SERVICE BULLETIN 71-3638.pdfSB 71-3638. 2 of 13 910027-3 RH rear engine mount fitting is damaged beyond allowable limits. Rework is accomplished to install the P/N 35-910003-85 engine

SERVICE BULLETIN

MANDATORY

Beech

1. Planning Information

A. Effectivity

(1) Airplanes

Raytheon Aircraft Model A36 Bonanza, Serials E-3471 through E-3508, E-3510, E-3512, and E-3514.

If you are no longer in possession of the airplane, please forward this information to the presentowner.

(2) Spares

None.

B. Reason

This Service Bulletin is being issued to inspect the aft (rear) engine mount isolators for the presence of a P/N 35-910003-85 engine mount (heat) shroud. If the P/N 35-910003-85 engine mount shroud is installedat the right aft mount fitting location, it may chafe on the cast aluminum RH rear engine mount fitting due toa difference in geometry between the left and right mounts. Such chafing could eventually lead to fractureof the right aft engine mount and further structural damage to the airplane. The P/N 35-910003-85 enginemount shroud is required only at the left aft engine mount isolator location to protect the engine mountisolator from exhaust system heat degradation.

C. Description

The aft (rear) engine mount isolators are inspected for correct location of the P/N 35-910003-85 enginemount (heat) shroud. If a P/N 35-910003-85 engine mount shroud is installed at the right aft engine mountisolator location, it is removed for possible reinstallation on the LH side. The P/N 35-910027-3 RH rearengine mount fitting is inspected for damage. If damaged, the RH rear engine mount fitting may bedressed out, if the fitting is within allowable damage limits. Replacement is required only if the P/N 35-

TITLE: POWER PLANT - ENGINE MOUNT HEAT SHROUD INSPECTION/REWORK

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Raytheon Aircraft Company (RAC) issues Service Information for the benefit of owners andfixed base operators in the form of two classes of Service Bulletins. The first class, MandatoryService Bulletins (red border) includes changes, inspections and modifications that couldaffect safety or crashworthiness. RAC also issues Service Bulletins with no red border whichare designated as either recommended or optional in the compliance section within thebulletin. In the case of recommended Service Bulletins, RAC feels the changes,modifications, improvements or inspections will benefit the owner/operator and althoughhighly recommended, Recommended Service Bulletins are not considered mandatory at thetime of issuance. In the case of Optional Service Bulletins, compliance with the changes,modifications, improvements or inspections is at the owner/operator’s discretion.

Both classes are mailed to:(a) RAC Authorized Service Centers.(b) Owners of record on the FAA Aircraft Registration Branch List and the RAC

International Owner Notification/Registration Service List.(c) Those having a publications subscription.

Information on Owner Notification Service or subscription can be obtained through any RAC Authorized Service Center. As Mandatory Service Bulletins and Service Bulletins are issued, temporary notification in the Service Bulletin Master Index should be made until the index is revised. Warranty will be allowed only when specifically defined in the Service Bulletin and in accordance with the RAC Warranty Policy.Unless otherwise designated, RAC Mandatory Service Bulletins, Service Bulletins and RAC Kits are approved for installation on RAC airplanes in original or RAC modified configurationsonly. RAC Mandatory Service Bulletins, Service Bulletins and Kits may not be compatible withairplanes modified by STC installations or modifications other than RAC approved kits.

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MANDATORY

SERVICE BULLETIN

D. Compliance

An Airworthiness Directive will be requested on the matter covered by this Service Bulletin.

Raytheon Aircraft Company considers this to be a mandatory modification and it must be accomplished atthe next scheduled inspection after receipt of this Service Bulletin, but no later than the next 100 flighthours or 12 months, whichever occurs first.

E. Approval

The engineering data contained in this Service Bulletin is FAA approved.

F. Manpower

The following information is for planning purposes only:

Estimated man-hours for relocation of engine mount shroud to LH side: 3 hours.

Estimated man-hours for RH rear engine mount fitting replacement: 6 hours.

Estimated man-hours for blend, fluorescent penetrant inspection, and paint rework: 1.5 hours.

Suggested number of men: 1 man.

The above is an estimate based on experienced, properly equipped personnel complying with this ServiceBulletin. Occasionally, after work has started, conditions may be found which could result in additionalman-hours.

G. Weight and Balance

None.

H. Electrical Load Data

Not changed.

I. Software Accomplishment Summary

Not applicable.

