AD 68-03-01
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Maryland Air Industries, Inc. | FH-227 | Airworthiness Directives; Fairchild-Hiller Model FH-227 Aircraft |
| aircraft | Maryland Air Industries, Inc. | FH-227B | Airworthiness Directives; Fairchild-Hiller Model FH-227 Aircraft |
| aircraft | Maryland Air Industries, Inc. | FH-227C | Airworthiness Directives; Fairchild-Hiller Model FH-227 Aircraft |
| aircraft | Maryland Air Industries, Inc. | FH-227D | Airworthiness Directives; Fairchild-Hiller Model FH-227 Aircraft |
| aircraft | Maryland Air Industries, Inc. | FH-227E | Airworthiness Directives; Fairchild-Hiller Model FH-227 Aircraft |
Unsafe Condition
Flutter of the elevator trim tab could lead to structural deformation, cracks, loose rivets, damaged bearings, or damaged parts in the elevator trim tab system, compromising flight safety.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect elevator trim tab for trailing edge free play not exceeding 0.100 inch; visually inspect hinge bearings, structure, clevis bolts, horn, actuator, rod assembly rivets, and hinges for damage or looseness; replace damaged bearings, loose rivets, deformed or cracked parts with inspected or approved parts; inspect tab spar area for cracks and repair or replace as needed; modify lower tab skin with a doubler and access holes for inspection; cover access holes with tape. Inspections must be done prior to further flight unless already within last 20 hours' time in service, with subsequent intervals not exceeding 25 or 600 hours' time in service depending on modification status.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Compliance required within the next 5 hours' time in service after the effective date of this AD unless already accomplished within the last 20 hours' time in service and thereafter at intervals not to exceed 25 hours' time in service from the last inspection. For modified tabs, comply with paragraphs (a), (b), (c), and (d) prior to accumulating 600 hours' time in service on the modified tab, and thereafter at intervals not to exceed 600 hours' time from the last inspection.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Maryland Air Industries, Inc. FH-227, FH-227B, FH-227C, FH-227D, FH-227E aircraft models.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Elevator Trim Tab
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_68-03-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 68-03-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Fairchild-Hiller Model FH-227 Aircraft Subject: Elevator Trim Tab Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/27/1970 Make: Maryland Air Industries, Inc. Model: FH-227 | FH-227B | FH-227C | FH-227D | FH-227E 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: 68-03-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-987 AD NUMBER: 68-03-01 SUBJECT HEADING: Airworthiness Directives; Fairchild-Hiller Model FH-227 Aircraft ACTION: SUMMARY: DATES: Effective May 27, 1970. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 68-03-01 FAIRCHILD-HILLER: Amdt. 39-547 as amended by Amendment 39-987. Applies to FH-227 Type Aircraft. Compliance required within the next 5 hours' time in service after the effective date of this AD unless already accomplished within the last 20 hours' time in service and thereafter at intervals not to exceed 25 hours' time in service from the last inspection. The repetitive inspections also apply to repaired and replacement parts. In view of flutter of the elevator trim tab, accomplish the following: (a) Inspect the elevator trim tab for trailing edge free play not to exceed 0.100 inch max. travel. Compliance with this limit must be met prior to further flight. (b) Visually inspect all elevator tab hinge bearings for damage. Replace damaged bearings, prior to further flight, with a part of the same part number that has been inspected in accordance with this directive prior to installation, or with an FAA approved equivalent part. (c) Visually inspect the entire elevator tab structure for loose rivets, cracks, or any structural deformation. Prior to further flight, remove and replace loose rivets, replace deformed trim tabs, and repair or replace cracked trim tabs with a part of the same part number that has been inspected in accordance with this directive prior to installation or with an equivalent part or repair approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (d) Inspect the elevator trim tab clevis bolts, elevator trim tab horn, elevator trim tab actuator, rod end and rod assembly rivets, for looseness and damage. Prior to further flight, loose items must be properly secured and damaged parts replaced with a part of the same part number that has been inspected in accordance with this directive prior to installation, or with an FAA approved equivalent part. (e) Visually inspect the 3 elevator trim tab hinges for elongated holes in the clevis holes of the aluminum blocks located behind the 3 elevator trim tab hinges. Replace blocks containing elongated holes prior to further flight with a part of the same part number that has been inspected in accordance with this directive prior to installation, or with an FAA approved equivalent part. (f) Inspect the elevator trim tab spar area around the 3 hinges for cracks. If cracks are found, prior to further flight, the cracked parts must be repaired in accordance with an FAA approved repair, or replaced with a part of the same part number that has been inspected in accordance with this directive prior to installation, or with an FAA-approved equivalent part. (g) Cut a one-inch hole in the lower tab skin in line chordwise with the existing access hole in the lower tab skin at tab station 14.662, and located spanwise 11.4 inches outboard of the most inboard tab rib. Fabricate a circular doubler 2 inch O.D. by 1 inch I.D. from 0.025 inch thick 2024T3 alclad material specification QQ-A-250/5. Finish with alodine or anodize and apply zinc chromate primer to the faying surface only. Install doubler over hole and secure the doubler with six equally spaced MS20600AD4 rivets or use an equivalent method for inspection approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (1) Inspect the tab ribs adjacent to the 3 tab hinges and also the tab ribs supporting the tab horn for cracks paying particular attention to rib flange radii using a borescope or light and mirror through the access holes or use an FAA-approved equivalent inspection method. The x-ray inspection procedure specified in Fairchild Hiller Alert Service Bulletin No. 27-17A (FH-227) Revision 1 dated January 5, 1968, is considered equivalent to the borescope or light and mirror inspection. If cracks are found, prior to further flight, the cracked parts must be repaired in accordance with an FAA approved repair, or replaced with a part of the same part number that has been inspected in accordance with this directive prior