FAA SPECIAL AIRWORTHINESS
Aviation Safety INFORMATION BULLETIN
SAIB: CE-17-16
SUBJ: Main Landing Gear – Actuator Inspection Date: June 9, 2017
This is information only. Recommendations aren’t mandatory.
Introduction
This Special Airworthiness Information Bulletin alerts owners, operators, maintenance technicians,
and inspectors of an airworthiness concern on Textron Aviation Inc. (Cessna Aircraft Company)
Models 172RG, R182, TR182, FR182, and all variants of 210/T210/P210-series airplanes with
the exception of the Models 210 and 210A airplanes. The intent is to emphasize the importance of
the inspection of main landing gear actuator assemblies following Textron Aviation Inc.
supplemental inspection documents (SIDs) applicable to each model to prevent malfunctions related
to gear extension and retraction.
At this time, the Federal Aviation Administration (FAA) has determined that this airworthiness
concern is not an unsafe condition that would warrant airworthiness directive (AD) action under Title
14 of the Code of Federal Regulations (14 CFR) part 39.
Background
The FAA recently investigated an accident involving a Model 172RG airplane that had performed a
gear up landing when the pilot was unsuccessful in getting the left main gear down and locked.
During review of the landing gear system, investigators found the left main gear actuator (part
number 9882015-2) housing cracked across the forward attach bolt hole. The crack allowed the
actuator bore to open enough such that the piston would not engage the landing gear pivot sector
sufficiently to move the gear. This failure will result in the affected side not being able to fully retract
or extend through normal method or prevent use of the emergency hand pump.
The main landing gear was subject to FAA AD 2001-06-06 and required inspection for cracks in the
gear pivot assemblies. However, the area of concern identified through this SAIB addresses the
actuator assembly that mates with the main gear pivot. The FAA has published maintenance alerts
(Advisory Circular 43-16) in prior years highlighting this issue and Textron Aviation published
SEB01-2 in 2001 and later revised in 2007 to address the need for initial and repetitive inspections of
the actuators. Textron later published inspection techniques and times within their SIDs.
The FAA has found through our review that most service difficulty reports (SDRs), incidents, or
accidents occur on the Model 172RG airplane. We believe this is primarily due to its heavy use in a
training environment. Our review of over 100 SDRs identifying cracks in the actuator reflect
mechanics and inspectors finding the majority of these during scheduled inspections (100
hour/annual) and often referencing Cessna bulletin SEB01-2.
Figures 1 and 2 reflect two actuators with the crack location most commonly noted that contributes to
the gear malfunction.
1
CRACK
CRACK
Figure 1 Figure 2
Textron (Cessna) produced several actuator assembly and actuator body part numbers with different
version or dash numbers for use on the affected airplane models.
Actuator assemblies utilize base part number 1298100, 1281000, 1281006, 9882000, and 9882015.
Actuator bodies utilize base part number 1281001 and 1241619.
Recommendations
The FAA recommends performing the inspections detailed in Textron SID 32-10-01 appropriate for
the applicable airplane model. These inspections incorporate a combination of visual, fluorescent
penetrant, and eddy current depending on the airplane model.
Initial inspection of the actuator is recommended at 3,000 hours time-in-service (TIS) or 10 years of
age, whichever occurs first, for all models except the 210/T210 series airplanes produced from 1962
to 1968. Repetitive inspections are recommended every 500 hours (TIS) or 5 years, whichever occurs
first.
Initial inspection of the actuator is recommended at 6,000 hours (TIS) or 10 years of age, whichever
occurs first, for 210/T210 series airplanes produced from 1962 to 1968 with repetitive inspections at
1,000 hours TIS or 3 years, whichever occurs first.
Additionally, an inspection is recommended following any unplanned event such as a hard landing to
ensure cracks have not developed.
Serial number applicability is identified in each SID accompanying this SAIB.
For Further Information Contact
Gary Park, Aerospace Engineer, 1801 Airport Road, Wichita, KS 67209; phone: (316) 946-4116
or Dan Withers, Aerospace Engineer; phone: (316) 946-4137; fax: (316) 946-4107
e-mail:
[email protected];
[email protected]
For Related Service Information Contact
Textron Aviation Customer Service, P.O. Box 7706, Wichita, KS 67277, U.S.A.; phone: (316) 517-
5800; fax: (316) 517-7271.
