Appendix A Service Instructions No. 0514-035, Rev. I
MODEL PART NUMBER DESCRIPTION QUANTITY All 95-55 through E55, 58, 58-4002-1 S Kit, Spar Inst'l. (contains 2 per airplane 95 through E95, 56TC, 60 parts and information to and A60 install new fwd. wing spars. Spars are not included. Order P/N 000- 110011-3(LH) or P/N 000- 110011-4(RH) for 95 and 55 series airplanes; order P/N 000-110011-5(H) or P/N 000-110011-6(RH) for 58 series airplanes; order P/N 000-110011-7(LH) or P/N 000-110011-8(RH) for 56TC and 60 series airplanes.)
A80, 65-B80 thru LD-477; All 65, A65; 70; 65-80, 65- 100-4002-1 S Kit, (contains parts LH Spar Inst'! and 2 per airplane 65-88: 65-90. 65-A90, B90. information to install new through LW-87; 99, 99A, C90 through L-624; E90 A99A, B99 through U-153 that have not replaced the O.B. wing main spar per spar assemblies). P/N 000-110012-1(LH) or P/N fwd. wing spars. Spars are not included. 000-110012-2(RH) order Service Instructions No.
0986 or subsequent; 100 and A100 through B-193.
Same as 100-4002-1 S 100-4002-3 S Kit, LH Spar Inst'l. (same 1 per airplane as kit P/N 100-4002-1 S except P/N 000-110012-1 spar assy. is included.)
Same as 100-4002-1 S 100-4002-4 S Kit, LH Spar Inst'l. (same 1 per airplane as kit P/N 100-4002-1 S except P/N 000-110012-2 spar assy. is included.)
WARRANTY: None.
SPECIAL TOOLS: None.
WEIGHT AND BALANCE: None.
REFERENCES: The applicable Parts Catalog for all models on which spar installation kits do not include the spars or on which spar installation kits are not available.
PUBLICATIONS AFFECTED: It is recommended that a note be made in the applicable section of all s hip manual copies to ¿See Service Instructions No. 0514-035, Rev. II for spar inspection procedures."
8/14/97 AC 43-204 Appendix A Service Instructions No. 0514-035, Rev. II
ACCOMPLISHMENT INSTRUCTIONS: The inspection of the upper and lower spar caps may be accomplished as described in the following procedure.
1. Wash all exposed area of the upper and lower spar caps using normal cleaning procedures.
2. Visually inspect all exposed area of the upper and lower spar caps for paint blisters, raised areas and/or unevenness and cracks in the metal. Paint blisters could be caused by corrosion, therefore. if blisters are detected during the visual inspection, the area of the blister should be examined closely for unevenness and/or raised areas and cracks in the metal. The exposed area of the spar caps are extruded flat, therefore, areas of unevenness and/or raised areas on the spar caps could indicate corrosion and should be considered suspect areas. (See illustration.)
NOTE Areas of unevenness and/or raised areas on the spare caps may be detected by sliding the fingers over the surface, by moving a straightedge over the surface or by sighting down the length of the spar cap.
3. If during visual inspection, any build up of a whitish salt-like non-metallic substance is detected, the area should be examined carefully, as this is indicative of corrosion. However, wax or paint that may be trapped between the edge of the skin and the exposed section of the spar cap should not be interpreted as corrosion.
4. If unusual conditions are noted which cannot be resolved locally, advise Commercial Product Support, Beech Aircraft Corporation, Wichita, Kansas 67201.
5. For models on which spar installation kits are available, instructions for installation of the replacement spars are continued in the applicable kits.
Appendix A Service Instructions No. 0514-035, Rev. II
THIS ILLUSTRATION REPRESENTS A
TYPICAL SECTION OF THE SPAR CAP
BOX SECTION SKIN AREAS TO BE INSPECTED FOR INDICATORS OF POSSIBLE CORROSION.
THE INDICATORS ARE ALL SHOWN IN ONE AREA AND ARE EXAGGERATED FOR CLARITY.
CRACKS ANY ONE OR ANY COMBINATION OF THE
INDICATORS ARE CAUSE FOR FURTHER INVESTIGATION.
