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. (2) UK IMPORTER: N/A

(3) CERTIFICATION: BCAR Section S, Advance Issue March 1983 BCAR Section S, Paper, 11 October 1988 (4) DEFINITION OF 440 Dual Master List of Drawings, Issue 7 BASIC STANDARD: Flash Wing Master Drawing List, Issue 6

(5) COMPLIANCE WITH THE MICROLIGHT DEFINITION

(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 (503) 333kg (litres / kg) (426) 341 kg (582) 343 kg (h) ZFW + 86 kg pilot + full fuel (503) 264 Kg [279 kg ( litres / 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 Designation Engine Type Rotax 503 Rotax 503 Rotax 503 Rotax 462 Upright Rotax 462 Upright Rotax 462 Upright Upright Upright Upright Single Points Ign Single Points Ign Single Points Ign or Twin Electronic or Twin Electronic or Twin Electronic Ign. Ign. 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 Rotax Side Rotax Side Rotax Side Mount Rotax Side Mount Rotax Side Mount Mounted with After Mounted with After Mounted with After with After Muffler with After Muffler with After Muffler Muffler Muffler Muffler Intake System Rotax Intake Rotax Intake Rotax Intake Rotax Intake Rotax Intake Rotax Intake Silencer Silencer Silencer Silencer Silencer Silencer Propeller Type Mainair Mainair Grd Mainair WD Grd Mainair Round Tip Mainair Ground Mainair WD Grd. Adjustable Adj Adjustable Adjustable Propeller Dia x Pitch 62” x 40” 3 Blade 62” 3 Blade 62” 62” x 44” 3 Blade 62” 3 Blade 62” 107deg at 12” 113deg at 12” 107deg at 12” 113deg at 12” Noise Type Cert No. 26M 50M 50M 35m 35m 35m AAN approving 23105 23105 23105 23105 Ad 2 23105 Ad 2 23105 Ad 2 configuration

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MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)

NO: BM43 ISSUE: 10

Mercury 582 Mercury 582 Mercury 582 Designation Engine Type Rotax 582-2V Rotax 582-2V Rotax 582-2V Upright 40k Upright 40k Upright 40k Version Version Version Reduction Gear 2.58:1 2.58:1 3.47:1 Exhaust System Rotax Side Mount Rotax Side Mount Rotax Side Mount with After Muffler with After Muffler with After Muffler Intake System K & N Filter K & N Filter K & N Filter Propeller Type Mainair Grd Mainair WD Grd Mainair WD Grd Adjustable Adjustable Adjustable Propeller Dia x Pitch 3 Blade 62”Dia 3 Blade 62”Dia 4 Blade 62” Dia 112deg at 12”r 116deg at 12”r 125deg at 12” Noise Type Cert No. 149m 149m 134m AAN approving 23105 Ad 3 23105 Ad 3 23105 Ad 3 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 N/A (C) CG datum 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)

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MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)

NO: BM43 ISSUE: 10

(I) Power Plant See Table Engine Rotax 503 Rotax 462 Rotax 582-2V Upright Upright Upright (40kw) Max RPM 6800 6800 6400 MAX CHT 250 degC 150 degC 150 degC MAX EGT 650 degC 650 degC 650 degC Fuel Spec 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. Engine Oil Spec Two Stroke Oil Two Stroke Oil Two Stroke Oil ASTM/CEC ASTM/CEC ASTM/CEC Standards, API- Standards, API- Standards, API- TC TC TC Classification Classification Classification Gearbox oil spec API-GL5 or API-GL5 or API-GL5 or GL6, SAE 140 GL6, SAE 140 GL6, SAE 140 EP EP 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

(8) INSTRUMENTS REQUIRED:

ASI Altimeter RPM CHT / Compass Coolant Fuel VSI Slip ball EGT temp Pressure Required Required Required N/A N/A N/A N/A N/A N/A (to 90 (Twin mph Ign Only) min.)

TADS BM43 Issue 10 Page 5 of 13 CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP

MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)

NO: BM43 ISSUE: 10

(9) CONTROL DEFLECTIONS: N/A

Elevator UP: ± Tailplane trim UP: ± Elevator DOWN: ± Tailplane trim DOWN ± Ailerons* UP: ± Rudder LEFT: ± Ailerons* Down: ± Rudder RIGHT: ±

(10) 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.