2
CESSNA AIRCRAFT COMPANY
MODEL 200 SERIES (1966 - 1968)
SERVICE MANUAL
SUPPLEMENTAL INSPECTION NUMBER: 32-10-01
1. TITLE:
Main Landing Gear Retraction System Inspection
2. EFFECTIVITY
T210-0001 thru T210-0392,
21058716 thru 21059061
INSPECTION COMPLIANCE
ALL USAGE: INITIAL 6,000 hours or 10 Years (NOTE)
REPEAT 1,000 hours or 3 Years (NOTE)
NOTE: Refer to Note 1, Section 2A-14-00
3. PURPOSE
To ensure integrity of main landing gear retraction system.
4. INSPECTION INSTRUCTIONS
A. Check airplane records to verify that Service Bulletin SEB01-2 has been accomplished. If not,
complete SEB01-2 with this inspection.
B. Remove seats and carpeting as required to gain access to the plate above the actuator.
C. Inspect the actuator, actuator support assembly, and shaft for cracks and corrosion. Refer to Figure
1.
(1) Clean area before inspecting if grime or debris are present.
D. Inspect the actuator pins, piston rack teeth, and sectors for cracks and wear.
E. Install parts removed for access.
5. ACCESS AND DETECTABLE CRACK SIZE
ACCESS/LOCATION/ZONE DETECTABLE CRACK SIZE
Main Gear Section Not Allowed
6. INSPECTION METHOD
Visual
7. REPAIR/MODIFICATION
A. Replace damaged parts.
8. COMMENTS
D606-2-13 Temporary Revision Number 7 - Aug 1/2011 2A-14-03 Page 1
© Cessna Aircraft Company Jun 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 200 SERIES (1966 - 1968)
SERVICE MANUAL
MAIN LANDING GEAR RETRACTION SYSTEM INSPECTION
Figure 1 (Sheet 1)
D606-2-13 Temporary Revision Number 7 - Aug 1/2011 2A-14-03 Page 2
© Cessna Aircraft Company Jun 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 200 SERIES (1960 - 1965)
SERVICE MANUAL
SUPPLEMENTAL INSPECTION NUMBER: 32-10-01
1. TITLE:
Main Landing Gear Retraction System Inspection
2. EFFECTIVITY
21057001 thru 21058715
INSPECTION COMPLIANCE
ALL USAGE: INITIAL 6,000 hours or 10 Years (NOTE)
REPEAT 1,000 hours or 3 Years (NOTE)
NOTE: Refer to Note 1, Section 2A-14-00
3. PURPOSE
To ensure integrity of main landing gear retraction system.
4. INSPECTION INSTRUCTIONS
A. Check airplane records to verify that Service Bulletin SEB01-2 has been accomplished. If not,
complete SEB01-2 with this inspection.
B. Remove seats and carpeting as required to gain access to the plate above the actuator.
C. Inspect the actuator, actuator support assembly, and shaft for cracks and corrosion. Refer to Figure
1.
(1) Clean area before inspecting if grime or debris are present.
D. Inspect the actuator pins, piston rack teeth, and sectors for cracks and wear.
E. Install parts removed for access.
5. ACCESS AND DETECTABLE CRACK SIZE
ACCESS/LOCATION/ZONE DETECTABLE CRACK SIZE
Main Gear Section Not Allowed
6. INSPECTION METHOD
Visual
7. REPAIR/MODIFICATION
A. Replace damaged parts.
8. COMMENTS
D470-13 Temporary Revision Number 6 - Aug 1/2011 2A-14-03 Page 1
© Cessna Aircraft Company Mar 1/1965
CESSNA AIRCRAFT COMPANY
MODEL 200 SERIES (1960 - 1965)
SERVICE MANUAL
MAIN LANDING GEAR RETRACTION SYSTEM INSPECTION
Figure 1 (Sheet 1)
D470-13 Temporary Revision Number 6 - Aug 1/2011 2A-14-03 Page 2
© Cessna Aircraft Company Mar 1/1965
CESSNA AIRCRAFT COMPANY
MODEL 210 SERIES (1969)
SERVICE MANUAL
SUPPLEMENTAL INSPECTION NUMBER: 32-10-01
1. TITLE:
Main Landing Gear Retraction System Inspection
2. EFFECTIVITY
21059062 thru 21059199
INSPECTION COMPLIANCE
ALL USAGE: INITIAL 3000 hours or 10 Years (NOTE)
REPEAT 500 hours or 5 Years (NOTE)
NOTE: Refer to Note 1, Section 2A-14-00
3. PURPOSE
To ensure integrity of main landing gear retraction system.
