Annex B to
PFA Paper
Dated 21 May 2007
ACCIDENTS TO UK REGISTERED SINGLE-ENGINE EX-MILITARY AEROPLANES AND MICROLIGHTS (1976 TO 2006) INVOLVING
STRUCTURAL FAILURE IN-FLIGHT AND SUBSEQUENT LOSS OF CONTROL
Data Source: UK CAA Mandatory Occurrence Reporting Scheme (MORS) database (for accidents) and G-INFO (for C of A / Permit to Fly details)
Notes:
1. Ex-Mil: aircraft designed specifically for military use before being registered onto the UK civil register have been included, but aircraft built for civil use and
subsequently used by the military have not been included. Aircraft meet CAP 632 criteria.
2. Microlights: inclusion based on how aircraft is categorised on G-INFO.
3. Structural Failure: only includes accidents that involved an actual failure (crashes resulting from incorrect rigging, for example, have been excluded).
Microlights
Occurrence
Number
Date
Aircraft
Aircraft
Type
Registration
Location
Nature of Phase of
Flight
Flight
198104247 29/07/1981 Unknown
Microlight
GSlinfold
UNKNOWN
Training
Descent
198201875 27/06/1982 Scorpion
G-MMMM
Buckland
Private
Initial
Climb
198202241 07/08/1982 Scorpion
G-MBLI
Kitchenham
Private
Cruise
Summary
Description
WING FAILED IN ATTEMPT TO RESTART
DIVE. PILOT
ENGINE.
KILLED.
AIRFRAME
VIOLENT MANOEUVRES IN
FAILURE
PITCH OCCURRED AND THE
SHORTLY
LEFT WING WAS SEEN TO
AFTER TAKE- FLEX. EXAMINATION
OFF.
SHOWED STRUCTURAL
FAILURE OF TAIL PLANE AND
LEFT WING INNER REAR
SPAR, AND NUMEROUS
OTHER FAULTS WERE
NOTED. SCORPION
GROUNDED WEF 24-AUG-82.
(AIB BULLETIN 7/82)
WINGS FOLDED STRUCTURAL FAILURE OF
IN FLIGHT.
LEFT WING IN LEVEL FLIGHT
PILOT
AFTER FLYING OVER A LOCAL
SERIOUSLY
FAIR AT 200 FT THE
INJURED.
AIRCRAFT MADE A GENTLE
TURN AND HEADED BACK
Fatal
C of A /
Structural
Permit to
Failure
Fly
Type
1 Unknown Unknown
1 Exemption? Mechanical?
0 Exemption? Mechanical?
-1-
Occurrence
Number
Date
Aircraft
Aircraft
Type
Registration
198202432 23/08/1982 Scorpion
G-MBUN
Location
Headcorn
Nature of Phase of
Flight
Flight
Training
Cruise
Summary
AIRFRAME
FAILURE IN
FLIGHT. 2
KILLED.
Description
TOWARDS THE GATHERING.
A SHARP CRACK WAS HEARD
AND THE A/C'S WINGS
APPEARED TO FOLD
VERTICALLY ABOVE ITS
CENTRAL POINT. THE A/C
FELL INTO A CORNFIELD, 200
METRES FROM THE FAIR. NO
MAJOR COMPONENTS HAD
SEPARATED. ALL FOUR
FLYING WIRES UNDER THE
RIGHT WING HAD FAILED.
EXAMINATION FAILED TO
REVEAL THE PRIMARY CAUSE
OF THE IN-FLIGHT BREAK UP.
CAA HAS WITHDRAWN
EXEMPTION FOR THE
SCORPION MICROLIGHT A/C.
(AIB BULLETIN 11/82)
THE MICROLIGHT TOOK OFF
WITH INSTR AND STUDENT IN
CONTRAVENTION OF BRIEF
WHICH WAS FOR LOW HOPS
ALONG R/W. AFTER A LEVEL
TURN THERE WAS A LOUD
CRACK, ENG NOISE
STOPPED, AND A STEEP
GLIDE ENSUED. THE WINGS
FOLDED AND A/C FELL TO
GROUND. THERE WAS
STRUCTURAL FAILURE OF
ONE OR BOTH MAIN PLANES
IN UNACCELERATED FLIGHT.
