BLACK SHIELD TECHNICAL MEETING (Sanitized) 12 AUGUST 1965.

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP71B00399R000600120017-3
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 26
• Document Creation Date: December 16, 2016
• Document Release Date: November 15, 2004
• Sequence Number: 17
• Publication Date: August 23, 1965
• Content Type: MFR

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23 AUG 1965
SUBJECT : BLACK SHIELD Technical Meeting
12 August 1965.
This report constitutes:
Part I
Part II
Attachment I
Attachment II
Attachment III
Attachment IV
- General Aircraft Items
- Propulsion Oriented Items;
- Agenda
- Decisions and Actions
- Aircraft Summary
- Engine Charts
Part I - Aircraft General:
1. Attention is called to Attachment II, Decisions and
Actions which summarize highlights of subject meeting.
2. With the exception of listing de-bug modification
service bulletins applicable to BLACK SHIELD aircraft and
presenting electrical and power transient mod status (charts
to be available in D/TECH), the LAC presentation focused on
management actions taken of Mr. Johnson's personal
in-house investigation at Burbank. This investi-
gation with its revealing findings was made possible by
Mr. Johnson's reorientation into OXCART matters at the expense
of other corporate responsibilities resulting from discussions
and agreements reached between the initiator, Mr. Parangosky
and Messrs Dan Haughton and Kelly Johnson.
3. Currentl.y._.al.L Lockheed effort is focused on the _
primary BLACK SHIELD aircraft 126, 127, and 128 in order
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that they be delivered to the detachment by 1 September.as
reliable weapon systems. Additional overtime effort is
needed and scheduled on aircraft 126 because of improperly
cured tank sealant in order to meet the 1 September delivery.
Nos. 127 and 128 were reported as out of trouble in,the
sealant area with a good chance of meeting the 1 September
delivery.
4. A brief report bj
122 tests showed that the
shape.
R&D indicated that aircraft
PIP,programs were in good
SO%
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Aircra Systems ivision
Special Activities
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Part II - Propulsion:
1. A chart supported presentation of engine related
agenda items was given by Mr. Caleen and Mr. McDermott of
Pratt & Whitney. Copies of the more significant charts are
included with this report and copies of other engine charts
are available in D/TECH.
2. Recent flight experience with "frosty" Hamilton-
Standard fuel controls was reviewed. The fact that some
trimming will be required for BLACK SHIELD was repeated.
It is recommended that minimum trimming to near side of trim
band only be used and that further test flights in aircraft
122 be accomplished using this technique while recording EGT
and CIT with trace data. The effect on cruise SFC with variation
of EGT over trim band was quoted as an improvement of 2.5%
in. SFC as EGT increases from 755?C to 805?C.
3. A brief review of experience acquired with the
derichment device on article 129 was reviewed. Results to
date show a maximum temperature of 868?C for a period of less
than 10 seconds.
4. "Chugging" and "die out" problems on the ground with
engine 207 on the Scotch Mist exercise due to a defective
compressor bleed pilot valve were reviewed. This problem has
since been more thoroughly reviewed through phone calls and
a meeting at Pratt & Whitney in Florida on 17 August.
5. The number 3 bearing compartment oil leakage problem
was reviewed. One flight on article 129 was accomplished which
reported good pressure data. It now appears that this data
agrees with seal pressures calculated at FRDC. It is hoped
that the testing now being accomplished on J engine 316 at
FRDC might result in a simple field operable fix to the problem..
A change to the no. 3 compartment already instituted in later
J engines may result in some tendency to reduce oil leakage
through seals in this compartment during windmilling conditions.
General expected levels of in-flight oil consumption were
reviewed. The amount of oil which would be'consumed before
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warning lights flicker etc. is 3.2 gal. For flights of
approximately three hours duration, oil consumption rates
should not exceed one quart per hour. As shown on one of
the attached charts for flights longer than three hours in
duration, average hourly oil consumption rates are less than
one quart per hour.
6. The problem of burning holes in burner cans, especially
in the cross-over tube area between cans as experienced in
engines 215 and 233 was reviewed. Engine no. 233 with 9 hours,
10 minutes of Mach 3 time was the first engine to approach the
10 hour limit of Mach 3 flight time between hot section
inspections. This engine had some history of overtemperatures
experienced in-flight but these were not considered at the
time. It is hoped that J cans will realize some improvement.
Five Y engines are now equipped with J cans, three sets are
being installed and deliveries will continue until all Y
engines are equipped with J cans in early 1966. It appears
that this experience may "put a crimp in the effort" to
increase Mach 3 hot section time beyond 10 hours, at least
for Y cans. It is hoped that the J cans will provide some
improvement. Engine 242 with J cans is now installed in the
left side of article 129 and will soon be due for hot section
inspection.