J. References

Raytheon Aircraft BEECH BONANZA SERIES Maintenance Manual, P/N 36-590001-9A24 or subsequentrevision, Chapters 20-01 and 71-10.

K. Publications Affected

It is recommended that a note “See Service Bulletin No. 71-3638” be made in the following:

Raytheon Aircraft BEECH BONANZA Illustrated Parts Catalog, P/N 36-590001-1G16 or subsequentrevision, Functional Group 240.

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MANDATORY

L. Interchangeability of Parts

Not applicable.

M. Warranty Credit

Warranty credit for labor and parts to the extent noted under MANPOWER and MATERIAL will be allowedon all affected airplanes.

Warranty coverage offered in this Service Bulletin will expire 12 months from the last day of the month thisService Bulletin is issued. After that date, the owner/operator assumes the responsibility for compliancecost. Raytheon Aircraft Company reserves the right to void warranty coverage in the area affected by thisService Bulletin until the date the Service Bulletin is accomplished by a Raytheon Aircraft CompanyAuthorized Service Center.

All warranty work must be accomplished by a Raytheon Aircraft Authorized Service Center rated toperform maintenance on the specific model of Beech Airplane.

All warranty reimbursements are handled through Raytheon Aircraft Company Authorized Service Centers.The owner/operator should arrange for an Authorized Service Center to perform the work and theAuthorized Service Center must submit the standard Raytheon Aircraft Company warranty claim.

2. Material Information

A. Materials - Price and Availability

Contact a Raytheon Aircraft Authorized Service Center for information.

B. Industry Support

Not applicable.

C. Airplanes

The following parts required for this modification may be ordered through a Raytheon AircraftAuthorized Service Center or RAPID:

Raytheon Aircraft Company expressly reserves the right to supersede, cancel and/or declareobsolete, without prior notice, any parts or publications that may be referenced in this ServiceBulletin.

Part Number DescriptionQuantity Per

Airplane

35-910003-85 Shroud, Engine Mount 1, As Required

35-910027-3 Fitting, Rear Engine Mount, RH 1, As Required

130909N3 Nut 2, As Required

79-028-125-1250 orMS171536

Roll Pin (CRES spring pin, 0.125-inch diameter,1.25-inch long)

1, As Required

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Part Number DescriptionQuantity Per

Airplane

TT-N-95, Type II Aliphatic Naphtha As Required

TT-I-735A or equivalent Isopropyl Alcohol As Required

ASTM D329 or equivalent Acetone As Required

MIL-DTL-81706 inaccordance with MIL-C-5541 (Alodine 1200, 1200S,or 1201 or equivalent)

Chemical Conversion Coating for Aluminumand Aluminum Alloys

As Required

CCC-C-C-440, A-A-1491 orequivalent

Cotton Cheesecloth As Required

DOD-R-003081 orequivalent

Rags As Required

Obtain from BartonSolvents, 201 S. Cedar,Valley Center, KS 67147 orEastman ChemicalProducts, Inc., P.O. Box431, Kingsport, TN 37662

Methyl Propyl Ketone As Required

A-A-53513 or equivalent orP/N 187 7711 (Obtain fromEastman Kodak Company,343 State Street, Rochester,NY 14650)

Gloves, Polyethylene, Industrial, SolventHandling

As Required

MIL-PRF-121, Grade A,Type II, Class 1 orequivalent

Barrier Material, Grease and Water Proof,Flexible

As Required

SAE AMS-T-22085, Type IIIor equivalent

Tape, Pressure Sensitive Adhesive (Masking) As Required

MIL-PRF-85285 or 560-025(P/N of Pratt & Lambert) or570-535-QT (P/N of SherwinWilliams) or equivalent

Paint, Touchup (Matterhorn White, FED-STD-595 or equivalent to match existing RH aftengine mount fitting finish)

As Required

MIL-P-23377 Epoxy Polyamide Primer As Required

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D. Spares

Not applicable.

E. Reidentified Parts

None.

F. Tooling - Price and Availability

3. Accomplishment Instructions

This Service Bulletin shall be accomplished as follows:

NOTEShould any difficulty be encountered in accomplishing this Service Bulletin,contact Raytheon Aircraft Company at 1-800-429-5372 or 316-676-3140.

