CLASS I

SUBJECT:

SYNOPSIS OF CHANGE:

EFFECTIVITY:

REASON:

COMPLIANCE:

APPROVAL:

SERVICE INSTRUCTIONS NO. 0042-031, Rev. II

ATA Cock 53-40 Recurring Inspection

FUSELAGE - INSPECTION OF FORWARD WING AlTACH POINT

Service lnstructions rewritten in current format. Deleted requirement to remove the attach bolt for inspection. MATERIAL and ACCOMPLISHMENT INSTRUCTIONS revised to use improved current configuration parts. Closed serial effectivity of these Service lnstructions to exclude those airplanes which were manufactured with improved parts. Option is given to retrofit affected airplanes with improved parts.

PART I

BEECHCRAFT A23-19 and 19A, serials MB-1 through MB-321; 23, A23, A23A and 823, serials M-1 through M-1095; A23-24, serials MA-1 through MA-312, except those airplanes on which the new bracket, frame, doubler and spacer as specrfied under MATERIAL have all been installed.

PART II

BEECHCRAFT 19A, M19A and B19. serials MB-322 through MB-520; B19 Sport 150, serials MB-521 through MB-708, 823 and C23, serials M-1096 through M-1361; C23 Sundowner 180, serials hA-1362 through M-1576; A23-24 and A24, serials MA-313 through MA-368; A24R, serials MC-2 through MC-95; A24R and B24R, serials MC-96 through MC-282, except those airplanes on which the new bracket, frame, doubler and spacer as specified under MATERIAL have all been installed,

To inspect the forward wing attach frames and brackets for possible cracks and to provide a method for repair and replacement of cracked frames and brackets.

Beech Aircraft Corporation considers this to be a mandatory inspection and it should be accomplished as soon as possible after receipt of these Service Instructions, but no later than the next 100 hour, annual or progressive inspection, whichever occurs first; at each 100 hour, annual or progressive inspection thereafter for the visual inspection, and each 500 hours for the dye penetrant inspection after the accumulation of 2000 hours in service. Inspection per these Service lnstructions is no longer required on airplanes on which all new parts are installed as specified under MATERIAL.

FAA Approved - DOA CE-2.

Beech Arcraft Corporat~on Issues servlce ~nfomlat~on for the beneflt of owners BEECHCRAFT lnternat~onal Owner Not~f~catton Servlce Llst and f~xed base operators ~n the form of three classes of Serv~ce lnstruct~ons (c) Those hav~ng a publtcat~ons subscr~pt~on CLASS I (Red Border) are changes Inspections, and mod~ftcat~ons that could affect safety The factory considers compl~ance mandatory CLASS II (Green CLASS Ill (No Border) covers changes whlch are optlonal malfltenance alds. Border) covers changes mod~f~cattons ~mprovements or lnspect~ons the factory product Improvement k~ts and m~scellaneous servlce ~nformatlon CompllanCe IS feels w~ll benef~t the owner and although h~ghly recommended they are not at the owner or operators prerogative Coples of Class Ill are d~str~buted per a considered mandatory compl~ance unless spec~f~ed at the t~me of Issuance and c above lnformat~on on Owner Not~ftcat~on Serv~ce or Subscr~pt~ons can be Class I and II are ma~led to obta~ned through any BEECHCRAFT Aero or Av~at~on Center, lnternatlonal

m D~str~butor and Dealer or the Factory As Servlce lnstruct~ons are Issued. N w (a) BEECHCRAFT Aero or Av~at~on Centers and lnternat~onal temporary notat~on ~n the ~ndex should be made unt~l the ~ndex IS rev~sed m D~str~butors and Dealers Warranty w~ll be allowed only when spec~f~cally def~ned In the Service lnstructlons m a, (b) Owners of record on the FAA Reg~strat~on l~st and Me and In accordance wtth Beech Warranty Pollcy

General Avmtnan Mmnulo<lurers Arroc~m+on

Service Instructions No. 00424131, Rev. II

MANPOWER: The following information is for planning purposes only:

Estimated man-hours for inspection: 4 hours. Suggested number of men: 1 man.

MATERIAL: The following parts, if required, may be ordered through BEECHCRAFT Aero or Aviation Centers and International Distributors and Dealers. Parts listed under OLD PIN are no longer available.

