AD 90-20-18
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | 727-100 Series | Airworthiness Directives; BOEING Model 727 Series Airplanes |
| aircraft | The Boeing Company | 727-100C Series | Airworthiness Directives; BOEING Model 727 Series Airplanes |
| aircraft | The Boeing Company | 727-200 Series | Airworthiness Directives; BOEING Model 727 Series Airplanes |
| aircraft | The Boeing Company | 727-200F Series | Airworthiness Directives; BOEING Model 727 Series Airplanes |
| aircraft | The Boeing Company | 727 Series | Airworthiness Directives; BOEING Model 727 Series Airplanes |
| aircraft | The Boeing Company | 727C Series | Airworthiness Directives; BOEING Model 727 Series Airplanes |
Unsafe Condition
Delamination of the upper body skin bonded tear straps from Fuselage Station 277 to Station 1130 and corrosion in delaminated areas.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect upper body skin bonded tear straps for delamination using ultrasonic methods per Boeing Service Bulletin 727-53-0082. Inspect for corrosion in delaminated areas before further flight. Perform repetitive inspections at intervals not exceeding 24 or 30 months depending on airplane group. Repair delaminations or corrosion exceeding limits, replace blind fasteners with solid fasteners within specified landing limits.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 14 months from August 20, 1981 (the effective date of Amendment 39-4194), and subsequent intervals as specified.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Boeing Model 727 series airplanes listed in Boeing Service Bulletin 727-53-0082, Revision 5, dated November 9, 1989.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Upper Body Skin Inspection
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_90-20-18.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 90-20-18 Document Type: AD Final Rules Docket Number: 90-NM-46-AD Subject Heading: Airworthiness Directives; BOEING Model 727 Series Airplanes Subject: Upper Body Skin Inspection Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/29/1990 Make: The Boeing Company Model: 727-100 Series | 727-100C Series | 727-200 Series | 727-200F Series | 727 Series | 727C Series 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: 90-20-18 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 90-NM-46-AD AMENDMENT: 39-6747 AD NUMBER: 90-20-18 SUBJECT HEADING: Airworthiness Directives; BOEING Model 727 Series Airplanes ACTION: SUMMARY: DATES: Effective October 29, 1990. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 90-20-18 BOEING: Amendment 39-6747. Docket No. 90-NM-46-AD. Applicability: Model 727 series airplanes, listed in Boeing Service Bulletin 727-53-0082, Revision 5, dated November 9, 1989, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect delamination of the upper body skin bonded tear straps from Fuselage Station 277 to Station 1130, accomplish the following: A. Within 14 months from August 20, 1981 (the effective date of Amendment 39-4194), inspect the upper body skin bonded tear straps for delamination from the upper body skin in accordance with the ultrasonic inspection procedures described in Boeing Service Bulletin 727-53-0082, Revision 3, dated June 19, 1981; Revision 4, dated April 16, 1982; or Revision 5, dated November 9, 1989. B. If the ultrasonic inspection required by paragraph A. of this AD reveals areas of delamination, prior to further flight, inspect the areas for corrosion in accordance with Boeing Service Bulletin 727-53-0082, Revision 5. C. Perform either of the following repetitive inspections: 1. Within 24 months from the initial inspection, reinspect as required by paragraph A. of this AD, and in accordance with the following schedule: a. Repeat inspections for Group I airplanes starting with Zone I, alternating between Zones I, II, and III at intervals not to exceed 24 months, in accordance with Boeing Service Bulletin 727-53- 0082, Revision 3, 4, or 5. b. Repeat inspections for Group II airplanes alternating between Zones I and II at intervals not to exceed 24 months, in accordance with Boeing Service Bulletin 727-53-0082, Revision 3, 4, or 5. c. Any strap found delaminated, while inspecting a zone, must be inspected along its entire length (e.g., stringer 14R to stringer 14L) prior to further flight. 2. Within 30 months from the initial inspection, reinspect Zones I, II, and, if applicable, Zone III, as required by paragraph A. of this AD. Repeat the inspection at intervals not to exceed 30 months. D. If tear strap corrosion is detected or bond delaminations exceed the limits specified in Boeing Service Bulletin 727-53-0082, Revision 5, prior to further flight, repair in accordance with the service bulletin. E. If tear strap corrosion is not detected and bond delaminations are within the limits specified in Boeing Service Bulletin 727-53-0082, Revision 5, perform either of the following: 1. Repair in accordance with the service bulletin prior to further flight. 2. Reinspect for delamination growth and corrosion at intervals not to exceed 24 months in accordance with the service bulletin. F. Repairs or modifications made in accordance with Boeing 727 Structural Repair Manual Subject 53-30-4, Paragraph 2.C., Method II or V; or Paragraph 2.D., Method III; terminate the inspection requirements of paragraph C. of this AD for the repaired area. G. Blind fasteners installed in accordance with Boeing 727 Structural Repair Manual Subject 53-30-4, Paragraph 2.D., Method IV, are approved as an interim repair only. Inspect blind fastener repair for loose or missing fasteners within the next 3,000 landings after the effective date of this AD, and thereafter at intervals not to exceed 2,500 landings. 1. Replace the tear strap blind splice fasteners with solid fasteners prior to accumulating 10,000 landings or within the next 10,000 landings after the effective date of this AD, whichever occurs later. NOTE: Splice fasteners are the 9 rivets at the terminating end of a tear strap. Each body station that has tear straps has 4 locations where the tear straps terminate with 9 splice rivets; just above stringer (S) 4L, S-4R, S-10L, and S-10R. 2. Replace the remaining tear strap blind fasteners with solid fasteners prior to accumulating 20,000 landings or within the next 10,000 landings after the effective date of this AD, whichever occurs later. In skin gauges .063 inches or greater, use solid fastener BACR15CE6D. In skin gauges less than .063 inches, use solid fastener MS20470D6. Replacement with solid fasteners terminates the inspection requirements of this AD for the repaired area. H. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Northwest Mountain Region. NOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. I. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue, S.W., Renton, Washington. Airworthiness Directive 90-20-18 supersedes AD 81-17-07, Amendment 39-4191. This amendment (39-6747, AD 90-20-18) becomes effective on October 29, 1990. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_90-20-18.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 90-20-18 Document Type: AD Final Rules Docket Number: 90-NM-46-AD Subject Heading: Airworthiness Directives; BOEING Model 727 Series Airplanes Subject: Upper Body Skin Inspection Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/29/1990 Make: The Boeing Company Model: 727-100 Series | 727-100C Series | 727-200 Series | 727-200F Series | 727 Series | 727C Series 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: 90-20-18 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 90-NM-46-AD AMENDMENT: 39-6747 AD NUMBER: 90-20-18 SUBJECT HEADING: Airworthiness Directives; BOEING Model 727 Series Airplanes ACTION: SUMMARY: DATES: Effective October 29, 1990. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 90-20-18 BOEING: Amendment 39-6747. Docket No. 90-NM-46-AD. Applicability: Model 727 series airplanes, listed in Boeing Service Bulletin 727-53-0082, Revision 5, dated November 9, 1989, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect delamination of the upper body skin bonded tear straps from Fuselage Station 277 to Station 1130, accomplish the following: A. Within 14 months from August 20, 1981 (the effective date of Amendment 39-4194), inspect the upper body skin bonded tear straps for delamination from the upper body skin in accordance with the ultrasonic inspection procedures described in Boeing Service Bulletin 727-53-0082, Revision 3, dated June 19, 1981; Revision 4, dated April 16, 1982; or Revision 5, dated November 9, 1989. B. If the ultrasonic inspection required by paragraph A. of this AD reveals areas of delamination, prior to further flight, inspect the areas for corrosion in accordance with Boeing Service Bulletin 727-53-0082, Revision 5. C. Perform either of the following repetitive inspections: 1. Within 24 months from the initial inspection, reinspect as required by paragraph A. of this AD, and in accordance with the following schedule: a. Repeat inspections for Group I airplanes starting with Zone I, alternating between Zones I, II, and III at intervals not to exceed 24 months, in accordance with Boeing Service Bulletin 727-53- 0082, Revision 3, 4, or 5. b. Repeat inspections for Group II airplanes alternating between Zones I and II at intervals not to exceed 24 months, in accordance with Boeing Service Bulletin 727-53-0082, Revision 3, 4, or 5. c. Any strap found delaminated, while inspecting a zone, must be inspected along its entire length (e.g., stringer 14R to stringer 14L) prior to further flight. 2. Within 30 months from the initial inspection, reinspect Zones I, II, and, if applicable, Zone III, as required by paragraph A. of this AD. Repeat the inspection at intervals not to exceed 30 months. D. If tear strap corrosion is detected or bond delaminations exceed the limits specified in Boeing Service Bulletin 727-53-0082, Revision 5, prior to further flight, repair in accordance with the service bulletin. E. If tear strap corrosion is not detected and bond delaminations are within the limits specified in Boeing Service Bulletin 727-53-0082, Revision 5, perform either of the following: 1. Repair in accordance with the service bulletin prior to further flight. 2. Reinspect for delamination growth and corrosion at intervals not to exceed 24 months in accordance with the service bulletin. F. Repairs or modifications made in accordance with Boeing 727 Structural Repair Manual Subject 53-30-4, Paragraph 2.C., Method II or V; or Paragraph 2.D., Method III; terminate the inspection requirements of paragraph C. of this AD for the repaired area. G. Blind fasteners installed in accordance with Boeing 727 Structural Repair Manual Subject 53-30-4, Paragraph 2.D., Method IV, are approved as an interim repair only. Inspect blind fastener repair for loose or missing fasteners within the next 3,000 landings after the effective date of this AD, and thereafter at intervals not to exceed 2,500 landings. 1. Replace the tear strap blind splice fasteners with solid fasteners prior to accumulating 10,000 landings or within the next 10,000 landings after the effective date of this AD, whichever occurs later. NOTE: Splice fasteners are the 9 rivets at the terminating end of a tear strap. Each body station that has tear straps has 4 locations where the tear straps terminate with 9 splice rivets; just above stringer (S) 4L, S-4R, S-10L, and S-10R. 2. Replace the remaining tear strap blind fasteners with solid fasteners prior to accumulating 20,000 landings or within the next 10,000 landings after the effective date of this AD, whichever occurs later. In skin gauges .063 inches or greater, use solid fastener BACR15CE6D. In skin gauges less than .063 inches, use solid fastener MS20470D6. Replacement with solid fasteners terminates the inspection requirements of this AD for the repaired area. H. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Northwest Mountain Region. NOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. I. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue, S.W., Renton, Washington. Airworthiness Directive 90-20-18 supersedes AD 81-17-07, Amendment 39-4191. This amendment (39-6747, AD 90-20-18) becomes effective on October 29, 1990. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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