DATE 

ALERT SERVICE BULLETIN 

REVISION NOTICE 

AN APPROPRIATE ENTRY SHOULD BE MADE IN THE AIRCRAFT LOGBOOK UPON ACCOMPLISHMENT 

IF OWNERSHIP OF AIRCRAFT HAS CHANGED PLEASE FORWARD TO NEW OWNER

Jan 10, 2011 

TO: All Owners/Operators of 210 Helicopters

SUBJECT: REVISION “B” TO ALERT SERVICE BULLETIN 210-08-03, MAIN 

ROTOR BLADE P/N 210-015-001-101, INSPECTION OF. 

Revision “B” to this bulletin is being issued to change the inspection interval and 

procedure. Changes were made to the following paragraphs: “HELICOPTERS 

AFFECTED”, “COMPLIANCE” AND “ACCOMPLISHMENT INSTRUCTIONS”. 
NO. 

 

DATE 

PAGE 

 DATE 

 REV 

ALERT SERVICE BULLETIN 

AN APPROPRIATE ENTRY SHOULD BE MADE IN THE AIRCRAFT LOGBOOK UPON ACCOMPLISHMENT 

IF OWNERSHIP OF AIRCRAFT HAS CHANGED PLEASE FORWARD TO NEW OWNER

210-08-03 

Jan 10, 2010 Dec 22, 2008 

B 1 of 6 

MODEL AFFECTED: 210

SUBJECT: MAIN ROTOR BLADE P/N 210-015-001-101, 

INSPECTION OF. 

HELICOPTERS AFFECTED: Model 210 helicopters serial number 21001, 

21002, 21003 and 21004. 

 

COMPLIANCE: Within the next 25 hours after receipt of this bulletin and every 25 

hours of operation thereafter. 

DESCRIPTION: 

 

A model 212 Main Rotor Blade P/N 212-015-501-115 with approximately 1000 hours 

total time was recently returned to BHTI for evaluation. The blade was found cracked 

through the blade retention bolt hole at Blade Station 28.0 and another crack through 

the lower doublers at Blade Station 36.0. The main rotor blade contained a fatigue 

fractured grip plate, fatigue fractured doublers and a fatigue cracked spar on the 

bottom of the blade as a result of inadequate bond between the doublers and grip 

plate. Further analysis and investigation of two more blades with similar defects 

required the introduction of a recurring inspection of the Main Rotor Blade every 25 

hours of operation. Refer to Figures 1 for the inspection area and Figure 2 showing 

typical cracks. As the 210-015-001-101 Main Rotor Blade on the Model 210 is 

virtually the same as the reference 212 Main Rotor Blade, this bulletin also applies to 

the 210 Main Rotor Blade. 

APPROVAL: 

The engineering design aspects of this bulletin are FAA/DER approved. 

MANPOWER: 

Approximately 1.0 man-hour is required to complete this bulletin. Man-hours are 

based on hands-on time, and may vary with personnel and facilities available. 

B

B
ASB 210-08-03 

Page 2 of 6 

WARRANTY: 

There is no warranty provided for this bulletin. 

MATERIAL: 

Required Material: 

None required 

Consumable Material: 

The following material is required to accomplish this bulletin, but may not require 

ordering, depending on the operator’s consumable material stock levels. This material 

may be obtained through your Bell Helicopter Textron Supply Center.

Part Number Nomenclature Quantity Reference

 

MILC87936TY1 Cleaning Compound 1 liter C-318 

WD-40 

TT-1735 ISOPROPYL 

Preservative Oil 

Isopropyl Alcohol 

12 OZ 

As required 

C-125 

C-385 

SPECIAL TOOLS: 

None required 

WEIGHT AND BALANCE: 

Not affected 

ELECTRICAL LOAD DATA: 

Not affected 

REFERENCES: 

Bell Model 210 Illustrated Parts Breakdown 

Bell Model 210 Maintenance Manual 

Bell Model 210 Component Repair and Overhaul Manual 

B
ASB 210-08-03 

Page 3 of 6 

PUBLICATIONS AFFECTED: 

210 MM Maintenance Manual 

ACCOMPLISHMENT INSTRUCTIONS: 

1. Wash upper and lower Main Rotor Blade surfaces with a solution of cleaning 

compound (C-318) and water. Rinse thoroughly and wipe dry. 

-NOTEAccomplishment of this inspection does not require removal 

of the blades from the Main Rotor Hub. 

2. Inspect the Main Rotor Blade upper and lower grip plates and doublers for their 

entire length and chord width. Inspect for signs of cracks, corrosion and edge 

voids, paying particular attention to the bond lines between doublers, grip plates 

and skin. Hair line cracks in the paint finish should be suspect for possible 

cracks / voids. 

3. Wipe the area to be inspected with an alcohol-soaked cloth (C-385) and wipe 

dry with a clean cloth. 

NOTE 

Accomplish Step 4 of this ASB immediately after carrying 

out the above alcohol wipe. Any potential cracks in the 

bond lines between doublers or grip plates will indicated by 

the presence of excess alcohol bleeding out of an edge 

void. This excess alcohol in the void will appear as a dark 

line between the bond lines of the doublers. 

CAUTION 

Pay particular attention not to remove any parent material 

from the skin / doublers during sanding operation. 

4. Carry out a detailed visual inspection of the top and bottom inspection areas of 

the blade using a 3X-power magnifying glass and a strong light source. Check 

for evidence of a dark line between doublers, grip plates and skin with excess 

alcohol bleeding out of the possible edge voids. Any cracks in the finish must 

B

B

B
ASB 210-08-03 

Page 4 of 6 

be investigated further by removing paint in the affected areas (sand with 180-

220 grit paper in a spanwise direction) to determine if the grip plate / doublers 

are cracked or voided. Any crack in paint finish which follows grip plate / 

doubler outline may indicate a possible edge void. 

5. If cracks in grip plate / doublers are are found, the affected blade must be 

immediately removed from service. If no cracks are detected, continue with Step 6. 

CAUTION 

Pay particular attention not to remove any parent material 

from the skin / doublers during sanding operation. 

6. If edge voids between grip plate / doublers / skin are found, determine depth and 

length by using 0.0015 in. feeler gage. If edge voids are near outboard tip of grip 

plate / doublers, also carefully tap inspect suspect area. Refer to BHT-210-CR&O,

62-8 thru 62-10 for void repair limits and inspection/repair instructions. If no voids 

are detected, continue with Step 7. 

7. Refinish the sanded area as per BHT-210-CR&O. 

8. Following the inspection, apply a light coat of preservative oil (C-125) to all 

surfaces of blade. 

9. Annotate records to indicate findings and compliance with this bulletin. 

B

B
ASB 210-08-03 

Page 5 of 6 

Figure 1 

Inspection Area 

Station 

24.5 

Station 

85 
ASB 210-08-03 

Page 6 of 6 

Figure 2 

Crack Indications