AD 67-06-02
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus SAS | BAC 1-11 200 Series | Airworthiness Directives; BRITISH AIRCRAFT Model BAC 1-11 200 and 400 Series Airplanes |
| aircraft | Airbus SAS | BAC 1-11 400 Series | Airworthiness Directives; BRITISH AIRCRAFT Model BAC 1-11 200 and 400 Series Airplanes |
Unsafe Condition
Inflight loss of engine stub access panels due to unlocked Camloc fasteners and sliding bar type fasteners, excessive vertical movement of access panels exceeding 0.1 inch, and improper clearance between panel edges and spigots exceeding 0.080 inch.
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Required Actions
Inspect Camloc and sliding bar fasteners to ensure locked per Alert Service Bulletin 54-A-PM-2649; replace Camloc grommets with steel grommets P/N 4002-0 if vertical movement exceeds 0.1 inch. Inspect panel clearances, reposition spigots P/N AB 16-549 and use 5/32 inch rivets if clearances exceed 0.080 inch. Stencil continuous lines across sliding bar fasteners if not present, lubricate and operate fasteners, replace non-responsive fasteners. Re-lubricate sliding bar fasteners with grease VP 93/2 within 1,800 hours. Exclusions apply for airplanes modified per the same service bulletin.
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Compliance Time
Within the next 150 hours' time in service after March 6, 1967 for initial inspections and replacements; 600 hours' time in service for clearance inspections and spigot adjustments; 1,800 hours' time in service for re-lubrication.
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Affected Aircraft
BRITISH AIRCRAFT Model BAC 1-11 200 and 400 Series airplanes not modified per Alert Service Bulletin 54-A-PM-2649.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Engine Stub Access Panels
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_67-06-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 67-06-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; BRITISH AIRCRAFT Model BAC 1-11 200 and 400 Series Airplanes Subject: Engine Stub Access Panels Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 03/06/1967 Make: Airbus SAS Model: BAC 1-11 200 Series | BAC 1-11 400 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: 67-06-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-359 AD NUMBER: 67-06-02 SUBJECT HEADING: Airworthiness Directives; BRITISH AIRCRAFT Model BAC 1-11 200 and 400 Series Airplanes ACTION: SUMMARY: DATES: Effective March 6, 1967. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 67-06-02 BRITISH AIRCRAFT: Amdt. 39-359 Part 39 Federal Register March 1, 1967. Applies to Model BAC 1-11 200 and 400 Series Airplanes. Compliance required as indicated. To prevent the inflight loss of engine stub access panels, accomplish the following: (a) Within the next 150 hours' time in service after the effective date of this AD, accomplish the following: (1) Inspect the access panels Camloc fasteners and sliding bar type fasteners to ensure they are locked in accordance with British Aircraft Corporation One-Eleven Alert Service Bulletin No. 54-A-PM-2649, dated September 22, 1966, or later ARB-approved issue. (2) Inspect the access panels for vertical movement. If found in excess of 0.1 inch, replace the Camloc grommets with steel grommets P/N 4002-0 or an FAA-approved equivalent. (b) Within the next 600 hours' time in service after the effective date of this AD, accomplish the following: (1) Inspect to ensure that each of the clearances between the leading and trailing edges of L.H. panels F3-3 and F3-4 and R.H. panels F3-24 and F3-25 is not greater than 0.080 inch. If any clearance is found to be greater, remove and reposition the two spigots P/N AB 16-549 to the forward face of the channel section and open up and countersink the existing rivet holes to receive 5/32 inch diameter 100 degree rivets to material Specification L86, or FAA- approved equivalent, to attach the spigots. (2) Inspect to ensure that a continuous line has been stenciled across the sliding bar fastener boss and skin in accordance with British Aircraft Corporation One-Eleven Alert Service Bulletin No. 54-A-PM-2649, dated September 22, 1966, or later ARB-approved issue. If this has not been accomplished, aline the locked indicator marks on the sliding bar fastener boss and the skin and stencil, with paint of a contrasting color to the local finish, a continuous line across the boss and the skin in line with the existing locked indicator marks. (3) Operate the sliding bar fasteners to ensure that the snapover locking action is positive and that no looseness exists. Lubricate and operate several times, in accordance with British Aircraft