4. INSPECTION INSTRUCTIONS
A. Check airplane records to verify that SEB01-2 has been accomplished. If not, complete SEB01-2 with
this inspection.
B. Remove seats and carpeting as required to gain access to the plate above the actuator.
C. Inspect the actuator, actuator support assembly, and shaft for cracks and corrosion. Refer to Figure
1.
(1) Clean area before inspecting if grime or debris are present.
D. Inspect the actuator pins, piston rack teeth, and sectors for cracks and wear.
E. Install parts removed for access.
5. ACCESS AND DETECTABLE CRACK SIZE
ACCESS/LOCATION/ZONE DETECTABLE CRACK SIZE
Main Gear Section Not Allowed
6. INSPECTION METHOD
Visual
7. REPAIR/MODIFICATION
A. Replace damaged parts.
8. COMMENTS
D693-1-13 Temporary Revision Number 8 - Aug 1/2011 2A-14-03 Page 1
© Cessna Aircraft Company Jun 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 210 SERIES (1969)
SERVICE MANUAL
MAIN LANDING GEAR RETRACTION SYSTEM INSPECTION
Figure 1 (Sheet 1)
D693-1-13 Temporary Revision Number 8 - Aug 1/2011 2A-14-03 Page 2
© Cessna Aircraft Company Jun 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 210 SERIES (1970 - 1976)
SERVICE MANUAL
SUPPLEMENTAL INSPECTION NUMBER: 32-10-01
1. TITLE:
Main Landing Gear Retraction System Inspection
2. EFFECTIVITY
668, 21059200 thru 21061573
INSPECTION COMPLIANCE
ALL USAGE: INITIAL 3000 hours or 10 Years (NOTE)
REPEAT 500 hours or 5 Years (NOTE)
NOTE: Refer to Note 1, Section 2A-14-00
3. PURPOSE
To ensure integrity of main landing gear retraction system.
4. INSPECTION INSTRUCTIONS
A. Check airplane records to verify that SEB01-2 has been accomplished. If not, complete SEB01-2 with
this inspection.
B. Remove seats and carpeting as required to gain access to the plate above the actuator.
C. Inspect the actuator, actuator support assembly, and shaft for cracks and corrosion. Refer to Figure
1.
(1) Clean area before inspecting if grime or debris are present.
D. Inspect the actuator pins, piston rack teeth, and sectors for cracks and wear.
E. Install parts removed for access.
5. ACCESS AND DETECTABLE CRACK SIZE
ACCESS/LOCATION/ZONE DETECTABLE CRACK SIZE
Main Gear Section Not Allowed
6. INSPECTION METHOD
Visual
7. REPAIR/MODIFICATION
A. Replace damaged parts.
8. COMMENTS
D2004-5-13 Temporary Revision Number 11 - Aug 1/2011 2A-14-03 Page 1
© Cessna Aircraft Company Jul 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 210 SERIES (1970 - 1976)
SERVICE MANUAL
MAIN LANDING GEAR RETRACTION SYSTEM INSPECTION
Figure 1 (Sheet 1)
D2004-5-13 Temporary Revision Number 11 - Aug 1/2011 2A-14-03 Page 2
© Cessna Aircraft Company Jul 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 210 SERIES (1977 - 1984)
SERVICE MANUAL
SUPPLEMENTAL INSPECTION NUMBER: 32-10-01
1. TITLE:
Main Landing Gear Retraction System Inspection
2. EFFECTIVITY
21061574 thru 21064897
INSPECTION COMPLIANCE
ALL USAGE: INITIAL 3000 hours or 10 Years (NOTE)
REPEAT 500 hours or 5 Years (NOTE)
NOTE: Refer to Note 1, Section 2A-14-00
3. PURPOSE
To ensure integrity of main landing gear retraction system.
4. INSPECTION INSTRUCTIONS
A. Check airplane records to verify that SEB01-2 has been accomplished. If not, complete SEB01-2 with
this inspection.
B. Remove seats and carpeting as required to gain access to the plate above the actuator. Refer to the
applicable Model 210 Service Manual.
C. Inspect the actuator, actuator support assembly, and shaft for cracks and corrosion. Refer to Figure
1.
(1) Clean area before inspecting if grime or debris are present.
