AD 73-12-05
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Maryland Air Industries, Inc. | F-27 | Airworthiness Directives; Fairchild Model F-27 and FH-227 Aircraft |
| aircraft | Maryland Air Industries, Inc. | F-27A | Airworthiness Directives; Fairchild Model F-27 and FH-227 Aircraft |
| aircraft | Maryland Air Industries, Inc. | F-27B | Airworthiness Directives; Fairchild Model F-27 and FH-227 Aircraft |
| aircraft | Maryland Air Industries, Inc. | F-27F | Airworthiness Directives; Fairchild Model F-27 and FH-227 Aircraft |
| aircraft | Maryland Air Industries, Inc. | F-27G | Airworthiness Directives; Fairchild Model F-27 and FH-227 Aircraft |
| aircraft | Maryland Air Industries, Inc. | F-27J | Airworthiness Directives; Fairchild Model F-27 and FH-227 Aircraft |
| aircraft | Maryland Air Industries, Inc. | F-27M | Airworthiness Directives; Fairchild Model F-27 and FH-227 Aircraft |
| aircraft | Maryland Air Industries, Inc. | FH-227 | Airworthiness Directives; Fairchild Model F-27 and FH-227 Aircraft |
| aircraft | Maryland Air Industries, Inc. | FH-227B | Airworthiness Directives; Fairchild Model F-27 and FH-227 Aircraft |
| aircraft | Maryland Air Industries, Inc. | FH-227C | Airworthiness Directives; Fairchild Model F-27 and FH-227 Aircraft |
| aircraft | Maryland Air Industries, Inc. | FH-227D | Airworthiness Directives; Fairchild Model F-27 and FH-227 Aircraft |
| aircraft | Maryland Air Industries, Inc. | FH-227E | Airworthiness Directives; Fairchild Model F-27 and FH-227 Aircraft |
Unsafe Condition
Cracks in the vertical stabilizer attachment fitting assemblies (P/N's 27-233000-11, -12, -31, -32, -41, and -42) due to corrosion and fatigue after accumulating 2500 hours or more in service.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect lugs of fittings for cracks using ultrasonic method or equivalent; inspect flanges and inner cavity for corrosion using dye penetrant and 10-power glass or equivalent. Repeat inspections at intervals not exceeding 12 months or 2500 hours, whichever comes first. Replace or repair cracked/corroded parts per service bulletins or approved methods.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 30 days for crack inspections (unless done in last 11 months) and within 60 days for corrosion inspections (unless done in last 10 months).
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Fairchild Model F-27 and FH-227 aircraft with vertical stabilizer attachment fitting assemblies P/N's 27-233000-11, -12, -31, -32, -41, and -42 that have accumulated 2500 hours or more in service.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Vertical Stabilizer Fittings
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_73-12-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 73-12-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Fairchild Model F-27 and FH-227 Aircraft Subject: Vertical Stabilizer Fittings Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/29/1979 Make: Maryland Air Industries, Inc. Model: F-27 | F-27A | F-27B | F-27F | F-27G | F-27J | F-27M | 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: 73-12-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3543 AD NUMBER: 73-12-05 SUBJECT HEADING: Airworthiness Directives; Fairchild Model F-27 and FH-227 Aircraft ACTION: SUMMARY: DATES: Effective August 29, 1979. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 73-12-05 FAIRCHILD: Amendment 39-1656 as amended by Amendment 39-2078 is further amended by Amendment 39-3543. Applies to all Fairchild F-27 and FH-227 Type Aircraft Certificated in all categories. Compliance required as indicated: 1. As to the vertical stabilizer attachment fitting assemblies for both front and rear spars, P/N's 27-233000-11, -12, -31, -32, -41 and -42 which have accumulated 2500 hours or more in service. a. Within the next 30 days, unless accomplished within the last 11 months, inspect all surfaces of the lugs of the fittings for cracks using an ultrasonic method in accordance with paragraph 2, Accomplishment Instructions, Part I, of Fairchild Service Bulletins F-27-55-20 and FH-227-55-11, reissued June 15, 1979, or an approved equivalent inspection. Inspect other areas of the fittings for cracks using a dye penetrant and a 10-power glass or an approved equivalent inspection. b. Within the next 60 days, unless accomplished within the last 10 months, inspect the fittings around the flanges and inner cavity for corrosion in accordance with paragraph 2, Accomplishment Instructions, Part II, of Fairchild Service Bulletins F-27-55-20 and FH-227-55-11, reissued June 15, 1979, or in accordance with an approved equivalent procedure. c. The inspection specified in "a" above shall be repeated at intervals not to exceed 12 calendar months or 2500 hours in service from the last inspection, whichever occurs first. d. The inspection specified in "b" above shall be repeated at intervals not to exceed 12 calendar months from the last inspection. 