FINAL REPORT OPERATIONAL SUITABILITY OF BLACK SHIELD AIRCRAFT AND COMPONENTS PROJECT 65-8 13 DECEMBER 1965

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP71B00399R000600130003-7
• Release Decision: RIPPUB
• Original Classification: T
• Document Page Count: 35
• Document Creation Date: December 19, 2016
• Document Release Date: August 3, 2006
• Sequence Number: 3
• Publication Date: December 13, 1965
• Content Type: REPORT

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FINAL REPORT
OPERATIONAL SUITABILITY OF BLACK SHIELD
AIRCRAFT AND COMPONENTS
PROJECT 65-8
13 December 1965
1129TH USAF SPECIAL ACTIVITIES SQUADRON
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TABLE OF CONTENTS
Page
Review and Approval
1
Introduction
2
Objective
2
Description of Equipment
2
Test Methods and Limitations
2
Data Collection and Reduction
3
Accuracy of Data
3
Test Results
3
Conclusions and Recommendations
7
Appendix A - Mission Profile
8
Appendix B - Detailed Validation Item Results
9
Distribution List
32
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REVIEW AND APPROVAL
REVIEWED BY:
REVIEWED BY:
REVIEWED BY:
REVIEWED BY:
APPROVED BY:
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INTRODUCTION
1. This test was conducted under the authority of the Deputy
Commander for Operations, Det 1, 1129th USAF Special Activities
Squadron. On 12 and 13 May, 1965, a meeting between Head-
quarters, 0 and LAC personnel was held to determine basic 25x1
test and system validation requirements to meet an Operational
Readiness Inspection Test date of 15 December on Black Shield
aircraft. The test was conducted from 1 October to 1 December
in accordance with the Test Plan as amended.
OBJECTIVE
2. The objective of this test is to determine the operational
suitability of A-12 aircraft and component systems as modified
to the Black Shield configuration.
DESCRIPTION OF EQUIPMENT
TEST ITEM
3. The test was conducted using the three A-12 airplanes des-
ignated as primary for Black Shield. These aircraft, numbers
126, 127 and 128, were in standard configuration and instru-
mented with two cockpit cameras each to photograph the instru-
ment panels, and one oscillograph each to record the perform-
ance of the inlet ducts. In addition, each airplane was
equipped with a voice recorder. Normal support equipment was
used during the test conduct.
TEST METHODS AND LIMITATIONS
TEST PROCEDURES
4. Prior to the initiation of this test, the subject airplanes
were engaged in a series of flights to demonstrate performance
and systems reliability. These>:flights, consisting of approxi-
mately six sorties per-aircraft, were completed satisfactorily
and this Operational Suitability Test was begun on 1 October
19'65, Physical Testing was completed on 20 November 1965. A
total of nine successful sorties were flown, consisting of
three per airplane. Six of-these sorties included three air
refuelings with four high speed cruise legs, for a total flight
time of approximately six hours each. The final three sorties
were simulated operational missions which included two air
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refuelings each with trans-continental routes. Flight times
for these sorties were approximately four hours each. Pilots
were briefed using standard Detachment procedures for mission
functions, and all tactics used were as specified in the
Detachment Tactical Doctrine. The Limited Climatic Test,
Black Shield Validation Item #25A, was completed as a separate
test and the results forwarded in a separate report. As
noted in the report the windshield deicing test has yet to be
completed.
DATA COLLECTION AND REDUCTION
5e During pre-mission briefings, the validation items were
reviewed for the pilots, along with the satisfactory-unsatis-
factory criteria. In the test flights, pilots noted the
functional operation of the validation items and voice record-
ed necessary data for climb, cruise and descent performance.