LH REPAIR NEW PIN OLD PIN DESCRIPTION QUANTITY

1 69-40001 3- 1 7 169-40001 3-3 Frame 1 per airplane

169-400005-837 1 69-400005-263 Angle 1 per airplane

1 69-40001 3-29 169-40001 3-5 Bracket 1 per airplane

169-40001 3-27 none Spacer 1 per side

169-40001 3-45 169-400013-13 Doubler 1 per airplane

*NAS1673-08L2 No PIN change Jo-bolt 5 per side

'NAS1673-08L3 No PIN change Jo-bolt

AN6-12A /MI No PIN change Bolt

MS20365-624A No PIN change Nut

MS20470AD5-6 No PIN change Rivet

MS20470AD5-12 MS20470AD5-7 Rivet

5 per side

1 per side

1 per side

14 per side

5 per side

AN960-616 No PIN change Washer 2 per side

100951 DD063YN None Washer 1 per side

RH REPAIR 169-400013-1 8 169-40001 3-4 Frame 1 per airplane

169-400005-838 169-400005-264 Angle 1 per airplane

169-40001 3-30 169-40001 3-6 Bracket 1 per airplane

1 69-40001 3-27 None Spacer 1 per side

169-40001 3-46 1 69-40001 3-1 4 Doubler 1 per airplane

'NAS1673-08L2 No PIN change Jo-bolt 5 per side

'NAS1673-08L3 No PIN change Jo-bolt

AN6-12A /MI No PIN change Bolt

MS20365-624A No PIN change Nut

MS20470AD5-6 No PIN change Rivet

MS20470AD5-12 MS20470AD5-7 Rivet

5 per side

1 per side

1 per side

14 per side

5 per side

AN960-616 No PIN change Washer 2 per side

100951 DD063YN None Washer 1 per side

Service lnstructions No. 0042-031, Rev. II

*MS27039-0808 bolts, MS20364-832 nuts and AN960-8 washers may be used in lieu of the NAS1673-08L2 and NAS1673-08L3 Jo-bolts.

The value of the parts required to incorporate these Service lnstructions on one airplane is to be advised. Prices, when issued, will be subject to change without notice.

WARRANTY: None.

SPECIAL TOOLS: None.

WEIGHT AND BALANCE: None.

REFERENCES: BEECHCRAFT 19, 23 and 24 series Shop Manual, PIN 169-59001 5F or subsequent. AC43.13-1 A, FAA Aircraft Inspection and Repair Manual.

PUBLICATIONS AFFECTED: It is recommended that a note to "See Service lnstructions No. 0042-031, Rev. II" be made in the following:

19, 23 and 24 series Shop Manual copies, P!N 169-590015F or subsequent, Section 3; 19, 23 and 24 series Parts Catalog copies, PIN 169-5900121 or subsequent, Figure 98.

ACCOMPLISHMENT INSTRUCTIONS: These Service lnstructions may be accomplished as follows:

1. On all airplanes listed under Part I and Part II of EFFECTIVITY, accomplish the following:

EXISTING RIVETS DO NOT REMOVE

a \A- MS20470AD5-6 RIVETS

- 44s- MS20470AD5-7 RIVETS

JO-BOLT AS SPECIFIED TO REPLACE RIVETS (5 PLACES.) + A

1 69-40001 3-1 3 (LH) 169-40001 3-1 4 (RH) DOUBLER

N X L

.3751.379 INCH D!A. AlTACH BOLT HOLE

169-40001 3-7 DOUBLER

F

1 69-40001 3-3 169-40001 3-4 FRAME

Figure 1.

Service Instructions No. 0042-031, Rev. II

JO-BOLT PIN 5 PLACES

a. Remove the pilot and copilot seats, forward carpets and upholstery panels below the cabin doors.

b. At each 100 hour, annual or periodic inspection, visually inspect for radial or circumferential cracks around the wing attach bolt head or nut in the following parts: PIN 169-40001 3-3 (LH) frame, PIN 169-40001 3-4 (RH) frame, PIN 169-40001 3-5 (LH) bracket, PIN 169-400013-6 (RH) bracket and the following doublers, if installed: PIN 169-400013-7 (LH and RH), PIN 169-40001 3-1 3 (LH), PIN 169-40001 3-14 (RH), 169-400013-45 (LH) and PIN 169-400013-46 (RH).

Each 500 hours after the accumulation of 2000 hours in service (i.e. at 2000, 2500, 3000 hrs, etc.), this inspection is to be accomplished by loosening the nut on the attach bolt and inspecting for possible cracks in the above parts using dye penetrant procedures as outlined in AC43.13-1A.

If cracks are found, jack the airplane, cradle the fuselage at stations 68 and 181, support the wings under the main spar to remove all stress on the wing attach points, and proceed to step 3.