D. Inspect the actuator pins, piston rack teeth, and sectors for cracks and wear.
E. Install parts removed for access.
5. ACCESS AND DETECTABLE CRACK SIZE
ACCESS/LOCATION/ZONE DETECTABLE CRACK SIZE
Main Gear Section Not Allowed
6. INSPECTION METHOD
Visual
7. REPAIR/MODIFICATION
A. Replace damaged parts.
8. COMMENTS
D2057-3-13 Temporary Revision Number 10 - Aug 1/2011 2A-14-03 Page 1
© Cessna Aircraft Company Mar 1/1996
CESSNA AIRCRAFT COMPANY
MODEL 210 SERIES (1977 - 1984)
SERVICE MANUAL
MAIN LANDING GEAR RETRACTION SYSTEM INSPECTION
Figure 1 (Sheet 1)
D2057-3-13 Temporary Revision Number 10 - Aug 1/2011 2A-14-03 Page 2
© Cessna Aircraft Company Mar 1/1996
CESSNA AIRCRAFT COMPANY
MODEL 210 SERIES (1985 - 1986)
SERVICE MANUAL
SUPPLEMENTAL INSPECTION NUMBER: 32-10-01
1. TITLE:
Main Landing Gear Retraction System Inspection
2. EFFECTIVITY
21064898 thru 21065009
INSPECTION COMPLIANCE
ALL USAGE: INITIAL 3,000 hours or 10 Years (NOTE)
REPEAT 500 hours or 5 Years (NOTE)
NOTE: Refer to Note 1, Section 2A-14-00
3. PURPOSE
To ensure integrity of main landing gear retraction system.
4. INSPECTION INSTRUCTIONS
A. Check airplane records to verify that SEB01-2 has been accomplished. If not, complete SEB01-2 with
this inspection.
B. Remove seats and carpeting as required to gain access to the plate above the actuator. Refer to the
applicable Model 210 Service Manual.
C. Inspect the actuator, actuator support assembly, and shaft for cracks and corrosion. Refer to Figure
1.
(1) Clean area before inspecting if grime or debris are present.
D. Inspect the actuator pins, piston rack teeth, and sectors for cracks and wear.
E. Install parts removed for access.
5. ACCESS AND DETECTABLE CRACK SIZE
ACCESS/LOCATION/ZONE DETECTABLE CRACK SIZE
Main Gear Section Not Allowed
6. INSPECTION METHOD
Visual
7. REPAIR/MODIFICATION
A. Replace damaged parts.
8. COMMENTS
D2073-2-13 Temporary Revision Number 8 - Aug 1/2011 2A-14-03 Page 1
© Cessna Aircraft Company Jun 3/1996
CESSNA AIRCRAFT COMPANY
MODEL 210 SERIES (1985 - 1986)
SERVICE MANUAL
MAIN LANDING GEAR RETRACTION SYSTEM INSPECTION
Figure 1 (Sheet 1)
D2073-2-13 Temporary Revision Number 8 - Aug 1/2011 2A-14-03 Page 2
© Cessna Aircraft Company Jun 3/1996
CESSNA AIRCRAFT COMPANY
MODEL P210 SERIES (1978 - 1983)
SERVICE MANUAL
SUPPLEMENTAL INSPECTION NUMBER: 32-10-01
1. TITLE:
Main Landing Gear Retraction System Inspection
2. EFFECTIVITY
P21000001 thru P21000834
INSPECTION COMPLIANCE
ALL USAGE: INITIAL 3,000 hours or 10 Years (NOTE)
REPEAT 500 hours or 5 Years (NOTE)
NOTE: Refer to Note 1, Section 2A-14-00
3. PURPOSE
To ensure integrity of main landing gear retraction system.
4. INSPECTION INSTRUCTIONS
A. Check airplane records to verify that SEB01-2 has been accomplished. If not, complete SEB01-2 with
this inspection.
B. Remove seats and carpeting as required to gain access to the plate above the actuator.
C. Inspect the actuator, actuator support assembly, and shaft for cracks and corrosion. Refer to Figure
1.
(1) Clean area before inspecting if grime or debris are present.
