AD 84-10-51 R1
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Columbia Helicopters, Inc. | 234 | Airworthiness Directives; BOEING VERTOL COMPANY Model 234 Series Helicopters |
Unsafe Condition
Cracking of the forward main rotor drive shaft could cause possible hazards in flight.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the rotor drive shaft within 70 hours time in service after the effective date or upon 1,600 total hours on the shaft, whichever is later. Subsequent inspections must be done at intervals not exceeding 35 hours time in service. Remove and replace cracked shafts before further flight. Use Service Bulletin 234-63-1009 or equivalent method approved by the FAA.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 70 hours time in service after the effective date of this amendment or upon accumulation of 1,600 total hours time in service on the rotor shaft, whichever occurs later, and thereafter at intervals not to exceed 35 hours time in service from the last inspection
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
BOEING VERTOL COMPANY Model 234 series helicopters equipped with forward main rotor drive shaft P/N 114D1245-7
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Forward Rotor Drive Shaft
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_84-10-51_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 84-10-51 R1 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; BOEING VERTOL COMPANY Model 234 Series Helicopters Subject: Forward Rotor Drive Shaft Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 07/24/1986 Make: Columbia Helicopters, Inc. Model: 234 Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 84-10-51 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5352 AD NUMBER: 84-10-51 R1 SUBJECT HEADING: Airworthiness Directives; BOEING VERTOL COMPANY Model 234 Series Helicopters ACTION: SUMMARY: DATES: Effective July 24, 1986. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 84-10-51 R1 BOEING VERTOL COMPANY: Amendment 39-5024 as amended by Amendment 39-5352. Applies to Model 234 series helicopters, certificated in any category, equipped with forward main rotor drive shaft P/N 114D1245-7. Compliance is required as indicated, unless already accomplished. To prevent possible hazards in flight associated with cracking of the forward main rotor drive shaft, accomplish the following: (a) Within 70 hours time in service after the effective date of this amendment or upon accumulation of 1,600 total hours time in service on the rotor shaft, whichever occurs later, and thereafter at intervals not to exceed 35 hours time in service from the last inspection, inspect the rotor drive shaft in accordance with paragraph 3, "Accomplishment Instructions," Boeing Vertol Service Bulletin No. 234-63-1009, dated June 29, 1984, or Revision 1 dated May 1, 1986, or an FAA-approved equivalent. (b) Remove from service forward main rotor drive shafts having a crack and replace with a serviceable part prior to further flight. (c) An equivalent method of compliance with this AD may be used when approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. (d) Upon submission of substantiating data by an owner through an FAA Maintenance Inspector, the Manager, New York Aircraft Certification Office, FAA New England Region, may adjust the compliance times specified in this AD. (e) The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Boeing Vertol Company, Boeing Center, P.O. Box 16858, Philadelphia, Pennsylvania 19142. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas. Amendment 39-5024 (50 FR 15539) became effective April 22, 1985, as to all persons except those persons to whom it was made immediately effective by telegraphic AD No. T84-10- 51, issued May 3, 1984, which contained this amendment. This Amendment 39-5352 becomes effective July 24, 1986. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_84-10-51_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 84-10-51 R1 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; BOEING VERTOL COMPANY Model 234 Series Helicopters Subject: Forward Rotor Drive Shaft Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 07/24/1986 Make: Columbia Helicopters, Inc. Model: 234 Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 84-10-51 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5352 AD NUMBER: 84-10-51 R1 SUBJECT HEADING: Airworthiness Directives; BOEING VERTOL COMPANY Model 234 Series Helicopters ACTION: SUMMARY: DATES: Effective July 24, 1986. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 84-10-51 R1 BOEING VERTOL COMPANY: Amendment 39-5024 as amended by Amendment 39-5352. Applies to Model 234 series helicopters, certificated in any category, equipped with forward main rotor drive shaft P/N 114D1245-7. Compliance is required as indicated, unless already accomplished. To prevent possible hazards in flight associated with cracking of the forward main rotor drive shaft, accomplish the following: (a) Within 70 hours time in service after the effective date of this amendment or upon accumulation of 1,600 total hours time in service on the rotor shaft, whichever occurs later, and thereafter at intervals not to exceed 35 hours time in service from the last inspection, inspect the rotor drive shaft in accordance with paragraph 3, "Accomplishment Instructions," Boeing Vertol Service Bulletin No. 234-63-1009, dated June 29, 1984, or Revision 1 dated May 1, 1986, or an FAA-approved equivalent. (b) Remove from service forward main rotor drive shafts having a crack and replace with a serviceable part prior to further flight. (c) An equivalent method of compliance with this AD may be used when approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. (d) Upon submission of substantiating data by an owner through an FAA Maintenance Inspector, the Manager, New York Aircraft Certification Office, FAA New England Region, may adjust the compliance times specified in this AD. (e) The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Boeing Vertol Company, Boeing Center, P.O. Box 16858, Philadelphia, Pennsylvania 19142. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas. Amendment 39-5024 (50 FR 15539) became effective April 22, 1985, as to all persons except those persons to whom it was made immediately effective by telegraphic AD No. T84-10- 51, issued May 3, 1984, which contained this amendment. This Amendment 39-5352 becomes effective July 24, 1986. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.
Related Airworthiness Directives
2018-16-11
final ruleAirworthiness Directives; Various Model 234 and Model CH-47D Helicopters
Unsafe Condition: cracking in the pitch housing lugs, located on the lead side of the lower vertical pin lug, due to fatigue and underestimated load conditions in the original life limit calculations.
2014-13-04
final ruleAirworthiness Directives; Columbia Helicopters, Inc. (Type Certificate Previously Held by Boeing Defense & Space Group) Helicopters
Unsafe Condition: Fatigue failure of the structure surrounding the aft pylon following an aft rotor blade failure, leading to blade separation, vibration, and overload of the aft pylon structure, resulting in pylon ...
2004-06-51
final ruleAirworthiness Directives; Boeing Defense and Space Group Model 234 Helicopters
Unsafe Condition: Crack in the upper shaft extension of the aft vertical shaft assembly, which could result in catastrophic failure of the assembly and subsequent loss of control of the helicopter.
2002-15-02
final ruleAirworthiness Directives; Hamilton Sundstrand Power Systems (Formerly Sundstrand Power Systems, Turbomach, and Solar) T-62T Series Auxiliary Power Units
Unsafe Condition: Stress levels in compressor wheels part number 100636-1 are high enough to initiate and drive crack growth, potentially leading to uncontained compressor wheel failure and damage to the airplane.