011B50Weight BalanceJointService20110930.pdf

NAVAIR 01-1B-50

USAF TO 1-1B-50

USCG TO 1-1B-50

ARMY TM 55-1500-342-23

JOINT SERVICE TECHNICAL MANUAL

AIRCRAFT WEIGHT AND BALANCE

SUPERSEDURE NOTICE. This manual supersedes NAVAIR 01-1B-50 dated 15 August 2003, USAF TO 01-1B-50 dated 1 April 2008, USCG TO 01-1B-50 dated 1 April 2008, and ARMY TM 55-1500-342-23 dated 29 August 1986. Destroy previously issued version of this manual to prevent disclosure of contents or reconstruction of the document.

DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited.

DESTRUCTION NOTICE. For unclassified, limited documents, destroy by any method that will prevent disclosure of contents or reconstruction of the document.

PUBLISHED BY DIRECTION OF COMMANDER, NAVAL AIR SYSTEMS COMMAND

30 SEPTEMBER 20110801LP1119776

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LIST OF EFFECTIVE PAGES

Dates of issue for original and changed pages are:

Original ........................ 0 ...............30 September 2011 hange............................x ......................... xx XXX 199X

Insert latest changed pages; dispose of superseded pages in accordance with applicable regulations.

NOTE: On a changed page, the portion of the text affected by the latest change is indicated be a vertical line, or other change symbol in the outer margin of the page. Change in illustrations are indicated by miniature pointing hands. Changes to wiring diagrams are indicated by shaded areas.

Total number of pages in this manual is 126, consisting of the following:

A Change X

*Zero in this column indicates an original page.

Title A i-ii

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LIST OF ILLUSTRATIONS .......................................... ii

LIST OF TECHNICAL PUBLICATIONS

DEFICIENCY REPORTS (TPDR)

INCORPORATED ................................TPDR-1

1 INTRODUCTION

1-1. Purpose ............................................1-1 1-2. Scope ................................................1-1 1-3. Terminology .......................................1-1 1-4. Reasons for Weight and Balance

Control ............................................1-2

2 AIRCRAFT WEIGHT AND BALANCE

PRINCIPLES

2-1. Aircraft Weight Principles ..................2-1 2-2. Aircraft Balance Principles ................2-3 2-3. Calculating Aircraft Center of Gravity

(CG) ...............................................2-3

2-4. Fuselage Station ...............................2-4 2-5. Percent Mean Aerodynamic Chord

(% MAC) ........................................2-5

2-6. Loading / Unloading ..........................2-5 2-7. Ballast ...............................................2-5

3 WEIGHT AND BALANCE SYSTEM

3-1. General .............................................3-1 3-2. Manufacturer Responsibilities ...........3-1 3-3. Commercial Maintenance

Responsibilities ..............................3-1 3-4. Depot / Intermediate Level

Maintenance Responsibilities .........3-1 3-5. Aircraft Custodian/Technician/Type

Commander Responsibilities .........3-1 3-6. Aircraft Weight and Balance

Classifications ................................3-1 3-7. Weight and Balance Handbooks ......3-2 3-8. Weight and Balance Flight

Clearance .......................................3-4 3-9. Aircraft Weighing Requirements .......3-5

4 INSTRUCTIONS FOR THE USE OF WEIGHT

AND BALANCE CHARTS AND FORMS

4-1. DD Form 365 – Record of Weight and Balance Personnel .........................4-1

4-2. DD Form 365-1 – Chart A – Basic Weight Checklist Record ................4-1

4-3. DD Form 365-2 – Form B – Aircraft Weighing Record ............................4-4

4-4. DD Form 365-3 – Chart C – Basic Weight and Balance Record...........4-5

4-5. Chart E – Aircraft Loading Manual / Weighing Instructions .....................4-7

4-6. DD Form 365-4 – Form F – Weight and Balance Flight Clearance Form F ..........................4-7

5 WEIGHING AIRCRAFT

5-1. General .............................................5-1 5-2. Weighing Equipment .........................5-1 5-3. Weighing Accessories ......................5-3 5-4. Weighing Procedures .......................5-5 5-5. Verification of Weighing Results ..... 5-11

6 WEIGHT AND BALANCE TOOLS

6-1. Automated Weight and Balance

System (AWBS) .............................6-1 6-2. Distribution of AWBS ........................6-1 6-3. Alternate Weight and

Balance Tools .................................6-1

7 CENTER OF GRAVITY LOADING

CALCULATIONS

7-1. General .............................................7-1 7-2. Principles of Moments ......................7-2 7-3. Effects of Moments on Aircraft ..........7-3 7-4. Determination of Balance Condition

(Location of Aircraft CG) ...............7-3 7-5. Effects of Unbalanced Loading .........7-3 7-6. Determining Center of Gravity for a

Group of Items ...............................7-3 7-7. Center of Gravity Limits ....................7-4 7-8. Expressing Center of Gravity ............7-4 7-9. Lateral and Vertical Center of

Gravity ............................................7-5 7-10. Most Forward and Most Aft CG

Calculations ....................................7-5 7-11. Sample ..............................................7-7 7-12. Chart E Loading Data .....................7-10

8 SERVICE SPECIFIC REQUIREMENTS

8-1. US Army Requirements ....................8-1 8-2. US Navy / US Marine Corps

Requirements ...............................8-11

TABLE OF CONTENTS

Section Page Section Page ii

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Figure Title Page Figure Title Page

LIST OF ILLUSTRATIONS

2-1. Weight Terminology ........................................2-2 2-2. Calculating Aircraft CG ...................................2-3 2-3. Balance Arm Fuselage Station .......................2-4 2-4. Percent MAC Example ...................................2-5