D. Inspect the actuator pins, piston rack teeth, and sectors for cracks and wear.
E. Install parts removed for access.
5. ACCESS AND DETECTABLE CRACK SIZE
ACCESS/LOCATION/ZONE DETECTABLE CRACK SIZE
Main Gear Section Not Allowed
6. INSPECTION METHOD
Visual
7. REPAIR/MODIFICATION
A. Replace damaged parts.
8. COMMENTS
D2058-2-13 Temporary Revision Number 9 - Aug 1/2011 2A-14-03 Page 1
© Cessna Aircraft Company Jun 3/1996
CESSNA AIRCRAFT COMPANY
MODEL P210 SERIES (1978 - 1983)
SERVICE MANUAL
MAIN LANDING GEAR RETRACTION SYSTEM INSPECTION
Figure 1 (Sheet 1)
D2058-2-13 Temporary Revision Number 9 - Aug 1/2011 2A-14-03 Page 2
© Cessna Aircraft Company Jun 3/1996
CESSNA AIRCRAFT COMPANY
MODEL P210 SERIES (1985 - 1986)
SERVICE MANUAL
SUPPLEMENTAL INSPECTION NUMBER: 32-10-01
1. TITLE:
Main Landing Gear Retraction System Inspection
2. EFFECTIVITY
P21000835 thru P21000874
INSPECTION COMPLIANCE
ALL USAGE: INITIAL 3000 hours or 10 Years (NOTE)
REPEAT 500 hours or 5 Years (NOTE)
NOTE: Refer to Note 1, Section 2A-14-00
3. PURPOSE
To ensure integrity of main landing gear retraction system.
4. INSPECTION INSTRUCTIONS
A. Check airplane records to verify that SEB01-2 has been accomplished. If not, complete SEB01-2 with
this inspection.
B. Remove seats and carpeting as required to gain access to the plate above the actuator.
C. Inspect the actuator, actuator support assembly, and shaft for cracks and corrosion. Refer to Figure
1.
(1) Clean area before inspecting if grime or debris are present.
D. Inspect the actuator pins, piston rack teeth, and sectors for cracks and wear.
E. Install parts removed for access.
5. ACCESS AND DETECTABLE CRACK SIZE
ACCESS/LOCATION/ZONE DETECTABLE CRACK SIZE
Main Gear Section Not Allowed
6. INSPECTION METHOD
Visual
7. REPAIR/MODIFICATION
A. Replace damaged parts.
8. COMMENTS
D2074-2-13 Temporary Revision Number 6 - Aug 1/2011 2A-14-03 Page 1
© Cessna Aircraft Company Aug 1/1996
CESSNA AIRCRAFT COMPANY
MODEL P210 SERIES (1985 - 1986)
SERVICE MANUAL
MAIN LANDING GEAR RETRACTION SYSTEM INSPECTION
Figure 1 (Sheet 1)
D2074-2-13 Temporary Revision Number 6 - Aug 1/2011 2A-14-03 Page 2
© Cessna Aircraft Company Aug 1/1996
CESSNA AIRCRAFT COMPANY
MODEL R182 SERIES
SERVICE MANUAL
SUPPLEMENTAL INSPECTION NUMBER: 32-10-01
1. TITLE:
Main Landing Gear Retraction System Inspection
2. EFFECTIVITY
R18200001 thru R18202032, FR18200001 thru FR18200070.
INSPECTION COMPLIANCE
ALL USAGE: INITIAL 3,000 Hours or 10 Years (NOTE)
REPEAT 500 Hours or 5 Years (NOTE)
NOTE: Refer to Note 1, Section 2A-14-00.
3. PURPOSE
To ensure structural integrity of the main landing gear retraction system.
4. INSPECTION INSTRUCTIONS
A. Check airplane records to verify that the latest revision of SEB90-1 has been accomplished. If not,
complete the latest revision of SEB90-1 with this inspection.
B. Check airplane records to verify that SEB01-2 has been accomplished. If not, complete SEB01-2 with
this inspection.
C. Remove seats and carpeting as required to gain access to the plate above the actuator.
D. Inspect the actuator, the actuator support assembly and the rod end bearings for cracks and corrosion.
(1) Clean area before inspecting if grime or debris is present.
(2) Conduct a surface eddy current inspection for cracks in the location indicated by Figure 1,
Detail E on both sides of the main landing gear actuator body. Refer to Section 2A-13-01,
Nondestructive Inspection Methods and Requirements, Eddy Current Inspection - (Surface
Inspection), for additional instructions.
E. Inspect the actuator pins, gears and sectors for cracks and wear.
F. Refer to Figure 1, Details B, C, and D. Inspect the main landing gear pivot fittings for cracks and
corrosion.
(1) Clean area before inspecting if grime or debris is present.
G. Inspect the downlock support assembly for cracks or corrosion.
(1) Clean area before inspecting if grime or debris is present.