EXAMINATION DID NOT
ESTABLISH THE PRIMARY
CAUSE OF THE STRUCTURAL
FAILURE. EXAMINATION OF
AN INTACT SCORPION
REVEALED A LACK OF
TORSIONAL STIFFNESS IN
Fatal
C of A /
Permit to
Fly
Structural
Failure
Type
2 Exemption? Mechanical?
-2-
Occurrence
Number
Date
Aircraft
Aircraft
Type
Registration
Location
Nature of Phase of
Flight
Flight
198301321 30/05/1983 Quicksilver G-MJSW
MXII
Swansea Dock
Private
Cruise
198302103 21/07/1983 Pathfinder G-MJUG
Mk1
Near St Girons,
France
Private
Cruise
Summary
Description
THE MAIN STRUCTURAL
COMPONENTS AND THE
POSSIBILITY OF
AEROELASTIC EFFECTS
CAUSING FAILURE(S) WITHIN
THE STRUCTURE COULD NOT
BE DISMISSED. (AIB
BULLETIN 11/82)
A/C DIVED INTO A/C SEEN FLYING AT ABOUT
MARINA AFTER 300 FT OVER WELSH BOAT
TAIL SECTION SHOW AT SWANSEA DOCK.
TWISTED.
AFTER LEVELLING WINGS
PILOT KILLED. FROM A TURN, TAIL SECTION
SEEN TO TWIST & A/C DIVED
STEEPLY INTO NEW MARINA.
A/C SANK BUT WAS BROUGHT
UP AFTER ABOUT 10 MINS.
EXAMINATION OF WRECKAGE
BY AIB FOUND ONE OF RH
TAIL BOOM ATTACHMENT PIP
PINS MISSING WITH
FRETTING DAMAGE AT THAT
LOCATION BUT NOT ON
OPPOSITE SIDE WHERE PIP
PIN STILL FITTED. ALSO KING
POST FOUND AT SHORTEST
ADJUSTMENT. EXTENSION
OF KING POST BY ROTATION
TENSIONS RIGGING WIRES
FOR BOTH MAINPLANE & TAIL
ASSY. PHOTOGRAPHS SHOW
RIGGING SLACK ON A/C ON
PREVIOUS DAY & AT TIME OF
ACCIDENT SHOW TAIL BOOM
BEGINNING TO SEPARATE IN
FLIGHT. (AIB BULLETIN 10/83)
WING FAILED IN 2 FATAL ACCIDENTS TO
SEVERE LOCAL PATHFINDER MICROLIGHT
TURBULENCE A/C ON 21-JULY-83 DURING
NEAR
ST GIRONS TO
Fatal
C of A /
Permit to
Fly
Structural
Failure
Type
1 Unknown
Mechanical?
1 Unknown
Turbulence
induced?
-3-
Occurrence
Number
Date
Aircraft
Aircraft
Type
Registration
Location
Nature of Phase of
Flight
Flight
Summary
PYRENEES.
198400639 14/03/1984 Flexiform G-MMWW
Sky Sails
Dual Striker
Near Leigh
Private
Cruise
AIRCRAFT
CRASHED IN
FIELD. TWO
KILLED.
STRUCTURE
FAILURE.
Description
CARCASSONNE STAGE OF A
RALLY. FIRST ACCIDENT TO
G-MJUG, 2ND TO FRENCH
OWNED A/C. BOTH SEEN TO
BREAK UP IN FLIGHT IN
SEVERE TURBULENCE.
PRELIMINARY INSPECTION
ON SITE INDICATED FAILURE
MAY HAVE ORIGINATED IN
TRAILING EDGE TUBE OF
LEFT WING AT RIGHT ANGLES
TO END OF AILERON.
FURTHER INFO AUG 84 ACCIDENT IN FRANCE 22-JUL84 AND ANOTHER IN
ZIMBABWE 17-JUN-84 HAVE
RESULTED IN CAA
GROUNDING A/C TYPE.
THE GEMINI STRIKER IS A
COMBINATION FORMED OF A
FLEXIFORM SKY SAILS, DUAL
STRIKER WING AND A
MAINAIR SPORTS GEMINI
TRICYCLE, CONTROLLED BY
WEIGHT- SHIFT. DURING
STATIC LOAD TESTS IT WAS
NOTED THAT CERTAIN
RIGGING WIRES FROM THE
BOWSPRIT TO THE A FRAME
WENT SLACK. FLEXIFORM
DETERMINED THAT THESE
WIRES WERE INEFFECTIVE
AND MODIFIED THE RIGGING
ON SOME AIRCRAFT. DURING
A DEMONSTRATION FLIGHT
BY A FLEXIFORM
REPRESENTATIVE
ACCOMPANIED BY A
CUSTOMER, THE WINGS
FOLDED AND THE AIRCRAFT
Fatal
C of A /
Permit to
Fly
2 Unknown
Structural
Failure
Type
Mechanical?