5-1. Typical Platform Scale Assembly ....................5-1 5-2. Electronic Weighing Kit (Typical) .....................5-2 5-3. Reading a Hydrometer ....................................5-4 5-4. Accessory Weighing Kit ..................................5-4 5-5. Estimation of “As Weighed” Weight .................5-7 5-6. Leveling Lugs Inside the Aircraft .....................5-8 5-7. Leveling Lugs Outside the Aircraft ..................5-8 5-8. Plumb Bob ......................................................5-9

6-1. Load Adjuster ..................................................6-3

7-1. Asymmetric Configurations .............................7-1 7-2. Aircraft Balance Point .....................................7-2 7-3. Locating Aircraft Center of Gravity ..................7-3

8-1. Aircraft Modification Example .........................8-9

B-1. Sample DD Form 365 Record of Weight and Balance Personnel .................. B-1

B-2. Sample DD Form 365-1 Chart A – Basic Weight Checklist Record .................. B-2

B-3. Sample DD Form 365-2 Form B – Aircraft Weighing Record ........................... B-3

B-4. Sample DD Form 365-3 Chart C – Basic Weight and Balance Record ............. B-5

B-5. Sample DD Form 365-4 Weight and Balance Flight Clearance Form F - Transport .................................................... B-6

B-6. Sample DD Form 365-4 Weight and Balance Flight Clearance Form F - Tactical ....................................................... B-7

8-3. US Air Force Requirements ............8-24 8-4. US Coast Guard Requirements ......8-35

8-4.1. Related References ..........8-35 8-4.2. Weight and Balance

Control ..............................8-35 8-4.3. Responsibilities .................8-36 8-4.4. Personnel Qualification

Requirements ...................8-36 8-4.5. Forms and Records

Disposition ........................8-36 8-4.6. Aircraft Classifications .......8-36 8-4.7. Form F ...............................8-36 8-4.8. Aircraft Weighings .............8-37 8-4.9. Transfer / Acceptance

Inventory ...........................8-38 8-4.10. Scales ...............................8-38 8-4.11. Unmanned Aerial Vehicles

(UAV’s) ............................8-38

8-4.12. Weight and Balance Guidance for Aircraft Modifications .....................8-38

8-4.13. Contact Information ...........8-38 8-4.14. Corrections to this

Manual ..............................8-38 8-4.15. Distribution of AWBS ........8-38

APPENDIX A. TERMINOLOGY AND

DEFINITIONS .......................................... A-1

APPENDIX B. SAMPLE CHARTS AND FORMS .... B-1

APPENDIX C. ACRONYMS .................................... C-1

APPENDIX D. SCALE CORRECTION FACTORS

(LATITUDE AND ALTITUDE) .................. D-1

Table Title Page Table Title Page

LIST OF TABLES

3-1. Aircraft Classifications ....................................3-2 3-2. Major Modifications or Repairs Guidelines .....3-6 iii

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Report Control Number (RCN) Location alskjalkj 0000/00000 Pg x-xx

0000/00000 Pg x-xx alskjalkj 0000/00000 Pg x-xx alskjalkj 0000/00000 Pg x-xx alskjalkj 0000/00000 Pg x-xx alskjalkj 0000/00000 Pg x-xx alskjalkj 0000/00000 Pg x-xx alskjalkj 0000/00000 Pg x-xx alskjalkj 0000/00000 Pg x-xx

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LIST OF TECHNICAL PUBLICATIONS DEFICIENCY REPORTS INCORPORATED

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Section 1 - Introduction

1-1. PURPOSE

This manual outlines and defines the requirements, procedures, and responsibilities for weight and balance control of military aircraft. This manual also provides information and instructions for maintaining the charts and forms (DD Form 365 series or electronic equivalent) that provide the means for maintaining continuous record and control of aircraft weight and balance. Information and explanation of principles, terms, and definitions are presented to provide weight and balance personnel with a general information manual pertinent to their particular function.

1-2. SCOPE

The use of this manual is mandatory for all weight and balance tasks that operate and/or maintain United States military aircraft (including fixed-wing aircraft, rotary-wing aircraft and select unmanned air vehicles).

See Section 8 (Service Specific Requirements) for additional information concerning select unmanned air vehicles. Sufficient explanation of principles, definitions, procedures and data are given to provide weight and balance personnel with a general information manual pertinent to their particular function. Also included is a complete description of related equipment and instructions for its use and operation. The general requirements and procedures of this manual are applicable to weight and balance control of all military aircraft. Additional requirements, procedures, and/or instructions for specific aircraft weight and balance control are specified in the aircraft specific manuals. See Section 8 (Service Specific Requirements) for additional reference documents.

1-3. TERMINOLOGY

1-3.1. Usage of the words "shall", "should", and "may" is in accordance with the following:

1-3.2. The word "shall," is used to indicate the requirements, procedures, and/or responsibilities are mandatory.

1-3.3. The word "should" is used to indicate a non-mandatory but highly recommended method of accomplishment.

1-3.4. The word "may" is used to indicate an acceptable or suggested means of accomplishment.

1-3.5. Weight and balance definitions are found in Appendix A.

1-3.6. WARNINGS, CAUTIONS, AND NOTES DEFINED. Warnings, cautions, and notes are used to emphasize important and critical instructions and are used for the following conditions:

1-3.6.1. WARNING: An operating procedure, practice, etc, which if not correctly followed, could result in personal injury or loss of life.

1-3.6.2. CAUTION: An operating procedure, practice, etc, which, if not strictly observed, could result in damage to or destruction of equipment.

