SERVICE

SUBJECT:

EFFECTIVITY:

REASON:

COMPLIANCE:

APPROVAL:

Kit NO. 77-3001-1 S

CLASS I

INSTRUCTIONS No. 1185

ATA Code 24-40

ELECTRICAL POWER - PART I, RELOCATION OF EXTERNAL ELECTRICAL POWER RECEPTACLE; PART II, INSPECTION AND MODIFICATION OF EXTERNAL POWER WIRING; PART Ill, INSTALLATION OF UPHOLSTERY RETAINER CLIP TO CLEAR EXTERNAL POWER WIRE ROUTING

The following BEECHCRAFT Skipper 77 airplanes which are equipped with the optional external power provision:

PART I

BEECHCRAFT Skipper 77, serials WA-1 through WA-79.

PART II

BEECHCRAFT Skipper 77, serials WA-80 through WA-134 and WA-137 through WA-239

PART Ill

BEECHCRAFT Skipper 77, serials WA-1 through WA-299.

PART I

To relocate the external electrical power receptacle from inside the engine cowling to a location just aft of the wing.

PART II and PART Ill

To preclude the possible loss of electrical power by modifying external power wiring and replacing upholstery screws which may interfere with the wiring.

NOTE

PART Ill of these Service Instructions (WA-1 through WA-299) must be accomplished, even if PARTS I and II are not accomplished.

PART I, II AND Ill

Beech Aircraft Corporation considers this to be a mandatory modification and it should be accomplished as soon as possible after receipt of these Service Instructions, but no later than the next 100 service hours.

FAA Approved.

Beech Arcraft Corporalmn Issues servlce ~nfonat~on for the benef~t of owners BEECHCRAFT lntemat~onal Owner Notlf~cat~on Sewm L~st and f~xed base operators ~n the form of three classes of Se rv~e Instruct~ons (c) Those hav~ng a publ~cat~ons subscr~pt~on CLASS I (Red Border) are changes, Inspections, and mod~f~cattons that could affect safely The factory considers compl~ance mandatory CLASS II (Green CLASS Ill (No Border) covers changes wh~ch are opt~onal, maintenance a~ds. Border) covers changes. mod~f~cations, Improvements or lnspectlons the factory product Improvement k~ts and m~scellaneous sewtce ~nformat~on Compl~ance is feels wlll beneftt the owner and although h~ghly recommended they are not at the owner or operators prerogat~ve Cop~es of Class Ill are d~str~buted per a considered mandatory compl~ance, unless spec~f~ed at the time of issuance and c above lnforrnat~on on Owner Not~f~cat~on Sew~ce or Subscr~pt~ons can be class I and II are ma~led to obta~ned through any BEECHCRAFT Aero or Av~atlon Center. International

m D~str~butor a ~ d Dealer, or the Factory As Sew~ce lnstruct~ons are ~ssued. N P (a) BEECHCRAFT Aero or Av~at~on Centers and lnternat~onal temporary notallon ~n the ~ndex should be made unt~l the ~ndex IS rev~sed m D~strtbutors and Dealers Warranty w~ll be allowed only when spec~f~cally def~ned ~n the Sew~ce lnstruct~ons 8 (b) Owners of record on the FAA Reg~strat~on l~st and the and In accordance w~th Beech Warranty Pol~cy

Gcncr.1 Avldlon M ~ n u l ~ ~ t u r c r r A ~ r o . , a t , ~ n

Service lnstructions No. 1185

MANPOWER: The following information is for planning purposes only:

PART I

Estimated man-hours: 4 hours. Suggested number of men: 2 men

PART II

Estimated man-hours: 1 hour. Suggested number of men: 1 man

PART Ill

Estimated man-hours: 1 hour. Suggested number of men: 1 man

MATERIAL: The following kit and parts required for this modification may be ordered through BEECHCRAFT Aero or Aviation Centers and lnternational Distributors and Dealers. The MS20470-AD3 and MS20470-AD4 rivets of the appropriate length. EC1368, EC1300L or equivalent adhesive (PIN of Minnesota Mining and Manufacturing Co.. St. Paul, MN 55101). may be ordered through BEECHCRAFT Aero or Aviation Centers and lnternational Distributors and Dealers, or may be obtained from local sources.

