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Ref No.: AOT - C212 - 53 - 0001 Rev No.: 1 Rev Date: 30/01/2020
SERVICES DIRECTORATE Pº John Lennon s/n 28906 Getafe, Madrid, SPAIN mta.technicalservice@es.airbus.com
Alert Operators Transmission Page : 1 / 6 ATA Chapter: 53 Subject:
Inspection of Fuselage Skin and FR5 LH/RH near Wing Leading Edge
Aircraft Type: C - 212 Applicability: C - 212 Fleet Referenced Documents:
Ref. [1] SB - 212 - 53 - 0054M Ref. [2] SB - 212 - 53 - 0054C Ref. [3 ] AMM 53 - 50 - 00 Ref. [ 4 ] IPC 53 - 21 - 01 Ref. [ 5 ] NDTM 51 - 60 - 00 NOTE: This AOT is considered by Airbus DS as a Mandatory Action
1. REASON FOR REVISION Issue 01 of the present AOT is edited to update inspection threshold and interval. The following paragraphs have been modified:
- Chapter 2.1 , 2.3, 3.1.1 , 3.2.3, 4.1 and 5
- Figure 3 and 4 updated in Annex 1
2. REASON
2.1 FACTS Some Operators have found cracks on the airframe of C - 212 aircraft.
Cracks were located on the fuselage skin and o n frame FR5 under the skin, near the leading edge of the wing, on both LH and RH side s.
After the publication of the first issue of the AOT, several Operators reported findings earlier than initially expected. For that reason, a new analysis was performed concluding in a revision of the inspection requirements .
2.2 CONSEQUENCES These cracks growth , if undetected, could lead to a n unsafe condition, affecting structural integrity of the airframe.
2.3 AIM The aim of this AOT is to provide instructions to ensure the structural integrity of the affected area by means of an inspection plan until perma nent solution is defined.
Reference No.: AOT - C212 - 53 - 0001 Revision No.: 1 Date: 30/01/2020 Alert Operators Transmission Page : 2 / 6 ATA Chapter: 53 Subject: Inspection of Fuselage Skin and FR5 LH/RH near Wing Leading Edge
2.4 INVESTIGATION An investigation of the damages found was performed to evaluate the impact of the cracks on the aircraft. Due to the analysis result, it was concluded that the inspection defined in this document , the same as the one defined in Service Bulletin Ref. [1] and Ref. [2], must be performed to assure the structural integrity of the airframe until a permanent solution is implemented.
The inspection requested by Service Bulletin Ref. [1] and Ref. [2] is c onsidered superseded by the present AOT.
3. SHORT TERM ACTION
3.1 PLANNING AND MANPOWE R
3.1.1 ACCOMPLISHMENT TIMES CALE Perform the inspection described in Chapter 3.2 following the threshold and interval defined in Table 1.
THRESHOLD INTERVAL 7000 FC or 7000FH since EIS* (whichever occurs first) Grace period 50FC or 50FH (whichever occurs first) 1750 FC or 1750 FH (whichever occurs first) Table 1 For A/C already inspected by previous issues of the AOT, continue inspection plan in accordance with Table 1.
For A/C not inspected by previous issues of the AOT, the inspection must be performed in accordance with the following compliance time , whichever occurs later :
Before exceeding 7000 FC or 7000FH (whichever occurs first) Wi thin 50FC or 50FH (whichever occurs first)
For aircraft repaired by means of a RDAS, the present AOT is no longer applicable. Applicable limitation and inspections (if any) are the ones explicitly shown in the RDAS.
*Entry into Service.
3.1.2 MANPOWER T he estimated time to get access and perform the inspection is 3 men hours per aircraft.
3.2 DESCRIPTION
3.2.1 ACCESS
Reference No.: AOT - C212 - 53 - 0001 Revision No.: 1 Date: 30/01/2020 Alert Operators Transmission Page : 3 / 6 ATA Chapter: 53 Subject: Inspection of Fuselage Skin and FR5 LH/RH near Wing Leading Edge
Get access to the inspection area removing the forward underwing Wing - Fuselage - Fairing LH and RH in accordance with Ref. [3 ] and Ref. [ 4 ].
Use a c herry picker to reach the location.
3.2.2 INSPECTION REQUIREME NTS Perform a Detailed Visual Inspection ( DVI ) of the affected area following the rules of Ref. [ 5 ].
The inspection area is defined in Figure 1 and Figure 2. The inspection must be performed on the fuselage skin edges and holes close to the edges around FR5 area and the upper to lower former joints, inner and outer caps, web and joint fittings at the joining area.
Perform the inspection looking for cracks similar to the ones shown in Figure 3 a nd Figure 4 .
3.2.3 FINDINGS In case of findings, r eport to Airbus Defence and Space the inspection results for further instructions.
In case of no findings, r eport to Airbus Defence and Space to confirm the inspection result.
3.3 SPARES AND TOOLING N/A
4. FURTHER INFORMATION
4.1 FOLLOW - UP PLAN Airbus Defence & Space is currently working on the definition of the terminating action for this topic.
4.2 IMPACTED DOCUMENTATI ON N/A
5. REPORTING
Questions about this AOT and inspection results with or without findings are to be sent to :
Airbus DS Technical Assistance Center (AMTAC):
Telephone: (+34) 91 600 79 99 E - mail: mta.technicalservice@es.airbus.com
This AOT is or it is expected to be subject to an Airworthiness Directive or Airworthiness Directive Recommendation Letter.
Reference No.: AOT - C212 - 53 - 0001 Revision No.: 1 Date: 30/01/2020 Alert Operators Transmission Page : 4 / 6 ATA Chapter: 53 Subject: Inspection of Fuselage Skin and FR5 LH/RH near Wing Leading Edge
Released by
HO Engineering Support Transport
The technical content of this document is approved under the authority of EASA DOA No. EASA. 21.J.032.
The technical content of this document is approved under the Airbus DS Design Assurance System, based upon accepted procedures under EASA Design Organization Approval No. EASA.21J.032 .
© AIRBUS DEFENCE AND SPACE. All rights reserved. Confidential and proprietary document.
This document and all information contained herein is the sole property of AIRBUS DEFENCE AND SPACE.
No intellectual property rights are granted by the delivery of this document or the disclosure of its content. This document shall not be reproduced or disclosed to a third party without the express written consent of AIRBUS DEFEN CE AND SPACE.
This document and its content shall not be used for any purpose other than that for which it is supplied.
© AIRBUS DEFENCE AND SPACE 2020 All right reserved
Reference No.: AOT - C212 - 53 - 0001 Revision No.: 1 Date: 30/01/2020 Alert Operators Transmission Page : 5 / 6 ATA Chapter: 53 Subject: Inspection of Fuselage Skin and FR5 LH/RH near Wing Leading Edge
ANNEX 1 - FIGURES
Figure 1. I nspection area location
Figure 2. Inspection area (LH shown, RH symmetrical)
Reference No.: AOT - C212 - 53 - 0001 Revision No.: 1 Date: 30/01/2020 Alert Operators Transmission Page : 6 / 6 ATA Chapter: 53 Subject: Inspection of Fuselage Skin and FR5 LH/RH near Wing Leading Edge
Figure 3 . T ypical damages on LH wing
Figure 4 . T ypical damages on RH wing