1000 HOUR INSPECTION ON U-2 343

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP81B00878R000600010029-9
• Release Decision: RIPPUB
• Original Classification: K
• Document Page Count: 3
• Document Creation Date: December 12, 2016
• Document Release Date: February 12, 2002
• Sequence Number: 29
• Content Type: REPORT

Approved For Release 2002/06/13: CIA-RDP81 B0087 D006000
E;UBJECT: 10U0 Hour Inspection on U?Z 343
The first U-2 tc approach 1000 hours was inspected at EAFB by LAC
personnel. Airplane serial nuriber was 343, flight time wss 991 hours and
s
, June 191.
20 rz-Anutes. The inspection was completed
25X1A
First flight .,n the airplane was made 27 October 1955. From thi3 time
until ::?arch 1957 the primary use of the airplane was pilot training
In March 1.957 an undershoot landing involving tearing out u: the rna n
gear wa experienced. After major repairs the airplane was assigned as a
test vehicle at . :A F:3.
General conditior. of the airplane at the start of the inspection appeared
good. There was no sign of corrosion ac had been noted on other atr, lanes
with less tim e. Absence of corrosion was attributed to two things. First, the
air. plane had never been polished or b& fed. Second, it had never been on the
ground any place but Burbank, EAFB, spending rcwst of it time
in the dry climate at the latter two. 25X1 A
Numerr.aus components were artibrarily replaced due to flight time or
calendar date, at the recornmendati=gin of their manufacturers. These items
are as follows:
Standby Compass
R/ C Indicator
;Al Pressure Indicator
?adio Cornpass Indicator
c.< Bay A1tirneter
M. L. G. Position Indicator
Tachometer
D. C. Loadmeter
H, Day Clock
M. L. G. Actuating Cylinder
M. L. G. Strut Assembly
T.L.G. Actuating Cylinder
T.L.G. Wheel
L. H. Brake Assembly (2)
Flap - Jack Screws (1t)
Right Wing Flap Hydro Motor
Aileron Tab Actuator
Elevator Tab Actuator
Check Valves .(L. H. Wing)(2)
Fuel Level Valves in Sump (4)
i,. H. Low Level Switch in Sump
Access Air Shutoff Valve
boost Pump Hydro Motor
Hydro Filter
eirigerator bypass Valve
Ram Air Shutoff Valve
uel Totalizer
Hydro Pressure Indicator
Fuel Pressure Indicator
Ships Altimeter
Wing Flap Pus. Indicator
Tai; Gear Position Inducator
Pressure Ratio Indicator
Elapsed Time Clock
M. L. G. Drag Strut
M. L. G. Uplock Cylinder
T.L.G. Drag Strut
r. L. G. Strut Assembly
Brake Master Cylinder
R. H. Brake Assembly (s)
Left Wing Flap Hydro 'Motor
Dive Brake Selector Valve
Aileron Gust Control Actuator
Suction Relief - check Valves (4)
Pilot Fuel Shutoff Valves in Sump Tank(4)
R. H. Low Level switch in Sump
Elect. Fuel Shutoff Valve at Engine
Access Air Pressure Regulator
Hydro Press. Regulator - Reservoir
Airflow Regulator
Refrigerator
,/P Safety Valve
Approved For Release 2002/06/13 : CIA-RDP81 B00878R000600010029-9
 Approved For Release 2002/06/13: CIA-1466130087C000600010029-9
1000 Hour Inspection on U Z 343 (cont. )
Filter - Water Separator *_'xygeen Regulator Shutoff twitch
e)xygex. Indicator D. C. Voltage Regulator
A. C. Voltage Regulator Reverse Current Relay
Fire Detector Ther:rj.o ",-,itches Injrtia ;cel
Lngine ,P607373
All of the auove components were still in working order when removed
for replacement. Some high consutrnption items had been replaced several
times during the airplane Life, but many of the original components were
removed at ti.?s inspection.
The following components were removed for failure or damage:
\ia..h Control A1.rnplif er
R. H. i.aading Light
Universal Joints (Flap:) (3) - Worn.
L. H. Dive f4rake Actuating Cylinder - Leaking.
R. H. Dive Brake Actuating Cylinder - Leaking.
R. H. Elevator Ta., - Warped.
Elevator Torque Tube Scratched.
i'uei Nines (i13-It.) Da!r,aged by Flea= Lines.
2'uel Line (H3-I7) - Barraged by Fles- Lines.
Hydro Pressure Lime - Leaking.
Defroster Fan - Damaged blades.
Ge-Leratcor Blast Flex Roue - Deteriorated.
Nose Cover Assembly - Glass was cracking, finish was peeling.
Scme of these items mead been noted as damaged earlier but replacement
delayed until the major inspection.
The airframe was carefully inspected for cracks, (.upped rivets, et(-.
It was r.ecessary to replace the forward inboard and outboard inner skins of
the L. H. air duct due to cracks. The R. H. duct had been. similarly repaired
200 hours before. Thin airplane was one of the early serial numbers which
had . 032 75ST duct skins. Beginning with serial 355 the duct skins were made
from . 040 24S T to eliminate the cracking. Some r-".}ets in the fuselage skin
over the living were replaced due to cupping.
The entire electrical systessi was inspected. To accomplish this it was
necessary to remove the ~:: bay tibreglaas liner which is peculiar to only the
"i.:" airplanes. All wiring was in good condition and no replacement was
necessary. -
Both landing, gears were replaced, The main gear appeared to be in good
condition but no facilitieb were readily available for zygic inspection. In the
interest of time it was decided to install a new one and send the old one in for
overnaul. The tail gear was badly worn in all the joints and replacement was
warranted.
Approved For Release 2002/06/13 : CIA-RDP81 B00878R000600010029-9
 Approved For Release 2002/06/13 : O --RDP81 B00878R900600010029-9
1000 HL;ur Inspection on the U- 2 343 (cr)nt. )
The wing flap system required repla:ement of the outboard guide
screws. The ttereads were pitted and the Electrof ni pIrtting was worn off.
The 1; Jack screw actuators were replaced due to lack of imbrication.
Prior to the inspection a. creaking had been noticed in the wings
when they were wa?' . ' upon. All wing removable panels were removed and
the structure carefully inspected for cracks or loose parts. Each wing had
one place where an upper and lower rib flange were rubbing. Tlie flanges
were Tent slightly to allow clearance. Nothing else could be found wrong
with the structure. The tank sealing compound had some cracks showing
but they had not been leaking. Cracked areas were painted over with Thiakol.
The wing tanks were quit: clean as compared to some other wings that had
been opened up. After the tank panels were reinstalled considerable trodblc
was experienced resealing them. It is felt that on future 1000 hour inspections
the panels need not be removed f=r structural inspection. Removal of the
suction relief valve panels allows an opportunity for cleanliness inspection.
Approved For Release 2002/06/13 : CIA-RDP81 B00878R000600010029-9