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MIL-C-18244A(WEP)
3.2.7
Electrical Power - The AFCS shall operate satisfactorily in accordance
with the performance requirements specified herein when supplied power from sources conforming
to the applicable requirements of MIL-STD-704. The performance and operation requirements of
this and the applicable component specifications shall be met with equipment supplied by this power,
Which may be subject to steady state and transient variations within the specified tolerances of
MIL-STD-704.
3.2.8
Calibration Adjustments, Controls and Knobs -
Controls and Knobs - Controls and knobs requiring manipulation in flight
3.2.8.1
shall operate smoothly with negligible backlash or binding. Means shall be provided to prevent
movement due to shock or vibrations encountered in service. Controls and knobs shall be readily
accessible and of a size and shape for convenience and ease of operation under all service conditions.
The direction of motion of the knob or control and the location within the cockpit shall be in accord-
ance with the requirements of MIL-STD-203.
Calibration Adjustments - Calibration adjustments required for ground
3.2.8.2
maintenance of the system or component shall be kept to a minimum. The system objective shall be
to concentrate all required ground adjustments in one major component of the system. It is preferred
that the removal of an auxiliary cover plate be necessary for access to calibration adjustment, Suit-
able means shall be provided to prevent a change in adjustment to occur due to shock or vibrations
encountered in service. These adjustments shall be labeled, indexed, and marked in such a manner
that only visual means are necessary for setting the desired adjustment.
Dynamic and Static Pressure and Air Data System - Whenever AFCS com-
3.2.9
ponents require connection to pitot tubes or static ports, the required performance shall be obtainable
from pitot tube and static port installations conforming to the requirements of Specification
MIL-I-6115. Compensation of static or dynamic signals, which may be required to obtain desired
performance, shall be accomplished within the system or components. Whenever the automatic
flight control system requires outputs from a central air data system in lieu of static and pitot
measurements, the characteristics of the outputs, both static and dynamic shall be submitted to the
using agency by the automatic flight control system contractor at the earliest possible date in order
to insure compatibility between the AFCS and air data system,
System Component Design Requirements -
3.3
Electrical and Electronic Components - All electrical equipment in the
3.3.1
control systems shall be designed and installed in accordance with Specifications MIL-E-5400,
MIL-E-7080, MIL-W-5088, MIL-A-8064, MIL-M-8609, MIL-E-4682, MIL-M-7969, and any other
applicable specifications. Critical components shall have the best possible relatability to insure
against loss of control of the aircraft. Specific consideration shall be directed toward achieving
simplicity, producibility, and maintainability of equipment. The procedures outlined in Specifica-
tion MIL-R-22256 shall be followed to insure that electronic equipment designs will have a high
level of inherent reliability.
Electron Tubes - Electron tubes shall not be used.
3.3.1.1
Electrical Tape - No pressure-sensitive (adhesive or friction) fabric or
3.3.1.2
textile tape shall be used. Nonmoisture absorbing tape may be used for mechanical purposes, with
the approval of the procuring activity.
Switches - Switches shall conform to the requirements of Specifications
3.3.1.3
MIL-S-3950, JAN-S-63, or MIL-S-6743 as the application may require. The operating position
requirements of Specification MIL-E-5400 shall normally apply.
Electron Devices - Transistors and diodes shall be chosen and applied,
3.3.1.4
and the complements reported, as outlined in Specification MIL-E-4682. The complement report
must be submitted to the procuring activity for review and approval prior to design approval testing.
Saturable Reactors - Saturable reactors in automatic flight control systems
3.3.1.5
and components shall comply with the environmental and performance requirements specified herein
and in detail system component specifications.
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