If no cracks are found, on airplanes noted in Part I of EFFECTIVITY, proceed to step 2. On airplanes noted in Part II of EFFECTIVITY, torque the nut to 1001120 inch-pounds and reinstall the side panels, carpets and seats.

NOTE

It is not necessary nor recommended that the wing attach bolt be removed to accomplish this inspection.

2. On airplanes noted in Part I of EFFECTIVITY only, accomplish the following at the initial inspection or at any time the forward wing attach bolts are removed for any reason.

NOTE

On airplanes which have been previously inspected for proper gap and the attach bolt has not been removed since that inspection, the inspection for proper gap need not be repeated. On airplanes which have had the PIN 169-40001 3-27 spacer and PIN 169-40001 3-29 (LH)

NEW

1 69-40001 3-6 (RH) BRACKET

169-40001 3-5 (LH) -

NASl673-08L2

k.01

169-40001 3-3 (LH) - 169-40001 3-4 (RH)

1 FRAME

3- ~ ~ 2 0 4 7 0 ~ ~ 5 - 7 RIVET

169-40001 3-1 3 (LH) C-- 1 69-40001 3-1 4 (RH)

DOUBLER

169-40001 3-7 DOUBLER

1;-.3751.379 INCH DIAMETER ATTACH

JO-BOLT PIN NAS1673-08L 3 5 PLACES

BOLT HOLE

169-40001 3-1 (LH), 169-1 0001 3-2 (RH) FRAME ASSEMBLY

Figure 2.

Service Instructions No. 0042-031, Rev. II

or PIN 169-40001 3-30 (RH) bracket installed, the inspection for proper gap need not be accomplished.

a. Jack the airplane, cradle the fuselage at stations 68 and 181, and support the wings under the main spar to remove all stress from the wing attach points.

b. Remove the nut on the wing attach bolt and measure the gap between the wing attach frame and the bracket to ensure the gap is .320 + .010 inch. Do not remove the attach bolt.

c. If the gap is of the proper size, ensure that a PIN AN960-616 washer is installed under the head of the bolt, install a PIN 100951DD063YN aluminum washer, then a PIN AN960-616 washer and install an MS20365-624A nut on the attach bolt and torque the nut to 10011 20 inch-pounds.

d. If the gap exceeds .320 5 .010 inch, back the wing attach bolt out just far enough to install PIN AN960-616 andlor AN960-616L washers as required to fill any gap between the lug on the wing and the bracket or frame. If a PIN AN960-616 washer is not installed under the head of the bolt, the bolt must be removed.

e. Ensure a PIN AN960-616 washer is installed under the head of the wing attach bolt and install the bolt. Install a PIN 100951DD063YN washer on the bolt next to the bracket, then a PIN AN960-616 washer, and install an MS20365-624A nut. Torque the nut to 1001120 inch-pounds and reinstall the side panels, carpets and seats.

169-40001 3-1 7 ( LH ) - 169-400013-18 (RH )

MS20470AD5-6

MS20470AD5-12 RIVET (5 HOLES)

1 69-40001 3-45 (LH) 169-40001 3-46 (RH)

AlTACH BOLT HOLE SPACE EVENLY BETWEEN RIVETS ON EITHER SIDE OF THIS LOCATION

Figure 3.

Service Instructions No. 0042-031, Rev. II

NOTE

If the frame, doubler, bracket and spacer are all installed as listed under new PIN in MATERIAL, the inspection requirements of this S.I. are no longer applicable, inspections should, however, be accomplished as required by applicable Federal Aviation Regulations and as recommended in the model 19,23 and 24 shop manual and inspection guides.

The 100 hour repetitive visual inspection is required on all airplanes on which any parts listed under old PIN in the MATERIAL section remain. Dye penetrant inspection is required on those airplanes at accumulation of 2000 hours time in service and each 500 hours thereafter.

3. Drill out the three rivets through the bracket and frame, and the five rivets through the outboard flange of the bracket and the fuselage skin (See Figures 1 and 2), and discard the bracket.

NOTE

It is recommended that a PIN 169-400013-45 (LH) or PIN 169-400013- 46 (RH) doubler be installed on the wing attach point frame whenever the bracket requires replacement.

4. Drill out the rivets attaching the floor skin to the fuselage side skin, F.S. 94 channel crossmember, and the angle PIN 169-400005-263 (LH) or PIN 169-400005-264 (RH) just forward of the wing attach point frame. Roll the floor skin up and inboard against the seat track, being careful not to crease it. Drill out the rivets attaching the angle and any doublers. Starting with the third rivet from the top, working downward, drill out five rivets through the outboard flange of the frame and fuselage side skin.