SPAR CAP
•
- RAISED AREAS
LEADING EDGE SKIN
- THIS RIVET PATTERN WILL VARY
ON DIFFERENT MODELS
- PAINT BLISTER Typical Section of the Spar Cap to be Inspected RECORD COMPLIANCE: Upon completion of the initial and all subsequent inspections, make an appropriate maintenance record entry. When kits are installed, it is recommended that the parts list contained in the kit be filed for future reference.
Appendix B APPENDIX B. BEACHCRAFT, ATA CODE 55-30
SAMPLE INSPECTION PROCEDURE Empennage-Vertical Stabilizer - Part I, Inspection of the Vertical Stabilizer Main Spar For Fatigue Cracks and/or Nicks:
Part II, Repair of Fatigue Cracks and/or Nicks in the Vertical Stabilizer Main Spar and Angle-Doubler.
Retyped with permission of Beachcraft A Raytheon Company .../ Page 1
Appendix B Service Instructions No. 0530-134, Rev. I
SAMPLE INSPECTION PROCEDURE Beechcraft SERVICE INSTRUCTIONS SUBJECT: EMPENNAGE - VERTICAL STABILIZER - PART I, INSPECTION OF
THE VERTICAL STABILIZER MAIN SPAR FOR FATIGUE CRACKS AND/OR NICKS; PART II, REPAIR OF FATIGUE CRACKS AND/OR
NICKS IN THE VERTICAL STABILIZER MAIN SPAR AND ANGLE-
SYNOPSIS OF CHANGE: Changed Part I to require removal of the vertical stabilizer for inspection and changed inspection procedures.
EFFECTIVITY: BEECHCRAFT 99, 99A. A99A and B99 Airliners, serials U-1 thru U-151 with 2000 hours or more of time in service, unless the intent of these Service Instructions has already been accomplished.
REASON: To provide procedures for inspecting the vertical stabilizer main spar and angle-doubler for possible fatigue cracks and/or nicks and repair or replacement of vertical stabilizer if cracks or nicks are found.
COMPLIANCE: PART I a. Inspection at 2000 hours of time in service.
PART I b. Inspection at intervals not to exceed 500 service hours after the initial inspection in Part I a. until the new P/N 115-640000-605 stabilizer is installed.
PART II. Repair or replace the vertical stabilizer as indicated in these Service Instructions.
NOTE The vertical stabilizer can be replaced or the doubler repair can be made as a strengthening measure at any time if the vertical stabilizer is removed from the airplane for any reason. If the doubler repair is made following detection of a cracked spar or angle-doubler. the 500 hour inspection intervals described herein should be continued. If the doubler is installed as a strengthening measure with no evidence of cracks in the spar, of if a new vertical stabilizer is installed, inspection of the area may revert to normal routine inspection intervals.
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Appendix B Service Instructions No. 0530-134, Rev. I DESCRIPTION: On the initial inspection, the vertical stabilizer is to be removed from the fuselage and the main spar and angle-doubler are to be dye penetrant inspected for possible fatigue cracks. If cracks are found, the stabilizer is to be repaired or replaced as described hercin. If nicks are noted in the flanges, they are to be sanded smooth as described herein. The doubler reinforcement described in Part Il is to be made, or as an option, the vertical stabilizer is to be replaced regardless of the inspection results.
If the doubler repair is made following detection of a cracked spar or angledoubler, the vertical stabilizer main spar flanges are to be visually inspected with a 3 to 5 power magnifying glass at each 500 hour interval thereafter until the vertical stabilizer has been replaced.
APPROVAL: FAA Approval - DOA CE-2.
MANPOWER: The following information is for planning purposes only.
Estimated man-hours for first inspection: 8 hours.
Suggested number of men for first inspection: 2 men Estimated man-hours for inspection following a doubler repair of a cracked spar: 2 hours.
Suggested number of men for inspection following a doubler repair of a cracked spar: 1 man.
Estimated man-hours for doubler installation: 16 hours Suggested number of men for doubler installation: 2 men.
Estimated man-hours for stabilizer replacement: 24 hours.
Suggested number of men for stabilizer replacement: 2 men.
MATERIAL: The following parts, if required, may be obtained through your BEECHCRAFT Parts and Service Outlet.
