single engine presentation faa ia burbank ca 2008 a

MD 500E MD 530F MD 520N MD 600N MD EXPLORER

John M. KerrField Service RepresentativeMD Helicopters Inc. (602) 284-7479 [email protected]


Courtesy: BOEING AH-6 light attack/reconnaissance helicopter.


Courtesy: BOEING UAV Unmanned Little Bird (ULB)


SUBJECTS TO BE COVERED MDHI WEB HOME PAGE AFTER HOURS NUMBERS USING ON LINE MANUALS SERVICE AND OPERATIONS REPORT SERVICE LETTERS SERVICE BULLETINS TECHNICAL BULLETINS AIRWORTHINESS DIRECTIVES PART NUMBER CROSS REFERENCE TORQUE EVENTS CALCULATING RETIREMENT INDEX NUMBER (RIN) HTC-MDHI MAIN ROTOR BLADES TECHNICAL NUTS & BOLTS NOW PROJECTS


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FLEET DATA COLLECTION


TB600N-007 Fuselage Aft Section and Tailboom Modification

30, 65%

16, 35%

Due Completed

Aircraft CompletedAircraft Not Completed


SERVICE LETTERS


SERVICE BULLETINS


• ONE TIME INSPECTION OF THE OIL COOLER BLOWER BELT (Issued 12 May 2008

)– SB369H-248– SB369D-205– SB369E-100– SB369F-085– SB500N-039

• TENSION TORSION STRAP REPLACEMENT (Issued 09 July 2008 )

– SB500N029R3– SB600N046R3

• DE-ENERGIZE YSAS AND REPLACE YSAS ADAPTER ( Issued 27 August 2008 )

– SB500N-040R1– SB600N-047R1

SERVICE BULLETINS


369H5648 / 369D25623 Oil Cooler Belts


500N5311-5 Tension Torsion Strap

The tension − torsion straps have a 5 year calendar life that starts the day the package is opened.


YSAS Adapter 500N7218-1


TECHNICAL BULLETINS


’08 AIRWORTHINESS DIRECTIVES


2008-20-05 Effective date: 10/27/08 ( Supersedes AD 2006-08-12, AD 2008-05-17 ) Model 600N

This AD requires compliance within the next 24 months, unless accomplished previously, to prevent failure of the tail boom attachment fittings, separation of the tail boom from the helicopter, and subsequent loss of control of the helicopter fuselage aft section.

Adds 25 and 100 hour inspection intervals until compliance of modification to

strengthen the tail boom attach fittings and upper longerons by following instructions, of MDHI TB600N-007R2.


2008-18-52 Effective date: Upon Receipt ( Supersedes AD 2008-18-51 ) Model 520N 600N 900N

Due to un-commanded yaw, caused by broken YSAS adapter. This AD requires de-energization of the Yaw Stability Augmentation System (YSAS) by pulling circuit breakers and installing a placard on the instrument panel. Airspeed reduced to 100 knots. Original configuration returned by replacing with new adapters manufactured after

8/15/08


PART NUMBER CROSS REFERENCE


MAIN ROTOR BLADE PART NUMBER CROSS REFERENCE

MDHI/HTC PMA REPLACES MODEL/TYPE

369D21123-503 500P2100-303 369A1100-511 369HS369D21120-503 500P2100-103 369D21100-523 369D/E 369D21121-

503 (1)500P2300-503 369D21102-517 FF/N/600

369D21122-501

500P2500-501 369D21102-523 FF/N/600

NOTES:(1) 369D21121-503 REPLACES 369D21122-501


MDHI/ HTC PMA REPLACES MODEL/TYPE369D21640-501 500P3100-101

(1)369D21613-61 369D/E 2-BLADE

T/R369D21640-503 500P3100-101

(2)369D21640-503 500P3100-101

(3)369D21640-505 500P3100-103

(4)369D21640-507 500P3100-103

(5)

369D21641-501 500P3100-301 (1)

369D21615-31 369D/E 4-BLADE T/R

369D21641-503 500P3100-301 (2)

369D21641-503 500P3100-301 (3)

