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Conquest SER VICE LETTER MANDA T OR Y CQL - 57 - 01 TITLE WINGS - FOR W ARD LOWER SP AR CAP
INSPECTION
EFFECTIVITY This service letter applies to the models and serials that have 1 1 , 000 or more flight hours as follows MODEL SERIAL
NUMBERS 425 425 - 0001 thru 425 - 0236 REASON Cracks have been found in the forward lower carry through spar cap.
An undetected crack can cause the spar cap to break which could result in flight instability and potential loss of control.
DESCRIPTION This service document provides instructions to complete an initial and recurring detailed visual inspection of the forward spar , lower carry through spar cap.
The detailed visual inspection is of the bottom surface of the carry through spar cap in the area around the fasteners located just inboard , of the left and right , forward lower wing fitting.
A surface eddy current inspection will be necessary if a crack is suspected.
W ARNING:
Further flight with a cracked carry through spar cap is prohibited.
The carry through spar cap must be replaced before further flight.
NOTE:
In order to reduce possible damage to the structure , it is recommended that the access panels be installed with CQB - 57 - 01 or SK425 -
49.
COMPLIANCE MANDA T OR Y .
This service document must be accomplished as follows:
Model W ith Flight Hours Of Flight Hours T o Comply W ith Initial Inspection Flight Hours For Recurring Inspection Interval 425 25 , 000 or more 25 Flight Hours 50 Flight Hours 425 1 1 , 000 thru 24 , 999 50 Flight Hours 50 Flight Hours NOTE:
Airplanes that have less than the minimum required number of flight hours upon receipt of this service letter must comply with this inspection within 50 flight hours of reaching the minimum flight hours listed in the above table.
A service document published by T extron A viation may be recorded as completed in an aircraft log only when the following requirements are satisfied:
1) The mechanic must complete all of the instructions in the service document , including the intent therein.
2) The mechanic must correctly use and install all applicable parts supplied with the service document kit.
Only with written authorization from T extron A viation can substitute parts or rebuilt parts be used to replace new parts.
3) The mechanic or airplane owner must use the technical data in the service document only as approved and published.
CQL - 57 - 01 December 18 , 2017 Page 1 of 8 T extron A viation Customer Service , P .O.
Box 7706 , Wichita , KS 67277 , U.S.A.
1 - 316 - 517 - 5800 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 © 2017
CQL - 57 - 01 Page 2 December 18 , 2017 Conquest SER VICE LETTER MANDA T OR Y CQL - 57 - 01
4) The mechanic or airplane owner must apply the information in the service document only to aircraft serial numbers identified in the Effectivity section of the document.
5) The mechanic or airplane owner must use maintenance practices that are identified as acceptable standard practices in the aviation industry and governmental regulations.
No individual or corporate organization other than T extron A viation is authorized to make or apply any changes to a T extron A viation - issued service document or flight manual supplement without prior written consent from T extron A viation.
T extron A viation is not responsible for the quality of maintenance performed to comply with this document , unless the maintenance is accomplished at a T extron A viation - owned Service Center .
CONSUMABLE MA TERIAL Y ou must use the consumable materials that follow , or their equivalent , to complete this service document.
NAME NUMBER MANUF
ACTURER USE Rivet MS20426AD4 Commercially A vailable For skin panel installation , various lengths determined at time of installation.
Rivet MS20470AD4 Commercially A vailable For skin panel installation , various lengths determined at time of installation.
T OOLING NAME NUMBER MANUF
ACTURER USE 10X Magnifying Lens Commercially A vailable For detailed visual inspection of forward spar cap
REFERENCES Cessna Model 425 Maintenance Manual NOTE:
T o make sure all publications used are complete and current , refer to www .txtavsupport.com.
PUBLICA TIONS
AFFECTED None
ACCOMPLISHMENT
INSTRUCTIONS
1.
Prepare the airplane for maintenance.
A.
Make sure that the airplane is electrically grounded.
B.
Make sure that all switches are in the OFF / NORM position.
C.
Disconnect electrical power from the airplane.
(1) Disconnect the airplane battery .
(2) Disconnect external electrical power .
D.
Attach maintenance warning tags to the battery and external power receptacle that have "DO NOT
CONNECT
ELECTRICAL POWER -
MAINTENANCE IN PROGRESS" written on them.
Conquest SER VICE LETTER MANDA T OR Y CQL - 57 - 01
2.
