AD 72-13-03
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Alexandria Aircraft, LLC | 17-30 | Airworthiness Directives; Bellanca Model 17-30 Airplanes |
Unsafe Condition
Failure of the fuel boost pump circuit could lead to engine flooding when using the fuel boost pump, potentially causing loss of engine power.
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Required Actions
Install a three-position toggle switch, three-ohm 20-watt resistor, switch guard, and five-amp circuit breaker per Bellanca Service Letter 61A/Revision A and Drawing SK-2-1040/Revision D; update Airplane Flight Manual with Revision 13 or 14. For Weldon pumps, install a two-position spring-loaded switch, five-amp breaker, and specific placards as outlined.
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Compliance Time
Within 50 hours' time in service after June 26, 1971, or within 10 hours' time in service after September 14, 1971, as applicable.
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Affected Aircraft
Bellanca Model 17-30 airplanes with serial numbers 30002 through 30262, equipped with Airborne Model 2B6-9 or Weldon 4020-A2A/10050-A fuel boost pumps.
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Federal Register Abstract
Fuel Boost Pump Circuit
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_72-13-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 72-13-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Bellanca Model 17-30 Airplanes Subject: Fuel Boost Pump Circuit Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/20/1972 Make: Alexandria Aircraft, LLC Model: 17-30 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 72-13-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1461 AD NUMBER: 72-13-03 SUBJECT HEADING: Airworthiness Directives; Bellanca Model 17-30 Airplanes ACTION: SUMMARY: DATES: Effective June 20, 1972. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 72-13-03 BELLANCA: Amdt. 39-1461. Applies to Model 17-30 Airplanes. Compliance: As indicated below, unless already accomplished. To prevent possible engine flooding when using the fuel boost pump, accomplish either Part A or Part B as applicable: PART A 1. On those airplanes equipped with Airborne Model 2B6-9 fuel boost pumps (Airplane serial numbers 30217 through 30262 were delivered from the factory with this model pump installed) which have not been modified in accordance with AD 71-13-04: a. Within 50 hours' time in service after June 26, 1971, modify the fuel boost pump electrical circuit by installing a three (3) position toggle switch, a three (3) ohm twenty (20) watt resistor, a switch guard and a five (5) amp circuit breaker between the bus and the switch in accordance with Bellanca Service Letter No. 61A, Revision A, dated April 26, 1971, or later FAA approved revisions, and Bellanca Drawing SK-2-1040, Sheet 1, Revision D. Do not connect any other equipment to the fuel boost pump circuit. b. Within 50 hours' time in service after June 26, 1971, insert Airplane Flight Manual, Revision No. 13, dated May 26, 1971, in the Airplane Flight Manual. (Revision No. 13 is included in Bellanca Service Kit SK-2-1040 referred to in Service Letter No. 61A, Revision A.) c. Any alternate equivalent method of compliance with Paragraphs a and b above must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, except that an equivalent five (5) amp circuit breaker may be utilized. 2. On those airplanes equipped with Airborne Model 2B6-9 fuel boost pumps (Airplane serial numbers 30217 through 30262 were delivered from the factory with this model pump installed) which have complied with AD 71-13-04: a. Within 50 hours' time in service after the effective date of this AD and install a five (5) amp circuit breaker between the bus and the fuel boost pump switch in accordance with Bellanca Drawing SK-2-1040, Sheet 1, Revision D. Do not connect any other equipment to the fuel boost pump circuit. b. Any alternate equivalent method of compliance with Paragraph a above must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, except that an equivalent five (5) amp circuit breaker may be utilized. PART B On those airplanes equipped with Weldon fuel boost pump Models 4020-A2A or 10050- A (Airplane serial numbers 30002 through 30216) were delivered from the factory with one of these model pumps installed: 1. Effective immediately, do not operate the fuel boost pump any longer than is necessary to achieve required fuel pressure. (Continued use of the fuel boost pump may cause engine flooding under certain operating conditions.) 2. Within 10 hours' time in service after September 14, 1971, install a placard beneath or adjacent to the fuel boost pump switch to read as follows: "TO PREVENT ENGINE FLOODING TURN OFF FUEL BOOST PUMP IMMEDIATELY AFTER FUEL PRESSURE IS RESTORED." NOTE: The operator may make and install this placard using letters approximately 1/8 inch in height. 3. Within 50 hours' time in service after the effective date of this AD: a. Install a two (2) position spring loaded switch and a five (5) amp circuit breaker between the bus and the fuel boost pump switch in accordance with Bellanca Service Letter No. 71, dated February 16, 1972, or later FAA approved revisions, and Bellanca Drawing SK-2-1040, Sheet 2, Revision A. Do not connect any other equipment to the fuel boost pump circuit. b. Insert Airplane Flight Manual, Revision No. 14, dated April 17, 1972, in the Airplane Flight Manual. (Revision No. 14 is included in kit referred to in Service Letter No. 71.) c. Remove placard installed under Part B, Paragraph 2, and install, in same location, placard Bellanca Part No. SK-2-1043 which reads as follows: "AUX FUEL PUMP USE TO RESTORE FUEL PRESSURE RELEASE TO PREVENT ENGINE FLOODING" 4. Any alternate equivalent method of compliance with Part B must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, except that an equivalent five (5) amp circuit breaker may be utilized. This AD supersedes AD 71-13-04. This amendment becomes effective June 20, 1972. FOOTER:
Document Text
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AD Final Rules - DRS_72-13-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 72-13-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Bellanca Model 17-30 Airplanes Subject: Fuel Boost Pump Circuit Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/20/1972 Make: Alexandria Aircraft, LLC Model: 17-30 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 72-13-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1461 AD NUMBER: 72-13-03 SUBJECT HEADING: Airworthiness Directives; Bellanca Model 17-30 Airplanes ACTION: SUMMARY: DATES: Effective June 20, 1972. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 72-13-03 BELLANCA: Amdt. 39-1461. Applies to Model 17-30 Airplanes. Compliance: As indicated below, unless already accomplished. To prevent possible engine flooding when using the fuel boost pump, accomplish either Part A or Part B as applicable: PART A 1. On those airplanes equipped with Airborne Model 2B6-9 fuel boost pumps (Airplane serial numbers 30217 through 30262 were delivered from the factory with this model pump installed) which have not been modified in accordance with AD 71-13-04: a. Within 50 hours' time in service after June 26, 1971, modify the fuel boost pump electrical circuit by installing a three (3) position toggle switch, a three (3) ohm twenty (20) watt resistor, a switch guard and a five (5) amp circuit breaker between the bus and the switch in accordance with Bellanca Service Letter No. 61A, Revision A, dated April 26, 1971, or later FAA approved revisions, and Bellanca Drawing SK-2-1040, Sheet 1, Revision D. Do not connect any other equipment to the fuel boost pump circuit. b. Within 50 hours' time in service after June 26, 1971, insert Airplane Flight Manual, Revision No. 13, dated May 26, 1971, in the Airplane Flight Manual. (Revision No. 13 is included in Bellanca Service Kit SK-2-1040 referred to in Service Letter No. 61A, Revision A.) c. Any alternate equivalent method of compliance with Paragraphs a and b above must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, except that an equivalent five (5) amp circuit breaker may be utilized. 2. On those airplanes equipped with Airborne Model 2B6-9 fuel boost pumps (Airplane serial numbers 30217 through 30262 were delivered from the factory with this model pump installed) which have complied with AD 71-13-04: a. Within 50 hours' time in service after the effective date of this AD and install a five (5) amp circuit breaker between the bus and the fuel boost pump switch in accordance with Bellanca Drawing SK-2-1040, Sheet 1, Revision D. Do not connect any other equipment to the fuel boost pump circuit. b. Any alternate equivalent method of compliance with Paragraph a above must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, except that an equivalent five (5) amp circuit breaker may be utilized. PART B On those airplanes equipped with Weldon fuel boost pump Models 4020-A2A or 10050- A (Airplane serial numbers 30002 through 30216) were delivered from the factory with one of these model pumps installed: 1. Effective immediately, do not operate the fuel boost pump any longer than is necessary to achieve required fuel pressure. (Continued use of the fuel boost pump may cause engine flooding under certain operating conditions.) 2. Within 10 hours' time in service after September 14, 1971, install a placard beneath or adjacent to the fuel boost pump switch to read as follows: "TO PREVENT ENGINE FLOODING TURN OFF FUEL BOOST PUMP IMMEDIATELY AFTER FUEL PRESSURE IS RESTORED." NOTE: The operator may make and install this placard using letters approximately 1/8 inch in height. 3. Within 50 hours' time in service after the effective date of this AD: a. Install a two (2) position spring loaded switch and a five (5) amp circuit breaker between the bus and the fuel boost pump switch in accordance with Bellanca Service Letter No. 71, dated February 16, 1972, or later FAA approved revisions, and Bellanca Drawing SK-2-1040, Sheet 2, Revision A. Do not connect any other equipment to the fuel boost pump circuit. b. Insert Airplane Flight Manual, Revision No. 14, dated April 17, 1972, in the Airplane Flight Manual. (Revision No. 14 is included in kit referred to in Service Letter No. 71.) c. Remove placard installed under Part B, Paragraph 2, and install, in same location, placard Bellanca Part No. SK-2-1043 which reads as follows: "AUX FUEL PUMP USE TO RESTORE FUEL PRESSURE RELEASE TO PREVENT ENGINE FLOODING" 4. Any alternate equivalent method of compliance with Part B must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, except that an equivalent five (5) amp circuit breaker may be utilized. This AD supersedes AD 71-13-04. This amendment becomes effective June 20, 1972. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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