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Multi - engine SER VICE LETTER MANDA T OR Y MEL - 57 - 01 TITLE WINGS - FOR W ARD LOWER SP AR CAP
INSPECTION
EFFECTIVITY This service letter applies to the models and serials that have 15 , 000 or more flight hours as follows MODEL SERIAL
NUMBERS 401 401 - 0001 thru 401 - 0322 401A 401A0001 thru 401A0132 401B 401B0001 thru 401B0221 402 402 - 0001 thru 402 - 0322 402A 402A0001 thru 402A0129 402B 402B0001 thru 402B1384 402C 689 , 402C0001 thru 402C1020 41 1 41 1 - 0001 thru 41 1 - 0250 41 1A 41 1 - 0251 thru 41 1 - 0300 414 414 - 0001 thru 414 - 0965 414A 414A0001 thru 414A1212 421 421 - 0001 thru 421 - 0200 421A 421A0001 thru 421A0158 This service letter applies to the models and serials that have 12 , 000 or more flight hours as follows MODEL SERIAL
NUMBERS 421B 421B0001 thru 421B0970 421C 421C0001 thru 421C1807 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 MEB - 57 - 01 , MEB - 57 - 02 , SK402 - 49 or SK421 -
152.
MEL - 57 - 01 December 18 , 2017 Page 1 of 9 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
MEL - 57 - 01 Page 2 December 18 , 2017 Multi - engine SER VICE LETTER MANDA T OR Y MEL - 57 - 01
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 All Airplanes 25 , 000 or more 25 Flight Hours Every 50 Flight Hours 421B , 421C 12 , 000 thru 24 , 999 50 Flight Hours Every 50 Flight Hours 401 , 401A , 401B , 402 , 402A , 402B , 402C , 41 1 , 41 1A , 414 , 414A , 421 , 421A 15 , 000 thru 24 , 999 50 Flight Hours Every 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.
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.
Multi - engine SER VICE LETTER MANDA T OR Y MEL - 57 - 01 T OOLING NAME NUMBER MANUF
ACTURER USE 10X Magnifying Lens Commercially A vailable For detailed visual inspection of forward spar cap
REFERENCES Cessna Model 401 and 402 (1967 - 1978) Service Manual Cessna Model 402C (1979 - 1985) Maintenance Manual Cessna Model 41 1 / 41 1A (1965 - 1968) Service Manual Cessna Model 414 / 414A (1970 - 1985) Service Manual Cessna Model 421 , 421A , 421B Series (1968 - 1975) Service Manual Cessna Model 421C (1976 - 1985) Service 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.
2.
Remove access panels as follows:
NOTE:
Forward spar access panels were installed with service bulletins MEB - 57 - 01 or MEB - 57 - 02 - Access Panel Installation for Forward Spar or service kits SK402 - 49 , and SK421 - 152 - Access Panel Installation and Stub Wing Fitting Removal / Installation.
These panels are directly below the forward spar wing fitting.
• Model 401 and 402 series airplanes remove panels 32 and
94.
(Refer to the Model 401 and 402 (1967 - 1978) Service Manual.)
• Model 402C airplanes remove panels 51 1AB , 51 1A T , 512BT , 61 1AB , 61 1A T and 612BT .
(Refer to the Model 402C (1979 - 1985) Maintenance Manual.)
• Model 41 1 airplanes remove panels 35 and
57.
(Refer to the Model 41 1 / 41 1A (1965 - 1968) Service Manual.)
• Model 414 airplanes remove panels 34 , 35 and
41.
(Refer to the Model 414 / 414A (1970 - 1985) Service Manual.)
• Model 414A airplanes remove panels 51 1AB , 51 1A T , 512A T , 61 1AB , 61 1A T and 612A T .
(Refer to the Model 414 / 414A (1970 - 1985) Service Manual.)
• Model 421 , 421A , and 421B airplanes remove panels 35 , 57 and
93.
(Refer to the Model 421 , 421A , 421B Series (1968 - 1975) Service Manual.)
MEL - 57 - 01 December 18 , 2017 Page 3
MEL - 57 - 01 Page 4 December 18 , 2017 Multi - engine SER VICE LETTER MANDA T OR Y MEL - 57 - 01
• Model 421C airplanes remove panels 51 1AB , 51 1A T , 512A T , 61 1AB , 61 1A T and 612A T .