In the post flight debriefings, pilots completed test mission
forms on which all validation items were listed Each item
was rated as satisfactory or unsatisfactory, the latter
rating requiring explanatory remarks. Similar forms were
completed by DCM personnel to acquire data on items best
evaluated during post flight functions. DCM personnel also
reviewed the voice recorder tape playback and the cockpit
camera film for additional data. Evaluation of payload mater-
ial, INS, etc., were provided by the applicable agencies and
included on the forms completed by DCM. Performance data was
transcribed from the voice recorders by DCOM personnel and
dispatched to LAC for reduction.
ACCURACY OF DATA
6. Most of the rating criteria was set to specified limits,
but in some cases the ratings were qualitative; based on,
pilot/technician experience and judgement. In the case of
performance, the profile presented in Appendix A is from data
based on average test day atmospheric conditions. Operational
performance will vary somewhat with changes in air temperatures.
TEST RESULTS
GENERAL
7. A total of 12 sorties were flown for 52:40 hours. Over-
all, nine sorties were rated as satisfactory with three air
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aborts. One abort was charged to a low oil pressure indi-
cation and the other two to ARC-50 UHF failure.. For an over-
all rating of satisfactory, a mission had to be completed as
briefed with the entire route covered and all refuelings met.
For overall performance success, inlet unstarts were accept-
able n as altitude loss did not exceed 2,000 feet or to
below feet during penetration legs. Only missions 25x1
which were a rborne were considered. Ground aborts and
schedule cancelations were not considered as they are beyond
the scope of this testa
PERFORMANCE
8. Appendix A contains a typical performance profile compiled
from data based on average test day atmospheric conditions.
Complete performance data generated from this and other tests
were published in the A-12 Utility Flight Manual in a change
dated 1 Dec 65. These data are presently being reduced to
standard conditions and when completed will be published in
the flight manual.
VALIDATION ITEMS
9. Appendix B contains a breakdown of validation items by
aircraft, date, rating, and explanatory remarks. The follow-
ing table summarizes the results by satisfactory-unsatisfactory
criteria and percent satisfactory.
ITEM
1A & 2A - Performance.
Multiple A/R High Speed
Profiles.
NOTE: No unsatisfactory
ratings were due to
inlet malfunctions.
3A - Inlets
SUMMARY OF RESULTS
CRITERIA RATE
1. All legs and refuel- 75%
ings completed as
briefed.
2. Maximum.alt, loss of
2000 ft during starts
or to a min of II
during penetration legs.
Unsatisfactory if any 64%
unstarts were encountered.
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ITEM
CRITERIA SUCCESS RATE
4A - Air Data Computer
Normal Function
100%
5A - LOX (Deleted)
6A - LN2
Minimum 15 liters reserve
100%
7A - TACAN
Normal functions and DME
75%
agreement with INS within
10%0
8A - IFF
As reported by Radar
92%
9A - Aft Fuel Feed and
Normal functions
100%
Transfer
10A- SR-3 Compass
Remained in sync after
92%
1800 turn, with attitude
indicator precession of
no more than 3?0
Normal Limits
67%
12A- All Attitude Fuel
No more than 2000 lbs
100%
Readout
13A- Fire Warning
fluctuation after attitude
or acceleration change.
Normal indications
100%
14A- Engine Durability
No engine change or major
82%
15A- SC & DM Switching
repair required.
Normal function
100%
16A-
to
No erroneous signals
92%
20 Proper signals transmitted
17A- DECM
Ground Report
63%
18A- SIP
Ground Report
100%
19A- ARC-50
Normal UHF, internal
17%
& external. Normal DME
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CRITERIA
SUCCESS RATE
20A - INS/ECM
Compatibility
INS not affected
by ECM-.
100%
21A - Plastics
22A - Mach Hold
No breaks or
de laminations
(Deleted)
100%
23A - SSB
Normal functions
100%
24A - Camera
25A - Climatic Test
Normal function and
acceptable resolution.
(Separate report)
90%
26A - INS
to Remained within specs
2. 50 Max steering bias
3. Auto Nav bank angle
73%
350 + 0-3?
