Instructions for Continued Airworthiness

McFarlane Aviation, LLC. FAA-PMA Part Number MC14064-102 CABLE, MC14064-103 CABLE, MC14065-101 CABLE, MC27050-101 CABLE. FAA PMA Number: PQ3732CE Notice: Verify that this document is the latest approved revision before use! Current version of document can be found at: www.mcfarlaneaviation.com/ICA Page 4 of 7 McFarlane Drawing: 2297 Installation: Slide the rubber tube component of EC04 boot over the push rod and guide tube. Work the tube component of EC04 boot over the end of the conduit terminal. The tube is in correct position when one of its ends is flush with the mounting groove on the conduit terminal, as shown in Figure 4. Slide the spring clamp component of EC04 boot over the push rod and guide tube. Install the spring clamp on the transition in the tube between the conduit terminal and guide tube. The spring clamp should be over the guide tube, but as close to the conduit terminal as possible. Install P/N 235 boot per When the control is completely reinstalled, ensure the quadrant and appliance control arm have full travel. If not, rig control so full travel is achieved. Refer to applicable Cirrus Aircraft Maintenance Manual for rigging instructions. Figure 3: Correct and incorrect installed positions of P/N 235 boot Figure 4: Correct installed position of P/N EC04 boot Instructions for Continued Airworthiness McFarlane Aviation, LLC. FAA-PMA Part Number MC14064-102 CABLE, MC14064-103 CABLE, MC14065-101 CABLE, MC27050-101 CABLE. FAA PMA Number: PQ3732CE Notice: Verify that this document is the latest approved revision before use! Current version of document can be found at: www.mcfarlaneaviation.com/ICA Page 5 of 7 McFarlane Drawing: 2297 TROUBLESHOOTING Refer to the applicable Cirrus Model Service Manual for troubleshooting instructions and the applicable Cirrus Illustrated Parts Catalog for component part numbers. See document listings in Data section below. In case of excessive resistance route, including or . Additionally, separate and independently test the functionality of mating components per Cirrus publications to determine the root of the issue. Kinks in the conduit are typically a result of improper handling or incorrect routing. A control with a kinked safely operate the aircraft. Melted portions of the conduit jacket indicate incorrect routing in the vicinity of excessive heat. Controls with melted jackets are not airworthy. If the outer jacket has melted, the inner conduit liner may have melted as well, causing increased binding of the inner wire. Damage to the inner liner may reduce the capacity of the flight crew to safely operate the aircraft. Controls should not be routed in such proximity to hot components, like exhaust components and turbochargers, that the jacket melts. Consult the relevant Cirrus Aircraft Maintenance Manual for correct routing of the control. Oil on or near the ends of a control may be wicked inside it when the push rod is actuated. Exposed to heat and abrasion, oil inside the control may turn to varnish, causing binding in the control. If oil is noted in proximity to temporarily reduce its resistance to motion, but will not keep the absorbed oil from continuing to deteriorate the In case of a control which es when in extended position and pushed, check that the guide tube of the extended push rod is keeping the push rod aligned. If the guide tube is damaged such that the push rod is not aligning with and sliding through the guide tube (end has ceased circularity and become elliptical), the part is no longer airworthy. When troubleshooting, ensure control is rigged to achieve full travel of the appliance control lever and quadrant or mixture lever. See additional details on rigging in the Inspection section of this document, and the applicable Cirrus Aircraft Maintenance Manual. To report service difficulties or obtain further support for McFarlane parts, fill out the contact form available at the bottom of most pages of the website www.McFarlaneaviation.com, or call 1-800-544-8594 (within the US) or 1-785-594-2741. PLACARDS None applicable. DATA All information to support the continued airworthiness of this replacement part is as defined herein and contained in: Relevant Cirrus Model Service Manuals. o AIRPLANE MAINTENANCE MANUAL For the CIRRUS SR22 AND SR22T P/N 13773-001 Aircraft Serials 22-0002 thru 22-4434, Serials 22T-0001 thru 22T-1459, 22T-1461 