7. The gearbox bearing problem was reviewed and the
modifications to the gearbox which will eliminate the gearbox
vibration check on future overhaul and production engines were
delineated.
8. The various engine wiring problems were discussed.
These problems were also discussed in complete detail by
D/TECH personnel during the visit to West Palm Beach on
17 August. A list of these wiring areas is as follows:
a. Thermocouple harness nut retention.
b. Tachometer cable connectors.
c. Wiring and connectors to trimmer motor.
d. General P&W experience with Bendix high temperature
connectors, methods of attaching, etc.
e. Supports for wiring and connectors so excessive
lengths of unsupported wire do not exist.
f. Jumper cable extension for right hand engine.
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9. One case of compressor first stage blade root
cracking on a shimmed blade has been discovered to'date.
This discovery was made at overhaul on a blade from engine
241. This engine had experienced 14 cycles to Mach 3. This
blade had been reworked for adaptation of the shim and had
therefore had .020" of material milled from the root,including
the original root surface plating. The instrumentation program
on engine 226 to investigate blade stresses and boundary layer
airflow at the engine face was reviewed. This program was
also reviewed in detail at the FRDC meeting on 17 August.
10. Priority engine flight test items were reviewed and
a list of these are included on an attached chart. However,
due to disagreements in priorities this list will be revised
by P&W and a copy forwarded to Headquarters.
11. Other miscellaneous engine developments were discussed
including the following:
a. Engine relight experience with the Bill of
Material 50 cc and the reduced 25 cc TEB shots.
b. Mach 3 flight time by months.
c. Ice ingestion tests on J58 engine.
12- It appears that the detachment especially Col.
J may offer some resistance to use of the new AAR
technique whereby one engine is left in A/B and throttle
adjustments are made only on the other engine which operates
below military power. It appears that there is some misunder-
standing as to the exact procedure used by LAC pilots. The
exact procedure being used by the LAC pilots and the weights
of aircraft during recent successful refuelings with the new
technique will be reviewed with the detachment. Due to the
apparent success of the new technique it appears that every
effort should be made to encourage the detachment to use it.
13. Engine associated action items are listed in the
attached action item list.
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14. P&W representatives present at the meeting were:
SIGNED
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Aircraft Systems Division
Special Activities
SECRET
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25X1 ASD/OSA
Distribution:
Cy 1,2,3 - ASD/OSA
4 - D/FA/OSA
5 - OXC/OSA
6 - D/OSA
7 - MD/OSA
8 - PS/OSA
9 - C&FE/OSA
10 - CD/OSA
11 - D/TECH/OSA
12 - chrono
13 - RB/OSA
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1(20 August 1965)
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AIRFRAME AGENDA ITEMS
A. Debug Mod program and progress.
B. Preliminary results, if any, of all weather mods as
result of SCOTCH MIST.
C. Replacement of tank sealant.
D. Outstanding items/systems not contemplated for,BLACK
SHIELD aircraft.
E. SB915 - isolation of ARC-50 induced power transients.
F. SB931 - Suppression of power transient effects on the
INS.
G. Aircraft 129 recommended test schedule priorities in
support of BLACK SHIELD and others.
H.. Is electrical connectors and wire debugging to encompass
areas beyond inlet control critical areas? If so, what
are Mods and S/B numbers.
I.. Plastic and other critical spares for BLACK SHIELD
deployment.
J. Big brakes.
K. Configuration freeze
L. Smoke in cockpit.
M. Electrical problem experiences encountered in Lac area
for possible dissemination to sub, or other, contractors.
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ENGINE AGENDA ITEMS
1. "Frosty" fuel control/EGT trim experience, and status
to date.
Derichment device experience, status, review of selected
EGT for automatic activation.
Modified TEB ignition relight experience. Progress of
tests to redefine relight envelope especially on a cold
windmilling engine. Possible effect of new AAR.technique
on required number of shots.
4. Third bearing compartment, results of recent #129
instrumented flights, FRDC testing results, relation
to BLACK SHIELD single engine testing, etc. Review of
normal oil consumption rates (i.e., expected rate of
oil consumption under average flight conditions on a
quart per hour basis.)
Inspection results of engines #215 and #233, burner can
burning problems, relation to installation effects,
relation to current HSI and overhaul time intervals and
possible improvements. Expected improvement with "J"
cans and availability of these units.
6. Recent roughness tests conducted on Article #122.
7. Engine main gear box status, inspection results,
8. Engine related aspects of recent recurring reports of
"Smoke in the cockpit".
