TASK CARD ATA 12

CHAPTER 12 − SERVICING

LIST OF EFFECTIVE PAGES

MAINTENANCE TASK CARD MANUAL

Jun 20/05Master

List of Effective Pages

Task TaskCard Page Date Card Page Date

Effective Pages 1* Jun 20/052* Jun 20/053* Jun 20/05

Table of Contents 1* Jun 20/052* Jun 20/053* Jun 20/05

000−12−120−001 1 Sep 30/042 Sep 30/04

000−12−120−701 1* Jun 20/052* Jun 20/053* Jun 20/054* Jun 20/055* DELETED6* DELETED

000−12−120−702 1* Jun 20/052* Jun 20/053* Jun 20/054* Jun 20/05

000−12−160−700 1* Jun 20/052* Jun 20/053* Jun 20/05

000−12−160−701 1* Jun 20/052* Jun 20/053* Jun 20/05

000−12−220−001 1 Sep 30/042 Sep 30/043 Sep 30/04

000−12−310−001 1 Sep 30/042 Sep 30/04

000−12−320−120 1* Jun 20/052* Jun 20/053* Jun 20/054* Jun 20/055* Jun 20/056* Jun 20/057* Jun 20/05

000−12−320−121 1* Jun 20/052* Jun 20/053* Jun 20/054* Jun 20/055* Jun 20/05

6* Jun 20/057* Jun 20/058* Jun 20/059* Jun 20/05

10* Jun 20/05

000−12−320−700 1* Jun 20/052* Jun 20/053* Jun 20/05

000−12−430−001 1 Sep 30/042 Sep 30/04


000−12−430−003 1* Jun 20/052* Jun 20/053* Jun 20/054* Jun 20/055* Jun 20/056* Jun 20/05

000−12−430−100 1* Jun 20/052* Jun 20/053* Jun 20/054* Jun 20/055* Jun 20/056* Jun 20/057* Jun 20/058* Jun 20/059* Jun 20/05

000−12−440−001 1 Sep 30/042 Sep 30/04


000−12−440−003 1* Jun 20/052* Jun 20/05



Jun 20/05Master


3* Jun 20/054* Jun 20/055* Jun 20/056* Jun 20/05


000−12−580−001 1 Sep 30/042 Sep 30/043 Sep 30/04


000−12−590−001 1 Sep 30/042 Sep 30/043 Sep 30/04


000−12−590−702 1* Jun 20/052* Jun 20/053* Jun 20/054* Jun 20/05

000−12−680−001 1 Sep 30/042 Sep 30/043 Sep 30/04


000−12−690−001 1 Sep 30/042 Sep 30/043 Sep 30/04


000−12−690−702 1* Jun 20/052* Jun 20/053* Jun 20/054* Jun 20/05

000−12−710−001 1 Sep 30/042 Sep 30/043 Sep 30/044 Sep 30/045 Sep 30/04


10* Jun 20/0511* DELETED12* DELETED13* DELETED



10* DELETED11* DELETED

000−12−740−001 1 Sep 30/042 Sep 30/043 Sep 30/044 Sep 30/04



Jun 20/05Master


5 Sep 30/04


10* DELETED11* DELETED

000−12−810−001 1 Sep 30/042 Sep 30/04


000−12−830−002 1 Sep 30/042 Sep 30/043 Sep 30/04

000−12−830−003 1 Sep 30/042 Sep 30/043 Sep 30/044 Sep 30/04



000−12−830−006 1 Sep 30/042 Sep 30/043 Sep 30/04

000−12−830−007 1 Sep 30/042 Sep 30/043 Sep 30/04

000−12−830−100 1* Jun 20/052* Jun 20/05

3* Jun 20/054* Jun 20/05

000−12−830−101 1* Jun 20/052* Jun 20/05

000−12−840−001 1 Sep 30/042 Sep 30/043 Sep 30/044 Sep 30/045 Sep 30/046 Sep 30/047 Sep 30/04

000−12−840−100 1* Jun 20/052* Jun 20/05

000−12−900−100 1* Jun 20/052* Jun 20/05


10* Jun 20/0511* Jun 20/0512* Jun 20/0513* Jun 20/0514* Jun 20/0515* Jun 20/0516* Jun 20/0517* Jun 20/0518* Jun 20/0519* Jun 20/0520* Jun 20/05

000−12−900−703 1* Jun 20/052* Jun 20/053* Jun 20/054* Jun 20/055* Jun 20/056* Jun 20/057* Jun 20/058* Jun 20/05


CHAPTER 12 − SERVICING

TABLE OF CONTENTS

Jun 20/05Page 1Master

Table of Contents

TaskSubject Card Page Effectivity

Lubrication of the Brake Control Valve 000−12−120−001 1 ALL

Lubrication of the Air Driven Generator (ADG) Pivot Shaft 000−12−120−701 1 ALL

Lubrication of the Air Driven Generator (ADG) Pivot Shaft 000−12−120−702 1 ALL

Lubrication of the Aileron Rear Quadrant Trim Lever Bearings 000−12−160−700 1 ALL

Lubrication of the Aileron Servo Clutch 000−12−160−701 1 ALL

Lubrication of the Parking Brake Handle Slider and Track 000−12−220−001 1 ALL

Lubrication of the Aft Equipment Compartment Door 000−12−310−001 1 ALL

Lubrication of the Horizontal Stabilizer Trim Actuator Screw Jack 000−12−320−120 1 ALL

Lubrication of the Horizontal Stabilizer Hinge Bushings 000−12−320−121 1 ALL

Lubrication of the Elevator Servo Clutch 000−12−320−700 1 ALL

Lubrication of the Left Engine Variable Guide Vanes 000−12−430−001 1 ALL

Lubrication of the Left Engine Thrust Reverser Tracks and Ballscrew Actuators 000−12−430−002 1 ALL

Servicing of the Left Engine IDG Oil 000−12−430−003 1 ALL

Lubrication of the Left Engine Thrust Reverser 000−12−430−100 1 ALL

Lubrication of the Right Engine Variable Guide Vanes 000−12−440−001 1 ALL

Lubrication of the Right Engine Thrust Reverser Tracks and Ballscrew Actuators 000−12−440−002 1 ALL

Servicing of the Right Engine IDG Oil 000−12−440−003 1 ALL




Table of Contents

Lubrication of the Right Engine Thrust Reverser 000−12−440−100 1 ALL

Lubrication of the Left Inboard Flap Actuators 000−12−580−001 1 ALL

Lubrication of the Left Inboard Flap 000−12−580−100 1 ALL

Lubrication of the Left Outboard Flap Actuators 000−12−590−001 1 ALL

Lubrication of the Left Outboard Flap 000−12−590−100 1 ALL

Lubrication of the Left−Wing Aileron Control Cables at the Wing Pulley Interfaces 000−12−590−702 1 ALL

Lubrication of the Right Inboard Flap Actuators 000−12−680−001 1 ALL

Lubrication of the Right Inboard Flap 000−12−680−100 1 ALL

Lubrication of the Right Outboard Flap Actuators 000−12−690−001 1 ALL

Lubrication of the Right Outboard Flap 000−12−690−100 1 ALL

Lubrication of the Right−Wing Aileron Control Cables at the Wing Pulley Interfaces 000−12−690−702 1 ALL

Lubrication of the Nose Landing Gear 000−12−710−001 1 ALL

Servicing of the Nose Landing Gear Shock Strut 000−12−710−002 1 ALL

Lubrication of the Left Main Landing Gear 000−12−730−001 1 ALL

Servicing of the Left Main Landing Gear Shock Strut 000−12−730−002 1 ALL

Lubrication of the Right Main Landing Gear 000−12−740−001 1 ALL

Servicing of the Right Main Landing Gear Shock Strut 000−12−740−002 1 ALL

Lubrication of the Main−Avionics Compartment Door 000−12−810−001 1 ALL

Lubrication of the Phase III Passenger Door 000−12−830−001 1 ALL

Lubrication of the Cargo Compartment Door 000−12−830−002 1 ALL

Lubrication of the Phase III Passenger Door Latch Pins 000−12−830−003 1 ALL




Table of Contents

Lubrication of the Phase III Passenger Door Outer Handle 000−12−830−004 1 ALL

Lubrication of the Phase III Passenger Door Outer Handle 000−12−830−005 1 ALL

Lubrication of the Phase IV Passenger Door Latch Pins and Latch Cam Assembly 000−12−830−006 1 ALL

Lubrication of the Phase IV Passenger Door Hinge 000−12−830−007 1 ALL

Lubrication of the Crew Escape Hatch 000−12−830−100 1 ALL

Lubrication of the Left Overwing−Emergency Exit 000−12−830−101 1 ALL

Lubrication of the Service Door 000−12−840−001 1 ALL

Lubrication of the Right Overwing−Emergency Exit 000−12−840−100 1 ALL

Lubrication of the Maintenance Servicing Doors 000−12−900−100 1 ALL

Sanitization of the Galley Potable Water System 000−12−900−702 1 ALL

Sanitization of the Lavatory Potable Water System 000−12−900−703 1 ALL

TASK TYPE SKILL

COMPLAINTS MOVED TO MAINTENANCE CARRY−OVER ITEM NUMBER(S):

NUMBER DATE

REVISION

TASK CARD NUMBERINTERVALWORK AREAAIRCRAFT MODEL

000−

c

AIRCRAFT EFFECTIVITY:

COMPONENT EFFECTIVITY

S/N OFF S/N ON

AIRCRAFT HOURS/CYCLESAIRCRAFT NUMBERSTATION

WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Brake Control Valve

26

LU 0.02

100

MECHANIC

5A

SEP 30/04

12−120−001

PAGE 1 OF 2

MRB 32−43−06−05

AMTOSS 12−20−32−640−804

1. Tools and Equipment

− Grease gun

2. Job Set−Up

A. Remove the nose−hydraulics−compartment access panel(121AL).

3. Procedure

Refer to Figure 1.

A. Lubricate the main−landing−gear break−controlvalve−assembly as follows:

(1) Apply 04−006 silicone grease with the grease gun to thegrease fittings (1) located at the bottom of the cross beamassembly until the grease starts to leak from the plungerscraper seals.

4. Close Out

A. Install the nose−hydraulics−compartment access panel(121AL).

B. Remove all tools, equipment, and unwanted materials from thework area.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Lubrication of the Brake Control Valve

26

LU 0.02

100

MECHANIC

5A

SEP 30/04

12−120−001

PAGE 2 OF 2

CROSS BEAMASSY

A

A

SYMBOL APPLICATION METHOD

Grease gun

1. Grease fittings.LEGEND

1

(REF)

04−006

121 AL

SCRAPERSEAL(REF)

Lubrication of the Brake Control ValveFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Air Driven Generator (ADG) Pivot Shaft

27 JUN 20/05

LU AVIONICS0.45

4000 FLT HRS100 12−120−701

PAGE 1 OF 4

ON A/C WITH WET ADG (A/C 7003−7304)

AMTOSS 12−20−24−640−801

1. Reason for the Job

Refer to MRB 24−23−11−07.

2. Job Set−Up Information

A. Tools and Equipment:

(1) Lockpin assy−ADG ground (G601R101202−1).

(2) Protector assy−ADG blade (G601R101204−1).

(3) Grease gun (Commercially Available).

(4) Lubrication nozzle, grease gun (None specified).

B. Consumable Materials:

(1) Grease, aircraft, general purpose wide temperature range(04−001).

(2) Cloths, cleaning, low lint (05−001).

C. Reference Information:

(1) Lowering of the ADG (TASK 24−23−01−840−801).

(2) Retraction of the ADG After Manual Deployment (TASK24−23−01−840−802).

(3) Removal of the ADG (TASK 24−23−01−000−801).

(4) Installation of the ADG (TASK 24−23−01−400−801).

(5) Solvent Cleaning (TASK 51−26−00−110−801).

3. Job Set−Up

A. Open, safety, and tag the circuit breakers that follow:

CB PANEL CB NO. NAME

CBP−1 C10 ADG DEPLOY SENS


B. Manually deploy the ADG (1) (Ref. TASK24−23−01−840−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

LU AVIONICS0.45

4000 FLT HRS100 12−120−701

PAGE 2 OF 4

C. Install the lockpin and the blade protectors when the ADG (1)is fully deployed.

4. Procedure

Refer to Figure 1.

WARNING: MAKE SURE THAT THE AREA NEAR THE DOOR OFTHE ADG IS CLEAR OF PERSONS ANDEQUIPMENT. DEPLOYMENT OF THE ADG IS VERYFAST. WHEN THE ADG FALLS INTO POSITION, ITCAN CAUSE INJURIES TO PERSONS AND/ORDAMAGE TO EQUIPMENT.

A. Lubricate the ADG pivot shaft as follows:

(1) Use a lint−free cloth moist with solvent to remove all dirt,contamination, and moisture from the lubrication fitting (2)and the shaft (3) (Ref. TASK 51−26−00−110−801).

(2) Apply 04−001 grease with a grease gun to the lubricationfitting (2) of the ADG until the grease extrudes from bothends of the pivot bore (4).

(3) Remove the lockpin and the blade protectors.

(4) Manually retract and deploy the ADG (1) two to threetimes to allow the grease to disperse correctly inside thebore (4) of the pivot shaft (3) ( Ref. TASK24−23−01−840−802 and TASK 24−23−01−840−801).

(5) Remove the excess grease from both ends of the pivotshaft (3).

(6) Make sure that the ADG (1) moves smoothly during thedeployment and retraction.

(7) If the ADG (1) does not deploy or retract smoothly, or ifmanual force is needed to deploy the ADG, replace theADG (Ref. TASK 24−23−01−000−801 and TASK24−23−01−400−801).

5. Close Out

A. If the ADG is in the deployed position do the steps that follow:

(1) Make sure that the blade protectors and the lockpin areremoved.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

LU AVIONICS0.45

4000 FLT HRS100 12−120−701

PAGE 3 OF 4

(2) Manually retract the ADG (Ref. TASK24−23−01−840−802).

B. Remove the tags and close the circuit breakers that follow:




C. Remove all tools, equipment, and unwanted materials from thework area.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27 JUN 20/05

LU AVIONICS0.45

4000 FLT HRS100 12−120−701

PAGE 4 OF 4

A

A

LEGEND

NOTE

3

4

2

1

1. Air Driven Generator.2. Lubrication fitting.3. Pivot shaft.4. Pivot bore.

in deployed position.

Lubrication of the Air Driven Generator (ADG) Pivot ShaftFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

LU AVIONICS0.45

4000 FLT HRS100 12−120−702

PAGE 1 OF 4

ON A/C WITH DRY ADG (A/C 7305−SUBS)

AMTOSS 12−20−24−640−802




A. Tools and Equipment:

(1) Lockpin assy−ADG ground (G601R101202−1).

(2) Protector assy−ADG blade (764531).

(3) Grease gun (Commercially Available).

(4) Lubrication nozzle, grease gun (None specified).

B. Consumable Materials:

(1) Grease, aircraft, general purpose wide temperature range(04−001).


C. Reference Information:

(1) Manual Lowering of the Dry ADG (TASK24−23−01−840−804).

(2) Retraction of the Dry ADG After Deployment (TASK24−23−01−840−805).

(3) Removal of the Dry ADG (TASK 24−23−01−020−803).

(4) Installation of the Dry ADG (TASK 24−23−01−420−801).


3. Job Set−Up

A. Open, safety, and tag the circuit breakers that follow:


CBP−2 N6 ADG DEPLOY CONT AUTO

CBP−2 N7 ADG DEPLOY CONT MAN

CBP−5 B10 ADG AUTO

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

LU AVIONICS0.45

4000 FLT HRS100 12−120−702

PAGE 2 OF 4

CBP−5 B11 ADG MAN

B. Manually lower the dry ADG (1) (Ref. TASK24−23−01−840−804).

C. Install the lockpin and the blade protectors when the ADG (1)is fully deployed.

4. Procedure

Refer to Figure 1.

WARNING: MAKE SURE THAT THE AREA NEAR THE DOOR OFTHE ADG IS CLEAR OF PERSONS ANDEQUIPMENT. DEPLOYMENT OF THE ADG IS VERYFAST. WHEN THE ADG FALLS INTO POSITION, ITCAN CAUSE INJURIES TO PERSONS AND/ORDAMAGE TO EQUIPMENT.

CAUTION: IF THE RADOME IS OPEN, MAKE SURE THAT THERADOME LATCHES ARE CLEAR. WHEN THE ADGFALLS INTO POSITION, IT CAN CAUSE DAMAGE TOEQUIPMENT.

A. Lubricate the dry ADG pivot shaft as follows:

(1) Use a lint−free cloth moist with solvent to remove all dirt,contamination, and moisture from the lubrication fitting (2)and the shaft (3) (Ref. TASK 51−26−00−110−801).

(2) Apply 04−001 grease with a grease gun to the lubricationfitting (2) of the ADG until the grease extrudes from bothends of the pivot bore (4).

(3) Remove the lockpin and the blade protectors.

(4) Manually retract and deploy the ADG (1) two to threetimes to allow the grease to disperse correctly inside thebore (4) of the pivot shaft (3) ( Ref. TASK24−23−01−840−804 and TASK 24−23−01−840−805).

(5) Remove the excess grease from both ends of the pivotshaft (3).

(6) Make sure that the ADG (1) moves smoothly during thedeployment and retraction.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

LU AVIONICS0.45

4000 FLT HRS100 12−120−702

PAGE 3 OF 4

(7) If the ADG (1) does not deploy or retract smoothly, or ifmanual force is necessary to deploy the ADG, replace theADG (Ref. TASK 24−23−01−020−803 and TASK24−23−01−420−801).

5. Close Out

A. Remove the tags and close the circuit breakers that follow:


CBP−2 N6 ADG DEPLOY CONT AUTO

CBP−2 N7 ADG DEPLOY CONT MAN

CBP−5 B10 ADG AUTO

CBP−5 B11 ADG MAN

B. If the ADG is in the deployed position do the steps that follow:

(1) Make sure that the blade protectors and the lockpin areremoved.

(2) Manually retract the Dry ADG (Ref. TASK24−23−01−840−805).


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27 JUN 20/05

LU AVIONICS0.45

4000 FLT HRS100 12−120−702

PAGE 4 OF 4

rtc1

2120

701_

001.

dg, o

m, 0

5/08

/03

2. Lubrication fitting.3. Pivot shaft.4. Pivot bore.

1. Air−driven generator (ADG).

LEGEND

2


Grease gun

1

3

4

Lubrication of the Air Driven Generator Pivot ShaftFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Aileron Rear Quadrant and Trim Lever Bearings

27

LU MECHANIC

100 5500 FLT HRS 12−160−700

JUN 20/05

0.17

PAGE 1 OF 3

AMTOSS 12−20−27−640−809


Refer to MRM Supplementary Requirement R27−11−A082−02.


A. Consumable Materials

(1) Lubricant, oil, general purpose (06−035).

B. Reference Information

(1) Pressurize Hydraulic System No. 3 (TASK12−00−06−863−803).

(2) Release Hydraulic Pressure − System No. 3 (TASK12−00−06−863−804).

(3) Removal of the MLG Wheel Bin (TASK53−83−01−000−801).

(4) Installation of the MLG Wheel Bin (TASK53−83−01−400−801).

3. Job Set−Up

WARNING: PUT THE SAFETY DEVICES, THE WARNING SIGNS, ANDTHE WARNING PLACARDS IN POSITION BEFORE YOUSTART A PROCEDURE ON OR NEAR:− FLIGHT CONTROLS− FLIGHT CONTROL SURFACES− COMPONENTS THAT MOVE.MAKE SURE THAT THERE ARE NO PERSONS OREQUIPMENT ON OR NEAR THE FLIGHT CONTROLSURFACES. ACCIDENTAL MOVEMENT OF THE FLIGHTCONTROLS CAN CAUSE INJURIES TO PERSONSAND/OR DAMAGE TO EQUIPMENT.

A. Install the applicable warning placards on the pilot’s andcopilot’s control wheels and on the AIL TRIM panel.

B. Connect the external AC power (Re. TASK12−00−07−861−801).

C. Remove the MLG wheel bins (Ref. TASK53−83−01−000−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LU MECHANIC

100 5500 FLT HRS 12−160−700

JUN 20/05

0.17

PAGE 2 OF 3

WARNING: MAKE SURE THAT THE FLIGHT CONTROLSURFACES ARE CLEAR OF PERSONS ANDEQUIPMENT DURING THE FULL RANGE OFTRAVEL. FLIGHT CONTROL MOVEMENT CANCAUSE INJURIES TO PERSONS AND/OR DAMAGETO EQUIPMENT.

D. Pressurize hydraulic system No. 3 (Ref. TASK12−00−06−863−803).

4. Procedure

Refer to Figure 1.

A. Apply a large quantity of 06−035 lubricant with anunpressurized spray bottle to both sides of the aft aileronquadrant bearings.

B. Apply a large quantity of 06−035 lubricant with anunpressurized spray bottle to both sides of the from leverbearings.

C. Cycle the aileron control wheel five times.

D. Apply the 06−035 lubricant again.

NOTE: If AV−25 has already been applied to the quadrants,it is considered acceptable for the initial applicationonly. After the initial application, 06−035 shall be theonly lubricant used. Removing the Av−25 is notrequired as the two products have been found to bechemically compatible.

5. Close Out

A. Release the pressure from hydraulic system No. 3 (Ref. TASK12−00−06−863−804).

B. Remove all tools, equipment, and unwanted materials fromthe work area.

C. Install the MLG wheel bins (Ref. TASK 53−83−01−400−801).

D. Remove the applicable warning placards on the pilot’s andcopilot’s control wheels and the AIL TRIM panel.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LU MECHANIC

100 5500 FLT HRS 12−160−700

JUN 20/05

0.17

PAGE 3 OF 3

rtc1

2160

700_

001.

dg,

lr, 1

7/11

/04

A

A

C

C

B

06−035

B

06−035


SPRAY BOTTLE

Aileron Rear Quadrant and Trim Lever Bearings − LubricationFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Aileron Servo Clutch

27

LU MECHANIC

6500 FLT HRS100

JUN 20/05

12−160−701

PAGE 1 OF 3

AMTOSS 12−20−22−640−801


Refer to MRB 22-11-00-09 and AWL Supplemetary RequirementR22−11−A083−01.


A. Tools and Equipment

(1) Brush, non−metallic medium stiff bristle.

B. Consumables

(1) Braycote 601EF.

(2) Christo−Lube MCG 117.

(3) Aeroshell 33 (MIL−PRF−23827).

C. Reference Information

(1) Removal of the Aileron Servo (TASK22−11−21−000−801).

(2) Cleaning of the Aileron Servo Clutch (TASK22−11−21−100−803).

(3) Installation of the Aileron Servo (TASK22−11−21−400−801).

3. Job Set−Up

A. Remove the aileron servo (Ref. TASK 22−11−21−000−801).

B. Clean the aileron servo clutch (Ref. TASK22−11−21−100−803).

4. Procedure

Refer to Figure 1.

A. Lubricate the aileron servo clutch gear set as follows:

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LU MECHANIC

6500 FLT HRS100

JUN 20/05

12−160−701

PAGE 2 OF 3

CAUTION: MAKE SURE THAT NO GREASE AND/ORCONTAMINATION GO INTO THE SERVO OR SERVOMOUNT AROUND THE CIRCUMFERENCE OF THECLUTCH HALVES.

CAUTION: DO NOT MIX LUBRICANTS ON A CLUTCH SET.AFTER YOU CLEAN THE SERVO AND THE SERVOMOUNT CLUTCH TEETH, APPLY ONLY ONELUBRICANT TYPE ON THE SERVO AND SERVOMOUNT CLUTCH FACE SET.

(1) From the table of Consumable Materials, select anylubricant and apply a thin film or bead of lubricant, ofapproximately 0.024 to 0.030 cu. in. (0.4 to 0.5 cc) to thecenter of each aileron servo/servo mount clutch face set.This amount will result in a bead of approximately 1/32 to1/16 inch (0.787 to 1.575 mm) in diameter.

NOTE: It is recommended to apply half of the lubricantto the aileron servo clutch face and theremaining half to the aileron servo mount clutchface.

(2) Using a clean brush, spread the lubricant from the centerto all of the teeth of the aileron servo clutch face.

NOTE: The brush is used to distribute the lubricant to allsurfaces of the teeth, especially down to thebottom gaps (roots) of all teeth of both theaileron servo and aileron servo mount clutchfaces.

(3) Repeat this for the aileron servo mount clutch face.

(4) Visually inspect the lubricant application to ensure that allof the bottom gaps (roots) of all teeth of both the aileronservo and aileron servo mount clutch faces have a supplyof lubricant in them and all surfaces of the clutch teeth arelubricated.

5. Close Out

A. Install the aileron servo (Ref. TASK 22−11−21−400−801).


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LU MECHANIC

6500 FLT HRS100

JUN 20/05

12−160−701

PAGE 3 OF 3


BRUSH

rtc1

2160

100_

001.

dg, l

r/rm

, 01/

12/0

4

1. Aileron servo clutch face.2. Aileron servo mount clutch face.

LEGEND

21

Aileron Servo Clutch −ServicingFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Parking Brake Handle Slider and Track

26

LU 0.20

200

MECHANIC

SEP 30/04

2A 12−220−001

PAGE 1 OF 3

Applicable only on aircraft with parking brake controlassembly p/n 7−44856−9, −11, −13, −15, and −17

AMTOSS 12−20−32−640−806





(1) Grease, aircraft and instrument, gear and actuator screw(04−005).


(1) Set the Parking Brake (TASK 32−45−00−910−801).

(2) Release the Parking Brake (TASK 32−45−00−910−802).

3. Job Set−Up

A. If the parking brake has not been set, do the steps that follow:

CAUTION: DO NOT TURN PARKING BRAKE HANDLE UNTILIT IS FULLY PULLED OUT. ALSO, DO NOTTURN THE HANDLE MORE THAN 90 DEGREESWHEN IT IS PULLED OUT AND TURNED TO THELOCK POSITION. DAMAGE TO THE INTERNALLOCKING DEVICE CAN OCCUR.

(1) Fully pull out the parking brake handle.

(2) Turn the parking brake handle 90 degrees clockwise.Make sure that the parking brake handle is locked.

4. Procedure

Refer to Figure 1.

A. To lubricate the slider and track of the parking brake handleassembly, do the steps that follow:

(1) Apply a thin layer of 04−005 grease by hand to the shaftof the parking brake handle.

(2) Release the parking brake (Ref. TASK32−45−00−910−802).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LU 0.20

200

MECHANIC

SEP 30/04

2A 12−220−001

PAGE 2 OF 3

(3) Remove any unwanted grease from the area that isadjacent to the parking brake handle.

5. Close Out

A. If the parking brake was set before you started this procedure,set it again (Ref. TASK 32−45−00−910−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LU 0.20

200

MECHANIC

SEP 30/04

2A 12−220−001

PAGE 3 OF 3

A


Hand

1. Parking brake handle.LEGEND

A

1

04−005

ram

1220

323_

006.

dg, s

w, 1

9/06

/01

Lubrication of the Parking Brake Handle Slider and TrackFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Aft Equipment Compartment Door

26

LU 0.03

300

MECHANIC

SEP 30/04

2A 12−310−001

PAGE 1 OF 2

AMTOSS 12−20−52−640−806





(1) Grease, silicone (04−006).

