AD 90-09-07
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Schweizer Aircraft Corporation | 269C | Airworthiness Directives; Schweizer Aircraft Corporation (Hughes Helicopter Inc.) Model 269C Series Helicopters |
Unsafe Condition
Improper location of the rod spring attachment clamp (P/N AN735-9) and misalignment of the spring attach angles on the lower longitudinal cyclic control rod assembly (P/N 269A9940-7) could lead to loss of longitudinal cyclic control and subsequent loss of the helicopter.
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Required Actions
Inspect the lower longitudinal cyclic control rod assembly to verify the clamp position and spring attach angles. Adjust the clamp and angles if necessary to achieve a distance of 7.85 to 7.97 inches between the rod forward jam nut and clamp, and ensure angles are parallel and aligned. Install a new worm type hose clamp (P/N AN737TW22 or AN737TW24) forward of the existing clamp and torque to 40-45 in-lb.
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Compliance Time
Required prior to further flight after the effective date of this AD
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Affected Aircraft
Schweizer Aircraft Corporation (Hughes Helicopter Inc.) Model 269C series helicopters, serial number 0004 through 1456
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Federal Register Abstract
Cyclic Control Rod Assembly
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_90-09-07.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 90-09-07 Document Type: AD Final Rules Docket Number: 90-ASW-29-AD Subject Heading: Airworthiness Directives; Schweizer Aircraft Corporation (Hughes Helicopter Inc.) Model 269C Series Helicopters Subject: Cyclic Control Rod Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/03/1990 Make: Schweizer Aircraft Corporation Model: 269C Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 90-09-07 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 90-ASW-29-AD AMENDMENT: 39-6717 AD NUMBER: 90-09-07 SUBJECT HEADING: Airworthiness Directives; Schweizer Aircraft Corporation (Hughes Helicopter Inc.) Model 269C Series Helicopters ACTION: Final Rule of priority letter AD SUMMARY: DATES: Effective October 3, 1990. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 90-09-07 SCHWEIZER AIRCRAFT CORPORATION (HUGHES HELICOPTER INC): Amendment 39-6717. Final Rule of priority letter AD. Docket No. 90-ASW-29-AD. Applicability: Model 269C series helicopters, serial number (S/N) 0004 through 1456, certificated in any category. Compliance: Required prior to further flight after the effective date of this AD, unless already accomplished. To prevent possible loss of longitudinal cyclic control and subsequent loss of the helicopter, accomplish the following: (a) Inspect the lower longitudinal cyclic control rod assembly, part number (P/N) 269A9940-7, to verify the proper location of the rod spring attachment clamp, P/N AN735-9, and position of the spring attach angles as follows: (1) Gain access to the lower longitudinal cyclic control rod assembly. (2) Position the cyclic stick to the full forward position. Verify that the stud in the friction linkage is completely forward in the friction link slot. If not, see paragraph (b). (3) On the lower longitudinal cyclic control rod assembly, measure the distance between the aft face of the forward jam nut and the forward edge of the clamp, P/N AN735-9. The distance should be between 7.85 and 7.97 inches. If not, see paragraph (b). (4) Verify that the horizontal legs of the angles attached to the clamp, P/N AN735-9, are parallel to the control rod and aligned with each other. If not, see paragraph (b). If correct, prevent movement of the parts, and torque the clamp nut to 20-25 in-lb. (b) Adjust the clamp and the attached angles, if necessary, by disconnecting the springs and loosening the screw and nut holding the angles and clamp, P/N AN735-9, together. Set a distance of 7.85 to 7.97 inches between the aft face of the rod forward jam nut and the forward edge of the clamp, P/N AN735-9. Position the horizontal legs of the angles attached to the clamp, P/N AN735-9, parallel to the control rod, and align with each other. Prevent movement of the parts, and torque the nut to 20-25 in-lb. Determine that the clamp is secure. Reconnect the springs to the angles. (c) Install the new worm type hose clamp, P/N AN737TW22 or AN737TW24, on the control rod, forward of and touching the clamp, P/N AN735-9. Torque the screw to a range of 40-45 in-1b. Determine that the clamp is secure. (d) Aircraft may be ferried in accordance with the provisions of FAR Sections 21.197 and 21.199 to a base where the requirements of the AD can be accomplished, provided cyclic control displacement is not reduced. (e) Alternate inspections, modification, or other actions which provide an equivalent level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, 181 South Franklin Avenue, Room 202, Valley Stream, New York. NOTE: Schweizer Service Bulletin No. B237 pertains to the requirements of this AD. This amendment (39-6717, AD 90-09-07) becomes effective October 3, 1990, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD 90-09-07, issued on April 24, 1990, which contained this amendment. FOOTER:
