Applicable to Luscombe 8, 8A, 8B, 8C, 8D, 8E, 8F and T–8F aircraft.
Compliance is required with FAA AD 96–24–17R1 as amended and expanded by this Directive, not later than 12 months from the effective date of this Directive, which is 10 September 2001. The inspection required by this Directive must be repeated at intervals not exceeding 12 months.
Inspect the wings, (and if necessary modify in accordance with the manufacturer’s approved data), to ensure that the access provisions are in accordance with:
Luscombe Drawings 082138 and SK082138 for fabric-covered wings; or Part (a) of FAA AD 96–24–17R1 for metal-covered wings.
Using these, and other available access points, inspect the wing spars and, if applicable, the metal wing skins for corrosion. Inspect the fittings mounted on the spars for any indication of corrosion between the mating surfaces or of the fasteners.
The alternative inspection procedures defined by the Appendix to FAA AD 96–24–
17R1 are NOT an acceptable means of compliance with this Directive as applied to UK-registered aircraft. Inspect the horizontal tailplane externally for signs of corrosion, including loose or damaged rivets, or deformation of the skin panels. Remove any readily detachable tailplane fairings and inspect the internal structure of the tailplane for corrosion to the extent permitted by the available access.
If any indications of corrosion are found, investigate further by dis-assembly as necessary, and replace or repair all affected parts. Such replacement or repair must be approved under the applicable UK airworthiness procedures.
30 November 2009
Section 2 Part 1, Miles M14A Page 1
UK National Airworthiness Directives previously published in CAP 476 – Mandatory Aircraft Modifications and Inspections Summary
CAA AD No: 2783 PRE 80 Associated Material: 2
Description: Introduction of fork end in lieu of eye end for flap ram attachment.
Applicability – Compliance – Requirement:
-CAA AD No: 2784 PRE 80 Associated Material: 12
Description: Strengthening of parallel motion link assembly on the rudder bar.
Applicability – Compliance – Requirement:
-CAA AD No: 2785 PRE 80 Associated Material: 14
Description: Introduction of anti-spinning strakes.
Applicability – Compliance – Requirement:
-CAA AD No: 2786 PRE 80 Associated Material: 26
Description: To prevent control fouling between seat and elevator control.
Applicability – Compliance – Requirement:
-CAA AD No: 2787 PRE 80 Associated Material: 35
Description: Introduction of steel sleeves on the throttle rods.
Applicability – Compliance – Requirement:
-CAA AD No: 2788 PRE 80 Associated Material: 36
Description: Introduction of improved attachment of spats.
Applicability – Compliance – Requirement
Not applicable when Mod. No. 116 (deletion of wheel spats and undercarriage oleo leg fairings) is embodied.
30 November 2009
Section 2 Part 1, Miles M14A Page 2
Description: Positive fixing of control column rudder grip.
Applicability – Compliance – Requirement:
-CAA AD No: 2790 PRE 80 Associated Material: 53
Description: Introduction of high aspect ratio rudder.
Applicability – Compliance – Requirement:
-CAA AD No: 2791 PRE 80 Associated Material: 58
Description: Introduction of markings on fuel cock handle.
Applicability – Compliance – Requirement:
-CAA AD No: 2792 PRE 80 Associated Material: 108
Description: Strengthening of rudder pedals.
Applicability – Compliance – Requirement:
-CAA AD No: 2793 PRE 80 Associated Material: 468
Description: Introduction of modification to fuel cock to prevent ‘all tanks on’ being selected.
Applicability – Compliance – Requirement:
-30 November 2009
Section 2 Part 1, Miles M38 Page 1
UK National Airworthiness Directives previously published in CAP 476 – Mandatory Aircraft Modifications and Inspections Summary
CAA AD No: 2706 PRE 80 Associated Material: 72
Description: To fireproof all necessary pipes forward of the fireproof bulkhead.
Applicability – Compliance – Requirement Applicable to Marks 2, 2A, 3, 4, 4A and 5.
CAA AD No: 2707 PRE 80 Associated Material: 134
Description: To introduce laminated safety glass or Perspex in cabin doors.
Applicability – Compliance – Requirement Applicable to Marks 2, 2A, 3, 4, 4A and 5.
CAA AD No: 2708 PRE 80 Associated Material: 153A
Description: To introduce improvements in the venting and draining of fuel tanks.
