CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP
MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM43 ISSUE: 10
TYPE:
Mainair Mercury
(1)
MANUFACTURER:
Mainair Sports Ltd now supported by P & M Aviation Ltd,
Unit B, Crawford Street Rochdale, Lancashire, OL16 5NU.
N/A
(2)
UK IMPORTER:
(3)
CERTIFICATION:
(4)
DEFINITION OF
BASIC STANDARD:
(5)
COMPLIANCE WITH THE MICROLIGHT DEFINITION
BCAR Section S, Advance Issue March 1983
BCAR Section S, Paper, 11 October 1988
440 Dual Master List of Drawings, Issue 7
Flash Wing Master Drawing List, Issue 6
(a) MTOW
370 kg
(b) No. Seats
2
(c) Maximum Wing Loading
23.78 kg/m²
(d) Vso
24 kts (25 mph)
(e) Permitted range of pilot weights
55 – 90 kg per seat.
(f) Typical Empty Weight (ZFW)
(Mercury 503) 146kg
(Mercury 462) 150kg
(Mercury 582) 153kg
(g) ZFW + 172 kg crew + 1 hr fuel
(litres / kg)
(503) 333kg
(426) 341 kg
(582) 343 kg
(h) ZFW + 86 kg pilot + full fuel
( litres / kg)
(503) 264 Kg [279 kg
with mod 99]
(462) 268kg [283 kg
with mod 99]
(582) 271 kg [286 kg
with mod 99]
(i) Max ZFW at initial permit issue
(503) 183 Kg
(462) 179 kg
(582) 180 kg
TADS BM43 Issue 10
Page 1 of 13
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP
MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM43 ISSUE: 10
(6)
POWER PLANTS
Mercury 503
Mercury 503
Mercury 503
Mercury 462
Mercury 462
Mercury 462
Rotax 503
Rotax 503
Rotax 503
Rotax 462 Upright
Rotax 462 Upright
Rotax 462 Upright
Upright
Upright
Upright
Single Points Ign
or Twin Electronic
Ign.
Single Points Ign
or Twin Electronic
Ign.
Single Points Ign
or Twin Electronic
Ign.
Reduction Gear
2.58:1
2.58:1
2.58:1
2.58:1
2.58:1
2.58:1
Exhaust System
Rotax Side
Mounted with After
Muffler
Rotax Side
Mounted with After
Muffler
Rotax Side
Mounted with After
Muffler
Rotax Side Mount
with After Muffler
Rotax Side Mount
with After Muffler
Rotax Side Mount
with After Muffler
Intake System
Rotax Intake
Silencer
Rotax Intake
Silencer
Rotax Intake
Silencer
Rotax Intake
Silencer
Rotax Intake
Silencer
Rotax Intake
Silencer
Propeller Type
Mainair
Mainair Grd
Adjustable
Mainair WD Grd
Adj
Mainair Round Tip
Mainair Ground
Adjustable
Mainair WD Grd.
Adjustable
Propeller Dia x Pitch
62” x 40”
3 Blade 62”
107deg at 12”
3 Blade 62”
113deg at 12”
62” x 44”
3 Blade 62”
107deg at 12”
3 Blade 62”
113deg at 12”
Noise Type Cert No.
26M
50M
50M
35m
35m
35m
23105
23105
23105
23105 Ad 2
23105 Ad 2
23105 Ad 2
Designation
Engine Type
AAN approving
configuration
TADS BM43 Issue 10
Page 2 of 13
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP
MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM43 ISSUE: 10
Mercury 582
Mercury 582
Mercury 582
Rotax 582-2V
Upright 40k
Version
Rotax 582-2V
Upright 40k
Version
Rotax 582-2V
Upright 40k
Version
Reduction Gear
2.58:1
2.58:1
3.47:1
Exhaust System
Rotax Side Mount
with After Muffler
Rotax Side Mount
with After Muffler
Rotax Side Mount
with After Muffler
Intake System
K & N Filter
K & N Filter
K & N Filter
Propeller Type
Mainair Grd
Adjustable
Mainair WD Grd
Adjustable
Mainair WD Grd
Adjustable
Propeller Dia x Pitch
3 Blade 62”Dia
112deg at 12”r
3 Blade 62”Dia
116deg at 12”r
4 Blade 62” Dia
125deg at 12”
Noise Type Cert No.