1-3.6.3. NOTE: An operating procedure or condition that must be emphasized.

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1-4. REASONS FOR WEIGHT AND BALANCE CONTROL

Flight characteristics of aircraft are directly dependent upon conditions of weight and balance. Gross Weight and center of gravity (CG) have a bearing on performance, stability, and control of the aircraft. For example, cargo placed too far aft in an already critically loaded aircraft could move the center of gravity out of the permissible balance limits. This could cause the pilot to lose control of the aircraft. Hazardous flight conditions and accidents resulting from these conditions can be prevented by adherence to the principles of weight and balance set forth in this manual. An aircraft whose weight is greater than its allowable maximum Gross Weight, or whose Center of Gravity (CG) is located outside its prescribed CG limits, may experience one or more of the following unsatisfactory flight characteristics, performance degradations or payload reduction:

• Longitudinal instability

• Lateral instability

• Increase in takeoff distance and/or required power setting or torque

• Increase in takeoff speed

• Increase in landing ground run

• Increase in control forces

• Increase in stall speeds

• Decrease in range and/or allowable payload

• Decrease in rate of climb

• Decrease in service ceiling

• Decrease in structural safety factors

• Decreased hover performance

• Decreased cruising speed

• Decreased maneuverability

Using the principles and following the instructions contained in this manual can prevent these flight conditions and potential associated mishaps.

1-5. COMMENTS – See Section 8 (Service Specific Requirements) for Points of Contact for each service.

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Section 2 – Aircraft Weight and Balance Principles

2-1. AIRCRAFT WEIGHT PRINCIPLES

One of the basic elements of aircraft design is weight. The weight of an aircraft is used in determining such design criteria as engine requirements, wing area, landing gear requirements, and payload capacity. Any weight changes, whether in manufacturing, modification, or maintenance, can have distinct effects on aircraft performance and/or payload capability.

2-1.1. WEIGHT TERMINOLOGY. Figure 2-1 illustrates the definition of, and relationships between, aircraft weight terminology. For related definitions, see Appendix A.

2-1.2. WEIGHT LIMITS. All aircraft are designed with a number of weight limits. These limits are determined by a combination of performance, control, and structural restrictions. Exceeding these limits can result in loss of aircraft and are expressly forbidden.

2-1.3. AIRCRAFT WEIGHT. The weight of an aircraft is determined through a combination of actual weighing, accurate record keeping, and proper use of the aircraft specific manuals, charts, forms, and loading manuals.

2-1.4. FLOOR LOADING. Floor loading is the weight, in pounds, of a load divided by the area of floor on which the load rests. These limits shall never be exceeded.

2-1.4.1. For example, the floor loading for a 100-pound container is determined as follows:

Base of container = 20 inches x 20 inches = 400 square inches

Floor loading = 100 pounds 400 square inches

= 0.25 pounds per square inch or

0.25 pounds per square inch x 144 square inches per square foot = 36 pounds per square foot

Floor loading limits or a plan view of the cargo floor showing variations in floor strength and weight concentration limitations for various compartments are specified in the applicable operator's manual.

NOTE

1 square foot = 144 square inches

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WEIGHT EMPTY

Unusable fuel, engine oil, permanent ballast, oxygen, and all non mission-specific internal or external equipment onboard the aircraft and will not be disposed of during the flight and is not listed in the Chart E.

BASIC WEIGHT

Crew, crew baggage, steward equipment, emergency equipment, special mission fixed equipment, and all other non-expendable items (such as fixed pylons and racks) not in Basic

Weight.

OPERATING WEIGHT

Payload items; such as cargo, ammunition, passengers, stores, droppable fuel tanks, and transfer fuel.

ZERO FUEL WEIGHT

Usable Fuel

RAMP WEIGHT

Taxi Fuel

TAKE-OFF GROSS WEIGHT

Load items that may or may not be expended in flight; such as fuel, stores, ammunition, cargo and paratroops.

LANDING GROSS WEIGHT

Figure 2-1 – Weight Terminology

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2-2. AIRCRAFT BALANCE PRINCIPLES

An aircraft is said to be in balance, or balanced, when all weight items in, on, or of the aircraft are distributed so that the Center of Gravity (CG) of the aircraft lies within pre-determined allowable CG limits. These limits are defined by the most forward and aft permissible CG locations and are called the forward and aft CG limits, respectively. To determine if an aircraft is balanced, the aircraft CG shall be calculated and compared to the forward and aft CG limits for that particular configuration and Gross Weight. This can be calculated for not only longitudinal but the lateral and vertical conditions as well, although few aircraft track lateral or vertical CG. Refer to aircraft specific manuals in these cases.

2-2.1. TERMINOLOGY. The terms balance, arm, balance arm, moment, simplified moment, load adjuster index, and CG are fundamental to understanding aircraft balance and control. These, and other terms used in this section, are defined in Appendix A.

2-3. CALCULATING AIRCRAFT CENTER OF GRAVITY (CG)

The CG of a loaded aircraft can be calculated when the weights and moment arms of the items which make up the aircraft Gross Weight are known. (See Figure 2-2) This can be done by using moments. The relationship between weight, arm and moment is as follows:

WEIGHT × ARM = MOMENT

2-3.1. It is important to note that arms may not be added or subtracted when calculating CG. CG is calculated by taking the summation of total moments divided by the summation of total weights.

Weights can be added and subtracted and moments can be added and subtracted but arms cannot be added and subtracted.

