Preservation of an Engine for a Period of 30 to 365 days [CFML]

TASK 72-00-00-620-802-A
Preservation of an Engine for a Period of 30 to 365 days

WARNING: BEFORE YOU INSTALL/REMOVE THE GSE TOOL, READ THE MANUFACTURER'S INSTRUCTIONS, AND, WHILE YOU OPERATE THIS TOOL, CAREFULLY OBEY THEM. IF YOU DO NOT DO THIS, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

ZONE: 400

1. Reason for the Job
This procedure provide instructions to protect the engine for a period up to 365 days of storage including preservation of the oil and fuel systems.
These instructions are applicable only to power plants that are installed (on-wing). There are different instructions available from CFM that are used for engines that are not installed (off-wing).
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	AR	CAP - PROTECTION
No specific	1	CONTAINER-FUEL RESISTANT, TRANSPARENT PLASTIC
No specific	AR	COVER - PROTECTION
No specific	1	INDICATOR-HUMIDITY
956A1602	1	KIT PRESERVATION - LUBE AND FUEL SYSTEM
956A6635	1	COVER, STORAGE - ENGINE ASSY
956A7683	1	COVER, STORAGE - QUICK ENGINE CHANGE
98N1010H001-000	1	INLET COVER
98N1010H005-000	1	EXHAUST COVER

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.CP2098)	desiccant bags
(Material No.CP2160)	vapor barrier film
(Material No.CP2442)	Engine oil
(Material No.CP5066)	fuel system corrosion preventive oil
(Material No.CP5067)	lube system corrosion preventive oil
(Material No.CP5075)	corrosion preventive additive

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
400	POWER PLANT, NACELLES AND PYLONS

D. Expendable Parts

FIG.ITEM	DESIGNATION	IPC-CSN
1	GASKET	EIPC 73-11-46-02-060

E. Referenced Information

REFERENCE	DESIGNATION
TASK 12-13-79-610-805-A	Check of the Oil Level and Replenishing
TASK 12-13-79-610-806-A	Check of the Oil Level and Replenishing (Pressure Filling)
TASK 12-13-79-610-808-A	Draining of the Oil Tank
TASK 71-00-00-700-805-A	Dry-Motoring Check
TASK 73-11-05-000-801-A	Removal of the Main Fuel Pump
TASK 73-11-05-400-801-A	Installation of the Main Fuel Pump
TASK 73-29-00-710-803-A	Fuel System Preservation (Menu Mode)
TASK 75-31-10-210-801-A	Visual Inspection of the Variable Bleed Valve (VBV) Doors
Preservation of an Engine for a Period of 30 to 365 days

3. Job Set-up
Subtask 72-00-00-710-074-A

A. Not Applicable

4. Procedure

WARNING: USE PERSONAL PROTECTION EQUIPMENT. USE THE ENGINE OIL IN A WELL-VENTILATED AREA. ENGINE OIL IS TOXIC.

WARNING: BE CAREFUL WHEN YOU OPEN THE FUEL CIRCUIT BECAUSE THERE IS A RESIDUAL PRESSURE OF 207 KPA (30 PSIG) IN THE LINES. WEAR EYE PROTECTION AND GLOVES TO PREVENT PERSONAL INJURY.

CAUTION: IF ENGINE WAS FERRIED OR SUBJECTED TO AN IN-FLIGHT SHUTDOWN (IFSD), ENGINE MUST BE "DRIED OUT" AND RELUBRICATED WITHIN 24 HOURS PER DRY-OUT PROCEDURE OF THIS SECTION.

CAUTION: WHEN YOU DO THE ENGINE MOTORING PROCEDURE WITHOUT THE ACCESSORIES, MAKE SURE THAT:

THE PAD COVERS AND O-RINGS ARE INSTALLED ON THE PADS WHERE ACCESSORIES ARE NORMALLY INSTALLED,
THE CAPS ARE INSTALLED ON THE PAD CAVITY DRAINS TO PREVENT THE LOSS OF ENGINE OIL.

Subtask 72-00-00-620-080-A

A. Operable Engine Preservation on Wing (With Menu Mode)

WARNING: DO NOT PRESERVE THE FUEL NOZZLES WHEN THE WIND SPEED IS MORE THAN 13 KPH (8 MPH). IF YOU DO NOT OBEY THIS INSTRUCTION, PERSONNEL CAN BREATHE OR COME IN CONTACT WITH FUEL AND OIL MIST AND INJURY CAN OCCUR.