149m
149m
134m
23105 Ad 3
23105 Ad 3
23105 Ad 3
Designation
Engine Type
AAN approving
configuration
TADS BM43 Issue 10
Page 3 of 13
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP
MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM43 ISSUE: 10
(7)
MANDATORY LIMITATIONS:
(A) Max Take-Off Weight
370 Kg
(B) CG Limits
(C) CG datum
N/A
N/A
(D) Cockpit Loadings
Front
Rear
Total
Min 55kg
15 kg
70 kg
Max 90kg
90 kg
180 kg
(E) Never Exceed Speed
77 knots (89 mph)
(F) Manoeuvring Speed
38 knots (44 mph)
(G) Permitted Manoeuvres
30° Nose up / 30° nose down
60deg Max Bank Angle
Non Aerobatic
Normal acceleration limits, +4 / -2g
(H) Fuel Contents (Max Useable)
44 litres (22 litres Optional)
65 litres (Mod 99)
TADS BM43 Issue 10
Page 4 of 13
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP
MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM43 ISSUE: 10
(I)
Power Plant
See Table
Rotax 503
Upright
Rotax 462
Upright
Rotax 582-2V
Upright (40kw)
Max RPM
6800
6800
6400
MAX CHT
250 degC
150 degC
150 degC
MAX EGT
650 degC
650 degC
650 degC
Engine
83 MON or 90 RON minimum unleaded to
BS(EN)228 or 97+ octane 4-star /MOGAS leaded
fuel to BS 4040, or AVGAS 100LL.
Fuel Spec
(8)
Engine Oil Spec
Two Stroke Oil
ASTM/CEC
Standards, APITC
Classification
Two Stroke Oil
ASTM/CEC
Standards, APITC
Classification
Two Stroke Oil
ASTM/CEC
Standards, APITC
Classification
Gearbox oil spec
API-GL5 or
GL6, SAE 140
EP
API-GL5 or
GL6, SAE 140
EP
API-GL5 or
GL6, SAE 140
EP
Fuel/Oil Mix
50/1
50/1
50/1
Coolant Temperature
N/A
80 DegC
80 DegC
Oil Pressure
N/A
N/A
N/A
Oil Temperature
N/A
N/A
N/A
Fuel Pressure
N/A
N/A
N/A
INSTRUMENTS REQUIRED:
ASI
Altimeter
RPM
Required
(to 90
mph
min.)
Required
Required
(Twin
Ign Only)
TADS BM43 Issue 10
CHT /
EGT
N/A
Compass
N/A
Page 5 of 13
Coolant
temp
N/A
Fuel
Pressure
N/A
VSI
Slip ball
N/A
N/A
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP
MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM43 ISSUE: 10
(9) CONTROL DEFLECTIONS: N/A
Elevator UP:
Elevator DOWN:
Ailerons* UP:
Ailerons* Down:
(10)
±
±
±
±
Tailplane trim UP:
Tailplane trim DOWN
Rudder LEFT:
Rudder RIGHT:
±
±
±
±
PILOT'S NOTES, MAINTENANCE MANUALS REFERENCES:
10.1 Manuals approved for use with this aircraft.
(a) Mercury Microlight Manual Doc Ref ME Manual (at appropriate issue)
10.2 The following placards are to be fitted:(a) Flight Limitations Placard (to be visible to pilot)
See Annex D.
(b) Engine Limitations Placard (to be located near to engine instruments)
See Annex D.
(c) Fuel Limitations Placard (to be located near to filler cap)
A placard is to be fitted showing fuel capacity ( litres), fuel type(s), fuel:oil ratio (if
relevant) and if MTOW can be exceeded with full fuel and maximum cockpit weight,
the fuel loads at MTOW for cockpit weights An example is shown at Annex D.
(d)
Switches
See Annex D.
TADS BM43 Issue 10
Page 6 of 13
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP
MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM43 ISSUE: 10
(11)
MANDATORY MODIFICATIONS / SERVICE BULLETINS / AIRWORTHINESS
DIRECTIVES ETC:
CAA MPD 1995-021 Flight limitations
CAA MPD 2000-003 Inspection of wing rigging
CAA MPD 2001-004 Upper torso restraint
Annual Bettsometer test is to be carried out to 1050 grammes with wing sails fitted and
tensioned to flight. Test must be to both upper and lower surfaces.
(12)
MINIMUM PERFORMANCE AT MAX TAKE-OFF WEIGHT
Rate of Climb:
408 fpm at 47 mph.
