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AC 068
AA
PIR.84
SYS 2701
MDIS.03DEC/JFK
T-0647
EMPL 089838
DURING
DEPARTURE CLIMB, AIRCRAFT ENCOUNTERED
TURBULENCE
AT ABOUT 300 FEET UP TO ABOUT 1200 FEET,
AND THE
AIRCRAFT YAWED SEVERAL TIMES. AIRCRAFT WAS
BEING HAND
FLOWN, WITH SLATS EXTENDED WITH TAKE OFF
FLAPS SET.
NO RUDDER TRAVEL FAULT INDICATED. NO YAW
DAMPER
DISCONNECTS. AIRCRAFT FLEW NORMALLY ON
AUTOPILOT
AFTER THE EVENT. AIRCRAFT FLEW NORMALLY
BEING HAND
FLOWN. THE AIRCRAFT FELT AS IF IT WAS
PURPOSEFUL
YAW INPUTS. NO RUDDER PEDAL MOVEMENT WAS
NOTED.
AIRSPEEDS WERE ABOUT 200 TO 225 KTS IAS.
0682700E7/1849.03DEC.JFK KQ NBR 3
AC 068
AA
TFI.
TWD 03DEC02 DTG
0 SYS 2720
PRI 1
MDIS.03DEC/TUL
**TECH LIST**
EMPL 159064
CREW
REPORTS UNCOMMANDED RUDDER MOVEMENT.
ATBT.03DEC/TUL
NAME R. B.
KNOX
EMPL 159064
1 PERFORM
ENGINEERING BILL OF WORK. IF UNAVAILABLE
2 CONTACT TECH.
SERVICES FOR A COPY.
3 BE SURE TO
CONTACT ENGINEER DAVID SERATT AT
4 918-641-5180 AND
REPORT RESULTS.
0682700E6/1732.03DEC.TUL KQ NBR 4
AC 068
AA TII.
TWD 13484 CTG 933 SYS 5700
PRI 4
MDIS.07NOV/TUL
EMPL 437846
*******1000 CYCLE REINSPECT*******
RH INBOARD
FLAP RIB 25A CRACKED. CRACK STOP DRILLED
PER AARD
57-00-00-6. DATE
ATBT.07NOV/TUL NAME A. E.
BENSON
EMPL 437846
1 ACCOMPLISH AN
EXTERNAL VISUAL INSPECTION OF THE
2 STEEL RUB STRIP
FOR CRACKS EVERY 4TH B CHECK.
3 NOTIFY TECH
SERVICE AND ENGINEERING IF CRACKS ARE
4 FOUND.ACCOMPLISH
AN INTERNAL INSPECTION OF RIB
5 25A REAR FOR
CRACK PROGRESSION AT 1000 FLT CYCLE
6 INTERVALS.
REPLACEMENT OF THE RIB TO BE DONE AT
7 NEXT MAIN BASE
VISIT.
06857009F/1601.07NOV.TUL...DFRD- 26 DAYS
KQ NBR 5
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Any
thoughts?
-----Original Message-----
From: Sent: Friday, December 06, 2002 5:04 PM To: T W Cc: David Subject: Re: #68 today Thanks,
Strange to say,
sounds like 'autopilot intrusion' of some kind... if
such an animal is possible. Brief autopilot
activation even though not engaged, signalling turn/rudder deflection not
from pedals but from autopilot computer down the line or servomechanism
itself.
1) Autopilot software fault or 2) arc-faulting event that caused spurious signals? HAS ANY UNCOMMANDED RUDDER A/C HAD A THOROUGH WIRING CHECK? (Visual and intrusive bundle inspection... a/c out of service for x time, "expensive" -- not really when you consider all airlines' current overcapacity. Mechanics' and avionics technicians' time, yes, but there seem to be potential time bombs and one thorough check might uncover something). Turbulence seems to be a possible catalyzing
factor--as perhaps with 587.
Just a thought.
Lee
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----- Original Message -----
From:
IASA
To: 'David
Sent: Tuesday, December 10, 2002 8:19
AM
Subject: RE: #68 today (two files
attached)
David
"NO RUDDER PEDAL MOVEMENT
WAS NOTED."
"Turbulence seems to be a possible catalyzing
factor--as perhaps with 587."
Re
turbulence. That's agreed, which brings me to "hysteresis" - the lagging of an
effect behind its cause.
I continue to
suspect that there is a flight control system hysteresis set up in the
rudder circuit whenever there is an external and extraneous event that brings
the yaw damper into very active play. A yaw damper normally constrains
inappropriate yaw (such as high-level Dutch Roll coupling) from
ever getting started in the first place. In sudden LOC/stall,
wake-induced or atmospheric turbulence situations involving sudden
large-displacement yawed flight conditions, it (the YD) is
entering the theatre halfway through Act One - and that may be a
large part of the problem. I'm not sure that when they set out to design
a yaw-damper, that it was ever a design requirement that it should
intervene capably in the midst of a mini LOC. Indeed I'm not sure if that
would be written into the flight-test program or indeed, could be set up
according to any laid-down test parameters. In particular I am always led
back to the fact that it is a 2 x YD dual-actuating affair acting
through a singular duplex valve - upon one of the system's three
rudder actuators. The hand-over/take-over ("you're malfunctioning" - "No
I'm not, you are") routine (and initiators) between the two yaw-dampers
may also be a wild-card in this equation.