thru 22T-1470, 22T-1472 o AIRPLANE MAINTENANCE MANUAL FOR THE CIRRUS SR22 AND SR22T P/N 13773-002 Aircraft Serials 22-4435 & Subsequent, Serials 22T-1460, 22T-1471, 22T-1473 & Subsequent Instructions for Continued Airworthiness McFarlane Aviation, LLC. FAA-PMA Part Number MC14064-102 CABLE, MC14064-103 CABLE, MC14065-101 CABLE, MC27050-101 CABLE. FAA PMA Number: PQ3732CE Notice: Verify that this document is the latest approved revision before use! Current version of document can be found at: www.mcfarlaneaviation.com/ICA Page 6 of 7 McFarlane Drawing: 2297 Cirrus Model Illustrated Parts Catalog. o ILLUSTRATED PARTS CATALOG For the CIRRUS SR22 AND SR22T P/N 13774-001 Aircraft Serials 22-0002 thru 22-4434, Serials 22T-0001 thru 22T-1459, 22T-1461 thru 22T-1470, 22T-1472 o ILLUSTRATED PARTS CATALOG FOR THE CIRRUS SR22 AND SR22T P/N 13774-002 Aircraft Serials 22-4435 & Subsequent, Serials 22T-1460, 22T-1471, 22T-1473 & Subsequent INSPECTION When inspecting the controls, check that each boot (P/N EC04, qty 2; P/N 235, qty 2) is intact and installed correctly, including the spring clamp component of P/N EC04. Correct installation is shown in Figure 2 Instructions for replacement of vibration damping boots A missing or damaged boot does not provide vibration damping to the control, which is critical for the service life of the control. If a boot is damaged or missing, ensure the swivel joint remains functional (rotates, swivels, push rod actuates) and replace the boot. Replacement parts 235 and EC04 are available for purchase from McFarlane Aviation. Directions for removing and reinstalling boots are provided in the Part Removal, Replacement, and Service Information section of this document. A swivel joint is functional if: o The push rod actuates smoothly, o The guide tube can rotate about its own axis (around the push rod), o The guide tube can deflect away from the primary axis of the attached conduit terminal in any direction, and o The guide tube is retained in the swivel joint, it does not fall out of the joint freely. When inspecting the controls: Ensure the control operates smoothly through its range of motion. This can be achieved by disconnecting both ends of the control and manually pushing and pulling it. If there is a portion of the travel experiencing excess Ensure the control is routed such that it does not chafe anywhere along the length of the conduit. If chafing is identified, confirm the control remains functional and airworthy, and adjust the routing of the control to avoid the chafing. E -throughs, rod end jam nuts, and conduit terminal bracket securements. Rigging Ensure the control is rigged to achieve full travel of the appliance control lever and quadrant or mixture control lever. Maximum and minimum positions should correspond between the appliance control levers and quadrant or mixture lever. If they do not, adjust the installed position of the rod ends and panel mounting jam nuts on the quadrant-side conduit terminal to achieve full travel of appliance control levers and quadrant or mixture control lever. Refer to the applicable Cirrus Model Service Manual for additional inspection instructions. Inspection intervals of the controls are not changed by this document. Instructions for Continued Airworthiness McFarlane Aviation, LLC. FAA-PMA Part Number MC14064-102 CABLE, MC14064-103 CABLE, MC14065-101 CABLE, MC27050-101 CABLE. FAA PMA Number: PQ3732CE Notice: Verify that this document is the latest approved revision before use! Current version of document can be found at: www.mcfarlaneaviation.com/ICA Page 7 of 7 McFarlane Drawing: 2297 RECOMMENDED OVERHAUL PERIODS No additional overhaul time limitations exist with the use of these parts. The McFarlane controls cannot be overhauled. If the control is rendered not airworthy, it must be replaced. AIRWORTHINESS LIMITATIONS The Airworthiness Limitations section is FAA approved and specifies maintenance required under Sec. 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. No additional airworthiness limitations exist. ASSISTANCE & REVISIONS ICA revisions shall be made available on the McFarlane website, www.mcfarlaneaviation.com/ICA. For questions or assistance regarding these Instructions for Continued Airworthiness (ICA), contact McFarlane Aviation, LLC. via email or phone. Email: engineering@mcfarlaneaviation.com Phone: 1-800-544-8594 (within the US) or 1-785-594-2741.