10-11-02 Pageblock 201

PROLONGED PARKING - MAINTENANCE PRACTICES

Effective on: AAL ALL

1. General

A. When an airplane is not operated for 7 days or more, the airplane must be protected. The procedures that follow

will help prevent deterioration of the airplane structure, finish, or system components. There are different

procedures to prepare some systems for storage. These procedures are calculated by the length of time the

airplane is in storage. The storage times are as follows:

(1) Short Term Storage - Applies to times that are 0-60 days unless specified differently.

(2) Long Term Storage - Applies to times that are more than 60 days unless specified differently.

B. The procedures necessary for the protection of a parked airplane are given in this section. These procedures are

the task named "Airplane Storage Procedures".

C. The procedures necessary to put the airplane back to a serviceable condition are also found in this section. These

procedures are the task named "Put the Airplane Back to a Serviceable Condition After Storage".

D. Use the applicable procedure for the length of time, and conditions that you park the airplane:

(1) Normal parking procedures for less than 7 days ( PAGEBLOCK 10-11-01/201 )

(2) Parking in high winds ( PAGEBLOCK 10-11-03/201 )

(3) Parking with the engines removed ( PAGEBLOCK 10-11-04/201

(4) Special procedures to park the airplane for engine operation ( PAGEBLOCK 71-00-00/201 )

List of Maintenance Tasks:

10-11-02-622-001 Airplane Storage Procedures

10-11-02-632-002 Put the Airplane Back to a Serviceable Condition After Storage

American Airlines

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For Reference Olny 
Task 10-11-02-622-001 "USE MCM CARD 05-92-60, 05-92-61, 05-92-62, 05-92-69, 05-92-70, 05-92-71, 05-92-73, 05-

92-75, 05-92-77, 32-92-01, as required by GPM 03-07"

Airplane Storage Procedures

Effective on: AAL ALL

A. References

Reference Title

06-44-00 P/B 201 WINGS (MAJOR ZONES 500 AND 600) ACCESS DOORS AND PANELS - MAINTENANCE PRACTICES

07-11-01 P/B 201 JACKING AIRPLANE - MAINTENANCE PRACTICES

07-11-03 P/B 201 JACKING AIRPLANE AXLES - MAINTENANCE PRACTICES

09-11-00 P/B 201 TOWING - MAINTENANCE PRACTICES

10-11-01 P/B 201 NORMAL PARKING - MAINTENANCE PRACTICES

10-11-03 P/B 201 PARKING IN HIGH WINDS - MAINTENANCE PRACTICES

10-11-04 P/B 201 PARKING WITH ENGINES REMOVED - MAINTENANCE PRACTICES

10-11-05 P/B 201 Chock Installation

12-11-02 P/B 301 FUEL TANK OVERWING FUELING

12-12-01 P/B 301 HYDRAULIC SYSTEMS - SERVICING

12-14-01

P/B 301 Config 1

POTABLE WATER SYSTEM - SERVICING

12-15-01 P/B 301 MAIN GEAR SHOCK STRUT - SERVICING

12-15-01-613-048 Main Gear Shock Strut Fluids (P/B 301)

12-15-02 P/B 301 NOSE GEAR SHOCK STRUT - SERVICING

12-15-02-613-055 Nose Gear Shock Strut Fluids (P/B 301)

12-15-03 P/B 301 LANDING GEAR TIRES - SERVICING

12-15-04 P/B 301 PARKING BRAKE ACCUMULATOR - SERVICING

12-15-08 P/B 301 OXYGEN - SERVICING

12-16-01 P/B 301 RAIN REPELLENT BOTTLE - SERVICING

12-17-01

P/B 301 Config 5

MANUAL DUMP WASTE TANK - SERVICING

12-21-00 P/B 301 AIRPLANE LUBRICATION - SERVICING

12-21-04 P/B 301 ELEVATOR CONTROL SYSTEM - SERVICING (LUBRICATION)

12-21-05 P/B 301 HORIZONTAL STABILIZER TRIM CONTROL SYSTEM - SERVICING (LUBRICATION)

12-21-06 P/B 301 RUDDER AND RUDDER TRIM CONTROL SYSTEM - SERVICING

12-21-07 P/B 301 AILERON AND AILERON-TRIM-CONTROL SYSTEM - SERVICING

American Airlines

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For Reference Olny 
Reference Title

12-21-08 P/B 301 LEADING EDGE SLAT SYSTEM (LUBRICATION) - SERVICING

12-21-09 P/B 301 TRAILING EDGE FLAP SYSTEM - SERVICING

12-21-10 P/B 301 SPOILER/SPEEDBRAKE CONTROL SYSTEM - SERVICING

12-21-12 P/B 301 NOSE GEAR AND ACTUATING MECHANISMS - SERVICING

12-21-13 P/B 301 NOSE GEAR DOORS AND ACTUATING MECHANISMS - SERVICING

12-21-14 P/B 301 MAIN GEAR AND ACTUATING MECHANISMS - SERVICING

12-21-15 P/B 301 MAIN GEAR DOORS AND ACTUATING MECHANISMS - SERVICING

12-21-18 P/B 301 NO. 1, 2, AND 4 PASSENGER DOORS - SERVICING

12-21-22 P/B 301 NO. 1 AND 2 CARGO DOORS - SERVICING

12-21-27 P/B 301 EQUIPMENT COMPARTMENT AND EXTERIOR SERVICE DOORS - SERVICING

12-21-30 P/B 301 RAM AIR TURBINE (RAT) - SERVICING

12-21-31 P/B 301 CONTROL CABLES - SERVICING (LUBRICATION)

12-21-32 P/B 301 WING NACELLE ATTACH FITTINGS - SERVICING (LUBRICATION)

12-21-33 P/B 301 WING STRUCTURE LUBRICATION - SERVICING

12-21-34 P/B 301 NO.2 WINDOW - SERVICING (LUBRICATION)

12-25-01 P/B 301 AIRPLANE SERVICING (CLEAN AND POLISH)

20-10-21 P/B 401 ELECTRICAL BONDING - REMOVAL/INSTALLATION

20-20-02 P/B 601 CONTROL CABLES - INSPECTION/CHECK

20-41-00 P/B 201 STATIC GROUNDING - MAINTENANCE PRACTICES

21-51-04 P/B 401 WATER EXTRACTOR - REMOVAL/INSTALLATION

24-31-03 P/B 401 APU BATTERY - REMOVAL/INSTALLATION

26-21-00 P/B 501 ENGINE FIRE EXTINGUISHING SYSTEM - ADJUSTMENT TEST

26-22-00 P/B 501 APU FIRE EXTINGUISHING SYSTEM - ADJUSTMENT TEST

27-11-00 P/B 501 AILERON AND AILERON TRIM CONTROL SYSTEM - ADJUSTMENT/TEST

27-21-00

P/B 501 Config 1

RUDDER AND RUDDER TRIM CONTROL SYSTEM - ADJUSTMENT/TEST

27-31-00 P/B 501 ELEVATOR CONTROL SYSTEM - ADJUSTMENT/TEST

27-51-00 P/B 001 TRAILING EDGE FLAP SYSTEM - DESCRIPTION AND OPERATION

27-51-00 P/B 501 TRAILING EDGE FLAP SYSTEM - ADJUSTMENT/TEST

27-61-00 P/B 501 SPOILER/SPEEDBRAKE CONTROL SYSTEM - ADJUSTMENT/TEST

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Reference Title

27-81-00 P/B 501 LEADING EDGE SLAT SYSTEM - ADJUSTMENT/TEST

28-21-00 P/B 501 PRESSURE FUELING SYSTEM - ADJUSTMENT/TEST

29-11-00 P/B 201 MAIN (LEFT, RIGHT, AND CENTER) HYDRAULIC SYSTEMS - MAINTENANCE PRACTICES

29-11-00 P/B 601 MAIN (LEFT, RIGHT, AND CENTER) HYDRAULIC SYSTEMS - INSPECTION/CHECK

30-42-03 P/B 401 WINDSHIELD WIPER ARM/BLADE - REMOVAL/INSTALLATION

30-43-00

P/B 201 Config 1

WINDSHIELD RAINBOE RAIN REPELLENT SYSTEM - MAINTENANCE PRACTICES

32-00-15 P/B 201 LANDING GEAR DOOR GROUND OPERATIONS AND LOCKING PROCEDURE - MAINTENANCE PRACTICES

32-00-20 P/B 201 LANDING GEAR DOWNLOCKS - MAINTENANCE PRACTICES

32-21-00 P/B 001 NOSE GEAR - DESCRIPTION AND OPERATION

32-21-09

P/B 401 Config 1

NOSE GEAR TORSION LINKS - REMOVAL/INSTALLATION

33-51-07 P/B 201 POWER SUPPLY - MAINTENANCE PRACTICES

34-11-00 P/B 301 PITOT-STATIC SYSTEM - SERVICING

35-11-00 P/B 201 CREW OXYGEN SYSTEM - MAINTENANCE PRACTICES

35-11-51 P/B 401 CREW OXYGEN MASK/STOWAGE BOX - REMOVAL/INSTALLATION

38-10-00 P/B 201 POTABLE WATER SYSTEM - MAINTENANCE PRACTICES

49-11-00 P/B 201 AUXILIARY POWER UNIT - MAINTENANCE PRACTICES

51-00-52 P/B 201 CORROSION PREVENTION - ENVIRONMENTAL EFFECTS MAINTENANCE PRACTICES

51-00-59 P/B 201 CORROSION PREVENTION - GENERAL INFORMATION STANDARD PREVENTIVE MAINTENANCE

PROCEDURES - MAINTENANCE PRACTICES

51-41-00 P/B 201 AIRFRAME DRAINAGE - MAINTENANCE PRACTICES

71-00-00 P/B 201 POWER PLANT - MAINTENANCE PRACTICES

71-00-02 P/B 401 POWER PLANT - REMOVAL/INSTALLATION

71-00-03 P/B 201 POWER PLANT - MAINTENANCE PRACTICES (PRESERVATION AND DEPRESERVATION)

B. Tools/Equipment

NOTE: When more than one tool part number is listed under the same "Reference" number, the tools shown are alternates to

each other within the same airplane series. Tool part numbers that are replaced or non-procurable are preceded by

"Opt:", which stands for Optional.