-4-
Occurrence
Number
Date
Aircraft
Aircraft
Type
Registration
Location
Nature of Phase of
Flight
Flight
198501327 04/05/1985 Flexiform
Sky Sails
Striker
G-MBNR
Ornezan, France Unknown
Cruise
198502788 17/08/1985 Puma
Sprint
G-MNDN
Near Derby
Cruise
Private
Summary
Description
FELL TO THE GROUND IN A
STEEP NOSE DOWN
ATTITUDE. THE AIRCRAFT
WAS DESTROYED AND BOTH
OCCUPANTS KILLED.
EXAMINATION OF THE
WRECKAGE REVEALED AN INFLIGHT STRUCTURAL
FAILURE. THE BOWSPRIT
SLIDER HAD FRACTURED
DUE TO UP LOAD AT THE
BOWSPRIT/KEEL JUNCTION.
THE RIGGING MODIFICATION
AFFECTED 6 AIRCRAFT
WHOSE OWNERS WERE
ADVISED. (AIB BULLETIN NO
6/84)
LH WING
INFORMATION AVAILABLE TO
FOLDED IN
CAA INDICATES PILOT MAY
FLIGHT. A/C
HAVE EXCEED A/C LIMITS BY
CRASHED.
FLYING WING-OVER
PILOT KILLED. MANOEUVRES.
A/C CRASHED THE AIRCRAFT HAD CLIMBED
AFTER TRIKE & TO APPROXIMATELY 300
WING
FEET AGL AND WAS HEADING
SEPARATED. 2 IN A WESTERLY DIRECTION
PERSONS
WHEN THE TRIKE UNIT
KILLED.
SEPARATED FROM THE WING
AND FELL ALMOST
VERTICALLY TO THE
GROUND. BOTH OCCUPANTS
WERE KILLED. IT APPEARS
THAT THE 'AIRCRAFT MAY
HAVE SUFFERED A
WHIPSTALL AND DURING THE
SUBSEQUENT PULL OUT
MANOEUVRE THE TRIKE
SEPARATED. THE RECOVERY
FROM A WHIPSTALL
INVOLVES SEVERE NEGATIVE
Fatal
C of A /
Permit to
Fly
Structural
Failure
Type
1 Unknown
Pilot induced
2 Unknown
Pilot induced
-5-
Occurrence
Number
Date
Aircraft
Aircraft
Type
Registration
198503697 22/10/1985 Gemini
Flash
G-MNEJ
Location
Middleton
Nature of Phase of
Flight
Flight
Private
Flight
Summary
Description
"G" FORCES BOTH DYNAMIC
AND AERODYNAMIC FOR
WHICH THE AIRCRAFT IS NOT
DESIGNED NOR STRESSED
TO COPE WITH. (AIB
BULLETIN 1/86)
CRASHED
THE TRIKE SEPARATED FROM
FROM HEIGHT. THE WING DURING FLIGHT
1 FATALITY.
AND FELL TO THE GROUND,
LANDING INVERTED. THE
PILOT DIED ON IMPACT.
DAMAGE TO THE AIRCRAFT
STRUCTURE WAS FOUND TO
BE CONSISTENT WITH INITIAL
FAILURE OF THE FRONT
STRUT, A PRIMARY
STRUCTURAL MEMBER, DUE
TO IMPACT BY THE LEFT
HAND END OF THE CONTROL
BAR, FOLLOWED BY FAILURE
OF THE MAST, WHICH WAS
UNABLE TO SUSTAIN THE
SUBSEQUENT HIGH BENDING
LOADS. IT IS KNOWN THAT
ON THE AFTERNOON OF THE
DAY OF THE ACCIDENT, THE
PILOT HAD INTENDED TO
CARRY OUT A PRACTICE
FLIGHT OF THE
MANOEUVRES REQUIRED TO
BE DEMONSTRATED DURING
THE QUALIFYING FLIGHT
TEST FOR THE ISSUE OF A
PPL (GROUP D). THIS
INCLUDES DEMONSTRATION
OF THE ABILITY TO RECOVER
FROM A STALL, BOTH IN
LEVEL FLIGHT AND WITH UP
TO 30 DEG OF BANK IN A
TURN. (AIB BULLETIN 4/86)
Fatal
C of A /
Permit to
Fly
1 Permit to
Fly
Structural
Failure
Type
Pilot induced
-6-
Occurrence
Number
Date
Aircraft
Aircraft
Type
Registration
198601876 18/06/1986 Lightning G-MMCH
Phase
II/Tri-Pacer
330
Location
Martin
Nature of Phase of
Flight
Flight
Private
Cruise
Summary
Description
A/C CRASHED THE AIRCRAFT WAS IN A LEFT
FOLLOWING
TURN OR HAD JUST ROLLED
APPARENT
OUT OF A TURN WHEN A
FAILURE OF A WIRE WAS SEEN TO DETACH
WING SUPPORT FROM THE RIGHT WING
WIRE. 1
AREA. THE RIGHT WING
KILLED.
