Title: atma generic
1 BARRY CONTROLS AEROSPACE TECHNICAL PRESENTATION
ON VIBRATION AND VIBRATION ISOLATION
2Introduction
- David Posavec
- Eastern Regional Sales Manager
- Barry Controls Aerospace
- Responsibilities Include
- OEMs
- Regional Major Airlines
- Cargo Airlines
- GA Distribution
- Trade Shows IA renewals
3Barry 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
4Barry 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.
5Product Line
- Vibration Isolation
- Fixed Wing
- Rotary Wing
- Tuned Mass Absorber
- Passive
- Active (ATMA)
- Other products include anti-vibration mounts,
avionics trays and racking systems
6Barry 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
7Barry 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
8General 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
9Business 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
10Regional 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
11Commercial 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
12Product 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
13Auxiliary 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
14 VibrationWhat Causes It?
15 VibrationRotating Mass Examples
- Examples of a Rotating Mass
- Crankshaft
- Propeller
- Turbine Disk
- Tire/Wheel Assembly
16 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
17 VibrationAerodynamic Asymmetry
18 VibrationPower Output Asymmetry
19 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
20 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
21 VibrationVibration Isolator
22Benefit 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.
23Benefits 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.
24 VibrationVibration Isolator Terminology
25 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
26 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.
27 VibrationDamping
Figure 3
28 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.
29 VibrationIsolator Installation
Typical Bed Mount Installations
Figure A Semi-focalized Bed Mount
30 VibrationIsolator Selection
31 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
32 VibrationTuned Vibration Absorber
DC-9/MD-80 Tuned Vibration Absorber
33 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.
34 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
35 Installed ATMA SystemNoise Reduction
No engine removal required Overnight
installation No interior modifications No special
tools required
36 Aircraft Vibration IsolatorsDescription and
Operation
Typical General Aviation Vibration Isolator
37Aircraft Vibration IsolatorsWhy bother with Cure
Dates?
38Aircraft Vibration IsolatorsDeciphering Cure
Dates
39Aircraft Vibration IsolatorsIsolator Materials
Cure Dates
40Aircraft Vibration IsolatorsSelection
Replacement Criteria
41 Aircraft Vibration IsolatorsMaintenance
42 Aircraft Vibration IsolatorsOn-Aircraft
Inspection
43 Aircraft Vibration IsolatorsOn-Aircraft
Inspection
44 Aircraft Vibration IsolatorsBench Inspection
45 Aircraft Vibration IsolatorsBench Inspection
46 Aircraft Vibration IsolatorsBench Inspection
Free Height
Eccentricity
47 Aircraft Vibration IsolatorsBench Inspection
48 Aircraft Vibration IsolatorsBench Inspection
49Aircraft Vibration IsolatorsReplacement
50Aircraft Vibration IsolatorsReplace vs. Overhaul
51Conebolt 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
52Conebolt 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
53Conebolt 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.
54Conebolt 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.
55Conebolt 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).
56Conebolt 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 (818) 845-6978 SITA BURBCCR
57Questions
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