Reference Description

COM-1503 Cover - Probe, Pitot Static

Effective on: AAL ALL; 757-200ER

(Part #: KPC3-480-325, Supplier: 0P9C7)

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Reference Description

COM-1505 Chocks - Wheel

Effective on: AAL ALL; 757-200ER

(Part #: 99-9028-6000, Supplier: 59603)

(Part #: W92, Supplier: 9L752)

COM-1519 Cover - Protective, Total Air Temperature Probe

Effective on: AAL ALL; 757-200ER

(Part #: FTC102, Supplier: 0P9C7)

COM-2499 Cover - Vane, Angle of Attack

Effective on: AAL ALL; 757-200ER

(Part #: R/C-AOAC-2, Supplier: 0P9C7)

SPL-1513 Cover - Probe, Ice Detector

Effective on: AAL ALL; 757-200ER

(Part #: 0061BN1, Supplier: 59885)

C. Consumable Materials

Reference Description Specification

B50080 Compound - Corrosion Preventive, Solvent Cutback, Cold-Application

(Grade 2 - Soft Film)

MIL-PRF-16173, Grade 2 (Supersedes MILC-16173, Grade 2)

C00174 Compound - Corrosion Preventive, Solvent Cutback, Cold Application MIL-PRF-16173 (Supersedes MIL-C-16173)

D00013 Grease - Aircraft And Instrument Grease MIL-PRF-23827 (NATO G-354) (Supersedes

MIL-G-23827)

D00054 Fluid - Hydraulic Assembly Lubricant - MCS 352B (Formerly Monsanto

MCS 352B)

D00070 Fluid - Hydraulic, Petroleum Base MIL-PRF-5606 (Replaces MIL-H-5606)

D00091 Oil - General Purpose, Low Temperature, Lubricating MIL-PRF-7870 (NATO O-142)

D00106 Fluid - Hydraulic, Petroleum Base, For Preservation And Operation MIL-PRF-6083 (NATO C-635)

D00153 Fluid - Hydraulic Fluid, Fire Resistant (Interchangable And Intermixable

With BMS 3-11 Type V)

BMS3-11 Type IV

D00233 Grease - Aircraft, General Purpose, Wide Temperature - Mobil 28 MIL-PRF-81322

D00378 Grease - Aircraft, General Purpose, Wide Temperature - Aeroshell 22 MIL-PRF-81322

D00510 Lubricant - Landing Gear Shock Strut Additive - Lubrizol 1395

D00633 Grease - Aircraft General Purpose BMS3-33

D50180 Grease - Aircraft General Purpose (AeroShell Grease 33) BMS 3-33, MIL-PRF-23827

G00087 Fabric, Insulation Covering (Self-Extinguishing) BMS8-142

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Reference Description Specification

G00452 Additive, Fuel - Biobor JF

G01994 Additive, Fuel PFA-55MB, MIL-I-17686

G02145 Tape - Aluminum Foil BMS8-289

G02219 Tape - Yellow Vinyl Adhesive, Scotch Brand No.471, 1.5 Inches (38.1

mm) Wide

G02347 Biocide - Fuel - Kathon FP1.5

G02444 Tag - Red Paper, "STATIC PORTS COVERED" - 3 inches (76.2 mm)

Wide, 6 inches (152.4 mm) Long

G02447 Tag - Red Paper, "PITOT PROBES COVERED" - 3 inches (76.2 mm)

Wide, 6 inches (152.4 mm) Long

G50309 Coating - Protective, Ardrox 306-N BMS 15-12

G50369 Coating - Alkaline Removable, Water Resistant BMS 15-12, Type I, Class 1

G50512 polyethylene bag

D. Procedure

Effective on: AAL ALL

SUBTASK 552-086

(1) Use the applicable procedure for the length of time, and conditions that you park the airplane:

(a) Normal parking procedures for less than 7 days ( PAGEBLOCK 10-11-01/201 )

(b) Parking in high winds ( PAGEBLOCK 10-11-03/201 )

(c) Parking with the engines removed ( PAGEBLOCK 10-11-04/201

(d) Special procedures to park the airplane for engine operation ( PAGEBLOCK 71-00-00/201 )

Effective on: AAL ALL

SUBTASK 862-082

WARNING: WHEN THE STATIC PORTS/PITOT PROBES ARE COVERED, MAKE SURE THAT CONDITION IS VISIBLE

FROM THE GROUND. IN ADDITION, ATTACH TAGS TO THE LEFT CONTROL WHEEL IN THE FLIGHT

DECK AS REMINDERS THAT STATIC PORTS/PITOT PROBES ARE COVERED. FAILURE TO OBSERVE AND

REMOVE COVERINGS OVER STATIC PORTS/PITOT PROBES BEFORE FLIGHT MAY CAUSE LARGE

ERRORS IN AIRSPEED-SENSING AND ALTITUDE-SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF

SAFE FLIGHT.

CAUTION: MAKE SURE THE PITOT PROBE COVERS ARE IN GOOD WORKING CONDITION WITH NO EVIDENCE OF

DAMAGE, ESPECIALLY FRAYING AROUND THE COVER OPENING. FRAYED FIBERS FROM THE COVER

COMBINED WITH OTHER SUBSTANCES SUCH AS DIRT, GREASE AND FLUIDS CAN CAUSE

OBSTRUCTION IN THE PROBE.

(2) The procedure for attaching static port covers to the airplane and the locations of the static ports and pitot

probes are given in Normal Parking - Maintenance Practices ( PAGEBLOCK 10-11-01/201 ).

Effective on: AAL ALL

SUBTASK 552-073

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For Reference Olny 
(3) Use the tables that follow to store the airplane.

Item

Procedures Repeat Intervals

(Days)

Initial 7 14 30 60 90 180 As

Rqd

ALL AREAS

1. Make sure all protective coverings are installed correctly. Reinstall the

protective coverings where necessary. X

EXTERNAL SURFACE PROTECTION

Inspection Criteria

1. Remove the dirt and contamination you can see on the surfaces that are

not painted. The maximum time recommended between the contamination

and the cleaning is 24 hours ( PAGEBLOCK 12-25-01/301 ).

X

NOTE: When the airplane skin becomes discolored, or stained, or the blending of adjacent surfaces for

appearance is necessary, refer to the operators standard procedures.

Short Term

1. On areas that do not have paint, do one of the steps that follows.

A. Wash the airplane at each 7- to 14-day cycle ( PAGEBLOCK 12-25-

01/301 ) or X X

B. Apply a temporary layer ofG50369 temporary coating (preferred)

orG50309 coating (alternate) to all metal that is not painted. Do not include

the engine tail cones or other components that operate at high

temperatures (the paint would burn off). Apply a layer ofG50369 temporary

coating (preferred) orG50309 coating (alternate) as follows:

X

(1) Procedure

(a) Alkaline clean the surface. X

(b) Apply with a spray gun (air or airless) to get a uniform dry film

thickness of 1.5 ±0.5 mils. The applied layer must be smooth, transparent,

and continuous.

(2) Cure

(a) Before you touch - let theG50369 temporary coating orG50309 coating

cure at room temperature for 20 minutes (minimum).

(b) Before you stack - let theG50369 temporary coating orG50309 coating

cure at room temperature for 4 hours (minimum).

C. Examine the coating for damage and corrosion of the substrate every 14

days. X X

D. Wash the painted surfaces each 28-day cycle ( PAGEBLOCK 12-25-

01/301 ) or at intervals per the corrosion prevention section (

PAGEBLOCK 51-00-52/201 and PAGEBLOCK 51-00-59/201 ).

X X

C. Each 180-day cycle, remove theG50369 temporary coating orG50309

coating and apply it again. X

Item

Procedures Repeat Intervals

(Days)

Initial 7 14 30 60 90 180 As

Rqd

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Item

Procedures Repeat Intervals

(Days)

Initial 7 14 30 60 90 180 As

Rqd

Long Term

1. Alkaline clean the surface. X

2. Apply theG50369 temporary coating (preferred) orG50309 coating

(alternate) to all metal that is not painted. Follow the instructions in the

Short Term procedures of the External Surface Protection paragraphs.

X

3. Examine all painted surfaces each 14-day cycle. Look for stains. To

remove the stains, wash the airplane ( PAGEBLOCK 12-25-01/301 ). X X

NOTE: Stains are the discoloration of the finish because of the collection of oil or other liquids. When the oil

and other liquids are mixed together with dust or other particles, the airplane finish can be

permanently deteriorated. The collection of rain streaked dust will not cause damage unless the dust

contains corrosive industrial or chemical pollutants.

E. Look for coating damage and/or corrosion of the substrate each 14-day

cycle. X X

4. Wash the painted surfaces each 28-day cycle ( PAGEBLOCK 12-25-

01/301 ) or at intervals per the corrosion prevention section (

PAGEBLOCK 51-00-52/201 and PAGEBLOCK 51-00-59/201 ).

X X

NOTE: For certain weather conditions the corrosion prevention section can allow washing intervals of up to

90 days.

5. ApplyG02219 Scotch Brand No.471 tape , or equivalent, around all

external opening doors, upper half of nose radome, and hatches on external

surface of the airplane. This is to cover the open areas and cracks to keep

the water out of the airplane.

X

6. Make sure all doors and hatches are closed when they are not used. X X

7. PutG02145 tape or other reflective material (such as aluminized mylar)

over the outside of the control cabin windows and windshields. Do not put

material that will permit heat to build up on the windshield.

X

8. Examine the structural drain holes each 90-day cycle ( PAGEBLOCK 51-

41-00/201 ). Make sure they are open. X X

WING LEADING EDGE, TRAILING EDGE, AND EMPENNAGE

1. Lubricate all flap tracks, carriages and rollersD00633 grease . Do it again

each 90-day cycle ( PAGEBLOCK 12-21-09/301 ). X X

2. Put a layer ofC00174 compound on all steel parts that are not painted. X

3. Lower (or open) all of the flaps (both leading and trailing edge) and the

spoilers, and examine them for corrosion. When completed, put all of the

flaps in the up (closed) position. Do this each 90-day cycle.

X X

4. Examine the structural drain holes and make sure they are open. Do this

again each 90-day cycle. X X

5. Before the airplane goes into storage, spray the front and rear spar

cavities with corrosion preventative compound. X

6. Put a layer ofD00091 oil on the fuel pump parts that are external to the

fuel tanks. Examine the fuel pump parts each 30-day cycle and apply a new

layer ( PAGEBLOCK 28-21-00/501 ).

X X

7. Make a visual spot check of the front and rear spars for corrosion. (You

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Item

Procedures Repeat Intervals

(Days)

Initial 7 14 30 60 90 180 As

Rqd

will have to remove some access panels in Zones 512, 524, 525, 612, 624,

and 625 ( PAGEBLOCK 06-44-00/201 ) which are aft of the slats, to

examine the front spar.)

x

EQUIPMENT/FURNISHINGS

Short Term

To give protection for a maximum of 30 days, do the procedures that follow:

1. Put dust covers on the seats. X

2. Carpets and seats can stay in the airplane for 30 days after the storage

starts (if applicable). Humidity control is not necessary for short term

parking.

3. If the toilet waste systems are serviced and activated, do the step that

follow:

A. Flush each toilet. X

B. Drain the waste tanks ( PAGEBLOCK 12-17-01/301 Config 5 ). X

C. Put the water supply override shutoff valve to the closed position and

flush the toilet twice. X

4. Clean as necessary all tray carriers, storage compartments waste

containers, and dispenser compartments in the lavatories and galleys. X

5. Examine the lavatories and galleys. Look for unusual conditions and

correct as necessary. X

6. Close the window shades and put aG00087 fabric on the main entry and

service door windows. Use an opaque material to prevent the fading of the

seats and carpet materials because of the sun's ultraviolet rays. If the seats

and carpets are removed, the window shades can be put to the up position.

X

7. Make sure that all main entry doors are in the manual mode. X

8. Open the closet, galley, and lavatory doors. This will permit the air to

flow. X

Long Term

To give protection for a maximum of 2 years, do the procedures that follow:

1. Examine the upholstery and carpets for moisture and mildew. Do this

after the start of the storage and each 60-day cycle. Correct as necessary. X X

2. When the seats and carpets remain in the airplane longer than 30 days,

the cabin humidity must be controlled to a maximum of 70%. If the

humidity cannot be controlled properly, remove the seats and carpets. Put

them in a storage area where the humidity can be properly controlled.

X

3. Disconnect and disassemble the attendant's flashlights and put them in

storage. X

INCLEMENT WEATHER CONDITIONS

1. When the snow on the airplane gets to a depth of 8 to 10 inches, remove

the snow. X

2. To make sure the airplane stays in its position when the wind is up to 65

knots, do the steps that follow ( PAGEBLOCK 10-11-03/201 ): X

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Item

Procedures Repeat Intervals

(Days)

Initial 7 14 30 60 90 180 As

Rqd

A. Make sure the engines or an equivalent weight are installed on the

airplane.

B. Put the flaps to the full up position and set the control surfaces to the

neutral position.

C. Put wheel chocks in a position forward and aft of the nose and main

landing gear wheels ( PAGEBLOCK 10-11-05/201 ).

D. Put two tiedown straps around the attach lugs of the lower drag strut on

the nose landing gear. ( PAGEBLOCK 10-11-03/201 ).

NOTE: Make sure you do not damage the hydraulic lines and the electrical wires that are found in the area

of the attach lugs.