3. Job Set−Up

A. Open the aft equipment−compartment door (311BB).

4. Procedure

Refer to Figure 1.

A. Lubricate the aft equipment−compartment door as follows:

(1) Apply 04−006 grease to the hinges (1).

(2) Apply 04−006 grease to the wear surfaces of the latchpins (2).

(3) Aplly 04−006 grease to all push rod bearings and hingepoints of the door latch mechanism (3).

5. Close Out

A. Remove all tools, equipment, and unwanted materials from thework area.

B. Close the aft equipment−compartment door (311BB).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Lubrication of the Aft Equipment Compartment Door

26

LU 0.03

300

MECHANIC

SEP 30/04

2A 12−310−001

PAGE 2 OF 2

2

1

04−006

04−006


Hand

04−006

3

2

04−006

LEGEND1. Hinge.2. Latch pin.3. Latch mechanism.

A

Lubrication of the Aft Equipment Compartment DoorFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Horizontal Stabilizer Trim Actuator Screw Jack

27 JUN 20/05

LU MECHANIC0.50

8000 FLT HRS300 12−320−120

PAGE 1 OF 7

AMTOSS 12−20−27−640−807





(1) Hot air blower (Stienel HL1802E or equivalent).

B. Consumable Materials




(1) Jacking of the Aircraft (TASK 07−11−01−582−801).

(2) Connect External AC Power (TASK12−00−07−861−801).

(3) Remove External AC Power (TASK 12−00−07−861−802).

(4) Functional Check (Ground Maintenance Test) of theHSTCU (TASK 27−41−00−740−801).

(5) Removal of the Middle Upper Fairing (TASK55−32−05−000−806).

(6) Installation of the Middle Upper Fairing (TASK55−32−05−400−806).

3. Job Set−Up

A. Put the rear fuselage support at FS755.00 (Ref. TASK07−11−01−582−801).

B. Connect the external AC power (Ref. TASK 12−00−07−861−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

LU MECHANIC0.50

8000 FLT HRS300 12−320−120

PAGE 2 OF 7

WARNING: PUT THE SAFETY DEVICES, THE WARNING SIGNS,AND THE WARNING PLACARDS IN POSITIONBEFORE YOU START A PROCEDURE ON OR NEAR:− FLIGHT CONTROLS− FLIGHT CONTROL SURFACES− COMPONENTS THAT MOVE.MAKE SURE THAT THERE ARE NO PERSONS OREQUIPMENT ON OR NEAR THE FLIGHT CONTROLSURFACES. ACCIDENTAL MOVEMENT OF THEFLIGHT CONTROLS CAN CAUSE INJURIES TOPERSONS AND/OR DAMAGE TO EQUIPMENT.

C. Install the applicable warning placards on the pilot’s andcopilot’s control wheels and the STAB TRIM/MACH TRIMpanel.

CAUTION: OBEY THE DUTY CYCLE OF THE HORIZONTALSTABILIZER PITCH−TRIM ACTUATOR (TWOMINUTES ON, THEN TWO MINUTES OFF). IF YOUDO NOT DO THIS YOU CAN CAUSE DAMAGE TOTHE EQUIPMENT.

D. Position the Horizontal Stabilizer Trim Actuator (HSTA) asfollows:

(1) On the EICAS control panel, push the STAT button to setthe status page on the EICAS secondary display (ED 2).

(2) On the STAB TRIM/MACH TRIM panel, push the STABTRIM CH1 or CH2 switch to engage one of the HSTCUchannels.

(3) Operate the pilot’s or copilot’s manual trim switch on thecontrol wheel and monitor the STAB trim pointer on ED 2.Move the horizontal stabilizer until the HSTA is at the midposition, approximately 7 or 8 on the EICAS secondarydisplay (ED 2).

E. Open, safety and tag the circuit breakers that follow:


CBP−2 B8 STAB CH1 HSTA

CBP−2 F5 STAB CH1 HSTCU

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

LU MECHANIC0.50

8000 FLT HRS300 12−320−120

PAGE 3 OF 7

CBP−3 A5 STAB CH2 HSTA

CBP−4 A1 STAB CH2 HSTCU

Refer to Figure 1.

F. Remove the middle upper fairing 326BT (Ref. TASK55−32−05−000−806).

G. Remove the end protection bellows of the HSTA as follows:

(1) Remove the screws (1) and half clamp (2).

(2) Remove the screws (3) and flange (4).

CAUTION: DO NOT APPLY TOO MUCH HEAT TO THEBELLOWS. IF THE BELLOWS GETS TOO HOT,DAMAGE TO THE BELLOWS CAN OCCUR.

(3) Using the hot air blower, heat the bellows (5) to atemperature of 212±18 degrees F (100±10 degrees C) atthe level of the grey indicator.

NOTE: Heat the bellows in order to insert a screwdriverin the groove of the nut (6).

(4) Using a screwdriver as a lever, turn the bellows andrelease it from the nut.

NOTE: If the bellows is difficult to turn or extract fromthe groove, heat it on all its circumference.

(5) Remove the bellows.

H. Remove the tags and close the circuit breakers that follow:






I. Operate the trim switch on the control wheel and monitor theSTAB trim pointer on ED 2. Move the horizontal stabilizer untilthe HSTA is at the retracted position, 15 on the EICASsecondary display (ED 2).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

LU MECHANIC0.50

8000 FLT HRS300 12−320−120

PAGE 4 OF 7

J. Open, safety and tag the circuit breakers that follow:






4. Procedure

A. Lubricate the screw jack of the HSTA as follows:

(1) Using a clean dry cloth, remove the grease from theexposed part of the screw jack.

NOTE: A thin film of grease remaining on the screw jackis permitted.

(2) Apply approximately 0.5 oz (15 g) of 04−005 greaseuniformly to the exposed part of the screw jack on alllength and circumference. Make sure all the exposed partof the screw jack is covered with 04−005 grease.

(3) Remove the tags and close the circuit breakers that follow:






(4) Using the trim switch on the control wheel, move theHSTA one full cycle to the extended position, 0 on EICASand back to the retracted position, 15 on the EICASsecondary display (ED 2).

5. Close Out

A. Install the bellows of the HSTA as follows:

(1) Using the trim switch on the control wheel, move theHSTA to the extended position, 0 on the EICAS secondarydisplay (ED 2).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

LU MECHANIC0.50

8000 FLT HRS300 12−320−120

PAGE 5 OF 7

(2) Open, safety and tag the circuit breakers that follow:






CAUTION: DO NOT APPLY TOO MUCH HEAT TO THEBELLOWS, IF THE BELLOWS GETS TOO HOT,DAMAGE TO THE BELLOWS CAN OCCUR.

(3) Attach the bellows (5) on the nut (6).

NOTE: If necessary heat the bellows to a temperature of212±18 degrees F (100±10 degrees C) at thelevel of the grey indicator.

(4) Attach the half clamp (2) on the nut (6) with the screws (1).

(5) Tighten the screws (1).

(6) Attach the flange (4) with the screws (3).


B. Do a final check of the operation of the bellows as follow:

(1) Remove the tags and close the circuit breakers that follow:






(2) Using the trim switch on the control wheel, move theHSTA two full cycles. Make sure that the bellows retractsand releases correctly during the test.


D. Do the functional check (ground maintenance test) of theHSTCU (Ref. TASK 27−41−00−740−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

LU MECHANIC0.50

8000 FLT HRS300 12−320−120

PAGE 6 OF 7

E. Remove the external AC power (Ref. TASK12−00−07−861−802).

F. Install the middle upper fairing (Ref. TASK55−32−05−400−806).

G. Remove the applicable warning placards on the pilot’s andcopilot’s control wheels and the STAB TRIM/MACH TRIMpanel.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27 JUN 20/05

LU MECHANIC0.50

8000 FLT HRS300 12−320−120

PAGE 7 OF 7

04−005

1

62

1

3

4

5

12


Hand

1. Screw.2. Half clamp.3. Screw.4. Flange.5. Bellows.6. Nut.

LEGEND

Heat bellows here.

NOTE

5

2 6

Lubrication of the Horizontal Stabilizer Trim Actuator Screw JackFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Horizontal Stabilizer Hinge Bushings

27 JUN 20/05

LU MECHANIC2.0

10000 FLT HRS300 12−320−121

PAGE 1 OF 10

AMTOSS 12−20−27−640−808





(1) Pads, jacking (G601R071001−1).

(2) Jack, forward fuse (5 tons) (ME5−2438C).

(3) Support, rear fuselage (03−5800−8000).

(4) Lift Sling − Horizontal Stabilizer (600−00001 HFIX−14).

(5) Horizontal Stabilizer Access Platforms (None specified).

(6) Crane or Lift which can lift 2000 pounds (907.20kilograms) or more (None specified).

NOTE: If the 600−00001 HFIX−14 lift sling and craneare not available, it is acceptable to lift thehorizontal stabilizer by hand using a minimum of4 people.


(1) Grease, Molybdenum Disulfide, Low and HighTemperature (04−009).


(3) Solvent, dry cleaning and degreasing, (Varsol) (11−002)


(1) Put the Aircraft on Jacks (TASK 07−11−01−582−801).

(2) Removal of the Aircraft from Jacks (TASK07−11−01−582−804).



(5) Operational Test of the Horizontal Stabilizer Trim System(TASK 27−40−00−710−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

LU MECHANIC2.0

10000 FLT HRS300 12−320−121

PAGE 2 OF 10

(6) Functional Check (Ground Maintenance Test) of theHSTCU (TASK 27−41−00−740−801).

(7) Removal of the Lower Visor Assembly (TASK55−32−05−000−805).

(8) Installation of the Lower Visor Assembly (TASK55−32−05−400−805).

3. Job Set−Up

A. Put the forward fuse jack below the jacking pad and extendthe jack until it lightly touches the jacking pad (Ref. TASK07−11−01−582−801).

B. Put the rear fuselage support at FS755.00 (Ref. TASK07−11−01−582−801).

C. Connect the external AC power (Ref. TASK12−00−07−861−801).

WARNING: PUT THE SAFETY DEVICES, THE WARNING SIGNS,AND THE WARNING PLACARDS IN POSITIONBEFORE YOU START A PROCEDURE ON OR NEAR:− FLIGHT CONTROLS− FLIGHT CONTROL SURFACES− COMPONENTS THAT MOVE.MAKE SURE THAT THERE ARE NO PERSONS OREQUIPMENT ON OR NEAR THE FLIGHT CONTROLSURFACES. ACCIDENTAL MOVEMENT OF THEFLIGHT CONTROLS CAN CAUSE INJURIES TOPERSONS AND/OR DAMAGE TO EQUIPMENT.

D. Install the applicable warning placards on the pilot’s andcopilot’s control wheels and the STAB TRIM/MACH TRIMpanel.

E. Position the Horizontal Stabilizer as follows:

(1) On the EICAS control panel, push the STAT button to setthe status page on the EICAS secondary display (ED 2).

(2) On the STAB TRIM/MACH TRIM panel, push the STABTRIM CH1 or CH2 switch to engage one of the HSTCUchannels.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

LU MECHANIC2.0

10000 FLT HRS300 12−320−121

PAGE 3 OF 10

(3) Operate the pilot’s or copilot’s manual trim switch on thecontrol wheel and monitor the STAB trim pointer on ED 2.Move the horizontal stabilizer until the horizontal stabilizercomes to 0−degree electrical up stop.

F. Open, safety and tag the circuit breakers that follow:






G. Remove the external AC power (Ref. TASK 12−00−07−861−802).

H. Set up access platforms under the horizontal stabilizer asnecessary.

I. Remove the lower visor assemblies 326 BL and 326 BR (Ref.TASK 55−32−05−000−805).

J. If available, set the crane with sling attached to horizontalstabilizer.

4. Procedure

Refer to Figure 1.

A. Do the anti−rotation check of the horizontal stabilizer hingebushings as follows:

(1) Examine the side faces of the lugs of the horizontal andvertical stabilizer for the presence of lacquer stripes acrossthe end face or flange of the bushings and theircorresponding lug surfaces.

NOTE: Lacquer stripes are used as alignment marksbetween the bushings and lugs. If the marksbetween the bushing and it’s corresponding lugmoves, it shows evidence of the bushing rotationin the lug.

(2) If lacquer stripes are present, make sure they are aligned.

(3) If lacquer stripes are not present, do as follows:

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

LU MECHANIC2.0

10000 FLT HRS300 12−320−121

PAGE 4 OF 10

(a) Where clearance permits, using a clean cloth and11−002 solvent cleaner, clean a suitable area for theapplication of a lacquer stripes on the bushings (11),the bushings (12), and their corresponding lugs.Using white lacquer, apply a stripe across the end ofthe bushings (11), the bushings (12), and theircorresponding lugs.

NOTE: Make sure you allow sufficient time for thelacquer to dry prior to the lubrication of thehinge bushings.

B. Do the lubrication of the horizontal stabilizer hinge bushings asfollows:

(1) Remove the inner pin (94) as follows:

(a) Remove the cotter pins (1), the nuts (2) and thewashers (3).

WARNING: MAKE SURE THAT THE OUTER PINS AREFULLY IN THEIR BORES WHEN YOUREMOVE THE INNER PIN. IF YOU DO NOTDO THIS, ACCIDENTAL MOVEMENT OFTHE HORIZONTAL STABILIZER CANOCCUR. INJURY TO PERSONS ANDDAMAGE TO EQUIPMENT CAN OCCUR.

(b) Remove the inner pin (4).

(c) Visually inspect the inner pin for unusual marks ordamage. Replace the inner pin if there is anyevidence of damage.

(2) Remove the left hand side outer pin (10) as follows:

(a) Remove the load caused by the weight of thehorizontal stabilizer from the left hand side outer pin(10) by one of the two methods listed below:

1 Using a crane with a sling if available, lift the horizontalstabilizer a sufficient amount to remove the load off theouter pins (10).

2 Using a minimum of 4 people, lift the horizontal stabilizera sufficient amount to remove the load off the left handouter pin (10).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

LU MECHANIC2.0

10000 FLT HRS300 12−320−121

PAGE 5 OF 10

WARNING: HOLD THE WEIGHT OF THE HORIZONTALSTABILIZER WHEN YOU REMOVE THEOUTER PINS. IF YOU DO NOT DO THIS,ACCIDENTAL MOVEMENT OF THEHORIZONTAL STABILIZER CAN OCCUR.INJURY TO PERSONS AND DAMAGE TOEQUIPMENT CAN OCCUR.

CAUTION: MAKE SURE THAT ONE OUTER PIN ISALWAYS INSTALLED. THE HORIZONTALSTABILIZER AND THE VERTICALSTABILIZER WILL NOT BE CORRECTLYALIGNED IF THE TWO OUTER PINS AREREMOVED AT THE SAME TIME. DAMAGETO THE AIRCRAFT CAN OCCUR.

(b) Carefully remove the left hand side outer pin (10)using a wooden shop aid if necessary.

(c) Visually inspect the outer pin (10) for unusual marksor damage. Replace the outer pin if there is anyevidence of damage.

(3) Make sure the bushings (11) and (12) on the left hand sidecannot be rotated by hand. Replace the bushings (11) and(12) if there is any evidence of rotation.

(4) Remove the anti−rotation fitting (9) as follows:

(a) Remove the nuts (5) and the washers (6).

(b) Remove the bolts (8) and the washers (7).

(c) Remove the anti−rotation fitting (9).

(5) Using a clean cloth and 11−002 solvent cleaner, clean theleft hand side bushings (11) and (12), the anti−rotationfitting (9) and the inner and outer diameters of the lefthand side outer pin (10).

(6) Visually inspect the bushings for unusual marks ordamage. Replace the bushings if there is any evidence ofdamage.

(7) Check the anti−rotation fitting (9) for cracks. Replace theanti−rotation fitting (9) if there is any evidence of damage.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

LU MECHANIC2.0

10000 FLT HRS300 12−320−121

PAGE 6 OF 10

(8) Apply a full layer of 04−009 grease uniformly to all thecomponents as follows:

− The inside diameters of the left hand side bushings (11)and (12)

− The inside and outside diameters of the left hand sideouter pin (10)

− The inside diameter of the anti−rotation fitting (9).

(9) Align the horizontal stabilizer fitting with the fitting on thevertical stabilizer.

(10) Install the left hand side outer pin (10) with the lugs facinginboard.

NOTE: If manpower has been used to lift the horizontalstabilizer, it can be released at this point.

(11) Remove the right hand side outer pin (10) as follows:

(a) Remove the load caused by the weight of thehorizontal stabilizer from the right hand side outer pin(10) by one of the two methods listed below:

1 Using a crane with a sling if available, lift the horizontalstabilizer a sufficient amount to remove the load off theouter pins (10).

2 Using a minimum of 4 people, lift the horizontal stabilizera sufficient amount to remove the load off the right handside outer pin (10).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

LU MECHANIC2.0

10000 FLT HRS300 12−320−121

PAGE 7 OF 10

WARNING: HOLD THE WEIGHT OF THE HORIZONTALSTABILIZER WHEN YOU REMOVE THEOUTER PINS. IF YOU DO NOT DO THIS,ACCIDENTAL MOVEMENT OF THEHORIZONTAL STABILIZER CAN OCCUR.INJURY TO PERSONS AND DAMAGE TOEQUIPMENT CAN OCCUR.

CAUTION: MAKE SURE THAT ONE OUTER PIN ISALWAYS INSTALLED. THE HORIZONTALSTABILIZER AND THE VERTICALSTABILIZER WILL NOT BE CORRECTLYALIGNED IF THE TWO OUTER PINS AREREMOVED AT THE SAME TIME. DAMAGETO THE AIRCRAFT CAN OCCUR.

(b) Carefully remove the right hand side outer pin (10)using a wooden shop aid if necessary.

(c) Visually inspect the outer pin (10) for unusual marksor damage. Replace the outer pin if there is anyevidence of damage.

(12) Make sure the bushings (11) and (12) on the right handside cannot be rotated by hand. Replace the bushings(11) and (12) if there is any evidence of rotation.

(13) Using a clean cloth and 11−002 solvent cleaner, clean theright hand side bushings (11) and (12), the inner and outerdiameters of the right hand side outer pin (10) and theinner pin (4).

(14) Visually inspect the bushings for unusual marks ordamage. Replace the bushings if there is any evidence ofdamage.

(15) Install the anti−rotation fitting as follows:

(a) Install the anti−rotation fitting (9).

(b) Install the washers (7) and the bolts (8).

(c) Install the washers (6) and the nuts (5).

(d) Do not tighten the nuts (5) at this time.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

LU MECHANIC2.0

10000 FLT HRS300 12−320−121

PAGE 8 OF 10

(16) Apply a full layer of 04−009 grease uniformly to all thecomponents as follows:

− The inside diameters of the right hand side bushings(11) and (12)

− The inside and outside diameters of the right hand sideouter pin (10)

− The outer diameter of the inner pin (4).

(17) Align the horizontal stabilizer fitting with the fitting on thevertical stabilizer.

(18) Install the right hand side outer pin (10) with the lugsfacing inboard.

NOTE: Make sure the lugs of the two outer pins (10) arefully engaged in the slots of the anti−rotationfitting (9).

NOTE: If manpower has been used to lift the horizontalstabilizer, it can be released at this point.

(19) Install the inner pin (4).

(20) Make sure the inner pin (4) rotates freely in the outer pins(10) and the anti−rotation fitting (9).

(21) Torque the nuts (5) of the anti−rotation fitting (9) from 50to 70 pounds−inches (5.6 to 7.9 N·m).

(22) Make sure the inner pin (4) rotates freely in the outer pins(10) and the anti−rotation fitting (9).

(23) Install the washers (3) and the nuts (2).

(24) Torque the nuts from 84 to 108 pounds−feet (113 to 146N·m).

(25) Install the new cotter pins (1).

5. Close Out


B. Install the lower visor assemblies 326 BL and 326 BR (Ref.TASK 55−32−05−400−805).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

LU MECHANIC2.0

10000 FLT HRS300 12−320−121

PAGE 9 OF 10

C. If necessary, remove the crane and sling attachment.

D. Remove the access platforms as necessary.

E. Remove the tags and close the circuit breakers that follow:






F. Do the operational test of the horizontal stabilizer trim system(Ref. TASK 27−40−00−710−801).

G. Do the functional check (ground maintenance test) of theHSTCU (Ref. TASK 27−41−00−740−801).

H. Remove the external AC power (Ref. TASK12−00−07−861−802).

I. Remove the forward fuse jack and rear fuselage support fromthe aircraft (Ref. TASK 07−11−01−582−801)

J. Remove the applicable warning placards on the pilot’s andcopilot’s control wheels and the STAB TRIM/MACH TRIMpanel.

K. Remove the applicable safety devices, warning signs andwarning placards from the flight controls, flight control surfacesand components that move.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27 JUN 20/05

LU MECHANIC2.0

10000 FLT HRS300 12−320−121

PAGE 10 OF 10

A

LEGEND

1

NOTE

HORIZONTALSTABILIZER

FITTING(REF)


Hand

11. Bushing.12. Bushing.

10. Outerpin.

4. Inner pin.

A

1

10

11

10

4

VERTICALSTABILIZER

FITTING(REF)

12

04−009

04−009

04−009

04−009

04−009

11

04−009

Horizontal stabilizerremoved for clarityonly.

56

1

23

78

1

23

9

1. Cotter pin.2. Nut.3. Washer.

5. Nut.6. Washer.7. Washer.8. Bolt.9. Anti rotation

Apply 04−009 greaseto inner diameter ofantirotation fitting.

LACQUERSTRIPE

LACQUERSTRIPE fitting.

rtc1

2320

121_

001.

dg, k

ms,

05/

04/0

2

Lubrication of the Horizontal Stabilizer Hinge BushingsFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Elevator Servo Clutch

27

LU MECHANIC

6500 FLT HRS300

JUN 20/05

12−320−700

PAGE 1 OF 3

AMTOSS 12−20−22−640−802


Refer to MRB 22-11-00-09.



(1) Brush, non−metallic medium stiff bristle.

B. Consumables

(1) Braycote 601EF.

(2) Christo−Lube MCG 117.

(3) Aeroshell 33 (MIL−PRF−23827).


(1) Removal of the Elevator Servo (TASK22−11−24−000−801).

(2) Cleaning of the Elevator Servo Clutch (TASK22−11−24−100−801).

(3) Installation of the Elevator Servo (TASK22−11−24−400−801).

3. Job Set−Up

A. Remove the elevator servo (Ref. TASK 22−11−24−000−801).

B. Clean the elevator servo clutch (Ref. TASK22−11−24−100−801).

4. Procedure

Refer to Figure 1.

A. Lubricate the elevator servo clutch gear set as follows:

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LU MECHANIC

6500 FLT HRS300

JUN 20/05

12−320−700

PAGE 2 OF 3

CAUTION: MAKE SURE THAT NO GREASE AND/ORCONTAMINATION GO INTO THE SERVO OR SERVOMOUNT AROUND THE CIRCUMFERENCE OF THECLUTCH HALVES.

CAUTION: DO NOT MIX LUBRICANTS ON A CLUTCH SET.AFTER YOU CLEAN THE SERVO AND THE SERVOMOUNT CLUTCH TEETH, APPLY ONLY ONELUBRICANT TYPE ON THE SERVO AND SERVOMOUNT CLUTCH FACE SET.

(1) Apply a thin film or bead of lubricant, of approximately0.024 to 0.030 cu. in. (0.4 to 0.5 cc) to the center of eachelevator servo/servo mount clutch face set.

This amount will result in a bead of approximately 1/32 to1/16 inch (0.787 to 1.575 mm) in diameter.

NOTE: It is recommended to apply half of the lubricantto the elevator servo clutch face and theremaining half to the elevator servo mount clutchface.

(2) Using a clean brush, spread the lubricant from the centerto all of the teeth of the elevator servo clutch face.

NOTE: The brush is used to distribute the lubricant to allsurfaces of the teeth, especially down to thebottom gaps (roots) of all teeth of both theelevator servo and elevator servo mount clutchfaces.

(3) Repeat this for the elevator servo mount clutch face.

(4) Visually inspect the lubricant application to ensure that allof the bottom gaps (roots) of all teeth of both the elevatorservo and elevator servo mount clutch faces have asupply of lubricant in them and all surfaces of the clutchteeth are lubricated.

5. Close Out

A. Install the elevator servo (Ref. TASK 22−11−24−400−801).


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LU MECHANIC

6500 FLT HRS300

JUN 20/05

12−320−700

PAGE 3 OF 3

rtc1

2320

122_

001.

dg, l

r/rm

, 01/

12/0

4

21


BRUSH

1. Elevator servoclutch face.

2. Elevator servo mount clutch face.

LEGEND

Elevator Servo Clutch − ServicingFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Left Engine Variable Guide Vanes

26

LUB 0.03

400

ENG/APU

SEP 30/04

2A 12−430−001

PAGE 1 OF 2

MRB 72−32−00−05

AMTOSS 12−20−75−640−801

1. Job Set−Up

A. Open the left engine access doors that follow:

(1) The lower translating−cowl door (Ref. TASK71−11−01−010−802).

(2) The upper translating−cowl door (Ref. TASK71−11−01−010−801).

(3) The lower core−cowl door (Ref. TASK71−12−01−010−803).

(4) The upper core−cowl door (Ref. TASK71−12−01−010−801).

2. Procedure

Refer to Figure 1.

A. Lubricate the left engine variable guide vanes 06−004 lightpenetrating oil as follows:

(1) Apply oil to the items that follow:

− The rod−end bearings (1)

− The forward bearings (2)

− The aft bearings (3).

3. Close Out


B. Close the left engine access doors that follow:





TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Lubrication of the Left Engine Variable Guide Vanes

26

LUB 0.03

400

ENG/APU

SEP 30/04

2A 12−430−001

PAGE 2 OF 2

ooiiiiiiiiiiiiiiiiiiiiiiiiiiiiuii

1. Rod−end bearing.2. Forward bearing.3. Aft bearing.

1 2

3

1 1 1

1 1 1

1

A

A

B

1 LEGEND

TYPICAL AT ALL LOCATIONS(1,2 AND 3)

06−004

1

06−004

B


Oil can

Lubrication of the Left Engine Variable Guide VanesFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Left Engine Thrust Reverser Tracks and Ballscrew Actuators

27

LU MECHANIC1.5

A400

JUN 20/05

12−430−002

PAGE 1 OF 7

AMTOSS 12−20−78−640−801 AND 12−20−78−640−803





(1) Grease gun with MS24203 coupling (None specified).



(2) Lubricant, fluorocarbon, telomer dispersion (dry film)(06−016).

C. Parts

REF NAME OF PART QTY IPC SEQUENCE NO.

1 Screw 1 IPC 78−32−01−01−031

3 Preformed packing 1 IPC 78−32−01−01−033

D. Reference Information


(2) Removal of the Upper Translating−Cowl Door (TASK71−11−01−000−801).

(3) Removal of the Lower Translating−Cowl Door (TASK71−11−01−000−802).

(4) Installation of the Upper Translating−Cowl Door (TASK71−11−01−400−801).

(5) Installation of the Lower Translating−Cowl Door (TASK71−11−01−400−802).