27A - Complete System
Test
OTHER ITEMS
Cmdr, DCO and
DCM evaluation
75%
10. Test Plan Revision Number 2 added the requirement for
further evaluation of cockpit radiation heat shields and
weather modifications. No evaluation of these items was accom-
plished as the heat shields were not available and rain, high
humidity, and icing conditions were not encountered during
the test. Pilots were asked to comment on cockpit heat
problems during descents and the consensus was generally
favorable. However, descents were initiated with fuel remain-
ing in the order of 20,000 lbs where adequate sink was still
available for air conditioning. It is anticipated that if
descent fuel remaining is in the order of 5000 lbs or less,
pilot comfort may become a flight safety hazard.
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CONCLUSIONS AND RECOMMENDATIONS
11. An overall satisfactory rate of 75% for the long endurance
high speed missions flown on this test illustrates the great
improvement in performance and reliability of the A-12 air-
craft. This improvement is primarily due to the Black Shield
modification program and more effective quality control. It
must be pointed out that the 75% is no really a true picture,
since two of the three aborts were due to ARC-50 radio failure
rather than basic airframe systems. Had the radio problems
been solved, the rate would have been more in the order of
90%. It is significant to note that none of the unsatis-
factory ratings for overall performance were due to inlet mal-
functions. With unmodified aircraft, inlet system malfunctions
was the most serious A-12 problem area. The most serious
problem now is the ARC-50 UHF radio which had a satisfactory
rate of 17%. The ARC-50 is important since external DME and
ADF modes are the primary tanker rendezvous aids, especially
under restricted visibility conditions. It may be argued that
during this test no air refuelings were missed in spite of the
poor ARC-50 performance, but back up aids were used and weather
conditions were better than will generally be encountered dur-
ing deployment operational flights. Based on the lack of a re-
liable all weather rendezvous aid, it is recommended that the
A-12 aircraft be considered operationally ready with a VFR
rendezvous restriction until improved or substitute equipment
is available. Efforts to improve the ARC-50 are being contin-
ued to provide an operationally suitable system.
12. DECM shows marginal performance with a rate of 63%. It
is recommended that an intensive flight test program be initi-
ated to isolate and solve the problems. Emphasis should be
placed on DECM performance below 60?000 feet to afford protect-
ion in the event an A-12 must descend over enemy territory.
13. Engine oil and pressure indicating systems continue to be
somewhat a problem with a rate of 67%. The indicating system
is the primary trouble and further efforts are.necessary to
eliminate this problem.
14. Cruising range of the A-12 has improved drastically but
more data is necessary to further refine the results to date.
Performance testing is being continued with a minimum of turns
in the flight profiles and range extensions to allow cruising
to 10,000 pounds of fuel remaining at start of descent. To date,
most of the data from 20,000 to 7,500 lbs of fuel remaining is
extrapolated. Performa e is lacking for a penetration
technique of a constant ft cruise altitude instead of
cruise climb. This area s ou be explored in the performance
follow-on testing.
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ITEM 1A & 2A
PERFORMANCE
Msn or Rat- Acft Flt
Route ing # Date Time
U 128 7 Oct 4:30 Air abort due to oil Pressure 25x1
RH engine shut down - 4th leg
not flown.
S 126 12 Oct 6:05
S 128 13 Oct 6:10
U 128 20 Oct 0:40 Air abort, UHF failure. Sub-
sonic flight
S 127 21 Oct 6:20
S 128 22 Oct 5:50
S 126 26 Oct 5:30
S 127 28 Oct 5:40
S 127 3 Nov 3:55
U 126 5 Nov 1:00 Air abort - ARC-50 failure.
S 12& 11 Nov 4:00
S 126 20 Nov 4:00
NOTE: The last 4 sorties
were actually under
Item 27A0
Appendix B - Detailed Vali-
dation Item
Results.