to installation or with an FAA-approved equivalent part. (2) After each inspection, cover the access holes with permacelle tape or equivalent. (h) For aircraft with a modified elevator trim tab approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, comply with paragraphs (a), (b), (c), and (d), prior to accumulating 600 hours' time in service on the modified tab, and thereafter at intervals not to exceed 600 hours' time from the last inspection. If the inspections of (a), (b), (c), or (d), reveal a discrepancy, then the requirements of paragraphs (e), (f), and (g)(1) and (g) (2), must be complied with prior to further flight. (i) Equivalent inspections may be approved by an FAA maintenance inspector. Equivalent repairs and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (j) Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance times specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Amendment 39-547 is effective February 2, 1968, for all persons except those to whom it was made effective immediately by telegram dated January 9, 1968. This Amendment (39-987) is effective May 27, 1970. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_68-03-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 68-03-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Fairchild-Hiller Model FH-227 Aircraft Subject: Elevator Trim Tab Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/27/1970 Make: Maryland Air Industries, Inc. Model: FH-227 | FH-227B | FH-227C | FH-227D | FH-227E 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: 68-03-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-987 AD NUMBER: 68-03-01 SUBJECT HEADING: Airworthiness Directives; Fairchild-Hiller Model FH-227 Aircraft ACTION: SUMMARY: DATES: Effective May 27, 1970. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 68-03-01 FAIRCHILD-HILLER: Amdt. 39-547 as amended by Amendment 39-987. Applies to FH-227 Type Aircraft. Compliance required within the next 5 hours' time in service after the effective date of this AD unless already accomplished within the last 20 hours' time in service and thereafter at intervals not to exceed 25 hours' time in service from the last inspection. The repetitive inspections also apply to repaired and replacement parts. In view of flutter of the elevator trim tab, accomplish the following: (a) Inspect the elevator trim tab for trailing edge free play not to exceed 0.100 inch max. travel. Compliance with this limit must be met prior to further flight. (b) Visually inspect all elevator tab hinge bearings for damage. Replace damaged bearings, prior to further flight, with a part of the same part number that has been inspected in accordance with this directive prior to installation, or with an FAA approved equivalent part. (c) Visually inspect the entire elevator tab structure for loose rivets, cracks, or any structural deformation. Prior to further flight, remove and replace loose rivets, replace deformed trim tabs, and repair or replace cracked trim tabs with a part of the same part number that has been inspected in accordance with this directive prior to installation or with an equivalent part or repair approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (d) Inspect the elevator trim tab clevis bolts, elevator trim tab horn, elevator trim tab actuator, rod end and rod assembly rivets, for looseness and damage. Prior to further flight, loose items must be properly secured and damaged parts replaced with a part of the same part number that has been inspected in accordance with this directive prior to installation, or with an FAA approved equivalent part. (e) Visually inspect the 3 elevator trim tab hinges for elongated holes in the clevis holes of the aluminum blocks located behind the 3 elevator trim tab hinges. Replace blocks containing elongated holes prior to further flight with a part of the same part number that has been inspected in accordance with this directive prior to installation, or with an FAA approved equivalent part. (f) Inspect the elevator trim tab spar area around the 3 hinges for cracks. If cracks are found, prior to further flight, the cracked parts must be repaired in accordance with an FAA approved repair, or replaced with a part of the same part number that has been inspected in accordance with this directive prior to installation, or with an FAA-approved equivalent part. (g) Cut a one-inch hole in the lower tab skin in line chordwise with the existing access hole in the lower tab skin at tab station 14.662, and located spanwise 11.4 inches outboard of the most inboard tab rib. Fabricate a circular doubler 2 inch O.D. by 1 inch I.D. from 0.025 inch thick 2024T3 alclad material specification QQ-A-250/5. Finish with alodine or anodize and apply zinc chromate primer to the faying surface only. Install doubler over hole and secure the doubler with six equally spaced MS20600AD4 rivets or use an equivalent method for inspection approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (1) Inspect the tab ribs adjacent to the 3 tab hinges and also the tab ribs supporting the tab horn for cracks paying particular attention to rib flange radii using a borescope or light and mirror through the access holes or use an FAA-approved equivalent inspection method. The x-ray inspection procedure specified in Fairchild Hiller Alert Service Bulletin No. 27-17A (FH-227) Revision 1 dated January 5, 1968, is considered equivalent to the borescope or light and mirror inspection. If cracks are found, prior to further flight, the cracked parts must be repaired in accordance with an FAA approved repair, or replaced with a part of the same part number that has been inspected in accordance with this directive prior to installation or with an FAA-approved equivalent part. (2) After each inspection, cover the access holes with permacelle tape or equivalent. (h) For aircraft with a modified elevator trim tab approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, comply with paragraphs (a), (b), (c), and (d), prior to accumulating 600 hours' time in service on the modified tab, and thereafter at intervals not to exceed 600 hours' time from the last inspection. If the inspections of (a), (b), (c), or (d), reveal a discrepancy, then the requirements of paragraphs (e), (f), and (g)(1) and (g) (2), must be complied with prior to further flight. (i) Equivalent inspections may be approved by an FAA maintenance inspector. Equivalent repairs and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (j) Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance times specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Amendment 39-547 is effective February 2, 1968, for all persons except those to whom it was made effective immediately by telegram dated January 9, 1968. This Amendment (39-987) is effective May 27, 1970. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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