NEW P/N OLD P/N DESCRIPTION QUANTITY PRICE* 115-640000-605 115-640000-603 Vertical Stabilizer 1 per aircraft To Be Advised Assembly CR2249-5-5 None Cherrylock rivet 6 per aircraft $.38 each CR2249-5-6 None Cherrylock rivet 58 per aircraft $.40 each *Estimated suggested selling price. (Subject to change without notice.)
WARRANTY: None.
SPECIAL TOOLS: None.
WEIGHT AND BALANCE: WEIGHT ARM MOMENT (LBS.) (INS) (LBS. INS) 2 431 862 REFERENCES: BEECHCRAFT 99 Airliner Series Maintenance Manual, PAV 99-590015-1 or subsequent.
Appendix B Service Instructions No. 0530-134, Rev. I
PUBLICATIONS AFFECTED: It is recommended that a note to ¿See Service Instructions No. 0530-134. Rev.
I" be made in all 99 through B99 Parts Catalog copies, PAN 99-590014D or subsequent, Figure 134.
ACCOMPLISHMENT INSTRUCTIONS: These Service Instructions may be accomplished as follows:
PART I a. FIRST INSPECTION
1. Remove the rudder and the vertical stabilizer as instructed in Chapters 27-20 and 55-30 respectively of the Maintenance Manual.
2. Drill out the rivets on both sides of the lower vertical stabilizer sufficiently to lift the skins and inspect the main spar and the angle-doubler.
3. Using dye penetrant procedures as outlined in AC43.13-1A, inspect both flanges of the main spar and the angle-doubler in the curved area just below the vertical stabilizer skin for possible cracks.
Also inspect the joggle in the angle-doubler beneath the skin and just aft of the main spar flanges for possible cracks. (See Figure 1.)
4. Check the spar and angle-doubler flanges for nicks which could possible develop into cracks.
INSPECT
• JOGGLE AREA
• OF ANGLE-
DOUBLER
INSPECTION AREA
INSPECT BOTH FLANGES Figure 1. Vertical Stabilizer Assembly Page 4
Appendix B Service Instructions No. 0530-134, Rev. I
CAUTION If any cracks are found, contact Parts and Service Operations, Beech Aircraft Corporation.
Wichita, Kansas, 67201, and report your findings for evaluation before proceeding with Part PART I b. If the doubler repair is made following detection of a cracked spar or angle-doubler, the following inspection must be made at each 500 hour interval thereafter until the vertical stabilizer has been replaced.
1. Remove the tail cone.
2. Lower the front of the horizontal stabilizer to gain the greatest accessibility to the vertical stabilizer main spar where it is attached to the airplane structure.
3. Through the tail of the airplane, inspect both flanges of the main spar and the angle-doubler in the curved area just below the upper fuselage skin (Figure 1) with the aid of a 3 to 5 power magnifying glass.
NOTE Remove the handle from the magnifying glass and fabricate a temporary handle approximately 24 inches long of wood or other suitable material. Mount the mirror on one end of the fabricated handle at an approximate 90° angle to the handle in such a manner as to hold it securely. (See Figure 2.) The long handle will facilitate the inspection through the tail opening.
4. If no new cracks or nicks are found in the main spar or the angle-doubler flanges, the tail cone may be reinstalled.
5. If new cracks of nicks are found, proceed with Part II for repair.
REMOVE THE HANDLE SHOWN AT RIGHT
AND MOUNT ON A TEMPORARY HANDLE
AS SHOWN AT LEFT APPROXIMATELY 24" (WOOD) HANDLE
SIZE AND SHAPE
OPTIONAL Figure 2. Inspection Magnifying Glass Page 5
Appendix B Service Instructions No. 0530-134, Rev. I
PART I REPAIR
1. If nicks are found in the spar or angle-doubler flanges, they should be sanded smooth to lessen the possibility of crack development.
2. If cracks are found in either the spar flanges or in the angle-doubler flanges but not in both on the same side, to a maximum depth of .25-inch, a repair may be made to the vertical stabilizer assembly as follows.
a. Slip a stainless steel shim between the spar flange and the angle-doubler flange to prevent damage to the adjacent flange and grind out the crack. Leave a smooth edge and flair the area out to the normal flange width. (Figure 3.)
b. Fabricate and install two doublers from .125-inch by 5.0-inches by 30.0-inches and two shim spacers from . 025-inch by 2.0-inches by 12.0-inches, 2024-T3 aluminum alclad, as shown in Figure 3.
c. Install one doubler and one shim on each side of the vertical stabilizer as shown in Figure 3.