(1) Drain the oil tank (Ref. AMM TASK 12-13-79-610-808).
(2) Do the servicing of the oil tank (Ref. AMM TASK 12-13-79-610-805) or (Ref. AMM TASK 12-13-79-610-806) with a mixture of:
(a) Engine oil (Material No.CP2442) and seven percent (by volume) corrosion preventive additive (Material No.CP5075) or engine oil (Material No.CP2442) and five percent (by volume) lube system corrosion preventive oil (Material No.CP5067) .
(3) Connect the oil reservoir (IAS-2600-01) to the main fuel pump inlet:
(a) Drain the fuel pump before to disconnect the main fuel pump inlet fuel supply to avoid personal injury when disconnecting the main fuel pump hose (Ref. AMM TASK 73-11-05-000-801).
(b) Disconnect the aircraft main fuel supply hose from main fuel pump (if installed). Retain the gasket (1) (Ref. AMM TASK 73-11-05-000-801).
(c) Using the gasket (1), connect the oil reservoir (IAS-2600-01) of 956A1602 KIT PRESERVATION - LUBE AND FUEL SYSTEM filled up to maximum level 32 l (8.5 USgal) of fuel system corrosion preventive oil (Material No.CP5066) to the main fuel pump supply interface with hose (IAS-3110-01) (6). Refer to Table 1 for tooling description:
1 TORQUE the four bolts 115 lbf.in (1.30 m.daN).
(d) Put the cap on the main fuel pump supply hose with the retained gasket (1) (cap provided with preservation kit).
(e) Pressurize the oil reservoir (IAS-2600-01) as follow:
1 Close the main supply valve on the oil reservoir (IAS-2600-01).
2 Pressurize oil reservoir (IAS-2600-01) and set pressure between 20 psi (1.38 bar) and 25 psi (1.72 bar).

NOTE: Air must be clean, dry and regulated (CDR). Nitrogen supplied at the same pressure range is usable, if available, but it is not required.

NOTE: Alternative is to raise the tank higher than 3 ft. (0.91 m) above the fuel pump inlet.

(f) Open main supply valve on the reservoir tank.
(g) Open the supply valve of the main fuel pump supply interface with hose (IAS-3110-01) (6).
(h) Put a CONTAINER-FUEL RESISTANT, TRANSPARENT PLASTIC below the engine Low Pressure Turbine (LPT) drains to collect the fuel.

NOTE: The tooling does not include a fuel mist collector.

(i) Do the fuel system preservation menu mode (Ref. AMM TASK 73-29-00-710-803).

NOTE: Engine will be motored and preservation fluid sprayed through the engine exhaust.

(4) Remove remaining fuel or oil from the flow path as follows:
(a) Let the fuel drop from LPT for 15 minutes or until no fluid drops.
(b) Make sure that minimum 3.7 USgal (14.01 l) remains in the tank and the main supply valves on reservoir tank are opened.
(c) Dry motor the engine (Ref. AMM TASK 71-00-00-700-805) for two minutes to remove remaining fuel or oil from the flow path.

NOTE: Engine dry motoring is to be done with preservation kit in place instead of the aircraft fuel supply.

(d) Close main supply valve on reservoir tank.
(e) Pull the fan rotor through a minimum of two complete turns if it did not turn during motoring.
(f) Remove the temporary oil supply line from the fuel pump inlet.
(g) Reconnect the fuel tube to the main fuel pump inlet port using a new EIPC 73-11-46-02-060 GASKET (1) (Ref. AMM TASK 73-11-05-400-801):
1 For engine scheduled to be removed:
a Put a cap on the main fuel-pump inlet-port.
b TORQUE to maximum 115 lbf.in (1.30 m.daN).
(h) Install vapor barrier film (Material No.CP2160) on all open pipes and struts.
(i) Install the COVER - PROTECTION and CAP - PROTECTION on all open ports, open tubes, open hoses and connectors:

NOTE: Drain holes or tubes are not to be capped or covered.

1 Make sure that Variable Bleed Valve (VBV) doors are closed (Ref. AMM TASK 75-31-10-210-801).

CAUTION: IT IS NOT PERMITTED TO USE: - WHITE TESA 4651 TAPE - GREY TESA 4651 TAPE - YELLOW TESA 4651 TAPE - RED TESA 4651 TAPE - GREEN TESA 4651 TAPE - RED TAPE 3M 471. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE PARTS CAN OCCUR.