(Refer to the Model 421C (1976 - 1985) Service Manual.)
A.
(Airplanes with the forward spar access panels.
Refer to Figure 1 , Detail A.)
Remove the 5292032 - 4 or 5292031 - 10 Forward Spar Access Panel if installed with MEB - 57 - 01 , MEB - 57 - 02 or SK425 -
49.
NOTE:
Forward spar access panels were installed with either service bulletins MEB - 57 - 01 or MEB - 57 - 02 - Access Panel Installation for Forward Spar or service kits SK402 - 49 , or SK421 - 152 - 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 side of the 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 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 instructions refer to inspection documents listed below .)
• Model 401 and 402 series airplanes refer to the Model 401 and 402 (1967 - 1978) Service Manual , Supplemental Inspection Number 57 - 10 - 10 - Lower Carry - Thru Main Spar Cap
• Model 402C airplanes refer to the Model 402C (1979 - 1985) Maintenance Manual , Supplemental Inspection Number 57 - 10 - 14 - Wing Lower Carry - Thru Front Spar Cap
• Model 41 1 airplanes refer to the Model 41 1 / 41 1A (1965 - 1968) Service Manual , Supplement Inspection Number 57 - 10 - 10 - Lower Carry - Thru Main Spar Cap
• Model 414 airplanes , refer to the Model 414 / 414A (1970 - 1985) Service Manual , Supplement Inspection Number 57 - 10 - 10 - Lower Carry - Thru Main Spar Cap
• Model 414A airplanes , refer to the Model 414 / 414A (1970 - 1985) Service Manual , Supplement Inspection Number 57 - 10 - 14 - Lower Carry - Thru Front Spar Cap
Multi - engine SER VICE LETTER MANDA T OR Y MEL - 57 - 01
• Model 421 , 421A , 421B airplanes , refer to the Model 421 , 421A , 421B Series (1968 - 1975) Service Manual , Supplement Inspection Number 57 - 10 - 10 - Lower Carry - Thru Main Spar Cap
• Model 421C airplanes , refer to the Model 421C (1976 - 1985) Service 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.
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 crack 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 25 , 500 flight hours , the next inspection is due at 25 , 550 flight hours.
MEL - 57 - 01 Forward Lower Spar Cap Inspection must be accomplished at or before 25 , 550 flight hours.
1.
Make an entry in the airplane logbook that states compliance and method of compliance with this service document.
MEL - 57 - 01 December 18 , 2017 Page 5
Beechcraft Hawker Multi-engine SERVICE LETTER Cessna TEXTRON ÀVIATION MANDATORY MEL-57-01 B21705 Forward Spar Access Panel (Reference, If Installed) Forward _ c Spar Angles LJ (Reference) C FWD
• OUTBD
DETAIL A View Looking Up at Forward Spar Airplanes with Forward Spar Access Panel NOTE: Model 402 shown for illustrative purposes.
Other models the inspection is in similar location.
A5991T001 Figure 1. Carry Through Spar Cap Inspection (Sheet 1) MEL-57-01 Page 6 December 18, 2017
Beechcraft Hawker Multi-engine SERVICE LETTER TEXTRON ÀVIATION Cessna MANDATORY MEL-57-01 B21707 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) MEL-57-01 December 18, 2017 Page 7
Beechcraft Hawker Multi-engine SERVICE LETTER Cessna TEXTRON ÀVIATION MANDATORY MEL-57-01 B21712 Area to Inspect FWD OUTBD
DETAIL C Figure 1. Carry Through Spar Cap Inspection (Sheet 3) MEL-57-01 Page 8 December 18, 2017
Multi - engine SER VICE LETTER MANDA T OR Y MEL - 57 - 01 MA TERIAL
INFORMA TION No parts are required to complete this service document.
MEL - 57 - 01 December 18 , 2017 Page 9
No text on this page: it may be a figure. Open the PDF to see it.
Multi - engine A TT
ACHMENT MANDA T OR Y MEL - 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 .
Multi - engine A TT
ACHMENT MANDA T OR Y MEL - 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 with a surface eddy current inspection?)
Send completed form / attachments to Cessna Structures at csstructures@txtav .com