FOLDED UPWARDS
FOLLOWED BY THE LEFT.
THE AIRCRAFT STRUCK THE
GROUND AT LOW FORWARD
SPEED & THE PILOT WAS
KILLED INSTANTLY.
EXAMINATION OF THE
WRECKAGE SHOWED THAT
BOTH FLYING WIRES HAD
FAILED DUE TO INCORRECT
SWAGING WHICH HAD
WEAKENED THE STRENGTH
OF THE CABLES.
METALLURGICAL INVSTN
SHOWED THAT NEARLY 90
PER CENT OF CABLE
STRANDS HAD FAILED OR
PARTIALLY FAILED IN SHEAR IE THE SWAGE FORMING
PROCESS HAD SEVERELY
DEGRADED CABLE
STRENGTH BEFORE CABLE
WAS INSTALLED ON A/C.
INITIAL REPORTS ALSO
INDICATE THAT AT THE TIME
OF THE ACCIDENT: 1. THE
PILOT WAS UNLICENSED
(EXPIRED 10/83), 2. THE A/C
WAS NOT CERTIFICATED (NO
RECORD OF ISSUE OF
PERMIT TO FLY/TEST OR
EXEMPTION FOR G-MMCH)
and 3. THE A/C HAD NOT BEEN
MAINTAINED ADEQUATELY.
Fatal
C of A /
Structural
Permit to
Failure
Fly
Type
1 None
Mechanical
-7-
Occurrence
Number
Date
Aircraft
Aircraft
Type
Registration
Location
198602783 27/08/1986 Gemini
Flash II
G-MNNF
Ashleworth
198603099 13/09/1986 Pegasus
Flash II
G-MNYY
Wombleton
Nature of Phase of
Flight
Flight
Summary
Description
A/C TYPE - SOUTHDOWN
LIGHTNING PHASE 2 WING
WITH ULTRASPORT
TRIPACER TRIKE.
Unknown Cruise
APPARENT
A/C CRASHED FROM 800-1000
WING
FT WHILE PRACTISING
COLLAPSE IN STALLS & CO-ORDINATED
FLIGHT. A/C
TURNS. WITNESS HEARD A
CRASHED TO LOUD 'BANG' AFTER WHICH
GROUND.
A/C SPIRALLED TO GROUND
COMPLETING SEVERAL
ROTATIONS BEFORE IMPACT.
PRELIM INVSTN FOUND
STRUCTURAL DAMAGE
CONSISTENT WITH TRIKE
UNIT FALLING ONTO RH WING
IN FLT. A/C MFTR
INVESTIGATING. (SEE ALSO
MAINAIR SPORTS ACCIDENT
REPORT 01SEP86). SEE ALSO
OCC 86/03099X - SIMILAR
ACCIDENT TO PEGASUS
FLASH 2 (COMMON WING
TYPE).
Test Flight Aerobatics WINGS FOLDED INITIAL WITNESS REPORTS
IN FLIGHT & A/C INDICATE THAT A/C WAS
SPIRALLED TO SEEN IN A STEEP BANK (90
GROUND.
DEG), THEN INVERTED
PILOT INJURED. SHORTLY BEFORE BOTH
WINGS APPEARED TO FOLD
UPWARDS. THE A/C
DROPPED APPROX 200 FT
THEN BEGAN TO ROTATE,
COMPLETING APPROX 10
ROTATIONS IN A RELATIVELY
SLOW DESCENT BEFORE
IMPACT. SEE ALSO OCC
86/02783B - SIMILAR
ACCIDENT TO GEMINI FLASH
2 (COMMON WING TYPE).
Fatal
C of A /
Permit to
Fly
Structural
Failure
Type
0 Permit to
Fly
Pilot induced
0 Unknown
Pilot induced
-8-
Occurrence
Number
Date
Aircraft
Aircraft
Type
Registration
Location
Nature of Phase of
Flight
Flight
198701990 08/08/1987 Gemini
Flash IIA
G-MTIA
N Waltham
Private
Flight
198801751 19/06/1988 Gemini
Flash
G-MMUF
Harlington
Private
Cruise
Summary
IN-FLIGHT
STRUCTURAL
FAILURE
DURING STEEP
TURNS. PILOT
KILLED.
Description
THE AIRCRAFT WAS SEEN TO
BE FLYING AT A HEIGHT OF
ABOUT 700 FEET
PERFORMING A TURN
THROUGH 360 DEGREES AT
OVER 60 DEGREES OF BANK
AND THEN BANKING STEEPLY
IN THE OPPOSITE DIRECTION.
