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BARRY CONTROLS AEROSPACE TECHNICAL PRESENTATION
ON VIBRATION AND VIBRATION ISOLATION
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Introduction

• David Posavec
• Eastern Regional Sales Manager
• Barry Controls Aerospace
• Responsibilities Include
• OEMs
• Regional Major Airlines
• Cargo Airlines
• GA Distribution
• Trade Shows IA renewals

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Barry Controls Aerospace

• Over 55 years developing and manufacturing
  aviation vibration and noise control solutions
• Worlds leading supplier of Engine and APU
  Vibration Isolators
• Jet, turboprop, and general aviation aircraft
  products
• Manufacture over 5,000 products and hold over 350
  PMAs
• Applications on virtually every commercial jet
  aircraft
• Three locations
• Burbank, California (pictured)
• Toulouse, France
• Hersham, England

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Barry Controls Aerospace

• Proven Supplier
• Worlds leader in the design, development,
  production and support of state of the art
  vibration isolation systems.
• Over 55 years of experience in providing main
  engine and APU isolation systems for a majority
  of the worlds commercial and business aircraft
  manufacturers.
• Issued first firm order in the industry to outfit
  a jet carriers entire fleet with an active cabin
  noise reduction system.
• Service Center direct product support
• ISO-9000 and D1-9000 approved
• Factory direct, product support engineers, field
  support personnel and warranty processing.

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Product Line

• Vibration Isolation
• Fixed Wing
• Rotary Wing
• Tuned Mass Absorber
• Passive
• Active (ATMA)
• Other products include anti-vibration mounts,
  avionics trays and racking systems

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Barry Controls Aerospace

• Quality System Approvals
• FAA - PMA/TSO - F.A.R. Part 21
• FAA - Organizational Designated Airworthiness
  Representative (ODAR) F.A.R. Part 21.303
• FAA - F.A.R. 145 Repair Station
• FAA - J.A.R. 145 Repair Station
• CAAC - China CCAR 145 Repair Station
• Government - MIL-I-45208A and MIL-Q-9858A
• Boeing - Advanced Quality System AQS/D1-9000A
• Coordinating Agency for Supplier Evaluation
  (CASE)
• ISO 9001 Compliance

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Barry Controls Aerospace

• Quality System Approvals by Major OEMs
• Aerospatiale
• Airbus
• Agusta
• B.F. Goodrich
• Boeing
• British Aerospace
• Cessna
• Fairchild/Dornier
• Fokker
• Gulfstream
• Lockheed-Martin
• Nordam
• Northrop
• Raytheon Aircraft
• Westland Aerospace

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General Aviation Experience

• General Aviation Isolation Systems
• Beech Bonanza, King Air, Queen Air, Musketeer,
  Travel Air
• Cessna Skyhawk, Stationair, Centurion, Eagle,
  Conquest
• Maule M4, 5, 6, 7 series -Mooney Mark, Ranger,
  Statesman
• Pilatus PC-6, -7, -9, -12
• Piper Aerostar, Apache, Arrow Series, Aztec,
  Cherokee, Cheyenne, Comanche, Dakota, Navajo
• Robin, Socata, Transavia, Wassmer, Xian and Zlin

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Business Jet Experience

• Business Jet Engine Isolation Systems
• All Gulfstream Applications, G-II, G-III, G-IV
• Raytheon Jayhawk, Premier I, 400A, and Hawker
  Horizon 4000
• Cessna Citation 1, 2, 3
• Israel Aircraft Industries 1121 1123
• Sabreliner NA-265-65 NA-265-75A
• Rockwell NA-265-40 NA-265-60
• Lockheed Jetstar
• Sino-Swearingen SJ30-2

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Regional Aircraft Experience

• Regional Transport Engine Isolation Systems
• All ATR Applications - ATR42 ATR72 Series
• All BAe/Jetstream Applications - J31, J41, ATP
• All Fokker Applications F50 F60
• Fairchild/Dornier Applications - Metro, Do228,
  Do328 Turboprop and Do328 Jet
• deHavilland Dash 8 Series 400
• Lockheed C-27J
• Saab 340
• Xian Y7-200A Harbin Y11-100
• CASA C212 C295
• IPTN N250

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Commercial Jet Experience

• Large Commercial Jet Engine Isolation Systems
• Boeing 717
• Boeing 727 Series
• Boeing 737 Series
• Douglas DC-9 Series
• Douglas MD-80 Series
• Fokker 70 and 100

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Product Experience
1. MD-80 Aft Isolator 2. MD-80 Fwd
Isolator 3. 727 Aft Isolator Side Center
Engines 4. DC-9 Fwd Isolator 5. DC-9 Aft
Isolator 6. DC-9 Conebolts 7. MD-80
Conebolts 8. 727 Aft Isolator 9. 737 Fwd
Isolator 10. 737 Aft Isolator 11. 727 Fwd
Isolator 12. A-320 APU Isolator 13. A-300 APU
Isolator 14. 747-400 APU Isolator
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Auxiliary Power Unit Experience