Blue Twill Medium Grit -#150, Fine Grit - #320, andExtra Fine - #400 Grit orequivalent

Emery Cloth As Required

A-A-58054 or Scotchbrite orequivalent

Abrasive Mat or Pad As Required

Part Number DescriptionQuantity Per

Airplane

GGG-C-105 or equivalent Digital Micrometer As Required

MIL-I-18422 or equivalent Depth Gage, Indicator Dial As Required

Zyglo #700085 orequivalent (Obtain fromTest EquipmentDistributors, Division of X-Ray Industries, Inc., 1370-T Piedmont, Troy, MI48083-6298, Telephone248.524.1900 or Newco,Inc., Florence, SC,Telephone1.800.545.9729)

Fluorescent Penetrant Kit 1, As Required

Part Number DescriptionQuantity Per

Airplane

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Observe all Warnings and Cautions contained in the aircraft manualsreferenced in this Service Bulletin.

Whenever any part of this system is dismantled, adjusted, repaired orrenewed, detailed investigation must be made on completion to make surethat distortion, tools, rags or any other loose articles or foreign matter thatcould impede the free movement and safe operation of the system are notpresent, and that the systems and installations in the work area are clean.

INSPECTION OF ENGINE MOUNT SHROUD LOCATION

(1) Open the left and right engine cowlings to gain access to the aft engine mounts.

(2) Refer to Figure 1 and inspect for presence of a P/N 35-910003-85 engine mount shroud at the left aft(rear) engine mount isolator location. An engine mount (heat) shroud is required at this location.

(3) Refer to Figure 1 and inspect the right aft engine mount isolator location. Verify that a P/N 35-910003-85 heat shroud is not installed at the right side location. An engine mount shroud is notrequired and is not to be installed in this location.

(4) If inspection reveals that a P/N 35-910003-85 engine mount shroud is correctly installed inaccordance with Figure 1 at the left aft engine mount isolator location and no engine mount shroud isinstalled at the right aft engine mount isolator location, proceed to steps (22) through (24) for closeup.

(5) If inspection reveals an incorrect installation, proceed to the following applicable steps to determinethe damage scope and disposition.

REMOVAL OF RH AFT ENGINE MOUNT SHROUD AND INSPECTION FOR ENGINE MOUNT DAMAGE

(6) Remove all power from the airplane and disconnect the battery. Display warning notices prohibitingreconnection of airplane electrical power.

Any time the P/N 130909B8 bolt is removed, the bolt removal may affectorientation of one or both of the engine mount isolator halves. Check the enginemount isolator to roll pin alignment for proper orientation (clocking). Spacer androll pin alignment and proper clocking are critical to proper installation of theengine mount isolators. When properly clocked, the roll pin installed in the P/N 35-910027-3 engine mount fitting inserts into a matching hole in the P/N J-10520-1engine isolator mounting kit. Replace the roll pin if it is damaged with a P/N 79-028-125-1250 or MS171536 roll pin.

(7) Refer to Figure 1 and remove the P/N 130909B8 bolt (right side), that secures the P/N 35-910003-85engine mount shroud at the right aft engine mount isolator location. Retain the bolt and washer forreinstallation in step (10). Discard the (nonreusable nylon insert) nut.

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(8) Remove the P/N 35-910003-85 engine mount shroud from the right aft engine mount isolatorlocation and retain the shroud for reinstallation at the left aft engine mount location.

(9) Inspect the P/N 35-910027-3 RH rear engine mount fitting for damage. Damage is defined as wear,scratches, gouges, and nicks. Damage may be degradation of the protective corrosion preventivepainted finish or the underlying metal and its manufacturer-applied protective treatment.

• If no damage is present, accomplish step (10), then steps (18) through (24).

• If damage is greater than 0.10-inch depth, replacement of the RH rear engine mount fitting is

required. Proceed to step (11).

• If damage is 0.10 inch or less in depth, accomplish step (10), skip step (11) and proceed to step

(12) for engine mount fitting dress out, cleaning, and touch up and shroud relocation.

(10) Using a new P/N 130909N3 nut and retained washer, reinstall the existing P/N 130909B8 boltretained from step (7) to secure the RH engine isolator mount. Torque to 300-350 inch-pounds. Referto Chapter 20-01 of the airplane Maintenance Manual.

REPLACEMENT OF DAMAGED RH AFT ENGINE MOUNT

(11) Replace the P/N 35-910027-3 RH rear engine mount fitting in accordance with the following:

Support the engine during RH rear engine mount fitting replacement. Damage toengine and structural components could result.

(a) Remove both upper cowling doors. Refer to Chapter 71-10 of the airplane Maintenance Manual.

(b) Use a suitable hoist to secure the engine during RH rear engine mount fitting removal.