Figure 2-2 – Calculating Aircraft CG

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2-4. FUSELAGE STATION

Fuselage Station (FS) is frequently synonymous to the balance arm scale. However, if the aircraft fuselage is shortened or lengthened, the original fuselage sections usually retain their old FS designations but will have different balance arms. This alters the FS–balance arm relationship (See Figure 2-3). The balance arm is what is used in the moment calculation formula. A fuselage plug can result in items being located ahead of the reference datum, leading to negative balance arms, as in Figure 2-3.

Balance calculations shall be made using balance arms; not FS locations.

Use only balance arms. For those aircraft whose fuselage station differs from its balance arm, the aircraft-specific loading manual will provide a conversion table and further details.

Figure 2-3 – Balance Arm Fuselage Station

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2-5. PERCENT MEAN AERODYNAMIC CHORD (% MAC)

In fixed-wing aircraft, the location of the aircraft CG is commonly expressed by %MAC instead of by its balance arm. %MAC identifies a location with respect to the position of the MAC. 0.0 %MAC is at the leading edge of the wing and runs along the MAC to 100.0% at the trailing edge. For definitions, see Appendix A. For weight and balance purposes, %MAC is found by a simple mathematical conversion equation or tables, particular to the aircraft, and listed in the aircraft-specific loading manual. (See Figure 2-4)

Figure 2-4 – Percent MAC Example

2-6. LOADING / UNLOADING

The loading or unloading of items can have a considerable effect on aircraft balance, even when the items total less than one tenth of one percent of the aircraft weight. Balance loading principles and the techniques for determining the CG for various aircraft configurations are discussed in Section 7 (Center of Gravity Loading Calculations).

2-7. BALLAST

Sometimes design, manufacturing, or maintenance changes cause the aircraft CG to exceed its limits. This is usually corrected by the addition of permanent ballast which is required to be installed in the aircraft before flight. When ballast is added to counter the temporary removal of an item or to balance a particular configuration, it is called temporary ballast. For a definition of ballast, see Appendix A. An equation for use in determining the amount of temporary ballast is included in Section 7 (Center of Gravity Loading Calculations).

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Section 3 – Weight and Balance System

3-1. GENERAL

This section defines the requirements, procedures and Command responsibilities relative to the US Military aircraft weight and balance control system. The overall objectives of the system are to provide current and correct information regarding aircraft Basic Weight and moment, and to maintain aircraft Gross Weight and center of gravity within permissible limits in order to ensure safety of flight. This is done to ensure safety of flight. All commands are responsible to assure that all personnel assigned weight and balance responsibility on US Military aircraft are qualified in accordance with service specific requirements in Section 8 (Service Specific Requirements).

3-2. MANUFACTURER RESPONSIBILITIES

The aircraft manufacturer inserts all identifying aircraft data on the title page of the Weight and Balance Handbook and completes all other applicable charts and forms prior to delivery of the aircraft.

The aircraft manufacturer or commercial modification facility shall maintain and update the aircraft Weight and Balance Handbook in accordance with this manual. Any associated electronic records in the AWBS or equivalent shall be updated as well prior to delivery or return to service.

3-3. COMMERCIAL MAINTENANCE RESPONSIBILITIES

Commercial activities involved in the weight and balance control of US Military aircraft shall comply with requirements of this manual.

3-4. DEPOT / INTERMEDIATE LEVEL MAINTENANCE RESPONSIBILITIES

Depot / Intermediate level maintenance facilities shall update individual aircraft Weight and Balance records and weigh aircraft as required in accordance with the requirements of this manual and other applicable service specific documents (See Section 8 – Service Specific Requirements). These facilities shall ensure that a dedicated staff of qualified personnel are available to accomplish the required tasks and shall designate the Lead Weight and Balance Specialist responsible.

3-5. AIRCRAFT CUSTODIAN/TECHNICIAN/TYPE COMMANDER RESPONSIBILITIES

Refer to Section 8 (Service Specific Requirements) for additional clarification of responsibilities.

3-6. AIRCRAFT WEIGHT AND BALANCE CLASSIFICATIONS

For weight and balance control purposes, US Military aircraft are divided into the following classifications:

3-6.1. CLASS 1A. Class 1A aircraft are those with published weight and CG limits that cannot be exceeded by normally employed loading arrangements and therefore need no loading control.

3-6.2. CLASS 1B. Class 1B aircraft are those with published weight and CG limits that can be exceeded by normally employed loading arrangements and therefore need loading control.

3-6.3. CLASS 2. Class 2 aircraft are those with published weight and CG limits that can readily be exceeded by normally employed loading arrangements and therefore need a higher degree of loading control.

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3-6.4. Table of Aircraft Classifications:

Class 1A Class 1B Class 2

USAF X X

US Army X X US Navy/Marines X

USCG X

Table 3-1 Aircraft Classifications

Service-unique requirements for UAVs are addressed in Section 8 (Service Specific Requirements).

3-7. WEIGHT AND BALANCE HANDBOOKS

An aircraft weight and balance handbook provides for the continuous record of the weight and balance data for a particular aircraft. A separate handbook shall be produced and maintained for each aircraft.

A weight and balance handbook is required for all active aircraft. Inactive aircraft (flyable temporary storage, static display, ground training) do not require weight and balance handbooks. If these inactive aircraft become active, the weight and balance handbook shall be updated with an actual weighing prior to first flight. If the weight and balance handbook is not available, one shall be initiated in accordance with paragraph 3-7.4.

3-7.1. HANDBOOK LOCATION. Weight and balance handbooks shall be stored as determined by the aircraft custodians/technicians, but always in a location readily available to the pilot and other personnel responsible for accomplishing weight and balance functions.