5. Position a PIN 169-400013-45 (LH) or PIN 169-400013-46 (RH) doubler on the frame

1 69-40001 3-27 SPACER

169-40001 3-29 1 69-40001 3-30 BRACKET

.375/.379 INCH DIAMETER ATTACH BOLT H O ~ E -

NAS1673-08L3 JO-BOLT 5 PLACES

f 1 169-40001 3-1 7 (LH ) 169-40001 3-1 8 (RH ) FRAME

MS20470AD5-6 RIVET 14 PLACES

169-400013-45 (LH ) 1 69-40001 3-46 ( RH ') DOUBLER

NAS1673-08L3 JO-BOLT - 5 PLACES

169-40001 3-1 5 (L.H.), 169-40001 3-1 6 (R.H.) FRAME ASSEMBLY

Figure 4.

Service Instructions No. 0042-031, Rev. II

as shown in Figure 3, and secure with a 'C' clamp. If cracks exist in the frame but are above the line of the floorboard, and are contained within the dimensions of the new PIN, 169-400013-45 (LH) or PIN 169-40001 3-46 (RH) doubler, do not appear to be elongating inboard or downward, and are not within 0.47 inch of any rivet on the doubler (See rivet pattern, Figure 3), the PIN 169-400013-45 (LH) or PIN 169-400013-46 (RH) doubler may be installed without replacing the frame. All cracks must be stop-drilled with a No. 57 (.0430 inch dia.) drill bit. If cracks exist in the frame which do not meet the above criteria, the frame must be replaced with a new PIN 169-400013-17 (LH) or PIN 169-400013-18 (RH) frame and a new PIN 169-400013-45 (LH) or PIN 169-400013-46 (RH) doubler installed on the frame (See Figures 3 & 4). 6. Drill holes in the new doubler and frame with a No. 21 (.I59 inch dia.) drill bit

according to the pattern shown in Figure 3. If a PIN 169-400013-13 (LH) or PIN 169- 400013-14 (RH) doubler was previously installed on the frame, the seven rivet holes above the floor line may be back drilled in the doubler through the frame rather than using the hole pattern shown in Figure 3. Countersink the two holes for the MS20426 rivets on the aft side of the frame and rivet the doubler to the frame. Using a hole finder, locate the five rivet holes through the outboard flange of the frame where rivets were drilled out in step 6. Drill these holes through the doubler, frame and skin with a No. 19 (.I66 inch dia.) drill bit and install NAS1673-08L3 Jo-bolts in all five holes. 7. Position a PIN 169-400013-29 (LH) or PIN 169-400013-30 (RH) bracket and a PIN

169-400013-27 spacer on the aft side of the frame in place of the bracket removed in Step 5 (See Figures 3 & 4). Using a 'C' clamp, secure the new bracket and spacer to the frame. Locate and drill the five holes through the outboard flange of the bracket to match the holes in the fuselage skin with a No. 19 (.I66 inch dia.) drill bit. Install NAS1673-08L2 Jo-bolts in the holes. Back drill the spacer and bracket through the three holes in the frame and doubler. Back drill the frame and doubler through the two holes in the new bracket and spacer. Install MS20470AD5-12 rivets in all five holes (See Figure 3.) Line ream the attach bolt hole to ,3751.379 inch diameter. 8. Position a new PIN 169-400005-837 (LH) or PIN 169-400005-838 (RH) angle against

the doubler on the forward side of the frame to replace the angle removed in step 6. Using the existing holes through the channel crossmember aft of the frame as a guide, back drill the doubler and angle with a No. 21 (.I59 inch dia.) drill bit and rivet the angle in place with MS20470AD5 rivets of the appropriate length. Roll the floor skin back into its original position and rivet to the angle, side skin and F.S. 94 crossmember with appropriate length MS20470AD5 rivets. 9. Reinstall the PIN AN6-12A wing attach bolt through the doubler frame, fuel tank rib

lug, and bracket with a PIN AN960-616 washer under the bolt head. Install a PIN 100951DD063YN washer on the bolt next to the bracket, and then a PIN AN960-616 washer and a PIN MS20365-624A nut. Torque the nut to 1001120 inch-pounds. Remove the airplane from jacks or cradles, and reinstall sidepanels, carpets, seats and any other upholstery andlor inspection panels removed to accomplish these Service Instructions.

RECORD COMPLIANCE: Upon completion of these Service Instructions, make an appropriate maintenance record entry.