LANDING GEAR

Short Term

1. Putwheel chocks, COM-1505 on all landing gear wheels (

PAGEBLOCK 10-11-05/201 ). X

2. Release the parking brake. X

3. Make sure the downlocks are installed on the nose and main landing gear

( PAGEBLOCK 32-00-20/201 ). X

WARNING: OBEY THE INSTALLATION PROCEDURE FOR THE DOOR LOCKS. THE DOORS OPEN AND CLOSE

QUICKLY. THE MOVEMENT OF THE DOORS CAN CAUSE INJURIES TO PERSONNEL, AND

DAMAGE TO EQUIPMENT.

4. Remove the door locks from the landing gear doors and close the doors (

PAGEBLOCK 32-00-15/201 ). x

5. Do not deflate the shock struts of the landing gear.

6. Lubricate all joints that have lubrication fittings, with grease (

PAGEBLOCK 12-21-14/301 ) x x

7. Turn the wheels one-third revolution each 14-day cycle. You can do this

by one of the procedures that follow: X X

A. Lift the wheels with an axle jack at the specified jack point (

PAGEBLOCK 07-11-03/201 ), or

B. Tow (move) the airplane ( PAGEBLOCK 09-11-00/201 ), or

C. Lift the airplane on jacks ( PAGEBLOCK 07-11-01/201 ).

Wheel rotation is necessary when the airplane is stored with rejectable tires

because the rotation minimizes the risk of wheel bearing fretting.

NOTE: As an option, you do not have to rotate the wheels with rejectable tires when the airplane is being

reactivated from storage. All of the wheel bearings and bearing inserts must be examined and

replaced individually when there are signs of fretting.

8. Do a check of the tire pressure every 14 days cycle. Make sure to keep

the tire pressure at the specified level ( PAGEBLOCK 12-15-03/301 ). X X

9. When you think the weather will freeze for a long time, put coarse sand

or a coarse fiber mat between tires and the ground surface.

NOTE: This is not necessary if the airplane will not to be moved during this time, and if the tires will be

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Item

Procedures Repeat Intervals

(Days)

Initial 7 14 30 60 90 180 As

Rqd

discarded.

Long Term

Do the procedures that follow at the start of the storage cycle and at the

specified intervals. Also do the short term storage procedures.

CAUTION: DO NOT LET THE GREASE TOUCH THE ADJACENT AREAS. THE GREASE CAN CAUSE

CONTAMINATION OF OTHER COMPONENTS.

1. Inflate the shock struts of the main landing gear until they are extended

6 inches. Butter lubricate the bare inner cylinder area that is chrome,

withD00633 grease and lower the shock strut to force grease into the inner

cylinder ( PAGEBLOCK 12-15-01/301 or PAGEBLOCK 12-15-02/301 ). If you

will fully deflate the shock strut or move the airplane, remove the remaining

grease.

X

2. Inflate the shock strut of the nose landing gear until it is extended 6

inches. Lubricate the bare inner cylinder area that is chrome, withD00633

grease and lower the shocks strut to force grease into the inner cylinder (

PAGEBLOCK 12-15-02/301 ). If you will fully deflate the shock strut or

move the airplane, remove the remaining grease.

X

3. Examine the shock struts for leaks within the first 15 days of the initial

storage, and examine them at 30-day cycle and repair as necessary. X X X

4. Lubricate all of the joints on the nose landing gear that have lubrication

fittings withD00633 grease orD00013 grease . X X

5. Lubricate all of the joints on the main landing gear that have lubrication

fittings withD00633 grease orD00013 grease . X X

6. Lubricate the wheel bearings withD00233 Mobil 28 grease orD00378

Aeroshell 22 grease . X

7. Put a cover on the tires. Use an opaque material which will keep the

weather wear to a minimum. X

8. Do a check of the pressures of the landing gear shock struts each 90-day

cycle. If you find a decrease in pressure, look for leaks and repair the shock

strut as necessary.

X

Short and Long Term

1. Use the ground release levers and operate the landing gear doors one

time each 30-day cycle. X

2. On the nose landing gear, disconnect the torsion link and operate the

steering actuators each 30-day cycle. Lubricate the bare surfaces of the

torsion link withD00633 grease orD00013 grease and keep the link

disconnected ( PAGEBLOCK 32-21-09/401 Config 1 ) ( PAGEBLOCK 32-21-

00/001 ).

X

3. If the shock struts are serviced with pureD00070 fluid , or pureD00106

fluid , then service the shock struts withD00510 Lubrizol 1395 lubricant per

Main Gear Shock Strut Fluids, TASK 12-15-01-613-048 and Nose Gear

Shock Strut Fluids, TASK 12-15-02-613-055 .

X

NOTE: It is not necessary to drain and service the shock struts that are filled with BMS 3-32 Type I or Type

II.

4. After the initial lubrication (when the storage started), and at each 90-

day cycle, do the servicing of all the lubrication fittings ( PAGEBLOCK 12- X X

American Airlines

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21-12/301 ).

5. After the initial lubrication at the start of the storage and at each 90 day

cycle, lubricate all control cables ( PAGEBLOCK 12-21-31/301 ). X X

NOTE: This does not include the cables in the body of airplane.

6. Lubricate the cables in the body of the airplane one time each year after

the initial lubrication ( PAGEBLOCK 12-21-31/301 ). X yr

FUEL SYSTEM

Short and Long Term

The procedures that follow are for protection of the fuel system for a time

up to 2 years.

1. Fill all fuel tanks to a minimum of 600-gallon capacity, and keep the fuel

at that capacity ( PAGEBLOCK 12-11-02/301 ). X

2. After the first 24 hours, after you fuel the airplane, and once each 7-day

cycle, drain all of the water. Do this through the sump drain valves from the

fuel tanks and surge tanks. This will prevent corrosion because of water

accumulation.

X X

WARNING: DO NOT BREATH OR TOUCH THE BIOCIDE FUEL ADDITIVE. IF YOU BREATH THE FUMES OR

TOUCH THE BIOCIDE FUEL ADDITIVE, IT COULD CAUSE INJURY OR DEATH TO PERSONNEL.

CAUTION: DO NOT ADD A LARGE CONCENTRATION OF THE BIOCIDE FUEL ADDITIVE TO THE FUEL TANKS.

A LARGE CONCENTRATION OF THE FUEL ADDITIVE CAN MAKE SALT DEPOSITS IN THE FUEL

TANKS.

3. Put theG02347 Kathon FP1.5 biocide orG00452 Biobor JF additive *[1] in

the fuel tanks. Add to the fuel, 135 to 270 parts per million of Biobor JF, or

0.05% to 0.15% by volume of PFA55MB (G01994 fuel additive ). Mix the

additive fully, in an open area away from airplane before it is fueled. This

will prevent high local concentrations of biocide.

X

NOTE: The fuel additive will prevent sealant deterioration in the fuel tanks.

4. Put a screen, mesh cloth, or an equivalent material over each vent

opening and cavity vent opening. UseG02219 Scotch Brand No.471 tape or

an equivalent to prevent the entry of insects into the lines. Attach red flags

to the material on each opening.

X

5. For long term storage, examine the material on each opening, each 6 to

8 weeks. X *

CONTROL CABIN

Short Term

To give protection for a maximum of 30 days, do the procedures that follow:

1. Install thepitot static probe cover, COM-1503 andG02447 "PITOT

PROBES COVERED" tag on all pitot probes. X

2. Put thepitot static probe cover, COM-1503 andG02444 "STATIC PORTS

COVERED" tag all of the static ports. The procedure to attach the static port

covers to the airplane is given in Normal Parking ( PAGEBLOCK 10-11-

01/201 ).

X

3. Putprobe cover, COM-1519 ,angle of attack vane cover, COM-2499 ,

American Airlines

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andprobe cover, SPL-1513 on the temperature probes, angle of attack

sensors, and ice detector (when installed).

X

4. Keep the main and APU fire extinguishing systems full and in a

serviceable condition ( PAGEBLOCK 26-21-00/501 , PAGEBLOCK 26-22-

00/501 ).

X X

5. Weigh the portable fire extinguishers. If the weight has decreased below

the specified weight on the nameplate, remove the extinguishers and fill

them.

X x

6. Install the dust covers on the seats. X

Long Term

Do the procedures that follow at the start of the storage cycle and at the

specified intervals. Also do the short term storage procedures.

1. When the seats and carpets remain in the airplane longer than 30 days,

the cabin humidity must be controlled to a maximum of 70%. If the

humidity cannot be controlled properly, remove the seats and carpet. Put

them in a storage area where the humidity can be properly controlled.

X

Effective on: AAL 601-610, 612-615, 617-635, 639-643, 645-647, 649, 652-660, 662, 663, 665-672, 681-999

WITHOUT THE RAIN REPELLENT SYSTEM DEACTIVATED BY ECO F0431

2. Remove the rain repellent bottle from the rain repellent system (

PAGEBLOCK 12-16-01/301 ). X

Effective on: AAL 601-610, 612-615, 617-635, 639-643, 645-647, 649, 652-660, 662, 663, 665-672, 681-999

WITHOUT THE RAIN REPELLENT SYSTEM DEACTIVATED BY ECO F0431

NOTE: The rain repellent bottle can stay installed on airplane. This is if the maximum storage is less than

60 days and the temperature inside the airplane stays less than 160°F.

Effective on: AAL 601-610, 612-615, 617-635, 639-643, 645-647, 649, 652-660, 662, 663, 665-672, 681-999

WITHOUT THE RAIN REPELLENT SYSTEM DEACTIVATED BY ECO F0431

3. Purge the rain repellent fluid from the two rain repellent lines with dry,

filtered air ( PAGEBLOCK 30-43-00/201 Config 1 ). X

4. Pitot and static system may remain intact and the drain valve assemblies

drained every 60-65 days ( PAGEBLOCK 34-11-00/301 ). X

5. Remove and store windshield wiper arms and blades ( PAGEBLOCK 30-

42-03/401 ). X

NOTE: The windshield wipers can stay installed on airplane. This is if the maximum storage is less than 60

days and the temperature inside the airplane stays less than 160°F.

6. If necessary, remove and return to stores equipment the clocks,

handsets, oxygen masks, and portable oxygen bottles. X

ELECTRICAL/ELECTRONIC SYSTEMS

Short Term (5 to 30 days)

To give protection for a maximum of 30 days, do the procedures that follow.

1. Put an electrical ground on the airplane ( PAGEBLOCK 20-41-00/201 ). X

2. Put all switches to the OFF position. This does not include the switches

used to deactivate the systems. X

American Airlines

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3. Open the circuit breakers for all electrical/electronic components that

have been removed from the airplane. X

4. Each 7-day cycle, set the main battery switch to the “ON” position and

make sure these circuit breakers are closed:

• Hot Battery Bus (P6-2)

• Alternate Landing Gear (P6-1)

• Main Battery Charger (P6-2)

• Hydraulic Generator 28B dc Sense (P6-2), if installed

• Hydraulic Generator 28V dc Power (P6-2), if installed

• APU Main Battery Tie (P6-2), if installed

X

5. Each 7-day cycle, apply power to all installed electrical/electronic

systems. Keep the power on for 2 hours. Make sure the main battery stays

in a fully charged condition. You can use ground electrical power for this

step.

X

6. On initial parking and each 7-day cycle, set the main battery switch to

the “OFF” position and make sure these circuit breakers are open:

• Hot Battery Bus (P6-2)

• Alternate Landing Gear (P6-1)

• Main Battery Charger (P6-2)

• Hydraulic Generator 28B dc Sense (P6-2), if installed

• Hydraulic Generator 28V dc Power (P6-2), if installed

• APU Main Battery Tie (P6-2), if installed

X X

7. Disconnect the APU battery ( PAGEBLOCK 24-31-03/401 ). X

Long Term (30 days to 2 years)

The procedures that follow are for protection of the airplane for a time up to

2 years. Do the procedures that follow at the start of the storage cycle and

at the specified intervals. Also do the short term storage procedures, steps

1 through 3.

