Feb 12/2013 

### KELOWNA 

# Flightcraft Ltd. CONVAIR ® 

### DIVISION 

# SERVICE BULLETIN SB 340-57-001

Page 1 of 5 INSPECTION OF LOWER WING SKIN FOR CRACKS BETWEEN WS 5 AND WS 6 1. Summary This service bulletin gives the following: • Planning information containing effectivity, reason, description, compliance, manpower and references; and • accomplishment instructions containing the de tailed procedures for incorporating the service bulletin on the aircraft. 2. Planning Information A. Effectivity • CV340, CV440 and C-131 (Military) series airplanes. • CV580 (CV340/440 aircraft modified by TCCA STC SA00-140) airplanes. • CV5800 (CV340/440 aircraft modified by TCCA STC SA93-208) airplanes. • CV640 (CV340/440 aircraft modified by TCCA STC SA00-135) airplanes. B. Concurrent Requirements Not applicable. C. Reason An operator has found a crack in the wing lower surface skin from a fastener location attaching the wing access door doubler finger to the skin. The crack was found during a general internal inspection for corrosion. General Dynamics Convair Division Report No. ZS-340-1000 Revision 1 Addendum I, II and IV, Structurally Significant Deta il (SSD) 57-1-4 provides instructions to inspect the lower surface skin at the end rivets attaching the access door doubler fingers to the lower surface skin. SSD 57-1-4 instructs to accomplish extern al visual or dye penetrant inspections of the skin. The inspections per Report ZS-3 40-1000 are mandated by AD 92-06-06. The external inspection of the wing lower surface skin specified by SSD 57-1-4 in the area of the access door doubler finger attachment located between WS 5 and WS 6 is not effective. The lower surface skin at this location is covered by the nacelle drag angle. D. Description This service bulletin describes how to inspect the wing lower surface skin between WS 5 and WS 6 at the WS 6-7 access door doubler fingers.Feb 12/2013 

### KELOWNA 

# Flightcraft Ltd. CONVAIR ® 

### DIVISION 

# SERVICE BULLETIN SB 340-57-001

Page 2 of 5 E. Compliance A visual inspection must be done within 20 ho urs, and a high frequency eddy current (HFEC) inspection within 100 hours after receiving this service bulletin. These service bulletin inspections must be repeated every 1000 hours after the initial inspection has been completed. Operators with a Damage Rate Factor (DRF) mu st divide 1000 hours by their DRF to get the next inspection interval. For example:

• Inspection interval = 1000 / 7 = 142 Hours F. Approval This service bulletin has been reviewed by Transport Canada Civil Aviation and the inspection herein complies with the applicable Aviation Regulations and is APPROVED. The service bulletin is approved as an alternat e means of compliance to AD 92-06-06 for SSD item number 57-1-4 and is specific to the area of the LH and RH lower wing skin surface between WS 5 and WS 6. This Service Bulletin and it’s approval is based on the configurations listed in Paragraph 2., A. Effectivity. If the airplane has a modification or repair done to the area of the structure inspected, the operator is responsible for obtaining the appropriate regulatory agency approval. G. Manpower AME – 6 hours. Aircraft downtime up to 6 hours. H. Weight and Balance Not affected. I. Electrical Load Data Not affected. J. Software Accomplishment Survey Not applicable. K. References 1CC2-1, Allison Prop-jet Convair Maintenanc e Manual, dated 1 March 1984 or latest revision. Kelowna Flightcraft NDT Technique 5-0201 (Gener al HFEC Inspection of Metallic Structures or equivalent).Feb 12/2013 

### KELOWNA 

# Flightcraft Ltd. CONVAIR ® 

### DIVISION 

# SERVICE BULLETIN SB 340-57-001

Page 3 of 5 L. Other Publications Affected Not applicable. M. Interchangeability or Intermixability of Parts Not applicable. 3. Material Information A. Material None. B. Industry Support Information Inform Kelowna Flightcraft Ltd. when this service bulletin has been incorporated: Kelowna Flightcraft Ltd. Engineering Department 5655 Airport Way Kelowna, BC V1V 1S1 Canada Phone: (250) 807-5416 FAX: (250) 765-7140 E-mail: kflengineering@flightcraft.ca C. Material Necessary for Each Aircraft Not applicable. D. Material Necessary for Each Spare Not applicable. E. Re-identified Parts Not applicable. F. Tooling Not applicable.Feb 12/2013 

### KELOWNA 

# Flightcraft Ltd. CONVAIR ® 

### DIVISION 

# SERVICE BULLETIN SB 340-57-001

Page 4 of 5 4. Accomplishment Instructions. Refer to Figure 1. A. Do an inspection on both the LH and RH wing as follows: (1) Remove the No. 2 dry bay access panels. (2) Get access to the No. 2 dry bay wing interior. (3) Do a detailed visual inspection of area around the inboard side of WS 6-7 access panel doubler fingers and between STGR’s 5 and 11. (4) Do a High Frequency Eddy Current (HFEC) ins pection of the lower skin area at STRG’S 6, 8, and 10 and the WS 6-7 access panel doubler fingers. Refer to Kelowna Flightcraft NDT Technique 5-0201. (5) Record findings (crack or no crack) in Table 1 - Inspection Results. NOTE: Report all findings (negative or posit ive) to Kelowna Flightcraft Convair Division (matt_palmberg@flghtcraft.ca).

B. Test Not applicable C. Material Sample Removals Not applicable. Table 1: Inspection Results Serial Number Hours Cycles Crack Detected No Yes CommentsFeb 12/2013Page 5 of 5KELOWNAFlightcraftLtd. CONVAIR®DIVISIONSERVICE BULLETINSB 340-57-001Figure 1. Inspection of Wing Lower Surface WS 5-6