number 11 - Feb 15/2013
Page 3A
Jan /82

CESSNA AIRCRAFT COMPANY
MODEL 404
MAINTENANCE MANUAL

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D2517-16-13 Temporary Revision Number 11 - Feb 15/2013 4-10
Page 3B
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Multi-engine OWNER ADVISORY MEL-05-01
TITLE
TIME LIMITS/MAINTENANCE CHECKS - NOTIFICATION OF RELEASE OF TEMPORARY REVISION
NUMBER 11 FOR THE MODEL 404 SERVICE MANUAL
TO:
Cessna Model 404 Owner
REASON
This owner advisory is to inform you that MEL-05-01 Revision 1 has been issued.
MEL-05-01 Revision 1 provides notification that Temporary Revision Number 11 (D2517-16TR11) dated
February 15, 2013 has been reissued for the Model 404 Service Manual.
The temporary revision revises the two sections of the Model 404 Service Manual that follow:
• Supplemental Inspection Document (SID) Section III 32-10-07, Main Landing Gear Trailing Link
• Section 4-10, Main Landing Gear.
COMPLIANCE
INFORMATIONAL. This service letter is for informational purposes only.
LABOR HOURS
Not applicable
MATERIAL AVAILABILITY
Not applicable
WARRANTY
Not applicable
Please contact a Cessna Service Facility for detailed information.
NOTE: As a convenience, service documents are now available online to all our customers through a
simple, free-of-charge registration process. If you would like to sign up, please visit the "Customer
Support Login" link at www.Cessna.com to register.
MEL-05-01
April 25, 2013 Page1of1
Cessna Aircraft Company, Cessna Customer Service, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-5800, Fax [phone],
Email: [e-mail]
This document contains technical data and is subject to U.S. export regulations. This information has been exported from the United States
in accordance with export administration regulations. Diversion contrary to U.S. law is prohibited. ECCN: 9E991
COPYRIGHT © 2013