Glen,
There is a AD on 1340 cylinder cracking, but it has nothing to do with a prop strike. It is thermal stresses causing the cracking. The cylinders are under enormous strain at take off. Tho blower is cramming air into the cylinders and increasing the pressure beyone what the cylinder in say a Lycoming would ever see. One reason the 1340 has developed cracking is due to the populariaty of the engine with crop dusters. They used them hard, and the 1340 cylinders that were on the market had been rebuilt untold number of times, and none of the rebuilds ever included stress relieving of the heads. There are now new build cylinders on the market as well as Aircraft cylinder and Turbines 1340 hybrid cylinder that used 1340 barrels and R-2000 heads.
The cracks either go around the cylinder head from spark plug bushing to spark plug bushing. Like this one did, it failed on take off
it was #3 cylinder, I replaced it with a NOS cylinder.
The other cracking location is over the top of the head. I have seen these go from a small crack, to taking the whole side of the head off.
Here is the AD
99-11-02 Pratt & Whitney: Amendment 39-11173. Docket 97-ANE-58-AD.
Applicability: Pratt & Whitney (PW) R-1340 series reciprocating engines including Wasp S1H1, S1H1-G, S1H2, S1H4, S1H5-G, S3H2, R-1340-61 under Type Certificate E-129, Wasp S3H1-G, R-1340-59 under Type Certificate E-142, and also Wasp S3H1 under Type Certificate E-143. These engines are installed on but not limited to the following aircraft: de Havilland DHC-3, Air Tractor AT-301, and Ag Cat Corporation G-164A.
Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding Applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
Compliance: Required as indicated, unless accomplished previously.
To prevent cylinder head cracking, which can result in engine power loss, forced landing, and damage to the aircraft, accomplish the following:
(a) Perform initial and repetitive visual inspections of cylinders for head cracking, and replace cracked cylinders with serviceable parts, in accordance with PW Service Bulletin (SB) No. 1787, dated September 7, 1983, as follows:
(1) For cowled and baffled installations, as follows:
(i) Perform the initial visual inspection within 125 hours time-in-service (TIS) after the effective date of this AD.
(ii) Thereafter, visually inspect at intervals not to exceed 250 hours TIS since last inspection.
(2) For all other installations, as follows:
(i) Perform the initial visual inspection within 50 hours TIS after the effective date of this AD.
(ii) Thereafter, visually inspect at intervals not to exceed 100 hours TIS since last inspection.
(b) At the next cylinder overhaul after the effective date of this AD, and at each subsequent overhaul, perform a fluorescent penetrant inspection (FPI) of cylinders for head cracking, and replace cracked cylinders with serviceable parts, in accordance with PW SB No. 1787, dated September 7, 1983.
(c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. Operators shall submit their request through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office.
Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office.
(d) The actions required by this AD shall be done in accordance with the following PW SB:
Document No Pages Date
1787 1-4 September 7, 1983
Total Pages: 4.
This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Pratt & Whitney, Publications Department, Supervisor Technical Publications Distribution, M/S 132-30, 400 Main Street, East Hartford, CT 06108; telephone (860)565-7700 (860)565-7700 , fax (860)565-4503. Copies may be inspected at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street NW, suite 700, Washington, DC.
(e) This amendment becomes effective on July 19, 1999.
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