Reinstall the rivets which were removed in Part I for inspection of the doublers.
d. Starting from a point approximately 8-inches forward of the vertical stabilizer main spar and aft from that point, drill out all rivets which attach the vertical stabilizer/fuselage angle-fairing to the fuselage.
e. Measure the width of the doublers at the vertical stabilizer skin lower edge. (See Figure 3.) The rectangular cutout in the upper fuselage should be lengthened to at least 1.5-inches longer than the width of the doublers to allow clearance between the stabilizer and the dorsal fairing during NOTE It may be necessary to relocate the small angle at the aft of the cutout in order to achieve the necessary clearance for the doublers.
f. Reinstall the vertical stabilizer as described in Chapter 55-30 of the Maintenance Manual.
NOTE Check the clearance between the forward surface of the main spar and the bulkhead. If the two surfaces are not flush the gap should be shimmed. (Shims may be fabricated locally from aluminum stock.)
g. Form the vertical stabilizer/fuselage angle-fairing around the doublers and reinstall the rivets which were removed in step d. Reinstall screws to attach the angle-fairing to the vertical stabilizer.
h. Reinstall and rerig the rudder and tab per Chapter 27-20 of the Maintenance Manual.
3. The preceding doubler installation is to be made on all affected airplanes for the vertical stabilizer may be replaced with a new P/N 115-640000-605 vertical stabilizer assembly), regardless of whether cracks are noted or not with the following exception:
8/14/97 AC 43-204 Appendix B Service Instructions No. 0530-134, Rev. I * LEAVE EXISTING FASTENERS INSTALLED AND ADD 16 EA CR 2249-5-6 FASTENERS
ON EACH SIDE AS SHOWN
• REMOVE EXISTING MS20426ADS FASTENERS AND REPLACE WITH CR 2249-5-6 AND ADD 6 EA CR 2249-5-6 FASTENERS ON EACH SIDE • VS 0.000
AS SHOWN
- 16 EQUAL SPACES 45° CHAMFER ALL AROUND
9.40 06 TYP
20.8 9.00R VS -8.500 DOUBLER (2 REQ.)
.125 X 5.0 X 30.0
- 16 EQUAL SPACES 2024-T3 ALUM ALCLAD
- JOGGLE AREA 0Q-A-250/5 OF
• + ANGLE-
DOUBLER
• CR 2249-5-5 (3 REQ.) ON EACH SIDE) O 4 ANGLE-
DOUBLER VS - 17.200 <10>
1.50 R MEASURE THIS DISTANCE ML
FRONT SPAR AREA CRACKING OCCURRED
- 10 EQUAL SPACES
10.01 INSTALL SHIM-SPACER (2 REQ.)
.025 X 2.0 X 12.0 2024 T3 ALUM ALCLAD
BETWEEN DOUBLER AND SPAR SHIM AS REQ. AND BELOW STABILIZER SKIN LINE
BETWEEN SPAR
AND BULKHEAD 48 25R
1.50 ® INDICATES EXISTING RIVETS Figure 3. Fabrication and Installation of Doublers and Spacer - Shims Ho Page 7
Appendix B Service Instructions No. 0530-134, Rev. I If cracks are found in both the spar and angle-doubler flanges on the same side and/or the cracks extend into the rivet holes or into the radius of the spar or angle-doubler, the vertical stabilizer assembly must be replaced. Removal and reinstallation of the rudder and the vertical stabilizer are described in Chapter 27-20 and 55-30 respectively of the Maintenance Manual. rerigging of the rudder and tab is described in Chapter 27-20 of the Maintenance Manual.
RECORD COMPLIANCE: Upon completion of these Service Instructions, make an appropriate maintenance record entry.
* Do Page 8
Appendix C APPENDIX C. PRATT & WHITNEY ENGINE GENERAL - INSPECTION/CHECK - 00
SAMPLE INSPECTION PROCEDURE Task 72-00-00-990-004 Paras 1-4 Task 72-31-82-990-001 Task 72-31-82-990-002 Task 72-31-82-200-003 Retyped with permission of Pratt & Whitney.