DI-SESS-82123

Strength Summary and Operating Restrictions (SSOR) Report

The Strength Summary and Operating Restrictions (SSOR) Report is used to define restrictions, in terms of capabilities and limitations, for service operation of the aircraft that permits rapid and accurate assessment of strength relative to loading conditions and operational parameters.

Approval DateMay 10, 2017

AMSC NumberF9805

Preparing Activity11 (AFLCMC/EZFS)

Project NumberSESS-2017-013

OPR—

DTIC ApplicableNo

GIDEP ApplicableNo

Limitation—

Applicable Forms—

Approval Limitation—

Form Version—

DID Formatfree_text

963C CompliantYes

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

Supersedes

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Description & Purpose

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Application & Interrelationship

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Use & Relationship

The Strength Summary and Operating Restrictions (SSOR) Report will be used to define restrictions (in terms of capabilities and limitations) for service operation of the aircraft that permits rapid and accurate assessment of strength relative to loading conditions, specification requirements, and the effects of varying important operational parameters such as gross weight, payload, and fuel.

a. The SSOR report shall summarize the strength of the aircraft structure for all design operating conditions at the specified and other critical weights by showing a comparison of strength required by applicable specifications with the strength determined by analysis and test; shall recommend restrictions for service operation of the aircraft; and shall afford a basis for determining the practicality of modifying restrictions, of varying useful loads, and for making structural modifications. The report shall present sufficient data and information to substantiate the structural strength and operating restrictions applicable to the authorized flight envelope and operating conditions. The report shall provide rapid visibility of the important structural characteristics, limitations, and capabilities in terms of operational (flight and ground) parameters. The summary shall include brief descriptions of each major structural assembly, indicating structural arrangements, materials, critical design conditions, and minimum margins of safety. Appropriate references to design drawings, detail analyses, test reports, and other back-up documentation shall be provided.

b. The report describes the contractor's revised analysis which accounts for differences revealed between analysis and test to relate important structural characteristics, limitations, and capabilities in terms of operational parameters.

c. This Data Item Description (DID) contains the format, content, and intended use information for the data deliverable resulting from the work task described by Task 4 of MIL-STD-1530, Aircraft Structural Integrity Program (ASIP).

(Copies of this document are available online at http://quicksearch.dla.mil.)

Preparation Instructions

1Reference documentsThe applicable issue of the documents cited herein, including their approval dates and dates of any applicable amendments, notices, and revisions, shall be as specified in the contract.

2FormatThe SSOR Report shall be in the contractor's format.

3ContentThe final SSOR report shall include the following information:

aBrief description of the aircraftA brief description of the aircraft. If the aircraft is a modified version of a previous model, the differences between the models shall be described and the effect of these differences on minimum margins of safety and operating restrictions shall be included.

bSummary of basic dataA summary of basic data, including design and actual weights, center of gravity positions, principle surface areas, and a three-view drawing showing front, top, and side views of the aircraft with physical dimensions, including control surfaces.

cV-n diagramsV-n diagrams depicting the required and available strength in terms of load factor, airspeed, and altitude. Load factors developed by specified symmetrical gusts and maximum speeds for which limit strength exists for specified side gusts shall be shown on these V-n diagrams. Values of static and dynamic aircraft normal force coefficients on which the V-n diagrams are based.

dEffects of variations in weightDiscussions of the effects of variations in weight, weight distribution, or both on strength, including all sources of potential aircraft weight variations (e.g., fuel, stores, and payload).

eMaximum design sinking speedsMaximum design sinking speeds at various design weights.

fTable of recommended combinationsA table of recommended combinations of the aircraft, racks, and stores to be authorized. For each combination listed, the following limits and configurations shall be stated: For each store listed, the load factors and flight or ground loading condition resulting from the specified design conditions including take-off, unsymmetrical landing, braking, turning, or other conditions that are critical for the supporting aircraft structure shall be shown.

(1)Maximum carriage limitsThe maximum carriage limits (airspeed, acceleration, and altitude)

(2)Release, launch, and jettison limitsThe release, launch, and jettison limits (airspeed, acceleration, altitude, dive angle, and attitude)

(3)Take-off and catapult launch configuration

(4)Field landing and arrested landing configurations

gRecommendations for restrictionsRecommendations for restrictions to be observed while in operation, including:

(1)Maximum weights for field take-offMaximum weights for field take-off, field landing, and when applicable, catapulting, arrested landing, and rough field take-off and landing.

(2)Maximum permissible speeds and load factorsMaximum permissible speeds and load factors for flight with and without external stores.

(3)Restrictions on use of lateral and directional controls

(4)Maximum permissible speeds with devicesMaximum permissible speeds with devices such as flaps; spoilers; cockpit enclosures; landing gear speed brakes; bomb bay doors in partially extended, fully extended or open positions, or both; and for combinations of devices when a combination results in adverse aerodynamic effects, such as buffet.

(5)Maximum permissible aircraft center of gravity accelerationsMaximum permissible aircraft center of gravity accelerations for arresting and catapulting versus gross weight.

(6)Maximum permissible drag load componentsMaximum permissible drag load components for arresting and catapulting.

(7)Maximum permissible drag load factorMaximum permissible drag load factor as a function of gross weight for both catapulting and arresting.

hSummary charts of all testsSummary charts of all tests performed to support the design conditions for the aircraft structure. These summaries are to include a comparison of specification design strength with the actual strength as revealed by analysis and test.

iList of critical margins of safetyList of critical margins of safety for each major structural component including margins of safety for supporting structures including stores listed in 3.f above. This list shall include, for each margin of safety listed, the critical design condition and reference to the report and page wherein the margin of safety was determined.

jDiagrams or reduced-size drawingsDiagrams or reduced-size drawings of each major aircraft component, such as, a wing, fuselage, landing gear, etc., which shows the most critical and second most critical loading conditions for each area or region of the component.

References

quicksearch.dla.mil http://quicksearch.dla.mil

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