Sudarsono has over 28 years of experience in fatigue and damage tolerance analyses. He has worked on projects for Airbus, Bombardier, GKN, SITEC and Indonesian Aerospace. His experience includes performing analyses using tools like DAMTOL, ISAMI and hand calculations. His areas of work have included the A350, A380, A320 and CN235 programs.

1. RESUME
Name : SUDARSONO
Current Address : Julius-Bruhns Strasse 7
28329 Bremen
Germany
Phone (evening): +49-421-68448182
Mobile phone: +49-(0)-17675208472
Email address : sudarsonop@yahoo.com
Skills : Fatigue and Damage Tolerance
Education : 1984 BSc Mechanical Engineering Department,
Bandung Institute of Technology (ITB),
Bandung – Indonesia
Date of Birth : 5th March 1957
Availability : January 2017
Summary of Experience
1. Fatigue and Damage Tolerance Analyses
2. Engineering Liaison & Production Support
3. Full Scale Fatigue Test support & Test Evaluation and documentation

2. Summary
I have gain experiences over 28 years in aero structures, primarily in the Fatigue area
including damage tolerance analyses using in house programs such as DAMTOL,
ISSY-DYNFEST, ISAMI and hand calculations.
I worked for BQ Engineering in Augsburg from October 2016 to December 2016. I am
involved in A350 project.
From November 2009 to October 2014 I worked for GECI GmbH. I was involved in
A350, A400, A330/A340, A320 P2F, Bombardier CSeries projects performing Fatigue
and Damage Tolerance analyses and Structural Repair Manual.
Before that I worked for SITEC/AIRBUS UK at Filton – Bristol from 2008 to 2009 in
charged of performing Fatigue and Damage Tolerance analyses for Daily Repairs
Justifications.
I joined GKN Engineering Services on the Isle of Wight from 2007 to 2008 and I was in
charge of the A380 fixed trailing edge check-stress and A400M Rear and Front Spar.
From 2001 until 2006 I worked for Airbus UK at Filton and I was involved in A380
project in charge of performing Fatigue and Damage Tolerance analyses for fixed
trailing edge in both design phase and check-stress support.
I started my career in aerospace in 1984 as a liaison engineer for CN235 and parallel I
also worked on concessions of NC212 and helicopters. I started working in fatigue and
damage tolerance analyses in 1987, in charge of Principal Structural Element (PSE)
analysis and Full Scale Fatigue Test on CN235 Aircraft project.

3. HISTORY OF EMPLOYMENT
10/2016 -12/2016 BQ Engineering GmbH Hamburg
Senior Fatigue and Damage Tolerance Engineer
Program: A350XWB-900/1000
at FERCHAU Engineering – Augsburg
Performing Fatigue and Damage Tolerance analysis
 Door Surrounding Structure FDT analysis
 Rear Pressure Bulkhead FDT analysis
 Titanium Frame and Frame Coupling
 Cross Beam to Fuselage Frame connection
1/2009 -10/2014 GECI GmbH Hamburg
Senior Fatigue and Damage Tolerance Engineer
Program: Structural Repair Manual (A320, A330, A380, A350)
at Airbus - Hamburg (07/2014 – 08/2014)
 A320 ESG1 Fuselage Dents FDT Justification
o Checked and updated the calculation
o Updated report
 A350XWB-900 Upper Lower Panel SRM
List of Findings preparations
 A330-200/300 Pre-Enhanced Fuselage Dents FDT
Justification
Checked Justification report
 A380 Upper Deck Door FAS and RAS Overview
Checked and Updated Fatigue Approval Sheet
(FAS) and Repair Approval Sheet (RAS)
Program: A350 Inboard Flap Ribs
at Ferchau - Bremen (04/ 2013 – 12/2013)
 Checked Fatigue and Damage Tolerance Analysis Report
for MSN-01 and MSN-05 (Internal Checking)
 Performed damage tolerance analysis (Crack Propagation
analysis) for MSN-05 (LK141 and LK171 Loading) using
ISAMI Computer Program
 Performed damage tolerance analysis (Crack Propagation
analysis) for MSN-21 (LK171 Loading) using ISAMI
Computer Program