(6) Removal of the Upper Nose Access−Cowl (TASK71−14−01−000−801).

(7) Removal of the Lower Nose Access−Cowl (TASK71−14−01−000−802).

(8) Installation of the Upper Nose Access−Cowl (TASK71−14−01−400−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LU MECHANIC1.5

A400

JUN 20/05

12−430−002

PAGE 2 OF 7

(9) Installation of the Lower Nose Access−Cowl (TASK71−14−01−400−802).

(10) Thrust−Reverser−System Safety Precautions (TASK78−30−00−910−801).

(11) Manual Extension of the Thrust Reverser (TASK78−30−00−910−802).

(12) Manual Retraction of the Thrust Reverser (TASK78−30−00−910−803).

3. Job Set−Up

WARNING: OBEY ALL THE SAFETY PRECAUTIONS FOR THEEXHAUST/THRUST REVERSER WHEN YOU DOWORK ON THE THRUST REVERSER SYSTEM. IFYOU DO NOT DO THIS, YOU CAN CAUSE INJURIESTO PERSONS AND/OR DAMAGE TO EQUIPMENT.

A. Obey the safety precautions for the thrust reverser system(Ref. TASK 78−30−00−910−801).

ON A/C WITH THE ENG IGN A CIRCUIT BREAKER LOCATEDAT THE CBP−1 PANEL (PRE−MODSUM TC601R15984)

B. Open, safety, and tag the circuit breakers that follow:


CBP−1 M2 ENG IGN A

CBP−1 M3 ENG IGN B

ON A/C WITH THE ENG IGN A CIRCUIT BREAKER LOCATEDAT THE CBP−4 PANEL (POST−MODSUM TC601R15984)

C. Open, safety, and tag the circuit breakers that follow:


CBP−4 C6 ENG IGN A


ON A/C ALL

D. Remove the left lower nose access−cowl (Ref. TASK71−14−01−000−802).

E. Remove the left upper nose access−cowl (Ref. TASK71−14−01−000−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LU MECHANIC1.5

A400

JUN 20/05

12−430−002

PAGE 3 OF 7

F. Remove the lower translating−cowl door (Ref.71−11−01−000−802).

G. Remove the upper translating−cowl door (Ref.71−11−01−000−801).

H. Remove the fairings that follow:

(1) 434BT (Upper thrust−reverser pylon track fairing)

(2) 434BB (Lower thrust−reverser pylon track fairing)

4. Procedure

Refer to Figure 1.

A. Lubricate the left ballscrew actuators as follows:

(1) Loosen, but do not remove the screws (1) and move theaccess cover (2) to get access to the lubrication fitting (5).

(2) Remove and discard the preformed packing (3).

(3) Make sure that you can get access to the ballscrewlubrication fitting (5).

NOTE: If you cannot access the ballscrew lubricationfitting (5), manually move the thrust reverser toturn the screw and nut assembly until you cansee all of the lubrication fitting (5) in the ballnutsleeve opening (Ref. TASK78−30−00−910−802).

(4) Attach the grease gun (with the coupling) to the lubricationfitting.

(5) Apply 04−005 grease with the grease gun until thelubrication cavity is full of grease (approximately 1.75 cc).

(6) Install a new preformed packing (3) and close the accesscover (2).


(8) If you moved the thrust reverser, manually retract thethrust reverser (Ref. TASK 78−30−00−910−803).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LU MECHANIC1.5

A400

JUN 20/05

12−430−002

PAGE 4 OF 7

Refer to Figure 2.

B. Lubricate the left−engine thrust−reverser tracks and sliderblocks as follows:

(1) Obey all the thrust−reverser−system safety precautions(Ref. TASK 78−30−00−910−801).

(2) Manually extend the thrust reverser (Ref. TASK78−30−00−910−802).

(3) Remove any lubricant from the thrust reverser sliderblocks (Ref. TASK 51−26−00−110−801). If necessary,clean any unwanted lubricant from the thrust reversertracks (1) and the pylon tracks (2).

(4) Apply a thin layer of 06−016 dry film lubricant to the insidesurfaces of the thrust reverser tracks (1) and the pylontracks (2).

NOTE: Apply the lubricant to a maximum thickness of0.001 inch (0.025 mm) (which is equivalent totwo spray passes).

NOTE: Do not apply the dry film lubricant to the maintrack slider−blocks or the pylon track sliderblocks. The slider blocks must be clean for thethrust reverser to operate correctly.

(5) Let the 06−016 dry film lubricant cure at roomtemperature for four hours.

(6) Manually retract the thrust reverser (Ref. TASK78−30−00−910−803).

5. Close Out


B. Install the fairings that follow:



C. Install the left upper translating−cowl door (Ref. TASK71−11−01−400−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LU MECHANIC1.5

A400

JUN 20/05

12−430−002

PAGE 5 OF 7

D. Install the left upper translating−cowl door (Ref. TASK71−11−01−400−802).

E. Install the left upper nose access−cowl (Ref. TASK71−14−01−400−801).

F. Install the left lower nose access−cowl (Ref. TASK71−14−01−400−802).


G. Remove the tags and close the circuit breakers that follow:









TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LU MECHANIC1.5

A400

JUN 20/05

12−430−002

PAGE 6 OF 7

1. Screw.2. Access cover.3. Preformed packing.4. Ballscrew actuator.

LEGEND

A

B B

B B

B

1

4

2 3

1

A

C

5. Fitting lubrication.


Grease gun

C

5

BALLNUT SLEEVEOPENING

3(REF)

04−005

Lubrication of the Left Engine Thrust Reverser Tracks and Ballscrew ActuatorsFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LU MECHANIC1.5

A400

JUN 20/05

12−430−002

PAGE 7 OF 7


Spray can

A

B

NOTE

MAIN TRACKS

UPPER PYLON

LOWER PYLON

SERVICE PYLONCASTING1

Left power plant shown,right power plant opposite.

(Typical 4 Places)

TRACK

TRACK

(Typical 4 Places)

PYLON TRACKSLIDER BLOCKS

C

A B

C

LEGEND1. Main track.2. Pylon track.

MAIN TRACK SLIDER BLOCKS

206−016

06−016

1

1

1 Do not lubricate the slider blocks

Lubrication of the Left Engine Thrust Reverser Tracks and Ballscrew ActuatorsFigure 2

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Servicing of the Left Engine IDG Oil

27

SV ENG/APU0.17

500 FLT HRS400

JUN 20/05

12−430−003

PAGE 1 OF 6

AMTOSS 12−13−24−610−801





(1) Container, fluid, minimum capacity 2 U.S. quarts (1.9 L)(None specified).

(2) Servicing unit, IDG and engine oil (5 U.S. gallons)(PF53481−5PWS).


(4) Servicing unit, IDG and engine oil (1 quart)(150QL−01−01).


(1) Oil, lubricating (03−018).



C. Parts


5 Spring clip 1 IPC 24−11−01−02−090

7 Packing, preformed 2 IPC 24−11−01−02−097


(1) Electrical/Electronic Safety Precautions (TASK24−00−00−910−801).

(2) Open the Lower Translating−Cowl Door (TASK71−11−01−010−802).

(3) Close the Lower Translating−Cowl Door (TASK71−11−01−410−802).

(4) Open the Lower Core−Cowl Door (TASK71−11−01−010−803).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

SV ENG/APU0.17

500 FLT HRS400

JUN 20/05

12−430−003

PAGE 2 OF 6

(5) Close the Lower Core−Cowl Door (TASK71−11−01−410−804).

3. Job Set−Up

WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOUDO MAINTENANCE ON OR NEARELECTRICAL/ELECTRONIC EQUIPMENT. IF YOUDO NOT DO THIS, YOU CAN CAUSE INJURIES TOPERSONS AND/OR DAMAGE TO THE EQUIPMENT.

A. Obey all the electrical/electronic safety precautions (Ref. TASK24−00−00−910−801).











ON A/C ALL

D. Get access to the IDG on the left engine as follows:

(1) Open the lower translating−cowl door 434AB (Ref. TASK71−11−01−010−802).

(2) Open the lower core−cowl door 435AB (Ref. TASK71−11−01−010−803).

4. Procedure

Refer to Figure 1.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

SV ENG/APU0.17

500 FLT HRS400

JUN 20/05

12−430−003

PAGE 3 OF 6

CAUTION: GIVE A MINIMUM TIME OF 3 MINUTES TO LET THEIDG OIL LEVEL BECOME STABLE AFTER THEENGINE IS STOPPED. IF YOU DO NOT DO THIS,THE QUANTITY INDICATION WILL BE INCORRECTAND YOU CAN FILL THE IDG WITH TOO MUCH OIL.THIS CAN CAUSE DAMAGE TO THE IDG.

A. Look at the low−level sight gauge (1) on the side of the IDG.If the oil fully fills the glass window (2) of the sight glass (1),there is sufficient oil in the IDG.

WARNING: RELEASE THE PRESSURE IN THE IDG HOUSINGBEFORE YOU DO THE SERVICING OF THE IDG. IFYOU DO NOT RELEASE THE PRESSURE, IT CANCAUSE A SPRAY OF HOT OIL WHEN YOU REMOVETHE STANDPIPE PLUG. THIS CAN CAUSEINJURIES TO PERSONS AND/OR DAMAGE TOEQUIPMENT.

WARNING: USE APPROVED SAFETY GOGGLES ANDINSULATED GLOVES WHEN YOU FILL OR DRAINTHE ENGINE OIL SYSTEM. HOT OIL CAN COMEOUT OF THE OIL DRAIN PLUGS WHEN THEY AREREMOVED. HOT OIL CAN CAUSE INJURIES TOPERSONS AND/OR DAMAGE TO EQUIPMENT.

CAUTION: ADD OIL THAT IS OF THE SAME APPROVED TYPEAS OIL IN THE COMPONENT. MIXING OF OILTYPES WILL RESULT IN DEGRADED OILPERFORMANCE.

B. If you see a level line or if you cannot see oil, fill the IDG asfollows:

NOTE: Mixing of oil brands within the same type is notprohibited, however, it is not recommended.

(1) Push and hold the vent valve button (3) for a minimum of5 seconds to let the air pressure out of the IDG housing.

(2) Put a container below the overfill standpipe (4) to catchthe oil that comes out when the IDG is filled.

(3) Remove the spring clip (5) from the overfill standpipe (4).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

SV ENG/APU0.17

500 FLT HRS400

JUN 20/05

12−430−003

PAGE 4 OF 6

(4) Remove the standpipe plug (6) from the overfill standpipe(4). Push the plug up and turn it counterclockwise torelease it.


(6) Remove the dust cap (8) from the pressure fill adapter (9).

(7) Connect the oil filler line to the pressure fill adapter (9).

(8) Operate the oil filler to add oil to the IDG.

(9) Stop the oil filler when oil comes out of the overfillstandpipe (4).

NOTE: As much as 2 U.S. quarts (1.9 L) of oil will comeout of the standpipe after you stop the filler.

(10) Let the oil come out of the overfill standpipe (4) until the oilflow decreases to drops.

(11) Install the preformed packing (7) on the standpipe plug(6).

CAUTION: DO NOT INSTALL THE STANDPIPE PLUGBEFORE THE OIL FLOW FROM THE STANDPIPEDECREASES TO DROPS. IF YOU INSTALL THEPLUG TOO SOON, THE IDG WILL HAVE TOOMUCH OIL. THIS CAN CAUSE DAMAGE TO THEIDG.

(12) Install the standpipe plug (6) in the overfill standpipe (4).Push the plug up and turn it clockwise to engage it.

(13) Install the spring clip (5) on the standpipe plug (6).

(14) Disconnect the oil filler line from the pressure fill adapter(9).

(15) Install the dust cap (8) on the pressure fill adapter (9).

(16) Remove the container from below the overfill standpipe(4).

C. A minimum of 3 minutes after the oil is added, do an oil levelcheck of the IDG sight gauge (1). Make sure that the oil fullyfills the glass window (2) of the sight gauge (1). If you can seean oil level line, do steps 4.B again.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

SV ENG/APU0.17

500 FLT HRS400

JUN 20/05

12−430−003

PAGE 5 OF 6

5. Close Out


B. Install the access doors on the left engine as follows:

(1) Close the lower core−cowl door 435AB (Ref. TASK71−11−01−410−804).

(2) Close the lower translating−cowl door 434AB (Ref. TASK71−11−01−410−802).


C. Remove the tags and close the circuit breakers that follow:





D. Remove the tags and close the circuit breakers that follow:




TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

SV ENG/APU0.17

500 FLT HRS400

JUN 20/05

12−430−003

PAGE 6 OF 6

VIEW ON LEFT SIDE

ADDOIL

ADDOIL

ADD LINE

SERVICEIF OIL

LEVEL IS BELOWADD LINE

1. Low−level sight gauge.2. Glass window.3. Vent valve.4. Overfill standpipe.5. Spring clip.6. Standpipe plug.7. Preformed packing.8. Dust cap.9. Pressure fill adapter.

LEGEND

A

B

1

2

4

56

7

8 9

rtc1

2430

703_

001.

dg, l

r, 16

/03/

04

A

FWD

B

VIEW ON RIGHT SIDEA

3

Servicing of the Left Engine IDG OilFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Left Engine Thrust Reverser

27

LUB MECHANIC1.5

4000 FLT HRS400

JUN 20/05

12−430−100

PAGE 1 OF 9

AMTOSS 12−20−78−640−802 and 12−20−78−640−805





(1) Vapor degreaser/Varsol wash basin or equivalent (nonespecified).

(2) Nylon brush, bristled (none specified).

(3) Nylon brush, bottle (none specified).


(1) Grease, aircraft, general purpose, wide temperature range(04−001).

(2) Cloth, cleaning, low−lint (05−001).

(3) Lubricant, Molybdenum Disulfate (Molykote Z) (06−011).

(4) Solvent, degreaser (Varsol) (11−002).

(5) Manual solvent cleaner (11−028A).

(6) Cotton swabs.







(6) Removal of the Flexshafts (TASK 78−32−05−000−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC1.5

4000 FLT HRS400

JUN 20/05

12−430−100

PAGE 2 OF 9

(7) Installation of the Flexshafts (TASK78−32−05−400−801).

3. Job Set−Up













ON A/C ALL

D. Remove the lower nose access−cowl (Ref. TASK71−14−01−000−802).

E. Remove the upper nose access−cowl (Ref. TASK71−14−01−000−801).

F. Remove the flexshafts (Ref. TASK 78−32−05−000−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC1.5

4000 FLT HRS400

JUN 20/05

12−430−100

PAGE 3 OF 9

4. Procedure

Refer to Figure 1.

A. Clean the flexshafts as follows:

(1) Remove the power core (1) from the casing assembly.

(2) Remove the old 04−001 grease from the power core (1)with a 05−001 clean cloth. If necessary, use a nylonbristle brush soaked with 11−002 or 11−028A solventcleaner to remove the dried 04−001 grease.

NOTE: Repeat this process until the power core (1) isclean.

(3) Clean the casing assembly as follows:

WARNING: OBEY ALL OF THE PRECAUTIONS THATFOLLOW WHEN YOU USE SOLVENTS:− USE SAFETY GOGGLES− PUT ON PAPER MASK− PUT ON PROTECTIVE CLOTHING− DO NOT LET SOLVENTS TOUCH YOUR SKIN, EYES, AND MOUTH− DO WORK IN AN AREA THAT HAS A GOOD FLOW OF CLEAN AIR− DO WORK IN AN AREA THAT IS FREE FROM SPARKS, FLAME, AND HOT SURFACES− OBEY THE MANUFACTURER’S INSTRUCTIONS− GET MEDICAL AID IF IRRITATION OCCURS.SOLVENTS ARE POISONOUS.

(a) Remove the old 04−001 grease from the casingassembly with a nylon bottle brush soaked in either11−002 or 11−028A solvent cleaner. Then flush theinner diameter of the casing assembly with either11−002 or 11−028A solvent cleaner in a vapordegreaser/Varsol wash basin.

NOTE: Repeat this process until the casingassembly is clean.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC1.5

4000 FLT HRS400

JUN 20/05

12−430−100

PAGE 4 OF 9

WARNING: COMPRESSED AIR− WHEN USING COMPRESSED AIR FOR ANY COOLING, CLEANING, OR DRYING OPERATION, DO NOT EXCEED 30 PSIG AT THE NOZZLE.− EYES CAN BE PERMANENTLY DAMAGED BY CONTACT WITH LIQUID OR LARGE PARTICLES PROPELLED BY COMPRESSED AIR. INHALATION OF AIR−BLOWN PARTICLES OR SOLVENT VAPOR CAN DAMAGE LUNGS.− WHEN USING AIR FOR CLEANING AT AN AIR−EXHAUSTED WORKBENCH, WEAR APPROVED GOGGLES OR FACE SHIELD.− WHEN USING AIR FOR CLEANING AT AN UNEXHAUSTED WORKBENCH, WEAR APPROVED RESPIRATOR AND GOGGLES.

(b) Use filtered compressed air to dry the parts.

B. Lubricate the flexshafts as follows:

(1) Apply a layer of grease 04−001 by hand to the power core(1).

(2) Put the power core (1) into the casing assembly.

Refer to Figure 2.

NOTE: It is necessary to remove the lock−piston assembly from the PDU in order to lubricate it.

C. Remove the PDU lock−piston assembly from the flexshaft lockunit as follows:

(1) Remove and retain the three screws (1) and the retainingclips (2).

(2) Remove the PDU lock−piston assembly from the flexshaftlock unit.

NOTE: Do not disassemble the PDU lock−pistonassembly.

D. Clean the PDU Lock−Piston Assembly as follows:

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC1.5

4000 FLT HRS400

JUN 20/05

12−430−100

PAGE 5 OF 9

WARNING: OBEY ALL OF THE PRECAUTIONS THATFOLLOW WHEN YOU USE −1,−1,−1TRICHLOROETHANE:− DO NOT USE IN AREAS WHERE THERE IS HIGH HEAT, SPARKS, OR FLAMES− DO WORK IN AN AREA THAT HAS A GOOD FLOW OF AIR− OBEY THE MANUFACTURER’S INSTRUCTIONS− DO NOT LET THE −1,−1,−1 TRICHLOROETHANE TOUCH YOUR SKIN, EYES, AND MOUTH− CLOSE THE CONTAINER WHEN IT IS NOT USED − 1,−1,−1 TRICHLOROETHANE IS AN IRRITANT AND IS POISONOUS.

(1) Moisten a low−lint cloth or a cotton swab withtrichloroethane and clean the housing bore and thebushing inside the bore. Make sure that the area is free ofall grease, dirt and unwanted particles.

(2) Moisten a low−lint cloth or a cotton swab withtrichloroethane and fully clean all external parts of the PDUlock−piston assembly. Make sure that the lock−pistonassembly is free of all grease, dirt and unwanted particles.

E. Lubricate the PDU lock−piston assembly as follows:

WARNING: MOLYBDENUM DISULFIDE (MOLYKOTE Z)DO NOT BREATH THE MOLYKOTE Z DUST AND DONOT LET IT TOUCH YOUR SKIN. WEAR APPROVEDGOGGLES AND GLOVES. MAKE SURE THAT YOUHAVE A GOOD FLOW OF AIR OR WEAR ANAPPROVED RESPIRATOR. MOLYKOTE Z DUST ISPOISONOUS AND FLAMMABLE.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC1.5

4000 FLT HRS400

JUN 20/05

12−430−100

PAGE 6 OF 9


(1) Apply the molybdenum disulfate to the outer diameter ofthe piston ring (6) and the inner diameter of the housingbore. Use a low−lint cloth or a cotton swab to rub thelubricant into the surfaces.

CAUTION: MAKE SURE THAT ONLY THE NECESSARYAMOUNT OF THE LUBRICANT IS APPLIED TOTHE LOCK−PISTON ASSEMBLY. TOO MUCHLUBRICANT ON THE LOCK−PISTON ASSEMBLYCAN CAUSE THE LUBRICANT TO GET ON THEINTERNAL COMPONENTS OF THE PDU. IF THELUBRICANT GETS ON THE INTERNALCOMPONENTS OF THE PDU, DAMAGE TO THEPDU CAN OCCUR.

(2) Use compressed air to remove all unwanted lubricant.The application is sufficient when the lubricated surfacesshow a dark grey and glossy finish.

F. Install the PDU lock−piston assembly as follows:

(1) Put the PDU lock−piston assembly in a position so thatthe gap in the piston ring (6) points in flight direction.

(2) Engage the PDU lock−piston assembly into the housingbore in the PDU.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC1.5

4000 FLT HRS400

JUN 20/05

12−430−100

PAGE 7 OF 9

(3) Secure the PDU lock−piston assembly in the housing withthe three retaining clips (2) and the screws (1). Tightenthe screws.

5. Close Out

A. Install the flexshafts (Ref. TASK 78−32−05−400−801).


C. Install the upper nose access−cowl (Ref. TASK71−14−01−400−801).

D. Install the lower nose access−cowl (Ref. TASK71−14−01−400−802).







F. Remove the tags and close the circuit breakers that follow:




TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LUB MECHANIC1.5

4000 FLT HRS400

JUN 20/05

12−430−100

PAGE 8 OF 9


Hand

1

CASINGASSY

POWERCORE

NAMETAG

BA

A

B04−001

Lubrication of the Left Engine Thrust ReverserFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LUB MECHANIC1.5

4000 FLT HRS400

JUN 20/05

12−430−100

PAGE 9 OF 9

A

1. Screw.2. Retaining clip.3. Flexshaft lock−release knob.4. Piston retainer.5. Piston assembly.

GEAR HOUSING

ARMING PORT

BUSHING

AIR SUPPLY TUBE

SPRINGPISTON RING

WASHER

WASHER

PISTON SHAFT

PISTON

KNOB ASSY.

5

43

21

A

B

B

LEGEND

FWD

−B B

Lubrication of the Left Engine Thrust ReverserFigure 2

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Right Engine Variable Guide Vanes

26

LUB 0.03

400

ENG/APU

SEP 30/04

2A 12−440−001

PAGE 1 OF 2

MRB 72−32−00−05

AMTOSS 12−20−75−640−801

1. Job Set−Up

A. Open the right engine access doors that follow:





2. Procedure

Refer to Figure 1.

A. Lubricate the right engine variable guide vanes 06−004 lightpenetrating oil as follows:

(1) Apply oil to the items that follow:

− The rod−end bearings (1)

− The forward bearings (2)

− The aft bearings (3).

3. Close Out


B. Close the right engine access doors that follow:





TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Lubrication of the Right Engine Variable Guide Vanes

26

LUB 0.03

400

ENG/APU

SEP 30/04

2A 12−440−001

PAGE 2 OF 2

1. Rod−end bearing.2. Forward bearing.3. Aft bearing.

1 2

3

1 1 1

1 1 1

1

A

A

B

1 LEGEND

TYPICAL AT ALL LOCATIONS(1,2 AND 3)

06−004

1

06−004

B


Oil can

Lubrication of the Right Engine Variable Guide VanesFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Right Engine Thrust Reverser Tracks and Ballscrew Actuators

27

LU MECHANIC1.5

A400

JUN 20/05

12−440−002

PAGE 1 OF 7

AMTOSS 12−20−78−640−801 AND 12−20−78−640−803





(1) Grease gun with MS24203 coupling (None specified).



(2) Lubricant, fluorocarbon, telomer dispersion (dry film)(06−016).

C. Parts


1 Screw 1 IPC 78−32−01−01−031




(2) Removal of the Upper Translating−Cowl Door (TASK71−11−01−000−801).

(3) Removal of the Lower Translating−Cowl Door (TASK71−11−01−000−802).

(4) Installation of the Upper Translating−Cowl Door (TASK71−11−01−400−801).

(5) Installation of the Lower Translating−Cowl Door (TASK71−11−01−400−802).




TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LU MECHANIC1.5

A400

JUN 20/05

12−440−002

PAGE 2 OF 7



(11) Manual Extension of the Thrust Reverser (TASK78−30−00−910−802).

(12) Manual Retraction of the Thrust Reverser (TASK78−30−00−910−803).

3. Job Set−Up













ON A/C ALL

D. Remove the right lower nose access−cowl (Ref. TASK71−14−01−000−802).

E. Remove the right upper nose access−cowl (Ref. TASK71−14−01−000−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LU MECHANIC1.5

A400

JUN 20/05

12−440−002

PAGE 3 OF 7

F. Remove the lower translating−cowl door (Ref.71−11−01−000−802).

G. Remove the upper translating−cowl door (Ref.71−11−01−000−801).

H. Remove the fairings that follow:

(1) 444BT (Upper thrust−reverser pylon track fairing).

(2) 444BB (Lower thrust−reverser pylon track fairing).

4. Procedure

Refer to Figure 1.

A. Lubricate the right ballscrew actuators as follows:

(1) Loosen, but do not remove the screws (1) and move theaccess cover (2) to get access to the lubrication fitting (5).


(3) Make sure that you can get access to the ballscrewlubrication fitting (5).

NOTE: If you cannot access the ballscrew lubricationfitting (5), manually move the thrust reverser toturn the screw and nut assembly until you cansee all of the lubrication fitting (5) in the ballnutsleeve opening (Ref. TASK78−30−00−910−802).

(4) Attach the grease gun (with the coupling) to the lubricationfitting.

(5) Apply 04−005 grease with the grease gun until thelubrication cavity is full of grease (approximately 1.75 cc).

(6) Install a new preformed packing (3) and close the accesscover (2).


(8) If you moved the thrust reverser, manually retract thethrust reverser (Ref. TASK 78−30−00−910−803).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LU MECHANIC1.5

A400

JUN 20/05

12−440−002

PAGE 4 OF 7

Refer to Figure 2.

B. Lubricate the right−engine thrust−reverser tracks and sliderblocks as follows:

(1) Obey all the thrust−reverser−system safety precautions(Ref. TASK 78−30−00−910−801).

(2) Manually extend the thrust reverser (Ref. TASK78−30−00−910−802).

(3) Remove any lubricant from the thrust reverser sliderblocks (Ref. TASK 51−26−00−110−801). If necessary,clean any unwanted lubricant from the thrust reversertracks (1) and the pylon tracks (2).

(4) Apply a thin layer of 06−016 dry film lubricant to the insidesurfaces of the thrust reverser tracks (1) and the pylontracks (2).

NOTE: Apply the lubricant to a maximum thickness of0.001 inch (0.025 mm) (which is equivalent totwo spray passes).

NOTE: Do not apply the dry film lubricant to the maintrack slider−blocks or the pylon track sliderblocks. The slider blocks must be clean for thethrust reverser to operate correctly.

(5) Let the 06−016 dry film lubricant cure at roomtemperature for four hours.

(6) Manually retract the thrust reverser (Ref. TASK78−30−00−910−803).

