AD 77-15-16
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | BAE Systems (Operations) Limited | HS 748 Series 2A | Airworthiness Directives; HAWKER SIDDELEY AVIATION, LTD Model H.S. 748, 2A Airplanes |
Unsafe Condition
Cracks in the outboard and center elevator hinge ribs and associated structure of the horizontal stabilizer.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Within 100 hours time in service after the effective date, and every 100 hours thereafter, visually inspect the outboard and center elevator hinge ribs per Service Bulletin 55/11. If cracks, loose rivets, or corroded bearings/pivot pins are found, conduct an internal inspection of the stabilizer rear spar attachment area per SB 55/11 and replace/repair affected parts before flight. Within 1000 hours time in service after the effective date, replace external gusset plates and add inspection holes per SB 55/12.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 100 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 100 hours time in service from the last inspection. For gusset plate replacement: within the next 1000 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
Hawker Siddeley Aviation, Ltd. Model H.S. 748, Series 2A airplanes, all serial numbers.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Structure of Horizontal Stabilizer
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_77-15-16.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 77-15-16 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; HAWKER SIDDELEY AVIATION, LTD Model H.S. 748, 2A Airplanes Subject: Structure of Horizontal Stabilizer Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/29/1977 Make: BAE Systems (Operations) Limited Model: HS 748 Series 2A Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 77-15-16 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2987 AD NUMBER: 77-15-16 SUBJECT HEADING: Airworthiness Directives; HAWKER SIDDELEY AVIATION, LTD Model H.S. 748, 2A Airplanes ACTION: SUMMARY: DATES: Effective August 29, 1977. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 77-15-16 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-2987. Applies to Model H.S. 748, Series 2A airplanes, all serial numbers, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent cracks in the outboard and center elevator hinge ribs and associated structure of the horizontal stabilizer, accomplish the following: (a) Within the next 100 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 100 hours time in service from the last inspection, visually inspect the area of the outboard and center elevator hinge ribs in accordance with Part 2A of the section entitled "Accomplishment Instructions" of Hawker Siddeley Aviation, Ltd., Service Bulletin No. 55/11, dated October 15, 1973, or an FAA-approved equivalent. (b) If, during an inspection required by paragraph (a) of this AD, a crack, loose rivets, or corroded support bearings or pivot pins are found, before further flight, conduct an internal inspection of the area where the affected hinge ribs attach to the stabilizer rear spar in accordance with Part 2B of the section entitled "Accomplishment Instructions" of Hawker Siddeley Aviation, Ltd., Service Bulletin No. 55/11, dated October 15, 1973, or an FAA-approved equivalent, and comply with paragraph (c) of this AD. (c) If, during an inspection required by paragraph (a) or (b) of this AD, a crack, loose rivets, or corroded support bearings or pivot pins are found, before further flight, replace or repair the affected parts, as appropriate, in accordance with Part 2C of the section entitled "Accomplishment Instructions" of Hawker Siddeley Aviation, Ltd., Service Bulletin No. 55/11, dated October 15, 1973, or an FAA-approved equivalent, and thereafter, continue to comply with paragraphs (a), (b), and (c) of this AD. (d) Within the next 1000 hours time in service after the effective date of this AD, replace the external gusset plates (top and bottom) at the outboard and center elevator hinge ribs with larger and heavier gusset plates and add inspection holes in accordance with Parts 2A, 2B, 2C, and 2E of the section entitled "Accomplishment Instructions" of Hawker Siddeley Aviation, Ltd., Service Bulletin No. 55/12, dated January 2, 1974, or an FAA-approved equivalent. (e) Upon incorporation of the alterations required by paragraph (d) of this AD, the repetitive inspections required by this AD may be discontinued. This amendment becomes effective August 29, 1977. FOOTER:
Document Text
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AD Final Rules - DRS_77-15-16.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 77-15-16 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; HAWKER SIDDELEY AVIATION, LTD Model H.S. 748, 2A Airplanes Subject: Structure of Horizontal Stabilizer Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/29/1977 Make: BAE Systems (Operations) Limited Model: HS 748 Series 2A 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: 77-15-16 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2987 AD NUMBER: 77-15-16 SUBJECT HEADING: Airworthiness Directives; HAWKER SIDDELEY AVIATION, LTD Model H.S. 748, 2A Airplanes ACTION: SUMMARY: DATES: Effective August 29, 1977. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 77-15-16 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-2987. Applies to Model H.S. 748, Series 2A airplanes, all serial numbers, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent cracks in the outboard and center elevator hinge ribs and associated structure of the horizontal stabilizer, accomplish the following: (a) Within the next 100 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 100 hours time in service from the last inspection, visually inspect the area of the outboard and center elevator hinge ribs in accordance with Part 2A of the section entitled "Accomplishment Instructions" of Hawker Siddeley Aviation, Ltd., Service Bulletin No. 55/11, dated October 15, 1973, or an FAA-approved equivalent. (b) If, during an inspection required by paragraph (a) of this AD, a crack, loose rivets, or corroded support bearings or pivot pins are found, before further flight, conduct an internal inspection of the area where the affected hinge ribs attach to the stabilizer rear spar in accordance with Part 2B of the section entitled "Accomplishment Instructions" of Hawker Siddeley Aviation, Ltd., Service Bulletin No. 55/11, dated October 15, 1973, or an FAA-approved equivalent, and comply with paragraph (c) of this AD. (c) If, during an inspection required by paragraph (a) or (b) of this AD, a crack, loose rivets, or corroded support bearings or pivot pins are found, before further flight, replace or repair the affected parts, as appropriate, in accordance with Part 2C of the section entitled "Accomplishment Instructions" of Hawker Siddeley Aviation, Ltd., Service Bulletin No. 55/11, dated October 15, 1973, or an FAA-approved equivalent, and thereafter, continue to comply with paragraphs (a), (b), and (c) of this AD. (d) Within the next 1000 hours time in service after the effective date of this AD, replace the external gusset plates (top and bottom) at the outboard and center elevator hinge ribs with larger and heavier gusset plates and add inspection holes in accordance with Parts 2A, 2B, 2C, and 2E of the section entitled "Accomplishment Instructions" of Hawker Siddeley Aviation, Ltd., Service Bulletin No. 55/12, dated January 2, 1974, or an FAA-approved equivalent. (e) Upon incorporation of the alterations required by paragraph (d) of this AD, the repetitive inspections required by this AD may be discontinued. This amendment becomes effective August 29, 1977. FOOTER:
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Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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