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ITEM 3A
INLETS
Rating_ Acft# Date Remarks
S
128
7 Oct
S
126
12 Oct
U
128
13 Oct
Spike too far Fwd - -Door open. LH
side malfunat ph 1,a.st leg - Computer
amplifierA U'nc' ion.
128
20 Oct
Air abort - EHd Subsonic
S
127
21 Oct
U
128
22 Oct
RH inlet unstarted at beginning of
two descents. LH inlet operated
manually on 4th leg.
TJ
126
26 Oct
RH inlet unstarted at beginning of
last descent. Both inlets unstarted
during turn - Due to erratic Mach
Hold.
S
127
28 Oct
S
127
3 Nov
S
126
5 Nov
Max Mach 2.5
S
128
11 Nov
U
126
20 Nov
Upstarts in two climbs & accel -
Mach 2.5.
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ITEM 4A
AIR DATA COMPUTER
Rating Acft # Date Remarks
S
128
7 Oct
s
126
12 Oct
S
128
13 Oct
S
128
20 Oct
S
127
21 Oct
S
128
22 Oct
S
126
26 Oct
S
127
28 Oct
S
127
3 Nov
S
126
5 Nov
S
128
11 Nov
S
126
20 Nov
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(ITEM 5A LOX - DELETED)
ITEM 6A LN2
Rating; Acft # Date Remarks
S
128
7 Oct
S
126
12 Oct
S
128
13 Oct
S
128
20 Oct
S
127
21 Oct
S
128
22 Oct
S
126
26 Oct
S
127
28 Oct
S
127
3 Nov
S
126
5 Nov
S
128
11 Nov
S
126
20 Nov
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ITEM 7A
TACAN
Rating Acft # Date Remarks
S
128
7 Oct
S
126
12 Oct
U
128
13 Oct
TACAN Inop due to faulty circuit
breaker.
S
128
20 Oct
S
127
21 Oct
S
128
22 Oct
U
126
26 Oct
TACAN failed in flight. Faulty
BHDI (DME stuck) and TACAN unit
itself (fuse blown).
S
127
28 Oct
U
127
3 Nov
40? right on Ch 57. Marginal
TACAN unit.
S
126
5 Nov
S
128
11 Nov
S
126
20 Nov
13
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ITEM 8A
IFF
Rating Acft # Date Remarks
S
128
7 Oct
S
126
12 Oct
S
128
13 Oct
S
128
20 Oct
U
127
21 Oct
IFF completely Inop - cause
unknown.
S
128
22 Oct
S
126
26 Oct
S
127
28 Oct
S
127
3 Nov
S
126
5 Nov
S
128
11 Nov
S
126
20 Nov
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ITEM 9A
AFT FUEL FEED & TRANSFER
Rating Acft # Date Remarks
S
128
7 Oct
S
126
12 Oct
S
128
13 Oct
S
128
20 Oct
S
127
21 Oct
S
128
22 Oct
S
126
26 Oct
S
127
28 Oct
S
127
3 Nov
S
126
5 Nov
S
128
11 Nov
S
126
20 Nov
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SR-3 COMPASS
Rating Acft # Date
S
128
7 Oct
S
126
12 Oct
S
128
13 Oct
S
128
20 Oct
S
127
21 Oct
S
128
22 Oct
U
126
26 Oct
Slaved Gyro would not hold sync.
Comp card fluctuated +2?.
S
127
28 Oct
S
127
3 Nov
S
126
5 Nov
S
128
11 Nov
S
126
20 Nov
16
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Rating
Acft #
Date
Remarks
U
128
7 Oct
RH oil pressure erratic then
dropped to zero. RH low quantity
lite came on. Found to be indicat-
ing system in both cases. Oil
quantity serviced 6.5 Qts low after
4:30 flight.
S
126
12 Oct
U
128
13 Oct
Oil pressure below 55 psi in flight.
RH low lite came on. Low warning
deactivated per letter.