5. Close Out


B. Install the fairings that follow:



C. Install the right upper translating−cowl door (Ref. TASK71−11−01−400−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LU MECHANIC1.5

A400

JUN 20/05

12−440−002

PAGE 5 OF 7

D. Install the right upper translating−cowl door (Ref. TASK71−11−01−400−802).

E. Install the right upper nose access−cowl (Ref. TASK71−14−01−400−801).

F. Install the right lower nose access−cowl (Ref. TASK71−14−01−400−802).


G. Remove the tags and close the circuit breakers that follow:









TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LU MECHANIC1.5

A400

JUN 20/05

12−440−002

PAGE 6 OF 7

1. Screw.2. Access cover.3. Preformed packing.4. Ballscrew actuator.

LEGEND

A

B B

B B

B

1

4

2 3

1

A

C

5. Fitting lubrication.


Grease gun

C

5

BALLNUT SLEEVEOPENING

3(REF)

04−005

Lubrication of the Right Engine Thrust Reverser Tracks and Ballscrew ActuatorsFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LU MECHANIC1.5

A400

JUN 20/05

12−440−002

PAGE 7 OF 7


Spray can

A

B

NOTE

MAIN TRACKS

UPPER PYLON

LOWER PYLON

SERVICE PYLONCASTING1

Left power plant shown,right power plant opposite.

(Typical 4 Places)

TRACK

TRACK

(Typical 4 Places)

PYLON TRACKSLIDER BLOCKS

C

A B

C

LEGEND1. Main track.2. Pylon track.

MAIN TRACK SLIDER BLOCKS

206−016

06−016

1

1

1 Do not lubricate the slider blocks

Lubrication of the Right Engine Thrust Reverser Tracks and Ballscrew ActuatorsFigure 2

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Servicing of the Right Engine IDG Oil

27

SV ENG/APU0.17

500 FLT HRS400

JUN 20/05

12−440−003

PAGE 1 OF 6

AMTOSS 12−13−24−610−801





(1) Container, fluid, minimum capacity 2 U.S. quarts (1.9 L)(None specified).



(4) Servicing unit, IDG and engine oil (1 quart)(150QL−01−01).





C. Parts


5 Spring clip 1 IPC 24−11−01−02−090

7 Packing, preformed 2 IPC 24−11−01−02−097


(1) Electrical/Electronic Safety Precautions (TASK24−00−00−910−801).

(2) Open the Lower Translating−Cowl Door (TASK71−11−01−010−802).

(3) Close the Lower Translating−Cowl Door (TASK71−11−01−410−802).

(4) Open the Lower Core−Cowl Door (TASK71−11−01−010−803).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

SV ENG/APU0.17

500 FLT HRS400

JUN 20/05

12−440−003

PAGE 2 OF 6

(5) Close the Lower Core−Cowl Door (TASK71−11−01−410−804).

3. Job Set−Up

WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOUDO MAINTENANCE ON OR NEARELECTRICAL/ELECTRONIC EQUIPMENT. IF YOUDO NOT DO THIS, YOU CAN CAUSE INJURIES TOPERSONS AND/OR DAMAGE TO THE EQUIPMENT.

A. Obey all the electrical/electronic safety precautions (Ref. TASK24−00−00−910−801).











ON A/C ALL

D. Get access to the IDG on the right engine as follows:

(1) Open the lower translating−cowl door 444AB (Ref. TASK71−11−01−010−802).

(2) Open the lower core−cowl door 445AB (Ref. TASK71−11−01−010−803).

4. Procedure

Refer to Figure 1.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

SV ENG/APU0.17

500 FLT HRS400

JUN 20/05

12−440−003

PAGE 3 OF 6

CAUTION: GIVE A MINIMUM TIME OF 3 MINUTES TO LET THEIDG OIL LEVEL BECOME STABLE AFTER THEENGINE IS STOPPED. IF YOU DO NOT DO THIS,THE QUANTITY INDICATION WILL BE INCORRECTAND YOU CAN FILL THE IDG WITH TOO MUCH OIL.THIS CAN CAUSE DAMAGE TO THE IDG.

A. Look at the low−level sight gauge (1) on the side of the IDG.If the oil fully fills the glass window (2) of the sight glass (1),there is sufficient oil in the IDG.

WARNING: RELEASE THE PRESSURE IN THE IDG HOUSINGBEFORE YOU DO THE SERVICING OF THE IDG. IFYOU DO NOT RELEASE THE PRESSURE, IT CANCAUSE A SPRAY OF HOT OIL WHEN YOU REMOVETHE STANDPIPE PLUG. THIS CAN CAUSEINJURIES TO PERSONS AND/OR DAMAGE TOEQUIPMENT.

WARNING: USE APPROVED SAFETY GOGGLES ANDINSULATED GLOVES WHEN YOU FILL OR DRAINTHE ENGINE OIL SYSTEM. HOT OIL CAN COMEOUT OF THE OIL DRAIN PLUGS WHEN THEY AREREMOVED. HOT OIL CAN CAUSE INJURIES TOPERSONS AND/OR DAMAGE TO EQUIPMENT.

CAUTION: ADD OIL THAT IS OF THE SAME APPROVED TYPEAS OIL IN THE COMPONENT. MIXING OF OILTYPES WILL RESULT IN DEGRADED OILPERFORMANCE.

B. If you see a level line or if you cannot see oil, fill the IDG asfollows:

NOTE: Mixing of oil brands within the same type is notprohibited, however, it is not recommended.

(1) Push and hold the vent valve button (3) for a minimum of5 seconds to let the air pressure out of the IDG housing.

(2) Put a container below the overfill standpipe (4) to catchthe oil that comes out when the IDG is filled.

(3) Remove the spring clip (5) from the overfill standpipe (4).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

SV ENG/APU0.17

500 FLT HRS400

JUN 20/05

12−440−003

PAGE 4 OF 6

(4) Remove the standpipe plug (6) from the overfill standpipe(4). Push the plug up and turn it counterclockwise torelease it.


(6) Remove the dust cap (8) from the pressure fill adapter (9).

(7) Connect the oil filler line to the pressure fill adapter (9).

(8) Operate the oil filler to add oil to the IDG.

(9) Stop the oil filler when oil comes out of the overfillstandpipe (4).

NOTE: As much as 2 U.S. quarts (1.9 L) of oil will comeout of the standpipe after you stop the filler.

(10) Let the oil come out of the overfill standpipe (4) until the oilflow decreases to drops.

(11) Install the preformed packing (7) on the standpipe plug(6).

CAUTION: DO NOT INSTALL THE STANDPIPE PLUGBEFORE THE OIL FLOW FROM THE STANDPIPEDECREASES TO DROPS. IF YOU INSTALL THEPLUG TOO SOON, THE IDG WILL HAVE TOOMUCH OIL. THIS CAN CAUSE DAMAGE TO THEIDG.

(12) Install the standpipe plug (6) in the overfill standpipe (4).Push the plug up and turn it clockwise to engage it.

(13) Install the spring clip (5) on the standpipe plug (6).

(14) Disconnect the oil filler line from the pressure fill adapter(9).

(15) Install the dust cap (8) on the pressure fill adapter (9).

(16) Remove the container from below the overfill standpipe(4).

C. A minimum of 3 minutes after the oil is added, do an oil levelcheck of the IDG sight gauge (1). Make sure that the oil fullyfills the glass window (2) of the sight gauge (1). If you can seean oil level line, do steps 4.B again.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

SV ENG/APU0.17

500 FLT HRS400

JUN 20/05

12−440−003

PAGE 5 OF 6

5. Close Out


B. Install the access doors on the right engine as follows:

(1) Close the lower core−cowl door 445AB (Ref. TASK71−11−01−410−804).

(2) Close the lower translating−cowl door 444AB (Ref. TASK71−11−01−410−802).







D. Remove the tags and close the circuit breakers that follow:




TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

SV ENG/APU0.17

500 FLT HRS400

JUN 20/05

12−440−003

PAGE 6 OF 6

VIEW ON LEFT SIDE

ADDOIL

ADDOIL

ADD LINE

SERVICEIF OIL

LEVEL IS BELOWADD LINE

1. Low−level sight gauge.2. Glass window.3. Vent valve.4. Overfill standpipe.5. Spring clip.6. Standpipe plug.7. Preformed packing.8. Dust cap.9. Pressure fill adapter.

LEGEND

A

B

1

2

4

56

7

8 9

rtc1

2430

703_

001.

dg, l

r, 16

/03/

04

A

FWD

B

VIEW ON RIGHT SIDEA

3

Servicing of the Left Engine IDG OilFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Right Engine Thrust Reverser

27

LUB MECHANIC1.5

4000 FLT HRS400

JUN 20/05

12−440−100

PAGE 1 OF 9

AMTOSS 12−20−78−640−802 and 12−20−78−640−805





(1) Vapor degreaser/Varsol wash basin or equivalent (nonespecified).

(2) Nylon brush, bristled (none specified).

(3) Nylon brush, bottle (none specified).



(2) Cloth, cleaning, low−lint (05−001).

(3) Lubricant, Molybdenum Disulfate (Molykote Z) (06−011).

(4) Solvent, degreaser (Varsol) (11−002).

(5) Manual solvent cleaner (11−028A).

(6) Cotton swabs.







(6) Removal of the Flexshafts (TASK 78−32−05−000−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC1.5

4000 FLT HRS400

JUN 20/05

12−440−100

PAGE 2 OF 9

(7) Installation of the Flexshafts (TASK78−32−05−400−801).

3. Job Set−Up













ON A/C ALL

D. Remove the lower nose access−cowl (Ref. TASK71−14−01−000−802).

E. Remove the upper nose access−cowl (Ref. TASK71−14−01−000−801).

F. Remove the flexshafts (Ref. TASK 78−32−05−000−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC1.5

4000 FLT HRS400

JUN 20/05

12−440−100

PAGE 3 OF 9

4. Procedure

Refer to Figure 1.

A. Clean the flexshafts as follows:

(1) Remove the power core (1) from the casing assembly.

(2) Remove the old 04−001 grease from the power core (1)with a 05−001 clean cloth. If necessary, use a nylonbristle brush soaked with 11−002 or 11−028A solventcleaner to remove the dried 04−001 grease.

NOTE: Repeat this process until the power core (1) isclean.

(3) Clean the casing assembly as follows:

WARNING: OBEY ALL OF THE PRECAUTIONS THATFOLLOW WHEN YOU USE SOLVENTS:− USE SAFETY GOGGLES− PUT ON PAPER MASK− PUT ON PROTECTIVE CLOTHING− DO NOT LET SOLVENTS TOUCH YOUR SKIN, EYES, AND MOUTH− DO WORK IN AN AREA THAT HAS A GOOD FLOW OF CLEAN AIR− DO WORK IN AN AREA THAT IS FREE FROM SPARKS, FLAME, AND HOT SURFACES− OBEY THE MANUFACTURER’S INSTRUCTIONS− GET MEDICAL AID IF IRRITATION OCCURS.SOLVENTS ARE POISONOUS.

(a) Remove the old 04−001 grease from the casingassembly with a nylon bottle brush soaked in either11−002 or 11−028A solvent cleaner. Then flush theinner diameter of the casing assembly with either11−002 or 11−028A solvent cleaner in a vapordegreaser/Varsol wash basin.

NOTE: Repeat this process until the casingassembly is clean.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC1.5

4000 FLT HRS400

JUN 20/05

12−440−100

PAGE 4 OF 9


(b) Use filtered compressed air to dry the parts.

B. Lubricate the flexshafts as follows:

(1) Apply a layer of grease 04−001 by hand to the power core(1).

(2) Put the power core (1) into the casing assembly.

Refer to Figure 2.

NOTE: It is necessary to remove the lock−piston assemblyfrom the PDU in order to lubricate it.

C. Remove the PDU lock−piston assembly from the flexshaft lockunit as follows:

(1) Remove and retain the three screws (1) and the retainingclips (2).

(2) Remove the PDU lock−piston assembly from the flexshaftlock unit.

NOTE: Do not disassemble the PDU lock−pistonassembly.

D. Clean the PDU Lock−Piston Assembly as follows:

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC1.5

4000 FLT HRS400

JUN 20/05

12−440−100

PAGE 5 OF 9

WARNING: OBEY ALL OF THE PRECAUTIONS THATFOLLOW WHEN YOU USE −1,−1,−1TRICHLOROETHANE:− DO NOT USE IN AREAS WHERE THERE IS HIGH HEAT, SPARKS, OR FLAMES− DO WORK IN AN AREA THAT HAS A GOOD FLOW OF AIR− OBEY THE MANUFACTURER’S INSTRUCTIONS− DO NOT LET THE −1,−1,−1 TRICHLOROETHANE TOUCH YOUR SKIN, EYES, AND MOUTH− CLOSE THE CONTAINER WHEN IT IS NOT USED − 1,−1,−1 TRICHLOROETHANE IS AN IRRITANT AND IS POISONOUS.

(1) Moisten a low−lint cloth or a cotton swab withtrichloroethane and clean the housing bore and thebushing inside the bore. Make sure that the area is free ofall grease, dirt and unwanted particles.

(2) Moisten a low−lint cloth or a cotton swab withtrichloroethane and fully clean all external parts of the PDUlock−piston assembly. Make sure that the lock−pistonassembly is free of all grease, dirt and unwanted particles.

E. Lubricate the PDU lock−piston assembly as follows:

WARNING: MOLYBDENUM DISULFIDE (MOLYKOTE Z)DO NOT BREATH THE MOLYKOTE Z DUST AND DONOT LET IT TOUCH YOUR SKIN. WEAR APPROVEDGOGGLES AND GLOVES. MAKE SURE THAT YOUHAVE A GOOD FLOW OF AIR OR WEAR ANAPPROVED RESPIRATOR. MOLYKOTE Z DUST ISPOISONOUS AND FLAMMABLE.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC1.5

4000 FLT HRS400

JUN 20/05

12−440−100

PAGE 6 OF 9


(1) Apply the molybdenum disulfate to the outer diameter ofthe piston ring (6) and the inner diameter of the housingbore. Use a low−lint cloth or a cotton swab to rub thelubricant into the surfaces.

CAUTION: MAKE SURE THAT ONLY THE NECESSARYAMOUNT OF THE LUBRICANT IS APPLIED TOTHE LOCK−PISTON ASSEMBLY. TOO MUCHLUBRICANT ON THE LOCK−PISTON ASSEMBLYCAN CAUSE THE LUBRICANT TO GET ON THEINTERNAL COMPONENTS OF THE PDU. IF THELUBRICANT GETS ON THE INTERNALCOMPONENTS OF THE PDU, DAMAGE TO THEPDU CAN OCCUR.

(2) Use compressed air to remove all unwanted lubricant.The application is sufficient when the lubricated surfacesshow a dark grey and glossy finish.

F. Install the PDU lock−piston assembly as follows:

(1) Put the PDU lock−piston assembly in a position so thatthe gap in the piston ring (6) points in flight direction.

(2) Engage the PDU lock−piston assembly into the housingbore in the PDU.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC1.5

4000 FLT HRS400

JUN 20/05

12−440−100

PAGE 7 OF 9

(3) Secure the PDU lock−piston assembly in the housing withthe three retaining clips (2) and the screws (1). Tightenthe screws.

5. Close Out

A. Install the flexshafts (Ref. TASK 78−32−05−400−801).


C. Install the upper nose access−cowl (Ref. TASK71−14−01−400−801).

D. Install the lower nose access−cowl (Ref. TASK71−14−01−400−802).







F. Remove the tags and close the circuit breakers that follow:




TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LUB MECHANIC1.5

4000 FLT HRS400

JUN 20/05

12−440−100

PAGE 8 OF 9


Hand

1

CASINGASSY

POWERCORE

NAMETAG

BA

A

B04−001

Lubrication of the Right Engine Thrust ReverserFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LUB MECHANIC1.5

4000 FLT HRS400

JUN 20/05

12−440−100

PAGE 9 OF 9

A

1. Screw.2. Retaining clip.3. Flexshaft lock−release knob.4. Piston retainer.5. Piston assembly.

GEAR HOUSING

ARMING PORT

BUSHING

AIR SUPPLY TUBE

SPRINGPISTON RING

WASHER

WASHER

PISTON SHAFT

PISTON

KNOB ASSY.

5

43

21

A

B

B

LEGEND

FWD

−B B

Lubrication of the Right Engine Thrust ReverserFigure 2

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Left Inboard Flap Actuators

26

LU MECHANIC0.15

A500

SEP 30/04

12−580−001

PAGE 1 OF 3

AMTOSS 12−20−27−640−805





(1) Grease gun (none specified).

(2) Lubricating nozzle, grease gun (MS 24203−1).

B. Consumables





(3) Electrical Extension of the Flaps (TASK27−54−00−866−801).

(4) Electrical Retraction of the Flaps (TASK27−54−00−866−802).

3. Job Set−Up

A. Connect the external AC power to the aircraft (Ref. TASK12−00−07−861−801).

B. Extend the flaps to the 45−degree position (Ref. TASK27−54−00−866−801).



CBP−1 B5 FLAPS PDU 1

CBP−1 F4 FLAPS CONT CH 1



TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LU MECHANIC0.15

A500

SEP 30/04

12−580−001

PAGE 2 OF 3

4. Procedure

Refer to Figure 1.

A. Apply 04−005 high/low temperature grease, with thelubricating nozzle on the grease gun, to the grease fitting oneach left inboard flap actuator box.

5. Close Out








C. Retract the flaps (Ref. TASK 27−54−00−866−802).

D. Remove the external AC power (Ref. TASK12−00−07−861−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LU MECHANIC0.15

A500

SEP 30/04

12−580−001

PAGE 3 OF 3

2

2

1

1. VisorLEGEND

04−005

box2. Flap actuator

Lubrication of the Left Inboard Flap ActuatorsFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Left Inboard Flap

27

LUB MECHANIC0.50

4000 FLT HRS500

JUN 20/05

12−580−100

PAGE 1 OF 5

AMTOSS 12−20−27−640−801 and 12−20−27−640−806






B. Consumables

(1) Compound, corrosion−preventative (06−013).

(2) Solvent, dry cleaning and degreasing (11−002).







(5) Removal of the Flexible Drive−Shaft Assembly Betweenthe PDU and the Inboard Actuator of the Inboard Flap(TASK 27−53−10−000−801).

(6) Installation of the Flexible Drive−Shaft Assembly Betweenthe PDU and the Inboard Actuator of the Inboard Flap(TASK 27−53−10−400−801).

(7) Removal of the Flexible Drive−Shaft Assembly Betweenthe Inboard Actuator and the Outboard Actuator of theInboard Flap (TASK 27−53−10−000−802).

(8) Installation of the Flexible Drive−Shaft Assembly Betweenthe Inboard Actuator and the Outboard Actuator of theInboard Flap (TASK 27−53−10−400−802).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC0.50

4000 FLT HRS500

JUN 20/05

12−580−100

PAGE 2 OF 5

(9) Removal of the Flexible Drive−Shaft Assembly Betweenthe Outboard Actuator of the Inboard Flap and theInboard Actuator of the Outboard Inboard Flap (TASK27−53−10−000−803).

(10) Installation of the Flexible Drive−Shaft Assembly Betweenthe Outboard Actuator of the Inboard Flap and theInboard Actuator of the Outboard Inboard Flap (TASK27−53−10−400−803).

(11) Removal of the Flexible Drive−Shaft Assembly Betweenthe Inboard Actuator and the Outboard Actuator of theOutboard Flap (TASK 27−53−10−000−804).

(12) Installation of the Flexible Drive−Shaft Assembly Betweenthe Inboard Actuator and the Outboard Actuator of theOutboard Flap (TASK 27−53−10−400−804).

(13) Removal of the Flexible Drive−Shaft Assembly Betweenthe Outboard Actuator of the Outboard Flap and theBPSU (TASK 27−53−10−000−805).

(14) Installation of the Flexible Drive−Shaft Assembly Betweenthe Outboard Actuator of the Outboard Flap and theBPSU (TASK 27−53−10−400−805).

3. Job Set−Up

A. Connect the external AC power to the aircraft (Ref. TASK12−00−07−861−801).








D. Remove the applicable flexible drive shaft (Ref. TASK27−53−10−000−801 and 27−53−10−000−802).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC0.50

4000 FLT HRS500

JUN 20/05

12−580−100

PAGE 3 OF 5

NOTE: For this procedure, complete removal of the flexibledrive shaft is not necessary. It is sufficient todisconnect the clamps from the structure asnecessary to keep to the minimum bend radius anddisconnect one end of the drive shaft.

4. Procedure

Refer to Figure 1.

CAUTION: DO NOT LET SOLVENT GET ON THE VISOR OF THEBEAM ASSEMBLY SHAFT. SOLVENT CAN CAUSEDAMAGE TO THE VISOR.

A. Lubricate the left inboard flap vane as follows:

(1) Put a cover on the visor to keep the solvent and lubricantoff of it.

(2) Clean the beam assembly shaft with a clean cloth and the11−002 solvent.

(3) Apply a small quantity of corrosion−preventativecompound 06−013 along the length of the beamassembly shaft.

B. Lubricate the left inboard flexible drive shafts as follows:

(1) Remove the core from the flexible drive shaft.

(2) Clean the surface 04−005 grease from the core with aclean, dry cloth.

NOTE: The drive shaft core is pressure impregnatedwith 04−005 grease. Do not use solvents toclean the surface of the core.

NOTE: If you see any damage to the core or casing,you can use the replacement criteria section,Table 601 of the detailed check of the flexibledrive shaft Ref. TASK 27−53−10−220−801 ifnecessary.

(3) Apply new 04−005 high/low temperature grease to thesurface of the core.

(4) Install the core in the casing of the flexible drive shaft.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC0.50

4000 FLT HRS500

JUN 20/05

12−580−100

PAGE 4 OF 5

(5) Remove unwanted 04−005 high/low temperature greasefrom the end of the flexible drive shaft where the core wasinstalled.

5. Close Out

A. Install the applicable flexible drive shaft (Ref. TASK27−53−10−400−801 and 27−53−10−400−802).








D. Retract the flaps (Ref. TASK 27−54−00−866−802).


F. Remove the applicable warning placards on the pilot’s andcopilot’s control wheels and the STAB TRIM/MACH TRIMpanel.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LUB MECHANIC0.50

4000 FLT HRS500

JUN 20/05

12−580−100

PAGE 5 OF 5

3. Movable vaneshaft

2

2

2

1

3

1. VisorLEGEND

06−013

04−005

2. Flexibledrive−shaft

Lubrication of the Left Inboard FlapFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Left Outboard Flap Actuators

26

LU MECHANIC0.15

A500

SEP 30/04

12−590−001

PAGE 1 OF 3

AMTOSS 12−20−27−640−805







B. Consumables







3. Job Set−Up

A. Connect the external AC power (Ref. TASK12−00−07−861−801).

B. Extend the flaps to the 45−degree position. (Ref. TASK27−54−00−866−801)







TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LU MECHANIC0.15

A500

SEP 30/04

12−590−001

PAGE 2 OF 3

4. Procedure

Refer to Figure 1.

A. Apply 04−005 high/low temperature grease, with thelubricating nozzle on the grease gun, to the grease fitting oneach left outboard flap actuator box.

5. Close Out










E. Remove the applicable warning placards on the pilot’s andcopilot’s control wheels and the STAB TRIM/MACH TRIMpanel.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LU MECHANIC0.15

A500

SEP 30/04

12−590−001

PAGE 3 OF 3

04−005

box

1

1

1. Flap actuator

Lubrication of the Left Outboard Flap ActuatorsFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Left Outboard Flap

27

LUB MECHANIC0.25

4000 FLT HRS500

JUN 20/05

12−590−100

PAGE 1 OF 6

AMTOSS 12−20−27−640−802, 12−20−27−640−803,and 12−20−27−640−806






B. Consumables












TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC0.25

4000 FLT HRS500

JUN 20/05

12−590−100

PAGE 2 OF 6







3. Job Set−Up









D. Remove the applicable flexible drive shaft (Ref. TASK27−53−10−000−803, 27−53−10−000−804 and27−53−10−000−805).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC0.25

4000 FLT HRS500

JUN 20/05

12−590−100

PAGE 3 OF 6


4. Procedure

Refer to Figures 1 and 2.

A. Lubricate the left outboard flexible drive shafts as follows:








B. Lubricate the left BUTE door hinge as follows:

(1) Apply 06−012 corrosion−preventative compound with aspray can along the length of the piano hinge (1).

(2) Remove the unwanted 06−012 corrosion−preventativecompound with a clean cloth.

C. Lubricate the left BUTE door rollers as follows:

NOTE: There are five rollers on each BUTE door.

(1) Apply 06−012 corrosion−preventative compound with aspray can to each end the BUTE door roller (2) to lubricatethe shaft of the roller.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC0.25

4000 FLT HRS500

JUN 20/05

12−590−100

PAGE 4 OF 6

(2) Remove the unwanted 06−012 corrosion−preventativecompound on the outer surface of the roller with a cleancloth.

5. Close Out

A. Install the applicable flexible drive shaft (Ref. TASK27−53−10−400−803, 27−53−10−400−804 and27−53−10−400−805).











TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LUB MECHANIC0.25

4000 FLT HRS500

JUN 20/05

12−590−100

PAGE 5 OF 6

04−005


1

1

1

1

Lubrication of the Left Outboard FlapFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LUB MECHANIC0.25

4000 FLT HRS500

JUN 20/05

12−590−100

PAGE 6 OF 6

A

A

B

B

C

C

C

C

1

2

1. Bute door hinge.

2. Bute door rollers.

06−012

06−012

Lubrication of the Left Outboard FlapFigure 2

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

27 JUN 20/05

LU MECHANIC0.42

5500 FLT HRS500

Lubrication of the Left−Wing Aileron Control Cables at the Wing PulleyInterfaces

12−590−702

PAGE 1 OF 4

AMTOSS 12−20−27−640−810








(2) Compound, corrosion−inhibiting, penetrating (Type 1)(15−003).


(1) Inspection of Wire−Rope Control Cables and RelatedComponents (TASK 20−23−00−200−801).

(2) Operational Test of the Aileron Control System (TASK27−11−00−710−801).

3. Job Set−Up

WARNING: PUT THE SAFETY DEVICES, THE WARNING SIGNS, ANDTHE WARNING PLACARDS IN POSITION BEFORE YOUSTART A PROCEDURE ON OR NEAR: − FLIGHT CONTROLS − FLIGHT CONTROL SURFACES − COMPONENTS THAT MOVE.MAKE SURE THAT THERE ARE NO PERSONS OREQUIPMENT ON OR NEAR THE FLIGHT CONTROLSURFACES. ACCIDENTAL MOVEMENT OF THE FLIGHTCONTROLS CAN CAUSE INJURIES TO PERSONSAND/OR DAMAGE TO EQUIPMENT.

A. Install placards at the HYDRAULIC control panel and at theexternal service connections to give warnings againstpressurization of the hydraulic systems.

B. Install a placard on the engine start panel to give warnings notto dry motor the engines (to prevent pressurization of theapplicable hydraulic system No. 1 and No. 2 with theengine−driven hydraulic pumps).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

27 JUN 20/05

LU MECHANIC0.42

5500 FLT HRS500


12−590−702

PAGE 2 OF 4

C. Remove the wing access panels that follow:

(1) Shroud 598AB.

(2) Shroud 598BB.

(3) Aileron Shroud 598LT.

(4) Aileron Shroud 598KT.

(5) Aileron Shroud 598JT.

(6) Aileron Leading Edge Access 599AB.

(7) Aileron Leading Edge Access 599BB.

4. Procedure

Refer to Figure 1.

