AD 91-24-11 R1
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
Failure of the body station (BS) 870 terminal fitting and depressurization of the airplane due to cracks and web separations.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Conduct visual, eddy current, and ultrasonic inspections of the BS 870 terminal fitting for cracks and web separations per Boeing Service Bulletin 727-53-0194. Rework uncracked fastener holes and install oversized fasteners during the initial inspection. Repair any found cracks or separations prior to further flight per the service bulletin. Repeat inspections at intervals not exceeding 6,000 flight cycles or 3 years (or 3,000 flight cycles/18 months if web separations are repaired with external doublers).
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Prior to the accumulation of 25,000 total flight cycles or within the next 3,000 flight cycles after the effective date of this AD, whichever occurs later.
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Affected Aircraft
Boeing Model 727 series airplanes, line numbers 001 through 875, certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Body Station 870 Inspection
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_91-24-11_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 91-24-11 R1 Document Type: AD Final Rules Docket Number: 91-NM-114-AD Subject Heading: Airworthiness Directives; BOEING Model 727 Series Airplanes Subject: Body Station 870 Inspection Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 01/07/1992 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: 91-24-11 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 91-NM-114-AD AMENDMENT: 39-8175 AD NUMBER: 91-24-11 R1 SUBJECT HEADING: Airworthiness Directives; BOEING Model 727 Series Airplanes ACTION: SUMMARY: DATES: Effective January 7, 1992. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 91-24-11 R1 BOEING: Amendment 39-8175. Docket No. 91-NM-114-AD. Revises AD 91- 24-11, Amendment 39-8097. Applicability: Model 727 series airplanes, line numbers 001 through 875, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent failure of the body station (BS) 870 terminal fitting and depressurization of the airplane, accomplish the following: (a) Prior to the accumulation of 25,000 total flight cycles or within the next 3,000 flight cycles after the effective date of this AD, whichever occurs later, conduct visual, eddy current, and ultrasonic inspections of the body station (BS) 870 terminal fitting for cracks and web separations, in accordance with Figure 1 of Boeing Service Bulletin 727-53-0194, dated November 8, 1990. During the initial inspection, rework uncracked fastener holes and install oversized fasteners, in accordance with Figure 1 of the service bulletin. Removal of weather caulking material from the fuselage skin butt splice cavity, as shown in Figure 1 of the service bulletin, is not required by this AD. (b) If cracks or separations are found, prior to further flight, repair the BS 870 terminal fitting in accordance with Boeing Service Bulletin 727-53-0194, dated November 8, 1990. After repairs, repeat the inspection requirements of paragraph (a) of this AD as follows: (1) For airplanes on which outboard flange cracks are removed by oversizing the fastener holes, repeat the inspections at intervals not to exceed 6,000 flight cycles or 3 years, whichever occurs first. (2) For airplanes on which the external doubler is used to repair only outboard flange cracks, repeat the inspections at intervals not to exceed 6,000 flight cycles or 3 years, whichever occurs first. (3) For airplanes on which the external doubler is used to repair either web separations, or web separations and outboard flange cracks, repeat the inspections at intervals not to exceed 3,000 flight cycles or 18 months, whichever occurs first. (c) If no cracks or separations are found, repeat the inspection requirements of paragraph (a) of this AD at intervals not to exceed 6,000 flight cycles or 3 years, whichever occurs first. (d) The partial replacement of the body station (BS) 870 terminal fitting in accordance with Boeing Service Bulletin 727-53-0194, dated November 8, 1990, constitutes terminating action for the inspection requirements of this AD, for the replaced portion of the fitting. Unreplaced portions must continue to be inspected in accordance with this AD. (e) The complete replacement of the body station (BS) 870 terminal fitting in accordance with Boeing Service Bulletin 727-53-0194, dated November 8, 1990, constitutes terminating action for the inspection requirements of this AD. (f) 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. (g) 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. (h) The inspection and repair requirements shall be done in accordance with Boeing Service Bulletin 727-53-0194, dated November 8, 1990. This incorporation by reference was previously approved by the Director of the Federal Register as of January 7, 1992 (56 FR 61354), in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Northwest Mountain Region, 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 (39-8175), AD 91-24-11 R1, is effective on January 7, 1992. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_91-24-11_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 91-24-11 R1 Document Type: AD Final Rules Docket Number: 91-NM-114-AD Subject Heading: Airworthiness Directives; BOEING Model 727 Series Airplanes Subject: Body Station 870 Inspection Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 01/07/1992 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: 91-24-11 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 91-NM-114-AD AMENDMENT: 39-8175 AD NUMBER: 91-24-11 R1 SUBJECT HEADING: Airworthiness Directives; BOEING Model 727 Series Airplanes ACTION: SUMMARY: DATES: Effective January 7, 1992. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 91-24-11 R1 BOEING: Amendment 39-8175. Docket No. 91-NM-114-AD. Revises AD 91- 24-11, Amendment 39-8097. Applicability: Model 727 series airplanes, line numbers 001 through 875, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent failure of the body station (BS) 870 terminal fitting and depressurization of the airplane, accomplish the following: (a) Prior to the accumulation of 25,000 total flight cycles or within the next 3,000 flight cycles after the effective date of this AD, whichever occurs later, conduct visual, eddy current, and ultrasonic inspections of the body station (BS) 870 terminal fitting for cracks and web separations, in accordance with Figure 1 of Boeing Service Bulletin 727-53-0194, dated November 8, 1990. During the initial inspection, rework uncracked fastener holes and install oversized fasteners, in accordance with Figure 1 of the service bulletin. Removal of weather caulking material from the fuselage skin butt splice cavity, as shown in Figure 1 of the service bulletin, is not required by this AD. (b) If cracks or separations are found, prior to further flight, repair the BS 870 terminal fitting in accordance with Boeing Service Bulletin 727-53-0194, dated November 8, 1990. After repairs, repeat the inspection requirements of paragraph (a) of this AD as follows: (1) For airplanes on which outboard flange cracks are removed by oversizing the fastener holes, repeat the inspections at intervals not to exceed 6,000 flight cycles or 3 years, whichever occurs first. (2) For airplanes on which the external doubler is used to repair only outboard flange cracks, repeat the inspections at intervals not to exceed 6,000 flight cycles or 3 years, whichever occurs first. (3) For airplanes on which the external doubler is used to repair either web separations, or web separations and outboard flange cracks, repeat the inspections at intervals not to exceed 3,000 flight cycles or 18 months, whichever occurs first. (c) If no cracks or separations are found, repeat the inspection requirements of paragraph (a) of this AD at intervals not to exceed 6,000 flight cycles or 3 years, whichever occurs first. (d) The partial replacement of the body station (BS) 870 terminal fitting in accordance with Boeing Service Bulletin 727-53-0194, dated November 8, 1990, constitutes terminating action for the inspection requirements of this AD, for the replaced portion of the fitting. Unreplaced portions must continue to be inspected in accordance with this AD. (e) The complete replacement of the body station (BS) 870 terminal fitting in accordance with Boeing Service Bulletin 727-53-0194, dated November 8, 1990, constitutes terminating action for the inspection requirements of this AD. (f) 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. (g) 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. (h) The inspection and repair requirements shall be done in accordance with Boeing Service Bulletin 727-53-0194, dated November 8, 1990. This incorporation by reference was previously approved by the Director of the Federal Register as of January 7, 1992 (56 FR 61354), in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Northwest Mountain Region, 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 (39-8175), AD 91-24-11 R1, is effective on January 7, 1992. FOOTER:
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Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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