THE OUTER END OF THE
LOWER WING FOLDED OVER
AND THE AIRCRAFT
SPIRALLED DOWN AND
CRASHED INTO THE
GROUND. THE PILOT WAS
KILLED BY THE IMPACT.
EXAMINATION SHOWED THAT
BOTH OUTER WING POLES
HAD FAILED IN DOWNLOAD
AND THAT MULTIPLE
AIRFRAME FAILURE HAD
RESULTED FROM NEGATIVE
LOADING. IT WAS NOT
POSSIBLE TO DETERMINE
THE PRECISE FAILURE
SEQUENCE DUE TO SEVERAL
CONTACTS BETWEEN THE
SAIL UNIT AND THE NACELLE.
TRIKE
THE A/C WAS CRUISING AT
SEPARATED
1,000 FT AGL WHEN IT MADE
FROM WING AT A GENTLE TURN TO AVOID AN
APPROX 1,000 ONCOMING MICROLIGHT.
FT. BOTH
DURING THIS TURN THE
OCCUPANTS
TRIKE & WING SEPARATED
KILLED.
WITH A LOUD BANG. BOTH
OCCUPANTS WERE KILLED
BY IMPACT WITH THE
GROUND. INVESTIGATION BY
AAIB REVEALED THAT AN
UNAUTHORISED
MODIFICATION TO THE
Fatal
C of A /
Structural
Permit to
Failure
Fly
Type
1 Permit to Pilot induced
Fly
2 Permit to
Fly
Mechanical
-9-
Occurrence
Number
Date
Aircraft
Aircraft
Type
Registration
Location
Nature of Phase of
Flight
Flight
198901303 24/04/1989 Gemini
Flash IIA
G-MTYZ
Balne
Test Flight Flight
198901451 07/05/1989 Gemini
Flash IIA
G-MTUW
Huddersfield
Test Flight Flight
Summary
Description
FRONT STRUT BOTTOM
SECTION ALTERED THE LOAD
PATHS WITHIN THE STRUT &
LED TO FAILURE OF AN
ALUMINIUM RIVET,
SEPARATION OF THE LOWER
STRUT & SECONDARY
OVERSTRESSING FAILURE OF
THE MAIN MONOPOLE
MEMBER. THE A/C
MANUFACTURER HAS ISSUED
SERVICE BULLETIN NR.29
DATED 27 JUN 1988 TO ALL
OWNERS DRAWING THEIR
ATTENTION TO THE
CORRECT PROCEDURES &
THE REQUIREMENT THAT
STRUCTURAL MODS OR
REPAIRS ARE CHECKED BY
APPROVED INSPECTORS.
IN-FLIGHT
THE A/C CRASHED DUE TO INSTRUCTURAL FLIGHT STRUCTURAL
FAILURE. A/C FAILURE WHICH WAS
CRASHED &
INDUCED BY DYNAMIC
DESTROYED. 2 OVERLOADING OF THE WING
FATALITIES.
IN DOWNLOAD. NOT
ESTABLISHED WHETHER THE
OVERLOADING WAS THE
RESULT OF AN INTENTIONAL
MANOEUVRE OR A LESSER
ONE WHICH WAS
UNCONTROLLABLE.
IN-FLIGHT
THE A/C CRASHED DUE TO
STRUCTURAL LOSS OF CONTROL
FAILURE AFTER FOLLOWING A POWER LOSS
WHIP STALL.
PROBABLY CAUSED BY FUEL
PILOT KILLED. STARVATION AT THE VERY
HIGH ANGLE OF CLIMB BEING
FLOWN. DURING THE
ATTEMPTED RECOVERY IT
Fatal
C of A /
Permit to
Fly
Structural
Failure
Type
2 Permit to
Fly
Pilot
induced?
1 Unknown
Pilot induced
- 10 -
Occurrence
Number
Date
Aircraft
Aircraft
Type
Registration
Location
Nature of Phase of
Flight
Flight
198901972 07/06/1989 Mainair
Razor
G-MVMS
Rochdale
Test Flight Flight
198902681 19/07/1989 Chaser S
G-MVLV
Hayling Island
Training
Flight
Summary
Description
SEEMS THE A/C
EXPERIENCED LOW OR
NEGATIVE 'G' WITH A
RESULTING FAILURE OF THE
WING STRUCTURE. THE
CONTROL LOADS AT ONE
STAGE WERE PROBABLY IN
EXCESS OF THE PHYSICAL
CAPABILITY OF THE PILOT.