Mercury 582 660 fpm at 47 mph
Stall or Minimum Flying Speed:
24kts (25mph) IAS at MTOW / idle.
TADS BM43 Issue 10
Page 7 of 13
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP
MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM43 ISSUE: 10
Issue History
Issue No.
Reason and signatory
1
__/09/91
Initial Issue
K D RUSSELL
2
__10/91
Introduce WD propeller and correction of editorial errors with initial
issue.
K D RUSSELL
3
__/02/92
Approval of Mod. 66 Dual Electronic Ignition Option
K D RUSSELL
4
__/12/93
Bank angle limitation to 60° (Service Bulletin No. 41 refers)
K D RUSSELL
5
__/06/94
Introduction of Rotax 462 and 582 engines with various propellers,
update optional modifications list and editorial corrections.
K D RUSSELL
6
__/07/94
Typographical corrections
K D RUSSELL
7
__/02/95
Approval of 582 engine/C Type Gearbox with Warp Drive Propeller
K D RUSSELL
8
08/07/02
Update using new format
J BARRATT
9
06/07/05
New company name
J BARRATT
10
18/11/09
To record Modification Number 187, which increases seat load limit to
110kg but still with a total cockpit load of 180g.
D S CORTIZO
TADS BM43 Issue 10
Page 8 of 13
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP
MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM43 ISSUE: 10
Illustration of Aircraft - 3 View
TADS BM43 Issue 10
Page 9 of 13
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP
MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM43 ISSUE: 10
ANNEX A – MANDATORY MODIFICATIONS
Modification 98
Shoulder Straps
ANNEX B - APPROVED OPTIONAL MODIFICATIONS
The installation of all optional modifications is to be inspected by a BMAA inspector and an
entry made in the appropriate logbook(s). Note that other approved modifications may exist
which are not listed here.
Mainair
Modification Number
Description
7
16
18
45
50
65
66
68
69
71
73
90
99
187
Rear Seat Steering
Front Strut Back Up Wire
Transit yoke
Boss Ballast Bag
Overrider Instructor Bar
Rotax wiring connector
Dual Electronic Ignition
Hand throttle lever
Wiring for points ignition
Alpha wing base bar moved 2”
Trailing link front suspension and brake
Clear Fuel Filter
65 Litre Fuel Tank
Increase Seat Load Limit to 110kg
TADS BM43 Issue 10
Page 10 of 13
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP
MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM43 ISSUE: 10
ANNEX C
WEIGHING INFORMATION
1. CG Datum:
N/A
2. Weighing attitude:
N/A
3. Mainwheel moment arm: N/A
4. Nosewheel moment arm: N/A ____ (units) (direction) of datum
5. Fuel moment arm:
N/A ____ (units) (direction) of datum
6. Crew moment arm:
N/A ____ (units) (direction) of datum
7. Crew weights:
Minimum 55 kg / maximum 90 kg
(maximum reducible, not below 86 kg, if required).
8. Aft CG Limit:
N/A ____ (units) (direction) of datum
9. Fwd CG Limit:
N/A ____ (units) (direction) of datum
TADS BM43 Issue 10
Page 11 of 13
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP
MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM43 ISSUE: 10
ANNEX D
EXAMPLE PLACARDS
(a)
Flight & Engine Limitations Placard (to be visible to pilot) [Typical Examples]
MAINAIR MERCURY
MAX. ALL UP WEIGHT
MIN. ALL UP WEIGHT
EMPTY WEIGHT
STALL SPEED
NEVER EXCEED (V.N.E.)