Review of proposed BLACK SHIELD priority engine flight
test items and schedule for Articles #122 and #129.
10. Review of solutions to problem of retaining nuts on
EGT thermocouple harness.
11. Review of first stage compressor blade situation.
Results of analysis, if available, of shimmed blade
recently discovered to have root crack at overhaul.
Review of delivery schedule for 30 additional sets of
waspalloy blades, and program for installing these
sets in, engines.
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 Att. II to
OXC-9140-65
DECISIONS AND ACTIONS
B. Additional aircraft 129 major flight test priorities
(not in order) to include additional Silver Javelins (high
altitude, low KEAS) range improvement, one engine out performance
as soon as engine windmilling restriction lifted, other BLACK
SHIELD specifics on pacing schedule, and investigation current
BLACK SHIELD pacing flight problems as required.
A. Aircraft 129 to be scheduled for multiple refueling
Scotch Mist/Silver Javelin route range flight prior Scotch
' , C: --Aircraft 122 to perform small number additional
25X1 production ests prior to engine instrumentation
switchover. Engine program immediately following ECM or con-
currently where feasible to include Frosty fuel control EGT
operating band limits confirmation tests with recommended
manual trim procedure in addition to other BLACK SHIELD and
engine specifics.
D. Aircraft 132, to perform Hycon, PE and EK camera and
MH family tests as time permits prior modification.
E. Aircraft 121 to perform engine compressor blade
strain gage survey tests as s in as feasible and prior to
scheduled 34K engine performane\ confirmation.
25X1
F. All OXCART-contractors including" and Comm-NAV
suppliers to be briefed asap by, Kelly Johnson on LAC BLACK
SHIELD management/technical acceleration improvement program
In addition, stress to be placed on quick reaction
capability to problems, quick feedback test results, cross
polinization techniques, and concurrent actions for problem
resolution.
G. Voice,recorder destruct, heretofore a BLACK SHIELD
go-no go requirement, because of technical problems will not
be finalized prior deployment and mission procedural changes
will be made in the use of the recorder prior destruct availability.
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H. Four outstanding previously coordinated details of the
design freeze will be finalized between LAC
and Headquarters communications.
I. Installed imin of increased capacity brakes to be
coordinated between LAC.
J. Detailed information will be supplied to Detachment
by LAC delineating AAR procedure with one engine in afterburner
and adjusting thrust with other engine. This information
should include experience acquired from recent Silver Javelin
and Scotch Mist flights with data on weights of A-12 aircraft,
amount of fuel onloaded, etc. at each refueling.
K. P&W will provide at General Ledford's request a paper
delineating management response and procedures being enacted
to intensify effort to improve the general level of engine
reliability for BLACK SHIELD.
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3.1 Xl-kCH AIRCRAFT & SYSTEMS
RELIABILITY VALIDATION
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DEMONSTRATE 3.1-
RELIABILITY. -
MINIMUM OF 2 FLTS
NON' REFUELED.
MINIMUM OF 2 FLTS
WITH REFUELING.
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BASIC ENGINE STATUS
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MAIN FUEL CONTROL STATUS
Jan.
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 Approved For Release 2004/11/29 :
FUEL DERICHMENT SYSTEM STATUS
Article -'Flight Altitude Mn Max. T
5 Time at Max T
Time Over 805`C
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129
133L
129
134L
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1 34R
83K 3.08 868'C 7. 5 Sec. Z9 Seca
81. 5K 3. 13 864'C 10 Sec. 15 Sec.
81. 5K 3,13 865'C 6 Sec. 1 1 Sec.
Delivery Schedule:
6 Engine Sets.on Service Test No. 39
2 Engine Sets Delivered for Engines for Article 2001
28 Engine Sets to be Shipped August 20, 1965
Retrofit Engineering Change 172058K Being lasued - Parts Schedule Not Yet Available.
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Jan
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"J" Afterburner Aacembliea for "Y" Engines - - Delivery Statue
July Aug
Approved For Malease 20041 '4
Sept Oct
Dec Jan Feb
1966
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 ENGINE FLIGHT TEST PROGRAMS
1. Evaluation of 34K Engine
2. Investigation of Compressor Blade Root Cracking
3. High Altitude. High Mn Fuel - Oil Heat Rejection Program
4. Breather Pressure. Chamber 4 Pressure, Nacelle Pressure Investigation
5. Fuel Control System Programs
6. Altitude Relight Envelope Program (Main Engine and A/B)
7. Establish Engine and A/B Blowout Limits.
8. Evaluation of Fixes for A/B Liner Distress
9. Evaluation of Improved Flame Pattern A/B
10. Miscellaneous Tests and Evaluations
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Plate St ckup
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