The value of the kit and parts required for the incorporation of these Service lnstructions on one airplane is to be advised. Prices, when issued, will be subject to change without notice. Beech Aircraft Corporation expressly reserves the right to supersede, cancel andlor declare obsolete any kits or publications that may be referenced in these Service lnstructions without prior notice.

NOTICE

All BEECHCRAFT kits, unless otherwise designated, are approved for installation on BEECHCRAFT airplanes in original or BEECHCRAFT modified configurations only. BEECHCRAFT Kits may not be compatible with airplanes modified by STC installations or modifications other than BEECHCRAFT approved kits.

PART NUMBER DESCRIPTION QUANTITY PER AIRPLANE

PART I

K i t , E x t e r n a l P o w e r 1 Receptacle

PART II

105-364029-3 Decal 1

PART Ill

Clip Rivet

'Ye inch dia. pop rivets of the appropriate length may be substituted for this rivet if necessary.

WARRANTY: Warranty credit for parts and labor to the extent noted under MATERIAL and MANPOWER will be allowed on claims submitted prior to July, 1982.

All warranty reimbursements are handled through franchised BEECHCRAFT Aero or Aviation Centers and lnternational Distributors and Dealers. Owners and operators shouid arrange with these

Service lnstructions No. 11 85

SPECIAL TOOLS:

WEIGHT AND BALANCE:

outlets to perform the work and have them submit the standard Beech Aircraft Corporation warranty claim form through BEECHCRAFT Parts and Equipment Marketing Wholesalers or International Distributors.

None.

PART I

WEIGHT (LBS)

ARM (IN)

MOMENT (LBSIIN)

The owner or operator is responsible to maintain compliance with FAR 23.25lCAR 3.74.

REFERENCES: None.

PUBLICATIONS AFFECTED: It is recommended that a note to "See Service Instructions No. 1185" be made in the following:

All Skipper 77 Maintenance Manual copies, PIN 108-590000-7 or subsequent, Chapter 39-20. All Skipper 77 Parts Catalog copies, PIN 108-590000-9 or subsequent, Chapter 24-40.

The following note also should be made in all of the above Maintenance Manual copies:

"The battery switch should be on prior to turning on the external power source."

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

PART I

1. Turn off and/or disconnect all electrical power and disconnect the battery.

2. Remove RH seat, baggage compartment floorboards and lower aft baggage compartment cover panel to gain access to the aft fuselage. The power receptacle will be relocated to the RH side of the airplane.

3. Position the 108-360027-3 doubler on the inside of the fuselage skin with the forward edge of the doubler at F.S. 129.00, as shown in Figure 1, and mark the rivets to be removed for attachment of the doubler.

4. Remove existing rivets and install the 108- 360027-3 doubler on the inside of the fuselage skin, using rivets of the appropriate length as shown in Figure 1.

5. Cut a 1.0611.09 inch diameter hole in the fuselage skin to match the hole in the 108-360027-3 doubler.

6. Remove the engine cowling, disconnect and remove the existing electrical power receptacle.

7. Position the power receptacle on the PIN 108- 360027-3 doubler and drill six .193/.200 inch diameter holes in the receptacle flange, using the doubler as a template. (See Figure 1 .)

8. Install the external power receptacle as shown in Figure 1.

9. Attach the 108-360012-653 cable assembly to the receptacle using existing hardware, and place the existing MS25171-45 rubber nipple over the stud for protection.

to. Using EC1368, EC1300L adhesive (per the man- ufacturers instructions), or equivalent, install an MS21266- 1 N grommet in the stringer cutout on the RH side of the aft baggage compartment bulkhead as shown in Figure 2.

11. Remove the lower side molding below the RH door and loosen the lower edges of the upper side molding both fore and aft of the door. Place the 106242-10 insulat- ing tubing over the cable assembly and route from the canted bulkhead, under the side panel and through the aluminum channel under the door so that the insulating tubing is inside the door channel to act as an anti-chafe shield. Route the cable assembly under the upper side molding, forward of the RH door to allow routing below the instrument panel and over to the firewall as shown in Figure 3.