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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

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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 Description Modification Number

7 Rear Seat Steering 16 Front Strut Back Up Wire 18 Transit yoke 45 Boss Ballast Bag 50 Overrider Instructor Bar 65 Rotax wiring connector 66 Dual Electronic Ignition 68 Hand throttle lever 69 Wiring for points ignition 71 Alpha wing base bar moved 2” 73 Trailing link front suspension and brake 90 Clear Fuel Filter 99 65 Litre Fuel Tank 187 Increase Seat Load Limit to 110kg

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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 370KG MIN. ALL UP WEIGHT 240KG EMPTY WEIGHT 149KG STALL SPEED 28MPH NEVER EXCEED (V.N.E.) 89MPH MIN LANDING APPROACH 42MPH MAX CROSS WIND 10MPH REC. ENGINE EGT 650 DEGC REC ENGINE CHT 150 DEGC REC. WATER TEMP 80DEGC REC. ENGINE MAX 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)

Empty Wt Kg Date Fuel Load Max Cockpit (litres) Wt (kg) 65 55 45 35 25 15 5

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MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)

NO: BM43 ISSUE: 10

(c) Fuel Capacity and Type (to be located near to filler cap)

FUEL - 22 LITRES FUEL - 65 LITRES EN228 UNLEADED or AVGAS 100LL EN228 UNLEADED or AVGAS 100LL INSPECT INTERNAL AND EXTERNAL INSPECT INTERNAL AND EXTERNAL FILTERS FREQUENTLY FILTERS FREQUENTLY

2 STROKE OIL MIX AT RATIO 50:1 2 STROKE OIL MIX AT RATIO 50:1

(d) Switches

All switches are to be marked with function and sense (up = on, down = off)

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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

Compliance/Action 3. If the inspection in paragraph 1 reveals damage to the webbing, Cont: 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. 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 E-mail: [email protected]

Mandatory Permit Directive 2016-008-E 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. Aircraft Type

BM2 Gemini Sprint BM43 Mainair Mercury BM3 Tri-Flyer Sprint BM44 Pegasus Quasar 2 TC BM4 Gemini Flash BM45 Cyclone AX3//503 BM5 Panther XL-S BM46 Pegasus Quantum 15 (Rotax 2-stroke engines) BM9 Pegasus XL-R BM47 Mainair Blade BM10 Pegasus Flash BM50 Pegasus Quantum 15-912 BM17 Pegasus Flash 2 BM51 Mainair Blade 912 BM14 Gemini Flash 2 BM53 Cyclone AX2000 BM16 Scorcher BM54 Mainair Rapier BM17 Pegasus Flash 2 BM56 Pegasus Quantum 15-HKS BM23 Gemini Flash 2 Alpha BM60 Mainair Blade 912S BM25 Pegasus XL-Q BM65 Flight Design CT2K (rudder control) BM27 Chaser S BM66 Pegasus Quik BM28 Pegasus Photon BM70 Quik GT450 BM31 Chaser S 1000 BM72 Flight Design CTSW (rudder control) BM33 Chaser S 508 BM77 QuikR BM37 Chaser S 447 BM80 Quik GTR BM38 Pegasus Quasar BM81 PulsR BM42 Pegasus Quasar – TC BM83 Flight Design CTSL (rudder control)

Mandatory Permit Directive 2016-011 Page 1 of 2

Civil Aviation Authority Mandatory Permit Directive SARG

Reason: 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 P & M Aviation Ltd Service Bulletin Number 144, Issue 3, dated Publications: 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 Civil Aviation Authority EMERGENCY MANDATORY PERMIT DIRECTIVE

Number: 2017-004-E Issue date: 15 May 2017

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: Rigging Cables with Roll Swaged End Terminals – Inspection / Replacement

Manufacturer: P&M Aviation Ltd

Applicability: All Microlights of the following types where P & M Aviation Ltd are the Type Approval Holder:

TADS No. Aircraft Type

BM4 Gemini Flash BM10 Pegasus Flash BM14 Gemini Flash 2 BM16 Scorcher BM17 Pegasus Flash 2 BM23 Gemini Flash 2 Alpha BM43 Mainair Mercury BM47 Mainair Blade BM51 Mainair Blade 912 BM54 Mainair Rapier BM60 Mainair Blade 912S BM70 Quik GT450 BM77 QuikR BM80 Quik GTR PulsR BM81

Mandatory Permit Directive 2017-004-E Page 1 of 3

Civil Aviation Authority Mandatory Permit Directive Safety and Airspace Regulation Group

Reason: A P&M Quik GT450 in a flying school had a partial failure of a lower side rigging cable (Part No. YQD-045) when recovering from a spiral manoeuvre, within the limits of the flight envelope. These cables are arranged in pairs, to give a backup load path. The second cable carried the load and the aircraft landed safely. This is the only recorded lower side cable failure since 1984. The partial failure was at the edge of the roll swaged terminal end. The alternative cable terminations using Nicopress sleeves and thimbles allow more progressive flexing of the cable.

The incident Quik GT450 lower side rigging cables had been in use for 1050 hours and 9 years. The aircraft had been subject to an accident and rebuilt once in its life. It was also operated quite near the coast where it is probable that sea air chlorides could have affected the material. There were corrosion pits in the S316 stainless steel material which accelerate fatigue failures. CLSCC (Chloride Stress Corrosion Cracking) is known to affect stainless steel.

The cable fitting was at the bottom end of the cable, where solutions can wick down it and collect. The strand failures were caused by bending and tensile fatigue because of cracks propagating from scratches and corrosion pits on the surface.

All the remaining cables had broken strands at the edge of the roll swaged terminals. Some of these strands had been failed for some time, as shown by discolouration of the failure surfaces. The cable is 7 cores of 7 strands construction.

Failure of a lower rigging cable would potentially reduce the integrity of the wing and hazard the aircraft.

Effective Date: 15 May 2017

Mandatory Permit Directive 2017-004-E Page 2 of 3 Civil Aviation Authority Mandatory Permit Directive Safety and Airspace Regulation Group

Compliance/Action: Compliance is required as follows, unless previously accomplished:

1. Before further flight, for lower side, front and rear rigging cables with roll swaged terminal ends with more than 750 flying hours or 7 years of service, whichever comes first, visually inspect at the edge of the roll-swaged terminal(s) using a magnifying glass with a power of at least 3x. Inspect closely for damage i.e. broken strands, corrosion, mechanical damage or slippage. If any damage is found, replace the affected cable before further flight. If no damage is found, replace the cable within 25 flying hours. See paragraphs 1 and 2 of P & M Aviation Ltd Service Bulletin 147 including the warning in paragraph 2.

2. Within 25 flying hours, for lower side, front and rear rigging cables with roll swaged terminal ends with less than 750 flying hours and less than 7 years of service, visually inspect at the edge of the roll- swaged terminal(s) using a magnifying glass with a power of at least 3x. Inspect closely for damage i.e. broken strands, corrosion, mechanical damage or slippage. If any damage is found, replace the affected cable before further flight. If no damage is found, replace the cable at 750 flying hours or 7 years of service, whichever comes first. See paragraphs 1 and 2 of P & M Aviation Ltd Service Bulletin 147 including the warning in paragraph 2.

3. Removal and replacement of any airframe structural cable requires a duplicate inspection - see paragraph 3 of P & M Aviation Ltd Service Bulletin 147.

4. Record the inspection from paragraph 1 or paragraph 2 and any necessary rectification action in the aircraft technical log in accordance with paragraph 3 of P & M Aviation Ltd Service Bulletin 147.

5. Repeat the inspection in paragraph 2 at each Permit to Fly revalidation and replace damaged cables as necessary. Replace the cables at 750 flying hours or 7 years of service, whichever comes first.

ENSURE COMPLIANCE WITH THIS MPD IS RECORDED IN THE AIRCRAFT LOGBOOK

Reference P & M Aviation Ltd Service Bulletin Number 147 Issue 1 dated 10 May 2017 Publications:

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 2017-004-E Page 3 of 3