1. Put an electrical ground on the airplane ( PAGEBLOCK 20-10-21/401 ). X

2. Do not remove the main battery from the airplane. It must stay on the

airplane to operate the fire detection and the fire extinguishing systems. X

3. Each 7-day cycle, set the main battery switch to the “ON” position and

make sure these circuit breakers are closed:

• Hot Battery Bus (P6-2)

• Alternate Landing Gear (P6-1)

American Airlines

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Item

Procedures Repeat Intervals

(Days)

Initial 7 14 30 60 90 180 As

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• Main Battery Charger (P6-2)

• Hydraulic Generator 28B dc Sense (P6-2), if installed

• Hydraulic Generator 28V dc Power (P6-2), if installed

• APU Main Battery Tie (P6-2), if installed

X

4. Each 7-day cycle, apply power to all installed electrical/electronic

systems. Keep the power on for 2 hours. Make sure the main battery stays

in a fully charged condition. You can use ground electrical power for this

step.

X

5. On initial parking and each 7-day cycle, set the main battery switch to

the “OFF” position and make sure these circuit breakers are open:

• Hot Battery Bus (P6-2)

• Alternate Landing Gear (P6-1)

• Main Battery Charger (P6-2)

• Hydraulic Generator 28B dc Sense (P6-2), if installed

• Hydraulic Generator 28V dc Power (P6-2), if installed

• APU Main Battery Tie (P6-2), if installed

X X

6. Remove the APU battery from the airplane. Examine, clean, and put the

battery in a storage area. The battery must be in a discharged condition.

The storage area humidity must be less than 90% and the temperatures

must not be more than 120°F (49°C) ( PAGEBLOCK 24-31-03/401 ). If

some electrical components will stay on the airplane, as shown in the

subsequent steps, do not remove the battery.

X

NOTE: External electrical power is satisfactory. Make sure that the batteries stay in a fully charged

condition.

7. Remove all of the batteries (wet and dry) that follow, from the airplane: X

A. The Emergency Light Battery Pack ( PAGEBLOCK 33-51-07/201 )

B. The Emergency Light Power Supply ( PAGEBLOCK 33-51-07/201 )

C. The batteries in the customer variable equipment on the airplane.

D. Power Megaphone Batteries

CAUTION: REMOVAL OF THE RACK-MOUNTED ELECTRONIC PACKAGES WILL CAUSE A DECREASE OF THE

COOLING AIR TO THE EQUIPMENT THAT IS USUALLY COOLED BY THE ELECTRONICS COOLING

SYSTEM. THE EQUIPMENT NOT REMOVED FROM THE AIRPLANE WILL BECOME TOO HOT IF THE

SPECIFIED PRECAUTIONS ARE NOT FOLLOWED.

8. If the relative humidity is not controlled below 70% during storage,

remove all rack-mounted electronic packages and make an inspection of

their condition, cleanliness, and signs of corrosion. After the inspection,

pack the components in moisture-resistant containers or plastic bags, and

store them in a bonded area. These electronic packages are found in the

Main Equipment Center, E1, E2, E3, E4, and E5 racks. They are also found

in the E6 Aft Equipment Center, and the Voice and Flight Recorder Shelf.

X

American Airlines

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Remove also the Warning Electronic Unit Modules from the chassis, which

found in the P51 rack.

After the removal of an equipment item, put plugs in the cooling air orifices

and the input vents for components that were removed.

NOTE: This is to make sure that an adequate cooling air flow will get to the components that stay in the

airplane.

A. The electrical equipment that follows can stay installed during the time

of storage. This is to supply electrical power for regular system tests, engine

operations, or other installed system tests.

Generator Control Units Bus Power Control Units Main Battery Charger APU

Battery Charger Static Inverter Transformer-Rectifier Units EICAS

Computers (if applicable) Spoiler Control Modules Equip. Cooling System

Controller CSEU Power Supply Modules Electronic Engine Control (EEC) (If

the EEC is installed and the engines are on the wings.)

When this equipment stays installed, the electrical power must be supplied,

and the equipment operated, each 14-day. Do this for a minimum of two

hours

X

NOTE: External electrical power is satisfactory. Make sure that the batteries stay in a fully charged

condition. Open all switches and circuit breakers, and disconnect the batteries after the electrical

power is removed.

9. The instructions in the FLIGHT CONTROLS storage procedures make it

necessary to operate the flight controls each 90-day cycle. To do this, the

Spoiler Control Modules and the CSEU Power Supply Modules must be

installed in the airplane. Remove or install these modules as specified in the

ELECTRICAL/ELECTRONIC Long Term procedures.

X X

AIR CONDITIONING SYSTEM

Short and Long Term

1. Open and ventilate the air conditioning mix bay. Keep open for the

storage period. X

2. Drain the water extractor tubing ( PAGEBLOCK 21-51-04/401 ). X

3. If the engine storage option of operating the engine to control the engine

total acid number and water (Refer to POWER PLANT AND APU STORAGE)

has been selected, operate the air conditioning systems (except the air flow

multiplier) in conjunction with the engine run as follows:

X

A. Operate each air conditioning system with its related engine for the

entire period of the engine run.

4. If the engine is removed for preservation storage and the APU is

preserved by periodic operation (Refer to POWER PLANT AND APU

STORAGE) do the procedures that follow:

X X

A. Cap the engine bleed ducts at the engine disconnect with the correct

pressure type plugs.

B. Operate the air conditioning systems for a minimum of 10 minutes

during each APU run (two packs at the same time).

HYDRAULIC SYSTEM

Short Term

American Airlines

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1. Make a check of the total hydraulic system for hydraulic fluid leakage.

Repair the leakage as necessary. Do this check each 14-day cycle (

PAGEBLOCK 29-11-00/601 ).

X X

2. Make sure the hydraulic system is filled withD00153 hydraulic fluid to the

specified level ( PAGEBLOCK 12-12-01/301 ). X

3. Clean and apply a layer ofD00054 MCS 352B fluid orD00153 hydraulic

fluid to the bare finished surfaces on all actuator piston rods, valve slides,

and other hydraulic components

( PAGEBLOCK 12-21-00/301 , PAGEBLOCK 12-21-04/301 , PAGEBLOCK 12-

21-05/301 , PAGEBLOCK 12-21-06/301 , PAGEBLOCK 12-21-07/301 ,

PAGEBLOCK 12-21-08/301 , PAGEBLOCK 12-21-09/301 , PAGEBLOCK 12-

21-10/301 , PAGEBLOCK 12-21-12/301 , PAGEBLOCK 12-21-13/301 ,

PAGEBLOCK 12-21-14/301 , PAGEBLOCK 12-21-15/301 , PAGEBLOCK 12-

21-18/301 , PAGEBLOCK 12-21-22/301 , PAGEBLOCK 12-21-27/301 ,

PAGEBLOCK 12-21-30/301 , PAGEBLOCK 12-21-31/301 , PAGEBLOCK 12-

21-32/301 , PAGEBLOCK 12-21-33/301 , PAGEBLOCK 12-21-34/301 , 12-

21-35-3)

X

NOTE: Do not useD00153 hydraulic fluid orD00054 MCS 352B fluid on components that contain MIL-PRF5606 or MIL-PRF-6083 (i.e., landing gear shock struts).D00054 MCS 352B fluid contains SKYDROL

and will cause damage to the seals that are used in the MIL oil systems.

4. Apply a layer ofB50080 compound preservative compound to all

aluminum actuator, valve, and equipment housings. Make sure the

compound does not spill on the piston rods and valve slides (this does not

include components that contain MIL-PRF-5606).

X

5. Apply a layer ofB50080 compound preservative compound to all

hydraulic system plumbing that is not painted. X

NOTE: It is not necessary to apply a protective layer to all hydraulic system plumbing. It is not necessary if

it is found in the areas which have the humidity and temperature controlled as specified in

INTERIORS storage requirements.

Long Term

1. When the storage is more than 30 days the procedures that follow are for

protection of the airplane for a time up to 2 years. Do the procedures that

follow at the start of the storage cycle and at the specified intervals. Also do

the short term storage procedures.

A. Each 60-day cycle, make a check of the hydraulic system components

that were cleaned and lubricated withD00153 hydraulic fluid assembly

lubricant. Make sure the specified components have a full layer of lubricant

and do not have corrosion ( PAGEBLOCK 12-12-01/301 ).

X

NOTE: When the lubrication is not complete and some components are corroded, clean the area fully and

do the preservation procedure. Refer to the Boeing Corrosion Manual for the necessary procedures.

B. Each 180-day cycle, release the pressure in the hydraulic reservoirs and

pressurize them with dry nitrogen ( PAGEBLOCK 29-11-00/201 ). X X

C. Each 180-day cycle, release the pressure in the hydraulic accumulators

that follow and pressurize them with dry nitrogen.

The Parking Brake Accumulator ( PAGEBLOCK 12-15-04/301 ).

X X

FLIGHT CONTROLS

Short and Long Term

American Airlines

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The procedures that follow are for protection of the airplane for a time up to

2 years. Do the procedures that follow at the start of the storage cycle and

at the specified intervals.

1. Initially and at each 90-day cycle, operate the flight controls that follow.

Do this for the complete cycles specified below:

A. The leading edge slats (one cycle) ( PAGEBLOCK 27-81-00/501 ) X X

B. The trailing edge flaps (one cycle) ( PAGEBLOCK 27-51-00/501 ) X X

C. The spoilers (three cycles) ( PAGEBLOCK 27-61-00/501 ) X X

D. The ailerons (three cycles) ( PAGEBLOCK 27-11-00/501 ) X X

E. The elevators (three cycles) ( PAGEBLOCK 27-31-00/501 ) X X

F. The rudder (three cycles) ( PAGEBLOCK 27-21-00/501 Config 1 ) X X

G. The horizontal stabilizer (three cycles). X X

2. After the flight controls have been cycled, put the flaps and slats to the

retracted position. Also put the control surfaces to the neutral position. X X

3. Initially and at each 90-day cycle, operate the stabilizer trim, the rudder

trim and the aileron trim for one complete cycle. Put the stabilizer trim, the

rudder trim, and aileron trim to a different position than it was set during

the last cycle.

X X

NOTE: You can use external electrical and hydraulic power when the airplane power is not available.

4. Initially and at each 90-day cycle, lubricate the flap jackscrew and

ballnut assemblies withD50180 AeroShell Grease 33 ( PAGEBLOCK 12-21-

09/301 ).

X X

5. Visually examine the condition of all control cables ( PAGEBLOCK 20-20-

02/601 ). Lubricate the control cables in the trailing edge and wheel wells (

PAGEBLOCK 12-21-31/301 1).

X X

6. Lubricate all control cables if they were lubricated within 60 days before

the start of storage. This applies to control cables inside and outside the

body with the exception of the control cables in the wing trailing edge and

the wheel wells ( PAGEBLOCK 12-21-31/301 ).

X X

7. Apply a layer ofB50080 compound corrosion preventive compound to all

not painted steel fittings, flap tracks, linkages to the flaps, and inside the

flap track fairings, as follows, ( PAGEBLOCK 27-51-00/001 ):

X X

A. Do not apply the corrosion preventative compound to areas which will be

subsequently painted or sealed.

B. Shield or protect the control cables, pulleys, wire bundles, etc., to

prevent the direct application of corrosion preventative compound to them.

C. Apply masking tape to the electrical connectors to prevent the

application of the compound to electrical contacts.

D. Apply the compound before the installation of equipment (if applicable).

E. Do not apply corrosion preventative compound to teflon bearings,

surfaces or joints, which are lubricated in other procedures.

F. The finished application of the corrosion preventive compound must be a

continuous film, with no puddles.