4. Program: A350 Doors Surrounding Structures
at Premium Aerotec - Hamburg (12/2012 – 04/2013)
 Performed fatigue and damage tolerance analysis on Cargo
Door Surrounding Structures
 Performed fatigue and damage tolerance analysis on
Passenger Door Surrounding Structures
 Performed element selection and grouping on DFEM used
for Equivalent Stress Calculations.
Program: Bombardier C-series (CS100 & CS300) Main and
Nose Landing Gears
at LIEBHERR GmbH - Lindenberg (10/2011- 11/ 2012)
 Performed fatigue analysis with hand calculations on Main
and Nose Landing Gears Structures For CS100 and CS300
Preliminary Design (PDR) and Critical Design Review
(CDR)
 Prepared Fatigue Load Spectrum for CS100 Main and Nose
Landing Gears Structures Fatigue Test
 Performed fatigue analysis with Hand Calculations on Main
and Nose Landing Gears Structures Concession
Program: A320PtoF (A320 Passenger to Freighter Conversion)
at IRKUT – Hamburg (11/ 2010 – 05/2011)
Performed fatigue and damage tolerance analyses on Fuselage
Circumferential and Longitudinal Splices of Section 17 using ISSY-
Dynfest Computer Program.
 Performed Equivalent Stress survey to obtain the critical
element for fatigue and crack growth analysis
 Fatigue and crack propagation calculations.
Program: A330 (Long Range) Inboard and Outboard Flap
Structural Repair Manual (SRM)
at GECI GmbH - Bremen(10/ 2010)
Involved in Fatigue and Damage Tolerance Analysis and
Justification for A330-200 WV057/058 Structural Repair Manual
(SRM):
 Allowable Damage Limit and Repair justification for Inboard
Flap according to SRM 57-54-00
 Repair justification for Outboard Flap according to SRM 57-
54-00

5. Program: A400M Lining Structures
at Airbus - Bremen(05/2010 – 10/2010)
Performed fatigue and damage tolerance analysis for Lining
Structure
Program: A330/A340 (Long Range) Aileron Interface Bolt
at GECI GmbH - Hamburg (01/2010 – 04/2010)
Performed fatigue and damage tolerance analysis for Aileron
Interface Bolt
Program: A400M Vertical and Horizontal Tail Plane
at GECI GmbH - Hamburg (11/ 2009 – 01/ 2010)
Performed fatigue and damage tolerance analysis for Vertical and
Horizontal Tail Plane Structures
06/2008-11/2009 SITEC GROUP FILTON - UK
Contract Fatigue and Damage Tolerance Engineer
Program: A300, A310, A318, A319, A320, A321, A330, A340,
A380
Performed fatigue and damage tolerance analysis for repair on
wing component of aircraft in service using DAMTOL Computer
Program.
 Performed fatigue and crack propagation calculations
 Determined Post Repair Fatigue Threshold and Repeat
Inspection interval
01/2007-05/2008 GKN Engineering Service Isle of Wight - UK
Contract Fatigue and Damage Tolerance Engineer
Program: A400M Front and Rear Spar Panel
Front Spar Panel Horizontal Stiffener
Performed Optimisation for Front Spar Panel Horizontal Stiffeners
geometries
Rear Spar Panel Breaker
Performed Optimisation for Rear Spar Panel Breaker Moment of
Inertia requirement

6. Rear Spar Panel Horizontal Stiffener
Provided Airbus Stress Data (ASD)
Program: A380 Fixed Trailing Edge Fatigue and Damage
Tolerance analyses
Overwing Panel Metallic Structures
Performed fatigue and damage tolerance analyses on Strut Fitting
at the following locations
 Lugs
 Webs
 Flanges
Upper Panel Metallic Structures
Performed fatigue and damage tolerance analyses on Sliding
Angle
Wing Landing Gear Hinged Door Metallic Structures
Performed fatigue and damage tolerance analyses on the following
components
 Forward and Aft Fitting at locations
o Lug
o Goose Neck
o Base Plate
 Strut Bracket
Fixed Trailing Edge Lower Panel 7 – 16 Metallic Structures
(C-Category - Multiple Load Path Structure)
Performed fatigue analyses
 Lug fatigue analyses
 Strut Bracket’s Flanges fatigue analyses
10/2001-12/2006 Airbus – UK Filton - Bristol
Contract Fatigue and Damage Tolerance Engineer
Program: A380 Wing Concessions
Performed fatigue analysis on Wing concessions;
 Wingbox
 Fixed Trailing Edge
Program: A380 Wing - Fixed Trailing Edge Fatigue and

7. Damage Tolerance Analyses
Phases/Loads: Loop 2 Loading
Developed Cycles Mission Files used in DAMTOL (in house)
program to generate fatigue load spectrums for the following
components.
 Aileron Support Structures (Hinge Ribs and Actuator
Brackets)
 Spoiler Support Structures (Hinge Ribs and Actuator
Brackets)
Phases/Loads: Loop 1 Loading
Developed Cycles Mission Files used in DAMTOL (in house)
program to generate fatigue load spectrums and for the following
components.
 Aileron Support Structures (Hinge Ribs and Actuator
Brackets)
 Spoiler Support Structures (Hinge Ribs and Actuator
Brackets)
Performed fatigue analyses using DAMTOL (in house) program for
the following locations.
 Aileron Support Structures (Hinge Ribs and Actuator
Brackets)
o Lugs
o Top Skin / Spar Attachment
o Bottom Skin / Spar Attachment
 Spoiler Support Structures (Hinge Ribs and Actuator
Brackets)
o Lugs
o Top Skin / Spar Attachment
o Bottom Skin / Spar Attachment
Developed Fatigue load for Spoiler Surface Panel
Phases/Loads: Pre-Loop 1C Loading (C-Scheme)
Developed Cycles Mission Files used in DAMTOL (in house)
program to generate fatigue load spectrums and for the following
components.
 Aileron Support Structures (Hinge Ribs and Actuator
Brackets)
 Spoiler Support Structures (Hinge Ribs and Actuator
Brackets)
Performed fatigue analyses using DAMTOL (in house) program for