That
SIA A340
event had simultaneous airspeed fluctuations - and so might this incident
(have had). It's likely that the flight-crew probably (and
routinely) dismiss those fluctuating airspeed indications as being
symptomatic of the turbulence and therefore not really reportable or indeed,
significant. Sharp pressure spikes in the Air Data Computer's input
data may be causing lagged (and
inappropriate) corrective rudder inputs and leading to a system
induced oscillation (SIO - aka an erratic hunting for equilibrium in
yaw). With the dubious DFDR filtering, it also becomes debatable as to whether
any such ADC high frequency pressure flux (or high-rate airspeed fluctuation
output) would be identifiably recorded. As a matter of urgency they first
up need to fit more informative flight-test variety DFDR's into a
reasonable number of these aircraft. However I doubt that they'd do that
while they are in passenger-carrying service - on liability grounds..... so
maybe just fit them to the freighters.
The "cause and
effect" key to the A300 tail-wagging is in the train of events kicked off
by the external initiator, apparently whether or not the autopilot is in the
circuit. The common denominator would seem to be the pressure spikes that
are present during LOC/stall/incipient autorotation, wake turbulence,
atmospheric turbulence - and also (once initiated) by the
continuing, undamped yawing condition itself. Any yaw could amplify static
port errors as the ports (one on each side of the aircraft) are
individually and alternatively airflow-blanked and then subjected to an
error-inducing inflow (as the face of a port on one side becomes
unblanked during a yaw cycle - and then presented obliquely to the
airflow). Any discrepancy in the sensed static (caused by the pro
and adverse flow of any water trapped in the static lines for
instance) has a disproportionate effect upon the airspeed (you will
recall). But on top of any such error will be the p1+ and
p2- flux induced by the port-face exposure during yawing and a further
superimposed error due to the actual pressure spikes present in a vortex
rotor. The net effect may well be that the sensed airspeed
(momentarily inputting to both the rudder limiter and yaw-damper) will
be, at any given moment, significantly in error and/or trending away from the
real indicated airspeed (i.e. CAS or calibrated). The undesired
outcome is likely to be a software integration issue. IAS and CAS do not
normally differ by significant amounts in a static situation - however dynamic
motion in the yawing plane (or side-gusts) can induce much larger
transient pressure errors, depending upon the particular installation and
its system's damping.
Any sudden yaw will invite a yaw-damper
correction to the rudder and that rudder deflection has to be an
appropriate and timely augment to the sizeable stabilizing moment
simultaneously acting (naturally) due to that large vertical fin -
or it will drastically overshoot the null position (instead of just slightly
overshooting it in a rapidly-damped, decreasing amplitude phugoid). If, due to
ADC-generated airspeed confusion, it's too large a yaw-damper input, the
yaw correction will overshoot, a further correction will be required of the
system and consequently the aircraft is going to cycle in an uncommanded
yaw i.e. describe a continuing undamped sinusoidal phugoid
around the yaw axis. Unlike a Pilot
Induced Oscillation (PIO) in the pitch axis, development of any PIO (or
SIO) in the yaw axis is limited by that large restorative moment
generated by the vertical fin..... and cannot become divergent (i.e. due
to yaw stability). However what can happen is
that the rudder's inputs can become so out-of-phase and inappropriately
deflected, that a fin overstress can result after a very few asynchronous
cycles of its hysteresis condition (per
AA587).
Two areas
that I have not touched upon are also speed sensitive - i.e. pilot pedal input
and any inappropriate rudder-limiter setting that might be caused by
airspeed flux and IAS sampling rates. CROW instability effects that might
occur in an along-track wake vortex encounter have been covered elsewhere
and would neither add or detract from the possibilities of the above described
theoretical phenomena. However, as a physical (and destructive) additive
to the above phenomena, the CROW hammer (see the attachment) may well
have been the final straw for AA587, particularly if the yaw onsets were
so pronounced that exacerbating pilot pedal intervention was a psychologically
natural outcome.
And, of
course, an autopilot malfunction per the attached AD (99-NM-189-AD) may
also have caused this incident below (see the box) - even though "AIRCRAFT WAS BEING HAND FLOWN"
IASA
From: David Sent: Tuesday, December 10, 2002 6:33 AM To: 'safety' Subject: FW: #68 today |
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David
It gets murkier and murkier. I just don't believe the "bad
lead" or the DFDR "bad sensor" (see below). All too facile.
I wonder if "a bad lead" is
similar to an intermittent arc-fault (in
AA maint parlance)?
Interesting that they are
keeping DFDR readouts under ongoing review.
It is all narrowing down to
being the yaw damper (as provoked by the wake encounter) (IMHO) - as chief
AA587 miscreant.
JS
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After the December 3 incident, tail # 068 was
released for flight two days after the event; and it was stopped minutes before
takeoff when the Tulsa tech unit at AA discovered a .46 lateral acceleration on
the DFDR from a previous flight. Subsequently, they have found a "bad
lead" on one of the yaw dampers and the uncommanded sequential yaw movements on
the Dec. 3 flight has been attributed to that. It has been speculated
that, since the flight crew from the previous flight (the one with the .46
lateral acceleration, which was NOT the Dec. 3 flight) did not write up any
problems, it was "just a bad sensor" on the DFDR. This leads to all sorts
of questions about DFDR data and its reliability, and the yaw damper problem
experienced by AA 587 on pre-flight at JFK.
Apparently, the F/O on the Dec. 3 flight has asked
for a transfer off the A300 and the Chief pilot has said he will accommodate
him.
Todd Wisisng
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