NOTEMake note of the length and location of each rear engine mount fitting bolt and thenumber and location of washers to aid in installation of the replacement P/N 35-910027-3 RH rear engine mount fitting.

(c) Remove and retain attaching hardware securing the RH rear engine mount fitting.

(d) Remove and discard the damaged RH rear engine mount fitting.

(e) Obtain replacement P/N 35-910027-3 RH rear engine mount fitting and press or drive a new P/N79-028-125-1250 or MS171536 roll pin through the fitting such that the roll pin protrudes equallyon both sides of the engine mount fitting. Assemble the top half of the engine mount isolator tothe engine mount fitting. Install to airplane structure using attachment hardware retained fromremoval procedures. Torque to 50-70 inch-pounds. Refer to Chapter 20-01 of the airplaneMaintenance Manual.

Do not cross-thread or force the bolt if it binds. Adjust alignment slightly and retry.Damage to the bolt and engine mount isolator could occur.

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the engine mount isolator to the engine mount fitting, then install P/N 130909B8 bolt at the rightaft engine mount isolator location to secure the engine mount. Torque to 300-350 inch-pounds.Refer to Chapter 20-01 of the airplane Maintenance Manual.

NOTEAt the installer’s option, it may be desirable to wait until all required installationoperations are complete before removing the hoist and installing upper cowlingdoors.

(g) Remove the hoist and install upper cowling doors. Refer to Chapter 71-10 of the airplaneMaintenance Manual.

(h) Skip steps (12) through (17), and proceed to steps (18) through (24).

REPAIR OF DAMAGE TO RH AFT ENGINE MOUNT

(12) Accomplish dress out, cleaning, and touch up of the P/N 35-910027-3 RH rear engine mount fittingin accordance with the following:

(a) Use progressively finer emery cloth to remove damage (wear, scratches, gouges, and nicks) upto a depth of 0.10 inch. Maintain a blend ratio or dress out ratio of 10:1 for parts with damageless than 0.10 inch depth. Do not remove any more material than necessary to remove alldamage. Refer to locally obtained materials section of MATERIAL INFORMATION for abrasivematerial information.

Solvents are flammable and hazardous. Avoid contact with skin, eyes, andrespiratory tract. Skin and eye protection is required. Avoid repeated orprolonged contact. Keep away from flames or sources of heat. Use in a well-ventilated area.

(b) Wipe up sanding debris with clean rags or CCC-C-440 clean cotton cheesecloth moistened witha suitable solvent (TT-N-95, Type II aliphatic naphtha, ASTM D239 acetone, TT-I-735A isopropylalcohol, or methyl propyl ketone).

All personnel performing the Fluorescent Penetrant Inspection must becertified Nondestructive Test Personnel that have obtained applicabletraining on the equipment and method being used.

(c) Perform a final cleaning prior to Fluorescent Penetrant Inspection in accordance with thefollowing:

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Solvents are flammable and hazardous. Avoid contact with skin, eyes, andrespiratory tract. Skin and eye protection is required. Avoid repeated orprolonged contact. Keep away from flames or sources of heat. Use in a well-ventilated area.

(i) Clean the inspection area with suitable solvent (TT-N-95, Type II aliphatic naphtha, ASTM

D239 acetone, TT-I-735A isopropyl alcohol, or methyl propyl ketone) and CCC-C-440

clean cotton cheesecloth to remove grime, oily films, and other contaminants. Use

nonmetallic, non-woven A-A-58054 (Scotchbrite or equivalent) abrasive pads and TT-N-

95, Type II aliphatic naphtha or equivalent solvent to remove tough foreign contaminants

such as grease, oil, water-based grime, mud, etc. Wipe the surface dry with clean cotton

cheesecloth. Repeat cleaning procedures until a waterbreak-free surface is achieved.

NOTEMany Class 2 solvent removers will not rapidly evaporate at room temperature.Make sure no residual solvent is on the fitting surface prior to application ofpenetrant. This can be accomplished by thoroughly drying the surface with cleancotton cheesecloth or clean rags, alternately using a more volatile solvent such asisopropyl alcohol to remove the less volatile solvent remover.

(d) Perform a Fluorescent Penetrant Inspection of the P/N 35-910027-3 RH rear engine mount fittingfor cracks in accordance with procedures specified in Part Number 700085 Zyglo FluorescentPenetrant Inspection Kit or equivalent.