2. Cracked parts shall be replaced and corroded parts shall be replaced or repaired prior to further flight. a. Parts replacement shall be in accordance with paragraph 2 of Fairchild Service Bulletins F-27-55-20 and FH-227-55-11, reissued June 15, 1979, and they shall be the same part number or approved equivalent parts. b. Parts repair shall be in accordance with paragraph 2 and Figures 2 and 3 of Fairchild Service Bulletins F-27-55-20 and FH-227-55-11, reissued June 15, 1979, or an approved equivalent repair. 3. The aircraft may be flown in accordance with FAR 21.197 to a base where the inspection or repairs can be performed. 4. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection interval specified in this AD. Equivalent inspections, parts or repair must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Amendment 39-1656 was effective June 14, 1973. Amendment 39-2078 was effective January 28, 1975. This Amendment 39-3543 is effective August 29, 1979. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_73-12-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 73-12-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Fairchild Model F-27 and FH-227 Aircraft Subject: Vertical Stabilizer Fittings Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/29/1979 Make: Maryland Air Industries, Inc. Model: F-27 | F-27A | F-27B | F-27F | F-27G | F-27J | F-27M | 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: 73-12-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3543 AD NUMBER: 73-12-05 SUBJECT HEADING: Airworthiness Directives; Fairchild Model F-27 and FH-227 Aircraft ACTION: SUMMARY: DATES: Effective August 29, 1979. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 73-12-05 FAIRCHILD: Amendment 39-1656 as amended by Amendment 39-2078 is further amended by Amendment 39-3543. Applies to all Fairchild F-27 and FH-227 Type Aircraft Certificated in all categories. Compliance required as indicated: 1. As to the vertical stabilizer attachment fitting assemblies for both front and rear spars, P/N's 27-233000-11, -12, -31, -32, -41 and -42 which have accumulated 2500 hours or more in service. a. Within the next 30 days, unless accomplished within the last 11 months, inspect all surfaces of the lugs of the fittings for cracks using an ultrasonic method in accordance with paragraph 2, Accomplishment Instructions, Part I, of Fairchild Service Bulletins F-27-55-20 and FH-227-55-11, reissued June 15, 1979, or an approved equivalent inspection. Inspect other areas of the fittings for cracks using a dye penetrant and a 10-power glass or an approved equivalent inspection. b. Within the next 60 days, unless accomplished within the last 10 months, inspect the fittings around the flanges and inner cavity for corrosion in accordance with paragraph 2, Accomplishment Instructions, Part II, of Fairchild Service Bulletins F-27-55-20 and FH-227-55-11, reissued June 15, 1979, or in accordance with an approved equivalent procedure. c. The inspection specified in "a" above shall be repeated at intervals not to exceed 12 calendar months or 2500 hours in service from the last inspection, whichever occurs first. d. The inspection specified in "b" above shall be repeated at intervals not to exceed 12 calendar months from the last inspection. 2. Cracked parts shall be replaced and corroded parts shall be replaced or repaired prior to further flight. a. Parts replacement shall be in accordance with paragraph 2 of Fairchild Service Bulletins F-27-55-20 and FH-227-55-11, reissued June 15, 1979, and they shall be the same part number or approved equivalent parts. b. Parts repair shall be in accordance with paragraph 2 and Figures 2 and 3 of Fairchild Service Bulletins F-27-55-20 and FH-227-55-11, reissued June 15, 1979, or an approved equivalent repair. 3. The aircraft may be flown in accordance with FAR 21.197 to a base where the inspection or repairs can be performed. 4. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection interval specified in this AD. Equivalent inspections, parts or repair must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Amendment 39-1656 was effective June 14, 1973. Amendment 39-2078 was effective January 28, 1975. This Amendment 39-3543 is effective August 29, 1979. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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