2 Cover VBV grids with vapor barrier film (Material No.CP2160) or with one of the following alternative VBV grids protections:

Blue tape 3M 471 (CP2109)
Blue, brown or black tesa 4651 tape (CP2158).

(j) Place desiccant bags (Material No.CP2098) with INDICATOR-HUMIDITY in inlet and exhaust of the engine to protect it from moisture as follows:

NOTE: Desiccant bags must be inspected or replaced at regular intervals depending on weather conditions. Make sure they are accessible for inspection or replacement while disturbing a minimum amount of protective material. Refer to Para. 5.A.:

1 Mark the date on the desiccant bags (Material No.CP2098) .
2 Attach the desiccant bags (Material No.CP2098) with INDICATOR-HUMIDITY in inlet and exhausts of the engine. Make sure they are not in contact with the engine hardware.
3 If necessary, use vapor barrier film (Material No.CP2160) to locally protect the engine hardware.
4 Seal inlet and exhaust of the engine with vapor barrier film (Material No.CP2160) to protect it from moisture.
5 For engine stored on wing, install the 98N1010H001-000 INLET COVER and the 98N1010H005-000 EXHAUST COVER. For engine removed and stored on shipping stand, install the 956A7683 COVER, STORAGE - QUICK ENGINE CHANGE or the 956A6635 COVER, STORAGE - ENGINE ASSY.
a If the engine inlet cover is not available, use barrier material (G00253), polyethylene film (G00252) or equivalent 6 MIL or thicker material, and tape (G00920).
b When using plastic sheeting to cover the inlet, do the steps that follow:

Use a lint-free cloth (CP2674) and solvent (B00666) to wipe the area where the tape will be used.
Cut approximately 70 in. (1.8 m) diameter circle from plastic sheet.
Tape the plastic circle on forward edge of the acoustic panel behind the lipskin. Apply with at least 3 layers of overlapping tape (G00920) around the perimeter of the inlet acoustic panel.

NOTE: Do not place plastic or tape over the lipskin or encase the lipskin with plastic.

Apply the tape (G00920) across the diameter of the circular sheet to reduce the pillowing of the plastic sheeting.

c If the engine exhaust cover is not available, use barrier material (G00253), polyethylene film (G00252) or equivalent 6 MIL or thicker material, and tape (G00920).

NOTE: When applying plastic sheeting and tape to the exhaust, make sure that the drain holes or tubes are not covered.

(k) Put a tag on the engine to show the engine is preserved.

5. Close-up
Subtask 72-00-00-620-082-A

A. Close-Up
(1) The best condition for engine storage is to keep an environment with less than 70% of humidity.

NOTE: This inspection procedure is to be done if desiccant bags (Material No.CP2098) and INDICATOR-HUMIDITY have been placed in the inlet and the exhaust of the engine.

(2) When you use desiccants, you must inspect and change them regularly as applicable. As an example, start monitoring of the desiccant bags (Material No.CP2098) as follow in order to determine the effective interval for desiccant bags (Material No.CP2098) replacement. A suggested schedule is as follows:
(a) Second day after beginning of storage period.
(b) Fourteenth day after beginning of storage period.
(c) Every three months after beginning of storage period.

NOTE: This inspection schedule must be adapted to specific environmental condition. If indication of important humidity or saturated desiccant bags (Material No.CP2098) is noted during inspection, consider reducing inspection interval and increasing quantity of desiccant bags (Material No.CP2098) .

(3) Remove the COVER - PROTECTION and CAP - PROTECTION cover and protective material as necessary to get access to INDICATOR-HUMIDITY.
(4) Do a check of the INDICATOR-HUMIDITY and desiccant bags (Material No.CP2098) condition. If necessary, do as follows:
(a) Open the plastic film cover.
(b) Remove, discard and replace desiccant bags (Material No.CP2098) and INDICATOR-HUMIDITY by new ones.
(c) Seal inlet and exhaust of the engine with vapor barrier film (Material No.CP2160) to protect it from moisture.
(d) Put COVER - PROTECTION and CAP - PROTECTION back in place.

[Rev.10 from 2021] 2026.04.01 02:50:28 UTC