For some aircraft it may be possible to have a completely electronic Weight and Balance handbook if authorized or required for a particular aircraft platform or by the appropriate governing authorities for each service.

However, a current backup shall be maintained at all times to prevent loss of data.

3-7.2. HANDBOOKS CONTENT. The weight and balance handbook shall be maintained for each assigned active aircraft by qualified weight and balance personnel. The handbook charts, forms and records shall be maintained in accordance with requirements and instructions of this manual. The contents of the weight and balance handbook shall include:

3-7.2.1. For paper records, a hard plastic cover or notebook style binder with cover page, containing the aircraft type and serial number shall be used.

3-7.2.2. DD Form 365, Record of Weight and Balance Personnel.

3-7.2.3. DD Form 365-1, Chart A – Basic Weight Checklist Record.

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3-7.2.4. DD Form 365-2, Form B – Aircraft Weighing Record.

3-7.2.5. DD Form 365-3, Chart C – Basic Weight and Balance Record.

3-7.2.6. Chart E - Loading Data for applicable aircraft. (See Section 8 – Service Specific Requirements)

3-7.2.7. Required copies of DD Form 365-4, Weight and Balance Flight Clearance Form F, except Class

1A aircraft.

3-7.2.8. ELECTRONIC MEDIA. When an aircraft is transferred, the transferring activity shall ensure an

AWBS data file (or equivalent) for that serial number aircraft in a suitable approved electronic format is included with the weight and balance handbook records transferred with the aircraft.

3-7.2.8.1. The electronic weight and balance file shall be backed up in accordance with standard service computing requirements. The data file shall be backed up in a location other than that of primary storage.

3-7.3. HANDBOOK SECURITY CLASSIFICATION. Aircraft weight and balance handbooks shall be classified in accordance with the highest security classification of the data contained therein.

Contact local or program security officers for additional requirements.

3-7.4. HANDBOOK INITIATION OR REPLACEMENT. In the event an aircraft weight and balance handbook or pages become lost, damaged, or for any reason need to be initiated or replaced, the individual assigned responsibility for that aircraft weight and balance handbook shall assemble a new handbook as follows:

3-7.4.1. Obtain a new hard plastic cover page or create new handbook cover page using blank binder cover page or suitable equivalent that includes the aircraft type and serial number.

3-7.4.2. Complete a new Record of Weight and Balance Personnel.

3-7.4.3. Create or obtain a new Chart A using an applicable existing Chart A or obtain a copy from the

Service Engineering Organization.

3-7.4.4. Inventory the aircraft in accordance with instructions in Section 4 (Instructions for the use of

Weight and Balance Charts and Forms).

3-7.4.5. Weigh the aircraft by an authorized source. Sources other than an authorized weighing facility shall be approved by the Service Engineering Organization. Record the results of the weighing on a Form B.

3-7.4.6. Create a new Chart C and begin it with an initial entry reflecting the newly created Form B.

Include a note identifying the reason for assembling a new handbook in the Chart C.

3-7.4.7. Copy an applicable aircraft Chart E from the handbook of another aircraft of the same TMS/MDS or obtain a copy from the Service Engineering Organization. (See Section 8 – Service Specific Requirements)

3-7.4.8. Obtain and prepare required Forms F.

3-7.4.9. Create a backup of the AWBS data file (or equivalent) that contains the handbook data, once established and up-to-date.

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If sufficient data is available to accurately reflect the aircraft's lost or damaged weight and balance data pages, as in the case of worn or water damaged pages, accomplish items 3-7.4.1 through 3-7.4.9 above as deemed necessary by the weight and balance authority. This may require obtaining a recent Chart A and Form B from the last weighing and making all applicable changes to the Chart C via a complete inventory and verification of all modifications (TCTO/MWO/TD) made since the last weighing. This is only possible if changes since the last weighing are known with full confidence.

AWBS electronic data (or equivalent) can also be used to create a replacement copy of the lost paper aircraft handbook.

3-7.4.10. AUTHORIZED SUBSTITUTE FORMS. Copies of charts and forms from the Automated Weight and Balance System (AWBS) may be used in lieu of the DD Form 365 paper charts, forms, and records. Data sheets from the AWBS Form F generator or other approved Automated Form F generator may be used in lieu of DD Form 365-4. Approval for all other Automated Form F generators shall be obtained from the Service Engineering Organization. (See Section 8 - Service Specific Requirements).

3-7.5. ENTRY ERRORS ON FORMS. If errors are found on the forms in the weight and balance handbooks, do not erase or change the entry. With paper forms, line out the erroneous entry and correct the entry. Make a note in the Chart C pertaining to the correction. When using electronic forms, simply add a note in the Chart C to explain the correction.

3-7.6. SUPPLY OF FORMS. Forms prescribed in this manual may be requisitioned through normal distribution channels or copied from the examples in Appendix B, or printed from AWBS.

3-7.7. CHARTS / FORMS / RECORDS DISPOSITION. Charts, Forms and Records shall be maintained in accordance with Section 8 – Service Specific Requirements.

3-8. WEIGHT AND BALANCE FLIGHT CLEARANCE

Weight and balance flight clearance is accomplished to ensure that aircraft remain within safe weight and balance limits during takeoff, flight, and landing. Such clearance is recorded through the use of the Weight and Balance Flight Clearance Form F, or through an authorized electronic substitute. The original copy of the Form F, when properly signed and filed in accordance with applicable procedures stated in this manual and other service directives (See Section 8 – Service Specific Requirements) serves as the record to certify that weight and balance flight clearance was properly accomplished.

3-8.1. REQUIRED CLEARANCE. Weight and balance flight clearance is required for Class 1B and Class 2 aircraft.

