# ~111111111111111. ALERT SERVICE

# BULLETIN~~ Bell ellcopter No. 430-07-39 A Subsidiary of Textron Inc
. DATE JAN 

### 09, 2007 1 ofS

# ~ IDATE

REV

MODEL AFFECTED:
SUBJECT:

HELICOPTERS AFFECTED:

COMPLIANCE:

DESCRIPTION: PAGE

430
TAIL ROTOR PITCH CHANGE MECHANISM, REVISED RIGGING PROCEDURES

Model 430 helicopters serial number 49001 through 49122 [Model 430 helicopters serial number 49123 and subsequent will have the intent of this bulletin accomplished prior to delivery.] At the next 150 hour or Annual inspection but no later than Dec. 31 , 2007

It has come to the attention of Bell Helicopter Textron that due to parts tolerance buildup , the existing rigging procedures for the tail rotor pitch change mechanism can create a condition in which the position of the tail rotor counterweight bellcranks may not be at their optimized position to assist the flight crew with the tail rotor pedal forces in an emergency type operation with 

### # 1 hydraulic system inoperative. This bulletin introduces a one time verification of the tail rotor pitch change mechanism rigging and introduces new rigging procedures for the tail rotor pitch change mechanism. APPROVAL: The engineering design aspects of this bulletin are Transport Canada Civil Aviation (TCCA) approved.

IF OWNERSHIP OF AIRCRAFT HAS CHANGED PLEASE FORWARD TO NEW OWNER

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### ASB 430-07-39 Page 2 of 8 MANPOWER: Approximately 2
.0 man-hours are required to complete this bulletin
. Man-hours are based on hands-on time, and may vary with personnel and facilities available
. Manhour estimates do not include the man-hours required to replace the tail rotor yoke if it is determined that it requires replacement. 

### WARRANTY: Owner 

### I Operators who have performed the inspection of the tail rotor hub outlined in this bulletin and could not achieve optimized positioning of the tail rotor counterweight bellcranks should order a replacement yoke part number 222-012-702-117. They will receive a pro-rated warranty credit based on a 5000 hour life limited part. If the lockplates part number 222-012-733-001 and 222-012-738-001 are required, 100% warranty credit will be allowed for the lockplates listed in the required material section of this ASB. 

### To Receive This Credit: Order a replacement tail rotor yoke part number 222-012-702-117 from an approved Bell Helicopter Supply Source, submit a warranty claim, and a pro-rated warranty will be issued based on a 5000 hour life limited part. The yoke removed from service will have to be returned to Bell. The returned yoke will be inspected at Bell. If the yoke can not be reworked , the original warranty credit will be rescinded and the discrepant yoke will be returned to the customer at their expense in "as is condition
." To be eligible for the credit mentioned above the ASB must be completed no later than 31 December 2007. There is no warranty credit for labor associated with this ASB. 

### MATERIAL: Required Material: The following material is required for the accomplishment of this bulletin and may be obtained through your Bell Helicopter Textron Supply Center

. 

### Part Number 222-012-733-001 222-012-738-001 222-012-702-117 

### Nomenclature Lockplate Lockplate Tail rotor yoke 

### Quantity As required (Note 1) As required (Note 1) As required (Note 1,2)-NOTE

### ASB 430-07-39 Page 3 of 8

1. Quantities to be determined by completing accomplishment instructions described below 2. Use with tail rotor blade P/N 222-016-001-139 only 

### Consumable Material: None required 

### SPECIAL TOOLS: None required 

### WEIGHT AND BALANCE: Not affected 

### ELECTRICAL LOAD DATA: Not affected 

### REFERENCES: BHT-430-MM-7 Maintenance Manual BHT-430-MM-7 Illustrated Parts Breakdown 

### T. B
. 430-06-41 

### PUBLICATIONS AFFECTED: BHT-430-MM -7 Maintenance Manual BHT-430-MM -7 Illustrated Parts Breakdown 

### ACCOMPLISHMENT INSTRUCTIONS: -NOTEIt is not required to verify the directional controls rig ging before complying with this bulletin. However if you suspect any discrepancy with the existing directional controls rigging, a verification of the directional controls rigging must be carried out before complying with this bulletin
. Hydraulic power is NOT required to verify the rigging of the tail rotor pitch change mechanism.ASB 430-07-39 Page 4 of 8 Any adjustment that may be carried out to the support (6) by turning nut (4) and nut (8) will not change or affect the existing tail rotor controls/blade angle rigging settings. 1. Move the tail rotor pedals as required and set the pitch change housing to obtain a 4.63 to 4.65 inches (117.6 to 118.1 mm) dimension as shown in Figure 1. Maintain this position. -NOTEThe lockplates (5 and 7) may remain in service if adjustment to nut (4) and nut (8) is required. However, re-bending/reusing any previously bent edge of the lockplates is not permitted. 2. Verify that the centerline of counterweight bellcranks, (12, Figure 2) are parallel with the centerline of the tail rotor gearbox output shaft. If the counterweight bellcranks (12) are parallel with the centerline of the tail rotor gearbox output shaft, proceed to step 3
. If the counterweight bellcranks (12) are not parallel with the centerline of the tail rotor gearbox output shaft, disconnect boot (9), pitch links (11) and counterweight links (1 0) as required. Straighten the bent edges of the lockplates (5 and 7) and adjust nut (4) and nut (8) to reposition support (6) until the counterweight bellcranks are parallel with the centerline of the tail rotor gearbox output shaft
. Hold the nut (8) in position and torque the nut (4) to 50 to 55 footpounds (68 to 75 Nm)