Document Text
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AD Final Rules - DRS_90-09-07.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 90-09-07 Document Type: AD Final Rules Docket Number: 90-ASW-29-AD Subject Heading: Airworthiness Directives; Schweizer Aircraft Corporation (Hughes Helicopter Inc.) Model 269C Series Helicopters Subject: Cyclic Control Rod Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/03/1990 Make: Schweizer Aircraft Corporation Model: 269C 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: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 90-09-07 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 90-ASW-29-AD AMENDMENT: 39-6717 AD NUMBER: 90-09-07 SUBJECT HEADING: Airworthiness Directives; Schweizer Aircraft Corporation (Hughes Helicopter Inc.) Model 269C Series Helicopters ACTION: Final Rule of priority letter AD SUMMARY: DATES: Effective October 3, 1990. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 90-09-07 SCHWEIZER AIRCRAFT CORPORATION (HUGHES HELICOPTER INC): Amendment 39-6717. Final Rule of priority letter AD. Docket No. 90-ASW-29-AD. Applicability: Model 269C series helicopters, serial number (S/N) 0004 through 1456, certificated in any category. Compliance: Required prior to further flight after the effective date of this AD, unless already accomplished. To prevent possible loss of longitudinal cyclic control and subsequent loss of the helicopter, accomplish the following: (a) Inspect the lower longitudinal cyclic control rod assembly, part number (P/N) 269A9940-7, to verify the proper location of the rod spring attachment clamp, P/N AN735-9, and position of the spring attach angles as follows: (1) Gain access to the lower longitudinal cyclic control rod assembly. (2) Position the cyclic stick to the full forward position. Verify that the stud in the friction linkage is completely forward in the friction link slot. If not, see paragraph (b). (3) On the lower longitudinal cyclic control rod assembly, measure the distance between the aft face of the forward jam nut and the forward edge of the clamp, P/N AN735-9. The distance should be between 7.85 and 7.97 inches. If not, see paragraph (b). (4) Verify that the horizontal legs of the angles attached to the clamp, P/N AN735-9, are parallel to the control rod and aligned with each other. If not, see paragraph (b). If correct, prevent movement of the parts, and torque the clamp nut to 20-25 in-lb. (b) Adjust the clamp and the attached angles, if necessary, by disconnecting the springs and loosening the screw and nut holding the angles and clamp, P/N AN735-9, together. Set a distance of 7.85 to 7.97 inches between the aft face of the rod forward jam nut and the forward edge of the clamp, P/N AN735-9. Position the horizontal legs of the angles attached to the clamp, P/N AN735-9, parallel to the control rod, and align with each other. Prevent movement of the parts, and torque the nut to 20-25 in-lb. Determine that the clamp is secure. Reconnect the springs to the angles. (c) Install the new worm type hose clamp, P/N AN737TW22 or AN737TW24, on the control rod, forward of and touching the clamp, P/N AN735-9. Torque the screw to a range of 40-45 in-1b. Determine that the clamp is secure. (d) Aircraft may be ferried in accordance with the provisions of FAR Sections 21.197 and 21.199 to a base where the requirements of the AD can be accomplished, provided cyclic control displacement is not reduced. (e) Alternate inspections, modification, or other actions which provide an equivalent level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, 181 South Franklin Avenue, Room 202, Valley Stream, New York. NOTE: Schweizer Service Bulletin No. B237 pertains to the requirements of this AD. This amendment (39-6717, AD 90-09-07) becomes effective October 3, 1990, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD 90-09-07, issued on April 24, 1990, which contained this amendment. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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