Airworthiness directives › 2005-17-19
AD 2005-17-19 Airworthiness Directives; Cirrus Design Corporation Models SR20 and SR22 Airplanes
Makes named: cirrus. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
(c) This AD affects the following airplane models and serial numbers that are certificated in any category: Model Serial Nos. (1) SR20 1005 through 1455. (2) SR22 0002 through 1044.
Required actions
(e) To address this problem, you must do the following: Actions Compliance Procedures (1) For Models SR20, serial numbers 1005 through 1423, and SR22, serial numbers 0002 through 0972, do the following actions: (i) Move the lower portion of the crew seat upholstery upward to expose the seat frame and locking mechanism. Measure the clearance between the break-over bolt and the seat frame for a clearance that meets the requirements in the service bulletin (ii) If the clearance does not meet that specified in the service bulletin, do the crew seat break-over bolt adjustment and re-cover the crew seat frame and locking mechanism with the upholstery (iii) If the clearance does meet that specified in the service bulletin, re-cover the crew seat frame and locking mechanism (iv) Repeat the above actions for the opposite crew seat Within 50 hours time-in-service (TIS) or within 180 days, whichever occurs first after October 13, 2005 (the effective date of this AD) Follow Cirrus Design Corporation Alert Service Bulletin SB A2X-25-08, dated June 22, 2004. (2) For Models SR20, serial numbers 1005 through 1455, and SR22, serial numbers 0002 through 1044, do the following actions: (i) Identify whether the recline lock is secured with two bolts or three bolts (ii) If the recline locks are secured with two bolts, remove the existing recline locks and replace with the new recline locks kit, kit number 70084-001 (iii) If the recline locks are secured with three bolts, remove existing recline locks and replace with the new recline locks kit, kit number 70084-002 (iv) Check break-over pin alignment and adjust as necessary (v) Check that the locks engage with the break-over bolts with the seat in the full recline position. If full seat recline is not possible or difficult to engage, grinding of the lower aft seat frame is necessary (vi) Repeat the above actions for the opposite crew seat Within 50 hours TIS or within 180 days, whichever occurs first after October 13, 2005 (the effect9ve date of this AD) Follow Cirrus Design Corporation Service Bulletin SB 2X-25-06 R4, revised May 5, 2005.
Unsafe condition
(d) This AD is the result of discovering that the crew seats, under emergency landing dynamic loads, may fold forward at less than 26 g required by the regulations, 14 Code of Federal Regulations (CFR) Section 23.562(b)(2). The actions specified in this AD are intended to prevent the crew seats from folding forward during emergency landing dynamic loads with consequent occupant injury.
Affected ADs
(b) None.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1