Corporation One-Eleven Alert Service Bulletin No. 54-A-PM-2649, dated September 22, 1966, or later ARB-approved issue, any fastener that fails to meet this requirement. Replace any fastener that fails to respond to this treatment with a new part. (4) Replace Camloc fastener grommets with steel grommets P/N 4002-0 or an FAA-approved equivalent. (c) Within the next 1,800 hours' time in service after the effective date of this AD, remove the access panels and re-lubricate the sliding bar fasteners using grease to Process Specification VP 93/2, or an FAA-approved equivalent. (d) The requirements of this AD do not apply to those airplanes that have been modified in accordance with British Aircraft Corporation One-Eleven Alert Service Bulletin No. 54-A-PM-2649, dated September 22, 1966, or later ARB-approved issue. This directive effective March 6, 1967. FOOTER:
Document Text
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AD Final Rules - DRS_67-06-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 67-06-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; BRITISH AIRCRAFT Model BAC 1-11 200 and 400 Series Airplanes Subject: Engine Stub Access Panels Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 03/06/1967 Make: Airbus SAS Model: BAC 1-11 200 Series | BAC 1-11 400 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: 67-06-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-359 AD NUMBER: 67-06-02 SUBJECT HEADING: Airworthiness Directives; BRITISH AIRCRAFT Model BAC 1-11 200 and 400 Series Airplanes ACTION: SUMMARY: DATES: Effective March 6, 1967. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 67-06-02 BRITISH AIRCRAFT: Amdt. 39-359 Part 39 Federal Register March 1, 1967. Applies to Model BAC 1-11 200 and 400 Series Airplanes. Compliance required as indicated. To prevent the inflight loss of engine stub access panels, accomplish the following: (a) Within the next 150 hours' time in service after the effective date of this AD, accomplish the following: (1) Inspect the access panels Camloc fasteners and sliding bar type fasteners to ensure they are locked in accordance with British Aircraft Corporation One-Eleven Alert Service Bulletin No. 54-A-PM-2649, dated September 22, 1966, or later ARB-approved issue. (2) Inspect the access panels for vertical movement. If found in excess of 0.1 inch, replace the Camloc grommets with steel grommets P/N 4002-0 or an FAA-approved equivalent. (b) Within the next 600 hours' time in service after the effective date of this AD, accomplish the following: (1) Inspect to ensure that each of the clearances between the leading and trailing edges of L.H. panels F3-3 and F3-4 and R.H. panels F3-24 and F3-25 is not greater than 0.080 inch. If any clearance is found to be greater, remove and reposition the two spigots P/N AB 16-549 to the forward face of the channel section and open up and countersink the existing rivet holes to receive 5/32 inch diameter 100 degree rivets to material Specification L86, or FAA- approved equivalent, to attach the spigots. (2) Inspect to ensure that a continuous line has been stenciled across the sliding bar fastener boss and skin in accordance with British Aircraft Corporation One-Eleven Alert Service Bulletin No. 54-A-PM-2649, dated September 22, 1966, or later ARB-approved issue. If this has not been accomplished, aline the locked indicator marks on the sliding bar fastener boss and the skin and stencil, with paint of a contrasting color to the local finish, a continuous line across the boss and the skin in line with the existing locked indicator marks. (3) Operate the sliding bar fasteners to ensure that the snapover locking action is positive and that no looseness exists. Lubricate and operate several times, in accordance with British Aircraft Corporation One-Eleven Alert Service Bulletin No. 54-A-PM-2649, dated September 22, 1966, or later ARB-approved issue, any fastener that fails to meet this requirement. Replace any fastener that fails to respond to this treatment with a new part. (4) Replace Camloc fastener grommets with steel grommets P/N 4002-0 or an FAA-approved equivalent. (c) Within the next 1,800 hours' time in service after the effective date of this AD, remove the access panels and re-lubricate the sliding bar fasteners using grease to Process Specification VP 93/2, or an FAA-approved equivalent. (d) The requirements of this AD do not apply to those airplanes that have been modified in accordance with British Aircraft Corporation One-Eleven Alert Service Bulletin No. 54-A-PM-2649, dated September 22, 1966, or later ARB-approved issue. This directive effective March 6, 1967. FOOTER:
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