American Airlines

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G. Inspect the application each 30-day cycle. X

OXYGEN SYSTEM

Short Term

When an airplane is put in storage for time that is not more than 60 days,

no special precautions are necessary. But, you must make sure that the

high pressure valves on the oxygen supply cylinders are closed. These

oxygen cylinders are for the crew and the passenger systems (

PAGEBLOCK 12-15-08/301 , PAGEBLOCK 35-11-00/201 ).

Long Term

The procedures that follow are for protection of the airplane for a time up to

2 years. Do the procedures that follow at the start of the storage cycle and

at the specified intervals.

WARNING: OBEY THE PRECAUTIONS IN PAGEBLOCK 12-15-08/301 WHEN YOU REMOVE AND INSTALL

OXYGEN CYLINDERS. IF YOU DO NOT OBEY THE PRECAUTIONS, INJURY TO PERSONS OR

DAMAGE TO EQUIPMENT CAN OCCUR.

1. Remove the portable oxygen cylinders and the crew oxygen cylinders

(this includes the regulator). Follow the operator's standard procedures and

put them in a spares storage.

X

NOTE: Attach a tag that identifies each cylinder as a serviceable part when the pressure is above 50 psi.

Also do this if the hydrostatic test date has not expired. When the hydrostatic test date has expired,

follow the operator's standard procedures.

2. Put a cap on the cylinder end of the oxygen distribution lines. Also, put a

cap on the connector end of the hoses that are in the oxygen mask stowage

boxes. Put cleanG50512 polyethylene bag on the lines and hoses that have

the caps. Attach red flags to the bags ( PAGEBLOCK 35-11-51/401 ).

X

3. Remove the crew system oxygen masks. Put the masks in cleanG50512

polyethylene bag for storage. Seal the oxygen hose connector on the

stowage box assembly with a cap.

X

POTABLE WATER SYSTEM

Short and Long Term

1. Drain all of the water system. This includes the galley and the lavatory

tanks. Do a purge of the complete potable water system, using a low

pressure source (45 PSI maximum), of dry air or nitrogen ( PAGEBLOCK 12-

14-01/301 Config 1 ).

X

NOTE: Do not close and seal the drains. Put screens on them to prevent the entrance of insects.

2. Remove the water filters and do not install them during the storage time,

( PAGEBLOCK 38-10-00/201 ). X

3. Remove all of the coffeemakers and water boilers from airplane. Store

them at temperatures that do not freeze. X

FIRE EXTINGUISHING SYSTEMS

Short and Long Term

The procedure that follows is for protection of the airplane for a time up to 2

years. Do the procedure that follows at the start of the storage cycle, and at

American Airlines

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the specified intervals ( PAGEBLOCK 26-21-00/501 ).

1. Make sure that the discharge squibs stay installed on all fire extinguisher

bottles. Also make sure the squibs are connected to their correct electrical

supply.

X

NOTE: The fire extinguisher bottles must stay in the airplane in a charged, and in a serviceable condition.

POWER PLANT AND APU

1. Refer to PAGEBLOCK 71-00-03/201 for the maintenance procedures that

are applicable to engine storage.

2. Store the airplane with the engines removed:

A. Make sure protective caps are installed on all tube ends, ducts, electrical

connectors, fuel fittings and hydraulic fittings ( PAGEBLOCK 71-00-02/401

).

B. Install a moisture barrier over exposed metal surfaces on the pylon.

C. Make drains in the moisture barrier to allow water to get out.

D. Add a desiccant inside the moisture barrier to keep humidity near the

exposed metal surface ## low.

2. Refer to PAGEBLOCK 49-11-00/201 for the procedures that are applicable

to APU storage.

*[1] The fuel additive listed certified by the airframe and engine manufacturer. It may not have been approved

in some geographic areas. Local regulatory agencies should be consulted with respect to approval status.

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AIRCRAFT MAINTENANCE MANUAL

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01/20/2012

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For Reference Olny 
Task 10-11-02-632-002 "USE MCM CARD 05-92-64, 05-92-78, as required by GPM 03-07"

Put the Airplane Back to a Serviceable Condition After Storage

Effective on: AAL ALL

E. References

Reference Title

07-11-01 P/B 201 JACKING AIRPLANE - MAINTENANCE PRACTICES

12-11-01 P/B 301 FUEL TANK PRESSURE FUELING

12-12-01 P/B 301 HYDRAULIC SYSTEMS - SERVICING

12-14-01

P/B 301 Config 1

POTABLE WATER SYSTEM - SERVICING

12-15-01 P/B 301 MAIN GEAR SHOCK STRUT - SERVICING

12-15-02 P/B 301 NOSE GEAR SHOCK STRUT - SERVICING

12-15-03 P/B 301 LANDING GEAR TIRES - SERVICING

12-15-04 P/B 301 PARKING BRAKE ACCUMULATOR - SERVICING

12-15-08 P/B 301 OXYGEN - SERVICING

12-16-01 P/B 301 RAIN REPELLENT BOTTLE - SERVICING

12-17-01

P/B 301 Config 5

MANUAL DUMP WASTE TANK - SERVICING

12-21-00 P/B 301 AIRPLANE LUBRICATION - SERVICING

12-21-09 P/B 301 TRAILING EDGE FLAP SYSTEM - SERVICING

12-21-12 P/B 301 NOSE GEAR AND ACTUATING MECHANISMS - SERVICING

12-21-13 P/B 301 NOSE GEAR DOORS AND ACTUATING MECHANISMS - SERVICING

12-21-14 P/B 301 MAIN GEAR AND ACTUATING MECHANISMS - SERVICING

12-21-15 P/B 301 MAIN GEAR DOORS AND ACTUATING MECHANISMS - SERVICING

12-21-18 P/B 301 NO. 1, 2, AND 4 PASSENGER DOORS - SERVICING

12-21-22 P/B 301 NO. 1 AND 2 CARGO DOORS - SERVICING

12-25-01 P/B 301 AIRPLANE SERVICING (CLEAN AND POLISH)

20-10-03 P/B 401 CONTROL CABLES - REMOVAL/INSTALLATION

20-20-02 P/B 601 CONTROL CABLES - INSPECTION/CHECK

21-00-00 AIR CONDITIONING

21-00-00 P/B 201 AIR CONDITIONING - GENERAL - MAINTENANCE/PRACTICES

24-11-00 P/B 501 GENERATOR DRIVE SYSTEM - ADJUSTMENT/TEST

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For Reference Olny 
Reference Title

24-21-00 P/B 501 POWER AND REGULATION - ADJUSTMENT/TEST

24-22-00 P/B 201 CONTROL (SUPPLY POWER) - MAINTENANCE PRACTICES

24-25-00 P/B 501 HYDRAULIC MOTOR GENERATOR SYSTEM- ADJUSTMENT/TEST

24-30-00 P/B 501 DC GENERATION - ADJUSTMENT/TEST

24-31-01 P/B 401 MAIN BATTERY - REMOVAL/INSTALLATION

24-31-03 P/B 401 APU BATTERY - REMOVAL/INSTALLATION

24-33-00 P/B 601 STANDBY POWER - INSPECTION/CHECK

24-41-00 P/B 501 AC EXTERNAL POWER - ADJUSTMENT/TEST

25-00-00 P/B 701 EQUIPMENT/FURNISHINGS - CLEANING AND PAINTING

26-21-01 P/B 401 ENGINE FIRE EXTINGUISHER BOTTLE - REMOVAL/INSTALLATION

26-23-00 P/B 501 CARGO FIRE EXTINGUISHING SYSTEM - ADJUSTMENT TEST

26-26-01 P/B 201 CARBON DIOXIDE FIRE EXTINGUISHER - MAINTENANCE PRACTICES

26-26-02 P/B 201 HALON/BCF EXTINGUISHER - MAINTENANCE PRACTICES

27-00-01 P/B 201 FLIGHT CONTROL CABLES - MAINTENANCE PRACTICES

27-09-00 P/B 201 FLIGHT CONTROL SYSTEM ELECTRONICS UNIT (CSEU) - MAINTENANCE PRACTICES

27-11-00 P/B 501 AILERON AND AILERON TRIM CONTROL SYSTEM - ADJUSTMENT/TEST

27-18-00 P/B 501 AILERON POSITION INDICATING SYSTEM - ADJUSTMENT/TEST

27-21-00

P/B 501 Config 1

RUDDER AND RUDDER TRIM CONTROL SYSTEM - ADJUSTMENT/TEST

27-23-00 P/B 501 RUDDER AND ELEVATOR HYDRAULIC SYSTEMS - ADJUSTMENT/TEST

27-28-00 P/B 501 RUDDER POSITION INDICATING SYSTEM - ADJUSTMENT/TEST

27-31-00 P/B 501 ELEVATOR CONTROL SYSTEM - ADJUSTMENT/TEST

27-32-00

P/B 501 Config 5

STALL WARNING SYSTEM - ADJUSTMENT/TEST

27-38-00 P/B 501 ELEVATOR POSITION INDICATING SYSTEM - ADJUSTMENT/TEST

27-41-00 P/B 501 HORIZONTAL STABILIZER TRIM CONTROL SYSTEM - ADJUSTMENT/TEST

27-48-00 P/B 501 STABILIZER TRIM POSITION INDICATING SYSTEM - ADJUSTMENT/TEST

27-51-00 P/B 201 TRAILING EDGE FLAP SYSTEM - MAINTENANCE PRACTICES

27-51-00 P/B 501 TRAILING EDGE FLAP SYSTEM - ADJUSTMENT/TEST

27-58-00 P/B 501 TRAILING EDGE FLAP POSITION INDICATING SYSTEM - ADJUSTMENT/TEST

27-61-00 P/B 501 SPOILER/SPEEDBRAKE CONTROL SYSTEM - ADJUSTMENT/TEST

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For Reference Olny 
Reference Title

27-62-00 P/B 501 AUTO-SPEEDBRAKE CONTROL SYSTEM - ADJUSTMENT/TEST

27-62-00

P/B 501 Config 1

AUTO-SPEEDBRAKE CONTROL SYSTEM - ADJUSTMENT/TEST

27-81-00 P/B 201 LEADING EDGE SLAT SYSTEM - MAINTENANCE PRACTICES

27-81-00 P/B 501 LEADING EDGE SLAT SYSTEM - ADJUSTMENT/TEST

27-88-00 P/B 501 LEADING EDGE SLAT POSITION INDICATING SYSTEM - ADJUSTMENT/TEST

28-11-00 P/B 201 FUEL TANKS - MAINTENANCE PRACTICES

28-22-07 P/B 601 FUEL LINE AND FITTINGS - INSPECTION/CHECK

28-26-00 P/B 201 DEFUELING - MAINTENANCE PRACTICES

29-00-00 P/B 601 HYDRAULIC POWER - INSPECTION/CHECK

29-11-00 P/B 201 MAIN (LEFT, RIGHT, AND CENTER) HYDRAULIC SYSTEMS - MAINTENANCE PRACTICES

29-11-00 P/B 601 MAIN (LEFT, RIGHT, AND CENTER) HYDRAULIC SYSTEMS - INSPECTION/CHECK

29-11-13 P/B 401 CENTER SYSTEM RETURN FILTER MODULE AND COMPONENTS - REMOVAL/INSTALLATION

29-11-15 P/B 401 LEFT AND RIGHT SYSTEM RETURN FILTER MODULE AND COMPONENTS - REMOVAL/INSTALLATION

29-11-17 P/B 401 LEFT AND RIGHT SYSTEM ENGINE-DRIVEN PUMP (EDP) PRESSURE AND CASE DRAIN FILTER MODULE AND

COMPONENTS - REMOVAL/INSTALLATION

29-11-19 P/B 401 CENTER SYSTEM ALTERNATING CURRENT MOTOR PUMP (ACMP) PRESSURE AND CASE DRAIN FILTER

MODULE AND COMPONENTS - REMOVAL/INSTALLATION

29-21-00 P/B 501 RAM AIR TURBINE (RAT) SYSTEM - ADJUSTMENT/TEST

29-22-00-710-

801

Operational Test - Power Transfer Unit (PTU) Auto Control and Indicating System (P/B 501)