NOTE

Accomplish steps 2 through 4 of Part Ill in conjunction with accomplishment of step 11 of Part I for the RH side of the airplane.

12. Cut a .75 inch diameter hole in the firewall as shown in Figure 4. Route the cable assembly through the hole and install the two piece 112149-1 1 grommet and NAS51-75 ring. Install the new cable assembly on the bus side of the battery relay and place an MS25171-45 rubber nipple over the stud for protection.

Service Instructions No. 1185

1.06/1.09 INCH DIAMETER

MS20470-AD3 RIVET (7 REQUIRED)

35-36421 4 6-C PLACARD

DIAMETER HOLE

MS21042L3 NUT (6 EA. RE0 ) MS20470-AD4 MIL OF STRINGER

RIVET (5 REQUIRED) FUS STA

-FORWARD F I N C H E S 1 129.00

FIGURE 1.

CANTED BULKHEAD I !

VlEW A

MS21266-1 N GROMMET (1 REQ.)

VlEW LOOKING AFT

FIGURE 2.

Service Instructions No. 1185

NOTE placard and attach PIN 35-364214 B-C, placard directly to the left of the new receptacle and a 105-364029-3 decal to

On airplanes with the optional flight hour meter the right of the new receptacle on the aft fuselage as installed, it may be necessary to reposition the shown in Figure 1. Reconnect the battery. Reactivate the hour meter pressure switch in order to provide electrical system, and check for proper operation of all clearance to route the external power cable systems. forward of the firewall. 14. Reinstall the RH seat, baggage compartment

floorboards and lower aft baggage compartment cover 13. Reinstall the engine cowling. Remove the old panel.

108-36001 2-653 CABLE ASSEMBLY (1 REQ) 106242-1 0 INSULATING

FIGURE 3. TUBING FROM CANTED BULKHEAD TO FIREWALL

RBL 15.00

URE SWITCH

.75 INCH DIAMETER HOLE 112149-1 1 GROMMET

BATTERY RELAY

108-36001 2-653 EXTERNAL POWER CABLE ASSEMBLY \

WL 100.00

VIEW LOOKING AFT

FIGURE 4.

Service Instructions No. 1 185

PART II

1. Turn off andlor disconnect all electrical power and disconnect the battery.

2. Remove the upper engine cowling. 3. Disconnect the external power supply cable from

the battery terminal of the battery relay and reconnect the cable to the bus terminal of the battery relay as shown in Figure 4.

4. Reconnect the battery and check operation of the external power supply. Battery voltage should be present at the center pin of the external power receptacle only when the battery switch is on. There should be no voltage present at this pin when the battery switch is off.

5. Install a PIPJ 105-364029-3 decal next to the external power receptacle as shown in Figure 1.

6. Reinstall the engine cowling.

PART Ill

NOTE

For airplane serials WA-1 through WA-79,

s t e p s 2 . 3 a n d 4 be l ow shou ld be accomplished in conjunction with step 11 of Part I on the RH side of the fuselage only. Airplane serials WA-1 through WA-299 on the LH side and WA-80 through WA-299 on the RH side should accomplish all Part Ill steps below.

1. Remove the threshold cover below the cabin door.

2. Drill out the one existing rivet through the door frame as shown in Figure 5.

3. Install a PIN 108-530063-5 clip as shown in Figure 5, replacing the rivet drilled out in step 2 with an equivalent rivet and installing a new AD45ABS rivet as shown in Figure 5. (See 'note under MATERIAL.)

4. Reinstall the threshold cover, making sure the cover screw goes into the clip and not into the area of the electrical wiring.

5. Repeat steps 1 through 4 for the opposite threshold cover unless already accomplished in Part I.

1.6 INCHES \

1- TRIM COVER AS REQ. TO FIT 108-530063-5 CLIP

THRESHOLD COVER

I '

THIS AREA FOR EL EXISTING RIVET

VIEW A-A AND INSTALL NEW EQUIVALENT RIVET

FIGURE 5.

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