AD 80-26-51
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | 737-100 Series | BOEING Model 737 Series Airplanes |
| aircraft | The Boeing Company | 737-200 Series | BOEING Model 737 Series Airplanes |
| aircraft | The Boeing Company | 737-200C Series | BOEING Model 737 Series Airplanes |
| aircraft | The Boeing Company | 737-300 Series | BOEING Model 737 Series Airplanes |
| aircraft | The Boeing Company | 737-400 Series | BOEING Model 737 Series Airplanes |
| aircraft | The Boeing Company | 737-500 Series | BOEING Model 737 Series Airplanes |
| aircraft | The Boeing Company | 737-600 Series | BOEING Model 737 Series Airplanes |
| aircraft | The Boeing Company | 737-700 Series | BOEING Model 737 Series Airplanes |
| aircraft | The Boeing Company | 737-800 Series | BOEING Model 737 Series Airplanes |
Unsafe Condition
Control system jamming due to improper installation of bolt assemblies at the upper and lower clevis of each elevator power control unit input rod assembly.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect bolt assemblies at the upper and lower clevis of each elevator power control unit input rod assembly for proper installation per Boeing Alert Service Bulletin 27A1109 or later FAA-approved revisions. Reinstall improperly installed bolt assemblies as required by the service bulletin.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within the next 150 hours time-in-service after the effective date
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Boeing Model 737 series airplanes certificated in all categories, prior to line number 726.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Control System Jamming
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_80-26-51.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 80-26-51 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: BOEING Model 737 Series Airplanes Subject: Control System Jamming Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 12/13/1980 Make: The Boeing Company Model: 737-100 Series | 737-200 Series | 737-200C Series | 737-300 Series | 737-400 Series | 737-500 Series...Show more 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: 80-26-51 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4072 AD NUMBER: 80-26-51 SUBJECT HEADING: BOEING Model 737 Series Airplanes ACTION: SUMMARY: DATES: Effective December 13, 1980. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 80-26-51 BOEING: Amendment 39-4072. Applies to Boeing Model 737 series airplanes, certificated in all categories, prior to line number 726. To prevent control system jamming, accomplish the following within the next 150 hours time-in-service after the effective date unless already accomplished, or unless the affected bolt assemblies have been removed and reinstalled since manufacture. 1. Inspect the bolt assemblies installed at the upper and lower clevis of each elevator power control unit input rod assembly for proper installation in accordance with Boeing Alert Service Bulletin 27A1109, dated December 11, 1980, or later FAA-approved revisions. Bolt assemblies not properly installed must be reinstalled in accordance with the service bulletin. 2. Alternate methods of compliance with this Airworthiness Directive may be used when they are approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. This amendment becomes effective April 1, 1981, and was effective earlier to those recipients of telegraphic AD T80-26-51, dated December 13, 1980. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_80-26-51.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 80-26-51 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: BOEING Model 737 Series Airplanes Subject: Control System Jamming Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 12/13/1980 Make: The Boeing Company Model: 737-100 Series | 737-200 Series | 737-200C Series | 737-300 Series | 737-400 Series | 737-500 Series...Show more 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: 80-26-51 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4072 AD NUMBER: 80-26-51 SUBJECT HEADING: BOEING Model 737 Series Airplanes ACTION: SUMMARY: DATES: Effective December 13, 1980. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 80-26-51 BOEING: Amendment 39-4072. Applies to Boeing Model 737 series airplanes, certificated in all categories, prior to line number 726. To prevent control system jamming, accomplish the following within the next 150 hours time-in-service after the effective date unless already accomplished, or unless the affected bolt assemblies have been removed and reinstalled since manufacture. 1. Inspect the bolt assemblies installed at the upper and lower clevis of each elevator power control unit input rod assembly for proper installation in accordance with Boeing Alert Service Bulletin 27A1109, dated December 11, 1980, or later FAA-approved revisions. Bolt assemblies not properly installed must be reinstalled in accordance with the service bulletin. 2. Alternate methods of compliance with this Airworthiness Directive may be used when they are approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. This amendment becomes effective April 1, 1981, and was effective earlier to those recipients of telegraphic AD T80-26-51, dated December 13, 1980. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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