369D21641-505 500P3100-303 (4)

369D21641-507 500P3100-303 (5)

369D21642-501 500P3500-701 (1)

369D21606-511 369FF

369D21642-503 500P3500-701 (2)

369D21642-503 500P3500-701 (3)

369D21642-505 500P3500-703 (4)

369D21642-507 500P3500-703 (5)

TAIL ROTOR BLADE PART NUMBER COMPARISON


TAIL ROTOR BLADE PART NUMBER COMPARISON

NOTES: 1. W/O “M” Not shot-peened 2. W/ “M” Shot-peened 3. Eddy Current Inspected, Machined Radius and shot-peened 4. No pocket & shot-peened 5. Titanium rivet installed in abrasion strip. “T” on blade root. HTC blade serial numbers

B472 & Subsequent

369D21643-501 500P3300-501 (1)

369A1613-507 369A/H/E/M/S

369D21643-503 500P3300-501 (2)

369D21643-503 500P3300-501 (3)

369D21643-505 500P3300-503 (4)

369D21643-507 500P3300-503 (5)

MDHI / HTC PMA REPLACESMODEL/TYPE


TORQUE EVENTS


TORQUE EVENT/ RETIREMENT INDEX NUMBER EXPLANATION

SL369H-132R1

SL369D-111R1

SL369E-063R1

SL369F-056R1

SL500N-008R1

SL600N-005R1


TORQUE EVENT (TE)

A TE is defined as the transition to a hover from forward flight or any external lift operation.

For this definition of TE, forward flight is considered to be flight at any airspeed in any direction after attaining transitional lift.

It has been determined that a TE accelerates fatigue damage on certain components.


TORQUE EVENT (TE)

Components are assigned retirement lives based upon flight test, fatigue test and field experience.

Components effected by TE’s will no longer have retirement lives or inspection intervals based solely on TIS (Time in Service).

Components that are effected by TE’s will have an inspection interval based on TE and/or be assigned a maximum Retirement Index Number ( RIN). This RIN corresponds to the maximum allowed fatigue damage resulting from Torque Events and accumulated flight hours.


TORQUE EVENT (TE)

For sling operations, each load will count as two (2) TE (pick-up and drop-off).

Hover taxi with no external lift will typically result in no TE’s.

Example: An operator taking off and moves six (6) sling loads then

lands. This would total twelve (12) TE’s. Thirteen (13) TE’s if the helicopter drops off the last load and then flies to another landing.

Autorotation from forward flight to a landing or a hover is one (1) TE.

Components that are affected by TE will have an inspection interval based on TE.


TORQUE EVENT (TE)

• How do I calculate my torque events if the torque events are unknown ???

– For non-cargo hook operations use: 6 torque events per hour if the number is unknown.

– For cargo hook operations use: 20 torque events per hour if the number is unknown.


TORQUE EVENT (TE)

TR06-001 Temp. Rev. to the 04-00-00 Airworthiness Limitations.

Main Rotor Drive Shaft 369F5510.

Effective on 369D/E/FF & 500N. No more retirement hours. RETIREMENT INDEX NUMBER (RIN) Retirement &

Inspection.


CALCULATING RETIREMENT INDEX NUMBER (RIN)


RETIREMENT INDEX NUMBER (RIN)


RINS (RETIREMENT INDEX NUMBER)

Example: 369F5510 driveshaft with 5000 TSNRIN= (Factor 1 x Flt. Hours ) + ( Factor 2 x Total TE’s )RIN= (29 x Flt. Hours) + (1 x Total TE’s)

Calculate TE’s 10 TE's per hour (operator determined) 10 TE’s x component time (5000 hrs.) = 50,000 TE’s

Calculate RINs 29 x 5000 = 145,000 + (1 x 50,000 TE’s) = 50,000 TE’s 145,000 + 50,000 = 195,000 RINS 195,000 RINs (just under 1/5 of the 1 million RINs)


RINS (RETIREMENT INDEX NUMBER)

Summary

Component Life Adjusted to Type of Operation = Increased Life

Reduced Direct Operating Cost (DOC)


TECHNICAL NUT & BOLTS


CAUTION:

When adjusting Main Rotor System for Track and Balance.