3-8.2. FORM F MAINTENANCE PROCEDURES. All Forms F shall be completed in accordance with the instructions of this technical manual. Forms F are utilized on a ONE TIME USE basis, or are CANNED for multiple uses.

3-8.3. ONE TIME USE FORM F. These are Forms F prepared for use on a one time basis and are kept on file for 90 days upon mission completion or in accordance with command procedures. They are used when the Command does not utilize a CANNED Form F approach or when an aircraft is loaded in a manner for which no CANNED Form F is on file or applicable.

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3-8.4. CANNED FORM F. These are Forms F prepared for “repetitive use” when an aircraft's Basic Weight and moment remain within certain specified tolerances as defined by appropriate service engineering organization (See Section 8 - Service Specific Requirements). They are filed in accordance with established Command procedures for future reference and use. CANNED Forms F shall be checked at least every 180 days for accuracy and a new Form F prepared as required. (See Section 8 - Service Specific Requirements) If no changes are required, the Form F may be re-dated and initialed, or a letter issued to state the review has been accomplished to certify its currency.

3-8.5. CLEARANCE PROCEDURE. When filing DD Form 175, Military Flight Plan (or authorized substitute), the basis for weight and balance flight clearance shall be noted. For ONE TIME USE Forms F, attach the original form to the flight plan, retain a copy with the aircraft until flight termination, and retain a copy in the weight and balance handbook with the aircraft custodian/technician for 90 days upon mission completion or in accordance with command procedures. For CANNED Forms F, retain the forms in the weight and balance handbooks until superseded.

3-8.6. AUTHORIZED SUBSTITUTIONS FOR DD FORM 365-4. The following substitutes are authorized for use as weight and balance clearance records in lieu of DD Form 365-4.

3-8.6.1. Computer output sheets when the data recorded is identical to that required on the DD Form

365-4.

3-8.6.2. The designated commercial type loading schedule for C-9 and C-40 aircraft.

3-8.6.3. Other Commercial loading schedules approved by the appropriate Service Engineering

Organization listed in Section 8 - Service Specific Requirements.

3-8.6.4. Computer programs that replicate the DD Form 365-4 forms shall follow the requirements in

Section 6-3.1 of this Technical Manual.

3-9. AIRCRAFT WEIGHING REQUIREMENTS

Aircraft shall be weighed when any of the following conditions exist:

3-9.1. As required by pertinent service directives or technical directives.

3-9.2. When weighing requirements are specified in the applicable aircraft loading/operators manual.

3-9.3. After completion of overhaul as defined by appropriate engineering service.

Overhaul or major airframe repairs to include the replacement of major structural members such as spars, wings, tail booms, etc.

3-9.4. When major modifications or repairs are made.

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The weight and balance technician/custodian or appropriate engineering authority shall determine when an aircraft has undergone a “major modification or repair”. As a guideline, a major modification or repair is one that affects the Basic Weight to an extent that exceeds the thresholds as reflected in Table 3-2 below.

When one or more modifications (minor or major) are subsequently made to an aircraft since last actual weighing that cumulatively affect Basic Weight by thresholds that meet or exceed Table 3-2 criteria, a weighing is required.

Chart A items are excluded.

Example: First modification, 100 pounds wiring removed, 105 pounds wiring installed. Second modification a few months later, 25 pounds structure removed, 30 pounds structure installed. The Weight Affected change is 260 pounds.

Aircraft Basic Weight (Pounds) Weight Affected by Major Mod as Percent of Basic Weight CG Change (Inches, %MAC or Index) 0-5,000 2.00% 0.5

5,001-50,000 1.50% 0.5 > 50,000 1.00% 0.2

Use inches for rotary wing aircraft and %MAC for fixed wing aircraft.

Table 3-2 Major Modifications or Repairs Guidelines

3-9.5. When aircraft modifications or repairs are accomplished and calculated or actual weight and moment data is not available or reliable.

3-9.6. When an aircraft is completely stripped and repainted or additional layer(s) of paint is added to the entire aircraft. Consult Service Engineering Center for guidance when aircraft are partially painted.

3-9.7. When the weight and balance data is suspected to be in error.

3-9.8. When unsatisfactory flight characteristics are reported that cannot be determined to be the result of improper aircraft loading, an error in weight and balance data, or any other identifiable cause.

3-9.9. When an aircraft is in a depot facility or other authorized weighing facility for any reason, and has not been weighed in five (5) years, (i.e., the most recent “as-weighed” Basic Weight entry in the Chart C is more than five (5) years ago). This applies unless a loading manual specifies a less restrictive requirement for a particular TMS/MDS aircraft.

3-9.10. Whenever inactive aircraft become active as described in paragraph 3-7.

3-9.11. When the weight and balance handbook needs replacement as described in paragraph 3-7.

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Section 4 – Instructions for the Use of Weight and Balance Charts and Forms

4-1. DD FORM 365: RECORD OF WEIGHT AND BALANCE PERSONNEL

4-1.1. This form is a continuous record of weight and balance personnel (civilian or military) responsible for the correctness and maintenance of an aircraft’s weight and balance handbook. It lists the name, grade/rate/rank, where and when qualified, duty station, date of initial responsibility for maintaining the weight and balance records, and date responsibility was relieved. Other qualified personnel may make entries in the weight and balance handbook if they have been designated to do so by the individual currently assigned responsibility for the handbook. The last line entry shall indicate the person who is currently responsible for maintaining the weight and balance handbook at all times.