(e) If cracks are still present, repeat steps (12)(a) through (12)(d) as many times as necessary untilthe cracks are removed without exceeding damage limits. Recheck for cracks using FluorescentPenetrant Inspection methods in accordance with step (12) (d). If cracks cannot be removedwithout exceeding the damage limits of step (9), then replace the damaged engine mount inaccordance with step (11).

(13) Accomplish masking and final cleaning procedures in preparation for touchup painting, inaccordance with the following:

Use care to protect adjacent areas and avoid dripping or overspray ontosurrounding engine surfaces and adjacent components. If required, protect workareas from drips or overspray.

(a) Mask off the rework area using MIL-PRF-121 barrier material and SAE AMS-T-22085 maskingtape.

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Solvents are flammable and toxic to skin, eyes, and respiratory tract. Avoideye and repeated skin contact. Use in a well-ventilated area. Keep away fromsparks and flames.

(b) Clean the rework area with suitable solvent (TT-N-95, Type II aliphatic naphtha, ASTM D239acetone, TT-I-735A isopropyl alcohol, or methyl propyl ketone) and CCC-C-440 clean cottoncheesecloth to remove grime, oily films, and other contaminants. Use nonmetallic, non-wovenA-A-58054 (Scotchbrite or equivalent) abrasive pads and TT-N-95, Type II aliphatic naphtha orequivalent solvent to remove tough foreign contaminants such as grease, oil, water-based grime,mud, etc. Wipe the surface dry with clean cotton cheesecloth. Repeat cleaning procedures untila waterbreak-free surface is achieved.

Chemical conversion coating (Alodine) may affect skin, eyes, andrespiratory tract. Chemical goggles and neoprene gloves should be worn.Use in a well-ventilated area.

(c) Apply Alodine 1200, 1200S, or 1201 (MIL-DTL-81706 in accordance with MIL-C-5541) ChemicalConversion Coating to the dressed out areas that were reworked (bare metal surfaces). Allowthe Alodine to dwell for approximately five minutes. After the dwell time has elapsed, wash thetreated area with water, and blot away water with clean cotton cheesecloth or blow dry (do notwipe dry).

Many paints, primers, and top coatings are flammable and toxic to skin,eyes and respiratory tract. Eye, skin, and respiratory protection is required.

(d) After Alodine 1200, 1200S, or 1201 (MIL-DTL-81706 in accordance with MIL-C-5541) ChemicalConversion Coating has dried, apply a coat of MIL-P-23377 Epoxy Polyamide Primer orequivalent primer to the rework area. Allow adequate drying time.

(14) Accomplish touchup painting procedures, applying Matterhorn White touchup paint (FED-STD-595or equivalent) over the primer coat to match existing top coat paint.

(15) Allow adequate paint drying time. Drying time is normally at least 24 hours under normaltemperature conditions. As an alternate method, use a blow dryer to force air dry the area for 1.5hours at 125 degrees Fahrenheit.

(16) Remove barrier material and masking tape.

(17) Clean up around the paint touchup area.

INSTALLATION OF LH AFT ENGINE MOUNT SHROUD

(18) If the inspection of step (2) found the engine mount shroud missing from the left aft engine mountisolator, refer to Figure 1 and remove existing P/N 130909B8 bolt at the left aft engine mount isolatorlocation.

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Damage to the rear engine mount fitting (casting) in the form of wear, scratches,gouges, and nicks could result if proper clearance is not maintained.

(19) Install the P/N 35-910003-85 engine mount shroud at the left aft location with the flange end up asshown in Figure 1. Use existing P/N 130909B8 bolt, P/N AN960-716 washer, and new P/N130909N3 nut mounting hardware. Torque to 300-350 inch-pounds. Refer to Chapter 20-01 of theairplane Maintenance Manual.

(20) Check for and ensure clearance exists between the P/N 35-910003-85 engine mount shroud and theP/N 35-910027-5 LH rear engine mount fitting.Proceed to steps (21) through (24) for close-upoperations to return the airplane to service.

RETURN TO SERVICE

(21) Reconnect the airplane battery, remove warning notices and restore power.

(22) Ensure all work areas are clean and clear of tools and miscellaneous items of equipment.

(23) Close the left and right engine cowlings that were opened to gain access to the aft engine mounts.

(24) Return airplane to service.

B. Spares

Not applicable.

C. Record of Compliance

Upon completion of this Service Bulletin, make an appropriate maintenance record entry.

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Engine Mount Shroud Installation

Figure 1

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RH Engine Mount Shroud Removal and RH Rear Engine Mount Fitting Inspection

Figure 2

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