| AD Number | 60-08-05 | Status | Active |
| Effective Date | May 19, 1971 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-1210 |
| Product Type | ["Engine"] | Product Subtype | Not specified |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Curtiss-Wright/Marquette, Inc. |
| Model(s) | Double Row Turbo Cyclone 972TC18DA1 (R-3350-34, -91) Double Row Turbo Cyclone 972TC18DA2 Double Row Turbo Cyclone 972TC18DA3 Double Row Turbo Cyclone 972TC18DA4 Double Row Turbo Cyclone 981TC18EA1 Double Row Turbo Cyclone 988TC18EA1 Double Row Turbo Cyclone 988TC18EA2 Double Row Turbo Cyclone 988TC18EA3 Double Row Turbo Cyclone 988TC18EA4 Double Row Turbo Cyclone 988TC18EA5 Double Row Turbo Cyclone 988TC18EA6 |
60-08-05 WRIGHT: Amdt. 126 Part 507 Federal Register April 9, 1960, as amended by Amendment 39- 1210. Applies to all TC18DA and TC18EA Series Engines.
Compliance required as indicated.
(a) To insure that the proper PRT cooling shield to wheel lip clearance is retained, this clearance must be checked at the next regular periodic inspection after May 15, 1960, and every 100 hours time in service thereafter. The maximum service limit for this clearance is 0.080 inch with the wheel in the outermost position and must be checked at the four support bolt locations. In addition to this clearance check, the turbine wheel and turbine shaft nut must be checked for security by attempting to wobble these components by hand. Any looseness is an indication that the nut or shaft has been overheated. If this condition is found, the PRT must be removed for overhaul prior to next flight.
(b) At the next overhaul of PRT components after May 15, 1960, and every such overhaul thereafter, dimensional control will be maintained such that a maximum of 0.040-inch wheel to cooling shield clearance with the wheel to cooling shield clearance with the wheel in the outermost position will not be exceeded when the components are assembled. (WAD Service Bulletins Nos. TC18-323 and TC18E-140 cover the above items.)
(c) To provide an adequate supply of PRT cooling air under critical engine operating conditions, the aircraft in which these engines are operated should not be climbed at air speeds below the all engine en route climb speed as shown in the FAA approved Flight Manual. It is recognized that under certain unusual conditions, this air speed limitation cannot be adhered to and as a result, the PRT units may be subjected to overheat operation. So that appropriate precautionary measures can be taken when such operation is experienced the flight crew must record in the aircraft log whenever the aircraft is operated below the all engine en route climb speed for periodsin excess of three (3) minutes with the engines operating in high impeller gear ratio at or above alternate climb power. When such operation is reported the No. 2 PRT on each engine must be inspected per item (a) at the first stop where adequate maintenance facilities are available.
(d) To further insure PRT cooling cap integrity, a cooling shield security check, with flight hood installed, must be accomplished at 50 hours after every inspection required in paragraph (a). This interval should be as close to the mid-periodic inspection point as practical. This check will be accomplished by individually attempting to move both the intermediate and outer cooling shield outlets. Any relative movement will be cause for flight hood removal and further investigation of the condition of the cooling cap and the security of the PRT wheel and shaft nut.
(e) Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, Eastern Region, may adjust the inspection intervals.
This supersedes and cancels item (6) of AD 58-13-05.
This amendment 39-1210 is effective May 19, 1971.