4-2. DD FORM 365-1: CHART A – BASIC WEIGHT CHECKLIST RECORD

4-2.1. There are three primary purposes of the Chart A. The first is to provide a definition of what is included in Basic Weight for a particular aircraft. The second is to provide weight and balance data for items that may be removed from or added to the Basic Weight of the aircraft. The third purpose is to facilitate the inventory process during aircraft weighings.

4-2.1.1. The Chart A consists of a list of equipment and the equipment weight, arm, and simplified moment that is installed or is approved for installation and is part of the aircraft’s Basic Weight.

Items that are readily removable, not necessary for flight, and identifiable are suitable Chart A items. Items shall be listed on the Chart A as separate entries, suitably identified in order to facilitate an inventory of equipment. Items shall be listed by descriptive name or type, part number or equipment designation, capacity, and other appropriate means to avoid ambiguity and to facilitate identification and inventory. The weight and arm shall reflect the line removable unit weight and arm. Equipment which are alternates to each other shall be suitably identified, e.g., "(alternate to item A-21)" or similar. If an item can be located in alternate positions (e.g.

"stowed" or "installed"), the item shall be listed for both locations and so labeled. Aircraft with a Basic Weight less than 5,000 pounds shall list items 1 pound or more. Aircraft with a Basic Weight between 5,001 and 50,000 pounds shall list items weighing 2 pounds or more. Aircraft with a Basic Weight greater than 50,000 pounds shall list items weighing 5 pounds or more.

Items that weigh less than the above criteria may be listed if it facilitates the aircraft inventory process or should be accounted for during an inventory.

NOTE

Alternate items shall be listed as a .10, .20, etc of the primary item. For example, if a primary item is A-015.00, but there exist several alternate items that may be installed in the same location, the alternates shall be listed as A-15.10, A-15.20, etc.

4-2.1.2. Aircraft compartments shall be designated by capital letters and appropriate descriptive nomenclature. The compartment letter designation and name shall be shown at the top of each list of equipment items for each compartment. In DD Form 365-1 (paper) form compartment designation shall be underlined and separated from the equipment list by a blank line. The limits of each compartment in inches from the reference datum shall be placed on the same line as the compartment description designation. External equipment compartment(s) are excluded from the dimensional limit requirements. These compartment limits should agree with those shown on the aircraft loading manual. Equipment located externally to the body compartments, e.g., in wings, nacelles, shall be listed at the end of Chart A under appropriate designations.

Illustrations of Chart A item locations should be kept with the Chart A to facilitate the inventory process.

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4-2.1.3. The order in which items are listed shall facilitate conducting the inventory. The balance arms should increase progressively from forward to aft in a compartment. If a floor or partition divides a compartment into distinct sections, the Chart A items for that compartment shall be listed by sections. No item or group of items shall be listed in a compartment unless the installed location of the item or group falls within the compartment. Items shall be numbered consecutively by compartment.

4-2.1.4. Weights, moments, and arms should be listed to at least one decimal place. Moments can be simplified by a constant (10; 100; 1,000; 10,000; 100,000).

4-2.2. A Chart A inventory shall be performed whenever:

4-2.2.1. The aircraft is transferred to a new custodian/technician. The receiving activity shall inventory the aircraft to ensure the Chart A is accurate (optional for USAF aircraft). The transferring activity may inventory the aircraft if desired or if mandated by local requirements.

4-2.2.2. As required by pertinent service directives or modifications. (See Section 8 Service Specific Requirements)

4-2.2.3. The pilot reports unsatisfactory flight characteristics with weight and/or balance implications.

4-2.2.4. The aircraft is weighed.

4-2.3. The Chart A shall be updated whenever:

4-2.3.1. The aircraft is inventoried.

4-2.3.2. The aircraft is weighed.

4-2.3.3. The aircraft is received. (optional for USAF aircraft)

4-2.3.4. As directed by a pertinent service directive or aircraft modification instruction.

4-2.3.5. As modifications or configuration changes are made to the aircraft affecting, adding, or deleting Chart A items.

4-2.4. At the time of delivery, the manufacturer inserts the designation of the AIRCRAFT TYPE/MODEL/SERIES and SERIAL NUMBER in the spaces provided at the top of the Chart A. The manufacturer marks the IN AIRCRAFT column to indicate the items of equipment in the aircraft for the delivery condition or an assumed operating condition.

NOTE

If an item is not in the aircraft at the time of weighing, but will be installed for delivery, then the manufacturer should mark the item as IN AIRCRAFT on the Chart A and add the item to COLUMN II of the Form B. The delivery inventory and weighing is the only time Chart A items should be added to COLUMN II of the Form B.

This delivery inventory shows the equipment included in the aircraft's initial Basic Weight and moment as listed on the CHART C.

4-2.5. All Chart A inventories subsequent to the manufacturer's delivery inventory shall be completed as follows:

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4-2.5.1. Inspect the aircraft for equipment actually installed. Record the date and location at which the inventory was completed. If the inventory is completed for an actual weighing, the date shall agree with the date on the Form B. Mark the IN AIRCRAFT column to indicate the presence of an item in the aircraft. If a partial quantity of an item is present at the time of inventory, make appropriate Chart A and Chart C entries to ensure that the Chart C Basic Weight corresponds to the configuration of the aircraft. Do not mark the item as IN AIRCRAFT unless the item is fully installed. If the aircraft is weighed in a dry condition, this NOTE does not apply.

If trapped fuel is listed on the Chart A, it shall not be marked as IN AIRCRAFT. If unusable fuel is listed on the Chart A, it shall be marked as IN AIRCRAFT. The adjustments to Basic Weight for the fuel condition at the time of weighing shall be made in COLUMNS I and II of the Form B.