8. the following locations.
 Inner Aileron Support Structures (Hinge Ribs and Actuator
Brackets)
o Lugs
o Top Skin / Spar Attachment
o Bottom Skin / Spar Attachment
 Spoiler Support Structures (Hinge Ribs and Actuator
Brackets)
o Lugs
o Top Skin / Spar Attachment
o Bottom Skin / Spar Attachment
Performed stress survey on Wing’s Top Skin Overhangs and
fatigue analysis on Top and Bottom Skin Overhang Penetrations
Phases/Loads: A-Scheme and B-Scheme
Performed fatigue analysis on Flap Track Support Structures (Flap
Track 3.to 6) at the following locations
 Forward Attachment
o Primary Lugs (lug hole and root)
o Secondary Lugs (lug hole and root)
 Aft Attachment
o Main Spigot Lugs
o Failsafe Shear Bolt Lugs
Performed stress survey on Wing’s Top and Bottom Rear Spar
Flange
Performed fatigue and crack propagation analyses on Wing’s Top
and Bottom Rear Spar Flange and Rear Spar Joints

9. 11/1984-10/2001 Indonesian Aerospace (Former: IPTN)
Bandung - Indonesia
Fatigue and Damage Tolerance Engineer
Program: NBO105 & CN235
IPTN – Bandung (01/2000 – 10/2001)
NBO105
Performed fatigue evaluation for modification from civil to military
version
CN235-220
Performed stress calculations and mapping for fuselage frames
and stringers
Program: CN235 & N250
IPTN – Bandung (1996 – 1999)
CN235-220
Performed damage tolerance analysis on the following locations
 Forward Fuselage Trunion to Diagonal Beam Splice (PSE
F60)
 Wing-Fuselage Aft Fitting (PSE W33)
CN235 Engineering Liaison and Production Support
 Performed fatigue and damage tolerance evaluation on
discrepancy parts/components
 Performed fatigue and damage tolerance evaluation on
Outer Wing Centre Plank and Machined Frame 21 Upper
Former
N250 Engineering Liaison and Production Support
 Performed fatigue and damage tolerance evaluation on
discrepancy parts/components
 Performed fatigue and damage tolerance evaluation on
Main Landing Gear Truss Fitting
N250-100 PA2
Rejection tag mapping
N250
Flap Fatigue Test specimen preparation and conformity
CN235 and N250
Cold working & Shot peening process evaluation for production
support

10. Program: CN235 & N250
IPTN – Bandung (1989 – 1996)
CN235 Full Scale Fatigue Test and Residual Strength Test
 Structural repair design preparation
 Test result evaluation and justification
 Structural modification and inspection program
determination
CN235 Aircraft in Service
Structural Maintenance Support for Aircraft in Service
N250 Engineering Liaison and Production Support
Performed fatigue and damage tolerance evaluation on
discrepancy parts/components
N250-100
Involved in Damage Tolerance Certification Plan preparation
Program: CN235 Principal Structural Elements (PSE) Fatigue
and Damage Tolerance Analysis
Job Training at DASA (Deutsche Airbus) – Hamburg (August
1987 – July 1988)
Performed fatigue and crack propagation analyses on Principal
Structural Elements (PSE) such as
 Outer Wing Longitudinal Splice (PSE W24)
 Rear Fuselage Longitudinal Skin Splice Stringer P14A
between Frames 30 and 42 (PSE F02)
 Horizontal Stabilizer Rear Cone Pick up Lug at Frame 50
(PSE F12)
 Centre Fuselage Passenger Door Corner Cut out at Frames
13 and 15 (PSE F41)
 Vertical Stabilizer Forward Pick up at Frame 46 (PSE V03)
Program: CN235, NC212, NSA332, NBO105 & NBELL412
IPTN – Bandung (November 1984 – July 1987)
CN235 & NC212
Engineering liaison and discrepancy components evaluation in
assembly line
CN235, NC212, NSA332, NBO105 and NBELL-412
Engineering liaison and non conforming material (discrepancy
parts) evaluation in production line (detail part manufacturing)

11. Related Course Work
2011
ISAMI Stress Training – Fatigue
Airbus Deutschland – Hamburg
1997
Aircraft Certification Process Course
IPTN – Bandung Indonesia
1993
Short Course Practical Consideration in Structural Fatigue
and Damage Tolerant of New and Aging Aircraft
FASIDE International Saltlake City – Utah USA
1993
Fatigue and Damage Tolerance Course (Residual Stress)
IPTN – Bandung Indonesia
1989
Fatigue Material and Structural Symposium
IPTN-Bandung Indonesia
1988
Damage Tolerance Course II
General Dynamic-IPTN-Bandung Indonesia
1988
Damage Tolerance Course I
General Dynamic-IPTN-Bandung Indonesia
Bremen, 28.12.2016
Sudarsono