AD 67-30-03
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Maryland Air Industries, Inc. | F-27A | Airworthiness Directives; Fairchild-Hiller Model FH-227, F-27A, F-27F, F-27G, and F-27J Airplanes |
| aircraft | Maryland Air Industries, Inc. | F-27F | Airworthiness Directives; Fairchild-Hiller Model FH-227, F-27A, F-27F, F-27G, and F-27J Airplanes |
| aircraft | Maryland Air Industries, Inc. | F-27G | Airworthiness Directives; Fairchild-Hiller Model FH-227, F-27A, F-27F, F-27G, and F-27J Airplanes |
| aircraft | Maryland Air Industries, Inc. | F-27J | Airworthiness Directives; Fairchild-Hiller Model FH-227, F-27A, F-27F, F-27G, and F-27J Airplanes |
| aircraft | Maryland Air Industries, Inc. | FH-227 | Airworthiness Directives; Fairchild-Hiller Model FH-227, F-27A, F-27F, F-27G, and F-27J Airplanes |
| aircraft | Maryland Air Industries, Inc. | FH-227B | Airworthiness Directives; Fairchild-Hiller Model FH-227, F-27A, F-27F, F-27G, and F-27J Airplanes |
| aircraft | Maryland Air Industries, Inc. | FH-227C | Airworthiness Directives; Fairchild-Hiller Model FH-227, F-27A, F-27F, F-27G, and F-27J Airplanes |
| aircraft | Maryland Air Industries, Inc. | FH-227D | Airworthiness Directives; Fairchild-Hiller Model FH-227, F-27A, F-27F, F-27G, and F-27J Airplanes |
| aircraft | Maryland Air Industries, Inc. | FH-227E | Airworthiness Directives; Fairchild-Hiller Model FH-227, F-27A, F-27F, F-27G, and F-27J Airplanes |
Unsafe Condition
Cracks in the rudder skin, stiffeners, and rear spar flange located between the ribs of the lower section of the rudder.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Visually inspect for cracks in the rudder skins, stiffeners, and rear spar flanges at specified stations. Use manual compression or FAA-approved equivalent inspection. Repair or replace cracked parts before further flight.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 50 hours' time in service after the effective date (November 1, 1967), and thereafter every 200 hours' time in service. For FH-227 and F-27 airplanes modified with specific service bulletins, initial compliance within 100 hours' time in service and thereafter every 400 hours' time in service.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Fairchild-Hiller Model FH-227, F-27A, F-27F, F-27G, and F-27J airplanes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Rudder Skin Cracks
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_67-30-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 67-30-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Fairchild-Hiller Model FH-227, F-27A, F-27F, F-27G, and F-27J Airplanes Subject: Rudder Skin Cracks Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/01/1967 Make: Maryland Air Industries, Inc. Model: F-27A | F-27F | F-27G | F-27J | 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: 67-30-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-503 AD NUMBER: 67-30-03 SUBJECT HEADING: Airworthiness Directives; Fairchild-Hiller Model FH-227, F-27A, F-27F, F-27G, and F-27J Airplanes ACTION: SUMMARY: DATES: Effective November 1, 1967. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 67-30-03 FAIRCHILD-HILLER: Amdt. 39-503 Part 39 Federal Register November 2, 1967. Applies to Type FH-227 Airplanes, and Type F-27A, F-27F, F-27G and F-27J Airplanes. Compliance required as indicated. To detect cracks in the rudder skin, stiffeners, and rear spar flange located between the ribs of the lower section of the rudder, accomplish the following: (a) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 150 hours' time in service, and thereafter at intervals not to exceed 200 hours' time in service from the last inspection, comply with (b). (b) Visually inspect for cracks the left and right rudder skins from Stations 10 to 71 between the middle and rear spars. By manual compression of the left and right rudder skins, inspect for indications of cracks in the rudder stiffeners at Stations 16, 28, 40, 52 and 64 between the middle and rear spars, and in the rear spar flanges at these stations, or use an FAA-approved equivalent inspection. If a skin crack or indications of a crack in the stiffeners or rear spar flanges are found, comply with (d). (c) Within the next 100 hours' time in service after the effective date of this AD, unless already accomplished within the last 300 hours' time in service, and thereafter at intervals not to exceed 400 hours' time in service from the last inspection, comply with (b) on FH-227 airplanes modified in accordance with Fairchild-Hiller Service Bulletin No. 27-4 (FH 227) dated December 27, 1966 or later FAA-approved revision, and on F-27 airplane modified in accordance with Fairchild-Hiller Service Bulletin No. 27-42 (F-27) dated December 27, 1966 or later FAA-approved revision, or an FAA-approved equivalent modification. If a skin crack or indications of a