AD 75-16-21
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | DC-10-10 | Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40 Airplanes |
| aircraft | The Boeing Company | DC-10-10F | Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40 Airplanes |
| aircraft | The Boeing Company | DC-10-30 | Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40 Airplanes |
| aircraft | The Boeing Company | DC-10-30F (KC-10A, KDC-10) | Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40 Airplanes |
| aircraft | The Boeing Company | DC-10-40 | Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40 Airplanes |
Unsafe Condition
Detachment of the flap vane assembly due to insufficient support from the outboard flap vane assembly supports.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Conduct dye penetrant inspection, installation check, and flap actuation per Alert Service Bulletin A57-48. Limit flap settings to 35 degrees and speed to 175 knots when using 35-degree flaps. Affix placards indicating the 175 knot limit. Modify outboard flap vane assembly supports per Service Bulletin 57-48 or 57-51 within specified landing limits, and replace modified parts before 2000 landings.
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 for inspections; within 5 days for placarding; within 450 landings or 2450 landings depending on landing count at AD effective date for modifications; replace parts prior to 2000 landings after modification.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
McDonnell Douglas DC-10-10, DC-10-10F, DC-10-30, DC-10-30F (KC-10A, KDC-10), DC-10-40 airplanes certificated in all categories.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Flap Vane Assembly
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_75-16-21.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 75-16-21 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40 Airplanes Subject: Flap Vane Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/06/1975 Make: The Boeing Company Model: DC-10-10 | DC-10-10F | DC-10-30 | DC-10-30F (KC-10A, KDC-10) | DC-10-40 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: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 75-16-21 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2287 AD NUMBER: 75-16-21 SUBJECT HEADING: Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40 Airplanes ACTION: SUMMARY: DATES: Effective August 6, 1975. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 75-16-21 MCDONNELL DOUGLAS: Amendment 39-2287. Applies to Model DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40 airplanes certificated in all categories. To prevent detachment of the flap vane assembly accomplish the following as indicated: 1. Within the next 150 hours time in service, unless already accomplished, on all airplanes with over 500 landings on or after the effective date of this AD, accomplish the dye penetrant inspection, installation check, and flap actuation described in paragraphs 1, 2, and 3 of McDonnell Douglas DC-10 Alert Service Bulletin No. A57-48, dated February 20, 1975, or later FAA-approved revisions. 2. Operators shall, by the most immediate and practicable means, notify flight crews and adopt procedures to: A. Use flap settings not to exceed 35 degrees; and B. Use speed not to exceed 175 knots when operating with 35 degree flaps. 3. Within 5 days after the effective date of this AD, unless already accomplished, affix a placard to the flap position indicator to show 175 knots limit for 35 degree flaps. The 35 degree flap limit and 175 knot limit may be removed when the outboard flap vane assembly supports are modified per McDonnell Douglas DC-10 Service Bulletin Nos. 57-48, dated March 14, 1975, or 57-51, dated April 23, 1975, or later FAA-approved revisions. 4. Modify the outboard flap vane assembly supports per paragraph 6, below, within 450 landings following the inspections and checks specified in paragraph 1, above, on all aircraft with 2000 or more landings time in service on the effective date of this AD, unless already accomplished. 5. Modify the outboard flap vane assembly supports per paragraph 6, below, prior to accumulation of 2450 landings on all airplanes with less than 2000 landings on the effective date of this AD unless already accomplished. 6. Modify outboard flap vane assembly supports at tracks 1, 2, 3, and 4, per McDonnell Douglas DC-10 Service Bulletin 57-48, dated March 14, 1975, or later FAA-approved revisions, or McDonnell Douglas Service Bulletin 57-51, dated April 23, 1975, or later FAA-approved revisions, or in accordance with an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region, within the compliance times specified in paragraph 4 or 5, above. 