WARNING: KEEP AWAY FROM THE GROUND SPOILERS, FLIGHTSPOILERS, AND SPOILERONS UNLESS YOU ARE SUREOF THE CONDITIONS THAT FOLLOW: − THERE IS NO HYDRAULIC PRESSURE TO THEAPPLICABLE ACTUATORS. − THE APPLICABLE HYDRAULIC SYSTEM IS MADESAFE FROM THE ACCIDENTAL APPLICATION OFHYDRAULIC PRESSURE.ACCIDENTAL MOVEMENT OF THE SPOILERS CANCAUSE INJURIES TO PERSONS AND DAMAGE TOEQUIPMENT.

A. Clean the aileron control cables with a clean cloth and 15−003corrosion−inhibiting compound (Ref. TASK20−23−00−200−801).

B. Apply a thin, equal layer of 04−001 grease to the pulleygrooves and cables. The grease must cover a minimum of 5.0in (127 mm) on each side of the pulleys when the ailerons areat neutral.

NOTE: Apply the grease with a brush. If you apply thegrease with a rag, grease will be removed from theouter strands of the cable.

NOTE: Make sure the treated cable is in contact with thepulleys through the full travel of the aileron controlsystem.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

27 JUN 20/05

LU MECHANIC0.42

5500 FLT HRS500


12−590−702

PAGE 3 OF 4

NOTE: The cables are thoroughly greased when a visiblelayer is seen on the outer surface.

5. Close Out


B. Do an operational test of the aileron control system (Ref. TASK27−11−00−710−801).

C. Install the wing access panels that follow:

(1) Shroud 598AB.

(2) Shroud 598BB.






D. Remove the applicable warning placards.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

27 JUN 20/05

LU MECHANIC0.42

5500 FLT HRS500


12−590−702

PAGE 4 OF 4

rtc1

2590

702_

001.

dg,

lr, 1

7/11

/04

DC

AB

A

B

C D

04−001

15−003

04−001

15−003

04−001

15−003

04−001

15−003


HAND

BRUSH

04−001

04−001

04−00104−001

NOTE

Left side is shown,right side is opposite

Lubrication of the Aileron Wing Pulleys and Control CablesFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Right Inboard Flap Actuators

26

LU MECHANIC0.15

A600

SEP 30/04

12−680−001

PAGE 1 OF 3

AMTOSS 12−20−27−640−805







B. Consumables







3. Job Set−Up









TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LU MECHANIC0.15

A600

SEP 30/04

12−680−001

PAGE 2 OF 3

4. Procedure

Refer to Figure 1.

A. Apply 04−005 high/low temperature grease, with thelubricating nozzle on the grease gun, to the grease fitting oneach right inboard flap actuator box.

5. Close Out










TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LU MECHANIC0.15

A600

SEP 30/04

12−680−001

PAGE 3 OF 3

2

2

1

1. VisorLEGEND

04−005

box2. Flap actuator

Lubrication of the Right Inboard Flap ActuatorsFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Right Inboard Flap

27

LUB MECHANIC0.50

4000 FLT HRS600

JUN 20/05

12−680−100

PAGE 1 OF 5

AMTOSS 12−20−27−640−801 and 12−20−27−640−806






B. Consumables


(2) Solvent, dry cleaning and degreasing (11−002).











TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC0.50

4000 FLT HRS600

JUN 20/05

12−680−100

PAGE 2 OF 5







3. Job Set−Up









D. Remove the applicable flexible drive shaft (Ref. TASK27−53−10−000−801 and 27−53−10−000−802).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC0.50

4000 FLT HRS600

JUN 20/05

12−680−100

PAGE 3 OF 5


4. Procedure

Refer to Figure 1.

CAUTION: DO NOT LET SOLVENT GET ON THE VISOR OF THEBEAM ASSEMBLY SHAFT. SOLVENT CAN CAUSEDAMAGE TO THE VISOR.

A. Lubricate the right inboard flap vane as follows:

(1) Put a cover on the visor to keep the solvent and lubricantoff of it.

(2) Clean the beam assembly shaft with a clean cloth and the11−002 solvent.

(3) Apply a small quantity of corrosion−preventativecompound 06−013 along the length of the beamassembly shaft.

B. Lubricate the right inboard flexible drive shafts as follows:







TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC0.50

4000 FLT HRS600

JUN 20/05

12−680−100

PAGE 4 OF 5


5. Close Out

A. Install the applicable flexible drive shaft (Ref. TASK27−53−10−400−801 and 27−53−10−400−802).











TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LUB MECHANIC0.50

4000 FLT HRS600

JUN 20/05

12−680−100

PAGE 5 OF 5

3. Movable vaneshaft

2

2

1

3

1. VisorLEGEND

06−013

04−005


2

Lubrication of the Right Inboard FlapFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Right Outboard Flap Actuators

26

LU MECHANIC0.15

A600

SEP 30/04

12−690−001

PAGE 1 OF 3

AMTOSS 12−20−27−640−805







B. Consumables







3. Job Set−Up









TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LU MECHANIC0.15

A600

SEP 30/04

12−690−001

PAGE 2 OF 3

4. Procedure


A. Apply 04−005 high/low temperature grease, with thelubricating nozzle on the grease gun, to the grease fitting oneach right outboard flap actuator box.

5. Close Out










TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LU MECHANIC0.15

A600

SEP 30/04

12−690−001

PAGE 3 OF 3

04−005

box1. Flap actuator

1

1

Lubrication of the Right Outboard Flap ActuatorsFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Right Outboard Flap

27

LUB MECHANIC0.25

4000 FLT HRS600

JUN 20/05

12−690−100

PAGE 1 OF 6

AMTOSS 12−20−27−640−802, 12−20−27−640−803, and 12−20−27−640−806






B. Consumables












TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC0.25

4000 FLT HRS600

JUN 20/05

12−690−100

PAGE 2 OF 6







3. Job Set−Up









D. Remove the applicable flexible drive shaft (Ref. TASK27−53−10−000−803, 27−53−10−000−804 and27−53−10−000−805).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC0.25

4000 FLT HRS600

JUN 20/05

12−690−100

PAGE 3 OF 6


4. Procedure


A. Lubricate the right outboard flexible drive shafts as follows:








B. Lubricate the right BUTE door hinge as follows:

(1) Apply 06−012 corrosion−preventative compound with aspray can along the length of the piano hinge (1).

(2) Remove the unwanted 06−012 corrosion−preventativecompound with a clean cloth.

C. Lubricate the right BUTE door rollers as follows:

NOTE: There are five rollers on each BUTE door.

(1) Apply 06−012 corrosion−preventative compound with aspray can to each end the BUTE door roller (2) to lubricatethe shaft of the roller.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC0.25

4000 FLT HRS600

JUN 20/05

12−690−100

PAGE 4 OF 6

(2) Remove the unwanted 06−012 corrosion−preventativecompound on the outer surface of the roller with a cleancloth.

5. Close Out

A. Install the applicable flexible drive shaft (Ref. TASK27−53−10−400−803, 27−53−10−400−804 and27−53−10−400−805).











TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LUB MECHANIC0.25

4000 FLT HRS600

JUN 20/05

12−690−100

PAGE 5 OF 6

04−005


1

1

1

1

Lubrication of the Right Outboard FlapFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LUB MECHANIC0.25

4000 FLT HRS600

JUN 20/05

12−690−100

PAGE 6 OF 6

1. Bute door hinge.

2. Bute door rollers.

A

BC

C

C

C2

06−012

06−012

Lubrication of the Right Outboard FlapFigure 2

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

27

LU MECHANIC0.42

5500 FLT HRS600

Lubrication of the Right−Wing Aileron Control Cables at the Wing PulleyInterfaces

12−690−702

JUN 20/05

PAGE 1 OF 4

AMTOSS 12−20−27−640−810








(2) Compound, corrosion−inhibiting, penetrating (Type 1)(15−003).


(1) Inspection of Wire−Rope Control Cables and RelatedComponents (TASK 20−23−00−200−801).

(2) Operational Test of the Aileron Control System (TASK27−11−00−710−801).

3. Job Set−Up

WARNING: PUT THE SAFETY DEVICES, THE WARNING SIGNS,AND THE WARNING PLACARDS IN POSITIONBEFORE YOU START A PROCEDURE ON OR NEAR: − FLIGHT CONTROLS − FLIGHT CONTROL SURFACES − COMPONENTS THAT MOVE.MAKE SURE THAT THERE ARE NO PERSONS OREQUIPMENT ON OR NEAR THE FLIGHT CONTROLSURFACES. ACCIDENTAL MOVEMENT OF THEFLIGHT CONTROLS CAN CAUSE INJURIES TOPERSONS AND/OR DAMAGE TO EQUIPMENT.

A. Install placards at the HYDRAULIC control panel and at theexternal service connections to give warnings againstpressurization of the hydraulic systems.

B. Install a placard on the engine start panel to give warnings notto dry motor the engines (to prevent pressurization of theapplicable hydraulic system No. 1 and No. 2 with theengine−driven hydraulic pumps).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

27

LU MECHANIC0.42

5500 FLT HRS600


12−690−702

JUN 20/05

PAGE 2 OF 4

C. Remove the wing access panels that follow:

(1) Shroud 698AB.

(2) Shroud 698BB.






4. Procedure

Refer to Figure 1.

WARNING: KEEP AWAY FROM THE GROUND SPOILERS, FLIGHTSPOILERS, AND SPOILERONS UNLESS YOU ARE SUREOF THE CONDITIONS THAT FOLLOW: − THERE IS NO HYDRAULIC PRESSURE TO THEAPPLICABLE ACTUATORS. − THE APPLICABLE HYDRAULIC SYSTEM IS MADESAFE FROM THE ACCIDENTAL APPLICATION OFHYDRAULIC PRESSURE.ACCIDENTAL MOVEMENT OF THE SPOILERS CANCAUSE INJURIES TO PERSONS AND DAMAGE TOEQUIPMENT.

A. Clean the aileron control cables with a clean cloth and 15−003corrosion−inhibiting compound (Ref. TASK20−23−00−200−801).

B. Apply a thin, equal layer of 04−001 grease to the pulleygrooves and cables. The grease must cover a minimum of 5.0in (127 mm) on each side of the pulleys when the ailerons areat neutral.

NOTE: Apply the grease with a brush. If you apply thegrease with a rag, grease will be removed from theouter strands of the cable.

NOTE: Make sure the treated cable is in contact with thepulleys through the full travel of the aileron controlsystem.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

27

LU MECHANIC0.42

5500 FLT HRS600


12−690−702

JUN 20/05

PAGE 3 OF 4

NOTE: The cables are thoroughly greased when a visiblelayer is seen on the outer surface.

5. Close Out


B. Do an operational test of the aileron control system (Ref. TASK27−11−00−710−801).

C. Install the wing access panels that follow:

(1) Shroud 698AB.

(2) Shroud 698BB.






D. Remove the applicable warning placards.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

27

LU MECHANIC0.42

5500 FLT HRS600


12−690−702

JUN 20/05

PAGE 4 OF 4

rtc1

2590

702_

001.

dg,

lr, 1

7/11

/04

DC

AB

A

B

C D

04−001

15−003

04−001

15−003

04−001

15−003

04−001

15−003


HAND

BRUSH

04−001

04−001

04−00104−001

NOTE

Left side is shown,right side is opposite

Lubrication of the Aileron Wing Pulleys and Control CablesFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Nose Landing Gear

26

LUB/SVC 0.08

700

MECHANIC

SEP 30/04

A 12−710−001

PAGE 1 OF 5

AMTOSS 12−20−32−640−801


Refer to MRB 32−00−00−03 and MRB 32−50−01−09.



(1) Grease gun (None specified).

(2) Brush, one inch (25 mm) wide (or equivalent) (Nonespecified).


(1) Hydraulic fluid, petroleum base (02−002).


(3) Cloth, cleaning, low−lint, Type II − General use (05−001).


(1) Installation of the Nose Landing Gear Lockpin (TASK10−11−00−400−801).

(2) Installation of the Main Landing Gear Lockpins (TASK10−11−00−400−802).

(3) Open and isolate the Nose Landing Gear Forward Doors(TASK 32−22−01−980−801).

(4) Close the Nose Landing Gear Forward Doors (TASK32−22−01−980−802).


3. Job Set−Up

WARNING: MAKE SURE THAT THE LOCKPINS ARE INSTALLEDON THE NOSE AND MAIN LANDING GEARS. THENOSE AND MAIN LANDING GEARS CANACCIDENTALLY RETRACT. THIS CAN CAUSEINJURIES TO PERSONS AND/OR DAMAGE TOEQUIPMENT.

A. Make sure that the safety lockpins are installed at the noselanding gear and at the main landing gear (Ref. TASK10−11−00−400−801 and TASK 10−11−00−400−802).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LUB/SVC 0.08

700

MECHANIC

SEP 30/04

A 12−710−001

PAGE 2 OF 5

WARNING: IF THE NOSE DOOR MAINTENANCE SWITCH ATTHE EXTERNAL SERVICES PANEL IS SET TO THE�FLT NORM" POSITION, THE NOSE LANDING GEAR(NLG) FORWARD DOORS WILL CLOSE WHENHYDRAULIC SYSTEM NO. 3 IS PRESSURIZED.WHEN YOU DO MAINTENANCE ON OR NEAR THENLG WITH THE FORWARD DOORS OPEN, MAKESURE THAT YOU:−ALWAYS SET THE NOSE DOOR MAINTENANCESWITCH TO THE �OPEN" POSITION TO ISOLATETHE NLG FORWARD DOORS FROM HYDRAULICSYSTEM NO. 3−RELEASE THE PRESSURE FROM HYDRAULICSYSTEM NO. 3.FAILURE TO DO THIS CAN CAUSE INJURY TOPERSONS AND/OR DAMAGE TO EQUIPMENT.

B. Open and isolate the forward doors of the nose landing gear(NLG) (Ref. TASK 32−22−01−980−801).

C. Clean the NLG to remove all dirt, contamination, and moisturefrom the lubrication fittings and adjacent areas.

4. Procedure

Refer to Figure 1.

A. Lubricate the NLG as follows:

(1) Apply 04−005 grease with a grease gun to the greasefittings at the locations that follow:

NOTE: The grease is to be applied until the old greasehas been removed and new grease can be seenvisually.

(a) The pivot trunnions (1) at the top of the NLG mainfitting.

(b) The steering collar (2).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LUB/SVC 0.08

700

MECHANIC

SEP 30/04

A 12−710−001

PAGE 3 OF 5

CAUTION: USE A HAND POWERED GREASE GUN TOAPPLY GREASE TO THE UPPER STEERINGSLEEVE/LOWER STEERING PLATE GREASEFITTINGS. TOO MUCH PRESSURE CANDAMAGE THE FEEDBACK RVDT OR THESWIVEL VALVE.

(c) The upper steering sleeve/lower steering plate (3) forthe left and right steering actuators. The grease willbe released from between the bushings in the uppersteering sleeve/lower steering plate and the relatedsteering actuator cylinder pivot.

NOTE: Before the lubrication procedure, it ispossible that lubricant will be seen at thevent holes of the left and/or right steeringactuator cylinder−pivots. This is lubricantthat was applied to the splines of thefeedback RVDT when it was installed and isa usual condition. The lubricant must notleak form the vent holes during thelubrication procedure. Damage to thefeedback RVDT can occur if the lubricant isforced around the internal preformedpacking (and out of the vent holes), whengrease is applied with too much pressure tothe grease fittings in the upper steeringsleeve/lower steering plate (3).

(d) The steering−actuator rod ends (4).

(e) The forked end (5) at the top of the upper torque link.

(f) The pins (6) that connect the upper and lower torquelinks.

(g) The forked end (7) at the bottom of the lower torquelink.

(h) The upper pivot of the drag brace (8).

(i) The lock mechanism (9) in the upper end of the dragbrace. Apply the grease until grease comes out ofthe vent hole.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LUB/SVC 0.08

700

MECHANIC

SEP 30/04

A 12−710−001

PAGE 4 OF 5

(j) The left and right sides of the center hinge of the dragbrace (10).

(k) The lower hinge point (11) of the drag brace.

(l) Each end of the retraction actuator (12).

(2) Clean the chrome surfaces (13) of the shock strut (Ref.TASK 51−26−00−110−801).

(3) Apply a small quantity of 02−002 hydraulic fluid with abrush to the chrome surfaces (13) of the shock strut.

CAUTION: WHEN YOU CLEAN A GREASE OR OIL LEAKAGE,USE ONLY APPROVED CLEANING MATERIALS,SOME CLEANING MATERIALS CAN CAUSEDAMAGE TO HYDRAULIC PARTS AND COMPOSITEMATERIALS.

B. Use a low−lint cloth to remove unwanted grease from thelubrication fittings and adjacent areas.

5. Close Out

A. Close the forward doors of the nose landing gear (Ref. TASK32−22−01−980−802).


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LUB/SVC 0.08

700

MECHANIC

SEP 30/04

A 12−710−001

PAGE 5 OF 5

8

9

10

11

3

2

1

12

5

6

7

1

Left grease nipples shown,right grease nipples opposite.

NOTE1

A

GREASEVENTHOLE


Grease gunBrush

13

02−002

04−005

04−005

04−005

04−005

04−005

04−005

04−005

04−005

04−005

04−005

04−005

41

04−005

B

B

Lubrication of the Nose Landing GearFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Servicing of the Nose Landing Gear Shock Strut

27 JUN 20/05

SV MECHANIC0.50

2500 FLT HRS700 12−710−002

PAGE 1 OF 10

AMTOSS 12−12−32−610−803





(1) Service cart, high/low pressure nitrogen gas(CTR200−538).

(2) Kit, nitrogen charging adapter (G601R121611−1).

(3) Servicing unit, 2 U.S. gallons (7.6 liters)(PF54124−3PWS).

(4) Regulator − strut/accumulator service (14−6804−6000).

(5) Kit − charging and gauging, strut/accumulator(14−6805−600).

(6) Intensifier, nitrogen gas (shop air powered or residual gaspowered) (18−4201−1010 or 90970).


(1) Fluid, petroleum based hydraulic (02−002).

(2) Landing gear shock strut fluid, anti−wear (02−003).

(3) Nitrogen, technical (05−002).

(4) Lock wire (05−005).

C. Parts


4 Oil filler plug 1 IPC 32−21−00−03−014



(1) Installation of the Nose Landing Gear Lock Pin (TASK10−11−00−400−801).

(2) Installation of the Main Landing Gear Lock Pins (TASK10−11−00−400−802).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.50

2500 FLT HRS700 12−710−002

PAGE 2 OF 10

(3) Extension Check and Adjustment (with Nitrogen) of theNLG Shock Strut (TASK 12−12−32−220−802).

(4) Hydraulic Safety Precautions (TASK29−00−00−910−801).

(5) Open and Isolate the Nose Landing Gear Forward Doors(TASK 32−22−01−980−801).

3. Job Set−Up

WARNING: MAKE SURE THAT THE SAFETY LOCKPINS AREINSTALLED ON THE NOSE AND MAIN LANDINGGEAR. THE NOSE AND MAIN LANDING GEAR CANACCIDENTALLY RETRACT. THIS CAN CAUSEINJURIES TO PERSONS AND/OR DAMAGE TOEQUIPMENT.

A. Install the safety lockpins at the nose landing gear and at themain landing gear (Ref. TASK 10−11−00−400−801 and TASK10−11−00−400−802).

WARNING: MAKE SURE THAT THE WHEEL CHOCKS ARE PUTAT THE MAIN WHEELS. IF YOU DO NOT DO THIS,THE AIRCRAFT CAN MOVE. THIS CAN CAUSEINJURIES TO PERSONS AND/OR DAMAGE TOEQUIPMENT.

B. Install the wheel chocks.

CAUTION: MAKE SURE THAT ALL EQUIPMENT IS AWAY FROMTHE AIRCRAFT WHEN YOU RELEASE THENITROGEN FROM THE SHOCK STRUT. THEAIRCRAFT WILL LOWER WHEN THE NITROGEN ISRELEASED. EQUIPMENT NEAR OR UNDER THEAIRCRAFT CAN CAUSE DAMAGE TO IT.

C. Make sure that the weight of the aircraft is fully on the landinggear and that all equipment is clear of the aircraft before youdeflate the shock strut.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.50

2500 FLT HRS700 12−710−002

PAGE 3 OF 10

WARNING: IF THE NOSE DOOR MAINTENANCE SWITCH ATTHE EXTERNAL SERVICES PANEL IS SET TO THE�FLT NORM" POSITION, THENOSE−LANDING−GEAR (NLG) FORWARD DOORSWILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 ISPRESSURIZED.WHEN YOU DO MAINTENANCE ON OR NEAR THENLG WITH THE FORWARD DOORS OPEN, MAKESURE THAT YOU:− ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE �OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3− RELEASE THE PRESSURE FROM HYDRAULIC NO. 3.FAILURE TO DO THIS CAN CAUSE INJURY TOPERSONS AND/OR DAMAGE TO EQUIPMENT.

D. If open, isolate the NLG forward doors from hydraulic systemNo. 3 (Ref. TASK 32−22−01−980−801).

E. Before you start this procedure, do a check of the pressure inthe nitrogen bottles.

NOTE: If necessary, install a nitrogen gas intensifier on theservicing equipment to increase its output pressure.A maximum output pressure of 1500 PSI (10342 kPa)may be necessary.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.50

2500 FLT HRS700 12−710−002

PAGE 4 OF 10

WARNING: OBEY THE SAFETY PRECAUTIONS THAT FOLLOWWHEN YOU DO WORK WITH HIGH−PRESSUREGAS NITROGEN:− USE A FACE SHIELD− USE SAFETY GOGGLES− CLOSE THE VALVES ON THE PIPING AND THE TANKS WHEN THEY ARE NOT USED OR WHEN EMPTY− GO TO AN AREA THAT HAS A GOOD FLOW OF CLEAN AIR AND GET MEDICAL AID IF YOU BREATHE IN GAS NITROGEN.NITROGEN CAN CAUSE SUFFOCATION ANDDEATH WHEN IT IS BREATHED IN.

WARNING: OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONSWHEN YOU DO WORK ON THE HYDRAULICSYSTEM AND/OR A HYDRAULIC SYSTEMCOMPONENT. IF YOU DO NOT DO THIS, YOU CANCAUSE INJURIES TO PERSONS AND/OR DAMAGETO EQUIPMENT.

F. Obey the hydraulic safety precautions (Ref. TASK29−00−00−910−801).

4. Procedure

Refer to Figure 1 and Figure 2.

WARNING: CLOSE ALL VALVES ON SERVICING EQUIPMENTAND ON THE EQUIPMENT THAT IS SERVICEDWHEN THE DISCONNECTION OF HOSES ANDEQUIPMENT IS MADE. DISCONNECT HOSESSLOWLY TO RELEASE THE RESIDUAL PRESSUREFROM THE EQUIPMENT. FAILURE TO DO THIS CANCAUSE INJURIES.

A. With the aircraft weight on the landing gear, do the servicing ofthe NLG shock strut with oil and nitrogen as follows:

NOTE: The chrome extension/compression limits for theNLG shock strut are:− extended fully: 14.50 inches (368.3 mm)− compressed fully: 0.00 inches (0.00 mm).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.50

2500 FLT HRS700 12−710−002

PAGE 5 OF 10

NOTE: Servicing oil 02−002 or 02−003 can be used in theprocedure that follows. They can be mixed in anyproportion.

(1) Open the protective cover at the bottom of the shock strutand remove the dust cap (1) from the nitrogen chargingvalve (2).

WARNING: DO NOT DEFLATE THE STRUT TOO QUICKLY.YOU CAN CAUSE A SPRAY OF OIL. THIS CANCAUSE INJURIES TO PERSONS.

(2) Slowly loosen the thin nut (3) on the nitrogen chargingvalve (2) and let the shock strut fully deflate. Make surethat the shock strut deflates at a rate of less than 1 inch(25.4 mm) every 5 seconds.

(3) When the shock strut is fully deflated, remove and discardthe lock wire from the oil filler plug (5) at the top of theshock strut.

WARNING: MAKE SURE THAT THE NITROGEN CHARGE ISFULLY RELEASED FROM THE SHOCK STRUTBEFORE THE OIL FILLER PLUG IS REMOVED.IF YOU DO NOT DO THIS, INJURIES CANOCCUR.

CAUTION: RELEASE THE OIL FILLER PLUG SLOWLY.THERE CAN POSSIBLY BE AIR PRESSURE ONTHE OIL SIDE OF THE FLOATING PISTON IFTHE PISTON IS LEAKING.

(4) Remove the oil filter plug (5) and discard its preformedpacking (6).

(5) Install a MS28778−4 preformed packing (7) on anAN815−4D union (8).

(6) Install the AN815−4D union (8) with the MS28778−4preformed packing (7) in the oil filler port (as an adapterfor the hydraulic servicing unit).

(7) Connect the line from the hydraulic servicing unit to theAN815−4D union (8) in the oil filler port.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.50

2500 FLT HRS700 12−710−002

PAGE 6 OF 10

(8) Slowly pump 02−002 or 02−003 oil into the shock strutuntil it is full and the gauge on the servicing unit shows apressure of 100 PSI (689 kPa).

(9) Open the valve on the hydraulic servicing unit anddecrease the pressure to 0 PSI (0 kPa).

(10) Disconnect the servicing unit from the AN815−4D union(8) in the oil filler port on the NLG shock strut and closethe valve on the servicing unit.

(11) Remove the AN815−4D union (8) with the MS28778−4preformed packing (7) from the oil filler port.

(12) If necessary, manually fill the shock strut with 02−002 or02−003 oil until it is full.

(13) Install a new preformed packing (6) on the oil filler plug(5).

(14) Install the oil filler plug (5) and safety it with lock wire.

(15) Connect the charging and gauging kit to the nitrogencharging valve (2) at the bottom of the shock strut.

(16) Connect the hose from the nitrogen bottle/serviceregulator to the charging and gauging kit.

CAUTION: DO NOT PRESSURIZE THE SHOCK STRUT TOMORE THAN 1500 PSI (10342 KPA).

(17) Pressurize the shock strut until the chrome extensionmeasures 6.5 inches (165 mm).

(18) Read the shock strut pressure on the charging andgauging kit.

(19) If the ambient temperature is 41°F to 77°F (5°C to 25°C),refer to the NLG shock strut service plate and find thecorrect extension for the shock strut as follows:

(a) On the service plate, find the pressure gauge readingon the vertical scale (PRESSURE GAUGE READING(PSI)).

(b) From the pressure reading, go across horizontally tothe area (range) between the two lines of theSERVICING CURVE.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.50

2500 FLT HRS700 12−710−002

PAGE 7 OF 10

(c) From this range, between the lines of the SERVICINGCURVE, go down vertically to the ’X’ DIMENSION(INCHES) scale.

(d) Record the range from the ’X’ DIMENSION (INCHES)scale.

(20) If the chrome extension (6.5 inches (165 mm)) is in thelimits found on the ’X’ DIMENSION (INCHES) scale, theshock strut extension is satisfactory.

(21) Add nitrogen to the shock strut if the dimension calculatedon the service plate is higher than 6.5 inches (165 mm).

NOTE: It is necessary to release nitrogen, release itthrough the nitrogen charging valve after theservice equipment is removed. Make sure thatall valves are closed when the service equipmentis disconnected.