crack in the stiffeners or rear spar flanges are found, comply with (d). (d) Repair cracked parts in accordance with Part 43 of the Federal Aviation Regulations or replace them with an unused part of the same part number or an FAA-approved equivalent before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed. (e) The repetitive inspection specified in (c) may be discontinued on FH-227 airplanes modified in accordance with Fairchild-Hiller Service Bulletin No. 27-11 (FH-227) Revision No. 1, dated September 7, 1967 or later FAA-approved revision, and on F-27 airplanes modified in accordance with Fairchild-Hiller Service Bulletin No. 27-54 (F-27) Revision No. 1, dated September 7, 1967 or later FAA-approved revision, or an FAA approved equivalent modification. (f) Equivalent inspections may be approved by an FAA maintenance inspector, Equivalent parts, Service Bulletin revisions, and modifications, must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (g) 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. This supersedes Amendment 39-390 (Part 39 F.R. April 8, 1967), AD 67-12-03. This amendment effective November 1, 1967. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_67-30-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 67-30-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Fairchild-Hiller Model FH-227, F-27A, F-27F, F-27G, and F-27J Airplanes Subject: Rudder Skin Cracks Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/01/1967 Make: Maryland Air Industries, Inc. Model: F-27A | F-27F | F-27G | F-27J | 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: 67-30-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-503 AD NUMBER: 67-30-03 SUBJECT HEADING: Airworthiness Directives; Fairchild-Hiller Model FH-227, F-27A, F-27F, F-27G, and F-27J Airplanes ACTION: SUMMARY: DATES: Effective November 1, 1967. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 67-30-03 FAIRCHILD-HILLER: Amdt. 39-503 Part 39 Federal Register November 2, 1967. Applies to Type FH-227 Airplanes, and Type F-27A, F-27F, F-27G and F-27J Airplanes. Compliance required as indicated. To detect cracks in the rudder skin, stiffeners, and rear spar flange located between the ribs of the lower section of the rudder, accomplish the following: (a) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 150 hours' time in service, and thereafter at intervals not to exceed 200 hours' time in service from the last inspection, comply with (b). (b) Visually inspect for cracks the left and right rudder skins from Stations 10 to 71 between the middle and rear spars. By manual compression of the left and right rudder skins, inspect for indications of cracks in the rudder stiffeners at Stations 16, 28, 40, 52 and 64 between the middle and rear spars, and in the rear spar flanges at these stations, or use an FAA-approved equivalent inspection. If a skin crack or indications of a crack in the stiffeners or rear spar flanges are found, comply with (d). (c) Within the next 100 hours' time in service after the effective date of this AD, unless already accomplished within the last 300 hours' time in service, and thereafter at intervals not to exceed 400 hours' time in service from the last inspection, comply with (b) on FH-227 airplanes modified in accordance with Fairchild-Hiller Service Bulletin No. 27-4 (FH 227) dated December 27, 1966 or later FAA-approved revision, and on F-27 airplane modified in accordance with Fairchild-Hiller Service Bulletin No. 27-42 (F-27) dated December 27, 1966 or later FAA-approved revision, or an FAA-approved equivalent modification. If a skin crack or indications of a crack in the stiffeners or rear spar flanges are found, comply with (d). (d) Repair cracked parts in accordance with Part 43 of the Federal Aviation Regulations or replace them with an unused part of the same part number or an FAA-approved equivalent before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed. (e) The repetitive inspection specified in (c) may be discontinued on FH-227 airplanes modified in accordance with Fairchild-Hiller Service Bulletin No. 27-11 (FH-227) Revision No. 1, dated September 7, 1967 or later FAA-approved revision, and on F-27 airplanes modified in accordance with Fairchild-Hiller Service Bulletin No. 27-54 (F-27) Revision No. 1, dated September 7, 1967 or later FAA-approved revision, or an FAA approved equivalent modification. (f) Equivalent inspections may be approved by an FAA maintenance inspector, Equivalent parts, Service Bulletin revisions, and modifications, must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (g) 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. This supersedes Amendment 39-390 (Part 39 F.R. April 8, 1967), AD 67-12-03. This amendment effective November 1, 1967. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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