H. Install parts removed for access.
5. ACCESS AND DETECTABLE CRACK SIZE
ACCESS/LOCATION DETECTABLE CRACK SIZE
Main Landing Gear Not Allowed
6. INSPECTION METHOD
Visual and Eddy Current
7. REPAIR/MODIFICATION
A. If cracks are detected, the actuator or actuator body must be replaced.
B. If no cracks are detected, rework in accordance with SEB01-2 Rev. 2 or latest revision.
D2069-3-13 Temporary Revision Number 8 - Dec 1/2011 2A-14-03 Page 1
© Cessna Aircraft Company Mar 1/1996
CESSNA AIRCRAFT COMPANY
MODEL R182 SERIES
SERVICE MANUAL
8. COMMENTS
D2069-3-13 Temporary Revision Number 8 - Dec 1/2011 2A-14-03 Page 2
© Cessna Aircraft Company Mar 1/1996
CESSNA AIRCRAFT COMPANY
MODEL R182 SERIES
SERVICE MANUAL
MAIN LANDING GEAR RETRACTION SYSTEM INSPECTION
Figure 1 (Sheet 1)
D2069-3-13 Temporary Revision Number 8 - Dec 1/2011 2A-14-03 Page 3
© Cessna Aircraft Company Mar 1/1996
CESSNA AIRCRAFT COMPANY
MODEL 172RG
SERVICE MANUAL
SUPPLEMENTAL INSPECTION NUMBER: 32-10-01
1. TITLE:
Main Landing Gear Retraction System Inspection
2. EFFECTIVITY
172RG0001 thru 172RG1191
INSPECTION COMPLIANCE
ALL USAGE: INITIAL 3,000 Hours or 10 Years (NOTE)
REPEAT 500 Hours or 5 Years (NOTE)
NOTE: Refer to Note 1, Section 2A-14-00.
3. PURPOSE
To ensure structural integrity of the main landing gear retraction system.
4. INSPECTION INSTRUCTIONS
A. Check airplane records to verify that Service Kit SK172-151 has been installed. If not, install Service
Kit SK172-151 with this inspection.
B. Check airplane records to verify that SEB01-2 has been accomplished. If not, complete SEB01-2 with
this inspection.
C. Remove seats and carpeting as required to gain access to the plate above the actuator.
D. Inspect the actuator, the actuator support assembly and the rod end bearings for cracks and corrosion.
(1) Clean area before inspecting if grime or debris is present.
(2) Conduct a surface eddy current inspection for cracks in the location indicated by Figure 1,
Detail E on both sides of the main landing gear actuator body. Refer to Section 2A-13-01,
Nondestructive Inspection Methods and Requirements, Eddy Current Inspection - Surface
Inspection, for additional instructions.
E. Inspect the actuator pins, gears and sectors for cracks and wear.
F. Refer to Figure 1, Details B, C, and D. Inspect the main landing gear pivot assemblies for cracks and
corrosion in the areas shown.
(1) Clean area before inspecting if grime or debris is present.
G. Inspect the downlock support assembly for cracks or corrosion.
(1) Clean area before inspecting if grime or debris is present.
H. Install parts removed for access.
5. ACCESS AND DETECTABLE CRACK SIZE
ACCESS/LOCATION DETECTABLE CRACK SIZE
Main Landing Gear Not Allowed
6. INSPECTION METHOD
Visual and Eddy Current
7. REPAIR/MODIFICATION
A. If cracks are detected in the actuator, the actuator or actuator body must be replaced.
B. If no cracks are detected in the actuator, rework in accordance with SEB01-2 Rev. 2 or latest revision.
C. If cracks are detected in the pivot assembly, the pivot assembly must be replaced.
D2066-1-13 Temporary Revision Number 6 - Dec 1/2011 2A-14-03 Page 1
© Cessna Aircraft Company Oct 2/1995
CESSNA AIRCRAFT COMPANY
MODEL 172RG
SERVICE MANUAL
D. If no cracks are detected in the pivot assembly, rework in accordance with SEB90-1 Rev. 3, SK172-
151.
8. COMMENTS
D2066-1-13 Temporary Revision Number 6 - Dec 1/2011 2A-14-03 Page 2
© Cessna Aircraft Company Oct 2/1995
CESSNA AIRCRAFT COMPANY
MODEL 172RG
SERVICE MANUAL
MAIN LANDING GEAR RETRACTION SYSTEM INSPECTION
Figure 1 (Sheet 1)
D2066-1-13 Temporary Revision Number 6 - Dec 1/2011 2A-14-03 Page 3
© Cessna Aircraft Company Oct 2/1995
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Should you have any questions, please contact the Agency by e-mail at
[email protected] or by fax,
No.: +49 221 89990 9515.
Safety Information Section Email:
[email protected]
EASA Website
(Attachment is in Acrobat PDF format)
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