Specifications

RotorWay International
Exec 162F Maintenance Manual
7
Rev. 1 10/01
Section 1: Airframe
The airframe is constructed of various size tubes consisting of geometric shapes which will allow the airframe to flex at key
areas during operation and still maintain a high structural integrity. The tubing is aircraft industry standard 4130 chrome-
moly. Where tubing requires bending, a mandrel bender is used and tubes are scribed, cut, and coped to a tolerance of
.062 inch. The oxygen acetylene gas method of welding is used and all weldments are air cooled to retain the original
strength of the alloy.
Reference prints: E10-2000, E13-2000
SERVICE NOTES:
1. Remove all inspection panels including the two upper panels that are held on by nut plates. Using a flashlight or a
suitable source of illumination and a mirror, inspect for cracks on the round and square tubes, paying close attention
to the welded areas. If a small hairline crack appears, remove the paint from the airframe at that position to further
verify the crack. It may be necessary to apply a pressure or load in such a manner as to help open up the crack to
verify. If close inspection verifies the crack, contact the factory for further assistance. If verification is negative, repaint
the suspect area and reassemble.
2. Remove skid pants. Inspect the rear landing gear, gear gusset, the area 6 inches above and below the landing gear
step, and the rear landing gear attachment bracket. These are critical inspection areas. Approximately 80% of the total
aircraft weight is transferred on the rear gear. After inspection, reinstall the skid pants.
The rear landing gear may spread with age or after a hard landing. The gear should be replaced if the distance
between rear landing gear shoes, measured inside, is greater than 62 inches.
3. Removal of the two rear lower fiberglass body panels (part no. E32-7130 and E32-7140) will allow you access for a
visual inspection of the Engine Mount Rubber Ring, part no. E13-3121. This part must be kept clean from oil and
grease. Allowing the part to become contaminated will deteriorate the rubber over a short period of time, changing the
alignment of the secondary to engine height. If in question, check secondary and engine alignment. The tolerance is
plus or minus 1/8". Refer to the engine installation section of the Construction Manual for further assistance.
4. Because the helicopter can be operated in many different terrains and will experience a variety of landing conditions,
the landing gear skid will remain an on-condition inspection item. Lift the front skid off the ground approximately 10
inches and block it up with a 2x4 board. Look for a flat wear area across the bottom of the skid. If a flat area appears
and measures more than 1/2" in width, replace the skid tube. Keeping the helicopter in the upright condition, remove
the two (2) front skid shoe bolts (part no. E00-2414) on the right front skid shoe and drop the skid 3" below the shoe.
This will allow an inspection on top of the skid which is normally hidden by the shoe. Check the holes for an oblong
condition and for any cracks in the skid tube. Also, inspect the bolts for wear prior to reinstalling the skid on the landing
gear shoe.
INSPECTION CHART
PART NO.
E10-1001 EXEC 162F Airframe 100 HR 2000 HR/OC 1-1
E00-2415 AN4-24A (1/4 x 2-1/2) Bolt 100 HR 2000 HR/OC Torque
E00-2601 AN6-10A (3/8 x 1) Bolt 100 HR 2000 HR/OC Torque
E11-9010 Rear Landing Gear 100 HR 2000 HR/OC 1-2
E13-3121 Engine Mount Rubber Ring 50 HR 2000 HR/OC 1-3
E00-2507 AN5-10A (5/16 x 1) Bolt 100 HR 2000 HR/OC Torque
E11-3130 Landing Gear Skid (Pilot) 500 HR 2000 HR/OC 1-4
E11-3131 Landing Gear Skid (Passenger) 500 HR 2000 HR/OC 1-4
DESCRIPTION
SERVICE
REFERENCE
INSPECTION
INTERVAL
R.C.O.