(22) If the ambient temperature is −65°F to 86°F (−54°C to30°C), refer to the alternate NLG servicing curve in Figure2 and find the correct extension for the shock strut asfollows:

(a) On the NLG servicing curve, find the strut pressurereading on the vertical scale (Strut Pressure X 103

(PSI)).

(b) From the pressure reading, go across horizontally toa point on the servicing curve depending on theambient temperature.

(c) From this point on the servicing curve, go downvertically to the Exposed Chrome (in.) scale.

(d) Record the range from the Exposed Chrome (in.)scale.

(23) If the chrome extension (6.5 inches (165 mm)) is in thelimits found on the Exposed Chrome (in.) scale, the shockstrut extension is satisfactory.

(24) Add nitrogen to the shock strut if the dimension calculatedon the NLG servicing curve is higher than 6.5 inches (165mm).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.50

2500 FLT HRS700 12−710−002

PAGE 8 OF 10

NOTE: It is necessary to release nitrogen, release itthrough the nitrogen charging valve after theservice equipment is removed. Make sure thatall valves are closed when the service equipmentis disconnected.

(25) When the shock strut is at the correct dimension, closethe thin nut (3) on the nitrogen charging valve (2).

(26) Tighten the thin nut (3) to a maximum of 50 lbf·in. ±5 lbf·in(5.65N·m ±1.13N·m).

(27) Close all of the valves on the service equipment.

(28) Carefully disconnect the charging and gauging kit fromthe nitrogen charging valve (2).

(29) If the dimension calculated on the service plate or on thealternate NLG servicing curve was lower than 6.5 inches(165 mm), do the steps that follow:

(a) Slowly open the thin nut (3) and release nitrogen fromthe shock strut until the shock strut is at the correctdimension.

(b) Close the thin nut (3) on the nitrogen charging valve(2).

(c) Tighten the thin nut (3) to a maximum of 50 lbf·in. ±5lbf·in (5.65N·m ±1.13N·m).

(30) Install the dust cap (1) on the nitrogen charging valve (2).

B. Do an extension check and, if necessary, adjustment of theshock strut after the aircraft is moved or after 24 hours (Ref.TASK 12−12−32−220−802).

5. Close Out


B. Clean any 02−002 or 02−003 oil that remains from the workarea with soap and water and dry the gear with a low−lintcloth.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27 JUN 20/05

SV MECHANIC0.50

2500 FLT HRS700 12−710−002

PAGE 9 OF 10

rtc1

2710

701_

001.

dg, l

r, 17

/12/

03

NOSE LANDING GEAR

1. Dust cap.2. Nitrogen charge valve.3. Thin nut.

5. Oil filler plug.6. Preformed packing.

LEGEND

X = Chrome extension.

NOTE

C

5

12

3

B

X

A

B

SHOCKSTRUT

SERVICEPLATE

C

ASSEMBLY

8. AN815−4D union.

7

6

VALVECOVER

8

DIAPHRAGMASSEMBLY

4

4. Preformed packing.

A

7. MS28778−4 preformed packing.

Servicing of the Nose Landing Gear Shock StrutFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27 JUN 20/05

SV MECHANIC0.50

2500 FLT HRS700 12−710−002

PAGE 10 OF 10

rtc1

2710

701_

002.

dg, l

r, 17

/12/

03

0.0

2.0

4.0

6.0

8.0

10.0

12.0

14.0

16.0

EX

PO

SE

D C

HR

OM

E (

in. )

3.0

2.5

2.0

1.5

1.0

0.5

0.0

18 16 14 12 10

8 6 4 2 0

STRUT PRESSURE ( X 10 PSI )

LOAD ( X 10 LBS )

30

15

0

−54

−30

3

3

−15

Servicing of the Nose Landing Gear Shock StrutFigure 2

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Left Main Landing Gear

26

LUB/SVC 0.08

700

MECHANIC

SEP 30/04

A 12−730−001

PAGE 1 OF 5

AMTOSS 12−20−32−640−802















3. Job Set−Up



B. Clean the main landing gear (MLG) to remove all dirt,contamination, and moisture from the lubrication fittings andadjacent areas.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LUB/SVC 0.08

700

MECHANIC

SEP 30/04

A 12−730−001

PAGE 2 OF 5

4. Procedure


A. Lubricate the MLG as follows:



(a) The mounting trunnions (1) at the forward and aftends of the MLG main fitting.

(b) The hinge joint (2) at the inboard end of the downlockassist actuator.

(c) The shock strut attachment point (3) to the MLG mainfitting (at three locations) on the inboard side.

(d) The trailing arm attachment point (4) to the shockstrut (at three locations) on the inboard side.

(e) At the bottom attachment point (5) of the shock strut(at one location) on the aft side.

(f) Each side of the trailing arm pivot at the bottom forkof the main gear leg (6).

(g) Each end (7) of the retraction actuator.

(2) Clean the chrome area (8) of the shock strut (Ref. TASK51−26−00−110−801).

(3) Apply a small quantity of 02−002 hydraulic fluid with abrush to the chrome area (8) of the shock strut.

B. Apply 04−005 grease with the grease gun and the lubricatingnozzle to the grease fitting (9) on the door operating bellcrank.

CAUTION: WHEN YOU CLEAN A GREASE OR OIL LEAKAGE,USE ONLY APPROVED CLEANING MATERIALS.SOME CLEANING MATERIALS CAN CAUSEDAMAGE TO HYDRAULIC PARTS AND COMPOSITEMATERIALS.

C. Use a low−lint cloth to remove unwanted grease from thelubrication fittings and adjacent areas.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LUB/SVC 0.08

700

MECHANIC

SEP 30/04

A 12−730−001

PAGE 3 OF 5

5. Close Out


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LUB/SVC 0.08

700

MECHANIC

SEP 30/04

A 12−730−001

PAGE 4 OF 5

04−005

1

04−005

2

04−005

5

04−005

6

04−005

7

Left grease nipple shown,right grease nipple opposite.

NOTES

SYMBOL APPLICATION METHODGrease gunBrush

8

02−002

A

04−005

3A

B

2 Three locations.

11

B

04−005

42

2

Left Main Landing Gear − LubricationFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LUB/SVC 0.08

700

MECHANIC

SEP 30/04

A 12−730−001

PAGE 5 OF 5

SYMBOL APLICATION METHOD

Grease gun

9

Right equipment shown,left equipment opposite.

04−005

NOTE

Lubrication of the Left Main Landing GearFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Servicing of the Left Main Landing Gear Shock Strut

27 JUN 20/05

SV MECHANIC0.58

2500 FLT HRS700 12−730−002

PAGE 1 OF 9

AMTOSS 12−12−32−610−801







(3) Servicing unit, 2 U.S. gallons (7.6 liters) or 5 U.S. gallons(18.9 liters) (PF54124−3PWS or PF53481−9PWS).




(7) Hose, transparent plastic (None specified).

(8) Container, petroleum−based hydraulic−fluid resistant(None specified).








(3) Extension Check and Adjustment (with Nitrogen) of theMLG Shock Strut (TASK 12−12−32−220−801).


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.58

2500 FLT HRS700 12−730−002

PAGE 2 OF 9

3. Job Set−Up







D. Before you start this procedure, do a check of the pressure inthe nitrogen bottles.


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.58

2500 FLT HRS700 12−730−002

PAGE 3 OF 9



E. Obey the hydraulic safety precautions (Ref. TASK29−00−00−910−801).

4. Procedure

Refer to Figure 1.


A. With the aircraft weight on the landing gear, do the servicing ofthe MLG shock strut with oil and nitrogen as follows:

NOTE: The procedure for one MLG shock strut is given. Theprocedure for the opposite side is the same. Alwayscomplete the servicing procedure for one shock strutbefore doing the servicing of the opposite side.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.58

2500 FLT HRS700 12−730−002

PAGE 4 OF 9

NOTE: The chrome extension/compression limits for theMLG shock strut are:− extended fully: 9.58 inches (243.33 mm)− compressed fully: −0.29 inches (−7.36 mm) (chrome inside cylinder).


(1) Remove the dust cap (1) from the nitrogen charging valve(2).

(2) Connect a transparent plastic hose to the nitrogencharging valve (2) and put the free end of the plastic hosein a container.


(3) Slowly loosen the thin nut (3) on the nitrogen chargingvalve (2) and let the shock strut fully deflate.

NOTE: Make sure that the shock strut deflates at a rateof less than 1 inch (25.4 mm) every 5 seconds.

(4) When the strut is fully deflated, remove the dust cap (4)from the oil−filler check valve (5) at the bottom of theshock strut.

(5) Connect the line from the oil servicing unit to the oil−fillercheck valve (5).

(6) Slowly pump 02−002 or 02−003 oil into the shock strutuntil a clear flow of oil (no air bubbles) comes out throughthe hose attached to the nitrogen charging valve (2).

(7) Disconnect the oil servicing unit from the oil−filler checkvalve (5).

(8) Install the dust cap (4) on the oil−filler check valve (5).

(9) Disconnect the plastic hose from the nitrogen chargingvalve (2).

(10) Connect the charging and gauging kit to the nitrogencharging valve (2).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.58

2500 FLT HRS700 12−730−002

PAGE 5 OF 9


WARNING: DO NOT PRESSURIZE THE SHOCK STRUT TOMORE THAN 3000 PSI (20685 KPA). DAMAGETO EQUIPMENT AND/OR INJURIES TOPERSONS CAN OCCUR.

(12) Pressurize the shock strut until the chrome extensionmeasures 2.08 inches (52.8 mm) and then immediatelystop the supply of nitrogen.


(14) If the ambient temperature is 41°F to 77°F (5°C to 25°C),refer to MLG shock strut strut service plate and find thecorrect extension for the shock strut as follows:

(a) On the service plate, find the pressure gauge readingon vertical scale (PRESSURE GAUGE READING(PSI)).




(15) If the chrome extension (2.08 inches (52.8 mm) is in thelimits found on the ’X’ DIMENSION (INCHES) scale, theshock strut extension is satisfactory.

(16) Add nitrogen to the shock strut if the dimension calculatedon the service plate is higher than 2.08 inches (52.8 mm).

NOTE: Release nitrogen, if necessary, through thecharging valve after the service equipment isremoved. Make sure that all valves are closedwhen service equipment is disconnected.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.58

2500 FLT HRS700 12−730−002

PAGE 6 OF 9

(17) If the ambient temperature is −65°F to 86°F (−54°C to30°C), refer to the alternate MLG servicing curve shown inFigure 2 and find the correct extension for the shock strutas follows:

(a) On the alternate MLG servicing curve, find the strutpressure reading on vertical scale (STRUTPRESSURE (X 103 PSI)).



(d) Record the reading from the Exposed Chrome (in.)scale.

(18) If the chrome extension (2.08 inches (52.8 mm) is in thelimits found on the Exposed Chrome (in.) scale, the shockstrut extension is satisfactory.

(19) Add nitrogen to the shock strut if the dimension calculatedon the servicing curve is higher than 2.08 inches (52.8mm).


(20) Close the thin nut (3) on the nitrogen charging valve (2).

(21) Tighten the thin nut (3) to 50 lbf·in. ±5 lbf·in (5.65N·m±1.13N·m).

(22) Close all valves on the service equipment.


(24) If the dimension calculated on the service plate or on theservicing curve was lower than 2.08 inches (52.8 mm), dothe steps that follow:

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.58

2500 FLT HRS700 12−730−002

PAGE 7 OF 9


(b) Close the thin nut (3).




5. Close Out

A. Clean any 02−002 or 02−003 oil that remains from the workarea with soap and water and dry the gear with a low−lintcloth.


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27 JUN 20/05

SV MECHANIC0.58

2500 FLT HRS700 12−730−002

PAGE 8 OF 9

rtc1

2710

701_

003.

dg, l

r, 17

/12/

03

1. Dust cap.2. Nitrogen charging valve.

LEGEND

X

3

2

1

54

MAIN LANDING GEAR

3. Thin nut.4. Dust cap.5. Oil filler check valve.


NOTE

SHOCKSTRUT

ASSEMBLY

SERVICEPLATE

A

A

B

C

B

C

Servicing of the Left Main Landing Gear Shock StrutFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27 JUN 20/05

SV MECHANIC0.58

2500 FLT HRS700 12−730−002

PAGE 9 OF 9

rtc1

2710

701_

004.

dg, l

r, 17

/12/

03

0.0

1.0

2.0

3.0

4.0

5.0

6.0

7.0

8.0

9.0

10.0

EX

PO

SE

D C

HR

OM

E (

in.)

6.0

5.5

5.0

4.5

4.0

3.5

3.0

2.5

2.0

1.5

1.0

0.5

0.0

100 90 80 70 60 50 40 30 20 10 0

3

3STRUT PRESSURE ( X 10 PSI )

LOAD ( X 10 LBS )

30 15

0

−15 −30 −54

−1.

0

Servicing of the Left Main Landing Gear Shock StrutFigure 2

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Right Main Landing Gear

26

LUB/SVC 0.08

700

MECHANIC

SEP 30/04

A 12−740−001

PAGE 1 OF 5

AMTOSS 12−20−32−640−802















3. Job Set−Up



B. Clean the main landing gear (MLG) to remove all dirt,contamination, and moisture from the lubrication fittings andadjacent areas.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LUB/SVC 0.08

700

MECHANIC

SEP 30/04

A 12−740−001

PAGE 2 OF 5

4. Procedure


A. Lubricate the MLG as follows:



(a) The mounting trunnions (1) at the forward and aftends of the MLG main fitting.

(b) The hinge joint (2) at the inboard end of the downlockassist actuator.

(c) The shock strut attachment point (3) to the MLG mainfitting (at three locations) on the inboard side.

(d) The trailing arm attachment point (4) to the shockstrut (at three locations) on the inboard side.

(e) At the bottom attachment point (5) of the shock strut(at one location) on the aft side.

(f) Each side of the trailing arm pivot at the bottom forkof the main gear leg (6).

(g) Each end (7) of the retraction actuator.

(2) Clean the chrome area (8) of the shock strut (Ref. TASK51−26−00−110−801).

(3) Apply a small quantity of 02−002 hydraulic fluid with abrush to the chrome area (8) of the shock strut.

B. Apply 04−005 grease with the grease gun and the lubricatingnozzle to the grease fitting (9) on the door operating bellcrank.

CAUTION: WHEN YOU CLEAN A GREASE OR OIL LEAKAGE,USE ONLY APPROVED CLEANING MATERIALS.SOME CLEANING MATERIALS CAN CAUSEDAMAGE TO HYDRAULIC PARTS AND COMPOSITEMATERIALS.

C. Use a low−lint cloth to remove unwanted grease from thelubrication fittings and adjacent areas.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LUB/SVC 0.08

700

MECHANIC

SEP 30/04

A 12−740−001

PAGE 3 OF 5

5. Close Out


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LUB/SVC 0.08

700

MECHANIC

SEP 30/04

A 12−740−001

PAGE 4 OF 5

04−005

1

04−005

2

04−005

5

04−005

6

04−005

7

Left grease nipple shown,right grease nipple opposite.

NOTES

8

02−002

A

04−005

3A

B

2 Three locations.

11

B

04−005

42

2

SYMBOL APPLICATION METHODGrease gunBrush

Right Main Landing Gear − LubricationFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LUB/SVC 0.08

700

MECHANIC

SEP 30/04

A 12−740−001

PAGE 5 OF 5


Grease gun

9

Right equipment shown,left equipment opposite.

04−005

NOTE

Lubrication of the Right Main Landing GearFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Servicing of the Right Main Landing Gear Shock Strut

27 JUN 20/05

SV MECHANIC0.58

2500 FLT HRS700 12−740−002

PAGE 1 OF 9

AMTOSS 12−12−32−610−801







(3) Servicing unit, 2 U.S. gallons (7.6 liters) or 5 U.S. gallons(18.9 liters) (PF54124−3PWS or PF53481−9PWS).




(7) Hose, transparent plastic (None specified).

(8) Container, petroleum−based hydraulic−fluid resistant(None specified).








(3) Extension Check and Adjustment (with Nitrogen) of theMLG Shock Strut (TASK 12−12−32−220−801).


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.58

2500 FLT HRS700 12−740−002

PAGE 2 OF 9

3. Job Set−Up







D. Before you start this procedure, do a check of the pressure inthe nitrogen bottles.


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.58

2500 FLT HRS700 12−740−002

PAGE 3 OF 9



E. Obey the hydraulic safety precautions (Ref. TASK29−00−00−910−801).

4. Procedure

Refer to Figure 1.


A. With the aircraft weight on the landing gear, do the servicing ofthe MLG shock strut with oil and nitrogen as follows:

NOTE: The procedure for one MLG shock strut is given. Theprocedure for the opposite side is the same. Alwayscomplete the servicing procedure for one shock strutbefore doing the servicing of the opposite side.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.58

2500 FLT HRS700 12−740−002

PAGE 4 OF 9

NOTE: The chrome extension/compression limits for theMLG shock strut are:− extended fully: 9.58 inches (243.33 mm)− compressed fully: −0.29 inches (−7.36 mm) (chrome inside cylinder).


(1) Remove the dust cap (1) from the nitrogen charging valve(2).

(2) Connect a transparent plastic hose to the nitrogencharging valve (2) and put the free end of the plastic hosein a container.


(3) Slowly loosen the thin nut (3) on the nitrogen chargingvalve (2) and let the shock strut fully deflate.

NOTE: Make sure that the shock strut deflates at a rateof less than 1 inch (25.4 mm) every 5 seconds.

(4) When the strut is fully deflated, remove the dust cap (4)from the oil−filler check valve (5) at the bottom of theshock strut.

(5) Connect the line from the oil servicing unit to the oil−fillercheck valve (5).

(6) Slowly pump 02−002 or 02−003 oil into the shock strutuntil a clear flow of oil (no air bubbles) comes out throughthe hose attached to the nitrogen charging valve (2).

(7) Disconnect the oil servicing unit from the oil−filler checkvalve (5).

(8) Install the dust cap (4) on the oil−filler check valve (5).

(9) Disconnect the plastic hose from the nitrogen chargingvalve (2).

(10) Connect the charging and gauging kit to the nitrogencharging valve (2).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.58

2500 FLT HRS700 12−740−002

PAGE 5 OF 9


WARNING: DO NOT PRESSURIZE THE SHOCK STRUT TOMORE THAN 3000 PSI (20685 KPA). DAMAGETO EQUIPMENT AND/OR INJURIES TOPERSONS CAN OCCUR.

(12) Pressurize the shock strut until the chrome extensionmeasures 2.08 inches (52.8 mm) and then immediatelystop the supply of nitrogen.


(14) If the ambient temperature is 41°F to 77°F (5°C to 25°C),refer to MLG shock strut strut service plate and find thecorrect extension for the shock strut as follows:

(a) On the service plate, find the pressure gauge readingon vertical scale (PRESSURE GAUGE READING(PSI)).




(15) If the chrome extension (2.08 inches (52.8 mm) is in thelimits found on the ’X’ DIMENSION (INCHES) scale, theshock strut extension is satisfactory.

(16) Add nitrogen to the shock strut if the dimension calculatedon the service plate is higher than 2.08 inches (52.8 mm).


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.58

2500 FLT HRS700 12−740−002

PAGE 6 OF 9

(17) If the ambient temperature is −65°F to 86°F (−54°C to30°C), refer to the alternate MLG servicing curve shown inFigure 2 and find the correct extension for the shock strutas follows:

(a) On the alternate MLG servicing curve, find the strutpressure reading on vertical scale (STRUTPRESSURE (X 103 PSI)).



(d) Record the reading from the Exposed Chrome (in.)scale.

(18) If the chrome extension (2.08 inches (52.8 mm) is in thelimits found on the Exposed Chrome (in.) scale, the shockstrut extension is satisfactory.

(19) Add nitrogen to the shock strut if the dimension calculatedon the servicing curve is higher than 2.08 inches (52.8mm).


(20) Close the thin nut (3) on the nitrogen charging valve (2).


(22) Close all valves on the service equipment.


(24) If the dimension calculated on the service plate or on theservicing curve was lower than 2.08 inches (52.8 mm), dothe steps that follow:

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC0.58

2500 FLT HRS700 12−740−002

PAGE 7 OF 9


(b) Close the thin nut (3).




5. Close Out

A. Clean any 02−002 or 02−003 oil that remains from the workarea with soap and water and dry the gear with a low−lintcloth.


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27 JUN 20/05

SV MECHANIC0.58

2500 FLT HRS700 12−740−002

PAGE 8 OF 9

rtc1

2710

701_

003.

dg, l

r, 17

/12/

03

1. Dust cap.2. Nitrogen charging valve.

LEGEND

X

3

2

1

54

MAIN LANDING GEAR

3. Thin nut.4. Dust cap.5. Oil filler check valve.


NOTE

SHOCKSTRUT

ASSEMBLY

SERVICEPLATE

A

A

B

C

B

C

Servicing of the Right Main Landing Gear Shock StrutFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27 JUN 20/05

SV MECHANIC0.58

2500 FLT HRS700 12−740−002

PAGE 9 OF 9

rtc1

2710

701_

004.

dg, l

r, 17

/12/

03

0.0

1.0

2.0

3.0

4.0

5.0

6.0

7.0

8.0

9.0

10.0

EX

PO

SE

D C

HR

OM

E (

in.)

6.0

5.5

5.0

4.5

4.0

3.5

3.0

2.5

2.0

1.5

1.0

0.5

0.0

100 90 80 70 60 50 40 30 20 10 0

3

3STRUT PRESSURE ( X 10 PSI)

LOAD ( X 10 LBS )

30 15

0

−15 −30 −54

−1.

0

Servicing of the Right Main Landing Gear Shock StrutFigure 2

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Main Avionics Compartment Door

26

LU 0.03

800

MECHANIC

SEP 30/04

2A 12−810−001

PAGE 1 OF 2

AMTOSS 12−20−52−640−804





(1) Grease, Silicone (04−006)

3. Job Set−Up

A. Open the main avionics−compartment door (811).

4. Procedure

Refer to Figure 1.

A. Apply 04−006 grease to the wear surfaces of the latch pins(1).

B. Apply 04−006 grease to all push rod end bearings and hingepoints of the door latch mechanism (2),

5. Close Out


B. Close the main avionics−compartment door (811).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Lubrication of the Main Avionics Compartment Door

26

LU 0.03

800

MECHANIC

SEP 30/04

2A 12−810−001

PAGE 2 OF 2

1

04−006

2

04−006

ram

1220

523_

004.

dg, p

t/jc,

19/

12/0

0

A

A

LEGEND1. Latch pin.2. Latch mechanism.

VIEW LOOKING UP


Hand

Lubrication of the Main Avionics Compartment DoorFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Phase III Passenger Door

26

LU 0.25

800

MECHANIC

SEP 30/04

2A 12−830−001

PAGE 1 OF 5

Applicable only on aircraft with Phase III passenger door.

AMTOSS 12−20−52−640−809





(1) Grease gun.




3. Job Set−Up

A. Open the passenger door (832).

B. Remove the upper and lower steps.

C. Remove access panel from the passenger door (832JL).

4. Procedure

Refer to Figures 1, 2 and 3.

A. Lubricate the passenger door as follows:

(1) Lubricate the piano hinge as follows:

(a) Apply 04−006 grease with a grease gun to the twopiano hinge lubrication points (1) until 04−006 greaseextrudes from the forward and aft ends of the pianohinge.

(2) Lubricate the latch cam torque tube assembly as follows:

(a) Lift the passenger door until the bottom step lifts togive access to the latch cam torque tube assembly.Hold the door at this position.

(b) Apply 04−006 grease with a grease gun to the latchcam torque tube bearings at the torque tube brackets(4) .

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LU 0.25

800

MECHANIC

SEP 30/04

2A 12−830−001

PAGE 2 OF 5

(c) Apply 04−006 grease to the inner surfaces (5) of thelatch cam torque tube where they touch the pawl.

(d) Lower the door to the open position.

(3) Apply 04−006 grease to the handrail pivot points (3).

(4) Apply 04−006 grease to the vent flap hinge (2).

(5) On aircraft with new lubrication type support−pulleyretention bolt, apply 04−006 grease with a grease gun tothe support−pulley retention bolt (6).

5. Close Out

A. Install access panel on the passenger door (832JL).

B. Install the upper and lower steps.

C. Close the passenger door (832).

D. Remove all tools, equipment, and unwanted materials from thework area.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LU 0.25

800

MECHANIC

SEP 30/04

2A 12−830−001

PAGE 3 OF 5

FS319.00 FS333.002

1

04−006

04−006

AC

C


Hand

Grease gun

ram

1220

523_

012.

dg, p

t/jc,

02/

01/0

1

LEGEND

1. Hinge lubrication point.2. Vent flap hinge.

A

B

B

VIEW LOOKING DOWN

Phase III Passenger Door − LubricationFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LU 0.25

800

MECHANIC

SEP 30/04

2A 12−830−001

PAGE 4 OF 5

3

3

4

04−006

04−006

5

04−006

A

A

C

C

B


Hand

Grease gun

ram

1220

523_

013.

dg, p

t/jc,

28/

01/0

1

LEGEND

B

3. Handrail pivot point.4. Latch cam bracket.5. Latch cam.

Lubrication of the Phase III Passenger DoorFigure 2

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LU 0.25

800

MECHANIC

SEP 30/04

2A 12−830−001

PAGE 5 OF 5

ram

1220

523_

027.

dg, i

k, 0

2/05

/01

6. Retention bolt.LEGEND

AFTCOUNTERBALANCE

GAS−SPRING(REF)

6

SUPPORT PULLEY(REF)

SYMBOL APPLICATIONMETHOD

GREASE GUN

Lubrication of the Phase III Passenger DoorFigure 3

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Cargo Compartment Door

26

LU 0.03

800

MECHANIC

SEP 30/04

2A 12−830−002

PAGE 1 OF 3

AMTOSS 12−20−52−640−805







(1) Removal of the Cargo Compartment Linings (TASK25−52−01−000−801).

(2) Installation of the Cargo Compartment Linings (TASK25−52−01−400−801).

3. Job Set−Up

A. Open the cargo compartment door (834).

B. Remove the cargo door liner from the cargo door (Ref. TASK25−52−01−000−801).

4. Procedure

Refer to Figure 1.

A. Lift the door sufficiently to let the latch pins be clear of thestructure.

B. Clean the areas to be greased.

C. Apply 04−006 grease to the wear surfaces of the latch pins(1). Operate the door handle to move the latch pins in andout.

D. Apply 04−006 grease to all push rod bearings and hingepoints of the door latch mechanism (2).

E. Apply 04−006 grease to all roller assemblies (3).

5. Close Out


B. Install the cargo door liner from the cargo door (Ref. TASK25−52−01−400−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LU 0.03

800

MECHANIC

SEP 30/04

2A 12−830−002

PAGE 2 OF 3

C. Close the cargo compartment door (834).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LU 0.03

800

MECHANIC

SEP 30/04

2A 12−830−002

PAGE 3 OF 3

04−006

04−006

04−006

1

2

1

VIEW LOOKING OUTBOARD

A04−006

3

04−006

3

04−006

3

04−006

3

rtc1

2830

002_

001.

dg, r

t, 11

/07/

01

A


Hand

LEGEND1. Latch pin.2. Latch mechanism.3. Roller assembly.

