AD 89-20-03 R1
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Schweizer Aircraft Corporation | 269A | Airworthiness Directives; SCHWEIZER AIRCRAFT CORPORATION (HUGHES HELICOPTERS, Inc.) All Model 269 Series Helicopters |
| aircraft | Schweizer Aircraft Corporation | 269A-1 | Airworthiness Directives; SCHWEIZER AIRCRAFT CORPORATION (HUGHES HELICOPTERS, Inc.) All Model 269 Series Helicopters |
| aircraft | Schweizer Aircraft Corporation | 269B | Airworthiness Directives; SCHWEIZER AIRCRAFT CORPORATION (HUGHES HELICOPTERS, Inc.) All Model 269 Series Helicopters |
| aircraft | Schweizer Aircraft Corporation | 269C | Airworthiness Directives; SCHWEIZER AIRCRAFT CORPORATION (HUGHES HELICOPTERS, Inc.) All Model 269 Series Helicopters |
Unsafe Condition
Loss of the abrasion strips on the tail rotor blades with subsequent loss of tail rotor control.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Install rivets in the tail rotor blades as specified in Appendix I of this AD. Visually check the abrasion strip for cracking or chipping daily before flight. Inspect bond line with magnifying glass, dye penetrant, or tap test if defects are found. Remove blades with bond separation from service before flight.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Prior to further flight after the effective date (February 22, 1991) for blades listed in paragraph (a)(1). Within the next 100 hours' time in service after the effective date for other blades. Daily checks must be done before each flight.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
All Model 269 series helicopters equipped with 269A6035 series tail rotor blades manufactured before September 15, 1989.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Tail Rotor Blades
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_89-20-03_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 89-20-03 R1 Document Type: AD Final Rules Docket Number: 89-ASW-41 Subject Heading: Airworthiness Directives; SCHWEIZER AIRCRAFT CORPORATION (HUGHES HELICOPTERS, Inc.) All Model 269 Se...Show more Subject: Tail Rotor Blades Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 02/22/1991 Make: Schweizer Aircraft Corporation Model: 269A | 269A-1 | 269B | 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: 89-20-03 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 89-ASW-41 AMENDMENT: 39-6863 AD NUMBER: 89-20-03 R1 SUBJECT HEADING: Airworthiness Directives; SCHWEIZER AIRCRAFT CORPORATION (HUGHES HELICOPTERS, Inc.) All Model 269 Series Helicopters ACTION: SUMMARY: DATES: Effective February 22, 1991. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 89-20-03 R1 SCHWEIZER AIRCRAFT CORPORATION (HUGHES HELICOPTERS, Inc.): Amendment 39-6540 as revised by Amendment 39-6863. Docket No. 89-ASW-41. Applicability: All Model 269 series helicopters, certified in any category, equipped with 269A6035 series tail rotor blades manufactured before September 15, 1989. Compliance: Required as indicated, unless already accomplished. To prevent the loss of the abrasion strips on the tail rotor blades with subsequent loss of tail rotor control, accomplish the following: (a) Install rivets in the tail rotor blades as follows: (1) Prior to further flight after the effective date of this AD, modify the affected tail rotor blades with the following serial numbers (S/N) in accordance with the procedures detailed in Appendix 1 of this AD: R0056 S524 S584 S640-S644 R0086 S534 S586 S646 R1059 S538 S588 S648-S650 R1066 S539 S589-S594 S653 R1560 S544 S596 S654 R1922 S546 S598-S603 S657 R3296 S547 S605 S660-S662 R3314 S549 S607 S664-S666 R3330 S550 S608 S668 R3349 S553 S611-S620 S670-S672 S21 S556-S563 S623-S626 S675-S677 S431 S565 S631-S633 S679-S682 S513 S566 5637 S684-S688 S515 S568-S571 S638 S691-S694 S518 S573 S521 S576-S582 (2) Within the next 100 hours' time in service after the effective date of this AD, modify all tail rotor blades, whether manufactured by Schweizer or Hughes, except those listed in paragraph (a)(1) in accordance with procedures described in Appendix I of this AD. (b) Before the first flight of each day, visually check the abrasion strip of these blades for any evidence of cracking or chipping along the entire abrasion strip/airfoil bond line and the blade tip. (c) If, during the check required by paragraph (b), cracking or chipping is observed, inspect the bond line for bond separation using a 10 power or higher magnifying glass. If evidence of debonding along the abrasion strip/bond line or blade tip is detected, inspect the tail rotor blade using dye penetrant or equivalent inspection method and tap test prior to further flight in accordance with Appendix I of this AD. (d) Remove from service, prior to further flight, any rotor blade found to contain bond separation. (e) The visual check required by paragraph (b) of this AD may be performed by the pilot and must be recorded in accordance with FAR Section 43.9. NOTE: The pilot, when complying, must make appropriate entries and the record must be maintained in accordance with FAR Section 91.173 or 135.439. (f) Aircraft may be ferried in accordance with the provisions of FAR Section 21.197 and 21.199 to a base where the requirements of this AD can be accomplished. (g) Alternative inspections, modifications, 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, NY. NOTE: Blades modified to Schweizer Installation Instructions No. CKP-C-40, Kit No. SCA-269-K-056, dated August 31, 1989, or Schweizer Service Information Notice No. N- 183.3, September 15, 1989, Part III, comply with paragraph (a) of this AD. (h) Tail rotor blades manufactured by Schweizer with a bond date on or after September 15, 1989, shown on the identification plate located on the inboard end of the blade, are exempt from the requirements of this AD. NOTE: Appendix I, which is not reprinted in this AD, includes material from Schweizer Aircraft Corporation Service Information Notice (S/N) N-183.3, dated September 15, 1989. A copy of the service information may be obtained from Schweizer Aircraft Corporation, P.O. Box 147, Elmira, New York 14902. Airworthiness Directive 89-20-03 R1 supersedes AD 87-22-07, Amendment 39-5730 (52 FR 4155, October 29, 1987). Airworthiness Directive 89-20-03 R1 amends AD 89-20-03, Amendment 39-6540 (55 FR 10228, March 20, 1990) which was the Final Rule of Priority Letter AD 89-20-03 issued on September 28, 1990. This amendment (39-6863, AD 89-20-03 R1) becomes effective on February 22, 1991. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_89-20-03_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 89-20-03 R1 Document Type: AD Final Rules Docket Number: 89-ASW-41 Subject Heading: Airworthiness Directives; SCHWEIZER AIRCRAFT CORPORATION (HUGHES HELICOPTERS, Inc.) All Model 269 Se...Show more Subject: Tail Rotor Blades Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 02/22/1991 Make: Schweizer Aircraft Corporation Model: 269A | 269A-1 | 269B | 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: 89-20-03 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 89-ASW-41 AMENDMENT: 39-6863 AD NUMBER: 89-20-03 R1 SUBJECT HEADING: Airworthiness Directives; SCHWEIZER AIRCRAFT CORPORATION (HUGHES HELICOPTERS, Inc.) All Model 269 Series Helicopters ACTION: SUMMARY: DATES: Effective February 22, 1991. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 89-20-03 R1 SCHWEIZER AIRCRAFT CORPORATION (HUGHES HELICOPTERS, Inc.): Amendment 39-6540 as revised by Amendment 39-6863. Docket No. 89-ASW-41. Applicability: All Model 269 series helicopters, certified in any category, equipped with 269A6035 series tail rotor blades manufactured before September 15, 1989. Compliance: Required as indicated, unless already accomplished. To prevent the loss of the abrasion strips on the tail rotor blades with subsequent loss of tail rotor control, accomplish the following: (a) Install rivets in the tail rotor blades as follows: (1) Prior to further flight after the effective date of this AD, modify the affected tail rotor blades with the following serial numbers (S/N) in accordance with the procedures detailed in Appendix 1 of this AD: R0056 S524 S584 S640-S644 R0086 S534 S586 S646 R1059 S538 S588 S648-S650 R1066 S539 S589-S594 S653 R1560 S544 S596 S654 R1922 S546 S598-S603 S657 R3296 S547 S605 S660-S662 R3314 S549 S607 S664-S666 R3330 S550 S608 S668 R3349 S553 S611-S620 S670-S672 S21 S556-S563 S623-S626 S675-S677 S431 S565 S631-S633 S679-S682 S513 S566 5637 S684-S688 S515 S568-S571 S638 S691-S694 S518 S573 S521 S576-S582 (2) Within the next 100 hours' time in service after the effective date of this AD, modify all tail rotor blades, whether manufactured by Schweizer or Hughes, except those listed in paragraph (a)(1) in accordance with procedures described in Appendix I of this AD. (b) Before the first flight of each day, visually check the abrasion strip of these blades for any evidence of cracking or chipping along the entire abrasion strip/airfoil bond line and the blade tip. (c) If, during the check required by paragraph (b), cracking or chipping is observed, inspect the bond line for bond separation using a 10 power or higher magnifying glass. If evidence of debonding along the abrasion strip/bond line or blade tip is detected, inspect the tail rotor blade using dye penetrant or equivalent inspection method and tap test prior to further flight in accordance with Appendix I of this AD. (d) Remove from service, prior to further flight, any rotor blade found to contain bond separation. (e) The visual check required by paragraph (b) of this AD may be performed by the pilot and must be recorded in accordance with FAR Section 43.9. NOTE: The pilot, when complying, must make appropriate entries and the record must be maintained in accordance with FAR Section 91.173 or 135.439. (f) Aircraft may be ferried in accordance with the provisions of FAR Section 21.197 and 21.199 to a base where the requirements of this AD can be accomplished. (g) Alternative inspections, modifications, 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, NY. NOTE: Blades modified to Schweizer Installation Instructions No. CKP-C-40, Kit No. SCA-269-K-056, dated August 31, 1989, or Schweizer Service Information Notice No. N- 183.3, September 15, 1989, Part III, comply with paragraph (a) of this AD. (h) Tail rotor blades manufactured by Schweizer with a bond date on or after September 15, 1989, shown on the identification plate located on the inboard end of the blade, are exempt from the requirements of this AD. NOTE: Appendix I, which is not reprinted in this AD, includes material from Schweizer Aircraft Corporation Service Information Notice (S/N) N-183.3, dated September 15, 1989. A copy of the service information may be obtained from Schweizer Aircraft Corporation, P.O. Box 147, Elmira, New York 14902. Airworthiness Directive 89-20-03 R1 supersedes AD 87-22-07, Amendment 39-5730 (52 FR 4155, October 29, 1987). Airworthiness Directive 89-20-03 R1 amends AD 89-20-03, Amendment 39-6540 (55 FR 10228, March 20, 1990) which was the Final Rule of Priority Letter AD 89-20-03 issued on September 28, 1990. This amendment (39-6863, AD 89-20-03 R1) becomes effective on February 22, 1991. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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