Engines Flashcards
When is the torque check on the high speed shaft due for the No. 1 Engine on Aircraft 09265 if maintenance was completed at 2134.5?
2147.5 Aircraft Hours
d.IF TORQUE ON ANY BOLT IS BELOW 130 INCH-POUNDS, RETORQUE TO 130 - 140 INCH-POUNDS. Repeat torque check after each 3 to 13 flight hours until torque stabilizes. e.If torque does not stabilize after third consecutive torque check, replace engine output shaft assembly connecting hardware and flange coupling. Perform engine output shaft balance testing (WP 0354).
Under the modular maintenance concept the engine is divided into what modules?
Under the modular maintenance concept, the turboshaftengineis divided into fourmodules:
● Accessory Section Module (Accessory Gearbox)
● Cold Section Module (Compressor Section)
● Hot Section Module (Combustion Section)
● Power Turbine Module (Power Turbine)
How are DECU/EDECU fault codes cleared after they have been corrected?
DECU, PNs 5086T83P03/4082T99G09 will display a 95% (±3%) fault code in the cockpit if test A and test B buttons are pressed repeatedly when the DECU is powered up by the APU generator or ground power cart and the main engines are off-line. This DECU response will not affect flight safety, nor will it affect the function of the DECU. The fault codes can be cleared by running the engine at 100% Np speed. DECU, PNs 5086T83P05/ 4082T99G12 will display a 95% (±3%) fault code in the cockpit if test A and test B buttons are pressed repeatedly when the DECU is powered up by the APU generator or ground power cart and the main engines are off-line. This DECU response will not affect flight safety, nor will it affect the function of the DECU. The fault codes can be cleared by running the engine at 100% Np speed. DECU, PNs 6068T56P06/5078T29G05 will display a 95% (±3%) fault code if the OVSP TEST switches are pressed repeatedly to clear DECU fault codes when the engine is not operating. This fault will be cleared during the next start after the starter has dropped off. This DECU response will not affect flight safety, nor will it affect the function of the DECU. DECU, PNs 6068T56P07/5078T29G06 will display a 95% (±3%) fault code if the OVSP TEST switches are pressed repeatedly to clear DECU fault codes when the engine is not operating. This fault will be cleared during the next start after the starter has dropped off. This DECU response will not affect flight safety, nor will it affect the function of the DECU. The fault codes can be suppressed by depressing either one of the engine overspeed test buttons. The fault codes can also be recalled by again depressing either one of the overspeed test buttons. Any fault code that appeared on the engine torque indicator should be recorded on form 2408-13. Refer to WP 0008 for the appropriate troubleshooting procedure. If the problem has been corrected, the fault code will be cleared. To verify the fixes following corrective action, it is required to operate the engine at flight idle. If the problem has not been corrected, the fault code will again flash on the engine torque indicator when the above conditions are met.
What events are cause for engine sudden stoppage removal and inspection?
● A high deceleration rotor incident resulting in removal of the main transmission, input modules, and/or nose gearboxes.
● The event caused damage to engine mounts or attaching hardware.
● The event caused unusual noise or rubs.
What checks must be performed an engine is re-installed? WP0698
40.Check engine oil level and service as required (WP 0220).
42.Perform operational cowlingheck of IVHMS (WP 0131).
43.Perform engine output shaft balance testing (WP 0354).
44.Perform the following: a.Run up engine for at least 10 minutes. Let engine cool down for one hour minimum. b.Perform a torque check of the deswirl duct loop clamp nuts. TORQUE SHOULD BE 35 - 40 INCH-POUNDS. If torque is below limit, repeat Step 39a. Torque stripes to be used only on loop clamp, 70300-30800-102.
46.Perform engine checkout procedure as part of maintenance operation check/maintenance test flight (TM 1-2840-248-23&P).
48.Perform a maintenance test flight (TM 1-1520-280-MTF).
What are the four modules of the turbo shaft engine?
Cold section module, Hot section module, Power turbine module, Accessory section module.
What are the oil sumps contained within the engine, and what bearings do they contain?
A sump – bearings 1, 2, 3 B sump – bearing 4 C sump – bearings 5, 6
What does the T701D incorporate on the internal engine components to improve the heat tolerance of those components?
Thermal Barrier Coating (TBC)
What component provides torque matching and how does it accomplish that?
DEC – by increasing the NP reference on the low torque engine
What connects the compressor section to the accessory gearbox?
PTO bevel gear through the radial drive shaft assembly.
What do the inlet swirl vanes do?
Swirls the air and throws heavy particles out to the particle separator blower.
Locate the two borescope port locations on the left side of the engine?
Compressor casing, 8:00 o’clock position (compressor aft) Ignitor port, 8:00 o’clock position (combustion section)
What is the max vibe allowed for the high speed shaft? At what vibe level must the shaft be replaced?
.5 IPS
2.0 IPS
If you have 3 stuck balance screws in the H/S shaft how many more balance screws can be installed?
3
After reconnecting the high speed shaft, what is the maximum time the aircraft can fly before performing a high speed shaft re-torque?
13 Hours (3-13hr TQ Check)