• APU Isolation Systems
• Airbus A300, A310, A319, A320, and A340
• Boeing 727, 737, 747, 757, 767, and 777
• Embraer ERJ-170 and ERJ-190
• deHavilland Dash 8-400
• Fokker 50 and 100
• Lockheed 1011 and C-27
• SAAB 340 and 2000

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VibrationWhat Causes It?
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VibrationRotating Mass Examples

• Examples of a Rotating Mass
• Crankshaft
• Propeller
• Turbine Disk
• Tire/Wheel Assembly

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VibrationRotating Mass Asymmetry

• Causes Of Asymmetry In A Rotating Mass
• Imbalance of mass about the axis of rotation
• Eccentricity about the axis of rotation
• Misalignment from the plane of rotation (such as
  a bent propeller flange), etc

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VibrationAerodynamic Asymmetry
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VibrationPower Output Asymmetry
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VibrationEffects of Vibration

• Vibration in an aircraft is undesirable due to
  its detrimental effects on the aircraft and its
  occupants. Some of these effects are
• High noise level
• Metal Fatigue
• Adhesive Disbond
• Reduced Avionics Life

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VibrationEngine Vibration Reduction

• Various steps can be taken to reduce engine
  vibration.
• Dynamic balancing of the engine and propeller
• Tighter manufacturing tolerances
• Match balancing of engine components
• In reality, the total elimination of vibration is
  an almost impossible task.
• Vibration Isolation is a cost-effective
  alternative

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VibrationVibration Isolator
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Benefit of Engine Isolators

• Offer optimum distribution of engine casing and
  airframe loads by design of isolator stiffness
  and snubbing.
• Thermal expansion of the engine can be taken by
  deflection of isolator
• Offer broad-band vibration isolation for high
  frequency vibration.

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Benefits of Engine Isolators

• Improves engine blade-out loading and flutter
  conditions.
• Facilitates engine installation and removal.
• Allows for increased airframe and engine
  tolerances using the allowance gained from
  isolator flexibility.
• Reduces possibility of damage to engine and
  airframe.

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VibrationVibration Isolator Terminology
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VibrationTransmissibility
Transmissibility is defined as the ratio of the
dynamic output (vibration applied to the
airframe) to the dynamic input (powerplant
vibration). A typical transmissibility curve is
shown in Fig. 2.
Figure 2
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VibrationDamping

• Damping refers to the phenomenon by which energy
  is dissipated in a vibratory system.
• It is an important property in aircraft engine
  isolators because aircraft engines operate over a
  wide range of rpms.
• As a transmissibility curve shows, when the
  engine RPM goes down, the amount of vibration
  transferred to the airframe can go up.

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VibrationDamping
Figure 3
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VibrationIsolator Installation
Typical Dynafocal Mount Installation

• Focuses the centerlines of the isolators at a
  point slightly ahead of but in the same plane as
  the engines center of gravity.
• Flight loads are applied equally to each isolator.

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VibrationIsolator Installation
Typical Bed Mount Installations
Figure A Semi-focalized Bed Mount
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VibrationIsolator Selection
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VibrationAbsorption

• Tuned Mass Absorption
• In addition to isolating vibration, it is
  possible to absorb vibration
• Absorption is accomplished using a mass and a
  spring.
• The spring is tuned to resonate at same
  frequency as disturbing frequency
• Resonation is out of phase with disturbing
  frequency, resulting in cancellation

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VibrationTuned Vibration Absorber
DC-9/MD-80 Tuned Vibration Absorber
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Benefits of Tuned Mass Absorbers

• Effectively attenuates vibration up to 90.
• Dramatically reduces vibration/noise levels.
• Self-contained units, ready for installation, low
  maintenance.
• Relatively low cost, light weight solution in
  comparison with other cabin noise reduction
  solutions.
• Reduces structure displacement and stress,
  improving structural fatigue life.
• Improves isolation system performance.