Applicability – Compliance – Requirement Applicable to Marks 2, 2A, 3, 4, 4A and 5.
CAA AD No: 2709 PRE 80 Associated Material: 240B
Description: To introduce an endless chain to operate the flap jack and an additional support.
Applicability – Compliance – Requirement
Applicable to Marks 2, 2A and 3 only. Complementary to Mod. No. 351. Not applicable to aircraft equipped with bucket type seats.
CAA AD No: 2710 PRE 80 Associated Material: 313
Description: To strengthen the lift flap bell crank levers.
Applicability – Compliance – Requirement
Applicable to Marks 2, 2A, 3, 4, 4A and 5. Essential only when Mod. No. 104 (to introduce a footstep into the flap) is embodied.
30 November 2009
Section 2 Part 1, Miles M38 Page 2
Description: To provide a guard on the flap operating chain pulley under the front seat.
Applicability – Compliance – Requirement
Applicable to Marks 2, 2A and 3 only. Complementary to Mod. No. 240B. Not applicable to aircraft equipped with bucket type seats.
CAA AD No: 2712 PRE 80 Associated Material: 363
Description: To reinforce the rear windows.
Part A – To reinforce the window.
Part B – To fit external metal frame.
Applicability – Compliance – Requirement
Applicable to Marks 2, 2A and 3 only. Essential for Part A or Part B only to be fitted.
CAA AD No: 2713 PRE 80 Associated Material: 368
Description: Part A –To provide a guard for the aileron torque shaft (forward end).
Part B – To fit a leather sleeve.
Applicability – Compliance – Requirement
Applicable to Marks 2, 2A, 3 and 4. Essential for Part A or Part B only to be fitted. Not applicable to three seater aircraft.
CAA AD No: 2714 PRE 80 Associated Material: 405A
Description: To prevent crossing of battery connection.
Applicability – Compliance – Requirement
Applicable to Marks 2, 2A, 3 and 4. Essential for aircraft with 24 volt electrical system only.
CAA AD No: 2715 PRE 80 Associated Material: 406
Description: To prevent crossing of battery connections.
Applicability – Compliance – Requirement
Applicable to Marks 2, 2A, 3 and 4. Essential for aircraft with 12 volt electrical system only.
30 November 2009
Section 2 Part 1, Miles M38 Page 3
Description: To delete the cabin door jettison gear.
Applicability – Compliance – Requirement Applicable to Marks 4A and 5.
CAA AD No: 2717 PRE 80 Associated Material: 434
Description: To reinforce the tailplane front false spar attachments to the tailplane root ribs.
Applicability – Compliance – Requirement
Applicable to all Marks. To be carried out in accordance with Handley Page (Reading) Ltd, Service Instruction Messenger/7.
CAA AD No: 2718 PRE 80 Associated Material: 462
Description: Introduction of starter isolation switch.
Applicability – Compliance – Requirement Applicable to all Marks.
CAA AD No: 2719 PRE 80 Associated Material: 465
Description: Replacement of plastic rudder bar parallel motion links by metal.
Applicability – Compliance – Requirement
Applicable to all Marks. To be carried out in accordance with Handley Page (Reading) Ltd, Service Instruction Messenger/13.
CAA AD No: 2720 PRE 80 Associated Material: 467
Description: Drilling of fuel tank filler caps, and alterations to vent and drain pipes.
Applicability – Compliance – Requirement
Applicable to all Marks. To be carried out in accordance with Handley Page (Reading) Ltd, Service Instruction Messenger/14.
CAA AD No: 2721 PRE 80 Associated Material: 1/13
Description: To reposition the fuel drain pipe in the engine bay.
Applicability – Compliance – Requirement Applicable to Mark 4A.
30 November 2009
Section 2 Part 1, Miles M38 Page 4
Description: To increase the size of the cable connections at the trim tabs.
Applicability – Compliance – Requirement Applicable to Marks 4A and 5.
CAA AD No: 2723 PRE 80 Associated Material: 1/40
Description: To strengthen Rib 4 at undercarriage attachment.
Applicability – Compliance – Requirement Applicable to Marks 4A and 5.
CAA AD No: 2724 PRE 80 Associated Material: 1/71
Description: To strengthen the nose cowl leg.
Applicability – Compliance – Requirement Applicable to Mark 4A.
CAA AD No: 2725 PRE 80 Associated Material: 1/80
Description: Screws for attachment of elevator hinge block.
