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DI-MGMT-81501A

Weight and Balance Report for Aircraft

The Weight and Balance Report for Aircraft provides up-to-date information required to maintain cognizance of deleterious trends, supports engineering activities, and provides safety of flight information regarding aircraft weight, balance, and inertia properties.

Approval DateSeptember 27, 2007
AMSC NumberF9014
Preparing Activity—
Project Number—
OPR11 (ASC/ENFS)
DTIC ApplicableYes
GIDEP ApplicableNo
Limitation—
Applicable Forms—
Approval Limitation—
Form Version—
DID Formatdd_form_1664
963C CompliantNo
DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited.
Supersedes
DI-MGMT-81501
Related
DI-MGMT-81452DI-MGMT-81504DI-MGMT-81503DI-MGMT-81502

Description & Purpose

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Application & Interrelationship

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Use & Relationship

The Weight and Balance Report for Aircraft provides up-to-date information required to maintain cognizance of deleterious trends which may require program office action, provide data for use by various engineering activities, and provide safety of flight information to the field. Aircraft weight, balance, and inertia properties officially affect system performance.

a. This Data Item Description (DID) interrelates with DI-MGMT-81452, Mass Properties Control and Management Process Report; DI-MGMT-81504, Inertia Report for Aircraft; DI-MGMT-81503, Post-Design Weight Analysis Report; and DI-MGMT-81502, Sample Chart A and Chart E Report for Aircraft.

b. This DID contains the format, content and intended use information for the data deliverable resulting from the work task described in the contract.

c. DI-MGMT-81501A supersedes DI-MGMT-81501.