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ATMA SystemNoise Reduction
System Components 4 N1 Absorbers 4 N2
Absorbers Controller Box Harnesses Sensor
Assemblies Power consumption 5 Amps maximum 30
Watts (or less during cruise) Health monitoring
function
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Installed ATMA SystemNoise Reduction
No engine removal required Overnight
installation No interior modifications No special
tools required
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Aircraft Vibration IsolatorsDescription and
Operation
Typical General Aviation Vibration Isolator
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Aircraft Vibration IsolatorsWhy bother with Cure
Dates?
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Aircraft Vibration IsolatorsDeciphering Cure
Dates
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Aircraft Vibration IsolatorsIsolator Materials
Cure Dates
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Aircraft Vibration IsolatorsSelection
Replacement Criteria
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Aircraft Vibration IsolatorsMaintenance
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Aircraft Vibration IsolatorsOn-Aircraft
Inspection
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Aircraft Vibration IsolatorsOn-Aircraft
Inspection
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Aircraft Vibration IsolatorsBench Inspection
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Aircraft Vibration IsolatorsBench Inspection
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Aircraft Vibration IsolatorsBench Inspection
Free Height
Eccentricity
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Aircraft Vibration IsolatorsBench Inspection
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Aircraft Vibration IsolatorsBench Inspection
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Aircraft Vibration IsolatorsReplacement
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Aircraft Vibration IsolatorsReplace vs. Overhaul
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Conebolt Inspection Criteria Service
LettersIssued May 2004
EFFECTIVITY CONEBOLT PARTS APPLICATION R184
23-53 R18424-54 Boeing727 with Fedex Hush Kit
with 95803-1 isolators R18423-53
R18423-54 Boeing 727 with 7350000
isolators R18207-51 R18206-52 Boeing 727
with K2223 isolators R18423-2, R18423-49,
R18424-2 Boeing 737 with BCA 5467-1
isolators R18424-50 R18210-2 R18211-2 DC-9
Series (Excluding DC-9-80 MD-80 Series with
BCA K2219-7 isolators K2219-9SA3, K2219-9SA7,
DC-9 MD-80 with BCA K2219-9
isolators K2219-9SA9
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Conebolt Inspection Criteria Service
LettersIssued May 2004
REFERENCES a) Barry Controls Aerospace Component
Maintenance Manual 71-20-01 for Type
7350000 b) Military Specification MIL-S-8879 c)
SAE Specification AS8879 (Supersedes
MIL-S-8879C) d) ANSI/ASME Specification B1.3M e)
Federal Standard FED-STD-H28/20B
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Conebolt Inspection Criteria Service
LettersIssued May 2004
BACKGROUND Barry Controls Aerospace (BCA) has
received powerplant mounting conebolts used on
the JT-8D series of engines back from operators
with complaints that the conebolt does not pass
the minimum run-on torque requirement for the
self-locking attach nut. Multiple tries with
different attach nuts yielded similar
results. Inspection of the conebolts 0.625-18
UNJF-3A threads found that the parts had worn and
no longer met the requirements of MIL-S-8879C (or
its replacement SAE AS8879), which prevented the
attach nut meeting its minimum run-on torque.
The wear to the threads is a result of loss of
material due to friction from contact with the
nut, rework of the threads with a thread chaser
or file, or bolt stretch due to repeated
torquing. BCA would like to clarify the
inspection requirements outlined in MIL-S-8879C
( SAE AS8879) to ensure that the conebolts are
properly inspected and overhauled in accordance
with the BCA Component Maintenance Manual
71-20-01 for Type 7350000.
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Conebolt Inspection Criteria Service
LettersIssued May 2004
Paragraph 4.4.2 of MIL-S-8879 ( paragraph 4.1,
System 22, of SAE AS8879) outlines the threads
characteristics that must be inspected to ensure
compliance (Note Application category for
conebolts is Other Thread). They are a) GO
functional diameter b) Pitch diameter size c)
Major diameter size d) Minor diameter size e)
Root radius The acceptable methods and tools used
to inspect these characteristics are presented in
FED-STD-H28/20 (or ANSI/ASME B1.3M). Please note
that a GO/NO-GO ring gage set is not capable of
measuring all of the dimensions listed above.
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Conebolt Inspection Criteria Service
LettersIssued May 2004

• OPERATOR ACTION
• Due to the critical function of the conebolt,
  Barry Controls Aerospace recommends that
  operators take the following actions
• Operators performing their own conebolt overhauls
  and repairs should review the MIL-S-8879C (or SAE
  AS8879) specification to ensure that the
  conebolts threads characteristics listed in this
  specification are being inspected using the
  methods prescribed by FED-STDH28/20 (or ANSI/ASME
  B1.3M).
• Operators procuring overhauled conebolts from
  third-party agencies or having third-party repair
  agencies perform their conebolt overhauls and
  inspections should verify that the conebolts
  threads characteristics outlined in MIL-S-8879C
  (or SAE AS8879) are being inspected using the
  methods prescribed by FED-STD-H28/20 (or
  ANSI/ASME B1.3M).

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Conebolt Inspection Criteria Service
LettersIssued May 2004
Barry Controls can also perform overhauls or
provide rebuild/exchanges of conebolts with all
units having the threads inspected to the
requirements of MIL-S-8879 (or SAE AS8879) and
using the methods prescribed by FED-STD-H28/20
(or ANSI/ASME B1.3M). For any questions,
contact Barry Controls Aerospace 4510 Vanowen
Street Burbank, California 91505 USA (818)
843-1000 FAX [phone] SITA BURBCCR
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Questions
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