A/C CRASHED THIS FLIGHT WAS A TEST
FROM
FLIGHT TO ASSESS THE
CONSIDERABLE STABILITY &
HEIGHT. PILOT MANOEUVRABILITY OF A
KILLED.
PROTOTYPE WING. AFTER
T/O IT CLIMBED TO APPROX
2,000 TO 2,500 FT AGL.
AFTER A LEFT TURN A SHARP
CRACK WAS HEARD, THE
WINGS WERE SEEN TO FOLD
& THE A/C DESCENDED "LIKE
A SYCAMORE LEAF" UNTIL IT
CRASHED. THE A/C
SUFFERED A STRUCTURAL
FAILURE IN FLIGHT BUT THE
AAIB WERE UNABLE TO
ESTABLISH THE EXACT
SEQUENCE NOR THE CAUSE.
THE DESIGN HAD NOT BEEN
FINALISED NOR CAA TYPE
APPROVAL GAINED. THE
PROJECT HAS BEEN
DISCONTINUED.
A/C WAS SEEN DURING SOLO GENERAL
TO CRASH INTO HANDLING EXERCISE, A/C
THE SEA FROM WAS SEEN TO ROCK, ENTER
APPROX 1,000 A SPIRAL DIVE & THEN THE
FT. PILOT
ENGINE NOISE STOPPED.
KILLED.
ONE WING FOLDED & THE A/C
CRASHED INTO THE SEA.
INVESTIGATION REVEALED
Fatal
C of A /
Permit to
Fly
Structural
Failure
Type
1 Unknown
Unknown
1 Permit to
Fly
Mechanical
- 11 -
Occurrence
Number
Date
Aircraft
Aircraft
Type
Registration
199201477 04/05/1992 Pegasus
XL-Q
G-MVCU
Location
Sunken Island
Nature of Phase of
Flight
Flight
Private
Cruise
Summary
Description
STRUCTURAL FAILURE TO
THE WINGS CAUSED BY
OVERLOAD DURING UNCONTROLLED FLIGHT OR
IMPACT. THERE WAS
EVIDENCE OF HEAVY ENGINE
VIBRATION & WING FABRIC
TEARS PRIOR TO IMPACT.
THESE WERE CONSISTENT
WITH BREAK-UP OF THE
PROPELLER IN FLIGHT. THE
CAUSE OF PROPELLER
FAILURE HAS NOT BEEN
ESTABLISHED. SEE AAIB
BULLETIN 12/89, REF:
EW/C1127. DESIGN
REQUIREMENTS (BCAR-S
PARA S905) AMENDED TO
REQUIRE CONSIDERATION
OF PROPELLER FAILURE
EFFECTS ON ADJACENT
STRUCTURE. APPROPRIATE
PUBLICITY GIVEN BY BMAA
ON THE LOOSE ARTICLE
HAZARD TO PUSHER
PROPELLERS.
A/C OBSERVED EYE-WITNESSES IN WEST
IN PITCHING
MERSEA OBSERVED A/C
MANOEUVRE, OVER LAND CARRYING OUT
THEN
TIGHT TURNS, STEEP CLIMB
CRASHED
MANOEUVRES & APPARENT
KILLING 2 POB. WHIPSTALLS. AFTER
WING FOUND CROSSING OVER THE SHORE
SOME
LINE & HEADING TOWARDS
DISTANCE
ESTUARY, THE WING
FROM REST OF SEPARATED FROM THE
WRECKAGE.
STRUCTURE & THE TRIKE,
WITH PILOT & PAX HELD INTO
IT BY THEIR RESTRAINING
HARNESSES, FELL ALMOST
Fatal
C of A /
Permit to
Fly
2 Permit to
Fly
Structural
Failure
Type
Pilot induced
- 12 -
Occurrence
Number
Date
Aircraft
Aircraft
Type
Registration
Location
Nature of Phase of
Flight
Flight
199501583 28/04/1995 Midland
G-MNFC
Ultralights
Sirocco
377GB
Near Bromyard
Private
Climb
199503731 31/08/1995 Mainair
Mercury
Near Sandtoft
Training
Cruise
G-MYGG
Summary
Description
VERTICALLY TO THE GROUND
FROM A HEIGHT OF SEVERAL
HUNDRED FEET. BOTH
OCCUPANTS DIED
INSTANTANEOUSLY. AAIB
INVSTGN ATTRIBUTES CAUSE
OF ACCIDENT TO RELATIVELY
INEXPERIENCED MICROLIGHT
PILOT WHO APPEARS TO
HAVE EXCEEDED THE
RECOMMENDED FLIGHT
LIMITATIONS & THEREBY
PRECIPITATED A
CATASTROPHIC IN-FLIGHT
STRUCTURAL FAILURE.
