MIL-S-6252D
following subparagraphs shall contain perD formance data as indicated. These data shall be prepared according to the rules and deD finitions of Specification MIL-C-5011, exD cept that rules and definitions contained in the design requirements document shall govD ern where they conflict with Specification MIL-C-5011.)
3.L2.l (USAF) Derigmd aircraft pero forma11&ce. (Items of performance that are specified· u "required" in the design reD quirements document shall be listed herein and compared with the designed performD ance. These items shall be clearly identified with the appropriate gross weight, engine power, configuration, etc.)
3.L.2.2 (USAF) Additional performance data. (Curves itummarizing the performance shall be prepared and included herein. The required performance listed in 3.1.2.1 shall be indicated on the curves. Mission profiles shall be presented for the required misD sion (s) and shall include fuel allowances, pertinent weights and configurations. AdD qitio_nal estimated performance data may be presented to show other performance capaD bilities if the designer so deslrea.I
3.1.2.3 The aircraft performance specified herein 'is based on the engine specification
number {engine manufacturer's specificaD
tion).
3.1.2 (BuAer) Guamnteed tabulated per-• formenee, Guaranteed performance shall be for the gross weights with the useful loads specified in the detail specification.
3.1.3 Weights. (Tables of MIL-STD-254
Group Weight Statement shall be reproduced here, unless equivalent abstracts are speciD fied by the procuring activity.)
3.1.3.1 (USAF) Alternate loading. (PrinD cipal alternate loading conditions shall be listed, with suitable explanation of the manD ner in which they differ from the "Design useful load condition", that is, showing inD creases or decreases in bomb or cargo load, full load, et cetera. Each ·of these alternate loading conditions shall be given an identiD fying...Dumber such as "I-A", "I-B", II-A", et cetera, to permit ready and definitive reference to each of these conditions. In addition, a "Useful load" sheet {page 4 of
AN-9103 (MIL-STD-254) form) shall be
prepared, properly labeled as to "condition",
for example, "Alternate useful load I-A'', and inserted in the detail specification immeD diately following the "Design useful load" sheet of the AN-9103 form.)
3.1.4 Center of g1·a:1Jity locations.
Design Gross Weight, cg location, basic flight condition: Aft LE of MAC percent MAC
(Above, below) LE of MAC .inch
Design Gross Weight, cg location, take-off configuration: Aft LE of MAC percent MAC
(Above, below) LE of MAC : .i-ch
Extreme forward Position, cg possible in flight regardless of loading at take-off (wheels up, wheels down) :
Aft LE of MAC percent MAC (Above, below) LE of MAC .inch Gross· Weight for this eondition .lb
Extreme rearward position, cg posible in fxi-ht regardD
less of loading at take-off (wheels up, wheels down) :
8
For Parts Inquires submit RFQ to Parts Hangar, Inc.
© Copyright 2015 Integrated Publishing, Inc.
A Service Disabled Veteran Owned Small Business