Preparation Instructions

1Reference documents.The applicable issue of the documents cited herein, including their approval dates and dates of any applicable amendments, notices, and revisions, shall be as cited in the contract.
2Format.The format shall be The Society of Allied Weight Engineers (SAWE) Recommended Practice number 8 (RP-8), Weight and Balance Data Reporting for Aircraft.
3Content.Depending on project phase, the following weight and balance information shall be included: a. Estimated b. Calculated c. Status d. Actual
3.1The following shall be included in the report (except for status updates).
3.1.1Contract number, aircraft designation, acquiring activity, and contract identification or serial numbers, as appropriate, of the aircraft for which the data in the report is considered to be representative.
3.1.2A table summarizing the weight, center of gravity (c.g.), and moments of inertia for weight empty, maximum gross weight, structural design weights, most forward, most aft, and all weight conditions covered in the design mission description and specification. Dimensional data suitably illustrated, locating the longitudinal, vertical, lateral, and radii of gyration axes, and mean aerodynamic chord (MAC) or main rotor centerline. The recommended c.g. limits shall be provided.
3.1.3Group Weight Statement.The useful load page shall detail the summary values in b. above.
3.1.4Detail Weight Statement
3.1.5Material breakdown by weight group for Structure Weight and Airframe Unit Weight.
3.1.6Longitude, vertical, and lateral balance calculations for values in b. above.
3.1.7List of government supplied equipment in weight empty and associated weight.
3.1.8Wetted areas of fuselage, wings, empennage, and all external items included in takeoff configurations (pylons, tanks, and weapons).
3.1.9Volumes of the fuselage, wings, empennage, and all external items included in mission takeoff configurations.The volumes shall be calculated with flaps, gears, and air brakes retracted.
3.1.10Scalable dimensional three-view drawings locating and identifying the following:
3.1.10.1The major dimensional data including major structural stations of the wing, rotor, tails, fuselage, alighting gear, nacelles, and inlets.
3.1.10.2Reference data for longitudinal, lateral, and vertical moment arms and Mean Aerodynamic Chord (MAC).
3.1.10.3Major structural members, cutouts, control surfaces, and other structural features.
3.1.10.4Major items of equipment, fuel, or propellant
3.1.10.5Types of construction and materials used in each major structural component section and tank.
3.1.11Outline sketch of the main propulsion power transmission system showing gearboxes, shafting, rated horsepower, and torque reduction ratio.
3.1.12Schematic diagram for major subsystems.
3.1.13Center of gravity (c.g.) diagrams showing plots of weight vs. c.g. for all specification missions, most forward loadings, and most aft loadings.Label all applicable limits.
3.1.14Oil and unusable fuel data.
3.1.15Derivation of the moment change owing to retracting the alighting gear.
3.1.16Tip back calculations.
3.2The following additional data are required on actual weight reports:
3.2.1Weight empty weighting form.
3.2.2A detailed list of items, weights, arms, and moments to be added to or subtracted from the as-weighed condition to arrive at the weight empty.
3.2.3All weight and balance calculations for the final Estimated or Calculated Weight Report, corrected to agree with the actual weight and c.g. data.
3.2.4A tabulation of specified and actual weights of all Government Furnished Aerospace Equipment (GFAE) included in the weight empty, based on weighing of the items prior to installation, and determination of the net underweight or overweight of this equipment
3.2.5Tabulations of authorized and pending changes included in the reported weight empty and useful load, the weights, and the groups to which the weights are allocated and associated engineering change proposals (ECPs) or corresponding numbers.
3.2.6A tabulation deriving the contractor responsibility for weight empty under or overweight, as follows:
3.2.6.1The original weight empty guarantee or specification weight empty.
3.2.6.2The weight empty increases or decreases owing to the weights of authorized changes, pending changes, and the net underweight or overweight of GFAE.
3.2.6.3The aircraft actual weight empty.
3.2.6.4The contractor responsible weight.
3.2.7Oil, unusable fuel, drainable fuel, and trapped fuel weight and c.g. data including description of how values were determined.
3.2.8Brief summary of internal loads and points of load concentration.If information is presented by drawings, it is desired, but is not necessary, that the cross-section of the related structure be included. Reduced size drawings and copies are acceptable. These data are required on first and last aircraft only.
3.3The following shall be included in Status Updates.Reports reflect the changes from the previous weight report (estimated, status, or calculated) as the design and fabrication proceeds. As individual components become defined, the status reports shall represent a mixture of estimated, calculated, and actual weight. Each report shall represent the status as determined by the contractor's weight control records at the end of the reporting period noted by the date on the form. The report shall include separate sections listing all possible and planned changes not yet included in the weight control records. Additional data will be required by the acquiring activity if weight or c.g. are considered to show an undesirable trend. The following general instructions shall apply:
3.3.1The values in the original specification or the original guarantee column shall be the same as in the original specification or approved Estimated Weight Report and shall not be changed.
3.3.2The initial issues of the status report shall include reference to the source or the recommended c.g. limits, brief indication of the critical flying qualities or structural considerations which dictated these limits, and reasons for any tapered or special c.g. restrictions.Similar data shall be furnished whenever limits are revised.
3.3.3A brief discussion of each major government responsible weight change.
3.3.4A brief discussion describing the reason for each major contractor responsibility weight variation and c.g. shift, including any remedial measures being investigated or applied.
3.3.5At the times when the current weight status and c.g. are brought into agreement with the Calculated Weight Report or the results of the actual weighing of the completed aircraft, appropriate note to this effect shall be made and the calculated or actual weight report shall be referenced by number, date, and title.
3.3.6During the flight test phase, if changes in the current weight status in a status report period are less than 0.25 percent of the weight empty and the weight empty c.g. shift is less than 0.5 percent MAC for aircraft or 2 percent of allowable c.g. range for rotor craft, the status report for that period may be omitted and the acquiring activity notified by letter.
3.3.7If a major modification is to be incorporated in one or a group of aircraft on the contract, information on the weight and c.g. status of the modified aircraft shall be included as an appendix to the status report.Status information furnished may be in the form of differences over the basic model and shall continue as a separate report, if necessary, until the modified aircraft is delivered to the acquiring activity.

References

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