U-2R AIRCRAFT BASE-LINE CONFIGURATION

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP71B00263R000200030019-5
• Release Decision: RIPPUB
• Original Classification: T
• Document Page Count: 9
• Document Creation Date: November 11, 2016
• Document Release Date: November 17, 1998
• Sequence Number: 19
• Content Type: REPORT

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ATTACHMENT II
AIRCRAFT BASE-LINE CONFIGURATION
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INTRODUCTION
In arriving at a base-line configuration for the
U-2R aircraft, the following considerations were
uppermost:
Establish an aircraft configuration fitted
to ready operational employment by either
the CIA or the DOD.
Apply wealth of long-time U-2 fleet experience
by operating commands and contractor associates
to design, construction and support of the U-2R.
Effect maximum utilization of on-shelf assets
and that hardware common to the U-2C and U-2R
models.
Leave the door open for subsystems showing
growth potential in technology.
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Io SCOPE AND CLASSIFICATION:
Service Model Designation Reconnaissance
Designer
Model Designation U-2R
Number/Places for Crew One Pilot - Flight Station
Number/Type Engine One Axial -
Jet
II. BASIC REFERENCES:
a. "Manufacturer's Model Specification, High Altitude
Reconnaissance Airplane" Model U-2R, Report No. SP-1125,
28 November 1966
b. Minutes of Configuration Control Board (CCB) and
Review Panel Meetings for the U-2R aircraft (as noted).
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III. GENERAL DESCRIPTION AND COMPONENTS:
PROPULSION:
25X1A5a1 (Ref:
Report No. SP-1125, 28 November 1966)
COMMUNICATIONS:
AN/ARC-51 - UHF Communication
VIIF-101 - VHF Communication
718T-6 - HF Communication
9 14 X 1 - IFF
AN/AIC-10 (-18) - Interphone Amplifier
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ecorder (provisions to accept)
(Ref: Minutes, U-2R Mock-Up Review, 29-30 November 1966
and Minutes, Comm/Nav Working Group, 10 November 1966).
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III. GENERAL DESCRIPTION AND COMPONENTS: (con.t'd)
NAVIGATION:
ARN-59
ARN-52
APN-153/ASN-66
Navigation System with provisions
for pilot readout of drift and
ground speed.
Provir-dionH to accopt prosonnt flight roforonco HyHtLom
plus Ho] ['-coat Lailiod standby atti'Ludo ind.ica Lor .
(Ref: Minutes, U-2R Mock-Up Review, 29-30 November 1966
and Minutes, Comm/Nav Working Group, 10 November 1966)
ELECTRONIC WARFARE SYSTEMS (EWS) :
CONTROL SYSTEM
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III. GENERAL DESCRIPTION AND COMPONENTS: (cont'd)
ELECTRONIC WARFARE SYSTEMS (EWS) : (cont'd)
(Ref: Minutes, U-2R Mock-Up Review, 29-30 November 1966
and Minutes, EWS Working Group Meeting, 21 October 1966)
SENSOR EQUIPMENT:
(Ref: Minutes, U-2R Mock-Up Review, 29-30 November 1966
and Minutes, U-2R Requirements Review Board Meeting,
20 October 1966)
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III. GENERAL DESCRIPTION AND COMPONENTS: (cont'd)
COCKPIT CONFIGURATION:
On 29 and 30 November 1966, six U-2 is
and
ssignees) Perfip"alviaual evaluation of the
U-2R cockpit mock-up.
Each pilot, after donning the full pressure suit, was
permitted 30 to 45 minutes (including approximately 10
minutes with the suit pressurized) in the cockpit. Each
individual evaluated readability of instruments, ready
access to controls, mobility within the cockpit (with
the pressure suit inflated or deflated) and ejection
sequence clearance with suit inflated. These evaluations
were followed by group discussion and critique.
Deficiencies found in the cockpit arrangement were
25X1A5a1 presented to U-2R engineers for corrective actions.
Subsequent cockpit review by these same pilots were
performed on individual placement and location of switches,
controls and instruments. Their recommendations permitted
a design "freeze" of the cockpit and will be reflected in
tho basic aircraft configuration.
(Ref: Minutes, U-2R Cockpit Configuration Panel Meeting,
29-30 November 1966)
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III. GENERAL DESCRIPTION AND COMPONENTS: (cont'd)
LIFE SUPPORT:
Discussions on Pilot's Protective Assemblies (PPA's)
led to selection of a full pressure suit for pilot employ-
ment in the U-2R aircraft. The full pressure suit being
considered is a modification of the suit developed for
25X1DOb The modifications being made will configure
this system to satisfy the crew member protection and
comfort requirements imposed by the specific performance
envelope of the U-2R. Because the hardware items on this
proposed system are standard USAF equipment, the required
AGE for supporting this system will require no develop-
mental efforts. The proposed pressure suit system is also
compatible with the ejection seat to be provided in the
25X1DOb U-2R, since it is the same seat used in the The
ejection seat provides for safe recovery from ground level
and zero airspeed through the entire altitude and speed
envelope of the U-2R. The personal parachute and seat
kit required to complete this system should also be the
25X1DOb same as those used in the lllllllllllllllllllllllllllalthough the manufacturer's
model specification (Attachment III) does not include these
two items. Consideration for funding for these later two
items must be made if they are not contained in the basic
aircraft contract.
(Ref: Minutes, U-2R Mock-Up Review, 29-30 November 1966)
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