AD 92-22-13
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Saab AB, Saab Aerosystems | SAAB 340B | Airworthiness Directives; SAAB-SCANIA Models SAAB SF340A and SAAB 340B Series Airplanes |
| aircraft | Saab AB, Saab Aerosystems | 340A (SAAB SF340A) | Airworthiness Directives; SAAB-SCANIA Models SAAB SF340A and SAAB 340B Series Airplanes |
Unsafe Condition
Corrosion on the wing upper panel in the fuel tank access door area could reduce strength and cause fuel leakage.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Within 6 months after the effective date, perform a visual inspection for corrosion on the wing upper panel in the fuel tank access door area per SAAB Service Bulletin 340-57-020, Revision 1. If corrosion is found, blend/grind it out, measure thickness, apply surface treatments if within tolerances, or repair if outside tolerances before further flight. A second inspection must be done within 6 months after the first, followed by installing protection plates and surface treatments before further flight.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 6 months after the effective date of this AD, and a second inspection within 6 months after accomplishing paragraph (a).
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
SAAB-SCANIA Models SAAB SF340A and SAAB 340B series airplanes listed in SAAB Service Bulletin 340-57-020, Revision 1.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Wing Upper Panel
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_92-22-13.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 92-22-13 Document Type: AD Final Rules Docket Number: 92-NM-122-AD Subject Heading: Airworthiness Directives; SAAB-SCANIA Models SAAB SF340A and SAAB 340B Series Airplanes Subject: Wing Upper Panel Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 12/03/1992 Make: Saab AB, Saab Aerosystems Model: SAAB 340B | 340A (SAAB SF340A) Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 92-22-13 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 92-NM-122-AD AMENDMENT: 39-8400 AD NUMBER: 92-22-13 SUBJECT HEADING: Airworthiness Directives; SAAB-SCANIA Models SAAB SF340A and SAAB 340B Series Airplanes ACTION: Final rule SUMMARY: DATES: Effective December 3, 1992. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 92-22-13 SAAB-SCANIA: Amendment 39-8400. Docket No. 92-NM-122-AD. Applicability: Models SAAB SF340A and SAAB 340B series airplanes; as listed in SAAB Service Bulletin 340-57-020, Revision 1, dated April 3, 1992; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the reduction of strength of the wing upper panel and possible fuel leakage, accomplish the following: (a) Within 6 months after the effective date of this AD, perform a visual inspection for corrosion on the wing upper panel in the fuel tank access door area, in accordance with SAAB Service Bulletin 340-57-020, Revision 1, dated April 3, 1992. (1) If corrosion is detected, prior to further flight, blend or grind it out, and measure the thickness of the blended or ground part, in accordance with the service bulletin. (i) If the thickness of the blended or ground part is within the tolerances specified in the service bulletin, apply surface treatments in accordance with the service bulletin. (ii) If the blended or ground part is outside the tolerances specified in the service bulletin, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (2) If corrosion is not found, apply surface treatments in accordance with the service bulletin. (b) Within 6 months after accomplishing paragraph (a) of this AD, perform a second visual inspection to detect corrosion on the wing upper panel in the fuel tank access door area, in accordance with SAAB Service Bulletin 340-57-020, Revision 1, dated April 3, 1992. (1) If corrosion is detected, prior to further flight, blend or grind it out, and measure the thickness of the blended or ground part, in accordance with the service bulletin. (i) If the thickness of the blended or ground part is within the tolerances specified in the service bulletin, apply surface treatments in accordance with the service bulletin. (ii) If the blended or ground part is outside the tolerances specified in the service bulletin, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (2) If corrosion is not found, apply surface treatments in accordance with the service bulletin. (3) Following the visual inspection and repairs required by paragraph (b) of this AD, prior to further flight, install protection plates on all fuel tank access hole doublers, and apply surface treatments, in accordance with the service bulletin. (c) Installation of protection plates on all fuel tank access hole doublers and application of surface treatments, in accordance with SAAB Service Bulletin 340-57-020, Revision 1, dated April 3, 1992, that is accomplished prior to further flight following the visual inspection required by paragraph (a) of this AD, constitutes terminating action for the visual inspection required by paragraph (b) of this AD. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The inspections, corrective actions, and the surface treatments shall be done in accordance with SAAB Service Bulletin 340-57-020, Revision 1, dated April 3, 1992, which contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1-5, 8-18 Original (Not Dated) 6-7, 19-20 1 April 3, 1992 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from SAAB-SCANIA AB, SAAB Aircraft Product Support, S-581 88, Linkoping, Sweden. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on December 3, 1992. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_92-22-13.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 92-22-13 Document Type: AD Final Rules Docket Number: 92-NM-122-AD Subject Heading: Airworthiness Directives; SAAB-SCANIA Models SAAB SF340A and SAAB 340B Series Airplanes Subject: Wing Upper Panel Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 12/03/1992 Make: Saab AB, Saab Aerosystems Model: SAAB 340B | 340A (SAAB SF340A) Product Type: Aircraft Product Subtype: Large 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: 92-22-13 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 92-NM-122-AD AMENDMENT: 39-8400 AD NUMBER: 92-22-13 SUBJECT HEADING: Airworthiness Directives; SAAB-SCANIA Models SAAB SF340A and SAAB 340B Series Airplanes ACTION: Final rule SUMMARY: DATES: Effective December 3, 1992. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 92-22-13 SAAB-SCANIA: Amendment 39-8400. Docket No. 92-NM-122-AD. Applicability: Models SAAB SF340A and SAAB 340B series airplanes; as listed in SAAB Service Bulletin 340-57-020, Revision 1, dated April 3, 1992; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the reduction of strength of the wing upper panel and possible fuel leakage, accomplish the following: (a) Within 6 months after the effective date of this AD, perform a visual inspection for corrosion on the wing upper panel in the fuel tank access door area, in accordance with SAAB Service Bulletin 340-57-020, Revision 1, dated April 3, 1992. (1) If corrosion is detected, prior to further flight, blend or grind it out, and measure the thickness of the blended or ground part, in accordance with the service bulletin. (i) If the thickness of the blended or ground part is within the tolerances specified in the service bulletin, apply surface treatments in accordance with the service bulletin. (ii) If the blended or ground part is outside the tolerances specified in the service bulletin, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (2) If corrosion is not found, apply surface treatments in accordance with the service bulletin. (b) Within 6 months after accomplishing paragraph (a) of this AD, perform a second visual inspection to detect corrosion on the wing upper panel in the fuel tank access door area, in accordance with SAAB Service Bulletin 340-57-020, Revision 1, dated April 3, 1992. (1) If corrosion is detected, prior to further flight, blend or grind it out, and measure the thickness of the blended or ground part, in accordance with the service bulletin. (i) If the thickness of the blended or ground part is within the tolerances specified in the service bulletin, apply surface treatments in accordance with the service bulletin. (ii) If the blended or ground part is outside the tolerances specified in the service bulletin, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (2) If corrosion is not found, apply surface treatments in accordance with the service bulletin. (3) Following the visual inspection and repairs required by paragraph (b) of this AD, prior to further flight, install protection plates on all fuel tank access hole doublers, and apply surface treatments, in accordance with the service bulletin. (c) Installation of protection plates on all fuel tank access hole doublers and application of surface treatments, in accordance with SAAB Service Bulletin 340-57-020, Revision 1, dated April 3, 1992, that is accomplished prior to further flight following the visual inspection required by paragraph (a) of this AD, constitutes terminating action for the visual inspection required by paragraph (b) of this AD. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The inspections, corrective actions, and the surface treatments shall be done in accordance with SAAB Service Bulletin 340-57-020, Revision 1, dated April 3, 1992, which contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1-5, 8-18 Original (Not Dated) 6-7, 19-20 1 April 3, 1992 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from SAAB-SCANIA AB, SAAB Aircraft Product Support, S-581 88, Linkoping, Sweden. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on December 3, 1992. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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