APPROPRIATE PUBLICITY
GIVEN BY BOTH THE CAA &
BMAA ON DANGERS OF
EXCEEDING AIRCRAFT
LIMITATIONS. SEE AAIB
BULLETIN 08/92, REF:
EW/C92/5/1.
A/c crashed
Loss of tailplane in flight probably
following
due to effect of repair and/or
structural failure modification to tailplane axle
of tailplane. 1
ends & locating rib. See AAIB
fatality.
Bulletin 09/95, ref: EW/C95/4/3.
A modification to the design of
the stabilator & mountings has
been produced & approved by
the BMAA under MAAN 1336.
CAA MPD 1999-005 requires
that this modification, or an
approved alternative, be
embodied before further flight.
Loss of control Student pilot, 32 hours total time,
led to airframe
was briefed to carry out solo
failure in flight. practice engine failure
Student pilot
procedures in local flying area.
killed.
A/c airborne for just over one
Fatal
C of A /
Permit to
Fly
Structural
Failure
Type
1 Permit to
Fly
Mechanical
1 Permit to
Fly
Pilot induced
- 13 -
Occurrence
Number
Date
Aircraft
Aircraft
Type
Registration
199602965 17/07/1996 Gemini
Flash IIA
G-MTLA
Location
Near Rhyl
Nature of Phase of
Flight
Flight
Test Flight Flight
Summary
Description
hour. No witnesses to final
manoeuvre, but had been
observed previously pitching
down hard to 45 deg nose down,
followed rapidly by pitch up to
about 10 deg nose up, then
continued normally, one km from
accident location. A/c was close
to minimum operating weight,
with empty fuel can positioned in
rear seat as backrest, instead of
usual approved ballast bag. The
can may have been improperly
secured & come loose during
manoeuvring, causing distraction
& loss of control which exceeded
a/c limitations. Both wing tips
failed in downward bending
(negative loading). Wing pitched
up hard causing front strut & 'A'
frame contact & failures.
Propeller blades then struck rear
keel. Monopole failed in rearward
bending. Trike unit separated
from wing & fell vertically from
about 500 ft agl. Wing spiralled
down & landed nearby. Fuel
can/backrest ejected during
break-up sequence. See AAIB
Bulletin 12/95.
Wings folded on The pilot had recently fitted a
test flight & a/c new propeller to his flex wing
fell from approx microlight, but had failed to
400 ft. 1 fatality. complete the necessary
paperwork or have the aircraft
officially checked before the next
flight. He made a solo flight and
the take off was observed as
normal. Later, as he flew back
towards the airfield, he was seen
Fatal
C of A /
Permit to
Fly
1 Permit to
Fly
Structural
Failure
Type
Pilot
induced?
- 14 -
Occurrence
Number
Date
Aircraft
Aircraft
Type
Registration
Location
Nature of Phase of
Flight
Flight
199606099 07/08/1996 Chaser S
508
G-MZBJ
Near Durban,
South Africa
Competition Flight
199705598 27/10/1997 Gemini
G-MVEP
Roydon
Training
Circuit
Summary
Description
to enter a tight turn which he
continued for approximately 540
deg. Towards the end of this
turn, witnesses heard a bang,
saw the left wing fold upwards
and saw the aircraft enter a
steep uncontrolled spiral which
continued until impact with the
ground. Towards the end of the
descent, the right wing was also
seen to fold upwards. The
aircraft manual includes a
warning not to fly into your own
wake. The propeller appeared to
operate correctly throughout the
flight. See AAIB Bulletin 01/97,
Ref: EW/C96/7/8.
A/c encountered During the World Microlight
severe
Championships, the pilot
turbulence &
experienced severe turbulence
broke-up in flight. whilst taking part in a thermalling
1 fatality.
(soaring) task & as a result the
a/c suffered an in-flight break-up,
due to the extreme forces
applied to the airframe structure.
The investigation report noted
that the washout adjustment tube
on the RH wingtip had been
loose prior to the accident & that
this may have affected stability &
control of the a/c in such adverse
weather conditions. The report
recommends that the a/c
manufacturer investigates the
reinforcing of the main spar &
down bars on the A-frame with
an inner tube. (South African
Dept of Transport AAR
J10/2/6585).
A/c spiralled into Student pilot was conducting a
Fatal
C of A /
Permit to
Fly
Structural
Failure
Type
1 Permit to
Fly
Turbulence
induced
1 Permit to
Turbulence
- 15 -
Occurrence
Number
Date
Aircraft
Aircraft
Type
Registration
Location
Nature of Phase of
Flight
Flight
Flash IIA
200400499 27/01/2004 Midland
G-MNDW
Ultralights
Sirocco
377GB
Summary
field after wings
folded in flight. 1
POB fatal. A/c
destroyed.