Lubrication of the Cargo Compartment DoorFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Phase III Passenger Door Latch Pins

26

LU MECHANIC0.15

800 A 12−830−003

SEP 30/04

PAGE 1 OF 4

Applicable only on aircraft with Phase III passenger door.

AMTOSS 12−20−52−640−808





(1) Grease gun (None Specified).




(2) On aircraft with modified interlock mechanism (Post SB601R−52−068), Duct tape (05−044).

3. Job Set−Up


B. Remove the access panels that follow from the passengerdoor:

− 832BL, 832BR, 832DL, 832DR, 832FR, 832GL.

4. Procedure

On Phase III passenger door with unmodified interlock mechanism (Pre Modsum 601R12872 or Pre SB 601R−52−068)

Refer to Figure 1.

A. Lubricate the latch pins as follows:

(1) Apply grease to the latch pin grease fittings (1) untilgrease appears on the outboard face of the latch pinfittings (2).

(2) Operate the latch pin mechanism approximately 5 cyclesto evenly distribute the grease within the latch pin fitting(2).

(3) Remove excess grease from the latch pin fittings (2).

(4) Apply to the push rod fork−end (3).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LU MECHANIC0.15

800 A 12−830−003

SEP 30/04

PAGE 2 OF 4

(5) Do steps (1) and (4) for all remaining latch pins.

On Phase III passenger door with modified interlock mechanism (Post Modsum 601R12872 or Post SB 601R−52−068)

Refer to Figure 2.

B. Lubricate the latch pins as follows:

(1) Lower the handrails to raise the lower step panel.

(2) Apply grease to the latch pin grease fittings (1) untilgrease appears on the outboard face of the latch pinfittings (2).

(3) Depress the open lock lever and hold it in place with thepiece of duct tape.

(4) Operate the latch pin mechanism approximately 5 cyclesto evenly distribute the grease within the latch pin fitting(2).

(5) Remove excess grease from the latch pin fittings (2).

(6) Apply to the push rod fork−end (3).

(7) Do steps (1) and (5) for all remaining latch pins.

C. Remove the duct tape from the open lock lever.

D. Lift the door handrails to the upright position.

On all Phase III passenger doors

5. Close Out

A. Install the access panels that follow on the passenger door:

− 832BL, 832BR, 832DL, 832DR, 832FR, 832GL.

B. Close the passenger door (832).


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LU MECHANIC0.15

800 A 12−830−003

SEP 30/04

PAGE 3 OF 4

1. Latch pin grease nipple.2. Latch pin fitting.3. Push rod fork end.

Forward lubrication points shown,aft lubrication points similar.

NOTE

LEGEND

1

2

EXTENDED POSITION (6 PLACES)

04−006

3

04−006

ram

1220

523_

028.

dg, i

k, 0

4/05

/01


Hand

Grease gun

Lubrication of the Phase III Passenger Door LatchpinsFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LU MECHANIC0.15

800 A 12−830−003

SEP 30/04

PAGE 4 OF 4

1. Latch pin grease nipple.2. Latch pin fitting.3. Push rod fork end.

Forward lubrication points shown,aft lubrication points similar.

NOTE

LEGEND

1

2

EXTENDED POSITION (6 PLACES)

04−006

3

04−006

ram

1220

523_

029.

dg, i

k, 0

4/05

/01


Hand

Grease gun

OPEN LOCK(REF)

Lubrication of the Phase III Passenger Door LatchpinsFigure 2

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Phase III Passenger Door Outer Handle

26

LUB MECHANIC0.10

800 A 12−830−004

SEP 30/04

PAGE 1 OF 5

ON AIRCRAFT WITH PHASE III PASSENGER DOOR WITH P/N H3414−29 (CANADAIR P/N 601R38132−11) OUTER HANDLE(PRE MODSUM 601R13193 AND PRE MODSUM 601R14500)

AMTOSS 12−20−52−640−813





(1) Grease gun.





3. Job Set−Up



− 832JL and 832KL.

4. Procedure

ON PHASE III PASSENGER DOOR WITH UNMODIFIED INTERLOCK MECHANISM (PRE MODSUM 601R12872 OR PRE SB 601R−52−068)

Refer to Figure 1.

A. Lubricate the passenger door outer handle mechanism asfollows:

(1) Get access to the outer handle mechanism through thepressure valve door.

(2) Apply 04−006 grease through the grease nipple (1).

NOTE: Do not use too much grease; approximately 20grams (less than 1 ounce) will be required toinitially fill the handle cavity.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LUB MECHANIC0.10

800 A 12−830−004

SEP 30/04

PAGE 2 OF 5

(3) Extend the pull−in handle.

(4) Apply grease with hand to all the sliding parts of thepull−in mechanism (2).

(5) Eject the outer handle and with the end cover held in thedown position, rotate the pull−in handle slowly to spreadgrease throughout the mechanism, then close the handle.

(6) Repeat steps (2) and (4) until the grease is seen along theedges of the external trigger lever.

(7) After greasing, eject the outer handle and lower the doorto the open position.

ON PHASE III PASSENGER DOOR WITH MODIFIED INTERLOCK MECHANISM (POST MODSUM 601R12872 OR POST SB 601R−52−068)

Refer to Figure 2.

B. Lubricate the passenger door outer handle mechanism asfollows:


(2) Depress the open lock lever and hold it in place with apiece of duct tape 05−044.

(3) Use a grease gun and inject small quantity of grease04−006 through the grease nipple (1) on the outer handle.




(6) After each step, eject the outer handle with the pushtrigger and operate the pull−in handle slowly to spreadthe grease throughout the mechanism.

(7) Repeat steps (3) and (5) until excess the grease is seenalong the edges of the outer handle trigger cavity.

(8) Remove the duct tape from the open lock lever.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LUB MECHANIC0.10

800 A 12−830−004

SEP 30/04

PAGE 3 OF 5

(9) Lift the door handrails to the upright position.

ON ALL PHASE III PASSENGER DOORS

5. Close Out


− 832JL and 832KL.



TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LUB MECHANIC0.10

800 A 12−830−004

SEP 30/04

PAGE 4 OF 5

1. Grease fitting.LEGEND

1

04−006

PULL−INHANDLE

OUTERHANDLE

ram

1220

523_

030.

dg, j

c/ik

, 04/

05/0

1


Hand

Grease gun

2

04−006

2. Pull−in mechanism.

Lubrication of the Phase III Passenger Door Outer HandleFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LUB MECHANIC0.10

800 A 12−830−004

SEP 30/04

PAGE 5 OF 5

ram

1220

523_

031.

dg, i

k, 0

7/05

/01

PULL−INHANDLE

OUTERHANDLE



Hand

Grease gun

1

04−006

OPEN LOCKLEVER(REF)

2. Pull−in mechanism..

2

04−006


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LUB MECHANIC0.10

800 5A 12−830−005

SEP 30/04

PAGE 1 OF 5

ON AIRCRAFT WITH PHASE III PASSENGER DOOR WITH P/N H3414−33 (CANADAIR P/N 601R38132−13) OUTER HANDLE(PRE MODSUM 601R13193 AND POST MODSUM 601R14500)

AMTOSS 12−20−52−640−813





(1) Grease gun.





3. Job Set−Up



− 832JL and 832KL.

4. Procedure

ON PHASE III PASSENGER DOOR WITH UNMODIFIED INTERLOCK MECHANISM (PRE MODSUM 601R12872 OR PRE SB 601R−52−068)

Refer to Figure 1.

A. Lubricate the passenger door outer handle mechanism asfollows:

(1) Get access to the outer handle mechanism through thepressure valve door.

(2) Apply 04−006 grease through the grease nipple (1).


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LUB MECHANIC0.10

800 5A 12−830−005

SEP 30/04

PAGE 2 OF 5



(5) Eject the outer handle and with the end cover held in thedown position, rotate the pull−in handle slowly to spreadgrease throughout the mechanism, then close the handle.

(6) Repeat steps (2) and (4) until the grease is seen along theedges of the external trigger lever.

(7) After greasing, eject the outer handle and lower the doorto the open position.

ON PHASE III PASSENGER DOOR WITH MODIFIED INTERLOCK MECHANISM (POST MODSUM 601R12872 OR POST SB 601R−52−068)

Refer to Figure 2.

B. Lubricate the passenger door outer handle mechanism asfollows:


(2) Depress the open lock lever and hold it in place with apiece of duct tape 05−044.

(3) Use a grease gun and inject small quantity of grease04−006 through the grease nipple (1) on the outer handle.




(6) After each step, eject the outer handle with the pushtrigger and operate the pull−in handle slowly to spreadthe grease throughout the mechanism.

(7) Repeat steps (3) and (5) until excess the grease is seenalong the edges of the outer handle trigger cavity.

(8) Remove the duct tape from the open lock lever.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LUB MECHANIC0.10

800 5A 12−830−005

SEP 30/04

PAGE 3 OF 5

(9) Lift the door handrails to the upright position.

ON ALL PHASE III PASSENGER DOORS

5. Close Out


− 832JL and 832KL.



TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LUB MECHANIC0.10

800 5A 12−830−005

SEP 30/04

PAGE 4 OF 5


1

04−006

PULL−INHANDLE

OUTERHANDLE

ram

1220

523_

030.

dg, j

c/ik

, 04/

05/0

1


Hand

Grease gun

2

04−006

2. Pull−in mechanism..

Lubrication of the Phase III Passenger Door Outer Handle Figure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LUB MECHANIC0.10

800 5A 12−830−005

SEP 30/04

PAGE 5 OF 5

ram

1220

523_

031.

dg, i

k, 0

7/05

/01

PULL−INHANDLE

OUTERHANDLE



Hand

Grease gun

1

04−006

OPEN LOCKLEVER(REF)

2. Pull−in mechanism.

2

04−006


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Phase IV Passenger Door Latch Pins and Latch Cam Assembly

26

LU MECHANIC0.20

800 A 12−830−006

SEP 30/04

PAGE 1 OF 3

Applicable only on aircraft with Phase IV passenger door.

AMTOSS 12−20−52−640−812





(1) Grease gun (Comercially available).




(2) Cloths, cleaning, low−lint (05−041).


(1) Cleaning Safety Precautions (TASK51−26−00−910−801).


3. Job Set−Up


B. Remove the rubber stop from the forward gas spring.

C. Deactivate the open lock lever with a piece of tape.

D. Open and tag the circuit breaker that follows:


CBP−1 F−1 DOOR ACT

E. Remove the access panels that follow:

− 832BL, 832EL, 832BR, 832ER.

F. Clean the door as follows:

(1) Obey the cleaning safety precautions (Ref. TASK51−26−00−910−801).

(2) Use a lint−free cloth moist with solvent to remove all dirt,contamination, and moisture from the lubrication points(Ref. TASK 51−26−00−110−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LU MECHANIC0.20

800 A 12−830−006

SEP 30/04

PAGE 2 OF 3

4. Procedure

Refer to Figure 3.

A. Lubricate the latch pins as follows:

(1) Apply grease to the latch−pin lubrication fitting (1) untilthe grease appears on the outboard face of the latch−pinfitting (2).

(2) Operate the latch pin mechanism approximately 5 cyclesto evenly distribute the grease within the latch−pin fitting(2).

(3) Remove excess grease from the latch−pin fitting (2) with aclean, dry lint free cloth.

(4) Apply grease to the latch−pin push−rod fork end (3).

(5) Do steps (1), (2), (3), and (4) for all remaining threelatch−pins and latch−pin push−rod fork ends.

B. Apply grease with a grease gun to the torque tube brackets(6).

C. Apply grease by hand to the latch−cam torque tube assembly(5) and to the latch cam inner surface (7).

D. Clean the excess grease from the all the lubrication points.

5. Close Out

A. Install the rubber stop on the forward gas spring.

B. Close the access panels that follow on the passenger door:

− 832BL, 832EL, 832BR, 832ER.

C. Remove the tape from the open lock lever.

D. Remove the tag and close the circuit breaker that follows:



E. Close the passenger door (832).

F. Remove all the tools, equipment and unwanted materials fromthe work area.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LU MECHANIC0.20

800 A 12−830−006

SEP 30/04

PAGE 3 OF 3


Grease gun

Hand

1. Latch−pin lubrication−fitting.2. Latch−pin fitting.3. Latch−pin push−rod fork−end.

LEGEND

A

04−006

04−0061

3

TYPICAL

4. Latch pin.

04−0066

04−006

5

04−0067

6

B

B

A

BTYPICAL

C

C

C2

5. Latch−cam torque tube assembly.6. Torque tube bracket.7. Latch cam inner surface.

4 ram

1220

523_

020.

dg ,

rm, 0

1/09

/00

Lubrication of the Phase IV Passenger Door Latch Pins and Latch Cam AssemblyFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Phase IV Passenger Door Hinge

26

LUB 0.12

800

MECHANIC

SEP 30/04

2A 12−830−007

PAGE 1 OF 3

Applicable only on aircraft with Phase IV passenger door.

AMTOSS 12−20−52−640−811





(1) Grease gun.




(2) On Phase III passenger door, Cloths, Lint−Free, Flushingand Cleaning (05−087).


(1) Cleaning Safety Precautions (TASK51−26−00−910−801).


(3) Removal of the Passenger−Door TOP Folding−Step(TASK 52−11−04−000−801).

(4) Installation of the Passenger−Door Top Folding−Step(TASK 52−11−04−400−801).

3. Job Set−Up

A. Open and tag the circuit breaker that follows:



B. Remove the passenger−door top folding−step (Ref. TASK52−11−04−000−801).

C. Clean the lubrication points on the door as follows:

(1) Obey the cleaning safety precautions (Ref. TASK51−26−00−910−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LUB 0.12

800

MECHANIC

SEP 30/04

2A 12−830−007

PAGE 2 OF 3

(2) Use a lint−free cloth moist with solvent to remove all dirt,contamination, and moisture from the lubrication points(Ref. TASK 51−26−00−110−801).

4. Procedure

Refer to Figure 1.

A. Lubricate the passenger door hinge as follows:

(1) Apply grease with a grease gun to the hinge greasefittings (3) until the grease extrudes from the forward andthe aft ends of the hinge at the door sill (2).

(2) Clean the excess grease from the hinge ends.

5. Close Out

A. Install the passenger−door top folding−step (Ref. TASK52−11−04−400−801).

B. Remove the tag and close the circuit breaker that follows:



C. Remove all tools, equipment and unwanted materials from thework area.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LUB 0.12

800

MECHANIC

SEP 30/04

2A 12−830−007

PAGE 3 OF 3

FS 333.00FS 319.00

33


Grease gun

Hand

04−00604−006 B

1. Top folding step.2. Grease fittings.3. Door sill.

LEGEND

04−006

31

A

A

B

2

Lubrication of the Phase IV Passenger Door HingeFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Crew Escape Hatch

27

LUB MECHANIC0.10

5000 FLT HRS800

JUN 20/05

12−830−100

PAGE 1 OF 4

AMTOSS 12−20−52−640−803







(1) Removal of the Crew Escape Hatch Panels (TASK25−15−06−000−801).

(2) Installation of the Crew Escape Hatch Panels (TASK25−15−06−400−801).

(3) Removal of the Crew Escape Hatch (TASK25−22−00−000−801).

(4) Installation of the Crew Escape Hatch (TASK25−22−00−400−801).

3. Job Set−Up

A. Remove the crew escape hatch (Ref. TASK52−22−00−000−801).

B. Remove the liner panel from the crew escape hatch (Ref. TASK25−15−06−000−801).

4. Procedure

ON A/C 7003−7521 (Pre Modsum TC601R15019)

Refer to Figure 1.

A. Apply 04−006 grease to the wear surfaces of the lockpins (1).

B. Apply 04−006 grease to all rod ends and pivot points (2).

ON A/C 7522−SUBS (Post Modsum TC601R15019)

Refer to Figure 2.

C. Apply 04−006 grease by hand to the following area of thecrew escape hatch:

− wear surfaces of the lockpins (1)

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27

LUB MECHANIC0.10

5000 FLT HRS800

JUN 20/05

12−830−100

PAGE 2 OF 4

− all push−rod end bearings (2)

− linkage pivot points (3)

− hinge points (4).

ON A/C ALL

5. Close Out

A. Install the panels on the crew escape hatch (Ref. TASK25−15−06−400−801).

B. Install the crew escape hatch (Ref. TASK52−22−00−400−801).


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LUB MECHANIC0.10

5000 FLT HRS800

JUN 20/05

12−830−100

PAGE 3 OF 4

2

1

2


Hand

04−006

04−006

04−006

rtc1

2830

100_

001.

dg, p

w, 0

1/08

/02

LEGEND

1. Lockpin.2. Pivot point.

A

A

VIEW LOOKING UP

Lubrication of the Crew Escape HatchFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27

LUB MECHANIC0.10

5000 FLT HRS800

JUN 20/05

12−830−100

PAGE 4 OF 4


HAND

04−006

1

04−006

2

04−006

2

rtc1

2830

100_

002.

dg, p

w, 0

1/08

/02

04−006

4

04−006

1

04−006

4

04−006

3

04−006

304−006

2

04−006

2

1. Lockpins.2. Push−rod end bearings.3. Pivot points.4. Hinge points.

LEGEND

Lubrication of the Crew Escape HatchFigure 2

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Left Overwing−Emergency Exit

27

LUB MECHANIC0.10

5000 FLT HRS800

JUN 20/05

12−830−101

PAGE 1 OF 2

MRB 52−00−00−09

AMTOSS 12−20−52−640−802

1. Job Set−Up

A. Remove the left overwing emergency exit (Ref. TASK52−21−00−000−801).

B. Remove the panels from the left emergency exit door (833AZand 833BZ).

2. Procedure

Refer to Figure 1.


B. Apply 04−006 to the handle mechanism (2).

C. Apply 04−006 grease to the surface of the pressure seal (3).

3. Close Out


B. Install the access panels on the left emergency exit (833AZand 833BZ).

C. Install the left overwing emergency exit (Ref. TASK52−21−00−400−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Lubrication of the Left Overwing−Emergency Exit

27

LUB MECHANIC0.10

5000 FLT HRS800

JUN 20/05

12−830−101

PAGE 2 OF 2

2 1

3

2


Hand

04−006 04−006

04−006

04−006

Lubrication of the Left Overwing−Emergency ExitFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Service Door

26

LU 0.03

800

MECHANIC

2A

SEP 30/04

12−840−001

PAGE 1 OF 7

AMTOSS 12−20−52−640−801









(2) Mold release agent (06−019).

(3) Solution, water glycol, anti−icing agent (10−001).

(4) Solution, water glycol, anti−icing agent (10−002).


(1) Removal of the Door Panels and Linings (TASK25−26−04−000−801).

(2) Installation of the Door Panels and Linings (TASK25−26−04−400−801).

3. Job Set−Up

ON SERVICE DOOR WITHOUT A SECOND STABILIZER ROD

A. Remove the access panels that follow (Ref. TASK25−26−04−000−801) from the service door:

(1) Upper lining panel (841AZ).

(2) Center lining panel (841BZ).

(3) Lower lining panel (841CZ).

(4) Cover, Door mechanism (841DZ).

(5) Cover, Door mechanism (841EZ).

ON SERVICE DOOR WITH A SECOND STABILIZER ROD

B. Remove the access panels that follow (Ref. TASK25−26−04−000−801) from the service door:

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LU 0.03

800

MECHANIC

2A

SEP 30/04

12−840−001

PAGE 2 OF 7



(3) Center lining panel (841CZ).

(4) Lower lining panel (841DZ).


(6) Cover, Door mechanism (841FZ).

(7) Cover, Stabilizing rod (841GZ).

4. Procedure


Refer to Figure 1.

A. Lubricate the service door as follows:

(1) Apply 04−006 grease to all push−rod end bearings (1),linkage pivot points (2) and hinge points (3) of the doorlatch mechanism.

(2) Apply 04−006 grease to the ends of the tension spring (4)and to the two stabilizer bars (5).

(3) Apply 04−006 grease with a grease gun and thelubricating nozzle to lubricate the guide rollers (6). Put thelubricating nozzle in the flush grease fitting in the center ofthe roller.

CAUTION: APPLY THE DEICING AGENT TO THE OUTERHANDLE SLOT. THE AGENT MAY CORRODEOTHER PARTS.

(4) Apply 50 milliliters of 10−001 or 10−002 anti−icing agentto the outer handle slot on the outer handle shaft. Movethe outer handle in and out to equally apply the deicingagent.

NOTE: Do not use too much of the anti−icing agent.

(5) Apply mold release agent 06−019 with a brush to theservice door seal on both sides of all seal strikers.

NOTE: Let the 06−019 mold release agent to air dry for10 minutes.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LU 0.03

800

MECHANIC

2A

SEP 30/04

12−840−001

PAGE 3 OF 7



B. Lubricate the service door as follows:

(1) Apply 04−006 grease to the upper−stabilizer−rod endbearing (2).

(2) Apply 04−006 grease to the lower−stabilizer−rod endbearing (3).

(3) Apply 04−006 grease to the sliding parts of the fullopen−lock assembly (4).

(4) Apply 04−006 grease with a grease gun and thelubricating nozzle to lubricate the guide rollers (5). Put thelubricating nozzle in the flush grease fitting in the center ofthe roller.

(5) Apply 04−006 grease to all hinge points (6), linkage pivotpoints (7), and all push−rod end bearings (9) of the doorlatch mechanism.

NOTE: Cycle the door mechanism approximately 5cycles to evenly distribute the 04−006 grease.

(6) Apply 04−006 grease to the bearings end of theinternal−stabilizer−rod (8).

(7) Apply 04−006 grease to lubricate the pivot points of theroller and roller arm (10).

(8) Apply 04−006 to the shaft fittings (11).

(9) Apply 04−006 to the tension spring (12) and to the slidingarea of the sector (13).

(10) Apply 50 milliliters of 10−001 or 10−002 anti−icing agentto the outer handle slot on the outer handle shaft. Movethe outer handle in and out to equally apply the deicingagent.

NOTE: Do not use too much of the anti−icing agent.

(11) Apply mold release agent 06−019 with a brush to theservice door seal on both sides of all seal strikers.

NOTE: Let the 06−019 mold release agent to air dry for10 minutes.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


26

LU 0.03

800

MECHANIC

2A

SEP 30/04

12−840−001

PAGE 4 OF 7

5. Close Out


A. Install the access panels that follow (Ref. TASK25−26−04−000−801) to the service door:



(3) Lower lining panel (841CZ).

(4) Cover, Door mechanism (841DZ).



B. Install the access panels that follow (Ref. TASK25−26−04−000−801) to the service door:



(3) Center lining panel (841CZ).

(4) Lower lining panel (841DZ).


(6) Cover, Door mechanism (841FZ).

(7) Cover, Stabilizing rod (841GZ).

ALL


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LU 0.03

800

MECHANIC

2A

SEP 30/04

12−840−001

PAGE 5 OF 7


Grease gun

1

04−006

Hand

6

04−006

6

04−006

5

04−006

4

04−006

2

04−006

5

04−006

1

04−006

2

04−006

3

04−006

6

04−006

6

04−006

ram

1220

523_

001.

dg, p

t/jc,

19/

12/0

0

A

A

LEGEND1. Push−rod end bearing.

4. Tension spring.5. Stabilizer bar.6. Guide roller. VIEW LOOKING OUTBD

2. Pivot point.3. Hinge point.

Lubrication of the Service DoorFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LU 0.03

800

MECHANIC

2A

SEP 30/04

12−840−001

PAGE 6 OF 7

5

04−006

3

04−006

LEGEND

VIEW LOOKING OUTBD WITHACCESS PANELS


Grease gun

Hand

1

3

04−006

2

04−006

5

04−006

4

04−006

13

04−006

1. Service door.2. Upper−stabilizer− rod end bearing.

3. Lower−stabilizer− rod end bearing.4. Full open−lock

5. Guide roller.13. Sector.

assembly.

rtc1

2840

001_

001.

dg, k

ms,

06/

02/0

2


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


26

LU 0.03

800

MECHANIC

2A

SEP 30/04

12−840−001

PAGE 7 OF 7

B


Grease gun

Hand

5

6

LEGEND4. Full open−lock assembly.5. Guide roller.6. Hinge points.7. Pivot points.

8. Internal stabilizer rod.9. Push−rod end bearings.

10. Roller and roller arm.11. Shaft fitting.12. Tension spring.

VIEW LOOKING OUTBD

48

7

7

1011

12

5

10

9

04−00604−006

04−006

04−006

04−006

04−00604−006

04−006

04−006

04−006

04−006

04−006

rtc1

2840

001_

002.

dg, k

ms,

06/

02/0

2


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

27 JUN 20/05

LUB MECHANIC0.10

5000 FLT HRS800

Lubrication of the Right Overwing−Emergency Exit

12−840−100

PAGE 1 OF 2

MRB 52−00−00−09

AMTOSS 12−20−52−640−802

1. Job Set−Up

A. Remove the right overwing emergency exit (Ref. TASK52−21−00−000−801).

B. Remove the panels from the right emergency exit door (843AZand 843BZ).

2. Procedure

Refer to Figure 1.


B. Apply 04−006 to the handle mechanism (2).

C. Apply 04−006 grease to the surface of the pressure seal (3).

3. Close Out


B. Install the access panels on the right emergency exit (843AZand 843BZ).

C. Install the right overwing emergency exit (Ref. TASK52−21−00−400−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

27 JUN 20/05

LUB MECHANIC0.10

5000 FLT HRS800

Lubrication of the Right Overwing−Emergency Exit

12−840−100

PAGE 2 OF 2

2 1

3

2


Hand

04−006 04−006

04−006

04−006

Lubrication of the Right Overwing−Emergency ExitFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Lubrication of the Maintenance Servicing Doors

27 JUN 20/05

LUB MECHANIC0.23

5000 FLT HRS100, 200 & 300 12−900−100

PAGE 1 OF 2

MRB 52−00−00−09

AMTOSS 12−20−53−640−802

1. Tools and Equipment

− Oil can

2. Procedure

Refer to Figure 1.

A. Apply 03−005 molybdenum disulfide oil with an oil can to thehinges of the servicing doors that follow:

(1) The dc ground−power receptacle (1) door (312AR).

(2) The lavatory toilet service−panel (2) door (196AR).

(3) The potable−water service−panel (3) doors (142BR and172CR).

(4) The ac ground−power receptacle (4) door (122BR).

(5) The external service panel (5) door (122CR).

(6) The refuel/defuel control−panel (6) door (162AB).

(7) The bleed−air ground connection (7) door (172BR).

3. Close Out


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Lubrication of the Maintenance Servicing Doors

27 JUN 20/05

LUB MECHANIC0.23

5000 FLT HRS100, 200 & 300 12−900−100

PAGE 2 OF 2

1


Oil can

7

2

3 5

4

1. DC ground power door.2. Lavatory service door.

4. AC ground power service door.5. External service panel door.

7. Ground air connection door.

LEGEND

3. Potable water service panel door.

6. Refuel/defuel control panel door.

6

3

03−005

03−00503−005

03−005

03−005 03−005

03−005

03−005

Lubrication of the Maintenance Servicing DoorsFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Sanitization of the Galley Potable Water System

27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 1 OF 20

AMTOSS 12−18−38−670−804





(1) Servicing cart − portable water (CPW100).