29-22-00-710-

802

Operational Test - Power Transfer Unit (PTU) Manual Ground Control System (P/B 501)

29-22-00-710-

803

Operational Test - Flow Limiter Valve for the Power Transfer Unit (PTU) System (P/B 501)

29-22-02 P/B 401 POWER TRANSFER UNIT (PTU) PRESSURE FILTER MODULE AND COMPONENTS - REMOVAL/INSTALLATION

29-22-05 P/B 401 POWER TRANSFER UNIT (PTU) CASE DRAIN FILTER MODULE AND COMPONENTS - REMOVAL/INSTALLATION

29-31-00 P/B 501 HYDRAULIC PRESSURE INDICATING SYSTEM - ADJUSTMENT/TEST

29-32-00 P/B 501 HYDRAULIC FLUID TEMPERATURE INDICATING SYSTEM - ADJUSTMENT/TEST

29-33-00 P/B 501 HYDRAULIC FLUID QUANTITY INDICATING SYSTEM - ADJUSTMENT/TEST

29-35-00 P/B 501 HYDRAULIC RESERVOIR PRESSURE INDICATION SYSTEM - ADJUSTMENT/TEST

30-31-00 P/B 501 PITOT PROBE ANTI-ICING - ADJUSTMENT/TEST

30-42-00 P/B 501 WINDSHIELD WIPER SYSTEM - ADJUSTMENT/TEST

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For Reference Olny 
Reference Title

30-42-00 P/B 601 WINDSHIELD WIPER SYSTEM - INSPECTION/CHECK

30-42-03 P/B 401 WINDSHIELD WIPER ARM/BLADE - REMOVAL/INSTALLATION

32-00-15 P/B 201 LANDING GEAR DOOR GROUND OPERATIONS AND LOCKING PROCEDURE - MAINTENANCE PRACTICES

32-00-20 P/B 201 LANDING GEAR DOWNLOCKS - MAINTENANCE PRACTICES

32-12-00 P/B 501 MAIN GEAR DOORS - ADJUSTMENT/TEST

32-35-00 P/B 501 LANDING GEAR ALTERNATE EXTENSION - ADJUSTMENT/TEST

32-45-01 P/B 401 MAIN GEAR WHEEL AND TIRE - REMOVAL/INSTALLATION

32-45-03 P/B 601 WHEELS - INSPECTION/CHECK

32-45-04 P/B 601 TIRES - INSPECTION/CHECK

33-11-00 P/B 501 FLIGHT COMPARTMENT ILLUMINATION - ADJUSTMENT/TEST

33-13-00 P/B 501 INTEGRAL PANEL LIGHTS - ADJUSTMENT/TEST

33-16-00 P/B 501 MASTER DIM AND TEST - ADJUSTMENT/TEST

33-22-00 P/B 501 PASSENGER LOADING LIGHTS - ADJUSTMENT/TEST

33-42-00 P/B 501 LANDING, RUNWAY TURNOFF AND TAXI LIGHTS - ADJUSTMENT/TEST

33-43-00 P/B 501 POSITION LIGHTS - ADJUSTMENT/TEST

33-44-00 P/B 501 ANTI-COLLISION LIGHTS - ADJUSTMENT/TEST

34-11-00 P/B 301 PITOT-STATIC SYSTEM - SERVICING

34-11-00 P/B 501 PITOT-STATIC SYSTEM - ADJUSTMENT/TEST

34-23-00 P/B 201 STANDBY MAGNETIC COMPASS - MAINTENANCE PRACTICES

35-11-00 P/B 201 CREW OXYGEN SYSTEM - MAINTENANCE PRACTICES

38-10-00 P/B 201 POTABLE WATER SYSTEM - MAINTENANCE PRACTICES

49-11-00 P/B 201 AUXILIARY POWER UNIT - MAINTENANCE PRACTICES

51-41-00 P/B 201 AIRFRAME DRAINAGE - MAINTENANCE PRACTICES

52-11-00 P/B 201 NO. 1, 2, AND 4 PASSENGER DOORS - MAINTENANCE PRACTICES

52-11-20 MECHANISM - PASSENGER DOOR EMERGENCY

52-11-25 MECHANISM - NO. 1, 2, AND 4 PASSENGER DOOR GIRT BAR

52-11-30 P/B 601 NO. 1, 2, AND 4 PASSENGER DOOR EMERGENCY POWER RESERVOIR - INSPECTION/CHECK

71-00-00 P/B 201 POWER PLANT - MAINTENANCE PRACTICES

SOPM 20-30-80 Solvents For General Cleaning of Metal (Series 80)

American Airlines

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For Reference Olny 
Reference Title

SOPM 20-30-81 Solvents For General Cleaning of all Organic Coatings (Series 81)

F. Tools/Equipment

NOTE: When more than one tool part number is listed under the same "Reference" number, the tools shown are alternates to

each other within the same airplane series. Tool part numbers that are replaced or non-procurable are preceded by

"Opt:", which stands for Optional.

Reference Description

COM-1502 Chocks - Wheel

Effective on: AAL ALL; 757-200ER

(Part #: W92, Supplier: 9L752)

G. Consumable Materials

Reference Description Specification

B01000 Solvent - General Cleaning Of Metal (AMM 20-30-80)

B01001 Solvent - General Cleaning Of All Organic Coatings (AMM 20-30-81/201) - Series 81

D00388 Grease - General Purpose, Wheel Bearing - Aeroshell 5

G00009 Compound - Organic Corrosion Inhibiting BMS3-23

G50267 Remover - Alkaline - Ardrox 7050W (used to remove Ardrox 306N protective coating)

H. Clean the Airplane

Effective on: AAL ALL

SUBTASK 612-003

(1) Remove the temporary layer of protective coating that was installed in the EXTERNAL SURFACE PROTECTION

procedure of the Long Term storage. Do the steps that follow:

CAUTION: OBEY THE PRECAUTIONS FOR THE ARDROX 7050W REMOVER. DO NOT PERMIT THE

REMOVER TO DRY. DO NOT PERMIT THE REMOVER TO TOUCH AN ACRYLIC SURFACE

FOR MORE THAN 60 MINUTES. DO NOT PERMIT THE REMOVER TO TOUCH HIGHSTRENGTH STEEL PARTS (180,000 PSI AND OVER). IF YOU DO NOT OBEY THESE

INSTRUCTIONS, DAMAGE TO THE COMPONENTS CAN OCCUR.

(a) ApplyG50267 remover . Put the remover on approximately 20 mils thick, and for a dwell time of

not less than 10 minutes.

1 Pressure flush the area with water.

NOTE: Make sure the water temperature is not more than 140°F (60°C).

(b) Remove the tape from the control cabin windows and windshields, external openings, doors,

hatches, and the nose radome.

Effective on: AAL ALL

SUBTASK 712-004

(2) Make sure the structural drain holes are open ( PAGEBLOCK 51-41-00/201 ).

Effective on: AAL ALL

American Airlines

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AIRCRAFT MAINTENANCE MANUAL

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For Reference Olny 
SUBTASK 642-005

(3) Lubricate the external doors that follow:

(a) The Number 1, 2, and 4 Passenger Door L and R ( PAGEBLOCK 12-21-18/301 ).

(b) The Number 1 and 2 Cargo Door ( PAGEBLOCK 12-21-22/301 ).

Effective on: AAL ALL

SUBTASK 212-006

(4) Examine the door seals visually for areas that are flat, and for deterioration.

Effective on: AAL ALL

SUBTASK 212-007

(5) Examine the internal and external door handles, on the entry and service doors. Make sure they have the

specified torque loads.

Effective on: AAL ALL

SUBTASK 712-008

(6) Operate the internal and external door handles, two or three times.

(a) Make sure they operate correctly and move freely.

Effective on: AAL ALL

SUBTASK 212-009

(7) Examine the mechanisms that follow for the passenger entry doors, and make sure they operate correctly:

(a) The Number 1, 2, and 4 Passenger Door Emergency Mechanism ( SUBJECT 52-11-20 ).

(b) The Number 1, 2, and 4 Passenger Door Girt Bar Mechanism ( SUBJECT 52-11-25 ).

Effective on: AAL ALL

SUBTASK 612-010

(8) Make sure the pressure of the emergency power reservoir bottle is correct ( PAGEBLOCK 52-11-30/601 ).

Effective on: AAL ALL

SUBTASK 612-011

(9) Clean the airplane ( PAGEBLOCK 12-25-01/301 ).

I. Landing Gear

Effective on: AAL ALL

SUBTASK 632-012

(1) Make sure you put the landing gear back to a serviceable condition. Do the steps that follow:

(a) Before you pressurize the landing gear, do the steps that follow:

1 Make sure that all landing gear are locked in the down position ( PAGEBLOCK 32-00-

20/201 ).

2 Make sure the downlocks are installed on the nose and main landing gear (

PAGEBLOCK 32-00-20/201 ).

3 Make sure the landing gear control handle, on the first officer's instrument panel, is

American Airlines

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For Reference Olny 
in the DOWN position.

4 Make sure the main landing gear doors are closed.

5 Make sure the ground door release handles for the main landing gear doors, are in

the DOOR CLOSE position.

6

6

Make sure the forward doors of the nose landing are open.

Make sure the forward doors of the nose landing are open.

7 Make sure the torsion link of the nose landing gear is connected.

Effective on: AAL ALL

SUBTASK 642-013

(2) Lubricate the landing gear:

(a) Lubricate the nose landing gear doors ( PAGEBLOCK 12-21-13/301 ).

(b) Lubricate the main landing gear doors and uplock hooks ( PAGEBLOCK 12-21-15/301 .

(c) Lubricate the nose landing gear and actuator mechanisms ( PAGEBLOCK 12-21-12/301 ).

(d) Lubricate the main landing gear and actuator mechanisms ( PAGEBLOCK 12-21-14/301 ).

Effective on: AAL ALL

SUBTASK 212-076

WARNING: BE CAREFUL WHEN YOU OPERATE THE DOORS OF THE NOSE AND MAIN LANDING GEAR. THE

LANDING GEAR DOORS CAN MOVE QUICKLY AND CAUSE INJURY TO PERSONS AND DAMAGE TO

EQUIPMENT.

(3) Examine the door areas of the nose and main landing gear. Make sure that there are no persons or equipment in

the area.

Effective on: AAL ALL

SUBTASK 862-015

(4) Energize the airplane's electrical system ( PAGEBLOCK 24-22-00/201 ).

Effective on: AAL ALL

SUBTASK 862-016

(5) Pressurize the airplane's hydraulic systems ( PAGEBLOCK 29-11-00/201 ).

Effective on: AAL ALL

SUBTASK 862-017

(6) Operate the doors of the nose and main landing gear 2 or 3 times ( PAGEBLOCK 32-00-15/201 ).

NOTE: This is to make sure they move freely when you use the release handles.

Effective on: AAL ALL

SUBTASK 710-001

(7) Do the Operational Test for the Landing Gear Alternate Extension ( PAGEBLOCK 32-35-00/501 ).

Effective on: AAL ALL

SUBTASK 212-018

(8) Examine the main landing gear door seals visually for areas that are flat, and for deterioration ( PAGEBLOCK 32-

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For Reference Olny 
12-00/501 ).

Effective on: AAL ALL

SUBTASK 212-019

(9) Examine the nose landing gear door seals visually for areas that are flat, and for deterioration.

Effective on: AAL ALL

SUBTASK 612-020

(10) Do the servicing of the shock struts for the main landing gear ( PAGEBLOCK 12-15-01/301 or PAGEBLOCK 12-

15-02/301 ).