MIN LANDING APPROACH
MAX CROSS WIND
REC. ENGINE EGT
REC ENGINE CHT
REC. WATER TEMP
REC. ENGINE MAX
370KG
240KG
149KG
28MPH
89MPH
42MPH
10MPH
650 DEGC
150 DEGC
80DEGC
6800RPM
WARNING
THIS AIRCRAFT IS
NON-AEROBATIC
MAXIMUM NOSE UP 30DEG
MAXIMUM NOSE DOWN 30DEG
MAXIMUM BANK ANGLE 60DEG
SPINNING ATTEMPTS PROHIBITED
NO WHIPSTALLS LOOPS TAILSLIDES
OR AEROBATIC MANOEUVRES
DO NOT EXCEED MAX LOAD
(b)
Fuel Limitations Placard (to be visible to pilot)
Kg
Empty Wt
Date
Fuel Load
(litres)
65
55
45
35
25
15
5
TADS BM43 Issue 10
Max Cockpit
Wt (kg)
Page 12 of 13
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP
MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM43 ISSUE: 10
(c)
(d)
Fuel Capacity and Type (to be located near to filler cap)
FUEL - 22 LITRES
FUEL - 65 LITRES
EN228 UNLEADED or AVGAS 100LL
INSPECT INTERNAL AND EXTERNAL
FILTERS FREQUENTLY
EN228 UNLEADED or AVGAS 100LL
INSPECT INTERNAL AND EXTERNAL
FILTERS FREQUENTLY
2 STROKE OIL MIX AT RATIO 50:1
2 STROKE OIL MIX AT RATIO 50:1
Switches
All switches are to be marked with function and sense (up = on, down = off)
TADS BM43 Issue 10
Page 13 of 13
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Civil Aviation Authority
EMERGENCY
MANDATORY PERMIT DIRECTIVE
Number: 2016-008-E
Issue date: 3 October 2016
In accordance with Article 41(1) of The Air Navigation Order 2016, as amended, the following
action required by this Mandatory Permit Directive (MPD) is mandatory for applicable aircraft
registered in the United Kingdom operating on a UK CAA Permit to Fly.
Type Approval Holder’s Name:
Type/Model Designation(s):
P&M Aviation Ltd
Pegasus XL-Q variants, Pegasus Quasar variants,
Pegasus Quantum variants, Pegasus Quik, Quik, Quik
GT450, Quik Lite, Gemini Flash IIA, Mainair Blade
variants
Title:
Wing – Luff Line Attachment Webbing – Inspection
Manufacturer:
P&M Aviation Ltd
Applicability:
Pegasus XL-Q variants, Pegasus Quasar variants, Pegasus Quantum
variants, Pegasus Quik, Quik, Quik GT450, Quik Lite, Gemini Flash IIA,
Mainair Blade variants.
Reason:
The port inner luff line attachment webbing failed on a GT450 wing with
620 hours airtime during taxiing.
The polyester webbing loop had chafed against the chrome plated
brass eyelet. The webbing wear was visible from the top side, but not
from the underside of the sail.
A detached luff line is hazardous as it may go into the propeller. Pitch
stability in a steep dive or in turbulence would also be compromised.
It appears that the eyeleting process has been forming a ridge inside it
capable of damaging the webbing. New tooling has been introduced at
the Factory to prevent recurrence of the problem.
Effective Date:
3 October 2016
Compliance/Action:
Compliance is required as follows, unless previously accomplished:
1. Before further flight, inspect the luff line attachment webbings in
accordance with paragraph 2.1 of P & M Aviation Ltd Service
Bulletin 142. If there is no sign of damage to the webbing, the
aircraft may continue in service.
2. Before further flight, inspect the luff line attachment webbings in
accordance with paragraph 2.1 of P & M Aviation Ltd Service
Bulletin 142. If there is no sign of damage to the webbing, the
aircraft may continue in service.
Mandatory Permit Directive 2016-008-E
Page 1 of 2
Civil Aviation Authority Mandatory Permit Directive
SARG Airworthiness
3. If the inspection in paragraph 1 reveals damage to the webbing,
it must be replaced or a back–up load path installed in
accordance with paragraph 2.3 of P & M Aviation Ltd Service
Bulletin 142 before further flight.
Compliance/Action
Cont:
4. Record the inspection from paragraph 1 and any necessary
rectification action from paragraph 2 in the aircraft technical log
in accordance with paragraph 3 of P & M Aviation Ltd Service
Bulletin 142.
5. Repeat the actions in paragraphs 1 and 2 at 50 flight hour
intervals.
ENSURE COMPLIANCE WITH THIS MPD IS RECORDED IN THE AIRCRAFT LOGBOOK
Reference Publications:
P & M Aviation Ltd Service Bulletin Number 142 Issue 4 dated 23
September 2016
Remarks:
1.
This MPD was not posted for consultation because of the urgency
of the requirement.
2.
Enquiries regarding this Mandatory Permit Directive should be
referred to: GA Unit, Civil Aviation Authority, Safety and Airspace
Regulation Group, Aviation House, Gatwick Airport South, West
Sussex, RH6 0YR.