(2) Two containers, 10 U.S. gallons (45 L) (None specified).

(3) Clear flexible hose 1/2 inch inside diameter (Nonespecified).

(4) Potable Water Supply Adapter (G601R121801−29).


(1) Tape, antiseize (Teflon) (05−038).

(2) Sanitizing Concentrate Bleach, 5.25% SodiumHypochlorite (17−002).

(3) Test paper for chlorine content in parts per million (ppm)includes comparison chart.

(4) Potable water (None specified).


(1) Servicing of the Galley Water System (TASK12−18−38−600−803).


(3) Remove External AC Power (TASK 12−00−07−861−802),as applicable.

(4) Removal of the Coffee Maker (TASK25−32−02−000−801), as applicable.

(5) Installation of the Coffee Maker (TASK25−32−02−400−801), as applicable.

3. Job Set−Up

A. Connect external ac electrical power (Ref. TASK12−00−07−861−801).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 2 OF 20

B. On the galley control panel, make sure that the circuit breakersthat follow are closed:

− CONTROL & IND

− TANK HTR

− LINE HTRS.

C. On the galley control panel, make sure that the GALLEYPOWER switch is ON.

D. On the galley control panel, make sure that the LAVATORYPOWER switch is OFF.

E. Open, safety, and tag the circuit breaker that follows:


CBP−2 D15 WATER HTRS TANKS

F. Open the potable water servicing point access door (142BR).

WARNING: OBEY THE PRECAUTIONS THAT FOLLOW WHENYOU USE DISINFECTANTS:− USE SAFETY GOGGLES− PUT ON PROTECTIVE CLOTHING− DO NOT LET DISINFECTANTS TOUCH YOUR SKIN, EYES, AND MOUTH− DO WORK IN AN AREA THAT HAS A GOOD FLOW OF AIR − OBEY THE MANUFACTURER’S INSTRUCTIONS−GET MEDICAL AID IF IRRITATION OCCURS.DISINFECTANTS CAN CAUSE INJURIES.

G. Mix potable water and sanitizing concentrate in the ratio thatfollows:

SANITIZING CONCENTRATE MIXTURE PER VOLUME

Bleach, 5.25% Sodium Hydochlorite One fluid ounce (30 cc) per 10 gallons US, (8 gallons Imperial), (36 L)

NOTE: You can use Purogene Sanitizing concentrate 2.0% Chlorine Dioxide as an alternative. Refer to the manufacturer’s instructions.

NOTE: The mixture above will give a concentration of 100parts per million. If you use a different concentrate,an adjustment of the mixture can be necessary.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 3 OF 20

ON A/C ALL EXCEPT AIR CANADA

4. Procedure


A. Connect a suitable drain hose between the water faucet on thecoffee maker and the galley sink.

NOTE: The coffee pot can be used to collect water samples.

B. Put a container on the ground below the forward drain mast(1).

C. Drain the galley water tank (Ref. TASK 12−18−38−600−803).

D. Remove the coffee pot (Ref. TASK 25−32−02−000−801).

E. Drain the heater reservoir of the coffee maker (Ref. TASK12−18−38−600−803).

F. Install the coffee pot (Ref. TASK 25−32−02−400−801).

G. Fill the galley potable water tank, the distribution system andthe heater reservoir of the coffee maker with sanitizingsolution. Do the steps that follow:

(1) Set The water supply control at the servicing cart to the offposition.

(2) Move the ball valve of the supply adapter (4) to the closedposition.

(3) Pour one fluid ounce (30 cc) of the concentrate into thecoupling (5) of the supply adapter (4).

(4) Install the coupling (5) of the supply adapter (4) on the fillport (3) of the potable water servicing point.

(5) Connect the water fill hose to the nipple fitting (6) on thesupply adapter (4).

(6) Set the water supply at the servicing cart to the onposition.

(7) Move the T−handle (2) clockwise to the FILL position.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 4 OF 20

CAUTION: MAKE SURE THAT THE INDICATION ON THEPRESSURE GAUGE OF THE SUPPLY ADAPTERIS NOT MORE THAN 20 PSI. IF YOU DO NOTDO THIS YOU CAN CAUSE DAMAGE TO THEWATER SYSTEM.

(8) Move the ball valve on the supply adapter (4) to the openposition. You can control the water pressure with thisvalve.

NOTE: The pressure relief valve in the aircraft will openat between 16 and 20 psi. If the water pressure ismore than 20 psi, water will flow from the forwarddrain mast (1) so that you think the tank is full.You must check the tank quantity with the waterlevel lights on the galley control panel. The waterlevel lights are visible from the ground with thegalley service door in the open position.

(9) Fill the potable water tank until the pressure gauge on thesupply adapter (4) indicates a decrease in pressure.

(10) Make sure that water comes out of the forward drain mast(1), then do the steps that follow:

(a) Let approximately 4 liters of water flow from theforward drain mast (1) into the container.

(b) Turn the T−handle (2) counterclockwise to the verticalposition and in the detent.

(c) Stop the water supply to the water fill port (3) with theball valve of the supply adapter (4).

NOTE: The fill hose and the supply adapter (4) mustremain attached to the fill port (3) to keepsanitization solution in the fill lines.

(d) Set the water supply control at the servicing cart tothe off position.

(11) If water does not flow from the forward drain mast (1)when the pressure gauge on the supply adapter (4) shows20 psi, do the steps that follow:

(a) Close the ball valve on the supply adapter (4).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 5 OF 20

(b) Stop the water flow from the servicing cart.

(c) If necessary, replace the defective pressure reliefvalve.

(d) When water flows steadily from the forward drain mast(1), Turn the T−handle (2) counterclockwise to thevertical position and in the detent.

Refer to Figure 2.

H. Make sure the heater reservoir of the coffee maker is full.

NOTE: On the control panel of the coffee maker, the LEDlight on the COLD WATER switch will go out whenthe heater reservoir of the coffee maker is full.

I. Put the coffee maker in the configuration that follows:

(1) The empty coffee pot is in place.

(2) The empty coffee brewer is in position with the handledown.

(3) The ON/OFF switch is in the ON position.

J. To test the galley potable water for chlorine content of thesanitization solution, do the steps that follow:

(1) Push the BREW switch on the coffee maker until thecoffee pot is full.

NOTE: The BREW switch will initially flash green. Whenthe reservoir water temperature reaches 195degrees F (90.6 degrees C) the switch will staygreen continuously. Water will only flow from theBREW head when the light stays greencontinuously.

NOTE: The flow of water will stop when the coffee potfills the automatic shut−off point.

(2) Use the chlorine test paper to test the solution for chlorinecontent.

(3) Push and hold the HOT WATER switch on the coffeemaker until one liter (one U.S. quart) of solution flows fromthe faucet on the front of the coffee maker.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 6 OF 20


(5) Push and hold the COLD WATER switch on the coffeemaker until one liter (one U.S. quart) of solution flows fromthe faucet on the front of the coffee maker.


NOTE: The test paper should indicate 100 parts permillion (ppm) of chlorine content.

(7) If the test paper indicates 100 ppm, fill the potable watertank again and let the system stand for four hours.

K. If the chlorine paper tests do not indicate 100 ppm do thesteps that follow:

(1) Remove the supply adapter (4) from the FILL PORT anddrain it.

(2) Pour 0.5 ounces (15 cc) of concentrate into the supplyadapter (4).

(3) Connect the supply adapter (4) to the FILL PORT and fillthe tank to overflow.

NOTE: Leave the fill hose attached to the FILL PORT tokeep the solution in the fill lines.

(4) Use the chlorine test paper to test the solution for chlorinecontent at each galley water outlet.

L. To test the galley potable water for chlorine content after theconcentrate is increased, do the steps that follow:



TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 7 OF 20

NOTE: The flow of water will stop when the coffee potfills the automatic shut−off level.


(3) Push and hold the HOT WATER switch on the coffeemaker until one liter (one U.S. quart) of solution flows fromthe faucet on the front of the coffee maker.


(5) Push and hold the COLD WATER switch on the coffeemaker until one liter (one U.S. quart) of solution flows fromthe faucet on the front of the coffee maker.


NOTE: The test paper should indicate 100 parts permillion (ppm) of chlorine content.

(7) If the test paper indicates 100 ppm, fill the potable watertank again and let the system stand for four hours.

M. Drain the galley water tank (Ref. TASK 12−18−38−600−803).

Refer to Figure 2.

N. Remove the coffee pot (Ref. TASK 25−32−02−000−801).

O. Drain the heater reservoir of the coffee maker (Ref. TASK12−18−38−600−803).

P. Install the coffee pot (Re. TASK 25−32−02−400−801).

Q. Fill the galley water tank (Ref TASK 12−18−38−600−803).

Refer to Figure 5.

R. To flush the water reservoir of the coffee maker and the coffeemaker, do the steps that follow:

(1) Push and hold the COLD WATER switch on thecoffee−maker until four liters (one U.S. gallon) of waterflows from the faucet on the front of the coffee maker.

(2) Push and hold the HOT WATER switch on thecoffee−maker until four liters (one U.S. gallon) of waterflows from the faucet on the front of the coffee maker.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 8 OF 20

(3) Push the BREW switch on the coffee−maker once to letfour liters (one U.S. gallon) of water flow into the coffeepot.

(4) Push the BREW switch to stop the flow, then empty thefilled pot into the galley sink.

NOTE: The BREW switch will initially flash green. Whenthe reservoir water temperature reaches 195degrees F (90.6 degrees C) the switch will staygreen continuously. Water will only flow from theBREW faucet when the light stays greencontinuously.

S. Fill the galley water tank (Ref TASK 12−18−38−600−803).

T. Do not touch the water system for 30 minutes.

U. To flush the galley water tank, do the steps that follow:

(1) Drain the galley water tank (Ref. TASK12−18−38−600−803).

(2) Remove the coffee pot to gain access to the drain valve ofthe heater reservoir.

(3) Drain the heater reservoir of the coffee maker (Ref. TASK12−18−38−600−803).

(4) Install the coffee pot (Ref. TASK 25−32−02−400−801).

(5) Fill the galley water tank (Ref. TASK12−18−38−600−803).

(6) Push and hold the HOT WATER switch on the coffeemaker until one liter (one U.S. quart) of water flows fromthe faucet on the front of the coffee maker.

(7) Push and hold the COLD WATER switch on the coffeemaker until one liter (one U.S. quart) of water flows fromthe faucet on the front of the coffee maker.


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 9 OF 20


NOTE: Water will only flow from the BREW head whenthe light stays green continuously. The waterflow will stop when the coffee pot is filled to theautomatic shut−off level.

(9) Use the chlorine test paper to test the water for chlorinecontent. Get samples of water from the BREW outlet, andthe HOT and COLD positions on the coffee maker.

NOTE: The chlorine test paper must show less than 50ppm.

Refer to Figure 2.

V. To drain the heater reservoir of the coffee maker, do the stepsthat follow:

(1) Remove the coffee server (1) from the coffee maker (2) togain access to the lever lock of the coffee maker.

(2) Put a container on the ground below the forward drainmast to catch the water from the heater reservoir of thecoffee maker.

(3) Open the drain valve (6) at the rear of the coffee makercompartment.

(4) When the water flow from the forward drain mast (1)stops, set the drain valve (6) to the closed position.

(5) Remove the container from below the forward drain mast(1).

ON A/C AIR CANADA ONLY

5. Procedure


A. Connect a suitable drain hose between the water faucet on thecoffee maker and the galley sink.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 10 OF 20

NOTE: The coffee server can be used to collect watersamples.

B. Put a container on the ground below the forward drain mast(1).

C. Drain the galley water tank (Ref. TASK 12−18−38−600−803).

D. Remove the coffee server (Ref. TASK 25−32−02−000−801).

E. Drain the heater reservoir of the coffee maker (Ref. TASK12−18−38−600−803).

F. Install the coffee server (Ref. TASK 25−32−02−400−801).

G. Fill the galley potable water tank, the distribution system andthe heater reservoir of the coffee maker with sanitizingsolution. Do the steps that follow:

(1) Set The water supply control at the servicing cart to the offposition.









TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 11 OF 20



(10) Make sure that water comes out of the forward drain mast(1), then do the steps that follow:









(c) If necessary, replace the defective pressure reliefvalve and open the water supply from the servicingcart again.

(d) When water flows steadily from the forward drain mast(1), Turn the T−handle (2) counterclockwise to thevertical position and in the detent.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 12 OF 20

(e) Set the water supply control at the servicing cart tothe off position.

Refer to Figure 3.

H. Make sure the heater reservoir of the coffee maker is full.

NOTE: On the control panel of the coffee maker, the NOWATER light will go out when the heater reservoir ofthe coffee maker is full.

I. Put the coffee maker (or the water boiler) in the configurationthat follows:

(1) The empty coffee server is in place.

(2) The empty coffee brewer is in place, with the handledown.

(3) The ON/OFF switch is in the ON position.

J. To test the galley potable water for chlorine content of thesanitization solution, do the steps that follow:

(1) Push the COFFEE BREW switch.

NOTE: The HOT WATER light will come on and waterwill flow when the water temperature is at 195degrees F (90.6 degrees C).

NOTE: The flow of water will stop when the server isfilled to the automatic shut−off level.

(2) Use the chlorine test paper to test for 100 ppm chlorinecontent.

(3) Pour the contents from the server into the sink.

(4) Put the server in the coffee maker.

(5) Push the TEA switch.


NOTE: The flow of water will stop when the server isfilled to the automatic shut−off level.

(6) Use the chlorine test paper to make sure that you have100 ppm of chlorine content.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 13 OF 20

(7) Drain one liter of water from the faucet above the sink.

(8) Test the second liter of water for 100 ppm chlorinecontent.

(9) If the test paper indicates 100 ppm, fill the potable watertank and do not touch the system for four hours.

K. If the chlorine paper tests do not indicate 100 parts per milliondo the steps that follow:

(1) Disconnect the supply adapter (4) from the FILL PORTand drain it.

(2) Pour one−half ounce (15 cc) of concentrate into the hose.

(3) Attach the supply adapter (4) to the FILL PORT and fill thetank to overflow.

NOTE: Leave the PRV monitor tool and the water supplyhose attached to the FILL PORT to keep thesolution in the fill hoses.


(5) If the test paper indicates 100 parts per million, fill thepotable water tank and do not touch the system for fourhours.

L. To test the galley potable water for chlorine content after theconcentrate is increased, do the steps that follow:

(1) Push the COFFEE BREW switch.

NOTE: The HOT WATER light will come on and waterwill flow when the water temperature is 195degrees F (90.6 degrees C).

NOTE: The water flow will stop when the server is filledto the automatic shut−off level.

(2) Use the chlorine test paper to test for 110 ppm chlorinecontent.



TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 14 OF 20




(6) Use the chlorine test paper and make sure you have 100ppm chlorine content.

(7) Drain one liter of water from the faucet above the sink.

(8) Test the second liter of water for 100 ppm chlorinecontent.

(9) Do not touch the system for four hours.

M. Drain the galley water tank (Ref. TASK 12−18−38−600−803).

N. Remove the coffee server (Ref. TASK 25−32−02−000−801).

O. Drain the heater reservoir of the coffee maker/water boiler (Ref.TASK 12−18−38−600−803).

P. Install the coffee server (Re. TASK 25−32−02−400−801).

Q. Fill the galley water tank (Ref TASK 12−18−38−600−803).

Refer to Figure 3.

R. To flush the water reservoir of the coffee maker/water boilerand the coffee maker, do the steps that follow:

(1) Push and hold the COFFEE BREW switch.



(2) Fill and empty the coffee server twice.

(3) Test the third server of water for chlorine content.

(4) Pour the contents from the server.


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 15 OF 20




(7) Fill and empty the coffee server twice.

(8) Test the third server of water for chlorine content.

(9) Drain four liters of water from the faucet above the sink.

(10) Test the fourth liter of water for chlorine content.

S. Fill the galley water tank (Ref. TASK 12−18−38−600−803).

T. Let the water system stand for 30 minutes.

Refer to Figure 3.

U. To flush the galley water tank, do the steps that follow:

(1) Remove the coffee server to gain access to the coffeemaker/water boiler lever lock.

(2) Put a container on the galley floor to catch the water fromthe reservoir of the water boiler.

(3) Remove the coffee pot from the coffee maker (1).

(4) Open the screw and lift the lever lock assembly (15).

(5) Remove the coffee maker (1) from the compartment (Ref.TASK 25−32−02−000−801).

(6) Put the coffee maker over the container.

(7) Open the drain valve (9) at the rear of the coffee maker.

(8) When the water flow from the drain valve (9) stops, closethe drain valve.

(9) Install the coffee maker into the compartment (Ref. TASK25−32−02−400−801).

(10) Lower the lever lock assembly and close the screw.

(11) Install the coffee server into the coffee maker as required.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 16 OF 20

Refer to Figure 3.

V. To flush the galley water tank, do the steps that follow:

(1) Drain the galley water tank (Ref. TASK12−18−38−600−803).

(2) Fill the galley water tank (Ref. TASK12−18−38−600−803).

Refer to Figure 3.

W. To test the galley potable water for chlorine content, do thesteps that follow:

(1) Push the COFFEE BREW switch on the coffee maker.



(2) Test the water in the server for chlorine content usingchlorine test paper.






(6) Use chlorine test paper to make sure that the water in theserver has less than 50 ppm of chlorine.

(7) Test each sample for taste, odor or color, If necessary,flush the system with clean water and do the test again.

X. Remove the drain hose from the faucet above the sink.

6. Close Out

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 17 OF 20

Refer to Figure 1.

A. Remove the supply adapter (4) from the fill port (3).

B. On the galley control panel, make sure that the GALLEY PUMPswitch is set to the OFF position.


D. Remove the tag and close the circuit breaker that follows:



E. Close the access doors that follow:

− Potable water servicing point (142BR)

− Main avionics compartment door (811).

F. Remove the external ac electrical power (Ref. TASK12−00−07−861−802).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 18 OF 20

A

A

F

I

L

LP

O

T

A

B

L

E

W

A

T

E

RP

U

L

LDRAIN

B

B

C

C

1. Drain mast.2. T−Handle.3. Fill port.4. Supply adapter.5. Coupling.6. Nipple fitting.7. Blanking plug.

LEGEND

2

3

1

4

5

6

7

VIEW LOOKING INBOARD rtc1

2900

702_

001.

dg, r

m, 0

6/04

/05

Sanitization of the Galley Potable Water SystemFigure 1

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 19 OF 20

1. Coffee pot.2. Coffee maker.3. Lever.4. Water connection.5. Electrical power connection.

LEGEND

GALLEY 1

GALLEY 2(REF)

2

1

UNLOCK

LOCK

UNLOCK

LOCK

VERSION 2

VERSION 15

4

3

B

C

B

C

6. Heater Reservoirdrain valve.

7. Heater reservoir.

7

6

DRAIN VALVE

D

D

rtc1

2900

702_

002.

dg, r

m, 0

6/04

/05


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27 JUN 20/05

SV MECHANIC2.0

12 MONTHS100/200 12−900−702

PAGE 20 OF 20

rtc1

2900

702_

003.

dg, r

m, 0

6/04

/05

A

A

AB

B

1

3

54

15

8

7

2

9

101112

13

14

LEGEND

GALLEY 1

NOTECoffee server isnot installed.

LOCKED UNLOCKED

15

B

6

1. Coffee maker.2. Heater reservoir.3. Coffee maker control panel.4. Auto shut−off probe.5. Coffee server spill tray.6. Coffee server retainer lever.7. Coffee brewer.8. Coffee brewer

release handle.

9. Drain valve.10. Preformed packing.11. Water inlet connector.12. Drain from coffee server

spill tray.13. Alignment guide.14. Electrical power connector.15. Lever lock assembly.


TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector

Sanitization of the Lavatory Potable Water System

27 JUN 20/05

SV MECHANIC1.0

12 MONTHS100/200 12−900−703

PAGE 1 OF 8

AMTOSS 12−18−38−670−805





(1) Servicing cart − portable water (CPW100).

(2) Two containers, 10 U.S. gallons (45 L) (None specified).

(3) Potable water supply adapter (G601R121801−29).


(1) Tape, antiseize (Teflon) (05−038).

(2) Sanitizing Concentrate Bleach, 5.25% SodiumHypochlorite (17−002).

(3) Test paper for chlorine content in parts per million (ppm)includes comparison chart.

(4) Potable water (None specified).


(1) Servicing of the Lavatory Water System (TASK12−18−38−600−804).


(3) Remove External AC Power (TASK 12−00−07−861−802),as applicable.

3. Job Set−Up

A. Connect external AC electrical power (Ref. TASK12−00−07−861−801).

B. On the galley control panel, make sure that the circuit breakersthat follow are closed:

− CONTL & IND

− TANK HTR

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC1.0

12 MONTHS100/200 12−900−703

PAGE 2 OF 8

− LINE HTRS.

C. On the galley control panel, make sure that the GALLEY PUMPswitch is set to the OFF position.

D. On the galley control panel, make sure that the LAVATORYPOWER switch is ON.

E. Open, safety, and tag the circuit breaker that follows:



F. Open the potable water service and drain access door(142BR).

WARNING: OBEY THE PRECAUTIONS THAT FOLLOW WHENYOU USE DISINFECTANTS:− USE SAFETY GOGGLES− PUT ON PROTECTIVE CLOTHING− DO NOT LET DISINFECTANTS TOUCH YOUR SKIN, EYES, AND MOUTH− DO WORK IN AN AREA THAT HAS A GOOD FLOW OF AIR − OBEY THE MANUFACTURER’S INSTRUCTIONS−GET MEDICAL AID IF IRRITATION OCCURS.DISINFECTANTS CAN CAUSE INJURIES.

G. Mix potable water and sanitizing concentrate in the ratio thatfollows:

SANITIZING CONCENTRATE MIXTURE PER VOLUME

Bleach, 5.25% Sodium Hydochlorite One fluid ounce (30 cu cm) per 10 gallons US, (8 gallons Imperial), (36 liters).

NOTE: The mixture above will give a concentration of 100parts per million. If you use a different concentrate,an adjustment of the mixture can be necessary.

4. Procedure

Refer to Figure 1.

A. Put the container on the ground below the aft drain mast (1).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC1.0

12 MONTHS100/200 12−900−703

PAGE 3 OF 8

B. Drain the lavatory water tank (Ref. TASK12−18−38−600−804).

C. To fill the lavatory potable water tank and the distributionsystem with sanitizing solution, do the steps that follow:

(1) Set the water supply control at the servicing cart to the offposition.











TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC1.0

12 MONTHS100/200 12−900−703

PAGE 4 OF 8

(10) Make sure the water comes out of the forward drain mast(1), then do the steps that follow:









(c) If necessary, replace the defective pressure reliefvalve and open the water supply from the servicingcart again.

(d) When water flows steadily from the forward drain mast(1), turn the T−handle (2) counterclockwise to thevertical position and in the detent.

(e) Set the water supply control at the servicing cart tothe off position.

D. To test the lavatory potable water for chlorine content of thesanitization solution, do the steps that follow:

(1) Move the stopper of the sink to the closed position.

(2) Operate the water faucet on the sink until the sink is full ofthe solution.

(3) Remove the stopper and let the solution drain from thesink.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC1.0

12 MONTHS100/200 12−900−703

PAGE 5 OF 8

(4) Operate the water faucet on the sink again until the sink isfull of the solution.

(5) Use the chlorine test paper to make sure that the solutionshows 100 parts per million (ppm) of chlorine.

(6) If the test paper indicates 100 ppm, fill the potable watertank again and do not touch the system for one hour.

E. If the chlorine paper tests do not indicate 100 ppm, do thesteps that follow:

(1) Move the ball valve on the supply adapter (4) to the openposition.

NOTE: The solution in the line from the fill port (3) to thefill valve will drain out of the lines.

(2) Move the ball valve on the supply adapter (4) to the closedposition.

(3) REmove the coupling (5) from the fill port (3) and drain thesolution from the coupling (5).

(4) Pour 0.5 ounces (15 cc) of concentrate into the coupling(5).

(5) Connect the coupling (5) to the fill port (3) and fill the tankto overflow.

NOTE: Leave the coupling (5) attached to the fill port (3)to keep the solution in the fill line.

F. To test the lavatory potable water for chlorine content after theconcentrate is increased, do the steps that follow:

(1) Operate the stopper of the sink to the closed position.

(2) Operate the faucet on the sink until the sink is full.

(3) Drain the sink of the solution.


(5) Use the chlorine test paper to make sure that the solutionshows 100 parts per million (ppm) of chlorine.

(6) If the test paper indicates 100 ppm, fill the potable watertank again and do not touch the system for one hour.

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC1.0

12 MONTHS100/200 12−900−703

PAGE 6 OF 8

G. To flush the water from the tank and the distribution system, dothe steps that follow:

(1) Drain the lavatory water tank (Ref. TASK12−18−38−600−804).

(2) Fill the lavatory water tank (Ref. TASK12−18−38−600−804).

(3) Close the stopper on the sink drain.


(5) Drain the sink.


(7) Use the chlorine test paper to make sure that the solutionhas less than 50 ppm chlorine content.

(8) If the test paper indicates less than 50 ppm, open thestopper and let the water drain from the sink.

(9) Drain the lavatory potable water tank (Ref. TASK12−18−38−600−804).

(10) Fill the lavatory potable water tank with clean water (Ref.TASK 12−18−38−600−804).

(11) If the test paper indicates greater than 50 ppm, drain thelavatory potable water tank (Ref. TASK12−18−38−600−804).

(12) Fill the lavatory water tank again with clean water (Ref.TASK 12−18−38−600−804).

(13) Use the chlorine test paper to make sure that the solutionhas less than 50 ppm chlorine content.

5. Close Out

Refer to Figure 1.

A. Remove the supply adapter (4) from the fill port (3).

B. On the galley control panel, make sure that the LAVATORYPOWER switch is OF.

C. Remove the tag and close the circuit breaker that follows:

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE

Mechanic Inspector


27 JUN 20/05

SV MECHANIC1.0

12 MONTHS100/200 12−900−703

PAGE 7 OF 8



D. Remove all tools, equipment, and unwanted materials from thework area.

E. Close the potable water servicing point access door (142BR).

F. Remove the external AC electrical power (Ref. TASK12−00−07−861−802).

TASK TYPE SKILL


NUMBER DATE

REVISION


000−

c



S/N OFF S/N ON


WORK ORDER

DATE RETURNED

DATE ISSUED

MAN−HOURS

AIRLINEDESIGNATOR

CODE


27 JUN 20/05

SV MECHANIC1.0

12 MONTHS100/200 12−900−703

PAGE 8 OF 8

A

A

F

I

L

LP

O

T

A

B

L

E

W

A

T

E

RP

U

L

LDRAIN

B

B

C

C

1. Drain mast.2. T−Handle.3. Fill port.4. Supply adapter.5. Coupling.6. Nipple fitting.7. Blanking plug.

LEGEND

2

3

1

4

5

6

7

VIEW LOOKING INBOARD rtc1

2900

702_

001.

dg, r

m, 0

6/04

/05

Sanitization of the Lavatory Potable Water SystemFigure 1

TASK CARD ATA 12

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Transcript of TASK CARD ATA 12