Remove access panels as follows:
NOTE:
Forward spar access panels were installed with service bulletin CQB - 57 - 01 - Access Panel Installation For Forward Spar or service kit SK425 - 49 - Access Panel Installation and Stub Wing Fitting Removal / Installation.
These panels are directly below the forward spar wing fitting.
• Access panels 51 1AB , 51 1BB , 51 1A T , 51 1CT , 61 1AB , 61 1BB , 61 1BT , and 61 1CT .
(Refer to the Model 425 Maintenance Manual.)
A.
(Airplanes with forward spar access panels.
Refer to Figure 1 , Detail A.)
Remove the 5292031 - 10 Forward Spar Access Panel if installed with CQB - 57 - 01 or SK425 -
49.
NOTE:
Forward spar access panels were installed with service bulletin CQB - 57 - 01 - Access Panel Installation For Forward Spar or service kit SK425 - 49 - Access Panel Installation and Stub Wing Fitting Removal / Installation.
These panels are directly below the forward spar wing fitting.
B.
(Airplanes without the forward spar access panels.
Refer to Figure 1 , Detail B.)
Remove rivets as necessary from the left and right lower stub wing skin suf ficient to get access to the bottom surface of the lower carry through spar cap for the visual inspection.
CAUTION:
Use caution when removing fasteners along the two lateral rows of rivets just forward and aft of the fitting.
These two rows are common to the lower carry through spar web flanges.
CAUTION:
T o prevent cracking dimples or damaging understructure , when removing rivets from dimpled holes , drill a hole into the rivet shank before driving it out.
(1) Remove all rivet butts , drill shavings , and foreign object debris.
3.
Clean the lower surface of the left and right carry through spar cap as follows:
A.
Use a suitable solvent to remove all grease and dirt from the lower spar cap area.
B.
W ash the remaining solvent of f with soap and water and let air dry .
4.
(Refer to Figure 1 , Detail C.)
Do a detailed visual inspection of the left and right side of the carry through spar cap as follows:
NOTE:
A detailed inspection is described as an intensive visual examination of a specific structural area , system , installation or assembly to detect damage , failure , or irregularity .
A vailable lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate by the inspector .
Inspection aids such as mirrors , magnifying lenses , etc.
may be used.
Surface cleaning and elaborate access procedures may be required.
A.
Use a suitable light source and a 10X Magnifying Lens to inspect the bottom surface of the left and right side of the carry through spar cap inboard of the lower fittings in the area extending 1 - inch inboard to 1 - inch outboard of the two rows of Hi - Lok fasteners and around all 10 fasteners.
W ARNING:
Further flight with a cracked carry through spar cap is prohibited.
The carry through spar cap must be replaced before further flight.
B.
If a crack is found , no further flight is permitted.
Contact Cessna Structures at:
csstructures@txtav .com , or phone:
316 - 517 - 6061.
C.
If an area is questionable , do a surface eddy current examination , go to Step
5.
D.
If no cracks or questionable areas are found , go to Step
6.
5.
Do a surface eddy current examination of the suspect area on the carry through spar cap.
(For surface eddy current inspection instructions , refer to the Model 425 Maintenance Manual , Supplement Inspection Number 57 - 10 - 14 - Lower Carry - Thru Front Spar Cap.)
NOTE:
The eddy current technician must be qualified and certified to Level 2 or 3 per the requirements of NAS 410 or equivalent.
A.
If a crack is found , contact Cessna Structures at:
csstructures@txtav .com , or phone:
316 - 517 - 6061.
CQL - 57 - 01 December 18 , 2017 Page 3
CQL - 57 - 01 Page 4 December 18 , 2017 Conquest SER VICE LETTER MANDA T OR Y CQL - 57 - 01
6.
Complete the attached
INSPECTION RESUL TS FORM and return to Cessna Structures at csstructures@txtav .com.
(Refer to the attached
INSPECTION RESUL TS FORM.)
NOTE:
Return the
INSPECTION RESUL TS FORM to Cessna Structures even if no cracking is found.
7.
(Airplanes without forward spar access panels.)
Install MS20426AD4 - X and MS20470AD4 - X Rivets to secure the stub wing skin.
NOTE:
Rivet length can vary , determine correct length at time of install.
8.
Install all removed access panels.
9.
Remove the maintenance warning tags and connect the airplane battery .