Applicability – Compliance – Requirement Applicable to Marks 4A and 5.
CAA AD No: 2726 PRE 80 Associated Material: R&W 036
Description: Introduction of strengthened fork ends to flap jacks.
Applicability – Compliance – Requirement
To be carried out in accordance with Western Manufacturing (Reading) Limited Service Instruction Messenger/17. Any one of the following approved Modification is acceptable:
Simpson’s Aeroservices Mod. SA/M 20 – replacement for original faulty Acme thread fork ends.
Simpson’s Aeroservices Mod. SA/M 21 – replacement for original faulty square thread fork ends.
30 November 2009
Section 2 Part 1, Miles M38 Page 5
Description: Inspection and rework of the flap jack mounting (Pt. No: 3838262) on the rear face of Frame 7.
Applicability – Compliance – Requirement
To be carried out in accordance with Handley Page (Reading) Ltd, Service Instruction Messenger/8.
CAA AD No: 2728 PRE 80 Associated Material: –
Description: Inspection of vent and drain connections on fuel tanks at periods of flying time not exceeding 150 hours.
Applicability – Compliance – Requirement
To be carried out in accordance with Handley Page (Reading) Ltd, Service Instruction Messenger/15.
CAA AD No: 2729 PRE 80 Associated Material: –
Description: Inspection of rudder bar pedals to ensure correct assembly and prevent fouling.
Applicability – Compliance – Requirement
To be carried out in accordance with Handley Page (Reading) Ltd, Service Instruction Messenger/16.
CAA AD No: 2730 PRE 80 Associated Material: –
Description: Inspection of Aileron Outer Hinge Bearing Housing.
Applicability – Compliance – Requirement
Western Manufacturing (Reading) Ltd, Service Instruction Messenger/18 refers.
30 November 2009
Section 2 Part 1, Miles M65 Page 1
UK National Airworthiness Directives previously published in CAP 476 – Mandatory Aircraft Modifications and Inspections Summary
CAA AD No: 2681 PRE 80 Associated Material: 153
Description: To improve the venting and draining of fuel tanks.
Applicability – Compliance – Requirement:
-CAA AD No: 2682 PRE 80 Associated Material: 240B
Description: To introduce an endless chain to operate the flap jack and an additional support.
Applicability – Compliance – Requirement
Complementary to Mod. No. 351. Not applicable to aircraft equipped with bucket type seats.
CAA AD No: 2683 PRE 80 Associated Material: 313
Description: To strengthen the lift flap bell crank levers.
Applicability – Compliance – Requirement
Essential only when Mod. No. 104 (to introduce a footstep into the flap) is embodied.
CAA AD No: 2684 PRE 80 Associated Material: 328
Description: Introduction of copper contacts in lieu of beryllium copper to prevent fusing of starter switch contacts.
Applicability – Compliance – Requirement
To be carried out in accordance with Handley Page (Reading) Limited, Service Instruction Gemini/15.
CAA AD No: 2685 PRE 80 Associated Material: 343
Description: Provision for positive locking of bolts at rear engine to the engine bearer.
Applicability – Compliance – Requirement Not applicable to Mark 3A or 3B.
30 November 2009
Section 2 Part 1, Miles M65 Page 2
Description: To provide a guard on the flap control chain pulley under the front seats.
Applicability – Compliance – Requirement
Complementary to Mod. No. 240B. Not applicable to aircraft equipped with bucket type seats.
CAA AD No: 2687 PRE 80 Associated Material: 363
Description: To reinforce the rear windows.
Part A – To reinforce the windows.
Part B – To fit external metal frame.
Applicability – Compliance – Requirement Essential for Part A or Part B only to be fitted.
CAA AD No: 2688 PRE 80 Associated Material: 368
Description: Part A – To provide a guard for the aileron torque shaft.
Part B – To fit leather sleeve.
Applicability – Compliance – Requirement Essential for Part A or Part B only to be fitted.
CAA AD No: 2689 PRE 80 Associated Material: 405
Description: To prevent crossing of battery connections.
Applicability – Compliance – Requirement:
-CAA AD No: 2690 PRE 80 Associated Material: 432B
Description: To be carried out in accordance with Handley Page (Reading) Limited, Service Instruction Gemini/9.
Applicability – Compliance – Requirement
To reinforce the engine nacelle structure at the front support brackets.
30 November 2009