AD 90-02-18 R1
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | SOCATA | TB 10 | Airworthiness Directives; SOCATA GROUPE AEROSPATIALE Models TB 9 and TB 10, TB 20, and TB 21 airplanes |
| aircraft | SOCATA | TB 20 | Airworthiness Directives; SOCATA GROUPE AEROSPATIALE Models TB 9 and TB 10, TB 20, and TB 21 airplanes |
| aircraft | SOCATA | TB 21 | Airworthiness Directives; SOCATA GROUPE AEROSPATIALE Models TB 9 and TB 10, TB 20, and TB 21 airplanes |
| aircraft | SOCATA | TB9 | Airworthiness Directives; SOCATA GROUPE AEROSPATIALE Models TB 9 and TB 10, TB 20, and TB 21 airplanes |
Unsafe Condition
Loss of power due to contamination of the fuel system.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Install applicable SOCATA modification kits 9154 or 9155 within 75 hours time-in-service from February 6, 1990. Replace Dukes fuel pump with Weldon fuel pump and add a check valve for TB 20/SN 1-730 and TB 21/SN 1-730 (unless modified with Modification 66). If parts unavailable, drain fuel tank sump every 50 hours TIS or perform preflight actions per SB 47/1.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 75 hours time-in-service from February 6, 1990
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
SOCATA Models TB 9, TB 10, TB 20, TB 21 (all serial numbers)
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Fuel System
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_90-02-18_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 90-02-18 R1 Document Type: AD Final Rules Docket Number: 89-CE-37-AD Subject Heading: Airworthiness Directives; SOCATA GROUPE AEROSPATIALE Models TB 9 and TB 10, TB 20, and TB 21 airplanes Subject: Fuel System Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/13/1990 Make: SOCATA Model: TB 10 | TB 20 | TB 21 | TB9 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 90-02-18 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 89-CE-37-AD AMENDMENT: 39-6619 AD NUMBER: 90-02-18 R1 SUBJECT HEADING: Airworthiness Directives; SOCATA GROUPE AEROSPATIALE Models TB 9 and TB 10, TB 20, and TB 21 airplanes ACTION: SUMMARY: DATES: This amendment becomes effective on June 13, 1990. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 90-02-18 R1 SOCATA GROUPE AEROSPATIALE: Amendment 39-6454 as revised by Amendment 39-6619. Docket No. 89-CE-37-AD. Applicability: Models TB 9 and TB 10, TB 20, and TB 21 (all serial numbers (S/N)) airplanes certificated in any category. Compliance: As indicated in the body of the AD, unless already accomplished per AD 90-02-18. To preclude loss of power due to contamination of the fuel system, accomplish the following: (a) Within the next 75 hours time-in-service (TIS) from February 6, 1990, except as indicated in paragraph (c) of this AD, modify the fuel system by the installation of the following applicable SOCATA modification kit, as described in SOCATA Service Bulletin (SB) Number 48/2, dated March 1990: Airplanes Kit Number All TB airplanes (S/N 1 through 822, 850 through 887, 889 and subsequent) 9154 Airplanes Kit Number TB 20 (S/N 823 through 849, and 888) 9155 (b) For Models TB 20 and TB 21 (S/N 1 through 730) airplanes (unless modified with SOCATA Modification Number 66), within the next 75 hours TIS from February 6, 1990, except as indicated in paragraph (d) of this AD, modify the fuel system by replacement of the installed Dukes fuel pump with a Weldon fuel pump and the addition of a check valve, in accordance with the instructions contained in SOCATA SB Number 47/1, dated October 1989. (c) If the required parts are not available to accomplish the modification specified in paragraph (a) of this AD, the airplane may continue operation for an additional 150 hours TIS after the compliance time specified in paragraph (a) of this AD provided the fuel tank sump is drained at intervals not to exceed each 50 hours TIS in accordance with the procedures specified in the DESCRIPTION section of SOCATA SB 48/2, dated March 1990. (d) If the required parts are not available to accomplish the modifications specified in paragraph (b) of this AD, the airplane may continue operation for an additional 150 hours TIS after the compliance time specified in paragraph (b) of this AD provided the following preflight actions are accomplished by the pilot prior to each engine start: (i) Select battery (main switch) ON. (ii) Advance the mixture control to FULL RICH. (iii) Select electric fuel boost pump ON. (iv) Advance the throttle until a positive fuel flow is observed on the fuel flow gauge, then retard the throttle and move the mixture control to IDLE/CUTOFF. (v) Select electric fuel boost pump OFF. (vi) Select battery (main switch) OFF. (vii) Visually inspect the electric fuel boost pump area for leaks. (viii) If no positive fuel flow is observed on the fuel flow gauge, or fuel leaks are detected from the electric fuel boost pump, repair or replace the defective component prior to further flight. NOTE: Avoid moving the propeller and standing in the propeller area while inspecting the engine. (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (f) An alternate method of compliance or adjustment of the initial or repetitive compliance times which provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium. NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to SOCATA Groupe Aerospatiale, B.P. 38, 65001 Tarbes, Cedex, France; Telephone 62.51.73.00, or 62.51.73.55 (for Telefax); or the Product Support Manager, U.S., AEROSPATIALE, 2701 Forum Drive, Grand Prairie, Texas 73053; Telephone (214) 641-3614; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This AD revises AD 90-02-18, Amendment 39-6454. This amendment (39-6619, AD 90-12-18 R1) becomes effective on June 13, 1990. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_90-02-18_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 90-02-18 R1 Document Type: AD Final Rules Docket Number: 89-CE-37-AD Subject Heading: Airworthiness Directives; SOCATA GROUPE AEROSPATIALE Models TB 9 and TB 10, TB 20, and TB 21 airplanes Subject: Fuel System Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/13/1990 Make: SOCATA Model: TB 10 | TB 20 | TB 21 | TB9 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: 90-02-18 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 89-CE-37-AD AMENDMENT: 39-6619 AD NUMBER: 90-02-18 R1 SUBJECT HEADING: Airworthiness Directives; SOCATA GROUPE AEROSPATIALE Models TB 9 and TB 10, TB 20, and TB 21 airplanes ACTION: SUMMARY: DATES: This amendment becomes effective on June 13, 1990. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 90-02-18 R1 SOCATA GROUPE AEROSPATIALE: Amendment 39-6454 as revised by Amendment 39-6619. Docket No. 89-CE-37-AD. Applicability: Models TB 9 and TB 10, TB 20, and TB 21 (all serial numbers (S/N)) airplanes certificated in any category. Compliance: As indicated in the body of the AD, unless already accomplished per AD 90-02-18. To preclude loss of power due to contamination of the fuel system, accomplish the following: (a) Within the next 75 hours time-in-service (TIS) from February 6, 1990, except as indicated in paragraph (c) of this AD, modify the fuel system by the installation of the following applicable SOCATA modification kit, as described in SOCATA Service Bulletin (SB) Number 48/2, dated March 1990: Airplanes Kit Number All TB airplanes (S/N 1 through 822, 850 through 887, 889 and subsequent) 9154 Airplanes Kit Number TB 20 (S/N 823 through 849, and 888) 9155 (b) For Models TB 20 and TB 21 (S/N 1 through 730) airplanes (unless modified with SOCATA Modification Number 66), within the next 75 hours TIS from February 6, 1990, except as indicated in paragraph (d) of this AD, modify the fuel system by replacement of the installed Dukes fuel pump with a Weldon fuel pump and the addition of a check valve, in accordance with the instructions contained in SOCATA SB Number 47/1, dated October 1989. (c) If the required parts are not available to accomplish the modification specified in paragraph (a) of this AD, the airplane may continue operation for an additional 150 hours TIS after the compliance time specified in paragraph (a) of this AD provided the fuel tank sump is drained at intervals not to exceed each 50 hours TIS in accordance with the procedures specified in the DESCRIPTION section of SOCATA SB 48/2, dated March 1990. (d) If the required parts are not available to accomplish the modifications specified in paragraph (b) of this AD, the airplane may continue operation for an additional 150 hours TIS after the compliance time specified in paragraph (b) of this AD provided the following preflight actions are accomplished by the pilot prior to each engine start: (i) Select battery (main switch) ON. (ii) Advance the mixture control to FULL RICH. (iii) Select electric fuel boost pump ON. (iv) Advance the throttle until a positive fuel flow is observed on the fuel flow gauge, then retard the throttle and move the mixture control to IDLE/CUTOFF. (v) Select electric fuel boost pump OFF. (vi) Select battery (main switch) OFF. (vii) Visually inspect the electric fuel boost pump area for leaks. (viii) If no positive fuel flow is observed on the fuel flow gauge, or fuel leaks are detected from the electric fuel boost pump, repair or replace the defective component prior to further flight. NOTE: Avoid moving the propeller and standing in the propeller area while inspecting the engine. (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (f) An alternate method of compliance or adjustment of the initial or repetitive compliance times which provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium. NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to SOCATA Groupe Aerospatiale, B.P. 38, 65001 Tarbes, Cedex, France; Telephone 62.51.73.00, or 62.51.73.55 (for Telefax); or the Product Support Manager, U.S., AEROSPATIALE, 2701 Forum Drive, Grand Prairie, Texas 73053; Telephone (214) 641-3614; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This AD revises AD 90-02-18, Amendment 39-6454. This amendment (39-6619, AD 90-12-18 R1) becomes effective on June 13, 1990. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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