10.
Make a logbook entry that states the recurring inspection is due at the specified flight hour interval as listed in the
COMPLIANCE section of this service letter .
NOTE:
An example of a log book entry on an airplane that currently has 18 , 500 flight hours , the next inspection is due at 18 , 550 flight hours.
CQL - 57 - 01 Forward Lower Spar Cap Inspection must be accomplished at or before 18 , 550 flight hours.
1.
Make an entry in the airplane logbook that states compliance and method of compliance with this service document.
Beechcraft Hawker Conquest SERVICE LETTER Cessna TEXTRON ÀVIATION MANDATORY CQL-57-01 B21706 BL
55.05 (Reference) 0811350 Fitting (Reference) Area to Inspect C 5911011 Skin Assembly 0(+0 Forward Spar (Reference) Access Panel (Reference, It Installed)
DETAIL A View Looking Up
• OUTBD FWD Airplanes with Forward Spar Access Panel A5991T001 Figure 1. Carry Through Spar Cap Inspection (Sheet 1) CQL-57-01 December 18, 2017 Page 5
Beechcraft Hawker Conquest SERVICE LETTER Cessna
TEXTRON AVIATION MANDATORY CQL-57-01 B21710 MS20470AD4 Rivets (Reference) FWD MS20426AD4 OUTBD Rivets (Reference)
DETAIL B Airplanes Without Forward Spar Access Panel NOTE: For airplanes that do not have access panel installed.
The rivet length determined at time of installation.
Figure 1. Carry Through Spar Cap Inspection (Sheet 2) CQL-57-01 Page 6 December 18, 2017
Beechcraft Hawker Conquest SERVICE LETTER Cessna TEXTRON ÀVIATION MANDATORY CQL-57-01 B21711 Area to Inspect FWD
• OUTBD
DETAIL C Figure 1. Carry Through Spar Cap Inspection (Sheet 3) CQL-57-01 December 18, 2017 Page 7
CQL - 57 - 01 Page 8 December 18 , 2017 Conquest SER VICE LETTER MANDA T OR Y CQL - 57 - 01 MA TERIAL
INFORMA TION No parts are required to complete this service document.
Conquest A TT
ACHMENT MANDA T OR Y CQL - 57 - 01 SP AR CAP
INSPECTION RESUL TS FORM Airplane Model Number Airplane Serial Number T otal Airframe Hours Left Engine Hours Forward Lower Spar Cap Hours Right Engine Hours Owner's Name Inspection Facility Name Owner's address Inspection Facility Address List all STC installed on the airplane In the table that follows please provide detailed and dimensioned descriptions of any crack(s).
Attach pictures to this form as necessary .
Conquest A TT
ACHMENT MANDA T OR Y CQL - 57 - 01 SP AR CAP
INSPECTION RESUL TS FORM
CONTINUED W as a crack found:
Y es / No?
Detailed description:
(Attach pictures and additional details as necessary , if a crack was found with visual inspection or eddy current inspection?)
Send completed form / attachments to Cessna Structures at csstructures@txtav .com
Conquest OWNER
ADVISOR Y CQL - 57 - 01 TITLE WINGS - FOR W ARD LOWER SP AR CAP
INSPECTION T O:
Cessna Model 425 Aircraft Owner REASON Cracks have been found in the forward lower carry through spar cap.
An undetected crack can cause the spar cap to break which could result in flight instability and potential loss of control.
COMPLIANCE MANDA T OR Y .
This service document must be accomplished as follows:
Model W ith Flight Hours Of Flight Hours T o Comply W ith Initial Inspection Flight Hours For Recurring Inspection Interval 425 25 , 000 or more 25 Flight Hours 50 Flight Hours 425 1 1 , 000 thru 24 , 999 50 Flight Hours 50 Flight Hours NOTE:
Airplanes that have less than the minimum required number of flight hours upon receipt of this service letter must comply with this inspection within 50 flight hours of reaching the minimum flight hours listed in the above table.
MA TERIAL A V
AILABILITY No parts are required to complete this service document.
W
ARRANTY None 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 Access link at www .txtavsupport.com to register .
CQL - 57 - 01 December 18 , 2017 Page 1 of 1 T extron A viation Customer Service , P .O.
Box 7706 , Wichita , KS 67277 , U.S.A.
1 - 316 - 517 - 5800 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 © 2017
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