Effective on: AAL ALL

SUBTASK 612-021

(11) Do the servicing of the shock strut for the nose landing gear ( PAGEBLOCK 12-15-02/301 ).

Effective on: AAL ALL

SUBTASK 612-022

(12) When there is too much grease on the inner cylinders of the shock struts, clean it off.

Effective on: AAL ALL

SUBTASK 092-023

(13) Remove the tiedown straps and thechocks, COM-1502 .

Effective on: AAL ALL

SUBTASK 582-024

(14) Lift the airplane on jacks to remove the wheels ( PAGEBLOCK 07-11-01/201 ).

Effective on: AAL ALL

SUBTASK 642-083

(15) If the aiplane was in storage for more than 30 days or if the wheel assemblies were pressure washed during

storage, remove the wheels to apply lubricant ( PAGEBLOCK 32-45-01/401 ), and do the steps that follow (

PAGEBLOCK 12-21-00/301 ):

(a) Do an inspection of the wheel bearings (this includes the cups in the wheels) ( PAGEBLOCK 32-

45-03/601 ).

(b) Fill the wheel bearings withD00388 Aeroshell 5 grease .

(c) Install the wheel bearings in the wheels.

(d) Install the wheels on the airplane.

Effective on: AAL ALL

SUBTASK 212-075

(16) Examine the condition and serviceability of the tires ( PAGEBLOCK 32-45-04/601 ).

Effective on: AAL ALL

SUBTASK 612-026

(17) Make sure the tires are inflated to the specified pressure with nitrogen ( PAGEBLOCK 12-15-03/301 ).

Effective on: AAL ALL

American Airlines

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For Reference Olny 
SUBTASK 582-027

(18) Tow or taxi the airplane sufficiently before flight to prevent tire flat spots.

J. Fuel System

Effective on: AAL ALL

SUBTASK 632-028

(1) Remove the items that follow from each vent opening and each cavity opening:

(a) The screen

(b) The mesh cloth

(c) All other equivalent material

(d) The red flags

(e) The 3M tape.

Effective on: AAL ALL

SUBTASK 652-029

(2) Do the servicing of the fuel tanks as follows:

(a) Defuel the fuel tanks ( PAGEBLOCK 28-26-00/201 ).

(b) Do the leakage test for the fuel system tubing ( PAGEBLOCK 28-22-07/601 ).

(c) When the airplane is in storage for more than 60 days, go into the fuel tanks ( PAGEBLOCK 28-

11-00/201 ).

1 Examine the fuel tanks for microbial growth and structural corrosion.

(d) ApplyG00009 corrosion inhibiting compound to the engine dry bays and center wing cavity.

NOTE: This will remove the moisture that collects.

(e) Refuel the airplane (fill all serviceable fuel tanks to full) ( PAGEBLOCK 12-11-01/301 ).

NOTE: When it is possible, do not operate the airplane for 24 hours. After 24 hours, examine

it for external fuel leaks.

K. Electrical/Electronics Systems

Effective on: AAL ALL

SUBTASK 632-031

(1) To make sure the Electrical/Electronic systems are serviceable, do the steps that follow:

(a) Make sure the electrical ground is installed on the airplane.

(b) Make sure the Electrical/Electronic systems circuit breakers are open or closed when it is

necessary.

(c) Make sure the Electrical/Electronic systems switches are in the OFF position.

(d) Make sure the equipment racks are clean, dry, and have no corrosion.

(e) Install all of the rack-mounted electronic packages when it is necessary.

American Airlines

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For Reference Olny 
1 These were the components that were removed in the Electrical/Electronic System

procedures for Long Term storage.

Effective on: AAL ALL

SUBTASK 712-032

(2) Do an operational test of the Electrical/Electronic components that are installed.

(a) GENERATOR DRIVE SYSTEM - ADJUSTMENT/TEST, PAGEBLOCK 24-11-00/501

(b) POWER AND REGULATION - ADJUSTMENT/TEST, PAGEBLOCK 24-21-00/501

Effective on: (AAL 172-179, 183-194, 197-199, 608, 609, 687-692; AAL 195, 196 POST SB 757-24-

0127) 172-179, 183-199, 608-609, 687-692

(c) HYDRAULIC MOTOR GENERATOR SYSTEM- ADJUSTMENT/TEST, PAGEBLOCK 24-25-00/501

(d) DC GENERATION - ADJUSTMENT/TEST, PAGEBLOCK 24-30-00/501

(e) STANDBY POWER - INSPECTION/CHECK, PAGEBLOCK 24-33-00/601

(f) AC EXTERNAL POWER - ADJUSTMENT/TEST, PAGEBLOCK 24-41-00/501

(g) FLIGHT COMPARTMENT ILLUMINATION - ADJUSTMENT/TEST, PAGEBLOCK 33-11-00/501

(h) INTEGRAL PANEL LIGHTS - ADJUSTMENT/TEST, PAGEBLOCK 33-13-00/501

(i) MASTER DIM AND TEST - ADJUSTMENT/TEST, PAGEBLOCK 33-16-00/501

(j) PASSENGER LOADING LIGHTS - ADJUSTMENT/TEST, PAGEBLOCK 33-22-00/501

(k) LANDING, RUNWAY TURNOFF AND TAXI LIGHTS - ADJUSTMENT/TEST, PAGEBLOCK 33-42-00/501

(l) POSITION LIGHTS - ADJUSTMENT/TEST, PAGEBLOCK 33-43-00/501

(m) ANTI-COLLISION LIGHTS - ADJUSTMENT/TEST, PAGEBLOCK 33-44-00/501

Effective on: AAL ALL

SUBTASK 422-033

(3) Install all of the batteries that were removed for storage.

Effective on: AAL ALL

SUBTASK 762-034

(4) Make sure the batteries that follow are fully charged:

(a) The main battery ( PAGEBLOCK 24-31-01/401 ).

(b) The APU battery ( PAGEBLOCK 24-31-03/401 ).

Effective on: AAL ALL

SUBTASK 722-035

(5) Do a functional test of the batteries that follow:

(a) The main battery ( PAGEBLOCK 24-31-01/401 ).

(b) The APU battery ( PAGEBLOCK 24-31-03/401 ).

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For Reference Olny 
Effective on: AAL ALL

SUBTASK 862-036

(6) If the batteries were not removed at the start of the storage, close all circuit breakers.

L. Control Cabin Equipment

Effective on: AAL ALL

SUBTASK 632-037

(1) To make the flight compartment equipment serviceable, do the steps that follow:

WARNING: FAILURE TO REMOVE COVERS FROM PITOT PROBES BEFORE FLIGHT MAY CAUSE

LARGE ERRORS IN AIRSPEED-SENSING AND ALTITUDE-SENSING SIGNALS WHICH

MAY LEAD TO LOSS OF SAFE FLIGHT.

CAUTION: REMOVE ALL COVERS. ENGINES SHOULD NOT BE OPERATED WITH COVERS IN PLACE

BECAUSE THE COVERS CAN COME OFF AND DAMAGE THE ENGINES.

CAUTION: MAKE SURE THE PITOT PROBE COVERS ARE IN GOOD WORKING CONDITION WITH NO

EVIDENCE OF DAMAGE, ESPECIALLY FRAYING AROUND THE COVER OPENING. FRAYED

FIBERS FROM THE COVER COMBINED WITH OTHER SUBSTANCES SUCH AS DIRT,

GREASE AND FLUIDS CAN CAUSE OBSTRUCTION IN THE PROBE.

(a) Remove the covers from the pitot probes and tubes.

(b) Remove the "PITOT PROBES COVERED" tag from the left control wheel in the flight deck.

(c) Check for ice or snow in the pitot probes.

1 If necessary, apply warm air to melt the ice or snow.

(d) Do the steps that follow if it is necessary:

1 Replace the quick-opening drain valve assembly to the pitot and static drain tubes (

PAGEBLOCK 34-11-00/501 ).

2 Replace the drain plug to the pitot and static drain tubes. ( PAGEBLOCK 34-11-

00/501 ).

(e) Remove the tape or covers from the items that follow:

1 The temperature probes

2 The angle of attack sensors

3 The ice detector (when installed)

WARNING: FAILURE TO REMOVE BARRICADE TAPE AND VINYL ADHESIVE TAPE FROM THE STATIC

PORTS BEFORE FLIGHT MAY CAUSE LARGE ERRORS IN AIRSPEED-SENSING AND

ALTITUDE-SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF SAFE FLIGHT.

CAUTION: REMOVE ALL BARRICADE TAPE AND VINYL ADHESIVE TAPE. ENGINES SHOULD NOT BE

OPERATED WITH COVERINGS IN PLACE BECAUSE THE COVERS CAN COME OFF AND

DAMAGE THE ENGINES.

(f) Remove all barricade tape and vinyl adhesive tape from the static ports.

1 Inspect each static port and if necessary use naphtha or equivalent to remove all

tape residue, dirt and other contaminants around the port.

2 Check the static ports for ice or snow.

a If necessary, apply warm air to melt the ice or snow.

American Airlines

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For Reference Olny 
(g) Remove the "STATIC PORTS COVERED" tag from the left control wheel in the flight deck.

(h) Weigh the portable fire extinguishers.

1 If the weight has decreased below the specified weight on the bottle, remove the

extinguishers and fill them.

Effective on: (AAL 601-610, 612-615, 617-635, 639-643, 645-647, 649, 652-660, 662, 663, 665-672,

681-999 WITHOUT THE RAIN REPELLENT SYSTEM DEACTIVATED BY ECO F0431) 601-610, 612-615,

617-635, 639-643, 645-647, 649-649, 652-660, 662-663, 665-672, 681-999

(i) Install the pressurized rain repellent bottle ( PAGEBLOCK 12-16-01/301 ).

(j) Install the windshield wipers ( PAGEBLOCK 30-42-03/401 ).

(k) Make a check of the windshield wiper system ( PAGEBLOCK 30-42-00/501 , PAGEBLOCK 30-42-

00/601 ).

Effective on: AAL ALL

SUBTASK 632-038

(2) Make the Pitot-Static system serviceable.

(a) Drain all of the pitot and static systems ( PAGEBLOCK 34-11-00/301 ).

1 You can find the drain fittings in the areas that follow:

a In the nose wheel well,

b In the electronic equipment bay,

c In the aft cargo compartment.

(b) Flush the pitot static system ( PAGEBLOCK 34-11-00/301 ).

(c) Do the full range pitot-static system test ( PAGEBLOCK 34-11-00/501 ).

(d) Do a test of the Pitot-Static System Heaters ( PAGEBLOCK 30-31-00/501 ).

M. Air Conditioning System

Effective on: AAL ALL

SUBTASK 632-040

(1) Make the air conditioning system serviceable after Short and Long Term storage.

Effective on: (AAL 172-179, 181-199, 673-680) 172-179, 181-199, 673-680

(a) Examine the water separator bags to make sure they are clean (replace the bags if they are dirty)

( SUBJECT 21-00-00 ).

(b) Close the air conditioning mix bay.

Effective on: AAL ALL

SUBTASK 712-041

(2) Do an operational test of the air conditioning system. ( PAGEBLOCK 21-00-00/201 ).

American Airlines

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For Reference Olny 
N. Hydraulic Systems

Effective on: AAL ALL

SUBTASK 632-044

(1) Make the hydraulic system serviceable after a Short Term (0 - 60 days) storage.

(a) If lubricant was applied during the HYDRAULIC SYSTEM procedures for Short Term storage,

remove the lubricant.

WARNING: DO NOT GET SOLVENTS IN YOUR MOUTH, OR YOUR EYES, OR ON YOUR

SKIN. DO NOT BREATHE THE FUMES FROM SOLVENTS. SOLVENTS ARE

HAZARDOUS MATERIALS. REFER TO PRODUCT MATERIAL SAFETY DATA

SHEETS (MSDS) AND LOCAL REQUIREMENTS FOR PROPER HANDLING

PROCEDURES.