Ensure positive control of the cyclic and collective

controls to avoid inadvertent loss of control and / or damage to the aircraft and personnel.

Track and Balance of Main Rotor Blades


TRACK AND BALANCE FIRST FLIGHT SET

• Collective loading: Set blade trim tab angle• Autorotation: Set with PC Links• Continue with flight tracking• Balance with weights to the hub• Trim Tab Tool MDHI vs. Chadwick 2 degree

variation• Off-setting M/R Blades from high to low track

reduces stick shake• Clean / Waxed blades improves performance


SAMPLE SUPPLEMENTAL TYPE CERTIFICATES FOR 2007-2008

• SH1861SO Installation of external cargo rack and work platform between the skid gears. Amended 05/27/2008

• SH3195NM Installation of generator kit No. 369-100. Reissued 06/27/2008

• SH5230NM Installation of side pull hook assembly. Amended 06/24/2008

• SH5813NM Installation of WECO Aerospace Systems, Inc. generator cooling kit and increase the maximum Reissued 06/27/2008

http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgSTC.nsf/0/C2DCFB6939263A978625748200713CE4?OpenDocument

http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgSTC.nsf/0/57C097456A5AA274862574820063054B?OpenDocument

http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgSTC.nsf/0/3341CB8B885A7008862574790079E2C2?OpenDocument

http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgSTC.nsf/0/E036CA3041EFF3F98625748200630485?OpenDocument


SAMPLE SUPPLEMENTAL TYPE CERTIFICATES FOR 2007-2008

• SR00376DE Installation of laser mapping system. Amended 06/30/2008

• SR00407SE Fabrication of Onboard Systems Model 200-187-00 cargo hook kit Amended 05/14/2008

• SR01614NY-D Installation of an Airborne Workstation. Amended 05/27/2008

• SR09074RC Installation of a replacement main rotor blade. Amended 07/18/2008

• SR09526RC Installation of Night Vision Imaging System (NVIS) / Night Vision Goggles (NVG) Cockpit Lighting. Issued 08/25/2008

http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgSTC.nsf/0/86BF8C1BB6D3611486257480007AB6E7?OpenDocument

http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgSTC.nsf/0/43E5F8F2D4D61F5E8625745C00757CDA?OpenDocument

http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgSTC.nsf/0/A648AF76A25015C886257488007034CE?OpenDocument

http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/9583DB8CDD4412CF862574C600722452?OpenDocument

http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/30745ADDF449A593862574BF007D6DE5?OpenDocument


Preliminary Technical Bulletin for Auto Re-Ignition PURPOSE

The purpose of this optional Technical Bulletin is to eliminate the requirement for the pilot having to manually reset the (XDS9) auto re-ignition (RE-IGN) indicator light after engine re-ignition. With this modification, the RE-IGN indicator light is automatically reset after engine restart. This modification can also be used to eliminate problems encountered with defective switches in the XDS9 assembly whose replacements are not available.


• Figure 1• XDS9 SWITCH ASSEMBLY

Figure 1.XDS9 SWITCH ASSEMBLY


Preliminary Technical Bulletin for Auto Re-Ignition APPLICABILITY This modification is only applicable to models 369H / 369D helicopters that have the 369H90118 Automatic Engine Re-ignition kit installed.

There are basically two configurations for the XDS9 switch

assembly. The early systems have an ARM switch and the

later systems are automatically armed and have a TEST switch (no ARM switch).


369D21120 M/R Blade

Lead edge abrasion strip


Droop Stop Ring - yielding of plating causing cyclic stick grab


500N5310-19 Fan Blade

Bulge

Any bulges or blisters over 0.10 inch(2.54 mm) long in area of pin near

outboard end of blade are reason forblade rejection


500N5310-19 Fan Blade

Bulge


500N3761-1 / CEKP3AR11-2

Flat Spot


K3LR48-E / CEKP3AR11-2

Flat Spot


500N9701-13 Yaw SAS / VSCS Test Box


500N9701-13 Yaw SAS / VSCS Test Box Re ID’d


Measure distance between bearings in fork.

