R2000 Service Manual 

Alpha Aviation ltd 

Section 3: Airworthiness Limitations, Time 

lLimits, & Maintenance Hnspections 

This section describes the Time Limits, Routine Inspections and Unscheduled Inspections required 

to ensure the applicable aircrart remains in an airworthy state throughout its' life. Instructions 

concerning the repair, or replacement of components found unserviceable during inspection, will be 

found In the sections corresponding to the particular systems. 

3.2 Airworthiness Limitations 

The following table identifies the lime limits and Inspection Interval set by Alpha Aviation 

M;mufacturlng Ltd for the R2000 series aircraft. 

The following limitations are approved by the Civil Aviation Authority of New Zealand and may not 

be changed without Airworthiness Authority approval. 

Item 

Airframe All R2000 

series 

Lateral Stability 

Springs 

Life Limitation and Inspection 

2000 hours 

CAANZ Approved: _ _ _ _ __ -\- --' ..,_~:,.....::" 

3.3 Recommended 

Applicability 

All 

R2120U 

-7 AUG 2015 

Because of the great variation between operators and the manner in which the aircraft is 

maintained, consideration should be given to reduction {or increasing) of the stated TBO's. In these 

cases application should be made to your local Airworthiness Authority for approval. 

Item Maintenance Action Applicability 

Engine Refer to latest issue of Textron Lycoming All Service Instruction 1009 

Propeller Refer to latest issue of Sensenich Service All Bulletin R-17 

ELTBattery Replacement date on unit Where fitted 

Seat Bells 12 vr reol:ace All 

3.4 Specific, non periodic checks 

3.4.1 

Issued: Aug ~t 2015 

Engine after 25 hours Initial operation 

After the first 25 hours operation Ume, new, remanufactured or newly overhauled 

engines should undergo a 50 hour Inspection including draining and renewing 

lubrication oil. These engines should be operated on slralght mineral oil for a minimum 

of 50 hours or until oll consumption has stabilized. 

Refer to the latest Issue of the Textron-Lycoming Service Instruction No. 1014. 

Paga 3-1 
3.4.6 

3.4.7 

3.4.8 

3.4.9 

Issued: August 2015 

R2000 Service Manual 

Alpha Avialio;.;. n .;:;. Lt;.;;d _ ______ _ 

Powerplant 

1 Carefully check engine mount and attachment to the firewall structure 

2 Check battery support and firewall surrounding attachment. 

3 Check state of piping, lines, cables, flexible lines, engine controls. 

Inspection after flight in turbulence or when the load 

factor has been exceeded 

Thoroughly check all surfaces (fuselage, wings, tail unit) 

1 Check all rivets (sheared, loose) 

2 Check panels and fairings (possible distortion, wrinkling) 

3 Check tail unit attachment points 

4 Check engine attachment points 

5 Ensure that all controls are free to move fully 

6 Check canopy guide rails 

7 Carry out a complete rigging and asymmetry check 

Engine inspection follow ing propeller impact 

Refer to Textron Lycoming Service Bulletin 553A (or latest revision). 

Inspection after exposure to high and gusty wind 

conditions 

This cannot be considered as a true flight case but it is normally included in specific, 

non periodic checks. 

Landing gears 

1 Check legs for distortion, cracks. Check state of axles. 

2 Check leg/wing and leg/fuselage attachment points 

3 Check state of tyros 

Flight controls 

1 Ensure that flight controls are froe to move fully, Check cables where in contact 

with pulleys. Check pulley attachment points 

2 Check flight control stops 

3 Check all bellcranks 

4 Check flight control surfaces deflection angles 

Wing 3500 hr Inspection 

On reaching 3500 hou·rs the wings shall be removed from the fuselage and the 

following inspections carried out. 

Record location of each bolt on removal. 

2 Carry out inspection of internal wing structure and main, front and rear wing 

attachment fittings. Use optical aids as necessary to ensure complete 

inspection. 

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R2000 Service Manual 

Alpha Aviation Ltd - -------

3 Carry out a Visible Dye Penetrant inspection of the steel double plates on main 

spar to fuselage attachment fittings. Refer to diagram below for probable 

location of any cracking. Note this inspection may be carried out using Eddy 

Current equipment if appropriate instrument and trained personnel are 

available. Replace cracked plates. While plates are removed inspect under lying 

structure for cracks. Any failure found during these inspections must be notified 

to Alpha Aviation Manufacturing Ltd. 

4 Carry out a Fluorescent Magnetic Particle inspection of the front, main and rear 

spar attachment bolts. If no defects are detected the bolts may be refitted in 

their original location using new nuts. If one bolt fails inspection then all bolts 

must be replaced. 

5 Refit wing in accordance with instructions in Section 4. 

6 Initially torque bolts to 16 ft/lb (22Nm) for pre-load then torque to 22 ft/lb (30Nm) 

+3.5 fVIb (5Nm), -o . Note: Nuts and threads to be freo from Mastinox/grease. 

Repeat wing inspections at every 750 hours 

If bolts are replaced for any :reason they shall be inspected at 750 hour intervals in 

accordance with 3.4.9 (4). 

3.5 Inspection Schedule 

3.5.1 

·Issued: August 2015 

Terminology 

Flight Time 

Time taken from the moment the aircraft first moves for the purpose of flight, unlil the 

moment it comes to rest at the end of the flight. Includes taxiing and holding time. 

Time In Service 

Means, for maintenance records, tho elapse time from the aircraft leaving the surface 

until touching it again on landing. 

Routine Inspection 

Means, In relation to a scheduled inspection, a visual inspection of an aircraft and its 

components, systems and equipment as far as practical without disassembly. 

Detailed Inspection 

Means, in relation to a scheduled inspection, a thorough examination of an aircraft and 

its components, systems and equipment with such disassembly as necessary in order 

to detect defective parts which could lead to failure. 

VIsual Investigation or visual check 

It is one of the components of the above mentioned routine inspection. The aim is to 

ensure that a given clement Is in good serviceable condition. This inspection is carried 

out visually, •in situ'. 

Example: Search for cracks or corrosion 

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