AD 92-14-04
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Fokker | F-28 0100 | Airworthiness Directives; FOKKER Model F-28 Mark 0100 Series Airplanes |
Unsafe Condition
Reduced structural capability of the vertical stabilizer due to potential cracks in rivet holes exceeding 0.8 mm in length.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Disassemble the vertical stabilizer per service bulletin steps, inspect rivet holes for cracks, and modify or repair based on crack length. Repair required before further flight if cracks are 0.8 mm or longer.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Prior to the accumulation of 6,500 landings, or within 60 days after the effective date of this AD, whichever occurs later.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
FOKKER Model F-28 Mark 0100 series airplanes with serial numbers 11244, 11245, 11250 through 11256, inclusive, and 11268 through 11273, inclusive.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Vertical Stabilizer
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_92-14-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 92-14-04 Document Type: AD Final Rules Docket Number: 91-NM-211-AD Subject Heading: Airworthiness Directives; FOKKER Model F-28 Mark 0100 Series Airplanes Subject: Vertical Stabilizer Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/18/1992 Make: Model: F.28 Mark 0100 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 92-14-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 91-NM-211-AD AMENDMENT: 39-8286 AD NUMBER: 92-14-04 SUBJECT HEADING: Airworthiness Directives; FOKKER Model F-28 Mark 0100 Series Airplanes ACTION: SUMMARY: DATES: Effective August 18, 1992. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 92-14-04 FOKKER: Amendment 39-8286. Docket No. 91-NM-211-AD. Applicability: Model F-28 Mark 0100 series airplanes; serial numbers 11244, 11245, 11250 through 11256, inclusive, and 11268 through 11273, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural capability of the vertical stabilizer, accomplish the following: (a) For airplanes having serial numbers 11244, and 11250 through 11256, inclusive: Prior to the accumulation of 6,500 landings, or within 60 days after the effective date of this AD, whichever occurs later, disassemble the vertical stabilizer in accordance with Part 1, Steps A. through C., of Fokker Service Bulletin SBF100-55-011, dated October 1, 1991. (1) For airplanes that have accumulated 3,000 or fewer landings at the time the airplane is disassembled to comply with paragraph (a) of this AD, modify the vertical stabilizer, in accordance with Part 1, Steps E. through G., of the service bulletin. (2) For airplanes that have accumulated more than 3,000 landings at the time the airplane is disassembled to comply with paragraph (a) of this AD, inspect the rivet holes for cracks, in accordance with Part 1, Step D., of the service bulletin. (i) If no cracks are found, or if cracks are found that are less than 0.8 mm in length, modify the vertical stabilizer, in accordance with Part 1, Steps E. through G., of the service bulletin. (ii) If any crack is found that is 0.8 mm or longer, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (b) For airplanes having serial numbers 11245, and 11268 through 11273, inclusive: Prior to the accumulation of 6,500 landings, or within 60 days after the effective date of this AD, whichever occurs later, disassemble the vertical stabilizer in accordance with Part 2, Steps A. through C., of Fokker Service Bulletin SBF100-55-011, dated October 1, 1991. (1) For airplanes that have accumulated 3,000 or fewer landings at the time the airplane is disassembled to comply with paragraph (b) of this AD, modify the vertical stabilizer, in accordance with Part 2, Steps E. through G., of the service bulletin. (2) For airplanes that have accumulated more than 3,000 landings at the time the airplane is disassembled to comply with paragraph (b) of this AD, inspect the rivet holes for cracks, in accordance with Part 2, Step D., of the service bulletin. (i) If no cracks are found, or if cracks are found that are less than 0.8 mm in length, modify the vertical stabilizer, in accordance with Part 2, Steps E. through G., of the service bulletin. (ii) If any crack is found that is 0.8 mm or longer, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (c) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Standardization Branch. (d) 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. (e) The inspections and modifications shall be done in accordance with Fokker Service Bulletin SBF100-55-011, dated October 1, 1991. 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. 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. (f) This amendment becomes effective on August 18, 1992. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_92-14-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 92-14-04 Document Type: AD Final Rules Docket Number: 91-NM-211-AD Subject Heading: Airworthiness Directives; FOKKER Model F-28 Mark 0100 Series Airplanes Subject: Vertical Stabilizer Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/18/1992 Make: Model: F.28 Mark 0100 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: 92-14-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 91-NM-211-AD AMENDMENT: 39-8286 AD NUMBER: 92-14-04 SUBJECT HEADING: Airworthiness Directives; FOKKER Model F-28 Mark 0100 Series Airplanes ACTION: SUMMARY: DATES: Effective August 18, 1992. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 92-14-04 FOKKER: Amendment 39-8286. Docket No. 91-NM-211-AD. Applicability: Model F-28 Mark 0100 series airplanes; serial numbers 11244, 11245, 11250 through 11256, inclusive, and 11268 through 11273, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural capability of the vertical stabilizer, accomplish the following: (a) For airplanes having serial numbers 11244, and 11250 through 11256, inclusive: Prior to the accumulation of 6,500 landings, or within 60 days after the effective date of this AD, whichever occurs later, disassemble the vertical stabilizer in accordance with Part 1, Steps A. through C., of Fokker Service Bulletin SBF100-55-011, dated October 1, 1991. (1) For airplanes that have accumulated 3,000 or fewer landings at the time the airplane is disassembled to comply with paragraph (a) of this AD, modify the vertical stabilizer, in accordance with Part 1, Steps E. through G., of the service bulletin. (2) For airplanes that have accumulated more than 3,000 landings at the time the airplane is disassembled to comply with paragraph (a) of this AD, inspect the rivet holes for cracks, in accordance with Part 1, Step D., of the service bulletin. (i) If no cracks are found, or if cracks are found that are less than 0.8 mm in length, modify the vertical stabilizer, in accordance with Part 1, Steps E. through G., of the service bulletin. (ii) If any crack is found that is 0.8 mm or longer, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (b) For airplanes having serial numbers 11245, and 11268 through 11273, inclusive: Prior to the accumulation of 6,500 landings, or within 60 days after the effective date of this AD, whichever occurs later, disassemble the vertical stabilizer in accordance with Part 2, Steps A. through C., of Fokker Service Bulletin SBF100-55-011, dated October 1, 1991. (1) For airplanes that have accumulated 3,000 or fewer landings at the time the airplane is disassembled to comply with paragraph (b) of this AD, modify the vertical stabilizer, in accordance with Part 2, Steps E. through G., of the service bulletin. (2) For airplanes that have accumulated more than 3,000 landings at the time the airplane is disassembled to comply with paragraph (b) of this AD, inspect the rivet holes for cracks, in accordance with Part 2, Step D., of the service bulletin. (i) If no cracks are found, or if cracks are found that are less than 0.8 mm in length, modify the vertical stabilizer, in accordance with Part 2, Steps E. through G., of the service bulletin. (ii) If any crack is found that is 0.8 mm or longer, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (c) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Standardization Branch. (d) 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. (e) The inspections and modifications shall be done in accordance with Fokker Service Bulletin SBF100-55-011, dated October 1, 1991. 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. 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. (f) This amendment becomes effective on August 18, 1992. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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