Measure distance each bearing protrudes from inner surface of fork.Determine shim thickness as required to make each bearing protrude equally (temporarily mark the side requiring the shim with an “S”)

Measure Hub outside Dimension.

Subtract dimension B from A.

Subtract 1.123 inch from B

Take the difference between 1.123 and

Dimension E equals shim thickness to make hub mounting face equal distance from centerline of hub. If D is larger than 1.123 inch temporarily mark bushed side of hub with a U. If 1.123 inch is larger than D temporarily mark unbushed side of hub with a U.

If H is greater than E then subtract E from H

If E is greater than H then subtract H from E

Enter I or J in Shim table.

Subtract I or J from C Dimension F= total clearance thickness after centering hub and bearings for preload.

Determine shim thickness required to ensure preload:

F minus .098 inch divided by 2 = G

Orient hub in fork so that S and U are together on the same side.

Add up columns in Table and install shims as required.

B

A

C

H

DE

IJ

F

G

S = Small Step Side

U = Widest HUB Side

Shim Thickness Required

GJG

ITotal =

“S” & “U” marked Unmarked

=

Actual Dim.

Formula Dim.

Shim Dim.


Measure distance between bearings in fork.

Measure distance each bearing protrudes from inner surface of fork.Determine shim thickness as required to make each bearing protrude equally (temporarily mark the side requiring the shim with an “S”)

Measure Hub outside Dimension.

Subtract dimension B from A.

Subtract 1.123 inch from B

Take the difference between 1.123 and D

Dimension E equals shim thickness to make hub mounting face equal distance from centerline of hub. If D is larger than 1.123 inch temporarily mark bushed side of hub with a U. If 1.123 inch is larger than D temporarily mark unbushed side of hub with a U.

If H is greater than E then subtract E from H

If E is greater than H then subtract H from E

Enter I or J in Shim table.

Subtract I or J from C Dimension F= total clearance thickness after centering hub and bearings for preload.

Determine shim thickness required to ensure preload:

F minus .098 inch divided by 2 = G

Orient hub in fork so that S and U are together on the same side.

Add up columns in Table and install shims as required.

B

A

C

H

D

2.4055

2.2195

.1860

1.0965.0265

.0100

.0165

.1695

.03575

E

IJ

F

G

S = Small Step Side

U = Widest HUB Side

Shim Thickness Required

GJG

ITotal =

“S” & “U” marked Unmarked

.03575 .03575.01650

= .05225.03575

Actual Dim.

Formula Dim.

Shim Dim.


A

.018.008 DifferenceH

Protrusion

2.4055 Inner Fork

H H

GS UG JC C

CTotal Clearance

E1.1230

2.2460 perfect hub

2.2195 actualB

1.0965D

Total Shims

HUB

FORK


3.646 Bolt Before Torque (REF)

GS

G JC C

369A1602-3 BOLT

3.654 Bolt Stretched (REF)

Bolt must stretch .008 to .011

MS21206C4BEVEL WASHER

369A1605-5 .015369A1605-7 .062NAS620C416L .033

MS24665-153COTTER PIN

VCU0001 orSPS79325–428NUT

2 HOLES90 DEGREES OUT


TEETER STOP

SPLIT RING

TANG WASHER

TAPERED RING


B

A

C

H

DE

IJ

F

G

A

.018.008 DifferenceH

Protrusion

2.4055 Inner Fork

H H

GS UG JC C

CTotal Clearance

E1.1230

2.2460 perfect hub

2.2195 actualB

1.0965D

Total Shims

G


NOW !!! Projects

• Competitive Pricing / and Superior Warranty compared to PMA parts, XMSN & Major Airframe Components

• MDHI Power Program covers Airframe and Rolls-Royce Engine.

• Revisionary governor for 600N 4th Quarter 2008.

• New Seals for T/R gearbox and Overrunning clutch.


Courtesy: Dillon Aero


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THANK YOU !!!

YOU ARE THE REASON FOR OUR SUCCESS

single engine presentation faa ia burbank ca 2008 a

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