1 Remove the lubricant withB01000 Series 80 solvent (SOPM 20-30-80).

Effective on: AAL ALL

SUBTASK 632-045

(2) Make the hydraulic system serviceable after a Long Term (more than 60 days) storage ( PAGEBLOCK 29-00-

00/601 ).

NOTE: Do the following steps in addition to the servicing steps of the Short Term storage procedures.

(a) Do a check of all of the hydraulic system components to make sure they are serviceable.

1 Examine all hydraulic systems for leakage ( PAGEBLOCK 29-11-00/601 ).

(b) Remove the layer of lubricant that was applied to all bare finished surfaces during the Short Term

storage procedures.

WARNING: DO NOT GET SOLVENTS IN YOUR MOUTH, OR YOUR EYES, OR ON YOUR

SKIN. DO NOT BREATHE THE FUMES FROM SOLVENTS. SOLVENTS ARE

HAZARDOUS MATERIALS. REFER TO PRODUCT MATERIAL SAFETY DATA

SHEETS (MSDS) AND LOCAL REQUIREMENTS FOR PROPER HANDLING

PROCEDURES.

1 Remove the lubricant withB01001 Series 81 solvent (SOPM 20-30-81).

(c) Do the servicing of the hydraulic reservoirs ( PAGEBLOCK 12-12-01/301 ).

(d) Do the servicing of the parking brake accumulator ( PAGEBLOCK 12-15-04/301 ).

Effective on: AAL ALL

SUBTASK 860-001

(3) Close this circuit breaker:

Overhead Circuit Breaker Panel, P11

Row Col Number Name

D 27 C04216 RAT AUTO PWR

Effective on: AAL ALL

SUBTASK 712-046

(4) Do a test of the hydraulic systems that follow:

(a) The main (left, right and center) hydraulic systems ( PAGEBLOCK 29-11-00/201 ).

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For Reference Olny 
(b) The Ram Air Turbine (RAT) system ( PAGEBLOCK 29-21-00/501 ).

(c) The Hydraulic Fluid Quantity Indicating system ( PAGEBLOCK 29-33-00/501 ).

(d) The Hydraulic Pressure Indicating System ( PAGEBLOCK 29-31-00/501 ).

(e) The Hydraulic Fluid Temperature Indicating System ( PAGEBLOCK 29-32-00/501 .

(f) Power Transfer Unit System ( Operational Test - Power Transfer Unit (PTU) Auto Control and

Indicating System, TASK 29-22-00-710-801 , Operational Test - Power Transfer Unit (PTU)

Manual Ground Control System, TASK 29-22-00-710-802 and Operational Test - Flow Limiter

Valve for the Power Transfer Unit (PTU) System, TASK 29-22-00-710-803 ).

(g) Hydraulic Reservoir Pressure Indication System ( PAGEBLOCK 29-35-00/501 ).

Effective on: AAL ALL

SUBTASK 962-047

(5) Replace the hydraulic system filter elements that follow:

(a) The System L and R EDP Pressure/Case Drain Filter Elements( PAGEBLOCK 29-11-17/401 ).

(b) The Center System ACMP Pressure/Case Drain Filter Elements ( PAGEBLOCK 29-11-19/401 ).

(c) The System L and R Return Filter Elements ( PAGEBLOCK 29-11-15/401 ).

(d) The Center Return Filter Element ( PAGEBLOCK 29-11-13/401 ).

(e) The PTU Pressure Filter Element ( PAGEBLOCK 29-22-02/401 ).

(f) The PTU Case Drain Filter Element ( PAGEBLOCK 29-22-05/401 ).

O. Flight Controls

Effective on: AAL ALL

SUBTASK 632-049

(1) Make the flight control system serviceable after a Long Term (more than 30 days) storage.

(a) Make sure the cable tension loads are correct in all primary and secondary control systems (

PAGEBLOCK 27-00-01/201 ).

NOTE: The cable tension charts can be found in the applicable AMM section for the cable

system.

(b) Examine all of the cables you can see visually, and lubricate them ( PAGEBLOCK 20-10-03/401 ).

NOTE: When the last control cable lubrication was more than 30 days, examine the cables (

PAGEBLOCK 20-20-02/601 ). If it is necessary, replace the defective cables that you

find.

(c) Extend all of the flaps (both leading edge [ PAGEBLOCK 27-81-00/201 and trailing edge [

PAGEBLOCK 27-51-00/201 ]) and the spoilers, and examine them for corrosion.

(d) Lubricate all of the flap tracks ( PAGEBLOCK 12-21-09/301 ).

Effective on: AAL ALL

SUBTASK 712-050

(2) Do an operational test of the primary and secondary control systems that follow:

American Airlines

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For Reference Olny 
(a) The Control System Electronics Unit (CSEU) ( PAGEBLOCK 27-09-00/201 ).

(b) The Aileron and Aileron Trim Control System ( PAGEBLOCK 27-11-00/501 ).

(c) The Aileron Position Indicating System ( PAGEBLOCK 27-18-00/501 ).

(d) The Rudder and Rudder Trim Control System ( PAGEBLOCK 27-21-00/501 Config 1 .

(e) The Rudder and Elevator Hydraulic Supply Shutoff ( PAGEBLOCK 27-23-00/501 ).

(f) The Rudder Position Indicating System ( PAGEBLOCK 27-28-00/501 ).

(g) The Elevator Control System ( PAGEBLOCK 27-31-00/501 ).

(h) The Stall Warning System ( PAGEBLOCK 27-32-00/501 Config 5 ).

(i) The Elevator Position Indicating System ( PAGEBLOCK 27-38-00/501 ).

(j) The Horizontal Stabilizer Trim Control System ( PAGEBLOCK 27-41-00/501 ).

(k) The Stabilizer Trim Indicating System ( PAGEBLOCK 27-48-00/501 ).

(l) The Trailing Edge Flap System ( PAGEBLOCK 27-51-00/501 ).

(m) The Trailing Edge Flap Position Indicating System ( PAGEBLOCK 27-58-00/501 ).

(n) The Spoiler/Speedbrake Control System ( PAGEBLOCK 27-61-00/501 ).

(o) The Auto-Speed Brake Control System ( PAGEBLOCK 27-62-00/501 or PAGEBLOCK 27-62-00/501

 Config 1 ).

(p) The Leading Edge Slat System ( PAGEBLOCK 27-81-00/501 ).

(q) The Leading Edge Slat Position Indicating System ( PAGEBLOCK 27-88-00/501 ).

P. Equipment/Furnishings

Effective on: AAL ALL

SUBTASK 612-051

(1) Do the servicing of the toilet tanks and the flush systems ( PAGEBLOCK 12-17-01/301 Config 5 ).

Effective on: AAL ALL

SUBTASK 632-053

(2) Remove the covers from the main entry and service door windows.

Effective on: AAL ALL

SUBTASK 792-054

(3) Make a check of the galley and lavatory plumbing and drains.

(a) Look for airlocks and leakage.

Effective on: AAL ALL

SUBTASK 212-057

(4) Weigh the engine fire extinguishers and the portable fire extinguishers just before returning the airplane to

service ( PAGEBLOCK 26-21-01/401 , PAGEBLOCK 26-26-01/201 , PAGEBLOCK 26-26-02/201 ).

American Airlines

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For Reference Olny 
NOTE: If the weight has decreased below the specified weight on the nameplate, replace the extinguishers.

Effective on: AAL ALL

SUBTASK 212-058

(5) Make sure the pressure of the escape slide bottle is at the specified level ( PAGEBLOCK 52-11-30/601 ).

Effective on: AAL ALL

SUBTASK 212-059

(6) Make sure that all of the escape slides are armed ( PAGEBLOCK 52-11-00/201 ).

Effective on: AAL ALL

SUBTASK 422-060

(7) Install the attendants' flashlights.

Effective on: AAL ALL

SUBTASK 632-055

(8) Remove the dust covers (when installed) from the seats.

Effective on: AAL ALL

SUBTASK 212-087

(9) Examine the upholstery, carpet, and tapestries for moisture and mildew, if applicable ( PAGEBLOCK 25-00-

00/701 ).

(a) If you find moisture or mildew, correct it when it is necessary.

Effective on: AAL ALL

SUBTASK 412-061

(10) Install the seats and carpets that were removed in the EQUIPMENT/FURNISHING procedures for Long Term

storage.

Q. Oxygen System

Effective on: AAL ALL

SUBTASK 612-062

WARNING: OBEY THE PRECAUTIONS IN PAGEBLOCK 12-15-08/301 WHEN YOU REMOVE AND INSTALL OXYGEN

CYLINDERS. IF YOU DO NOT OBEY THE PRECAUTIONS, INJURY TO PERSONS OR DAMAGE TO

EQUIPMENT CAN OCCUR.

(1) To make sure the oxygen system is serviceable, do the steps that follow ( PAGEBLOCK 35-11-00/201 ):

(a) Make a visual check of the oxygen system and look for signs of corrosion.

1 If you find corrosion, remove it.

(b) Flush the crew oxygen system plumbing with dry nitrogen or clean air.

(c) Prepare to install the portable oxygen bottle and crew oxygen bottle as follows:

1 Remove the red flags from the polyethylene bags.

2 Remove the polyethylene bags from the lines and hoses that have the caps.

3 Remove the cap from the connector end of the hoses that are in the stowage boxes

American Airlines

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For Reference Olny 
for the oxygen masks.

4 Remove the cap from the cylinder end of the oxygen distribution lines.

(d) Install the oxygen bottles (this includes the regulator).

(e) Open the high pressure valves on the oxygen supply cylinders.

(f) Install the oxygen masks for the crew oxygen system.

NOTE: If the crew oxygen masks were in storage for more than 90 days, they must be

examined. Look for deterioration of the rubber and plastic parts.

1 Make sure the oxygen masks operate correctly.

(g) Make sure the passenger oxygen system operates correctly.

(h) Make sure the drop system for the passengers oxygen masks operates correctly.

R. Potable Water System

Effective on: AAL ALL

SUBTASK 612-063

(1) To make sure the potable water system is serviceable, do the steps that follow

( PAGEBLOCK 38-10-00/201 ):

(a) Remove the plugs and seals from all of the drains.

(b) Do the disinfectant procedure to the potable water system.

( PAGEBLOCK 12-14-01/301 Config 1 )

(c) Install new filters in the potable water system.

( PAGEBLOCK 12-14-01/301 Config 1 )

(d) Do the servicing of the water tanks

( PAGEBLOCK 12-14-01/301 Config 1 )

(e) Install the coffeemakers.

(f) Install the water boilers.

S. Cargo Compartment Fire Extinguisher System

Effective on: AAL ALL

SUBTASK 612-064

(1) To make sure the fire extinguisher system for the cargo compartment is serviceable, do the steps

that follow

( PAGEBLOCK 26-23-00/501 )

(a) Make sure the fire extinguisher bottles are pressurized to the specified pressure.

(b) Examine the fire extinguisher bottles as follows:

1 Make sure the test dates for the fire extinguisher bottle life, have not

expired.

2 Make sure the test dates of the discharge squibs are not expired.

American Airlines

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T. Power Plant

Effective on: AAL ALL

SUBTASK 612-065

(1) Make sure the power plants are serviceable ( PAGEBLOCK 71-00-00/201 ).

U. APU

Effective on: AAL ALL

SUBTASK 612-066

(1) Make sure the APU is serviceable ( PAGEBLOCK 49-11-00/201 ).

V. Compass

Effective on: AAL ALL

SUBTASK 822-085

(1) If the airplane has been parked for over one year on the same heading perform a compass swing (

PAGEBLOCK 34-23-00/201 ).

American Airlines

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AIRCRAFT MAINTENANCE MANUAL

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For Reference Olny