AD 82-22-05
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus Helicopters | AS332C | Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS332C/AS332L Series Helicopters |
| aircraft | Airbus Helicopters | AS332L | Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS332C/AS332L Series Helicopters |
Unsafe Condition
Fretting corrosion and possible cracking of the main rotor head spindle yoke lugs could result in loss of main rotor control.
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Required Actions
Conduct daily visual inspections of main rotor spindles, check torque of flap hinge pin nut every 25 hours' time in service, inspect spindle yoke lug every 100 hours' total time in service, reduce spindle service life limit to 300 hours, limit collective pitch to 16 degrees and airspeed as specified, and install placards near airspeed indicators.
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Compliance Time
Prior to the first flight of each day following the effective date, within 25 hours' time in service, within 100 hours' time in service after the effective date, and at intervals not to exceed specified time frames.
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Affected Aircraft
Societe Nationale Industrielle Aerospatiale (SNIAS) Model AS332C/AS332L series helicopters equipped with main rotor spindles P/N 330A31.1122.09 and .10.
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Federal Register Abstract
Main Rotor Spindles
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_82-22-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 82-22-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS332C/AS332L Se...Show more Subject: Main Rotor Spindles Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/11/1982 Make: Airbus Helicopters Model: AS332C | AS332L Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 82-22-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4478 AD NUMBER: 82-22-05 SUBJECT HEADING: Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS332C/AS332L Series Helicopters ACTION: SUMMARY: DATES: Effective November 11, 1982. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 82-22-05 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4478. Applies to Model AS332C/AS332L series helicopters certificated in all categories that are equipped with main rotor spindles P/N 330A31.1122.09 and .10. Compliance is required as indicated. To detect fretting corrosion and to prevent possible cracking of the main rotor head spindle yoke lugs, accomplish the following: (a) Prior to the first flight of each day following the effective date of the AD, accomplish a visual inspection in accordance with Aerospatiale AS332 Service Bulletin No. 05.02, paragraph 1C(2)(a) or equivalent approved by the Manager, FAA, Europe, Africa and Middle East office. (b) Within the next 25 hours' time in service following the effective date of this AD, unless already accomplished, check the torque of the flap hinge pin nut in accordance with Aerospatiale AS332 Service Bulletin No. 05.02, paragraph 1C(1)(a) or an equivalent approved by the Manager, FAA, Europe, Africa and Middle East office. Thereafter, at intervals not to exceed 25 hours' time in service since the last inspection, accomplish the inspection in accordance with Aerospatiale AS332 Service Bulletin No. 05.02, paragraph 1C(1)(c) or an equivalent approved by the Manager, FAA, Europe, Africa and Middle East office. (c) Within the next 100 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 100 hours' total time in service, inspect the spindle yoke lug in accordance with Aerospatiale AS332 Service Bulletin No. 05.02, paragraph 1C(2)(b) or an equivalent inspection approved by the Manager, FAA, Europe, Africa and Middle East office. NOTE: (1) For spindles having 90 hours' or more time in service, accomplish the inspection of paragraph (c) of this AD within 10 hours' additional time in service following the effective date of this AD. (2) For spindles having less than 90 hours' time in service, accomplish the inspection of paragraph (c) of this AD prior to attaining 100 hours' total time in service. (d) In addition to the inspection instructions noted in paragraphs (a), (b) and (c) of this AD, the service life limit of the main rotor hub spindles, PN 330A31.1112.09 and .10 is effectively reduced from 1500 hours' to 300 hours' total time in service. For spindles with more than 300 hours' time in service on the effective date of this AD, remove from service prior to attaining an additional 25 hours' time in service. (e) The collective pitch limit in level flight specified in the Rotorcraft Flight Manual, Section 2-1, paragraph 15, is reduced from 16.5 degrees to 16 degrees or less and the airspeed is limited to IAS = 131 KT (243 KM/HR). The following placard must be installed adjacent to the pilot and copilot airspeed indicators. The placard must be within sight of and readable by the pilot and copilot. EXCEPT IN CASE OF EMERGENCY, COLLECTIVE PITCH IN LEVEL FLIGHT IS LIMITED TO 16 DEGREES AND THE AIRSPEED IS NOT TO EXCEED THE FOLLOWING LIMITS: HP A/S KTS IAS SL 131 1000 128 2000 126 3000 124 4000 120 5000 116 7000 108 9000 96 11000 85 13000 71 This amendment becomes effective November 11, 1982. FOOTER:
Document Text
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AD Final Rules - DRS_82-22-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 82-22-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS332C/AS332L Se...Show more Subject: Main Rotor Spindles Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/11/1982 Make: Airbus Helicopters Model: AS332C | AS332L 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: 82-22-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4478 AD NUMBER: 82-22-05 SUBJECT HEADING: Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS332C/AS332L Series Helicopters ACTION: SUMMARY: DATES: Effective November 11, 1982. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 82-22-05 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4478. Applies to Model AS332C/AS332L series helicopters certificated in all categories that are equipped with main rotor spindles P/N 330A31.1122.09 and .10. Compliance is required as indicated. To detect fretting corrosion and to prevent possible cracking of the main rotor head spindle yoke lugs, accomplish the following: (a) Prior to the first flight of each day following the effective date of the AD, accomplish a visual inspection in accordance with Aerospatiale AS332 Service Bulletin No. 05.02, paragraph 1C(2)(a) or equivalent approved by the Manager, FAA, Europe, Africa and Middle East office. (b) Within the next 25 hours' time in service following the effective date of this AD, unless already accomplished, check the torque of the flap hinge pin nut in accordance with Aerospatiale AS332 Service Bulletin No. 05.02, paragraph 1C(1)(a) or an equivalent approved by the Manager, FAA, Europe, Africa and Middle East office. Thereafter, at intervals not to exceed 25 hours' time in service since the last inspection, accomplish the inspection in accordance with Aerospatiale AS332 Service Bulletin No. 05.02, paragraph 1C(1)(c) or an equivalent approved by the Manager, FAA, Europe, Africa and Middle East office. (c) Within the next 100 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 100 hours' total time in service, inspect the spindle yoke lug in accordance with Aerospatiale AS332 Service Bulletin No. 05.02, paragraph 1C(2)(b) or an equivalent inspection approved by the Manager, FAA, Europe, Africa and Middle East office. NOTE: (1) For spindles having 90 hours' or more time in service, accomplish the inspection of paragraph (c) of this AD within 10 hours' additional time in service following the effective date of this AD. (2) For spindles having less than 90 hours' time in service, accomplish the inspection of paragraph (c) of this AD prior to attaining 100 hours' total time in service. (d) In addition to the inspection instructions noted in paragraphs (a), (b) and (c) of this AD, the service life limit of the main rotor hub spindles, PN 330A31.1112.09 and .10 is effectively reduced from 1500 hours' to 300 hours' total time in service. For spindles with more than 300 hours' time in service on the effective date of this AD, remove from service prior to attaining an additional 25 hours' time in service. (e) The collective pitch limit in level flight specified in the Rotorcraft Flight Manual, Section 2-1, paragraph 15, is reduced from 16.5 degrees to 16 degrees or less and the airspeed is limited to IAS = 131 KT (243 KM/HR). The following placard must be installed adjacent to the pilot and copilot airspeed indicators. The placard must be within sight of and readable by the pilot and copilot. EXCEPT IN CASE OF EMERGENCY, COLLECTIVE PITCH IN LEVEL FLIGHT IS LIMITED TO 16 DEGREES AND THE AIRSPEED IS NOT TO EXCEED THE FOLLOWING LIMITS: HP A/S KTS IAS SL 131 1000 128 2000 126 3000 124 4000 120 5000 116 7000 108 9000 96 11000 85 13000 71 This amendment becomes effective November 11, 1982. FOOTER:
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Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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