AD 90-21-05
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | ATR - GIE Avions de Transport R gional | ATR42-300 | Airworthiness Directives; AEROSPATIALE Model ATR42-300 and ATR42-320 Series Airplanes |
| aircraft | ATR - GIE Avions de Transport R gional | ATR42-320 | Airworthiness Directives; AEROSPATIALE Model ATR42-300 and ATR42-320 Series Airplanes |
Unsafe Condition
The propeller brake may overheat and cause damage to the engine.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Modify the propeller brake electronic control wiring, modify the propeller brake control unit, replace the pushbutton switch with a two-position mechanical switch, install a new brake control unit, install a modified propeller brake, modify the propeller brake indicating logic, or remove the propeller brake as an alternative. Compliance may be adjusted with FAA approval.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 100 hours time-in-service after May 29, 1989 for paragraphs A-C; within 180 days after October 30, 1990 for paragraphs D-F. Compliance adjustments require FAA approval.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
AEROSPATIALE Model ATR42-300 and ATR42-320 series airplanes, certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Propeller Brake
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_90-21-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 90-21-05 Document Type: AD Final Rules Docket Number: 90-NM-68-AD Subject Heading: Airworthiness Directives; AEROSPATIALE Model ATR42-300 and ATR42-320 Series Airplanes Subject: Propeller Brake Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/30/1990 Make: ATR - GIE Avions de Transport R gional Model: ATR42-300 | ATR42-320 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 90-21-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 90-NM-68-AD AMENDMENT: 39-6757 AD NUMBER: 90-21-05 SUBJECT HEADING: Airworthiness Directives; AEROSPATIALE Model ATR42-300 and ATR42-320 Series Airplanes ACTION: SUMMARY: DATES: Effective October 30, 1990. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 90-21-05 AEROSPATIALE: Amendment 39-6757. Docket No. 90-NM-68-AD. Applicability: All Model ATR42-300 and ATR42-320 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent the propeller brake from overheating and causing damage to the engine, accomplish the following: A. Within 100 hours time-in-service after May 29, 1989 (the effective date of AD 88- 14-06 R1) for airplanes listed in Aerospatiale Service Bulletin ATR42-61-0013, Revision 1, dated December 8, 1987, modify the propeller brake electronic control wiring, in accordance with this service bulletin. B. Within 100 hours time-in-service after May 29, 1989 (the effective date of AD 88- 14-06 R1), for the airplanes listed in Aerospatiale Service Bulletin ATR42-61-0014, Revision 2, dated November 15, 1988, modify the propeller brake control unit, in accordance with this service bulletin. C. Within 100 hours time-in-service after May 29, 1989 (the effective date of AD 88- 14-06 R1), for the airplanes listed in Aerospatiale Service Bulletin ATR42-61-0010, Revision 3, dated December 19, 1988, replace the pushbutton switch with a two-position mechanical switch, in accordance with this service bulletin. D. Within 180 days after the effective date of this AD, install a new brake control unit in accordance with Aerospatiale Service Bulletin ATR42-61-0005, Revision 2, dated January 2, 1990; Revision 3, dated March 15, 1990; or Revision 4, dated June 19, 1990. E. Within 180 days after the effective date of this AD, install a modified propeller brake in accordance with Aerospatiale Service Bulletin ATR42-61-0022, Revision 1, dated September 25, 1989, or Revision 2, dated March 15, 1990. F. Within 180 days after the effective date of this AD, modify the propeller brake indicating logic, in accordance with Aerospatiale Service Bulletin ATR42-61-0023, Revision 1, dated December 1, 1989; or Revision 2, dated March 15, 1990. G. As an alternative to paragraphs A. through F. of this AD, operators may remove the propeller brake from the airplane in accordance with Aerospatiale Service Bulletin ATR42-61- 0016, Revision 1, dated September 1, 1988. H. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. I. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. Airworthiness Directive 90-21-05 supersedes AD 88-14-06 (Amendment 39-5967) as revised by AD 88-14-06 R1 (Amendment 39-6202). This amendment (39-6757, AD 90-21-05) becomes effective on October 30, 1990. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_90-21-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 90-21-05 Document Type: AD Final Rules Docket Number: 90-NM-68-AD Subject Heading: Airworthiness Directives; AEROSPATIALE Model ATR42-300 and ATR42-320 Series Airplanes Subject: Propeller Brake Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/30/1990 Make: ATR - GIE Avions de Transport R gional Model: ATR42-300 | ATR42-320 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: 90-21-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 90-NM-68-AD AMENDMENT: 39-6757 AD NUMBER: 90-21-05 SUBJECT HEADING: Airworthiness Directives; AEROSPATIALE Model ATR42-300 and ATR42-320 Series Airplanes ACTION: SUMMARY: DATES: Effective October 30, 1990. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 90-21-05 AEROSPATIALE: Amendment 39-6757. Docket No. 90-NM-68-AD. Applicability: All Model ATR42-300 and ATR42-320 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent the propeller brake from overheating and causing damage to the engine, accomplish the following: A. Within 100 hours time-in-service after May 29, 1989 (the effective date of AD 88- 14-06 R1) for airplanes listed in Aerospatiale Service Bulletin ATR42-61-0013, Revision 1, dated December 8, 1987, modify the propeller brake electronic control wiring, in accordance with this service bulletin. B. Within 100 hours time-in-service after May 29, 1989 (the effective date of AD 88- 14-06 R1), for the airplanes listed in Aerospatiale Service Bulletin ATR42-61-0014, Revision 2, dated November 15, 1988, modify the propeller brake control unit, in accordance with this service bulletin. C. Within 100 hours time-in-service after May 29, 1989 (the effective date of AD 88- 14-06 R1), for the airplanes listed in Aerospatiale Service Bulletin ATR42-61-0010, Revision 3, dated December 19, 1988, replace the pushbutton switch with a two-position mechanical switch, in accordance with this service bulletin. D. Within 180 days after the effective date of this AD, install a new brake control unit in accordance with Aerospatiale Service Bulletin ATR42-61-0005, Revision 2, dated January 2, 1990; Revision 3, dated March 15, 1990; or Revision 4, dated June 19, 1990. E. Within 180 days after the effective date of this AD, install a modified propeller brake in accordance with Aerospatiale Service Bulletin ATR42-61-0022, Revision 1, dated September 25, 1989, or Revision 2, dated March 15, 1990. F. Within 180 days after the effective date of this AD, modify the propeller brake indicating logic, in accordance with Aerospatiale Service Bulletin ATR42-61-0023, Revision 1, dated December 1, 1989; or Revision 2, dated March 15, 1990. G. As an alternative to paragraphs A. through F. of this AD, operators may remove the propeller brake from the airplane in accordance with Aerospatiale Service Bulletin ATR42-61- 0016, Revision 1, dated September 1, 1988. H. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. I. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. Airworthiness Directive 90-21-05 supersedes AD 88-14-06 (Amendment 39-5967) as revised by AD 88-14-06 R1 (Amendment 39-6202). This amendment (39-6757, AD 90-21-05) becomes effective on October 30, 1990. 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
98-09-22
final ruleAirworthiness Directives; Aerospatiale Model ATR42-200, -300, and -320 Series Airplanes
Unsafe Condition: Fatigue cracking of the windshield frame structure could reduce structural integrity of the airplane.
98-06-34
final ruleAirworthiness Directives; Aerospatiale Model ATR-42 and ATR-72 Series Airplanes
Unsafe Condition: Loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
97-26-11
final ruleAirworthiness Directives; Aerospatiale Model ATR42-200, -300, and -320 Series Airplanes
Unsafe Condition: Corrosion of the rear spars of the wings, which could result in reduced structural integrity of the wing.
97-25-18
final ruleAirworthiness Directives; Aerospatiale Model ATR42 Series Airplanes
Unsafe Condition: Wear of the main landing gear attachment pins could result in collapse of the main landing gear.