Ashby de la
Zouch
Private
Flight
Description
qualifying solo cross-country
flight for the award of a PPL.
Approximately 25 mins after take
off the a/c was observed by
witnesses who reported hearing
a sharp 'crack' & seeing the left
wing move up to an almost
vertical position. Shortly
afterwards the right wing did the
same & the a/c spiralled to the
ground with the wings folded
together. The pilot survived the
impact but died shortly
afterwards from his injuries. The
subsequent investigation was
inconclusive as to the cause of
the accident but it was noted that
there were heavy indentations on
the lower left hand side of the
keel, suggesting that a propeller
strike had occurred. Further
testing showed that the wing,
rigged as it was for the accident
flight, had characteristics that
could cause it to become
divergent in nose down pitch
through the actions of a vertical
gust of only 15kt. The onset of
this divergence would be
sufficiently rapid so as to
preclude any significant pilot
recovery response before the
manoeuvre became catastrophic.
See AAIB Bulletins 2/1998 and
5/2000.
Sirocco 377GB AAIB Bulletin 11/2004, ref:
microlight
EW/C2004/01/04 - Summary:
crashed and was The aircraft experienced an indestroyed
flight structural failure of the
following an in- tailplane, which rendered it
Fatal
C of A /
Structural
Permit to
Failure
Fly
Type
Fly
induced?
1 Permit to
Fly
Mechanical
- 16 -
Occurrence
Number
Date
Aircraft
Aircraft
Type
Registration
Location
Nature of Phase of
Flight
Flight
Summary
Description
C of A /
Permit to
Fly
Structural
Failure
Type
flight structural
failure of the
tailplane. 1 POB
fatal.
200405798 21/08/2004 Pegasus
Quik
G-STYX
Eastchurch
Private
Flight
uncontrollable. This is the
second such occurrence within
the United Kingdom. Following a
previous fatal accident in 1995
(occurrence 199501583), UK
Sirocco aircraft were modified to
address concerns over the
design of the tailplane and its
attachments. Although these
modifications had been
accomplished on G-MNDW, the
tailplane failed in flight through
loss of structural integrity and in
a similar manner. The
investigation identified
shortcomings in the method of
accomplishment of the
modifications and raised further
concerns over the design and
construction of the tailplane and
its mountings. One Safety
Recommendation (2004-76) was
made to the British Microlight
Aircraft Association (BMAA).
Pegasus Quik
AAIB Aircraft Accident Report
microlight
2/2005 - Summary: The Pegasus
suffered
Quik microlight, with an instructor
structural failure and passenger on board,
in-flight, leading departed Rochester Airfield for a
to loss of control trial lesson. Thirty five minutes
and trike
into the flight, as it was flying at
separation. 2
500ft along the north coast of the
POB fatal.
Isle of Sheppey, it pitched up
steeply to the near vertical and
entered a series of tumbling
manoeuvres. As the microlight
tumbled, the trike unit, containing
the two occupants, separated
from the wing and descended
vertically to the ground. Neither
Fatal
2 Permit to
Fly
Mechanical
- 17 -
Occurrence
Number
Date
Aircraft
Aircraft
Type
Registration
Location
Nature of Phase of
Flight
Flight
Summary
Description
Fatal
C of A /
Permit to
Fly
Structural
Failure
Type
the pilot nor his passenger
survived the impact. The
initiation of the pitching moment
and subsequent entry into the
tumbling sequence was brought
about by the failure of the right
upright upper fitting, which
caused full nose-up trim to be
suddenly applied. Some time
previously the microlight's
uprights upper fittings had been
modified to comply with Service
Bulletin 116 requiring the fitting
of additional rivets.
The additional rivets were not
only fitted incorrectly, and without
reference to the Service Bulletin,
but two of them did not match the
specification of those rivets
supplied by the manufacturer in
the modification kit. Additionally,
no duplicate independent
inspection was carried out on the
correct embodiment of the
modification. The investigation
identified the following causal
factors: 1) Failure of the right
upright upper fitting caused the
microlight to enter a tumble
manoeuvre from which it was not
possible to recover; 2) Service
Bulletin 116, which introduced
additional rivets in the upper
fitting, was not correctly
embodied. Eleven Safety
Recommendations (2004-080, 081 and 2005-082 to -090) have
been made as a result of the
investigation.
- 18 -
Ex-Military Aeroplanes
No such occurrences involving ex-military aeroplanes.
- 19 -