AD 92-14-01
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Saab AB, Saab Aerosystems | SAAB 340B | Airworthiness Directives; SAAB-SCANIA Model SAAB SF340A and SAAB 340BSeries Airplanes |
| aircraft | Saab AB, Saab Aerosystems | 340A (SAAB SF340A) | Airworthiness Directives; SAAB-SCANIA Model SAAB SF340A and SAAB 340BSeries Airplanes |
Unsafe Condition
Loss of structural integrity of the powerplant installation and subsequent damage to the engine forward frame.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect upper and lower drag strut attachment fittings and adjacent skin area, upper longeron and attaching frame, and angle attaching the frame to the side wall for loose fasteners, loose fittings, and cracks; torque inspect MS21042 nuts. If loose fasteners or fittings are found, perform a detailed inspection. If nuts are out of torque tolerance, retorque. If cracks are found, repair as approved. Additionally, inspect drag strut attaching holes for elongation, damage, and abnormal wear, and repair if necessary. Conduct a detailed inspection of lower drag strut attachment holes and related areas, and repair if defects or excessive damage are found.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 1,500 hours time-in-service after the effective date; thereafter at intervals not to exceed 1,500 hours time-in-service for initial inspections. For drag strut attaching holes inspections, within 3,000 hours time-in-service after the effective date; thereafter at intervals not to exceed 3,000 hours time-in-service. For lower drag strut attachment holes inspection, prior to the total accumulation of 22,000 landings or within 500 landings after the effective date, whichever occurs later.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Saab AB, Saab Aerosystems Model SAAB 340B and 340A (SAAB SF340A) airplanes, serial numbers 004 through 159 for SF340A, and 160 through 166 for 340B.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Powerplant Installation
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_92-14-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 92-14-01 Document Type: AD Final Rules Docket Number: 92-NM-07-AD Subject Heading: Airworthiness Directives; SAAB-SCANIA Model SAAB SF340A and SAAB 340BSeries Airplanes Subject: Powerplant Installation Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/18/1992 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: 92-14-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 92-NM-07-AD AMENDMENT: 39-8283 AD NUMBER: 92-14-01 SUBJECT HEADING: Airworthiness Directives; SAAB-SCANIA Model SAAB SF340A and SAAB 340BSeries Airplanes ACTION: Final rule SUMMARY: DATES: Effective August 18, 1992. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 92-14-01 SAAB-SCANIA: Amendment 39-8283. Docket No. 92-NM-07-AD. Applicability: Model SAAB SF340A series airplanes, serial numbers 004 through 159, inclusive; and Model SAAB 340B series airplanes, serial numbers 160 through 166, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent loss of structural integrity of the powerplant installation and subsequent damage to the engine forward frame, accomplish the following: (a) If, when accomplishing the inspections required by AD 90-05-10, Amendment 39-6530 (reference SAAB Service Bulletin 340-54-026), it was determined that MS21042 nuts had already been installed, and no change from collars to nuts had taken place, then accomplishment of this AD is not required. (b) Except as provided in paragraph (a) of this AD, within 1,500 hours time-in-service after the effective date of this AD; and thereafter at intervals not to exceed 1,500 hours time-in-service; accomplish a visual inspection of the upper and lower drag strut attachment fittings and the adjacent skin area, the upper longeron and attaching frame, and the angle attaching the frame to the side wall to detect loose fasteners, loose fittings, and cracks; and accomplish a torque inspection of the MS21042 nuts, in accordance with section 1.B.(i) of SAAB Service Bulletin 340-54-027, Revision 2, dated March 10, 1992. (1) If loose fasteners or fittings are found, prior to further flight, perform the detailed inspection required by paragraph (c) of this AD. (2) If the installed MS21042 nuts are not loose, check the torque; and retorque, prior to further flight, if nuts are out of torque tolerance. (3) If cracks are found, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (c) Except as provided in paragraph (a) of this AD, within 3,000 hours time-in-service after the effective date of this AD; and thereafter at intervals not to exceed 3,000 hours time-in-service; inspect the drag strut attaching holes at each end of the drag strut (one upper and one lower attach fitting) to detect elongation, damage, and abnormal wear, in accordance with section 2.B.(ii) of SAAB Service Bulletin 340-54-027, Revision 2, dated March 10, 1992. (1) If any holes are elongated or outside the specified tolerance, prior to further flight, repair in accordance with sections E. and F. of the service bulletin, as appropriate. (2) If any damage found exceeds the limits of the modifications described in the service bulletin, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (d) Except as provided in paragraph (a) of this AD, prior to the total accumulation of 22,000 landings, or within 500 landings after the effective date of this AD, whichever occurs later, accomplish a detailed inspection of the lower drag strut attachment holes (Eddy Bolt/Hi-Lok) of the lower drag strut fitting, the inner side beam skin and the upper longerons, and the drag strut attachment holes in the upper and lower fittings, in accordance with section 2.D. of SAAB Service Bulletin 340-54-027, Revision 2, dated March 10, 1992. (1) If the attaching holes are elongated or out of the specified tolerance, prior to further flight, repair in accordance with sections E. and F. of the service bulletin, as appropriate. (2) If defects such as gouges, nicks, cracks, and creases are found, or if the damage found exceeds the limits of the modifications described in the service bulletin, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (e) Accomplishment of paragraph (d) of this AD constitutes terminating action for the requirements of paragraphs (b) and (c) of this AD. (f) 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. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (g) 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. (h) The inspections and repair shall be done in accordance with SAAB Service Bulletin 340-54-027, Revision 2, dated March 10, 1992, which incorporates the following list of effective pages: Page Number Revision Level Date 1-3, 5-12, 14 1 July 4, 1991 4, 13 2 March 10, 1992 15-20 Original Undated 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, 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, 1100 L Street NW., Room 8401, Washington, DC. (i) This amendment becomes effective on August 18, 1992. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_92-14-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 92-14-01 Document Type: AD Final Rules Docket Number: 92-NM-07-AD Subject Heading: Airworthiness Directives; SAAB-SCANIA Model SAAB SF340A and SAAB 340BSeries Airplanes Subject: Powerplant Installation Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/18/1992 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: 92-14-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 92-NM-07-AD AMENDMENT: 39-8283 AD NUMBER: 92-14-01 SUBJECT HEADING: Airworthiness Directives; SAAB-SCANIA Model SAAB SF340A and SAAB 340BSeries Airplanes ACTION: Final rule SUMMARY: DATES: Effective August 18, 1992. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 92-14-01 SAAB-SCANIA: Amendment 39-8283. Docket No. 92-NM-07-AD. Applicability: Model SAAB SF340A series airplanes, serial numbers 004 through 159, inclusive; and Model SAAB 340B series airplanes, serial numbers 160 through 166, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent loss of structural integrity of the powerplant installation and subsequent damage to the engine forward frame, accomplish the following: (a) If, when accomplishing the inspections required by AD 90-05-10, Amendment 39-6530 (reference SAAB Service Bulletin 340-54-026), it was determined that MS21042 nuts had already been installed, and no change from collars to nuts had taken place, then accomplishment of this AD is not required. (b) Except as provided in paragraph (a) of this AD, within 1,500 hours time-in-service after the effective date of this AD; and thereafter at intervals not to exceed 1,500 hours time-in-service; accomplish a visual inspection of the upper and lower drag strut attachment fittings and the adjacent skin area, the upper longeron and attaching frame, and the angle attaching the frame to the side wall to detect loose fasteners, loose fittings, and cracks; and accomplish a torque inspection of the MS21042 nuts, in accordance with section 1.B.(i) of SAAB Service Bulletin 340-54-027, Revision 2, dated March 10, 1992. (1) If loose fasteners or fittings are found, prior to further flight, perform the detailed inspection required by paragraph (c) of this AD. (2) If the installed MS21042 nuts are not loose, check the torque; and retorque, prior to further flight, if nuts are out of torque tolerance. (3) If cracks are found, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (c) Except as provided in paragraph (a) of this AD, within 3,000 hours time-in-service after the effective date of this AD; and thereafter at intervals not to exceed 3,000 hours time-in-service; inspect the drag strut attaching holes at each end of the drag strut (one upper and one lower attach fitting) to detect elongation, damage, and abnormal wear, in accordance with section 2.B.(ii) of SAAB Service Bulletin 340-54-027, Revision 2, dated March 10, 1992. (1) If any holes are elongated or outside the specified tolerance, prior to further flight, repair in accordance with sections E. and F. of the service bulletin, as appropriate. (2) If any damage found exceeds the limits of the modifications described in the service bulletin, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (d) Except as provided in paragraph (a) of this AD, prior to the total accumulation of 22,000 landings, or within 500 landings after the effective date of this AD, whichever occurs later, accomplish a detailed inspection of the lower drag strut attachment holes (Eddy Bolt/Hi-Lok) of the lower drag strut fitting, the inner side beam skin and the upper longerons, and the drag strut attachment holes in the upper and lower fittings, in accordance with section 2.D. of SAAB Service Bulletin 340-54-027, Revision 2, dated March 10, 1992. (1) If the attaching holes are elongated or out of the specified tolerance, prior to further flight, repair in accordance with sections E. and F. of the service bulletin, as appropriate. (2) If defects such as gouges, nicks, cracks, and creases are found, or if the damage found exceeds the limits of the modifications described in the service bulletin, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (e) Accomplishment of paragraph (d) of this AD constitutes terminating action for the requirements of paragraphs (b) and (c) of this AD. (f) 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. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (g) 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. (h) The inspections and repair shall be done in accordance with SAAB Service Bulletin 340-54-027, Revision 2, dated March 10, 1992, which incorporates the following list of effective pages: Page Number Revision Level Date 1-3, 5-12, 14 1 July 4, 1991 4, 13 2 March 10, 1992 15-20 Original Undated 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, 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, 1100 L Street NW., Room 8401, Washington, DC. (i) This amendment becomes effective on August 18, 1992. FOOTER:
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Retrieved: Apr 8, 2026
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