Trapped fuel is listed in COLUMN I as it is not part of Basic Weight, while Unusable fuel is listed in COLUMN II. (See Section 8 - Service Specific Requirements).

4-2.5.2. During this inventory, note whether any new items or equipment have been installed or previous items permanently removed from the aircraft. For new items, enter on the Chart A an item number, the name or description (include pertinent information such as date entered and/or service directive number), weight, arm, and moment data. Chart A item numbers shall never be re-used. For permanently removed items, mark the item as not IN AIRCRAFT, and change the description to indicate that the item has been permanently removed, and why such as a service directive. Preserve alternate items if still in use. If an alternate item will be permanently installed, follow the numbering convention specified in 4-2.1.1. NOTE.

PAPER FORMS - When using manual DD FORM 365 Forms, marks in the IN AIRCRAFT and CHART C ENTRY columns are made only at the time of a complete inventory. Never change the marks or add new ones under a previously accomplished inventory.

4-2.5.3. When using DD Form 365 forms, compare this new inventory with the last completed inventory, noting any changes in the items or quantities of equipment installed in the aircraft. Refer to Chart C to ascertain whether the necessary weight and moment corrections have been made. If so, place check marks opposite such items in the CHART C ENTRY column of Chart A. If not, correct the calculated Basic Weight and moment data on Chart C and then enter the CHART C ENTRY column check marks. A check mark in the CHART C ENTRY column indicates the appropriate weight and moment change has been recorded on the Chart C. To assist with this procedure between inventories, when a Chart A item is added or removed from the aircraft, enter the date, in the ITEM DESCRIPTION column of the Chart A. Make sure the name of the station at which the inventory is performed and the inventory date is entered in the INVENTORY column on the Chart A. Enter the same date in the DATE column of the Chart C for the corresponding weight and moment calculations.

PAPER FORMS – When using manual DD FORM 365 forms, mark in the “IN” AIRCRAFT and CHART C ENTRY columns are made only at the time of a complete inventory. Never change the marks or add new ones under a previously accomplished inventory.

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4-3. DD FORM 365-2; FORM B - AIRCRAFT WEIGHING RECORD

4-3.1. The purpose of the Form B is to record the data obtained from an actual aircraft weighing. This form also provides the necessary instructions for computing the current weight, moment and center of gravity (CG) of the aircraft.

WARNING

The Form B is the only time in which un-simplified moments are employed when the aircraft has a constant assigned.

NOTE

Instructions for weighing aircraft are in the aircraft specific manuals or in Section 5 (Weighing Aircraft) of this manual.

4-3.2. The following are instructions for completion of the Form B:

4-3.2.1. Fill in the Form B header information.

4-3.2.2. Identify the reaction points used in the REACTION column (wheels or jack-points).

4-3.2.3. Enter the as-weighed weight data in the SCALE READING column for each reaction.

4-3.2.4. In the separate CORRECTIONS block, enter the calibration correction as given by the calibration laboratory; scale correction factor (correction factor necessary when the scale does not return to zero after unloading and gravitational or latitude correction factor - see scale operating instructions); temperature correction factor (see scale operating instructions); equipment such as chocks, blocks, slings, and jacks included in the scale reading but not part of the aircraft weight;

and any other appropriate corrections. Add all the corrections and enter in the appropriate blocks.

4-3.2.5. Total the corrections block for each reaction and use these values in the CORRECTIONS column for each reaction.

4-3.2.6. Sum the SCALE READING and CORRECTIONS block to obtain the NET WEIGHT for each reaction.

4-3.2.7. Distances E and F shall be obtained and entered in both the MEASUREMENTS section and the ARM column. When the aircraft is weighed on wing and/or fuselage jack points; distances E and F may be obtained from the aircraft specific manuals. When weighing the aircraft on its wheels or landing gear jack points, the values of E and F shall be calculated by measuring dimensions B, D, and I. Using B, D and I, calculate and enter dimensions E and F in inches.

4-3.2.8. Multiply the NET WEIGHT of each reaction by the ARM to obtain the un-simplified MOMENT of each reaction.

4-3.2.9. Sum the NET WEIGHT and MOMENT columns of all reactions to determine the TOTAL (as weighed) row.

4-3.2.10. Divide the TOTAL MOMENT by the TOTAL NET WEIGHT to obtain the TOTAL ARM of the aircraft before adjustments.

4-3.2.11. In COLUMN I, record the weight and moment of all items in aircraft when weighed, but NOT part of Basic Weight.

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4-3.2.12. In COLUMN II, record the weight and moment of all Basic Weight items that were not in the aircraft when weighed. Chart A items listed in the column shall also be checked in on the Chart A.

4-3.2.13. Subtotal Columns I and II.

4-3.2.14. Add the TOTAL NET WEIGHT and MOMENT (as weighed) from the front of the Form B and the totals from COLUMN I and II to determine the BASIC AIRCRAFT NET WEIGHT and MOMENT in the provided section. This will be posted to the Chart C.

NOTE

The term NET WEIGHT indicates an “as weighed” value including

CORRECTIONS.

4-3.2.15. In the SCALE section, fill in SCALE TYPE (make and model), SERIAL NUMBER (of all scales/load-cells used), and DATE CALIBRATED.

4-3.2.16. Identify REACTIONS USED (wheels or jack-points).

4-3.2.17. In the REMARKS Section, enter at a minimum: "Aircraft clean, dry, fuel system condition (dry, trapped, or full using open-port method), fuel density X.X pounds per gallon, (if fuel system is full), weighed in level or non-level condition, aircraft…