. Do not bend the edge of the lockplates (5 and 7) into the slots of nut (4 and 8) at this time. -NOTETail rotor yoke P/N 222-012-702-117 incorporates a larger cut-out area that will provide additional clearance with nut (4) while maintaining the correct position of the counterweight bellcranks (12). Tail rotor yoke P/N 222-012-702-117 can only be used with tail rotor blades P/N 222-016-001-139 which incorporate the improved feathering bearings per T.B. 430-06-41. 3. Move the tail rotor assembly through the full flap range (verify at both full flap positions). Verify if the tail rotor yoke touches the flapping stop (3) before it touches nut (4). If a gap exists between the tail rotor yoke and the flapping stop (3), replace the existing tail rotor yoke with yoke P/N 222-012-702-117. Notify BHT Product Support Engineering if yoke replacement is required.CAUTION ASB 430-07-39 Page 5 of 8

Do not use standard width feeler gauges to measure the referenced gap as these feeler gauges are too wide and they do not permit measuring gaps between mating parts that have a curvature. Wire type feeler gauges are best suited for this application. Due to possible variations in parts tolerances, the measured gap reference below shall be the smallest gap that is measured at any location between the tail rotor yoke and nut (4) when the tail rotor assembly is moved through the full flap range (verify at both full flap positions)

.-NOTEThere is no maximum limit on the gap that may exist between the tail rotor yoke and nut (4) when the pitch change housing is positioned as shown in figure 1 and the counterweight bellcranks (12) are parallel to the tail rotor gearbox output shaft. 4
. If there is no gap between the flapping stop (3) and the tail rotor yoke, verify if a 0.020 inch (0

.50 mm) wire type feeler gauge can be inserted between the tail rotor yoke and nut (4). If the smallest gap between the tail rotor yoke and nut (4) is 0.020 inch (0

.50 mm) or more, bend the edge of the lockplates (5 and 7) into the slots of nut (4 and 8). Connect boot (9), pitch links (11) and counterweight links (1 0) as required and proceed to step 6. -NOTEAdjusting nut (4) and nut (8) to obtain a 0.020 to 0
.030 inch (0.50 to 0.76 mm) gap between the tail rotor yoke and nut (4) will result in a minor misalignment of the counterweight bellcranks (12) in relation to the tail rotor gearbox output shaft
. A maximum misalignment of 1
.6 degrees of the counterweight bellcranks (12) in relation to the tail rotor gearbox output shaft is acceptab le when the pitch change housi ng is positioned as shown in fi gure 1. CAUTION Do not adjust nut (4) and nut (8) to obtain a gap of more than 0.030 inch (0.76 mm) between the tail rotor yoke and nut (4). This will result in misalignment of the counterweightASB 430-07-39 Page 6 of 8 bellcranks ( 12) beyond the permissible maximum lim it of 1.6 degrees (in relation to the tail rotor gearbox output shaft) when the pitch change housing is positioned as shown in figure 1. Th is is NOT acceptable. 5
. If the gap between the tail rotor yoke and nut (4) measures between 0
.000 and 0
.019 inch (0 to 0.48 mm), adjust nut (4) and nut (8) until a gap of 0.020 to 0
.030 inch (0.50 to 0.76 mm) maximum exists between the tail rotor yoke and nut (4). Hold the nut (8) in position and torque the nut (4) to 50 to 55 foot-pounds (68 to 75 Nm). Bend the edge of the lockplates (5 and 7) into the slots of the nut (4) and nut (8). Connect boot (9), pitch links (11) and counterweight links (1 0) as required
. 6. Examine and adjust the tail rotor pedal forces if any adjustments were carried out to support (6). Refer to BHT-430-MM -7, chapter 64-00-00
.

. 7. Annotate helicopter record s to reflect compliance with thi s bulletin
.

8. Insert the BHT-430-MM -7 Revision 14, dated 15 Dec. 2006 into the BHT-430-MM-7 manual.TAIL ROTOR GEARBOX NUT

# \

- \ r 

# I 

# )

I I 4.63 TO 4.65 IN
. (117
.6 TO 118
. 1 mm)

-I / ASB 430-07-39 Page 7 of 8

COUNTERWEIGHT BELLCRANK PITCH CHANGE HOUSING

RAM 06568
_002

Figure 1. Tail Rotor Pitch Change Mechanism (Position)ASB 430-07-39 Page 8 of 8



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# ~ DETAILA 

## @
SEE O DETAIL A

1. Lockplate 222-012-738-001 2. Nut 222-012-737-001 / 3
. Flapping stop 222-012-735-103 4. Nut 222-012-731-001 5
. Lockplate 222-012-733-001 6
. Support 222-012-730-003 7
. Lockplate 222-012-733-001 8. Nut 222-012-732-001 9
. Boot 222-012-758-001 10
. Counterweight link 222-012-711-ALL 11. T/R pitch link (all P/N) 12
. Counterweight bellcrank 222-012-727-ALL

RAM 06568_001 Figure 2
. Tail Rotor Pitch Change Mechanism