S
128
20 Oct
S
127
21 Oct
U
128
22 Oct
RH oil pressure went to 0 on final.
30-32 psi in flight. Pressure
transmitter problem.
U
126
26 Oct
Oil pressure erratic RH side. Ex-
cessive oil consumption (17 qts in
5:30). Engine changed.
S
128
28 Oct
S
127
3 Nov
S
126
5 Nov
S
128
11 Nov
S
126
20 Nov
17
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ITEM 12A
ALL ATTITUDE FUEL READOUT
Rating
Acft #
Date
Remarks
S
128
7 Oct
S
126
12 Oct
S
128
13 Oct
S
128
20 Oct
S
127
21 Oct
S
128
22 Oct
Fuel Ind. fluctuated 1
Tito 5 M #o Duplicated
Small wiring problem.
time
on
ground -
S
126
26 Oct
S
127
28 Oct
S
127
3 Nov
S
126
5 Nov
S
128
11 Nov.
S
126
20 Nov
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ITEM 13A
FIRE WARNING
Rating Acft # Date Remarks
S
128
7 Oct
S
126
12 Oct
S
128
13 Oct
S
128
20 Oct
S
127
21 Oct
S
128
22 Oct
S
126
26 Oct
S
127
28 Oct
S
127
3 Nov
S
126
5 Nov
S
128
11 Nov
S
126
20 Nov
19
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ITEM 14A
ENGINE DURABILITY
Rating
Acft #
Date
Remarks
S
128
7 Oct
U
126
12 Oct
LH engine exhaust heat shield
failed.
S
128
13 Oct
S
128
20 Oct
S
127
21 Oct
S
128
22 Oct
U
126
26 Oct
Excessive oil consumption, RH.
S
127
28 Oct
S
127
3 Nov
S
126
5 Nov
S
128
11 Nov
S
126
20 Nov
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ITEM 15A
SC & DM SWITCHING
Rating Acft # Date Remarks
S
128
7 Oct
S
126
12 Oct
S
128
13 Oct
S
127
21 Oct
S
128
22 Oct
S
126
26 Oct
S
127
28 Oct
S
127
3 Nov
S
128
11 Nov
S
126
20 Nov
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ITEM 16A
Rating
Acft #
Date
Remarks
S
128
7 Oct
S
126
12 Oct
S
128
13 Oct
S
127
21 Oct
S
128
22 Oct
U
126
26 Oct
Erroneous chirps such as cabin
pressure failure.
S
127
28 Oct
S
127
3 Nov
S
126
5 Nov
S
128
11 Nov
S
126
20 Nov
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ITEM 17A
DECM
Rating Acft # Date Remarks
S 128 7 Oct
S 126 12 Oct
S 128 13 Oct
S 127 21 Oct OK on 1st run. Acft not acquired
by radar on 2nd run.
S 128 22 Oct
U 126 26 Oct OK on 1st run, Inop on 2nd run.
Replaced antenaeo
U 127 28 Oct
correlation. did not see
ground emissi
]not triggered by proper
U 126 20 Nov DECM ineffective.
NOTE: No DECM installed on two
missions.
23
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ITEM 18A
Rating
Aeft #
Date Remarks
S
128
7 Oct
S
126
12 Oct
S
128
13 Oct
S
127
21 Oct
S
128
22 Oct
S
126
26 Oct
S
127
28 Oct
24
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ITEM 19A
ARC-50
Rating Acft # Date Remarks
U
128
7 Oct
U
126
12 Oct
U
128
13 Oct
U
128
20 Oct
S
127
21 Oct
U
128
22 Oct
U
126
26 Oct
U
127
28 Oct
U
127
3 Nov
U
126
5 Nov
S
128
11 Nov
U
126
20 Nov
DME erratic. Receiver weak.
Ext failed completely for 3rd
rendezvous.
Ext DME Inop.