7. Parts modified per Service Bulletin 57-48, per paragraph 6, above, must be replaced prior to the accumulation of 2000 landings following their modification with either serviceable parts per S.B. 57-48, or new parts, per S.B. 57-51. 8. Modification of the outboard flap vane assembly supports per Service Bulletin 57-51, dated April 23, 1975, or later FAA-approved revisions, when accomplished, relieves the operator from the requirements of this AD. The new parts installed per Service Bulletin 57-51 are not life-limited. 9. Equivalent inspections and repairs may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. 10. Special flight permits may be issued under FAR 21.197 and 21.199 for the purpose of moving the aircraft to a base to perform the requirements of this AD. 11. This supersedes the telegraphic AD dated March 14, 1975. This amendment becomes effective August 6, 1975. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_75-16-21.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 75-16-21 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40 Airplanes Subject: Flap Vane Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/06/1975 Make: The Boeing Company Model: DC-10-10 | DC-10-10F | DC-10-30 | DC-10-30F (KC-10A, KDC-10) | DC-10-40 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: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 75-16-21 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2287 AD NUMBER: 75-16-21 SUBJECT HEADING: Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40 Airplanes ACTION: SUMMARY: DATES: Effective August 6, 1975. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 75-16-21 MCDONNELL DOUGLAS: Amendment 39-2287. Applies to Model DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40 airplanes certificated in all categories. To prevent detachment of the flap vane assembly accomplish the following as indicated: 1. Within the next 150 hours time in service, unless already accomplished, on all airplanes with over 500 landings on or after the effective date of this AD, accomplish the dye penetrant inspection, installation check, and flap actuation described in paragraphs 1, 2, and 3 of McDonnell Douglas DC-10 Alert Service Bulletin No. A57-48, dated February 20, 1975, or later FAA-approved revisions. 2. Operators shall, by the most immediate and practicable means, notify flight crews and adopt procedures to: A. Use flap settings not to exceed 35 degrees; and B. Use speed not to exceed 175 knots when operating with 35 degree flaps. 3. Within 5 days after the effective date of this AD, unless already accomplished, affix a placard to the flap position indicator to show 175 knots limit for 35 degree flaps. The 35 degree flap limit and 175 knot limit may be removed when the outboard flap vane assembly supports are modified per McDonnell Douglas DC-10 Service Bulletin Nos. 57-48, dated March 14, 1975, or 57-51, dated April 23, 1975, or later FAA-approved revisions. 4. Modify the outboard flap vane assembly supports per paragraph 6, below, within 450 landings following the inspections and checks specified in paragraph 1, above, on all aircraft with 2000 or more landings time in service on the effective date of this AD, unless already accomplished. 5. Modify the outboard flap vane assembly supports per paragraph 6, below, prior to accumulation of 2450 landings on all airplanes with less than 2000 landings on the effective date of this AD unless already accomplished. 6. Modify outboard flap vane assembly supports at tracks 1, 2, 3, and 4, per McDonnell Douglas DC-10 Service Bulletin 57-48, dated March 14, 1975, or later FAA-approved revisions, or McDonnell Douglas Service Bulletin 57-51, dated April 23, 1975, or later FAA-approved revisions, or in accordance with an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region, within the compliance times specified in paragraph 4 or 5, above. 7. Parts modified per Service Bulletin 57-48, per paragraph 6, above, must be replaced prior to the accumulation of 2000 landings following their modification with either serviceable parts per S.B. 57-48, or new parts, per S.B. 57-51. 8. Modification of the outboard flap vane assembly supports per Service Bulletin 57-51, dated April 23, 1975, or later FAA-approved revisions, when accomplished, relieves the operator from the requirements of this AD. The new parts installed per Service Bulletin 57-51 are not life-limited. 9. Equivalent inspections and repairs may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. 10. Special flight permits may be issued under FAR 21.197 and 21.199 for the purpose of moving the aircraft to a base to perform the requirements of this AD. 11. This supersedes the telegraphic AD dated March 14, 1975. This amendment becomes effective August 6, 1975. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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