Tel: +44 (0)1293 573988
Mandatory Permit Directive 2016-008-E
E-mail: [email protected]
Page 2 of 2
Civil Aviation Authority
EMERGENCY
MANDATORY PERMIT DIRECTIVE
Number: 2016-011-E
Issue date: 23 November 2016
In accordance with Article 41(1) of The Air Navigation Order 2016, as amended, the following
action required by this Mandatory Permit Directive (MPD) is mandatory for applicable aircraft
registered in the United Kingdom operating on a UK CAA Permit to Fly.
Type Approval Holder’s Name:
Type/Model Designation(s):
P&M Aviation Ltd
Various, see below
Title:
Clevis Pin / Split Ring Installations – Inspection / Replacement
Manufacturer:
P&M Aviation Ltd
Applicability:
All Microlights where P & M Aviation Ltd is the Type Approval Holder:
TADS No. Aircraft Type
TADS No.
BM2
BM3
BM4
BM5
Gemini Sprint
Tri-Flyer Sprint
Gemini Flash
Panther XL-S
BM43
BM44
BM45
BM46
BM9
BM10
BM17
BM14
BM16
BM17
BM23
BM25
Pegasus XL-R
Pegasus Flash
Pegasus Flash 2
Gemini Flash 2
Scorcher
Pegasus Flash 2
Gemini Flash 2 Alpha
Pegasus XL-Q
BM47
BM50
BM51
BM53
BM54
BM56
BM60
BM65
BM27
BM28
BM31
Chaser S
Pegasus Photon
Chaser S 1000
BM66
BM70
BM72
BM33
BM37
BM38
BM42
Chaser S 508
Chaser S 447
Pegasus Quasar
Pegasus Quasar – TC
BM77
BM80
BM81
BM83
Mandatory Permit Directive 2016-011
Aircraft Type
Mainair Mercury
Pegasus Quasar 2 TC
Cyclone AX3//503
Pegasus Quantum 15
(Rotax 2-stroke engines)
Mainair Blade
Pegasus Quantum 15-912
Mainair Blade 912
Cyclone AX2000
Mainair Rapier
Pegasus Quantum 15-HKS
Mainair Blade 912S
Flight Design CT2K
(rudder control)
Pegasus Quik
Quik GT450
Flight Design CTSW
(rudder control)
QuikR
Quik GTR
PulsR
Flight Design CTSL
(rudder control)
Page 1 of 2
Civil Aviation Authority Mandatory Permit Directive
Reason:
SARG
Following maintenance, a clevis pin came out of the RP-4 roll trim system
pulley on a QuikR causing a left turn. The split ring securing the clevis pin
had come out. It is not known if the ring was disturbed during the
maintenance.
The split ring which came out was the same “spiral start” pattern as that
which has caused trouble before (see Service Bulletin 139). This pattern of
ring has no positive stop, so that simple rotation of the ring (e.g. caused by
it getting caught on something) will cause it to disengage.
Disengagement of the split ring and subsequent clevis pin departure could
affect the control of the aircraft.
Effective Date:
24 November 2016
Compliance/Action:
Compliance is required as follows, unless previously accomplished:
1. Before further flight, from the effective date of this MPD, inspect all
clevis pin / split ring installations on the aircraft in accordance with
paragraph 2 of P & M Aviation Ltd Service Bulletin 144.
2. If the inspection in paragraph 1 reveals any spiral start pattern split
rings they must be replaced in accordance with paragraph 2 of P &
M Aviation Ltd Service Bulletin 144 before further flight.
3. Record the inspection from paragraph 1 and any necessary
rectification action from paragraph 2 in the aircraft technical log in
accordance with paragraph 3 of P & M Aviation Ltd Service Bulletin
144.
4. Repeat the actions in paragraphs 1, 2 and 3 at each Permit to Fly
revalidation.
ENSURE COMPLIANCE WITH THIS MPD IS RECORDED IN THE AIRCRAFT LOGBOOK
Reference
Publications:
P & M Aviation Ltd Service Bulletin Number 144, Issue 3, dated
27 October 2016.
Remarks:
1.
This MPD was not posted for consultation because of the urgency of
the requirement.
2.
Enquiries regarding this Mandatory Permit Directive should be referred
to: GA Unit, Civil Aviation Authority, Safety and Airspace Regulation
Group, Aviation House, Gatwick Airport South, West Sussex, RH6 0YR.
Tel: +44 (0)1293 573988
E-mail: [email protected]
Mandatory Permit Directive 2016-011
Page 2 of 2