Air abort due to ARC-50 failure.
No ADF antenna. Ext interrogate
would.not stay in continuous for
more than 4-5 cycles.
Ext DME failed after 1st AR.
Ext DME Inop.
Ext DME & Voice failed after 1st AR.
Ext failed after lst ARe
Entire X-MTR ARC-50 failed after
T.O. Air abort.
No ADF.
No ADF. Erratic DME.
NOTE: If other functions were
normal, ARC-50 was consider-
ed satisfactory with ADF
failure or ADF antenna not
installed.
25
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Rating
Acft #
ITEM 20A
INS COMPATIBILITY W/ECM
Date Remarks
S
128
7 Oct
S
126
12 Oct
S
128
13 Oct
S
127
21, Oct
S
128
22 Oct
S
126
26 Oct
S
127
28 Oct
S
126
20 Nov
26
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ITEM 21A
PLASTICS
Rating Acft # Date Remarks
S
128
7 Oct
S
126
12 Oct
S
128
13 Oct
S
127
21. Oct
S
128
22 Oct
S
126
26 Oct
S
127
28 Oct
S
127
3 Nov
S
128
11 Nov
S
126
20 Nov
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Rating,
Acft #
(ITEM 22A - MACH HOLD - DELETED)
ITEM 23A
SSB
Date Remarks
S
128
7 Oct
S
126
12 Oct
S
128
13 Oct
S
127
21 Oct
S
128
22 Oct
S
126
26 Oct
S
127
28 Oct
S
127
3 Nov
S
126
5 Nov
S
128
11 Nov
S
126
20 Nov
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a 1W
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ITEM 24A
Rating
Acft
Date
S
128
7 Oct
Type I
S
126
12 Oct
Type II
U
128
13 Oct
Type I.
Malfunction lite, last leg.
Material tension regulator
problem.
S
127
21 Oct
Type II
S
128
22 Oct
Type I.
Ran out of material toward
end of last leg.
S
126
26 Oct
Type II
S
127
28 Oct
Type II
S
127
3 Nov
Type I
S
128
11 Nov
Type II
S
126
20 Nov
Type I
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 P,&00600130003-7
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(ITEM 25A - CLIMATIC - COMPLETED)
ITEM 26A
INS
Rating
Acft #
Date
Remarks
S
128
7 Oct
U
126
12 Oct
1.1 Times spec error.
S
128
13 Oct
U
127
21 Oct
1.6 Spec error.
S
128
22 Oct
U
126
26 Oct
19 mile error.
S
127
28 Oct
Bank angle went to 50?
turn - cause unknown.
on
one
S
127
3 Nov
S
126
5 Nov
Short flight.
S
128
11 Nov
S
126
20 Nov
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 0600130003-7
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SECRET
TOP
COMPLETE WEAPON SYSTEM TEST
Route Rating Aeft # Date
S
127
3 Nov
No ECM. ARC-50 Ext failed
after lst A/R. TACAN
Marginal.
U
126
5 Nov
Air abort due to ARC-50
failure.
S
128
11 Nov
No ECM. No ARC-50 ADF.
S
126.
20 Nov
ECM Inop.
NOTE: These missions were considered
satisfactory although ECM was
not installed or malfunctioned.
31
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TS i(~ 2 6 29
3 ~ 3 Y
1 i ~
Aooroved For Release 2006/08109 ? (',IA-RI7P71 R0039c)RnC1C1AQQ1'iC1QQ3-7
 Approved For Ruse 2006/08/09: CIA-RDP71 B00399F 00600130003-7
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DISTRIBUTION LIST
Agency
1129th USAF Sp Actys Sq, Det 1
Commander
Copies
1129th. USAF Sp Actys,Sq
Project Headquarters
Other
32
TOP SECRET
fis #%62ba p
Approved For Release 2006/0R/09 - c IA-RI7P71 R0O39GR0006f 0l *10 lfl`1-7